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

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

7-13. CLEANING AIRCRAFT EXTERIOR AND ROTOR BLADES

Use care to prevent scratching of aluminium skin when cleaning

CAUTION_{main rotor blades. Never use volatile solvents or abrasive materials.}

Never apply bending loads to blades or blade tabs during cleaning.

Wash helicopter exterior, including fiberglass and composite components and

rotor blades, when necessary, using a solution of clean water and mild soap.

NOTE: Avoid directing soapy or clean water concentrations toward engine air intake

area and instrument static ports.

Clean surface stained with fuel or oil by wiping with soft cloth dampened by

solvent, followed by washing with clean water and mild soap.

Rinse washed areas with water and dry with soft cloth.

7-14. CLEANING - CANOPY AND DOOR TRANSPARENT PLASTIC

Clean outside surfaces of plastic by rinsing with clean water and rubbing light-

ly with palm of hand.

Use mild soap and water solution or aircraft type plastic cleaner to remove oil

spots and similar residue.

Never attempt to dry plastic panels with cloth. To do so causes

CAUTION_{any abrasive particles lying on plastic to scratch or dull surface.}

Wiping with dry cloth also builds up an electrostatic charge that

attracts dust particles from air.

After dirt is removed from surface of plastic, rinse with clean water and let air

dry or dry with soft, damp chamois.

Clean inside surfaces of plastic panels by using aircraft type plastic cleaner

and tissue quality paper towels.

7-15. FLUID LEAK ANALYSIS

Main or tail rotor transmission oil leak:

Oil leakage, seepage or capillary wetting at oil seals or assembly joint lines

of main or tail rotor transmission are permissible if leakage rate does not

exceed 2cc per hour (one drop per minute).

An acceptable alternate rate of leakage from either transmission is if oil

loss is not more than from full to the add mark on sight gauge within 25

flight hours.

Revision 18

7-17

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

NOTE: On transmission input gear oil seals with less that 2 hours of operation, some

seepage or wetting of adjacent surfaces is normal until seal is wetted and

worn-in (seated). If seepage continues at rate of one drop per minute or less,

seal may be continued in service. Check transmission oil level and observe

seepage rate after every 2 hours of operation. Shorter inspection periods may

be required if seal leakage appears to be increasing.

Engine oil leaks:

Refer to engine operating and maintenance manual for definition of permis-

sible engine oil leakage.

Landing gear damper hydraulic fluid leaks:

Hydraulic fluid leakage from any landing gear dampers is not permissible.

If leakage is present, damper assembly should be overhauled as required

and a serviceable unit installed. If leaking landing damper is not replaced

when leakage is noticed, continuation of damper in service can cause inter-

nal damage that might not otherwise occur.

NOTE: It is normal for a thin hydraulic oil film to remain on damper piston as a result of

wiping contact with piston seal. Newly installed dampers may also have slight

oil seepage from oil trapped in end cap threads during damper assembly. Neither

of these should be considered damper leakage or cause from damper

replacement.

7-16. PRESERVATION AND STORAGE

A helicopter placed in storage or nonoperative status must have adequate in-

spection, maintenance and preservation to avoid unnecessary deterioration of

airframe and components or equipment.

Extent of preventive maintenance that is to be performed on the helicopter for

storage up to 45 days, storage up to 6 months, and indefinite storage is cov-

ered in the HMI.

7-17. FLYABLE STORAGE - NO TIME LIMIT

Inspection before storage:

Perform Daily Preflight Check (Ref. Section IV).

Ensure that fuel cells are full (topped off), and that oil in engine oil tank

and main and aft transmissions is at FULL level.

Storage:

To maintain a flyable storage condition, ground runup must be performed at

least once every 5 days.

Perform daily preflight check.

7-18

Revision 18

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

Start engine (Ref. Section IV). After idle stabilizes, accelerate engine to

103 percent N₂. Operate until oil temperature shows an increase and

ammeter reads zero.

Shut down engine (Ref. Section IV).

Replenish fuel as necessary.

Open movable air vents in each cargo door; positioning air vent openings

downward.

Install covers and equipment used to park and moor helicopter.

Install static ground.

Before next flight:

Remove covers and equipment used to park and moor helicopter.

Perform daily preflight check (Ref. Section IV).

7-18. COCKPIT DOOR REMOVAL AND INSTALLATION

Door removal:

Open door.

Remove interior cover plates (pilot's side - remove fire extinguisher).

Pull lower hinge pin up to remove.

While holding door, rotate upper hinge pin until hinge pin tab clears the

slot and pull down on pin to remove.

Remove door.

Stow hinge pins and cover plates.

Door installation:

Place door hinges into door frame and hold open.

While holding door open, push in and rotate upper hinge pin until hinge

pin tab enters and fully seats in the slot.

Install lower hinge pin.

Install interior cover plates.

Install fire extinguisher (pilot's side).

Revision 18

7-19

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Handling, Servicing,

and Maintenance

7-19. SPECIAL OPERATIONAL CHECKS AND PROCEDURES

The following checks are typically utilized as part of a post maintenance run up

associated with scheduled inspections, troubleshooting or maintenance on specific

aircraft systems. Refer to the Handbook of Maintenance Instruction (HMI-2) for

the recommended use and frequency of the following checks.

COMPRESSOR WASH

Water wash provisions are incorporated in current configuration helicopters

(Ref. Figure 7-4).

Engine compressor cleaning should be performed by qualified personnel in ac-

cordance with the HMI and the Engine Operation and Maintenance Manual.

The following information is provided for pilots assisting qualified personnel in

the cleaning process.

The starter-generator can be used to motor the Rolls-Royce 250 Series en-

gine for compressor cleaning cycle.

Input voltage should be 24 vdc, but it is permissible to use 12 vdc.

To prevent starter-generator damage, duty cycle (cranking) time limits that

must not be exceeded are:

24 vdc External

24 vdc Helicopter

Auxiliary Power

Battery Power

25 Seconds ON

30 Seconds ON

30 Seconds OFF

2 Minutes OFF

25 Seconds ON

30 Seconds ON

30 Seconds OFF

2 Minutes OFF

25 Seconds ON

30 Seconds ON

30 Minutes OFF

12 vdc External Auxiliary Power

2 Minutes ON

30 Minutes OFF

2 Minutes ON

NOTE: Current required by starter-generator to maintain10 percent N₁ rpm should be

approximately 150 amperes with 12 vdc input.

Revision 18

7-21

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Handling, Servicing,

and Maintenance

Procedures:

F Ensure engine anti-ice, cabin heat, and scav air (if installed) are off prior

to engine wash or rinse.

F Water injection will be started three seconds prior to starter engagement.

F Motor the engine with the twistgrip in CUTOFF.

F Release starter switch as necessary to maintain between 5% and 10% N₁

speed during the wash/rinse.

F Water injection will continue during coast down until N₁ stops.

F Allow engine to drain.

F Within 15 minutes of the water rinse, operate the engine at idle for five

minutes and actuate anti-ice, cabin heat, and scav-air (if installed) sys-

tems for one minute to purge and evaporate all residual water .

MAIN ROTOR HUB BALANCING

NOTE: Refer to HMI-2, Section 18-10-00. This procedure shall be performed by

qualified maintenance personnel only. Hub balancing is performed at 103% N₂

with the main rotor blades removed.

F Follow the normal Pre-start and Engine Start procedures in Section IV

except:

Before starting, place governor increase/decrease switch at “minim-

um beep” by pressing and holding switch down for several seconds.

F After completing start, turn generator on and increase twistgrip to flight

idle: do not delay.

Observe N₂ speed avoid range limits during this procedure and

CAUTION

exercise caution when increasing twistgrip to flight idle position to

avoid N₂ overshoots.

F Using the governor increase/decrease switch, carefully increase N₂ speed

to 103%.

After balance data is recorded:

F From 103% N₂, shutdown engine.

NOTE: Shut down from 103% N₂. Do not observe two minute cool-down at ground idle.

7-22

Revision 18

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Additional Operations

and Performance Data

S ECTION VIII

ADDITIONAL OPERATIONS

AND PERFORMANCE DATA

TABLE OF CONTENTS

PARAGRAPH

PAGE

8-1. Hover Ceiling - Out of Ground Effect (OGE)

8-1

Figure 8-1. Hover Ceiling Versus Gross Weight, Out of Ground Effect,

Takeoff Power, Two or Four Bladed Tail Rotor,

Rolls Royce 250-C20B

8-2

Figure 8-2. Hover Ceiling Versus Gross Weight, Out of Ground Effect,

Takeoff Power, Two or Four Bladed Tail Rotor

Rolls Royce 250-C20R/2

8-3

Figure 8-3. Hover Ceiling Versus Gross Weight, Out of Ground Effect,

Utility Floats Installed, Takeoff Power,

Rolls Royce 250-C20B

8-4

Revision 17

8-i

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Additional Operations

and Performance Data

SECTION VIII

ADDITIONAL OPERATIONS AND

PERFORMANCE DATA

8-1. HOVER CEILING - OUT OF GROUND EFFECT (OGE)

Select the appropriate hover performance chart for the engine

CAUTION_{(Rolls Royce 250-C20B or 250-C20R/2) and/or optional equipment}

installed.

Description:

The hover ceiling chart shows the maximum hover weight capability, out of

ground effect (OGE), at take off power for known conditions of pressure alti-

tude and outside air temperature, or alternately, the maximum hover ceiling

for a known gross weight and outside air temperature.

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

4. Wind less than 3 knots

Use of chart:

To determine OGE hover performance, refer to Section V, Hover Ceiling

(IGE), ``Use of chart''.

NOTE: Aircraft with 4-bladed tail rotors:

Pilots should be aware that the IGE directional controllability tests have

demonstrated that the two-bladed tail rotor has more margin than the

four-bladed tail rotor. OGE directional controllability in winds greater than 3

knots has not been determined for either tail rotor configuration.

Revision 14

8-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

CSP-E-1

(Model 369E)

Additional Operations

and Performance Data

THIS CHART BASED ON WINDS LESS THAN 3 KNOTS, CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE,

APPLICABLE TO PARTICAL SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET.

REDUCE WEIGHT:

INCREASE WEIGHT:

50 LB WITH ABRASION STRIPS ON

55 LB WITH SCAVENGE ON

MAIN ROTOR BLADES ONLY

40 LB WITH MIST ELIMINATOR INSTALLED

DECREASE WEIGHT:

50 LB WITH ABRASION STRIPS ON

TAIL ROTOR BLADES ONLY

INCREASE (OR DECREASE) WT.

CAPABILITY LBS (ABOVE CRITICAL

16000

ALTITUDE) PER 10 AMP REDUCTION (OR

INCREASE) IN ELECTRICAL LOAD

NOT VERIFIED WHEN MAIN ROTOR

OAT°C

-5

BLADES HAVING ABRASION STRIPS

DWT

ARE INSTALLED

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

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

F03-044-1

<<<< 250-C20B>>>>

Figure 8-1. Hover Ceiling Versus Gross Weight, Out of Ground Effect,

Takeoff Power, Two or Four Bladed Tail Rotor,

Rolls Royce 250-C20B

8-2

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Additional Operations

and Performance Data

THIS CHART BASED ON WINDS LESS THAN 3 KNOTS, 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

NOT VERIFIED WHEN

MAIN ROTOR BLADES

INCREASE (OR DECREASE) WT.

HAVING ABRASION STRIPS

CAPABILITY LBS (ABOVE CRITICAL

ARE INSTALLED

ALTITUDE) PER 10 AMP REDUCTION (OR

-25

IJNCREASE) IN ELECTRICAL LOAD

16000

OAT°C

-5

-15

DWT

-5

14000

MAXIMUM INTERNAL

GROSS WEIGHT

GROSS WEIGHTS ABOVE

3000 LB MUST BE EXTERNAL

AND JETTISONABLE

12000

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

2000

2200

2400

2600

2800

3000

3200

3400

3600

GROSS WEIGHT - POUNDS

<<<< 250-C20R/2>>>>

F03-044-2

Figure 8-2. Hover Ceiling Versus Gross Weight, Out of Ground Effect,

Takeoff Power, Two or Four Bladed Tail Rotor

Rolls Royce 250-C20R/2

Revision 14

8-3

ROTORCRAFT FLIGHT MANUAL

MD 500E

CSP-E-1

(Model 369E)

Additional Operations

and 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

18000

ROTOR BLADES ONLY

HOVER OGE BASED ON HUGHES TAHOE TEST

INCREASE (OR DECREASE) WT.

ADJUSTED TO BE CONSISTENT WITH IGE HOVER

CAPABILITY LBS (ABOVE CRITICAL

ALTITUDE) PER 10 AMP REDUCTION (OR

16000

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

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

F03-048

<<<< 250-C20B >>>>

Figure 8-3. Hover Ceiling Versus Gross Weight, Out of Ground Effect,

Utility Floats Installed, Takeoff Power,

Rolls Royce 250-C20B

8-4

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

S E C T I O N IX

OPTIONAL EQUIPMENT

TABLE OF CONTENTS

PARAGRAPH

PAGE

9-1.

General Information

9-1

9-2.

Listing - Optional Equipment

9-1

Table 9-1. Optional Equipment - Model 369E Helicopter

(250-C20B or C20R/2)

9-2

Table 9-2. Optional Equipment - Model 369E Helicopter (250-C20B)

9-2

9-3.

Optional Equipment Performance Data

9-3

9-4.

Compatibility - Combined Optional Equipment

9-3

Table 9-3. Optional Equipment Kit Compatibility - Model 369E Helicopter

9-3

9-5.

Operating Instructions: Cargo Hook Kit

9-5

Figure 9-1. VNE Placards - C20B or C20R/2 Engine

9-7

Figure 9-2. Cargo Hook Release - Electrical and Mechanical

9-8

Figure 9-3. Cargo Hook

9-10

9-6.

Operating Instructions: Anti-Ice Airframe Fuel Filter

9-13

Figure 9-4. Anti-Ice Airframe Fuel Filter

9-16

9-7.

Operating Instructions: Four-Bladed Tail Rotor

9-17

Table 9-4. Center of Gravity Limits

9-21

Figure 9-5. Longitudinal Center of Gravity Limits

9-22

Figure 9-6. Lateral Center of Gravity Limits

9-23

9-8.

Operating Instructions - Emergency Floats

9-25

Figure 9-7. V_NE Placards - Rols Royce 250-C20B (Sheet 1 of 2)

9-28

Figure 9-7. V_NE Placards - Rolls Royce 250-C20B (Sheet 2 of 2)

9-29

Figure 9-8. V_NE Placards - Rolls Royce 250-C20R/2 (Sheet 1 of 2)

9-30

Figure 9-8. V_NE Placards - Rolls Royce 250-C20R/2 (Sheet 2 of 2)

9-31

Figure 9-9. Float Pressure Gauge

9-34

9-9.

Operating Instructions - Engine Air Inlet Diverter

9-35

Figure 9-10. V_NE Placards (Sheet 1 of 2)

9-36

Figure 9-10. V_NE Placards (Sheet 2 of 2)

9-37

9-10. Operating Instructions - Utility Floats

9-39

Figure 9-11. V_NE Placards (Sheet 1 of 2)

9-42

FAA Approved

Revision 14

9-i

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Optional Equipment

PARAGRAPH

PAGE

Figure 9-11. V_NE Placards (Sheet 2 of 2)

9-43

Figure 9-12. Height-Velocity Diagram - Utility Floats Installed

9-46

Figure 9-13. Airspeed Calibration Curve - Utility Floats Installed

9-47

9-11. Operating Instructions: Garmin G500H Integrated System

9-49

Figure 9-14. Instrument Panel, LH Command - Layout Typical

9-52

Figure 9-15. Instrument Panel, RH Command - Layout Typical

9-53

Figure 9-16. Runtime (Hobbs) Meter, OAT Probe and NAV/COM

Antenna Locations - Typical

9-54

FAA Approved

9-ii

Revision 18

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

SECTION IX

OPTIONAL EQUIPMENT

9-1. GENERAL INFORMATION

This section provides general supplemental information on optional equipment

for the MD 500E Helicopter. The information includes a listing of usable op-

tional equipment and compatibility of combined equipment on the helicopter.

Supplemental data is prepared and included in this section whenever the in-

stallation of that equipment affects the FAA Approval Data for Limitations

(Section II), Emergency and Malfunction Procedures (Section III), Normal Pro-

cedures (Section IV), and Performance Data (Section V).

The Flight Manual Supplemental Data is to be used in conjunction with the

basic Flight Manual data and takes precedence over that data when the equip-

ment is installed.

Be sure to include a review of the appropriate flight manual

CAUTION_{supplemental data for type of optional equipment installed}

(including STC items) as a regular part of preflight planning.

9-2. LISTING - OPTIONAL EQUIPMENT

Table 9-1 lists MDH optional equipment items available that require additional

operating instructions. This table does not include non-MDHI STC items that

may be FAA approved for use. Other optional equipment items may be found

in the HMI. These kits are approved and usable on the 369E Helicopter

Equipped with either the Rolls Royce 250-C20B or C20R/2 engines.

Table 9-2 lists optional equipment kits and flight manual supplements ap-

proved and usable on the 369E Helicopter equipped with the 250-C20B engine

only. This table does not include non-MDHI STC items that may be FAA ap-

proved for use.

SPECIAL NOTE:

Items in the table marked with an asterisk (*) are optional equipment items that

have had their supplemental data incorporated into the main body of the flight

manual and are identified by the statement, ``If installed''.

FAA Approved

Revision 14

9-1

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Table 9-1. Optional Equipment - Model 369E Helicopter (250-C20B or C20R/2)

Publication

Equipment

No.

*Pitot heat

CSP-E-1

*Extended landing gear

CSP-E-1

*Rotor brake

CSP-E-1

*Engine air particle separator filter

CSP-E-1

Cargo hook

CSP-E-1 Section IX

Emergency floats

CSP-E-1 Section IX

Four-bladed T/R

CSP-E-1 Section IX

*Indicates data incorporated into the flight manual (Sections I thru VII where appropriate).

NOTE: See Table 9-2 for Optional Equipment Supplements certified for model 369E

helicopters equipped with Allison Model 250-C20B engines only.

Table 9-2. Optional Equipment - Model 369E Helicopter (250-C20B)

Publication

Equipment

No.

Anti-ice airframe fuel filter

CSP-E-1 Section IX

Engine air inlet diverter kit

CSP-E-1 Section IX

Rotorcraft utility floats

CSP-E-1 Section IX

FAA Approved

9-2

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

9-3. OPTIONAL EQUIPMENT PERFORMANCE DATA

SPECIAL NOTE:

Optional equipment that affect hover performance require addition-

al hover performance charts. Optional Equipment IGE hover perfor-

mance charts are located in Section V and Optional Equipment OGE

hover performance charts are located in Section VIII.

9-4. COMPATIBILITY - COMBINED OPTIONAL EQUIPMENT

Table 9-3. Optional Equipment Kit Compatibility - Model 369E Helicopter

Compatibility: Blank=Yes; X=No

Optional

Part Number

Equipment

(369H/369D)

290121

290007

292500

90022

90148

90072

290086

292044

A. Emergency Floats

369D290121-527

(1)

(2)

B. Extended Landing

369D290007-501, -50

Gear

3,-509, -511

C. Four-Bladed Tail

369D292500

Rotor

D. Anti-Ice Airframe

369H90022-503

Fuel Filter

E. Engine Air Particle

369H90148-519, -521,

Separator Kit

-535, -537, -539

F. Cargo Hook

369H90072-505

(1)

(2)

G. Utility Floats (3)

369D290086-501,

-503

H. Engine Air Inlet

369D292044-501,

Diverter Kit

369D292045

250-C20R/2

369D298000

Engine Installa-

tion

Notes:

(1)

Cyclic stick grip kit 369H90129-505 must be installed.

(2)

For functional use of Cargo Hook, emergency floats must be in stowed configuration for either standard or

extended landing gear.

(3)

Not compatible with 369H90045, *(wheel, pneumatic) or standard landing gear.

*Remove before flight.

FAA Approved

Revision 17

9-3

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Cargo Hook Kit

9-5. OPERATING INSTRUCTIONS: CARGO HOOK KIT

PART I

GENERAL

The MDHI 369H90072-505 Cargo Hook Kit consists of a cargo hook which at-

taches to the fuselage keel beam, electrical connections to provide the pilot

with cargo release or jettison capability using a switch on the cyclic stick, and

a manual backup release mechanism. The cargo hook kit is designed to carry

hook loads up to 2000 pounds.

When the kit is installed, an owner or operator holding a valid Rotorcraft Ex-

ternal Load Operator Certificate may utilize the helicopter for transportation of

external cargo when operated by a qualified pilot. OPERATIONS WITH CAR-

GO ON THE HOOK SHALL BE CONDUCTED IN ACCORDANCE WITH AP-

PLICABLE PORTIONS OF FEDERAL AVIATION REGULATIONS PART 133.

Information provided in these operating instructions is presented with the in-

tent of furnishing important data that can be used in the Rotorcraft Load

Combination Flight Manual. The Combination Flight Manual, which is re-

quired by FAR Part 133, will be prepared by the applicant to obtain the rotor-

craft External Load Operator Certificate.

FAA Approved

Revision 14

9-5

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Cargo Hook Kit

PART II

LIMITATIONS

Weight Limitations:

Maximum takeoff and landing gross weight 3000 pounds. Weight

CAUTION_{in excess of 3000 pounds must be external and jettisonable.}

Maximum Rotorcraft - Load Combinations operating gross weight 3550

pounds (FAR 133).

Center of Gravity Limitations:

Center of gravity not to exceed the limits certificated for the basic helicop-

ter.

For gross weights greater than 3000 pounds, center of gravity limits for

3000 pounds apply.

Cargo Hook Limitations:

Cargo hook structural load limit is 2000 pounds.

Airspeed Limitations:

With no load on hook, airspeed limits are unchanged.

With load on hook, airspeed limits are presented on the exterior load V_NE

placards. The airspeed presented on these placards apply to either C20B or

C20R/2 engine installations.

NOTE: Use caution as size and shape of load, and load attaching cable size and length

may affect flight characteristics. Satisfactory flight characteristics have been

demonstrated with a compact 2000 pound load suspended on a 3/8-inch cable

5 feet long.

Altitude Limitations:

Maximum operating altitude is 14,000 feet density altitude.

FAA Approved

9-6

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Cargo Hook Kit

Placards:

Make placards stating approved load class(es) and occupancy limitations.

Display placards in a conspicuous location in cockpit.

Placard stating, ``External Load Limit 2000 Pounds'' installed on or next to

cargo hook.

EXTERIOR LOAD

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 3200 LB OR LESS

°C

−30

−20

−10

NO FLIGHT

EXTERIOR LOAD

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 3201 TO 3550 LB

°C

−30

−20

−10

NO FLIGHT

Figure 9-1. VNE Placards - C20B or C20R/2 Engine

FAA Approved

Revision 14

9-7

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Cargo Hook Kit

PART III

EMERGENCY AND

MALFUNCTION PROCEDURES

ENGINE FAILURE:

The presence of an external load may further complicate a failed engine

condition. Release of loads attached through the cargo hook should be ac-

complished as soon as practical; consistent with other safety of flight factors

(rotor RPM, altitude, airspeed, ground personnel safety, etc).

EMERGENCY RELEASE:

Actuate mechanical release handle to release cargo in the event of an elec-

trical failure. Operate handle quickly and deliberately (Ref. Figure 9-2).

NOTE: Ground support personnel should manually assure positive reset of the cargo

hook after use of mechanical release, prior to further cargo pickups.

Static electricity discharge:

Instruct ground crew to insure that the helicopter has been electrically

grounded prior to attaching cargo to drain charges of static electricity that

may build up in flight.

CARGO HOOK MECHANICAL RELEASE

CARGO HOOK

ELECTRICAL RELEASE

CYCLIC-MOUNTED ELECTRICAL HOOK RELEASE

CARGO HOOK

RELEASE CABLE

MECHANICAL HOOK RELEASE

Figure 9-2. Cargo Hook Release - Electrical and Mechanical

FAA Approved

9-8

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Cargo Hook Kit

PART IV

NORMAL PROCEDURES

Normal Operation:

Preflight

Place battery switch in BAT position and check that HOOK circuit

breaker is in.

Push cargo load ring into hook throat. Cargo hook keeper should permit

easy entrance into throat. Leave ring in hook for remainder of operation-

al checks (Ref. Figure 9-3).

Pull aft and downward on load ring; hook must remain in locked posi-

tion.

Operational Checks

Check electrical and emergency operation of cargo hook release (Ref.

Figure 9-3).

Check operation of external release knob (located on left side of cargo

hook body).

Hook should return to the closed position after above checks.

Move pilot's cyclic to all extreme positions. Cargo hook must remain

locked and external release knob must not rotate.

With load ring in cargo hook, swing hook to the limits of trav-

el in all directions. Hook must remain in the closed position.

Inflight

Check cargo HOOK circuit breaker IN.

Use care to avoid passing load attaching cables over landing gear

CAUTION_{skid tube when attaching load to hook with helicopter on the}

ground.

Apply collective smoothly when lifting cargo.

Activate cargo release switch on cyclic stick to release cargo.

FAA Approved

Revision 17

9-9

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Cargo Hook Kit

EXTERNAL RELEASE

(TURN CLOCKWISE)

ELECTRICAL WIRE HARNESS

KEEPER

MANUAL RELEASE CABLE

HOOK (LOAD BEAM)

KEEPER

CORRECT RIGGING

LOAD ARM

LOAD

ARM

INSIDE

PRIMARY CIRCULAR RING

DIAMETER

ENGAGING LOAD ARM

CIRCULAR

PRIMARY

LOAD RING

SECONDARY LOAD MEMBER

SECONDARY MEMBER

(RING OR SHACKLE)

VIEW LOOKING

FORWARD

TO LOAD

F60-052-3

Figure 9-3. Cargo Hook

FAA Approved

9-10

Revision 17

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Cargo Hook Kit

PART V

PERFORMANCE DATA

Refer to Section V for IGE hover performance or Section VIII for OGE hover

performance to assist in planning operations with the cargo hook.

PART VI

WEIGHT AND BALANCE DATA

The following table of Cargo Hook Loading Data should be used by the opera-

tor to assist in evaluating the helicopter center of gravity for various hook load

weights.

Cargo Hook Loading Data:

Cargo Longitudinal CG = 99.3

Cargo Weight

Moment/100

(lb)

(in.-lb)

100

200

199

300

298

400

397

500

497

600

596

700

695

800

794

900

894

1000

993

1100

1092

1200

1191

1300

1291

1400

1390

1500

1490

1600

1589

1700

1688

1800

1787

1900

1887

2000

1986

FAA Approved

Revision 17

9-11

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Four-Bladed Tail Rotor

9-6. OPERATING INSTRUCTIONS: ANTI-ICE AIRFRAME FUEL FILTER

PART I

GENERAL

The MDHI Anti-Ice Airframe Fuel Filter is designed to strip the fuel of ice

particles prior to entering the engine fuel system. Installation of the filter

will delete the requirement for use of fuel containing anti-ice additives.

The anti-ice airframe fuel filter incorporates a filter unit mounted in series

between the aircraft fuel system and the engine fuel system. Electrical and

mechanical equipment sense the build-up of ice in the filter unit and will

automatically illuminate a cockpit caution on the annunciator panel. The pi-

lot then actuates a switch to activate the aircraft start pump. When the fil-

ter becomes fully clogged, a by-pass valve contained in the filter unit opens

and the fuel by-passes the filter element.

FAA Approved

Revision 14

9-13

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Four-Bladed Tail Rotor

PART II

LIMITATIONS

Altitude limitations:

If ground temperature prior to flight is 5°C or less, flight operations are

limited to 12,000 feet pressure altitude maximum.

If ground temperature prior to flight is above 5°C, flight operations are lim-

ited to 14,000 feet pressure altitude maximum, but not to exceed limitations

of Basic RFM Section II.

Anti-Ice fuel additives:

Installation of the Anti-Ice Airframe Fuel Filter eliminates the need for

anti-ice fuel additives in the fuel (i.e., Prist).

Placards:

Anti-Ice Airframe Fuel Filter Installation

For ground temp of 5°C or less max ALT 12,000 H_P.

For ground temp greater than 5°C max ALT 14,000 H_P.

PART III

EMERGENCY AND

MALFUNCTION PROCEDURES

ANTI-ICE AIRFRAME FUEL FILTER

AIR

Indications: Yellow

caution indicator ON.

FRAME

FILTER

Conditions: Anti-ice airframe fuel filter becoming clogged with ice or other solid

contaminants.

Procedures:

F Turn start pump ON.

F Land as soon as practical.

FAA Approved

9-14

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Four-Bladed Tail Rotor

PART IV

NORMAL PROCEDURES

Preflight checks:

Battery switch - BAT or EXT PWR

Start Pump - ON

Do not open drain valve unless start pump is ON. An unexpected

WARNING

flameout or power loss may occur if air is allowed to enter the fuel

system.

Drain any residual water in the filter unit through the drain valve on the

bottom of the filter unit.

NOTE: If aircraft has been exposed to freezing temperatures, failure to drain may be due

to ice formation in the filter element.

Start Pump - OFF

Press red press-to-test button located on the top of filter unit (Ref.

Figure 9-4); AIR FRAME FILTER light should come on.

Release press-to-test button; AIR FRAME FILTER light should go out.

Post flight filter cleaning:

When ambient temperature is expected to go below freezing, any water in

the filter unit should be drained following completion of the flight.

Following any actuation of AIR FRAME FILTER light, fuel filter should be

serviced (Ref. HMI-2).

FAA Approved

Revision 14

9-15

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Four-Bladed Tail Rotor

9-7. OPERATING INSTRUCTIONS: FOUR-BLADED TAIL ROTOR

PART I

GENERAL

The MDHI Four-Bladed Tail Rotor Kit has been developed to reduce the exter-

nal noise signature of the helicopter. It consists of two principal assemblies, a

four bladed tail rotor, and gearbox. The pedal bungee has been changed to

compensate for tail rotor produced loads.

There is a weight increase of 9.4 pounds which will cause an aft C.G. shift of

0.6 to 0.9 inch depending on gross weight. The exact shift must be determined

by individual helicopter weight and balance.

The four-bladed tail rotor turns at reduced RPM thus substantially reducing

the external noise signature which is a function of rotor tip speed.

FAA Approved

Revision 14

9-17

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Four-Bladed Tail Rotor

PART II

LIMITATIONS

Flight restrictions:

NOTE: MD 500E (Model 369E) helicopters equipped with the Allison 250-C20R/2

engine and the four-bladed tail rotor kit are approved in combination only with

the optional equipment depicted in Section IX, Table 9-3.

Rotor speed limits:

Minimum RPM: Power Off 415 N_R (lower red bar on rotor tachometer).

Center of gravity envelope:

The forward CG limit is 99.0 inches; the aft CG varies linearly from 103.0

inches at 3000 pounds gross weight, to 106.0 at 2000 pounds, then linearly

to 108.1 at minimum flying weight of 1592 pounds (Ref. Table 9-4).

The lateral CG limits are ±3.0 inches at gross weights from 3000 to 2000

pounds, then vary linearly to ±1.7 inches at 1592 (Ref. Table 9-4).

FAA Approved

9-18

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Four-Bladed Tail Rotor

PART III

EMERGENCY AND

MALFUNCTION PROCEDURES

ENGINE FAILURE

Conditions: In flight.

Procedures:

F Allow the speed to reduce to 130 knots IAS or lower (see V_NE placard).

Maintain rotor speed between 415 and 523 RPM by use of collective con-

trol.

F Maximum gliding distance is obtained at 80 knots and 415N_R.

F Minimum rate of descent is obtained at 60 knots and 415N_R.

PART IV

NORMAL PROCEDURES

Preflight check:

F Output shaft dust cover, retaining nut,

tang washer, and rubber bumper

CHECK

NOTE: Deformation of the teetering stop support portion of the retaining nut may indicate

that excessive T/R flapping has occurred and should be inspected in accordance

with the HMI prior to flight.

Engine start:

F Pedals

NEUTRAL

Excessive tail rotor flapping will result if pedals are not in neutral position.

CAUTION

NOTE: The pedal bungee is an overcenter type. Consequently, if not restrained, the

pedals will snap from one side to the other when moving through its load center

position.

FAA Approved

Revision 14

9-19

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Four-Bladed Tail Rotor

Low speed maneuvering:

Certain maneuvers may cause extreme T/R flapping and pounding

CAUTION_{of the T/R teetering stop support portion of the retaining nut (felt}

and heard by the pilot as a momentary medium frequency vibration).

These maneuvers usually involve rapid yaw rates that allow the

T/R to pass through the relative wind line. Maneuvers such as

simulating a T/R failure in a hover, rapid pedal turns at speeds

above translational lift, and uncoordinated agricultural type turns

may fall into this category and should be avoided.

Repeated pounding of the stop support may lead to the shearing

of the inner key on the tang washer and subsequent loosening

of the retaining nut.

Practice autorotation:

Practice autorotation should be conducted at 130 knots IAS or below (see

V_NE placards). Maintain rotor speed between 415 and 523 RPM by use of

collective control.

Maximum gliding distance is obtained at 80 knots; 415N_R.

Minimum rate of descent is obtained at 60 knots; 415N_R.

Engine/aircraft shut down:

Maintain pedals in center position until rotor has stopped turning to pre-

CAUTION

vent excessive tail rotor flapping.

PART V

PERFORMANCE DATA

Hover performance:

IGE controllability has been demonstrated to be adequate in winds up to 17

knots from any direction - the least favorable wind azimuth, which would

have the least left pedal margin, is 45 degrees right of the nose.

Refer to Section V for IGE hover performance.

FAA Approved

9-20

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Four-Bladed Tail Rotor

PART VI

WEIGHT AND BALANCE DATA

Weight and balance characteristics:

See Table 9-4 and Figure 9-5 and Figure 9-6 for CG limits.

Table 9-4. Center of Gravity Limits

Gross Weight

Longitudinal C.G. Limit

Lateral C.G. Limit

(lb)

(Sta-in.)

Forward

Aft

(+) Right, (-) Left

3000

99.0

103.0

±3.0

2500

99.0

104.5

±3.0

2300

99.0

105.1

±3.0

2000

99.0

106.0

±3.0

1592

99.0

108.1

±1.7

The forward CG limit is 99.0 inches; the aft CG varies linearly from 103.0

inches at 3000 pounds gross weight, to 106.0 at 2000 pounds, then linearly

to 108.1 at minimum flying weight of 1592 pounds.

The lateral CG limits are ±3.0 inches at gross weights from 3000 to 2000

pounds, then vary linearly to ±1.7 inches at 1592 pounds.

FAA Approved

Revision 14

9-21

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Emergency Floats

9-8. OPERATING INSTRUCTIONS - EMERGENCY FLOATS

PART I

GENERAL

MDHI Emergency Float Kit, consists of inflatable bag-type floats intended for

use in emergency landings only, during over-water operation. It is furnished

with squib-actuated valves and with steel pressure vessels.

The floats are normally carried in the stowed configuration, mounted as a com-

pact package on top of each skid. A press-to-test indicator light is provided to

check the condition of the electrical actuation circuits for each float. This indi-

cator is located on the caution and warning indicator panel. The circuit break-

er is located at the bottom of the circuit breaker panel. A recessed switch is

provided on the cyclic stick for the pilot to initiate inflation when required.

The switch activates valves allowing air or nitrogen stored in pressure vessels

within the float packages to inflate the floats. An optional Night Landing Kit

is available consisting of dual belly mounted sealed beam lights, a circuit

breaker, and a three position switch installed on the collective control. Forward

position illuminates the standard nose mounted landing light; center position is

off; and aft position illuminates the belly lights. Night flight over water is per-

mitted with the night landing light kit installed.

FAA Approved

Revision 14

9-25

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Optional Equipment

Emergency Floats

PART II

LIMITATIONS

Night flight over water beyond autorotational capability to ground is prohib-

ited, unless 369D292032 Night Landing Kit is installed.

Flight with floats inflated, or at time of inflation, is limited to the conditions of

altitude and temperature presented on the EMERGENCY FLOATS INFLATED

V_NE PLACARD.

Operations with the emergency floats inflated is limited to flight to a servicing

facility for repacking and recharging the system. Airspeed with the floats in-

flated is limited. Refer to the appropriate V_NE placards (Ref. Figure 9-7 and

Figure 9-8).

Environmental operating conditions:

Operating temperature range

Operational temperature range for over water-flight is:

-25°F (-31.7°C) minimum

+117°F (+47°C) maximum

Altitude limits - floats inflated

For water and ground landings, change of altitude is limited to 6500 feet

below the altitude at inflation or to 6500 feet below the maximum alti-

tude to which the inflated floats are subsequently flown. This assumes

the normal variation in ambient temperature associated with altitude

changes.

NOTE: If the allowable altitude change noted above is exceeded, the minimum

operational float pressure (2.0 psig) for water and ground landings may not be

available.

Air speed limits:

With floats stowed

With floats stowed, airspeed limitations are presented on the V_NE IAS

(knots) FLOATS STOWED placards (Ref. Figure 9-7 and Figure 9-8).

For float inflation

Maximum speed for float inflation is 81 knots IAS at less than 6,000

feet altitude, 77 knots IAS at 6,000 feet altitude and above.

FAA Approved

9-26

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Emergency Floats

Gross weight limitations:

Maximum gross weight is 3000 pounds.

Minimum gross weight is 1680 pounds.

Center of gravity limits:

Longitudinal C.G. Limit

Lateral C.G. Limit

Gross Weight (lb)

(Sta-in.)

Forward

Aft*

(-) Left, (+) Right

3000

99.0

103.0

± 3.0

2500

99.0

104.5

± 3.0

2000

99.0

106.0

± 3.0

1680

99.0

107.0

± 3.0

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

pounds at Station 103.0 to 1680 pounds at Station 107.0.

Placards:

When emergency floats are installed, the following placards are required:

WARNING: FLOAT INFLATION ABOVE 81 KNOTS IAS AT

Placard 1.

LESS THAN 6,000 FEET ALTITUDE, 77 KNOTS IAS AT

6,000 FEET AND ABOVE, IS PROHIBITED.

NIGHT FLIGHT OVER WATER BEYOND AUTOROTATION

Placard 2.

CAPABILITY TO GROUND IS PROHIBITED.

NOTE: Placard 2 not required if 369D292032 Night Landing Kit is installed.

V_NE Placards

Refer to Figure 9-7 for helicopters equipped with Rolls Royce 250-C20B

engines.

Refer to Figure 9-8 for helicopters equipped with Rolls Royce

250-C20R/2 engines.

Be sure to select the appropriate V_NE Placard for type of engine

CAUTION_{installed in helicopter.}

Kit compatibility:

The passenger step kit may not be installed in combination with emergency

floats.

FAA Approved

Revision 14

9-27

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Optional Equipment

Emergency Floats

EMER FLOATS - INFLATED

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 1680 TO 3000 LB

°C

−30

−20

100

−10

101

100

NO FLIGHT

100

FOR AUTOROTATION V_NE REDUCE SPEED BY 22K

(85K MIN); DO NOT EXCEED CHART V_NE

FLOATS STOWED

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 1680 TO 2000 LB

°C

−30

141

136

131

127

122

118

113

109

104

−20

149

144

139

134

129

124

119

115

101

−10

151

145

140

135

130

125

110

146

141

136

121

102

152

151

148

144

138

111

150

146

143

123

104

151

148

145

141

114

NO FLIGHT

150

147

143

126

106

149

146

143

121

103

FOR AUTOROTATION VNE REDUCE SPEED BY 22K

(85K MIN); DO NOT EXCEED CHART V_NE

MAX V_NE 130KTS WITH LESS THAN 35 LB FUEL

Figure 9-7. V_NE Placards - Rols Royce 250-C20B (Sheet 1 of 2)

FAA Approved

9-28

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Emergency Floats

FLOATS STOWED

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 2001 TO 2500 LB

°C

−30

141

136

131

127

122

118

113

102

−20

149

144

139

134

129

124

110

−10

151

145

140

135

121

102

146

137

111

152

151

148

122

103

150

142

113

151

148

125

105

NO FLIGHT

150

147

115

149

135

111

FOR AUTOROTATION V_NE REDUCE SPEED BY 22K

(90K MIN); DO NOT EXCEED CHART V_NE

MAX V_NE 130 KTS WITH LESS THAN 30 LB FUEL

FLOATS STOWED

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 2501 TO 3000 LB

°C

−30

141

136

131

127

122

114

−20

149

144

139

134

124

104

−10

151

145

138

114

124

105

152

139

114

125

106

143

116

NO FLIGHT

128

108

123

104

FOR AUTOROTATION V_NE REDUCE SPEED BY 22K

(95K MIN); DO NOT EXCEED CHART V_NE

MAX V_NE 130 KTS WITH LESS THAN 30 LB FUEL

Figure 9-7. V_NE Placards - Rolls Royce 250-C20B (Sheet 2 of 2)

FAA Approved

Revision 14

9-29

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Optional Equipment

Emergency Floats

250 - C20R/2

EMER FLOATS - INFLATED

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 1680 TO 3000 LB

°C

−30

−20

−10

101

NO FLIGHT

FOR AUTOROTATION V_NE REDUCE SPEED BY 22K

(90K MIN); DO NOT EXCEED CHART V_NE

250 - C20R/2

FLOATS STOWED

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 1680 TO 2000 LB

°C

−30

141

136

131

126

122

117

113

108

104

−20

148

143

138

133

129

124

119

114

−10

150

145

140

135

130

125

108

151

146

141

135

118

100

152

150

147

144

132

109

149

145

142

120

102

154

147

144

138

111

NO FLIGHT

149

146

143

122

104

148

145

142

119

101

FOR AUTOROTATION V_NE REDUCE SPEED BY 22K

(85K MIN); DO NOT EXCEED CHART V_NE

MAX V_NE 130 KTS WITH LESS THAN 35 LB FUEL

Figure 9-8. V_NE Placards - Rolls Royce 250-C20R/2 (Sheet 1 of 2)

FAA Approved

9-30

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Emergency Floats

250 - C20R/2

FLOATS STOWED

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 2001 TO 2500 LB

°C

−30

141

136

131

126

122

117

112

−20

148

143

138

133

129

124

103

−10

152

145

140

135

112

151

146

125

104

152

150

147

113

147

128

105

150

147

115

NO FLIGHT

149

136

107

148

124

104

FOR AUTOROTATION V_NE REDUCE SPEED BY 22K

(90K MIN); DO NOT EXCEED CHART V_NE

MAX V_NE 130 KTS WITH LESS THAN 30 LB FUEL

250 - C20R/2

FLOATS STOWED

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 2501 TO 3000 LB

°C

−30

141

136

131

126

122

110

−20

148

143

138

133

121

−10

150

145

136

109

151

121

100

152

136

110

122

101

139

112

NO FLIGHT

125

103

119

FOR AUTOROTATION V_NE REDUCE SPEED BY 22K

(95K MIN); DO NOT EXCEED CHART V_NE

MAX V_NE 130 KTS WITH LESS THAN 30 LB FUEL

Figure 9-8. V_NE Placards - Rolls Royce 250-C20R/2 (Sheet 2 of 2)

FAA Approved

Revision 14

9-31

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Optional Equipment

Emergency Floats

PART III

EMERGENCY AND

MALFUNCTION PROCEDURES

EMERGENCY FLOAT INFLATION

If emergency occurs at airspeeds greater than maximum

CAUTION_{permissible float inflation speed, i.e., 81 knots IAS at less than 6,000}

feet altitude, 77 knots IAS at 6,000 feet altitude and above, reduce

speed to an appropriate value prior to float inflation. Do not exceed

airspeed limits of the EMERGENCY FLOATS INFLATED V_NE placard.

NOTE: Inflations have been demonstrated up to 90 knots IAS in autorotation and in

powered flight.

Procedures:

F Check float circuit breaker IN.

F Actuate float inflation switch. (Only momentary switch actuation is re-

quired.)

F Inflation should be accomplished at 2,000 feet or less above landing sur-

face to minimize differential pressure change with altitude change.

F For over-water operation in conditions near the Height-Velocity Diagram,

immediate pilot reaction will be required to ensure float inflation prior to

water contact.

F Make a normal landing approach. Minimize forward speed prior to water

contact. Recommended water contact speed 10 knots or less. Do not lower

collective until forward speed is 5 knots or less. Landings have been dem-

onstrated at gross weights up to 3,000 pounds and touchdown speeds up

to approximately 10 knots.

F If emergency occurs at night over water, the dual landing lights should

not be illuminated above 1000 feet in order to preserve battery power. Ap-

proach and landing as noted above.

NOTE: Landings should be made with the helicopter as level as possible laterally and

the nose of the helicopter slightly high. One-float-first landings may produce

undesirable but controllable yaw.

FAA Approved

9-32

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Emergency Floats

PART IV

NORMAL PROCEDURES

Preflight checks:

Check condition and security of stowed float package.

Check pressure gauge in each float package. If the pressure vessel is at

70°F (21.1°C), the pressure should read within 3000 to 3500 psig (Ref.

Figure 9-9).

Indicated gauge pressure will increase (decrease) approximately, as tabu-

lated below, per 1°F (1°C) increase (decrease) in temperature of the pressure

vessel.

Charge

Psig °F

Psig °C

Pressure

3000

5.7

10.2

3100

5.9

10.5

3500

6.6

11.9

Set BAT-EXT switch in proper position (BAT when using rotorcraft battery.

EXT when using an external power source.)

Check FLOATS circuit breaker IN.

FLOAT

P TEST

LH/RH

Press to test green float

indicator. LH and RH indicator lamps

should illuminate indicating that each circuit is operational.

Landing:

Tail-low landings on hard surfaces should be avoided, as stress

CAUTION_{damage to the float extensions may occur.}

In-flight float inflation data:

Float inflation time and altitude required for deployment are presented be-

low. Time is affected by temperature. Deployment altitude is based on a sta-

bilized autorotational rate of descent of 1800 feet per minute. It was calcu-

lated using the tabulated float inflation time, and a two second increment

for pilot reaction time:

Float Inflation Time

9.0 sec Temps up to 21°C

6.3 sec Temps above 21°C

Altitude Required For Deployment

330 feet Temps up to 21°C

250 feet Temps up to 21°C

FAA Approved

Revision 14

9-33

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Optional Equipment

Emergency Floats

PRESSURE GAGE

INSPECTION WINDOW

RIGHT HAND SKID (LEFT HAND SIMILAR)

PRESSURE GAGE

F03

Figure 9-9. Float Pressure Gauge

PART V

PERFORMANCE DATA

Hover Performance with Stowed Floats

No change from that of the basic helicopter with extended landing gear.

PART VII

HANDLING SERVICING

AND MAINTENANCE

Inspection and functional checks of the emergency float system should be con-

ducted in accordance with applicable installation instructions.

FAA Approved

9-34

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Engine Air Inlet Diverter

9-9. OPERATING INSTRUCTIONS - ENGINE AIR INLET DIVERTER

PART I

GENERAL

The MDHI Engine Air Inlet Diverter Kit (either 1 or 2 piece) inhibits ingesting

foreign objects into the engine air inlet which might be of sufficient mass to

puncture the inlet screen/particle separator and damage the engine. It reduces

ingestion of large dust and sand particles. It also reduces ingestion of snow and

slush, which may accumulate on the canopy at very slow speeds to be subse-

quently swept toward the inlet when forward speed is increased. The kit in-

cludes a hub and engine air inlet cover to prevent the entrance of snow and

water when the helicopter is parked.

FAA Approved

Revision 14

9-35

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Optional Equipment

Engine Air Inlet Diverter

PART II

LIMITATIONS

Environmental operating conditions:

Maximum operating OAT is 28°C at sea level, with 2.0°C per 1000 feet

lapse rate.

Airspeed limits:

V_NE is limited to 122 knots IAS or less (Ref. Figure 9-10).

V_NE is limited to 99 knots IAS or less during autorotation (Ref.

Figure 9-10).

Kit Compatibility:

The Mist Eliminator, 369D290125-21, may not be used with the Engine Air

Inlet Diverter Kit.

The Inlet Diverter Kit is not approved for use with the Allison 250-C20R/2

engine.

Placards:

Refer to Figure 9-10 for V_NE limitations.

V_NE IAS (KTS) INLET DIVERTER

OAT

PRESS ALT X 1000

GROSS WT = 2000 LB OR LESS

°C

−30

117

112

109

104

−20

119

114

110

105

−10

121

116

100

122

111

NO FLIGHT

FOR AUTOROTATION VNE REDUCE SPEED BY 23K

(85K MIN); DO NOT EXCEED CHART V_NE

Figure 9-10. VNE Placards (Sheet 1 of 2)

FAA Approved

9-36

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Engine Air Inlet Diverter

V_NE IAS (KTS) INLET DIVERTER

OAT

PRESS ALT X 1000

GROSS WT = 2001 TO 2500 LB

°C

−30

117

113

109

104

−20

119

114

103

−10

114

122

115

NO FLIGHT

FOR AUTOROTATION VNE REDUCE SPEED BY 23K

(90K MIN); DO NOT EXCEED CHART V_NE

V_NE IAS (KTS) INLET DIVERTER

OAT

PRESS ALT X 1000

GROSS WT = 2501 TO 3000 LB

°C

−30

117

113

106

−20

116

−10

122

106

116

106

118

NO FLIGHT

FOR AUTOROTATION VNE REDUCE SPEED BY 23K

(95K MIN); DO NOT EXCEED CHART V_NE

Figure 9-10. VNE Placards (Sheet 2 of 2)

FAA Approved

Revision 14

9-37

MD 500E

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

(Model 369E)

Optional Equipment

Engine Air Inlet Diverter

PART III

EMERGENCY AND

MALFUNCTION PROCEDURES

AIR RESTART - ENGINE

Procedures:

F Follow the emergency air restart procedure described in Section III.

F Recommended pressure altitude is 11,000 feet or below.

PART IV

NORMAL PROCEDURES

Cruise:

If at high cruise speed engine oil temperature approaches its limit, it may

be reduced by reducing airspeed.

FAA Approved

9-38

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Utiltiy Floats

9-10. OPERATING INSTRUCTIONS - UTILITY FLOATS

PART I

GENERAL

The MDHI Utility Float Kit is designed to facilitate operation of the helicopter

from both land and water. The kit consists of two multicell bag type floats, two

aft skid tube extensions, two sets of stabilizing surfaces, and the necessary

hardware for attachment. The floats mount on Extended Landing Gear.

An optional Night Landing Lighting Kit is available consisting of dual belly

mounted sealed beam lights, a circuit breaker, and a three position switch

installed on the collective control. Forward position illuminates the standard

nose mounted landing light; center position is off; and aft position illuminates

the belly lights. Night flight over water is permitted with the night landing

lighting kit installed.

FAA Approved

Revision 14

9-39

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Utiltiy Floats

PART II

LIMITATIONS

Float inflation pressure:

Minimum float operational pressure is 2.0 psig.

Types of operation:

Night flight over water beyond autorotation capability to ground is prohib-

ited, unless Night Landing Lighting Kit is installed .

Takeoff and landing on water at night is prohibited, unless Night Landing

Lighting Kit is installed.

Environmental operating conditions:

Changes of altitude are limited in accordance with the following.

The water landing site altitude may be at any altitude equal to or higher

than the takeoff base altitude, provided that the descent from the peak

altitude flown does not exceed 7700 feet.

NOTE: Each float cell has a pressure relief valve nominal setting of 5 psig. If the above

noted allowable decrease in altitude is exceeded, minimum operational float

pressure (2.0 psig) may not be available should the relief valve function at its

lower tolerance limit. This assumes the increase in temperature with decrease

in altitude is the standard lapse rate, i.e., (+) 3.6°F per (-) 1000 feet.

For takeoff from a high altitude base with the water landing site at a

lower altitude:

If the float pressure

The allowable altitude

(psig) at takeoff is:

decrease (feet) is:

2.0

2.5

1300

3. 0

2700

3.5

4300

4.0

5900

4.5

7700

5.0

9500

FAA Approved

9-40

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Utiltiy Floats

NOTE: To account for anticipated variations in ambient temperature or water

temperature at a scheduled landing site, the following procedure should be used

to maintain the minimum 2. 0 psig inflation pressure.

For ambient (air) temperature or water temperature colder than the temperature

at initial inflation, float inflation pressure should be increased 0.5 psig (above) the

minimum 2.0 psig) for each 15°F decrease in temperature anticipated.

Example:

70°F Ambient temperature at time of inflation minus

45°F Anticipated water temperature at scheduled landing sited equals

25°F Temperature decrease

Inflation pressure change to account for temperature change

(25° B 15°) x 0.5 psig = 0.8 psig

Minimum float inflation pressure for this operation would be

2.0 psig + 0.8 psig = 2.8 psig

NOTE: Temperature increase will increase float inflation pressure and need not be

considered.

Center of gravity (C.G. Envelope):

NOTE: The installation of the float kit contributes to an aft shift of the C.G. For conditions

requiring pilot only operations, ballast will be required in the utility stowage

compartment or front seat. The operator should determine the proper amount of

ballast required to remain within the aft C. G. limit for the zero fuel condition .

Placards:

Placards 1, and 2, are required when the utility floats are installed.

PLACARD #1 NIGHT FLIGHT OVER WATER BEYOND

AUTOROTATION CAPABILITY TO

GROUND PROHIBITED.

PLACARD #2 MINIMUM FLOAT PRESSURE 2.0 PSIG.

NOTE: Placard 1 not required if 369D292032 Night Landing Lighting Kit is installed.

Refer to Figure 9-11 for V_NE placards with utility floats installed.

FAA Approved

Revision 14

9-41

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Utiltiy Floats

UTILITY FLOATS

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 2000 OR LESS

°C

−30

127

122

118

113

109

100

−20

129

124

119

109

−10

122

100

130

110

124

101

112

103

NO FLIGHT

115

110

FOR AUTOROTATION V_NE REDUCE SPEED BY 2K

(85K MIN); DO NOT EXCEED CHART V_NE

UTILITY FLOATS

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 2001 TO 2500

°C

−30

127

122

118

110

−20

121

102

−10

110

130

121

102

111

123

103

112

NO FLIGHT

125

105

120

102

FOR AUTOROTATION V_NE REDUCE SPEED BY 2K

(90K MIN); DO NOT EXCEED CHART V_NE

Figure 9-11. V_NE Placards (Sheet 1 of 2)

FAA Approved

9-42

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Utiltiy Floats

UTILITY FLOATS

V_NE IAS (KNOTS)

OAT

PRESS ALT X 1000

GROSS WT = 2501 T0 3000

°C

−30

127

122

107

−20

116

100

−10

126

107

130

116

100

126

108

117

101

128

109

NO FLIGHT

118

102

115

FOR AUTOROTATION V_NE REDUCE SPEED BY 2K

(95K MIN); DO NOT EXCEED CHART V_NE

Figure 9-11. V_NE Placards (Sheet 2 of 2)

Kit combination limitations:

The Passenger Step Kit 369H90060 may not be installed in combination

with utility floats.

The Cargo Hook Kit may be used in combination with the utility floats.

With an external load on the hook, the V_NE limitations of the Cargo Hook

Kit apply (Ref. Figure 9-1). The external load on the hook is limited to 1865

lbs maximum.

Litter Kits may not be used in combination with the utility floats.

The Four-Bladed Tail Rotor Kit may not be used in combination with the

utility floats.

FAA Approved

Revision 14

9-43

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Utiltiy Floats

PART III

EMERGENCY AND

MALFUNCTION PROCEDURES

AUTOROTATIONAL LANDING

Procedures:

F Make a normal autorotational approach. Minimize forward speed prior to

water contact.

F Recommended water contact speed 10 knots or less. Do not lower collec-

tive until forward speed is 5 knots or less.

F Landings have been demonstrated at gross weights up to 3000 pounds and

touchdown speeds up to approximately 15 knots.

NOTE: Landings should be made with the helicopter as level as possible laterally and

the nose of the helicopter slightly high. One-float-first landings may produce

undesirable but controllable yaw.

If emergency occurs at night over water, the dual landing lights should not be

illuminated above 1000 feet altitude in order to preserve battery power.

PART IV

NORMAL PROCEDURES

Rotor engagement on water:

Determine that sufficient clearance exists between the helicopter and any

obstacle during engine start. Tail swing, before directional control is ob-

tained, will be approximately 200 degrees.

Landing:

Make a normal landing approach. Minimize forward speed prior to water

contact. Recommended water contact speed 10 knots or less. Do not lower

collective until forward speed is 5 knots or less. Landings have been demon-

strated at gross weights up to 3000 pounds and touchdown speeds up to

approximately 15 knots.

NOTE: Landings should be made with the helicopter as level as possible laterally and

the nose of the helicopter slightly high. One-float-first landings may produce

undesirable but controllable yaw.

FAA Approved

9-44

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Utiltiy Floats

Water taxiing:

Water taxi speed should be less than 10 knots. It will be necessary to use

some collective pitch to taxi at greater than 5 knots.

Some collective pitch may be required under certain conditions to stop heli-

copter during water taxi. The use of aft longitudinal cyclic is not completely

effective under all conditions.

Rotor brake application on water:

Determine that sufficient clearance exists between the helicopter and any

obstacle during rotor brake application. Azimuth change will be approxi-

mately 200° (nose left).

PART V

PERFORMANCE DATA

Hover performance:

Refer to Section V for IGE hover performance data.

Height-Velocity diagram:

Refer to Figure 9-12.

Airspeed calibration:

Refer to Figure 9-13.

FAA Approved

Revision 14

9-45

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Utiltiy Floats

SMOOTH HARD SURFACE

OR CALM WATER

WIND CALM

AVOID OPERATION IN

CROSS-HATCHED AREAS

600

500

400

RECOMMENDED TAKEOFF

PROFILE

300

200

100

ÎÎ

ÎÎÎÎ

ÎÎ

100

120

140

INDICATED AIRSPEED - KNOTS

F03-046

(CORRECTED FOR INSTRUMENT ERROR)

Figure 9-12. Height-Velocity Diagram - Utility Floats Installed

FAA Approved

9-46

Revision 14

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Garmin G500H Integrated System

9-11. OPERATING INSTRUCTIONS: GARMIN G500H INTEGRATED

SYSTEM

PART I

GENERAL

Information for operating the Garmin Avionics Suite is contained with the fol-

lowing supplied vendor documents.

G500H Cockpit Reference Guide - 190-01150-03 Rev B, or later

G500H Pilot's Guide - 190-01150-02 Rev B, or later

GMA 347 Audio Panel Pilot Guide

GNS 430W Pilot Guide and Reference

GNC 420W Pilot Guide and Reference

GTX 330 Transponder Pilot Guide

Major components:

GDU 620 Dual Display (PDF/MFD)

GNS 430W all-in-one GPS/NAV/COM

GNC 420W GPS/COM

GMA 347 Audio Panel

GTX 330 Mode S Transponder

GDC 74H Air Data Computer (ADC)

GTP 59 OAT Probe

GRS 77H Attitude and Heading Reference System (AHRS)

GMU 44 Magnetometer

Other integrated equipment:

Emergency Locator Transmitter - 406MHz

Avionics Cooling Fan

Avionics Master Switch

Collective Hobbs Hour Meter

PART II

LIMITATIONS

NOTE: Flight operations with the Garmin Suite requires compliance with Section II,

Paragraph 2-2, “Kinds of Operations”, specifically “for day and night VFR

operations only”.

FAA Approved

Revision 18

9-49

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Garmin G500H Integrated System

PART III

EMERGENCY AND

MALFUNCTION PROCEDURES

GENERAL

NOTE: GDU 620 PFD airspeed tape may lag during aggressive acceleration or

deceleration.

AVIONICS POWER FAILURE

Indications: Loss of avionics equipment on AVIONICS BUS and avionics master circuit

breaker switch

not in UP position.

Conditions: Power failure to Avionics Bus

NOTE: Only the GNS 430, PFD, MFD and audio panel remain functional.

Procedures:

F Cycle avionics master switch back to ON.

F If condition remains, ensure avionics master switch remains OFF.

F Continue flight using remaining avionics, and advise maintenance after

landing.

PART IV

NORMAL PROCEDURES

No change for start or shutdown procedures found in Section IV except:

Daily Preflight Checks - Exterior Fuselage - Forward End

OAT Probe

CHECK: SECURED /

NO DAMAGE

Pre-start cockpit check - Electrical Power ON

G500H PFD and MFD

CHECK ON

Basic pre-start checks

COMPLETE

G500H PFD and MFD

CHECK FOR ALERT

INDICATIONS

DURING START-UP

FAA Approved

9-50

Revision 18

MD 500E

ROTORCRAFT FLIGHT MANUAL

CSP-E-1

(Model 369E)

Optional Equipment

Garmin G500H Integrated System

Engine run-up:

Basic start procedures

COMPLETE

Avionics master switch

GNS 430

ON / CHECK

DATABASE

CURRENT

Press ENTER on GNS 430 /

CHECK INSTRUMENT

select GPS 1 on PFD

PANEL SELF-TEST

ON PFD

GNC 420

ON / CHECK

DATABASE

CURRENT

Press ENTER on GNC 420 /

CHECK INSTRUMENT

select GPS 2 on PFD

PANEL SELF-TEST

ON PFD

FAA Approved

Revision 18

9-51

CSP-E-1

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Optional Equipment

Garmin G500H Integrated System

COLLECTIVE HOBBS METER

AIRFRAME HOBBS METER

NOTE: COLLECTIVE HOBBS METER TRACKS TIME ONCE

THE COLLECTIVE IS RAISED OFF THE STOP

COM 2

GPS2 (IF INSTALLED)

ELT

GPS1

TOP VIEW

COM 1

MARKER BEACON

OAT PROBE

NAV

TRANSPONDER

BOTTOM VIEW

F03-056

Figure 9-16. Runtime (Hobbs) Meter, OAT Probe and NAV/COM Antenna Locations -

Typical

FAA Approved

9-54

Revision 18

Helicopter MD 500E. Flight Manual (1982-2011) - page 3