HANDBOOK OF MAINTENANCE INSTRUCTIONS FOR MDHI 369D/E/FF-500/600N HELICOPTERS (ISSUED: 1990)

MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

MODEL

SERIAL NO.

REGISTRATION NO.

DATE

EXAMPLES OF FORWARD, AFT AND LATERAL LOADING

LONG.

WEIGHT

EXAMPLE 1, FORWARD

ARM

MOMENT

(LBS)

(IN.)

(IN. LB.)

BASIC WEIGHT

PILOT

43.5

COPILOT

43.5

FULL FUEL QUANTITY

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

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

INCHES.

LONG.

WEIGHT

EXAMPLE 2, AFT

ARM

MOMENT

(LBS)

(IN.)

(IN. LB.)

BASIC WEIGHT

PILOT

GROSS WEIGHT (ZERO FUEL) − AFT C.G.

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

INCHES.

LATERAL

WEIGHT

EXAMPLE 3, LATERAL

ARM

MOMENT

(LBS)

(IN.)

(IN. LB.)

BASIC WEIGHT

PILOT

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

APPROVED LATERAL C.G. FOR EXAMPLE 3 GROSS WEIGHT

INCHES.

*SEE FLIGHT MANUAL, SECTION 6, FOR C.G. LIMITS AT GROSS WEIGHT

Figure 206. Weight and Balance Report Form (Sheet 2 of 2)

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CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

TABLE 1 SURPLUS AND MISSING EQUIPMENT

MODEL

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

)

(

)

(

1549

)

(

)

ONE QT. ENGINE OIL

2.1

133.4

280

UNUSABLE FUEL

12.0

93.0

1116

FLIGHT MANUAL

1.8

85.0

153

McDonnell Douglas

FORM 1702 (REV 4−83)

Page

Helicopter Company

Figure 207. Surplus and Missing Items Report

Page 214

Revision 23

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CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

Determining total unadjusted net weight and longitudinal CG - 369D/E/FF

(a)

(b)

(c)

(d)

Tare or

Weighing

Scale

Calibration

Net

Arm

Points

Reading (lbs)

Correction (lbs)

Weight (lbs)

(inches)

Moment (in.-lb)

Left Main

648.9

- 1.5

647.4

96.9

62733

Right Main

618.9

+ 0.5

619.4

96.9

60020

Tail

195.9

197.2

38631

Total Unadjusted Net Weight

1462.7

110.3

161384

(f)

(e)

Determining total unadjusted net weight, longitudinal and lateral CG - 500MD

(a)

(b)

(c)

(d)

(g)

Tare or

Scale

Calibration

Net

Longitudinal

Lateral

Longitudinal

Weighing

Reading

Correction

Weight

Arm

Moment

Points

(lbs)

(inches)

(inch-lb)

Left Main

1020.0

0.0

1020.0

96.9

- 25.6

98838

62733

Right Main

939.0

0.0

939.0

96.9

+ 25.6

90989

60020

Tail

128.0

0.0

128.0

197.2

0.0

25242

Total Unadjusted Net Weight

2087.0

103.1

- 1.0

215069

- 2084

(f)

(i)

(e)

(h)

Determining total unadjusted net weight, longitudinal and lateral CG - 500N

(a)

(b)

(c)

(d)

(g)

Tare or

Scale

Calibration

Net

Longitudinal

Lateral

Longitudinal

Weighing

Reading

Correction

Weight

Arm

Moment

Points

(lbs)

(inches)

(inch-lb)

Left Main

759.0

0.0

759.0

96.9

-25.6

73547.1

-19430.4

Right Main

738.8

0.0

738.8

96.9

+25.6

71589.7

18913.2

Tail

136.8

0.0

136.8

275.4

3764.7

Total Unadjusted Net Weight

1634.6

111.8

-.3

182811.5

-5172

(f)

(i)

(e)

(h)

Figure 209. Example 1 (Sheet 1 of 2)

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CSP-HMI-2

MAINTENANCE MANUAL

Determining total unadjusted net weight, longitudinal and lateral CG - 600N

(a)

(b)

(c)

(d)

(g)

Tare or

Scale

Calibration

Net

Longitudinal

Lateral

Longitudinal

Lateral

Weighing

Reading

Correction

Weight

Arm

Moment

Points

(lbs.)

(inches)

(inch-lbs.)

Left Main

919.2

0.0

919.2

96.9

-26.0

89070

-23899

Right Main

885.4

0.0

885.4

96.9

+26.0

85795

23020

Tail

104.7

0.0

104.7

303.3

31756

Total Unadjusted Net Weight

1909.3

108.2

-.5

206621

-879

(f)

(i)

(e)

(h)

Determining basic weight and the longitudinal and lateral CG - 500MD

Weighing

Scale

Tare or

Net Weight

Arm

Moment

Points

Reading

Calibration

(lbs)

(in.)

(in.-lb)

(lbs)

Correction

(lbs)

Left Main

648.9

- 1.5

647.4

96.9

62733

Right Main

618.9

+ 0.5

619.4

96.9

60020

Tail

195.9

197.2

38631

Total Unadjusted Net Weight

1462.7

110.3

161384

Total Weight of Missing Equipment (Ref. Figure 207)

+ 21.0

93.6

+ 1966

Total Weight of Surplus Equipment (Ref. Figure 207)

- 1.3

96.9

- 126

Total Basic Weight

1482.4

110.1

163224

Determining basic weight and the longitudinal and lateral CG - 600N

Tare or

Scale

Calibration

Longitudin

Lateral

Longitudin

Lateral

Weighing

Reading

Correction

Net Weight

al Arm

Arm

al Moment

Moment

Points

(lbs.)

(inches)

(inch-lbs.)

Left Main

919.2

0.0

919.2

96.9

-26.0

89070

-23899

Right Main

885.4

0.0

885.4

96.9

+26.0

85795

23020

Tail

104.7

0.0

104.7

303.3

31756

Total Unadjusted Net Weight

1909.3

108.2

-.5

206621

-879

Total Weight of Missing Equipment

+15.9

97.4

1549

(Ref. Figure 207)

Total Weight of Surplus Equipment

-1.3

96.9

-126

(Ref. Figure 207)

Total Basic Weight

1923.9

108.1

-.5

208044

-879

Figure 209. Example 1 (Sheet 2 of 2)

Page 217

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

TOWING

MAINTENANCE PRACTICES

1. Ground Handling Wheels

Excessive lead-lag load applied

CAUTION

to the main rotor blades during

ground handling can result in damage to the

NOTE: At regular intervals, check wheel tire

elastomeric damper buns and failure of the

pressure and repack wheel bearings (Ref.

damper assembly. Operators and mainte

Sec. 32-40-00/32-40-60).

nance personnel should use extra caution to

avoid lead-lag loads in excess of 35 lb. (16

kg) at the tip of the main rotor blades.

A. Standard Ground Handling Wheels

(1). Attach ground handling wheels (ST101

or ST104) as shown (Ref. Figure 201),

(Ref. Figure 201) Standard ground handling

and hold tail up while lowering the

wheels, available as a special tool for helicop

wheels (raising helicopter) with

ters not equipped with floats, are used for

detachable jack handle (ST102 or

moving helicopter by hand and for towing

ST103).

helicopter. The wheels are manually lowered

with a detachable jack handle and are held in

(2). Manually move helicopter on ground

the down position (helicopter raised on wheels)

handling wheels by balancing at

by a mechanical lock. The wheels for the

tailboom and pushing on rear fuselage

369D/E/FF - 500N helicopters are equipped

portion of airframe.

with tow bar attach fitting.

Except under extreme emergen

CAUTION

cy conditions, do not tow heli

B. Special Ground Handling Wheels

copter at speeds over 5 mph (8 KmH). Do not

(Float−Equipped Helicopters, 369D/E/FF −

allow front ends of skid tubes to drag on

500N)

ground. Avoid sudden stops and starts, and

short turns which could cause helicopter to

turn over. Allow inside wheel to turn (not

Special ground handling wheels are available

pivot) while helicopter is being turned. Safe

for towing helicopters equipped with utility or

minimum turning radius is approximately

emergency floats (Ref. Sec. 32-40-00).

20 ft. (6 M).

NOTE: If tow bar is not equipped to keep front

end of skid tubes from dragging, have an as

2. Helicopter Towing and Manual Moving

sistant balance helicopter at tailboom.

(369D/E/FF − 500N)

(3). Tow helicopter on ground handling

wheels by attaching suitable tow bar to

Special Tools

tow bar fittings.

(Ref. Section 91−00−00)

Item

Nomenclature

3. Helicopter Manual Moving (600N)

ST101

Ground handling wheels

(Ref. Figure 202)

ST102

Handle-jack assembly, ground handling

(straight)

Special Tools

ST103

Handle-jack assembly, ground handling

(Ref. Section 91−00−00)

(offset)

Item

Nomenclature

ST104

Ground handling wheels (one side)

ST101

Ground handling wheels

Page 201

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CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

Excessive lead-lag load applied

ground handling wheel set, allowing the

CAUTION

to the main rotor blades during

helicopter to be moved by one person.

ground handling can result in damage to the

elastomeric damper buns and failure of the

Special Tools

damper assembly. Operators and mainte

(Ref. Section 91−00−00)

nance personnel should use extra caution to

Item

Nomenclature

avoid lead-lag loads in excess of 35 lb. (16

ST101

Ground handling wheels

kg) at the tip of the main rotor blades.

ST105

Tow bar (600N)

(1). Ensure all stress panels are installed

on helicopter before jacking.

Excessive lead-lag load applied

NOTE:

CAUTION

to the main rotor blades during

D The ground handling wheel set can be at

ground handling can result in damage to the

tached to the skids facing either direction

elastomeric damper buns and failure of the

for ease of jacking.

damper assembly. Operators and mainte

nance personnel should use extra caution to

D Ensure all four ground handling attach

avoid lead-lag loads in excess of 35 lb. (16

points are engaged in ground handling

kg) at the tip of the main rotor blades.

wheel set.

(2). Attach ground handling wheels (ST101)

(1). Ensure all stress panels are installed

and hold tail up while lowering the

on helicopter before jacking.

wheels (raising helicopter).

(2). Raise helicopter with ground handling

(3). Manually move helicopter on ground

wheel set (ST101).

handling wheels by balancing at

(3). Position tow bar (ST105), with caster

tailboom and pushing on rear fuselage

wheels, straddling front of skid tube

portion of airframe.

assembly.

Except under extreme emergen

CAUTION

(4). Attach nylon straps under skid tube

cy conditions, do not tow heli

and ratchet skid tube into rubber cups

copter at speeds over 5 mph (8 KmH). Do not

on tow bar.

allow front ends of skid tubes to drag on

ground. Avoid sudden stops and starts, and

Except under extreme emergen

short turns which could cause helicopter to

CAUTION

cy conditions, do not tow heli

turn over. Allow inside wheel to turn (not

copter at speeds over 5 mph (8 KmH). Do not

pivot) while helicopter is being turned. Safe

allow front ends of skid tubes to drag on

minimum turning radius is approximately

ground. Avoid sudden stops and starts, and

20 ft. (6 M).

short turns which could cause helicopter to

turn over. Allow inside wheel to turn (not

4. Helicopter Towing (600N)

pivot) while helicopter is being turned. Safe

(Ref. Figure 202) The tow bar is equipped with

minimum turning radius is approximately

caster wheels and is designed for use with the

20 ft. (6 M).

Page 202

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CSP-HMI-2

MAINTENANCE MANUAL

TABLE OF CONTENTS

Para/Figure/Table

Title

Page

10-10-00 Parking and Mooring

Maintenance Practices

201

1. Helicopter Parking

201

2. Helicopter Mooring

201

Figure 201. Parking and Mooring (Sheet 1 of 2)

203

10-20-00 Storage

Maintenance Practices

201

1. Preservation and Storage

201

2. Flyable Storage (No Time Limit)

201

A. Inspection Before Storage

201

B. Storage

201

C. Return to Service

201

3. Storage Up to 45 Days

201

A. Inspection During Storage

201

B. Storage

201

C. Return to Service

202

4. Storage Up to 6 Months

202

A. Inspection During Storage

202

B. Storage

202

C. Return to Service

203

10-30-00 Blade Folding

Maintenance Practices

201

1. Main Rotor Blades Storage Rack Description

201

2. Main Rotor Blades Storage Rack Inspection

201

3. Main Rotor Blades Folding and Unfolding

201

A. Helicopter Location for Blade Folding

201

B. Main Rotor Blades Folddown Preparation

201

C. Aft Main Rotor Blades Folding

202

D. Forward Main Rotor Blades Folding

203

Figure 201. Folding and Stowing Main Rotor Blades

204

E. Main Rotor Blades Unfolding Preparation

205

F. Aft Main Rotor Blades Unfolding

205

G. Forward Main Rotor Blades Unfolding

206

H. Main Rotor Blades Storage Rack Removal and Storage

206

4. Main Rotor Flight Controls Adjustment and Testing

206

Page i

10 Contents

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

PARKING AND MOORING

MAINTENANCE PRACTICES

1. Helicopter Parking

(c). Secure blade sock tiedown cord for

blade located above tailboom to

To park helicopter for short intervals, perform

tailboom. Secure other blade sock

following steps (1). thru (4). For longer

tiedown cords to fuselage jack fittings

duration parking, also perform steps (5). and

(ST202).

(6).

(4). Secure six-bladed main rotor blades as

follows:

Special Tools

(Ref. Section 91−00−00)

When securing blade sock tie

CAUTION

Item

Nomenclature

down cords, take up slack but do

not apply bending loads on blades.

ST202

Jack fittings

ST2002

Blade socks

(a). Position blades so that three blades

ST2004

Air inlet fairing cover

are on each side of helicopter (Ref.

ST2005

Engine exhaust cover

Figure 201).

(b). Install blade socks (ST2002) on all

blades.

To prevent rotor damage from

CAUTION

blade flapping

(droop stop

(c). Secure blade sock tiedown cords to

pounding) as a result of air turbulence from

fuselage jack fittings or cabin steps.

other aircraft landing, taking off or taxiing,

or sudden wind gusts, rotor blades should be

(5). Install air inlet fairing cover (ST2004)

secured whenever helicopter is parked.

on air inlet front fairing (Ref.

Figure 201).

(1). Locate helicopter slightly more than

blade clearance from nearby objects on

(6). Install engine exhaust cover (ST2005)

most level ground available.

on exhaust tailpipe (Ref. Figure 201).

(2). Apply friction to lock cyclic and collec

2. Helicopter Mooring

tive sticks so that friction control knobs

are positioned as follows: neutral for

Whenever severe storm conditions or wind

cyclic stick and full down for collective

velocities higher than 40 knots are forecast,

stick.

helicopter should be hangared or evacuated to

a safer area. If these precautions are not

NOTE: If not already accomplished, apply

possible, moor helicopter as follows.

paint mark on edge of guide to locate neu

tral position for future reference (Ref. Sec.

Special Tools

67-10-00).

(Ref. Section 91−00−00)

Item

Nomenclature

(3). Secure five-bladed main rotor blades as

follows:

N/A

Stakes or ground anchors (two)

N/A

Cable or rope

When securing blade sock tie

CAUTION

ST202

Jack fittings

down cords, take up slack but do

ST2001

Pitot tube cover

not apply bending loads on blades.

ST2004

Air inlet fairing cover

(a). Turn blades until one blade is

ST2005

Engine exhaust cover

directly above tailboom (Ref.

Figure 201).

(1). Park helicopter (Ref. Helicopter

(b). Install blade socks (ST2002) on all

Parking) or remove main rotor blades

blades.

(Ref. Sec. 62-10-00) and install air

Page 201

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

STORAGE

MAINTENANCE PRACTICES

1. Preservation and Storage

(e). Open movable air vents in each door

of cargo compartment. Position

A helicopter to be placed in storage or non-op

opening in each air vent downward.

erational status must have adequate inspec

Close all other vents.

tion, maintenance and preservation to avoid

unnecessary deterioration of airframe and

(f). Install covers and equipment used to

components of equipment. Extent of preventive

park and moor helicopter.

maintenance that is to be performed depends

(g). Install a static ground.

on anticipated time in storage. Following

paragraphs describe what should be performed

C. Return to Service

in helicopter: for flyable storage; for up to 45

days in storage; and for up to 6 months in

(1). Remove covers and equipment used to

storage.

park and moor helicopter.

(2). Perform Daily Pre-Flight Check (Ref.

2. Flyable Storage (No Time Limit)

appropriate PFM or RFM).

A. Inspection Before Storage

3. Storage Up to 45 Days

(1). Perform Daily Pre-Flight Check (Ref.

A. Inspection During Storage

appropriate PFM or RFM).

(1).

Where local average humidity exceeds

(2). Ensure that fuel cells are full (topped

40 percent, carefully inspect helicopter

off), and that oil in engine oil tank and

every 15 days for corrosion. Perform

main, fan and tail rotor transmissions

corrosion control as necessary (Ref. Sec.

is at FULL level (Ref. Sec. 12-00-00).

20-40-00). When inspecting for

corrosion, pay particular attention to

B. Storage

those areas where moisture deposits do

not evaporate rapidly.

To maintain a flyable storage condition,

perform the following:

(2).

Where local average humidity is 40

percent or less, inspect for corrosion

(1). Perform Daily Pre-Flight Check (Ref.

every 30 days.

appropriate PFM or RFM).

(3).

If interior temperature of fuselage

(2). Perform ground runup at least once

exceeds 160°F (71°C), ventilate helicop

every five days (Ref. applicable PFM or

ter by opening all doors and vents. If

RFM, Table 201, Sec. 01-00-00).

necessary, promote air circulation by

use of fans or other forced air equip

(a). Start engine. After idle stabilizes,

ment.

accelerate engine to 100 percent N₂,

collective full down. Operate until oil

(4).

Ensure that fuel cells are full (topped

temperature is in normal operating

off) and that rotor transmissions are at

range and ammeter indicates battery

FULL level.

is fully charged.

(5).

Drain fuel cell sump daily. (Replenish

fuel as necessary.)

(b). Shut down engine.

(6).

Check fuel and oil systems periodically

(c). Drain fuel cell sump (Ref. Sec.

for leakage. Replenish as necessary.

12-00-00). (Replenish fuel as neces

sary.)

B. Storage

(d). Ensure that fuel shutoff valve is

(1). Perform engine preservation according

closed (Ref. Sec. 28-00-00).

to applicable Allison Engine Operation

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CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

and Maintenance Manual (Ref. Table

(8). Perform Daily Pre-Flight Check (Ref.

201, Sec. 01-00-00) and current engine

appropriate PFM or RFM).

service letters.

4. Storage Up to 6 Months

(2).

Remove battery (Ref. Sec. 96-05-00)

A. Inspection During Storage

and store in cool, dry area.

(1). Perform same inspection as for 45 days

(3).

If necessary, clean battery compartment

of storage.

(Ref. Sec. 20-20-00).

(2). Check main rotor, tail rotor and fan

blades for damage every 15 days (Ref.

(4).

Ensure that fuel shutoff valve is closed

Chap. 62 and 64).

(Ref. Sec. 28-00-00).

(3). Check areas around mooring attach

(5).

Clean entire helicopter.

ments for damage every 15 days.

(6).

Inspect all drain holes (blades, fuselage,

B. Storage

etc.) for obstructions and clear where

necessary.

Consumable Materials

(Ref. Section 91−00−00)

(7).

Open movable air vents in each door of

Item

Nomenclature

cargo compartment; position opening in

each air vent downward. Close all other

CM201

Protective coating

air vents.

CM210

Corrosive preventive

CM729

Tape, masking, pressure sensitive

(8).

Park and moor helicopter.

(9).

Install a static ground.

Special Tools

(Ref. Section 91−00−00)

(10).

Remove from area any objects that are

Item

Nomenclature

likely to strike helicopter during high

ST2001

Pitot tube cover

wind conditions.

C. Return to Service

(1).

Perform engine preservation according

to applicable Allison Engine Operation

(1). Check that battery area is clean; then

and Maintenance Manual (Ref. Table

install and connect battery (Ref. Sec.

201, Sec. 01-00-00) and current

96-05-00).

applicable engine service letters.

(2). Check that fuel cells are full (Ref. Sec.

(2).

Drain engine oil system (Ref. Sec.

12-00-00).

12-00-00) and fill engine oil tank with

corrosion preventive (CM210).

(3). Remove covers and equipment used to

(3).

Remove battery (Ref. Sec. 96-05-00)

park and moor helicopter.

and store it in cool, dry area.

(4). Inspect areas around mooring attach

(4).

Clean battery compartment, if neces

ments for damage. Repair damage as

sary.

necessary.

(5).

Ensure that fuel shutoff valve is closed

(5). Clean helicopter, as necessary.

(Ref. Sec. 28-00-00).

(6). Check that all drain holes in helicopter

(6).

Seal static source openings in engine

are free of obstructions.

inlet fairing with masking tape

(CM729) and cover pitot tube with pitot

(7). Perform engine depreservation accord

tube cover (ST2001).

ing to applicable Allison Engine

(7).

Clean entire helicopter.

Operation and Maintenance Manual

(Ref. Table 201, Sec. 01-00-00) and

(8).

Inspect all drain holes (blades, fuselage,

current applicable engine service

etc) for obstructions and clear them

letters.

where necessary.

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CSP-HMI-2

MAINTENANCE MANUAL

(9). Spray or brush on the canopy and all

(2). Remove masking tape from all external

windows a 0.008 inch (0.203 mm)

access doors.

thickness of protective coating (CM201).

Do not use steam or unautho

Cover and overlap all edges.

CAUTION

rized cleaning compounds to

(10). Inspect all external access doors for

clean helicopter as damage to equipment

close fit. If doors are likely to admit

may result.

moisture, seal edges with masking tape

(CM729).

(3). Drain corrosion preventive from oil

tank and replenish with correct oil (Ref.

(11). Park and moor helicopter.

Sec. 12-00-00).

(12). Install a static ground.

(4). Perform same procedures as for return

to service after 45 days of storage.

(13). Remove any objects from area that are

likely to strike helicopter during high

NOTE: Depreservation of engine fuel system

wind conditions.

can usually be accomplished by making a

normal start. (Ref. applicable Allison En

C. Return to Service

gine Operation and Maintenance Manual,

(1). Carefully lift protective coating along

Table 201, Sec. 01-00-00 and current appli

edges and peel it from canopy and

cable engine service letters for engine de

windows.

preservation procedures.)

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CSP-HMI-2

MAINTENANCE MANUAL

BLADE FOLDING

MAINTENANCE PRACTICES

1. Main Rotor Blades Storage Rack

(1). Verify that front and rear support

Description

assemblies are complete and tight in all

details.

(Ref. Figure 201)

(2). Visually inspect for missing nuts, bolts,

cushions, and shock cords.

(1).

The main rotor blade storage rack

(3). Verify that no support tubing is bent.

stows and secures the main rotor blades

on Model 369 helicopters during ground

(4). Verify that plywood of rear support is

handling operations. The storage rack

not split, cushions not torn, or nylon

consists of fore and aft units which,

webbing harness not missing its buckle.

when installed, provide blade protection

for helicopters that cannot be placed in

3. Main Rotor Blades Folding and Unfolding

hangers or evacuated during adverse

The following paragraphs provide instruction

weather conditions.

for operation of the main rotor blade storage

rack: For the unpinning of the main rotor

(2).

The aft blade storage rack supports

blades; for folding, unfolding, and repining of

three blades and consists of a plywood

the blades. Adjustment and testing of main

blade rack which incorporates shock

rotor flight controls, necessary after the blades

(bungee) cords and nylon-webbing

have been re-pinned, is also covered here.

harness straps with buckles, pull tabs,

(Ref. Sec. 20-40-00 for information about

and a grommet. The aft storage rack is

adjustment and corrosion protection of main

installed on the tailboom at Sta. 197.78,

rotor blade attaching pins.)

just above the jack fitting. A decal on

the aft side of the storage rack facili

If main rotor blades are to re

CAUTION

tates proper fore and aft positioning on

main folded for a considerable

the tailboom. The harness grommet

length of time, main rotor hub must be cov

engages the jack fitting and holds the

ered with a suitable weather-resistant cov

storage rack in position when the

er.

harness straps are tightened and

NOTE: A mechanic's assistant is needed for

secured. Shock cords secure the blades.

blade folding and unfolding.

(3).

The forward blade storage rack sup

A. Helicopter Location for Blade Folding

ports two blades and consists of a

(1). Locate helicopter slightly more than

plywood blade rack which incorporates

rotor span from other aircraft or

shock cords, blade clamp (top blade

vehicles.

only), rack support tubes, and landing

gear clamps. The storage rack is

(2). Park helicopter on the most level

installed forward of the fuselage so that

ground available so that the load is

the blade clamp support is positioned

balanced as much as possible.

left of the helicopter centerline. The

rack support tubes are secured with

B. Main Rotor Blades Folddown Preparation

clamps to the landing gear just aft of

the skid tip lights. Shock cords secure

Special Tools

the blades.

(Ref. Section 91−00−00)

Item

Nomenclature

Main Rotor Blades Storage Rack

ST2003

Main rotor blade storage rack

Inspection

ST2004

Air inlet fairing cover

ST2005

Engine exhaust cover

(Ref. Figure 201)

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CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

(1). Inspect rack (Ref. Main Rotor Blades

(a). Position rear blade support assembly

Storage Rack Inspection).

on tailboom at Sta. 197.78, with its

lower step on left side of helicopter.

(2). Position main rotor so that one blade is

(b). Attach and secure straps. Adjust

directly above and parallel to helicopter

strap pull tabs so that harness

tailboom.

grommet engages jack fitting on

tailboom.

(3). Lock cyclic control stick (by applying

friction) in the following positions:

(2). Install trailing rotor blade to aft storage

rack.

(a). Set collective pitch to mid position.

(a). Into center cushioned support step of

(b). Set longitudinal cyclic to full aft

rear blade support assembly, position

position.

trailing rotor blade (blade that is

directly above and parallel to tail

(c). Set lateral cyclic to two thirds of total

boom).

stick travel from full left toward full

right.

Blade movement must be re

CAUTION

strained in the following steps

During blade folding, continual

to prevent damage since, with damper dis

CAUTION

ly monitor stick positions to

engaged, the blade is free to pivot on blade

make sure no change occurs. Serious blade

attaching pin.

damage may result from improper stick

(b). Remove bolt or (alternatively)

placement.

attaching pin from damper arm of

trailing rotor blade, and move

(4). Disconnect wires or antennas (as

damper away from blade; replace bolt

applicable) at tailboom attach fitting,

and coil them.

(or attaching pin) in damper arm.

NOTE: It is not necessary to remove a blade at

(5). Cover (ST2004 and ST2005) engine air

taching pin in order to fold the first blade.

inlet and exhaust openings to prevent

entry of foreign objects during blade

(c). Secure blade in support assembly

folding.

with shock cord fastener.

During blade folding, use blade

(3). Install remaining blades to aft storage

CAUTION

support pole (ST2003). Prevent

rack.

scratching of blade by attaching pins or

Blade movement must be re

bolts. Avoid brushing of blades against one

CAUTION

strained in the following steps

another or against any other surface. Lift

to prevent damage since, with damper dis

blade near tip to remove load on blade at

engaged, the blade is free to pivot on blade

taching pins.

attaching pin.

C. Aft Main Rotor Blades Folding

NOTE: The right blade goes to the top hold

down position, and the left blade to the bot

(Ref. Figure 201)

tom holddown position.

(a). Remove bolt or (alternatively)

Special Tools

attaching pin from damper arm of

(Ref. Section 91−00−00)

rotor blade, and move damper away

Item

Nomenclature

from blade; replace bolt (or attaching

ST2003

Main rotor blade storage rack

pin) in damper arm.

(b). Unlock (but do not remove) blade

(1). Install aft storage rack (ST2003) to

attaching pin that secures leading

helicopter.

edge of blade to main rotor hub.

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CSP-HMI-2

MAINTENANCE MANUAL

(c). Unlock and remove blade attaching

(d). Attach upper ends of support tubes to

pin that secures trailing edge of blade

double blade support. Adjust tube

to lead-lag link, and position cam

length to proper height as required

handle vertically above pin.

for extended or standard landing

gear. Secure with hardware provided.

(d). Instruct mechanic's assistant using

blade-support pole (ST2003) to guide

(2). Install left forward blade to forward

rotor blade to its proper position on

storage rack. Observe that one blade is

rear support assembly.

directly above the left side of the front

blade support assembly. Secure that

(e). Secure blade in support assembly

blade in support with shock cord

with shock cord fastener.

fastener and hinged clamp fastener

(f). Reinstall blade attaching pin its

support.

original position in lead-lag link of

main rotor hub.

NOTE: It is not necessary to remove blade at

taching pins from the main rotor assembly

D. Forward Main Rotor Blades Folding

or damper arm in order to secure this blade.

(Ref. Figure 201)

(3). Install right forward blade to forward

storage rack.

Special Tools

(Ref. Section 91−00−00)

Blade movement must be re

CAUTION

Item

Nomenclature

strained in the following steps

to prevent damage since, with damper dis

ST2003

Main rotor blade storage rack

engaged, the blade is free to pivot on blade

attaching pin.

(1). Install forward storage rack (ST2003)

to helicopter.

(a). Remove bolt or (alternatively)

attaching pin from damper arm of

(a). Position blade storage rack so that

right forward blade and move damp

top holddown position on rack is

er away from rotor blade; replace bolt

approximately 15 degrees left of

(or attaching pin) in damper arm.

helicopter centerline.

(b). Unlock and remove blade attaching

(b). Attach U-bolt clamp subassemblies

pin that secures trailing edge of blade

to forward ends of each landing gear

to lead-lag link, and position cam

skid. Secure with hardware provided.

handle vertically above pin.

Ensure that each U-bolt is attached

ahead of curved portion of skid (but

(c). Instruct mechanic's assistant using

aft of skid tip light) to assure ground

blade support pole to guide rotor

clearance.

blade to its proper position on right

side of double blade front support.

NOTE: Top adjustment holes in support tubes

are for extended landing gear; bottom holes

(d). Secure blade in support assembly

are for standard landing gear.

with shock cord fastener.

(c). Attach lower ends of support tubes to

U-bolt clamp brackets. Attach short

(e). Reinstall blade attaching pin into its

tube to left skid. Secure with hard

original position in lead-lag link of

ware provided.

main rotor hub.

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CSP-HMI-2

MAINTENANCE MANUAL

E. Main Rotor Blades Unfolding Preparation

(1). Begin with the trailing blade, the one

supported by the center support step of

the rear blade support assembly.

Special Tools

(Ref. Section 91−00−00)

Blade movement must be re

CAUTION

Item

Nomenclature

strained in the following steps

to prevent damage since, with damper dis

ST2003

Main rotor blade storage rack

engaged, the blade is free to pivot on blade

ST2004

Air inlet fairing cover

attaching pin.

ST2005

Engine exhaust cover

(a). Remove damper arm bolt or (alterna

tively) attaching pin from damper

Before unfolding the main rotor blades,

arm clevis. Extend and align damper

perform the following steps:

arm with bolt hole in trailing edge of

blade. Insert bolt or attaching pin,

(1). Lock cyclic control stick, by applying

but: If pin is used, do not lock pin at

friction, in the following positions:

this time; if bolt is used, tighten to

torque of 30 - 60 inch-pounds (3.39

(a). Set collective pitch to mid position.

- 6.78 Nm) and insert cotter pin.

(b). Set longitudinal cyclic to full aft

(b). Remove shock cord fastener and

position.

release blade from support.

NOTE: Only the damper arm attaching bolt (or

(c). Set lateral cyclic to two thirds of total

pin) was removed from this blade during

stick travel from full left toward full

folding, not a lead-lag link attaching pin.

right.

(2). For the remaining aft secured rotor

During blade unfolding, contin

blades, proceed as follows:

CAUTION

ually monitor stick positions to

make sure no change occurs. Serious blade

Blade movement must be re

CAUTION

damage may result from improper stick

strained in the following steps

placement.

to prevent damage since, with damper dis

engaged, the blade is free to pivot on blade

(2). Cover (ST2004 and ST2005) engine air

attaching pin.

inlet and exhaust openings to prevent

(a). Remove shock cord fastener and

entry of foreign objects during blade

release blade from support.

folding.

(b). Instruct mechanic's assistant using

During blade unfolding, use

blade support pole (ST2003) to lift

CAUTION

blade support pole (ST2003).

and rotate blade forward to align

Prevent scratching of blade by attaching

trailing edge of blade and attachment

pins or bolts. Avoid brushing of blades

hole in lead-lag link of main rotor

against one another or against any other

hub (remove attaching pin from

surface. Lift blade near tip to remove load

lead-lag link to allow hole align

on attaching pin.

ment). Re-insert attaching pin (but

do not lock at this time).

F. Aft Main Rotor Blades Unfolding

(c). Remove damper arm bolt or (alterna

(Ref. Figure 201)

tively) attaching pin from damper

arm clevis. Extend and align damper

arm with bolt hole in trailing edge of

Special Tools

blade. Insert bolt or attaching pin

(Ref. Section 91−00−00)

but: If pin is used, do not lock pin at

Item

Nomenclature

this time; if bolt is used, tighten to

ST2003

Main rotor blade storage rack

torque of 30 - 60 inch-pounds (3.39

- 6.78 Nm) and insert cotter pin.

Page 205

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Revision 23

CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

G. Forward Main Rotor Blades Unfolding

H. Main Rotor Blades Storage Rack Removal

and Storage

(Ref. Figure 201)

Special Tools

(Ref. Section 91−00−00)

(1). Remove covers from engine exhaust

Item

Nomenclature

and air inlet fairing.

ST2003

Main rotor blade storage rack

(2). Unbuckle nylon webbing harness of

rear blade support assembly to disen

(1). Begin with the blade stowed on the left

gage aft blade storage rack from

side of the double blade front support

tailboom. Further disassembly is not

assembly. No attaching pins were

required.

removed from this blade for storage.

Release hinged clamp fastener support

(3). Loosen or remove wing nuts to disen

and shock cord fastener. Alignment is

gage U-bolt clamp subassemblies from

not necessary.

front end of landing gear skid assembly.

Remove forward blade storage rack

(2). For remaining forward rotor blade,

from helicopter.

proceed as follows:

Blade movement must be re

(4). Store blade storage racks.

CAUTION

strained in the following steps

to prevent damage since, with damper dis

(5). Reconnect any wires or antennas

engaged, the blade is free to pivot on blade

disconnected for blade folding.

attaching pin.

(a). Remove shock cord fastener and

4. Main Rotor Flight Controls Adjustment

release blade from support.

and Testing

(b). Instruct mechanic's assistant using

(Ref. Figure 201) Perform the following steps

blade support pole (ST2003) to lift

after main rotor blades have been unfolded

and rotate blade aft to align trailing

and repined.

edge of blade and attachment hole in

lead-lag link of main rotor hub

(1). Lock all attaching pins and check that

(remove attaching pin from lead-lag

locking force required to close pin

link to allow hole alignment). Re-in

handle is 25 - 35 pounds force (111.2

sert attaching pin (but do not lock at

- 155.7 N) (Ref. Sec. 62-10-00 Main

this time).

Rotor Blade and Damper Attach Pin

Installation and Adjustment, Sec.

(c). Remove damper arm bolt or (alterna

62-10-00).

tively) attaching pin from damper

arm clevis. Extend and align damper

arm with bolt hole in trailing edge of

NOTE: Blade attaching pin handle is posi

blade. Insert bolt or attaching pin,

tioned behind retainer clip as shown.

but: If pin is used, do not lock pin at

this time; if bolt is used, tighten to

(2). Loosen friction on cyclic and collective

torque of 30 - 60 inch pounds (3.39

sticks and check movement of controls

- 6.78 Nm) and insert cotter pin.

through complete range of travel.

Page 206

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CSP-HMI-2

MAINTENANCE MANUAL

TABLE OF CONTENTS

Para/Figure/Table

Title

Page

11-00-00 Placards and Markings

Maintenance Practices

201

1. General

201

2. Decal Application

201

Figure 201. Placards - Exterior (Sheet 1 of 5)

202

Figure 202. Placards - Interior (Sheet 1 of 5)

207

Figure 203. Placards - Instrument Panels (Sheet 1 of 2)

212

Figure 204. Placards - Optional Equipment (Sheet 1 of 4)

214

11-40-00 Placards and Markings (600N)

Maintenance Practices

201

1. General

201

2. Decal Application

201

Figure 201. Exterior Placards and Markings (Sheet 1 of 4)

202

Figure 202. Interior Placards and Markings (Sheet 1 of 4)

206

Figure 203. Instrument Panel Placards and Markings (Sheet 1 of 2)

210

Page i

11 Contents

Revision 23

MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

PLACARDS AND MARKINGS

MAINTENANCE PRACTICES

1. General

2. Decal Application

(1). Where a decal overlaps or covers drain

(Ref. Figure 201 thru Figure 204 for placards

holes, access doors, etc., the decal shall

and markings most common to 369D/E/FF -

be cut out to provide proper draining or

500N Model Helicopters). Nomenclature

ease of opening or removing of doors,

corresponds to that used in the IPC. (Ref.

plates, etc.

Illustrated Parts Catalog for each decal part

number and the quantity required.)

(2). Where a decal is applied over a skin lap

(one skin overlapping another), the

The following illustrations cover different

decal must be cut so that it lies flat and

areas of decal placement on the helicopter:

makes a positive bond.

(1). Exterior - Figure 201.

(3). Seal edges of all exterior decals, and

only those interior decals in the engine

(2). Interior - Figure 202.

compartment and cargo compartment

aft of the transmission, with epoxy

(3). Instrument panels - Figure 203.

adhesive. Edge sealing to be a mini

mum of 1/32 inch (0.8mm) and a

(4). Optional equipment (various exterior

maximum of 1/8 inch (3mm) around

and interior locations) - Figure 204.

perimeter of decal.

Page 201

11-00-00

Revision 23

CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

500E

(NOTE 1)

ROTATING

SWASHPLATE

INNER

SCISSORS

DETAIL A-A

CRANK

CARGO

HANDLE

OUTER

FLOOR

LOCK

HANDLE

OPEN

CAUTION

JACK PAD

500E

EXT. LH DOOR SHOWN

OIL CAP

RH OPPOSITE

(REF)

N9011F

SHIP

FAIRING

AIR

DUCT

(REF)

HEATER

(NOTE 2)

DUCT

(REF)

FUEL CAP

(REF)

NOTES:

EFFECTIVE ON S/N:

369D;

001 AND SUBS.

369E;

001 - 300

369FF;

001 - 054

EFFECTIVE ON S/N:

369E;

301 AND SUBS

369FF;

055 AND SUBS

G11-0000-1B

500N

001 AND SUBS

Figure 201. Placards − Exterior (Sheet 1 of 5)

Page 202

Revision 23

11-00-00

CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

CAUTION

PUSH

DISCONNECT ELECTRICAL WIRING

BEFORE REMOVING BOOM

PUSH

ELECTRICAL

DISCONNECT

500D / 500E / 530F / 520N

LOCK

CAUTION

SAFELOCK

INNER HANDLE

IN POSITION

INSTALL THIS SIDE

SHOWN BEFORE

TOWARD BLADES

LOCKED

FLIGHT

MAIN ROTOR

LOCKED

OPEN

OPEN AND LOCK,

LOCK BEFORE FLIGHT,

OUTER, LH & RH

LH & RH

FULL

CAP. 0.4 U.S. PTS.

JIG POINT

SEE FLT MANUAL

CHECK LEVEL

STA 92.64

AND LOG BOOK

FOR OIL USAGE

ADD

TAIL ROTOR

CHECK LEVEL

10. OIL LEVEL PLUG

11. JIG POINT

TRANSMISSION OIL

THRU

ATTACH JACK PAD

12. JACK PAD

THRU

DANGER

LEFT-HAND

RIGHT-HAND

LETTERS AND NUMERALS

13. DANGER

14. RADIO CALL

G11−0000−3A

Figure 201. Placards − Exterior (Sheet 3 of 5)

Page 204

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

STATIC LINE

DRAIN VALVE

PUSH BOTTOM UP

THRU

16. STATIC LINE

15. RADIO CALL

OIL

17. OIL

18. NON SELF-SEALING FUEL CELLS

18. SELF-SEALING FUEL CELLS

FUEL 62.1 GALLONS

FUEL 60.0 GALLONS

STATIC PORT

KEEP HOLES AND

MCDONNELL DOUGLAS

SURFACE CLEAN

HELICOPTER CO. MESA, AZ

MODEL NO. 369

SERIAL NO.

TYPE CERT NO. H3WE

PROD CERT NO. 410

19. STATIC PORT

20. GROUND SYMBOL

21. MODEL IDENTIFICATION

WARNING

CAP. 12.0 U.S. PTS.

SEE FLT MANUAL

DO NOT SUPPORT

TORQUE SCREWS

AND LOG BOOK

GEAR BOX WEIGHT FROM

TO 20−25 IN−LB

FOR OIL USAGE

DRIVE SHAFT COUPLING

22. HUB FAIRING

23. MAIN ROTOR

24. TAIL ROTOR

SCREW TORQUE

TRANSMISSION OIL

GEARBOX WARNING

ENGINE VENT

27. ENGINE VENT

25. FUEL DRAIN

26. OIL DRAIN

G11-0000-4

Figure 201. Placards − Exterior (Sheet 4 of 5)

Page 205

11-00-00

Revision 23

CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

CONTROLS ACCESS DOOR

VOLTAGE REGULATOR

CAUTION

WARNING

ONLY QUALIFIED PERSONNEL

LAT TRIM

LONG TRIM

REPLACE DOOR BEFORE FLIGHT

WILL ADJUST THIS ASSEMBLY

CONTROLS ACCESS DOOR

VOLTAGE REGULATOR

LATERAL TRIM

LONGITUDINAL TRIM

WARNING - REPLACE DOOR

(369D;

S/N 002 AND

BEFORE FLIGHT

SUBS.)

(369E;

S/N 001 THRU

383 )

(369FF;

S/N 001 THRU

075)

FRICTION

IF MOISTURE VISIBLE

AND O.A.T. BELOW 5o C

INCREASE

24 VOLT DC

USE ANTI-ICE

OPEN

OUTSIDE AIR TEMPERATURE

FRICTION INCREASE

24 VOLTS DC

THROTTLE OPEN

OFF

BYP

DOOR

CAUTION

CABIN

ACTIVATE BOOST

HEAT

FUEL ACCESS DOOR

OPEN

PUMP BEFORE AND

WARNING

DURING DRAINING

LEVEL HERE

REPLACE DOOR BEFORE FLIGHT

FUEL SAMPLE

AND JACKING AIRCRAFT

LEVEL HERE

10. FUEL ACCESS DOOR

11. BYPASS DOOR

12. FUEL SAMPLING

ENGINE ANTI-ICE

(369D;

S/N 002 AND

SUBS.)

(369E;

S/N 001 THRU

383 )

DAMPER CHARGED RECOMMENDED

(369FF;

S/N 001 THRU

SERVICE BETWEEN 125

F TO 10

075)

SEE HANDBOOK OF MAINTENANCE

INSTRUCTIONS.

WARNING

CAUTION

UNIT CHARGED WITH HIGH PRES -

USE ONLY WITH

USE ONLY IN TWO

DAMPER CHARGED RECOMMENDED

SURE GAS. REFER TO HANDBOOK

STANDARD LANDING

AFT POSITIONS OR

SERVICE BETWEEN 70Fo TO -40 Fo

MAINTENANCE INSTRUCTIONS OR

GEAR OR IN TWO

EXTENDED LANDING

SEE HANDBOOK OF MAINTENANCE

RETURN TO MANUFACTURER ON

FORWARD POSITIONS

GEAR. DO NOT USE

INSTRUCTIONS.

OR EXTENDED

WITH STANDARD

EVIDENCE OF LEAKAGE OR

LANDING GEAR

LANDING GEAR.

MALFUNCTION.

DAMPER CHARGED RECOMMENDED

WHITE

BLACK

SERVICE BETWEEN 90Fo TO -25 Fo

DAMPER

SEE HANDBOOK OF MAINTENANCE

14. DAMPER WARNING

ONLY

INSTRUCTIONS.

13. DAMPER SERVICE

15. DAMPER CAUTION

G11-0002-4A

Figure 202. Placards − Interior (Sheet 4 of 5)

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

DANGER

WHEN EXITING, WALK AWAY FROM THE

CAUTION - TO ASSURE PROPER RESTRAINT. ADJUST SHOULDER

HARNESS SLIDE SO HARNESS IS SNUG AGAINST TORSO

HELICOPTER, KEEP HANDS AND HEAD LOW,

WHILE SEATED UPRIGHT. FULL BACK IN THE SEAT

DO NOT WALK TO THE REAR.

16. CAUTION - SHOULDER HARNESS

17. EXIT

OPEN

CAUTION

SAFELOCK

HANDLE IN

LONG RANGE TANK CONN

POSITION

SHOWN BEFORE

FLIGHT

19. LONG RANGE TANK CONNECTION

LOCK

20. LOOK BEFORE EXIT

18. DOOR INSTRUCTIONS

PULL & TURN

TANK

COOLER

90o TO DRAIN

OIL TANK VENT

OIL TANK OUTLET

ENGINE LUBE OIL

ENGINE OIL DRAINS

23. OIL TANK OUTLET

24. OIL TANK VENT

22. OIL DRAINS

21. ENGINE OIL DRAINS

(369D:

S/N 002 −

605)

M/R

XMSN

FULL

WARNING

OIL

OIL TANK INLET

FAILURE TO PROPERLY INSTALL,ALIGN

COOLER

AND TORQUE,FUEL,OIL AND AIR TUBES

AND FITTINGS COULD RESULT IN AN

DRAIN

ENGINE FAILURE.REFER TO THE APPLI

25. DECAL. OIL TANK INLET

ADD 1 PINT

CABLE MANUAL FOR PROPER INSTAL4

ATION AND TORQUE PROCEDURES

26. MAIN ROTOR TRANSMISSION

28. WARNING

27.

,OIL LEVEL

OIL COOLER DRAIN

G11-0002-5A

Figure 202. Placards − Interior (Sheet 5 of 5)

Page 211

11-00-00

Revision 23

CSP-HMI-2

MD Helicopters, Inc.

MAINTENANCE MANUAL

BATTERY

140 F

150 F

ENGINE

XMSN

GEN

ENGINE

XMSN

FUEL

PRESS

OUT

OIL

OUT

CHIPS

LOW

FILTER

PRESS

CHIPS

TEST

TEMP

140

120

100

ALTITUDE

120

110

100

CAUTION

CYCLECYFSWWP

TO TRIM

THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING

TO NEUTRAL

BRINGHTEVKKD

LIMITATIONS SPECIFIED IN THE F.A.A. APPROVED ROTORCRAFT FLIGHT MANUAL.

ADJUPLVVCMTMRUE

TQI

100

FLIGHT COMPLIANCE

120

TORQUE

PSI

100

PERCENT

150

RPM

PRESS

RADIO CALL

PULL

AMPS

UTILITY

START

PWR

PUMP

PULL

FOR

AIR

OFF

GYRO

RADIO CALL

CFM

POS

ANTI-COLL

PNL

OFF

BRT

TRIM

PRESS TO

ENG OUT

MID FRONT SEAT IS

RESET

NOT TO BE OCCUPIED

REIGN

NAV/COM

ARMED

IN FALLING AND/ OR

AUTO REIGN

ADF

BLOWING SNOW

TEST

XPDR

SNOW WARNING

EMERG FLOATS

SEARCHLIGHT

AUTO

PRESS TO TEST

PWR

CONT

EXT

BATTERY

PRESS TO

HOIST

TEST

OFF

PRESS TO TEST

CARGO

HOOK

PWR

CTR

CAUTION

CIGAR LIGHTER

RADIO

PWR

COMM 1

-CYCLIC

XMIT

FORCES TO

SYS

COMM 2

BE TRIMMED TO

NEUTRAL DURING

STARTUP AND SHUT-

DOWN

SLIM-LINE INSTRUMENT PANEL (369D)

CYCLIC STICK POSITION WARNING

G11-0001-1A

Figure 203. Placards − Instrument Panels (Sheet 1 of 2)

Page 212

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MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

RADIO CALL

THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING

LIMITATIONS SPECIFIED IN THE F.A.A. APPROVED ROTORCRAFT FLIGHT MANUAL.

FLIGHT COMPLIANCE

RADIO CALL

100

VNE

TORQUE

120

140

PSI

130 KTS. I.A.S.

120

WITH LESS THAN

5ALTITUDE

100

35 LBS. FUEL

TQI

LOW FUEL WARNING

120

100

110

100

PERCENT

RPM

CAUTION CYCLIC FORCES TO BE

100

TRIMMED TO NEUTRAL DURING

150

STARTUP AND SHUTDOWN

PRESS

AMPS

CYCLIC STICK POSITION WARNING

PULL

FOR

AIR

START RECOMMENDATIONS

OAT

-32 TO -18

-18 TO 7

7 TO 46

1 7o/o

T-INSTRUMENT PANEL (369MD)

START RECOMMENDATIONS

RADIO CALL

EXT

ANTI-COLL

PITOT

FUEL

START PUMP

HTR

PULLFOR

VALVE

AIR

EXT PWR

OFF

GEN

SCAV

POS

UTIL

OVSPD

FAULT

AIR

LTS

ANTI-ICE

PWR

TEST

THIS HELICOPTER MUST

LIMITATIONS SPECIFIED

BE OPERATED IN COMP-

IN THE F.A.A. APPROVED

OFF

LIANCE WITH OPERATING

ROTORCRAFT FLT MANUAL.

FLIGHT COMPLIANCE

CAUTION CYCLIC FORCES TO BE

TRIMMED TO NEUTRAL DURING

STARTUP AND SHUTDOWN

CYCLIC STICK POSITION WARNING

V NE 50 KTS MAX WHEN

TORQUE EXCEEDS 48.9 CONT.

WARNING HIGH TORQUE. 369 FF

T-INSTRUMENT PANEL (369E/FF - 500N)

G11-0001-2A

Figure 203. Placards − Instrument Panels (Sheet 2 of 2)

Page 213

11-00-00

Revision 23

MD Helicopters, Inc.

CSP-HMI-2

MAINTENANCE MANUAL

CARGO HOOK

FILTER BY−PASS CONTROL

EXTERNAL LOAD LIMIT

EMERGENCY

HOOK

PULL HANDLE FWD

2000 POUNDS

RELEASE

1. PARTICLE

SEPARATOR

CARGO HOOK

ANTI−ICE

AIRFRAME

FUEL FILTER

INSTL

AUTO−RE−IGNITION

FOR GROUND

ARM

TEMP. OF 5° C OR

CAUTION: SPRING LOADED, DO NOT PUSH

LESS MAX. ALT.

LESS. MAX. ALT.

12,000 FT.

OFF

5. FOUR−BLADED TAIL ROTOR

PRESS TO RESET

FOR GROUND

TEMP. GREATER

7. AUTOMATIC

THAN 5° C MAX.

ENGINE REIGNITION

ALT. 14,000 FT.

6. ANTI−ICE FUEL FILTER

WARNING

FLOAT INFLATION ABOVE 81 KNOTS IAS

PITOT MAY BE HOT

AT LESS THAN 6000 FEET ALTITUDE,

DO NOT TOUCH

EMERGENCY FLOATS

77 KNOTS IAS AT 6000 FEET AND ABOVE,

FLOAT LDG LT

PRESS TO TEST

IS PROHIBITED

9. LANDING

10. AUXILIARY

11. WARNING

LIGHT FLOAT

ELECTRICAL PANEL

8. HEATED

PITOT TUBE

EMERGENCY FLOATS

NIGHT FLIGHT OVER

MINIMUM FLOAT

WATER BEYOND

OPERATIONAL

Facet^{FILTER PRODUCTS DIVISION}

GREENSBORO, NC 27409

AUTOROTATION CAPABILITY

PRESSURE IS

TO GROUND PROHIBITED

2.0 PSIG

A. INSPECT RED BUTTON ON BOTTOM

OF BOWL FOR INDICATION OF FILTER

12. NIGHT FLIGHT

13. MIN. OPERATIONAL

BYPASS.

RESTRICTION

PRESSURE

B. IF RED BUTTON IS NOT SHOWING

PROCEED WITH PREFLIGHT.

(ALSO EMERGENCY

C. RED BUTTON SHOWING, RESET

FLOATS)

BUTTON ONCE AND RUN ENGINE.

D. IF RED BUTTON REAPPEARS,

DISCONTINUE OPERATIONS AND IN−

UTILITY FLOATS

VESTIGATE REASON FOR FILTER

BYPASS INDICATION.

WARNING

14.

ENGINE OIL SCAVENGE

USE CORRECT LOAD

FILTER (MODEL D

RINGS, RINGS WITH

AND E WITH A C20/R−2

INTERNAL DIM.

ENGINE CONVERSION

GREATER THAN

1.5

INCHES

CAN SLIP OFF

15. CARGO HOOK

P/N 17149−1 THRU −5

G11-0003-4B

Figure 204. Placards − Optional Equipment (Sheet 4 of 4)

Page 217

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Revision 23

HANDBOOK OF MAINTENANCE INSTRUCTIONS FOR MDHI 369D/E/FF-500/600N HELICOPTERS (ISSUED: 1990) - page 4