Robinson Helicopter Company RTR 660 (Number R00015LA). Maintenance Manual (2012)

6-63 Water Line (WL) Station Locations

Teeter Hinge Bolt (main rotor)

WL 138.00

Upper Rib (top)

WL 125.17

Middle Rib (top)

WL 104.88

Lower Rib (top)

WL 84.59

5* Tail Rotor Gearbox (centerline)

WL 75.50

Main Rotor Gearbox (tail rotor and main rotor drive shaft intersection point)

WL 66.00

Baggage Compartment (ceiling, lowest point)

WL 45.60

Baggage Compartment (floor)

WL 22.59

Belly

WL 20.78

Landing Gear

WL 0.79

Origin

WL 0.00

FIGURE 6-6 WATER LINE STATION LOCATIONS

Page 6.8

Chapter 6 Dimensions and Descriptions

25 OCT 2010

6-70 Access and Inspection Panels

ITEM

PART NO. DESCRIPTION

ITEM

PART NO. DESCRIPTION

A412-3

Cover - Pedal Bearing Block

F082-2

Fairing Assembly - Landing Gear, Forward (RH)

2451

Cover - Floor Panel

F082-3

Fairing Assembly - Landing Gear, Forward (LH)

A412-1

Cover - Pedal Bearing Block

G308-2

Cover - Aft Cowling

F490-1

Panel Assembly - Circuit Breaker

F082-4

Fairing Assembly - Landing Gear, Aft (RH)

F444-1

Cover - Cyclic Box

F082-5

Fairing Assembly - Landing Gear, Aft (LH)

B050

Console Assembly - Upper

F261-1

Mast Fairing Assembly

F445-1

Cover Assembly - Forward Tunnel

F706-1

Tailcone Cowling Assembly

F680-3

Cover Assembly - Collective (Pilot)

G004-2

Aft Fuselage Assembly - Door, Fuel Fill

F680-1

Cover Assembly - Collective (Copilot)

G004-10

Aft Fuselage Assembly - Door, Access

F461-1

Cover Assembly - Collective Cross Tube

G927-1

Aft Fuselage Assembly - Door, Fuel Sample

F463-1

Cover Assembly - Mid Tunnel

G900-1

Door Assembly - Baggage

F380-8

Angle

G910-1

Scoop Assembly - Air Inlet

F474-1

Cover Assembly - Middle Seat

G040-5

(2) Cowling Assembly - Aft (Door)

F931-1

Seat Assembly - Middle

G248-1

Cover - GCU

F003-4

Seat Back Assembly (RH)

G040-1

Cowling Assembly - Aft (Engine)

F932-1

Back Rest Assembly - Middle Seat

A231-1

(5) Plug Assembly - Tailcone Inspection

F474-2

Cover - Middle Seat

A558-2

Cover - Tailcone Inspection, Aft

F003-3

Seat Back Assembly (LH)

F794-1

Panel - Belly Cover (FWD)

F475-1

Cover Assembly - Cross Tube

F475-6

(2) Cover - Cross Tube, Outboard

F748-1

Cover Assembly - Battery

F794-2

Panel - Belly Cover (AFT)

FIGURE 6-9 EXTERIOR ACCESS & INSPECTION PANELS

Chapter 6 Dimensions and Descriptions

Page 6.11

6-80 Antenna Locations

ITEM ANTENNA

MHz

PART NO.

ITEM

ANTENNA

MHz

PART NO.

ADF

—

KA44B

Upper Aft COM . . .

—

CI 121, CI 248-5

Marker Beacon

—

CI 102

Upper Aft FM

—

CI 177

RH Belly UHF

400-960

CI 285

UpperAftCOM/GPS

—

CI 2580-200

DME

—

CI 105-16, KA60

Lower Fwd FM

—

CI 177

LH/RH Belly (Ref)

—

See Item 7 and 8

Lower Fwd FM

403-512

CI 273, CI 272-1, CI 271

Transponder

—

CI 105-16, KA60

800-870

CI 306

RH Belly FM

138-174

CI 292-3

Lower Aft FM

—

CI 177

450-470

CI 177-20

Lower Aft VHF

118-136

CI 122

RH Belly AM/FM

—

CI 222

Lower Aft FM

403-512

CI 273, CI 272-1, CI 271

RH Belly FM

403-512

CI 273, CI 272-1, CI 271

800-870

CI 306

LH Belly FM

138-174

CI 292-3

NAV

108-118 &

D20543 (VOR &

329-335

LOCALIZER)

450-470

CI 177-20

220-225

D721-1

108-118 &

D20543 (VOR &

329-335

LOCALIZER W/DIPLEXER)

LH Belly FM

403-512

CI 273, CI 272-1, CI 271

LH Belly COM

118-136

CI 122

ELT

—

AV-300

Cowling GPS

—

GA 29

Upper Fwd COM

—

CI 121, CI 248-5

Upper Fwd FM

—

CI 177

Upper Fwd FM

403-512

CI 273, CI 272-1, CI 271

800-870

CI 306

Upper Fwd COM/GPS

—

CI 2580-200

FIGURE 6-10 ANTENNA LOCATIONS

Page 6.12

Chapter 6 Dimensions and Descriptions

CHAPTER 7

JACKING AND HOISTING

7-10 Jacking

CAUTION

When jacking helicopter, use mechanical or locking hydraulic

jacks, when available. Unlocked hydraulic jacks are subject

to pressure-loss which can affect critical measurements during

leveling or cause a raised helicopter to become unstable.

CAUTION

Never jack helicopter in windy conditions.

CAUTION

Perform jacking on a clean, flat, hard surface free of water,

oil, solvent, grease, or residue that could cause equipment or

personnel to slip during jacking procedure.

CAUTION

Do not actuate jacks from underneath helicopter. Remain clear

of landing gear skid tubes when helicopter is raised.

A. Jacking

1. Refer to Figure 7-1. Place one (appropriate capacity) jack under each (landing gear)

aft strut assembly jack lug/tab and under the ground handling ball. Install jacking point

adapters as required.

CAUTION

Ground handling ball must slide unrestricted across a flat surface

during jacking. When weighing, verify ball is not under side

load which could produce an erroneous weight indication.

2. Position jack levers for convenient access and engage jacks at lugs/tabs and ball.

Sandbag jacks for increased stability, as required.

3. Actuate jacks slowly and simultaneously (one person per jack recommended), maintaining

helicopter stability. Raise helicopter to required height.

CAUTION

Minimize personnel movement around raised helicopter.

Chapter 7 Jacking and Hoisting

Page 7.1

7-20 Hoisting

CAUTION

Avoid hoisting helicopter in windy conditions.

CAUTION

Verify ground is free of water, oil, solvent, grease, or residue

that could cause equipment or personnel to slip during hoisting

procedure.

CAUTION

Remain clear of area beneath helicopter when helicopter is raised.

Minimize personnel movement around raised helicopter.

A. Hoisting with Lifting Fixture

1. Refer to Figure 7-2. Verify hoisting equipment has minimum load capacity of 3000 lbs.

2. Position main rotor hub directly under hoist to minimize helicopter swing once aloft.

3. Remove two spring pins and four nylon bushings from MT527-1 lifting fixture and install

bushings in main rotor hub lightening holes. Position lifting fixture on hub then insert

spring pins through fixture and bushings until pins lock. Verify security.

4. Connect hoist to lifting fixture. Verify security.

5. Stabilize helicopter as required by guiding tail skid, but do not exert force (tail skid is

secondary structure). Raise helicopter to required height.

Hoisting with Nylon Rope

1. Refer to Figure 7-2. Verify hoisting equipment has minimum load capacity of 3000 lbs.

Verify minimum work load limit for 1-inch diameter twisted or double braided (preferred)

soft nylon rope is 3000 lbs.

2. Position main rotor hub directly under hoist to minimize helicopter swing once aloft.

3. Insert rope through main rotor hub lightening holes, form a double loop, and knot ends.

Connect hoist to nylon rope. Verify security.

4. Stabilize helicopter as required by guiding tail skid, but do not exert force (tail skid is

secondary structure). Raise helicopter to required height.

25 OCT 2010

Chapter 7 Jacking and Hoisting

Page 7.5

CHAPTER 8

WEIGHT AND BALANCE

8-10 Leveling

NOTE

Perform leveling and weighing in a zero-wind environment.

NOTE

Verify spirit level is calibrated by placing level on a designated

surface and noting bubble position. Rotate spirit level 180°;

verify bubble is in the same position.

8-11 Leveling for Weight and Balance

NOTE

Main rotor blade position does not affect weight and balance

calculations.

1. Jack helicopter per Section 7-10.

2. Refer to Figure 8-1. Place a spirit level laterally on F463-1 aft tunnel cover. Verify

cover is flat; if cover is not flat, remove cover and place spirit level across keel panel

flanges.

3. Adjust jacks at (landing gear) aft strut assembly jack lugs/tabs until helicopter is level

laterally.

4. Position spirit level longitudinally on aft tunnel cover, or atop left or right keel panel

if cover is removed. Adjust jack under ground handling ball until helicopter is level

longitudinally.

Chapter 8 Weight and Balance

Page 8.1

8-12 Leveling for Rigging

1. Refer to Figure 8-2. Place cyclic stick in vertical position and apply cyclic friction.

Position main rotor blades approximately fore and aft and apply rotor brake.

(Teeter

hinge bolt is aligned with lateral axis of helicopter.)

2. Jack helicopter per Section 7-10.

3. Place a spirit level parallel with teeter hinge bolt at location marked "LEVEL HERE" on

top of main rotor hub.

4. Adjust jack at (landing gear) aft strut assembly jack lugs/tabs until helicopter is level

laterally.

5. Release rotor brake and rotate main rotor until teeter hinge bolt is aligned with longitudinal

axis of the helicopter. Apply rotor brake. Verify cyclic stick is in vertical position with

friction applied.

6. Adjust jack under ground handling ball until helicopter is level longitudinally. Remove

spirit level.

Chapter 8 Weight and Balance

Page 8.3

8-20 Weighing

Reweigh helicopter when helicopter empty weight and empty weight center of gravity have

been modified and if the accuracy of additional calculations is suspect.

Maintain a continuous record of the helicopter’s weight and balance using the Weight and

Balance Record in R66 Pilot’s Operating Handbook (POH) Section 6.

NOTE

Verify scales are calibrated. Operate scales according to scale

manufacturer’s instructions.

NOTE

Never weigh the helicopter in the wind. Weigh helicopter on a

flat, hard surface in a zero-wind environment for accurate scale

readings.

8-21 Preparing Helicopter for Weighing

1. Defuel helicopter per Section 12-42.

2. Service engine oil, hydraulic fluid, and main & tail rotor gearboxes per Chapter 12.

3. Clean aircraft per Section 20-10. Ensure helicopter is completely dry prior to weighing.

4. Remove foreign objects from baggage compartments and stowage areas.

5. Verify cowlings, removable panels, cabin doors, removable controls, and R66 Pilot’s

Operating Handbook (POH) are installed.

6. Verify Equipment List/Weight and Balance Data sheet (RF 134) and modifications

recorded in the Weight and Balance Record correspond with installed equipment and

recorded equipment locations.

25 OCT 2010

Chapter 8 Weight and Balance

Page 8.5

8-22 Weighing Procedure and Calculations

NOTE

• Arm is the distance in inches from datum.

• Datum is located 100 inches forward of main rotor centerline.

• CG (arm) is determined by dividing total moment by total weight.

Refer to Section 8-20. Prepare helicopter for weighing per Section 8-21.

Refer to Figure 8-3. Place a jack and one 1000-lb capacity (minimum) scale under each

(landing gear) aft strut assembly jack lug/tab and under the ground handling ball.

Zero scales, or record tare weight (items between scale and weighing point such as

adapter, jack, stand, sandbags, etc.) at each scale.

Level helicopter for weight and balance per Sections 8-10 and 8-11. Remove spirit

level. If removed, carefully replace F463-1 aft tunnel cover, unsecured, on top of keel

panels.

Calculate net weights:

Weighing Point Scale Indication

Tare Weight

Net Weight

Forward:

Left:

Right:

Chapter 8 Weight and Balance

Page 8.7

8-22 Weighing Procedure and Calculations (continued)

Calculate weight and CG per the following table. Adjust ballast per steps 6b thru 6e as

required until calculated CG is between 101.50 and 102.50 per step 6a.

Longitudinal CG

Item

Weight (lb)

(arm, inches)

Moment (in.-lb)

Forward Net:

32.67

Left Net:

127.35

Right Net:

127.35

Pilot (right forward seat; add):

160.00

49.00

7840.00

Unusable fuel (add):

6.70

110.40

739.68

Calculated weight and CG:

If Calculated CG is between 101.50 and 102.50, (additional) ballast is not required.

Proceed to step 7.

If Calculated CG is less than 101.50 and nose ballast is not installed, install empennage

ballast per Section 8-32. Reweigh helicopter and calculate new weight and CG per

the previous steps.

If Calculated CG is less than 101.50 and nose ballast is installed, determine (minimum)

nose ballast to remove:

(102.50 - Calculated CG) X Calculated weight

97.35

Round down to nearest 0.25 lb. Remove nose ballast per Section 8-31. Reweigh

helicopter and calculate new weight and CG per the previous steps.

If Calculated CG is greater than 102.50 and empennage ballast is installed, remove

empennage ballast per Section 8-32. Reweigh helicopter and calculate new weight

and CG per the previous steps.

If Calculated CG is greater than 102.50 and empennage ballast is not installed,

determine (minimum) additional nose ballast required:

(Calculated CG - 102.50) X Calculated weight

97.35

Round up to nearest 0.25 lb. Install nose ballast per Section 8-31. Reweigh helicopter

and calculate new weight and CG per the previous steps.

Lower helicopter per Section 7-10. Secure aft tunnel cover.

Page 8.8

Chapter 8 Weight and Balance

8-22 Weighing Procedure and Calculations (continued)

Calculate basic empty weight and longitudinal CG:

Longitudinal CG

Item

Weight (lb)

(arm, inches)

Moment (in.-lb)

Forward Net:

32.67

Left Net:

127.35

Right Net:

127.35

Unusable fuel (add):

6.70

110.40

739.68

Basic empty weight and

longitudinal CG:

Calculate basic empty weight and lateral CG:

Lateral CG

Item

Weight (lb)

(arm, inches)

Moment (in.-lb)

Forward Net:

4.13

Left Net:

- 16.73

Right Net:

16.73

Unusable fuel (add):

6.70

- 20.70

- 138.69

Basic empty weight

and lateral CG:

25 OCT 2010

Chapter 8 Weight and Balance

Page 8.9

8-30 Fixed Ballast

8-31 Nose Ballast

Refer to R66 Illustrated Parts Catalog (IPC) Figure 8-1.

NOTE

Maximum allowable nose ballast is 15.00 lb.

CAUTION

Altering fixed ballast can appreciably affect helicopter center of

gravity (CG). If fixed ballast information is unknown, reweigh

helicopter per Section 8-22.

Refer to Figure 8-4. Remove screws securing B050-22 or -23 upper console assembly to

F033-1 lower console assembly and hinge upper console assembly aft. Protect instrument

face with foam support or equivalent.

Remove hardware securing A941-5 or -6 ballast plate(s), if installed, to F361-1 panel.

Remove or install ballast plates per calculations performed in Section 8-22. Select NAS6603

bolt length to meet torque requirements per Section 20-30. Install hardware, torque bolts

per Section 20-32, and torque stripe per Figure 5-1.

Hinge upper console assembly forward and install screws securing upper and lower

console assemblies. Verify security.

Reweigh and/or calculate basic empty weight and CG per Section 8-22.

Revise Weight and Balance Record in R66 Pilot's Operating Handbook (POH) Section 6

to reflect ballast removal or installation using the following data:

Weight

Longitudinal

Lateral Arm

Lateral

Arm

Moment

Nose ballast

0-15.00 lb

5.15 in.

Variable

0.00 in.

0.00 in.-lb

25 OCT 2010

Chapter 8 Weight and Balance

Page 8.11

8-32 Empennage Ballast

Refer to R66 Illustrated Parts Catalog (IPC) Figure 8-1.

NOTE

Use only approved materials listed in Section 20-70.

CAUTION

Altering fixed ballast can appreciably affect helicopter center of

gravity (CG). If fixed ballast information is unknown, reweigh

helicopter per Section 8-22.

WARNING

Maximum allowable empennage ballast is 3.00 lb. If empennage

ballast is required per Section 8-22, two D301-2 weights must

be installed as shown in Figure 8-5.

A. Removal

1. Refer to Figure 8-5. Remove empennage assembly, including D301-2 ballast weights,

per Section 53-50.

2. Solvent-clean bare metal around and between bolt holes on horizontal stabilizer upper

and lower surfaces.

3. Apply light coat zinc-chromate or epoxy primer to bare metal surfaces. While primer

is wet, install empennage assembly per Section 53-50. Topcoat hardware with

colored paint as desired.

4. Reweigh and/or calculate basic empty weight and CG per Section 8-22.

5. Revise Weight and Balance Record in R66 Pilot's Operating Handbook (POH) Section

6 to reflect ballast removal using the following data:

Weight

Longitudinal

Lateral

Arm

Moment

Arm

Moment

Empennage ballast

3.00 lb

325.44 in.

976.32 in.-lb

4.45 in.

13.35 in.-lb

Installation

1. Refer to Figure 8-5. Remove empennage assembly per Section 53-50.

2. Solvent-clean bare metal around and between bolt holes on horizontal stabilizer upper

and lower surfaces.

3. Temporarily install D301-2 weights per R66 IPC Figure 8-1. Torque bolts per Section

20-32.

4. Trace outline of weights onto horizontal stabilizer upper and lower surfaces using

felt-tip, non-permanent marker or tape. Remove weights.

Chapter 8 Weight and Balance

Page 8.13

8-32 Empennage Ballast (continued)

B. Installation (continued)

5. Remove paint within traced outlines on stabilizer by block sanding (to maintain

flatness). Finish sanding using 320-grit or finer wet-or-dry sandpaper, or using

approved stripper per Section 20-71. Similarly, on each D301-2 weight, remove

paint from one flat surface which will clamp against stabilizer.

6. Remove tracing media. Solvent-clean bare metal on horizontal stabilizer and weight

clamping surfaces.

7. Reweigh and/or calculate basic empty weight and CG per Section 8-22.

8. Revise Weight and Balance Record in R66 Pilot's Operating Handbook (POH) Section

6 to reflect ballast installation using the following data:

Weight

Longitudinal

Lateral

Arm

Moment

Arm

Moment

Empennage ballast

3.00 lb

325.44 in.

976.32 in.-lb

4.45 in.

13.35 in.-lb

Page 8.14

Chapter 8 Weight and Balance

CHAPTER 9

GROUND HANDLING

9-10 Ground Handling

9-11 Ground Handling Wheels

Refer to R66 Illustrated Parts Catalog (IPC) Figure 9-1.

NOTE

R66 ground handling wheels are installed inboard of landing

gear skid tubes. C063-5 (LH) and C063-6 (RH) ground handling

wheel assemblies are not interchangeable. When wheels are

installed and in locked position, both handles point aft.

CAUTION

Handle has a tendency to snap over when raising and lowering the

helicopter. Grip handle firmly with both hands during operation.

CAUTION

Remain clear of landing gear skid tubes when helicopter is

raised.

WARNING

Remove ground handling wheels for flight.

A. Installation

NOTE

Verify proper inflation of ground handling wheel tires. Maximum

tire inflation pressure is 70 psi.

1. Extend ground handling wheel retractable handle by depressing locking pins and

sliding handle out until pins engage outer holes. Verify security.

2. Refer to Figure 9-1. Hold ground handling wheel assembly inboard of skid with

handle forward, wheel aft, and spindle pointed outboard. Insert spindle completely

into skid-mounted support, then pull handle in rearward arc (raises helicopter) until

handle is in locked position, parallel with the skid.

3. Repeat steps to install second wheel assembly. Helicopter will rest on skid toes.

25 OCT 2010

Chapter 9 Ground Handling

Page 9.1

1. Insert spindle into skid-mounted support.

2. Verify flange is outboard of cradle.

3. Pull handle in rearward arc to raise helicopter.

4. Handle is in locked position when parallel with the skid.

NOTE

R66 ground handling wheels are installed inboard of landing

gear skid tubes. C063-5 (LH) and C063-6 (RH) ground handling

wheel assemblies are not interchangeable. When wheels are

installed and in locked position, both handles point aft.

FIGURE 9-1 GROUND HANDLING WHEELS

Page 9.2

Chapter 9 Ground Handling

25 OCT 2010

9-11 Ground Handling Wheels (continued)

B. Removal

1. Refer to Figure 9-1. Pull ground handling wheel handle in forward arc (lowers

helicopter) until handle is in unlocked position, parallel with the skid. Remove spindle

from skid-mounted support and remove wheel assembly. Repeat step to remove

second wheel assembly.

2. Retract handle by depressing locking pins and sliding handle in until pins engage

inner holes. Verify security.

9-12 Moving Helicopter on Ground Handling Wheels

Position main rotor blades approximately fore and aft and apply rotor brake.

Install ground handling wheels per Section 9-11.

Verify ground handling area is free of foreign object debris.

Have one person pull down on tail rotor gearbox until skid tubes are parallel with the

ground. During ground handling, balance helicopter to minimize wear on forward skid

shoes and rear extensions.

NOTE

Steer helicopter by gripping the tail rotor gearbox, aft tailcone

section, or inboard part of horizontal stabilizer between tailcone

and vertical stabilizers.

CAUTION

Do not steer helicopter by gripping the tail rotor guard, vertical

stabilizers, outboard part of horizontal stabilizer, tail rotor, tail

rotor controls, or tail skid.

a. If moving helicopter forward, nose first: Open engine cowling door(s). Have one

person (or two people) push on the engine door frame(s) forward ledge.

b. If moving helicopter backward, tail first: Have one person (or two people) push on

either side of nose vent.

9-13 Ground Handling Carts

The R66 can be handled by one person using the MT950-1 Universal ground handling cart.

Product specifications, as well as MT950 Operating Instructions, Maintenance Manuals,

and Illustrated Parts Catalogs are available on our website, www.robinsonheli.com , under

the Customer Support tab.

9-14 Ground Power Start

See R66 Pilot's Operating Handbook (POH) Section 4.

Chapter 9 Ground Handling

Page 9.3

9-20 Trailering

CAUTION

Trailering the R66 is not normally recommended. Most trailers

large enough to accommodate the helicopter are designed for

much heavier loads; the trailer’s springs and shock absorbers

will not function properly when lightly-loaded. Also, without

support, the tailcone can resonate with trailer vibrations,

subjecting the tailcone to greatly amplified loads.

If trailering is unavoidable, observe the following precautions:

1. Load trailer with ballast to an average weight the trailer is designed to carry.

2. Support the tailcone. Cushion support point(s) to prevent tailcone damage.

3. Perform one of the following options:

a. Remove main rotor blades per Section 62-10. Pack blades in shipping crate. See R66

Illustrated Parts Catalog [IPC] Figure 99-11.

b. Install main rotor blade supports per Section 10-13.

c. Fabricate blade supports to unload droop stops. Position supports inboard of blade

extended tab. Cushion support points to prevent blade damage.

4. Restrain tail rotor to prevent teetering.

5. Fuel helicopter per Section 12-41.

6. Protect windshield, windows, rotor systems, and all fragile equipment from exposure to

highway debris and subsequent damage.

7. After trailering, perform 100-hour maintenance and inspection per Section 5-45.

Page 9.4

Chapter 9 Ground Handling

CHAPTER 10

PARKING AND STORAGE

10-10 Parking

Place cyclic stick in vertical position and apply cyclic friction.

Place collective stick full down and apply collective friction.

CAUTION

Never pull down on main rotor blade. To teeter blades, push up

on the opposite blade.

Open three left-side fuselage access doors, observe placards, and climb steps to access

main rotor. Teeter blades by pushing up on one blade until opposite blade contacts teeter

stop. Rotate low blade forward. Position rotor blades approximately fore and aft and apply

rotor brake.

Install main rotor blade tie-down(s) per Section 10-12. Install engine exhaust cover.

Close and latch all access doors. Close and latch baggage compartment door.

Verify BATTERY switch is OFF, buckle seat harnesses, and close and latch cabin doors (if

installed).

10-11 Parking in High Wind or Turbulent Air

A. High Wind or Turbulent Air

Helicopter should be hangared or moved to a safe area during storm conditions or when

storm conditions are forecasted. When parking helicopter in high winds or when aircraft

is exposed to prop/rotor wash or jet blast:

1. Position helicopter with nose pointed in the direction of prevailing wind or turbulent

air.

2. Park helicopter per Section 10-10. Position rotor blades slightly offset from fore and

aft to prevent aft blade from flapping into tailcone, and apply rotor brake.

Extreme Conditions

In extreme conditions, at the operator's discretion:

1. Remove main rotor blades per Section 62-10. Remove tail rotor assembly per Section

64-10. Store main rotor blades and tail rotor assembly in hangar or safe area.

2. Remove main rotor pitch links per steps below, or temporarily secure links together

using ty-rap(s) or safety wire:

a. Mark an "X" on one pitch link lower rod end and corresponding swashplate ear

using a colored grease pencil. Mark an "O" on opposite link and corresponding

swashplate ear.

Chapter 10 Parking and Storage

Page 10.1

10-11 Parking in High Wind or Turbulent Air (continued)

B. Extreme Conditions (continued)

2. b. Remove hardware securing pitch links to swashplate assembly.

3. Remove tail rotor pitch links per steps below:

a. Refer to Figure 64-1. Tag each pitch link with corresponding blade serial number.

Disconnect pitch links from tail rotor blades; keep associate balancing hardware

with each link.

b. Remove hardware securing pitch links to tail rotor pitch control assembly.

10-12 Main Rotor Blade Tie-Downs

CAUTION

Overtightening tie-down straps can damage main rotor blades.

Maximum tie-down tension is 5 lb.

1. Park helicopter and position blades per Section 10-10 or 10-11.

2. Refer to Figure 10-1. Slide MT290-3 tie-down jacket over forward (lowered) main rotor

blade tip, with white lettering facing down. Thread strap through nose bracket and

secure tie-down hook and loop tape. Push up on secured blade to remove slack in tie-

down strap.

3. As required, install MT290-3 tie-down on aft main rotor blade. Slide jacket over blade

tip, with white lettering facing down. Wrap strap 1¾ times around tailcone forward of

strobe light, twist strap around strobe light base, and secure tie-down hook and loop

tape. Push up on secured blade to remove slack in tie-down strap.

25 OCT 2010

Chapter 10 Parking and Storage

Page 10.3

10-13 Main Rotor Blade Supports

Refer to R66 Illustrated Parts Catalog (IPC) Figure 10-7.

CAUTION

Do not allow strut assemblies to hang from cradle assemblies

installed on main rotor blades. Support strut assemblies during

strut removal or installation.

A. Removal

1. Refer to Figure 10-2. Remove 92384A034 retaining pins securing MT347-7 strut

assembly to MT564-2 cradle assembly and MT348-7 clamp assembly; remove strut

assembly. Remove cradle and clamp assemblies.

2. Remove retaining pin securing one MT347-8 strut assembly to landing gear eyebolt,

then remove pin securing same strut to MT564-1 cradle assembly. Repeat step to

remove second strut assembly.

3. Detach MT568-3 strap assembly hook and loop tape near roof-mounted cleat and

unthread strap from cleat. Remove cradle assembly.

Installation

NOTE

B221-3 attachment installation (landing gear eyebolts and roof-

mounted cleat) is required for mounting blade supports.

1. Refer to Figure 10-2. Position main rotor blades approximately fore and aft.

2. Install MT564-1 cradle assembly inboard of forward blade extended tab, with MT568-

3 strap assembly attached. Thread opposite end of strap assembly through roof-

mounted cleat and secure strap hook and loop tape.

3. Secure one MT347-8 strut assembly to cradle assembly, then to landing gear eyebolt,

using 92384A034 retaining pins. Repeat step to secure second strut assembly.

4. Install MT564-2 cradle assembly inboard of aft blade extended tab. Install MT348-7

clamp assembly against forward edge of rivets between tailcone bays 3 and 4.

5. Secure MT347-7 strut assembly to cradle and clamp assemblies using retaining pins.

Verify strut is approximately vertical.

6. Engage rotor brake. If desired, mark cradle assembly location on blade using felt-tip

marker, to facilitate future installation.

25 OCT 2010

Chapter 10 Parking and Storage

Page 10.5

10-20 Storage (Greater than 30 days)

NOTE

Helicopter should be hangared or moved to a safe area during

storage.

NOTE

Periodically inspect aircraft for corrosion and correct as required.

Aircraft stored in humid environments are subject to aggressive

corrosive reaction and require more frequent inspection.

Record the date helicopter is prepared and placed in storage.

Preserve engine for aircraft storage per RR300 Series Operation and Maintenance Manual

(OMM).

Refinish main rotor blades per Section 62-52. Refinish tail rotor blades per Section 64-36.

Open applicable circuit breakers.

Remove battery per Chapter 96. Inspect & service battery according to battery manufacturer’s

instructions.

Service engine oil, hydraulic fluid, and main & tail rotor gearboxes per Chapter 12.

Fuel helicopter per Section 12-41.

NOTE

Fuel lubricates bladder inner liner and keeps it from drying out

or cracking. Refuel helicopter after run-ups during storage per

Section 12-41.

Clean aircraft per Section 20-10. Ensure helicopter is clean and dry prior to storing. Open

door vents and doors to ventilate cabin and baggage compartment as required.

Close and latch all access doors. Install engine exhaust cover.

Page 10.6

Chapter 10 Parking and Storage

25 OCT 2010

11-10 Placard Locations

ITEM

PART NO.

DESCRIPTION

QTY

A654-18

Decal - "LEVEL HERE"

A654-25

Decal - “NEVER PULL DOWN / PUSH UP OPPOSITE BLADE”

A654-94

Decal - “DANGER HOT EXHAUST”

F654-21

Decal - “Push handle down...”

F654-22

Decal - “EXIT” (above each cabin door)

F654-20

Decal - “PUSH TO LOCK / DO NOT LOCK IN FLIGHT”

F654-19

Decal - "ENERGY-ABSORBING SEAT / DO NOT MODIFY"

C654-17

Decal - “INTERCOM”

F654-10

Decal - “CAUTION” (seat compartment loading)

F654-17

Decal - "MAX FILL LINE"

F654-1

Decal - “THROTTLE OPEN”

A654-7

Decal - “FRICTION INCREASE” (collective stick)

F445-1

Cover Assembly - FWD Tunnel

F445-3

Cover Assembly - FWD Tunnel (float ships; not shown)

A654-45

A950-1 Guard Assembly (fuel valve)

F444-1

Cover - Cyclic Box

F490-1

Panel Assembly - Circuit Breaker

A654-6

Decal - “THROTTLE OPEN” (collective stick)

A654-21

Decal - “NO STOWAGE / KEEP AREA CLEAR”

A654-12

Decal - “OPEN” (LH door, outside; black lettering)

A654-10

Decal - “OPEN” (LH door, outside; white lettering)

C654-7

Decal - “STATIC PORT” (black lettering)

C654-8

Decal - “STATIC PORT” (white lettering)

F654-5

Decal - “FUEL GRADE”

F654-6

Decal - “GROUND EITHER PLACE”

F654-15

Decal - "STEP HERE/HAND HOLD"

F654-12

Decal - “HYDRAULIC FLUID AND GEARBOX OIL”

F654-3

Decal - “ENGINE OIL”

23052363

Decal - “FAILURE TO PROPERLY INSTALL...”

A654-38

Decal - "PUSH TO OPEN"

F654-11

Decal - “STEP HERE”

F654-16

Decal - "STEP HERE LEFT FOOT"

A321-19

Marking - Weldment, Pistol Grip (left side)

A756-24

Marking - Weldment, Pistol Grip (right side)

F654-4

Decal - “NEVER EXCEED SPEED”

F654-28

Decal - “NEVER EXCEED SPEED” (float ships / police version; not shown)

B051-20

Face Assembly - R66 (Phaostron)

A654-45

A950-3 Guard Assembly (fuel cutoff)

A654-17

Decal - “NO SMOKING”

Chapter 11 Placards and Markings

Page 11.1

11-10 Placard Locations (continued)

ITEM

PART NO.

DESCRIPTION

QTY

F463-1

Cover Assembly - Mid Tunnel

F654-27

Decal (console compartment capacity)

G749-2

Console Assembly (Incl item 38, Ref)

C710-1

Cover

C712-2

Cover - Spotlight

D119-1

Handle - Rotor Brake

F436-6

Cover Assembly (RH)

F436-5

Cover Assembly (LH)

A654-16

Decal - “HEADSET” (early R66s)

F654-25

Decal (dongle programming instructions)

A654-11

Decal - “OPEN” (RH door, outside; black lettering)

A654-9

Decal - “OPEN” (RH door, outside; white lettering)

F654-24

Decal - “BATTERY LOCATED BEHIND THIS PANEL”

F654-8

Decal - “LATCH” (black lettering)

F654-9

Decal - “LATCH” (white lettering)

F654-7

Decal - “CAUTION” (baggage compartment loading)

F654-26

Decal - “CAUTION” (baggage compartment loading; police version)

G598-1

Faceplate - "28V / BATT CHARGE"

A654-3

Decal - “DANGER” Arrow (tail rotor)

D079-1

Tail Rotor Guard (Ref)

C654-2

Decal - “DANGER” Arrow (tail rotor)

11-20 Placard Illustrations

NOTE

Placards (decals) and markings are not to scale.

1. Decal A654-18

2. Decal A654-25

3. Decal A654-94

4. Decal F654-21

5. Decal F654-21

Chapter 11 Placards and Markings

Page 11.3

CHAPTER 12

SERVICING

Section

Title

Page

12-10

Main Rotor Gearbox

12.1

12-11

Servicing

12.1

12-12

Filter Replacement

12.3

12-13

Chip Detector and Sight Gage

12.3

12-20

Tail Rotor Gearbox

12.7

12-21

Servicing

12.7

12-22

Chip Detector and Sight Gage

12.8

12-23

Drain and Flush

12.8

12-30

Hydraulic System

12.9

12-31

Servicing

12.9

12-32

Filter Replacement

12.9

12-33

Drain and Flush

12.11

12-34

Bleeding

12.12

12-40

Fuel System

12.13

12-41

Fueling

12.13

12-42

Defueling

12.13

12-50

Main Rotor Blades

12.15

12-51

Pitch Bearing Housing

12.15

12-60

Engine Oil Servicing

12.16

12-70

(Engine) Compressor Rinse and Wash

12.17

12-80

Air Conditioning System

12.18

12-81

Refrigerant Recovery and System Charging

12.18

12-82

Desiccant Replacement

12.19

12-83

Leak Detection

12.19

Chapter 12 Servicing

Page 12.i

CHAPTER 12

SERVICING

12-10 Main Rotor Gearbox

WARNING

Refer to appropriate Material Safety Data Sheet (MSDS) and

take necessary safety precautions when working in proximity

to hazardous materials.

12-11 Servicing

NOTE

Inspect main rotor gearbox and gearbox lubrication system for

leaks when “top off” is required.

NOTE

Verify aircraft is on level ground when evaluating gearbox oil

level.

A. Draining Fluid

1. Refer to Figure 12-1. Disconnect chip detector wiring, as required. Remove chip

detector from housing.

2. Refer to Figure 12-2. Insert MT054-1 drain assembly into chip detector housing.

Position drain hose overboard into a suitable drain container. Jam wedge between

support panel stiffener and drain assembly fitting to open valve.

Adding Fluid

1. Install chip detector per Section 12-13, if removed.

2. Refer to Figure 12-1. Remove gearbox filler-plug. Fill gearbox with A257-22 lubricant

to center of sight glass.

3. Rotate rotor system by hand for several revolutions and pull down on tail rotor

gearbox several times. Check gearbox oil level and adjust level as required.

4. Install filler-plug and special torque plug per Section 20-33.

5. Run-up helicopter approximately five minutes at

60-70% RPM per R66 Pilot’s

Operating Handbook (POH) Section 4.

6. Check gearbox oil level, and adjust level per steps 2 thru 6 as required.

Chapter 12 Servicing

Page 12.1

12-12 Filter Replacement

Refer to R66 Illustrated Parts Catalog (IPC) Figure 63-13.

NOTE

Replace main rotor gearbox oil every

600 hours. When

replacing a filter after new or overhauled main rotor gearbox

has accumulated 100 hours, replacing oil is not required.

1. Drain main rotor gearbox oil per Section 12-11, if required.

2. Cut and discard safety wire securing bowl & indicator assembly to head assembly.

Unscrew bowl and remove and discard element. Remove o-ring and back-up ring from

head assembly.

3. Clean and dry bowl assembly; install new F651-3 seals kit and F651-2 element.

4. Hand-tighten bowl assembly until tight against head assembly. Install 0.032-inch

diameter lockwire and safety bowl to head.

5. Service main rotor gearbox per Section 12-11.

12-13 Chip Detector and Sight Gage

A. Removal

1. Refer to Figure 12-1. Disconnect chip detector wiring, as required. Remove chip

detector from housing.

NOTE

Remove chip detector housing and inspect for obvious damage

if housing leaks.

2. Drain main rotor gearbox oil per Section 12-11, if removing chip detector housing or

sight gage. Remove housing and/or gage as required.

B. Cleaning Chip Detector (and Housing)

1. Scrub chip detector (and housing, if applicable) with a toothbrush and approved

solvent per Section 20-70. To remove debris, use compressed air or masking tape;

do not use a magnet. Dry chip detector with compressed air or a lint-free cloth.

2. Refer to Figure 12-1. Connect chip detector electrical wiring and special torque

terminal nut per Section 20-33. Turn BATTERY switch ON and ground detector’s

central magnetic probe to airframe. Verify appropriate CHIP warning segment

illuminates. Turn BATTERY switch OFF.

Chapter 12 Servicing

Page 12.3

12-13 Chip Detector and Sight Gage (continued)

C. Installation

1. Refer to Figure 12-1. Verify cleanliness and clarity of sight gage. As required,

remove sight gage per Part A and clean with approved solvent per Section 20-70.

Install sight gage and special torque per Section 20-33.

2. Verify cleanliness of chip detector and housing. As required, remove and clean

chip detector and housing per Parts A and B. Install housing and special torque per

Section 20-33. Install chip detector.

3. Turn BATTERY switch ON. Verify MR CHIP warning segment illuminates when test

button is depressed. Turn BATTERY switch OFF.

Chapter 12 Servicing

Page 12.5

12-20 Tail Rotor Gearbox

WARNING

Refer to appropriate Material Safety Data Sheet (MSDS) and

take necessary safety precautions when working in proximity

to hazardous materials.

12-21 Servicing

NOTE

Inspect tail rotor gearbox for leaks when “top off” is required.

NOTE

Verify aircraft is on level ground when evaluating gearbox oil

level.

A. Draining Fluid

1. Refer to Figure 12-3. Cut and discard ty-raps as required and disconnect chip detector

wiring from airframe harness at connectors.

2. Place a suitable drain container under gearbox to catch oil, then remove chip

detector.

B. Adding Fluid

1. Install chip detector per Section 12-22.

2. Refer to Figure 12-3. Remove filler-vent plug and fill gearbox with A257-22 lubricant

to center of sight glass.

3. Install plug and special torque per Section 20-33.

Chapter 12 Servicing

Page 12.7

12-22 Chip Detector and Sight Gage

A. Removal

1. Drain tail rotor gearbox oil per Section 12-21.

2. Remove sight gage, as required.

Cleaning Chip Detector

1. Clean chip detector per Section 12-13 Part B (main rotor gearbox).

C. Installation

1. Refer to Figure 12-3. Verify cleanliness and clarity of sight gage. As required,

remove sight gage per Part A and clean with approved solvent per Section 20-70.

Install sight gage and special torque per Section 20-33.

2. Verify cleanliness of chip detector. As required, clean chip detector per Section 12-

13 Part B (main rotor gearbox). Install chip detector and special torque per Section

20-33.

3. Connect chip detector wiring and install ty-raps, as required. Cinch ty-raps until

snug without over-tightening, and trim tips flush with heads.

4. Turn BATTERY switch ON. Verify TR CHIP warning segment illuminates when test

button is depressed. Turn BATTERY switch OFF.

5. Service tail rotor gearbox per Section 12-21.

12-23 Drain and Flush

1. Drain tail rotor gearbox oil per Section 12-21.

2. Install chip detector and special torque per Section 20-33.

3. Remove filler-vent plug and add approximately five ounces of SAE30, SAE40, SAE50,

or SAE20W50 straight mineral engine oil to gearbox. Install plug and special torque per

Section 20-33.

4. Run-up helicopter approximately five minutes at 60-70% RPM per R66 Pilot's Operating

Handbook (POH) Section 4.

5. Drain tail rotor gearbox oil (mineral oil) per Section 12-21.

6. Clean and install chip detector per Section 12-22 Parts B and C.

Page 12.8

Chapter 12 Servicing

12-30 Hydraulic System

CAUTION

Do not contaminate hydraulic fluid. Service hydraulic system

with clean fluid from sealed containers, using clean tools.

WARNING

Refer to appropriate Material Safety Data Sheet (MSDS) and

take necessary safety precautions when working in proximity to

hazardous materials.

12-31 Servicing

A. Draining Fluid

1. Perform drain and flush per Section 12-33.

B. Adding Fluid

NOTE

Inspect hydraulic system for leaks when “top off” is required.

1. Refer to Figure 12-4. Remove filler-vent plug. With system filled and bled, fill

hydraulic reservoir to center of sight glass with new A257-15 fluid.

2. Install filler-vent plug and special torque per Section 20-33.

12-32 Filter Replacement

1. Refer to Figure 12-4. Remove D516-1 cap and filter and visually inspect element for

contaminants. If element is clear, proceed to step 3. If metal contamination is found, use

a magnet to determine if metal is ferrous. If metal is ferrous, perform the following:

a. Install new filter per steps 3 thru 5.

b. After one flight-hour, remove filter and inspect for ferrous metal. If ferrous metal is

found upon second inspection, replace hydraulic pump per Section 67-50, then drain

and flush hydraulic system per Section 12-33.

2. Discard cap packing. Clean cap with approved solvent per Section 20-70, and dry cap

with compressed air or a lint-free cloth. Lubricate new packing with A257-15 fluid and

install on cap.

3. Lubricate packing inside new filter with A257-15 fluid and install filter in reservoir.

Install cap and special torque per Section 20-33.

4. Service hydraulic reservoir per Section 12-31.

Chapter 12 Servicing

Page 12.9

12-33 Drain and Flush

NOTE

Drain and flush hydraulic system if oil turns dark or emits bad

odor.

WARNING

Keep limbs clear of flight controls when operating test pump.

Hydraulic forces can cause injury.

Refer to Figure 12-4. Remove filler-vent plug. Place a suitable drain container under

F902-1 (pressure) and F902-2 (suction) line assembly T-fittings, and remove caps.

Pour small amount of new A257-15 fluid into hydraulic reservoir to purge suction line.

Pressure line will drain in following step, when D516-1 cap is removed.

Replace filter per Section 12-32.

Connect MT384 (or equivalent) 0.8-1.2 gpm hydraulic test pump assembly to T-fittings.

(Pressure and suction fittings are different sizes to ensure correct connection.)

Service hydraulic reservoir per Section 12-31.

Disconnect D205-18 hose assembly (return) from reservoir. Place line into drain

container; cap union with a T-fitting cap.

Activate test pump and inspect hydraulic system for leaks.

Simultaneously fully raise collective and move cyclic fully forward then simultaneously

fully lower collective and move cyclic fully aft. Monitor reservoir fluid level and fill as

required. Repeat procedure until return line fluid is clean.

Simultaneously fully raise collective and move cyclic fully aft then simultaneously fully

lower collective and move cyclic fully forward. Monitor reservoir fluid level and fill as

required. Repeat procedure until return line fluid is clean.

Turn off test pump and disconnect equipment. Remove cap and connect hose assembly

(return) to reservoir. Using back-up wrench, standard torque hose nut per Section 20-

32 and torque stripe per Figure 5-1. Install caps on T-fittings, special torque caps per

Section 20-33, and torque stripe per Figure 5-1.

10. Bleed hydraulic system per Section 12-34.

11. Remove cap and filter and visually inspect element for contaminants. If debris is found,

repeat drain and flush procedure. If filter is clean, install filter & cap and special torque

cap per Section 20-33.

12. Service hydraulic reservoir per Section 12-31.

Chapter 12 Servicing

Page 12.11

12-34 Bleeding

WARNING

Keep limbs clear of flight controls when operating test pump.

Hydraulic forces can cause injury.

Remove F902-1 (pressure) line assembly T-fitting cap. Connect MT384 (or equivalent)

0.8-1.2 gpm hydraulic test pump pressure line to T-fitting. (Pressure and suction fittings

are different sizes to ensure correct connection.)

Remove filler-vent plug and cover hydraulic reservoir hole with finger to prevent fluid

loss (until suction line is connected). Remove F902-2 (suction) line assembly T-fitting

cap. Connect test pump suction line to T-fitting. Service reservoir with new A257-15

fluid, as required.

Activate test pump and inspect hydraulic system for leaks.

Simultaneously fully raise collective and move cyclic fully forward then simultaneously

fully lower collective and move cyclic fully aft. Repeat procedure ten times.

Simultaneously fully raise collective and move cyclic fully aft then simultaneously fully

lower collective and move cyclic fully forward. Repeat procedure ten times.

Turn off test pump and verify no leaks in hydraulic system.

Cover reservoir hole with finger (until suction line T-fitting is capped). Disconnect test

pump suction line from suction line T-fitting and install cap.

Disconnect test pump pressure line from pressure line T-fitting and install cap. Special

torque caps per Section 20-33 and torque stripe per Figure 5-1.

Service hydraulic reservoir per Section 12-31.

Page 12.12

Chapter 12 Servicing

12-40 Fuel System

WARNING

Refer to appropriate Material Safety Data Sheet (MSDS) and

take necessary safety precautions when working in proximity to

hazardous materials.

WARNING

Always fuel helicopter in a well-ventilated area. No smoking

within 100 feet of aircraft during fueling.

12-41 Fueling

1. Turn BATTERY switch OFF.

2. Ground helicopter and ground fuel vehicle. Open fueling cowl door and connect fuel

vehicle ground cable to helicopter at location identified by decal.

3. Verify proper grade of aviation fuel. See R66 Pilot's Operating Handbook (POH) Section

2 for approved fuel grades and instructions for use of anti-ice additive.

4. Remove fuel cap and fuel helicopter as required.

5. Install fuel cap, remove grounding equipment, and close cowl door.

12-42 Defueling

Refer to R66 Illustrated Parts Catalog (IPC) Figure 28-9.

1. Remove engine cowling per Section 53-21.

2. Turn BATTERY switch OFF. Pull fuel valve control OFF.

3. Disconnect B283-12 hose at F670-1 valve, raise hose vertically, and plug hose inlet.

4. Fabricate drain hose (3 feet clear tubing with fitting) and connect to valve outlet. Position

drain hose overboard into a suitable, grounded drain container.

NOTE

If desired, perform low-fuel switch assembly check per Section

28-22.

5. Push fuel valve control ON and drain fuel; drain residual fuel via sump valve. Pull fuel

valve control OFF. Perform maintenance tasks as required.

6. Add minimum 5 gallons fuel per Section 12-41. Push fuel valve control ON until fuel

flows thru drain hose without bubbles. Pull fuel valve control OFF.

7. Connect B283-12 hose, special torque hose nut per Section 20-33, and torque stripe

per Figure 5-1.

8. Defuel engine as required per RR300 Series Operation and Maintenance Manual (OMM).

Chapter 12 Servicing

Page 12.13

12-50 Main Rotor Blades

WARNING

Refer to appropriate Material Safety Data Sheet (MSDS) and

take necessary safety precautions when working in proximity to

hazardous materials.

12-51 Pitch Bearing Housing

NOTE

MT147-1 Main rotor blade spindle air bleed tool includes supply

container, hose assemblies, and bleed fittings.

A. Servicing

Remove main rotor blades per Section 62-10.

Refer to Figure 12-5. Place a suitable drain container below main rotor blade spindle

assembly. Remove two B289-2 bolts and drain fluid.

Install MT147-1 bleed tool fittings into ports. Attach drain hose assembly to (top)

bleed fitting, secure with two wraps 0.032-inch diameter lockwire, and safety tight.

Position drain hose into drain container.

Place supply container with sufficient A257-4 fluid approximately 3 feet above

spindle. Route fill hose assembly into drain container and open brass valve. Open

supply container plastic valve and purge air from hose. Close valves.

Connect brass valve to (bottom) bleed fitting by tightening brass compression

sleeve.

Open valves and fill spindle housing until no air bubbles are visible in drain hose

assembly. Massage spindle boot, “pitch” blade up & down, and raise blade tip up &

down to remove trapped air.

Remove drain hose assembly and (top) bleed fitting, and install B289-2 bolt. Roll

the blade over. After five minutes, inspect the boot for leaks. If no leaks are found,

close valves, remove fill hose assembly brass valve and (bottom) bleed fitting, and

install other bolt.

Torque B289-2 bolts per Section 20-33 and torque stripe per Figure 5-1.

Repeat steps for opposite blade.

Chapter 12 Servicing

Page 12.15

12-60 Engine Oil Servicing

Refer to R66 Illustrated Parts Catalog (IPC) Figures 79-5 and 79-7.

A. Draining Fluid

1. Run-up helicopter two to five minutes at 60-70% RPM per R66 Pilot's Operating

Handbook (POH) Section 4 to warm engine oil, as required.

2. Remove engine cowling per Section 53-21.

3. Place a suitable drain container below B289-2 bolt in bend of F723-1 line assembly, and

below AS5169D04 (drain) fitting in F649-1 oil cooler assembly.

4. Remove line assembly bolt and oil cooler assembly (drain) fitting and drain oil.

5. Service the engine oil system per RR300 Series Operation and Maintenance Manual

(OMM).

Adding Fluid

NOTE

Do not contaminate engine oil. Service engine oil system with

clean fluid from sealed containers, using clean tools.

NOTE

When servicing airframe oil tank, full oil quantity is six quarts;

minimum quantity for takeoff is four quarts.

Six quart indication is top of knurled section of dipstick. Four

quart indication is bottom of knurled section of dipstick or center

of oil tank sight gage.

Install B289-2 bolt in bend of F723-1 line assembly and special torque per Section 20-

33.

Install AS5169D04 (drain) fitting in F649-1 oil cooler assembly and special torque per

Section 20-33.

Install engine cowling per Section 53-21.

Open access door, remove dipstick, and service airframe oil tank using approved turbine

engine oil per R66 Pilot's Operating Handbook (POH) Section 8.

Install dipstick and close access door.

Perform engine test per RR300 Series Operation and Maintenance Manual (OMM) as

required.

Page 12.16

Chapter 12 Servicing

12-70 (Engine) Compressor Rinse and Wash

Refer to R66 Illustrated Parts Catalog (IPC) Figure 71-9.

CAUTION

See RR300 Series Operation and Maintenance Manual (OMM)

requirements for compressor rinse and wash intervals.

CAUTION

Always perform compressor rinse or wash with sufficient

clearance for possible rotor system rotation.

Remove engine cowling per Section 53-21.

Open access door and remove (engine) compressor fluid-delivery tube cap.

Refer to RR300 Series Operation and Maintenance Manual (OMM) for equipment and material

requirements. Operate compressor cleaning system per manufacturer's instructions.

Connect appropriate cleaning system hose to delivery tube.

Refer to RR300 Series OMM for compressor rinse and wash procedures.

To motor engine without ignition system:

a. Release rotor brake.

b. Turn BATTERY switch ON.

c. Verify fuel cutoff pulled OFF. Verify igniter (key) switched OFF.

d. Verify area is clear.

e. Close throttle.

f. Push and release start button as required to maintain N1 speed for required interval.

Disconnect cleaning system hose from delivery tube. Install delivery tube cap and standard

torque per Section 20-32. Close access door.

Refer to RR300 Series OMM for returning engine to service.

To perform ground run:

a. Refer to R66 Pilot's Operating Handbook (POH) Section 4 for run-up and shutdown

procedures.

Install engine cowling per Section 53-21.

Chapter 12 Servicing

Page 12.17

12-80 Air Conditioning System

12-81 Refrigerant Recovery and System Charging

NOTE

In the United States, only personnel with EPA certification under

Section 609 of the Clean Air Act may charge the system with

refrigerant or work on the refrigerant system once it has been

charged. Different requirements may apply in countries other

than the United States.

Automotive-style air conditioning service equipment, compatible with R134a refrigerant,

is required to recover and charge the system with refrigerant. This equipment is available

from many manufacturers in varying levels of automation and complexity. Minimum

components include a vacuum pump, pressure pump, refrigerant supply, scale to measure

refrigerant charge, pressure/vacuum gage, and appropriate lines and fittings.

Ensure that the technician performing the task is appropriately qualified.

A. Refrigerant Recovery

NOTE

If a leak or other service problem is encountered after system is

charged with refrigerant, refrigerant must be recovered before

work on system can proceed.

1. Remove tailcone cowling per Section 53-23.

2. Automotive-style high- and low-side system service ports are located on G794

hose assemblies where they mount to the compressor assembly. Connect service

equipment to system quick-disconnect ports and recover refrigerant per equipment

manufacturer’s instructions.

System Charging

CAUTION

Do not overcharge system. Perform leak detection per Section

12-83 if a leak is suspected, then use correct charge.

1. Remove tailcone cowling per Section 53-23.

2. Automotive-style high- and low-side system service ports are located on G794

hose assemblies where they mount to the compressor assembly. Connect service

equipment to system quick-disconnect ports.

3. Replace desiccant per Section 12-82. Vacuum system, then charge with R134a

refrigerant per equipment manufacturer’s instructions. Correct charge is 2.5 lb (40

oz) refrigerant.

4. Install tailcone cowling per Section 53-23.

Page 12.18

Chapter 12 Servicing

12-82 Desiccant Replacement

Refer to R66 Illustrated Parts Catalog (IPC) Figure 21-7.

NOTE

Replace desiccant when condenser or refrigerant system is

exposed to air. To eliminate moisture, replace desiccant, then

immediately vacuum system for charging per Section 12-81.

1. Remove engine cowling per Section 53-21.

2. Recover refrigerant per Section

12-81, if not previously accomplished. Remove

condenser cap and replace desiccant.

3. Install cap, special torque cap per Section 20-33, and torque stripe.

4. Charge system with refrigerant per Section 12-81.

12-83 Leak Detection

Leaks may be detected using several techniques, depending on equipment available. Leak

detection should not be attempted with the aircraft/system running. In addition to safety

hazards, leaks are more difficult to detect with the varying pressures and temperatures of

an operating system.

An empty system should hold full vacuum (27 to 29 inches mercury vacuum at sea level)

with no assistance from the vacuum pump for 20 minutes minimum. If a vacuumed system

creeps up in pressure, a leak may be present. The technician should be thoroughly familiar

with vacuum equipment to ensure leak is in aircraft system and not in vacuum equipment

or connections.

Leaks in a charged system may be detected using a mild soap and water solution applied

to lines and fittings in suspected leak areas (bubbles indicate leaks) or using commercially

available electronic refrigerant detectors. Follow detector manufacturer’s instructions.

Large leaks may be detected audibly if area is quiet or by formation of frost in area of leak.

NOTE

Frost does not necessarily indicate a leak. Normal system

operation and/or charging procedures can cause frost to

accumulate on some components.

NOTE

System pressure is not a reliable indicator of charge state or

the presence of leaks. Because R134a is a liquid/vapor mixture

with the system at rest, pressure will remain constant as more

liquid vaporizes until majority of charge is lost.

Very small leaks can be detected by charging the system with helium gas. Helium molecules

are smaller than R134a molecules and will leak more quickly. Charge system to 200

psi maximum. Use commercially available electronic helium detector or soap and water

solution to locate leaks.

Leaks are most likely to occur at fittings and crimped transitions between hard line and

flexible hose. Concentrate initial leak detection efforts in these areas.

Chapter 12 Servicing

Page 12.19

CHAPTER 18

TRACK AND BALANCE

Section

Title

Page

18-10

Main Rotor Track and Balance

18.1

18-11

Preparing Helicopter for Main Rotor Track and Balance . .

18.3

18-12

Flight Checks

18.5

18-13

Track Adjustment

18.7

18-14

Balance Adjustment

18.10

18-15

Troubleshooting

18.11

18-16

Autorotational RPM Adjustment

18.12

18-20

Tail Rotor Dynamic Balance

18.17

18-21

Preparing Helicopter for Tail Rotor Dynamic Balance . . .

18.17

18-22

Ground Checks

18.19

18-23

Balance Adjustment

18.19

18-30

Main Rotor Flight Control Rigging

18.21

18-40

Main Rotor Blade Angle Rigging

18.23

18-41

Collective Travel

18.24

18-42

Cyclic Travel

18.26

18-50

Tail Rotor Flight Control Rigging

18.28

18-51

Pedals

18.28

18-52

Forward Bellcrank

18.28

18-53

Intermediate Bellcrank

18.28

18-60

Tail Rotor Blade Rigging

18.29

Chapter 18 Track and Balance

Page 18.i

18-11 Preparing Helicopter for Main Rotor Track and Balance

NOTE

Use the following track & balance procedures in conjunction with

approved equipment manufacturer’s balancing instructions.

CAUTION

Cable security is critical; helicopter will be flown at V_NE.

Perform swashplate and rotor hub inspection per Section 5-45. Inspect tail rotor rod

ends and elastomeric bearings per Sections 5-33 and 5-34.

Clean main and tail rotor blades per Section 20-10. Install main rotor blade target tape

per Figure 18-1.

Refer to Figure 18-1. Using appropriate hardware, attach brackets to vibration transducer

and attach assembly to F359-1 panel as shown. Remove removable controls.

Install magnetic pickup onto swashplate bracket. Set (swashplate-mounted) interrupter-

to-pickup gap to 0.030 inch ± 0.010 inch and tighten pickup nuts against bracket.

Safety nuts using 0.020-inch diameter lockwire. Recheck gap.

Pull collective stick full up, push cyclic stick full left, and apply frictions. Connect proper

cable to magnetic pickup. Route cable down seam and to base of mast fairing, across

the cabin roof left side, and through the aft left door vent door. Attach the cable to the

fuselage using MS21919WDG3 clamps and existing fasteners, or secure cable every

12 inches with duct tape. Release control frictions and verify sufficient cable slack and

freedom of controls through full range of travel.

Connect proper cable to vibration transducer. Connect transducer, magnetic pickup,

and tracker or strobe cables to analyzer. If strobe light is used, battery power may be

accessed thru auxiliary power socket located on circuit breaker panel. Neatly stow and

secure excess cables.

Verify security of installation.

25 OCT 2010

Chapter 18 Track and Balance

Page 18.3

DATE

SERIAL NO.

TIP WEIGHTS

TEETER HINGE SHIMS

PAGE

(1) AN960-10 Washer

(2)

AN960-10L Washers

C117-8

0.012 inch

CHORD ARM WEIGHTS

(1) C298-2 Weight

(5)

AN960-10 Washers

C117-9

0.015 inch

(1) A255-1 Weight

(8)

AN970-4 Washers

(1) C298-3 Weight

(11)

AN960-10 Washers

C117-10

0.020 inch

(1) A255-2 Weight

(3)

A255-1 Weights

(1) C298-4 Weight

(4)

C298-3 Weights

C117-11

0.025 inch

BALANCE

TRACK (KNOTS)

CLOCK

IPS

HOVER

100

110

120

130

140

Adjustment:

CLOCK

IPS

HOVER

100

110

120

130

140

Adjustment:

CLOCK

IPS

HOVER

100

110

120

130

140

Adjustment:

CLOCK

IPS

HOVER

100

110

120

130

140

FIGURE 18-2 MAIN ROTOR TRACK AND BALANCE CHART

Page 18.4

Chapter 18 Track and Balance

25 OCT 2010

18-12 Flight Checks

NOTE

Run-up and shutdown helicopter throughout procedure as

required per R66 Pilot's Operating Handbook (POH) Section 4.

NOTE

Refer to Section 18-15 for track and balance troubleshooting

procedures.

WARNING

Tail rotor balancing equipment must be removed for flight.

WARNING

Do not exceed V_NE of helicopter during flight checks.

Prepare helicopter for main rotor track and balance per Section 18-11.

Make a photocopy of Figure 18-2; use copy to record flight data. Check main rotor

blade track in a hover and record data. Maximum blade spread in a hover is 0.25 inch.

Adjust track per Section 18-13 as required, record change, and recheck blade track in a

hover. Repeat step as required until blade track is within limits.

Check main rotor balance in a hover and record data. Maximum vibration allowance

is 0.2 ips (inches per second). Adjust balance per Section 18-14 as required, record

data, and recheck balance in a hover. Repeat step as required until main rotor balance

is within limits.

Fly helicopter at 50, 60, 70, 80, 90, 100, 110, 120, 130, and 140 knots. Check main

rotor blade track at each airspeed and record data. Maximum blade spread between

airspeeds is 3/8 inch. Adjust trim tab(s) per Section 18-13 as required and record data.

Repeat step as required until blade track is within limits.

Recheck main rotor balance in a hover per step 3.

Perform autorotation RPM check per Section 18-16. Recheck main rotor balance in a

hover per step 3.

Evaluate collective trim, longitudinal cyclic trim, and lateral cyclic trim. Adjust as

required. Recheck main rotor balance in a hover per step 3.

Remove track and balance equipment. Torque stripe fasteners. Reinstall removable

controls, as required.

25 OCT 2010

Chapter 18 Track and Balance

Page 18.5

18-13 Track Adjustment

A. Main Rotor Blade Pitch Link

Refer to R66 Illustrated Parts Catalog (IPC) Figure 62-5.

NOTE

Shorten high pitch blade when adjusting track in a hover.

NOTE

During rigging, adjust both pitch links exactly the same for

collective adjustments.

Refer to Figure 18-3. For coarse length adjustment, adjust rod end and fitting per

the following steps:

a. Cut and discard pitch link assembly safety wire. Using backup wrench on link

assembly, loosen jam nut in middle of pitch link. Remove hardware securing

upper rod end to blade pitch horn.

b. Rotate rod end and fitting to shorten or lengthen pitch link as required. One full

turn changes blade angle by approximately 0.88°.

c. Refer to Figure 5-1. Verify rod end threaded shank blocks passage of 0.020-inch

diameter lockwire through pitch link witness hole. Install hardware securing rod

end to pitch horn and torque fastener per Section 20-32.

d. Position rod ends to allow as much pitch link rotation as possible without binding.

Using backup wrench on link assembly, torque jam nut per Section 20-32. Safety

fitting to link assembly using 0.032-inch diameter lockwire.

e. Repeat steps on opposite pitch link as required. Torque stripe per Figure 5-1.

For medium length adjustment, adjust rod end only per the following steps:

a. Using backup wrench on fitting, loosen upper rod end palnut and jam nut. Remove

hardware securing rod end to blade pitch horn.

b. Rotate rod end to shorten or lengthen pitch link as required. One-half rod end

turn changes blade track approximately 0.25 inch. One full rod end turn changes

blade angle by approximately 0.48°.

c. Refer to Figure 5-1. Verify rod end threaded shank blocks passage of 0.020-inch

diameter lockwire through pitch link witness hole. Install hardware securing rod

end to pitch horn and torque fastener per Section 20-32.

d. Position rod ends to allow as much pitch link rotation as possible without binding.

Using backup wrench on fitting, torque rod end jam nut and palnut per Section

20-32.

e. Repeat steps on opposite pitch link as required. Torque stripe per Figure 5-1.

25 OCT 2010

Chapter 18 Track and Balance

Page 18.7

18-13 Track Adjustment (continued)

A. Main Rotor Blade Pitch Link (continued)

3. For fine adjustment, adjust fitting only per the following steps:

a. Remove and discard pitch link assembly safety wire. Using backup wrench on

link assembly, loosen jam nut in middle of pitch link. Using backup wrench on

fitting, loosen upper rod end palnut and jam nut.

b. Rotate fitting to shorten or lengthen pitch link as required. One full turn changes

blade track approximately 0.25 inch. One full turn of fitting changes blade

angle approximately 0.40°. For finer adjustment, count hex flats while rotating

fitting.

c. Refer to Figure 5-1. Verify rod end threaded shank blocks passage of 0.020-inch

diameter lockwire through pitch link witness hole.

d. Using backup wrench on link assembly, torque jam nut per Section 20-32. Using

backup wrench on fitting, torque rod end jam nut and palnut per Section 20-32.

Safety fitting to link assembly using 0.032-inch diameter lockwire.

e. Repeat steps on opposite pitch link as required. Torque stripe per Figure 5-1.

Main Rotor Blade Trim Tab

NOTE

To correct for a "climbing" blade condition (blade spread that

exceeds 3/8 inch with forward airspeed), bend high blade trim

tab down.

CAUTION

Do not use other helicopter manufacturers' trim tab bending

tools. Use of these tools will damage Robinson blades.

CAUTION

MT352-1 gage must contact trim tab trailing edge. If gage

does not contact tab trailing edge, tab is bent beyond limit.

CAUTION

Tighten MT526-8 bending tool bolt to bend tab; do not use tool

as a lever.

CAUTION

Bend tab upward only when absolutely necessary; bending tab

upward can increase rotor vibration.

Using felt tip marker, ink mark main rotor blade trim tab per Figure 18-4. Mark line

with a measuring point in the center of the tab (approximate).

25 OCT 2010

Chapter 18 Track and Balance

Page 18.9

18-13 Track Adjustment (continued)

B. Main Rotor Blade Trim Tab (continued)

2. Position MT352-1 gage chordwise across blade upper surface and tab trailing edge.

Zero dial indicator on measuring point.

3. Position MT526-8 bending tool on tab per Figure 18-4. Slide tool completely over

tab until tool stops contact blade trailing edge. Double-rib side of tool should contact

tab upper surface to bend tab down. Double-rib side of tool should contact tab

bottom surface to bend tab up.

4. Tighten MT526-8 bending tool bolt to bend tab. Make slight bends and remeasure tab

with MT352-1 gage. Bend trim tab 0.015 inch (down) to effect dynamic movement

of main rotor blade tip approximately 0.2 inch (downward).

18-14 Balance Adjustment

WARNING

A rotor which is smooth after balancing but goes out of balance

within a few flights is suspect and must be examined by RHC

before further flight.

A. Tip Weights (Spanwise Balance Adjustment)

1. Remove screws securing tip cover to blade. Balance rotor assembly spanwise

by adjusting tip weights as required per Figure 18-2. Washers may be trimmed.

Special torque fasteners securing tip weights per Section 20-33. Install tip cover

and standard torque fasteners per Section 20-32.

(1) AN960-10 or NAS1149F0363P Washer =

(2) AN960-10L or NAS1149F0332P Washers

(1) C298-2 Weight

= (5) AN960-10 or NAS1149F0363P Washers

(1) C298-3 Weight

= (11) AN960-10 or NAS1149F0363P Washers

(1) C298-4 Weight

= (4) C298-3 Weights

Teeter Hinge Bolt Shims (Chordwise Balance Adjustment - Coarse Adjustment)

1. Remove and discard teeter hinge nut cotter pin. Remove nut, thrust washer, and any

shims.

2. Have two people cone the main rotor blades. Push out teeter hinge bolt (and any

shims) with another bolt.

3. Balance rotor assembly chordwise by moving (or exchanging) existing teeter hinge

shims to other side of bolt (under head or under nut) as required per Figure 18-2.

Install teeter hinge bolt per Section 62-10.

C. Chord Arm Weight (Chordwise Balance Adjustment - Fine Adjustment)

1. Balance rotor assembly chordwise by adjusting chord arm weights or washers per

Figure 18-2. Total weight not to exceed four A255-2 weights (or equivalent).

(1) A255-1 Weight

(8) AN970-4 Washers

(1) A255-2 Weight

(3) A255-1 Weights

Page 18.10

Chapter 18 Track and Balance

25 OCT 2010

18-15 Troubleshooting

The following are some of the symptoms and corrections which occur in the Track and Balance

operations of the helicopter. Decide on the various causes of a given trouble and then eliminate

causes one by one, beginning with the most probable.

Symptom

Probable Cause

Correction

Excessive Cyclic or

Main rotor (MR) out of track.

Track and balance per Section 18-10.

Stick Shake

Rough or binding A205-7 fork

Replace or refer to Section 67-40.

assembly (upper swashplate).

Brinelled spindle bearing

Send blade(s) to RHC for spindle bearing

(rough movement).

replacement.

Rough blade surface (chipped paint).

Repair blades per Section 62-60.

Rough or binding pitch links.

Replace pitch link rod ends

MR blade boot misaligned.

Realign or replace boot per Section 62-11.

MR teeter or coning hinge binding.

Replace bearings per Section 62-21.

MR blade trim tabs bent upward.

Bend trim tabs evenly down per Section 18-13.

Blade mismatch.

Send blade(s) to RHC for replacement.

Excessive Ship

MR out of track and balance.

Track and balance per Section 18-10.

Vibration

MR teeter or coning hinge friction.

Adjust hinge friction per Section 62-32.

MR teeter or coning hinge binding.

Replace bearings per Section 62-21.

Brinelled spindle bearing

Send blade(s) to RHC for spindle bearing

(rough movement).

replacement.

MR teeter hinge bearings worn.

Replace bearings per Section 62-21.

Excessive Cyclic

Brinelled spindle bearing

Send blade(s) to RHC for spindle bearing

Stick Forces

(rough movement).

replacement.

Intermittent Blade

MR teeter or coning hinge friction

Adjust hinge friction per Section 62-32.

Track Picture

MR coning hinge binding.

Replace bearings per Section 62-21.

MR teeter hinge not "broken-in."

Track and balance per Section 18-10. Adjust

track to minimize error.

Brinelled spindle bearing

Send blade(s) to RHC for spindle bearing

(rough movement).

replacement.

Radical Changes to

MR teeter hinge bearings worn.

Replace bearings per Section 62-21.

Cyclic Trim

Brinelled spindle bearing

Send blade(s) to RHC for spindle bearing

(rough movement).

replacement.

25 OCT 2010

Chapter 18 Track and Balance

Page 18.11

18-16 Autorotational RPM Adjustment

Use the following procedure for checking and adjusting autorotational RPM:

WARNING

Failure to properly adjust autorotational RPM (RPM too low)

may prevent the rotorcraft from achieving proper RPM at low

gross weights.

Perform autorotation RPM check at minimum practical gross weight (less than 1900

lb). Calculate the takeoff gross weight of the helicopter. Record the time on the

hourmeter.

Take-Off gross weight:

Take-Off hourmeter reading:

Set the altimeter to 29.92” Hg (1013.2 millibars) prior to performing the autorotation.

Autorotate with the collective control firmly held against the down stop with an airspeed

of 50 KIAS.

WARNING

Do not allow the rotor to overspeed when performing autorotation

checks. Progressively lengthen both main rotor pitch link rod

ends until full down collective can be obtained without over-

speeding the rotor.

Take at least 3 RPM readings at 500 to 1000 foot altitude intervals.

Record the following in-flight data:

Hourmeter

Pressure

Test %

Test #

Reading

OAT

Altitude

RPM

Page 18.12

Chapter 18 Track and Balance

25 OCT 2010

18-16 Autorotational RPM Adjustment (continued)

3. After test flight, determine the following:

Test #

Elapsed Time (in-flight hourmeter reading

minus take-off hourmeter reading):

Pounds of Fuel Consumed

(elapsed time x 140 lb/hr):

Test Gross Weight

(take-off gross weight minus fuel consumed):

Test Longitudinal Center of Gravity:

Chart % RPM*:

Test % RPM (from in-flight data):

RPM Correction

(chart % RPM minus test % RPM):

*Perform step 4 to obtain value.

4. Refer to Figure 18-5. To find Chart % RPM, perform the following:

a. Start at outside air temperature, and draw a vertical line up to pressure altitude.

b. Draw a horizontal line from pressure altitude to rotorcraft gross weight at time of

autorotation.

c. Draw a vertical line down from autorotation gross weight to required auto RPM.

5. Adjust pitch links based on average RPM correction required. Lengthen both pitch links

to decrease RPM if test RPM is greater than chart RPM; shorten both pitch links to

increase RPM. One full rod end turn will change RPM approximately 3½%. Adjust both

pitch links exactly the same so track will not be affected.

6. Repeat previous steps as required until the RPM correction is ± 1% of chart RPM.

25 OCT 2010

Chapter 18 Track and Balance

Page 18.13

18-20 Tail Rotor Dynamic Balance

NOTE

Calibrate track and balance equipment per manufacturer's

recommendation, at least once a year, or if equipment is

dropped, misused, or calibration is suspect.

NOTE

The Chadwick-Helmuth Vibrex system, the TEC ACES system,

the Dynamic Solutions Systems’ MicroVib system, or equivalent

equipment is required to perform dynamic rotor balancing and

in-flight track checks.

18-21 Preparing Helicopter for Tail Rotor Dynamic Balance

NOTE

Use the following balance procedures in conjunction with

approved equipment manufacturer’s balancing instructions.

WARNING

Ensure cable(s) cannot entangle tail rotor.

Clean tail rotor blades per Section 20-10. Inspect tail rotor rod ends and elastomeric

bearings per Sections 5-33 and 5-34.

Track tail rotor blades per Section 64-10.

Refer to Figure 18-6. If using photocell to obtain clock angle, install a target tape

spanwise on inboard side of one arm of tail rotor hub; if using Strobex, install a target

tape spanwise on outboard side of hub.

Using appropriate hardware, attach bracket(s) to vibration transducer, and photocell, if

used. Secure bracket to tail rotor gearbox output shaft cap at forward, top attachment

bolt. Orient vibration transducer vertically.

Connect cable(s) to transducer, and photocell, if used. Route cable(s) forward and into

cabin; wrap around tailcone several times, and secure with duct tape. If using Strobex,

route cable to a position located approximately 20 feet to left of tail rotor. Place

sandbags (or similar) on cable to prevent cable movement.

Connect cable(s) to balancer. Verify security of installation.

Chapter 18 Track and Balance

Page 18.17

DATE

SERIAL NO.

PAGE

PITCH HORN-TO-PITCH LINK FASTENER (CHORDWISE) WEIGHTS

BLADE-TO-HUB OUTBOARD FASTENER (SPANWISE) WEIGHTS

(1) NAS1149F0463P Washer

(2)

NAS1149F0432P Washers

(1) C141-23 Washer

(3.5)

NAS1149F0663P Washers

(1) A214-3 Washer

(3.5)

NAS1149F0432P Washers

(1) C141-24 Washer

(7)

NAS1149F0663P Washers

(1) A141-14 Washer

(5)

NAS1149F0432P Washers

(2) NAS1149F0632P

(1)

NAS1149F0663P Washer

BALANCE

CLOCK

IPS

ADJUSTMENT:

CLOCK

IPS

ADJUSTMENT:

CLOCK

IPS

ADJUSTMENT:

CLOCK

IPS

ADJUSTMENT:

FIGURE 18-7 TAIL ROTOR DYNAMIC BALANCE CHART

Page 18.18

Chapter 18 Track and Balance

18-22 Ground Checks

NOTE

Run-up and shutdown helicopter throughout procedure as

required per R66 Pilot's Operating Handbook (POH) Section 4.

NOTE

Use the following balancing procedures in conjunction with

approved equipment manufacturer’s balancing instructions.

WARNING

Tail rotor balancing equipment must be removed for flight.

Prepare helicopter for tail rotor dynamic balance per Section 18-21.

Make a photocopy of Figure 18-7; use copy to record ground check data. Check tail rotor

balance at 99-101% RPM on ground and record data. Maximum vibration allowance is

0.2 ips (inches per second).

(If using Chadwick-Helmuth system, set Function Knob on

Balancer to appropriate channel, set balancer RPM Range knob to X10, and set RPM to

231. During ground run, view tail rotor assembly target tape through Strobex and tune

Balancer by adjusting RPM dial.)

Adjust balance per Section 18-23 as required, record change, and recheck balance.

Repeat steps 2 and 3 as required until tail rotor balance is within limits.

Remove track and balance equipment. Install tail rotor gearbox output shaft cap forward,

top attachment bolt and special torque per Section 20-33. Install 0.032-inch diameter

lockwire securing cap retaining hardware and safety in pairs.

WARNING

A rotor which is smooth after balancing but goes out of balance

within a few flights is suspect and must be examined by RHC

before further flight.

18-23 Balance Adjustment

Refer to R66 Illustrated Parts Catalog (IPC) Figure 64-1. Refer to Section 64-11 for tail

rotor assembly static balance procedure.

A. Pitch Horn-to-Pitch Link Fastener (Chordwise Balance Adjustment)

Chordwise dynamic balance is achieved by varying NAS6604 bolt length and nut-side

washers on tail rotor blade pitch horn-to-pitch link fastener. Select bolt length and

washers as required to balance tail rotor assembly chordwise per Figure 18-7, and

to meet torque requirements per Section 20-30. Standard torque nut and palnut per

Section 20-32, but do not torque stripe.

B. Blade-to-Hub Outboard Fastener (Spanwise Balance Adjustment)

Spanwise dynamic balance is achieved by varying nut-side washer size on tail rotor

blade-to-hub outboard fastener. Four washers are required under outboard nuts. Select

a combination of four washers to balance tail rotor assembly spanwise per Figure 18-7,

placing largest washers closest to hub assembly. Standard torque nuts and palnuts per

Section 20-32, but do not torque stripe.

25 OCT 2010

Chapter 18 Track and Balance

Page 18.19

18-30 Main Rotor Flight Control Rigging

NOTE

Refer to Section 5-33, and Figures 5-1 & 5-2 for standard rod

end adjustment procedures. Refer to Section 18-13 for main

rotor pitch link adjustment procedure.

For collective adjustments, both pitch links must be adjusted

exactly the same.

Track and balance helicopter per Sections 18-10 & 18-20 as

required after adjusting flight controls.

NOTE

Cyclic stick travel is non-adjustable. Travel is limited by A211-4

stop attached to the cyclic box assembly.

Collective stick travel is non-adjustable. Travel is limited by

A333-1 stop integral to the collective stick friction assembly.

Perform the following check to verify collective travel and

swashplate travel do not interfere.

Install MT559-1 rigging blocks inside A211-4 cyclic stick stop. Position collective stick

full down. Apply cyclic and collective stick frictions.

Rig the following push-pull tube assemblies and fork assembly, located between keel

panels, to the noted rod end center-to-center dimensions:

PART NUMBER

DIMENSION

C121-1

= 51.15 ± 0.03 inches

F121-1

= 32.36 ± 0.03 inches

G205-1

= 5.40 ± 0.03 inches

Adjust length of F121-1 tube so that with collective full up, there is a 0.50 inch gap

between G205-1 yoke and F315-1 support.

Refer to Figure 18-8. Position MT146-4 swashplate rigging blocks between lower, non-

rotating swashplate and C281-1 fitting. Refer to Section 5-33, and adjust push-pull

tube rod ends until aligned with swashplate attachment holes.

Cut and discard ty-rap(s) as required to lift swashplate boot.

Position collective stick full up. Verify top of C201-1 ball assembly is flush with top

edge of C208-1 tube within 0.030 inch. Refer to Section 5-33, and adjust push-pull

tube rod ends in or out equally to raise or lower swashplate as required.

Refer to Figure 18-9. Adjust swashplate A205-5 lower fork assembly (non-rotating) to

3.70 ± 0.03 inch, and upper fork assembly (rotating) to 3.85 ± 0.03 inch.

25 OCT 2010

Chapter 18 Track and Balance

Page 18.21

18-40 Main Rotor Blade Angle Rigging

A. Procedure

NOTE

Refer to Section 5-33, and Figures 5-1 & 5-2 for standard rod

end adjustment procedures. Refer to Section 18-13 for main

rotor pitch link adjustment procedure.

1. Perform main rotor flight control rigging per Section 18-30.

2. Level helicopter laterally and longitudinally via main rotor hub per Section 8-12.

3. Perform collective travel rigging per Section 18-41 Parts A and B.

4. Perform cyclic travel rigging per Section 18-42 Parts A, B, C, and D.

5. Perform track and balance per Section 18-10 as required.

Measuring Blade Angles

NOTE

Hydraulic flight controls must be pressurized while measuring

blade angles.

WARNING

Never adjust flight controls while hydraulics are pressurized.

Hydraulic forces can cause injury.

Teeter main rotor hub until blade tips are approximately level. Place a tracking stick

at the end of one blade and mark the tip height. Rotate the rotor 180° and mark the

opposite blade’s tip height. Teeter main rotor hub as required until blade tips are level

within 1 inch.

Refer to Figure 18-10. Using felt tip marker, mark upper surface of both main rotor

blades 49.5 inches inboard of seam between blade tip and tip cover. Lay 1-inch wide

length of masking tape chordwise on each blade, centered over marking. Mark each

rotor blade with a different color designation, such as red and blue.

Hang a 6-inch length of masking tape from one blade tip for reference. Zero Kell-Strom

KS113 propeller protractor (or equivalent) on top of the main rotor hub, parallel to the

teeter hinge bolt, at location marked “LEVEL HERE”. During zeroing, point protractor

face toward the blade with hanging tape. When taking blade angle readings, always

point protractor face toward the blade with hanging tape.

Position MT525-1 fixture on top of the blade’s tape at 49.5 inches, and tight against

the leading edge. Position protractor on top of fixture, point protractor face toward the

blade with hanging tape, and take blade angle reading.

Chapter 18 Track and Balance

Page 18.23

Robinson Helicopter Company RTR 660 (Number R00015LA). Maintenance Manual (2012) - page 2