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

CHAPTER 96

ELECTRICAL SYSTEM

96-00 Description

CAUTION

The installation of electrical devices can affect the accuracy

and reliability of the electronic tachometer.

A 28-volt DC electrical system is standard. Primary system components are a sealed lead-acid

battery, a starter-generator, and a generator control unit. The battery is located beneath the

left front seat or in a compartment in the left side of the baggage compartment.

The circuit breaker panel is on the ledge just forward of the left front seat. Breakers are

marked to indicate function and amperage and are of the push-to-reset type.

The battery switch controls the battery relay which connects the battery to the electrical

system. A wire protected by a fuse near the battery bypasses the battery relay to allow the

tachometers and clock to receive battery power with the battery switch OFF.

The avionics switch controls power to avionics. This allows avionics to be switched OFF via

a single switch. Having sensitive electrical equipment off when the generator is switched ON

protects against voltage spikes.

An ammeter indicates total generator output. A digital voltmeter which reads main bus voltage

at the circuit breaker panel is incorporated as part of the OAT indicator. Normal indication is

27.3 to 28.7 volts with the generator ON.

A generator control unit (GCU) controls starter-generator function. Below 58 percent N₁ RPM,

the GCU is in start mode regardless of generator switch position. Above 58 percent, the GCU

automatically switches to generate mode. The generator switch should normally be off for

starting to prevent applying generator load to the engine before reaching idle RPM.

If the GEN annunciator illuminates in flight, turn off nonessential electrical equipment and

switch generator to reset (momentary position) and then ON. If the GEN annunciator remains

illuminated, land as soon as practical.

Chapter 96 Electrical System

Page 96.1

96-10 Battery

NOTE

Refer to Concorde Battery Corporation's Owner/Operator's

Manual, and Instruction for Continued Airworthiness for battery

maintenance procedures.

CAUTION

B237-7 battery (standard; forward and aft) weighs 42 lb and

B237-8 battery (alternate; aft only) weighs

52 lb including

electrolyte. Carefully remove/install battery using handle

provided to prevent injury.

CAUTION

To minimize risk of electrical discharge: When disconnecting

battery, disconnect negative (ground) cable from battery first,

then the positive cable. When connecting battery, connect

positive cable to battery first, then the negative (ground) cable.

A. Disconnecting and Removing Battery

1. Turn BATTERY switch OFF. Refer to Section 6-70.

a. Forward battery: Hinge forward left seat forward and remove F003-11 insulation.

Remove hardware securing F748-1 (battery) cover assembly and remove cover.

b. Aft battery: Open baggage compartment door. Remove hardware securing G248-1

(baggage compartment) cover and remove cover.

2. Remove hardware securing negative (ground) cable to battery negative terminal.

3. Slide nipple away from battery positive terminal and remove hardware securing positive

cable to battery positive terminal. Carefully remove battery.

Installing and Connecting Battery

1. Turn BATTERY switch OFF.

2. a. Forward battery: Hinge forward left seat forward; carefully install B237-7 battery.

b. Aft battery: Open baggage compartment door. Refer to Figure 96-1.

i. If B237-7 battery was removed and B237-8 battery is being installed: Remove

hardware securing G131-1 shim to G249-1 tray and remove shim. Install

hardware securing shim to G131-2 plate as shown. Verify security. Carefully

install B237-8 battery.

ii. If B237-8 battery was removed and B237-7 battery is being installed: Remove

hardware securing G131-1 shim to G131-2 plate. Install hardware securing shim

to G249-1 tray as shown. Verify security. Carefully install B237-7 battery.

iii. If the battery being installed is the same part number as the battery that was

removed: Verify security, proper orientation, and installation of G131-1 shim and

G131-2 plate. Carefully install battery.

Chapter 96 Electrical System

Page 96.3

96-10 Battery (continued)

Verify G131-2 plate just contacts top of battery (holes are slotted). Adjust as required.

Verify battery terminal surfaces are clean to ensure electrical conductivity. Install

positive cable on battery positive terminal and install battery hardware. Special torque

terminal bolt as noted on battery label, and torque stripe per Figure 5-1. Slide nipple

over terminal.

Install negative (ground) cable to battery negative terminal and install battery hardware.

Special torque terminal bolt as noted on battery label, and torque stripe per Figure 5-1.

Refer to Section 6-70.

a. Forward battery: Install F748-1 (battery) cover assembly, and install hardware.

Verify security. Install F003-11 insulation and hinge seat back.

b. Aft battery: Install G248-1 (baggage compartment) cover, and install hardware.

Verify security. Close and latch baggage compartment door.

Aft battery:

If B237-7 battery was removed and B237-8 battery was just installed, revise Weight

and Balance Record in R66 Pilot's Operating Handbook (POH) Section 6 to incorporate

the following data:

Subtract:

Weight

Long. Arm

Long. Moment

Lat. Arm

Lat. Moment

B237-7 Battery

42.00 lb

96.88 in.

4068.96 in.-lb

-20.87 in.

-876.54 in.-lb

Add:

Weight

Long. Arm

Long. Moment

Lat. Arm

Lat. Moment

B237-8 Battery

52.00 lb

96.88 in.

5037.76 in.-lb

-21.73 in.

-1129.96 in.-lb

If B237-8 battery was removed and B237-7 battery was just installed, revise Weight

and Balance Record in R66 Pilot's Operating Handbook (POH) Section 6 to incorporate

the following data:

Subtract:

Weight

Long. Arm

Long. Moment

Lat. Arm

Lat. Moment

B237-8 Battery

52.00 lb

96.88 in.

5037.76 in.-lb

-21.73 in.

-1129.96 in.-lb

Add:

Weight

Long. Arm

Long. Moment

Lat. Arm

Lat. Moment

B237-7 Battery

42.00 lb

96.88 in.

4068.96 in.-lb

-20.87 in.

-876.54 in.-lb

Page 96.4

Chapter 96 Electrical System

96-20 External Power

A 28-volt MS3506-compatible external power receptacle is located inside the right engine cowl

door. When the battery is switched ON, the external power relay and the battery relay both

close, connecting external power to the aircraft electrical system and battery The external

power relay will not close if reverse polarity is provided to the receptacle.

A separate wire from the external power receptacle to the battery bypasses the external

power and battery relays. This wire allows battery charging via the external receptacle with

the battery switch OFF. A 10-amp circuit breaker at the receptacle opens if current exceeds

normal charging levels, and a diode provides polarity protection.

96-30 Starter and Ignition System

A single starter-generator is used for engine starting and electrical power generation. A

generator control unit (GCU) controls starter-generator function. During a start, the GCU

latches the starter on until N₁ reaches 58 percent RPM. Therefore, the pilot is not required to

hold the start button down throughout the start sequence. Above 58 percent N₁ RPM, the GCU

automatically switches out of start mode, but the generator switch should not be switched ON

until idle RPM stabilizes to prevent the generator load from bringing the RPM down.

When the igniter key switch is in the enable position, depressing the start button causes a

normal start sequence with the starter latching on and the igniter firing. Above 58 percent N₁

RPM, the igniter will fire while the start button is depressed.

When the igniter switch is OFF, the engine can be motored by the starter by depressing the

start button without the starter latching or the igniter firing. This is useful for performing

a compressor wash or rinse. If the igniter is switched OFF during a start, the starter will

disengage. If the igniter is switched OFF while the engine is running, the engine will continue

to run; however, this is not recommended.

NOTE

Start button is active when battery switch is ON, even if igniter

switch is OFF. Rotor brake may be left engaged after shutdown

to disable start button.

Chapter 96 Electrical System

Page 96.5

96-40 Lighting System

A red anti-collision light is installed on the tailcone and is controlled by the strobe switch on

the instrument console. Position lights are installed on each side of the cabin and in the tail

and are controlled by the nav lights switch. A light at the top of the windshield and post

lights illuminate the instrument panel. Panel lighting is active when the nav lights switch is

ON and lighting is dimmed via the knob above the nav lights switch. An overhead map light

mounted on a swivel is controlled by an adjacent switch with high and low settings. The map

light may be used for emergency lighting of the instrument panel. An additional cabin light

with an adjacent switch is located just aft of the map light. The map and cabin lights are not

connected to the dimmer circuit.

Two long-life, high intensity discharge (HID) landing lights are installed in the nose. One wide-

angle and one narrow-beam light are used to increase lighted area. The landing light switch is

located on the cyclic center post.

NOTE

Continuous operation of landing and position lights in flight is

recommended to promote collision avoidance.

An optional flashing light may be mounted on the tailcone in addition to the standard anti-

collision light. The optional light is controlled by an additional position on the strobe switch

and may be turned on or off anytime at pilot discretion.

96-50 Annunciator Panel

The annunciator panel consists of illuminated segments located at the top of the main instrument

panel. If a caution or warning condition occurs, the appropriate segment(s) illuminate indicating

the nature of the problem.

The CHIP segments are illuminated by magnetic chip devices in each gearbox which collect

metallic particles in order to complete an electric circuit. The engine gearbox has two magnetic

chip detectors, either of which can illuminate the ENGINE CHIP segment.

The MR TEMP/PRESS segment is illuminated by either the temperature switch or oil pressure

switch at the main gearbox. The ENGINE FIRE segment is illuminated by a temperature switch

in the engine compartment. The ENGINE OIL segment is activated by a pressure switch which

is independent of the oil pressure sender. The ANTI-ICE segment illuminates via a pressure

switch in the engine anti-ice air line. The GEN segment illuminates when the generator is

disconnected from the main electrical bus.

The LOW FUEL segment is illuminated by a float switch in the tank which is independent

of the fuel quantity sender. The FUEL FILTER segment illuminates when a pressure switch

detects excessive pressure drop across the fuel filter. The LOW RPM segment is illuminated

by a sensor measuring driveline speed at the aft end of the main gearbox. A horn sounds

simultaneously with illumination of the LOW RPM segment when rotor speed is below 95%

RPM. The horn is disabled when the collective is fully down.

The COWL DOOR segment is illuminated when the fuel filler cowl door, the right engine cowl

door (which accesses the external power receptacle), or the baggage door is not closed. The

AIR FILTER segment illuminates when pressure drop across the filter opens bypass doors,

allowing unfiltered air to the engine. The EMU (Engine Monitoring Unit) segment indicates the

EMU status with either steady, flashing, or no illumination. The EMU segment will illuminate

only when the test button is depressed.

Page 96.6

Chapter 96 Electrical System

96-50 Annunciator Panel

A push-to-test button on the instrument panel should cause all segments on the annunciator

panel, as well as the ROTOR BRAKE light, to illuminate when depressed. The LOW FUEL

segment takes approximately two seconds before it illuminates due to a time delay in the

circuit.

(The time delay prevents sloshing fuel from giving a false indication.) The EMU

segment takes approximately ten seconds to perform a self-test after the battery is switched

ON before it will illuminate. The test button may be used on the ground or in flight to verify

all circuits are functioning.

96-60 Low Rotor RPM Warning Unit Adjustment

The low rotor RPM warning unit is located inside the upper console, mounted to the left vertical

panel. Two magnets attached to the main gearbox tail rotor driveline output yoke provide an

RPM signal for the warning unit's gearbox-mounted Hall-effect senders. When the collective

is at least 0.2 to 0.4 inch (measured at grip) above the full down position and rotor RPM is

95% or less, the warning unit illuminates the Low RPM annunciator segment and sounds two

warning horns. Fully lowering the collective will silence both horns, but will not extinguish

the annunciator segment. The Low RPM annunciator segment and both horns must remain

off above 95% rotor RPM.

To make an adjustment, remove the plastic plug (from a 3/8-inch diameter hole) in the left-

vertical panel exterior. Adjust screw on back of warning unit (2 turns equals approximately

1% change).

96-70 Audio System

A five-place audio system is standard. An audio control panel allows control of communication

radios, intercom, and stereo-capable auxiliary audio (e.g. music) input.

The system has four modes of operation. In normal mode, all occupants hear incoming and

outgoing radio communications, intercom, and auxiliary audio. The pilot and copilot can both

transmit on the selected radio.

In crew mode, the pilot and copilot are isolated from rear seat occupants. The crew does not

hear rear seat intercom or auxiliary audio and rear seat occupants do not hear crew intercom

or radio communications.

In pilot isolate mode, the pilot is isolated from all other occupants. The copilot is grouped with

the rear seat occupants for intercom and auxiliary audio.

In emergency mode, the pilot transmits and receives on the number one radio only (regardless

of audio panel switch position). All other audio is disabled.

The first three modes are selectable via the audio control panel. Emergency mode occurs if

power to the panel is lost. In addition to the mode control, the audio panel has controls for

squelch, volume, and selection of transmit and receive radios. A detail description of these

controls can be found in the audio system operation manual.

Headset jacks are located in the ceiling near each seat. Pilot and copilot intercom and transmit

are controlled via trigger switches on the cyclic grips. The trigger has two detents; the first

detent activates the intercom and the second detent transmits. Additional intercom buttons

are located on the forward side of the rear seats and on the left forward floor. Intercom may

also be set to be voice activated. Auxiliary audio may be plugged in to a jack on the forward

face of the circuit breaker panel. In normal mode, auxiliary audio is automatically muted during

radio communication.

Chapter 96 Electrical System

Page 96.7

96-80 Engine Monitoring Unit (EMU)

Refer to Section 71-43 for EMU maintenance procedures.

The Engine Monitoring Unit (EMU) is a digital recording device mounted behind the right rear

seatback panel. The EMU continuously monitors N₁, N₂, engine torque, and MGT. EMU

status is indicated by the EMU segment on the annunciator panel. The EMU segment will

only illuminate while the annunciator panel test button is depressed. The EMU requires

approximately ten seconds to initialize after the aircraft battery is switched ON. Once

initialization is complete, steady illumination of the annunciator means normal EMU operation.

A slowly flashing indication (once every two seconds) is given if the EMU detects a fault in its

senders or circuitry. A fast flashing indication (four times per second) is given if the EMU has

detected an exceedance. A fault or exceedance indication should be investigated and reset by

a qualified mechanic prior to further flight.

The EMU records exceedances of Rolls-Royce engine limits, not airframe operating limits as

given in Section 2. The EMU will record an exceedance if any of the following are exceeded:

MGT during start:

999°C, or 927°C for 1 second, or 810°C for 10 seconds.

MGT engine running:

843°C, or 782°C for 6 seconds, or 706°C for 5 minutes.

N₁:

106%, or 105% for 15 seconds.

N₂:

110%, or 105% for 15 seconds.

78% to 88% for 60 seconds over 38% torque.

Torque:

122% for 15 seconds, or 104% for 5 minutes.

The EMU also records a start cycle when N₁ exceeds 30% and MGT is at least 343°C.

The EMU is intended to be used only as a maintenance aid. It is the pilot's responsibility to

report any observed exceedances and the operator's responsibility to maintain a record of

engine starts and time in service.

96-90 Emergency Locator Transmitter (ELT)

Refer to Section 25-61 for ELT programming instructions and maintenance procedures.

The Emergency Locator Transmitter (ELT) installation consists of a transmitter with internal

battery pack, an external antenna, and a remote switch/annunciator. The transmitter is

mounted to the upper steel tube frame and is accessible through the spring loaded air intake

door in the right-side cowl. The remote switch/annunciator is located left of the cyclic stick.

The ELT is operated by a switch on the transmitter and by the remote switch. The transmitter

switch has been set in the ARM position at installation and should always be in this position

for flight. The remote switch/annunciator is a three position switch with indicator light. This

switch should be in the ARMED position for flight. With both switches set to armed, the ELT

will begin transmitting when subjected to a high "G" load. When the unit is transmitting, the

red indicator light illuminates.

Moving the remote switch to ON activates the transmitter. Use the ON position if an emergency

landing is imminent and time permits.

If the ELT is inadvertently activated, use the momentary RESET & TEST position of the remote

switch to stop transmission and reset the unit. The red indicator will extinguish when unit is

reset.

For more detailed instructions on ELT operation, maintenance, and required tests, refer to

manufacturer's instructions supplied with the unit.

Page 96.8

Chapter 96 Electrical System

96-100 Electrical Load Analysis

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

COMPONENT

QTY

AMPS EACH

TOTAL

MAIN BUS

WARNING LT PANEL

0.006

0.320

0.006

0.320

ROTOR BRAKE LT

---

0.044

0.000

0.044

MAPLIGHT

0.020

INTERIOR DOME LT

0.020

OAT GAGE

0.150

ENGINE TORQUEMETER

0.050

INSTRUMENT CLUSTER

0.375

MOP SENDER

0.025

TORQ SENDER

0.025

LOW RPM UNIT W/HORN

0.045

0.160

0.045

0.160

AA12S-600 AUDIO PANEL

1.000

N₂ GOVERNOR SYSTEM

0.000

0.087¹

N₂

GOV ACTUATOR @ 12V

---

0.150

0.000

0.087¹

N₂ GOV RELAY @ 12V

---

0.010

ANTI-ICE SOLENOID

0.670

HEATED PITOT

4.000

ENGINE HOUR METER

0.015

0.030

HYD CONTROL SOLENOID

---

0.800

0.000

0.800

ENGINE MONITORING UNIT

0.180

AVIONICS RELAY

---

0.060

0.000

0.060

LOW FUEL RELAY

---

0.010

0.000

0.010

WARNING LIGHT TEST CB

---

0.020

0.000

0.020

TACH PWR TEST RELAY

---

0.060

0.000

0.060

BOSE HEADSET

0.025

0.500

0.125

2.500

AUX POWER PLUG

2.000

SUBTOTAL (MAIN BUS)

8.721

12.606

Chapter 96 Electrical System

Page 96.9

96-100 Electrical Load Analysis (continued)

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

COMPONENT

QTY

AMPS EACH

TOTAL

LIGHTS BUS

LANDING LT BALLAST

1.600³

5.250³

3.200

10.500

LANDING LT RELAY

0.060

CIRCUIT BREAKER LTS

0.001³

0.001

INSTRUMENT LT

0.500⁵

POST LTS

0.040¹

0.080

INTERNAL AVIONICS LTS

0.100¹

0.600

VERT CARD COMPASS LT

0.050³

0.050

POSITION LT RH (GREEN)

0.250

POSITION LT LH (RED)

0.250

POSITION LT TAIL (WHT)

0.300

STROBE LIGHT

0.670

3.000

0.670

3.000

SUBTOTAL (LIGHTS BUS)

5.961

15.591

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

COMPONENT

QTY

AMPS EACH

TOTAL

AVIONICS BUS

KY196A COM

1.000

5.000

1.000

5.000²

GNC 420W GPS/COM

1.215

4.200

1.215

1.215²

GNS 530AW GPS/COM/NAV

1.415

4.400

1.415

1.415²

GTX 330 XPDR

1.640

9.090

1.640

9.090

BLIND ENCODER

0.600

AM/FM/CD RCVR

1.500

KR87 ADF RCVR

0.429

KR22 MARKER BEACON

0.040

0.500

0.040

0.500

AVIONIC BLOWER

0.180

PILOT AV BLOWER

0.100

ELT⁴

---

HSI (PICT NAV SYSTEM)

1.730

ATTITUDE HORIZON

0.270

0.700

0.270

0.700

TURN COORDINATOR

0.350

RADAR ALTIMETER

0.727

SUBTOTAL (AVIONICS BUS)

11.196

23.536

Page 96.10

Chapter 96 Electrical System

96-100 Electrical Load Analysis (continued)

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

COMPONENT

QTY

AMPS EACH

TOTAL

TACH BUS

N₂ TACH (INCL REG)

0.022¹

N₂ TACH @ 13.75V

0.035

ROTOR TACH (INCL REG)

0.022¹

ROTOR TACH @13.75V

0.035

SUBTOTAL (TACH BUS)

0.044

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

COMPONENT

QTY

AMPS EACH

TOTAL

OTHER EQUIPMENT

TACH RELAY

0.060

CLOCK (DIGITAL)

0.003

BATTERY RELAY

0.250

6.000

0.250

6.000

START/GEN RELAY

0.250

6.000

0.250

6.000

GEN LT RELAY

0.010

GEN CONTROL UNIT

0.200⁴

2.000⁵

0.200

2.000

IGNITION EXCITER

---

1.500

0.000

1.500

EXTERNAL PWR RELAY²

0.250

6.000

---

BAGGAGE COMPARTMENT

0.020

---

LT²

SIGHT GLASS LED²

0.020

---

LATCHING START RELAY³

0.060

---

STARTER-GENERATOR³

---

231.06

---

SUBTOTAL (OTHER)

0.773

15.573

TOTAL (MAIN + LIGHTS + AVIONICS + TACH + OTHER)

26.70

67.357

STARTER-GENERATOR MARGIN (160-AMP MAX)

+133.30

+92.657

Chapter 96 Electrical System

Page 96.11

99-20 Illustrations and Tasks

Item

Part No.

Name and Reference Section

MT054-1

Main Rotor Gearbox Drain Assembly - Quick Disconnect

REFER TO SECTION 12-11 MAIN ROTOR GEARBOX SERVICING

MT122-6

Micrometer Assembly - Main Rotor Hub, Bolt Stretch

REFER TO SECTION 62-10 MAIN ROTOR BLADES

MT146-4

Blocks - Swashplate Rigging (set of 2)

REFER TO SECTION 18-30 MAIN ROTOR FLIGHT CONTROL RIGGING

MT147-1

Bleed Tool - Main Rotor Blade Spindle

REFER TO SECTION 12-51 MAIN ROTOR BLADE SPINDLE SERVICING

MT179-4

Balancing Bar - Tail Rotor Assembly Static Balance

REFER TO SECTION 64-11 TAIL ROTOR ASSEMBLY STATIC BALANCE

MT260-6

Tail Rotor Drive Shaft Runout Attachments Kit

REFER TO SECTION 65-21 TAIL ROTOR DRIVE SHAFT RUNOUT

MT329-6

Plug - Main Rotor Hub Bearing Installation

REFER TO SECTION 62-21 MAIN ROTOR HUB BEARING REPLACEMENT

MT352-1

Main Rotor Blade Trim Tab Gage

REFER TO SECTION 18-13 MAIN ROTOR BLADE TRACK ADJUSTMENT

MT354-4

Teeter Moment Tool

REFER TO SECTION 62-32 ADJUSTING HINGE FRICTION

10.

MT357-2

0.375-inch diameter Reamer

VARIOUS; REAM BORE AFTER INSTALLATION OF A139-1 BEARING TO 0.376/0.375-INCH DIA

11.

MT357-3

0.156-inch diameter Steel Drill

REFER TO SECTION 62-33 DRILLING NUTS AND BOLTS

12.

MT357-4

Hex Driver (Snap-On Part No. FABL8)

REFER TO SECTION 65-40 TAIL ROTOR GEARBOX

13.

MT357-5

Torque Adapter (Snap-On Part No. FRDH101)

REFER TO SECTION 65-40 TAIL ROTOR GEARBOX

14.

MT359-1

Spring Scale (0-30 lb)

REFER TO SECTION 62-32 ADJUSTING HINGE FRICTION AND SECTION 67-22 COLLECTIVE FRICTION

15.

MT384-1

Hydraulic Test Pump (U.S / Canada / Mexico - 110-volt)

REFER TO SECTION 12-34 HYDRAULIC SYSTEM BLEEDING

16.

MT384-2

Hydraulic Test Pump (Outside North America - 220-volt)

REFER TO SECTION 12-34 HYDRAULIC SYSTEM BLEEDING

Chapter 99 Special Tools

Page 99.3

99-20 Illustrations and Tasks (continued)

Item

Part No.

Name and Reference Section

17.

MT525-7

Main Rotor Blade Rigging Fixture

REFER TO SECTION 18-40 MAIN ROTOR BLADE ANGLE RIGGING

18.

MT525-9

Tail Rotor Blade Rigging Fixture

REFER TO SECTION 18-60 TAIL ROTOR BLADE RIGGING

19.

MT526-8

Bender Assembly - Trim Tab, Main Rotor Blade

REFER TO SECTION 18-13 MAIN ROTOR BLADE TRACK ADJUSTMENT

20.

MT527-1

Helicopter Lifting Fixture

REFER TO SECTION 7-20 HOISTING

21.

MT548-8

Fitting (Engine Hoist Adapter)

REFER TO SECTION 71-10 ENGINE

22.

MT549-1

Spacer - Spindle Boot (set of 2)

REFER TO SECTION 62-10 MAIN ROTOR BLADES

23.

MT549-2

Plate - Spindle Boot

REFER TO SECTION 62-10 MAIN ROTOR BLADES

24.

MT556-11

Kit Tools - Tail Rotor Hub Bearing Replacement

REFER TO SECTION 64-41 TAIL ROTOR HUB BEARING REPLACEMENT

25.

MT643-1

Support Weldment - Main Rotor Hub Bearing Installation

REFER TO SECTION 62-21 MAIN ROTOR HUB BEARING REPLACEMENT

26.

MT569-2

Guide Assembly - Drill (main rotor hub nut)

REFER TO SECTION 62-33 MAIN ROTOR ASSEMBLY DRILLING NUTS AND BOLTS

27.

MT759-1

Blocks - Cyclic Rigging

REFER TO SECTION 18-30 MAIN ROTOR FLIGHT CONTROL RIGGING

28.

2020HR

ACES Probalancer Analyzer (or equivalent dynamic balancer)

REFER TO SECTION 18-10 MAIN ROTOR TRACK AND BALANCE

29.

MT850-1

Engine Stand Assembly

REFER TO SECTION 71-10 ENGINE

30.

AN970-4

Washer - Tap Test Tool (or 1965 or later U.S. quarter dollar coin in

good condition; not shown)

REFER TO SECTIONS 62-40 MAIN ROTOR BLADE INSPECTION AND REPAIR AND 64-30 TAIL ROTOR

BLADE INSPECTION AND REPAIR

Chapter 99 Special Tools

Page 99.5

REVISION LOG

The R66 Maintenance Manual (MM) list of effective pages and effective dates are given below.

If a previously issued page is not listed below, it is no longer an effective page and must be

discarded. The issue or revision date is in bold at the top of each revision log page.

Please visit www.robinsonheli.com , under the Publications tab, to verify the issue or revision

date is current. A subscription service form is included in the front of this manual.

Page

Date

Page

Date

Page

Date

4.ii

25 OCT 2010

5.22

4.1

SEP 2011

5.23

iii

4.2

SEP 2011

5.24

4.3

25 OCT 2010

5.25

4.4

25 OCT 2010

5.26

4.5

25 OCT 2010

5.27

vii

4.6

25 OCT 2010

5.28

viii

4.7

25 OCT 2010

5.29

4.8

25 OCT 2010

5.30

5.31

5.i

5.32

xii

5.ii

5.33

xiii

5.1

5.34

xiv

5.2

5.35

5.3

5.36

xvi

5.4

5.36A

xvii

5.5

5.36B

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5.6

5.36C

5.7

5.36D

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5.38

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18.27

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28.9

25 OCT 2010

18.28

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28.10

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18.29

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18.30

21.6

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21.13

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52.5

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52.6

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62.4

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52.7

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62.23

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62.1

25 OCT 2010

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67.1

MAR 2012

71.10

95.ii

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MAR 2012

71.11

95.1

25 OCT 2010

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25 OCT 2010

71.12

95.2

25 OCT 2010

67.4

25 OCT 2010

71.13

95.3

25 OCT 2010

67.5

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71.14

95.4

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67.6

25 OCT 2010

71.15

95.5

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95.6

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25 OCT 2010

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95.7

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25 OCT 2010

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67.15A

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67.19

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67.21

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67.22

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67.23

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98.i

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79.1

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98.5

71.4

79.5

98.6

71.5

79.6

98.7

71.6

79.7

98.8

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98.9

71.8

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95.i

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98.11

Chapter 100 Revision Log

Page 100.5

Robinson Helicopter Company RTR 660 (Number R00015LA). Maintenance Manual (2012) - page 6