Robinson R22 Helicopter. MAINTENANCE MANUAL (2018)

33-110 Troubleshooting (continued)

B. General (continued)

TROUBLE

PROBABLE CAUSE

CORRECTION

Starter kicks back while

Retard breaker contact in engine

Measure retard breaker lead con-

cranking; may cause broken

left magneto pushed out or no

nection. Must be 0.609 in. ±

starter or starter ring gear

connection between lead and

0.10 in. There must be a small

magneto contact

amount of springback which into

magneto.

Incorrect ignition vibrator wiring

Trace ignition vibrator wiring

from ignition switch to magneto.

Correct as required.

Bad ignition switch (See RHC

Replace ignition switch

Service Letter R22 SL-29)

Bad ignition vibrator

Replace vibrator

Incorrect internal magneto re-

Correct as required. Consult

tard breaker timing. Engine left

TCM Aircraft Products literature.

magneto

Impulse coupling starting assist

Replace impulse coupling with

ignition vibrator starting assist.

RHC KI-4.

OCT 2018

Chapter 33 Electrical System

Page 33.15

33-110 Troubleshooting (continued)

C. Clutch Actuator Electrical Troubleshooting

CLUTCH LIGHT

TROUBLE

PROBABLE CAUSE

OFF

Disengaged actuator will

Motor assembly seized

not engage

Motor fuse blown (1½-amp)

Open circuit in motor wiring

Overtravel switch assembly tripped

No voltage at circuit breaker

Circuit breaker tripped

Spring switch open (normally closed)

-88 wire not grounded

Engaged actuator will not

Motor assembly seized

disengage

Motor fuse blown (1½-amp)

Open circuit in motor wiring

Overtravel switch assembly tripped

No voltage at circuit breaker

Circuit breaker tripped

Up limit switch stuck (normally closed)

-88 wire not grounded

Clutch light flickers in flight

Actuator column spring uncalibrated

A190 drive belts mismatched

Lower drive sheave improperly torqued

A184 or A181 bearing running rough

Clutch light comes on for 1-6 seconds in flight

Normal operation of actuator as it retensions drive belts

Clutch light comes on for more than 6

Drive belts stretched beyond limit of actuator over-

seconds in flight

travel switch. Belts must be replaced.

Actuator overtravel switch activated by outside force

Page 33.16

Chapter 33 Electrical System

OCT 2018

33-110 Troubleshooting (continued)

D. Electrically Powered Instrument Calibration Values

Using Vibrex 2000 balancing equipment (or similar) capable of displaying ± 1 rpm

resolution and calibrated within one year, verify tachometer accuracy per following

tables. Connect equipment in accordance with §§ 10.221 and 6.240 (use photocell

instead of Strobex per Figure 6-4A). Operate aircraft at noted tachometer indications

and verify engine and rotor rpms as specified. Tachometer needles are 1% wide.

A792-x Dual Tachometer

Tachometer indication

Engine RPM

Rotor RPM

97%

2471-2476

494-495

100%

2548-2552

509-510

104%

2649-2655

529-530

The rotor tachometer may be adjusted per § 33-50. No other adjustments are

permitted. If tachometer does not meet accuracy tolerance then it must be replaced

or returned to RHC for repair.

A058-5 Carb. Air Temp. Probe

A604-2 Carb. Air Temp. Gage at 13.7 Vdc;

0° = 89.68/91.08 ohms

77.40 ohms = -30° ± 2°C

15° = 95.67/98.07 ohms

81.73 ohms = -20° ± 1.75°C

16° = 96.10/98.50 ohms

86.05 ohms = -10° ± 1.5°C

17° = 96.54/98.94 ohms

90.38 ohms =

0° ± 1°C

18° = 96.97/99.37 ohms

94.71 ohms =

10° ± 1.5°C

19° = 97.40/99.80 ohms

99.03 ohms =

20° ± 1.75°C

20° = 97.83/100.23 ohms

103.36 ohms =

30° ± 2°C

21° = 98.27/100.67 ohms

22° = 98.70/101.10 ohms

23° = 99.13/101.53 ohms

24° = 99.56/101.96 ohms

25° = 100.00/102.40 ohms

Example: Replacing the carburetor air temperature probe with a ¼ to 1-watt 100-ohm

resistor should result in an indication of approximately 21°C (measure exact resistor

value & refer to above). A probe dipped in a Styrofoam cup full of crushed ice

and water should indicate 90.38 ohms resistance per above table. Probe installation

torque is 3 to 4 inch-pounds; over-torquing probe will result in damage.

OCT 2018

Chapter 33 Electrical System

Page 33.17

33-110 Troubleshooting (continued)

D. Electrically Powered Instrument Calibration Values (continued)

Following instrument cluster gages are calibrated at 20 to 25 degree angle from horizontal.

Fuel level senders should have 90 ± 2 ohms resistance when fully up (full fuel) and 0

to 0.5 ohm when fully down (no fuel). Perform fuel sender calibration per § 12.410

whenever sender is replaced, or if factory-set fuel gage potentiometers have been

disturbed. On backside of each fuel gage are “Null” and “Gain” potentiometer screws,

covered with aluminum tape pressed against the screw heads to prevent rotation.

“Null” potentiometer is adjusted so gage indicates empty at 0.7 ohm sender circuit

resistance; “Gain” potentiometer is adjusted so gage indicates half at 42 ohms sender

circuit resistance. Calibration values are:

Fuel Quantity Gages 6246-00473 (14V)

0.70 ohm = E (empty) -1, +0 pointer width

21.20 ohms =

1/4 full ± 1

pointer width

42.00 ohms =

1/2 full ± 1

pointer width

67.50 ohms =

3/4 full ± 1

pointer width

90.00 ohms =

F (full) ± 1

pointer width

Ammeter 6246-00468 (14V)

-104 mV =

-70 amps ± 1 pointer width

-52 mV =

-35 amps ± 1 pointer width

0 mV =

0 amps ± ¼ pointer width

+52 mV = +35 amps ± 1 pointer width

+ 104 mV = +70 amps ± 1 pointer width

CHT Probe 3080-38 (14V)

CHT Gage 6246-00088 (14V)

200°F = 745 ohms

745 ohms = 200 degrees F ± 1 pointer width

475°F =

38 ohms

110 ohms = 350 degrees F ± 1 pointer width

500°F =

32 ohms

34 ohms = 500 degrees F ±% pointer width

Oil Pressure Sender

115-psi redline Oil Pressure Gage

B308-1 (14V)

6246-00647 (14V)

0 psi =

5-13 ohms

9 ohms =

0 psi ± 1 pointer width

29 psi =

48-57 ohms

46 ohms =

25 psi ± 1 pointer width

58 psi =

84-94 ohms

84 ohms =

55 psi ± 1 pointer width

87 psi = 119-131 ohms

131 ohms =

95 psi ± 1 pointer width

115 psi = 145-161 ohms

152 ohms = 115 psi ± 1 pointer width

Page 33.18

Chapter 33 Electrical System

OCT 2018

33-110 Troubleshooting (continued)

D. Electrically Powered Instrument Calibration Values (continued)

Older, 100-psi red line Oil Pressure Gage

6246-00089 (14V)

0 psi

= 10.0 ohms

25 psi

= 46.5 ohms

60 psi

= 90.0 ohms

90 psi

= 125.5 ohms

100 psi

= 137.0 ohms

Oil Temperature Sender

Oil Temperature Gage

A760-1 (14V)

6246-00090 (14V)

100°F = 497 ohms

903.5 ohms

= 75°F ± 1 pointer width

150°F = 179 ohms

100.0 ohms

= 180°F ± 1 pointer width

200°F = 72 ohms

36.0 ohms

= 245°F ± 1 pointer width

250°F = 34 ohms

OCT 2018

Chapter 33 Electrical System

Page 33.19

33-120 Electrical Load Analysis

To calculate the total electrical load for a specific helicopter, identify all items of equipment

installed on the helicopter from the table below and sum the corresponding continuous and

intermittent loads.

Maximum continuous alternator load is given in the table below:

System Voltage

Alternator Rating

Maximum Continuous Load

14V

60 amp

54 amps

Intermittent loads are provided for reference.

Alternately, the electrical load may be measured directly at the battery output terminal with

the alternator switched off and all other equipment turned on. The measured load may be

scaled by the ratio of battery voltage to nominal system voltage to obtain a value that is

compared with the alternator load limit.

WARNING

Field (non-factory) installation of electronic equipment can

be hazardous. Due to the compactness of the console and

tunnel containing the controls and wire bundles, installation

of any additional wires can interfere with flight controls.

Electronic tachometers, warning systems, and navigation

equipment essential to flight are sensitive to interference from

other electrical devices. The reliability and accuracy of the

tachometers is essential for safe operation of the helicopter,

and installation of an electrical device not tested and approved

by RHC may result in a hazardous condition.

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

EQUIPMENT

QTY

AMPS EACH

TOTAL

MAIN BUS

ESSEX BATTERY RELAY

0.75

KISSLING BATTERY RELAY

0.35

ALTERNATOR FIELD

2.40

AVIONICS RELAY

0.13

ENGINE GAGE CLUSTER

0.60

HOURMETER

0.03

CARB AIR TEMP

0.13

AMMETER

0.50

DIGITAL OAT GAGE

0.15

MAP LIGHT

0.00

0.58

0.00

0.58

WARNING LIGHTS

0.00

0.08

0.00

0.64

FULL THROTTLE CAUTION LIGHT

0.00

0.08

0.00

0.08

Page 33.20

Chapter 33 Electrical System

OCT 2018

33-120 Electrical Load Analysis (continued)

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

EQUIPMENT

QTY

AMPS EACH

TOTAL

MAIN BUS (continued)

RPM GOVERNOR MOTOR

0.00

1.50

0.00

1.50

BELT TENSION ACTUATOR

0.00

1.20

0.00

1.20

AUX POWER PLUG (MAX)

10.00

HEATER BLOWER

7.50

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

EQUIPMENT

QTY

AMPS EACH

TOTAL

TACH BUS

DUAL TACHOMETER (E)

0.10

DUAL TACHOMETER (R)

0.10

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

EQUIPMENT

QTY

AMPS EACH

TOTAL

LIGHTS BUS

POSITION LIGHTS (L, R, & AFT,

2.20

6.60

INCANDESCENT)

POSITION LIGHTS (L & R, LED)

0.25

0.50

POSITION LIGHT (AFT, LED)

0.30

OVERHEAD PANEL LIGHT

1.00

POST LIGHTS

0.08

0.56

INSTRUMENT LIGHTS

0.20

0.80

LANDING LIGHT RELAY

0.20

LANDING LIGHTS

7.70

15.40

(INCANDESCENT)

LANDING LIGHTS (HID)

2.90

9.52

5.80

19.04

ANTI-COLLISION LIGHT &

3.20

POWER SUPPLY

ANTI-COLLISION LIGHT (LED)

0.90

4.00

0.90

4.00

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

EQUIPMENT

QTY

AMPS EACH

TOTAL

AVIONICS

KY197A COM

0.80

5.20

0.80

5.20

GTR225B COM

0.59

5.31

0.59

5.31

GNS430 COM/NAV/GPS

2.44

8.40

2.44

8.40

GTN650 COM/NAV/GPS

2.65

6.97

2.65

6.97

KX155 OR KX165 NAV/COM

0.70

8.50

0.70

8.50

OCT 2018

Chapter 33 Electrical System

Page 33.21

33-120 Electrical Load Analysis (continued)

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

EQUIPMENT

QTY

AMPS EACH

TOTAL

AVIONICS (continued)

KR87 ADF

1.24

KN63 DME

1.21

GARMIN TRANSPONDER

1.10

3.10

1.10

3.10

GARMIN RADIO NAVIGATION

0.41

INDICATOR

KING RADIO NAVIGATION

0.08

INDICATOR

MARKER BEACON

0.50

KCS55A HSI

3.23

RADAR ALTIMETER

1.45

AA12S AUDIO CONTROL

1.00

GMA 350H AUDIO CONTROL

0.80

1.50

0.80

1.50

ASPEN 1000H EFD

4.80

ATTITUDE HORIZON

0.54

1.40

0.54

1.40

(MECHANICAL)

ATTITUDE HORIZON (LCD)

0.20

TURN COORDINATOR

0.70

DIRECTIONAL GYRO

0.44

1.40

0.44

1.40

PA/SIREN CONTROL

0.05

PA/SIREN SPEAKER

7.70

ICOM IC-M412 MARINE

1.50

5.50

1.50

5.50

TRANSCIEVER

KENWOOD TK-7160 OR TK8160

1.00

8.00

1.00

8.00

FM TRANSCIEVER

KENWOOD TK-7180 OR TK8180

1.00

9.00

1.00

9.00

FM TRANSCIEVER

YAESU FT-8800R FM

0.50

8.00

0.50

8.00

TRANSCIEVER

VERTEX VX-2200 FM

2.50

11.00

2.50

11.00

TRANSCIEVER

CONTINUOUS

INTERMITTENT

CONTINUOUS

INTERMITTENT

EQUIPMENT

QTY

AMPS EACH

TOTAL

OTHER EQUIPMENT

STARTER RELAY

0.00

15.00

0.00

15.00

STARTING VIBRATOR

0.00

2.50

0.00

2.50

STARTER MOTOR

0.00

200.00

0.00

200.00

CLOCK, STANDARD

0.02

CLOCK, DIGITAL

0.00

Page 33.22

Chapter 33 Electrical System

OCT 2018

CHAPTER 34

AVIONICS

Section Title

Page

34-10

Avionics Switch Description

34.1

34-20

Transponder Installations

34.1

34-21

A804-12 Transponder (Garmin GTX 330 ES) Installation

34.1

34-30

COM Radio Installations

34.4

34-31

C802-2 COM Radio (Garmin GTR 225B) Installation

34.4

34-40

Audio Control Installations

34.6

34-41

C822-1 Audio Control (Garmin GMA 350H) Installation

34.6

34-50

GPS Installations

34.8

34-51

C831 GPS (Garmin GTN 600 series) Installation

34.8

34-60

Avionics Software

34.10

OCT 2018

Chapter 34 Avionics

Page 34.i

CHAPTER 34

AVIONICS

34-10 Avionics Switch Description

R22 Helicopters S/N 4591, 4650, 4651, 4656 & subsequent have a dedicated avionics

switch located on the main switch panel on top of the avionics stack. Earlier R22s have an

avionics bus, but the master radio relay interrupts power to the avionics bus during start-

up, eliminating the need for a switch. The avionics switch controls a relay which interrupts

power to the avionics bus (system is fail-safe ON).

34-20 Transponder Installations

34-21 A804-12 Transponder (Garmin GTX 330 ES) Installation

NOTE

Refer to Garmin GTX

330 ES Maintenance Manual and

Instructions for Continued Airworthiness.

A. Description

Automatic Dependent Surveillance-Broadcast (ADS-B) “Out” equipment transmits aircraft

specific-data and position information to air traffic control via GPS-based surveillance

(rather than radar-based surveillance). ADS-B Out equipment will be required for R22

operation in certain airspace in the United States after January 1, 2020.

ADS-B Out system operates mostly automatically. ADS-B Out equipment is

programmed with aircraft-specific data at installation. ADS-B Out system uses

the primary installed GPS for position information. Additional flight-specific data is

entered by the pilot using transponder controls. ADS-B data is transmitted via the

transponder’s Extended Squitter (ES) on frequency 1090 MHz.

ADS-B Out equipment (transponder and primary GPS) must have power and must

be in normal operating modes for systems to function properly. ADS-B Out system

faults are annunciated on the transponder and primary GPS screens.

Change of aircraft registration may require ADS-B equipment programming by

qualified maintenance personnel.

Refer to R22 Pilot’s Operating Handbook Section 9 for additional information.

B. Schematic

Refer to Figure 14-41 for A804-12 transponder & blind encoder electrical schematic.

OCT 2018

Chapter 34 Avionics

Page 34.1

34-21 A804-12 Transponder (Garmin GTX 330 ES) Installation (continued)

C. Removal

1. Turn battery switch off and pull out XPDR circuit breaker (5 amp) at panel.

2. Loosen radio key securing A804-12 transponder to avionics tray.

3. Carefully unplug/remove transponder from tray.

D. Installation

1. Turn battery switch off and pull out XPDR circuit breaker (5 amp) at panel.

2. Carefully plug-in/install A804-12 transponder in appropriate location in avionics

tray.

3. Tighten radio key securing transponder to tray. Verify equipment security.

4. Push in XPDR circuit breaker (5 amp) at panel. Turn battery & avionics switches

on.

5. Perform appropriate functional checks per Garmin GTX 330 ES Pilot's Guide.

Turn battery and avionics switches off.

E. Antenna

Refer to § 16-70 for antenna locations and R22 Illustrated Parts Catalog (IPC) Chapter

NOTE

Antenna installation depends on optional equipment installed.

Removal

1. Turn battery switch off and pull out XPDR circuit breaker (5 amp) at panel.

2. Using plastic scraper, remove B270-1 sealant from around transponder antenna

at corners where it attaches to A794-2 panel.

3. Remove screws securing panel to cabin skin and disconnect antenna cable

from antenna. Remove hardware securing antenna and ground wire to panel

and remove antenna.

Page 34.2

Chapter 34 Avionics

OCT 2018

34-21 A804-12 Transponder (Garmin GTX 330 ES) Installation (continued)

E. Antenna (continued)

Installation

1. Turn battery switch off and pull out XPDR circuit breaker (5 amp) at panel.

2. Remove paint and primer from A794-2 panel where ground wire attaches to

ensure electrical ground.

3. Install hardware securing transponder antenna and ground wire to panel. Verify

security. Connect antenna cable to antenna and install screws securing panel

to cabin skin. Verify security.

4. Apply small bead B270-1 sealant (0.1 inch max in height) around antenna at

corners where it attaches to panel and allow to dry.

5. Perform ground checks per Part D steps 4 and 5.

F. Scheduled Maintenance and Inspections

NOTE

All factory-installed Garmin units are “on condition” and do not

require scheduled periodic maintenance. Units feature a BIT

(Built-In Test) function during each initial power-up that will

detect internal failure(s) and alert pilot.

NOTE

Refer to § 34-60 for avionics software information.

G. Special Maintenance and Inspections

1. Turn battery and avionics switches off. Open circuit breaker panel and upper

console.

2. Inspect condition of and verify no obvious damage to transponder, radio tray,

copper bus bars, circuit breaker, and wiring. Verify no loose, chafed, or broken

wires or terminals. Verify no evidence of arcing. Verify equipment security.

3. Secure circuit breaker panel and upper console. Perform ground checks per Part

D steps 4 and 5.

OCT 2018

Chapter 34 Avionics

Page 34.3

34-30 COM Radio Installations

34-31 C802-2 COM Radio (Garmin GTR 225B) Installation

A. Description

The C802-2 COM radio (Garmin GTR 225B) includes similar communication features

available in the earlier King KY197A COM radio, but includes an airport frequency

database, ability to monitor the standby frequency, and improved user memory

channel functionality. The Garmin GTR 225B is a dual voltage unit, suitable for use

in 14V and 28V systems.

B. Schematic

Refer to Figure 14-43 for C802-2 COM Radio Installation electrical schematic.

C. Removal

1. Turn battery switch off and pull-out COM radio circuit breaker (10 amp) at panel.

2. Loosen radio key securing C802-2 COM radio to avionics tray.

3. Carefully unplug/remove radio from tray.

D. Installation

1. Turn battery switch off and pull-out COM radio circuit breaker (10 amp) at panel.

2. Carefully plug-in/install C802-2 COM radio in appropriate location in avionics

tray.

3. Tighten radio key securing radio to tray. Verify equipment security.

4. Push-in COM radio circuit breaker (10 amp) at panel. Turn battery and avionics

switches on.

5. Perform appropriate functional checks per Garmin GTR 225B Pilot's Guide. Turn

battery and avionics switches off.

E. Antenna

Refer to § 16-70 for antenna locations and R22 Illustrated Parts Catalog (IPC) Chapter

NOTE

Antenna installation depends on number of COM installations

and additional equipment installed.

Page 34.4

Chapter 34 Avionics

OCT 2018

34-31 C802-2 COM Radio (Garmin GTR 225B) Installation (continued)

E. Antenna (continued)

Removal

1. Turn battery switch off and pull out COM radio circuit breaker (10 amp) at panel.

2. Using plastic scraper, remove B270-1 sealant from around COM antenna at

corners where it attaches to tailcone.

3. Disconnect antenna cable from antenna. As required, remove B270-13 sealant from

fastener holes. Remove screws securing antenna to tailcone and remove antenna.

Installation

1. Turn battery switch off and pull out COM radio circuit breaker (10 amp) at panel.

2. Remove paint & primer from antenna mating surfaces to ensure electrical ground.

3. As required, apply light coat B270-13 sealant to screw threads and install

screws securing antenna to tailcone. As required, seal around screw heads and

fill fastener holes using B270-13 sealant and allow to dry. Verify security.

4. Apply small bead B270-1 sealant (0.1 inch max in height) around antenna at

corners where it attaches to tailcone and allow to dry.

5. Connect antenna cable to antenna. Verify security.

6. Perform ground checks per Part D steps 4 and 5.

F. Scheduled Maintenance and Inspections

NOTE

All factory-installed Garmin units are “on condition” and do not

require scheduled periodic maintenance. Units feature a BIT

(Built-In Test) function during each initial power-up that will

detect internal failure(s) and alert pilot.

NOTE

Refer to § 34-60 for avionics software information.

G. Special Maintenance and Inspections

1. Turn battery and avionics switches off. Open circuit breaker panel and upper console.

2. Inspect condition of and verify no obvious damage to COM radio, radio tray,

copper bus bars, circuit breaker, and wiring. Verify no loose, chafed, or broken

wires or terminals. Verify no evidence of arcing. Verify equipment security.

3. Secure circuit breaker panel and upper console. Perform ground checks per Part

D steps 4 and 5.

OCT 2018

Chapter 34 Avionics

Page 34.5

34-40 Audio Control Installations

34-41 C822-1 Audio Control (Garmin GMA 350H) Installation

NOTE

Refer to Garmin GMA 350H series Maintenance Manual and

Instructions for Continued Airworthiness.

A. Description

The Garmin GMA 350H audio control includes improved squelch and background

noise suppression, 3D audio (if stereo headsets are used) which allows inputs from

separate radios to sound as if they are coming from separate locations around the

listener, and some control functions via voice command when a momentary push-

button switch is depressed on the pilot's cyclic grip.

B. Schematic

Refer to Figure 14-44 for C822-1 Audio Control Installation electrical schematic.

C. Removal

1. Turn battery switch off and pull out AUDIO PANEL circuit breaker (5 amp) at

panel.

2. Loosen radio key securing Garmin GMA 350H audio control to avionics tray.

3. Carefully unplug/remove audio control from tray.

D. Installation

1. Turn battery switch off and pull out AUDIO PANEL circuit breaker (5 amp) at

panel.

2. Carefully plug-in/install Garmin GMA 350H audio control in appropriate location

in avionics tray.

3. Tighten radio key securing audio control to tray. Verify equipment security.

4. Push in AUDIO PANEL circuit breaker (5 amp) at panel. Turn battery & avionics

switches on.

5. Perform appropriate functional checks per Garmin GMA 350H series Pilot's Guide.

Turn battery & avionics switches off.

E. Antenna

Refer to § 16-70 for antenna locations and R22 Illustrated Parts Catalog (IPC) Chapter

Page 34.6

Chapter 34 Avionics

OCT 2018

34-41 C822-1 Audio Control (Garmin GMA 350H) Installation (continued)

E. Antenna (continued)

Removal

1. Turn battery switch off & pull out AUDIO PANEL circuit breaker (5 amp) at panel.

2. Using plastic scraper, remove B270-1 sealant from around CI 102 marker

beacon antenna at corners where it attaches to A794-2 panel.

3. Remove hardware securing panel to belly and disconnect A850-210 antenna cable

from antenna. Carefully remove screws (they are installed with threadlocker)

securing antenna to panel and remove antenna.

Installation

1. Turn battery switch off & pull out AUDIO PANEL circuit breaker (5 amp) at panel.

2. Remove paint & primer from antenna mating surfaces to ensure electrical ground.

3. Apply light coat B270-11 adhesive to new screw threads and install screws

securing CI 102 marker beacon antenna to A794-2 panel. Verify security.

4. Connect A850-210 antenna cable to antenna. Install screws securing forward

belly panel to belly. Verify security.

5. Apply small bead B270-1 sealant (0.1 inch max in height) around antenna at

corners where it attaches to belly panel and allow to dry.

6. Perform ground checks per Part D steps 4 and 5.

F. Scheduled Maintenance and Inspections

NOTE

All factory-installed Garmin units are “on condition” and do not

require scheduled periodic maintenance. Units feature a BIT

(Built-In Test) function during each initial power-up that will

detect internal failure(s) and alert pilot.

NOTE

Refer to § 34-60 for avionics software information.

G. Special Maintenance and Inspections

1. Turn battery & avionics switches off. Open circuit breaker panel and upper console.

2. Inspect condition of and verify no obvious damage to audio control, radio tray,

copper bus bars, circuit breaker, and wiring. Verify no loose, chafed, or broken

wires or terminals. Verify no evidence of arcing. Verify equipment security.

3. Secure circuit breaker panel and upper console. Perform ground checks per Part

D steps 4 and 5.

OCT 2018

Chapter 34 Avionics

Page 34.7

34-50 GPS Installations

34-51 C831 GPS (Garmin GTN 600 series) Installation

NOTE

Refer to Garmin GTN 600 series Maintenance Manual and

Instructions for Continued Airworthiness.

A. Description

The C831 GPS (Garmin GTN 600 series) includes similar navigation features available

in the earlier Garmin GNS 400 series GPS, but the interface offers a combination of

touch screen technology with traditional buttons and knobs.

One GTN 600 series GPS may be installed in the pilot-side console location only.

Note: R22 ADS-B Out system requires Garmin GTN 600-series GPS. Refer to §

14.1230.

B. Schematic

Refer to Figure 14-45 for C831 GPS (Garmin GTN 600 series) installation electrical

schematic.

C. Removal

1. Turn battery switch off and pull out COM circuit breakers(s) (10 amp) and GPS

circuit breaker(s) (7.5 amp) as required at panel.

2. Loosen radio key securing C831 GPS to tray in pilot's side console.

3. Carefully unplug/remove GPS from tray.

D. Installation

1. Turn battery switch off and pull out COM circuit breakers(s) (10 amp) and GPS

circuit breaker(s) (7.5 amp) as required at panel.

2. Carefully plug-in/install C831 GPS in tray in pilot's side console.

3. Tighten radio key securing GPS to tray. Verify equipment security.

4. Push in COM circuit breaker(s) (10 amp) and GPS circuit breaker(s) (7.5 amp) as

required at panel. Turn battery and avionics switches on.

5. Perform appropriate functional checks per Garmin GTN 600 series Pilot's Guide.

Turn battery and avionics switches off.

Page 34.8

Chapter 34 Avionics

OCT 2018

34-51 C831 GPS (Garmin GTN 600 series) Installation (continued)

E. Antenna

Refer to § 16-70 for antenna locations and R22 Illustrated Parts Catalog (IPC) Chapter 6.

NOTE

Antenna installation depends on number COM installations and

additional equipment installed.

Removal

1. Turn battery switch off and pull out COM circuit breaker(s) (10 amp) and GPS

circuit breaker(s) (7.5 amp) as required at panel.

2. Using plastic scraper, remove B270-1 sealant from around GPS antenna at

corners where it attaches to tailcone.

3. Disconnect antenna cable from antenna. As required, remove B270-13 sealant

from fastener holes. Remove screws securing antenna to tailcone and remove

antenna.

Installation

1. Turn battery switch off and pull out COM circuit breaker(s) (10 amp) and GPS

circuit breaker(s) (7.5 amp) as required at panel.

2. Remove paint & primer from antenna mating surfaces to ensure electrical ground.

3. As required, apply light coat B270-13 sealant to screw threads and install

screws securing antenna to tailcone. As required, seal around screw heads

and fill fastener holes using B270-13 sealant and allow to dry. Verify security.

4. Apply small bead B270-1 sealant (0.1 inch max in height) around antenna at

corners where it attaches to tailcone and allow to dry.

5. Connect antenna cable to antenna. Verify security.

6. Perform ground checks per Part D steps 4 and 5.

F. Scheduled Maintenance and Inspections

NOTE

All factory-installed Garmin units are “on condition” and do not

require scheduled periodic maintenance. Units feature a BIT

(Built-In Test) function during each initial power-up that will

detect internal failure(s) and alert pilot.

NOTE

Refer to § 34-60 for avionics software information.

OCT 2018

Chapter 34 Avionics

Page 34.9

34-51 C831 GPS (Garmin GTN 600 series) Installation (continued)

G. Special Maintenance and Inspections

1. Turn battery and avionics switches off. Open circuit breaker panel. Remove

hardware securing pilot's side console shell assembly to tray and carefully pivot

shell assembly upward (GPS and faceplate may be also be removed).

2. Inspect condition of and verify no obvious damage to GPS, tray, copper bus bars,

circuit breaker, and wiring. Verify no loose, chafed, or broken wires or terminals.

Verify no evidence of arcing. Verify equipment security.

3. Secure circuit breaker panel and pilot's side console. Perform ground checks per

Part D steps 4 and 5.

34-60 Avionics Software

Modern avionics software is complex and subject to rigorous testing by RHC to assure proper

function and integration in the aircraft. Only specified software versions and software

configurations have been FAA-approved for installation in Robinson helicopters. Software

updates should not be attempted without a thorough understanding of approval status and

compatibility. Technical support from either RHC or the avionics manufacturer will likely be

required. In some cases, updating software for one item of avionics may require additional

avionics to be updated to assure compatibility.

As long as RHC-installed equipment is functioning properly, there is no continuing

airworthiness requirement to check or update software levels in Robinson helicopters; RHC

will issue an SB (or FAA will issue an AD) for any mandatory updates.

Consult www.robinsonheli.com > Customer Support > Avionics Support > Avionics

Software page for approved software configurations.

NOTE

The above statements apply to avionics operating software.

Databases (e.g. charts, terrain, etc.) may be updated regularly

using avionics manufacturer’s recommended procedures.

Page 34.10

Chapter 34 Avionics

OCT 2018

36-20 Illustrations and Tasks

Refer to Figure 36-1.

Item

Part Number

Description

MT016-1

Engine Hoist

MT050-1

Main Rotor Rigging Fixture

MT050-2

Tail Rotor Rigging Fixture

MT053-1

Main Gearbox Drain Assembly - Thread Type Chip Detector

MT054-1

Main Gearbox Drain Assembly - Quick Disconnect Chip Detector

MT068-1

Horizontal Stabilizer Rigging Tool

MT091-1

Holder - Engine Ring Gear (includes MT091-3 decal)

MT091-3

Decal (torquing instructions)

FIGURE 36-1 SPECIAL TOOLS

Page 36.2

Chapter 36 Special Tools

OCT 2018

36-20 Illustrations and Tasks (continued)

Refer to Figure 36-2.

Item

Part Number

Description

MT092-1

Fan Puller (includes MT092-3 spacer)

MT092-3

Spacer - Fan Puller

MT122-1

Main Rotor Hub, Bolt Elongation (teeter hinges & A154-1 hub coning hinges)

MT122-15

Main Rotor Hub, Bolt Elongation (B370-1 hub coning hinges)

MT146-1

Blocks - Swashplate Rigging (set of 2)

MT147-1

Bleed Tool - Main Rotor Blade Spindle

MT173-4

Socket - 1-11/16 (3/4-inch drive, 12-point)

MT173-5

Torque Wrench Extension - Tool Set (no longer available)

MT173-6

Tube Weldment (no longer available)

MT173-7

Socket - 1-1/2-inch (3/4-inch drive, 12-point)

MT173-8

Socket - 2-inch (3/4-inch drive, 12-point)

FIGURE 36-2 SPECIAL TOOLS

OCT 2018

Chapter 36 Special Tools

Page 36.3

36-20 Illustrations and Tasks (continued)

Refer to Figure 36-3.

Item

Part Number

Description

MT179-4

Balancing Bar - Tail Rotor Assembly Static Balance

MT200-1

Dial Indicator

MT201-1

Pressing Fixture - Tail Rotor Hub Bearing

MT234-1

Helicopter Lifting Fixture

MT260-6

Tail Rotor Drive Shaft Runout Attachments Kit

MT294-1

Collective Spring Retainer

FIGURE 36-3 SPECIAL TOOLS

Page 36.4

Chapter 36 Special Tools

OCT 2018

36-20 Illustrations and Tasks (continued)

Refer to Figure 36-4.

Item

Part Number

Description

MT295-1

Tail Rotor Gearbox Output Shaft Seal Replacement Tools (includes items 2, 3, 4,

and Figure 36-9 item 5)

MT295-3

Punch

MT295-6

Screw

MT295-10

Mandrel

MT303-1

Clutch Bearing (A184) Removal and Installation Tools

MT303-3

Clutch Bearing (A184) Removal and Installation Tools (use with MT303-1 tools

when hydraulic press is unavailable)

FIGURE 36-4 SPECIAL TOOLS

OCT 2018

Chapter 36 Special Tools

Page 36.5

36-20 Illustrations and Tasks (continued)

Refer to Figure 36-5.

Item

Part Number

Description

MT329-1

Plug Assembly (A648-1 or A648-3 Bearings)

MT329-2

Support Weldment (A154-1 Hub)

MT329-8

Plug - Main Rotor Hub Bearing Installation

MT329-10

Tube

MT329-11

Plug Assembly (A648-2 Bearings)

MT329-13

Support Weldment

MT331-4

Sheave Alignment Bar

MT352-1

Main Rotor Blade Trim Tab Gage (includes MT200-1 dial indicator)

MT354-1

Teeter Moment Tool (no longer available; replaced by MT354-7)

MT354-7

Teeter Moment Tool (R22, R44, R66)

FIGURE 36-5 SPECIAL TOOLS

Page 36.6

Chapter 36 Special Tools

OCT 2018

36-20 Illustrations and Tasks (continued)

Refer to Figure 36-6.

Item

Part Number

Description

MT357-1

0.125-inch dia. Cobalt Drill Bit

MT357-2

0.375-inch diameter Reamer

MT357-4

Hex Driver (Snap-On Part No. FABL8)

MT357-5

Torque Adapter (Snap-On Part No. FRDH101)

MT357-6

Wrench (Open end; Snap-On Part No. LTA1214)

MT357-7

Wrench (Box end; Snap-On Part No. XDH78A)

MT357-8

Nipple Chuck

MT357-9

Taper Gage

FIGURE 36-6 SPECIAL TOOLS

OCT 2018

Chapter 36 Special Tools

Page 36.7

36-20 Illustrations and Tasks (continued)

Refer to Figure 36-7.

Item

Part Number

Description

MT358-1

0.750-inch dia. Spot-Facing Tool

MT359-1

Spring Scale (0-30 lb)

MT376-1

Blocks - Main Rotor Rigging (set; holds cyclic in neutral position)

MT526-1

Main Rotor Blade Trim Tab Bender (stainless steel skin)

MT526-8

Main Rotor Blade Trim Tab Bender (aluminum skin)

FIGURE 36-7 SPECIAL TOOLS

Page 36.8

Chapter 36 Special Tools

OCT 2018

36-20 Illustrations and Tasks (continued)

Refer to Figure 36-8.

Item

Part Number

Description

MT556-1

Tail Rotor Elastomeric Bearing Replacement Tools (includes items 2 thru 4, and 7)

MT556-2

Mandrel Assembly

MT556-5

Support

MT556-6

Cap

MT569-1

Main Rotor Bolt Drilling Fixture (teeter hinge & A154-1 hub coning hinge bolts)

MT569-6

Main Rotor Bolt Drilling Fixture (B370-1 hub coning hinge bolts)

AN4-25A

Bolt

AN970-4*

Washer - Tap Test Tool

* Or 1965 or later U.S. quarter dollar coin in good condition.

FIGURE 36-8 SPECIAL TOOLS

OCT 2018

Chapter 36 Special Tools

Page 36.9

36-20 Illustrations and Tasks (continued)

Refer to Figure 36-9.

Item

Part Number

Description

2020HR

ACES Probalancer Analyzer (or equivalent dynamic balancer)

60297-12

Engine Operator’s Manual (O-360 engine; refer to Lycoming Service Letter No. L114)

60297-30

Engine Operator’s Manual (O-320 engine; refer to Lycoming Service Letter No. L114)

9HT4441

Extension Bar (3/4 square drive x 8 inch)

92470A113

Screws (#4 x 0.75 inch)

FIGURE 36-9 SPECIAL TOOLS

Page 36.10

Chapter 36 Special Tools

OCT 2018

REVISION LOG

OCT 2018

The R22 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 , and click on 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

OCT 2018

2.3

OCT 2018

2.35

OCT 2018

2.4

OCT 2018

2.36

OCT 2018

iii

OCT 2018

2.5

OCT 2018

2.37

OCT 2018

2.6

OCT 2018

2.38

OCT 2018

2.7

OCT 2018

2.39

OCT 2018

2.8

OCT 2018

2.40

OCT 2018

2.9

APR 2007

2.41

OCT 2018

1.i

OCT 2018

2.10

JUN 2006

2.42

OCT 2018

1.ii

OCT 2018

2.11

JUN 2006

2.43

JUN 2006

1.1

OCT 2018

2.12

JUN 2006

2.44

JUN 2006

1.2

OCT 2018

2.13

OCT 2018

2.45

JUN 2006

1.3

OCT 2018

2.14

OCT 2018

2.46

APR 2007

1.4

OCT 2018

2.15

JUN 2006

2.47

JUN 2006

1.5

OCT 2018

2.16

JUN 2006

2.48

JUN 2006

1.6

OCT 2018

2.17

OCT 2018

2.49

JUN 2006

1.7

OCT 2018

2.18

OCT 2018

2.50

APR 2007

1.8

OCT 2018

2.19

OCT 2018

2.51

JUN 2006

1.9

OCT 2018

2.20

OCT 2018

2.52

JUN 2006

1.10

OCT 2018

2.21

OCT 2018

2.53

JUN 2006

1.11

OCT 2018

2.22

OCT 2018

2.54

JUN 2006

1.12

OCT 2018

2.23

OCT 2018

2.55

JUN 2006

1.13

OCT 2018

2.24

OCT 2018

2.56

JUN 2006

1.14

OCT 2018

2.25

OCT 2018

2.57

JUN 2006

1.15

OCT 2018

2.26

OCT 2018

2.58

JUN 2006

1.16

OCT 2018

2.27

OCT 2018

2.59

OCT 2018

1.17

OCT 2018

2.28

OCT 2018

2.60

OCT 2018

1.18

OCT 2018

2.29

OCT 2018

2.61

OCT 2018

2.30

OCT 2018

2.62

OCT 2018

2.i

OCT 2018

2.31

OCT 2018

2.63

OCT 2018

2.ii

OCT 2018

2.32

OCT 2018

2.64

OCT 2018

2.1

OCT 2018

2.33

OCT 2018

2.65

OCT 2018

2.2

OCT 2018

2.34

OCT 2018

2.66

OCT 2018

Chapter 37 Revision Log

Page 37.1

REVISION LOG

OCT 2018

Page

Date

Page

Date

Page

Date

2.67

OCT 2018

4.19

26 JUL 96

6.13

19 SEP 97

2.68

OCT 2018

4.20

30 JUN 99

6.14

19 SEP 97

2.69

OCT 2018

4.21

JUN 2006

6.15

JAN 2005

2.70

OCT 2018

4.22

JUN 2006

6.16

26 JUL 96

4.23

7 AUG 92

6.16A

7 AUG 92

3.i

OCT 2018

4.24

7 AUG 92

6.16B

JAN 2005

3.ii

OCT 2018

4.25

7 AUG 92

6.16C

7 AUG 92

3.1

OCT 2018

6.16D

7 AUG 92

3.2

OCT 2018

5.i

OCT 2018

6.17

APR 2007

3.3

OCT 2018

5.ii

OCT 2018

6.18

APR 2007

3.4

OCT 2018

5.1

OCT 2018

6.19

APR 2007

3.5

OCT 2018

5.2

OCT 2018

6.20

APR 2007

3.6

OCT 2018

5.3

OCT 2018

6.21

OCT 2014

3.7

OCT 2018

5.4

OCT 2018

6.22

OCT 2014

3.8

OCT 2018

5.5

OCT 2018

6.23

MAR 2004

3.9

OCT 2018

5.6

OCT 2018

6.24

MAR 2004

3.10

OCT 2018

5.7

5/22/87

6.25

APR 2007

5.8

28 JUL 89

6.26

APR 2007

4.i

OCT 2018

5.9

28 JUL 89

6.27

APR 2007

4.ii

OCT 2018

5.10

28 JUL 89

6.28

APR 2007

4.1

OCT 2018

5.11

28 JUL 89

6.29

APR 2007

4.2

OCT 2018

5.12

JUN 2000

6.30

APR 2007

4.3

OCT 2018

5.13

28 JUL 89

4.4

OCT 2018

7.i

OCT 2018

4.5

31 JAN 89

6.i

OCT 2014

7.ii

OCT 2018

4.6

APR 2005

6.ii

OCT 2014

7.1

OCT 2014

4.7

5/22/87

6.1

OCT 2014

7.2

OCT 2014

4.8

5/22/87

6.2

OCT 2014

7.3

JUN 2006

4.9

5/22/87

6.3

APR 2007

7.4

5/22/87

4.10

JAN 2005

6.4

APR 2007

7.5

JUN 2006

4.11

5/22/87

6.5

JUN 2006

7.6

JUN 2006

4.12

APR 2007

6.6

JUN 2006

7.7

OCT 2018

4.13

5/22/87

6.7

APR 2005

7.8

OCT 2018

4.14

29 MAR 93

6.8

APR 2005

7.9

19 SEP 97

4.15

JAN 2005

6.9

OCT 2018

7.9A

19 SEP 97

4.16

JAN 2005

6.10

OCT 2018

7.9B

19 SEP 97

4.17

JUN 2000

6.11

26 JUL 96

7.10

JUN 2000

4.18

30 JUN 99

6.12

30 JUN 99

7.11

5/22/87

Page 37.2

Chapter 37 Revision Log

OCT 2018

REVISION LOG

OCT 2018

Page

Date

Page

Date

Page

Date

7.12

3 MAR 99

7.44

19 SEP 97

8.14

4/15/88

7.13

3 MAR 99

7.44A

4/15/88

8.15

5/22/87

7.14

JUN 2000

7.44B

5 JUL 90

8.16

5/22/87

7.15

OCT 2018

7.44C

26 JUL 96

8.17

5/22/87

7.16

OCT 2018

7.44D

7 AUG 92

8.18

7 AUG 92

7.17

APR 2005

7.45

OCT 2018

8.19

12 JAN 90

7.18

MAR 2004

7.46

OCT 2018

8.20

12 JAN 90

7.19

OCT 2018

7.47

JUN 2000

8.21

5/22/87

7.20

OCT 2018

7.48

JUN 2000

8.22

5/22/87

7.21

OCT 2018

7.48A

31 DEC 98

8.23

5/22/87

7.22

OCT 2018

7.48B

MAR 2004

8.24

5/22/87

7.23

OCT 2018

7.49

OCT 2018

8.25

5/22/87

7.24

OCT 2018

7.50

OCT 2018

8.26

MAR 2004

7.25

OCT 2018

7.51

OCT 2018

8.27

26 JUL 96

7.26

OCT 2018

7.52

OCT 2018

8.28

MAR 2004

7.27

OCT 2018

7.53

OCT 2018

8.29

5/22/87

7.28

OCT 2018

7.54

OCT 2018

8.30

MAR 2004

7.29

OCT 2018

7.55

OCT 2018

8.31

19 SEP 97

7.29A

OCT 2018

7.56

OCT 2018

8.32

5 JUL 90

7.29B

OCT 2018

7.57

31 JAN 89

8.33

OCT 2018

7.30

OCT 2018

8.34

OCT 2018

7.31

OCT 2018

8.i

OCT 2014

8.34A

MAR 2004

7.32

OCT 2018

8.ii

OCT 2014

8.34B

26 JUL 96

7.33

OCT 2014

8.iii

OCT 2014

8.34C

MAR 2004

7.33A

OCT 2014

8.iv

OCT 2014

8.34D

MAR 2004

7.33B

MAR 2004

8.1

OCT 2014

8.35

5/22/87

7.34

5/22/87

8.2

OCT 2014

8.36

5/22/87

7.35

26 JUL 96

8.3

5/22/87

8.37

JUN 2006

7.36

MAR 2004

8.4

5/22/87

8.38

JUN 2006

7.37

26 JUL 96

8.5

5/22/87

8.39

OCT 2018

7.38

26 JUL 96

8.6

5/22/87

8.40

OCT 2018

7.38A

26 JUL 96

8.7

5/22/87

8.41

OCT 2018

7.38B

26 JUL 96

8.8

5/22/87

8.42

OCT 2018

7.39

19 SEP 97

8.9

5/22/87

8.43

OCT 2018

7.40

19 SEP 97

8.10

5/22/87

8.44

OCT 2018

7.41

19 SEP 97

8.11

5/22/87

8.45

OCT 2018

7.42

19 SEP 97

8.12

5/22/87

8.46

OCT 2018

7.43

19 SEP 97

8.13

5/22/87

8.47

19 SEP 97

OCT 2018

Chapter 37 Revision Log

Page 37.3

REVISION LOG

OCT 2018

Page

Date

Page

Date

Page

Date

8.48

26 JUL 96

10.i

OCT 2018

10.32A

OCT 2014

8.49

MAR 2004

10.ii

OCT 2018

10.32B

OCT 2014

8.50

5/22/87

10.1

OCT 2014

10.33

5/22/87

8.51

5/22/87

10.2

OCT 2014

10.34

5/22/87

8.52

5/22/87

10.3

5/22/87

10.35

JAN 2005

8.53

5/22/87

10.4

5/22/87

10.36

JAN 2005

8.54

5/22/87

10.5

APR 2005

10.37

JAN 2005

8.55

JAN 2005

10.6

APR 2007

10.38

JAN 2005

8.56

JAN 2005

10.7

APR 2005

10.39

JAN 2005

8.57

5/22/87

10.8

5/22/87

10.40

JAN 2005

8.58

5/22/87

10.9

5/22/87

8.59

JUN 2006

10.10

5/22/87

11.i

OCT 2018

8.60

JUN 2006

10.11

5/22/87

11.ii

OCT 2018

8.61

22 JAN 93

10.12

5/22/87

11.1

OCT 2018

8.62

22 JAN 93

10.13

5/22/87

11.2

OCT 2018

8.63

APR 2005

10.14

5/22/87

11.3

OCT 2018

8.64

APR 2005

10.15

APR 2007

11.4

OCT 2018

10.16

APR 2007

11.5

OCT 2018

9.i

OCT 2018

10.17

5/22/87

11.6

OCT 2018

9.ii

OCT 2018

10.18

5/22/87

9.1

OCT 2018

10.19

5/22/87

12.i

OCT 2018

9.2

OCT 2018

10.20

MAR 2004

12.ii

OCT 2018

9.26C

OCT 2014

10.21

OCT 2018

12.1

OCT 2018

9.26D

OCT 2014

10.22

OCT 2018

12.2

OCT 2018

9.27

JUN 2000

10.23

28 JUL 89

12.3

OCT 2014

9.28

JUN 2000

10.24

30 JUN 99

12.4

OCT 2014

9.29

JUN 2006

10.25

5/22/87

12.5

OCT 2014

9.30

JUN 2006

10.25A

28 JUL 89

12.6

OCT 2014

9.31

31 DEC 98

10.25B

28 JUL 89

12.7

OCT 2014

9.32

31 DEC 98

10.26

28 JUL 89

12.8

OCT 2014

9.32A

JUN 2000

10.26A

JUN 2006

12.9

OCT 2018

9.32B

JUN 2000

10.26B

JUN 2006

12.9A

OCT 2018

9.32C

MAR 2004

10.27

JUN 2006

12.9B

OCT 2018

9.32D

JUN 2000

10.28

MAR 2004

12.10

OCT 2018

9.33

5/22/87

10.29

19 SEP 97

12.11

OCT 2014

9.34

5/22/87

10.30

5/22/87

12.12

OCT 2014

9.35

19 SEP 97

10.31

OCT 2014

12.13

OCT 2018

10.32

OCT 2014

12.14

OCT 2018

Page 37.4

Chapter 37 Revision Log

OCT 2018

REVISION LOG

OCT 2018

Page

Date

Page

Date

Page

Date

12.15

OCT 2014

14.13

5/22/87

14.26E

JUN 2000

12.16

OCT 2014

14.14

5/22/87

14.26F

JUN 2000

12.17

OCT 2014

14.15

5/22/87

14.26G

JUN 2000

12.18

OCT 2014

14.16

12 JAN 90

14.26H

JUN 2000

14.16A

12 JAN 90

14.26I

JUN 2000

13.i

OCT 2018

14.16B

12 JAN 90

14.26J

JUN 2000

13.ii

OCT 2018

14.17

12 JAN 90

14.26K

MAR 2004

13.1

OCT 2018

14.17A

12 JAN 90

14.26L

MAR 2004

13.2

OCT 2018

14.17B

12 JAN 90

14.27

5 JUL 90

13.3

OCT 2018

14.17C

12 JAN 90

14.28

5/22/87

13.4

OCT 2018

14.17D

12 JAN 90

14.28A

5 JUL 90

13.5

OCT 2018

14.18

5/22/87

14.28B

5 JUL 90

13.6

OCT 2018

14.18A

30 JUN 99

14.29

5/22/87

13.7

OCT 2018

14.18B

30 JUN 99

14.30

5/22/87

13.8

OCT 2018

14.19

OCT 2018

14.31

5/22/87

13.9

OCT 2018

14.20

OCT 2018

14.32

5/22/87

13.10

OCT 2018

14.20A

OCT 2018

14.33

5/22/87

13.11

OCT 2018

14.20B

OCT 2018

14.34

5/22/87

13.12

OCT 2018

14.21

30 JUN 99

14.35

5/22/87

13.13

OCT 2018

14.21A

30 JUN 99

14.36

5/22/87

13.14

OCT 2018

14.21B

30 JUN 99

14.37

5/22/87

13.15

OCT 2018

14.22

5/22/87

14.38

5/22/87

13.16

OCT 2018

14.23

OCT 2018

14.39

28 JUL 89

13.17

OCT 2018

14.23A

OCT 2018

14.40

5/22/87

13.18

OCT 2018

14.23B

OCT 2018

14.40A

JUN 2000

13.19

OCT 2018

14.23C

OCT 2018

14.40B

JUN 2000

13.20

OCT 2018

14.23D

OCT 2018

14.40C

JUN 2000

13.21

OCT 2018

14.23E

OCT 2018

14.40D

JUN 2000

13.22

OCT 2018

14.23F

OCT 2018

14.41

9/25/87

13.23

OCT 2018

14.23G

OCT 2018

14.42

9/25/87

13.24

OCT 2018

14.23H

OCT 2018

14.43

5/22/87

14.24

OCT 2018

14.44

5/22/87

14.i

OCT 2018

14.25

26 JUL 96

14.45

5/22/87

14.ii

OCT 2018

14.26

5/22/87

14.46

5/22/87

14.1

OCT 2018

14.26A

7 AUG 92

14.47

5/22/87

14.2

OCT 2018

14.26B

30 JUN 99

14.48

5/22/87

14.11B

OCT 2018

14.26C

JUN 2000

14.49

9/25/87

14.12

OCT 2018

14.26D

JUN 2000

14.50

5/22/87

OCT 2018

Chapter 37 Revision Log

Page 37.5

REVISION LOG

OCT 2018

Page

Date

Page

Date

Page

Date

14.51

7 AUG 92

15.8

OCT 2018

19.2

OCT 2018

14.52

5/22/87

19.3

OCT 2018

14.53

5/22/87

16.i

OCT 2018

19.4

OCT 2018

14.54

4/22/87

16.ii

OCT 2018

19.5

OCT 2018

14.55

5/22/87

16.1

OCT 2018

19.6

OCT 2018

14.56

5/22/87

16.2

OCT 2018

19.7

OCT 2018

14.57

5/22/87

16.3

OCT 2018

19.8

OCT 2018

14.58

5/22/87

16.4

OCT 2018

14.59

5/22/87

16.5

OCT 2018

20.i

OCT 2018

14.60

5/22/87

16.6

OCT 2018

20.ii

OCT 2018

14.61

5/22/87

16.7

OCT 2018

20.1

OCT 2018

14.62

5/22/87

16.8

OCT 2018

20.2

OCT 2018

14.63

5/22/87

20.3

OCT 2018

14.64

19 SEP 97

17.i

OCT 2018

20.4

OCT 2018

14.65

OCT 2018

17.ii

OCT 2018

14.66

OCT 2018

17.1

OCT 2018

21.i

OCT 2018

14.67

OCT 2018

17.2

OCT 2018

21.ii

OCT 2018

14.68

OCT 2018

17.3

OCT 2018

21.1

OCT 2018

14.69

OCT 2018

17.4

OCT 2018

21.2

OCT 2018

14.70

OCT 2018

17.5

OCT 2018

14.71

OCT 2018

17.6

OCT 2018

22.i

OCT 2018

14.72

OCT 2018

22.ii

OCT 2018

14.73

OCT 2018

18.i

OCT 2018

22.1

OCT 2018

14.74

OCT 2018

18.ii

OCT 2018

22.2

OCT 2018

14.75

OCT 2018

18.1

OCT 2018

22.3

OCT 2018

14.76

OCT 2018

18.2

OCT 2018

22.4

OCT 2018

14.77

OCT 2018

18.3

OCT 2018

22.5

OCT 2018

14.78

OCT 2018

18.4

OCT 2018

22.6

OCT 2018

18.5

OCT 2018

22.7

OCT 2018

15.i

OCT 2018

18.6

OCT 2018

22.8

OCT 2018

15.ii

OCT 2018

18.7

OCT 2018

22.9

OCT 2018

15.1

OCT 2018

18.8

OCT 2018

22.10

OCT 2018

15.2

OCT 2018

18.9

OCT 2018

22.11

OCT 2018

15.3

OCT 2018

18.10

OCT 2018

22.12

OCT 2018

15.4

OCT 2018

22.13

OCT 2018

15.5

OCT 2018

19.i

OCT 2018

22.14

OCT 2018

15.6

OCT 2018

19.ii

OCT 2018

15.7

OCT 2018

19.1

OCT 2018

23.i

OCT 2018

Page 37.6

Chapter 37 Revision Log

OCT 2018

REVISION LOG

OCT 2018

Page

Date

Page

Date

Page

Date

23.ii

OCT 2018

26.29

OCT 2018

23.1

OCT 2018

25.i

OCT 2018

26.30

OCT 2018

23.2

OCT 2018

25.ii

OCT 2018

26.31

OCT 2018

23.3

OCT 2018

25.1

OCT 2018

26.32

OCT 2018

23.4

OCT 2018

25.2

OCT 2018

26.33

OCT 2018

23.5

OCT 2018

25.3

OCT 2018

26.34

OCT 2018

23.6

OCT 2018

25.4

OCT 2018

23.7

OCT 2018

27.i

OCT 2018

23.8

OCT 2018

26.i

OCT 2018

27.ii

OCT 2018

23.9

OCT 2018

26.ii

OCT 2018

27.1

OCT 2018

23.10

OCT 2018

26.1

OCT 2018

27.2

OCT 2018

23.11

OCT 2018

26.2

OCT 2018

23.12

OCT 2018

26.3

OCT 2018

28.i

OCT 2018

23.13

OCT 2018

26.4

OCT 2018

28.ii

OCT 2018

23.14

OCT 2018

26.5

OCT 2018

28.1

OCT 2018

23.15

OCT 2018

26.6

OCT 2018

28.2

OCT 2018

23.16

OCT 2018

26.7

OCT 2018

23.17

OCT 2018

26.8

OCT 2018

29.i

OCT 2018

23.18

OCT 2018

26.9

OCT 2018

29.ii

OCT 2018

23.19

OCT 2018

26.10

OCT 2018

29.1

OCT 2018

23.20

OCT 2018

26.11

OCT 2018

29.2

OCT 2018

23.21

OCT 2018

26.12

OCT 2018

23.22

OCT 2018

26.13

OCT 2018

30.i

OCT 2018

23.23

OCT 2018

26.14

OCT 2018

30.ii

OCT 2018

23.24

OCT 2018

26.15

OCT 2018

30.1

OCT 2018

23.25

OCT 2018

26.16

OCT 2018

30.2

OCT 2018

23.26

OCT 2018

26.17

OCT 2018

23.27

OCT 2018

26.18

OCT 2018

31.i

OCT 2018

23.28

OCT 2018

26.19

OCT 2018

31.ii

OCT 2018

23.29

OCT 2018

26.20

OCT 2018

31.1

OCT 2018

23.30

OCT 2018

26.21

OCT 2018

31.2

OCT 2018

26.22

OCT 2018

24.i

OCT 2018

26.23

OCT 2018

32.i

OCT 2018

24.ii

OCT 2018

26.24

OCT 2018

32.ii

OCT 2018

24.1

OCT 2018

26.25

OCT 2018

32.1

OCT 2018

24.2

OCT 2018

26.26

OCT 2018

32.2

OCT 2018

24.3

OCT 2018

26.27

OCT 2018

24.4

OCT 2018

26.28

OCT 2018

33.i

OCT 2018

Chapter 37 Revision Log

Page 37.7

REVISION LOG

OCT 2018

Page

Date

Page

Date

Page

Date

33.ii

OCT 2018

35.1

OCT 2018

33.1

OCT 2018

35.2

OCT 2018

33.2

OCT 2018

33.3

OCT 2018

36.i

OCT 2018

33.4

OCT 2018

36.ii

OCT 2018

33.5

OCT 2018

36.1

OCT 2018

33.6

OCT 2018

36.2

OCT 2018

33.7

OCT 2018

36.3

OCT 2018

33.8

OCT 2018

36.4

OCT 2018

33.9

OCT 2018

36.5

OCT 2018

33.10

OCT 2018

36.6

OCT 2018

33.11

OCT 2018

36.7

OCT 2018

33.12

OCT 2018

36.8

OCT 2018

33.13

OCT 2018

36.9

OCT 2018

33.14

OCT 2018

36.10

OCT 2018

33.15

OCT 2018

33.16

OCT 2018

37.i

OCT 2018

33.17

OCT 2018

37.ii

OCT 2018

33.18

OCT 2018

37.1

OCT 2018

33.19

OCT 2018

37.2

OCT 2018

33.20

OCT 2018

37.3

OCT 2018

33.21

OCT 2018

37.4

OCT 2018

33.22

OCT 2018

37.5

OCT 2018

37.6

OCT 2018

34.ii

OCT 2018

37.7

OCT 2018

34.1

OCT 2018

37.8

OCT 2018

34.2

OCT 2018

34.3

OCT 2018

34.4

OCT 2018

34.5

OCT 2018

34.6

OCT 2018

34.7

OCT 2018

34.8

OCT 2018

34.9

OCT 2018

34.10

OCT 2018

35.i

OCT 2018

35.ii

OCT 2018

Page 37.8

Chapter 37 Revision Log

OCT 2018

CLASS A

SUBSCRIPTION SERVICE

If you wish to receive future changes to the R22 Pilot’s

Operating Handbook and copies of future Safety Notices,

you may order online at www.robinsonheli.com. The Class

A subscription costs $40 USD for a period of two years.

You may also remit your payment by filling out the contact

information below and sending it and your check or money

order to:

ROBINSON HELICOPTER COMPANY

2901 Airport Drive

Torrance, CA 90505

Note: The date stamped below reflects the revision of this

handbook at the time it was assembled. Please refer to

www.robinsonheli.com for date of most recent revision.

If outdated, the most recent revision is available for an

additional charge of $20 USD.

Name:

Complete Address:

Phone:

E-mail:

Aircraft Serial Number:

ROBINSON

R22 SERIES

LOG OF PAGES

LOG OF PAGES APPROVED BY FAA

TYPE CERTIFICATE NO. H10WE

Page

Approval

Page

Approval

No.

Date

No.

Date

Cover

16 Mar 79

Log of Pages

11 May 20

Section 2

2-i

23 Dec 09

2-8

11 May 20

Limitations

2-1

26 Jun 12

2-9

1 Jul 05

2-2

26 Oct 16

2-10

13 Oct 00

2-3

5 Mar 15

2-11

13 Oct 00

2-4

1 Jul 05

2-12

20 Jun 19

2-5

1 Jul 05

2-13

26 Oct 16

2-6

11 May 20

2-14

26 Oct 16

2-7

20 Jun 19

2-15

20 Jun 19

Section 3

3-i

11 May 20

3-6

26 Oct 16

Emergency

3-1

26 Oct 16

3-7

20 Jun 19

Procedures

3-2

21 Feb 14

3-8

13 Oct 00

3-3

6 Jul 95

3-9

26 Oct 16

3-4

21 Feb 14

3-10

11 May 20

3-5

11 May 20

3-11

11 May 20

Section 4

4-i

26 Oct 16

4-8

26 Oct 16

Normal

4-1

11 May 20

4-9

20 Jun 19

Procedures

4-2

11 May 20

4-10

26 Jun 12

4-3

11 May 20

4-11

26 Jun 12

4-4

11 May 20

4-12

26 Oct 16

4-5

11 May 20

4-13

11 May 20

4-6

21 Feb 14

4-14

26 Jun 12

4-7

11 May 20

4-15

26 Jun 12

Section 5

5-i

23 Feb 04

5-7

13 Oct 00

Performance

5-1

23 Feb 04

5-8

13 Oct 00

5-2

16 Mar 79

5-9

23 Feb 04

5-3

16 Mar 79

5-10

23 Feb 04

5-4

15 Sep 87

5-11

23 Feb 04

5-5

13 Oct 00

5-12

23 Feb 04

5-6

13 Oct 00

Section 9

9-i

11 May 20

Supplements

Approved By:

Manager, West Flight Test Section, AIR-716

Federal Aviation Administration

Los Angeles, CA

Date of Approval: 11 May 2020

ROBINSON

R22 SERIES

LOG OF PAGES

NOT REQUIRING FAA APPROVAL

Page

Revision

Page

Revision

No.

Date

No.

Date

Section 1

1-i

26 Jun 12

1-5

23 Dec 09

General

1-1

26 Jun 12

1-6

23 Dec 09

1-2

26 Jun 12

1-7

5 Mar 15

1-3

6 Jul 95

1-8

5 Mar 15

1-4

11 May 20

Section 6

6-i

21 Feb 14

6-5

21 Feb 14

Weight and

6-1

21 Feb 14

6-6

21 Feb 14

Balance

6-2

21 Feb 14

6-7

21 Feb 14

6-3

21 Feb 14

6-8

23 Feb 04

6-4

21 Feb 14

Section 7

7-i

11 May 20

7-16

21 Feb 14

Systems

7-1

5 Mar 15

7-17

26 Oct 16

Description

7-2

21 Feb 14

7-18

20 Jun 19

7-3

21 Feb 14

7-19

26 Oct 16

7-4

21 Feb 14

7-20

26 Oct 16

7-5

21 Feb 14

7-21

20 Jun 19

7-6

21 Feb 14

7-22

26 Oct 16

7-7

26 Oct 16

7-23

26 Oct 16

7-8

21 Feb 14

7-24

11 May 20

7-9

26 Oct 16

7-25

11 May 20

7-10

26 Oct 16

7-26

11 May 20

7-11

11 May 20

7-27

11 May 20

7-12

21 Feb 14

7-28

11 May 20

7-13

21 Feb 14

7-29

11 May 20

7-14

21 Feb 14

7-30

11 May 20

7-15

21 Feb 14

7-31

11 May 20

Section 8

8-i

20 Jun 19

8-8

20 Jun 19

Handling and

8-1

20 Jun 19

8-9

11 May 20

Maintenance

8-2

20 Jun 19

8-10

11 May 20

8-3

11 May 20

8-11

20 Jun 19

8-4

20 Jun 19

8-12

20 Jun 19

8-5

20 Jun 19

8-13

20 Jun 19

8-6

20 Jun 19

8-14

20 Jun 19

8-7

20 Jun 19

Section 10

10-i

26 Oct 16

10-4

26 Oct 16

Safety Tips

10-1

26 Oct 16

10-5

20 Jun 19

10-2

26 Oct 16

10-6

20 Jun 19

10-3

26 Oct 16

REVISED: 11 MAY 2020

iii

ROBINSON

SECTION 1

R22 SERIES

GENERAL

DESCRIPTIVE DATA

MAIN ROTOR

Articulation

Free to teeter and cone,

rigid inplane

Number of Blades

Diameter

25 feet 2 inches

Blade Chord

7.2 inches inboard,

7.7 inches outboard

Blade Twist

-8 degrees

Tip Speed at 104% RPM

698 feet per second

TAIL ROTOR

Articulation

Free to teeter, rigid inplane

Number of Blades

Diameter

42 inches

Blade Chord

4 inches (constant)

Blade Twist

0 degrees

Precone Angle

1 degree 11 minutes

Tip Speed at 104% RPM

622 feet per second

DRIVE SYSTEM

Engine to Upper Sheave:

Two double Vee-belts with

.8536:1 speed reducing

ratio

Upper Sheave to Drive Line: Sprag-type overrunning

clutch

Drive Line to Main Rotor:

Spiral-bevel gears with

11:47 speed reducing ratio

Drive Line to Tail Rotor:

Spiral-bevel gears with 3:2

speed increasing ratio

REVISED: 11 MAY 2020

1-4

ROBINSON

SECTION 1

R22 SERIES

GENERAL

PERFORMANCE DEFINITIONS (cont’d)

OAT Outside Air Temperature

CAT

Carburetor Air Temperature

CHT

Cylinder Head Temperature

GPH

Gallons Per Hour

AGL

Above Ground Level

IGE

In Ground Effect

OGE

Out of Ground Effect

ALT

Alternator

WEIGHT AND BALANCE DEFINITIONS

Reference

A vertical plane from which horizontal

Datum

distances are measured for balance

purposes. The longitudinal reference datum

is 100 inches forward of the main rotor

shaft centerline for the R22.

Station

Fore-and-aft location along the helicopter

fuselage given in terms of distance in inches

from the longitudinal reference datum.

Arm

Horizontal distance from a reference datum

to the center of gravity (CG) of an item.

Moment

The weight of an item multiplied by its arm.

Center of

Location along the fuselage (usually

Gravity (CG)

expressed in inches from the reference datum)

at which the helicopter would balance. CG

is calculated by dividing the total helicopter

moment by total helicopter weight.

CG Limits

Extreme CG locations within which the heli-

copter must be operated at a given weight.

Usable Fuel

Fuel available for flight planning.

Unusable Fuel

Fuel remaining in the tank that cannot

reliably provide uninterrupted fuel flow in

the critical flight attitude.

Standard

Weight of standard helicopter including

Empty Weight

unusable fuel, full operating fluids, and full

engine oil.

Basic

Standard empty weight plus weight of

Empty Weight

installed optional equipment.

Payload

Weight of occupants, cargo, and baggage.

Useful Load

Difference between maximum gross weight

and basic empty weight.

REVISED: 5 MAR 2015

1-7

ROBINSON

SECTION 1

R22 SERIES

GENERAL

CONVERSION TABLES

METRIC TO ENGLISH

Multiply

To Obtain

centimeters (cm)

0.3937

inches (in)

kilograms (kg)

2.2046

pounds (lb)

kilometers (km)

0.5400

nautical miles (nm)

kilometers (km)

0.6214

statute miles (mi)

liters (I)

0.2642

gallons, U.S. (gal)

liters (I)

1.0567

quarts (qt)

meters (m)

3.2808

feet (ft)

millibars (mb)

0.0295

inches mercury (in. Hg)

ENGLISH TO METRIC

Multiply

To Obtain

feet (ft)

0.3048

meters (m)

gallons, U.S. (gal)

3.7854

liters (I)

inches (in)

2.5400

centimeters (cm)

inches (in)

25.4000

millimeters (mm)

inches mercury (in. Hg)

33.8638

millibars (mb)

nautical miles (nm)

1.8520

kilometers (km)

pounds (lb)

0.4536

kilograms (kg)

quarts (qt)

0.9464

liters (I)

statute miles (mi)

1.6093

kilometers (km)

1 nautical mile = 1.1508 statute miles

1 statute mile = 0.8690 nautical mile

TEMPERATURE

°F = 9/5 (°C) + 32

°C = 5/9 (°F - 32)

REVISED: 5 MAR 2015

1-8

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

SECTION 2

LIMITATIONS

GENERAL

This section includes operating limitations, instrument

markings, and basic placards required for safe operation

of the helicopter, its engine, and other standard systems.

The helicoper is approved as a normal category rotorcraft

under FAA Type Certificate No. H10WE as Models R22,

R22 Alpha, R22 Beta, and R22 Mariner.

COLOR CODE FOR INSTRUMENT MARKINGS

Red

Operating limit. Edge of red line indicates limit.

Pointer should not enter red during normal

operation.

Yellow Precautionary or special operating procedure

range.

Green

Normal operating range.

AIRSPEED LIMITS

NEVER-EXCEED AIRSPEED (V_NE)

Up to 3000 feet density altitude: 102 KIAS

Above 3000 feet density altitude, see placards on page

2-11.

FAA APPROVED: 26 JUN 2012

2-1

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

ROTOR SPEED LIMITS

TACHOMETER

ACTUAL

READING

RPM

Power On

Maximum

104%

530

Minimum*

101%**

515

Power Off

Maximum

110%

561

Minimum

90%

459

*Transient operation at lower RPM permitted for emergency

procedures training.

**97% (495 RPM) permitted on R22s with O-320 engine

and tachometer with 97% to 104% green arc installed.

POWERPLANT LIMITATIONS

ENGINE

One Lycoming Model O-320 or O-360

OPERATING LIMITS

Engine Maximum Speed

2652 RPM (104%)

Cylinder Head Max Temperature

500°F (260°C)

Oil Maximum Temperature

245°F (118°C)

Oil Pressure***

Minimum during idle

25 psi

Minimum during flight

55 psi

Maximum during flight

95 psi

Maximum during start & warm up

115 psi

Oil Quantitiy, minimum for takeoff

4 qt (3.8 liters)

Manifold Pressure: See placards on pages 2-10 and 2-11

for MAP schedules.

***These limits apply to all engines. Earlier oil pressure

gages show green arc from 60 to 90 psi and red line

at 100 psi. Regulations require that limits indicated by

installed gage are not exceeded.

FAA APPROVED: 26 OCT 2016

2-2

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

WEIGHT LIMITS

Maximum gross weight - Standard & HP 1300 lb (590 kg)

Maximum gross weight - Alpha, Beta,

and Beta II

1370 lb (622 kg)

Minimum gross weight

920 lb (417 kg)

Maximum per seat

including baggage compartment

240 lb (109 kg)

Maximum in either baggage compartment

50 lb (23 kg)

CENTER OF GRAVITY LIMITS

See figures on pages 2-4 and 2-5. Reference datum is 100

inches forward of main rotor shaft centerline.

NOTE

With both doors installed, a solo pilot

plus baggage weight of 135 lb (61 kg) or

greater will ensure CG within limits. For

lower weight, compute weight and balance;

removable ballast may be required to obtain

CG at or forward of aft limit. (See Loading

Instructions in Section 6.)

FAA APPROVED: 5 MAR 2015

2-3

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

FLIGHT AND MANEUVER LIMITATIONS

Aerobatic flight prohibited.

CAUTION

Abrupt control inputs may produce high fatigue

stresses and cause catastrophic failure of a critical

component.

Low-G cyclic pushovers prohibited.

CAUTION

A pushover (forward cyclic maneuver) performed

from level flight or following a pull-up causes a

low-G (near weightless) condition which can result

in catastrophic loss of lateral control. To eliminate

a low-G condition, immediately apply gentle aft

cyclic. Should a right roll commence during a

low-G condition, apply gentle aft cyclic to reload

rotor before applying lateral cyclic to stop the roll.

Flight prohibited with governor selected off, with

exceptions for in-flight system malfunction or emergency

procedures training.

Flight in known icing conditions prohibited.

Maximum operating density altitude 14,000 feet.

Alternator, RPM governor, low rotor RPM warning system,

and OAT gage must be operational for dispatch.

Minimum crew is one pilot in the right seat. A flight

instructor may act as pilot in command from the left seat.

Solo flight from right seat only.

Left seat belt must be buckled.

Operation approved with either or both cabin doors

removed. Loose items in cabin must be properly secured

during doors-off flight.

A functioning headset must be worn by each pilot.

FAA APPROVED: 11 MAY 2020

2-6

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

KINDS OF OPERATION LIMITATIONS

VFR day and night operations are approved.

VFR operation at night is permitted only when landing,

navigation, instrument, and anti-collision lights are opera-

tional. Orientation during night flight must be maintained

by visual reference to ground objects illuminated solely by

lights on the ground or adequate celestial illumination.

Note: There may be additional requirements in countries

outside the United States.

FUEL LIMITATIONS

APPROVED FUEL GRADES

Grade

Color

Specification

100

Green

100LL

Blue

ASTM D910

100VLL

Blue

UL 91

Clear to

Yellow

ASTM D7547

UL 94

(no dye)

Clear to

HJELMCO

Hjelmco Oil, Inc.

Yellow

91/96 UL

Sollentuna, Sweden

(no dye)

TU 38.5901481-96

Yellow

Ukrainian National

Standard

B91/115

Green

GOST 1012-72

Russian National

B95/130

Amber

Standard

FAA APPROVED: 20 JUN 2019

2-7

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

FUEL LIMITATIONS (cont’d)

FUEL CAPACITY

Total Capacity

Usable Capacity

US gallons (liters) US gallons (liters)

Tanks with bladders:

Main tank

18.3 (69)

16.9 (64)

Auxiliary tank

9.7 (37)

9.4 (36)

Combined capacity

28.0 (106)

26.3 (100)

Tanks without bladders:

Main tank

19.8 (75)

19.2 (73)

Auxiliary tank

10.9 (41)

10.5 (40)

Combined capacity

30.7 (116)

29.7 (112)

Note: Per R22 Service Bulletin SB-109A, fuel tanks without

bladders should no longer be in service.

INSTRUMENT MARKINGS

AIRSPEED INDICATOR

Green arc

50 to 102 KIAS

Red line

102 KIAS

ROTOR TACHOMETER

Yellow arc

60 to 70%

Lower red line

90 %

Lower Yellow arc

90 to 101%*

Green arc

101 to 104%*

Upper Yellow arc

104 to 110%

Upper red line

110%

ENGINE TACHOMETER

Yellow arc

60 to 70%

Lower red arc

90 to 101%*

Green arc

101 to 104%*

Upper red arc

104 to 110%

*R22s with O-320 engine may have tachometer with green

arc from 97% to 104% RPM.

FAA APPROVED: 11 MAY 2020

2-8

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

PLACARDS (cont’d)

Near main fuel tank filler cap:

FUEL

100 OCT MIN GRADE AVIATION GASOLINE

FUEL

91/96 MIN GRADE AVIATION GASOLINE

FUEL

AVIATION GASOLINE - GRADE 100LL

OR SEE PILOT’S HANDBOOK

R22s with O-320-A2B or -A2C engine may have:

FUEL

80/87 MIN GRADE AVIATION GASOLINE

Near aux fuel tank filler cap:

AUX FUEL

100 OCT MIN GRADE AVIATION GASOLINE

AUX FUEL

91/96 MIN GRADE AVIATION GASOLINE

AUX FUEL

AVIATION GASOLINE - GRADE 100LL

OR SEE PILOT’S HANDBOOK

FAA APPROVED: 20 JUN 2019

2-12

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

PLACARDS (cont’d)

Near shut-off valve:

FUEL

OFF

Near main tank fuel gage:

For bladder-style tank

16.9 US GAL

For aluminum (non-bladder) tank

19.2 US GAL

Near aux tank fuel gage:

For bladder-style tank

AUX 9.4 US GAL

For aluminum (non-bladder) tank

AUX 10.5 US GAL

In clear view of both occupants:

NO SMOKING

In clear view of pilot (Alpha, Beta, and Beta II with aft

battery installations):

MINIMUM SOLO PILOT WEIGHT 130 LB

(135 LB WITH FULL AUX FUEL)

SEE PILOT’S HANDBOOK FOR SOLO PILOT

WEIGHT LESS THAN 135 LB (61KG)

FAA APPROVED: 26 OCT 2016

2-13

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

PLACARDS (cont’d)

In clear view of pilot:

THIS ROTORCRAFT APPROVED FOR

DAY AND NIGHT VFR OPERATIONS

LOW-G PUSHOVERS PROHIBITED

On left-hand cyclic:

SOLO FROM RIGHT SEAT ONLY

On or near collective controls:

NO STOWAGE

KEEP AREA CLEAR

Inside each baggage compartment:

CAUTION

DO NOT EXCEED ANY OF THE FOLLOWING:

• COMPARTMENT CAPACITY: 50 LB MAX

• COMBINED SEAT PLUS COMPARTMENT: 240 LB MAX

• ROTORCRAFT GROSS WEIGHT LIMIT

SEE ROTORCRAFT FLIGHT MANUAL FOR ADDITIONAL

INSTRUCTIONS

On carburetor air temperature gage:

CAUTION

BELOW 18 IN. MP, IGNORE GAGE

& APPLY FULL CARB HEAT

Near heater push-pull control when heater is installed:

IN CASE OF ENGINE FIRE

PUSH HEATER CONTROL TO OFF

FAA APPROVED: 26 OCT 2016

2-14

ROBINSON

SECTION 2

R22 SERIES

LIMITATIONS

INFORMATION PER FAA AD 95-26-04

The following limitations (1-3) are to be observed unless

the pilot manipulating the controls has logged 200 or more

flight hours in helicopters, at least 50 of which must be

in the RHC Model R22 helicopter, and has completed the

awareness training specified in Special Federal Aviation

Regulation (SFAR) No. 73, issued February 27, 1995.

1. Flight when surface winds exceed

25 knots,

including gusts, is prohibited.

2. Flight when surface wind gust spreads exceed 15

knots is prohibited.

3. Continued flight in moderate, severe, or extreme

turbulence is prohibited.

Adjust forward airspeed to between 60 knots indicated

airspeed (KIAS) and 0.7 V_ne but no lower than 57 KIAS,

upon inadvertently encountering moderate, severe, or

extreme turbulence.

Note: Moderate turbulence is turbulence that causes: (1)

changes in altitude or attitude; (2) variations in indicated

airspeed; and (3) aircraft occupants to feel definite strains

against seat belts.

RHC NOTE

This AD is issued by the FAA and is applicable to

US-registered helicopters.

FAA APPROVED: 20 JUN 2019

2-15

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

SECTION 3

EMERGENCY PROCEDURES

CONTENTS

Page

Definitions

3-1

Power Failure - General

3-1

Power Failure Above 500 Feet AGL

3-2

Power Failure Between 8 Feet and 500 Feet AGL

3-2

Power Failure Below 8 Feet AGL

3-3

Maximum Glide Distance Configuration

3-3

Air Restart Procedure

3-3

Emergency Water Landing - Power Off

3-4

Emergency Water Landing - Power On

3-4

Loss of Tail Rotor Thrust in Forward Flight

3-5

Loss of Tail Rotor Thrust in Hover

3-5

Headset Audio Failure

3-5

Engine Fire During Start on Ground

3-6

Engine Fire in Flight

3-6

Electrical Fire in Flight

3-6

Tachometer Failure

3-7

Governor Failure

3-7

Warning/Caution Lights

3-8

Audio Alerts

3-10

Information per FAA AD 95-26-04

3-11

FAA APPROVED: 11 MAY 2020

3-i

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

SECTION 3

EMERGENCY PROCEDURES

DEFINITIONS

Land Immediately - Land on the nearest clear area where

a safe normal landing can be performed. Be prepared to

enter autorotation during approach, if required.

Land as soon as practical - Landing site is at pilot’s

discretion based on nature of problem and available landing

areas. Flight beyond nearest airport is not recommended.

POWER FAILURE - GENERAL

A power failure may be caused by either an engine or

drive system failure and will usually be indicated by the

low RPM horn. An engine failure may be indicated by a

change in noise level, nose left yaw, an oil pressure light,

or decreasing engine RPM. A drive system failure may

be indicated by an unusual noise or vibration, nose right

or left yaw, or decreasing rotor RPM while engine RPM is

increasing.

In case of power failure, immediately lower collective to

enter autorotation.

CAUTION

Aft cyclic is required when collective is

lowered at high airspeed.

CAUTION

Do not apply aft cyclic during touchdown or

ground slide to prevent possible blade strike

to tailcone.

FAA APPROVED: 26 OCT 2016

3-1

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

POWER FAILURE ABOVE 500 FEET AGL

1. Lower collective immediately to maintain rotor RPM.

2. Establish a steady glide at approximately 65 KIAS. (For

maximum glide distance, see page 3-3.)

3. Adjust collective to keep RPM between 97 and 110%

or apply full down collective if light weight prevents

attaining above 97%.

4. Select landing spot and, if altitude permits, maneuver

so landing will be into wind.

5. A restart may be attempted at pilot’s discretion if

sufficient time is available (See “Air Restart Procedure”,

page 3-3).

6. If unable to restart, turn unnecessary switches and fuel

valve off.

7. At about 40 feet AGL, begin cyclic flare to reduce rate

of descent and forward speed.

8. At about 8 feet AGL, apply forward cyclic to level ship and

raise collective just before touchdown to cushion landing.

Touch down in level attitude with nose straight ahead.

POWER FAILURE BETWEEN 8 FEET AND 500 FEET AGL

1. Lower collective immediately to maintain rotor RPM.

2. Adjust collective to keep RPM between 97 and 110%

or apply full down collective if light weight prevents

attaining above 97%.

3. Maintain airspeed until ground is approached, then begin

cyclic flare to reduce rate of descent and forward speed.

4. At about 8 feet AGL, apply forward cyclic to level ship and

raise collective just before touchdown to cushion landing.

Touch down in level attitude and nose straight ahead.

FAA APPROVED: 21 FEB 2014

3-2

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

EMERGENCY WATER LANDING - POWER OFF

1. Follow same procedures as for power failure over land

until contacting water. If time permits, unlatch doors

prior to water contact.

2. Apply lateral cyclic when aircraft contacts water to stop

rotors.

3. Release seat belt and quickly clear aircraft when rotors

stop.

EMERGENCY WATER LANDING - POWER ON

1. Descend to hover above water.

2. Unlatch doors.

3. Passenger exit aircraft.

4. Fly to safe distance from passenger to avoid possible

injury by rotors.

5. Switch battery and alternator OFF.

6. Roll throttle off into overtravel spring.

7. Keep aircraft level and apply full collective as aircraft

contacts water.

8. Apply lateral cyclic to stop rotors.

9. Release seat belt and quickly clear aircraft when rotors

stop.

FAA APPROVED: 21 FEB 2014

3-4

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

LOSS OF TAIL ROTOR THRUST IN FORWARD FLIGHT

Failure is usually indicated by nose right yaw which cannot

be corrected by applying left pedal.

1. Immediately enter autorotation.

2. Maintain at least 70 KIAS if practical.

3. Select landing site, roll throttle off into overtravel

spring, and perform autorotation landing.

NOTE

When a suitable landing site is not available,

the vertical stabilizers may permit limited

controlled flight at low power settings and

airspeeds above 70 KIAS; however, prior to

reducing airspeed, enter full autorotation.

LOSS OF TAIL ROTOR THRUST IN HOVER

Failure is usually indicated by nose right yaw which cannot

be stopped by applying left pedal.

1. Immediately roll throttle off into overtravel spring and

allow aircraft to settle.

2. Raise collective just before touchdown to cushion

landing.

HEADSET AUDIO FAILURE

If headset audio fails, land as soon as practical.

CAUTION

For aircraft which provide low RPM horn

through the audio system, pilot will not hear

horn with a failed headset.

FAA APPROVED: 11 MAY 2020

3-5

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

ENGINE FIRE DURING START ON GROUND

1. Cranking - Continue and attempt to start which would

suck flames and excess fuel into engine.

2. If engine starts, run at 50-60% RPM for a short time.

3. Fuel mixture - OFF.

4. Fuel valve - OFF.

5. Battery switch - OFF.

6. If time permits, apply rotor brake to stop rotors.

7. Exit helicopter.

ENGINE FIRE IN FLIGHT

1. Enter autorotation.

2. Cabin heat - OFF (if installed and time permits).

3. Cabin vent - ON (if time permits).

4. If engine is running, perform normal landing, then fuel

mixture OFF and fuel valve OFF.

If engine stops running, fuel valve OFF and complete

autorotation landing.

5. Battery switch - OFF.

6. If time permits, apply rotor brake to stop rotors.

7. Exit helicopter.

ELECTRICAL FIRE IN FLIGHT

1. Battery and alternator switches - OFF.

2. Open cabin vents.

3. Land immediately.

4. Fuel mixture OFF and fuel valve OFF.

5. If time permits, apply rotor brake to stop rotors.

6. Exit helicopter.

CAUTION

Low RPM warning system and governor

are inoperative with battery and alternator

switches both off.

FAA APPROVED: 26 OCT 2016

3-6

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

TACHOMETER FAILURE

If rotor or engine tach malfunctions in flight, use remaining

tach to monitor RPM. If it is not clear which tach is

malfunctioning or if both tachs malfunction, allow governor

to control RPM and land as soon as practical.

NOTE

Each tach, the governor, and the low RPM

horn are on separate power circuits. A special

circuit allows the battery to supply power

to the tachs with the battery and alternator

switches both off.

GOVERNOR FAILURE

If engine RPM governor malfunctions, grip throttle firmly to

override the governor, then switch governor off. Complete

flight using manual throttle control.

FAA APPROVED: 20 JUN 2019

3-7

ROBINSON

SECTION 3

MODEL R22

EMERGENCY PROCEDURES

WARNING/CAUTION LIGHTS

NOTE

If a light causes excessive glare at night,

bulb may be unscrewed or circuit breaker

pulled to eliminate glare during landing.

OIL

Indicates loss of engine power or oil pressure.

Check engine tach for power loss. Check

oil pressure gage and, if pressure loss is

confirmed, land immediately.

Continued

operation without oil pressure will cause

serious engine damage and engine failure may

occur.

MR TEMP Indicates excessive temperature of main rotor

gearbox. See note below.

MR CHIP Indicates metallic particles in main rotor

gearbox. See note below.

TR CHIP Indicates metallic particles in tail rotor gearbox.

See note below.

NOTE

If light is accompanied by any indication

of a problem such as noise, vibration, or

temperature rise, land immediately. If

there is no other indication of a problem,

land as soon as practical.

Break-in fuzz will occasionally activate

chip lights. If no metal chips or slivers

are found on detector plug, clean and

reinstall (tail rotor gearbox must be

refilled with new oil). Hover for at least

30 minutes. If chip light comes on again,

replace gearbox before further flight.

FAA APPROVED: 13 OCT 2000

3-8

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

WARNING/CAUTION LIGHTS (cont’d)

LOW

Indicates approximately one gallon of usable

FUEL

fuel remaining for all-aluminum fuel tanks or 1.5

gallons for bladder-style tanks. The engine will

run out of fuel after approximately five minutes

at cruise power for aircraft with all-aluminum

tanks or ten minutes with bladder-style tanks.

CAUTION

Do not use low fuel caution light as

a working indication of fuel quantity.

CLUTCH

Indicates clutch actuator circuit is on, either

engaging or disengaging clutch. When switch

is in the ENGAGE position, light stays on until

belts are properly tensioned. Never take off

before light goes out.

NOTE

Clutch light may come on momentarily

during run-up or during flight to

retension belts as they warm-up and

stretch slightly. This is normal. If,

however, the light flickers or comes

on in flight and does not go out within

10 seconds, pull CLUTCH circuit

breaker and land as soon as practical.

Reduce power and land immediately

if there are other indications of drive

system failure (be prepared to enter

autorotation).

Have drive system

inspected for a possible malfunction.

ALT

Indicates low voltage and possible alternator

failure. Turn off nonessential electrical equipment

and switch ALT off and back on after one second

to reset alternator control unit. If light stays on,

land as soon as practical. Continued flight without

functioning alternator can result in loss of power

to tachometers, producing a hazardous flight

condition.

FAA APPROVED: 26 OCT 2016

3-9

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

WARNING/CAUTION LIGHTS (cont’d)

STARTER

Indicates starter motor is engaged. If light does

not go out when ignition switch is released

from start position, immediately pull mixture

off and turn battery switch off. Have starter

motor serviced.

LOW RPM

Indicates rotor speed below 97% RPM. To

restore RPM, immediately lower collective,

roll throttle on and, in forward flight, apply aft

cyclic. Light is disabled when collective is full

down.

GOV OFF

Indicates engine RPM governor is switched off.

CARBON

Indicates elevated levels of carbon monoxide

MONOXIDE

(CO) in cabin. Shut off heater and open nose

(if installed)

and door vents. If hovering, land or transition

to forward flight. If symptoms of CO poisoning

(headache, drowsiness, dizziness) accompany

light, land immediately.

BRAKE

Indicates rotor brake is engaged. Release

immediately in flight or before starting engine.

FULL

Indicates engine near full throttle. The governor

THROTTLE

will be ineffective because it cannot increase

(if installed)

throttle to maintain RPM. Lower collective as

required to extinguish light.

AUDIO ALERTS

LOW RPM HORN

Horn is provided by a speaker in the side of the instrument

console on earlier aircraft or through the audio system on

later aircraft. The horn activates simultaneously with

the LOW RPM caution light and indicates rotor speed

below 97% RPM. To restore RPM, lower collective, roll

throttle on and, in forward flight, apply aft cyclic. Horn

and Light are disabled when collective is full down.

FAA APPROVED: 11 MAY 2020

3-10

ROBINSON

SECTION 3

R22 SERIES

EMERGENCY PROCEDURES

AUDIO ALERTS (Cont’d)

HIGH RPM WARBLE

On later aircraft, a warble (high/low tone) in the audio

system indicates rotor speed is approaching 110% RPM

limit. Raise collective as required to control RPM.

INFORMATION PER FAA AD 95-26-04

1) RIGHT ROLL IN LOW “G” CONDITION

Gradually apply aft cyclic to restore positive “G”

forces and main rotor thrust. Do not apply lateral

cyclic until positive “G” forces have been established.

2) UNCOMMANDED PITCH, ROLL. OR YAW RESULTING

FROM FLIGHT IN TURBULENCE.

Gradually apply controls to maintain rotor RPM,

positive “G” forces, and to eliminate sideslip.

Minimize cyclic control inputs in turbulence; do not

overcontrol.

3) INADVERTENT ENCOUNTER WITH MODERATE,

SEVERE, OR EXTREME TURBULENCE.

If the area of turbulence is isolated, depart the area;

otherwise, land the helicopter as soon as practical.

FAA APPROVED: 11 MAY 2020

3-11

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

SECTION 4

NORMAL PROCEDURES

CONTENTS

Page

Recommended Airspeeds

4-1

Daily or Preflight Checks

4-1

Before Starting Engine

4-6

Starting Engine and Run-Up

4-7

Takeoff Procedure

4-8

Cruise

4-8

Doors-Off Operation

4-9

Practice Autorotation - Power Recovery

4-9

Practice Autorotation - With Ground Contact

4-10

Use of Carburetor Heat

4-11

Use of Carb Heat Assist

4-11

Descent, Approach, and Landing

4-12

Shutdown Procedure

4-13

Noise Abatement

4-14

Information per FAA AD 95-26-04

4-15

FAA APPROVED: 26 OCT 2016

4-i

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

SECTION 4

NORMAL PROCEDURES

RECOMMENDED AIRSPEEDS

Takeoff and Climb

60 KIAS

Maximum Rate of Climb (V_Y )

53 KIAS

Maximum Range

83 KIAS*

Significant Turbulence

60 to 70 KIAS*

Landing Approach

60 KIAS

Autorotation

60 to 70 KIAS*

* Certain conditions may require lower airspeed.

See V_ne placards in Section 2.

DAILY OR PREFLIGHT CHECKS

Remove ground handling wheels and all covers and

tiedowns. Remove even small accumulations of frost, ice,

or snow, especially from rotor blades. Check maintenance

records to verify aircraft is airworthy.

Check general condition of aircraft and verify no visible

damage, fluid leakage, or abnormal wear. Verify no fretting

at rivets and seams where parts are joined together.

Fretting of aluminum parts produces a fine black powder

while fretting of steel parts produces a reddish-brown or

black residue. Verify Telatemps show no temperature

increase that cannot be attributed to a change in operating

conditions (mechanics draw a reference line to the right

of the highest temperature square which has darkened in

operation). Verify torque stripes on critical fasteners are

not broken or missing.

FAA APPROVED: 11 MAY 2020

4-1

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

DAILY OR PREFLIGHT CHECKS (cont’d)

1. Cowl Doors

Battery switch

Oil pressure and alternator lights

Warning light test switches

Push to test

Fuel quantity

Check gages

Battery switch

OFF

Aux fuel tank quantity

Check

Fuel filler cap

Tight

Aux fuel tank

No leaks

Fuel lines

No leaks

Fuel tank sump drain(s)

Sample

Gearbox oil

Full, no leaks

Rotor brake

Actuation normal

Flex coupling

No cracks, nuts secure

Yoke flanges

No cracks

Gearbox Telatemp

Normal

Sprag clutch

No leaks

Static source

Clear

Control rod ends

Free without looseness

Steel tube frame

No cracks

All fasteners

Secure

Tail rotor control

No interference

Cowl doors

Latched

2. Engine Right Side

Carb air ducts

Secure

Carb heat scoop

Secure

Engine sheet metal

No cracks

Electrical terminals

Tight

Fuel line

No leaks

Oil cooler door

Check

Oil lines

No leaks or chafing

Exhaust system

No cracks

Engine general condition

Check

V-belt condition

Check

V-belt slack

Check

Sprag clutch

No leaks

Upper bearing

No leaks

Telatemp - upper bearing

Normal

FAA APPROVED: 11 MAY 2020

4-2

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

DAILY OR PREFLIGHT CHECKS (cont’d)

2. Engine Right Side (cont’d)

Upper Sheave Condition

Check

Lower sheave groove wear

Smooth & Uniform

Flex coupling

No cracks, nuts secure

Yoke flanges

No cracks

Steel tube frame

No cracks

Tail rotor control

No interference

3. Engine Rear

Cooling fan nut

Pin in line with marks

Cooling fan

No cracks

Fan scroll

No cracks

Teletemps - lower bearing

Normal

Lower bearing

No leaks

4. Empennage

Tail surfaces

No cracks

Fasteners

Secure

Position light

Check

5. Tail Rotor

Gearbox Telatemp

Normal

Gearbox

Oil visible, no leaks

Blades

Clean and no damage/cracks

Pitch links

No looseness

Teeter bearings

Check condition

Teeter bearing bolt

Does not rotate

Control bellcrank

Free without looseness

6. Tailcone

Skins

No cracks or dents

Strobe light condition

Check

Antenna

Check

FAA APPROVED: 11 MAY 2020

4-3

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

DAILY OR PREFLIGHT CHECKS (cont’d)

7. Engine Left Side

Engine oil

4-6 qt

Oil filter (if installed)

Secure, no leaks

Fuel lines

No leaks

Gascolator drain

Sample

Throttle linkage

Operable

Battery and relay (if located here)

Secure

Alternator belt tension

Check

Steel tube frame

No cracks

Engine sheet metal

No cracks

Exhaust system

No cracks

Engine general condition

Check

8. Main Fuel Tank

Quantity

Check

Filler cap

Tight

Leakage

None

9. Main Rotor

CAUTION

Do not pull down on blades to teeter

rotor. To lower a blade, push up on

opposite blade.

Blades

Clean and no damage/cracks

CAUTION

Verify erosion on lower surface of

blades has not exposed skin-to-spar

bond line. Reference Rotor Systems

description in Section 7.

Pitch change boots

No leaks

Main hinge bolts

Cotter pins installed

All rod ends

Free without looseness

All fasteners

Secure

Swashplate scissors

No excessive looseness

FAA APPROVED: 11 MAY 2020

4-4

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

DAILY OR PREFLIGHT CHECKS (cont’d)

10. Fuselage Left Side

Baggage compartment

Check

Removable controls

Secure if installed

Collective control

Clear

Seat Belt

Check condition and fastened

Door

Unlocked and latched

Door hinge safety pins

Installed

Landing gear

Check

Position light

Check

11. Nose Section

Pitot tube

Clear

Windshield condition and cleanliness

Check

Landing lights

Check

Yaw string

Check

12. Fuselage Right Side

Landing gear

Check

Position light

Check

Door hinge safety pins

Installed

Baggage compartment

Check

13. Cabin Interior

Loose articles

Removed or stowed

Seat belt

Check condition

Instruments, switches, and controls . . Check condition

Clock

Functioning

CAUTION

For helicopters with removable con-

trols, remove left seat controls if per-

son in that seat is not a rated helicopter

pilot.

CAUTION

Be sure rotor blades are approximately

level to avoid possible tailcone strike.

FAA APPROVED: 11 MAY 2020

4-5

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

DAILY OR PREFLIGHT CHECKS (cont’d)

CAUTION

When flying solo, fill left baggage compartment

to capacity before using right compartment.

Avoid placing objects in compartments which

could injure occupant if seat collapses during

a hard landing.

CAUTION

Shorter pilots may require cushion to obtain

full travel of all controls. Verify aft cyclic

travel is not restricted.

BEFORE STARTING ENGINE

Seat belts

Fastened

Fuel shut-off valve

Cyclic/collective friction

OFF

Cyclic, collective, pedals

Full travel free

Throttle

Full travel free

Collective

Full down, friction ON

Cyclic

Neutral, friction ON

Pedals

Neutral

Rotor brake

Disengaged

Circuit breakers

Carb heat

OFF

Mixture

Full rich

Mixture guard*

Installed

Primer (if installed)

Down and locked

Landing lights

OFF

Avionics switch (if installed)

OFF

Clutch

Disengaged

Altimeter

Set

Governor switch

* Mixture guard is not used on aircraft with vernier mixture

control on console face.

FAA APPROVED: 21 FEB 2014

4-6

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

STARTING ENGINE AND RUN-UP

Throttle twists for priming

As required

Throttle

Closed

Battery, strobe switches

Area

Clear

Ignition switch

Start, then Both

Starter-On light

Out

Set engine RPM

50 to 60%

Clutch switch

Engaged

Blades turning

Less than 5 seconds

Alternator switch

Oil pressure within 30 seconds

25 psi minimum

Avionics, headsets

Audio alert (if equipped)

Test

Wait for clutch light out

Circuit breakers in

Warm-up RPM

70 to 75%

Engine gages

Green

Mag drop at 75% RPM

7% max in 2 seconds

Carb heat

CAT rise/drop, set as required

Sprag clutch check

Needles split

Doors (if installed)

Closed and latched

Limit MAP chart

Check

Cyclic/collective friction

OFF

Governor On, increase throttle

RPM 102-104%

Warning lights

Out

Lift collective slightly, reduce RPM

Horn/light at 97%

CAUTION

For aircraft which provide low RPM horn

through the audio system, a headset for each

pilot is required to hear the horn.

CAUTION

Avoid continuous operation at rotor speed of

60 to 70% to minimize tail resonance.

CAUTION

On slippery surfaces, be prepared to counter

nose-right rotation with left pedal as governor

increases RPM.

FAA APPROVED: 11 MAY 2020

4-7

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

TAKEOFF PROCEDURE

1. Verify doors latched, governor ON, and RPM stabilized

at 102 to 104%.

2. Clear area. Slowly raise collective until aircraft is light

on skids. Reposition cyclic as required for equilibrium,

then gently lift aircraft into hover.

3. Check gages in green and adjust carb heat if required.

4. Lower nose and accelerate to climb speed following

profile shown by height-velocity diagram in Section 5.

If RPM drops below 102%, lower collective.

CRUISE

1. Adjust carb heat if required. (See page 4-11.)

2. Verify RPM near top of green arc.

3. Set manifold pressure as desired with collective. Observe

MAP and airspeed limits.

4. Pull RT TRIM knob.

5. Verify gages in green, warning lights out.

CAUTION

In turbulence, reduce power and use a slower

than normal cruise speed. If turbulence is

significant or becomes uncomfortable for the

pilot, use 60 to 70 KIAS.

CAUTION

Exercise extreme care never to inadvertently

pull mixture control as engine stoppage will

result.

CAUTION

In-flight leaning with engine mixture control

is not recommended. Engine stoppage may

result as there is no propeller to keep engine

turning should overleaning occur.

FAA APPROVED: 26 OCT 2016

4-8

ROBINSON

SECTION 4

R22 SERIES

NORMAL PROCEDURES

DOORS-OFF OPERATION

Avoid removing left door to protect tail rotor from loose

objects. If left door must be removed, warn passenger

to secure loose objects and to keep head and arms inside

cabin to avoid high velocity airstream.

PRACTICE AUTOROTATION - POWER RECOVERY

1. Adjust carb heat if required. (See page 4-11.)

2. Lower collective to down stop and reduce throttle as

desired for tachometer needle separation.

CAUTION

To avoid inadvertent engine stoppage, do

not chop throttle to simulate a power failure.

Always roll throttle off smoothly. Recover

immediately if engine is rough or engine RPM

continues to drop.

NOTE

Governor is inactive below 80% engine RPM

regardless of governor switch position.

NOTE

When entering autorotation from above 4000

feet, reduce throttle slightly before lowering

collective to prevent engine overspeed.

3. Adjust collective to keep rotor RPM within limits and

adjust throttle for tachometer needle separation.

4. Keep airspeed 60 to 70 KIAS.

5. At about 40 feet AGL, begin cyclic flare to reduce rate

of descent and forward speed.

6. At about 8 feet AGL, apply forward cyclic to level

aircraft and raise collective to control descent. Add

throttle if required to keep RPM in green arc.

FAA APPROVED: 20 JUN 2019

4-9

Robinson R22 Helicopter. MAINTENANCE MANUAL (2018) - page 8