r44 raven ii - flight manual, poh

PILOT'S OPERATING HANDBOOK AND FAA APPROVED ROTORCRAFT FLIGHT MANUAL

RTR 462 THE R44I I IS FAA APPROVED IN NORMAL CATEGORY BASED ON FAR 27 AND FAR 21. THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY FAR 27 AND FAR 21 AND MUST BE CARRIED IN THE HELICOPTER AT ALL TIMES.

HELICOPTER SERIAL NO.

HELICOPTER REGISTRATION NO.

SECTIONS 2, 3, 4, 5, FAA APPROVED BY:

MKNAGER, FLIGHT TEST BRANCH, ANM-I GOL FEDERAL AVIATION ADMINISTRATION LOS ANGELES AIRCRAFT CERTIFICATION OFFICE TRANSPORT AIRPLANE DIRECTORATE

DATE: & a k 3. z o o r

ROBINSON HELICOPTER COMPANY TORRANCE, CALIFORNIA

THIS PAGE INTENTIONALLY LEFT BLANK.

CLASS V SUBSCRIPTION SERVICE

If you wish t o receive future changes to the R44 I1 Pilot's Operating Handbook and copies of Safety Notices, send

a check or money order for U.S. $10.00 to:

ROBINSON HELICOPTER COMPANY 2901 Airport Drive

Torrance, CA 90505

You will receive all changes to the handbook and Safety Notices for a period of one year.

Please print your name, address and telephone number in the space provided below and return this page

together wi th your check or money order.

INTENTIONALLY BLANK

ROBINSON MODEL R44 I1 LOG OF PAGES

LOG OF PAGES APPROVED BY FAA TYPE CERTIFICATE NO. H11NM

Approved By: AL-tLd& Manager, Flight Test Branch, ANM-16OL "'9 Fed era1 Aviation Administration LOS Angeles Aircraft Certification Office Transport Airplane Directorate

Cover Log of Pages

Section 2 Limitations

Section 3 Emergency Procedures

Section 4 Normal Procedures

Section 5 Performance

Sect~on 9 Supplements

Date of Approval: .7-1%~4 13, Z ~ O S

Page No.

2-7 2-8 2-9

2-1 0 2-1 1 2-1 2

3-6 3-7 3-8 3-9

3-10

4-8 4-9

4-10 4-1 1 4-1 2 4-13 4-14

5-5 5-6 5-7 5-8

Approval Date

3 Oct 02 3 Oct 02 3 Oct 02 3 Oct 0 2 3 Oct 0 2 3 Oct 02

3 Oct 0 2 3 Oct 02 3 Oct 0 2 3 Oct 0 2 3 Oct 0 2

3 Oct 0 2 3 Oct 0 2

13 Jun 05 3 Oct 02 3 Oct 02

1 3 Jun 05 3 Oct 0 2

3 Oct 0 2 3 Oct 0 2 3 Oct 0 2 3 Oct 0 2

- Page No.

I

I I

2-i 2-1 2-2 2-3 2-4 2-5 2-6

3-i 3- 1 3-2 3-3 3-4 3-5

4-i 4- 1 4-2 4-3 4 -4 4-5 4-6 4-7

5-i 5-1 5-2 5-3 5 -4

9-i

Approval Date

3 Oct 0 2 1 3 Jun 0 5

3 Oct 02 3 Oct 02 3 Oct 02 3 Oct 0 2 3 Oct 0 2 3 Oct 02 3 Oct 02

3 Oct 02 3 Oct 02 3 Oct 0 2 3 Oct 0 2 3 Oct 0 2 3 Oct 02

3 Oct 02 3 Oct 02 3 Oct 0 2 3 Oct 0 2

13 Jun 05 13 Jun 05

3 Oct 02 13 Jun 05

3 Oct 02 3 Oct 0 2 3 Oct 0 2 3 Oct 0 2 3 Oct 0 2 -- 9 Mar 0 4

ROBINSON MODEL R44 I1 LOG OF PAGES

LOG OF PAGES NOT REQUIRING FAA APPROVAL

REVISED: 13 JUN 2005

Revision Date

3 Oct 0 2 3 Oct 0 2 3 Oct 0 2 3 Oct 02

-

13 Jun 05 13 Jun 05 3 Oct 0 2

3 Oct 02 3 Oct 0 2 3 Oct 02 3 Oct 02 3 O c t 0 2 3 O c t 0 2 3 Oct 0 2 3 Oct 02

13 Jun 05 3 Oct 0 2

13 Jun 05 3 Oct 02 3 Oct 02

13 Jun 05 13 Jun 05 13 Jun 05 1 3 J u n 0 5

3 Oct 0 2 3 Oct 0 2

3 Oct 0 2 3 Oct 0 2

Page Revision Date

3 Oct 0 2 3 Oct 0 2 3 Oct 0 2 3 Oct 02 3 Oct 02

13 Jun 05 13 Jun 05 13 Jun 05 13 Jun 05

3 Oct 0 2 3 Oct 02 3 Oct 0 2 3 Oct 0 2 3 Oct 0 2 3 Oct 0 2 3 Oct 02 3 Oct 02 3 Oct 02 3 Oct 0 2 3 Oct 0 2

1 3 J u n 0 5 3 O c t 0 2

1 3 J u n 0 5

13 Jun 0 5 3 Oct 0 2 3 Oct 02 3 Oct 0 2 3 Oct 0 2 3 Oct 02 3 Oct 0 2

3 Oct 0 2 3 Oct 0 2 3 Oct 0 2

Section 1 General

Section 6 Weight & Balance

Section 7 Systems Description

Section 8 Handling and Maintenance

Section 10 Safety Tips

Page No.

1-5 1-6 1-7 1-8

6-4 6-5 6-6

7-14 7-1 5 7-1 6 7-1 7 7-18 7-19 7-20 7-2 1 7-22 7-23 7-24 7-25 7-26

8-7 8-8 8-9

8-10 8-1 1 8-12

10-3 10-4

No.

I -i 1-1 1-2 1-3 1-4

6-i 6-1 6-2 6-3

7-i 7-1 7-2 7-3 7-4 7-5 7-6 7-7 7-8 7-9

7-10 7-11 7-12 7-13

8-i 8-1 8-2 8-3 8-4 8-5 8-6

10-i 10-1 10-2

ROBINSON SECTION 1 MODEL R44 I1 GENERAL

SECTION 1

GENERAL

CONTENTS

Page

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1

Three-View of R44 Helicopter . . . . . . . . . . . . . . . . . 1-3

Descriptive Data . . . . . . . . . . . . . . . . . . . . . . . . . 1 -4

Performance Definitions . . . . . . . . . . . . . . . . . . . . 1-6

Weight and Balance Definitions . . . . . . . . . . . . . . . 1-7

Conversion Tables . . . . . . . . . . . . . . . . . . . . . . . . 1-8

ISSUED: 3 OCT 2 0 0 2

INTENTIONALLY BLANK


SECTION 1

GENERAL

INTRODUCTION

This Pilot's Operating Handbook is designed as an operating guide for the pilot. It includes material required t o be furnished t o the pilot by FAR 27 and FAR 21. I t also contains supplemental data supplied by the helicopter manufacturer.

This handbook is not designed as a substitute for adequate and competent flight instruction or for knowledge of current airworthiness directives, applicable federal aviation regulations, and advisory circulars. Nor is it intended t o be a guide for basic flight instruction or a training manual. It should not be used for operational purposes unless kept in a current status.

Assuring that the helicopter is in airworthy condition is the responsibility of the owner. The pilot in command is responsible for determining that the helicopter is safe for flight. The pilot is also responsible for remaining wi th in operating limitations as outlined by instrument markings, placards, and this handbook.

Since it is very difficult t o refer t o a handbook while flying a helicopter, the pilot should study the entire handbook and become very familiar w i th limitations, performance, procedures, and operational handling characteristics of the helicopter before flight.

This handbook has been divided into ten numbered sections. Limitations and emergency procedures have been placed ahead of normal procedures, performance, and other sections t o provide easier access t o that information. Provisions for expansion of the handbook have been made b y deliberate omission of certain paragraph numbers, figure numbers, item numbers, and pages noted as being intentionally left blank.

ISSUED: 3 OCT 2002

ROBINSON MODEL R44 I1

SECTION 1 GENERAL

THIS PAGE INTENTIONALLY LEFT BLANK.

!SSLIED: 3 OCT 2002


ROTOR RAD 198 IN.

459 IN. OVERALL

THREE VIEW OF R44 HELICOPTER

ISSUED: 3 OCT 2002


DESCRIPTIVE DATA

MAIN ROTOR

Articulation Free t o teeter and cone, rigid inplane

Number of Blades 2

Diameter 3 3 feet

Blade Chord 10.0 inches inboard, 10.6 inches outboard

Blade Twist -6 Degrees

Tip Speed @ 102% RPM 7 0 5 FPS

TAIL ROTOR

Articulation Free t o teeter, rigid inplane

Number of Blades 2

Diameter 4 feet 1 0 inches

Blade Chord 5.1 inches (constant)

Blade Twist 0

Precone Angle 1 Degree

Tip Speed @ 1 0 2 % RPM 6 1 4 FPS

DRIVE SYSTEM

Engine t o Upper Sheave: Four double Vee-belts w i t h 0.778: 1 speed reducing ratio

Upper Sheave t o Drive Line: Sprag type overrunning clutch

Drive Line t o Main Rotor: Spiral-bevel gears w i th 1 1 :57 speed reducing ratio

Drive Line t o Tail Rotor: Spiral-bevel gears w i th 3 1 :27 speed increasing ratio

ISSUED: 3 OCT 2002 1-4


DESCRIPTIVE DATA (cont'd)

POWERPLANT

Model: Lycoming 10-540-AE1 A5

Type: Six cylinder, horizontally opposed, direct drive, air cooled, fuel injected, normally aspirated

Displacement: 541.5 cubic inches

Maximum continuous rating: 205 BHP at 271 8 RPM (1 0 2 % on tachometer)

5 Minute takeoff rating: 245 BHP at 271 8 RPM

Cooling system: Direct drive squirrel-cage blower

FUEL

Approved fuel grades and capacity: See Section 2.

OIL

Approved oil grades and capacity: See Section 8.

ISSUED: 3 OCT 2002


SECTION 1 GENERAL

PERFORMANCE DEFINITIONS

KlAS Knots Indicated Airspeed is speed shown on the Airspeed Indicator.

KCAS Knots Calibrated Airspeed is speed shown on the Air- speed Indicator corrected for instrument and position error. (See page 5-2 for position error correction.)

KTAS Knots True Airspeed is airspeed relative to undisturbed air. It is KCAS corrected for pressure altitude and temperature.

Vne Never-Exceed Airspeed.

v Y Speed for best rate o f climb.

VI, Stabilized level-flight speed at maximum continuous power.

MSL Altitude above sea level, in feet, indicated by the altimeter Altitude (corrected for position and instrument error) when the ba-

rometric subscale is set t o the atmospheric pressure existing at sea level.

Pressure Altitude, in feet, indicated by the altimeter (corrected for Altitude position and instrument error) when the barometric sub-

scale is set t o 29.92 inches of mercury (101 3.2 mb).

Density Altitude, in feet, in ISA conditions at which the air would Altitude have the same density (it is pressure altitude corrected

for OAT).

I SA International Standard Atmosphere exists when pressure is 29.92 inches of mercury at sea level, temperature is 15OC at sea level, and temperature decreases 1.98OC per 1 0 0 0 feet of altitude.

BHP Brake Horsepower is actual power output of the engine.

MAP Manifold Pressure is the absolute pressure, in inches of mercury, in the engine intake manifold.

RPM Revolutions Per Minute or speed of engine or main rotor. (Shown by Tachometer as percentage of 2665 engine RPM or 4 0 0 main rotor RPM).

MCP Maximum Continuous Power.

TOP Takeoff Power (usually for a maximum of 5 minutes).

Critical Altitude at which full thrott le produces maximum allow- Altitude able power (MCP or TOP).

TOGW Takeoff Gross Weight.

ISSUED: 3 OCT 2002


SECTION 1 GENERAL

PERFORMANCE DEFINITIONS (cont'd) OAT Outside 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 An imaginary vertical plane from which all horizontal Datum distances are measured for balance purposes.

Station A fore-and-aft location along the helicopter fuselage usually given in terms of distance in inches from the reference datum.

Arm Horizontal distance from the reference datum to the center of gravity (CG) o f an item.

Moment The weight of an item multiplied by its arm. (Moment divided by a constant is used to simplify balance calculations by reducing the number of digits).

Center o f Point at which a helicopter would balance i f suspend- Gravity (CG) ed. Its distance from the reference datum is found

by dividing total moment by total weight of the helicopter.

CG Arm Arm from the reference datum obtained by adding individual moments and dividing the sum by the total weight.

CG Limits Extreme center o f gravity locations within which the helicopter must be operated at a given weight.

Usable Fuel Fuel available for flight planning.

Unusable Fuel Fuel remaining after a runout test has been completed in accordance wi th government regulations.

Standard Weight of a standard helicopter including unusable Empty Weight fuel, full operating fluids, and full oil.

Basic Empty Standard empty weight plus weight of installed op- Weight tional equipment.

Payload Weight o f occupants, cargo, and baggage.

Useful Load Difference between maximum takeoff weight and basic empty weight.

ISSUED: 3 OCT 2002 1-7


CONVERSION TABLES

METRIC TO ENGLISH

Multiplv BY centimeters (cm) .3937

kilograms (kg) 2.2046

kilometers (km) .5400

kilometers (km) .6214

liters (I) .2642

liters (I) 1.0567

meters (m) 3.2808

ENGLISH TO METRIC

Multiplv !& feet ( f t ) .3048

gallons, U.S. (gal) 3.7854

inches (in) 2.5400

inches (in) 25.4000

nautical miles (nm) 1.8520

pounds (Ib) .4536

quarts (qt) .9464

statute miles (mi) 1.6093

SECTION 1 GENERAL

To Obtain

inches (in)

pounds (Ib)

nautical miles (nm)

statute miles (mi)

gallons, U.S. (gal)

quarts (qt)

feet ( f t )

To Obtain

meters (m)

liters (I)

centimeters (cm)

millimeters (mm)

kilometers (km)

kilograms (kg)

liters (I)

kilometers (km)

ISSUED: 3 OCT 2002

ROBINSON SECTION 2 MODEL R44 I1 LIMITATIONS

SECTION 2

CONTENTS Page

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . General 2-1

. . . . . . . . . . . . . Color Code for Instrument Markings 2-1

. . . . . . . . . . . . . . . . . . . . . . . . . . . Airspeed Limits 2-1

. . . . . . . . . . . . . . . . . . . . . . . . . Rotor Speed Limits 2-2

. . . . . . . . . . . . . . . . . . . . . . Powerplant Limitations 2-2

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . Weight Limits 2-3

. . . . . . . . . . . . . . . . . . . . . Center of Gravity Limits 2-3

. . . . . . . . . . . . . . . . Flight and Maneuver Limitations 2-5

. . . . . . . . . . . . . . . . Kinds of Operation Limitations 2-6

. . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Limitations 2-6

. . . . . . . . . . . . . . . . . . . . . . . . Instrument Markings 2-7

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Placards 2-9

FAA APPROVED: 3 OCT 2002

INTENTIONALLY BLANK


SECTION 2 LIMITATIONS

SECTION 2

LIMITATIONS

GENERAL

Information contained in Section 2 is approved by the Federal Aviation Administration. This section includes operating limitations, instrument markings, and basic placards required for safe operation of the helicopter, its engine, and other standard systems. This helicopter is approved under FAA Type Certificate No. H 1 1 NM as Model R44 11.

COLOR CODE FOR INSTRUMENT MARKINGS

Red Indicates operating limits. Pointer should not enter red during normal operation.

Red Cross- Indicates power-off Vne. hatch

Yellow Precautionary or special operating procedure range.

Green Normal operating range.

AIRSPEED LlNllTS

NEVER-EXCEED AIRSPEED (Vne)

Up t o 3000 feet density altitude:

2200 Ib TOGW & below 130 KlAS Over 2200 Ib TOGW 120 KlAS Autorotation I00 KlAS

Above 3000 feet density altitude, see placard on page 2-9.

ADDITIONAL AIRSPEED LIMITS

Do not exceed 100 KlAS when operating at power above MCP.

Do not exceed 100 KlAS wi th any door(s) removed.

FAA APPROVED: 3 OCT 2002 2- 1


SECTION 2 LIMITATIONS

ROTOR SPEED LIMITS

TACHOMETER ACTUAL RPM READING

Power On Maximum 102% 408 Minimum 101% 404

Power Off IVlaximum 108% 432 Minimum 90% 360

POWERPLANT LIMITATIONS

ENGINE

One Lycoming Model 10-540-AE1 A5

OPERATING LIMITATIONS

Engine Maximum Speed 2718 RPM (102%

Cylinder Head Max Temperature 500°F (260°C)

Oil Maximum Temperature 245°F (1 18OC)

Oil Pressure Minimum during idle 25 psi Minimum during flight 55 psi Maximum during flight 95 psi Maximum during start & warm up 11 5 psi

Oil Quantity, minimum for takeoff 7 qt

Manifold Pressure: See placard on page 2-9 for MAP schedule.



WEIGHT LIMITS

Maximum gross weight 2500Ibs (1 134 kg)

Minimum gross weight 1600 Ibs (726 kg)

Maximum per seat including baggage compartment 300 Ibs (1 36 kg)

Maximum in any baggage compartment 50 Ibs (23 kg)

Minimum solo pilot plus forward baggage weight with all doors installed is 150 Ibs (68 kg) unless a weight and balance computation shows CG is within limits. Ballast may be required.

CENTER OF GRAVITY (CG) LIMITS

See figure on page 2-4. Datum line is I 0 0 inches forward of main rotor shaft centerline.



FUSELAGE STATION (IN. FROM DATUM)

3 L - '- 8 L

1 1 1 1 1 1 1 1 1 1 r 1 -

232 236 2 4 0 2 4 4 2 4 8 252 256 2 6 0

FUSELAGE STATION (CM FROM DATUM)

CENTER OF GRAVITY LlWllTS



FLIGHT AND MANEUVER LIMITATIONS

Aerobatic flight prohibited.

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 wi th governor selected off, wi th exceptions for in-flight system malfunction or emergency procedures training.

Flight in known icing conditions prohibited.

Maximum operating density altitude 14,000 feet.

Maximum operating altitude 9000 feet AGL to allow landing within 5 minutes in case of fire.

Alternator, RPM governor, low rotor RPM warning system, OAT gage, and hydraulic control system must be operational for flight.

Solo flight from right seat only.

Forward left seat belt must be buckled.

Minimum crew is one pilot.

Doors-off operation up t o 100 KlAS approved with any or all doors removed.

No loose items allowed in cabin during doors- off flight.


ROBINSON SECTION 2 MODEL R44 I1 I-IMITATIONS

FLIGHT AND MANEUVER LIMITATIONS (cont'd)

Avoid abrupt control inputs. They produce high fatigue stresses and could lead t o a premature and catastrophic failure o f a critical component.

KINDS OF OPERATION LIMITATIONS

VFR day is approved.

VFR operation at night is permitted only when landing, navigation, instrument, and anti-collision lights are operational. Orientation during night flight must be maintained by visual reference t o ground objects illuminated solely by lights on the ground or adequate celestial illumination.

Note: There may be additional requirements in countries outside the U.S.

FUEL LIMITATIONS

Approved Fuel Grades:

100LL grade aviation fuel

100 /130 grade aviation fuel

Fuel Capacity:

Main tank total capacity: 31.6 US gallons (1 2 0 liters)

Main tank usable capacity: 30.6 US gallons (1 1 6 liters)

Aux tank total capacity: 18.5 US gallons ( 7 0 liters)

Aux tank usable capacity: 18.3 US gallons (69 liters)



INSTRUMENT MARKINGS

AIRSPEED INDICATOR

Green arc 0 to 130 KlAS Red line 130 KlAS Red cross-hatch 100 KlAS

ROTOR TACHOMETER

Upper red line 108% Green arc 9 0 t o 108% Lower red line 90%

ENGINE TACHOMETER

Upper red line 102% Green arc 101 to 102% Lower red line 101 %

OIL PRESSURE

Lower red line 25 psi Lower yellow arc 25 to 55 psi Green arc 55 to 95 psi Upper yellow arc 95 to 115 psi Upper red line 1 15 psi

OIL TEMPERATURE

Green arc 75 to 245OF (24 t o 1 18OCI Red line 245OF (1 18OC)

CYLINDER HEAD TEMPERATURE

Green arc 200 t o 500°F (93 to 260°C) Red line 5OO0F (260°C)

MANIFOLD PRESSURE

Green arc Yellow arc Red line

15.0 to 23.3 in. Hg 19.1 to 26.1 in. Hg 26.1 in. Hg

Yellow arc denotes variable MAP limits. See placard on page 2-9.


r44 raven ii - flight manual, poh

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