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“Mil Moscow Helicopter Plant” Joint-Stock Company

APPROVED171A1.0000.00 РЛЭ-ЛУ

Mi-171A1 HELICOPTER

FLIGHT MANUAL

171A1.0000.00 РЛЭ

P A R T I

CREW OPERATING PROCEDURES

APPROVED: General Designer of the "Mil MHP" JSC 18.02.05

Title Page

Russia, Moscow, 107113, Sokolnichesky Val, 2Tel/fax: (095) 264-55-71, 264-91-74

telex: 412144 Mil, teletype: 112247 ”Yubilyar”

2005

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FLIGHT MANUAL APPROVED BY IAC AVIATION REGISTER CREW OPERATING PROCEDURES

JSC "Ulan-Ude Aviation Plant"

Russia, 670009, Ulan-Ude, Khorinskaya St., 1

(Manufacturer and Its Address)

171A1.0000.00 РЛЭ (Document No.)

Mi-171A1 HELICOPTER

FLIGHT MANUAL

Applicable to the helicopters operating in Brazil

This Flight Manual has been approved by the IAC Aviation Register in the name of the AerospaceEngineering Center for the helicopter registered in Brazil in compliance with the airworthiness standardsaccepted in Brazil (RBHA), Part 21, Section 21.29

This helicopter should be operated in compliance with the limitations and instructions specified in this document.

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PART I


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RECORD OF REVISIONS

Revision No.

Date

First Edition ............................................................ 0.................................................................... Feb 18/05

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LIST OF EFFECTIVE PAGES

P A R T 1


Page Revision

Title Page 1/2.............................................................. 0

Record of Revisions 3/4.............................................................. 0

List of Effective Pages 5/6.............................................................. 0

Record of Temporary Revisions 7/8.............................................................. 0

Table of Contents 9 to 17/18 ................................................... 0

Section 0 0-1/2 to 0-17/18.......................................... 0

Section 1 1-1/2 to 1-47/48.......................................... 0

Section 2 2-1/2 to 2-67/68.......................................... 0

Section 3 3-1/2 to 3-71/72.......................................... 0

Section 4 4-1/2 to 4-47/48.......................................... 0

Section 5 5-1/2 to 5-37/38.......................................... 0

Section 6 – Supplements

Title Page 1/2 0

Introduction 3/4 0

Supplement No. 1 6-1-1/2 to 6-1-92 ........................................ 0

Supplement No. 2 6-2-1/2 to 6-2-42 ........................................ 0

Supplement No. 3 6-3-1/2 to 6-3-36 ........................................ 0

Supplement No. 4 6-4-1/2 to 6-4-63/64 ................................... 0

Supplement No. 5 6-5-1/2 to 6-5-36 ........................................ 0

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TABLE OF CONTENTS

P A R T 1


Page

Title Page............................................................................................................................................... 1/2

Record of Revisions ................................................................................................................................ 3/4

Lift of Effective Pages.............................................................................................................................. 5/6

Record of Temporary Revisions .............................................................................................................. 7/8

Table of Contents.................................................................................................................................... 9

SECTION 0. SERVICE INFORMATION

Title Page.............................................................................................................. 0-1/2

Table of Contents.................................................................................................. 0-3/4

01. Purpose of Flight Manual.............................................................................................. 0-5

02. Duties of Flight Manual User ........................................................................................ 0-7

03. Accepted Terminology, Abbreviations and Symbols..................................................... 0-8

04. Procedure for Introduction of Revisions and Supplements ........................................... 0-12

05. General Description of Helicopter................................................................................. 0-13

06. Basic Dimensions of Helicopter......................................................................................... 0-14

List of Illustrations

Figure 01. Three-View General Arrangement of Helicopter.................................................... 0-15/16

Figure 02. Interior Layout Cabin............................................................................................. 0-17/18

SECTION 1. LIMITATIONS

Title Page .................................................................................................................... 1-1/2

Table of Contents ......................................................................................................... 1-3

1.1. Certification Basis......................................................................................................... 1-5

1.2. Varieties of Operating Conditions ................................................................................. 1-51.3. Installation of Additional Equipment.............................................................................. 1-5

1.4. Minimum Crew Size...................................................................................................... 1-5

1.5. Carriage of Passengers ................................................................................................ 1-5

1.6. Limitations on Opening of Sliding Windows .................................................................. 1-6

1.7. Mass Limit .................................................................................................................... 1-7

1.8. Center of gravity Limits ................................................................................................. 1-8

1.9. Airspeed Limitations ..................................................................................................... 1-9

1.10. Maximum Wind Velocity Limitations ............................................................................ 1-10

1.11. Vertical Descent Rate Limitations................................................................................ 1-10

1.12. Maximum Flight Altitude Limitations ............................................................................ 1-10

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1.13. Outside Air Temperature Limitations............................................................................ 1-10

1.14. Zones of Dangerous "Altitude-Speed" Combinations of

Helicopters, Categories A and B................................................................................... 1-11

1.15. Piloting Limitations.........................................................................................................1-12

1.16. Limitations at Takeoffs and Landings on Surface with Slopes .......................................1-13

1.17. Main Rotor Speed Limitations........................................................................................1-14

1.18. Power Plant Limitations .................................................................................................1-15

1.19. Electrical Power System Limitations ..............................................................................1-18

1.20. Hydraulic System Limitations.........................................................................................1-18

1.21. Limitations on Flights in Icing Conditions..................................................................... 1-19

1.22. Noise Levels................................................................................................................ 1-19

1.23. Dimensions of Landing Sites and Sub-Soil Strength.................................................... 1-20

1.24. Marking of Instruments ................................................................................................ 1-21


Figure 1.1. Zones of Dangerous "Altitude-Speed" Combinations of

Category A Helicopter.............................................................................................. 1-25/26

Figure 1.2. Nomogram for Determining Helicopter Maximum Permissible

Mass Meeting Category A Requirements in Case of One Engine

Failure ..................................................................................................................... 1-27/28

Figure 1.3. Main Rotor Speed in Autorotation Condition at Minimum

Pitch Versus Helicopter Flight Mass, Flight Altitude and

Outside Air Temperature.......................................................................................... 1-29/30


Category B Helicopter .............................................................................................. 1-31/32

Figure 1.5. Nomogram for Determining Maximum Permissible Mass of

Category B Helicopter at Vertical Takeoff and Landing with

the Use of Ground Effect ............................................................................................1-33/34


Mass Variation Valve Versus Wind Velocity and Direction at Takeoff

and Landing with the Use of Ground Effect ................................................................1-35/36

Figure 1.7. Diagrams of Landing Sites Limited in Dimensions

20×20 m (65×65 ft) and Paths of Normal, Continued and

Aborted Takeoffs of Category A Helicopter .............................................................. 1-37/38

Figure 1.8. Diagram of Landing Site (Airstrip) and Paths of Normal,

Continued and Aborted Takeoffs of Category A Helicopter ...................................... 1-39/40

Figure 1.9. Diagram of Landing Site and Approach Zones at Vertical

Takeoffs and Landings of Category B Helicopter with the

Use of Ground Effect ................................................................................................ 1-41/42

Figure 1.10. Placards and Lighted Signs in Cabins................................................................... 1-43/44

Figure 1.11. Placards on the Outside of Port Side .................................................................... 1-45/46

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Figure 1.12. Placards on the Outside of Starboard................................................................... 1-47/48

List of Tables

Table 1.1. Never Exceed and Minimum Speeds Versus Flight Mass and

Pressure Altitude of Flight............................................................................................... 1-9

Table 1.2. Maximum Wind Velocities............................................................................................. 1-10

Table 1.3. Hydraulic System Limitations ....................................................................................... 1-18

Table 1.4. Minimum Dimensions of Landing Sites .......................................................................... 1-20

SECTION 2. NORMAL PROCEDURES

Title Page ................................................................................................................... 2-1/2

Table of Contents ....................................................................................................... 2-3/4

2.1. Introduction .................................................................................................................... 2-5

2.2. Calculation of Flight........................................................................................................ 2-6

2.3. Preflight Inspection and Check of Systems with Inoperative

Engines.......................................................................................................................... 2-7

2.4. External Inspection of Helicopter.................................................................................... 2-8

2.5. Internal Inspection of Helicopter................................................................................... 2-12

2.6. Preparation for Start..................................................................................................... 2-18

2.7. Start, Warm-Up and Test of Engines............................................................................ 2-20

2.8. Check of Systems and Equipment with Operating Engines.......................................... 2-26

2.9. Taxiing ......................................................................................................................... 2-28

2.10. Takeoff ......................................................................................................................... 2-31

2.11. Climb ............................................................................................................................ 2-36

2.12. Cruising Flight............................................................................................................... 2-38

2.13. Descent and Landing.................................................................................................... 2-40

2.14. Crew Procedures After Landing.................................................................................... 2-46

2.15. Shutdown of Engines.................................................................................................... 2-46

2.16. Flight Engineer-Actions After Leaving Helicopter.......................................................... 2-47

2.17. Extreme-Low-Altitude Flights ........................................................................................ 2-47

2.18. Flights in Mountainous Area ......................................................................................... 2-492.19. Takeoff from and Landings on Dust-Covered, Sand-Covered and Snow-Covered Sites...... 2-54

2.20. Landings on and Takeoffs from Sites Selected in Flight ............................................... 2-57

2.21. Flights in Icing Conditions............................................................................................. 2-60

2.22. Passenger Safety Instructions ...................................................................................... 2-62

2.23. Cabin Attendant’s Duties, Rights and Responsibility .................................................... 2-64


Figure 2.1. Helicopter Walk-Around Inspection Circuit............................................................. 2-65/66

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Figure 2.2. Position of Conventional "Pilot’s Eyes – Leaf Sight –Line of Sight

on Windshield –Touchdown Point"Line During Approach of

Category A Helicopter................................................................................................ 2-67/68

SECTION 3. CREW PROCEDURES IN EMERGENCY AND IN THE EVENT

OF FAILURES (MALFUNCTIONS) OF SYSTEM AND EQUIPMENT

Title Page........................................................................................................................ 3-1/2

Table of Contents............................................................................................................... 3-3

3.1. General ............................................................................................................................. 3-7

3.1.1. Basic Rules ....................................................................................................................... 3-7

3.1.2. Determination.................................................................................................................... 3-7

3.1.3. Warning and Caution System............................................................................................ 3-8

3.2. Crew Operating Procedure................................................................................................ 3-9

3.2.1. Fire in Engine and Auxiliary Power Unit Compartments or in Helicopter Cabins ............... 3-9

Fire on Ground .................................................................................................................. 3-9

Fire in Flight..................................................................................................................... 3-10

Fire in Engine Compartment............................................................................................ 3-10

Fire in Auxiliary Power Unit Compartment ....................................................................... 3-11

Fire in Helicopter Cabins................................................................................................. 3-12

3.2.2. Failure of Two Engines in Flight ...................................................................................... 3-15

3.2.3. Failure of One Engine in Flight ........................................................................................ 3-163.2.4. Troubles Requiring Emergency Shutdown of One of Engines ........................................ 3-28

3.2.5. Troubles Malfunctions of Gearboxes............................................................................... 3-34

3.2.6. Failure of Directional Control ........................................................................................... 3-35

3.2.7. Troubles in Cooling System of Various Equipment in Flight ............................................ 3-39

3.2.8. Failure and Troubles of Hydraulic System....................................................................... 3-39

(A) Failure of Main Hydraulic System.............................................................................. 3-39

(B) Excess of Nominal Pressure in Main Hydraulic System ............................................ 3-40

(C) Considerable Increase of Frequency of Variation of Operating

Pressure in Main Hydraulic System Caused By Nitrogen

Leakage from Both Hydraulic Accumulators.............................................................. 3-40(D) Failure of Auxiliary Hydraulic System with Main Hydraulic

System Operating ..................................................................................................... 3-41

(E) Failure of Pressure Transmitter or Indicator in Main (Auxiliary) Hydraulic System........... 3-41

(F) Failure of Master Slide Valve of the KAU-80B (КАУ-80Б)Combination Control Hydraulic Booster in One of Helicopter

Control Channels ...................................................................................................... 3-42

3.2.9. Remaining Fuel Reserve of 145 L ................................................................................... 3-43

3.2.10. Failure of Fuel Boost Pumps............................................................................................ 3-44

3.2.11. "Vortex Ring" Mode.......................................................................................................... 3-45

3.2.12. Disturbance of Main Rotor Balancing............................................................................... 3-46

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3.2.13. Occurrence of Low-Frequency Vertical Oscillations in Flight........................................... 3-46

3.2.14. Spontaneous Counterclockwise Rotation of Helicopter at Vertical

Takeoff or Landing.......................................................................................................... 3-47

3.2.15. Ground Resonance......................................................................................................... 3-49

During Engine Test

During Taxiing, Takeoff or Landing Run

3.2.16. Pilot’s Actions Before Emergency Landing and Crew Operating

Procedures After Emergency Landing on Ground........................................................... 3-49

3.2.17. Cabin Attendant’s Actions ............................................................................................... 3-50

In Case of Passenger State of Health Worsening in Flight ............................................. 3-50

During Emergency Landing on Dry Land........................................................................ 3-50

3.2.18. Failures and Troubles of Fuel System............................................................................. 3-51

Off-Design Decrease in Fuel Reserve ............................................................................ 3-51

Decrease of Fuel Level in Flow-Compensating Chamber Below

Tolerable Value .............................................................................................................. 3-51

Clogging of Fuel Filter .................................................................................................... 3-52

Failure of Fuel Quantity Indicator.................................................................................... 3-52

3.2.19. Failures and Troubles of Electrical Power System .......................................................... 3-52

Failure of Two Generators in Flight ................................................................................ 3-52

Failure of Both Rectifiers ................................................................................................ 3-54

Storage Battery Charge Overcurrent .............................................................................. 3-54

Rise of Storage Battery Temperature Over 71 °C........................................................... 3-55

3.2.20. Failures and Troubles of Landing Gears ......................................................................... 3-56

Trouble of Landing Gear Legs or Wheels....................................................................... 3-56

3.2.21. Failure and Troubles of Helicopter Control Systems ....................................................... 3-56

Failure of Trim Switch or Electromagnetic Brakes .......................................................... 3-56

Failure of Longitudinal Control Hydraulic Stop in Flight .................................................. 3-57

Failure of SPUU-52 (СПУУ-52) Tail Rotor Pitch Limit System........................................ 3-58

3.2.22. Troubles of Instruments and Signalling Devices Monitoring

Transmission Operation.................................................................................................. 3-58Trouble of Oil Pressure Indicator in Main Gearbox ......................................................... 3-58

Troubles of Oil Temperature Indicators in Gearboxes..................................................... 3-59

Troubles of Indicators and Signalling Devices of Main Rotor

Rotational Speed ............................................................................................................ 3-60

3.2.23. Troubles of Instruments and Signalling Devices Monitoring Operation of Engines.......... 3-60

3.2.24. Troubles of Ice Protection System................................................................................... 3-62

Troubles of Engine Ice Protection System and Dust Protection Devices ........................ 3-62

Troubles of Ice Protection System of Rotors................................................................... 3-62

Troubles of Windshield Heating System ......................................................................... 3-64

Troubles of Windshield Wiper ......................................................................................... 3-64

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3.2.25. Failure and Troubles of Autopilot ..................................................................................... 3-65

Failure of Channels (Channel)......................................................................................... 3-65

Impossibility of Introducing Corrections with the Use of Pitch Trim Control Knobs .......... 3-65

3.2.26. Troubles of Lighting Facilities .......................................................................................... 3-66

Trouble of Integral Red Lights ......................................................................................... 3-66

Troubles of Light Caution Indication System ................................................................... 3-66

Failure of FPP-7M (ФПП-7М) Searching-Landing Lights................................................. 3-67

3.2.27. Troubles of BUR-1-2 (БУР-1-2) Flight Data Recorder (FDR) ........................................... 3-67

3.2.28. Troubles of Pneumatic System ..........................................................................................3-67

Failure of Wheel Brakes .................................................................................................. 3-673.2.29. Troubles of Oxygen Equipment........................................................................................ 3-68

3.2.30. Failures and Troubles of Flight-Control Equipment .......................................................... 3-68

Failure of Pilot’s and Co-Pilot’s Speed Indicators ........................................................... 3-68

Failure of Pilot’s or Co-Pilot’s Speed Indicator ................................................................ 3-69

Trouble of Pitot and Static Pressure System

of Pitot-Static Tube.......................................................................................................... 3-70

Failures of Two AGB-96 ( АГБ-96) Gyro Horizons............................................................ 3-70

3.2.31. Failures of Navigation Equipment ............................................................................... 3-71/72

Failure of GMK-1GE (ГМК-1ГЭ) Gyro-Magnetic Compass System ............................ 3-71/72

Failure of ARK-15 ( АРК-15) Automatic Direction Finder............................................. 3-71/72SECTION 4. HELICOPTER PERFORMANCE

Title Page....................................................................................................................... 4-1/2

Table of Contents.............................................................................................................. 4-3

Introduction ....................................................................................................................... 4-5

4.1. Basic Determining Data .................................................................................................... 4-6

4.2. Hovering. Main Rotor Thrust Characteristics..................................................................... 4-8

4.3. Takeoff .............................................................................................................................. 4-9

4.4. Climb............................................................................................................................... 4-11

4.5. Cruising Flight................................................................................................................. 4-12

4.6. Descent........................................................................................................................... 4-13

4.7. Landing ........................................................................................................................... 4-14

4.8. Aerodynamic Corrections for Airspeed Indicators ........................................................... 4-16

4.9. Aerodynamic Corrections for Altimeters.......................................................................... 4-16


CAUTION. THE LIST OF ILLUSTRATIONS OF SECTION 4 CONTAINS A CERTAIN PART OF ILLUSTRATIONS

DETERMINING THE HELICOPTER PERFORMANCE. THE ILLUSTRATIONS PROPER ARE GIVEN

IN SECTION 1.

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Figure 1.2. Nomogram for Determining Helicopter Maximum Permissible Mass

Meeting Category A Requirements in Case of One Failure Engine.................................... 1-27/28

Figure 1.3. Main Rotor Speed in Autorotation Condition at Minimum Pitch Versus Helicopter Flight Mass,

Flight Altitude and Outside Air Temperature..................................................................... 1-29/30

Figure 1.4. Zones of Dangerous "Altitude-Speed" Combinations of Category B Helicopter...... 1-31/32

Figure 1.6. Nomograms for Determining Helicopter Maximum Permissible

Mass Variation Value Versus Wind Velocity and Direction at

Takeoff and Landing with the Use of Ground Effect ................................................ 1-35/36

Figure 4.1. Helicopter Mass Versus Actual Rotational Speed of Engine Gas

Generators in Hovering Out of Ground Effect ......................................................... 4-17/18

Figure 4.2. Main Rotor Thrust Versus Hovering Height Above GroundSurface ................................................................................................................... 4-19/20

Figure 4.3. Curves for Determining Critical Decision Point and Rejected

Takeoff Distance ..................................................................................................... 4-21/22

Figure 4.4. Vertical Speed Versus Altitude and Ambient Air Temperature,

with One Engine Operating at 30-Minute Power at Best Speed

(Dust Protection Device and Ice Protection System

are Switched Off) .................................................................................................... 4-23/24

Figure 4.5. Vertical Speed Versus Altitude and Ambient Air Temperature,

with One Engine Operating at 2.5-Minute Power

at Vsfty (Vsfty IAS = 90 km/h (50 kt) and at H ≤ 2000 m (6.560 ft),

Vsfty IAS = 85 km/h (45 kt) and at H > 2000 m (6.560 ft)(Dust Protection Device and Ice Protection System

are Switched Off) .................................................................................................... 4-25/26

Figure 4.6. Normal and Rejected Takeoff Paths and Rejected Takeoff

Distance Lrej. t.o of Helicopter Belonging to Category B............................................ 4-27/28

Figure 4.7. Change in Minimum, Best, Cruising and Never-Exceed Flying

Speeds (True) Depending on Helicopter Altitude

and Gross Mass...................................................................................................... 4-29/30

Figure 4.8. Change in Minimum, Best, Cruising and Never-Exceed Flying

Speeds (Indicated) Depending on Helicopter Altitude

and Gross Mass...................................................................................................... 4-31/32

Figure 4.9. Vertical Speed Versus Altitude and Ambient Air Temperature,with Two Engines Operating at Maximum Continuous Power

and at Best Speed (Dust Protection Devices and Ice Protection

System are Switched Off) ....................................................................................... 4-33/34

Figure 4.10. "Vortex Ring" Zone.................................................................................................. 4-35/36

Figure 4.11. Helicopter Flight Parameters at Main Rotor Autorotation

Depending on Flight Speed and Gross Mass........................................................... 4-37/38

Figure 4.12. Helicopter Normal Landing Performance Data ........................................................ 4-39/40

Figure 4.13. Continued and Aborted Landings Performance Data

of Helicopter............................................................................................................. 4-41/42

Figure 4.14. Curve Showing Position Error Corrections to Airspeed

Indicator................................................................................................................... 4-43/44

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Figure 4.15. Equivalent Airspeed Versus Indicated Airspeed....................................................... 4-45/46

Figure 4.16. Radius of Turn Versus Flight Speed and Angle of Roll............................................. 4-47/48

SECTION 5. HELICOPTER WEIGHT AND BALANCE DATA

Title Page............................................................................................................................................. 5-1/2

Table of Contents.................................................................................................................................... 5-3

Introduction ............................................................................................................................................. 5-5

5.1. General ............................................................................................................................................ 5-6

5.1.1. Purpose of Helicopter.................................................................................................................... 5-6

5.1.2. Helicopter Center of Gravity and Mass Limits ............................................................................... 5-6

5.1.3. Refill Capacity of Fuel Tanks......................................................................................................... 5-65.2. Helicopter Mass Data....................................................................................................................... 5-7

5.2.1. Helicopter Takeoff Mass Composition........................................................................................... 5-7

5.2.2. Examples of Helicopter Loading Variants...................................................................................... 5-7

5.2.3. Additional Operational Items ....................................................................................................... 5-10

5.2.4. Dependence of Number of On-Line Passengers on Helicopter Fuel Load .................................. 5-10

5.3. Helicopter Center of Gravity........................................................................................................... 5-11

5.3.1. General Data on Center of Gravity.............................................................................................. 5-11

5.3.2. Calculations of Helicopter Centers of Gravity.............................................................................. 5-11

5.3.3. Calculations of Helicopter Takeoff Masses and Centers of Gravity ............................................. 5-12

5.3.4. Calculations of Helicopter Operating Center of Gravity Limits..................................................... 5-12

5.4. Helicopter Loading .................................................................................................................... 5-33/34


Figure 5.1. Diagram of Helicopter Body Axes .................................................................................. 5-35/36

Figure 5.2. Envelope of Helicopter Tolerable Masses and Centers of Gravity

with Account for Loads on Landing Gear .........................................................................5-37/38

List of Tables

Table 5.2.1. Examples of Helicopter Loading Variants......................................................................... 5-8

Table 5.3.1. Masses, Centers of Mass Coordinates, Loading Moments and

Equipment of Helicopter ................................................................................................ 5-12

Table 5.3.2. Calculation of Helicopter Empty Mass and Center of Gravity,

Takeoff Mass and Center of Gravity of Helicopter.................................................................. 5-26

Table 5.3.3. Calculation of Forward Center of Gravity Limit of

Helicopter ...................................................................................................................... 5-30

Table 5.3.4. Calculation of Aft Center of Gravity Limit of Passenger

Helicopter ...................................................................................................................... 5-31

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SECTION 6. SUPPLEMENTS

Title Page......................................................................................................................... 1/2

Introduction ...................................................................................................................... 3/4

Supplement 1. Instrument Flights................................................................................. 6-1-1/2 to 6-1-89/90

Supplement 2. Flights in Active Thunderstorm and Heavy Shower

Zones........................................................................................................ 6-2-1/2 to 6-2-42

Supplement 3. Search Flights ........................................................................................... 6-3-1/2 to 6-4-36

Supplement 4. Overwater Flights................................................................................ 6-4-1/2 to 6-5-63/64

Supplement 5. Flights Assisted with Pitch Detector .......................................................... 6-5-1/2 to 6-5-36

PART 2

DESIGN DATA

SECTION 7. DESCRIPTION OF SYSTEMS AND EQUIPMENT

SECTION 8. OPERATION AND MAINTENANCE

SECTION 9. ADDITIONAL INFORMATION

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SERVICE INFORMATION

Table of Contents

Page

Title Page.......................................................................................................................... 0-1/2

Table Contents.................................................................................................................. 0-3/4

01. Purpose of Flight Manual ..................................................................................................... 0-5

02. Duties of Flight Manual User ................................................................................................ 0-7

03. Accepted Terminology, Abbreviations and Symbols............................................................. 0-8

04. Procedure for Introduction of Revisions and Supplements................................................. 0-12

05. General Description of Helicopter ........................................................................................ 0-13

06. Basic Principal Dimensions of Helicopter ...................................................................... 0-15/16


Figure 0.1. Three-View General Arrangement of Helicopter ......................................................... 0-17/18

Figure 0.2. Interior Layout of Mi-171A1 (Ми-171 А1)Helicopter Passenger Cabin ....................................................................................... 0-19/20

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01. Purpose of Flight Manual

The Flight Manual of the Mi-171A1 (Ми-171 А1) helicopter has been worked out by the "Mil MoscowHelicopter Plant" joint-stock company (hereinafter referred to as "Mil MHP" JSC). Reissue of the

Flight Manual, development of the Supplements and Revisions to it, including the temporary

revisions, without consent of the "Mil MHP" JSC are intolerable.

This Flight Manual of the Mi-171A1 (Ми-171 А1) helicopter is the basic document determining andregulating the particular flight operation rules for the given helicopter within the scope required for

ensuring the helicopter airworthiness in compliance with the SB 17.29 (СБ 17.29) Certification Basis.

The requirements laid down in this Flight Manual shall be mandatory for all flying personnel during the

flight operation of the given type of helicopter.

The Flight Manual consists of two parts:

Part I – CREW OPERATING PROCEDURES.

Part II – DESIGN DATA.

Parts I and II of the Flight Manual are issued in separate books.

Part I contains the following sections:

Section 0 – SERVICE INFORMATION;

Section 1 – LIMITATIONS;

Section 2 – NORMAL PROCEDURES;

Section 3 – EMERGENCY PROCEDURES AND PROCEDURES IN THE EVENT OF FAILURES

(MALFUNCTIONS) OF SYSTEMS AND EQUIPMENT;

Section 4 – PERFORMANCE;

Section 5 – WEIGHT AND BALANCE DATA;

Section 6 – SUPPLEMENTS.

Part II contains the following sections:

Section 7 – DESCRIPTION OF SYSTEMS AND EQUIPMENT;

Section 8 – MAINTENANCE AND SERVICING;

Section 9 – ADDITIONAL INFORMATION.

The rules for flight operations of the Helicopter Mi-171A1 furnished with standard equipment are laiddown in Sections 0 to 4 and 7 to 9.

NOTE. The helicopter furnished with standard equipment configuration is the helicopter furnished

with minimum equipment components. The list of minimum components of the equipment of

standard configuration is presented in Item 5 of Table 5.3.1, Section 5 of the Flight Manual.

Section 5 of the Flight Manual contains the weight and balance data on the helicopters of various

versions of employment, furnished both with the standard equipment configuration and with

additionally installed equipment.

Section 6 is a Supplement to the Flight Manual and contains the information on peculiarities of

operation of a cargo/helicopter as well as the passenger and cargo/helicopters furnished with

additional equipment different from the standard equipment configuration.

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Each Supplement is an independent document and in its general construction is similar to the Flight

Manual. However, the Supplement shall be used together with the Flight Manual.

The materials placed in Parts I of the Flight Manual and each Supplement contain the certain

limitations, rules and recommendations of the Mi-171A1 (Mи-171 А) helicopter flight operation,approved by the IAC Aviation Register.

Revisions and amendments shall be introduced into Part I only with consent and approval of the IAC

Aviation Register.

Parts II of the Flight Manual and each Supplement contain the information on construction of the

helicopter, its systems and equipment, information on operation and maintenance as well as the other

information which the developer considers to be brought to the crew. Parts II of the Flight Manual and

each Supplement shall not be subject to approval by the IAC Aviation Register.

If necessary, the revisions and amendments are introduced in Part II by the "Mil MHP" JSC or by the

operators in consultation with the "Mil MHP" JSC.

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02. Duties of Flight Manual User

1. The Flight Manual user is the pilot.

2. The Flight Manual user bears responsibility for timely and correct introduction of all issued revisions and

supplements in compliance with the established order.

3. This Flight Manual corresponds to its purpose provided it is timely brought in conformity with

introduced revisions.

CAUTION. ANY MISSION OF THE HELICOPTER WITHOUT THE FLIGHT MANUAL ABOARD IS

PROHIBITED.

THE PILOT BEARS RESPONSIBILITY FOR KEEPING THE FLIGHT MANUAL ABOARD

THE HELICOPTER.

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03. Accepted Terminology, Abbreviations and Symbols

The Flight Manual text is laid down with due account of the generally used aviation terminology

acceptable not only for quick familiarization and memorization of the crew operating procedures and

other service information, but also for facilitation and speeding-up of the analysis and learning of the

Instructions.

On actions in all situations which may occur during pre-flight preparations, flight and after touchdown.

The special accents of the crew attention attraction in the Flight Manual are presented in three forms

of display in the text: "WARNING", "CAUTION" and "Note".

The "WARNING" form is used only for the important instructions when nonfulfilment of certain

prescribed actions or wrong actions may lead to the immediate safety risk – to the dangerous in their

consequences failures of equipment (materiel) or to essential and transient changes in the flight

regime.The "CAUTION" form is used when nonfulfilment of certain prescribed actions or wrong actions may

lead to undesirable consequences, occurrence of troubles, malfunctions or to reduction of

serviceability of the certain systems and equipment.

The "Note" form is used in presenting the auxiliary texts containing the explanation of the previous

basic material, additional (secondary) information, etc.

For reducing the volume of the Flight Manual, its text contains the following abbreviations and

symbolic designations of separate, most frequently used terms, words and groups of words.

Abbreviations:

ADF – automatic direction finder

AC – aircraft clock

A/C – aircraft

ALT CONT – altitude controller

AM – amplitude modulation

ANT – antenna

AP – autopilot

APU – auxiliary power unit

ATC – air traffic control

AUTO – automatic control unit

IAC – Inter-State Aviation Committee

BATT – storage battery

C/A – cabin attendant

CDP – check decision point

COMP – compass

CHK – check

CP – co-pilot

CP – control panel

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CS – compass system

CTL – control

C-W – continuous-wave communication

DG – directional gyro

DTK – desired track

DUST PROT – dust protection device

EEC – engine electronic light

EMER – emergency

ENG – engine

EWS – emergency warning system

EXT PWR – external power

F/E – flight engineer

FGD – flux-gate detector

FIRE EXT – fire extinguishing

FM – flight manual

GCA – ground-controlled approach system

GC (ALL) – general call to all stations

GEN – generator

GH – gyro horizon

HDG – selected heading

HIS – horizontal situation indicator

ICE PROT (IPS) – ice protection system

IFR – instrument flight rules

IN LOC – inner locator

MAN – manual

MH – magnetic heading

MR – main rotor

MWL – master warning light

NAV LT – navigation lights

NS – noise suppressor

OFF – switched off

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ON – switched on

OPER – operating

OUT LOC – outer locator

PITOT – pitot static tube

RB – relative bearing

REC – recorder

REG – regulator

R-S – rough sea

RWY – runway

SIGNAL – signalling

STBY – standby

STCL – separate throttle control lever

SW – short wave

SWBS – stall warning and barrier system

SYS – system

TR – transformer

TR – tail rotor

VFR – visual flight rules

VHF – very high frequency

VOICE – voice communication

Symbols:

A, B, C – AC phases, AC buses

~ – alternating current

= – direct current

ft – foot

ft/min – foot/minute

in – inch

kg – unit of measurements of mass

kt – knot (mile/hour)

lb – libra

Nm – nautical mile

Max – maximum

Min – minimum

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m – mass

m A – helicopter mass according to category A

VNE – never exceed speed of flight

Vind – indicated airspeed

Vsafe – safe climb speed

Vo.c – optimum (best) climb speed

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04. Procedure for Introduction of Revisions and Amendments

In the process of service of the helicopters, the Flight Manual is refined and brought in conformity

with due account of structural changes and installation of the new equipment as well as accumulation

and perfection of the in-service experience.

The Flight Manual is refined by replacing the sheets (adding the new sheets). The issued revisions

sheets (of a standard form) are sent to the Flight Manual users. The record of revisions effective for

the given Flight Manual is carried out in the form of the record of revisions and record of temporary

revisions sheets.

Parts 1 and 2 of the Flight Manual have the own record of revisions and record of temporary revisions

sheets.

The record of revisions sheets of Flight Manual Part 1 and Supplements contain the information on

approval of revisions by the IAC Aviation Register.

A vertical line applied to a margin of a sheet on its outside against the text indicates that this portion

of text is affected by a current revision or amendment.

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05. General Description of Helicopter

The Mi-171A1 (Ми-171 А1) helicopter furnished with the standard equipment configuration ispermitted to carry the passengers up to 26 persons.

When the respective equipment is installed in the helicopter by the customer’s decision, the helicopter

may be employed in the a search and rescue version – for searching a distressed aircraft with the aid of

an automatic VHF radio beacon.

Apart from that, when the additional equipment is installed in the helicopter by the customer’s

decision, the helicopter in the above-mentioned versions may be permitted for the following flights:

– instruments flights;

– flights in the thunderstorm activity and heavy showers areas;

– overwater flights.

The peculiarities of the helicopter operation in the cargo/passenger, search and rescue versions and

also in the various conditions are laid down in Section 6 "Supplement" of the Flight Manual.

The Mi-171A1 (Ми-171 А1) helicopter is manufactured according to the single-rotor lay-outconfiguration with five-blade main rotor and three-blade tail rotor.

The helicopter mounts two TV3-117VM (TB3-117BM) turboshaft engines and AI-9V ( АИ-9В) auxiliarypower unit to start them.

The helicopter rotor drive system consists of a main gearbox, transmission shaft, intermediate and

tail gearboxes.

The total fuel reserve (2800 lit) is arranged in two main fuel tanks on the fuselage port side and starboard.

If necessary, for increasing the flying range (during the helicopter ferries), one additional fuel tank of

915±10 liter capacity may be installed inside the fuselage on port side, with the passenger seatsbeing removed.

The helicopter port side mounts an entrance stairs (door) with handrail, the fuselage tail section

mounts an entrance door with emergency exit hatch and droppable stairs.

For carriage of passengers, the helicopter cabin accommodates 13 two-place seats (for 26 persons).

By the operator’s decision, a buffet may be installed in the passenger cabin instead of a pair of seats

being removed on the starboard at frame No. 12. In this case, the passengers carried shall be no more

than 24 in number.

A lavatory is arranged behind port side frame No. 13.

A hinged seat is arranged for the cabin attendant at the entrance stairs (door). The cabin attendant’s

work station is provided with the radio facilities for communication with the flight crew.

The passenger seats and cabin attendant’s folding seat are furnished with waste safety belts havinga fastener of single-shot action.

For arranging the passenger property (luggage) and clothes, a storage room with baggage compartment

is provided in the passenger cabin rear section.

The passenger cabin interior layout of the Mi-171A1 (Ми-171 А1) helicopter is shown in Figure 0.2.

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06. Basic Dimensions of Helicopter

General Data

Helicopter length, m (in):

– without main and tail rotors ..................................................................................... 18.854 (742.28);

– with rotating main and tail rotors ............................................................................. 25.310 (996.45).

Helicopter height, m (in):

– without tail rotor......................................................................................................... 4.865 (191.53);

– with rotating tail rotor................................................................................................. 5.544 (218.26).

Distance from ground to the fuselage bottom point

(clearance), m (in) ............................................................................................................ 0.445 (17.5).

Rotor diameters, m (in):

– main rotor ...................................................................................................................... 21.3 (838.5);

– tail rotor ................................................................................................................... 3.908 (153.858).

Main landing gear wheel track at parking, m (in) ............................................................ 4.510 (177.5).

Wheelbase, m (in) .......................................................................................................... 4.281 (168.5).

Overall dimensions of passenger cabin and doors

Passenger cabin:

– length (with reference to cabin floor), m (in) .............................................................. 5.340 (210.23);

– maximum width, m (in) .............................................................................................. 2.340 (92.125);

– height, m (in) ............................................................................................................. 1.800 (70.866).Port side entrance stairs/door aperture:

– width, m (in) ..................................................................................................................0.825 (32.48):

– height, m (in) ............................................................................................................. 1.405 (55.314).

Entrance door aperture in rear doors:

– width, m (in) .............................................................................................................. 0.750 (29.527);

– height, m (in) ............................................................................................................... 2.000 (78.74).

Passenger cabin aperture with rear doors open:

– width, m (in) ................................................................................................................ 2.000 (78.74);

– height, m (in) ...............................................................................................................1.600 (62.992).

The three-view general arrangement of the helicopter is shown in Figure 0.1.

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Three-View General Arrangement of Helicopter

Figure 0.1

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1. Flight Compartment Right Sliding Window2. Access Door in Flight Compartment Ceiling3. FASTEN SEAT BELTS, NO SMOKING

(ПРИСТЕГНУТЬ ПРИВЯЗНЫЕ РЕМНИ, НЕ КУРИТЬ)Lighted Sign

4. Covers and Domes of Lighting5. EXIT (ВЫХОД) Lighted Sign6. Emergency Exit Hatch-Window7. Crash Axe8. OR-1-2-20-30 (ОР-1-2-20-30) Hand Fire Extinguisher9. Two Bottles of Therapeutic Oxygen Equipment10. Door and Stairs in Small Doors of Fuselage11. Coat Room Curtain12. Hatch in Passenger Cabin Floor13. Side Panels of Interior Furnishing14. Dummy Panel15. GLF5 (EROS) Oxygen Supply Unit, MS10-06-125

(MC10-06-125) Oxygen Mask, MH210-00 (MX210-00)Smoke Goggles

16. Co-Pilot’s Seat17. Flight Engineer’s Seat

18. Passenger Cabin Right Partition19. Interior Furnishing Ceiling Panels20. Curtain21. Partition on Frame No. 1622. Lavatory Front Wall23. Hygienic Cloth Box24. Toilet Paper Box25. Compact Lavatory Bowl26. Used Paper and Cloth Box27. Passenger Cabin Left Partition28. Passenger Seat29. Flooring and Carpeting30. Entrance Stairs31. Cabin Attendant’s Seat32. Housing33. BKP-2-2-210 (БКП-2-2-210) Oxygen Supply Unit with

DKM-1M (ДКМ-1М) Smoke Protection Oxygen Mask34. OR-1-2-20-30 (ОР-1-2-20-30) Hand Fire Extinguisher35. Flight Compartment Left Sliding Window36. Pilot’s Seat

Interior LayoutFigure 0.2

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S E C T I O N 1

LIMITATIONS

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S E C T I O N 1

LIMITATIONS

Table of Contents

Page

Title Page............................................................................................................................. 1-1/2

Table of Contents .................................................................................................................... 1-3

1.1. Certification Basis.................................................................................................................... 1-5

1.2. Varieties of Operating Conditions............................................................................................ 1-5

1.3. Installation of Additional Equipment......................................................................................... 1-5

1.4. Minimum Crew Size................................................................................................................. 1-5

1.5. Carriage of Passengers........................................................................................................... 1-5

1.6. Limitations on Opening of Sliding Windows............................................................................. 1-6

1.7. Mass Limits ............................................................................................................................. 1-6

1.8. Center of gravity Limits............................................................................................................ 1-8

1.9. Airspeed Limitations ................................................................................................................ 1-9

1.10. Maximum Wind Velocity Limitations....................................................................................... 1-10

1.11. Vertical Descent Rate Limitations .......................................................................................... 1-10

1.12. Maximum Flight Altitude Limitations....................................................................................... 1-101.13. Outside Air Temperature Limitations...................................................................................... 1-10

1.14. Zones of Dangerous "Altitude-Speed" Combinations of

Helicopters, Categories A and B............................................................................................ 1-11

1.15. Piloting Limitations ................................................................................................................ 1-12

1.16. Limitations at Takeoffs and Landings on Surface with Slopes............................................... 1-13

1.17. Main Rotor Speed Limitations ............................................................................................... 1-14

1.18. Power Plant Limitations......................................................................................................... 1-15

1.19. Electrical Power System Limitations...................................................................................... 1-18

1.20. Hydraulic System Limitations ................................................................................................. 1-18

1.21. Limitations on Flights in Icing Conditions ............................................................................... 1-19

1.22. Noise Levels .......................................................................................................................... 1-19

1.23. Dimensions of Landing Sites and Sub-Soil Strength.............................................................. 1-20

1.24. Marking of Instruments........................................................................................................... 1-21



Category A Helicopter ............................................................................................. 1-25/26

Figure 1.2. Nomogram for Determining Helicopter Maximum Permissible Mass

Meeting Category A Requirements in Case of One Engine Failure.................................. 1-27/28

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Page

Figure 1.3. Main Rotor Speed in Autorotation Condition at Minimum Pitch

Versus Helicopter Flight Mass, Flight Altitude and Outside

Air Temperature.................................................................................................... 1-29/30


Category B Helicopter........................................................................................... 1-31/32

Figure 1.5. Nomogram for Determining Maximum Permissible Mass of

Category B Helicopter at Vertical Takeoff and Landing with

the Use of Ground Effect ........................................................................................1-33/34


Mass Variation Value Versus Wind Velocity and Direction at Takeoff

and Landing with the Use of Ground Effect ............................................................1-35/36

Figure 1.7. Diagrams of Landing Sites Limited in Dimensions

20×20 m (65×65 ft) and Paths of Normal, Continued and

Aborted Takeoffs of Category A Helicopter........................................................... 1-37/38

Figure 1.8. Diagram of Landing Site (Airstrip) and Paths of Normal,

Continued and Aborted Takeoffs of Category A Helicopter .................................. 1-39/40

Figure 1.9. Diagram of Landing Site and Approach Zones at Vertical

Takeoffs and Landings of Category B Helicopter with the

Use of Ground Effect ............................................................................................ 1-41/42

Figure 1.10. Placards and Annunciators in Cabins.................................................................... 1-43/44

Figure 1.11. Placards on the Outside of Port Side .................................................................... 1-45/46

Figure 1.12. Placards on the Outside of Starboard ................................................................... 1-47/48

List of Tables

Table 1.1. Never Exceed and Minimum Speeds Versus Flight Mass and

Barometric Altitude of Flight............................................................................................ 1-9

Table 1.2. Maximum Wind Velocities ............................................................................................. 1-10

Table 1.3. Hydraulic System Limitations ........................................................................................ 1-18

Table 1.4. Minimum Dimensions of Landing Sites............................................................................1-20

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CAUTION. THE HELICOPTER SHALL BE OPERATED IN CONFORMITY WITH THE LIMITATIONS

INDICATED IN THE PRESENT SECTION.

In case of the helicopter parameters fall outside the operating limitations, the respective entry should

be made in the helicopter Log Book.

The entry should contain the information on what limitation is exceeded and by what value and within

what time or any other information allowing determination of the maintenance operations to be

performed.

1.1. Certification Basis

The Mi-171A1 (Ми-171 А1) helicopter has been certified for categories A and B in conformity withthe requirements laid down in the SB 17.29 (СБ 17.29) Certification Basis and AP-36 ( АП-36) Aviation Regulations.

1.2. Varieties of Operating Conditions

The Mi-171A1 (Ми-171 А1) helicopter in the passenger version is permitted for operations in the variousgeographic conditions (plain and high ground terrain, highlands, poorly marked terrain) by the visual flight

rules on the local airlines, airways routes, international airlines and the routes passing out of the airways

both from the aerodromes (helidromes) furnished with radio aids and from the sites non furnished with

them, including the sites selected in flight air and in the icing conditions.

The helicopter operating conditions and basic limitations are given in the table placed in the field of

view of the pilots.

1.3. Installation of Additional Equipment

In case of installation of the additional equipment, the respective limitations, operating conditions

and characteristics are given in Section 6 of the Supplement.

1.4. Minimum Crew Size

The minimum crew size of the helicopter is three persons:

– a pilot (captain);

– a co-pilot (first officer);

– a flight engineer.

When carrying the passengers, a cabin attendant may be included into the crew. In absence of the cabin

attendant, the flight engineer performs the cabin attendant’s duties.

1.5. Carriage of Passengers

The Mi-171A1 (Ми-171 А1) helicopter may carry up to 26 passengers.

NOTE. In case of installation of a buffet (instead of one seat unit), no more than 24 passengers shall

be aboard the helicopter.

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Simultaneous carriage of passengers and cargoes except the passenger luggage, is prohibited.

1.6. Limitations on Opening of Sliding Windows

The helicopter hoverings and flights at the speeds up to 50 km/h (25 kt) are permissible, with the

flight compartment sliding windows being open.

When flying the helicopter at the speeds of 50 to 200 km/h (25 to 110 kt), it is permissible to slide

one blister (right or left) by no more than 10 cm (4 in), with the blister being locked.

When flying the helicopter at the speeds over 200 km/h (110 kt), the blisters should be closed and

locked.

NOTE. Prior to opening a blister, make certain that the personal equipment and items, navigational

tools and flight documentation are reliably secured.

1.7. Mass Limits

1.7.1. Category A

The helicopter normal takeoff (landing) mass.................................................. 11,100 kg (24,450 lb);

The helicopter maximum takeoff mass:

– at takeoff from an airstrip ............................................................................. 12,000 kg (26,450 lb);

– at takeoff from a ground site having limited dimensions ............................... 10,500 kg (23,130 lb);

– at takeoff from a raised site having limited dimensions ................................ 11,000 kg (24,230 lb).

The maximum permissible takeoff mass of the helicopter (m A MAX PERM) versus the actual conditions at

the takeoff point is determined from the nomogram shown in Figure 1.2, Section 1 of the Flight

Manual.

In this case, at takeoff from the sites having limited dimensions, m A MAX PERM value determined form

the nomogram shown in Figure 1.2 should be decreased:

– at takeoff from a ground site – by 1700 kg (3,750 lib);

– at takeoff from a raised site – by 1200 kg (2,650 lib).

The helicopter maximum landing mass:

– at landing on an airstrip ................................................................................ 12,000 kg (26,450 lb);

– at landing on a ground site having limited dimensions ................................. 12,000 kg (26,450 lb);

– at landing on a raised site having limited dimensions................................... 11,000 kg (24,230 lb).

The helicopter maximum permissible landing mass versus the actual conditions in the landing area is

determined from the nomogram shown in Figure 1.2. In this case, when landing on a raised site having

limited dimensions, the m A MAX PERM value determined from the nomogram shown in Figure 1.2 should be

decreased by 1200 kg (2,50 lb).

In all cases, the helicopter maximum permissible takeoff (landing) mass determined in conformity

with the indicated requirements should not exceed the maximum takeoff (landing) mass.

Category B

The helicopter normal takeoff (landing) mass.................................................. 11,100 kg (24,450 lb).

The helicopter maximum takeoff (landing) mass ............................................... 13,000 kg (28,650 lb).

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The helicopter maximum permissible mass versus the actual conditions at the takeoff point and in

the landing area is determined from the nomograms shown in Figs 1.5 and 1.6.

NOTE. When carrying 10 and more passengers, the helicopter should be operated according to

category A.

When carrying 9 and less passengers, it is permissible to operate the helicopter according to

categories A and B.

1.7.2. The helicopter minimum flight mass is 7500 kg (16,520 lb).

NOTE. The indicated minimum flight mass of the helicopter ensures at least 80 % of the main rotor

rotational speed at descent in autorotation at the outside air subzero temperatures.

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1.9. Airspeed Limitations

Dependiong on the altitude and flight mass in the ISA conditions, it is permissible to perform the

flights within the indicated airspeed range indicated in Table 1.1.

The never exceed speed value of flight (VNE) at the flight mass of 11,100 kg (24,450 lb) and less at

the altitudes up to 1000 m (3,280 ft) is 250 km/h (135 kt).

T a b l e 1.1

Flight mass, kg (lb)

more than 11,100 (24,450) 11,100 (24,450) and lessFlight altitude, m (ft)

never exceedspeed, km/h (kt) minimum speed,km/h (kt) never exceedspeed, km/h (kt) minimum speed,km/h (kt)

Up to 1000 (3,280)

1500 (4,921)

2000 (6,560)

3000 (9,840)

4000 (13,120)

4800 (15,740)

230 (125)

210 (115)

195 (105)

160 (85)

120 (65)

100 (55)

-

0

0

60 (35)

60 (35)

60 (35)

80 (45)

-

250 (135)

240 (130)

230 (125)

210 (115)

170 (90)

140 (75)

130 (70)

0

0

0

0

0

60 (35)

60 (35)

NOTES: 1. At the air temperature higher than +15 °C ISA, the never exceed speed of flight for every10 °C should be decreased by 10 km/h (5 ft).

2. At the normal flight mass and aft center of gravity limit less than 0, the never exceedspeed is limited to 240 km/h (130 kt).

3. At the flight mass more than normal one and aft center of gravity limit less than 0, the

never exceed speed of flight at climb is limited to 220 km/h (120 kt).

The never exceed indicated airspeed in the main rotor autorotation at the altitudes of 0 to 3000 m

(0 to 9,840 ft), with the flight mass of 11,100 kg (24,450 lb) and less, and 0 to 1750 m (0 to 5,740 ft),

with the flight mass exceeding 11,100 kg (24,450 lb), amounts to 200 km/h (110 kt). At the other

altitudes, the VNE (autorotation) value should be less by 10 km/h (5 kt) than that indicated in Table 1.1.

The minimum indicated descent rates in the main rotor autorotation at all the altitudes irrespective of the

flight mass correspond to the speeds given in Table 1.1.

The tolerable speed of the helicopter motions near ground backward, to the left and right is not more

than 10 km/h (5 kt) and at the tailwind velocity of 5 to 10 m/s (10 to 20 kt), carry out the backward

motion at a speed of 5 km/h (2.5 kt).

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1.10. Maximum Wind Velocity Limitations

T a b l e 1.2

Direction of wind

Tolerable wind

velocity at start and

shutdown of engines,

m/s (kt)

Tolerable wind velocity at

hovering, hops and motions

near ground, m/s (kt)

Tolerable wind velocity at

takeoff and landing, m/s

(kt)

Headwind 25 (50) 25 (50) 25 (50)

Right cross-wind 10 (20) 10 (20) 10 (20)

Left cross-wind 15 (30) 10 (20) 10 (20)

Tail wind 8 (16) 10 (20) 0 (0)

It is permissible to taxi the helicopter at the wind velocity not exceeding 15 m/s (30 kt).

1.11. Vertical Descent Rate Limitations

The maximum permissible vertical descent rates during power-on glide at the speed less than 50

km/h (27 kt) is not more than 4 m/s (800 ft/min) and at the vertical descent – not more than 3 m/s

(600 ft/min).

1.12. Maximum Flight Altitude Limitations

The maximum barometric pressure altitude of flight:

– with passengers aboard the helicopter .............................................................. 4200 m (13,770 ft);

– without passengers aboard the helicopter ......................................................... 5000 m (16,400 ft).

NOTE. When flying the helicopter at the altitudes above 3000 m (9,840 ft), the crew (passengers at

the altitudes above 2400 m (7,870 ft) should be guided by the oxygen use rules laid down

in Subsection 7.14 of the Flight Manual.

1.13. Outside Air Temperature Limitations

The helicopter is permitted for operations at the maximum outside air temperature of +50 °C andminimum outside air temperature of minus 40 °C.

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1.14. Zones of Dangerous "Altitude-Speed" Combinations of Helicopters,

Categories A and B

Category A Helicopter

The zones of dangerous combinations of altitude and forward speed of flight, including the hovering,

for the category A helicopter are presented on the chart shown in Figure 1.1.

These zones determine combination of the altitude and speed at which in case of a failure of one

engine and running of the second engine at the 2.5-minute power rating, the helicopter safe landing

is not ensured.

The chart illustrates the left zone at takeoff (landing) of the category A helicopter having the m A MAX

PERM mass on an air strip in conformity with that shown in Figure 1.2 and on a raised platform with

the mass being decreased by 1200 kg (2652 lb) and also on a ground site having the limited

dimensions (20×20 m (65×65 ft)), with the mass being decreased by 1700 kg (3,750 lb).

Category B Helicopter

The zones of dangerous combinations of altitude and forward speed, including the hovering,

determine combination of the altitude and speed at which, in case of a failure of one engine, the

helicopter safe landing is not ensured. The zones are determined during running of the second

engine at the 2.5-minute power setting.

Figure 1.4 illustrates the category B helicopter dangerous zones.

The left zone is determined for the helicopter maximum permissible mass with the use of the ground effect.

The right zone is common for both categories of maximum permissible mass of the helicopter and is

determined with due account of the need for application of intensive deceleration of the forward

speed after a failure of the engine. In this case, at the flight speeds higher than 90 km/h (50 kt) and

altitudes below 15 m (50 ft), as a result of angle of pitch increase at deceleration and landing of the

helicopter at the first moment after an engine failure, the helicopter tail boom and tail rotor may

touch the ground.

A safe landing can be executed in three cases when a failure of an engine occurs at combinations of

altitude and speed which are beyond the hatched zones of the charts shown in Figs 1.1 and 1.4.

The flights of the helicopters of categories A and B within the dangerous zones are prohibited.

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1.15. Piloting Limitations

1.15.1. It is permissible to make the turns, 360° banked turns and spirals within the allowable speed range

of the flight:

– at a flight mass of 11,100 kg (24,450 lb) and less within the flight altitude range from 50 m (165 ft)

to 3000 m (9,840 ft) at the roll angles up to 30° and at the altitudes above 3000 m (9,840 ft) – at

the angles of roll up to 15°;

– at the fl ight mass more than 11,100 kg (24,450 lb) and also in the severe turbulence conditions,

with one engine running, and in the main rotor autorotation regime at the flight altitude range

from 50 m (165 ft) to 3000 m (9,840 ft) at the roll angles up to 20° and at the altitudes above

3000 (9,840 ft) – at the angles of roll up to 15°.

It is permissible to make the energetic turns, in case of necessity, at the flight mass of 11,100 kg

(24,450 lb) and less at the flight speeds of 100 to 200 km/h (55 to 110 kt) and altitudes of 50 to 1000m (165 to 3,280 ft) at the angles of roll up to 45°.

When making the turns and 360° banked turns at the altitudes up to 50 m (165 ft) above the relief, the

tolerable angle of roll is numerically equal in value to a flight altitude in meters (i. e. at an altitude of 10 m

(35 ft) -10°, at an altitude of 20 m (65 ft) -20°, at an altitude of 30 m (100 ft) -30°, but in all cases it should

not exceed 45°.

1.15.2. It is permissible to make the turns at hovering at the angular rate not exceeding 12 °/s.

The pedals full travel time in changing the helicopter turn direction is at least 3 s.

It is permissible to make turns through 360° during hovering at the ground at the wind velocity not

exceeding 10 m/s (20 kt).

1.15.3. To prevent a possible impact of the main rotor blades upon the tail boom, it is prohibited: – to pull the control stick from the neutral position by amount of more than 1/2 of its travel in all flight regimes

at the forward speeds more than 80 km/h (45 kt);

– to pull the control stick from the neutral position by amount of more than 1/2 of the control stick

travel at the main rotor collective pitch less than 3° against the collective-pitch indicator at

running landing and at taxiing.

1.15.4. It is permissible to execute the flights above the difficult country (hills, ravines, etc.) at the altitudes not less

than 20 m (65 ft) and at the speeds not less than 60 km/h (35 kt).

1.15.5. In the normal operating conditions under the transient regimes of flight, the maximum rate of pitch

angle change should be:

– at the speeds of 200 km/h (110 kt) and less ............................................. not more than 5 °/s;

– at the speeds more than 200 km/h (110 kt) ............................................... not more than 3 °s.

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1.16. Limitations at Takeoffs and Landings on Surface with Slopes

1.16.1. It is permissible to perform the vertical takeoff and landing without shutdown of the engines on the

sites with slopes:

– with the helicopter nose on uphill slope up to 7°;

– with the helicopter nose on downhill slope up to 5°;

– with the helicopter port side on uphill slope up to 7°;

– with the helicopter starboard on uphill slope up to 3°.

The maximum amounts of the site slopes for performing the vertical takeoff and landing, with

shutdown of the engines after landing and their subsequent start for takeoff, should not exceed 3°.

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1.17. Main Rotor Speed Limitations

1.17.1. The maximum permissible speed of the main rotor (against the indicator) for not more than 10 s at

the flight power-on settings:

– at the maximum continuous power and higher .............................................................. 101 %;

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Mi-171A1 RFM Part-I

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