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PHENOM 100Airplane Flight Manual

List of Effective Pages

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LIST OF EFFECTIVE PAGES

ORIGINAL ................. 0 ..................DEC 12, 2008 REVISION ................. 1 ..................DEC 29, 2008 REVISION ................. 2 ..................AUG 19, 2009 REVISION ................. 3 ..................OCT 20, 2009 REVISION ................. 4 .................. FEB 03, 2010 REVISION ................. 5 .................. APR 28, 2010 REVISION ................. 6 .................. JUN 10, 2010 REVISION ................. 7 .................. SEP 28, 2010 REVISION ................. 8 ..................NOV 04, 2010 REVISION ................. 9 ..................NOV 30, 2010 REVISION ................ 10 .................MAY 24, 2011 REVISION ................ 11 .................DEC 09, 2011

PHENOM 100 Airplane Flight Manual

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Table of Contents

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TABLE OF CONTENTS

SECTION 1 GENERAL

SECTION 2 LIMITATIONS

SECTION 3 NORMAL PROCEDURES

SECTION 4 EMERGENCY AND ABNORMAL PROCEDURES

SECTION 5 PERFORMANCE

SECTION 6 WEIGHT AND BALANCE

SUPPLEMENTS

APPENDICES


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Airplane Flight Manual

General

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SECTION 1

GENERAL

TABLE OF CONTENTS

Block Page

Introduction ........................................................................ 1-00.......... 02

Definition of Terms............................................................. 1-10.......... 01

Abbreviations and Acronyms Used ................................... 1-20.......... 01

Service Bulletin Table........................................................1-30.......... 01


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INTRODUCTION This Airplane Flight Manual (AFM) meets certification requirements set by 14CFR 23 and provides the approved information necessary to safely operate the PHENOM 100.

For additional information, please contact:

EMBRAER − Empresa Brasileira de Aeronáutica S.A. Flight Operations Engineering Section (VAE/DA1/GA3) - PC036/2 Av. Brigadeiro Faria Lima, 2170 - P.O.BOX 8050 São José dos Campos - São Paulo - BRASIL CEP 12227-901 PHONE: 55 12 3927-1409 E-MAIL: [email protected]

REVISIONS EMBRAER may periodically revise this manual as required to update information or provide information not available at the time of printing. Revised data may result from EMBRAER approved airplane modifications or from improved techniques gained through operational experience. Changes to the text are indicated by a vertical line on the outside margin of the page.

A vertical line adjacent to the page number will indicate relocated or rearranged text or illustrations.

A Log of Revisions can be found at the beginning of this Manual.

The basic issue date of this Manual is presented on the title page. The revisions to the basic Manual will be numbered sequentially (Rev. 1, 2, 3 and so forth). This also applies to pages revised by an earlier revision.

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TEMPORARY REVISIONS Temporary revisions may be issued when the need arises. The temporary revision will be clearly identified and will be replaced as soon as possible. Temporary revisions will not be included in the List of Effective Pages. A dedicated Log of Temporary Revisions is provided.

LIST OF EFFECTIVE PAGES A List of Effective Pages for all the Sections is located at the beginning of this Manual. This list presents the date of issue for each page and it is revised with the Manual. Its purpose is to verify that the Manual is current.

ORGANIZATION This Airplane Flight Manual is divided as follows:

− Section 1 - General − Section 2 - Limitations − Section 3 - Normal Procedures − Section 4 - Emergency and Abnormal Procedures − Section 5 - Performance − Section 6 - Weight and Balance − Supplements − Appendices

The Sections and their use are explained below.

SECTION 1 – GENERAL

This Section contains general information pertaining to the Manual, such as the revision rules, its organization and a definition of terms.

SECTION 2 – LIMITATIONS

This Section contains airworthiness certification limitations.

The limitations restrict airplane operation in accordance with the airworthiness certificate.


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SECTION 3 – NORMAL PROCEDURES

This Section contains the required normal procedures.

SECTION 4 – EMERGENCY AND ABNORMAL PROCEDURES

This Section contains the actions to be performed in the event of failures.

SECTION 5 – PERFORMANCE

This Section contains performance data and general information and configurations.

SECTION 6 – WEIGHT AND BALANCE

This Section provides instructions referring to the weighing and loading of the PHENOM 100 airplane.

SUPPLEMENTS

The Supplements provide the necessary additional information for the airplane operation, when equipped with optional systems and equipment not provided with the standard airplane, or when specific operational information is applicable to the airplane (e.g. ferry flights, special operation etc). Supplements may modify or complete the limitations, procedures or performance data of the basic AFM.

APPENDICES

Appendices may be incorporated in the AFM to provide additional information for the operation of the airplane, in a format that may not be the same as the basic AFM.

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DEFINITION OF TERMS The following definitions apply to the terms below:

WARNING: OPERATING PROCEDURES, TECHNIQUES AND OTHER RELATED INFORMATION WHICH MAY RESULT IN PERSONAL INJURY OR LOSS OF LIFE, IF NOT FOLLOWED.

CAUTION: OPERATING PROCEDURES, TECHNIQUES AND OTHER RELATED INFORMATION WHICH MAY RESULT IN DAMAGE OR DESTRUCTION OF EQUIPMENT, IF NOT FOLLOWED.

NOTE: Operating procedures, techniques and other related information which are considered essential to emphasize.

LAND AS SOON AS POSSIBLE

An emergency will be declared. A landing should be accomplished at the nearest suitable airfield considering the severity of the emergency, weather conditions, field facilities, ambient lighting, airplane gross weight and ATC guidance. Depending on the situation criticality and considering the occupants safety, a landing off the runway may have to be attempted.

LAND AS SOON AS PRACTICAL

The emergency conditions are less urgent, and although the flight is to be terminated, the degree of the emergency is such that an immediate landing at the nearest adequate airfield may not be necessary.

NO ICING

Atmospheric conditions are such that no ice formation is predicted or there is no perceptible ice formation on airplane surfaces.

IN ICING/WITH ICE

Atmospheric conditions may lead to ice formation or there is ice accreted on airplane surfaces.


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ABBREVIATIONS AND ACRONYMS USED ABBREVIATIONS OR

ACRONYMS MEANING

°C Degrees Celsius °F Degrees Fahrenheit ft Feet hPa Hectopascal kg Kilogram kt Knot ℓ Liter lb Pound m Meter mph Miles per Hour psi Pound per Square Inch sec Second VA Volt-Ampere AC Advisory Circular ACJ Advisory Circular Joint ADC Air Data Computer ADF Automatic Direction Finder ADS Air Data System AEO All Engines Operating AFM Airplane Flight Manual AFT After AGL Above Ground Level AHRS Attitude and Heading Reference System A-I Anti-Ice ALT Alternate


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ABBREVIATIONS OR

ACRONYMS MEANING

AMS Air Management System ANAC Agência Nacional de Aviação Civil AOA Angle of Attack AP or A/P Autopilot ARM Armed ASTM American Society for Testing and MaterialsATC Air Traffic Control ATR Automatic Thrust Reserve AUX Auxiliary BA Balance Arms BC Back Course BRNAV Basic Area Navigation Standards BS Body Station CAS Crew Alerting System CB Circuit Breaker CDI Course Deviation Indicator CG Center of Gravity COMM Communication CON Continuous CRS Course DC Direct Current/Digital Controller DH Decision Height D-I De-Ice DISAG Disagree DME Distance Measurement Equipment

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ABBREVIATIONS OR

ACRONYMS MEANING

DR Dead Reckoning EFCU Electronic Fuel Control Unit EIS Engine Indication System ELT Emergency Locator Transmitter ENG Engine FAA Federal Aviation Administration FADEC Full Authority Digital Electronic Control FAR Federal Aviation Regulations FCSOV Flow Control Shutoff Valve FIREX Fire Extinguisher FL Flight Level FMA Flight Mode Annunciation FMS Flight Management System FPA Flight Path Angle FWD Forward GA Go-Around GFC Garmin Flight Control GIA Garmin Integrated Avionics GND Ground GPS Global Positioning System GPU Ground Power Unit GS Ground Speed HDG Heading HTR Heater ICAO International Civil Aviation Organization


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ABBREVIATIONS OR

ACRONYMS MEANING

IESI Integrated Electronic Standby Instrument IFR Instrument Flight Rules ILS Instrument Landing System IMC Instrument Meteorological Conditions ISA International Standard Atmosphere ITT Interturbine Temperature KOEL Kinds of Operation Equipment List LDG Landing LEMAC Leading Edge Mean Aerodynamic Chord LNAV Lateral Navigation LOC Localizer LRN Long Range Navigation MAC Mean Aerodynamic Chord MAN Manual MAX Maximum MEA Minimum Enroute Altitude MEL Minimum Equipment List MFD Multifunction Display MIL Military MIN Minimum MLG Main Landing Gear MMO Maximum Operating Mach

MNPS Minimum Navigational Performance Specifications

MRA Maximum Recommended Turbulent Air Penetration Speed

MSL Mean Sea Level

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ABBREVIATIONS OR

ACRONYMS MEANING

N1 Fan Speed N2 High Pressure Compressor Speed NAT North Atlantic NAV Navigation NAVCOM Navigation and Communication NEXRAD Next-Generation Radar NLG Nose Landing Gear NPRV Negative Pressure Relief Valve OAT Outside Air Temperature OEI One Engine Inoperative OPERA Optimized Performance Analyzer OVHT Overheat PAX Passenger PBE Protective Breathing Equipment PFD Primary Flight Display PRNAV Precision Area Navigation PRSOV Pressure Regulator Shutoff Valve PRV Pressure Relief Valve QAV Aviation Kerosene QFE Field Elevation Altimeter Setting RA Radar Altimeter or Resolution Advisory RAIM Receiver Autonomous Integrity Monitoring

RBHA Regulamento Brasileiro de Homologação Aeronáutica

RNAV Area Navigation System RNP Required Navigation Performance


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ABBREVIATIONS OR

ACRONYMS MEANING

RPM Revolutions Per Minute RVSM Reduced Vertical Separation Minimum SAT Static Air Temperature SDF Simplified Directional Facility STBY Standby SVS Synthetic Vision System SWPS Stall Warning and Protection System TA Traffic Advisory TAT Total Air Temperature TAWS Terrain Awareness and Warning System

TCAS Traffic Alert and Collision Avoidance System

TFC TCAS Function TGL Temporary Guidance Leaflet TIS Traffic Information System TO or T/O Takeoff TO/GA Takeoff/Go-Around TSO Technical Standard Order V Volt/Vertical V1 Decision Speed V2 Takeoff Safety Speed VAC Approach Climb Speed

VAP Approach Speed VDI Vertical Deviation Indicator VFE Maximum Flaps Extended Speed VFR Visual Flight Rules

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ABBREVIATIONS OR

ACRONYMS MEANING

VFS Final Segment Speed VHF Very High Frequency VLE Maximum Landing Gear Extended Speed VLO Maximum Landing Gear Operating SpeedVLOF Lift-Off Speed

VMC Minimum Control Speed

VMO Maximum Operating Speed VNAV Vertical Navigation VO Operating Maneuvering Speed VOR VHF Omnidirectional Range VR Rotation Speed

VREF Landing Reference Speed

VS Stall Speed VSI Vertical Speed Indicator WAAS Wide Area Augmentation System WOW Weight on Wheels WX Weather XFR Transfer XPDR Transponder YD Yaw Damper


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SERVICE BULLETIN TABLE The following table shows the Service Bulletins which affect the airplane operation and have been incorporated into AFM.

SB SUBJECT

SB 500-27-0001 Replacement of the SWPC and FSCU WOW function activation.

SB 500-27-0003 Removal of the flap limitation.

SB 500-31-0001 Installation of G1000 Load 25.30 Avionics Software and CMC Load 6 Software.

SB 500-73-0001 New FADEC (Full Authority Digital Engine Control) Software Upgrade – Version 4.0.

SB 500-73-0002 New FADEC (Full Authority Digital Engine Control) Software Upgrade – Version 5.3.


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SECTION 2

LIMITATIONS

TABLE OF CONTENTS

Block Page

Introduction ........................................................................ 2-00.......... 02

Weight................................................................................2-05.......... 01

Loading ..............................................................................2-05.......... 01

Center of Gravity Envelope ...............................................2-05.......... 02

Operational Limitations......................................................2-10.......... 01

Systems:

Flight Controls.................................................................... 2-30.......... 01

Hydraulic............................................................................ 2-30.......... 01

Warning .............................................................................2-30.......... 01

Electrical ............................................................................ 2-34.......... 01

Fuel .................................................................................... 2-36.......... 01

Power Plant ....................................................................... 2-40.......... 01

Pneumatic, Air Conditioning and Pressurization ............... 2-48.......... 01

Ice and Rain Protection .....................................................2-50.......... 01

Autopilot/Yaw Damper....................................................... 2-56.......... 01

Flight Director .................................................................... 2-56.......... 01

Navigation and Communication Equipment ...................... 2-56.......... 01

Electronic Display System................................................. 2-56.......... 04


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INTRODUCTION This airplane must be operated in accordance with the limitations presented in this Section. These limitations also apply to operations in accordance with an approved Supplement or Appendix to this AFM, except as altered by such Supplement or Appendix.

The safety and integrity of the airplane and its occupants is highly dependent on the compliance with the operating limitations. Flight crew is the primary responsible for such compliance and so should have all the limitations committed to memory. Some limitations, however, may be too complex to memorize, thus requiring an AFM consultancy. Such limitations are like the following:

- Limitations which are automatically complied with by the airplane systems;

- Limitations associated to more than one parameter and that constantly varies in time;

- Tables; - Charts.

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WEIGHT

AIRPLANE MODEL

MAX Ramp

Weight(MRW)

(lb)

MAX TakeoffWeight(MTOW)

(lb)

MAX LandingWeight(MLW)

(lb)

MAX ZeroWing Fuel

Weight (MZFW)

(lb)

PHENOM 100 10516 10472 9766 8444 To comply with the performance and operating limitations of the regulations, the maximum allowable takeoff and landing operational weights may be equal to, but not greater than design limits.

The takeoff weight (weight at brake release or at start of takeoff run) is the lowest between MTOW and the following weights:

− Maximum takeoff weight as calculated using the Simplified Takeoff Analysis Tables or using the OPERA software and as limited by runway length, altitude, temperature, tire speed, brake energy and climb requirements.

− Maximum takeoff weight, as limited by enroute, and landing operating requirements.

The landing weight is the lowest between MLW and the following weights:

− Maximum approach and landing weight as calculated using the Landing Tables or using the OPERA software and as limited by runway length, altitude, temperature, tire speed, brake energy, approach climb, and landing climb requirements.

LOADING The airplane must be loaded in accordance with the information contained in the Section 6, Weight and Balance.


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CENTER OF GRAVITY ENVELOPE

PHENOM 100

6200

6600

7000

7400

7800

8200

8600

9000

9400

9800

10200

10600

11000

10 20 30 40 50

INFLIGHT LIMITS (FLAPS AND GEAR UP)TAKEOFF AND LANDING LIMITS

500F

AA

02 -

26O

CT2

008

WEI

GH

T - l

b

CG POSITION - %MAC

23.5%

7099 lb

35.5

10472 lb

36.9%

6614 lb

21.5%

7540 lb

9766 lb

38.5%

21.5%19.5%

8885 lb8885 lb

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OPERATIONAL LIMITATIONS

OPERATIONAL ENVELOPE

-5000

0

5000

10000

15000

20000

25000

30000

35000

40000

45000

-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

ALT

ITU

DE

- ft

10000 ft

500C

TA01

- 17

JAN

07

STATIC AIR TEMPERATURE - °C

TAKEOFF, LANDING & GROUND START

ISA + 35°C

41000 ft-21.5°C

52°C-54°C

-60°C

-40°C

-1000 ft

NOTE: - Yaw damper must be engaged above 25000 ft, and above 250 KIAS.

- In the event of a landing below -40°C, report to the maintenance personnel.


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AIRSPEEDS

LANDING GEAR OPERATION/EXTENDED SPEED (VLO AND VLE)

VLO ...........................................................................180 KIAS VLO is the maximum speed at which the landing gear can be safely extended and retracted.

VLE ...........................................................................275 KIAS VLE is the maximum speed at which the airplane can be safely flown with the landing gear extended and locked.

NOTE: For emergency purposes only, the landing gear may be extended at speeds higher than 180 KIAS but not exceeding 250 KIAS. If landing gear is extended above 180 KIAS, report to the maintenance personnel.

MINIMUM CONTROL SPEEDS (VMC)

For takeoff:

- VMC .........................................................................97 KIAS

NOTE: The VMC above represents the highest value to be found within the takeoff envelope. Specifics VMC may be obtained through the OPERA as a function of altitude, temperature, weight and according to the takeoff flaps.

For landing:

- VMC (no icing conditions)........................................86 KIAS - VMC (icing conditions).............................................97 KIAS

NOTE: VMC is the airspeed at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the airplane with that engine still inoperative, and thereafter maintain straight flight at the same speed with an angle of bank of not more than 5 degrees.

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MAXIMUM OPERATING SPEED (VMO/MMO)

0

5000

10000

15000

20000

25000

30000

35000

40000

45000

150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300

ALT

ITU

DE

- ft

AIRSPEED - KIAS

500C

TA00

3 - 1

9NO

V20

08

MMO=0.70

VMO

NOTE: VMO/MMO may not be deliberated exceeded in any regime of flight (climb, cruise or descent), unless a higher speed is authorized for flight test or pilot training.


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OPERATING MANEUVERING SPEED (VO)

VO ...........................................................................186 KIAS

NOTE: - Maneuvers that involve angle of attack near the stall or full application of rudder, elevator, and aileron controls should be confined to speeds below VO. In addition, the maneuvering flight load factor limits, presented in this Section, should not be exceeded.

- Maneuvers are limited to any maneuver incident to normal flying, stalls (except whip stalls) and steep turns in which the angle of bank is not more than 60 degrees.

CAUTION: RAPID AND LARGE ALTERNATING CONTROL INPUTS, ESPECIALLY IN COMBINATION WITH LARGE CHANGES IN PITCH, ROLL, OR YAW (E.G. LARGE SIDESLIP ANGLES) MAY RESULT IN STRUCTURAL FAILURES AT ANY SPEED, EVEN BELOW VO.

MAXIMUM FLAP EXTENDED SPEED (VFE)

NOTE: Applicable to airplanes Post-Mod. SB 500-27-0003 or with an equivalent modification factory incorporated, for airplanes Pre-Mod. SB 500-27-0003, refer to Supplement 2.

Flaps 1 .....................................................................200 KIAS Flaps 2 .....................................................................160 KIAS Flaps 3 .....................................................................160 KIAS Flaps FULL ..............................................................145 KIAS

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MAXIMUM ALTITUDE FOR FLAP EXTENDED Maximum Altitude for Flap Extended:

Yaw Damper Operative ...................................... 15000 ft Yaw Damper Not Operative ............................... 12000 ft

MAXIMUM TIRE GROUND SPEED Maximum Tire Ground Speed ................................. 139 kt

NOTE: Whenever the tire speed limit is exceeded the tires must be replaced.

MANEUVERING No acrobatic maneuvers, including spins, are authorized.

MANEUVERING FLIGHT LOAD FACTORS


These corresponding accelerations limit the bank angle during turns and limit the pull-up maneuvers.

LOAD FACTOR LIMIT FLAPS UP FLAPS DOWN (1, 2, 3 AND FULL)

Positive 3.27 g 2.00 g

MINIMUM CREW Minimum Flight Crew............................................... 1 PILOT

NOTE: - The pilot must occupy the left cockpit seat. - An operative autopilot and flight director are required for

single pilot operations. - Pilot must use a headset mounted microphone.


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KINDS OF OPERATION This airplane may be flown day and night in the following conditions, when the appropriate equipment and instruments required by airworthiness and operational requirements are approved, installed and in an operable condition as defined in the KINDS OF OPERATIONS EQUIPMENT LIST:

− Visual Flight Rules (VFR); − Instrument Flight Rules (IFR); − Icing conditions; − Extended over water *.

* For extended over water operation, operating rules may require additional equipment. Such equipment must be properly approved.

KINDS OF OPERATION EQUIPMENT LIST The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicted. The systems and items of equipment listed must be installed and operable unless:

1. The airplane is approved to be operated in accordance with a current Minimum Equipment List (MEL) approved by the Local Authority, or

2. An alternate procedure is provided in the approved Airplane Flight Manual for the inoperative state of the listed equipment and all limitations are complied with.

The following systems and equipment list does not include all specific flight, emergency and radio-navigation equipments required by local operating rules. It also does not include components obviously required for the airplane to be airworthy such as wings, primary flight controls, empennage, engines, control panels etc.

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KINDS OF OPERATION EQUIPMENT LIST (KOEL) OPERATION: DAY VFR 1) INSTALLATIONS

System Function/Equipment

Environmental/Pressurization Pressure Relief Valve (PRV)

Environmental/Pressurization Negative Pressure Relief Valve (NPRV)

Environmental/Pressurization Outflow Valve

Environmental/Pressurization Pressurization Control

Environmental/Pressurization Flow Control Shutoff Valve (FCSOV)

Environmental/Pressurization Pressure Regulating Shutoff Valve (PRSOV)

Electrical Starter Generators

Electrical Batteries

Fire Protection Portable Fire Extinguisher

Fire Protection Engine Fire Detection System

Fire Protection Engine Fire Extinguisher System

Fuel Fuel Jet Pumps

Fuel Fuel Emergency Pumps

Fuel Fuel Shutoff Valves

Hydraulics Hydraulics System

Landing Gear Brakes System

Landing Gear Steering System

Landing Gear Landing Gear Emergency Operation System

Lights Anti-Collision Lights


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KINDS OF OPERATION EQUIPMENT LIST (KOEL) OPERATION: DAY VFR 1) INSTALLATIONS (Continued)


Flight Instruments/Navigation Air Data System (ADS)

Flight Instruments/Navigation Attitude and Heading Reference System (AHRS)

Oxygen Oxygen System

Miscellaneous ELT

Miscellaneous Seat Belts

Miscellaneous Hand Microphone

Miscellaneous Water Barrier

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KINDS OF OPERATION EQUIPMENT LIST (KOEL) OPERATION: DAY VFR 2) INSTRUMENTS/INDICATIONS System Function/Equipment Environmental/Pressurization Pressurization Indications

(Cabin Altitude, Rate and Delta Pressure, Landing Field Elevation)

Electrical Battery Voltage Indication Flight Controls Flaps Position Indication Fuel Fuel Quantity Indications Landing Gear Landing Gear Position Indication Flight Instruments/Navigation Primary Flight Displays (PFD)

(Airspeed Indication, Altitude Indication, Heading Indication, Warning Caution and Advisory Function)

Flight Instruments/Navigation Integrated Electronic Standby Instrument (IESI) (Airspeed Indication, Altitude Indication, Heading Indication)

Flight Instruments/Navigation Multi-Function Display (MFD) Flight Instruments/Navigation Magnetic Compass Engine Engine Indications (Oil Pressure

and Temperature, Fuel Flow, ITT, N1, N2)

Warning Aural Warning System Warning Takeoff Warning System Miscellaneous Approved Airplane Flight Manual

(AFM) Miscellaneous Embraer Prodigy Cockpit

Reference Guide


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KINDS OF OPERATION EQUIPMENT LIST (KOEL) OPERATION: NIGHT VFR INSTALLATIONS


All equipment/indications required for day VFR

Lights Instruments Lights

Lights Position Lights

Lights Anti-Collision Lights

Lights Landing/Taxi Lights

Lights Courtesy Lights

Lights Flash Light

Flight Instruments/Navigation Attitude Indication

OPERATION: IFR

INSTALLATIONS AND INDICATIONS


All equipment/indications required for day VFR

All equipment/indications required for night VFR (for night flights)

Ice Protection Pitot/Static-AOA Heating System

Flight Instruments/Navigation Slip-Skid Indication

Flight Instruments/Navigation Clock

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KINDS OF OPERATION EQUIPMENT LIST (KOEL) OPERATION: ICING CONDITIONS INSTALLATIONS


All equipment/indications required for IFR

Environmental/Pressurization Cockpit Fan

Ice Protection Wing and Horizontal Stabilizer De-Icing System

Ice Protection Engine Anti-Icing System

Ice Protection Windshield Heating System

Lights Wing Inspection Light *

* Only required for night operations.


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MAXIMUM PASSENGER SEATING Maximum Passenger Seating Configuration:

INTERIOR DESCRIPTION CONFIGURATION SIDE FACING

SEAT BELTED

TOILET SEAT

MAXIMUM PASSENGER

NUMBER

STANDARD NO NO 5

OPTION 1 NO YES 6

OPTION 2 YES NO 6

OPTION 3 YES YES 7

NOTE: - A passenger may occupy the right cockpit seat only in single pilot operations.

- The side facing seat is installed through SB 500-25-0008 or is factory incorporated.

- The belted toilet seat is installed through SB 500-25-0007 or is factory incorporated.

- For airplanes without belted toilet, the use of the lavatory is prohibited for taxi, takeoff and landing.

- For airplanes with belted toilet, the lavatory rigid door must be latched OPEN for taxi, takeoff and landing when occupied.

- The maximum seating configuration refers to adult passengers. The aft forward-facing seats share one extra oxygen mask.

COCKPIT AND PASSENGER CABIN - Pilots sunvisors must be kept at the vertical position when in use and

must be stowed for taxi, takeoff and landing. - Cockpit curtain to be used on ground only during cabin temperature

pull down.

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BAGGAGE LOADING Maximum Loading:

Wardrobe............................................................ 66 lb Lavatory Cabinet ................................................ 33 lb Aft Baggage Compartment................................. 353 lb Forward Baggage Compartment ........................ 66 lb

NOTE: The maximum intensity of loading in each compartment is the following: - Aft Compartment ...................................... 29.7 lb/ft2 - Forward Compartment - Upper ................ 12.5 lb/ft2 - Forward Compartment - Bottom............... 18.2 lb/ft2

RUNWAY Runway Slope.......................................................... -2% TO +2% Runway Surface Type ............................................. PAVED

WIND LIMITATIONS Maximum Takeoff and Landing Tailwind

Component ......................................................... 10 kt


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FLIGHT CONTROLS

FLAPS For airplanes Pre-Mod. SB 500-27-0003:

- Flaps 3 must not be used. Refer to Supplement 2 for further information.

For airplanes Pre-Mod. SB 500-27-0001:

- Flaps FULL must not be used to land in “no icing conditions”.

HYDRAULIC The hydraulic system must be checked each 15 consecutive calendar days or before next flight, whichever occurs last.

WARNING

STALL WARNING AND PROTECTION The stall warning and protection system must be tested prior each flight.

TERRAIN AWARENESS AND WARNING SYSTEM (TAWS)

NOTE: For operation with TAWS, refer to Supplement 4.


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TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM I (TCAS I) (IF APPLICABLE) TCAS I is intended for advisory use only to aid the pilot in visually acquiring traffic.

No avoidance maneuver should be based solely upon TCAS I traffic information.

TCAS I does not relieve the pilot of the responsibility to “see and avoid” other airplane.

NOTE: For operation with TCAS II, refer to Supplement 3.

TRAFFIC INFORMATION SYSTEM (TIS) (IF APPLICABLE) TIS is not intended to be used as a collision avoidance system and does not relieve the pilot of the responsibility to “see and avoid” other airplane.

TIS shall not be used for avoidance maneuvers during instrument meteorological conditions (IMC) or when there is no visual contact with the intruder airplane.

NOTE: TIS is available only when the airplane is within the service volume of a TIS-capable terminal radar site.

SATELLITE WEATHER RADIO SYSTEM (XM WEATHER) XM Weather information must not be used for hazardous weather penetration. Weather information is provided only for hazardous weather avoidance.

NEXRAD weather data is intended for long-range planning purposes only. Due to inherent delays and relative age of the data, NEXRAD weather data should not be used for short-range avoidance of hazardous weather.

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SYNTHETIC VISION SYSTEM (SVS) (IF APPLICABLE) SVS is intended to be used as an aid to situational awareness only.

Use of SVS as primary information to base decisions and/or plan maneuvers to navigate, or to avoid terrain, obstacles or traffic is prohibited.

The SVS does not assure IFR operations below published minimums.

SVS DATABASES

The SVS databases have an area of coverage as detailed below:

- The Terrain Database has an area of coverage from North 75° Latitude to South 60° Latitude in all longitudes.

- The Airport Terrain Database coverage is worldwide. Not all airfields are depicted in the SVS.

- The Obstacle Database is limited to the United States and Europe.

The terrain data has a resolution of 9 arc-seconds, this means that the terrain elevation contours in the database are stored broken down into squares 9 arc-seconds on each side.

SVS PATHWAYS

Pathways provide a three-dimensional perspective view of the selected route of flight and its presentation is intended only to aid the pilot’s awareness of the programmed flight path location relative to the airplane’s current position.

The pathway is not intended for use as a primary reference in tracking the navigation path, thus, it does not substitute standard course and altitude deviation information provided by the CDI, VSI, and VDI.

The Pathway boxes are ± 100 ft in vertical plane and approximately ± 380 ft horizontally from the center of the box.

The pathway is only displayed for navigation paths that are fully defined by the sensor in use, including GPS and ILS paths.

No vertical Pathway information is presented for climbs or for navigation paths that are not fully defined by the sensor in use, like heading legs, VOR, LOC, BC or ADF segments.


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ELECTRICAL

BATTERIES VOLTAGE Minimum Voltage for Engines Start ......................... 24 V

NOTE: Minimum GPU voltage for batteries charging is 27 V.

GENERATORS LOAD Maximum Generator Load....................................... 250 A EACH

NOTE: May be exceeded up to 300 A inflight below 34000 ft.


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FUEL

AIRPLANE MODEL PHENOM 100

Maximum usable quantity per tank 209.4 US Gal (1403 lb)

Unusable quantity per tank 3.3 US Gal (22 lb)

NOTE: - Maximum fuel capacity is 425.4 US Gal (2850 lb). - The maximum permitted imbalance between tanks is

33 US Gal (220 lb). - When operating in engine suction mode (jet pump and DC

pump failed on the same tank) the unusable fuel quantity is 13.6 US Gal (91.3 lb) per tank.

- Fuel can not be transferred from one wing to another when fuel quantity reaches 46 US Gal (308 lb) for single engine condition and 54.2 US Gal (363 lb) for dual engine condition.

- When EIS fuel quantity is zero, any fuel remaining in the tanks can not be used safely in flight.

- The weights above have been determined for an adopted fuel density of 6.701 lb/US Gal. Different fuel densities may be used provided the volumetric limits are not exceeded.

FUEL SPECIFICATION Brazilian Specification ............................................. QAV1 ASTM Specification ................................................. D1655-JET A AND

JET A-1 American Specification ............................................ MIL-T-83133A-JP8

NOTE: For approved fuel additives see AMM.

FUEL TANK TEMPERATURE Minimum .................................................................. -37°C Maximum (on ground) ............................................. 52°C

NOTE: In flight, the maximum fuel temperature may be extended but not exceeding 80°C.


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TRANSFER VALVE OPERATION FUEL XFR Button must be pushed out during takeoff, landing, maneuvers and turbulence.

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POWER PLANT

ENGINES Two Pratt & Whitney Canada PW617F-E.

OPERATIONAL LIMITS OPERATING CONDITION OPERATING LIMITS

Thrust Setting Time Limit Maximum ITT

(°C) N2 (%)

N1(%)

Oil Pressure(psig)

Oil Temperature

(°C)

Maximum 10 minutes(1) 845 100.4 100 - -

Takeoff 5 minutes(2) 830 100.4 100 170 (3) 14 to 130 (4)

Maximum Continuous/

Climb (7) 830 100.4 100 170 (3) 14 to 130

Ground Idle Sea Level

Not time limited - 54

(5) - 170 (3) -40 to 130

Flight Idle Sea Level

Not time limited - 59

(5) - 170 (3) 14 to 130

Starting N/A 830 (6) - - 0-275 -40 (5)

20 seconds 830 (8) 102 101 (3) - Transient

90 seconds - - - (3) 130 to 141

NOTE: 1) Maximum is an ATR intended to be used for a period of not over 10 minutes after the failure of one engine.

NOTE: 2) The total time during which takeoff thrust may be used is limited to 5 minutes per flight. This limit commences when the thrust lever is first set at TO/GA detent.

NOTE: 3) May be exceeded up to 250 psig during 500 seconds. For lower oil pressure limit see Figure 2-1.

(Continues on the next page)


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(Continued from the previous page)

NOTE: 4) After completing a start under cold conditions or with cold fuel (below 0°C) and achieving a stabilized idle, remain at ground idle for the time required for the oil to reach the minimum operating temperature of 14°C. During this time the transient oil pressure limit applies. Run the engine for an additional 3 minutes to ensure that no ice particles are present in the fuel supplied to the engine.

NOTE: 5) Minimum limit.

NOTE: 6) For airplanes Pre-Mod. SB 500-73-0001: - May be exceeded up to 892°C during 5 seconds. For airplanes Post-Mod. SB 500-73-0001 or with an equivalent modification factory incorporated: - May be exceeded up to 950°C during 5 seconds.

NOTE: 7) Maximum Continuous is not intended for regular, normal operation.

NOTE: 8) For normal and ATR takeoff modes, may be exceeded up to 862°C during 20 seconds. For ATR takeoff mode only, may be exceeded up to 845°C.

OIL SPECIFICATION Engine oil must comply with MIL-PRF-23699F specification.

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OIL PRESSURE LIMITATION

AREA TIME LIMIT

A

B

C

D

500 sec

90 sec

15 sec

CONTINUOUS

300

250

200

150

100

50

0

0 25 50 75 100

EM

500E

NA

OM

0200

05C

.DG

N

A

D

B

C

% N2

MO

P (

psi

g)

FIGURE 2-1


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STARTER LIMITS

MOTORING NUMBER

COOL-DOWN TIME

1 60 seconds

2 60 seconds

3 15 minutes

4 30 minutes

NOTE: After four sequential motorings, cycle may be repeated following the 30 minutes cool-down period.

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PNEUMATIC, AIR CONDITIONING AND PRESSURIZATION

AIR CONDITIONING For air conditioning system operation on ground the GPU must be used or both generators must be turned on.

PRESSURIZATION Maximum Differential Pressure ............................... 8.3 psi Maximum Differential Overpressure........................ 8.6 psi Maximum Differential Negative Pressure ................ -0.4 psi Maximum Differential Pressure for

Takeoff and Landing........................................... 0.2 psi


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ICE AND RAIN PROTECTION

OPERATION IN ICING CONDITIONS Minimum Temperature for Wing/

Stabilizer Deice System Operation..................... -40°C Minimum Airspeed................................................... 150 KIAS

Crew must activate the ice protection system when icing conditions exist or are anticipated as follows:

If SAT (TAT inflight) is between 5°C and 10°C with visible moisture: ENG 1 and ENG 2 Switches ......................... ON WINGSTAB Switch........................................ OFF WSHLD 1 and WSHLD 2 Switches............... OFF

At the first sign of ice formation or if SAT (TAT inflight) is below 5°C with visible moisture:

WSHLD 1 and WSHLD 2 Switches............... ON ENG 1 and ENG 2 Switches ......................... ON WINGSTAB Switch........................................ ON

NOTE: - Icing conditions may exist whenever the Static Air Temperature (SAT) on the ground or for takeoff, or Total Air Temperature (TAT) in flight, is 10°C or below and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet, and ice crystals).

- Icing conditions may also exist when the SAT on the ground and for takeoff is 10°C or below when operating on ramps, taxiways, or runways where surface snow, ice, standing water, or slush may be ingested by the engines, or freeze on engines, nacelles, or engine sensor probes.

- WINGSTAB switch must remain at the ON position until the entire wing, including unprotected areas and areas behind the wing deicing boot, are free of ice accretion.



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- In icing conditions the airplane must be operated, and its ice protection systems used as described in the operating procedures section of this manual. Where specific operational speeds and performance information have been established for such conditions, this information must be used.

- Take-off is prohibited with frost (polished or not), ice, snow or slush adhering to wings, control surfaces, engine inlets, or other critical surfaces.

- The airplane must exit SLD (Super Cooled Large Droplet) icing conditions environment. SLD conditions will be recognized by ice formation aft of protected surfaces or in areas that are not normally observed to collect ice.

- Intentional flight in freezing drizzle or freezing rain is prohibited. If the airplane encounters conditions that are determined to contain freezing rain or freezing drizzle, the pilot must immediately exit the freezing rain or freezing drizzle conditions by changing altitude or course. Such conditions may be identified by the following visual cues:

- Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice.

- Accumulation of ice on the upper surface or lower surface of the wing aft of the protected area.

- There are many methods to ensure the wing is clear of ice. If visual inspection does not indicate wing contamination, a tactile (hands on surface) check of the wing leading edge and the upper surface must be accomplished prior to takeoff. The tactile check must also be performed when the holdover time is exceeded after airplane de/anti-icing fluids have been applied. This check must be performed whenever the outside temperature is less than 6°C or if it cannot be ascertained that the wing fuel temperature is above 0°C, and there is visible moisture, or:

- Water is present on the wing; or - When difference between the dew point and the outside

air temperature is 3°C or less; or


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- The atmospheric conditions have been conducive to frost formation.

- Since the autopilot can mask tactile cues that indicate adverse changes in handling characteristics, the pilot should consider not using the autopilot when any ice is visible on the airplane. The autopilot use is prohibited in the following conditions:

- Severe icing; - Unusual control force or control deflection, or unusually

large control forces to move flight controls when the autopilot is disconnected periodically for checking purposes; or

- Indications of frequent autopilot re-trimming during straight and level flight.

CAUTION: ON GROUND, DO NOT RELY ON VISUAL ICING EVIDENCE TO TURN ON THE DE-ICING/ANTI-ICING SYSTEM. USE THE TEMPERATURE AND VISUAL MOISTURE CRITERIA AS SPECIFIED ABOVE. DELAYING THE USE OF THE DE-ICING/ANTI-ICING SYSTEM UNTIL ICE BUILD-UP IS VISIBLE FROM THE COCKPIT MAY RESULT IN ICE INGESTION AND POSSIBLE ENGINE DAMAGE OR FLAMEOUT.


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AUTOPILOT/YAW DAMPER Minimum Engagement Height (dual engine) ........... 500 ft AGL Minimum Engagement Height (single engine) ........ 1000 ft AGL Minimum Use Height ............................................... 195 ft AGL Altitude Loss (maneuvering/cruise) ......................... 54 ft

Airplane is approved for CAT I approaches. This statement does not grant operational approval to conduct CAT I operations.

FLIGHT DIRECTOR Flight Director must not be used during takeoff in “no icing conditions”.

NAVIGATION AND COMMUNICATION EQUIPMENT

ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS) The airplane must not operate in the regions stated on the table below:

MAGNETIC CUT-OUT REGIONS

LATITUDE LONGITUDE

Between 65°N and 70°N

Between 75°W and 120°W North

North of 70°N Between 0° and 180°W/E

Between 55°S and 70°S

Between 120°E and 165°E South

South of 70°S Between 0° and 180°W/E

NOTE: Alternative procedures must be established for dispatch if the indication GEO LIMITS is displayed.


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GARMIN G1000 AVIONICS SYSTEM Refer to Prodigy Cockpit Reference Guide for further information on system characteristics. The GARMIN G1000 avionics system has the following limitations:

- Use of VNAV is prohibited during the intermediate segment of an approach that includes a teardrop course reversal.

- Dead Reckoning Mode use is allowed only in Enroute (ENR) or Oceanic (OCN) phases of flight. The estimated navigation data supplied by the system in DR Mode must not be used as a sole means of navigation.

- The fuel quantity, fuel required, fuel remaining and gross weight estimate functions of the G1000 presented in AUX-WEIGHT PLANNING and AUX-TRIP PLANNING pages of MFD are supplemental information only and must be confirmed by the flight crew prior to use.

GARMIN G1000 GPS NAVIGATION SYSTEM

OPERATIONAL APPROVALS

The Garmin G1000 GPS receivers are approved under TSO C145a Class 3. The Garmin G1000 system has been demonstrated capable of, and has been shown to meet the accuracy requirements for, the following operations provided it is receiving usable navigation data. These do not constitute operational approvals.

- Enroute, terminal, non-precision instrument approach operations using GPS and WAAS (including "GPS", "or GPS", and "RNAV" approaches), and approach procedures with vertical guidance (including "LNAV/VNAV", "LNAV + V", and "LPV") within the U.S. National Airspace System in accordance with AC 20-138A.

- Barometric VNAV is approved to enroute and terminal descents, as per AC 20-129. Guidance is provided up to the FAF waypoint when there is not a procedure that provides vertical guidance following the FAF. Guidance is provided up to the waypoint preceding the FAF (FAF-1) when there is a procedure that provides vertical guidance (ILS or GPS WAAS) following the FAF.

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- Oceanic/Remote/MNPS/RNP-10 (per FAA AC 20-138A and FAA Order 8400-12A). Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation (LRN) sensor.

NOTE: For Oceanic/Remote operations, the G1000 WFDE prediction program works in combination with the Route Planning Software (version 1.2 or later approved version). For information on using the WFDE prediction program, refer to the WFDE Prediction Program Instructions Garmin part number 190-00643-01.

- Enroute and Terminal including RNP-5/BRNAV and PRNAV (RNP-1) in accordance with JAA TGL-10 and ACJ 20X4, provided the FMS is receiving usable navigation information from one or more GPS receivers.

LIMITATIONS

- GPS based IFR enroute, oceanic, and terminal navigation is prohibited unless the pilot verifies the currency of the database or verifies each selected waypoint for accuracy by reference to current approved data.

- RNAV/GPS instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the G1000 navigation database.

The G1000 database must incorporate the current update cycle.

NOTE: Not all the published approaches are in the navigation database. The flight crew must ensure that the planned approach is in the database.

- Receiver Autonomous Integrity Monitoring (RAIM) must be available when conducting instrument approaches utilizing the GPS receiver.

- IFR non-precision approach approval is limited to published approaches within the local Airspace System. Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority.

- When using GPS/NAV mode to intercept the final approach course, monitor the flight director transition to LOC/GS. If the transition does not occur automatically, manually select HDG mode and CDI source to LOC in order to intercept the final approach course.


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- Use of the Garmin G1000 GPS receiver to accomplish ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay is not authorized.

- Operation in airspace referenced to a datum other than WGS-84 or NAD-83 is prohibited.

- RNP operations are not authorized except as noted in the Operational Approvals Section.

- Use of the Garmin G1000 system for GPS or WAAS navigation under Instrument Flight Rules (IFR) requires that:

1. The airplane must be equipped with an approved and operational alternate means of navigation appropriate to the route being flown (NAV receiver, DME or ADF).

2. For flight planning purposes, if an alternate airport is required, it must have an approved instrument approach procedure, other then GPS or RNAV, which is anticipated to be operational and available at the estimated time of arrival. All equipment required for this procedure must be installed and operational.

ELECTRONIC DISPLAY SYSTEM

ELECTRONIC CHECKLIST Operational approval is required in order to load database into the airplane and use the electronic checklist.

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SECTION 3

NORMAL PROCEDURES

TABLE OF CONTENTS

Block Page

Introduction ........................................................................ 3-00.......... 02

Cockpit/Cabin Safety Inspection........................................ 3-01.......... 01

External Inspection ............................................................ 3-01.......... 03

Power Up ........................................................................... 3-01.......... 07

Before Start........................................................................ 3-01.......... 07

Engine Start ....................................................................... 3-01.......... 08

After Start........................................................................... 3-01.......... 08

Before Takeoff ................................................................... 3-02.......... 01

Takeoff...............................................................................3-02.......... 01

After Takeoff/Climb............................................................ 3-02.......... 02

Descent..............................................................................3-02.......... 02

Approach ...........................................................................3-03.......... 01

Before Landing .................................................................. 3-03.......... 01

Landing ..............................................................................3-03.......... 01

Go-Around ......................................................................... 3-03.......... 02

After Landing ..................................................................... 3-03.......... 03

Shutdown...........................................................................3-03.......... 03

Leaving the Airplane.......................................................... 3-03.......... 03

Operation in Icing Conditions ............................................ 3-04.......... 01

Demonstrated Crosswind .................................................. 3-04.......... 05

Turbulent Air Penetration...................................................3-04.......... 05


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INTRODUCTION The normal procedures contained in this manual have been developed and recommended by the manufacturer and approved by the certification authorities for use during the operation of the PHENOM 100 airplanes.

Indented explanations (lines beginning further from the margin than the others) follow previous items and provide further information.

* Items marked with an asterisk (*) need to be accomplished at least before the first flight of the day.

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COCKPIT/CABIN SAFETY INSPECTION Courtesy Light.......................................................... CHECK

NOTE: The courtesy light check is only required for flights with landings after sunset.

Emergency Door Locking Pin .................................. REMOVE

Emergency Door...................................................... SECURED AND LOCKED

Water Barrier ........................................................... AS REQUIRED

Documents, Manuals and Charts ............................ CHECK ON BOARD

Maintenance Status................................................. CHECK

Emergency Equipment ............................................ CHECK Verify Fire Extinguisher, Flashlight, First Aid Kit, and the following optional items, if installed: Protective Breathing Equipment (PBE), Smoke Goggles, Overwater Life Vest and Survival Kit.

Oxygen Bottle Valve Handle.................................... PUSH TO RESTORE

SUPPLY CONTROL Knob ...................................... PAX AUTO

Oxygen Mask Regulator .......................................... CHECK 100%

ELECTRICAL Panel ................................................ CHECK Check GEN 1 & 2 Switches and BUS TIE Knob in the AUTO position, set GPU Button as required and check BATT 1 & 2 Switches in the OFF position.

Circuit Breakers ....................................................... CHECK

FUEL PUMP 1 & 2 Switches ................................... AUTO

FUEL XFR Button .................................................... PUSHED OUT

ELT Switch............................................................... ARMED

PUSHER CUTOUT Button ...................................... PUSHED OUT

HYD PUMP Knob .................................................... AUTO



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Gust Lock Pin...........................................................REMOVE

Rudder Gust Lock ....................................................RELEASE

HEATING Panel.......................................................CHECK Check WSHLD 1 & 2 Switches in the OFF position and ADS/AOA Knob in the AUTO position.

ICE PROTECTION Panel ........................................CHECK Check ENG 1 & 2 Switches, WINGSTAB and INSP LIGHT Switches in the OFF position.

LDG GEAR Lever ....................................................DN

PRESSURIZATION Panel .......................................CHECK Check Pressurization MODE Switch in the AUTO position, BLEED Knob in the BOTH position and DUMP Button pushed out.

AIR CONDITIONING Panel .....................................AS REQUIRED

ENG FIRE EXTINGUISHER Panel..........................CHECK Check SHUTOFF 1 & 2 Buttons pushed out and BOTTLE Switch in the OFF position.

Start/Stop Knobs......................................................STOP

Flaps Lever ..............................................................ZERO

Parking Brake ..........................................................SET

NOTE: If parking brake pressure is suspected to be low, use wheel chocks to secure the airplane.

Seats and Belts........................................................CONDITION

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EXTERNAL INSPECTION External Lights ......................................................... CHECK

Turn the lights OFF immediately after check them to avoid batteries discharge.

Recommended Walk-Around sequence:

EM

500E

NA

OM

0300

01A

.DG

N

AOA Vane................................................................ CHECK FREE

Pitot Tube and Static Pressure Ports ...................... CONDITION, NO OBSTRUCTION

Oxygen Discharge Indicator .................................... GREEN DISK IN PLACE

Antennas.................................................................. CONDITION



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Red Beacon Light ....................................................CONDITION

NLG Doors, Wheel and Tire ....................................CONDITION

NLG Torque Link......................................................CONNECTED AND SECURED

NLG Locking Pin ......................................................REMOVED

Fwd Baggage Compartment Door ...........................LOCKED

Radome....................................................................CONDITION

Air Inlet .....................................................................NO OBSTRUCTION

Access Door.............................................................SECURED

Pitot Tube and Static Pressure Ports.......................NO OBSTRUCTION

AOA Vane ................................................................CHECK FREE

LDG/Taxi Lights .......................................................CONDITION

Fuselage Air Inlet .....................................................NO OBSTRUCTION

Engine Fan...............................................................CONDITION

Engine Air Inlet.........................................................NO OBSTRUCTION

Starter/Generator Air Inlets ......................................CLEAR

* Fuel Drains ............................................................DRAIN AND CHECK FOR CONTAMINATION

Fuel Drains and Dump Valves .................................NO LEAKS

Right Wing De-Ice Boot ...........................................CONDITION

MLG Doors, Wheels, Brakes and Tires ...................CONDITION

MLG Locking Pin......................................................REMOVED


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Fuel Cap .................................................................. CLOSED AND LOCKED

Fuel Tank Air Inlet.................................................... NO OBSTRUCTION

Navigation/Strobe Lights ......................................... CONDITION

Right Aileron ............................................................ CHECK FREE

Static Dischargers ................................................... NUMBER AND CONDITION

Right Flaps............................................................... CONDITION

Battery Access Door................................................ SECURED

Cowlings .................................................................. LATCHED

Engine Exhaust........................................................ CLEAR

Drain Masts.............................................................. CONDITION

Oil Level................................................................... CHECK

Oil Filter Impending Bypass Indicator...................... NOT EXTENDED

Heat Exchanger Air Exhaust ................................... CLEAR

Pylon........................................................................ CONDITION

Vertical Stabilizer ..................................................... CONDITION

Rudder ..................................................................... CONDITION

Yaw Trim Tab .......................................................... CONDITION

Horizontal Stabilizer................................................. CONDITION

Horizontal Stabilizer De-Ice Boot ............................ CONDITION

Elevator.................................................................... CONDITION

Pitch Trim Tab ......................................................... CONDITION

Static Dischargers ................................................... NUMBER AND CONDITION

Antennas.................................................................. CONDITION



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Air Exhaust...............................................................NO OBSTRUCTION

Aft Baggage Compartment Door .............................SECURE

Pylon ........................................................................CONDITION

Cowlings...................................................................LATCHED

Exhausts ..................................................................CLEAR

Drain Masts..............................................................CONDITION

Oil Level ...................................................................CHECK

Oil Filter Differential Indicator ..................................NOT EXTENDED

DC Power Receptacle..............................................CHECK

Static Pressure Port .................................................NO OBSTRUCTION

Left Flaps .................................................................CONDITION

Static Dischargers....................................................NUMBER AND CONDITION

Left Aileron...............................................................CHECK FREE

Roll Trim Tab ...........................................................CONDITION

Navigation/Strobe Lights..........................................CONDITION

Left Wing De-Ice Boot..............................................CONDITION

Fuel Cap...................................................................CLOSED AND LOCKED

Fuel Tank Air Inlet....................................................NO OBSTRUCTION

MLG Doors, Wheels, Brakes and Tires ...................CONDITION

MLG Locking Pin......................................................REMOVED

LDG/Taxi Lights .......................................................CONDITION

Wing Inspection Light...............................................CONDITION


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Fuselage Air Inlet..................................................... NO OBSTRUCTION

Engine Fan .............................................................. CONDITION

Engine Air Inlet ........................................................ NO OBSTRUCTION

Starter/Generator Air Inlets...................................... CLEAR

POWER UP BATT 1 & 2 Switches............................................... ON

NOTE: If the battery has been cold soaked for 2 hour or longer at ambient temperature of -18°C (0°F) or lower, it must be pre-heated to above -18°C (0°F) prior to engine start.

GPU Button (if applicable) ....................................... AS REQUIRED Verify AVAIL light illuminated before pushing the GPU Button in. When GPU is not available or is not necessary, maintain GPU Button pushed out.

CVDR Panel (if operative) ....................................... CHECK Set the toggle Switch to TEST HOLD 5 SEC position and hold for 5 seconds. Verify no fail indication on CVDR panel annunciators.

BEFORE START Oxygen Mask Flow and Microphone ....................... CHECK

Set MASK MIC Switch in ON position and press TEST/RESET Button. Set MASK MIC Switch in the OFF position.

SIGNS/OUTLET Switch........................................... BELTS/ON

AFCS Control Unit ................................................... SET

External Lights ......................................................... AS REQUIRED

Fuel Quantity and Balance ...................................... CHECK

Oxygen Pressure..................................................... VERIFY

TEST Panel ............................................................. TEST Test Annunciator, Fire Protection and Stall Protection Systems.



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Thrust Levers ........................................................... IDLE

Parking Brake ..........................................................SET

Doors........................................................................CLOSED

ENG IGNITION Switches.........................................AUTO

ENGINE START Associated Start/Stop Knob.....................................START, THEN

RUN

Engine Parameters ..................................................MONITOR Check N2, ITT, N1 and oil pressure within operational limits.

Repeat the sequence for the other engine.

AFTER START ELEC EMER Button.................................................PUSH IN

Battery 1 & 2 Voltage ...............................................CHECK

CAUTION: EACH BATTERY VOLTAGE MUST BE AT LEAST 23.8 VOLTS.

NOTE: The parking brake must be applied and the main brake must be released for battery voltage check.

ELEC EMER Button.................................................PUSH OUT

External Lights .........................................................AS REQUIRED

AFCS Control Unit ...................................................SET

Altimeters (pilots and IESI) ......................................SET & X-CHECK

Transponder.............................................................SET Set CODE and verify GND mode.

Takeoff Speeds (V1, VR, V2, VFS) .............................SET


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Takeoff Data ............................................................ SET Select the ENG TDS SET page on the MFD and set the data below:

OAT .................................................................... SET

ATR..................................................................... ON OR OFF

Landing Field Elevation ........................................... SET

Flight Controls.......................................................... CHECK FREE

Trims........................................................................ CHECK/SET Verify that Roll, Yaw and Pitch (NORM and BKP) trims are operating properly both ways. Adjust Yaw and Roll trims to the neutral position and Pitch trim to Takeoff (green band).

Flaps ........................................................................ SET FOR TAKEOFF

Ice Protection........................................................... AS REQUIRED

WARNING: IF ICING CONDITIONS EXIST OR ARE FORECAST, REFER TO OPERATION IN ICING CONDITIONS PROCEDURE.


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INTENTIONALLY BLANK

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BEFORE TAKEOFF Takeoff Configuration .............................................. CHECK

Press the T/O CONFIG Button on the central console and check if the aural TAKEOFF OK sounds.

CAS Messages........................................................ CHECK

SIGNS/OUTLET Switch........................................... PED-BELTS/OFF

--------------------------SHORTLY BEFORE TAKEOFF-------------------------

Passengers.............................................................. ADVISE

Lights ....................................................................... AS REQUIRED

TAKEOFF Flight Director .......................................................... OFF

Thrust Levers........................................................... TO/GA

NOTE: After checking thrust levers to TO/GA, check N1 equal to N1 target and green ATR indication presented on MFD if ATR ON is selected.

Engine Parameters.................................................. MONITOR

At VR rotate the airplane according to the table below.

FLAPS POSITION 1 2

PITCH ANGLE 9.5° 9°

With positive rate of climb: LDG GEAR Lever ............................................... UP

Airspeed ............................................................. V2 + 10 KIAS MINIMUM


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AFTER TAKEOFF/CLIMB LDG GEAR Lever ....................................................CHECK UP

Flaps ........................................................................ZERO Retract flaps according to the Maximum Flap Extended Speed (VFE).

Thrust Levers ...........................................................CON/CLB

Altimeters (pilots and IESI) ......................................SET & X-CHECK

Yaw Damper ............................................................ON

Icing Conditions .......................................................VERIFY

Flight Director...........................................................AS REQUIRED

------------------------------------ABOVE 10000 ft-----------------------------------

SIGNS/OUTLET Switch ...........................................AS REQUIRED

External Lights .........................................................AS REQUIRED

Weather Radar (if installed) .....................................AS REQUIRED

Airspeed...................................................................AS REQUIRED

DESCENT Windshield Heating ..................................................ON

Pressurization ..........................................................CHECK LFE

Landing Speeds .......................................................SET Set VREF, VAC and VFS.

Icing Conditions .......................................................VERIFY

------------------------------------BELOW 10000 ft-----------------------------------

SIGNS/OUTLET Switch ...........................................PED-BELTS/OFF

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APPROACH Passengers.............................................................. ADVISE

FUEL XFR Button .................................................... PUSHED OUT

Altimeters (pilots and IESI) ...................................... SET & X-CHECK

Icing Conditions ....................................................... VERIFY

BEFORE LANDING Yaw Damper ............................................................ OFF

LDG GEAR Lever .................................................... DN AND CHECK

Flaps ........................................................................ SET FOR LANDING

Airspeed................................................................... VREF

LANDING Thrust Levers........................................................... IDLE

Brakes (after touchdown) ........................................ APPLY MAXIMUM


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GO-AROUND

NOTE: - Applicable to airplanes Post-Mod. SB 500-27-0003 or with an equivalent modification factory incorporated, for airplanes Pre-Mod. SB 500-27-0003, refer to Supplement 2.

- For airplanes Pre-Mod. SB 500-27-0001, the GO-AROUND Procedure of the AD 2009-05-06 (action 2) must be accomplished.

TO/GA Buttons.........................................................PRESS

Thrust Levers ...........................................................TO/GA

Rotate the airplane following the flight director guidance or according to the table below.

LANDING FLAPS POSITION

GO-AROUND PITCHANGLE

3 7.5°

FULL 5.5°

Select flaps according to the table below.


GO-AROUND FLAPSPOSITION

3 1

FULL 2

CAUTION: DO NOT PRESS THE TO/GA BUTTON AFTER SELECTING GO-AROUND FLAPS.

With positive rate of climb: LDG GEAR Lever ...............................................UP

Airspeed..............................................................VAC MINIMUM

At the acceleration altitude proceed as in a normal takeoff.

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AFTER LANDING Flaps ........................................................................ ZERO

Lights ....................................................................... AS REQUIRED

SHUTDOWN Thrust Levers........................................................... IDLE

Emergency/Parking Brake....................................... APPLY

CAUTION: MAINTAIN IDLE FOR ΑΤ LEAST 2 MINUTES PRIOR TO ENGINE SHUTDOWN.

HEATING Panel....................................................... CHECK Check WSHLD 1 & 2 Switches in the OFF position and ADS/AOA Knob in the AUTO position.

ICE PROTECTION Panel........................................ CHECK Check ENG 1 & 2 Switches in the OFF position and WINGSTAB and INSP LIGHT Switches in the OFF position.

Start/Stop Knobs...................................................... STOP Check MFD status page for engine message.

SIGNS/OUTLET Switch........................................... OFF/ON

LEAVING THE AIRPLANE Oxygen Bottle Valve Handle.................................... PULL TO CUTOUT

BATT 1 & 2 Switches............................................... OFF

Gust Lock Pin .......................................................... INSTALL

Rudder Gust Lock.................................................... LOCK


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INTENTIONALLY BLANK

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OPERATION IN ICING CONDITIONS The procedures below complement or change the remaining procedures presented in this Section.

NOTE: If necessary, set the CKPT FAN Switch to HI position to avoid fog in the cockpit side window.

BEFORE START ADS/AOA HTR Switch............................................. ON

NOTE: It is recommended to turn on the system immediately before engine start.

BEFORE TAKEOFF With engines running check the ice protection system as follows:

WSHLD 1 and WSHLD 2 Switches.................... ON The CAS messages WSHLD 1 (2) HTR FAIL must not be displayed.

WSHLD 1 and WSHLD 2 Switches.................... OFF

ENG 1 and ENG 2 Switches .............................. ON The CAS messages A-I E1 (2) ON must be displayed (after 10 seconds).

ENG 1 and ENG 2 Switches .............................. OFF The CAS messages must disappear.

BLEED Knob ...................................................... OFF VENT

WINGSTAB Switch............................................. ON, THEN OFF The CAS message D-I WINGSTB FAIL must be displayed (after 6 seconds). After 1 minute maximum, the CAS message must disappear.

BLEED Knob ...................................................... AS REQUIRED

N2 ....................................................................... SET Depending on the conditions, it will be required N2 as high as 87%.



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WINGSTAB Switch .............................................ON The CAS message D-I WINGSTB ON must be displayed.

WINGSTAB Switch .............................................OFF

After completing a successful test: Ice Protection System.........................................SET

NOTE: The windshield is the best indication for early ice formation detection. If no ice is building up in the windshield and if not required for defog, leave the windshield heater off, turning it on when required.

--------------------------SHORTLY BEFORE TAKEOFF-------------------------

N2 .......................................................................87% MINIMUM

WINGSTAB Switch .............................................ON

ADS/AOA HTR Switch........................................AUTO

TAKEOFF NOTE: Applicable to airplanes Post-Mod. SB 500-27-0003 or with an

equivalent modification factory incorporated, for airplanes Pre-Mod. SB 500-27-0003, refer to Supplement 2.


NOTE: During takeoff roll, after checking thrust levers to TO/GA, check N1 equal to N1 target and green ATR indication presented on MFD if ATR ON is selected.

Engine Parameters ..................................................MONITOR

Initially rotate the airplane according to the table below.

FLAPS POSITION 1 2

PITCH ANGLE 6° 5.5°


Airspeed..............................................................V2 + 10 KIAS MINIMUM

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AFTER TAKEOFF, CRUISE, DESCENT OR APPROACH If TAT is below 10°C with visible moisture:

ENG 1 and ENG 2 Switches .............................. ON The CAS messages A-I E1 (2) ON must be displayed (after a delay of approximately 10 seconds).

At the first sign of ice accretion in the airplane or if TAT is below 5°C with visible moisture:

WSHLD 1 and WSHLD 2 Switches............... ON

ENG 1 and ENG 2 Switches ......................... ON

WINGSTAB Switch........................................ ON The CAS messages A-I E1 (2) ON, D-I WINGSTB ON and SWPS ICE SPEED must be displayed after few seconds.

NOTE: If any of the above messages is not presented consider the associated system failed. Refer to the applicable Abnormal Procedure.

HOLDING LDG GEAR Lever .................................................... UP

Flaps ........................................................................ UP

Airspeed................................................................... 150 KIAS MINIMUM

WARNING: THE ICE PROTECTION SYSTEM MUST BE KEPT ON UNTIL CREW IS CERTAIN ALL ICE HAS BEEN REMOVED.

APPROACH Airspeed................................................................... VREF + 5 KIAS

MINIMUM

NOTE: Airspeed to be maintained at runway threshold is VREF.


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GO-AROUND


TO/GA Buttons.........................................................PRESS


Rotate the airplane according to the table below.



3 4.0°

FULL 2.0°




3 1

FULL 2



Airspeed..............................................................VAC MINIMUM


AFTER LANDING If the D-I WINGSTB FAIL is presented during taxi in:


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DEMONSTRATED CROSSWIND The maximum demonstrated crosswind component for takeoff and landing is 17 kt. This value is not considered to be limiting.

NOTE: For crosswind landings the “de-crab” technique shall be accomplished.

TURBULENT AIR PENETRATION Turn on the fasten seat belts signs and adjust airspeed. Set thrust for penetration and avoid large thrust variations. Set trim for target speed and do not change it.

Use attitude indicator as the primary instrument. Allow altitude and airspeed to vary and maintain attitude. Avoid abrupt and large control inputs.

NOTE: Do not extend flaps except for approach and landing.

The maximum recommended turbulence air penetration speed can be obtained from the following chart.


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MAXIMUM RECOMMENDED TURBULENT AIR PENETRATION SPEED

0

5000

10000

15000

20000

25000

30000

35000

40000

45000

150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300

ALT

ITU

DE

- ft

AIRSPEED - KIAS

500C

TA00

4 - 1

9NO

V20

08

MRA=0.59

VRA

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SECTION 4

EMERGENCY AND ABNORMAL PROCEDURES

TABLE OF CONTENTS

Block Page

Introduction ........................................................................ 4-00.......... 03

Non-Annunciated Procedures ........................................... 4-01.......... 01

Emergency Procedures................................................ 4-01.......... 03

Abnormal Procedures................................................... 4-01.......... 11

Airplane General (Doors, Baggage Compartment and Lighting)................................................................. 4-02.......... 01

AMS (Air Conditioning, Pneumatics and Pressurization) ...................................................... 4-04.......... 01

Automatic Flight ................................................................. 4-06.......... 01

Electrical ............................................................................ 4-08.......... 01

Engine................................................................................4-10.......... 01

Fire Protection ................................................................... 4-12.......... 01

Flight Controls.................................................................... 4-14.......... 01

Flight Instruments, Communication and Navigation.......... 4-16.......... 01

Fuel .................................................................................... 4-18.......... 01

Hydraulic............................................................................ 4-20.......... 01

Ice and Rain Protection .....................................................4-22.......... 01

Landing Gear and Brakes.................................................. 4-24.......... 01

Oxygen ..............................................................................4-26.......... 01

Warning .............................................................................4-28.......... 01

Smoke Procedures ............................................................ 4-30.......... 01


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INTENTIONALLY BLANK

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INTRODUCTION The emergency and abnormal procedures contained in this manual have been developed by the airplane manufacturer and approved by the Certification Authority for use in the operation of this airplane.

This Section provides the emergency and abnormal procedures to be performed in case of a system malfunction or failure, in order to protect passengers and/or crew from serious harm and to maintain the airworthiness of the airplane.

The Emergency and Abnormal Procedures, in this Section, are ordered in alphabetical sequence and divided into three blocks:

− Non-Annunciated Procedures: procedures, which may not be related to a CAS message but rather to a condition presented in the airplane.

− Annunciated Procedures: procedures related to a CAS message. These procedures are grouped by system and titled with the correspondent CAS message wording.

− Smoke Procedures: contain all annunciated and non-annunciated smoke related procedures.

The actions identified with φ are recall items. They must be performed expeditiously and from memory. The other actions should be performed as soon as the condition permits.

Some procedures require to LAND AS SOON AS POSSIBLE or LAND AS SOON AS PRACTICAL, refer to Section 1, General.

Conditions resulting in a red, yellow or white message must be corrected prior to flight, unless the airplane dispatch is allowed by an approved MEL or another authorized special condition. If messages occur in flight and the safety conditions permit, consideration should be given to landing at an airfield where corrective maintenance can be performed.


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The procedures contained herein assume that:

− Normal procedures have been properly accomplished; − System controls are in normal condition prior to initiation of the

associated procedure; − Airplane systems are operating normally prior to the failure; − All emergency and abnormal checklists are performed in the

order they are presented in the procedure; − Aural warnings are silenced as applicable. Master Warning/

Caution lights are reset as soon as the failure is recognized; − Circuit breakers must not be reset, unless is requested by the

procedures instruction.

TM

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Non-Annunciated Procedures Emergency and Abnormal Procedures


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NON-ANNUNCIATED PROCEDURES

TABLE OF CONTENTS

Block Page

EMERGENCY PROCEDURES

BAGGAGE COMPARTMENT FIRE ..................................4-01.......... 03

DITCHING .........................................................................4-01.......... 04

DUAL ENGINE FAILURE .................................................. 4-01.......... 06

EMERGENCY DESCENT ................................................. 4-01.......... 07

EMERGENCY EVACUATION ........................................... 4-01.......... 07

ENGINE ABNORMAL START........................................... 4-01.......... 08

ENGINE FIRE, SEVERE DAMAGE OR SEPARATION ..............................................................4-01........08A

FORCED LANDING........................................................... 4-01........08B

FUEL LEAKAGE................................................................ 4-01.......... 09

REJECTED TAKEOFF (AT OR BELOW V1)..................... 4-01.......... 09

TAKEOFF WITH ENGINE FAILURE AT OR ABOVE V1..................................................................... 4-01.......... 10

ABNORMAL PROCEDURES

ABNORMAL LANDING GEAR EXTENSION .................... 4-01.......... 11

BLANK DISPLAY UNIT WITH AUTOMATIC REVERSION .......................................... 4-01.......... 11

BLANK DISPLAY UNIT WITHOUT AUTOMATIC REVERSION .......................................... 4-01.......... 11

ENGINE ABNORMAL VIBRATION ...................................4-01.......... 12

ENGINE IN-FLIGHT START ............................................. 4-01.......... 12

ENGINE IN-FLIGHT START ENVELOPE......................... 4-01........12B

ENGINE ITT OVERTEMPERATURE................................ 4-01.......... 14


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Block Page

ABNORMAL PROCEDURES

ENGINE SHUTDOWN .......................................................4-01 ..........14

FUEL TEMPERATURE INDICATION FAILURE ...............4-01 ..........14

FUEL TEMPERATURE OUT OF RANGE .........................4-01 ..........14

GEAR LEVER CAN NOT BE MOVED UP.........................4-01 ..........15

IMPAIRED OR CRACKED WINDSHIELD.........................4-01 ..........15

INADVERTENT PUSHER ACTUATION............................4-01 ..........15

LOSS OF PRESSURIZATION INDICATION.....................4-01 ..........16

ONE ENGINE INOPERATIVE APPROACH AND LANDING .............................................................4-01 ..........17

OXYGEN LEAKAGE..........................................................4-01 ..........18

PARTIAL OR GEAR UP LANDING ...................................4-01 ..........18

STRUCTURAL DAMAGE ..................................................4-01 ..........19

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EMERGENCY PROCEDURES

BAGGAGE COMPARTMENT FIRE LAND AS SOON AS POSSIBLE.


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DITCHING NOTE: - Applicable to airplanes Post-Mod. SB 500-27-0003 or with

an equivalent modification factory incorporated, for airplanes Pre-Mod. SB 500-27-0003, refer to Supplement 2.

- The airplane is not certified for ditching. The procedure below is recommended to be followed if required.

During descent: Passengers .........................................................PREPARE/LIFE

VESTS, IF AVAILABLE, DON

ATC.....................................................................NOTIFY Transponder........................................................7700 SIGNS/OUTLET Switch......................................PED-BELTS/OFF Water Barrier....................................................... INSTALL

At 10000 ft, push the Pressurization DUMP Button in. Ditching configuration:

LDG GEAR Lever ...............................................UP Flaps ...................................................................MAX AVAILABLE Oxygen Bottle Valve Handle...............................PULL TO CUTOUT For airplanes Pre-Mod. SB 500-27-0001, if it is not possible to achieve the selected flaps position, maintain airspeed according to the following:

MINIMUM AIRSPEED FLAPS POSITION NO ICING IN ICING/WITH ICE

0 VREF FULL + 47 KIAS VREF FULL + 51 KIAS 1 VREF FULL + 40 KIAS VREF FULL + 40 KIAS

2 and 3 VREF FULL + 25 KIAS VREF FULL + 30 KIAS FULL VREF FULL + 20 KIAS VREF FULL + 25 KIAS

NOTE: - If flaps stop between two positions, use the minimum airspeed associated to the next retracted position and the VFE associated to the next extended position.

- Disregard green circle indication, as it may indicate slower speeds.


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For airplanes Post-Mod. SB 500-27-0001 or with an equivalent modification factory incorporated, if it is not possible to achieve the selected flaps position, maintain airspeed according to the following:



2 and 3 VREF FULL + 5 KIAS VREF FULL + 30 KIAS FULL VREF FULL VREF FULL + 25 KIAS



Just before water contact: Passengers......................................................... ANNOUNCE

After ditching: Thrust Levers...................................................... IDLE Start/Stop Knobs ................................................ STOP Fire Extinguish System....................................... AS REQUIRED Emergency Evacuation....................................... ANNOUNCE BATT 1 & 2 Switches.......................................... OFF


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DUAL ENGINE FAILURE LAND AS SOON AS POSSIBLE.

φ Thrust Levers........................................................ IDLE

If both engines were restarted via auto relight: Engine Parameters .............................................MONITOR

Monitor the engine parameters for remainder of the flight.

If no engine was restarted via auto relight: Airspeed and Altitude..........................................AS PER

REGION 3 OF ENGINE IN-FLIGHT START ENVELOPE

Either Engine Start/Stop Knob............................START, THEN RUN

NOTE: Start the engines one at a time, initiating the in-flight start sequence through the right engine, if possible.

If the dual engine failure condition persists: FORCED LANDING or

DITCHING Procedure...............................ACCOMPLISH

If at least on engine is recovered: Engine Parameters ........................................MONITOR

Monitor the engine parameters for remainder of the flight.

If applicable: ONE ENGINE INOPERATIVE APPROACH

AND LANDING Procedure ..................ACCOMPLISH

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EMERGENCY DESCENT φ SIGNS/OUTLET Switch ....................................... PED-BELTS/OFF φ Altitude.................................................................. 10000 ft OR MEA,

WHICHEVER IS HIGHER

φ Thrust Levers........................................................ IDLE φ Airspeed ............................................................... 250 KIAS/MMO

MAXIMUM φ LDG GEAR Lever................................................. DN φ Airspeed ............................................................... 275 KIAS/MMO

MAXIMUM φ Transponder ......................................................... 7700 φ ATC ...................................................................... NOTIFY

EMERGENCY EVACUATION φ Thrust Levers........................................................ IDLE φ Emergency/Parking Brake.................................... ON φ Start/Stop Knobs .................................................. STOP φ Fire Shutoff Button ............................................... PUSH IN φ Pressurization DUMP Button................................ PUSH IN φ ATC ...................................................................... NOTIFY φ Emergency Evacuation ........................................ ANNOUNCE φ BATT 1 & 2 Switches ........................................... OFF


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ENGINE ABNORMAL START φ Start/Stop Knob (affected engine) ........................STOP

If an engine dry motoring is considered: Associated Ignition Switch ..................................OFF Associated Start/Stop Knob................................START, THEN

RUN

After 30 seconds: Associated Start/Stop Knob...........................STOP Associated Ignition Switch.............................AUTO

If applicable: ONE ENGINE INOPERATIVE APPROACH

AND LANDING Procedure.............................ACCOMPLISH

TM

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ENGINE FIRE, SEVERE DAMAGE OR SEPARATION φ Thrust Lever (affected engine) ............................. IDLE φ Start/Stop Knob (affected engine) ........................ STOP φ Fire Shutoff Button (affected engine) ................... PUSH IN

LAND AS SOON AS POSSIBLE.

Wait 30 seconds and if fire persists: Fire Extinguishing Switch ................................... DISCH

Altitude..................................................................... 31000 ft MAXIMUM

BLEED Knob............................................................ OPPOSITE SIDE Thrust Lever (operative engine) .............................. AS REQUIRED

If high vibration exists: Airspeed.............................................................. REDUCE

(130 KIAS MINIMUM)

Reduce airspeed as required to keep vibration within acceptable levels.

When appropriate: ONE ENGINE INOPERATIVE APPROACH

AND LANDING Procedure ............................ ACCOMPLISH


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4-01 ANAC APPROVED Page 8B code 01 REVISION 5

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FORCED LANDING


This procedure is recommended for landings with all engines inoperative or for landings in unprepared surfaces. Landing on unprepared surfaces is not recommended. However, if specific circumstances render such landing inevitable, accomplish the procedures below:

Passengers .........................................................PREPARE ATC.....................................................................NOTIFY Transponder........................................................7700 SIGNS/OUTLET Switch......................................PED-BELTS/OFF ELT .....................................................................ON Landing Data.......................................................SET

At 10000 ft push in the Pressurization DUMP Button and set the altimeters during approach.

For landing configuration: LDG GEAR Lever ...............................................AS REQUIRED

NOTE: The decision to land with gear up or extended is left to pilots. The choice of configuration is based on airplane load distribution, controllability and conditions of the landing field.

Flaps ...................................................................MAXIMUM AVAILABLE


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PHENOM 100



ANAC APPROVED 4-01 REVISION 5 code 01 Page 8C

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For airplanes Pre-Mod. SB 500-27-0001, if it is not possible to achieve the selected flaps position, maintain airspeed according to the following:














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4-01 ANAC APPROVED Page 8D code 01 REVISION 2

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Oxygen Bottle Valve Handle...............................PULL TO CUTOUT

Just before touchdown: Passengers .........................................................ANNOUNCE

IMPACT

After landing, if conditions permit: Thrust Lever........................................................ IDLE Start/Stop Knobs.................................................STOP Fire Shutoff Buttons ............................................PUSH IN Emergency Evacuation.......................................ANNOUNCE BATT 1 & 2 Switches..........................................OFF

TM

PHENOM 100




AFM

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FUEL LEAKAGE LAND AS SOON AS POSSIBLE.

FUEL XFR Button .................................................... PUSH OUT Thrust Levers........................................................... SAME N1 SET ON

BOTH ENGINES

If N1 and fuel flow indications from both engines match: Thrust Levers................................................. ADJUST

Use asymmetric thrust to improve or maintain fuel balance.

If the fuel leakage continues and is severe: Affected Engine Shutdown....................... CONSIDER

If N1 from both engines match, but fuel flow indications are discrepant:

Affected Engine ............................................. SHUTDOWN

If engine shutdown is performed: Affected Fire Shutoff Button ............................... PUSH IN


AND LANDING Procedure ....................... ACCOMPLISH

REJECTED TAKEOFF (AT OR BELOW V1) φ Thrust Levers........................................................ IDLE Brakes...................................................................... APPLY MAXIMUM Directional Control ................................................... MAINTAIN

Immediately after stopping: ENGINE SHUTDOWN or

ENGINE FIRE, SEVERE DAMAGE OR SEPARATION Procedure.............................. AS REQUIRED


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AFM

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TAKEOFF WITH ENGINE FAILURE AT OR ABOVE V1 φ At VR rotate the airplane according to the table below:

PITCH ANGLE FLAPS POSITION NO ICING IN ICING/WITH ICE

1 9.5° 6.0°

2 9° 5.5°

φ With positive rate of climb:

φ LDG GEAR Lever ............................................UP φ Airspeed...........................................................V2 MININUM

Maintain V2 up to the acceleration altitude. At the acceleration altitude, select flaps up according to the following flaps retraction schedule:

SELECT FLAPS AT SPEED T/O FLAPS

1 0

1 - V2 + 11 KIAS

2 V2 + 9 KIAS V2 + 20 KIAS

Accelerate the airplane to the final segment speed (VFS) and set the engine thrust rate to continuous.

NOTE: After reaching the minimum airspeed, maintain the airspeed regardless of the pitch angle.

After retracting flaps, accomplish the ENGINE 1 (2) FAILURE Procedure.

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PHENOM 100




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ABNORMAL PROCEDURES

ABNORMAL LANDING GEAR EXTENSION LDG GEAR Lever .................................................... DN Free Fall Handle ...................................................... PULL AND

ROTATE

If gear does not lock down: Airspeed.............................................................. 140 KIAS

MINIMUM

Slip the airplane to attempt to lock the main gears.

Check landing gear indications. If landing gear indications are still not confirmed down, accomplish the PARTIAL OR GEAR UP LANDING Procedure.

BLANK DISPLAY UNIT WITH AUTOMATIC REVERSION Cycle the display backup button (OUT then IN). If the system does not revert to the normal condition or an abnormal behavior occurs, press the display backup button again.

NOTE: Only one attempt to return to a normal condition is allowed.

BLANK DISPLAY UNIT WITHOUT AUTOMATIC REVERSION Press the display backup button and select the reversionary mode, as required.


TM



AFM

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ENGINE ABNORMAL VIBRATION Reduce the associated thrust lever to IDLE in order to keep vibration within acceptable levels.

NOTE: Reduce the thrust levers one at a time to attempt identifying the affected engine.

If the engine abnormal vibration persists, accomplish the ENGINE SHUTDOWN Procedure.

CAUTION: CONTINUOUS HIGH VIBRATION MAY DAMAGE THE ENGINE.

ENGINE IN-FLIGHT START Check the in-flight envelope and set the inoperative engine as follows:

Thrust Lever........................................................ IDLE ENG IGNITION Switch .......................................AUTO Start/Stop Knob...................................................START, THEN

RUN

If the engine is normally restarted: Thrust Levers (operative engine)........................AS REQUIRED

If the engine fails to restart or abnormal start occurs: Start/Stop Knob...................................................STOP Thrust Lever (operative engine)..........................AS REQUIRED Fuel .....................................................................BALANCE ONE ENGINE INOPERATIVE APPROACH


CAUTION: THE ENGINE MAY BE ACCELERATED ONCE A STABLE IDLE HAS BEEN ACHIEVED, BUT, IF THE ENGINE HAS BEEN OPERATED ABOVE IDLE DURING THE PRIOR 30 MINUTES, REMAIN AT IDLE FOR AT LEAST 2 MINUTES AFTER ROUTINE ENGINE STARTS, TO REDUCE THE POTENTIAL OF TURBINE BLADE RUB.

TM

PHENOM 100



ANAC APPROVED 4-01 REVISION 9 code 01 Page 12A

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INTENTIONALLY BLANK


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4-01 ANAC APPROVED Page 12B code 01 REVISION 9

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ENGINE IN-FLIGHT START ENVELOPE

FOR AIRPLANES 50000005 THRU 50000216 PRE-MOD. SB 500-73-0002

0

5000

10000

15000

20000

25000

30000

35000

80 100 120 140 160 180 200 220 240 260 280

ALT

ITU

DE

- ft

AIRSPEED - KIAS500A

NAC

005

- 30S

ET20

08

31

2

REGIONS - 1, 2 AND 3 - GENERATOR ASSISTED STARTREGION 2 - RELIGHT IS NOT GUARANTEED IF ITT IS BELOW 80°CREGION 3 - REQUIRED FOR BATTERY EMERGENCY START

27000 ft275 KIAS

110 KIAS


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PHENOM 100




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FOR AIRPLANES 50000005 THRU 50000216 POST-MOD. SB 500-73-0002 AND FOR AIRPLANES 50000218 AND ON

0

5000

10000

15000

20000

25000

30000

35000

80 100 120 140 160 180 200 220 240 260 280

ALT

ITU

DE

- ft

AIRSPEED - KIAS500A

NAC

005

- 31A

GO

2010

3

1

2

REGIONS - 1, 2 AND 3 - GENERATOR ASSISTED STARTREGION 2 - RECOMMENDED ITT ABOVE 80°CREGION 3 - REQUIRED FOR BATTERY EMERGENCY START

27000275 KIAS

110 KIAS


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AFM

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ENGINE ITT OVERTEMPERATURE The ITT gray quadrant indication becomes red.

Associated Thrust Lever ..........................................REDUCE

ENGINE SHUTDOWN LAND AS SOON AS POSSIBLE.

Thrust Lever (affected engine)................................. IDLE Start/Stop Knob (affected engine)............................STOP Thrust Lever (operative engine)...............................AS REQUIRED Fuel ..........................................................................BALANCE Airspeed...................................................................130 KIAS

MINIMUM

When appropriate, accomplish the ONE ENGINE INOPERATIVE APPROACH AND LANDING Procedure.

FUEL TEMPERATURE INDICATION FAILURE If in flight, descend to lower altitudes if external temperature is below -37°C.

FUEL TEMPERATURE OUT OF RANGE In flight:

If fuel temperature is below -37°C descend to lower altitudes.

If fuel temperature is above 80°C: LAND AS SOON AS PRACTICAL.

TM

PHENOM 100




AFM

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GEAR LEVER CAN NOT BE MOVED UP If possible, wait until 400 ft height is achieved to verify if the LG WOW SYS FAIL message is presented.

If the message is not presented: DN LCK REL Button ........................................... PRESS LDG GEAR Lever ............................................... UP

WARNING: IF CLIMB PERFORMANCE IS REQUIRED TO CLEAR OBSTACLES DURING TAKEOFF OR GO-AROUND, MOVE LANDING GEAR LEVER TO UP POSITION AT ANY TIME.

IMPAIRED OR CRACKED WINDSHIELD Affected Windshield Heating Switch........................ OFF Airspeed................................................................... 220 KIAS

MAXIMUM Altitude..................................................................... 10000 ft OR MEA,

WHICHEVER IS HIGHER

During descent: Pressurization MODE Switch ............................. MAN Cabin Altitude ..................................................... INCREASE

Maintain cabin altitude at 10000 ft.

At or below 10000 ft: BLEED Knob ...................................................... OFF VENT

For dual pilot operation and if only one side is impaired, the pilot flying must be on the non-impaired side.

INADVERTENT PUSHER ACTUATION AP/YD/TRIM/PUSHER Disc Button......................... PRESS PUSHER CUTOUT Button ...................................... PUSH IN PUSHER FAILURE Procedure................................ ACCOMPLISH


TM



AFM

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LOSS OF PRESSURIZATION INDICATION Use the remaining indications to maintain cabin altitude below 10000 ft, according to the table below:

AIRPLANE ALTITUDE

(ft)

CABIN ALTITUDE

(ft)

DIFFERENTIAL PRESSURE

(PSID) 10000 600 3.9 11000 700 4.2 12000 800 4.5 13000 1000 4.8 14000 1100 5.0 15000 1300 5.3 16000 1500 5.6 17000 1600 5.8 18000 1800 6.0 19000 2000 6.2 20000 2200 6.4 21000 2500 6.6 22000 2700 6.7 23000 2900 6.9 24000 3100 7.0 25000 3400 7.2 26000 3700 7.3 27000 3900 7.4 28000 4200 7.5 29000 4400 7.6 30000 4700 7.7 31000 5000 7.7 32000 5300 7.8 33000 5600 7.8 34000 5900 7.9 35000 6200 7.9 36000 6500 7.9 37000 6800 7.9 38000 7100 7.9 39000 7400 8.1 40000 7700 8.2 41000 8000 8.3

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PHENOM 100




AFM

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ONE ENGINE INOPERATIVE APPROACH AND LANDING NOTE: - Applicable to airplanes Post-Mod. SB 500-27-0003 or with

an equivalent modification factory incorporated, for airplanes Pre-Mod. SB 500-27-0003, refer to Supplement 2.

- For airplanes Pre-Mod. SB 500-27-0001, the GO-AROUND Procedure of the AD 2009-05-06 (action 3) must be accomplished.

During descent: Landing Speeds.................................................. SET Landing Field Elevation ...................................... SET Approach Aids .................................................... SET Altimeters............................................................ SET/CHECK

Landing configuration: LDG GEAR Lever ............................................... DN Flaps................................................................... 3 Airspeed.............................................................. VREF FULL + 10 KIAS

MINIMUM

CAUTION: MULTIPLY THE FULL FLAPS UNFACTORED LANDING DISTANCE BY 1.25.

If a go-around is required: Go-Around Button............................................... PRESS Thrust Levers...................................................... TO/GA


Rotate the airplane to 7.5° nose up.

Flaps................................................................... 1

With positive rate of climb: LDG GEAR Lever ............................................... UP Airspeed.............................................................. APPROACH

CLIMB SPEED


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AFM

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OXYGEN LEAKAGE Leakage may be identified through the pressure indication on MFD. Communicate the passenger cabin for not smoking.

Altitude .....................................................................14000 ft OR MEA, WHICHEVER IS HIGHER

Oxygen Bottle Valve Handle ....................................PULL TO CUTOUT

PARTIAL OR GEAR UP LANDING Burn off fuel to reduce touchdown speed.

Passengers ..............................................................NOTIFY

Prior to approach: Pressurization DUMP Button ..............................PUSH IN LDG GEAR Lever ...............................................AS REQUIRED

NOTE: The decision to land with all gear up or with any gear extended is left to pilots. The choice of configuration is based on the number of gear available, airplane load distribution, controllability and conditions of the landing field.

Just before touchdown, announce to the passengers.

After landing: Thrust Levers ...................................................... IDLE Start/Stop Knobs.................................................STOP Fire Extinguishing System ..................................AS REQUIRED Emergency Evacuation.......................................ANNOUNCE BATT 1 & 2 Switches..........................................OFF

If a go-around is required: LDG GEAR Lever ...............................................MAINTAIN DN

TM

PHENOM 100




AFM

-265

6

STRUCTURAL DAMAGE LAND AS SOON AS POSSIBLE.

Limit the airspeed to 160 KIAS maximum.

If the fuselage is damaged: Altitude................................................................ 10000 ft OR MEA,

WHICHEVER IS HIGHER

When reaching 10000 ft: Pressurization DUMP Button......................... PUSH IN

Establish landing configuration early.


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INTENTIONALLY BLANK

TM

PHENOM 100


Airplane General Emergency and Abnormal Procedures


AFM

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AIRPLANE GENERAL (DOORS, BAGGAGE COMPARTMENT

AND LIGHTING)

TABLE OF CONTENTS

Block Page

WARNING

DOOR EMERGENCY OPEN ............................................ 4-02.......... 03

DOOR PASSENGER OPEN ............................................. 4-02.......... 03

CAUTION

DOOR BAGGAGE AFT OPEN..........................................4-02.......... 04

DOOR BAGGAGE FORWARD OPEN..............................4-02.......... 04


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Emergency and Abnormal Procedures Airplane General


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INTENTIONALLY BLANK

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PHENOM 100


Airplane General Emergency and Abnormal Procedures


AFM

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DOOR EMERGENCY OPEN SIGNS/OUTLET Switch........................................... PED-BELTS/OFF

If pressurization is normal, continue the flight monitoring the pressurization.

If pressurization is abnormal: LAND AS SOON AS POSSIBLE.

Altitude................................................................ 10000 ft OR MEA, WHICHEVER IS HIGHER

DOOR PASSENGER OPEN SIGNS/OUTLET Switch........................................... PED-BELTS/OFF

If pressurization is normal: Door Lock Indicators........................................... GREEN

If at least seven door latch indicators are in green, continue the flight monitoring the pressurization.

If two or more door indicators are not in green or if pressurization is abnormal:


Altitude................................................................ 10000 ft OR MEA, WHICHEVER IS HIGHER

At 10000 ft: Pressurization DUMP Button......................... PUSH IN BLEED Knob ................................................. OFF VENT


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Emergency and Abnormal Procedures Airplane General


AFM

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DOOR BAGGAGE AFT OPEN Airspeed...................................................................REDUCE TO

160 KIAS

DOOR BAGGAGE FORWARD OPEN LAND AS SOON AS PRACTICAL.

Airspeed...................................................................REDUCE TO 160 KIAS

TM

PHENOM 100


AMS (Air Conditioning, Pneumatics and Pressurization)



AFM

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AMS (AIR CONDITIONING, PNEUMATICS AND PRESSURIZATION)

TABLE OF CONTENTS

Block Page

WARNING

CABIN ALTITUDE HIGH ................................................... 4-04.......... 03

CAUTION

BLEED 1 (2) FAILURE ......................................................4-04.......... 03

BLEED 1 (2) LEAKAGE..................................................... 4-04.......... 04

CABIN DELTA PRESSURE FAILURE..............................4-04.......... 05

DUCT 1 (2) OVERTEMPERATURE..................................4-04.......... 05

ELECTRONIC BAY OVERHEAT ...................................... 4-04.......... 06

PRESSURIZATION AUTO FAILURE................................4-04.......... 07

ADVISORY

BLEED 1 (2) OFF .............................................................. 4-04.......... 07

RAM AIR FAILURE............................................................ 4-04.......... 07


TM

Emergency and Abnormal Procedures AMS (Air Conditioning, Pneumatics

and Pressurization)


AFM

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INTENTIONALLY BLANK

TM

PHENOM 100





AFM

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CABIN ALTITUDE HIGH φ Crew Oxygen Masks ............................................ DON, 100% φ Crew Communication ........................................... ESTABLISH φ SIGNS/OUTLET Switch ....................................... PED-BELTS/OFF φ Altitude.................................................................. 10000 ft OR MEA,

WHICHEVER IS HIGHER

φ Thrust Levers ....................................................... IDLE φ Airspeed ............................................................... 250 KIAS/MMO

MAXIMUM φ LDG GEAR Lever................................................. DN φ Airspeed ............................................................... 275 KIAS/MMO

MAXIMUM φ Transponder ......................................................... 7700 φ ATC ...................................................................... NOTIFY

If passenger masks are not deployed automatically or PAX OXY NO PRES message is displayed:

Oxygen SUPPLY CONTROL Knob.................... PAX OVRD

At 10000 ft: Pressurization DUMP Button.............................. PUSH IN BLEED Knob ...................................................... OFF VENT LDG GEAR Lever ............................................... AS REQUIRED

If landing is not soon, consider retracting landing gear.

BLEED 1 (2) FAILURE BLEED Knob............................................................ OPPOSITE SIDE

Wait 1 minute.

BLEED Knob............................................................ BOTH

If the BLEED 1 (2) FAIL message persists: BLEED Knob ...................................................... OPPOSITE SIDE Altitude................................................................ 31000 ft

MAXIMUM


TM


and Pressurization)


AFM

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6

BLEED 1 (2) LEAKAGE

CAUTION: LIMIT THE ALTITUDE TO 31000 ft MAXIMUM AND SIMULTANEOUSLY ACCOMPLISH STEPS BELOW.

If associated with EBAY OVHT message, accomplish the ELECTRONIC BAY OVERHEAT Procedure.

BLEED Knob............................................................OPPOSITE SIDE Altitude .....................................................................31000 ft

MAXIMUM

If the affected side BLEED OFF message is not displayed or BLEED LEAK message persists after 3 minutes:

Associated Thrust Lever ..................................... IDLE BLEED Knob.......................................................OFF VENT Altitude ................................................................10000 ft OR MEA,

WHICHEVER IS HIGHER


Leave and avoid icing conditions. At 10000 ft: Pressurization DUMP Button.........................PUSH IN

If the associated BLEED LEAK message still persists, shutdown the associated engine.

When applicable: ONE ENGINE INOPERATIVE APPROACH

AND LANDING Procedure .......................ACCOMPLISH

TM

PHENOM 100





AFM

-265

6

CABIN DELTA PRESSURE FAILURE If the cabin differential pressure reached the red limit, check its indication.

Altitude..................................................................... 10000 ft OR MEA, WHICHEVER IS HIGHER

If the cabin differential pressure indication is positive: PRESSURIZATION MODE Selector.................. MAN CABIN ALT Switch ............................................. UP

If not possible to modulate cabin altitude: Pressurization DUMP Button ........................ PUSH IN BLEED Knob ................................................. OFF VENT Crew Oxygen Masks ..................................... DON, 100% Crew Communication .................................... ESTABLISH

Leave and avoid icing conditions.

If the indication is negative: Airplane Descent Rate ....................................... REDUCE

DUCT 1 (2) OVERTEMPERATURE AIR CONDITIONING MODE Switch ....................... MAN AIR CONDITIONING TEMP Switch ........................ COLD FOR

5 SECONDS

Wait 1 minute.

If the DUCT 1 (2) OVERTEMP message still persists, after 1 minute: BLEED Knob ...................................................... OPPOSITE BLEED Altitude................................................................ 31000 ft

MAXIMUM



TM


and Pressurization)


AFM

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6


If the BLEED 1 (2) FAIL message is displayed: Associated Thrust Lever ..................................... IDLE

When applicable: ONE ENGINE INOPERATIVE APPROACH

AND LANDING Procedure .......................ACCOMPLISH

ELECTRONIC BAY OVERHEAT AIR CONDITIONING MODE Switch........................MAN AIR CONDITIONING TEMP Switch.........................COLD FOR

15 SECONDS

If the EBAY OVHT message extinguishes: Altitude ................................................................25000 ft

MAXIMUM

If the EBAY OVHT message persists: SIGNS/OUTLET Switch......................................PED-BELTS/OFF

Wait 2 minutes and if the EBAY OVHT message persists: LAND AS SOON AS POSSIBLE.

Altitude...........................................................10000 ft OR MEA, WHICHEVER IS HIGHER

Thrust Levers................................................. IDLE Airspeed.........................................................250 KIAS/MMO

MAXIMUM LDG GEAR Lever ..........................................DN Airspeed.........................................................275 KIAS/MMO

MAXIMUM ATC................................................................NOTIFY

At 10000 ft: Pressurization DUMP Button....................PUSH IN BLEED Knob ............................................OFF VENT

TM

PHENOM 100





AFM

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6

PRESSURIZATION AUTO FAILURE Pressurization MODE Switch .................................. MAN, THEN AUTO

If the PRESN AUTO FAIL message persists and the manual mode is operative:

Pressurization MODE Switch ............................. MAN CABIN ALT Switch ............................................. AS REQUIRED

When appropriate before landing: CABIN ALT Switch ........................................ HOLD UP FOR

15 SECONDS

If the PRESN AUTO FAIL message persists and the manual mode is inoperative:

Crew Oxygen Masks .......................................... DON, 100% Crew Communication ......................................... ESTABLISH BLEED Knob ...................................................... OFF VENT Altitude................................................................ 10000 ft OR MEA,

WHICHEVER IS HIGHER

At 10000 ft: Leave and avoid icing conditions.

BLEED 1 (2) OFF Altitude..................................................................... 31000 ft

MAXIMUM

RAM AIR FAILURE If associated with both bleeds failure, LAND AS SOON AS PRACTICAL.


TM


and Pressurization)


AFM

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INTENTIONALLY BLANK

TM

PHENOM 100


Automatic Flight Emergency and Abnormal Procedures


AFM

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AUTOMATIC FLIGHT

TABLE OF CONTENTS

Block Page

CAUTION

AUTOPILOT FAILURE ...................................................... 4-06.......... 03

AUTOPILOT PITCH MISTRIM .......................................... 4-06.......... 03

AUTOPILOT ROLL MISTRIM............................................ 4-06.......... 03

AUTOMATIC PITCH TRIM FAIL ....................................... 4-06.......... 03

YAW DAMPER FAILURE.................................................. 4-06.......... 03

YAW DAMPER MISTRIM.................................................. 4-06.......... 04


TM

Emergency and Abnormal Procedures Automatic Flight


AFM

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INTENTIONALLY BLANK

TM

PHENOM 100


Automatic Flight Emergency and Abnormal Procedures


AFM

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6

AUTOPILOT FAILURE Autopilot................................................................... DISCONNECT

Fly the airplane manually and refer to the RVSM Operation Supplement.

AUTOPILOT PITCH MISTRIM Control Wheel .......................................................... HOLD FIRMLY AP/YD/TRIM/PUSHER Disc Button......................... PRESS Pitch Trim................................................................. AS REQUIRED Autopilot................................................................... AS REQUIRED

AUTOPILOT ROLL MISTRIM Control Wheel .......................................................... HOLD FIRMLY AP/YD/TRIM/PUSHER Disc Button......................... PRESS Roll Trim .................................................................. AS REQUIRED Autopilot................................................................... AS REQUIRED

AUTOMATIC PITCH TRIM FAIL Control Wheel .......................................................... HOLD FIRMLY AP/YD/TRIM/PUSHER Disc Button......................... PRESS Pitch Trim................................................................. AS REQUIRED Autopilot................................................................... AS REQUIRED

YAW DAMPER FAILURE Airspeed................................................................... 250 KIAS

MAXIMUM Altitude..................................................................... 25000 ft

MAXIMUM


TM

Emergency and Abnormal Procedures Automatic Flight


AFM

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YAW DAMPER MISTRIM Control Wheel ..........................................................HOLD FIRMLY Rudder Pedal ...........................................................HOLD AP/YD/TRIM/PUSHER Disc Button.........................PRESS Rudder Pedal ...........................................................APPLY Yaw Trim..................................................................AS REQUIRED Yaw Damper ............................................................AS REQUIRED

TM

PHENOM 100


Electrical Emergency and Abnormal Procedures


AFM

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6

ELECTRICAL

TABLE OF CONTENTS

Block Page

EMERGENCY

ELECTRICAL EMERGENCY ............................................4-08.......... 03

ELECTRICAL EMERGENCY TRANSFER FAIL ............... 4-08.......... 05

CAUTION

BATTERY 1 (2) OFF BUS .................................................4-08.......... 05

BATTERY DISCHARGE.................................................... 4-08.......... 05

BATTERY EXCEEDANCE ................................................ 4-08.......... 05

GENERATOR 1 (2) OFF BUS...........................................4-08.......... 06

GENERATOR OVERLOAD............................................... 4-08.......... 06

GENERATOR START FAULT...........................................4-08.......... 06

ADVISORY

DC BUS 1 OFF.................................................................. 4-08.......... 07

DC BUS 2 OFF.................................................................. 4-08.......... 09

EMERGENCY BUS OFF................................................... 4-08.......... 10


TM

Emergency and Abnormal Procedures Electrical


AFM

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INTENTIONALLY BLANK

TM

PHENOM 100




AFM

-265

6

ELECTRICAL EMERGENCY


Reset both generators.

If message persists: LAND AS SOON AS POSSIBLE.

ADS/AOA Knob .................................................. ON

Exit and avoid icing conditions.

Confirm that IESI has reverted. If not, select ADSTBY on PFD.

Pressurization MODE Switch ............................. MAN CABIN ALT Switch ............................................. AS REQUIRED Airspeed.............................................................. 250 KIAS

MAXIMUM Altitude................................................................ 25000 ft

MAXIMUM

CAUTION: BATTERIES DURATION IS 45 MINUTES MAXIMUM.

When landing maintain airspeed according to the following:

FLAPS POSITION MINIMUM AIRSPEED 0 VREF FULL + 30 KIAS 1 VREF FULL + 15 KIAS

2 and 3 VREF FULL + 5 KIAS FULL VREF FULL



During landing run: Emergency/Parking Brake.................................. APPLY



TM



AFM

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6


CAUTION: WHEN APPLYING EMERGENCY BRAKES, PULL THE HANDLE PROGRESSIVELY, MONITORING THE EMERGENCY/PARKING BRAKE LIGHT.

NOTE: The emergency/parking brake accumulator allows 6 actuations.

CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS FULL BY ONE OF THE FACTORS BELOW.

FLAPS POSITION CORRECTION FACTOR0 2.25 1 1.75

2 and 3 1.65 FULL 1.50

If a go-around is required, maintain the minimum airspeed presented in the applicable flaps configuration from the table above, until the acceleration altitude is reached.

The list below presents the relevant inoperative equipment. Items marked with an asterisk have dedicated failure procedures, which may have to be performed, at pilot’s discretion: - ADC 1 and 2 (*) - Pitch Trim (Main) (*) - AHRS 2 (*) - Pressurization Auto (*) - Air Conditioning - Radar Altimeter (If Installed) - Anti-Ice/De-Ice Systems - Roll Trim - Audio Panel 2 (*) - Stick Pusher (*) - Autopilot (*) - TAWS-A (If Installed) - DME’s - TCAS I or TCAS II (If Installed) - Flap System (*) - Transponder 2 - FMS Panel - VHF 2 - GIA 2 (*) - Windshields Heater (*) - GPS 2/VOR 2/ILS 2 - WX Radar - Landing/Taxi Lights - Yaw Damper - Main Brake (*) - Yaw Trim - PFD 2

TM

PHENOM 100



ANAC APPROVED 4-08 ORIGINAL code 01 Page 5 A

FM-2

656

ELECTRICAL EMERGENCY TRANSFER FAIL LAND AS SOON AS POSSIBLE.

ELEC EMER Button................................................. PUSH IN

If transference is still failed: Electrical Load .................................................... REDUCE

If transference is confirmed: ELECTRICAL EMERGENCY Procedure ........... ACCOMPLISH

BATTERY 1 (2) OFF BUS Associated BATT Switch ......................................... OFF, THEN ON

If message persists: Associated BATT Switch .................................... ON

BATTERY DISCHARGE LAND AS SOON AS POSSIBLE.

ELEC EMER Button................................................. PUSH IN

CAUTION: BATTERY DURATION IS 45 MINUTES.

BATTERY EXCEEDANCE BATT 1 Switch ......................................................... OFF

If exceedance message persists: BATT 1 Switch.................................................... ON BATT 2 Switch.................................................... OFF

If exceedance message persists: BATT 2 Switch............................................... ON ELEC EMER Button ...................................... PUSH IN



TM



AFM

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6

GENERATOR 1 (2) OFF BUS Associated GEN Switch ...........................................OFF, THEN AUTO

If message persists: Associated GEN Switch......................................OFF

GENERATOR OVERLOAD AIR CONDITIONING MODE Switch........................OFF

If the message persists: WSHLD 2 Knob...................................................OFF

If the message persists: Electrical Load ....................................................REDUCE

GENERATOR START FAULT BATT 2 Switch .........................................................OFF ELEC EMER Button.................................................PUSH IN ELECTRICAL EMERGENCY Procedure.................ACCOMPLISH


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ANAC APPROVED 4-08 REVISION 7 code 01 Page 7 A

FM-2

656

DC BUS 1 OFF NOTE: Applicable to airplanes Post-Mod. SB 500-27-0003 or with an


ADS/AOA Knob ....................................................... ON Icing Conditions ....................................................... EXIT/AVOID

For landing proceed: - Maintain airspeed according to the following:







CORRECTION FACTOR FLAPS

POSITION NO ICING IN ICING/WITH ICE

0 1.40 1.70 1 1.20 1.60

2 and 3 1.10 2.00 FULL 1.00 1.95



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The list below presents the relevant inoperative equipment. Items marked with an asterisk have dedicated failure procedures, which may have to be performed, at pilot’s discretion:

- ADC 1 (*) - Roll Trim

- Cockpit FCSOV - Stick Pusher (*)

- De-Ice System (*) - TAWS-A (If Installed)

- DME 1 - TCAS I or TCAS II (If Installed)

- Engine 1 Anti-Ice (*) - VHF 2

- Engine 1 Flowmeter - Windshield Heater 1 (*)

- Flap System (*) - WX Radar

- Left Landing/Taxi Light - Yaw Trim

- Radar Altimeter (If Installed)

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656

DC BUS 2 OFF Icing Conditions ....................................................... EXIT/AVOID Airspeed................................................................... 250 KIAS

MAXIMUM Altitude..................................................................... 25000 ft

MAXIMUM


CAUTION: • MULTIPLY THE FULL FLAPS UNFACTORED LANDING DISTANCE BY 1.5.

• WHEN APPLYING EMERGENCY BRAKES, PULL THE HANDLE PROGRESSIVELY, MONITORING THE EMERGENCY/PARKING BRAKE LIGHT.



- ADC 2 (*) - GIA 2 (*)

- AHRS 2 (*) - GPS 2/VOR 2/ILS 2

- Audio Panel 2 - Main Brake (*)

- Autopilot (*) - PFD 2

- Cabin FCSOV - Pitch Trim (Main) (*)

- DME 2 - Pressurization Auto (*)

- EFCU 2 - Right Landing/Taxi Light

- Engine 2 Anti-Ice (*) - Stick Pusher (*)

- Engine 2 Flowmeter - Transponder 2

- Flight Director 2 - Windshield Heater 2 (*)

- FMS Panel - Yaw Damper


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EMERGENCY BUS OFF ADS/AOA Knob........................................................ON Airspeed...................................................................250 KIAS

MAXIMUM Altitude .....................................................................25000 ft

MAXIMUM


- AFCS Control Unit - LDG Indication/Warning

- AHRS 1 (*) - Oxygen Transducer

- Audio Panel 1 (*) - Pax Mask Deploy (Auto)


- EFCU 1 - Pitch Trim (Back-Up) (*)

- Engines Fire Detection (*) - PRSOV 1 & 2

- Flight Director 1 - Red Beacon

- Fuel Booster Pumps - Stall Warning

- Fuel Shutoff Valves - Stick Pusher (*)

- Fuel Transfer Valve (*) - Transponder 1

- GIA 1 (*) - WOW (*)

- GPS 1/VOR 1/ILS 1 - Yaw Damper

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Engine Emergency and Abnormal Procedures


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ENGINE

TABLE OF CONTENTS

Block Page

WARNING

ENGINE 1 (2) OIL LOW PRESSURE................................ 4-10.......... 03

CAUTION

ENGINE 1 (2) CONTROL FAULT .....................................4-10.......... 03

ENGINE 1 (2) FAILURE ....................................................4-10.......... 03

ENGINE 1 (2) FUEL IMPENDING BYPASS ..................... 4-10.......... 04

ENGINE 1 (2) TLA FAIL .................................................... 4-10.......... 04

ENGINE 1 (2) TT0 HEATER FAIL..................................... 4-10.......... 04

ENGINE EXCEEDANCE (PRE-MOD. SB 500-31-0001)...................................... 4-10.......... 04

ENGINE NO DISPATCH (PRE-MOD. SB 500-31-0001)...................................... 4-10.......... 04

ENGINE NO TO DATA...................................................... 4-10.......... 04

ADVISORY

ENGINE 1 (2) CHIP DETECTED ......................................4-10.......... 04

ENGINE EXCEEDANCE (POST-MOD. SB 500-31-0001 OR WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED).......... 4-10.......... 04

ENGINE NO DISPATCH (POST-MOD. SB 500-31-0001 OR WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED).......... 4-10.......... 04


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Engine Emergency and Abnormal Procedures


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ENGINE 1 (2) OIL LOW PRESSURE If the affected oil pressure indication is abnormal:

ENGINE SHUTDOWN Procedure...................... ACCOMPLISH

ENGINE 1 (2) CONTROL FAULT LAND AS SOON AS POSSIBLE.

CAUTION: AVOID QUICK THRUST LEVER MOVEMENT AND HIGH ENGINE THRUST OPERATION.

If it is not possible to control engine: Associated Thrust Lever..................................... IDLE

If engine parameters are still unstable: ENGINE SHUTDOWN Procedure...................... ACCOMPLISH

ENGINE 1 (2) FAILURE LAND AS SOON AS POSSIBLE.

Associated Thrust Lever.......................................... IDLE

If the affected engine was not successfully restarted via auto relight: Start/Stop Knob .................................................. STOP

If not accomplishing the takeoff procedure: Remaining Engine ......................................... CON

If fuel leak is suspected: FUEL LEAKAGE Procedure.......................... ACCOMPLISH

If fuel leak is not suspected and a restart is considered: ENGINE INFLIGHT START Procedure......... ACCOMPLISH

If affected engine is not recovered and when appropriate: ONE ENGINE INOPERATIVE APPROACH

AND LANDING Procedure.................. ACCOMPLISH


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ENGINE 1 (2) FUEL IMPENDING BYPASS Report to the maintenance personnel.

CAUTION: IF BOTH E1 FUEL IMP BYP AND E2 FUEL IMP BYP MESSAGES ARE DISPLAYED, LAND AS SOON AS POSSIBLE.

ENGINE 1 (2) TLA FAIL

NOTE: The engine thrust may be set to idle automatically.



ENGINE 1 (2) TT0 HEATER FAIL Exit or avoid icing conditions.

ENGINE EXCEEDANCE On ground: Do not take off.

In flight: Report to the maintenance personnel after landing.

ENGINE NO DISPATCH On ground: Do not take off.

In flight: Report to the maintenance personnel after landing.

ENGINE NO TO DATA Enter the Engine Takeoff Data.

ENGINE 1 (2) CHIP DETECTED Report to the maintenance personnel.

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Fire Protection Emergency and Abnormal Procedures


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FIRE PROTECTION

TABLE OF CONTENTS

Block Page

WARNING

ENGINE 1 (2) FIRE ........................................................... 4-12.......... 03

CAUTION

ENGINE 1 (2) FIRE DETECTION FAILURE ..................... 4-12.......... 03

ENGINE FIRE EXTINGUISHER SYSTEM FAILURE....................................................................... 4-12.......... 03


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Emergency and Abnormal Procedures Fire Protection


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Fire Protection Emergency and Abnormal Procedures


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ENGINE 1 (2) FIRE φ Thrust Lever (affected engine) ............................. IDLE φ Start/Stop Knob (affected engine) ........................ STOP φ Fire Shutoff Button (affected engine) ................... PUSH IN


Wait 30 seconds and if fire persists: Fire Extinguishing Switch ................................... DISCH

Altitude..................................................................... 31000 ft MAXIMUM

BLEED Knob............................................................ OPPOSITE SIDE Thrust Lever (operative engine) .............................. AS REQUIRED

If airplane high vibration exists: Airspeed.............................................................. REDUCE

(130 KIAS MINIMUM)

Reduce airspeed as required to keep vibration within acceptable levels.

When appropriate: ONE ENGINE APPROACH AND

LANDING Procedure..................................... ACCOMPLISH

ENGINE 1 (2) FIRE DETECTION FAILURE If engine fire or overheat is suspected or if E1 (2) FIRE DET FAIL appears simultaneously with engine failure:

ENGINE FIRE Procedure................................... ACCOMPLISH

ENGINE FIRE EXTINGUISHER SYSTEM FAILURE LAND AS SOON AS PRACTICAL.


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Emergency and Abnormal Procedures Fire Protection


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Flight Controls Emergency and Abnormal Procedures


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FLIGHT CONTROLS

TABLE OF CONTENTS

Block Page

CAUTION

FLAPS FAILURE ............................................................... 4-14.......... 03

PITCH TRIM BACK-UP FAILURE.....................................4-14.......... 05

PITCH TRIM DISCONNECT (POST-MOD. SB 500-31-0001 OR WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED).......... 4-14.......... 06

PITCH TRIM NORMAL FAILURE .....................................4-14.......... 06

ADVISORY

PITCH TRIM DISCONNECT (PRE-MOD. SB 500-31-0001)...................................... 4-14.......... 06

PITCH TRIM SWITCH 1 (2) FAILURE .............................. 4-14.......... 06


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FLAPS FAILURE NOTE: Applicable to airplanes Post-Mod. SB 500-27-0003 or with an


Flaps Lever .............................................................. CYCLE Up to 3 cycles may be attempted.

If failure persists: Altitude................................................................ 15000 ft

MAXIMUM


If is not possible to avoid icing conditions: LAND AS SOON AS POSSIBLE.

For landing proceed: - Check the available airports within the current range and choose

the one that best matches the required runway length. Considerations for uphill slope and occurrence of headwind should be also made.

- Burn as much fuel as possible to reduce the landing weight. - Maintain bank angle below 20°. - For airplanes Pre-Mod. SB 500-27-0001, maintain the airspeed

according to the following:








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- For airplanes Post-Mod. SB 500-27-0001 or with an equivalent modification factory incorporated, maintain the airspeed according to the following:









CORRECTION FACTOR FLAPS POSITION NO ICING IN ICING/WITH ICE

0 1.90 2.00 1 1.70 1.70

2 and 3 1.75 2.00 FULL 1.75 1.95


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For airplanes Post-Mod. SB 500-27-0001 or with an equivalent modification factory incorporated:


0 1.40 1.70 1 1.20 1.60

2 and 3 1.10 2.00 FULL 1.00 1.95

PITCH TRIM BACK-UP FAILURE NOTE: Applicable to airplanes Post-Mod. SB 500-27-0003 or with an


PITCH BKP Switch .................................................. OFF Pitch Trim Switch ..................................................... USE AS

REQUIRED

NOTE: Message PTRIM DISCONNECT may be presented.

If associated with the PTRIM NML FAIL message: Landing configuration:

Flaps.............................................................. 3 Airspeed ........................................................ VREF FULL + 5 KIAS



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PITCH TRIM NORMAL FAILURE Control Wheel ..........................................................HOLD FIRMLY AP/YD/TRIM/PUSHER Disc Button.........................PRESS PITCH BKP Switch ..................................................BKP

Use the pitch trim backup mode as required.

NOTE: Autopilot will remain inoperative.

PITCH TRIM DISCONNECT AP/YD/TRIM/PUSHER Disc Button.........................PRESS Pitch Trim Backup....................................................SET AT NEUTRAL

POSITION Set the backup mode pointer at the middle mark of pitch trim scale.

Pitch Trim Normal ....................................................USE AS REQUIRED

NOTE: Autopilot will remain inoperative.

PITCH TRIM SWITCH 1 (2) FAILURE For dual pilot operation:

Remaining PITCH TRIM Switch .........................USE AS REQUIRED

For single pilot operation: Pitch Trim Backup Mode.....................................USE AS

REQUIRED

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Flight Instruments Emergency and Abnormal Procedures


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FLIGHT INSTRUMENTS, COMMUNICATION AND NAVIGATION

TABLE OF CONTENTS

Block Page

CAUTION

ADS 1 (2) FAILURE........................................................... 4-16.......... 03

ADS 1 (2) HEATER FAILURE...........................................4-16.......... 03

AHRS 1 (2) FAILURE ........................................................4-16.......... 03

AUDIO PANEL 1 (2) FAILURE..........................................4-16.......... 03

CONFIGURATION MODULE FAILURE............................4-16.......... 03

GIA 1 (2) FAILURE............................................................ 4-16.......... 04

GIA 1 (2) OVERHEAT ....................................................... 4-16.......... 04

MFD CONFIGURATION.................................................... 4-16.......... 04

MFD FAULT....................................................................... 4-16.......... 04

MFD OVERHEAT .............................................................. 4-16.......... 05

PFD 1 (2) CONFIGURATION............................................4-16.......... 07

PFD 1 (2) FAULT............................................................... 4-16.......... 07

PFD 1 OVERHEAT............................................................ 4-16.......... 07

PFD 2 OVERHEAT............................................................ 4-16.......... 08

STBY HEATER FAILURE ................................................. 4-16.......... 09


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Emergency and Abnormal Procedures Flight Instruments


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ADS 1 (2) FAILURE Confirm the affected ADS automatic reversion. If necessary, manually revert to a not affected ADS.

Refer to the RVSM Operation Supplement.

NOTE: If both ADS are lost, the airspeed and pressure altitude from IESI may be used.

ADS 1 (2) HEATER FAILURE Monitor the air data indications. If the information seems to be unreliable, revert to a not affected ADS.

If more than one ADS heater is failed, set the ADS/AOA Knob to ON position and pull the ADS/AOA HTR CTRL circuit breaker (A5 or A15 depending on airplane configuration).

If messages persist, leave and avoid icing conditions.

AHRS 1 (2) FAILURE Confirm the affected AHRS automatic reversion. If necessary, manually revert to the other AHRS.

NOTE: If both AHRS are lost, attitude from IESI may be used.

AUDIO PANEL 1 (2) FAILURE Use headset as required.

NOTE: For affected side, the following items are operative: - On-side VHF transmission/reception; - Cross-side VHF reception.

CONFIGURATION MODULE FAILURE Do not takeoff.


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GIA 1 (2) FAILURE Airspeed...................................................................250 KIAS

MAXIMUM Altitude .....................................................................25000 ft

MAXIMUM Icing Conditions .......................................................EXIT/AVOID

Relevant inoperative items:

GIA 1 failed: GIA 2 failed:

- Flight Director 1 - Flight Director 2

- GPS 1 - GPS 2

- VHF/NAV 1 - VHF/NAV 2

- Autopilot - Autopilot

- Pitch Trim Normal Mode - Pitch Trim Normal Mode

- Yaw Damper - Pressurization Auto Mode

- DME 1 - LFE Indication

- Yaw Damper

- DME 2

GIA 1 (2) OVERHEAT Avoid using radios from the affected side.

MFD CONFIGURATION Do not takeoff.

MFD FAULT DISPLAY BACKUP Button.......................................PRESS

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MFD OVERHEAT For dual pilot operation and if associated with smoke in the MFD:

Crew Oxygen Masks .......................................... DON, 100% Smoke Goggles (if available) ............................. DON Crew Communication ......................................... ESTABLISH MFD Circuit Breakers (A8 and A24 CB’s) .......... PULL

For single pilot operation and if associated with smoke in the MFD: Crew Oxygen Masks .......................................... DON, 100% Smoke Goggles (if available) ............................. DON MFD Circuit Breaker (A8 CB) ............................. PULL Bus Tie Knob ...................................................... 2 OPEN GEN 2 Switch ..................................................... OFF Icing Conditions .................................................. EXIT/AVOID Airspeed ............................................................. 250 KIAS

MAXIMUM Altitude................................................................ 25000 ft

MAXIMUM

During landing run: Emergency/Parking Brake ............................ APPLY






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- AHRS 2 (*) - GIA 2 (*)

- ADC 2 (*) - GPS 2/VOR 2/ILS 2










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PFD 1 (2) CONFIGURATION Do not take off.

PFD 1 (2) FAULT In case of a dual pilot operation:

- Crosscheck the affected PFD display information (Attitude, Airspeed, Altitude, FMA, FPA, Minimums, Baro Setting, NAVCOM Radio Frequencies, HDG and CRS) with the opposite side PFD display information.

- Disregard any non-reliable information from the affected PFD.

In case of a single pilot operation and PFD 1 Failure: DISPLAY BACKUP Button ................................. PRESS - Crosscheck the PFD 1 display information (Attitude, Airspeed,

Altitude, FMA, FPA, Minimums, Baro Setting, NAVCOM Radio Frequencies, HDG and CRS) with the reverted MFD display information.

- Disregard any non-reliable information of the PFD 1.

PFD 1 OVERHEAT If associated with smoke in the PFD 1:

Crew Oxygen Masks .......................................... DON, 100% Smoke Goggles (if available) ............................. DON Crew Communication ......................................... ESTABLISH PFD 1 Circuit Breaker (A7)................................. PULL DISPLAY BACKUP Button ................................. AS REQUIRED


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PFD 2 OVERHEAT For dual pilot operation and if associated with smoke in the PFD 2:

Crew Oxygen Masks...........................................DON, 100% Smoke Goggles (if available)..............................DON Crew Communication .........................................ESTABLISH PFD 2 Circuit Breaker (B24) ...............................PULL

NOTE: For airplanes Pre-Mod. SB 500-31-0001, autopilot will not engage after pulling the PFD 2 circuit breaker.

DISPLAY BACKUP Button .................................AS REQUIRED

For single pilot operation and if associated with smoke in the PFD 2: Crew Oxygen Masks...........................................DON, 100% Smoke Goggles (if available)..............................DON BUS TIE Knob.....................................................2 OPEN GEN 2 Switch......................................................OFF Icing Conditions ..................................................EXIT/AVOID Airspeed..............................................................250 KIAS

MAXIMUM Altitude ................................................................25000 ft

MAXIMUM

During landing run: Emergency/Parking Brake.............................APPLY





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- ADC 2 (*) - GIA 2 (*)

- AHRS 2 (*) - GPS 2/VOR 2/ILS 2










STBY HEATER FAILURE Monitor the air data indications. If the information seems to be unreliable, disregard IESI altitude and airspeed indication.

If more than one ADS heater is failed, set the ADS/AOA Knob to ON position and pull the ADS/AOA HTR CTRL circuit breaker (A5 or A15 depending on airplane configuration).

If messages persist, leave and avoid icing conditions.


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PHENOM 100


Fuel Emergency and Abnormal Procedures


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FUEL

TABLE OF CONTENTS

Block Page

CAUTION

FUEL 1 (2) LOW LEVEL.................................................... 4-18.......... 03

FUEL 1 (2) LOW PRESSURE ...........................................4-18.......... 03

FUEL 1 (2) SHUTOFF VALVE FAILURE .......................... 4-18.......... 03

FUEL IMBALANCE............................................................ 4-18.......... 04

FUEL OVERFILLING......................................................... 4-18.......... 04

FUEL TRANSFER VALVE FAILURE ................................4-18.......... 04


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Fuel Emergency and Abnormal Procedures


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FUEL 1 (2) LOW LEVEL Thrust Levers........................................................... REDUCE TO

LONG RANGE

Level the airplane and check both fuel quantities.

If fuel quantity is not sufficient: LAND AS SOON AS POSSIBLE.

CAUTION: AVOID EXCESSIVE NOSE UP AND DOWN ATTITUDES, UNCOORDINATED MANEUVERS AND NEGATIVE G’S.

If fuel leak is suspected: FUEL LEAK Procedure....................................... ACCOMPLISH

If fuel leak is not suspected: FUEL XFR Button............................................... AS REQUIRED

FUEL 1 (2) LOW PRESSURE Associated Fuel Pump Switch ................................. ON Associated Thrust Lever.......................................... AS REQUIRED Engine Parameters .................................................. MONITOR

If engine parameters are abnormal: Altitude................................................................ 25000 ft

MAXIMUM

FUEL 1 (2) SHUTOFF VALVE FAILURE If associated with engine fire:


Associated Fuel Pump Switch............................ OFF


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FUEL IMBALANCE If fuel leak is suspected, accomplish the FUEL LEAK Procedure.

If fuel leak is not suspected: Attitude................................................................WINGS LEVEL FUEL XFR Button ...............................................PUSH IN Fuel Quantity.......................................................MONITOR

After fuel balancing: FUEL XFR Button ..........................................PUSH OUT

FUEL OVERFILLING FUEL XFR Button ....................................................PUSH OUT

FUEL TRANSFER VALVE FAILURE If failure occurs when the XFR valve is commanded open to correct fuel imbalance:

Fuel Quantity.......................................................MONITOR

If fuel imbalance is not being corrected: FUEL XFR Button ..........................................PUSH OUT Thrust Levers.................................................ADJUST

Use asymmetric thrust to improve or maintain fuel balance.

If asymmetric thrust can not be used: LAND AS SOON AS PRACTICAL.

If failure occurs when the XFR valve is commanded closed after fuel balancing:

Fuel Quantity.......................................................MONITOR

Avoid uncoordinated maneuvers.

If fuel imbalance occurs: Attitude...........................................................WINGS LEVEL

LAND AS SOON AS PRACTICAL.

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Hydraulic Emergency and Abnormal Procedures


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HYDRAULIC

TABLE OF CONTENTS

Block Page

CAUTION

HYDRAULIC HIGH TEMPERATURE ...............................4-20.......... 03

HYDRAULIC LOW PRESSURE........................................ 4-20.......... 04


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Emergency and Abnormal Procedures Hydraulic


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Hydraulic Emergency and Abnormal Procedures


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HYDRAULIC HIGH TEMPERATURE HYD PUMP Knob .................................................... AUTO

NOTE: The HYD HI TEMP message will be displayed until the oil temperature does not decrease.

BUS TIE Knob ......................................................... 2 OPEN BATT 2 Switch ......................................................... OFF

Before landing: BUS TIE Knob .................................................... AUTO BATT 2 Switch.................................................... ON HYD PUMP Selector .......................................... CHECK IN AUTO


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HYDRAULIC LOW PRESSURE

NOTE: LG LEVER DISAG message may be presented.

HYD PUMP Selector................................................ON

Wait 10 seconds.

If the HYD LO PRES message persists: HYD PUMP Selector...........................................OFF

If landing gear system is extended: Airspeed.........................................................180 KIAS

MAXIMUM

Consider to LAND AS SOON AS PRACTICAL.

If landing gear is up, accomplish the ABNORMAL LANDING GEAR EXTENSION Procedure before landing.

Landing configuration: Flaps ..............................................................FULL Airspeed.........................................................VREF FULL

Before landing: HYD PUMP Selector......................................ON

During landing run, if required: Emergency/Parking Brake.............................APPLY




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PHENOM 100


Ice and Rain Protection Emergency and Abnormal Procedures


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ICE AND RAIN PROTECTION

TABLE OF CONTENTS

Block Page

CAUTION

ANTI-ICE ENGINE 1 (2) FAILURE.................................... 4-22.......... 03

DE-ICE WING/STABILIZER FAILURE.............................. 4-22.......... 03

WINDSHIELD 1 (2) HEATER FAILURE............................ 4-22.......... 03


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Emergency and Abnormal Procedures Ice and Rain Protection


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Ice and Rain Protection Emergency and Abnormal Procedures


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ANTI-ICE ENGINE 1 (2) FAILURE Affected Engine Ice Protection Switch .................... OFF, THEN ON

If the A-I E1 (2) FAIL message persists, exit and avoid icing conditions.

If high engine vibration develops: ENGINE ABNORMAL VIBRATION

Procedure...................................................... ACCOMPLISH

DE-ICE WING/STABILIZER FAILURE Airspeed................................................................... 165 KIAS

MINIMUM Wing/Stabilizer Ice Protection Switch...................... OFF, THEN ON

If D-I WINGSTB FAIL message persists after 1 minute, exit and avoid icing conditions.

NOTE: Keep the WINGSTAB Switch in ON until the airplane is clear of ice.

During landing: Flaps................................................................... FULL Airspeed ............................................................. VREF FULL + 25 KIAS

MINIMUM


WINDSHIELD 1 (2) HEATER FAILURE Affected Windshield Heating Switch........................ OFF, THEN ON

If the WSHLD 1 (2) HTR FAIL message persists, turn the affected windshield-heating off.


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Emergency and Abnormal Procedures Ice and Rain Protection


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PHENOM 100


Landing Gear and Brakes Emergency and Abnormal Procedures


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LANDING GEAR AND BRAKES

TABLE OF CONTENTS

Block Page

WARNING

LANDING GEAR LEVER DISAGREE............................... 4-24.......... 03

CAUTION

ANTISKID FAILURE.......................................................... 4-24.......... 03

BRAKE FAILURE .............................................................. 4-24.......... 04

EMERGENCY BRAKE LOW PRESSURE ........................4-24.......... 04

LANDING GEAR WEIGHT-ON-WHEEL SYSTEM FAILURE....................................................... 4-24.......... 04

PARKING BRAKE NOT RELEASED ................................ 4-24.......... 04


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Emergency and Abnormal Procedures Landing Gear and Brakes


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Landing Gear and Brakes Emergency and Abnormal Procedures


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LANDING GEAR LEVER DISAGREE Airspeed................................................................... 180 KIAS

MAXIMUM Hydraulic Pressure .................................................. CHECK

If hydraulic pressure is below 2300 psi: HYDRAULIC LOW PRESSURE Procedure....... ACCOMPLISH

LDG GEAR Lever .................................................... CYCLE

If the LG LEVER DISAG message persists and it was displayed after a landing gear extension:

ABNORMAL LANDING GEAR EXTENSION Procedure ................................ ACCOMPLISH

If the LG LEVER DISAG message persists and it was displayed after a landing gear retraction:

LDG GEAR Lever ............................................... DN Airspeed ............................................................. 180 KIAS

MAXIMUM Icing Conditions .................................................. EXIT/AVOID

Consider to LAND SOON AS PRACTICAL.

ANTISKID FAILURE Apply moderate brake according to the runway condition. Continuous brake application may be applied below 10 KIAS.

When committed to land: Flaps................................................................... FULL Airspeed ............................................................. VREF FULL



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Emergency and Abnormal Procedures Landing Gear and Brakes


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BRAKE FAILURE Landing configuration:

Flaps ...................................................................FULL Airspeed..............................................................VREF FULL

During landing run: Emergency/Parking Brake.............................APPLY




EMERGENCY BRAKE LOW PRESSURE If normal brake is inoperative and it is necessary to use the emergency/parking brake, apply it progressively monitoring the Emergency/Parking brake light.

When parking the airplane, use the wheel blocks.

LANDING GEAR WEIGHT-ON-WHEEL SYSTEM FAILURE If climb performance is required to clear obstacles during takeoff and go-around, simultaneously proceed:

DN LCK REL Button ...........................................PRESS LDG GEAR Lever ...............................................UP

PARKING BRAKE NOT RELEASED Before landing, release the emergency/parking brake.

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Oxygen Emergency and Abnormal Procedures


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OXYGEN

TABLE OF CONTENTS

Block Page

CAUTION

OXYGEN LOW PRESSURE ............................................. 4-26.......... 03

PASSENGER OXYGEN NO PRESSURE ........................4-26.......... 03


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Oxygen Emergency and Abnormal Procedures


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OXYGEN LOW PRESSURE Limit altitude to 14000 ft or MEA, whichever is higher.

PASSENGER OXYGEN NO PRESSURE Set the OXYGEN SUPPLY CONTROL Knob to PAX OVRD.


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Warning Emergency and Abnormal Procedures


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WARNING

TABLE OF CONTENTS

Block Page

WARNING

NO TAKEOFF CONFIGURATION .................................... 4-28.......... 03

CAUTION

AURAL WARNING FAILURE ............................................ 4-28.......... 03

PUSHER FAILURE............................................................ 4-28.......... 03

PUSHER OFF.................................................................... 4-28.......... 03

STALL WARNING AND PROTECTION SYSTEM FAILURE....................................................... 4-28.......... 03

STALL WARNING AND PROTECTION SYSTEM FAULT .......................................................... 4-28.......... 04

STALL WARNING AND PROTECTION SYSTEM HEATER 1 (2) FAULT ..................................4-28.......... 04

STALL WARNING AND PROTECTION SYSTEM UNTESTED .................................................. 4-28.......... 04


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Emergency and Abnormal Procedures Warning


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NO TAKEOFF CONFIGURATION Configure the airplane for takeoff.

AURAL WARNING FAILURE Monitor visual indications.

NOTE: Aural warnings, including TAWS, TCAS, TIS and Stall Callouts are lost.

PUSHER FAILURE Avoid side slipping the airplane and high angle of attack.

PUSHER OFF If the pusher was inadvertently cut off:

PUSHER CUTOUT Button ................................. PUSH IN

If the pusher was intentionally cut off: Avoid side slipping the airplane and high angle of attack.

STALL WARNING AND PROTECTION SYSTEM FAILURE Avoid side slipping the airplane and high angle of attack.


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STALL WARNING AND PROTECTION SYSTEM FAULT For airplanes Pre-Mod. SB 500-27-0001:

Avoid side slipping the airplane and high angle of attack.

For landing configuration: Flaps ..............................................................FULL Airspeed.........................................................VREF FULL + 25 KIAS



FLAPS FAILURE Procedure...............................ACCOMPLISH

STALL WARNING AND PROTECTION SYSTEM HEATER 1 (2) FAULT Avoid side slipping the airplane and high angle of attack.

STALL WARNING AND PROTECTION SYSTEM UNTESTED Pre-Flight SWPS System Test.................................ACCOMPLISH

If the SWPS UNTESTED message persists: Do not takeoff.

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SMOKE PROCEDURES

TABLE OF CONTENTS

Block Page

WARNING

BAGGAGE FORWARD (AFT) SMOKE............................. 4-30.......... 03

SMOKE/FIRE/FUME ......................................................... 4-30.......... 03

SMOKE EVACUATION ..................................................... 4-30.......... 05


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BAGGAGE FORWARD (AFT) SMOKE LAND AS SOON AS POSSIBLE.

SMOKE/FIRE/FUME φ Crew Oxygen Masks ............................................ DON, EMER THEN

100% EMER may be selected during 2 minutes maximum then set to 100%.

φ Crew Oxygen Masks Auto Dilution Valve............. CLOSED φ Smoke Goggles (if available) ............................... DON φ Crew Communication ........................................... ESTABLISH


If smoke origin is identified, remove the affected source and if applicable, accomplish the SMOKE EVACUATION Procedure.

NOTE: Discharge of the entire contents of the fire extinguisher bottle into the occupied cabin area may exceed safe exposure limits. Use only the amount necessary to extinguish the fire.

If smoke origin is not identified: SIGNS/OUTLET Switch...................................... PED-BELTS/OFF Altitude................................................................ 10000 ft OR MEA,

WHICHEVER IS HIGHER

Thrust Levers...................................................... IDLE Airspeed ............................................................. 250 KIAS/MMO

MAXIMUM LDG GEAR Lever ............................................... DN Airspeed ............................................................. 275 KIAS/MMO

MAXIMUM Transponder ....................................................... 7700 ATC..................................................................... NOTIFY Pressurization DUMP Button.............................. PRESS

NOTE: Smoke will initially decrease due to pressurization dumping, even if the correct source has not been removed.



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(Continued from the previous page) If smoke persists:

GEN 2 Switch ................................................OFF BUS TIE Knob ...............................................2 OPEN

Wait 1 minute and if smoke persists: GEN 2 Switch ................................................AUTO GEN 1 Switch ................................................OFF BUS TIE Knob ...............................................1 OPEN

Wait 1 minute and if smoke persists: GEN 1 Switch ................................................AUTO BUS TIE Knob ...............................................AUTO BATT 1 & 2 Switches.....................................OFF

Wait 1 minute and if smoke persists: BUS TIE Knob ...............................................AUTO BATT 1 & 2 Switches.....................................ON Non-Essential Equipments ............................OFF Passenger Oxygen Supply ............................AS REQUIRED

NOTE: Supply the passenger oxygen masks as appropriate if fire source is away from the oxygen system.

Depending on which bus is off, refer to DC BUS 1 OFF, DC BUS 2 OFF or EMERGENCY BUS OFF Procedure for additional guidance.

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SMOKE EVACUATION φ Crew Oxygen Masks ............................................ DON, EMER THEN

100% EMER may be selected during 2 minutes maximum then set to 100%.

φ Crew Oxygen Masks Auto Dilution Valve............. CLOSED φ Smoke Goggles (if available) ............................... DON φ Crew Communication ........................................... ESTABLISH φ Pressurization DUMP Button ............................... PUSH IN φ BLEED Knob ........................................................ OFF VENT


SIGNS/OUTLET Switch........................................... PED-BELTS/OFF Altitude..................................................................... 10000 ft OR MEA,

WHICHEVER IS HIGHER

Thrust Levers........................................................... IDLE Airspeed................................................................... 250 KIAS/MMO

MAXIMUM LDG GEAR Lever .................................................... DN Airspeed................................................................... 275 KIAS/MMO

MAXIMUM Transponder ............................................................ 7700 ATC.......................................................................... NOTIFY


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SECTION 5

PERFORMANCE

TABLE OF CONTENTS

Block Page

Introduction ........................................................................ 5-00.......... 02

Performance Configuration................................................ 5-01.......... 01

Definitions .......................................................................... 5-01.......... 02

Noise Levels ...................................................................... 5-01.......... 05

Software Presentation ....................................................... 5-02.......... 01

Position Error Corrections .................................................5-05.......... 01

Stall Speed ........................................................................ 5-08.......... 01

Thrust Setting Tables ........................................................ 5-10.......... 01

Takeoff Data ...................................................................... 5-15.......... 01

Driftdown Tables (Gross Gradient).................................... 5-18.......... 01

Enroute Gradient ............................................................... 5-18.......... 04

Approach Data................................................................... 5-20.......... 01

Landing Data ..................................................................... 5-25.......... 01


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INTRODUCTION The performance information given in this Section is applicable to the PHENOM 100 airplane.

The performance data are based on the following conditions:

− Pertinent power less installation, air bleed, and accessory losses.

− Full temperature accountability within the operational limits for which the airplane is certified.

− For the performance tables contained in this Section, the ANTI-ICE ON condition means the ENG 1, ENG 2 and WINGSTAB switches at ON position.

The performance information is not valid if:

− The airplane’s gross weight exceeds the appropriate maximum allowable limits.

− Any of the limitations in Section 2 is not observed. − A reading from any performance analysis is obtained by

extrapolation (i.e. using values of parameters outside the range given on the graph).

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PERFORMANCE CONFIGURATION


The configurations applicable to each performance phase are shown below.

OPERATINGENGINES TLA FLAPS GEAR AIRSPEED

TAKEOFF RUN

2 until VEF, 1 after VEF TO/GA 1 or 2 DOWN 0 TO VLOF

1ST SEGMENT 1 TO/GA 1 or 2 DOWN TOUP VLOF TO V2

2ND SEGMENT 1 TO/GA 1 or 2 UP V2

3RD SEGMENT 1 TO/GA TAKEOFF FLAPS TO 0 UP

V2 TO FINALSEGMENT

SPEED

FINAL SEGMENT 1 MAX CON 0 UP

FINAL SEGMENT

SPEED

ENROUTE 1 MAX CON 0 UP ENROUTE

CLIMB SPEED

APPROACH CLIMB 1 TO/GA 1 or 2 UP

APPROACHCLIMB SPEED

LANDING CLIMB 2 TO/GA 3 or FULL DOWN

LANDING CLIMB SPEED

LANDING 2 IDLE 3 or FULL DOWN VREF


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DEFINITIONS

OUTSIDE AIR TEMPERATURE – OAT OR SAT Free static (ambient) temperature.

TOTAL AIR TEMPERATURE – TAT Total temperature measured and corrected by the ADS system with airplane in motion.

INDICATED AIRSPEED – KIAS It is the reading on the airspeed indicator (knots), as installed in the airplane. Zero instrument error is assumed by the OPERA.

CALIBRATED AIRSPEED – KCAS It is the indicated airspeed corrected for the anemometric system position error.

TRUE AIRSPEED – TAS It is the airplane speed in relation to the air and equal to the equivalent air speed corrected for air density. At sea level, ISA, the true airspeed is equal to the equivalent airspeed.

GROUND SPEED – GS It is the airplane speed in relation to the ground. It is the true airspeed corrected for the wind speed.

TAKEOF DECISION SPEED – V1 It is the maximum speed in the takeoff at which the pilot must take the first action (e.g., apply brakes, reduce thrust) to stop the airplane within the accelerate-stop distance. V1 also means the minimum speed in the takeoff, following a failure of the critical engine at VEF, at which the pilot can continue the takeoff and achieve the required height above the takeoff surface within the takeoff distance.

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STALL SPEED – VS It is the minimum steady flight speed at which the airplane is controllable.

ROTATION SPEED – VR It is the speed at which the pilot starts to rotate the airplane during the takeoff ground run.

LIFT-OFF SPEED – VLOF It is the speed at which the airplane first becomes airborne during takeoff.

FIRST SEGMENT Starts at 35 ft above the takeoff surface, at the end of the one-engine-inoperative takeoff distance, and extends to the point where the landing gear is fully retracted using a constant V2 speed and takeoff flaps.

TAKEOFF SAFETY SPEED – V2 It is the target speed to be attained at 35 ft height above runway surface, the critical engine having failed at VEF.

SECOND SEGMENT Extends from the end of the first segment up to the level-off height, with takeoff flaps, gear up, and constant V2 speed.

LEVEL-OFF HEIGHT It is the height or altitude where the airplane is leveled for acceleration and flap retraction.

MINIMUM LEVEL-OFF HEIGHT It is defined by regulations as 400 ft AGL. The user can define higher levels.


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MAXIMUM LEVEL-OFF HEIGHT It is the height where the takeoff thrust time limit occurs at the end of the final segment.

EXTENDED SECOND SEGMENT It is an extension of the second takeoff climb segment, above the maximum level off height, to improve obstacle clearance performance.

THIRD (OR ACCELERATION) SEGMENT Extends from the end of the second segment, at the level-off height, up to a point where the airplane is accelerated to final segment speed (VFS) while retracting flaps.

FINAL SEGMENT SPEED – VFS It is the speed to be achieved at the end of the acceleration segment and start of the final segment of the takeoff flight path, with one engine inoperative, landing gear retracted, and flaps retracted.

FINAL SEGMENT Extends from the end of the third segment to a gross height at least at 1500 ft AGL, with flaps up and at final segment speed (VFS).

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NOISE LEVELS The following Effective Perceived Noise Levels (EPNL’s) comply with the Stage 4 noise limits set forth in 14CFR 36, equivalent to ICAO Annex 16, Volume 1, Appendix 2, Amendment 8, effective July 11, 2005.

NOISE LEVEL IN EPNdb

CONDITION Noise Level

Flyover Lateral Approach Engine Model

MaximumAllowable 89.0 94.0 98.0

PW617F-E Actual 70.4 81.4 86.1

The noise levels for EMB-500 equipped with two Pratt & Whitney PW617F-E engines, were established as follows.

- Flyover: at maximum takeoff weight, flap setting 1, using thrust power cutback and V2 + 20 KIAS;

- Lateral: at maximum takeoff weight, flap setting 1 and with all engines at maximum takeoff power setting;

- Approach: at maximum landing weight, 3° glide slope, VREF + 10 KIAS and flap setting FULL.

No determination has been made by the Airworthiness Authority that the noise levels in this manual are or should be acceptable or unacceptable for operation at, into, or out of any airport.


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SOFTWARE PRESENTATION OPERA is the Optimized Performance Analyzer software certified to provide takeoff, landing and enroute approved performance data. The OPERA replaces or supplements portions of the paper AFM, and is an approved source for that AFM information. As paper AFM performance information is generally based on a simplified analysis, it may show performance data more conservative than OPERA. Any modification to the approved OPERA software application, or subsequent alteration to the generated output, will cancel the airworthiness approval of the information, unless this change was approved by the appropriate airworthiness authority. This statement applies regardless of any approval notation printed on a generated output. Performance wise, OPERA offers applicable aerodynamic and systems calculation options, to be selected according to the airplane specific configuration. The OPERA installer incorporates the media identification, which will be displayed on the screen after installation and must be crosschecked with the AFM OPERA configuration. The OPERA version is composed of two numbers. The second number identifies different databases. If there is an update only to the databases, only the second number moves on. When the OPERA is revised with changes on the Main Computer Interface or Calculation Modules the version moves on (e.g.: version 4.1 evolves to version 5.1). Any time OPERA is revised, a new installer media is issued and the AFM is revised accordingly. After approval, both are provided to operators. Previous installer remains valid only if listed at Valid Versions table. A dedicated User's Guide is also issued, as a separate document, providing detailed information on software usage aspects. In addition, the OPERA interface provides a Help feature with useful on line information. If not mentioned, the latest Software Configuration Media incorporates all capabilities of the previous media. The OPERA has been tested only on WINDOWS® XP and WINDOWS® 7 Operational Systems.


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SOFTWARE CONFIGURATION

OP500FA617FE version 7.2

The software OP500FA617FE version 7.2 allows performance calculations for airplanes with the following configuration:

- PHENOM 100.

- PW617F-E engines.

- FADEC Software 5.3 and on.

- Placard "Standard Takeoff Thrust OPERA Type B".

WARNING: • OPERA VERSION MUST BE IN ACCORDANCE WITH AIRPLANE CONFIGURATION.

• REFER TO SUPPLEMENT 2 OR 6 FOR OTHER AIRPLANES CONFIGURATIONS ACCORDING TO VALID VERSIONS TABLE.

• VERSIONS NOT PRESENTED IN AFM ARE AUTOMATICALLY CANCELLED AND MUST NOT BE USED.

• FOR AIRPLANES PRE-MOD. SB 500-27-0001, OPERA LANDING PERFORMANCE FOR NO ICE CONDITIONS (WINGSTAB OFF) MUST NOT BE USED. REFER TO AD 2009-05-06.

CAUTION: AFTER USING THE AIRPORT ANALYSIS OPTION, CHECK THE MINIMUM REQUIRED RUNWAY LENGTH FOR TAKEOFF BY INPUTING THE ACTUAL TAKEOFF WEIGHT IN THE GIVEN WEIGHT OPTION.

NOTE: - OPERA provides guidance information when operating from contaminated runways.

- When operating from wet runways apply correction factors according to local regulations or guidance information suggested by the Embraer.

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VALID VERSIONS

The table below presents valid OPERA versions.

AIRPLANE SERIAL

NUMBER 500:

AIRPLANE CONFIGURATION AFM LOCATION

VALID OPERA

VERSIONS

Pre-Mod. SB 500-27-0003. Supplement 2 7.0

00005 thru 00118; 00121;

00123 thru 00131; 00133; 00134; 00136;

00137; 00139 thru

00144; 00148; 00149;

00152 thru 00154

Post-Mod. SB 500-27-0003.

00120; 00122; 00132; 00135;

00138; 00145 thru

00147; 00150; 00151;

00155 thru 00216

ALL

Enhanced Takeoff Thrust OPERA Type A

cockpit placard installed.

Supplement 6 7.1

00218 and on

Standard Takeoff Thrust OPERA Type B

cockpit placard installed. Section 5-02 7.2


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POSITION ERROR CORRECTIONS The corrections to be applied to indicated airspeed or altitude in order to eliminate the effect of location of the static port on instrument readings are shown in the Airspeed Position Error Correction charts and in the Altitude Position Error Correction charts. No position error correction is required for ADS 1 and ADS 2, as their indication is already corrected. The position correction charts are only applicable for ADS Stand-by for flaps 0 (zero) according to the following conditions:

- Airspeed Position Error Correction for landing gear down and up.

- Altitude Position Error Correction for landing gear down and up.

AIRSPEED POSITION ERROR CORRECTION CHART

USE

Enter the chart with indicated airspeed, considering the appropriate configuration, to read airspeed correction. The calibrated airspeed will be the sum of the indicated airspeed and airspeed correction.

EXAMPLE

Given: ADS Stand-by Indicated Airspeed.............................................. 270 KIAS Landing Gear...................................................... UP Flaps................................................................... ZERO Altitude................................................................ SEA LEVEL

Determine:

Airspeed Correction............................................ -2.0 Calibrated Airspeed............................................ 268 KCAS


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AIRSPEED POSITION ERROR CORRECTIONADS STAND-BY

LANDING GEAR DOWN - FLAPS ZERO

-5

-4

-3

-2

-1

0

1

80 100 120 140 160 180 200 220 240 260 280 300 320

INDICATED AIRSPEED - kt

CO

RR

ECTI

ON

- kt

ALL WEIGHTS

ALL ALTITUDES

500A

NAC

07 -2

5SEP

2008

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AIRSPEED POSITION ERROR CORRECTIONADS STAND-BY

LANDING GEAR UP - FLAPS ZERO

-5

-4

-3

-2

-1

0

1

2

3

4

5

80 100 120 140 160 180 200 220 240 260 280 300 320


CO

RR

ECTI

ON

- kt

ALL WEIGHTS

40000 ft

30000 ft

10000 ft

20000 ft

SEA LEVEL

500A

NAC

08-2

5SEP

2008


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ALTITUDE POSITION ERROR CORRECTION CHARTS

USE

Enter the appropriate chart with indicated airspeed, the indicated pressure altitude considering the appropriate airplane configuration to read the altimetric correction. The true pressure altitude will be the indicated pressure altitude plus the altimetric correction.

EXAMPLE

Given: ADS Stand-by Indicated Airspeed ..............................................190 KIAS Landing Gear ......................................................UP Flaps ...................................................................ZERO Altitude ................................................................30000 ft

Determine:

Altimetric Correction ...........................................20 ft True Pressure Altitude ........................................30020 ft

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ALTITUDE POSITION ERROR CORRECTIONADS STAND-BY

LANDING GEAR DOWN - FLAPS ZERO

-100

-90

-80

-70

-60

-50

-40

-30

-20

-10

0

10

20

30

40

50

80 100 120 140 160 180 200 220 240 260 280 300 320


CO

RR

ECTI

ON

- ft

ALL ALTITUDES

ALL WEIGHTS

500A

NAC

09 -2

5SEP

2008


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ALTITUDE POSITION ERROR CORRECTIONADS STAND-BY

LANDING GEAR UP - FLAPS ZERO

-100

-80

-60

-40

-20

0

20

40

60

80

100

120

140

80 100 120 140 160 180 200 220 240 260 280 300 320


CO

RR

ECTI

ON

- ft

ALL WEIGHTS

40000 ft

30000 ft

20000 ft

10000 ftAND

BELOW

500A

NAC

10 -2

5SEP

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STALL SPEED


This table presents the stall speed value according to the airplane bank angle for the MTOW (10472 lb) with landing gear and flaps up.

BANK

ANGLE 0° 15° 30° 45° 60°

STALL SPEED (KIAS)

100 102 108 119 141

This table presents the stall speed values according to the airplane bank angle for the MLW (9766 lb) with landing gear down and landing flaps 3 or FULL.

STALL SPEEDS (KIAS)

BANK ANGLE 0° 15° 30° 45° 60°

FLAPS 3 81 82 87 96 115

FLAPS FULL 77 79 83 92 109


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THRUST SETTING TABLES Thrust setting table is presented for various pressure altitudes and static air temperatures, with engine bleed open, and anti-ice on or off.

The following tables present Takeoff N1 setting for TO/GA mode on PW617F-E engines.


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N1 FOR T/O MODE

ANTI-ICE OFF

AIRSPEED: 0 KIAS

PW617F-E ENGINES

Static Air Temperature (°C) Pressure Altitude

(ft) -40 -35 -30 -25 -20 -15 -10 -5 0 -1000 78.3 79.1 80.0 80.8 81.6 82.4 83.2 84.0 84.8

0 79.5 80.3 81.2 82.0 82.9 83.7 84.5 85.4 86.2 1000 79.6 80.5 81.3 82.2 83.0 83.8 84.7 85.5 86.3 2000 79.7 80.6 81.4 82.3 83.1 84.0 84.8 85.6 86.4 3000 79.7 80.6 81.4 82.2 83.1 83.9 84.8 85.6 86.4 4000 79.9 80.7 81.6 82.4 83.3 84.1 85.0 85.8 86.6 5000 79.9 80.7 81.6 82.4 83.3 84.1 85.0 85.8 86.7 6000 80.0 80.8 81.7 82.5 83.4 84.2 85.1 85.9 86.8 7000 80.1 81.0 81.8 82.7 83.5 84.4 85.2 86.1 86.9 8000 80.3 81.2 82.0 82.9 83.7 84.6 85.4 86.3 87.1 9000 80.4 81.3 82.1 83.0 83.8 84.7 85.5 86.4 87.2

10000 80.6 81.5 82.3 83.2 84.0 84.9 85.7 86.6 87.4


(ft) 5 10 15 20 25 30 35 40 45 -1000 85.6 86.3 87.1 87.8 88.6 88.7 87.9 87.0 86.0

0 86.9 87.7 88.5 89.2 89.8 89.0 88.0 87.0 86.0 1000 87.1 87.8 88.6 89.4 89.8 88.8 87.8 86.8 85.8 2000 87.2 88.0 88.8 89.5 89.6 88.7 87.7 86.6 85.6 3000 87.3 88.0 88.8 89.6 89.4 88.4 87.3 86.3 - 4000 87.4 88.2 89.0 89.6 89.2 88.2 87.1 86.2 - 5000 87.5 88.3 89.1 89.7 88.9 87.9 86.8 85.8 - 6000 87.6 88.4 89.2 89.6 88.7 87.6 86.6 - - 7000 87.8 88.5 89.3 89.4 88.5 87.4 86.4 - - 8000 87.9 88.7 89.5 89.4 88.3 87.2 - - - 9000 88.1 88.9 89.7 89.2 88.1 86.9 - - -

10000 88.3 89.1 89.8 89.0 87.8 86.6 - - -


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N1 FOR T/O MODE

ANTI-ICE ON

AIRSPEED: 0 KIAS

PW617F-E ENGINES


(ft) -40 -35 -30 -25 -20 -15 -1000 78.3 79.1 80.0 80.8 81.6 82.4

0 79.5 80.4 81.2 82.1 82.9 83.7 1000 79.6 80.5 81.3 82.2 83.0 83.8 2000 79.7 80.6 81.4 82.2 83.1 83.9 3000 79.7 80.6 81.4 82.3 83.1 84.0 4000 79.9 80.7 81.6 82.4 83.2 84.1 5000 79.9 80.7 81.6 82.4 83.3 84.1 6000 80.0 80.8 81.7 82.5 83.4 84.2 7000 80.1 81.0 81.8 82.7 83.5 84.4 8000 80.3 81.2 82.0 82.9 83.7 84.6 9000 80.5 81.3 82.2 83.0 83.9 84.7

10000 80.6 81.5 82.3 83.2 84.0 84.9


(ft) -10 -5 0 5 10 -1000 83.2 84.0 84.8 85.6 86.3

0 84.6 85.4 86.2 86.9 87.7 1000 84.7 85.5 86.3 87.1 87.9 2000 84.8 85.6 86.4 87.2 88.0 3000 84.8 85.6 86.5 87.3 88.0 4000 84.9 85.8 86.6 87.4 88.2 5000 85.0 85.8 86.7 87.5 88.3 6000 85.1 85.9 86.8 87.6 88.4 7000 85.2 86.1 86.9 87.8 88.5 8000 85.4 86.3 87.1 87.9 88.7 9000 85.6 86.4 87.3 88.1 88.9

10000 85.7 86.6 87.4 88.3 89.1

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TAKEOFF DATA

TAKEOFF TECHNIQUE The takeoff performance data in this manual is based on the following conditions:

- Thrust lever set to TO/GA position with the airplane stopped and brakes applied;

- Brakes released after N1 stabilized; - When VR is attained the airplane is rotated to appropriate pitch

angle according to flaps selection until 35 ft or until reaching V2;

- Pitch angle adjusted as required to maintain V2; - Landing gear retracted when a positive rate of climb is

established.

SIMPLIFIED TAKEOFF ANALYSIS TABLES Simplified Takeoff Analysis tables are presented for a set of pressure altitudes, temperatures and minimum required runway lengths for the conditions below:

• Takeoff flaps 1 or 2; • Zero slope;

• Ice Protection OFF or ON (WINGSTAB+ENG 1/2); • Zero wind;

• ATR OFF; • Minimum level-off height (400 ft);

• Dry runway; • Balanced V1;

• No clearway; • No obstacles *.

• No stopway; * analysis assumption

NOTE: - ATR OFF does not ensure a conservative performance when compared to ATR ON due to VMCG characteristics.

- Always check the climb weight limitation presented in the tables.

- Refer to the OPERA software configuration to check if any special setting is required in addition to the choices above.


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EXAMPLE

Given: Airplane Takeoff Weight .....................................9800 lb Airport Pressure Altitude.....................................2000 ft Outside Air Temperature ....................................20°C Ice Protection ......................................................OFF Flaps ...................................................................1

Determine:

Minimum Required Runway Length....................4075 ft V1 ........................................................................104 KIAS VR ........................................................................106 KIAS V2 ........................................................................109 KIAS VFS.......................................................................126 KIAS Climb Limited Weight..........................................10470 lb

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SIMPLIFIED TAKEOFF ANALYSIS FLAPS 1 – DRY RUNWAY

ICE PROTECTION (WINGSTAB+ENG) OFF – ATR OFF PW617F-E ENGINES

Airport Pressure Altitude: -1000 ft

TAKEOFF WEIGHT (lb) MINIMUM REQUIRED RUNWAY LENGTH (ft) – LIMITATION CODE

V1/VR/V2 (KIAS) TEMP (°C)

8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2089 2170 2387 2607 2831 3059 3217 10470 90/94/100 92/97/102 96/100/104 100/103/107 103/105/109 107/108/111 109/109/112

-35 2126 2206 2428 2651 2879 3112 3273 10470 90/94/100 92/97/102 96/100/104 100/103/107 103/105/109 106/108/111 108/109/112

-30 2163 2243 2468 2695 2927 3164 3328 10470 90/94/100 92/97/102 96/100/104 100/103/107 103/105/109 106/108/111 108/109/112

-25 2200 2279 2508 2739 2975 3217 3383 10470 90/94/100 91/97/102 96/100/104 100/103/107 103/105/109 106/108/111 108/109/112

-20 2237 2316 2548 2784 3023 3269 3438 10470 90/94/100 91/97/102 96/100/104 99/103/107 103/105/109 106/108/111 108/109/112

-15 2273 2352 2588 2827 3071 3321 3493 10470 90/94/100 91/97/102 96/100/104 99/103/107 103/105/109 106/108/111 108/109/112

-10 2310 2388 2629 2872 3120 3374 3549 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

-5 2347 2425 2669 2917 3169 3427 3606 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

0 2384 2461 2710 2962 3219 3481 3663 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

5 2421 2498 2750 3006 3268 3535 3720 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

10 2456 2536 2793 3053 3318 3591 3778 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

15 2489 2580 2840 3104 3374 3650 3840 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

20 2523 2624 2889 3157 3432 3713 3906 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

25 2556 2669 2938 3211 3490 3775 3972 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

30 2555 2805 3082 3365 3654 3951 4156 10470 88/94/100 92/97/102 96/100/104 100/103/107 103/106/109 107/108/111 108/110/112

35 2739 3023 3313 3610 3915 4229 4446 10470 90/95/100 94/98/102 98/101/104 102/104/107 105/106/109 108/109/111 110/110/112

40 2967 3266 3571 3886 4209 4544 4787 10470 92/95/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

45 3194 3508 3833 4167 4514 5142 5625 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

50 3433 3767 4111 4497 5233 5971 - 10232 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 110/110/111 -

51 3483 3820 4170 4657 5396 - - 10124 96/97/100 99/100/102 103/103/104 105/105/107 108/108/109 - -

VFS 116 118 121 123 126 128 130

WARNING: THE VALUES ABOVE DO NOT TAKE INTO ACCOUNT OBSTACLES.


TM

Performance


AFM

-265

6



Airport Pressure Altitude: 0 ft



8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2155 2231 2455 2681 2912 3148 3311 10470 90/94/100 92/97/102 96/100/104 100/103/107 103/105/109 106/108/111 108/109/112

-35 2193 2268 2496 2726 2961 3202 3367 10470 90/94/100 91/97/102 96/100/104 100/103/107 103/105/109 106/108/111 108/109/112

-30 2232 2304 2536 2771 3010 3255 3424 10470 90/94/100 91/97/102 96/100/104 99/103/107 103/105/109 106/108/111 108/109/112

-25 2270 2340 2576 2815 3059 3309 3480 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

-20 2308 2378 2619 2862 3109 3363 3538 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

-15 2347 2417 2661 2908 3159 3417 3595 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

-10 2384 2456 2704 2955 3211 3474 3655 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

-5 2422 2495 2747 3003 3264 3531 3715 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

0 2458 2535 2791 3051 3316 3588 3775 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

5 2495 2574 2835 3099 3369 3645 3835 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

10 2532 2617 2881 3150 3423 3704 3898 10470 90/94/100 91/97/102 95/100/104 99/103/107 102/105/109 106/108/111 108/109/112

15 2566 2663 2932 3205 3484 3769 3966 10470 90/94/100 91/97/102 95/100/104 99/103/107 102/105/109 106/108/111 108/109/112

20 2599 2710 2984 3261 3544 3835 4035 10470 90/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

25 2632 2770 3048 3328 3615 3909 4112 10470 89/94/100 91/97/102 95/100/104 99/103/107 103/105/109 106/108/111 108/109/112

30 2713 2999 3291 3589 3895 4209 4427 10470 89/95/100 93/98/102 97/101/104 101/103/107 104/106/109 107/108/111 109/110/112

35 2951 3251 3559 3873 4198 4533 4767 10470 92/95/100 95/98/102 99/101/104 103/104/107 106/107/109 108/109/111 110/111/112

40 3190 3507 3832 4166 4513 4972 5459 10470 93/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

45 3434 3768 4114 4474 5099 5845 - 10388 95/97/100 99/100/102 102/102/104 105/105/107 108/108/109 110/110/111 -

50 3689 4046 4427 5160 5921 - - 9855 96/97/100 100/100/102 103/103/104 106/106/107 108/108/109 - -

VFS 116 118 121 123 126 128 130


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2173 2406 2641 2880 3124 3374 3547 10470 89/94/100 93/97/102 97/100/104 101/103/107 104/106/109 107/108/111 109/110/112

-35 2208 2445 2685 2928 3177 3432 3608 10470 89/94/100 93/97/102 97/100/104 101/103/107 104/106/109 107/108/111 109/110/112

-30 2247 2484 2728 2976 3229 3490 3669 10470 89/94/100 93/97/102 97/100/104 101/103/107 104/106/109 107/108/111 109/110/112

-25 2286 2524 2772 3025 3283 3548 3731 10470 89/94/100 93/97/102 97/100/104 101/103/107 104/106/109 107/108/111 109/110/112

-20 2325 2565 2818 3075 3337 3606 3792 10470 89/94/100 93/97/102 97/100/104 100/103/107 104/106/109 107/108/111 109/110/112

-15 2364 2607 2864 3125 3391 3665 3854 10470 88/94/100 93/97/102 97/100/104 100/103/107 104/106/109 107/108/111 109/110/112

-10 2403 2649 2910 3175 3447 3725 3917 10470 88/94/100 93/97/102 97/100/104 100/103/107 104/106/109 107/108/111 109/110/112

-5 2442 2691 2956 3226 3501 3785 3980 10470 88/94/100 92/97/102 97/100/104 100/103/107 104/106/109 107/108/111 109/110/112

0 2479 2733 3003 3277 3557 3845 4044 10470 88/94/100 92/97/102 96/100/104 100/103/107 104/106/109 107/108/111 109/110/112

5 2515 2776 3050 3328 3613 3906 4109 10470 88/94/100 92/97/102 96/100/104 100/103/107 104/106/109 107/108/111 109/110/112

10 2552 2822 3101 3384 3674 3973 4179 10470 88/94/100 92/97/102 96/100/104 100/103/107 103/106/109 107/108/111 108/110/112

15 2592 2871 3154 3442 3738 4041 4250 10470 88/94/100 92/97/102 96/100/104 100/103/107 103/106/109 107/108/111 108/110/112

20 2637 2920 3207 3500 3801 4109 4322 10470 88/94/100 92/97/102 96/100/104 100/103/107 103/106/109 107/108/111 108/110/112

25 2729 3019 3314 3614 3923 4240 4459 10470 89/94/100 93/97/102 97/100/104 101/103/107 104/106/109 107/108/111 109/110/112

30 2958 3262 3571 3889 4215 4553 4788 10470 91/95/100 95/98/102 99/101/104 102/104/107 105/106/109 108/109/111 110/111/112

35 3202 3522 3850 4188 4539 4908 5380 10470 93/96/100 97/99/102 100/102/104 104/104/107 106/107/109 109/109/111 111/111/112

40 3452 3789 4138 4499 5013 5765 6271 10470 95/96/100 98/99/102 102/102/104 105/105/107 108/108/109 110/110/111 112/112/112

45 3712 4071 4444 5091 5863 - - 9958 96/97/100 100/100/102 103/103/104 105/105/107 108/108/109 - -

48 3875 4249 4807 5579 - - - 9656 97/97/100 100/100/102 103/103/104 106/106/107 - - -

VFS 116 118 121 123 126 128 130



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2346 2591 2839 3091 3350 3617 3802 10470 90/95/100 94/98/102 98/101/104 102/103/107 105/106/109 108/109/111 110/110/112

-35 2386 2634 2887 3144 3408 3680 3868 10470 90/95/100 94/98/102 98/101/104 102/103/107 105/106/109 108/109/111 110/110/112

-30 2425 2678 2935 3197 3466 3742 3934 10470 90/95/100 94/98/102 98/101/104 102/103/107 105/106/109 108/109/111 110/110/112

-25 2464 2722 2984 3250 3524 3805 4000 10470 90/95/100 94/98/102 98/101/104 102/103/107 105/106/109 108/109/111 110/110/112

-20 2503 2766 3032 3303 3581 3868 4066 10470 90/95/100 94/98/102 98/101/104 102/103/107 105/106/109 108/109/111 110/110/112

-15 2543 2810 3080 3356 3639 3930 4133 10470 90/95/100 94/98/102 98/101/104 101/103/107 105/106/109 108/109/111 110/110/112

-10 2583 2853 3128 3409 3697 3993 4198 10470 90/95/100 94/98/102 98/101/104 101/103/107 105/106/109 108/109/111 109/110/112

-5 2623 2898 3177 3462 3755 4056 4265 10470 90/95/100 94/98/102 98/101/104 101/103/107 105/106/109 107/109/111 109/110/112

0 2663 2942 3226 3516 3814 4120 4332 10470 90/95/100 94/98/102 98/101/104 101/103/107 104/106/109 107/108/111 109/110/112

5 2706 2990 3279 3574 3877 4188 4404 10470 90/95/100 94/98/102 98/101/104 101/103/107 104/106/109 107/109/111 109/110/112

10 2752 3040 3334 3634 3943 4260 4480 10470 90/95/100 94/98/102 98/101/104 101/103/107 104/106/109 107/109/111 109/110/112

15 2798 3091 3390 3695 4009 4332 4556 10470 90/95/100 94/98/102 98/101/104 101/103/107 104/106/109 107/109/111 109/110/112

20 2845 3143 3447 3757 4075 4404 4632 10470 90/95/100 94/98/102 98/101/104 101/103/107 104/106/109 107/109/111 109/110/112

25 2989 3296 3611 3933 4264 4606 4845 10470 91/95/100 95/98/102 99/101/104 102/104/107 105/106/109 108/109/111 110/110/112

30 3215 3537 3868 4209 4561 4926 5277 10470 93/96/100 96/99/102 100/102/104 103/104/107 106/107/109 109/109/111 111/111/112

35 3471 3811 4163 4527 4929 5688 6198 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

40 3738 4100 4477 5036 5824 - - 10040 96/97/100 99/100/102 102/103/104 105/105/107 108/108/109 - -

45 4021 4409 5093 5896 - - - 9513 97/97/100 100/100/102 103/103/104 106/106/107 - - -

46 4080 4480 5266 6071 - - - 9407 97/98/100 101/101/102 103/103/104 106/106/107 - - -

VFS 116 118 121 123 126 128 130


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2530 2787 3049 3318 3594 3879 4087 10470 92/95/100 96/98/102 99/101/104 103/104/107 106/106/109 109/109/111 111/111/112

-35 2573 2835 3102 3375 3656 3947 4152 10470 92/95/100 96/98/102 99/101/104 103/104/107 106/106/109 109/109/111 111/111/112

-30 2616 2883 3154 3432 3719 4015 4221 10470 91/95/100 95/98/102 99/101/104 103/104/107 106/106/109 109/109/111 110/111/112

-25 2659 2930 3207 3490 3781 4082 4292 10470 91/95/100 95/98/102 99/101/104 103/104/107 106/106/109 109/109/111 110/111/112

-20 2702 2977 3259 3547 3844 4150 4363 10470 91/95/100 95/98/102 99/101/104 102/104/107 106/106/109 108/109/111 110/111/112

-15 2744 3025 3311 3604 3906 4218 4434 10470 91/95/100 95/98/102 99/101/104 102/104/107 106/106/109 108/109/111 110/111/112

-10 2787 3072 3363 3661 3968 4285 4505 10470 91/95/100 95/98/102 99/101/104 102/104/107 105/106/109 108/109/111 110/111/112

-5 2830 3119 3415 3718 4030 4352 4576 10470 91/95/100 95/98/102 99/101/104 102/104/107 105/106/109 108/109/111 110/111/112

0 2872 3166 3467 3775 4092 4419 4647 10470 91/95/100 95/98/102 99/101/104 102/104/107 105/106/109 108/109/111 110/111/112

5 2918 3217 3523 3836 4159 4492 4723 10470 91/95/100 95/98/102 99/101/104 102/104/107 105/106/109 108/109/111 110/111/112

10 2967 3271 3582 3901 4229 4569 4804 10470 91/95/100 95/98/102 99/101/104 102/104/107 105/106/109 108/109/111 110/111/112

15 3016 3325 3642 3966 4300 4646 4885 10470 91/95/100 95/98/102 99/101/104 102/104/107 105/106/109 108/109/111 110/111/112

20 3078 3392 3715 4046 4387 4739 4984 10470 91/95/100 95/98/102 99/101/104 102/104/107 105/106/109 108/109/111 110/111/112

25 3240 3566 3900 4244 4600 4967 5242 10470 92/96/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

30 3490 3833 4188 4554 4935 5590 6106 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

35 3761 4127 4506 4944 5733 - - 10177 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 - -

40 4052 4443 5034 5850 - - - 9603 97/97/100 100/100/102 103/103/104 106/106/107 - - -

44 4279 4835 5680 - - - - 9218 98/98/100 101/101/102 104/104/104 - - - -

VFS 116 118 121 123 126 128 130



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2715 2986 3264 3548 3843 4160 4424 10470 93/96/100 97/99/102 100/101/104 104/104/107 107/107/109 109/109/111 111/111/112

-35 2761 3037 3320 3610 3910 4226 4489 10470 93/96/100 97/99/102 100/101/104 104/104/107 107/107/109 109/109/111 111/111/112

-30 2808 3089 3376 3672 3977 4293 4553 10470 93/96/100 97/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

-25 2854 3140 3432 3733 4043 4365 4617 10470 93/96/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

-20 2900 3191 3488 3795 4110 4438 4681 10470 92/96/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

-15 2946 3242 3545 3856 4177 4510 4747 10470 92/96/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

-10 2993 3294 3601 3918 4244 4583 4821 10470 92/96/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

-5 3039 3344 3657 3980 4311 4655 4895 10470 92/95/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

0 3084 3395 3713 4040 4378 4727 4971 10470 92/95/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

5 3133 3449 3773 4106 4449 4805 5053 10470 92/95/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 110/111/112

10 3185 3506 3836 4175 4524 4886 5143 10470 92/96/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 110/111/112

15 3237 3563 3899 4243 4598 4967 5233 10470 92/96/100 96/99/102 100/101/104 103/104/107 106/107/109 109/109/111 111/111/112

20 3307 3640 3982 4335 4698 5075 5371 10470 92/96/100 96/99/102 100/102/104 103/104/107 106/107/109 109/109/111 111/111/112

25 3502 3849 4207 4577 4960 5497 6018 10470 93/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

30 3773 4142 4523 4918 5619 6416 - 10320 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 110/110/111 -

35 4068 4461 4919 5741 - - - 9740 96/97/100 100/100/102 103/103/104 106/106/107 - - -

40 4369 4925 5783 - - - - 9220 98/98/100 101/101/102 104/104/104 - - - -

42 4493 5253 6122 - - - - 9028 98/98/100 101/101/102 104/104/104 - - - -

VFS 116 118 121 123 126 128 130


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2929 3216 3512 3817 4145 4635 5084 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

-35 2979 3272 3573 3883 4210 4702 5158 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

-30 3028 3326 3633 3949 4277 4769 5232 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

-25 3078 3381 3694 4015 4348 4836 5305 10470 94/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

-20 3128 3436 3754 4081 4421 4903 5378 10470 94/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

-15 3178 3492 3815 4148 4493 4969 5451 10470 94/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

-10 3227 3547 3875 4214 4565 5035 5523 10470 93/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

-5 3277 3602 3936 4280 4637 5101 5595 10470 93/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

0 3326 3656 3996 4345 4708 5165 5665 10470 93/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

5 3378 3714 4059 4414 4783 5239 5745 10470 93/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

10 3433 3774 4125 4487 4862 5324 5837 10470 93/96/100 97/99/102 100/102/104 104/105/107 107/107/109 110/110/111 111/111/112

15 3487 3834 4191 4559 4941 5409 5928 10470 93/96/100 97/99/102 100/102/104 104/105/107 107/107/109 110/110/111 111/111/112

20 3561 3914 4279 4654 5044 5564 6091 10470 93/96/100 97/99/102 101/102/104 104/105/107 107/107/109 110/110/111 111/111/112

25 3807 4180 4565 4964 5576 6381 - 10417 95/97/100 98/100/102 102/102/104 105/105/107 108/108/109 110/110/111 -

30 4101 4498 4911 5684 6515 - - 9844 96/97/100 100/100/102 103/103/104 106/106/107 108/108/109 - -

35 4426 4930 5797 - - - - 9273 97/98/100 101/101/102 104/104/104 - - - -

40 4890 5786 - - - - - 8783 98/98/100 101/101/102 - - - - -

VFS 116 118 121 123 126 128 130



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3145 3450 3766 4099 4561 5254 5721 10470 95/96/100 99/99/102 102/102/104 105/105/107 108/108/109 110/110/111 112/112/112

-35 3198 3509 3831 4164 4627 5330 5804 10470 95/96/100 99/99/102 102/102/104 105/105/107 108/108/109 110/110/111 112/112/112

-30 3252 3568 3896 4234 4693 5406 5886 10470 95/96/100 98/99/102 102/102/104 105/105/107 108/108/109 110/110/111 112/112/112

-25 3305 3628 3960 4305 4758 5481 5968 10470 95/96/100 98/99/102 102/102/104 105/105/107 108/108/109 110/110/111 112/112/112

-20 3359 3687 4025 4376 4823 5556 6050 10470 95/96/100 98/99/102 102/102/104 105/105/107 108/108/109 110/110/111 112/112/112

-15 3413 3746 4090 4447 4888 5630 6131 10470 95/96/100 98/99/102 102/102/104 105/105/107 108/108/109 110/110/111 112/112/112

-10 3467 3805 4155 4518 4953 5704 6211 10470 94/96/100 98/99/102 101/102/104 105/105/107 108/108/109 110/110/111 112/112/112

-5 3520 3865 4220 4588 5017 5778 6292 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/108/109 110/110/111 112/112/112

0 3573 3923 4285 4659 5080 5851 6371 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/107/109 110/110/111 112/112/112

5 3628 3985 4353 4733 5157 5933 6460 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/107/109 110/110/111 112/112/112

10 3687 4050 4424 4811 5245 6028 6561 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/108/109 110/110/111 112/112/112

15 3746 4115 4496 4890 5333 6122 6662 10470 94/96/100 98/99/102 101/102/104 104/105/107 107/108/109 110/110/111 112/112/112

20 3863 4242 4634 5040 5617 6432 - 10452 94/97/100 98/100/102 101/102/104 104/105/107 108/108/109 110/110/111 -

25 4134 4535 4952 5626 6467 - - 9943 96/97/100 99/100/102 102/103/104 106/106/107 108/108/109 - -

30 4458 4888 5727 - - - - 9378 97/98/100 100/101/102 103/103/104 - - - -

35 4855 5764 - - - - - 8852 98/98/100 101/101/102 - - - - -

38 5356 - - - - - - 8580 99/99/100 - - - - - -

VFS 116 118 121 123 126 128 130


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3366 3691 4028 4434 5153 - - 10161 96/97/100 99/100/102 103/103/104 105/105/107 108/108/109 - -

-35 3424 3755 4098 4499 5229 - - 10170 96/97/100 99/100/102 103/103/104 105/105/107 108/108/109 - -

-30 3483 3819 4169 4564 5304 - - 10179 96/97/100 99/100/102 102/103/104 105/105/107 108/108/109 - -

-25 3541 3884 4239 4628 5379 - - 10188 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 - -

-20 3599 3948 4309 4692 5453 - - 10196 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 - -

-15 3657 4012 4379 4764 5527 6298 - 10205 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 110/110/111 -

-10 3715 4076 4449 4838 5600 6382 - 10214 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 110/110/111 -

-5 3773 4140 4519 4913 5672 6465 - 10223 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 110/110/111 -

0 3829 4202 4589 4989 5744 6546 - 10232 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 110/110/111 -

5 3890 4269 4661 5068 5825 6638 - 10238 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 110/110/111 -

10 3954 4340 4739 5154 5923 6746 - 10232 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 110/110/111 -

15 4019 4411 4818 5243 6020 6854 - 10225 95/97/100 99/100/102 102/103/104 105/105/107 108/108/109 110/110/111 -

20 4184 4591 5014 5624 6474 - - 10007 96/97/100 99/100/102 102/103/104 106/106/107 108/108/109 - -

25 4489 4923 5647 6524 - - - 9489 97/98/100 100/101/102 103/103/104 106/106/107 - - -

30 4843 5714 - - - - - 8942 98/98/100 101/101/102 - - - - -

35 5663 - - - - - - 8475 99/99/100 - - - - - -

36 5836 - - - - - - 8386 99/99/100 - - - - - -

VFS 116 118 121 123 126 128 -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3606 3953 4329 5030 5778 - - 9824 97/97/100 100/100/102 103/103/104 106/106/107 108/108/109 - -

-35 3669 4022 4398 5105 5863 - - 9833 96/97/100 100/100/102 103/103/104 106/106/107 108/108/109 - -

-30 3731 4091 4467 5179 5948 - - 9841 96/97/100 100/100/102 103/103/104 106/106/107 108/108/109 - -

-25 3794 4160 4540 5252 6032 - - 9850 96/97/100 100/100/102 103/103/104 106/106/107 108/108/109 - -

-20 3857 4229 4616 5325 6116 - - 9859 96/97/100 100/100/102 103/103/104 106/106/107 108/108/109 - -

-15 3919 4298 4692 5397 6199 - - 9868 96/97/100 100/100/102 103/103/104 106/106/107 108/108/109 - -

-10 3982 4367 4767 5469 6282 - - 9877 96/97/100 99/100/102 103/103/104 106/106/107 108/108/109 - -

-5 4045 4435 4842 5541 6364 - - 9886 96/97/100 99/100/102 103/103/104 106/106/107 108/108/109 - -

0 4106 4504 4917 5611 6445 - - 9894 96/97/100 99/100/102 103/103/104 106/106/107 108/108/109 - -

5 4169 4573 4994 5684 6528 - - 9903 96/97/100 99/100/102 102/103/104 106/106/107 108/108/109 - -

10 4237 4649 5076 5774 6628 - - 9899 96/97/100 99/100/102 102/103/104 106/106/107 108/108/109 - -

15 4311 4729 5164 5874 6736 - - 9894 96/97/100 99/100/102 102/103/104 106/106/107 108/108/109 - -

20 4509 4946 5532 6421 - - - 9614 96/97/100 100/100/102 103/103/104 106/106/107 - - -

25 4862 5588 6515 - - - - 9072 98/98/100 101/101/102 104/104/104 - - - -

30 5601 - - - - - - 8565 99/99/100 - - - - - -

VFS 116 118 121 123 126 - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3942 4327 4981 5773 - - - 9493 97/98/100 101/101/102 103/103/104 106/106/107 - - -

-35 4011 4396 5053 5856 - - - 9502 97/98/100 101/101/102 103/103/104 106/106/107 - - -

-30 4079 4472 5124 5939 - - - 9513 97/98/100 100/101/102 103/103/104 106/106/107 - - -

-25 4148 4547 5196 6022 - - - 9522 97/98/100 100/101/102 103/103/104 106/106/107 - - -

-20 4216 4622 5266 6104 - - - 9531 97/98/100 100/101/102 103/103/104 106/106/107 - - -

-15 4284 4697 5336 6185 - - - 9539 97/98/100 100/100/102 103/103/104 106/106/107 - - -

-10 4353 4772 5406 6266 - - - 9548 97/98/100 100/100/102 103/103/104 106/106/107 - - -

-5 4420 4847 5475 6346 - - - 9559 97/97/100 100/100/102 103/103/104 106/106/107 - - -

0 4489 4922 5543 6425 - - - 9568 97/97/100 100/100/102 103/103/104 106/106/107 - - -

5 4559 4999 5620 6513 - - - 9572 96/97/100 100/100/102 103/103/104 106/106/107 - - -

10 4632 5081 5709 6613 - - - 9570 96/97/100 100/100/102 103/103/104 106/106/107 - - -

15 4715 5171 5821 6731 - - - 9564 96/98/100 100/101/102 103/103/104 106/106/107 - - -

20 5002 5633 6586 - - - - 9171 97/98/100 101/101/102 104/104/104 - - - -

25 5637 6629 - - - - - 8662 98/98/100 101/101/102 - - - - -

VFS 116 118 121 123 - - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 4310 4887 5737 - - - - 9218 98/98/100 101/101/102 104/104/104 - - - -

-35 4386 4959 5821 - - - - 9224 98/98/100 101/101/102 104/104/104 - - - -

-30 4461 5030 5904 - - - - 9231 98/98/100 101/101/102 104/104/104 - - - -

-25 4537 5101 5986 - - - - 9237 98/98/100 101/101/102 104/104/104 - - - -

-20 4612 5170 6068 - - - - 9244 97/98/100 101/101/102 104/104/104 - - - -

-15 4686 5240 6149 - - - - 9248 97/98/100 101/101/102 104/104/104 - - - -

-10 4762 5309 6230 - - - - 9255 97/98/100 101/101/102 104/104/104 - - - -

-5 4836 5378 6311 - - - - 9262 97/98/100 101/101/102 104/104/104 - - - -

0 4911 5446 6390 - - - - 9268 97/98/100 101/101/102 104/104/104 - - - -

5 4988 5520 6476 - - - - 9270 97/98/100 101/101/102 104/104/104 - - - -

10 5068 5605 6571 - - - - 9268 97/98/100 101/101/102 104/104/104 - - - -

15 5162 5734 6704 - - - - 9251 97/98/100 101/101/102 104/104/104 - - - -

20 5693 6711 - - - - - 8746 98/98/100 101/101/102 - - - - -

25 6728 - - - - - - 8256 99/99/100 - - - - - -

VFS 116 118 121 - - - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2240 2244 2253 2266 2327 2674 2930 10470 91/91/95 91/91/95 90/90/94 90/90/94 91/92/95 94/94/96 95/95/97

-35 2280 2284 2293 2308 2365 2711 2970 10470 91/91/95 91/91/95 90/90/94 90/90/94 91/92/95 94/94/96 95/95/97

-30 2319 2324 2334 2349 2403 2748 3011 10470 91/91/95 91/91/95 90/90/94 90/90/94 91/92/95 94/94/96 95/95/97

-25 2359 2364 2375 2391 2440 2785 3051 10470 91/91/95 91/91/95 90/90/94 90/90/94 91/92/95 94/94/96 95/95/97

-20 2398 2404 2415 2432 2478 2821 3090 10470 91/91/95 90/90/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/97

-15 2437 2443 2455 2472 2515 2857 3130 10470 91/91/95 90/90/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/97

-10 2476 2483 2496 2513 2553 2894 3170 10470 91/91/95 90/90/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/97

-5 2515 2523 2536 2554 2591 2930 3209 10470 91/91/95 90/90/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/97

0 2555 2563 2577 2595 2629 2966 3249 10470 91/91/95 90/90/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/97

5 2594 2602 2617 2637 2666 3002 3288 10470 91/91/95 90/90/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/97

10 2631 2640 2656 2676 2708 3044 3334 10470 91/91/95 90/90/95 90/90/94 90/90/93 90/92/95 94/94/96 95/95/97

15 2666 2676 2692 2713 2757 3100 3393 10470 90/90/95 90/90/95 90/90/94 90/90/93 90/92/95 94/94/96 95/95/97

20 2701 2711 2728 2750 2808 3157 3454 10470 90/90/95 90/90/94 90/90/94 90/90/93 90/92/95 94/94/96 95/95/97

25 2735 2747 2764 2787 2860 3215 3515 10470 90/90/95 90/90/94 90/90/94 90/90/93 90/92/95 94/94/96 95/95/97

30 2725 2741 2762 2787 3066 3520 - 10280 89/89/93 89/89/93 88/88/92 88/90/93 92/92/95 94/94/96 -

35 2666 2687 2725 3098 - - - 9753 86/86/91 86/86/90 86/88/91 90/90/93 - - -

40 2604 2718 3151 - - - - 9235 83/83/88 85/86/90 89/89/91 - - - -

45 2678 3149 - - - - - 8768 83/84/88 87/87/90 - - - - -

50 3121 - - - - - - 8338 85/85/88 - - - - - -

51 3220 - - - - - - 8256 85/85/88 - - - - - -

VFS 116 118 121 123 126 128 129



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2311 2315 2325 2340 2390 2733 - 10450 91/91/95 91/91/95 90/90/94 90/90/94 91/92/95 94/94/96 -

-35 2352 2357 2367 2383 2427 2767 - 10465 91/91/95 91/91/95 90/90/94 90/90/94 90/92/95 94/94/96 -

-30 2393 2398 2410 2426 2464 2801 3069 10470 91/91/95 91/91/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/98

-25 2434 2440 2452 2468 2501 2835 3106 10470 91/91/95 91/91/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/98

-20 2475 2481 2494 2511 2540 2874 3149 10470 91/91/95 91/91/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/98

-15 2516 2523 2536 2554 2580 2912 3192 10470 91/91/95 91/91/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/98

-10 2556 2563 2577 2596 2621 2955 3238 10470 91/91/95 90/90/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/98

-5 2595 2604 2618 2638 2663 2997 3284 10470 91/91/95 90/90/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/98

0 2634 2643 2658 2678 2706 3040 3330 10470 91/91/95 90/90/95 90/90/94 90/90/94 90/92/95 94/94/96 95/95/98

5 2672 2682 2698 2719 2749 3083 3376 10470 90/90/95 90/90/95 90/90/94 90/90/93 90/92/95 94/94/96 95/95/98

10 2711 2722 2738 2760 2794 3132 3428 10470 90/90/95 90/90/95 90/90/94 90/90/93 90/92/95 94/94/96 95/95/98

15 2747 2758 2776 2798 2848 3193 3493 10470 90/90/95 90/90/94 90/90/94 90/90/93 90/92/95 94/94/96 95/95/98

20 2782 2794 2812 2836 2902 3255 3559 10470 90/90/95 90/90/94 90/90/94 90/90/93 90/92/95 94/94/96 95/95/98

25 2815 2828 2848 2872 2968 3344 - 10417 90/90/95 90/90/94 90/90/93 89/90/93 90/92/95 94/94/96 -

30 2750 2770 2795 2992 3426 - - 9921 87/87/92 87/87/91 87/88/91 89/90/93 92/92/95 - -

35 2683 2709 3023 - - - - 9387 84/84/89 84/86/90 88/88/91 - - - -

40 2647 3047 - - - - - 8889 82/84/88 87/87/90 - - - - -

45 3037 - - - - - - 8430 85/85/88 - - - - - -

VFS 116 118 121 123 126 128 129


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2315 2324 2338 2365 2696 - - 10091 89/89/93 89/89/93 88/88/92 88/90/93 92/92/95 - -

-35 2356 2366 2381 2404 2730 - - 10102 89/89/93 89/89/93 88/88/92 88/90/93 92/92/95 - -

-30 2397 2408 2423 2443 2763 - - 10115 89/89/93 89/89/93 88/88/92 88/90/93 92/92/95 - -

-25 2439 2450 2466 2486 2798 - - 10126 89/89/93 89/89/93 88/88/92 88/90/93 92/92/95 - -

-20 2480 2492 2509 2530 2835 - - 10132 89/89/93 89/89/93 88/88/92 88/90/93 92/92/95 - -

-15 2522 2534 2552 2574 2874 - - 10139 89/89/93 89/89/93 88/88/92 88/90/93 92/92/95 - -

-10 2563 2576 2595 2617 2916 - - 10143 89/89/93 89/89/93 88/88/92 88/90/93 92/92/95 - -

-5 2604 2618 2637 2660 2958 - - 10146 89/89/93 89/89/93 88/88/92 88/90/93 92/92/95 - -

0 2644 2658 2678 2702 3000 - - 10150 89/89/93 88/88/93 88/88/92 88/90/93 92/92/95 - -

5 2682 2697 2718 2743 3043 - - 10152 89/89/93 88/88/93 88/88/92 88/90/93 92/92/95 - -

10 2720 2736 2757 2783 3092 - - 10143 89/89/93 88/88/93 88/88/92 88/90/93 92/92/95 - -

15 2758 2775 2797 2824 3151 - - 10128 88/88/93 88/88/92 88/88/92 88/90/93 92/92/95 - -

20 2795 2812 2835 2866 3210 - - 10115 88/88/93 88/88/92 88/88/92 88/90/93 92/92/95 - -

25 2818 2837 2863 2991 3396 - - 9963 88/88/92 88/88/92 87/88/91 89/90/93 92/92/95 - -

30 2757 2782 2994 3454 - - - 9491 85/85/89 85/86/90 88/88/91 91/91/93 - - -

35 2695 2995 - - - - - 8986 82/84/88 86/86/90 - - - - -

40 2983 - - - - - - 8523 84/84/88 - - - - - -

VFS 116 118 121 123 126 - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2324 2338 2356 2648 - - - 9738 87/87/91 87/87/91 87/88/91 90/90/93 - - -

-35 2366 2380 2399 2683 - - - 9747 87/87/91 87/87/91 87/88/91 90/90/93 - - -

-30 2408 2423 2443 2718 - - - 9755 87/87/91 87/87/91 87/88/91 90/90/93 - - -

-25 2450 2465 2486 2753 - - - 9764 87/87/91 87/87/91 87/88/91 90/90/93 - - -

-20 2492 2508 2529 2787 - - - 9773 87/87/91 87/87/91 87/88/91 90/90/93 - - -

-15 2534 2551 2573 2825 - - - 9780 87/87/91 87/87/91 87/88/91 90/90/93 - - -

-10 2576 2593 2616 2868 - - - 9786 87/87/91 87/87/91 87/88/91 90/90/93 - - -

-5 2616 2634 2658 2912 - - - 9793 87/87/91 87/87/91 86/88/91 90/90/93 - - -

0 2655 2674 2698 2956 - - - 9797 87/87/91 87/87/91 86/88/91 90/90/93 - - -

5 2693 2713 2738 3003 - - - 9800 87/87/91 87/87/91 86/88/91 90/90/93 - - -

10 2732 2753 2779 3054 - - - 9791 87/87/91 86/86/90 86/88/91 90/90/93 - - -

15 2771 2793 2819 3106 - - - 9780 87/87/91 86/86/90 86/88/91 90/90/93 - - -

20 2810 2832 2860 3160 - - - 9771 86/86/91 86/86/90 86/88/91 90/90/93 - - -

25 2813 2840 3013 3455 - - - 9542 85/85/90 85/86/90 87/88/91 91/91/93 - - -

30 2764 2973 3456 - - - - 9087 83/84/88 86/86/90 89/89/91 - - - -

35 2949 3482 - - - - - 8607 84/84/88 87/87/90 - - - - -

VFS 116 118 121 123 - - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2335 2353 2589 3029 - - - 9407 85/85/89 85/86/90 88/88/91 91/91/93 - - -

-35 2377 2396 2625 3070 - - - 9414 85/85/89 85/86/90 88/88/91 91/91/93 - - -

-30 2419 2439 2662 3112 - - - 9423 85/85/89 85/86/90 88/88/91 91/91/93 - - -

-25 2461 2482 2703 3153 - - - 9429 85/85/89 85/86/90 88/88/91 91/91/93 - - -

-20 2504 2525 2743 3194 - - - 9438 85/85/89 85/86/90 88/88/91 91/91/93 - - -

-15 2546 2568 2784 3234 - - - 9445 85/85/89 85/86/90 88/88/91 91/91/93 - - -

-10 2588 2611 2824 3275 - - - 9453 85/85/89 85/86/90 88/88/91 91/91/93 - - -

-5 2631 2654 2865 3315 - - - 9460 85/85/89 85/86/90 88/88/91 91/91/93 - - -

0 2673 2697 2905 3354 - - - 9467 85/85/89 85/86/90 88/88/91 91/91/93 - - -

5 2715 2739 2951 3402 - - - 9471 85/85/89 85/86/90 88/88/91 91/91/93 - - -

10 2753 2778 3002 3458 - - - 9462 85/85/89 85/86/90 88/88/91 91/91/93 - - -

15 2791 2817 3054 3514 - - - 9453 85/85/89 84/86/90 88/88/91 91/91/93 - - -

20 2831 2858 3127 3606 - - - 9425 85/85/89 84/86/90 88/88/91 91/91/93 - - -

25 2823 2981 3437 - - - - 9169 83/84/88 85/86/90 89/89/91 - - - -

30 2935 3431 - - - - - 8710 83/84/88 87/87/90 - - - - -

35 3428 - - - - - - 8259 85/85/88 - - - - - -

VFS 116 118 121 123 - - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2358 2503 2941 - - - - 9081 83/84/88 86/86/90 89/89/91 - - - -

-35 2401 2543 2981 - - - - 9087 83/84/88 85/86/90 89/89/91 - - - -

-30 2443 2583 3021 - - - - 9096 83/84/88 85/86/90 89/89/91 - - - -

-25 2486 2624 3061 - - - - 9105 83/84/88 85/86/90 89/89/91 - - - -

-20 2529 2664 3101 - - - - 9114 83/84/88 85/86/90 89/89/91 - - - -

-15 2572 2704 3140 - - - - 9121 83/84/88 85/86/90 89/89/91 - - - -

-10 2616 2745 3180 - - - - 9129 83/84/88 85/86/90 89/89/91 - - - -

-5 2659 2785 3219 - - - - 9136 83/84/88 85/86/90 89/89/91 - - - -

0 2701 2825 3257 - - - - 9145 83/84/88 85/86/90 89/89/91 - - - -

5 2744 2868 3302 - - - - 9149 83/84/88 85/86/90 89/89/91 - - - -

10 2784 2918 3355 - - - - 9143 83/84/88 85/86/90 89/89/91 - - - -

15 2824 2967 3409 - - - - 9138 83/84/88 85/86/90 89/89/91 - - - -

20 2862 3046 3510 - - - - 9105 83/84/88 85/86/90 89/89/91 - - - -

25 2917 3363 - - - - - 8803 82/84/88 87/87/90 - - - - -

30 3346 - - - - - - 8358 85/85/88 - - - - - -

VFS 116 118 121 - - - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2440 2869 - - - - - 8759 83/84/88 87/87/90 - - - - -

-35 2479 2907 - - - - - 8768 83/84/88 87/87/90 - - - - -

-30 2518 2946 - - - - - 8774 82/84/88 87/87/90 - - - - -

-25 2557 2984 - - - - - 8783 82/84/88 87/87/90 - - - - -

-20 2598 3022 - - - - - 8790 82/84/88 87/87/90 - - - - -

-15 2639 3060 - - - - - 8799 82/84/88 87/87/90 - - - - -

-10 2680 3098 - - - - - 8805 82/84/88 87/87/90 - - - - -

-5 2721 3135 - - - - - 8812 82/84/88 87/87/90 - - - - -

0 2760 3172 - - - - - 8818 82/84/88 87/87/90 - - - - -

5 2803 3214 - - - - - 8825 82/84/88 87/87/90 - - - - -

10 2848 3263 - - - - - 8823 82/84/88 87/87/90 - - - - -

15 2893 3312 - - - - - 8818 82/84/88 87/87/90 - - - - -

20 2960 3405 - - - - - 8783 82/84/88 87/87/90 - - - - -

25 3323 - - - - - - 8422 85/85/88 - - - - - -

VFS 116 118 - - - - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2741 - - - - - - 8477 84/84/88 - - - - - -

-35 2778 - - - - - - 8486 84/84/88 - - - - - -

-30 2815 - - - - - - 8492 84/84/88 - - - - - -

-25 2851 - - - - - - 8499 84/84/88 - - - - - -

-20 2888 - - - - - - 8505 84/84/88 - - - - - -

-15 2925 - - - - - - 8512 84/84/88 - - - - - -

-10 2961 - - - - - - 8521 84/84/88 - - - - - -

-5 3002 - - - - - - 8527 84/84/88 - - - - - -

0 3044 - - - - - - 8534 84/84/88 - - - - - -

5 3088 - - - - - - 8541 84/84/88 - - - - - -

10 3138 - - - - - - 8536 84/84/88 - - - - - -

15 3189 - - - - - - 8532 84/84/88 - - - - - -

20 3345 - - - - - - 8437 85/85/88 - - - - - -

VFS 116 - - - - - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3103 - - - - - - 8208 85/85/88 - - - - - -

-35 3146 - - - - - - 8217 85/85/88 - - - - - -

-30 3188 - - - - - - 8223 85/85/88 - - - - - -

-25 3230 - - - - - - 8230 85/85/88 - - - - - -

-20 3272 - - - - - - 8236 85/85/88 - - - - - -

-15 3313 - - - - - - 8243 85/85/88 - - - - - -

-10 3354 - - - - - - 8250 85/85/88 - - - - - -

-5 3395 - - - - - - 8259 85/85/88 - - - - - -

0 3435 - - - - - - 8265 85/85/88 - - - - - -

5 3476 - - - - - - 8270 85/85/88 - - - - - -

10 3532 - - - - - - 8267 85/85/88 - - - - - -

15 3589 - - - - - - 8261 85/85/88 - - - - - -

VFS 116 - - - - - -



TM

Performance


AFM

-265

6

INTENTIONALLY BLANK

TM

PHENOM 100


Performance


FM-2

656


ICE PROTECTION (WINGSTAB+ENG) ON – ATR OFF PW617F-E ENGINES




8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2659 2939 3225 3515 3811 4116 4325 10470 103/109/114 108/112/117 112/115/119 116/118/122 119/121/124 122/124/127 124/125/128

-35 2704 2990 3281 3576 3879 4189 4403 10470 103/109/114 108/112/117 112/115/119 116/118/122 119/121/124 122/124/127 124/125/128

-30 2749 3040 3337 3638 3945 4261 4479 10470 103/109/114 108/112/117 112/115/119 115/118/122 119/121/124 122/124/127 124/125/128

-25 2794 3091 3392 3699 4013 4334 4556 10470 103/109/114 108/112/117 112/115/119 115/118/122 119/121/124 122/124/127 124/125/128

-20 2839 3141 3447 3760 4080 4407 4634 10470 103/109/114 108/112/117 112/115/119 115/118/122 119/121/124 122/124/127 124/125/128

-15 2883 3190 3503 3821 4146 4479 4710 10470 103/109/114 107/112/117 112/115/119 115/118/122 119/121/124 122/124/127 124/125/128

-10 2929 3241 3559 3882 4213 4552 4788 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 122/124/127 124/125/128

-5 2975 3292 3615 3943 4280 4626 4865 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 122/124/127 124/125/128

0 3023 3345 3673 4006 4349 4702 4945 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 122/124/127 124/125/128

5 3071 3398 3732 4072 4420 4779 5027 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 122/124/127 124/125/128

10 3119 3453 3792 4139 4493 4857 5109 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 122/124/127 124/125/128

VFS 133 136 139 141 144 147 148



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2736 3025 3319 3618 3925 4239 4455 10470 103/109/114 108/112/117 112/115/119 115/118/122 119/121/124 122/124/127 124/125/128

-35 2782 3077 3377 3682 3994 4314 4535 10470 103/109/114 108/112/117 112/115/119 115/118/122 119/121/124 122/124/127 124/125/128

-30 2829 3129 3435 3745 4063 4389 4614 10470 103/109/114 108/112/117 112/115/119 115/118/122 119/121/124 122/124/127 124/125/128

-25 2875 3181 3492 3809 4132 4464 4694 10470 103/109/114 107/112/117 112/115/119 115/118/122 119/121/124 122/124/127 124/125/128

-20 2922 3233 3549 3872 4201 4539 4774 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 122/124/127 124/125/128

-15 2968 3284 3606 3934 4270 4614 4853 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 122/124/127 124/125/128

-10 3017 3338 3665 3998 4340 4691 4934 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 122/124/127 124/125/128

-5 3066 3392 3724 4062 4411 4769 5017 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 122/124/127 124/125/128

0 3117 3449 3787 4133 4487 4852 5103 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 121/124/127 124/125/128

5 3169 3507 3851 4203 4563 4934 5191 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 121/124/127 124/125/128

10 3221 3565 3915 4274 4641 5018 5278 10470 103/109/114 107/112/117 111/115/119 115/118/122 118/121/124 121/124/127 124/125/128

VFS 133 136 139 141 144 147 148


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2951 3256 3566 3882 4207 4542 4773 10470 105/110/114 109/113/117 113/116/119 116/118/122 120/121/124 123/124/127 125/126/128

-35 3002 3312 3628 3951 4282 4623 4858 10470 105/110/114 109/113/117 113/116/119 116/118/122 120/121/124 123/124/127 125/126/128

-30 3052 3368 3690 4019 4355 4704 4943 10470 105/110/114 109/113/117 113/116/119 116/118/122 119/121/124 123/124/127 125/126/128

-25 3102 3424 3752 4086 4430 4784 5029 10470 105/110/114 109/113/117 113/116/119 116/118/122 119/121/124 123/124/127 125/126/128

-20 3153 3479 3814 4154 4505 4866 5115 10470 104/110/114 109/113/117 113/116/119 116/118/122 119/121/124 123/124/127 125/126/128

-15 3204 3536 3876 4223 4579 4947 5201 10470 104/110/114 109/113/117 113/116/119 116/118/122 119/121/124 122/124/127 125/126/128

-10 3256 3594 3940 4292 4655 5030 5290 10470 104/110/114 109/113/117 113/116/119 116/118/122 119/121/124 122/124/127 125/126/128

-5 3309 3653 4004 4363 4733 5114 5378 10470 104/110/114 109/113/117 112/116/119 116/118/122 119/121/124 122/124/127 124/126/128

0 3364 3713 4070 4436 4813 5201 5469 10470 104/110/114 109/113/117 112/116/119 116/118/122 119/121/124 122/124/127 124/126/128

5 3417 3773 4137 4510 4893 5288 5561 10470 104/110/114 109/113/117 112/116/119 116/118/122 119/121/124 122/124/127 124/126/128

10 3474 3836 4207 4587 4976 5378 5657 10470 104/110/114 109/113/117 112/116/119 116/118/122 119/121/124 122/124/127 124/126/128

VFS 133 136 139 141 144 147 148



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3181 3502 3830 4166 4512 4869 5167 10470 106/110/114 110/113/117 114/116/119 117/119/122 120/122/124 124/124/127 126/126/128

-35 3237 3563 3897 4240 4593 4957 5257 10470 106/110/114 110/113/117 114/116/119 117/119/122 120/122/124 124/124/127 126/126/128

-30 3292 3625 3965 4314 4674 5045 5346 10470 106/110/114 110/113/117 114/116/119 117/119/122 120/122/124 123/124/127 126/126/128

-25 3347 3686 4032 4388 4754 5134 5437 10470 106/110/114 110/113/117 114/116/119 117/119/122 120/122/124 123/124/127 126/126/128

-20 3401 3747 4099 4462 4835 5221 5527 10470 106/110/114 110/113/117 114/116/119 117/119/122 120/122/124 123/124/127 126/126/128

-15 3457 3808 4167 4537 4916 5309 5618 10470 106/110/114 110/113/117 114/116/119 117/119/122 120/122/124 123/124/127 126/126/128

-10 3512 3869 4235 4610 4998 5398 5708 10470 106/110/114 110/113/117 114/116/119 117/119/122 120/122/124 123/124/127 126/126/128

-5 3568 3931 4303 4685 5079 5488 5800 10470 106/110/114 110/113/117 114/116/119 117/119/122 120/122/124 123/124/127 126/126/128

0 3623 3993 4371 4760 5161 5576 6057 10470 106/110/114 110/113/117 113/116/119 117/119/122 120/122/124 123/124/127 125/126/128

5 3682 4058 4443 4839 5247 5670 6508 10470 106/110/114 110/113/117 113/116/119 117/119/122 120/122/124 123/124/127 123/126/128

10 3745 4127 4520 4923 5338 5768 7045 10470 106/110/114 110/113/117 113/116/119 117/119/122 120/122/124 123/124/127 122/126/128

VFS 133 136 139 141 144 147 148


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3425 3764 4112 4470 4841 5370 5904 10470 107/111/114 111/114/117 115/117/119 118/119/122 121/122/124 125/125/127 127/127/128

-35 3485 3830 4185 4550 4928 5449 5990 10470 107/111/114 111/114/117 115/117/119 118/119/122 121/122/124 125/125/127 127/127/128

-30 3544 3897 4258 4630 5015 5528 6076 10470 107/111/114 111/114/117 115/117/119 118/119/122 121/122/124 125/125/127 127/127/128

-25 3604 3962 4331 4711 5103 5605 6162 10470 107/111/114 111/114/117 115/117/119 118/119/122 121/122/124 125/125/127 127/127/128

-20 3664 4028 4404 4790 5189 5683 6247 10470 107/111/114 111/114/117 115/117/119 118/119/122 121/122/124 125/125/127 127/127/128

-15 3723 4094 4477 4870 5276 5773 6344 10470 107/111/114 111/114/117 115/117/119 118/119/122 121/122/124 125/125/127 127/127/128

-10 3782 4160 4548 4949 5364 5863 6779 10470 107/111/114 111/114/117 115/117/119 118/119/122 121/122/124 125/125/127 125/127/128

-5 3841 4226 4621 5029 5449 5953 7344 10470 107/111/114 111/114/117 114/117/119 118/119/122 121/122/124 124/125/127 124/127/128

0 3900 4291 4693 5108 5536 6045 8018 10470 107/111/114 111/114/117 114/117/119 118/119/122 121/122/124 124/125/127 122/127/128

5 3964 4362 4771 5193 5630 6429 8647 10470 107/111/114 111/114/117 114/117/119 118/119/122 121/122/124 123/125/127 121/127/128

10 4032 4437 4854 5285 5728 6942 9235 10470 107/111/114 111/114/117 114/117/119 118/119/122 121/122/124 122/125/127 120/127/128

VFS 133 136 139 141 144 147 148



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3670 4029 4398 4779 5249 6070 - 10419 108/111/114 112/114/117 116/117/119 119/120/122 122/122/124 125/125/127 -

-35 3735 4100 4477 4866 5329 6158 - 10426 108/111/114 112/114/117 116/117/119 119/120/122 122/122/124 125/125/127 -

-30 3799 4171 4556 4952 5418 6246 - 10432 108/111/114 112/114/117 116/117/119 119/120/122 122/122/124 125/125/127 -

-25 3862 4243 4634 5039 5509 6333 - 10439 108/111/114 112/114/117 115/117/119 119/120/122 122/122/124 125/125/127 -

-20 3927 4314 4712 5124 5599 6419 - 10448 108/111/114 112/114/117 115/117/119 119/120/122 122/122/124 125/125/127 -

-15 3991 4385 4791 5211 5691 6506 - 10454 108/111/114 112/114/117 115/117/119 118/120/122 122/122/124 125/125/127 -

-10 4055 4456 4870 5296 5782 6641 - 10461 108/111/114 112/114/117 115/117/119 118/120/122 122/122/124 125/125/127 -

-5 4119 4527 4948 5382 5873 7127 - 10468 108/111/114 112/114/117 115/117/119 118/120/122 122/122/124 123/125/127 -

0 4183 4597 5025 5467 5963 7737 10456 10470 108/111/114 112/114/117 115/117/119 118/120/122 122/122/124 122/125/127 120/127/128

5 4251 4673 5108 5559 6065 8489 11234 10470 108/111/114 112/114/117 115/117/119 118/120/122 122/122/124 121/125/127 119/127/128

10 4322 4752 5195 5654 6171 9159 - 10461 108/111/114 112/114/117 115/117/119 118/120/122 122/122/124 120/125/127 -

VFS 133 136 139 141 144 147 148


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3956 4338 4733 5194 6043 - - 10020 109/111/114 113/114/117 116/117/119 120/120/122 123/123/124 - -

-35 4025 4415 4818 5283 6129 - - 10029 109/111/114 113/114/117 116/117/119 120/120/122 123/123/124 - -

-30 4095 4492 4903 5372 6215 - - 10035 109/111/114 113/114/117 116/117/119 120/120/122 123/123/124 - -

-25 4164 4568 4987 5462 6300 - - 10044 109/111/114 113/114/117 116/117/119 120/120/122 123/123/124 - -

-20 4234 4645 5072 5551 6385 - - 10051 109/111/114 113/114/117 116/117/119 120/120/122 123/123/124 - -

-15 4303 4723 5157 5642 6469 - - 10057 109/111/114 113/114/117 116/117/119 119/120/122 123/123/124 - -

-10 4372 4799 5242 5731 6553 - - 10066 109/111/114 113/114/117 116/117/119 119/120/122 123/123/124 - -

-5 4441 4876 5326 5821 6636 - - 10073 109/111/114 113/114/117 116/117/119 119/120/122 123/123/124 - -

0 4509 4952 5409 5910 6719 - - 10080 109/111/114 113/114/117 116/117/119 119/120/122 123/123/124 - -

5 4582 5032 5497 6006 7081 - - 10084 109/111/114 113/114/117 116/117/119 119/120/122 122/123/124 - -

10 4657 5115 5589 6108 7673 - - 10077 109/111/114 113/114/117 116/117/119 119/120/122 120/123/124 - -

VFS 133 136 139 141 144 - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 4246 4653 5095 5918 - - - 9676 110/112/114 114/115/117 117/118/119 120/120/122 - - -

-35 4320 4736 5182 6002 - - - 9683 110/112/114 114/115/117 117/118/119 120/120/122 - - -

-30 4395 4818 5270 6086 - - - 9689 110/112/114 114/115/117 117/118/119 120/120/122 - - -

-25 4470 4902 5359 6169 - - - 9698 110/112/114 114/115/117 117/118/119 120/120/122 - - -

-20 4544 4984 5448 6252 - - - 9705 110/112/114 114/115/117 117/118/119 120/120/122 - - -

-15 4619 5067 5536 6334 - - - 9711 110/112/114 114/115/117 117/118/119 120/120/122 - - -

-10 4694 5149 5624 6416 - - - 9720 110/112/114 113/115/117 117/118/119 120/120/122 - - -

-5 4768 5232 5714 6497 - - - 9727 110/112/114 113/115/117 117/118/119 120/120/122 - - -

0 4842 5313 5803 6577 - - - 9736 110/112/114 113/115/117 117/118/119 120/120/122 - - -

5 4920 5400 5898 6668 - - - 9738 110/112/114 113/115/117 117/118/119 120/120/122 - - -

10 5001 5490 5999 6773 - - - 9731 110/112/114 113/115/117 116/118/119 120/120/122 - - -

VFS 133 136 139 141 - - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 4543 4977 5727 - - - - 9356 111/112/114 114/115/117 118/118/119 - - - -

-35 4625 5067 5809 - - - - 9363 111/112/114 114/115/117 118/118/119 - - - -

-30 4705 5158 5891 - - - - 9370 111/112/114 114/115/117 118/118/119 - - - -

-25 4787 5247 5972 - - - - 9376 111/112/114 114/115/117 118/118/119 - - - -

-20 4868 5338 6053 - - - - 9385 111/112/114 114/115/117 118/118/119 - - - -

-15 4949 5427 6133 - - - - 9392 111/112/114 114/115/117 118/118/119 - - - -

-10 5030 5517 6212 - - - - 9398 111/112/114 114/115/117 118/118/119 - - - -

-5 5111 5606 6291 7306 - - - 9407 111/112/114 114/115/117 118/118/119 121/121/122 - - -

0 5191 5696 6369 7396 - - - 9414 111/112/114 114/115/117 118/118/119 121/121/122 - - -

5 5274 5787 6457 - - - - 9416 110/112/114 114/115/117 118/118/119 - - - -

10 5364 5887 6561 - - - - 9409 110/112/114 114/115/117 118/118/119 - - - -

VFS 133 136 139 141 - - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 4867 5498 6465 - - - - 9043 112/113/114 116/116/117 118/118/119 - - - -

-35 4955 5578 6559 - - - - 9050 112/113/114 116/116/117 118/118/119 - - - -

-30 5043 5657 6652 - - - - 9057 112/113/114 115/116/117 118/118/119 - - - -

-25 5131 5736 6744 - - - - 9063 111/113/114 115/115/117 118/118/119 - - - -

-20 5218 5814 6836 - - - - 9070 111/113/114 115/115/117 118/118/119 - - - -

-15 5306 5901 6927 - - - - 9076 111/112/114 115/115/117 118/118/119 - - - -

-10 5393 5994 7018 - - - - 9081 111/112/114 115/115/117 118/118/119 - - - -

-5 5480 6087 7108 - - - - 9087 111/112/114 115/115/117 118/118/119 - - - -

0 5567 6179 7197 - - - - 9094 111/112/114 115/115/117 118/118/119 - - - -

5 5655 6274 - - - - - 9098 111/112/114 115/115/117 - - - - -

10 5753 6384 - - - - - 9092 111/112/114 115/115/117 - - - - -

VFS 133 136 139 - - - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 5360 6350 - - - - - 8748 113/113/114 116/116/117 - - - - -

-35 5453 6442 - - - - - 8755 113/113/114 116/116/117 - - - - -

-30 5546 6533 - - - - - 8761 112/113/114 116/116/117 - - - - -

-25 5640 6624 - - - - - 8768 112/113/114 116/116/117 - - - - -

-20 5733 6714 - - - - - 8772 112/113/114 116/116/117 - - - - -

-15 5826 6803 - - - - - 8779 112/113/114 116/116/117 - - - - -

-10 5920 6892 - - - - - 8785 112/113/114 116/116/117 - - - - -

-5 6013 6980 - - - - - 8792 112/113/114 116/116/117 - - - - -

0 6106 7067 - - - - - 8796 112/113/114 116/116/117 - - - - -

5 6202 7156 - - - - - 8803 112/113/114 116/116/117 - - - - -

10 6307 - - - - - - 8799 112/113/114 - - - - - -

VFS 133 136 - - - - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 6189 - - - - - - 8459 113/113/114 - - - - - -

-35 6279 - - - - - - 8466 113/113/114 - - - - - -

-30 6368 - - - - - - 8472 113/113/114 - - - - - -

-25 6456 - - - - - - 8479 113/113/114 - - - - - -

-20 6544 - - - - - - 8483 113/113/114 - - - - - -

-15 6631 - - - - - - 8490 113/113/114 - - - - - -

-10 6718 - - - - - - 8497 113/113/114 - - - - - -

-5 6804 - - - - - - 8503 113/113/114 - - - - - -

0 6889 - - - - - - 8510 113/113/114 - - - - - -

5 6975 - - - - - - 8514 113/113/114 - - - - - -

VFS 133 - - - - - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2365 2582 2805 3038 - - - 9561 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-35 2405 2626 2854 3090 - - - 9568 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-30 2446 2670 2902 3141 - - - 9577 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-25 2486 2713 2949 3192 - - - 9583 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-20 2526 2757 2998 3243 - - - 9590 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-15 2565 2801 3046 3294 - - - 9599 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-10 2605 2844 3094 3346 - - - 9601 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-5 2645 2888 3142 3399 - - - 9599 93/98/102 97/101/104 100/103/106 103/106/108 - - -

0 2686 2934 3192 3453 - - - 9599 93/98/102 97/101/104 100/103/106 103/106/108 - - -

5 2728 2981 3243 3509 - - - 9597 93/98/102 97/101/104 100/103/106 103/106/108 - - -

10 2771 3028 3295 3566 - - - 9595 93/98/102 97/101/104 100/103/106 103/106/108 - - -

VFS 133 136 139 141 - - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2434 2658 2888 3126 - - - 9577 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-35 2476 2703 2938 3178 - - - 9583 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-30 2517 2748 2988 3232 - - - 9590 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-25 2559 2794 3037 3284 - - - 9597 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-20 2599 2839 3087 3337 - - - 9606 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-15 2641 2883 3136 3390 - - - 9612 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-10 2682 2929 3187 3446 - - - 9608 93/98/102 97/101/104 100/103/106 103/106/108 - - -

-5 2724 2975 3238 3502 - - - 9603 93/98/102 96/101/104 100/103/106 103/106/108 - - -

0 2770 3026 3293 3563 - - - 9599 93/98/102 96/101/104 100/103/106 103/106/108 - - -

5 2815 3076 3348 3624 - - - 9595 93/98/102 97/101/104 100/103/106 103/106/108 - - -

10 2861 3127 3403 3685 - - - 9588 93/98/102 97/101/104 100/103/106 103/106/108 - - -

VFS 133 136 139 141 - - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2615 2855 3098 - - - - 9224 94/99/102 98/101/104 101/104/106 - - - -

-35 2658 2904 3152 - - - - 9231 94/99/102 98/101/104 101/104/106 - - - -

-30 2702 2953 3205 - - - - 9237 94/99/102 98/101/104 101/104/106 - - - -

-25 2746 3002 3259 - - - - 9244 94/99/102 98/101/104 101/104/106 - - - -

-20 2791 3051 3312 - - - - 9251 94/99/102 98/101/104 101/104/106 - - - -

-15 2835 3100 3367 - - - - 9255 94/99/102 98/101/104 101/104/106 - - - -

-10 2880 3150 3422 - - - - 9255 94/99/102 98/101/104 101/104/106 - - - -

-5 2927 3201 3478 - - - - 9253 94/99/102 98/101/104 101/104/106 - - - -

0 2975 3254 3536 - - - - 9251 94/99/102 98/101/104 101/104/106 - - - -

5 3024 3307 3594 - - - - 9246 94/99/102 98/101/104 101/104/106 - - - -

10 3074 3363 3653 - - - - 9240 94/99/102 98/101/104 101/104/106 - - - -

VFS 133 136 139 - - - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 2813 3067 - - - - - 8878 96/99/102 99/102/104 - - - - -

-35 2861 3120 - - - - - 8882 96/99/102 99/102/104 - - - - -

-30 2909 3173 - - - - - 8889 96/99/102 99/102/104 - - - - -

-25 2957 3226 - - - - - 8893 96/99/102 99/102/104 - - - - -

-20 3005 3279 - - - - - 8898 96/99/102 99/102/104 - - - - -

-15 3053 3332 - - - - - 8904 95/99/102 99/102/104 - - - - -

-10 3101 3385 - - - - - 8909 95/99/102 99/102/104 - - - - -

-5 3152 3441 - - - - - 8911 95/99/102 99/102/104 - - - - -

0 3203 3497 - - - - - 8911 95/99/102 99/102/104 - - - - -

5 3256 3555 - - - - - 8907 95/99/102 99/102/104 - - - - -

10 3311 3614 - - - - - 8893 95/99/102 99/102/104 - - - - -

VFS 133 136 - - - - -


TM

PHENOM 100


Performance


FM-2

656






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3025 - - - - - - 8550 97/100/102 - - - - - -

-35 3078 - - - - - - 8556 97/100/102 - - - - - -

-30 3131 - - - - - - 8561 97/100/102 - - - - - -

-25 3183 - - - - - - 8565 97/100/102 - - - - - -

-20 3236 - - - - - - 8569 97/100/102 - - - - - -

-15 3288 - - - - - - 8574 97/100/102 - - - - - -

-10 3340 - - - - - - 8580 97/100/102 - - - - - -

-5 3392 - - - - - - 8585 97/100/102 - - - - - -

0 3444 - - - - - - 8589 97/100/102 - - - - - -

5 3501 - - - - - - 8589 97/100/102 - - - - - -

10 3561 - - - - - - 8578 97/100/102 - - - - - -

VFS 133 - - - - - -



TM

Performance


AFM

-265

6






8200 8600 9000 9400 9800 10200 10470 CLIMB LIMIT

WEIGHT

-40 3265 - - - - - - 8263 98/100/102 - - - - - -

-35 3322 - - - - - - 8267 98/100/102 - - - - - -

-30 3377 - - - - - - 8274 98/100/102 - - - - - -

-25 3432 - - - - - - 8278 98/100/102 - - - - - -

-20 3488 - - - - - - 8283 98/100/102 - - - - - -

-15 3544 - - - - - - 8289 98/100/102 - - - - - -

-10 3599 - - - - - - 8294 98/100/102 - - - - - -

-5 3654 - - - - - - 8298 98/100/102 - - - - - -

0 3710 - - - - - - 8305 98/100/102 - - - - - -

5 3769 - - - - - - 8303 98/100/102 - - - - - -

10 3835 - - - - - - 8294 98/100/102 - - - - - -

VFS 133 - - - - - -


TM

PHENOM 100


Performance


AFM

-265

6

DRIFTDOWN TABLES (GROSS GRADIENT) In the event of an engine failure during cruise the maximum airplane operating altitude is affected. The driftdown tables present the one engine ceiling according to the airplane weight and temperature.

The airplane should level off at the ceiling altitude.

EXAMPLE Given:

Airplane Weight .................................................. 9600 lb Temperature ....................................................... ISA + 10°C Ice Protection...................................................... OFF

Determine:

Ceiling................................................................. 22000 ft Driftdown Speed ................................................. 125 KIAS


TM

Performance


AFM

-265

6

PW617F-E ENGINES

CEILING ALTITUDE (x 100 ft) ICE PROTECTION (WINGSTAB+ENG) OFF WEIGHT

(lb)

DRIFT DOWN SPEED (KIAS) ISA - 10 ISA ISA + 10 ISA + 20 ISA + 35

7000 108 310 340 330 290 220 7200 109 310 330 320 280 210 7400 111 310 330 310 270 200 7600 112 310 320 300 260 190 7800 113 310 320 290 250 180 8000 115 310 310 280 240 170 8200 116 300 300 280 230 160 8400 117 300 300 270 220 150 8600 119 290 290 260 210 140 8800 120 280 290 250 200 130 9000 121 280 280 250 190 120 9200 122 270 270 240 190 110 9400 124 270 270 230 180 100 9600 125 260 260 220 170 90 9800 126 250 250 220 160 80

10000 127 250 250 210 150 70 10200 128 240 240 200 150 60

TM

PHENOM 100


Performance


AFM

-265

6

PW617F-E ENGINES

CEILING ALTITUDE (x 100 ft) ICE PROTECTION (WINGSTAB+ENG) ON WEIGHT

(lb)

DRIFT DOWN SPEED(KIAS) ISA - 30 ISA - 20 ISA - 10 ISA ISA + 10

7000 150 190 240 250 240 200 7200 150 190 240 240 230 190 7400 150 190 240 240 230 180 7600 150 190 240 240 220 170 7800 150 190 240 240 220 170 8000 150 190 240 240 210 160 8200 151 190 230 230 210 150 8400 153 190 230 230 200 140 8600 155 190 220 220 190 130 8800 156 190 210 210 180 120 9000 158 190 200 200 170 110 9200 159 190 190 190 160 100 9400 160 170 170 170 150 90 9600 161 150 160 160 140 80 9800 162 140 140 140 130 70

10000 164 120 120 120 120 60 10200 165 100 100 110 110 50

NOTE: Considered the minimum airspeed of 150 KIAS for operation in icing conditions according to Section 2-50.


TM

Performance


AFM

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6

ENROUTE GRADIENT This table presents the corrected gradient value due to the wind effect on the enroute gradient of climb/descent with one engine inoperative.

The wing effect correction is applicable for all weights, temperature and altitudes, considering the landing gear and flaps up, and must replace the gradient for zero wind.

EXAMPLE Given:

Headwind Wind...................................................40 kt Gradient for Zero Wind .......................................4.0%

Determine:

Gradient for 40 kt (headwind) .............................4.6%

CORRECTED GRADIENT % HEADWIND (kt) TAILWIND (kt) ZERO

WIND 60 40 20 20 40 60 -6.0 -6.7 -6.4 -6.2 -5.4 -5.0 -4.7 -4.0 -4.6 -4.4 -4.1 -3.6 -3.2 -3.0 -2.0 -2.4 -2.2 -2.1 -1.7 -1.5 -1.4 0.0 0.0 0.0 0.0 0.0 0.0 0.0 2.0 2.5 2.3 2.1 1.7 1.4 1.2 4.0 5.0 4.6 4.3 3.2 2.7 2.3 6.0 7.7 7.0 6.5 4.7 3.9 3.3 7.0 9.0 8.2 7.6 5.4 4.5 3.8

TM

PHENOM 100


Performance


AFM

-265

6

APPROACH DATA

APPROACH CLIMB, LANDING CLIMB AND LANDING REFERENCE SPEEDS

NOTE: - Applicable to airplanes Post-Mod. SB 500-27-0003 or with an equivalent modification factory incorporated, for airplanes Pre-Mod. SB 500-27-0003, refer to Supplement 2.

- For WINGSTAB OFF (Engine Anti-Ice 1/2 ON or OFF), the Landing Climb Speed is equal to the Landing Reference Speed.

- For WINGSTAB+ENG 1/2 ON, the Approach Climb Speed, Landing Climb Speed and Landing Reference Speed have the same value.

- For airplanes Pre-Mod. SB 500-27-0001, the WINGSTAB OFF performance data must be used according to AD 2009-05-06 (action 5).

EXAMPLE

Given: Airplane Landing Weight .................................... 8700 lb Approach Flaps .................................................. 2 Landing Flaps ..................................................... FULL Engine Anti-Ice ................................................... OFF Wingstab............................................................. OFF

Determine:

Approach Climb Speed ...................................... 101 KIAS Landing Climb Speed ......................................... 95 KIAS VREF..................................................................... 95 KIAS


TM

Performance


AFM

-265

6

APPROACH FLAPS 1 AND LANDING FLAPS 3 ENGINE ANTI-ICE OFF/ON – WINGSTAB OFF

PW617F-E ENGINES

APPROACH LANDING (CLIMB/REFERENCE)

FLAPS 1 FLAPS 3 WEIGHT

(lb)

VAC – KIAS VREF – KIAS

7100 100 91

7500 102 92

7900 104 94

8300 107 97

8700 109 99

9100 111 101

9500 114 104

9900 116 106

CAUTION: CHECK CLIMB LIMITED WEIGHT BEFORE USING VALUES IN SHADED AREA.


TM

PHENOM 100


Performance


AFM

-265

6

APPROACH FLAPS 2 AND LANDING FLAPS FULL ENGINE ANTI-ICE OFF/ON – WINGSTAB OFF

PW617F-E ENGINES


FLAPS 2 FLAPS FULL WEIGHT

(lb)


7100 92 91

7500 94 91

7900 96 91

8300 99 92

8700 101 95

9100 103 97

9500 104 99

9900 106 101




TM

Performance


AFM

-265

6

APPROACH FLAPS 1 AND LANDING FLAPS 3 ENGINE ANTI-ICE ON – WINGSTAB ON (SWPS ICE SPEED)

PW617F-E ENGINES

APPROACH CLIMB/LANDING (CLIMB/REFERENCE) WEIGHT

(lb) SPEED – KIAS

7100 110

7500 113

7900 116

8300 119

8700 121

9100 124

9500 127

9900 130



TM

PHENOM 100


Performance


AFM

-265

6

APPROACH FLAPS 2 AND LANDING FLAPS FULL ENGINE ANTI-ICE ON – WINGSTAB ON (SWPS ICE SPEED)

PW617F-E ENGINES


(lb) SPEED – KIAS

7100 105

7500 108

7900 111

8300 114

8700 117

9100 119

9500 122

9900 125




TM

Performance


AFM

-265

6

INTENTIONALLY BLANK

TM

PHENOM 100


Performance


AFM

-265

6

LANDING DATA

LANDING TECHNIQUE The landing performance data in this manual is based on the following conditions:

- Steady three degree angle approach at VREF in landing configuration;

- VREF airspeed maintained at runway threshold; - Idle thrust established at runway threshold; - Attitude maintained until MLG touchdown; - Maximum brake applied immediately after MLG touchdown; - Antiskid system operative.

MAXIMUM LANDING WEIGHT CLIMB LIMITED The maximum landing weight for altitude and temperature, in compliance with the airworthiness climb requirements, is shown in the Maximum Landing Weight Climb Limited tables in function of the temperature and altitude and according to the anti-ice system condition. When landing weight is not limited by the climb requirements it will be structural limited and the most limiting weights in the table are codified as follows: - (A) Approach Climb Limited - (L) Landing Climb Limited - (E) Enroute Climb - (S) Maximum Landing Weight

NOTE: For airplanes Pre-Mod. SB 500-27-0001, the WINGSTAB OFF performance data must be used according to AD 2009-05-06 (action 6).

EXAMPLE Given:

Airport Pressure Altitude .................................... 2000 ft Approach Flaps .................................................. 2 Landing Flaps ..................................................... FULL Engine Anti-Ice ................................................... OFF Wingstab............................................................. OFF Temperature ....................................................... 20°C

Determine: Maximum Landing Weight.................................. 9766 lb


TM

Performance


AFM

-265

6

MAXIMUM LANDING WEIGHT – CLIMB LIMITED APPROACH FLAPS 1 – LANDING FLAPS 3 ENGINE ANTI-ICE OFF – WINGSTAB OFF

PW617F-E ENGINES

MAXIMUM LANDING WEIGHT (lb)

ALTITUDE TEMP (°C)

-1000 ft 0 ft 1000 ft 2000 ft 3000 ft 4000 ft -40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9358 (A) 45 9766 (S) 9766 (S) 9766 (S) 9667 (E) - - 50 9766 (S) 9766 (S) - - - -


TM

PHENOM 100


Performance


AFM

-265

6


PW617F-E ENGINES


ALTITUDE TEMP (°C)

5000 ft 6000 ft 7000 ft 8000 ft 9000 ft 10000 ft -40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9623 (A) 9409 (A) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9632 (A) 9415 (A) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9643 (A) 9424 (A) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9651 (A) 9431 (A) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9660 (A) 9437 (A) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9671 (A) 9444 (A) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9680 (A) 9451 (A) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9689 (A) 9457 (A) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9698 (A) 9464 (A) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9704 (A) 9471 (A) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9704 (A) 9468 (A) 15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9693 (A) 9415 (A) 20 9766 (S) 9766 (S) 9766 (S) 9759 (A) 9321 (A) 8889 (A) 25 9766 (S) 9766 (S) 9647 (A) 9215 (A) 8781 (A) 8364 (A) 30 9766 (S) 9526 (A) 9091 (A) 8688 (A) 8304 (A) 7894 (A) 35 9415 (A) 8997 (A) 8611 (A) - - - 40 8926 (A) - - - - -



TM

Performance


AFM

-265

6

MAXIMUM LANDING WEIGHT – CLIMB LIMITED APPROACH FLAPS 2 – LANDING FLAPS FULL

ENGINE ANTI-ICE OFF – WINGSTAB OFF PW617F-E ENGINES


ALTITUDE TEMP (°C)

-1000 ft 0 ft 1000 ft 2000 ft 3000 ft 4000 ft -40 9766 (S) 9766 (S) 9766 (S) 9757 (A) 9424 (A) 9094 (A) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9433 (A) 9102 (A) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9442 (A) 9111 (A) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9451 (A) 9120 (A) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9457 (A) 9129 (A) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9466 (A) 9138 (A) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9473 (A) 9144 (A) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9482 (A) 9153 (A) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9488 (A) 9162 (A) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9490 (A) 9164 (A) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9482 (A) 9158 (A) 15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9473 (A) 9151 (A) 20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9444 (A) 9120 (A) 25 9766 (S) 9766 (S) 9766 (S) 9563 (A) 9191 (A) 8814 (A) 30 9766 (S) 9766 (S) 9504 (A) 9096 (A) 8717 (A) 8351 (A) 35 9766 (S) 9396 (A) 8994 (A) 8615 (A) 8254 (A) 7901 (A) 40 9239 (A) 8884 (A) 8523 (A) 8159 (A) 7813 (A) 7489 (A) 45 8767 (A) 8434 (A) 8079 (A) 7736 (A) - - 50 8318 (A) 8000 (A) - - - -


TM

PHENOM 100


Performance


AFM

-265

6




ALTITUDE TEMP (°C)

5000 ft 6000 ft 7000 ft 8000 ft 9000 ft 10000 ft -40 8767 (A) 8481 (A) 8207 (A) 7943(A) 7683 (A) 7517 (A) -35 8776 (A) 8487 (A) 8216 (A) 7949(A) 7689 (A) 7522 (A) -30 8783 (A) 8496 (A) 8223 (A) 7958 (A) 7698 (A) 7528 (A) -25 8792 (A) 8503 (A) 8232 (A) 7965 (A) 7705 (A) 7533 (A) -20 8800 (A) 8512 (A) 8238 (A) 7971 (A) 7711 (A) 7537 (A) -15 8807 (A) 8518 (A) 8245 (A) 7978 (A) 7718 (A) 7544 (A) -10 8814 (A) 8525 (A) 8251 (A) 7987 (A) 7725 (A) 7548 (A) -5 8822 (A) 8531 (A) 8260 (A) 7993 (A) 7733 (A) 7553 (A) 0 8829 (A) 8540 (A) 8267 (A) 8000 (A) 7740 (A) 7559 (A) 5 8833 (A) 8547 (A) 8271 (A) 8004 (A) 7744 (A) 7564 (A) 10 8831 (A) 8540 (A) 8267 (A) 8002 (A) 7742 (A) 7559 (A) 15 8829 (A) 8536 (A) 8260 (A) 7996 (A) 7736 (A) 7515 (A) 20 8789 (A) 8439 (A) 8108 (A) 7793 (A) 7447 (A) 7105 (A) 25 8423 (A) 8055 (A) 7707 (A) 7374 (A) 7050 (A) 6796 (A) 30 7978 (A) 7616 (A) 7279 (A) 6999 (A) 6763 (A) 6613 (A) 35 7530 (A) 7204 (A) 6953 (A) - - - 40 7147 (A) - - - - -



TM

Performance


AFM

-265

6

MAXIMUM LANDING WEIGHT – CLIMB LIMITED APPROACH FLAPS 1 – LANDING FLAPS 3

ENGINE ANTI-ICE ON – WINGSTAB OFF PW617F-E ENGINES


ALTITUDE TEMP (°C)

-1000 ft 0 ft 1000 ft 2000 ft 3000 ft 4000 ft -40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9486 (E) 35 9766 (S) 9766 (S) 9766 (S) 9733 (E) 9316 (E) 8911 (E) 40 9766 (S) 9766 (S) 9541 (E) 9129 (E) 8732 (E) 8357 (E) 45 9766 (S) 9347 (E) 8930 (E) 8538 (E) - - 50 9142 (E) 8741 (E) - - - -


TM

PHENOM 100


Performance


AFM

-265

6




ALTITUDE TEMP (°C)

5000 ft 6000 ft 7000 ft 8000 ft 9000 ft 10000 ft -40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9587 (A) 9378 (A) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9598 (A) 9385 (A) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9607 (A) 9391 (A) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9618 (A) 9400 (A) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9627 (A) 9407 (A) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9636 (A) 9413 (A) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9645 (A) 9422 (A) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9656 (A) 9429 (A) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9665 (A) 9435 (A) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9673 (A) 9442 (A) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9669 (A) 9358 (E) 15 9766 (S) 9766 (S) 9766 (S) 9651 (E) 9219 (E) 8803 (E) 20 9766 (S) 9766 (S) 9457 (E) 9049 (E) 8659 (E) 8269 (E) 25 9673 (E) 9263 (E) 8871 (E) 8496 (E) 8126 (E) 7742 (E) 30 9078 (E) 8703 (E) 8337 (E) 7976 (E) 7616 (E) 7268 (E) 35 8525 (E) 8163 (E) 7804 (E) - - - 40 7982 (E) - - - - -



TM

Performance


AFM

-265

6




ALTITUDE TEMP (°C)

-1000 ft 0 ft 1000 ft 2000 ft 3000 ft 4000 ft -40 9766 (S) 9766 (S) 9766 (S) 9717 (A) 9387 (A) 9056 (A) -35 9766 (S) 9766 (S) 9766 (S) 9726 (A) 9396 (A) 9065 (A) -30 9766 (S) 9766 (S) 9766 (S) 9735 (A) 9402 (A) 9076 (A) -25 9766 (S) 9766 (S) 9766 (S) 9746 (A) 9411 (A) 9085 (A) -20 9766 (S) 9766 (S) 9766 (S) 9755 (A) 9420 (A) 9094 (A) -15 9766 (S) 9766 (S) 9766 (S) 9764 (A) 9429 (A) 9102 (A) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9435 (A) 9109 (A) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9444 (A) 9118 (A) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9451 (A) 9127 (A) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9455 (A) 9131 (A) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9446 (A) 9127 (A) 15 9766 (S) 9766 (S) 9766 (S) 9764 (A) 9437 (A) 9120 (A) 20 9766 (S) 9766 (S) 9766 (S) 9735 (A) 9356 (A) 8986 (A) 25 9766 (S) 9766 (S) 9678 (A) 9257 (A) 8869 (A) 8487 (A) 30 9766 (S) 9528 (A) 9133 (A) 8752 (A) 8381 (A) 8033 (A) 35 9409 (A) 9021 (A) 8642 (A) 8278 (A) 7936 (A) 7605 (A) 40 8893 (A) 8538 (A) 8194 (A) 7846 (A) 7524 (A) 7220 (A) 45 8441 (A) 8104 (A) 7773 (A) 7451 (A) - - 50 8004 (A) 7691 (A) - - - -


TM

PHENOM 100


Performance


AFM

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6




ALTITUDE TEMP (°C)

5000 ft 6000 ft 7000 ft 8000 ft 9000 ft 10000 ft -40 8732 (A) 8445 (A) 8174 (A) 7912 (A) 7656 (A) 7493 (A) -35 8741 (A) 8454 (A) 8183 (A) 7921 (A) 7665 (A) 7497 (A) -30 8750 (A) 8463 (A) 8190 (A) 7927 (A) 7672 (A) 7504 (A) -25 8758 (A) 8470 (A) 8198 (A) 7936 (A) 7678 (A) 7508 (A) -20 8767 (A) 8478 (A) 8205 (A) 7943 (A) 7685 (A) 7515 (A) -15 8774 (A) 8485 (A) 8214 (A) 7949 (A) 7694 (A) 7519 (A) -10 8783 (A) 8492 (A) 8221 (A) 7958 (A) 7700 (A) 7526 (A) -5 8792 (A) 8501 (A) 8227 (A) 7965 (A) 7707 (A) 7530 (A) 0 8798 (A) 8507 (A) 8236 (A) 7971 (A) 7713 (A) 7535 (A) 5 8805 (A) 8516 (A) 8243 (A) 7978 (A) 7720 (A) 7542 (A) 10 8803 (A) 8514 (A) 8240 (A) 7976 (A) 7720 (A) 7248 (A) 15 8800 (A) 8512 (A) 8236 (A) 7925 (A) 7592 (A) 6900 (A) 20 8589 (A) 8207 (A) 7855 (A) 7511 (A) 7162 (A) - 25 8101 (A) 7747 (A) 7414 (A) 7092 (A) 6856 (A) - 30 7678 (A) 7332 (A) 7037 (A) 6810 (A) - - 35 7255 (A) 6988 (A) 6768 (A) - - - 40 6953 (A) - - - - -



TM

Performance


AFM

-265

6


ENGINE ANTI-ICE ON – WINGSTAB ON (SWPS ICE SPEED) PW617F-E ENGINES


ALTITUDE TEMP (°C)

-1000 ft 0 ft 1000 ft 2000 ft 3000 ft 4000 ft -40 9495 (A) 9349 (A) 9041 (A) 8732 (A) 8445 (A) 8161 (A) -35 9501 (A) 9358 (A) 9047 (A) 8739 (A) 8452 (A) 8170 (A) -30 9508 (A) 9369 (A) 9056 (A) 8747 (A) 8461 (A) 8179 (A) -25 9515 (A) 9378 (A) 9065 (A) 8754 (A) 8467 (A) 8185 (A) -20 9521 (A) 9389 (A) 9074 (A) 8763 (A) 8474 (A) 8194 (A) -15 9530 (A) 9398 (A) 9080 (A) 8769 (A) 8483 (A) 8203 (A) -10 9532 (A) 9400 (A) 9087 (A) 8778 (A) 8490 (A) 8210 (A) -5 9530 (A) 9402 (A) 9091 (A) 8785 (A) 8496 (A) 8216 (A) 0 9528 (A) 9398 (A) 9091 (A) 8792 (A) 8503 (A) 8225 (A) 5 9521 (A) 9393 (A) 9091 (A) 8794 (A) 8507 (A) 8229 (A) 10 9517 (A) 9389 (A) 9085 (A) 8785 (A) 8498 (A) 8225 (A)


ALTITUDE TEMP (°C)

5000 ft 6000 ft 7000 ft 8000 ft 9000 ft 10000 ft -40 7877 (A) 7623 (A) 7383 (A) 7145 (A) 6951 (A) 6834 (A) -35 7885 (A) 7630 (A) 7389 (A) 7151 (A) 6957 (A) 6838 (A) -30 7892 (A) 7639 (A) 7396 (A) 7158 (A) 6962 (A) 6843 (A) -25 7901 (A) 7645 (A) 7403 (A) 7165 (A) 6968 (A) 6845 (A) -20 7907 (A) 7652 (A) 7411 (A) 7173 (A) 6973 (A) 6849 (A) -15 7916 (A) 7658 (A) 7418 (A) 7180 (A) 6977 (A) 6854 (A) -10 7923 (A) 7667 (A) 7425 (A) 7187 (A) 6984 (A) 6858 (A) -5 7932 (A) 7674 (A) 7431 (A) 7193 (A) 6988 (A) 6862 (A) 0 7938 (A) 7680 (A) 7438 (A) 7200 (A) 6993 (A) 6867 (A) 5 7945 (A) 7685 (A) 7442 (A) 2041 (A) 6999 (A) 6869 (A) 10 7941 (A) 7683 (A) 7440 (A) 7200 (A) 6997 (A) 6847 (A)


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ALTITUDE TEMP (°C)



ALTITUDE TEMP (°C)




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UNFACTORED LANDING DISTANCES Unfactored landing distance is the actual distance to land the airplane on a zero slope, ISA temperature, dry runway, from a point 50 ft above runway threshold, at VREF speed, to complete stop using only the brakes as deceleration device.

NORMAL OPERATION

The required landing distance for dispatch is the unfactored landing distance increased by a factor according to the operating regulations.

EXAMPLE

Given: Airplane Landing Weight.....................................8700 lb Airport Pressure Altitude.....................................2000 ft Engine Anti-Ice....................................................OFF Wingstab .............................................................OFF Flaps ...................................................................3 Wind....................................................................10 kt

Determine:

Unfactored Landing Distance .............................2573 ft

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UNFACTORED LANDING DISTANCE (ft) ENGINE ANTI-ICE OFF/ON – WINGSTAB OFF – FLAPS 3

PW617F-E ENGINES

ALTITUDE -1000 ft 0 ft

WIND Weight

(lb)

-10 kt 0 kt 10 kt 20 kt -10 kt 0 kt 10 kt 20 kt 7100 2801 2328 2177 2030 2853 2376 2224 2075 7500 2801 2328 2177 2030 2853 2376 2224 2075 7900 2871 2398 2247 2100 2925 2448 2296 2147 8300 2961 2482 2329 2180 3017 2534 2380 2229 8700 3053 2568 2413 2262 3111 2622 2466 2314 9100 3142 2651 2495 2342 3202 2708 2550 2395 9500 3238 2742 2583 2428 3301 2800 2641 2484 9900 3332 2830 2670 2513 3397 2891 2729 2571

ALTITUDE 1000 ft 2000 ft

WIND Weight

(lb)





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UNFACTORED LANDING DISTANCE (ft) ENGINE ANTI-ICE OFF/ON – WINGSTAB OFF – FLAPS FULL

PW617F-E ENGINES


WIND Weight

(lb)



WIND Weight

(lb)




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PW617F-E ENGINES


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WIND Weight

(lb)





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UNFACTORED LANDING DISTANCE (ft) ENGINE ANTI-ICE ON – WINGSTAB ON (SWPS ICE SPEED)

FLAPS 3 PW617F-E ENGINES


WIND Weight

(lb)



WIND Weight

(lb)





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WIND Weight

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FLAPS FULL PW617F-E ENGINES


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WIND Weight

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WIND Weight

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SECTION 6

WEIGHT AND BALANCE

TABLE OF CONTENTS

Block Page

Introduction ........................................................................ 6-00.......... 02

Weight and Center of Gravity Limits.................................. 6-05.......... 01

Balance Reference System............................................... 6-10.......... 01

Configuration Checklist/Equipment List............................. 6-20.......... 01

Fuel Data ........................................................................... 6-30.......... 01

Miscellaneous Fluids ......................................................... 6-30.......... 05

Weighing and Balance Computation ................................. 6-35.......... 01

Baggage Loading .............................................................. 6-40.......... 01


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INTRODUCTION The Weight and Balance Section provides instructions referring to the weighting and loading of the PHENOM 100 airplane model.

The instructions and data herein presented are approved by the airworthiness authority to comply with the applicable regulations.

The basic empty weight value obtained during the airplane weighing procedures should be used as point of departure for each loading operation.

Based on the presented information, the operator can determine airplane weight and CG at any time of flight.

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WEIGHT AND CENTER OF GRAVITY LIMITS To comply with the performance and operating limitations of the regulations, the maximum allowable takeoff and landing operational weights may be equal to, but not greater than design limits.

Refer to Section 2, Limitations, for further information.


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BALANCE REFERENCE SYSTEM

BALANCE ARMS Longitudinal location of the Centers of Gravity (CG) identified throughout this manual regarding airplane and components will be referred to as Balance Arms. Balance Arms are the distance in inches from Airplane Datum, which is located at the zero station of the fuselage.

AIRPLANE DATUM

The Airplane Datum is a plane, perpendicular to the fuselage centerline.

WING MEAN AERODYNAMIC CHORD (MAC)

MAC length = 64.57 in.

LEMAC balance arm = 209.64 in.

Percentage of MAC is obtained using the following formula:

57.64100)64.209..(% ×−

=ABMAC

Where B.A. = Balance arm of airplane CG measured in inches.


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CONFIGURATION CHECKLIST/EQUIPMENT LIST The balance arms are shown in the applicable Interior arrangement. Herein, the Standard Configuration is presented as an illustrative example, including the plan view and the Balance Arms.

For other interior configuration options, the respective Balance Arms are supplied together with the “Airplane Weighing Form”, inserted in the “FINAL INSPECTION REPORT”, by the time of the airplane’s delivery.

STANDARD CONFIGURATION – CREW AND PASSENGERS

Balance Arm (in)

Pilot & Copilot Passengers 1 & 2

Passengers 3 & 4 Lavatory

108.90 176.97 214.68 249.76

NAVIGATION KIT

Weight (lb) Balance Arm (in) 16.54 129.06

STANDARD CONFIGURATION – BAGGAGE COMPARTMENTS

Balance Arm (in) FWD BaggageCompartment

AFT BaggageCompartment Wardrobe Lavatory

Cabinet 45.47 314.29 143.46 249.76

Refer to Section 2, Limitations, for further information on baggage compartments load capacity.


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EM

500E

NA

OM

0600

02A

.DG

N

FWD BAGGAGE

PILOT & COPILOT

WARDROBE

PASSENGERS 1 & 2

PASSENGERS 3 & 4

LAVATORY CABINET

LAVATORY

AFT BAGGAGE

1 2

3 4

P C

STANDARD CONFIGURATION

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FUEL DATA

FUEL QUANTITIES

FUEL CATEGORY VOLUME(US Gal)

WEIGHT(lb)

CG BALANCE ARM (in)

UNUSABLE 6.6 44.2 228.98

UNDRAINABLE 0.8 5.3 229.29

USABLE 418.7 2806 230.93

NOTE: The values specified above have been determined for an adopted fuel density of 6.701 lb/US Gal.


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FUEL DISTRIBUTION TABLE

FUEL DISTRIBUTION ON THE LEFT AND RIGHT WING TANKS

WEIGHT (lb)

CG BALANCE ARM (in)

50 228.65

100 228.23

150 227.83

200 227.46

250 227.05

300 226.74

350 226.44

400 226.16

450 226.00

500 225.86

550 225.75

600 225.73

650 225.70

700 225.73

750 225.75

800 225.82

850 225.90

900 225.95

950 226.02

1000 226.12

1050 226.20

1100 226.31

1150 226.37

1200 226.44

1250 226.52

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WEIGHT (lb)

CG BALANCE ARM (in)

1300 226.60

1350 226.70

1400 226.77

1450 226.88

1500 226.97

1550 227.05

1600 227.16

1650 227.27

1700 227.40

1750 227.50

1800 227.64

1850 227.76

1900 227.92

1950 228.06

2000 228.22

2050 228.39

2100 228.54

2150 228.71

2200 228.88

2250 229.06

2300 229.22

2350 229.38

2400 229.56

2450 229.73

2500 229.89

2550 230.07


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WEIGHT (lb)

CG BALANCE ARM (in)

2600 230.23

2650 230.40

2700 230.57

2750 230.73

2800 230.91

2806 230.93

NOTE: The values specified above have been determined for an adopted fuel density of 6.701 lb/US Gal.

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MISCELLANEOUS FLUIDS

FLUID WEIGHT(lb)

BALANCE ARM(in)

ENGINE OIL (1) 17.6 302.52

HYDRAULIC (2) 3.1 34.17

WASTE TANK FLUID 7.7 249.17

NOTE: 1) Adopted engine oil Density (ref. MIL-L-7808): 8.34 lb/US Gal.

2) Adopted hydraulic fluid density (ref. SAE AS 1241A TYPE IV): 7.09 lb/US Gal.


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WEIGHING AND BALANCE COMPUTATION The BEW (Basic Empty Weight) is the weight of the empty airplane in its delivered configuration plus the weight of fluids (engine oil and hydraulic fluid serviced full, and the unusable fuel). The BEW and its respective balance arm is obtained from the airplane weighting record.

In order to determine the airplane weight and CG arm, it is necessary to add to the BEW all the weight and moment variations referent to the loaded items. The total moment divided by the total weight gives the final CG arm. The CG arm must be converted into %MAC. The pair Weight/CG must then be checked against the Weight/CG envelope given in Section 2, Limitations.

Example: Computation of Weight and CG arm.

For a BEW equal 6887 lb and BEW moment equal 1620580 lb.in:

Item Weight (lb)

Arm (in)

Moment (lb.in)

BEW 6887 235.31 1620580 Pilot and Copilot 379 108.90 41273 Pax 1 and 2 388 176.97 68664 Pax 3 196 214.68 42077 Fuel (211 US Gal) (1) 1414 226.81 320709 Aft Baggage 176 314.29 55315 Airplane Weight & CG 9440 227.61 2148618

9.2757.64

100)64.20961.227(% =×−

=MAC

NOTE: - (1) The value specified above have been determined for an adopted fuel density of 6.701 lb/US Gal.

- The values above are for exemplification purpose. Use the airplane actual BEW for determining the Weight and CG arm.


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BAGGAGE LOADING

BAGGAGE WEIGHT AND LOCATION The baggage weight limits, location and the respective balance arm may be obtained from the applicable interior arrangement.

The data shown enclosed are applicable to the airplane’s Standard Configuration. For other interior configuration options, the weight limits, location and the respective balance arm are supplied together with the “Airplane Weighing Form”, inserted in the “FINAL INSPECTION REPORT”.

BAGGAGE COMPARTMENT The baggage should be evenly distributed in each compartment to avoid load concentration.

Baggage/Cargo must not become a hazard to the airplane structure or systems as a result of shifting under operational loads. Therefore, sharp edge volumes and/or dense cargo (objects significantly more dense than typical passenger baggage) must be arranged with adjacent soft volumes or protections thus preventing airplane damage in case of baggage/cargo shifting due to operational loads.


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Supplements

ANAC APPROVED S-TOC

SUPPLEMENTS

TABLE OF CONTENTS

SUPPLEMENT 1 RVSM OPERATION

SUPPLEMENT 2 OPERATION WITH AIRPLANES PRE-MOD. SB 500-27-0003

SUPPLEMENT 3 TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM II (TCAS II)

SUPPLEMENT 4 TERRAIN AWARENESS AND WARNING SYSTEM (TAWS)

SUPPLEMENT 5 OPERATION WITH AIRPLANES EQUIPPED WITH GROUND SPOILERS

SUPPLEMENT 6 AIRPLANES WITH ENHANCED TAKEOFF THRUST CONFIGURATION

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REVISION 9 code 01 Page 1


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Page 2 code 01 ORIGINAL

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Supplement 1 RVSM Operation

ANAC APPROVED S1-00 ORIGINAL code 01 Page 1 A

FM-2

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SUPPLEMENT 1

RVSM OPERATION

TABLE OF CONTENTS

Block Page

General ..............................................................................S1-00 ....... 02

Limitations..........................................................................S1-00 ....... 02

Normal Procedures............................................................S1-05 ....... 01

Emergency and Abnormal Procedures..............................S1-05 ....... 02

Performance ......................................................................S1-05 ....... 02


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GENERAL

INTRODUCTION This Supplement is provided to present the data required for operation in the RVSM (Reduced Vertical Separation Minimum) airspace. The RVSM operation reduces the PHENOM 100 model minimum vertical separation from 2000 ft to 1000 ft between FL 290 and FL 410.

Airworthiness approval alone does not authorize flight into airspace for which an RVSM operational approval is required by an ICAO Regional Navigation Agreement.

The information herein presented must replace or complement the equivalent data in the basic AFM.

LIMITATIONS

MINIMUM EQUIPMENT REQUIRED During RVSM operation it is necessary that the following equipment and instruments be in proper operating condition:

− 2 RVSM Compliant Air Data Systems;

− 1 Autopilot with Altitude Hold Mode Operative;

− 1 Altitude Alerter;

− 1 Transponder.

NOTE: - The ADS 1 and ADS 2 are compliant with RVSM operation. - The IESI must not be used for RVSM operation. - Should any of the required equipment fail prior to the

airplane entering RVSM airspace, the pilot should request a new clearance.

- The local authority determines the requirements for an operational transponder in each area where operations are intended.

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NORMAL PROCEDURES The actions listed below must complement the procedures contained in the basic AFM. The remaining Normal Procedures Section remains unchanged.

EXTERNAL SAFETY INSPECTION NOSE SECTION

Pitot Tubes and Static Ports .................................... CONDITION, NO OBSTRUCTION

Particular attention should be paid to the condition of static sources and to the marked area on the fuselage skin near each primary static source.

BEFORE TAKEOFF Altimeters................................................................. SET TO THE

AIRFIELD QNH Altitude Indications................................................... CHECK

NOTE: - An alternative procedure using QFE may also be used. - The maximum difference between both primary altimeters

indications must not exceed 23 m (75 ft).

CRUISE Be sure that all required equipment is in proper operating condition.

Ensure that the airplane is flown at the cleared flight level and that ATC clearances are fully understood and followed. Do not depart from cleared flight level without a positive clearance from ATC except for a contingency or emergency situation.

While changing flight levels do not overshoot or undershoot the cleared flight level by more than 45 m (150 ft).

The autopilot should be operative and engaged during level cruise, except for circumstances such as the need to re-trim the airplane or when it must be disengaged due to turbulence.


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AFTER LANDING In case of failure or malfunction, the following information should be recorded when appropriate:

− ADS 1, ADS 2 altimeter readings;

− Altitude selector setting;

− Baro Set value and Baro Set unit (InHg/HPa);

− Flight Director used with the Autopilot to control the airplane and any differences when the other Flight Director was coupled;

− Use of air data system reversion for fault diagnosis procedure;

− The transponder selected to provide altitude information to ATC and any difference noted when an alternative transponder was selected, if applicable.

EMERGENCY AND ABNORMAL PROCEDURES The actions listed below must complement the procedures contained in the basic AFM. The remaining Emergency and Abnormal Procedures Section remains unchanged.

− In case of emergency or abnormal situation or contingencies (equipment failures, weather, etc.) which affect the ability to maintain the cleared flight level, notify ATC and co-ordinate an action plan that is appropriate to the airspace concerned;

− Notify ATC when encountering greater than moderate turbulence;

− If unable to notify ATC and obtain an ATC clearance prior to deviating from the cleared flight level, follow any established contingency procedures and obtain ATC clearance as soon as possible.

PERFORMANCE Performance Data presented in the basic AFM remain unchanged.

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ANAC APPROVED S2-00 REVISION 5 code 01 Page 1

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SUPPLEMENT 2

OPERATION WITH AIRPLANES PRE-MOD. SB 500-27-0003

TABLE OF CONTENTS

Block Page

General ..............................................................................S2-00 ....... 03

Limitations..........................................................................S2-05 ....... 01



Performance ......................................................................S2-15 ....... 01


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GENERAL

INTRODUCTION This Supplement presents the required information and performance data to operate airplanes Pre-Mod. SB 500-27-0003, “Removal of the Flap Limitation”.

Flaps 3 operation for airplanes Pre-Mod. SB 500-27-0003 is not approved.

The information herein presented must replace or complement the equivalent data in the basic AFM.


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LIMITATIONS

OPERATIONAL LIMITATIONS MAXIMUM FLAP EXTENDED SPEED (VFE)

Flaps 1 ..................................................................... 200 KIAS Flaps 2 ..................................................................... 160 KIAS Flaps 3 ..................................................................... 145 KIAS Flaps FULL .............................................................. 145 KIAS

NOTE: Flaps 3 is not approved for operation.

MANEUVERING FLIGHT LOAD FACTORS

These corresponding accelerations limit the bank angle during turns and limit the pull-up maneuvers.

LOAD FACTOR LIMIT FLAPS UP FLAPS DOWN (1, 2, 3 AND FULL)

Positive 3.27 g 2.00 g

NOTE: Flaps 3 is not approved for operation.

FLIGHT CONTROLS FLAPS

Flaps 3 must not be used.


- Flaps FULL must not be used to land in “no icing conditions”.


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NORMAL PROCEDURES The actions listed below must complement the procedures contained in the basic AFM. The remaining Normal Procedures Section remains unchanged.

GO-AROUND NOTE: For airplanes Pre-Mod. SB 500-27-0001, the GO-AROUND

Procedure of the AD 2009-05-06 (action 2) must be accomplished.

TO/GA Buttons ........................................................ PRESS


Rotate the airplane following the flight director guidance or according to the table below.



2 7.5°

FULL 5.5°




2 1

FULL 2



Airspeed.............................................................. VAC MINIMUM



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OPERATION IN ICING CONDITIONS TAKEOFF

Only for airplanes with G1000 system version 0734.07 and version 0734.21:

Flight Director......................................................OFF


NOTE: During takeoff roll, after checking thrust levers to TO/GA, check N1 equal to N1 target and green ATR indication presented on MFD if ATR ON is selected.

Engine Parameters ..................................................MONITOR

Initially rotate the airplane according to the table below.

FLAPS POSITION 1 2

PITCH ANGLE 6° 5.5°


Airspeed..............................................................V2 + 10 KIAS MINIMUM

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GO-AROUND

TO/GA Buttons ........................................................ PRESS


Rotate the airplane according to the table below.



2 4.0°

FULL 2.0°

CAUTION: ONLY FOR AIRPLANES WITH G1000 SYSTEM VERSION 0734.07 AND VERSION 0734.21 INSTALLED, DO NOT FOLLOW THE FLIGHT DIRECTOR.




2 1

FULL 2



Airspeed.............................................................. VAC MINIMUM

Airplanes featuring a G1000 system version 0734.07 and version 0734.21 must turn off the Flight Director as soon as possible.



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EMERGENCY AND ABNORMAL PROCEDURES The actions listed below must complement the procedures contained in the basic AFM. The remaining Emergency and Abnormal Procedures Section remains unchanged.

DITCHING NOTE: The airplane is not certified for ditching. The procedure below

is recommended to be followed if required.

During descent: Passengers .........................................................PREPARE/LIFE

VESTS, IF AVAILABLE, DON

ATC.....................................................................NOTIFY Transponder........................................................7700 SIGNS/OUTLET Switch......................................PED-BELTS/OFF Water Barrier....................................................... INSTALL

At 10000 ft, push the Pressurization DUMP Button in.

Ditching configuration: LDG GEAR Lever ...............................................UP Flaps ...................................................................MAX AVAILABLE Oxygen Bottle Valve Handle...............................PULL TO CUTOUT


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0 VREF FULL + 47 KIAS VREF FULL + 51 KIAS 1 VREF FULL + 40 KIAS VREF FULL + 40 KIAS 2 VREF FULL + 25 KIAS VREF FULL + 30 KIAS

3 and FULL VREF FULL + 20 KIAS VREF FULL + 25 KIAS






3 and FULL VREF FULL VREF FULL + 25 KIAS





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Just before water contact: Passengers .........................................................ANNOUNCE

After ditching: Thrust Levers ...................................................... IDLE Start/Stop Knobs.................................................STOP Fire Extinguish System .......................................AS REQUIRED Emergency Evacuation.......................................ANNOUNCE BATT 1 & 2 Switches..........................................OFF

FORCED LANDING This procedure is recommended for landings with all engines inoperative or for landings in unprepared surfaces. Landing on unprepared surfaces is not recommended. However, if specific circumstances render such landing inevitable, accomplish the procedures below:

Passengers .........................................................PREPARE ATC.....................................................................NOTIFY Transponder........................................................7700 SIGNS/OUTLET Switch......................................PED-BELTS/OFF ELT .....................................................................ON Landing Data.......................................................SET

At 10000 ft push in the Pressurization DUMP Button and set the altimeters during approach.

For landing configuration: LDG GEAR Lever ...............................................AS REQUIRED

NOTE: The decision to land with gear up or extended is left to pilots. The choice of configuration is based on airplane load distribution, controllability and conditions of the landing field.

Flaps ...................................................................MAXIMUM AVAILABLE


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Oxygen Bottle Valve Handle...............................PULL TO CUTOUT

Just before touchdown: Passengers .........................................................ANNOUNCE

IMPACT

After landing, if conditions permit: Thrust Lever........................................................ IDLE Start/Stop Knobs.................................................STOP Fire Shutoff Buttons ............................................PUSH IN Emergency Evacuation.......................................ANNOUNCE BATT 1 & 2 Switches..........................................OFF

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ONE ENGINE INOPERATIVE APPROACH AND LANDING NOTE: For airplanes Pre-Mod. SB 500-27-0001, the GO-AROUND

Procedure of the AD 2009-05-06 (action 3) must be accomplished.

During descent: Landing Speeds.................................................. SET Landing Field Elevation ...................................... SET Approach Aids .................................................... SET Altimeters............................................................ SET/CHECK

Landing configuration: LDG GEAR Lever ............................................... DN Flaps................................................................... 2 Airspeed.............................................................. VREF FULL + 10 KIAS

MINIMUM


If a go-around is required: Go-Around Button............................................... PRESS Thrust Levers...................................................... TO/GA


Rotate the airplane to 7.5° nose up.

Flaps................................................................... 1

With positive rate of climb: LDG GEAR Lever ............................................... UP Airspeed.............................................................. APPROACH

CLIMB SPEED


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ELECTRICAL EMERGENCY Reset both generators.

If message persists: LAND AS SOON AS POSSIBLE.

ADS/AOA Knob...................................................ON

Exit and avoid icing conditions.

Confirm that IESI has reverted. If not, select ADSTBY on PFD.

Pressurization MODE Switch..............................MAN CABIN ALT Switch..............................................AS REQUIRED Airspeed..............................................................250 KIAS

MAXIMUM Altitude ................................................................25000 ft

MAXIMUM

CAUTION: BATTERIES DURATION IS 45 MINUTES MAXIMUM.

When landing maintain airspeed according to the following:

FLAPS POSITION MINIMUM AIRSPEED 0 VREF FULL + 30 KIAS 1 VREF FULL + 15 KIAS 2 VREF FULL + 5 KIAS

3 and FULL VREF FULL




CAUTION: WHEN APPLYING EMERGENCY BRAKES, PULL THE HANDLE PROGRESSIVELY, MONITORING THE EMERGENCY/PARKING BRAKE LIGHT.


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FLAPS POSITION CORRECTION FACTOR0 2.25 1 1.75 2 1.65

3 and FULL 1.50



- ADC 1 and 2 (*) - Main Brake (*) - AHRS 2 (*) - PFD 2 - Air Conditioning - Pitch Trim (Main) (*) - Anti-Ice/De-Ice Systems - Pressurization Auto (*) - Audio Panel 2 (*) - Roll Trim - Autopilot (*) - Stick Pusher (*) - DME’s - TCAS - Engine 1 and 2 Fuel Flow Information - Transponder 2 - Flap System (*) - VHF 2 - FMS Panel - Windshields Heater (*) - GIA 2 (*) - WX Radar - GPS 2/VOR 2/ILS 2 - Yaw Damper - Landing/Taxi Lights - Yaw Trim

NOTE: Engine 1 and 2 Fuel Flow information is lost only for airplanes with G1000 system version 0734.07 and version 0734.21 installed.


TM



AFM

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6

DC BUS 1 OFF ADS/AOA Knob........................................................ON Icing Conditions .......................................................EXIT/AVOID

For landing proceed: - Maintain airspeed according to the following:








0 1.40 1.70 1 1.20 1.60 2 1.10 2.00

3 and FULL 1.00 1.95


TM

PHENOM 100




AFM

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6



- ADC 1 (*) - Left Landing/Taxi Light

- Cockpit FCSOV - Roll Trim

- De-Ice System (*) - Stick Pusher (*)

- DME 1 - VHF 2

- Engine 1 Anti-Ice (*) - Windshield Heater 1 (*)

- Engine 1 Flowmeter - WX Radar

- Flap System (*) - Yaw Trim


TM



AFM

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6

FLAPS FAILURE Flaps Lever ..............................................................CYCLE

Up to 3 cycles may be attempted.

If failure persists: Altitude ................................................................15000 ft

MAXIMUM


If is not possible to avoid icing conditions: LAND AS SOON AS POSSIBLE.

For landing proceed: - Check the available airports within the current range and choose

the one that best matches the required runway length. Considerations for uphill slope and occurrence of headwind should be also made.

- Burn as much fuel as possible to reduce the landing weight. - Maintain bank angle below 20°. - For airplanes Pre-Mod. SB 500-27-0001, maintain the airspeed

according to the following:







TM

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AFM

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- For airplanes Post-Mod. SB 500-27-0001 or with an equivalent modification factory incorporated, maintain the airspeed according to the following:










0 1.90 2.00 1 1.70 1.70 2 1.75 2.00

3 and FULL 1.75 1.95



TM



AFM

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6




0 1.40 1.70 1 1.20 1.60 2 1.10 2.00

3 and FULL 1.00 1.95

PITCH TRIM BACK-UP FAILURE PITCH BKP Switch ..................................................OFF Pitch Trim Switch .....................................................USE AS

REQUIRED

NOTE: Message PTRIM DISCONNECT may be presented.

If associated with the PTRIM NML FAIL message: Landing configuration:

Flaps ..............................................................2 Airspeed.........................................................VREF FULL + 5 KIAS


TM

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PERFORMANCE

PERFORMANCE CONFIGURATION The configurations applicable to each performance phase are shown below.

OPERATINGENGINES TLA FLAPS GEAR AIRSPEED

TAKEOFF RUN

2 until VEF, 1 after VEF TO/GA 1 or 2 DOWN 0 TO VLOF

1ST SEGMENT 1 TO/GA 1 or 2 DOWN TOUP VLOF TO V2

2ND SEGMENT 1 TO/GA 1 or 2 UP V2

3RD SEGMENT 1 TO/GA TAKEOFF FLAPS TO 0 UP

V2 TO FINALSEGMENT

SPEED

FINAL SEGMENT 1 MAX CON 0 UP

FINAL SEGMENT

SPEED

ENROUTE 1 MAX CON 0 UP ENROUTE

CLIMB SPEED

APPROACH CLIMB 1 TO/GA 1 or 2 UP

APPROACHCLIMB SPEED

LANDING CLIMB 2 TO/GA 2 or FULL DOWN

LANDING CLIMB SPEED

LANDING 2 IDLE 2 or FULL DOWN VREF


TM



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The software OP500FA617FE version 7.0 allows performance calculations for airplanes with the following configuration:

- PHENOM 100.

- PW617F-E engines.

- Pre-Mod. SB 500-27-0003.





NOTE: - OPERA version 7.0 provides guidance information when operating from contaminated runways.


VALID VERSIONS


AIRPLANE CONFIGURATION VALID VERSION

Pre-Mod. SB 500-27-0003 7.0

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STALL SPEED This table presents the stall speed value according to the airplane bank angle for the MTOW (10472 lb) with landing gear and flaps up.

BANK

ANGLE 0° 15° 30° 45° 60°

STALL SPEED (KIAS)

100 102 108 119 141

This table presents the stall speed values according to the airplane bank angle for the MLW (9766 lb) with landing gear down and landing flaps 2 or FULL.

STALL SPEEDS (KIAS)

BANK ANGLE 0° 15° 30° 45° 60°

FLAPS 2 81 82 87 96 115

FLAPS FULL 77 79 83 92 109


TM



AFM

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APPROACH DATA

APPROACH CLIMB, LANDING CLIMB AND LANDING REFERENCE SPEEDS

NOTE: - For WINGSTAB OFF, the Landing Climb Speed is equal to the Landing Reference Speed.

- For WINGSTAB ON, the Approach Climb Speed, Landing Climb Speed and Landing Reference Speed have the same value.

- For airplanes Pre-Mod. SB 500-27-0001, the WINGSTAB OFF performance data must be used according to AD 2009-05-06 (action 5).

EXAMPLE

Given: Airplane Landing Weight.....................................8700 lb Airport Pressure Altitude.....................................2000 ft Approach Flaps...................................................2 Landing Flaps .....................................................FULL Engine Anti-Ice....................................................OFF Wingstab .............................................................OFF

Determine:

Approach Climb Speed.......................................101 KIAS Landing Climb Speed .........................................95 KIAS VREF .....................................................................95 KIAS

TM

PHENOM 100




AFM

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6

APPROACH FLAPS 1 AND LANDING FLAPS 2 ENGINE ANTI-ICE OFF/ON – WINGSTAB OFF

PW617F-E ENGINES


FLAPS 1 FLAPS 2 WEIGHT

(lb)


7100 100 91

7500 102 92

7900 104 94

8300 107 97

8700 109 99

9100 111 101

9500 114 104

9900 116 106



TM



AFM

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6

APPROACH FLAPS 2 AND LANDING FLAPS FULL ENGINE ANTI-ICE OFF/ON – WINGSTAB OFF

PW617F-E ENGINES


FLAPS 2 FLAPS FULL WEIGHT

(lb)


7100 92 91

7500 94 91

7900 96 91

8300 99 92

8700 101 95

9100 103 97

9500 104 99

9900 106 101


TM

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AFM

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6

APPROACH FLAPS 1 AND LANDING FLAPS 2 ENGINE ANTI-ICE ON – WINGSTAB ON (SWPS ICE SPEED)

PW617F-E ENGINES


(lb) SPEED – KIAS

7100 110

7500 113

7900 116

8300 119

8700 121

9100 124

9500 127

9900 130



TM



AFM

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6

APPROACH FLAPS 2 AND LANDING FLAPS FULL ENGINE ANTI-ICE ON – WINGSTAB ON (SWPS ICE SPEED)

PW617F-E ENGINES


(lb) SPEED – KIAS

7100 105

7500 108

7900 111

8300 114

8700 117

9100 119

9500 122

9900 125


TM

PHENOM 100




AFM

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6

LANDING DATA LANDING TECHNIQUE The landing performance data in this manual is based on the following conditions:

- Steady three degree angle approach at VREF in landing configuration;

- VREF airspeed maintained at runway threshold; - Idle thrust established at runway threshold; - Attitude maintained until MLG touchdown; - Maximum brake applied immediately after MLG touchdown; - Antiskid system operative.

MAXIMUM LANDING WEIGHT CLIMB LIMITED

The maximum landing weight for altitude and temperature, in compliance with the airworthiness climb requirements, is shown in the Maximum Landing Weight Climb Limited tables in function of the temperature and altitude and according to the anti-ice system condition. When landing weight is not limited by the climb requirements it will be structural limited and the most limiting weights in the table are codified as follows:

- (A) Approach Climb Limited - (L) Landing Climb Limited - (E) Enroute Climb Limited - (S) Structural-Maximum Landing Weight Limited

NOTE: For airplanes Pre-Mod. SB 500-27-0001, the WINGSTAB OFF performance data must be used according to AD 2009-05-06 (action 6).

EXAMPLE Given:

Airport Pressure Altitude..................................... 2000 ft Approach Flaps .................................................. 2 Landing Flaps ..................................................... FULL Engine Anti-Ice ................................................... OFF Wingstab............................................................. OFF Temperature ....................................................... 20°C

Determine:

Maximum Landing Weight .................................. 9766 lb


TM



AFM

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6


PW617F-E ENGINES


ALTITUDE TEMP (°C)

-1000 ft 0 ft 1000 ft 2000 ft 3000 ft 4000 ft -40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9358 (A) 45 9766 (S) 9766 (S) 9766 (S) 9667 (E) - - 50 9766 (S) 9766 (S) - - - -

TM

PHENOM 100




AFM

-265

6


PW617F-E ENGINES


ALTITUDE TEMP (°C)

5000 ft 6000 ft 7000 ft 8000 ft 9000 ft 10000 ft -40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9623 (A) 9409 (A) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9632 (A) 9415 (A) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9643 (A) 9424 (A) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9651 (A) 9431 (A) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9660 (A) 9437 (A) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9671 (A) 9444 (A) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9680 (A) 9451 (A) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9689 (A) 9457 (A) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9698 (A) 9464 (A) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9704 (A) 9471 (A) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9704 (A) 9468 (A) 15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9693 (A) 9415 (A) 20 9766 (S) 9766 (S) 9766 (S) 9759 (A) 9321 (A) 8889 (A) 25 9766 (S) 9766 (S) 9647 (A) 9215 (A) 8781 (A) 8364 (A) 30 9766 (S) 9526 (A) 9091 (A) 8688 (A) 8304 (A) 7894 (A) 35 9415 (A) 8997 (A) 8611 (A) - - - 40 8926 (A) - - - - -


TM



AFM

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6




ALTITUDE TEMP (°C)

-1000 ft 0 ft 1000 ft 2000 ft 3000 ft 4000 ft -40 9766 (S) 9766 (S) 9766 (S) 9757 (A) 9424 (A) 9094 (A) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9433 (A) 9102 (A) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9442 (A) 9111 (A) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9451 (A) 9120 (A) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9457 (A) 9129 (A) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9466 (A) 9138 (A) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9473 (A) 9144 (A) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9482 (A) 9153 (A) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9488 (A) 9162 (A) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9490 (A) 9164 (A) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9482 (A) 9158 (A) 15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9473 (A) 9151 (A) 20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9444 (A) 9120 (A) 25 9766 (S) 9766 (S) 9766 (S) 9563 (A) 9191 (A) 8814 (A) 30 9766 (S) 9766 (S) 9504 (A) 9096 (A) 8717 (A) 8351 (A) 35 9766 (S) 9396 (A) 8994 (A) 8615 (A) 8254 (A) 7901 (A) 40 9239 (A) 8884 (A) 8523 (A) 8159 (A) 7813 (A) 7489 (A) 45 8767 (A) 8434 (A) 8079 (A) 7736 (A) - - 50 8318 (A) 8000 (A) - - - -

TM

PHENOM 100




AFM

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6




ALTITUDE TEMP (°C)

5000 ft 6000 ft 7000 ft 8000 ft 9000 ft 10000 ft -40 8767 (A) 8481 (A) 8207 (A) 7943(A) 7683 (A) 7517 (A) -35 8776 (A) 8487 (A) 8216 (A) 7949(A) 7689 (A) 7522 (A) -30 8783 (A) 8496 (A) 8223 (A) 7958 (A) 7698 (A) 7528 (A) -25 8792 (A) 8503 (A) 8232 (A) 7965 (A) 7705 (A) 7533 (A) -20 8800 (A) 8512 (A) 8238 (A) 7971 (A) 7711 (A) 7537 (A) -15 8807 (A) 8518 (A) 8245 (A) 7978 (A) 7718 (A) 7544 (A) -10 8814 (A) 8525 (A) 8251 (A) 7987 (A) 7725 (A) 7548 (A) -5 8822 (A) 8531 (A) 8260 (A) 7993 (A) 7733 (A) 7553 (A) 0 8829 (A) 8540 (A) 8267 (A) 8000 (A) 7740 (A) 7559 (A) 5 8833 (A) 8547 (A) 8271 (A) 8004 (A) 7744 (A) 7564 (A) 10 8831 (A) 8540 (A) 8267 (A) 8002 (A) 7742 (A) 7559 (A) 15 8829 (A) 8536 (A) 8260 (A) 7996 (A) 7736 (A) 7515 (A) 20 8789 (A) 8439 (A) 8108 (A) 7793 (A) 7447 (A) 7105 (A) 25 8423 (A) 8055 (A) 7707 (A) 7374 (A) 7050 (A) 6796 (A) 30 7978 (A) 7616 (A) 7279 (A) 6999 (A) 6763 (A) 6613 (A) 35 7530 (A) 7204 (A) 6953 (A) - - - 40 7147 (A) - - - - -


TM



AFM

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6

MAXIMUM LANDING WEIGHT – CLIMB LIMITED APPROACH FLAPS 1 – LANDING FLAPS 2 ENGINE ANTI-ICE ON – WINGSTAB OFF

PW617F-E ENGINES


ALTITUDE TEMP (°C)

-1000 ft 0 ft 1000 ft 2000 ft 3000 ft 4000 ft -40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9486 (E) 35 9766 (S) 9766 (S) 9766 (S) 9733 (E) 9316 (E) 8911 (E) 40 9766 (S) 9766 (S) 9541 (E) 9129 (E) 8732 (E) 8357 (E) 45 9766 (S) 9347 (E) 8930 (E) 8538 (E) - - 50 9142 (E) 8741 (E) - - - -

TM

PHENOM 100




AFM

-265

6

MAXIMUM LANDING WEIGHT – CLIMB LIMITED APPROACH FLAPS 1 – LANDING FLAPS 2 ENGINE ANTI-ICE ON – WINGSTAB OFF

PW617F-E ENGINES


ALTITUDE TEMP (°C)

5000 ft 6000 ft 7000 ft 8000 ft 9000 ft 10000 ft -40 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9587 (A) 9378 (A) -35 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9598 (A) 9385 (A) -30 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9607 (A) 9391 (A) -25 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9618 (A) 9400 (A) -20 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9627 (A) 9407 (A) -15 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9636 (A) 9413 (A) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9645 (A) 9422 (A) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9656 (A) 9429 (A) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9665 (A) 9435 (A) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9673 (A) 9442 (A) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9669 (A) 9358 (E) 15 9766 (S) 9766 (S) 9766 (S) 9651 (E) 9219 (E) 8803 (E) 20 9766 (S) 9766 (S) 9457 (E) 9049 (E) 8659 (E) 8269 (E) 25 9673 (E) 9263 (E) 8871 (E) 8496 (E) 8126 (E) 7742 (E) 30 9078 (E) 8703 (E) 8337 (E) 7976 (E) 7616 (E) 7268 (E) 35 8525 (E) 8163 (E) 7804 (E) - - - 40 7982 (E) - - - - -


TM



AFM

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6




ALTITUDE TEMP (°C)

-1000 ft 0 ft 1000 ft 2000 ft 3000 ft 4000 ft -40 9766 (S) 9766 (S) 9766 (S) 9717 (A) 9387 (A) 9056 (A) -35 9766 (S) 9766 (S) 9766 (S) 9726 (A) 9396 (A) 9065 (A) -30 9766 (S) 9766 (S) 9766 (S) 9735 (A) 9402 (A) 9076 (A) -25 9766 (S) 9766 (S) 9766 (S) 9746 (A) 9411 (A) 9085 (A) -20 9766 (S) 9766 (S) 9766 (S) 9755 (A) 9420 (A) 9094 (A) -15 9766 (S) 9766 (S) 9766 (S) 9764 (A) 9429 (A) 9102 (A) -10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9435 (A) 9109 (A) -5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9444 (A) 9118 (A) 0 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9451 (A) 9127 (A) 5 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9455 (A) 9131 (A) 10 9766 (S) 9766 (S) 9766 (S) 9766 (S) 9446 (A) 9127 (A) 15 9766 (S) 9766 (S) 9766 (S) 9764 (A) 9437 (A) 9120 (A) 20 9766 (S) 9766 (S) 9766 (S) 9735 (A) 9356 (A) 8986 (A) 25 9766 (S) 9766 (S) 9678 (A) 9257 (A) 8869 (A) 8487 (A) 30 9766 (S) 9528 (A) 9133 (A) 8752 (A) 8381 (A) 8033 (A) 35 9409 (A) 9021 (A) 8642 (A) 8278 (A) 7936 (A) 7605 (A) 40 8893 (A) 8538 (A) 8194 (A) 7846 (A) 7524 (A) 7220 (A) 45 8441 (A) 8104 (A) 7773 (A) 7451 (A) - - 50 8004 (A) 7691 (A) - - - -

TM

PHENOM 100




AFM

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6




ALTITUDE TEMP (°C)

5000 ft 6000 ft 7000 ft 8000 ft 9000 ft 10000 ft -40 8732 (A) 8445 (A) 8174 (A) 7912 (A) 7656 (A) 7493 (A) -35 8741 (A) 8454 (A) 8183 (A) 7921 (A) 7665 (A) 7497 (A) -30 8750 (A) 8463 (A) 8190 (A) 7927 (A) 7672 (A) 7504 (A) -25 8758 (A) 8470 (A) 8198 (A) 7936 (A) 7678 (A) 7508 (A) -20 8767 (A) 8478 (A) 8205 (A) 7943 (A) 7685 (A) 7515 (A) -15 8774 (A) 8485 (A) 8214 (A) 7949 (A) 7694 (A) 7519 (A) -10 8783 (A) 8492 (A) 8221 (A) 7958 (A) 7700 (A) 7526 (A) -5 8792 (A) 8501 (A) 8227 (A) 7965 (A) 7707 (A) 7530 (A) 0 8798 (A) 8507 (A) 8236 (A) 7971 (A) 7713 (A) 7535 (A) 5 8805 (A) 8516 (A) 8243 (A) 7978 (A) 7720 (A) 7542 (A) 10 8803 (A) 8514 (A) 8240 (A) 7976 (A) 7720 (A) 7248 (A) 15 8800 (A) 8512 (A) 8236 (A) 7925 (A) 7592 (A) 6900 (A) 20 8589 (A) 8207 (A) 7855 (A) 7511 (A) 7162 (A) - 25 8101 (A) 7747 (A) 7414 (A) 7092 (A) 6856 (A) - 30 7678 (A) 7332 (A) 7037 (A) 6810 (A) - - 35 7255 (A) 6988 (A) 6768 (A) - - - 40 6953 (A) - - - - -


TM



AFM

-265

6




ALTITUDE TEMP (°C)



ALTITUDE TEMP (°C)


TM

PHENOM 100




AFM

-265

6




ALTITUDE TEMP (°C)



ALTITUDE TEMP (°C)



TM



AFM

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6

UNFACTORED LANDING DISTANCES

Unfactored landing distance is the actual distance to land the airplane on a zero slope, ISA temperature, dry runway, from a point 50 ft above runway threshold, at VREF speed, to complete stop using only the brakes as deceleration device.

NORMAL OPERATION

The required landing distance for dispatch is the unfactored landing distance increased by a factor according to the operating regulations.

EXAMPLE

Given: Airplane Landing Weight.....................................8700 lb Airport Pressure Altitude.....................................2000 ft Engine Anti-Ice....................................................OFF Wingstab .............................................................OFF Flaps ...................................................................2 Wind....................................................................10 kt

Determine:

Unfactored Landing Distance .............................2573 ft

TM

PHENOM 100




AFM

-265

6


PW617F-E ENGINES


WIND Weight

(lb)



WIND Weight

(lb)




TM



AFM

-265

6


PW617F-E ENGINES


WIND Weight

(lb)



WIND Weight

(lb)



TM

PHENOM 100




AFM

-265

6


PW617F-E ENGINES


WIND Weight

(lb)



WIND Weight

(lb)




TM



AFM

-265

6


PW617F-E ENGINES


WIND Weight

(lb)



WIND Weight

(lb)



TM

PHENOM 100




AFM

-265

6


PW617F-E ENGINES


WIND Weight

(lb)



WIND Weight

(lb)




TM



AFM

-265

6


PW617F-E ENGINES


WIND Weight

(lb)



WIND Weight

(lb)



TM

PHENOM 100




AFM

-265

6




WIND Weight

(lb)



WIND Weight

(lb)




TM



AFM

-265

6




WIND Weight

(lb)



WIND Weight

(lb)



TM

PHENOM 100




AFM

-265

6




WIND Weight

(lb)



WIND Weight

(lb)




TM



AFM

-265

6




WIND Weight

(lb)



WIND Weight

(lb)



TM

PHENOM 100




AFM

-265

6




WIND Weight

(lb)



WIND Weight

(lb)




TM



AFM

-265

6




WIND Weight

(lb)



WIND Weight

(lb)



TM

PHENOM 100


Supplement 3 Traffic Alert and CollisionAvoidance System II (TCAS II)


AFM

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SUPPLEMENT 3

TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM II

(TCAS II)

TABLE OF CONTENTS

Block Page

General ..............................................................................S3-00 ....... 03

Limitations..........................................................................S3-05 ....... 01



Performance ......................................................................S3-10 ....... 06

Weight and Balance...........................................................S3-10 ....... 06


TM

Traffic Alert and Collision Avoidance System II (TCAS II)

Supplement 3


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GENERAL This Supplement is part of, and must be placed in the basic Airplane Flight Manual for all PHENOM 100 equipped with TCAS II mode S transponder.

For limitations, operational procedures or performance information not contained in this Supplement, consult the basic AFM. TCAS II system description is in the EMBRAER Pilot's Operating Handbook.

TCAS II is an airborne collision avoidance and traffic situation display system designed to identify and display potential collision traffic threats, and issue advisories maneuvers guidance to the pilots.

The TCAS II additional information to the ATC system enhances spatial awareness of the airplane.

For further information refer to EMBRAER ProdigyTM Flight Deck 100 Pilot's guide. The Pilot's Guide reflects the operation of system software version 0734.19 for the PHENOM 100.


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LIMITATIONS The following limitations are applicable to the Traffic Alert and Collision Avoidance System II (TCAS II):

− Deviation from ATC assigned altitude is authorized only to the extent necessary to comply with a TCAS Resolution Advisory (RA).

− Maneuver must not be based solely on information presented in the traffic display.


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NORMAL PROCEDURES

TCAS II TEST To test the system:

On the PFD: XPDR/TFC Softkey ....................................... PRESS TCAS Softkey ................................................ PRESS TEST Softkey ................................................ PRESS

"TCAS TEST PASS" sounds indicating the system is operational.

NOTE: The test mode does not affect normal TCAS operation, provided the selected transponder remains in normal operation during test cycle. Should a TA or RA occur during the test sequence, the test aborts, and the advisory is announced and displayed.

AFTER START Transponder/TCAS II............................................... SET

Set CODE and verify transponder in ALT mode and TCAS II in STBY mode.

NOTE: On ground, transponder in ALT mode does not transmit.

TCAS TRAFFIC ADVISORY (TA) The pilot must not initiate evasive maneuvers using Traffic Advisory (TA) information only, without visually sighting conflicting traffic.

The traffic display and advisories are intended for assistance in visually locating the indicated conflicting traffic.


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TCAS RESOLUTION ADVISORY (RA) Compliance with a Resolution Advisory (RA) is necessary unless the pilot considers it unsafe to do so, or unless the pilot has information about the cause of the RA and can maintain safe separation (visual acquisition of, and safe separation from, a nearby airplane on a parallel approach).

WARNING: IT IS POSSIBLE IN SOME CASES TO HAVE INSUFFICIENT AIRPLANE PERFORMANCE TO FOLLOW THE TCAS II COMMAND WITHOUT FLYING INTO STALL WARNING OR BUFFET. CONDITIONS WHERE THIS MAY OCCUR INCLUDE:

• BANK ANGLE IN EXCESS OF 15 DEGREES.

• ENGINE INOPERATIVE.

• OPERATIONS AT AIRPORTS ABOVE 5300 FT MSL OR TEMPERATURES GREATER THAN ISA + 28°C (ISA + 50°F).

• SPEEDS BELOW NORMAL OPERATING SPEEDS.

• FAILURE TO CONFIGURE THE AIRPLANE TO GO-AROUND FOLLOWING A CLIMB RA IN LANDING CONFIGURATION.

• FAILURE TO ADVANCE THRUST LEVERS TO MAX CONTINOUS THRUST FOLLOWING A CLIMB RA AT REDUCED THRUST.

• CONFIGURATIONS THAT REDUCE PERFORMANCE (E.G. GEAR DOWN).

• BUFFET MARGIN LESS THAN 0.3G.

WARNING: IF STALL WARNING OCCURS DURING AN RA MANEUVER, IMMEDIATELY ABANDON THE RA AND EXECUTE STALL RECOVERY PROCEDURES. TCAS II WILL CONTINUE TO PROVIDE RA WARNINGS DURING STALL WARNING AND RECOVERY PROCEDURE.


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WARNING: IF HIGH SPEED BUFFET IS ENCOUNTERED WHEN INITIALLY RESPONDING TO A RA, RELAX PITCH FORCE AS NECESSARY TO REDUCE BUFFET, BUT STILL CONTINUE TO MANEUVER.

WARNING: NONCOMPLIANCE WITH A CROSSING RA, BY ONE AIRPLANE MAY RESULT IN REDUCED VERTICAL SEPARATION; THEREFORE, SAFE HORIZONTAL SEPARATION MUST ALSO BE ASSURED BY VISUAL MEANS.

CAUTION: UNDER CERTAIN CONDITIONS, COMMANDED MANEUVERS MAY SIGNIFICANTLY REDUCE STALL MARGINS WITH THE NEED TO RESPECT THE STALL WARNING WHERE THIS MAY OCCUR.

CAUTION: ONCE A NON-CROSSING RA HAS BEEN ISSUED, SAFE OPERATION COULD BE COMPROMISED IF CURRENT VERTICAL SPEED IS CHANGED, EXCEPT AS NECESSARY TO COMPLY WITH THE RA. THIS IS BECAUSE TCAS II TO TCAS II COORDINATION MAY BE IN PROGRESS WITH THE INTRUDER AIRPLANE, AND ANY CHANGE IN VERTICAL SPEED THAT DOES NOT COMPLY WITH RA MAY NEGATE EFFECTIVENESS OF THE OTHER AIRPLANE'S COMPLIANCE WITH ITS RA.



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NOTE: - The consequences of not following an RA may result in additional RA's in which aural alert and visual annunciations may not agree with each other.

- Using every available means, clear the airspace into which you are going to maneuver. If needed, promptly and smoothly adjust the airplane's pitch to fly into the green rectangle (if displayed), and fly out of the red trapezoidal shaped avoidance zone(s). This should require no more than 0.75 g to 1.25 g maneuver (± 0.25 g).

- Evasive maneuvering should be limited to the minimum required to comply with the RA. Excessive responses to RAs are not desirable or appropriate because of the other potential traffic conflicts and ATC consequences. From level flight, proper response to a TCAS RA typically results in an overall altitude deviation of 300 ft to 500 ft to resolve a traffic conflict.

- If a CLIMB RA is issued with the airplane in the landing configuration, a normal go-around should be initiated including the appropriate thrust increase and configuration change.

- Initiating go-around procedure for a CLIMB RA does not mandate a missed approach. It is intended to ensure the airplane is properly configured for the TCAS II maneuver. In most cases, the TCAS II event will be resolved with only minor deviation to the intended flight path, and sufficient time and altitude may exist to recover safely to the desired flight path.

- The threat airplane track or altitude information can be lost during an RA. If so, the RA will terminate without a "Clear of Conflict" annunciation.

- The pilot should promptly return to the previous ATC clearance after the TCAS II voice message "Clear of Conflict" is announced.


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NOTE: - An immediate smooth response to a RA is required to obtain maximum separations. TCAS II algorithms are based on the pilot initiating the initial maneuver within 5 seconds of the RA and within 2 1/2 seconds for additional corrective RA's (increases or reversals). Any delay in responding to RA's will reduce the separations provided, because of these requirements, all RA responses must be hand-flown and not with the autopilot.

- Unnecessary RAs can be issued by TCAS II when other airplane are operating at an altitude adjacent to the one that has been assigned to the climbing or descending TCAS airplane. When climbing or descending in an environment where these unnecessary advisories are considered likely to occur (based on either airspace design, air traffic communications, visual acquisition or utilization of traffic displays), a reduction in vertical velocity is recommended until reaching the assigned altitude. As appropriate, the vertical velocity should be reduced to a rate between 500 and 1500 ft/min, when approaching an altitude between 1000 and 2000 ft above or below the altitude assigned in the ATC instruction or clearance.

- After deviating from an ATC clearance or instructions in response to a RA, notify ATC of the deviation as soon as possible.

- At ON mode or ALTITUDE mode, TCAS II switches to STBY mode.

- Resolution advisory vertical guidance will only be issued when the airplane is at or above 1000 ft.

- TCAS II may not function at distances less than 900 ft.

- When below 1000 ft, TCAS II will automatically switch into TA only mode.

- INCREASE CLIMB RAs are inhibited for flaps 1, 2, 3, and FULL position below 2000 ft.



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NOTE: - DESCEND RAs are inhibited below 1200 ft while climbing and below 1000 ft while descending.

- INCREASE DESCENT RAs are inhibited below 1450 ft.

- Voice messages are inhibited below 600 ft while climbing and below 400 ft while descending.

- During TAWS Warnings, TCAS II switches automatically into a TA only mode with aural annunciation inhibited. In this mode, RAs are not issued and current RAs become TAs. The TCAS II remains in TA only mode for 10 seconds after the TAWS warning is removed. TCAS II aural annunciations are enabled immediately following the removal of TAWS warning aural annunciation.


TCAS FAIL TCAS has failed. Confirm that the transponder is operating normally.

ELECTRICAL EMERGENCY TCAS II is inoperative.

DC BUS 1 OFF TCAS II is inoperative.

PERFORMANCE Performance Data presented in the AFM remain unchanged.

WEIGHT AND BALANCE Weight and Balance Data presented in the AFM remain unchanged.

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Supplement 4 Terrain Awareness andWarning System (TAWS)


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SUPPLEMENT 4

TERRAIN AWARENESS AND WARNING SYSTEM (TAWS)

TABLE OF CONTENTS

Block Page

General ..............................................................................S4-00 ....... 03

Limitations..........................................................................S4-05 ....... 01



Performance ......................................................................S4-10 ....... 03



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Terrain Awareness and Warning System (TAWS)

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GENERAL This Supplement is part of, and must be placed in the basic Airplane Flight Manual for all PHENOM 100 equipped with TAWS.

For limitations, operational procedures or performance information not contained in this Supplement, consult the basic AFM. TAWS system description is in the EMBRAER Pilot's Operating Handbook.

TAWS is intended to provide pilots with aural and visual alert aids aimed at preventing Controlled Flight Into Terrain (CFIT) accident through increased terrain awareness.

There are two available TAWS system for the PHENOM 100, TAWS-B and TAWS-A. This Supplement information is valid for both TAWS systems and wherever necessary, systems differentiation will be noted.

For further information refer to EMBRAER ProdigyTM Flight Deck 100 Pilot's guide. The Pilot's Guide reflects the operation of system software version 0734.19 for the PHENOM 100.


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LIMITATIONS Terrain Awareness and Warning System displays terrain and obstructions relative to the altitude of the airplane. The following applies:

− Navigation must not be predicated upon the use of the TAWS.

NOTE: The terrain display is intended to serve as a situational awareness tool only. It may not provide either the accuracy or fidelity, or both, on which to solely base decisions and plan maneuvers to avoid terrain or obstacles.

− To avoid giving unwanted alerts, the TAWS must be inhibited when landing at an airport that is not included in the airport database.

− Pilots are authorized to deviate from their current ATC clearance only to the extent necessary to comply with TAWS warnings.

− Terrain database coverage is worldwide. However the Terrain data is not displayed when the airplane latitude is greater than 75°N or 60°S.

− The MSL altitude indication on upper right-hand corner of terrain awareness page must not be used for navigation, especially for maintaining an assigned ATC altitude.

− ILS approaches with manually overridden frequency or course information are prohibited only for airplanes equipped with TAWS-A and G1000 system version 0734.24.


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NORMAL PROCEDURES When a TAWS alert occurs, use the flight controls and thrust as necessary to correct the airplane attitude, flight path and configuration, according to the voice message presented, to provide terrain clearance.

WARNING: IF A TERRAIN AWARENESS WARNING OCCURS, IMMEDIATELY INITIATE AND CONTINUE A CLIMB THAT WILL PROVIDE MAXIMUM TERRAIN CLEARANCE UNTIL ALL ALERTS CEASE. ONLY VERTICAL MANEUVERS ARE RECOMMENDED, UNLESS OPERATING IN VISUAL METEOROLOGICAL CONDITIONS (VMC), AND/OR THE PILOT DETERMINES, BASED ON AVAILABLE INFORMATION, THAT TURNING IN ADDITION TO THE VERTICAL ESCAPE MANEUVER IS A SAFER COURSE OF ACTION.

CAUTION: WHEN A TERRAIN AWARENESS CAUTION OCCURS, VERIFY THE AIRPLANE FLIGHT PATH AND CORRECT IT IF REQUIRED. IF IN DOUBT, PERFORM A CLIMB UNTIL THE CAUTION ALERT CEASES.

NOTE: It is the operator's responsibility to ensure that the database in use is valid for the planned route.


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NUISANCE TAWS ALARMS (TAWS-A ONLY) FLAP OVRD Button .................................................PRESS

NOTE: For the DITCHING and FORCED LANDING Procedures, override TAWS flap signal to avoid nuisance TAWS alarms when the flaps are not in landing configuration.

INCOMPLETE TERRAIN DATABASE TERR INHIB Button .................................................PRESS

NOTE: - Landing at an airport not included in the terrain database will cause nuisance alarms if not inhibited.

- For TAWS-B, PDA and FLTA alerts may be inhibited through INHIBIT Softkey on MFD.

ELECTRICAL EMERGENCY TAWS-A is inoperative.

DC BUS 1 OFF TAWS-A is inoperative.

DITCHING (TAWS-A ONLY) During descent:

FLAP OVRD Button ............................................PRESS

FORCED LANDING (TAWS-A ONLY) During descent:

FLAP OVRD Button ............................................PRESS

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Supplement 5 Operation with AirplanesEquipped with Ground Spoilers


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SUPPLEMENT 5

OPERATION WITH AIRPLANES EQUIPPED WITH GROUND SPOILERS

TABLE OF CONTENTS

Block Page

General ..............................................................................S5-00 ....... 03

Limitations..........................................................................S5-10 ....... 01



Performance ......................................................................S5-10 ....... 03



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Operation with Airplanes Equipped with Ground Spoilers

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GENERAL This Supplement is part of, and must be placed in the basic Airplane Flight Manual for all PHENOM 100 equipped with Ground Spoilers.

The information herein presented replaces or complements the equivalent data in the basic AFM.

For limitations, operational procedures or performance information not contained in this Supplement, consult the basic AFM.


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LIMITATIONS Operation of Ground Spoilers with airplanes Pre-Mod. SB 500-27-0003 (Supplement 2) is prohibited.

NORMAL PROCEDURES

EXTERNAL INSPECTION Left and Right Spoiler Panels .................................. CONDITION

BEFORE TAKEOFF GSPLR OPEN Light................................................. NOT

ILLUMINATED


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INADVERTENT GROUND SPOILER DEPLOYMENT INDICATION: GSPLR OPEN Light illuminated. On ground:

Do not takeoff.

In flight: Spoiler Circuit Breaker (A16) ..............................PULL

If Ground Spoilers do not close: LAND AS SOON AS PRACTICAL.

Recommended Airspeed ...............................150 KIAS

Landing configuration: LDG GEAR Lever .....................................DN Flaps .........................................................3 Airspeed....................................................VREF FULL + 10 KIAS

MINIMUM

CAUTION: • TO DETERMINE THE MINIMUM LANDING DISTANCE, MULTIPLY THE FULL FLAPS UNFACTORED LANDING DISTANCE BY 1.25.

• AVOID CROSSWINDS.

ELECTRICAL EMERGENCY Ground Spoilers are inoperative.

DC BUS 1 OFF Ground Spoilers are inoperative.

EMERGENCY BUS OFF Ground Spoilers Indication Light is inoperative.

HYDRAULIC LOW PRESSURE Ground Spoilers are inoperative.

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Supplement 6 Airplanes with Enhanced TakeoffThrust Configuration


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SUPPLEMENT 6

AIRPLANES WITH ENHANCED TAKEOFF THRUST CONFIGURATION

TABLE OF CONTENTS

Block Page

General ..............................................................................S6-00 ....... 03

Limitations..........................................................................S6-15 ....... 01



Performance ......................................................................S6-15 ....... 02



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GENERAL This Supplement is part of, and must be placed in the basic Airplane Flight Manual for all PHENOM 100 with Enhanced Takeoff Thrust configuration.

Airplanes with Enhanced Takeoff Thrust configuration use 100% of maximum certified thrust in case of an OEI condition during takeoff if ATR is selected ON.

The information herein presented replaces or complements the equivalent data in the basic AFM.

For limitations, operational procedures or performance information not contained in this Supplement, consult the basic AFM.


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ANAC APPROVED S6-15 REVISION 9 code 01 Page 1 A

FM-2

656

LIMITATIONS Limitations Data presented in the AFM remain unchanged.

NORMAL PROCEDURES Normal Procedures Data presented in the AFM remain unchanged.

EMERGENCY AND ABNORMAL PROCEDURES Emergency and Abnormal Procedures Data presented in the AFM remain unchanged.


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PERFORMANCE



The software OP500FA617FE version 7.1 allows performance calculations for airplanes with one of the following configurations:

- PHENOM 100.

- PW617F-E engines.

- FADEC Software 5.3 and on.

- Placard "Enhanced Takeoff Thrust OPERA Type A".

Or

- PHENOM 100.

- PW617F-E engines.

- FADEC Software up to 4.0.

- Post-Mod. SB 500-27-0003 or with an equivalent modification factory incorporated.






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NOTE: - OPERA provides guidance information when operating from contaminated runways.


VALID VERSIONS


AIRPLANE SERIAL

NUMBER 500:

AIRPLANE CONFIGURATION AFM LOCATION

VALID OPERA

VERSIONS

00005 thru 00118; 00121;

00123 thru 00131; 00133; 00134; 00136;

00137; 00139 thru

00144; 00148; 00149;

00152 thru 00154

Post-Mod. SB 500-27-0003.

00120; 00122; 00132; 00135;

00138; 00145 thru

00147; 00150; 00151;

00155 thru 00216

ALL

00218 and on Enhanced Takeoff Thrust

OPERA Type A cockpit placard installed.

Supplement 6 7.1


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TAKEOFF DATA SIMPLIFIED TAKEOFF ANALYSIS TABLES

ATR OFF takeoff performance for airplanes equipped with Enhanced Takeoff Thrust is the same of those equipped with Standard Takeoff Thrust. Thus, takeoff performance tables available in basic AFM can be used by both configurations if ATR is selected OFF.
