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S2R-H80 Single & Dual Cockpit

AIRPLANE FLIGHT MANUAL

AFM H8001 SINGLE & DUAL COCKPIT Revision A

Page xiv

FAA APPROVAL DATE: 8/05/2014

GLOSSARY OF TERMS & ABBREVIATIONS

AFT

To the Rear

C.G.

Center of Gravity

CAP

Capacity

Inertial Multiplier: 1G = Weight

G LIMITS

Maximum Permitted G’s

GAL

Gallons

GEN

Generator

IAS

Indicated Air Speed

IFR

Instrument Flight Rules

ITT

Inter-Turbine Temperature

LBS

Pounds

MAX

Maximum

MCAS

Miles Calibrated Air Speed

MPH

Miles Per Hour

Gas Generator RPM

Propeller RPM

OAT

Outside Air Temperature

PRES

Pressure

PSI

Pounds per Square Inch

– Absolute

PSIG

Pounds per Square Inch

– Gage

RPM

Revolutions per Minute

SHP

Shaft Horsepower

TEMP

Temperature

Maneuvering Speed

Maximum Flaps Extend Speed

VFR

Visual

Flight Rules

Never Exceed Speed

Maximum Structural Cruising Speed

Summary of Contents for S2R-H80

Page 1: ......

Page 2: ...not intended for Single Cockpit Single Control Aircraft SECTION 1 11 2 d Corrected placard to UNLESS HEADED OUT OF THE WIND Per FAA request Added placard dd ee and ff for new fuel filter bypass circui...

Page 3: ......

Page 4: ...TUDE LIMITATIONS 12 000 MSL 6 1 5 MAXIMUM WEIGHT AND CENTER OF GRAVITY LIMITS 6 1 6 USING FORWARD BALLAST TO MANAGE AFT EMPTY CG POSITION FOR THE DUAL CONFIGURATION 7 1 7 HIGH ALTITUDE AIRPORT OPERATI...

Page 5: ...FORCED LANDINGS 40 3 15 EMERGENCY EGRESS 41 3 16 ELEVATOR TRIM RUDDER CENTERING SPRING FAILURE 41 3 17 NOSE BAGGAGE DOOR OPENING IN FLIGHT 41 3 18 LOSS OF HOPPER RINSE BALLAST IN THE DUAL 41 3 19 SUSP...

Page 6: ...9 15 9 3 19 15 10 9 03 15 11 3 19 15 12 3 19 15 13 3 19 15 14 3 19 15 SECTION 2 NORMAL PROCEDURES 15 3 19 15 16 3 19 15 17 3 19 15 18 3 19 15 19 3 19 15 20 3 19 15 21 3 19 15 22 3 19 15 23 3 19 15 24...

Page 7: ...AGES PAGE FAA APPROVAL DATE PAGE FAA APPROVAL DATE AFM H8001 SINGLE DUAL COCKPIT Revision C Page vii FAA APPROVAL DATE 09 03 2015 60 8 05 14 61 8 05 14 62 8 05 14 63 8 05 14 64 8 05 14 65 8 05 14 SECT...

Page 8: ...imited to those normally performed in special purpose operations and approved by Administrator The S2R H80 Turbo Thrush is approved for day and night VFR flight Flight into or near thunderstorms or in...

Page 9: ...nearest suitable landing area without delay The primary consideration is to ensure the survival of the pilot s Land as soon as Practicable This term is defined as landing at a suitable landing area T...

Page 10: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page x FAA APPROVAL DATE 8 05 2014 3 VIEW OF S2R H80 SINGLE COCKPIT...

Page 11: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page xi FAA APPROVAL DATE 8 05 2014 DIMENSIONAL 3 VIEW OF S2R H80 SINGLE COCKPIT...

Page 12: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page xii FAA APPROVAL DATE 8 05 2014 3 VIEW OF S2R H80 DUAL COCKPIT...

Page 13: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page xiii FAA APPROVAL DATE 8 05 2014 DIMENSIONAL 3 VIEW H80 DUAL COCKPIT...

Page 14: ...Indicated Air Speed IFR Instrument Flight Rules ITT Inter Turbine Temperature LBS Pounds MAX Maximum MCAS Miles Calibrated Air Speed MPH Miles Per Hour NG Gas Generator RPM NP Propeller RPM OAT Outsi...

Page 15: ...N TURBO OIL 2380 CASTROL 599 ROYCO TURBINE OIL The purity of filled oil should meet the max grade 8 in accordance with NAS 1638 standard or max grade 11 in accordance with GOST 17216 71 standard POWER...

Page 16: ...000 feet and from 80 MPH to 126 MPH air speed Refer to Section III AMBIENT TEMPERATURE Satisfactory engine cooling has been demonstrated at a temperature of 38 C PROPELLER Hartzell Four Blade Propell...

Page 17: ...on is allowed but special attention must be paid in order to prevent exceeding a limit You may be in a time limited range for example Operating anything in the YELLOW range will cause the indication c...

Page 18: ...ormal Range 34 0 RED Radial Maximum ITT C 0 to 750 GREEN Arc Normal Range 750 780 YELLOW Arc Caution Range 780 RED Radial Maximum TORQUE 0 to 100 GREEN Arc Normal Range 100 to 106 YELLOW Arc Caution R...

Page 19: ...aximum gross weight with flaps up 3 Maneuvering speed VA 158 No full or abrupt control movements above this speed 4 Max Structural Cruising VNO 165 Do not exceed in turbulent air 5 Never Exceed VNE 18...

Page 20: ...T of Datum Forward C G Max Gross Weight 10 500 lbs 28 0 in AFT of Datum Most AFT C G Max Gross Weight 10 500 lbs 30 5 in AFT of Datum Most AFT C G Regardless of Weight 7600 lbs 31 0 in AFT of Datum NO...

Page 21: ...ast tank weight must be adjusted accordingly to maintain an aft CG of not more than 30 5 inches at 10 500 and no more than 31 0 inches at 7 600 with straight line variation between d A baggage compart...

Page 22: ...G OFF IN VISIBLE MOISTURE BELOW 40 F IS PROHIBITED THIS AIRPLANE MUST BE OPERATED AS A RESTRICTED CATEGORY AIRPLANE IN ACCORDANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND THE...

Page 23: ...PACITY JET A JET A1 g Located on upper instrument panel h Located on top of hopper MAX HOPPER CAP 4000 LBS i At the door knockout panel PUSH OUT AND LIFT HINGE PIN FOR EMERGENCY EXIT j Located at each...

Page 24: ...RECEPTACLE r Locate at fuel filter door FUEL FILTER INSPECTION s Locate at smoker tank port centered on inside of filler door SMOKER TANK FILLER PORT t Locate above Pitot Static Buttons STATIC AIR KEE...

Page 25: ...baggage compartment on floor in proximity to compartment door latches NOTE 2 latches 2 placards DO NOT SLAM DOOR PULL LATCH TO CLOSE SEAT LATCHES FLUSH cc Locate inside the baggage compartment and cen...

Page 26: ...WITH THE ENGINE RUNNING UNLESS HEADED OUT OF THE WIND WITH PROPELLER FEATHERED e Located inverted at each door hinge pin PULL HINGE DOWN FOR EMERGENCY EXIT f Locate at each door handle OPEN g Locate...

Page 27: ...TTACH SEAT BELT AND SHOULDER HARNESS AND WEAR A D O T APPROVED OR MIL SPEC HELMET f Locate at the forward side of lower rear door window PUSH OUT AND LIFT HINGE PIN FOR EMERGENCY EXIT g Locate at the...

Page 28: ...Position Lights Red Green White 0 1 0 1 0 1 Landing Light System Left and Right 0 1 0 1 0 1 INSTRUMENTS MVP 50T Glass Panel Engine Monitoring System 1 1 1 1 2 2 NAVIGATION Airspeed Indicator 1 1 1 1...

Page 29: ...AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision B Page 15 FAA APPROVAL DATE 3 19 2015 SECTION 2 NORMAL PROCEDURES 2 1 PRE FLIGHT VISUAL INSPECTION EXTERIOR INSPECTION ROUTE SINGLE AND D...

Page 30: ...FORWARD IDLE STOP e Fuel Condition Lever CUTOFF f Fuel Valve ON g Battery switch ON h Fuel Quantity CHECK i Flaps DOWN j Battery Switch OFF k Elevator Trim Tab SET for takeoff Position 2 a Fuel Quanti...

Page 31: ...on 1 l Battery Switch ON m Emergency Fuel Pump Switch ON Position 4 Cont d f Firewall Fuel Filter DRAIN Position 1 n Battery Switch OFF o Emergency Fuel Pump Switch OFF Position 4 Cont d g Main Wheel...

Page 32: ...der for mounting and security e Oil Quantity CHECK Dipstick and secure cap Position 6 d Wheel Chocks REMOVE e Main Wheel Tire and Brake CHECK for inflation damage and wear f Baggage Compartment CHECK...

Page 33: ...y f Fuel Quantity CHECK and secure cap g Battery Vent CHECK for obstruction h Static Port Opening CHECK for blockage i Rudder Gust Lock REMOVE Position 9 a Empennage CHECK for condition b Struts CHECK...

Page 34: ...r up and should be monitored throughout the flight Buttons operate as follows EXIT Exits out of a field or screen returns the display to the Main Screen and acknowledges blinking cautions and warnings...

Page 35: ...ion and an annunciator will alert the pilot Red Warning and yellow Caution lights above the screen will also blink To acknowledge the alarm and stop the blinking on the MVP 50T display and stop the bl...

Page 36: ...e a Battery Switch ON b Engine display panel ENSURE it passes self test and reset Master Caution and Master Warning lights c Fuel Filter Bypass Light Press to test d Power Lever FORWARD IDLE STOP BETA...

Page 37: ...nter turbine temperature starting limit is not exceeded n Autostart Enable Switch OFF o Oil Pressure CHECK within Green operating range p Oil Temp CHECK within Green operating range prior to accelerat...

Page 38: ...ine driven fuel pumping elements e AutoStart Enable Switch ON f Engine Starter Switch AFT to MOTOR position for 3 seconds and release Dry motoring is automatic and starter will disengage automatically...

Page 39: ...and check for a small decrease in RPM d Reduce power back to idle e Flight Controls Check free and correct f Elevator Tab SET for take off g Flaps Flaps 15 to achieve para 4 5 take off performance h...

Page 40: ...le retaining altitude c Airspeed Maintain best rate of climb speed of 106 MCAS with flaps up Approach Landing Clearing the Runway a Airspeed on Approach 1 3 VS for flap weight configuration See charts...

Page 41: ...h OFF h Battery Switch OFF NOTE During the shutdown be sure that the gas generator decelerates freely Minimum run down time is 18 seconds NOTE Allow the engine to stabilize at idle for a minimum of 5...

Page 42: ...ompliance with Section 2 of GE Aviation Business General Aviation Turboprops Service Bulletin No H80 100 80 0005 R4 can be demonstrated Engine restart within 0 5 minutes If engine restart is planned w...

Page 43: ...the following steps a Perform Dry motoring as described in this document b Wait minimum 5 minutes c Immediately before starting perform Dry motoring as described in this document d Then wait 2 minute...

Page 44: ...he survival of the occupants LAND AS SOON AS PRACTICABLE defined as landing at a suitable landing area The primary consideration is the urgency of the emergency 3 3 EMERGENCY BASIC RULES Three basic r...

Page 45: ...ng ground operations it indicates that the propeller is properly positioned for application of reverse thrust CHIP Indicates presence of metal in the engine lubricating oil LAND AS SOON AS PRACTICABLE...

Page 46: ...parameters FUEL P Fuel pressure low EMERGENCY FUEL PUMP ON Main Fuel Pump OFF LAND AS SOON AS PRACTICABLE OIL P Engine oil pressure low as determined by oil pressure gauge reading confirm MIN OP ligh...

Page 47: ...available Stop as soon as possible and before engine shut down swing tail of aircraft into wind Shut off fuel valve first and then proceed as follows f Power Lever IDLE POSITION g Propeller Lever FEAT...

Page 48: ...llow these procedures a Battery and Generator switches OFF b All other Electrical switches OFF c Circuit Breakers OUT If electric power is essential for flight check to identify and isolate the faulty...

Page 49: ...ure above redline or both d Loss of power following overspeed of gas generator Ng e Engine explosion and flame smoke If it is clear that the engine has failed proceed as follows f Hopper Dump DUMP LEV...

Page 50: ...hat allows smooth increases and decreases of power while not exceeding any engine limitations during acceleration or deceleration In the event the automatic fuel scheduling fails the engine will exper...

Page 51: ...operating range b Power Lever IDLE c Battery Switch ON d Fuel Valve ON e Fuel Condition Lever CUT OFF f Fuel Pump Switch ON g Fuel Pressure Indicator In the Green NOTE Reverse or Beta is not available...

Page 52: ...starting attempt is to be made NOTE Propeller feathering is dependent on circumstances and is at the discretion of the pilot Fine pitch selection will pump air through the engine and therefore increa...

Page 53: ...a takeoff the following steps are advised a Power Control Lever Full Beta or Reverse as necessary b Brakes Apply as permitted by aircraft attitude and directional control c Consider dumping the hopper...

Page 54: ...is to be made on road with a strong cross wind leave flaps retracted f If landing in open field extend flaps and maintain at least 80 MPH IAS until flare for landing g Turn Fuel Valve OFF once air st...

Page 55: ...d rudder centering spring will cause an uneven force of approximately eleven lbs to overcome In either case a failed spring is a flight control failure and the spring must be replaced to continue the...

Page 56: ...formation when the aircraft is loaded to weights in excess of 6000 pounds up to and including 10 500 lbs Refer to C G Limits on page 1 6 of this manual Data provided in this Supplement was obtained by...

Page 57: ...ISA is used in most aircraft operations and is standard throughout the industry Temperature values for this atmosphere are provided below for ease in navigating the following series of performance ch...

Page 58: ...d proceed vertically until the line is encountered Then proceed horizontally to the left to read the value for calibrated airspeed If an Indicated Airspeed is desired from a known Calibrated Airspeed...

Page 59: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 45 FAA APPROVAL DATE 8 05 2014...

Page 60: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 46 FAA APPROVAL DATE 8 05 2014...

Page 61: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 47 FAA APPROVAL DATE 8 05 2014...

Page 62: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 48 FAA APPROVAL DATE 8 05 2014...

Page 63: ...XAMPLE To determine the Stalling Speed at an Aircraft Weight of 8500 pounds enter the Flaps Up chart at that weight Proceed horizontally until encountering the line Then proceed vertically down to rea...

Page 64: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 50 FAA APPROVAL DATE 8 05 2014 STALLING SPEED FLAPS UP CALIBRATED MPH...

Page 65: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 51 FAA APPROVAL DATE 8 05 2014 STALLING SPEED FLAPS 15 CALIBRATED MPH...

Page 66: ...ler turning 1900 RPM versus Percent Torque EXAMPLE Assuming an ISA 30 degree day at a Pressure Altitude of 8000 ft enter the Installed Torque versus Altitude Chart at 8000 ft and proceed horizontally...

Page 67: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 53 FAA APPROVAL DATE 8 05 2014...

Page 68: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 54 FAA APPROVAL DATE 8 05 2014...

Page 69: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 55 FAA APPROVAL DATE 8 05 2014...

Page 70: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 56 FAA APPROVAL DATE 8 05 2014...

Page 71: ...of a headwind the takeoff distance will be less than the distances given Downwind takeoffs will increase the distances given and should be avoided EXAMPLE Assuming a 25 ambient temperature and an air...

Page 72: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 58 FAA APPROVAL DATE 8 05 2014...

Page 73: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 59 FAA APPROVAL DATE 08 05 2014...

Page 74: ...MCAS at Sea Level to 101 MCAS at 10 000 ft EXAMPLE Given an ambient temperature of 20 C a Pressure Altitude of 3000 ft and a Gross Weight of 8000 lbs enter the rate of climb chart for a 10 500 gross...

Page 75: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 61 FAA APPROVAL DATE 08 05 2014 Note Flaps at 15...

Page 76: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 62 FAA APPROVAL DATE 08 05 2014...

Page 77: ...ons of a headwind the landing distance will be less than that shown Downwind landings will increase the distances provided and should be avoided AIRCRAFT WEIGHT LBS APPROACH AIRSPEED MCAS 7600 114 700...

Page 78: ...PLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 64 FAA APPROVAL DATE 08 05 2014 THRUSH S2R H80 LANDING DISTANCE FROM 50 FT ABOVE GROUND LEVEL AT 7600 LBS APPROACH SPEED IS 114 MCAS W...

Page 79: ...FM H8001 SINGLE DUAL COCKPIT Revision A Page 65 FAA APPROVAL DATE 08 05 2014 THRUSH S2R H80 LANDING DISTANCE FROM 50 FT ABOVE GROUND LEVEL AT REDUCED WEIGHT WITH REVERSE THRUST AND FLAPS 15 REDUCE APP...

Page 80: ...d weight and does not include any overload No overload in accordance with CAR 8 is authorized Maximum Landing Weight 7 600 lbs Minimum Weight 4 500 lbs C G Range Forward limit 25 inches up to 6000 lbs...

Page 81: ...S2R H80 Single Dual Cockpit AIRPLANE FLIGHT MANUAL AFM H8001 SINGLE DUAL COCKPIT Revision A Page 67 FAA APPROVAL DATE 8 05 2014 5 2 S2R H80 SINGLE AND DUAL COCKPIT C G ENVELOPE...

Page 82: ...ft s CG is determined by simply dividing the total Moment by the total Weight Single and Dual Cockpit Baggage Compartment Arm 14 0 inches and max load is 100 lbs Smoker Tank Arm 9 1 inches holds four...

Page 83: ...of fuel that weighs 1005 lbs at an arm of 38 5 equal a total moment of 38 692 5 Hopper rinse is full of water so the weight of water is 200 lbs its arm is 30 0 inches with a total moment of 6000 0 Sm...

Page 84: ...Weights ARM Moments units units units AIRCRAFT 5 037 00 26 81 135 042 PILOT 200 89 17 800 HOPPER 3 637 00 29 9 108 746 FUEL 800 38 5 30 800 HOPPER RINSE 200 30 6 000 SMOKER 26 9 1 237 CARGO 200 114 2...

Page 85: ...ated as a negative number Any compartment behind the wing leading edge has a positive arm NOTE In the dual cockpit S2R H80 the hopper rinse tank is utilized for ballast when the rear cockpit is occupi...

Page 86: ...was delivered with a forward ballast box with a designated required weight that ballast must be installed when the rear cockpit is occupied The maximum weight of this ballast box is 100 and any capaci...

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