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S2R-H80 Single & Dual Cockpit

AIRPLANE FLIGHT MANUAL

AFM H8001 SINGLE & DUAL COCKPIT Revision B

Page 6

FAA APPROVAL DATE: 3/19/2015

1.4.

ALTITUDE LIMITATIONS: 12,000 MSL

1.5.

MAXIMUM WEIGHT AND CENTER OF GRAVITY LIMITS

For Single and Dual Cockpit

Maximum Weight:

10,500 lbs.

Maximum Landing Weight:

7600 lbs.

Minimum Weight:

4500 lbs.

C.G. Range:

Forward C.G. Regardless of Weight:

6000 lbs. @ 25.0 in. AFT 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

NOTE:

DATUM is the leading edge of the wing.

NOTE:

It is the responsibility of the airplane owner and the pilot to insure
that the airplane is properly loaded. See the Weight & Balance
Sheet for loading information.

NOTE:

Hopper rinse tank must be full when rear cockpit is occupied by
a crewmember.

NOTE:

Required forward ballast must be installed when rear cockpit is
occupied by a crewmember.

Содержание S2R-H80

Страница 1: ......

Страница 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...

Страница 3: ......

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

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

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

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

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

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

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

Страница 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...

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

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

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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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