Rans S-6ES Pilot’s Operating Handbook
RANS S-6ES
(Your N-number Here)
Pilot Operating Handbook
INTRODUCTION
DESCRIPTIVE DATA
ENGINE:
PROPELLER:
FUEL:
OIL
MAXIMUM WEIGHTS
TYPICAL AIRPLANE WEIGHTS
COCKPIT DIMENSIONS
BAGGAGE SPACE
SPECIFIC LOADINGS
SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
METEOROLOGICAL TERMINOLOGY
POWER TERMINOLOGY
ENGINE CONTROLS AND INSTRUMENTS TERMINOLOGY
AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
WEIGHT AND BALANCE TERMINOLOGY
SECTION 2
LIMITATIONS
GENERAL
AIR SPEED LIMITATIONS
POWER PLANT LIMITATIONS
WEIGHTS
CENTER OF GRAVITY LIMITS
MANEUVERING LIMITS
FLIGHT LOAD FACTOR LIMITS
FUEL LIMITATIONS
PLACARDS
SECTION 3
NORMAL PROCEDURES
PRE-FLIGHT INSPECTION
NORMAL PROCEDURES CHECKLIST
PREFLIGHT CHECKLIST:
SECTION 4
PERFORMANCE
RATE OF CLIMB
CRUISE PERFORMANCE
TAKEOFF DISTANCE
LANDING DISTANCE
SECTION 5
WEIGHT AND BALANCE
GENERAL
AIRPLANE WEIGHING PROCEDURES
AIRCRAFT LOADING
SECTION 6
FLYING THE S-6ESS
FUEL SYSTEM
ENGINE OPERATIONS
TAXIING
TAKE OFFS
LANDINGS
AIRWORK
STALLS
TURNS
FLYING WITH THE DOORS OPEN OR REMOVED
APPROVED MANEUVERS
SPECIAL OPERATIONAL CONSIDERATIONS
CHECK THE CARBURETORS
FUEL SHUT OFF VALVE
SLOW DOWN
HINGES and BEARINGS
FLAPS
IN GENERAL
LANDING WITH FLAPS
TRAILERING AND TOWING PRECAUTIONS
DISASSEMBLY FOR TRANSPORT
MAINTENANCE
CLEANING
AIRFRAME UP KEEP
Section 1
3 View drawing of S-6ES Coyote II
Figure 1-1
INTRODUCTION
This handbook is not designed as a substitute for proper flight instructionor knowledge of current airworthiness directives, federal air regulations, oradvisory circular. This handbook should not be used for operationalpurposes unless it is kept current. The pilot should study the entirehandbook to familiarize himself with the limitations, performance,procedures, and handling characteristics of the airplane prior to flight.
Assurance that the airplane is in airworthy condition is the responsibility ofthe owner. The pilot in command is responsible for determining that theaircraft is safe for flight. The pilot is also responsible for operating theaircraft within the limitations set forth in this handbook and displayed bythe instrument markings and placards.
DESCRIPTIVE DATA
ENGINE:
Number of Engines 1
Engine Manufacturer Rotax
Engine Model Number 912ULS
Engine Type: Normally aspirated, water cooled, horizontallyopposed, carburetor equipped, four-cylinder enginewith 73.9 indisplacement.
Horsepower and Engine Rotational Speed:
Maximum Takeoff (Max allowable 3 min) 5800 RPM
Maximum Continuous 78 bhp (59 kw) 5500 RPM
Idle speed (aprox.) 1400 RPM
PROPELLER:
Number of Propellers 1
Propeller Manufacturer Tennessee propellers
Propeller Model Number 6656RH
Propeller Diameter 66 in
Propeller Type 2 blade, 56 in wood Fixed Pitch
FUEL:
Fuel Grade: Premium grade gasoline
91 octaneor AVGAS 100LL (blue)
Total Capacity 18 US Gal
***CAUTION***
DUE TO HIGHER LEAD CONTENT IN AVGAS, THE WEAR OF THE VALVE SEATS IN THE COMBUSTION CHAMBER WILL INCREASE. THEREFORE, USE AVGAS ONLY IF YOU ENCOUNTER PROBLEMS WITH VAPOR LOCK OF IF MOGAS IS NOT AVAILABLE.
OIL
Total Oil Capacity 6.4 qts.
Oil Grade Automotive engine oil with API, SFor SG classification
Viscosity Recommendations:-22 F TO +77 F - SAE 5W-50
+77 F TO +104 F - SAE 40
***CAUTION***
DO NOT USE AIRCRAFT ENGINE OIL.
MAXIMUM WEIGHTS
Maximum Takeoff Weight 1200 lbs
Maximum Landing Weight 1200 lbs
Maximum Weight in
Baggage Compartment 50 lbs
Maximum Weight in Aft
Baggage Compartment 30 lbs
TYPICAL AIRPLANE WEIGHTS
Standard Empty Weight 600 lbs
Maximum Useful Load 600 lbs
COCKPIT DIMENSIONS
Width (Maximum) 41"
Length (Rudders pedals to Seat Back) 42"
Height (Maximum) 37"
BAGGAGE SPACE
Inside cabin:Compartment Volume 2.0 ft(.06 m)
Maximum width 37.5" (95 cm)
Maximum Length 9" (23 cm)
Maximum Depth 10" (25 cm)
Tail cone:Compartment Volume 6.6 ft(.19 m)
Maximum width 34" (86 cm)
Maximum Height 28" (71 cm)
Maximum Depth 12" (31 cm)
SPECIFIC LOADINGS
At Maximum Takeoff Weight:Wing Loading: 7.29 lbs/ft
Power Loading: 15.38 lbs/hp
SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY
The following definitions are of symbols, abbreviations, and terminologyused in this handbook and those which may be of operational significanceto the pilot:
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
CAS
Calibrated Airspeed means the indicatedpeed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equalto true airspeed in standard atmosphere at sealevel.
KCAS
Calibrated Airspeed expressed in "knots".
GS
Ground speed is the speed of an airplanerelative to the ground.
IAS
Indicated Airspeed is the speed of an aircraftas shown in the airspeed indicator whencorrected for instrument error. IAS valuespublished in this Manual assume zeroinstrument error.
KIAS
Indicated Airspeed expressed in "knots".
TAS
True airspeed is the airspeed of an airplanerelative to undisturbed air which is the CAS corrected for altitude, temperature, andcompressibility.
VA
Maneuvering Speed is the maximum speed atwhich application of full available aerodynamiccontrol will not overstress the airplane.
VFE
Maximum Flap Extended Speed is the highestspeed permissible with wing flaps in aprescribed extended position.
VNE
Never Exceed Speed is the speed limit thatmust not be exceeded at any time.
VNO
Maximum Structural Cruising Speed is thespeed that should not be exceeded except insmooth air and then only with caution.
VS
Stalling speed or the minimum steady flightspeed at which the airplane is controllable.
VSO
Stalling speed or the minimum steady flightspeed at which the airplane is controllable inthe landing configuration.
VX
Best Angle-Of-Climb Speed is the airspeedwhich delivers the greatest gain of altitude inthe shortest possible horizontal distance.
VY
Best Rate-Of-Climb is the airspeed whichdelivers the greatest gain in the altitude in theshortest possible time.
METEOROLOGICAL TERMINOLOGY
ISA
International Standard Atmosphere in which:
-The air is a dry perfect gas;
-The temperature at sea level is 15Celsius (59 Fahrenheit);
-The pressure at sea level is 29.92inches Hg (1013.2 mb);
-The temperature gradient from sealevel to the altitude at which thetemperature is -56.5 C (-69.7 F) isapproximately -2 C for each 305m(1000 feet) of altitude.
-
OAT
Outside Air Temperature is the free air statictemperature, obtained either from in flighttemperature indications or groundmeteorological sources, adjusted forinstrument error and compressibility effects.
IndicatedPressure Altitude
The number actually read from an altimeterwhen the pressure barometric sub-scale hasbeen set to 29.92 inches of Hg (1013.2milibars).
PressureAltitude
Altitude measured from standard sea-levelpressure 29.92 inches Hg (1013.2 milibars) bya pressure or barometric altimeter. It is theindicated pressure altitude corrected forposition and instrument error. In thishandbook, altimeter instrument errors areassumed to be zero.
Station Pressure
Actual atmospheric pressure at field elevation.
Wind
The wind velocities recorded as variables onthe charts of this handbook are to beunderstood as the headwind or tailwindcomponents of the reported winds.
POWER TERMINOLOGY
Takeoff Power
Maximum power permissible for takeoff.
MaximumContinuous Power
Maximum power permissible continuouslyduring flight.
MaximumClimb Power
Maximum power permissible during climb.
Maximum CruisePower
Maximum power permissible during cruise.
BHP
Brake Horsepower is the power developed bythe engine. Percent power values in thishandbook are based on the maximumcontinuous power rating.
RPM
Revolutions Per Minute is the engine speed.
ENGINE CONTROLS AND INSTRUMENTS TERMINOLOGY
Throttle Control
Used to control power by introducing fuel airmixture into the intake passages of the engine.
Tachometer
Indicates the RPM of the engine/propeller.
EGT Gauge
Exhaust Gas Temperature Gauge.
CHT
Cylinder Head Temperature.
AIRPLANE PERFORMANCE AND FLIGHT PLANNINGTERMINOLOGY
Climb Gradient
The demonstrated ratio of the change in height duringa portion of a climb, to the horizontal distancetraversed in the same time interval.
DemonstratedCrosswind Velocity
The demonstrated crosswind velocity is thevelocity of the crosswind component for whichadequate control of the airplane during takeoffand landing was actually demonstrated duringflight tests.
WEIGHT AND BALANCE TERMINOLOGY
Reference Datum
An imaginary vertical plane from which allhorizontal distances are measured for balancepurposes.
Station
A location along the airplane fuselage usually given interms of distance from the reference datum.
Arm
The horizontal distance from the referencedatum to the center of gravity (CG) of an item.
Moment
The product of the weight of an item multipliedby its arm. (Moment divided by a constant isused to simplify balance calculations byreducing the number of digits).
Center Gravity (CG)
The point at which an airplane would balance ifsuspended. Its distance from the referencedatum is found by dividing the total moment bythe total weight of the airplane.
C.G. Arm
The arm obtained by adding the airplane'sindividual moments and dividing the sum bythe total weight.
C.G. Limits
The extreme center of gravity locations whichindicate limits within which the aircraft must beoperated at a given weight.
Usable Fuel
Fuel available for flight planning.
Unusable Fuel
Fuel remaining after a runout test has beencompleted.
Standard EmptyWeight
Weight of a standard airplane includingunusable fuel, full operating fluids and fulloil.
Basic Empty Weight
Standard empty weight plus optionalequipment.
Payload
Weight of occupants, cargo and baggage.
Useful Load
Difference between takeoff weight and basicempty weight.
Maximum TakeoffWeight
Maximum weight approved for the start of the takeoffrun.
Maximum LandingWeight
Maximum weight approved for the landingtouchdown.
Tare
The weight of chocks, blocks, stands, etc.,used on the scales when weighing an airplane.
SECTION 2
LIMITATIONS
GENERAL
The limitations provided in this section include operating limitations,instrument markings, color codings and required placards. This airplanemust be operated in compliance with the operating limitations stated in thishandbook and those associated with the required placards and markings.
AIR SPEED LIMITATIONS
SPEED / IAS (MPH) / REMARKSVA / Mauvering Speed / 93 / Do not make full or abrupt control movements above this speed
VFE / Maximum Flap Extension Speed (15 – 30 deg) / 65 / Do not exceed this speed with a given flap setting. (15 - 30 Flaps)
VNO / Maximum structural cruising speed / 106 / Do not exceed this speed except in smooth air and then only with caution.
VNE / Never exceed speed / 120 / Do not exceed this speed in any operation.
***CAUTION***
Maneuvering speed should not be exceeded while operating in rough air.
AIRSPEED INDICATOR MARKINGS
MARKING / IAS VALUE OR RANGE (MPH) / SIGNIFICANCEWHITE ARC / 40 – 65 / Full flap operating range.
Lower limit is maximum weightstalling speed in landingconfiguration. Upper limit ismaximum speed permissiblewith flaps extended.
GREEN ARC / 43 - 106 / Normal Operating Range.
Lower limit is maximum weight stalling speed. Upper limit is maximum structural cruising speed
Yellow Arc / 106 – 120 / Operations must be conducted with caution and only in smooth air.
Red Line / 120 / Maximum speed for all operations.
Figure 2-2 - Airspeed Indicator Markings
POWER PLANT LIMITATIONS
Number of engines ……………………………………………………………….. 1
Engine Manufacturer ……………………………………………………………. Rotax
Engine Model Number ………………………………………………………….. 912ULS
Engine Operating Limits
Maximum Horsepower ………………………………………………… 78
Maximum Rotational Speed (RPM)(Max. 3 Minutes) ……. 5800
Maximum Oil Temperature …………………………………………. 285F(140C)
Minimum Oil Pressure …………………………………………………. 58 PSI
Maximum Oil Pressure ………………………………………………… 72 PSI
Minimum Fuel Pressure ………………………………………………. 2.2 PSI
Maximum Fuel Pressure ……………………………………………… 5.8 PSI
Maximum Coolant Pressure …………………………………………. 17 PSI
Maximum Cylinder Head Temperature ……………………….. 300F(150C)
Fuel Grade (MOGAS ONLY)
Minimum Octane …………………………………………………………. 92 octane
Oil Grade (Automotive Engine Oil Only)
Below +77F (+25C) ……………………………………………………….. SAE 5W-50
Above +77F (+25C) ……………………………………………………….. SAE 40
Number of Propellers ……………………………………………………………. 1
Propeller Manufacturer ………………………………………………………… Tennessee Propeller
Propeller Model ……………………………………………………………………. 6656 RH
Propeller Diameter ………………………………………………………………… 66 in (1.68 m)
Propeller Operating Limits
Rotational speed restriction ………………………………………… 5800 RPM
WEIGHTS
Maximum Weight ...... 1200 lbs (544 Kg)
Maximum Baggage at Fuselage Station 90 (229 cm) ...... 50 lbs (23 Kg)
Maximum Baggage at Fuselage Station 105 (267 cm)...... 30 lbs (14 Kg)
CENTER OF GRAVITY LIMITS
Forward limit ...... 64" (162.6 cm)
Rearward limit ...... 73" (185 cm)
The datum used is the face of the propeller flange. Leveling point is at thebottom of the door in the cockpit cage.
***CAUTION***
It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded. See Section 5 (Weight and Balance) for proper loading instructions.
MANEUVERING LIMITS
Maneuvering Speed: (VA) 93 IAS (MPH)
FLIGHT LOAD FACTOR LIMITS
Flight Load Factors
Flaps Up ……………………………………………………………………….. + 3.8 g -1.9 g
Flaps Down …………………………………………………………………………… + 2.0 g
FUEL LIMITATIONS
Total Capacity ...... 18 US Gal
Usable Fuel...... 17.5 US Gal
Fuel grade (MOGAS Minimum octane) 91 Octane
***CAUTION***
Fuel remaining when quantity indicator reads zero can not be used safely in flight
PLACARDS
Except as may be otherwise indicated on a placard, the markings andplacards installed in the airplane contain operating limitations which mustbe complied with.
In full view of the pilot:
EXPERIMENTAL
PASSENGER WARNING
THIS AIRCRAFT IS AMATEUR BUILT ANDDOES NOT COMPLY WITH THE FEDERALSAFETY REGULATIONS FORSTANDARD AIRCRAFT
DO NOT OPEN DOOR ABOVE 65 MPH
SECURE ALL LOOSE OBJECTS BEFORE FLIGHT
DRAIN GASCOLATOR BEFORE FLIGHT
On the inside of the baggage compartment door (for the optional AFT.baggage compartment.)
MAXIMUM BAGGAGE 30 LBS
On the instrument panel ( for the cabin baggage compartment.)
MAXIMUM BAGGAGE 50 LBS
Adjacent to fuel filler caps. (2 Places)
FUEL CAPACITY 9 GAL. US - 91 OCTANE MINIMUM
SECTION 3
NORMAL PROCEDURES
AIRSPEEDS FOR NORMAL OPERATIONS
Unless otherwise noted, the following speeds are based on a maximum weight of 1100 lbs and may be used for any lesser weight.
IAS (MPH)
Best Rate of Climb Speed (Vy) ...... 75
Best Angle of Climb Speed (VX) ...... 55
Approach Speed :
Flaps UP ...... 55
Full Flaps DOWN ...... 50
Rotation Speeds ...... 35
Maximum Demonstrated Crosswind Velocity ...... 20
Maximum Flap Speed ...... 65
NORMAL PROCEDURES CHECKLIST
PREPARATION
Airplane Status ...... AIRWORTHY PAPERS ON BOARD
Pilot's Operating Handbook ...... AVAILABLE
Weather ...... SUITABLE
Baggage ...... WEIGHED, STOWED, TIED
Weight and C.G ...... WITHIN LIMITS
Navigation ...... PLANNED
Charts and navigational equipment ...... ON BOARD
Performance and range ...... COMPUTED AND SAFE
Figure 3 – 1
PREFLIGHT INSPECTION CHECKLIST:
(Refer to Figure 3 -1)
1. COCKPIT
Flight Controls ...... REMOVE RESTRAINTS
Ignition Switch ...... OFF
Primary Flight Controls ...... CHECK
Flaps ...... CHECK AND UP
Fuel valve ...... ON
Passenger Seat Belts and Harness ...... CHECKED
Windshield & doors ...... CHECK, CLEAN
Baggage ...... SECURE
Fuel Tank ...... VISUALLY CHECK SUPPLY
Seats ...... ADJUST AS NEEDED
2. LEFT WING
Wing &Control Surfaces ...... FREE OF DAMAGE,
ICE, SNOW OR FROST
Flaps and Hinges ...... CHECK FOR INTERFERENCE
Ailerons and Hinges .... CHECK FOR INTERFERENCE
Wing root connection
pins and bolts in place ...... CHECK
Lift strut bolts/pins secure ...... CHECK
Jury strut/connections ...... CHECK
Fabric ...... CHECK FOR TEARS
Wing Tip & Lights ...... CHECK
Pitot and static probes ...... CLEAR
Tie Down and Chock ...... REMOVE
Tire and Wheel ...... CHECK
Brake Assembly and Brake Line ...... CHECK
Fuel filler cap ...... SECURE
Before first flight of the day and after each fueling, use sampler cup and drain small quantity of fuel from tank sump quick-drain valve to check for water sediment and proper fuel grade (color).
3. FUSELAGE (LEFT SIDE)
General Condition ...... CHECK
Fabric ...... CHECK FOR TEARS
Tubes ...... NO BEND
4. EMPENNAGE
General Condition ...... FREE OF DAMAGE,
ICE, SNOW OR FROST
Elevator & Trim Tab ...... FREE OF INTERFERENCE
Rudder ...... FREE OF INTERFERENCE
Tie Down ...... REMOVE
5. FUSELAGE (RIGHT SIDE)
General Condition ...... CHECK
Antennas ...... CHECK
Fabric ...... CHECK FOR TEARS
Tubes ...... NO BENDS OR DENTS
6. RIGHT WING
Wing & Control Surfaces ...... FREE OF DAMAGE,
ICE, SNOW OR FROST
Ailerons and Hinges ..... CHECK FOR INTERFERENCE
Flaps and Hinges ...... CHECK FOR INTERFERENCE
Wing root connection
pins and bolts in place ...... CHECK
Lift strut bolts/pins secure ...... CHECK
Jury strut/connections ...... CHECK
Fabric ...... CHECK FOR TEARS
Wing Tip & Lights ...... CHECK
Tie Down and Chock ...... REMOVE
Tire and Wheel ...... CHECK WEAR AND INFLATION
Brake Assembly / Brake Line .... CHECK FOR LEAKS
Fuel filler cap ...... SECURE
Before first flight of the day and after each fueling, use sampler cup and drain small quantity of fuel from tank sump quick-drain valve to check for water sediment and proper fuel grade (color).
7. NOSE SECTION
Engine Compartment ...... CHECK FOR LEAKS
Oil ...... CHECK FOR QUANTITY
Dipstick and Oil Cap...... SECURE
Engine mount structure free of cracks .... CHECK
Gear reduction system /
Gear box ...... NO OIL LEAKS
Air filter ...... CLEAN AND SECURE
Spark plug wire ...... CHECK
Carburetor position
and clamp tightness ...... CHECK
Coolant level ...... CHECK
Muffler spring tension ...... CHECK
Muffler free of cracks ...... CHECK
Cowling ...... CLOSED AND SECURED
Propeller ...... SECURE, FREE OF NICKS
Spinner ...... SECURE
Air Inlets ...... CLEAR
Gear/Tire and Wheel ...... CHECK
BEFORE ENGINE STARTING:
Preflight Inspection ...... COMPLETE
Seat Belts and Harnesses ...... FASTENED
Brakes ...... APPLY
Switches ...... OFF
Circuit Breakers ...... IN
Radios ...... OFF
Cockpit Lighting ...... CHECK
Nav. & Strobe Lights ...... CHECK
All Switches ...... OFF
Fuel Valve ...... ON
STARTING ENGINE WHEN COLD
Brakes ...... APPLY
Throttle ...... SET
Propeller Area ...... CLEAR
Starter ...... ENGAGE
Throttle ...... ADJUST
Oil Pressure ...... CHECK
Coolant Pressure ...... CHECK
If engine does not start within 10 seconds, prime and repeat starting procedure.
STARTING ENGINE WHEN HOT
Throttle ...... SET
Brakes ...... APPLY
Propeller Area ...... CLEAR
Starter ...... ENGAGE
Throttle ...... ADVANCE
Oil Pressure ...... CHECK
Coolant Pressure ...... CHECK
WARM-UP
Throttle ...... 1800 to 2500 RPM
BEFORE TAXIING
Seat Belts & Harnesses ...... FASTENED, CHECK
Avionics ...... ON, AS REQUIRED
Lights ...... AS REQUIRED
Taxi Area ...... CLEAR
TAXIING
Throttle ...... APPLY SLOWLY
Brakes ...... CHECK
Nosewheel Steering ...... CHECK
Compass ...... CHECK
BEFORE TAKEOFF
Brakes ...... APPLY
Fuel Valve ...... ON
Throttle ...... 3000 RPM
Magnetos ...... CHECK BOTH, MAX. DROP 200 RPM
Engine Instruments ...... CHECK
Throttle...... IDLE
Avionics ...... CHECKED & SET
Flight Instruments ...... CHECKED & SET
Flaps ...... CHECK, THEN UP
Flight Controls ...... FREE & CORRECT
Seat Belts & Harnesses ...... FASTENED, CHECK