THRUSH S2R-H80 Flight Manual
REV.
PAGE
DESCRIPTION OF REVISION
BY:
REV.
PAGE
DESCRIPTION OF REVISION
BY:
IR
ALL
New Document Initial Release.
Melvin D Taylor
Manager Federal Aviation
Administration Aircraft
Certification Office
Atlanta, GA
July 2, 2013
A
A
(cont)
ALL
Cover
ii
v-vi
SECT 1:
pg 6
pg 9
pg 11
pg 12
pg 14
SECT 2:
pg 24
pg 27
pg 28
SECT 4:
pg 59
SECT 5:
pg 66:
pg 72
Added Document Control “# AFM H8001 SINGLE & DUAL COCKPIT” to document.
Replaced the picture to reflect an S2R-H80 model airplane.
Updated Log of Revision to reflect Revision A.
Log of Effective Pages: updated for revised page numbering & all pages affected due to
Document Control # added.
Corrected Sub-section/Paragraph Numeration t/o Section 1.
SECTION 1.5: Changed Max Landing Weight to 7600 Lbs. per FAA Project #
TD12022AT-A.
SECTION 1.11.1: Corrected placard (h) to (…”UNLESS HEADED OUT OF THE
WIND…”). Per FAA request.
Removed placard for SC/SC airplane(“HOPPER RINSE TANK MUST BE FULL WHEN
REAR COCKPIT IS OCCUPIED BY A CREWMEMBER”). Per FAA Request.
SECTION 1.11.2: revised wording for Dual Cockpit/Single Control Placards to alleviate
reference to placard 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 circuit breaker.
Deleted instructions to check fuel filter bypass as it cannot be done due to location of
the fuel filter. Letter g.
SECTION 1.11.3: Revised wording for Dual Cockpit/Dual Control.
Removed placard (“PASSENGER OR CARGO- 200 LBS. MAX”)
No Substantiation to Designate Rear Cockpit As Cargo Area.
SECTION 1.11.3.h: Corrected placard to (…”UNLESS HEADED OUT OF THE
WIND…”). Per FAA request.
SECTION 1.12: Revised “Kinds of Operations” table to clearly designate front cockpit
instruments; also clearly define required items by coloring.
Added check for the fuel filter bypass light: Press to test.
Added a definition for the “FUEL FILTER BYPASS” light and to land as soon practicable
if illuminated signaling a restricted fuel filter.
SECTION 2.4: Revised “Dry Motoring Run” Definition per GE-H80-100 Operation
Manual 0983302.
SECTION 2.8: Corrected “Note” allowing the engine to stabilize for a period now a
minimum of 5 minutes, was 3 minutes.
SECTION 2.9: Added “Engine Re-Start Procedures On The Ground” per GE-SB-H80100-80-0005 Per FAA request.
SECTION 4.5: Added chart for reduced weight takeoff distance, inadvertently omitted
from Revision IR.
SECTION 5.1: Changed Max Landing Weight back to 7600 Lbs. FAA Project #
AT12022AT-A, also referenced in CG range.
SECTION 5.5: Change Max Landing Weight back to 7600 lbs.
Bruce S. Remick
For Manager Federal Aviation
Administration Aircraft
Certification Office
Atlanta, GA
DATED: Aug 5, 2014
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
LOG OF REVISIONS
NOTE: Re-formatting and correction of typographical errors is not considered revision. True revisions are indicated
by a dark vertical line at the right margin of the line revised.
AFM H8001 SINGLE & DUAL COCKPIT Revision C Page ii
FAA APPROVAL DATE: 09/03//2015
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
TABLE OF CONTENTS
LOG OF REVISIONS ............................................................................................................................................... II
INTRODUCTION .................................................................................................................................................. VIII
WARNINGS, CAUTIONS & NOTES DEFINED ...................................................................................................... IX
3-VIEW OF S2R-H80 SINGLE COCKPIT ............................................................................................................... X
DIMENSIONAL 3-VIEW OF S2R-H80 SINGLE COCKPIT .................................................................................... XI
3-VIEW OF S2R-H80 DUAL COCKPIT ................................................................................................................. XII
DIMENSIONAL 3-VIEW H80 DUAL COCKPIT .................................................................................................... XIII
GLOSSARY OF TERMS & ABBREVIATIONS .................................................................................................... XIV
SECTION 1 LIMITATIONS: .................................................................................................................................... 1
1.1. POWERPLANT LIMITS: .............................................................................................................................. 1
1.2. POWERPLANT INSTRUMENT MARKINGS ............................................................................................... 3
1.3. AIRSPEED LIMITS....................................................................................................................................... 5
1.4. ALTITUDE 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 OPERATIONS ................................................................................................ 7
1.8. TYPES OF OPERATION .............................................................................................................................. 7
1.9. FLIGHT LOAD FACTORS ........................................................................................................................... 7
1.10. MANEUVERS ............................................................................................................................................... 7
1.11. PLACARDS .................................................................................................................................................. 8
1.11.1. SINGLE COCKPIT/SINGLE CONTROL ...................................................................................................... 8
1.11.2. DUAL COCKPIT/SINGLE CONTROL ........................................................................................................ 12
1.11.3. DUAL COCKPIT/DUAL CONTROL ........................................................................................................... 12
1.12. KINDS OF OPERATION EQUIPMENT LIST ............................................................................................. 14
SECTION 2: NORMAL PROCEDURES: .............................................................................................................. 15
2.1. PRE-FLIGHT VISUAL INSPECTION ......................................................................................................... 15
2.2. MVP-50T GLASS PANEL ENGINE MONITORING SYSTEM ................................................................... 20
2.3. OPERATING CHECKLIST ................................................................ ......................................................... 22
2.4. DRY MOTORING RUN ............................................................................................................................... 24
2.5. TAXI 24
2.7. BEFORE TAKE-OFF.................................................................................................................................. 25
2.8. NORMAL FLIGHT PROCEDURES ............................................................................................................ 25
2.9. ENGINE RE-START PROCEDURES ON THE GROUND ......................................................................... 28
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page iv
FAA APPROVAL DATE: 3/19/2015
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
SECTION 3: EMERGENCY PROCEDURES ........................................................................................................ 30
3.1. INTRODUCTION ........................................................................................................................................ 30
3.2. DEFINITION OF EMERGENCY TERMS .................................................................................................... 30
3.3. EMERGENCY BASIC RULES ................................................................................................................... 30
3.4. MVP-50T ANNUNCIATION LIGHTS .......................................................................................................... 30
3.5. GROUND ENGINE FIRE ............................................................................................................................ 33
3.6. IN-FLIGHT ENGINE FIRE .......................................................................................................................... 33
3.7. EMERGENCY HOPPER DUMP ................................................................................................................. 34
3.8. ELECTRICAL FIRE IN-FLIGHT ................................................................................................................. 34
3.9. 3.9 ENGINE FAILURE IN-FLIGHT ............................................................................................................. 34
3.10. ENGINE FLAMEOUT ................................................................................................................................. 36
3.11. FAILURE OF AUTOMATIC FUEL SCHEDULING ..................................................................................... 36
3.12. AIR STARTS .............................................................................................................................................. 37
3.13. ABORTED TAKE-OFF ............................................................................................................................... 39
3.14. 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. SUSPICION OF HOPPER RINSE TANK LEAKING .................................................................................. 41
SECTION 4: PERFORMANCE ............................................................................................................................. 42
4.1. INTRODUCTION ........................................................................................................................................ 42
4.2. AIRSPEED CALIBRATION ........................................................................................................................ 44
4.3. STALLING SPEED VERSUS AIRCRAFT WEIGHT .................................................................................. 49
4.4. INSTALLED ENGINE HORSEPOWER ...................................................................................................... 52
4.5. TAKEOFF DISTANCE TO 50 FEET ABOVE GROUND LEVEL ............................................................... 57
4.6. CLIMB PERFORMANCE ........................................................................................................................... 60
4.7. LANDING DISTANCE FROM 50 FEET ABOVE GROUND LEVEL ......................................................... 63
SECTION 5: WEIGHT & BALANCE ........................................................................................................................... 66
5.1. WEIGHT & BALANCE PROCEDURE ....................................................................................................... 66
5.2. S2R-H80 SINGLE AND DUAL COCKPIT C.G. ENVELOPE ..................................................................... 67
5.3. WAM - EXAMPLE ...................................................................................................................................... 68
5.5. USING FORWARD BALLAST TO MANAGE AFT EMPTY CG POSITION FOR THE DUAL COCKPIT
CONFIGURATION. ................................................................................................................................... 72
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page v
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S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
LOG OF EFFECTIVE PAGES
AFM H8001 SINGLE & DUAL COCKPIT Revision C Page vi
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S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
LOG OF EFFECTIVE PAGES
AFM H8001 SINGLE & DUAL COCKPIT Revision C Page vii
FAA APPROVAL DATE: 09/03/2015
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
INTRODUCTION
These instructions are for use by the operators of the S2R-H80 Turbo Thrush aircraft. This
manual contains optimum operating instructions for this model under most circumstances. This
aircraft is certificated in the RESTRICTED CATEGORY and flight maneuvers shall be limited 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 into known icing conditions is PROHIBITED. The observance of limitations,
performance, and weight & balance data provided in this manual are mandatory.
This manual shall be carried in this aircraft at all times.
Changes to the text and tables, including new material on added pages, are indicated by a vertical
bar in the outer margin. This is also reflected in the Log of Revisions (page iii) and the Log of
Pages (page vi).
AFM H8001 SINGLE & DUAL COCKPIT Revision A Page viii
FAA APPROVAL DATE: 8/05/2014
S2R-H80 Single & Dual Cockpit
A WARNING IS DEFINED AS AN OPERATING PROCEDURE,
PRACTICE, CONDITION OR STATEMENT, WHICH IF NOT
CORRECTLY FOLLOWED, COULD RESULT IN PERSONAL
INJURY OR LOSS OF LIFE.
WARNING
A caution is defined as an operating procedure, practice,
condition or statement, which if not strictly observed,
could result in damage to or destruction of equipment,
loss of effectiveness or long term health hazards to
NOTE:
A note is defined as an operating procedure, condition or
statement, which is essential to emphasize.
CAUTION
AIRPLANE FLIGHT MANUAL
WARNINGS, CAUTIONS & NOTES DEFINED:
USE OF SHALL, SHOULD & MAY:
“Shall”: used to indicate a mandatory requirement.
“Should”: used to indicate a non-mandatory but preferred method of
accomplishment.
“May”: used to indicate an acceptable method of accomplishment.
AIRSPEEDS:
All airspeeds in this Manual are Indicated Air Speeds (IAS) in Miles per Hour (MPH),
unless otherwise noted.
EMERGENCY LANDING TERMS:
“LAND AS SOON AS POSSIBLE”:
This term is defined as landing at the 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. The primary
consideration is the urgency of the emergency
AFM H8001 SINGLE & DUAL COCKPIT Revision A Page ix
FAA APPROVAL DATE: 8/05/2014
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
3-VIEW OF S2R-H80 SINGLE COCKPIT
AFM H8001 SINGLE & DUAL COCKPIT Revision A Page x
FAA APPROVAL DATE: 8/05/2014
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
DIMENSIONAL 3-VIEW OF S2R-H80 SINGLE COCKPIT
AFM H8001 SINGLE & DUAL COCKPIT Revision A Page xi
FAA APPROVAL DATE: 8/05/2014
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
3-VIEW OF S2R-H80 DUAL COCKPIT
AFM H8001 SINGLE & DUAL COCKPIT Revision A Page xii
FAA APPROVAL DATE: 8/05/2014
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
DIMENSIONAL 3-VIEW H80 DUAL COCKPIT
AFM H8001 SINGLE & DUAL COCKPIT Revision A Page xiii
FAA APPROVAL DATE: 8/05/2014
S2R-H80 Single & Dual Cockpit
AFT
To the Rear
C.G.
Center of Gravity
CAP
Capacity
G
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
NG
Gas Generator RPM
NP
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
VA
Maneuvering Speed
VFE
Maximum Flaps Extend Speed
VFR
Visual Flight Rules
VNE
Never Exceed Speed
VNO
Maximum Structural Cruising Speed
AIRPLANE FLIGHT MANUAL
GLOSSARY OF TERMS & ABBREVIATIONS
AFM H8001 SINGLE & DUAL COCKPIT Revision A Page xiv
FAA APPROVAL DATE: 8/05/2014
SECTION 1 LIMITATIONS:
POWER SETTING
SHP
TORQUE
%
ITT
(°C)
(%) NG
NP
(RPM)
OIL
PRES.
(PSIG)
OIL TEMP
(°C)
Takeoff –
(5 minute limit)
800
100
780
101.5
2080
26 to 39
+20 to 85
Maximum Continuous
800
100
750
100.1
2080
26 to 39
+20 to 85
Climb
800
100
750
100.1
2080
26 to 39
+20 to 85
Ground Idle
550
57-60
18
minimum
+20 to 85
Starting
730
26 to 39
-20 to 85
Acceleration
106*
780
102.5*
2140*
26 to 39
+20 to 85
Maximum Reverse
710
96
1900
26 to 39
+20 to 85
Emergency Governor
800
100
780
101.5
2080
26 to 39
+20 to 85
1.1. POWERPLANT LIMITS:
ENGINE : General Electric Model GE-H80-100
FUEL: JET A 1 acc. To AST< D 1655 89 or DERD 2494
FUEL
CAPACITY: 230 US Gallons
OILS :
JET A acc. to ASTMD 1655 89
AERO SHELL TURBINE OIL 500 acc. to MIL L 23699C
AERO SHELL TURBINE OIL 560 acc. to MIL L 23699C
MOBILE JET OIL II acc. to MIL L 23699C
Synthetic oil B3V acc. to TJU 38 101295 85
EASTMAN TURBO OIL 2380
CASTROL 599
ROYCO TURBINE OIL
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
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.
*Short term overshoot. – 5 Seconds Maximum.
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 1
FAA APPROVAL DATE: 3/19/2015
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
STARTER: Maximum starter engagement duration is 30 seconds
followed by a 60 second cool-down period; a total of 3 cycles
to be followed by a 30 minute starter cool-down period.
FUEL PUMPS: Continuous simultaneous operation of both fuel pumps is
prohibited due to high fuel pressure.
AIR STARTS: Normal air starts are approved from sea level to 12,000 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 Propeller:
0 Model #HC-B4TW-3/T10282N(S)
Minimum Diameter: 102” / Maximum Diameter: 103”
PROPELLER
LIMITATIONS: Stabilized ground operation is prohibited between 400
and 1100 RPM. The propeller may be operated when
feathered at or below 400 RPM.
REVERSE POWER: Do not use in flight.
NOISE
ABATEMENT: This airplane has not been shown to comply with the
noise limits in 14 CFR Part 36 and must be operated
in accordance with the noise operating limitation
prescribed under 14 CFR Part 91.815.
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 2
FAA APPROVAL DATE: 3/19/2015
S2R-H80 Single & Dual Cockpit
RED
You have exceeded a limit and an immediate action is required.
Exceeding any limit will cause the indication display color to change
to RED and flash, as well as illuminate a flashing Master Warning
Light.
YELLOW
You are operating in a range where operation 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
color to flash YELLOW and will illuminate a YELLOW flashing Master
Caution Light.
GREEN
A range where continuous operating is allowed, also known as
normal operating range.
Operating in a green range will have the display color GREEN, with
no flashing or illumination of the Master Warning or Master Caution
Light.
AIRPLANE FLIGHT MANUAL
1.2. POWERPLANT INSTRUMENT MARKINGS
The following conventions represent the colors used in the MVP-50T Glass Panel Engine
Monitoring display panel:
The OAT indicator will turn BLUE at 40°F to remind the pilot that he is prohibited from flight in
visible moisture at temperatures 40°F and below. If these conditions are encountered in flight:
Land as soon as Practicable.
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 3
FAA APPROVAL DATE: 3/19/2015
S2R-H80 Single & Dual Cockpit
LIMITS
FEATURES
MEANING
OIL TEMP (°C)
-20
RED Radial
Minimum
-20 to +20
YELLOW Arc
Caution Range
20 to 85
GREEN Arc
Normal Range
85
RED Radial
Maximum
OIL PRESSURE (PSI)
18
RED Radial
Minimum
18 to 26
YELLOW Arc
Caution Range
26 to 39
GREEN Arc
Normal Range
39 to 49
YELLOW Radial
Caution Range
49
RED Radial
Maximum
FUEL PRESSURE (PSI)
12.5
RED Radial
Minimum
12.5 to 34.0
GREEN Arc
Normal 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 Range
106
RED Radial
Maximum
PROP RPM (NP)
0 to 400 RPM
GREEN Arc
Normal Range
400 to 1100 RPM
YELLOW Arc
Caution Range
1100 TO 2080 RPM
GREEN arc
Normal Range
2080 TO 2140 RPM
YELLOW arc
Caution Range
2140 RPM
RED Radial
Maximum
GAS GEN SPEED
(NG)
0 to 100.1
GREEN Arc
Normal OP Range
100.1 – 101.5
YELLOW Arc
Caution Range
101.5
RED Radial
Maximum
AIRSPEED
MPH
88 to 157
WHITE Arc
Flap Operating Range
94 to 158
GREEN Arc
Normal Operating Range
159 to 186
YELLOW Arc
Caution Range
>186
RED Line
Never Exceed
AIRPLANE FLIGHT MANUAL
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 4
FAA APPROVAL DATE: 3/19/2015
1.3. AIRSPEED LIMITS
Limits
Speed
(MPH)
Remarks
1. Flaps down stall speed – VSO
88
Stall speed at maximum gross weight with
flaps full down (15ᵒ)
2. Flaps up stall speed - VS
94
Stall speed at maximum 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
186
Basic Airplane Limit
6. Max. Flap Extended Speed
VFE
157
Limit with flaps extended
7. Max. Dump Speed
158
Limit for Hopper Dump
8. Max. Crosswind Velocity
15
Maximum demonstrated crosswind for
Landing.
9. Max. Airspeed with Taxi Light
Extended
158
Structural Limit.
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
All Airspeeds are given in Indicated Air Speeds (IAS).
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 5
FAA APPROVAL DATE: 3/19/2015
S2R-H80 Single & Dual Cockpit
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.
AIRPLANE FLIGHT MANUAL
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:
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 6
FAA APPROVAL DATE: 3/19/2015
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
1.6. USING FORWARD BALLAST TO MANAGE AFT EMPTY CG
POSITION FOR THE DUAL CONFIGURATION.
a. A second battery is standard and will be used as permanent Ballast.
b. A Hopper Rinse System is standard equipment and must be filled with water
whenever the rear seat is occupied by a crewmember. The water becomes
removable ballast if the rear seat is not occupied.
c. If the aircraft 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 capacity above the required
weight may be used for optional addition forward ballast. If the airplane
configuration is changed so as to affect the weight and balance, the required
ballast 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 compartment is standard with capacity to hold up to 100# of
removable Ballast, if required to keep the airplane within aft CG limitations.
1.7. HIGH ALTITUDE AIRPORT OPERATIONS
For operations at airports above 10,000 ft. MSL reduce gross weight to 10,300 lbs.
in order to meet rate of climb requirements.
1.8. TYPES OF OPERATION
The model S2R-H80 aircraft is approved for day and night VFR flight conditions.
Flight into or near thunderstorms or into known icing conditions is PROHIBITED.
GROUND OPERATION:
Ground operation is approved at ground idle power with the propeller feathered for
30 minutes. The pilot should monitor the engine instruments for operations within
limits during all ground operations.
1.9. FLIGHT LOAD FACTORS
Design Load Factors:
FLAP UP 3.27 Positive 1.31 Negative
FLAP DOWN 2.0 Positive 0.0 Negative
1.10. MANEUVERS
No acrobatic maneuvers, including spins, are approved.
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 7
FAA APPROVAL DATE: 3/19/2015
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
1.11. PLACARDS
1.11.1. SINGLE COCKPIT/SINGLE CONTROL
a. Located on Right Hand lower instrument panel:
“THE OPERATION OF THIS AIRPLANE IS LIMITED TO DAY AND
NIGHT VFR FLIGHT CONDITIONS. FLIGHT INTO OR NEAR
THUNDERSTORMS OR INTO KNOWN ICING CONDITIONS IS
PROHIBITED.
SULFUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE
PREVENTION MEASURES HAVE BEEN INCORPORATED IN
AIRCRAFT.
TAKING 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
AIRPLANE FLIGHT MANUAL. NO ACROBATIC MANEUVERS,
INCLUDING SPINS APPROVED.
DESIGN MANEUVERING SPEED - 158 MPH
MAX. FLAP DOWN SPEED - 157 MPH
MAX. CROSSWIND VELOCITY LANDING 15 MPH. USABLE TANK
CAPACITY 114 GALS EACH SIDE.”
“PUSH STICK FORWARD
TO UNLOCK TAILWHEEL.”
“NO SMOKING”
b. Located on the Left Hand Instrument Panel:
“OCCUPANT MUST ATTACH SEAT BELT AND
SHOULDER HARNESS, AND WEAR A D.O.T.
APPROVED OR MIL-SPEC HELMET”
c. Located near the Park Brake Valves:
“PARK BRAKE
ON
DEPRESS PEDAL
PULL LEVER
OFF
DEPRESS PEDAL”
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 8
FAA APPROVAL DATE: 3/19/2015
WARNING
DO NOT USE REVERSE POWER IN FLIGHT. AT HIGH TAXI
SPEEDS USE REVERSE POWER ONLY IF THE TAIL WHEEL IS
LOCKED AND HELD FIRMLY ON THE GROUND.
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
e. Located on the forward Lower Corner of Each side door window:
“DO NOT OPEN DOOR IN FLIGHT.”
“DO NOT OPEN DOOR ON THE GROUND WITH THE ENGINE
RUNNING UNLESS HEADED OUT OF THE WIND WITH PROPELLER
FEATHERED.”
f. At both main fuel filler caps:
“FUEL 115 GAL CAPACITY
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 door latch: (left and right) “
Open
DO NOT OPEN DOOR IN FLIGHT”
k. Located (inverted) at each door hinge pin:
“PULL HINGE PIN ⇩ FOR EMERGENCY EXIT.”
l. Located on face of fuel shut off bracket:
“ON
PUSH BUTTON
TO TURN
OFF
FUEL
228 U.S.GAL
USEABLE”
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 9
FAA APPROVAL DATE: 3/19/2015
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
n. LocatedbelowMVP-50Tscreen:
“USEABLE FUEL 114 U.S. GAL.PER TANK.
FUEL ABOVE 82 GAL. IS UNGAGEABLE”
o. Locate inside baggage compartment on floor near baggage compartment
doors:
“100 POUNDS MAXIMUM BAGGAGE”
p. Locate at hopper rinse port:
”HOPPER RINSE FILLER PORT”
q. Locate at external power receptacle centered on the inside of the
receptacle door.
“EXTERNAL POWER 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 – KEEP CLEAN”
u. Located near door:
“RESTRICTED”
v. Locate on the Outside in the Center of Oil Dipstick Access Door.
“OIL”
w. Locate on the inside in the Center of Oil Dipstick Access Door.
“OIL
SEE AFM SECTION 1.1
FOR PERMISSIBLE OIL”
x. Located on center upper instrument panel:
“STABILIZED GROUND OPERATION IS PROHIBITED BETWEEN 400
AND 1100 RPM. THE PROPELLER MAY BE OPERATED WHEN
FEATHERED AT OR BELOW 400 RPM.”
y. Locate on left upper instrument panel above MVP:
“MAX ENGINE GROUND RUN TIME: 30 MINUTES”
AFM H8001 SINGLE & DUAL COCKPIT Revision C Page 10
FAA APPROVAL DATE: 09/03/2015
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
z. Locate above main fuel filler caps:
“FUEL LEVEL INDICATOR
110 U. S. GAL
100 U. S. GAL
88 U. S. GAL
66 U. S. GAL”
aa. Locate below main fuel filler caps:
“FUEL TANKS ARE INTERCONNECTED.
ALLOW SUFFICIENT TIME FOR FUEL LEVEL
TO EQUALIZE BEFORE TOP OFF OF TANK.”
bb. Locate inside 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 centered 1.25” from outside
edge:
“SECURE BAGGAGE TO TIE DOWN CLAMPS
TO PREVENT SHIFTING IN FLIGHT”
dd. Locate on the Right Hand Instrument Panel Above the Fuel Filter Bypass
Circuit Breaker.
FUEL FILTER.
ee. Locate on the Right Hand Instrument Panel below the Fuel Filter Bypass
Circuit Breaker.
BYPASS.
ff. Locate on the Left Hand Instrument Panel Below the Fuel Filter Bypass
Light.
FUEL FILTER BYPASS
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 11
FAA APPROVAL DATE: 3/19/2015
S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
1.11.2. DUAL COCKPIT/SINGLE CONTROL
All placards listed in 1.11.1 for the single cockpit/single control with these
additional placards for dual cockpit/single control:
a. Locate in rear cockpit on extrusion. Part of Padding installation.
“OCCUPANT MUST ATTACH SEAT BELT AND
SHOULDER HARNESS, AND WEAR A
D.O.T. APPROVED OR MIL-SPEC HELMET”
b. Locate at the rear door knockout panel:
“PUSH OUT AND LIFT HINGE PIN FOR EMERGIENCY EXIT.”
c. Locate at the forward side of lower rear door window.
”DO NOT OPEN IN FLIGHT”
d. Locate at the aft side of lower rear door window
“DO NOT OPEN DOOR ON THE GROUND 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 center upper instrument panel and on extrusion. Part of padding
installation in the rear cockpit.
“HOPPER RINSE TANK MUST BE FULL
WHEN REAR COCKPIT IS OCCUPIED”
h. Locate on center upper instrument panel and on extrusion. Part of
Padding installation in the rear cockpit.
“FORWARD BALLAST BOX MUST BE INSTALLED
ANYTIME THE REAR SEAT IS OCCUPIED.”
1.11.3. DUAL COCKPIT/DUAL CONTROL
All placards listed in 1.11.1 for the single cockpit/single control with additional
placards for dual cockpit/dual control:
a. Locate on rear instrument panel on right side of MVP-50T.
“THE OPERATION OF THIS AIRPLANE IS LIMITED TO
DAY AND NIGHT VFR CONDITIONS. FLIGHT INTO OR
NEAR THUNDERSTORMS OR INTO KNOWN ICING
CONDITIONS IS PROHIBITED.”
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 12
FAA APPROVAL DATE: 3/19/2015
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