THRUSH S2R-H80 Technical specifications

S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
REV.
PAGE
DESCRIPTION OF REVISION
BY:
AFM H8001 SINGLE & DUAL COCKPIT Revision C Page ii
FAA APPROVAL DATE: 09/03//2015
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.
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-H80-
100-80-0005 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
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page iv
FAA APPROVAL DATE: 3/19/2015
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

S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page v
FAA APPROVAL DATE: 3/19/2015
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

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AIRPLANE FLIGHT MANUAL
LOG OF EFFECTIVE PAGES
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AIRPLANE FLIGHT MANUAL
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S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
AFM H8001 SINGLE & DUAL COCKPIT Revision A Page viii
FAA APPROVAL DATE: 8/05/2014
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).

S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
AFM H8001 SINGLE & DUAL COCKPIT Revision A Page ix
FAA APPROVAL DATE: 8/05/2014
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
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
weaning
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
personnel.
NOTE:
A note is defined as an operating procedure, condition or
statement, which is essential to emphasize.
CAUTION

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

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

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

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

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
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

S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 1
FAA APPROVAL DATE: 3/19/2015
SECTION 1 LIMITATIONS:
1.1. POWERPLANT LIMITS:
ENGINE : General Electric Model GE-H80-100
FUEL:JET A 1 acc. To AST< D 1655 89 or DERD 2494
JET A acc. to ASTMD 1655 89
FUEL
CAPACITY: 230 US Gallons
OILS :
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
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 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
*Short term overshoot. –5 Seconds Maximum.

S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 2
FAA APPROVAL DATE: 3/19/2015
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.

S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 3
FAA APPROVAL DATE: 3/19/2015
1.2. POWERPLANT INSTRUMENT MARKINGS
The following conventions represent the colors used in the MVP-50T Glass Panel Engine
Monitoring display panel:
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.
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.

S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 4
FAA APPROVAL DATE: 3/19/2015
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

S2R-H80 Single & Dual Cockpit
AIRPLANE FLIGHT MANUAL
AFM H8001 SINGLE & DUAL COCKPIT Revision B Page 5
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.
All Airspeeds are given in Indicated Air Speeds (IAS).

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 responsibilityof 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.