Searey LSA Owner's manual

Searey LS –Pilot’s Operating Handbook Version 5.0, Revision 8 i
Publication Number: SeareyLS-001
Pilot’s Operating
Handbook
Searey LSA
Airplane Registration Number:
Airplane Serial Number:
PROGRESSIVE AERODYNE
3801 State Road 19
Tavares, Florida 32778
Version 5.0 Revision 8 Issue Date: 05 July 2017

Searey LSA –Pilot’s Operating Handbook Version 5.0, Revision 8
ii
Record of Manual Revisions
Any revisions or amendments to the present manual shall be issued in the form of bulletins with
attached new pages. It is in the interest of every owner/operator to enter each revision into the
table of revisions and replace the existing page with the new one.
Revision
Number
Bulletin
Number
Date of
Issuance
Pages
Affected
New Page(s)
Insertion
Date with Signature
0
---
July 16, 2014
---
Original manual
1~4
Corrected
miscellaneous
editing errors
5
December 23,
2014
Updated fuel tank
6
December 8,
2015
Updated 914,
Miscellaneous Data
7
January 12, 2017
---
Updated Adventure
Model
8
July 5, 2017
Updated Elite G3X

Searey LSA –Pilot’s Operating Handbook Version 5.0, Revision 8
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Table of Contents
I
RECORD OF MANUAL REVISIONS....................................................................................................................................II
PILOT’S OPERATING HANDBOOK - POH 1
INTRODUCTION...........................................................................................................................................................1
0.1 ASTM STANDARDS.......................................................................................................................1
0.2 MANUFACTURER CONTACT INFORMATION ................................................................................1
0.3 SUPPORT CONTINUATION INFORMATION ..................................................................................2
SECTION 1–GENERAL INFORMATION .............................................................................................................................3
1.1 INTRODUCTION TO AIRPLANE .....................................................................................................3
1.2 PERFORMANCE SPECIFICATIONS .................................................................................................4
SECTION 2–LIMITATIONS ............................................................................................................................................6
2.1 AIRSPEED INDICATOR –SPEED RANGE MARKINGS .....................................................................6
2.2 STALLING SPEEDS AT MAXIMUM TAKEOFF WEIGHT (VSto VSO)..................................................7
2.3 FLAP EXTENDED SPEED RANGE (VSO to VFE): ................................................................................7
2.4 MANEUVERING SPEED (VA) AT GROSS WEIGHT AND MINIMUM WEIGHT..................................7
2.5 NEVER EXCEED SPEED (VNE) .........................................................................................................7
2.6 SERVICE CEILING ..........................................................................................................................7
2.7 MANEUVERING LOAD FACTORS ..................................................................................................7
2.8 APPROVED MANEUVERS .............................................................................................................7
2.9 TOTAL FUEL CAPACITY .................................................................................................................8
2.10 TOTAL USABLE FUEL ....................................................................................................................8
2.11 APPROVED FUEL TYPES................................................................................................................8
2.12 MAXIMUM ENGINE POWER OUTPUT AT STATED RPM...............................................................8
2.13 ENVIRONMENTAL LIMITATIONS..................................................................................................9
2.14 VFR NIGHT OR IFR USE LIMITATIONS ........................................................................................10
SECTION 3–EMERGENCY PROCEDURES ........................................................................................................................11
3.1 GENERAL INFORMATION ON EMERGENCY PROCEDURES .........................................................11
3.2 AIRSPEEDS FOR EMERGENCY PROCEDURES ..............................................................................11
3.3 EMERGENCY CHECKLISTS...........................................................................................................11
SECTION 4–NORMAL PROCEDURES.............................................................................................................................21
4.1 PREFLIGHT CHECK......................................................................................................................21

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4.2 ENGINE STARTING .....................................................................................................................25
4.3 TAXIING......................................................................................................................................26
4.4 NORMAL TAKEOFF.....................................................................................................................27
4.5 BEST ANGLE OF CLIMB SPEED (VX) ............................................................................................27
4.6 BEST RATE OF CLIMB SPEED (VY)...............................................................................................28
4.7 CRUISE .......................................................................................................................................28
4.8 APPROACH.................................................................................................................................28
4.9 NORMAL LANDING ....................................................................................................................28
NOTE: It is not recommended to operate in wave height exceeding 12 inches.....................................29
4.10 SHORT FIELD TAKEOFF AND LANDING PROCEDURES ................................................................29
4.11 SOFT FIELD TAKEOFF AND LANDING PROCEDURES...................................................................30
4.12 BALKED LANDING PROCEDURES................................................................................................30
4.13 AFTER LANDING.........................................................................................................................31
4.14 AFTER LANDING –WATER OPERATIONS –DOCKING & BEACHING...........................................31
4.15 SHUT DOWN ..............................................................................................................................31
4.16 SECURING AIRCRAFT..................................................................................................................32
SECTION 5-PERFORMANCE ........................................................................................................................................33
5.1 TAKEOFF TOTAL DISTANCE OVER A FIXED-HEIGHT OBSTACLE USING NORMAL TAKEOFF
PROCEDURES ..........................................................................................................................................33
5.2 LANDING TOTAL DISTANCE OVER A FIXED-HEIGHT OBSTACLE USING NORMAL LANDING
PROCEDURES ..........................................................................................................................................35
5.3 RATE OF CLIMB (ROC)................................................................................................................36
5.4 CRUISE SPEEDS ..........................................................................................................................37
5.5 RPM SETTING AND FUEL CONSUMPTION..................................................................................38
6.1 WEIGHT AND BALANCE CHART..................................................................................................39
WEIGHT AND BALANCE LIMITS...............................................................................................................40
6.2 OPERATING WEIGHT AND LOADING (OCCUPANTS, BAGGAGE, FUEL, BALLAST).......................43
6.3 CENTER OF GRAVITY (CG) RANGE AND DETERMINATION .........................................................45
6.4 INSTALLED OPTIONAL EQUIPMENT LIST AFFECTING WEIGHT AND BALANCE OR A REFERENCE AS
TO WHERE THIS INFORMATION CAN BE FOUND ....................................................................................46
SECTION 7–DESCRIPTION OF AIRPLANE AND SYSTEMS ....................................................................................................47
7.1 GENERAL....................................................................................................................................47
7.2 AIRFRAME..................................................................................................................................48
7.3 FLIGHT CONTROLS .....................................................................................................................51
7.4 INSTRUMENT PANEL..................................................................................................................54
7.5 ENGINE ......................................................................................................................................58
7.6 PROPELLER.................................................................................................................................61
7.7 BAGGAGE COMPARTMENT .......................................................................................................61
7.8 SEAT BELTS & INERTIA REELS.....................................................................................................61
7.9 SLIDING CANOPIES.....................................................................................................................62
7.10 CONTROL LOCKS ........................................................................................................................62
SECTION 8–HANDLING AND SERVICING........................................................................................................................63
8.1 INTRODUCTION .........................................................................................................................63

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8.2 GROUND HANDLING..................................................................................................................63
8.3 TOWING INSTRUCTIONS............................................................................................................64
8.4 TIE-DOWN INSTRUCTIONS.........................................................................................................64
8.5SERVICING FUEL, OIL, COOLANT AND OTHER OPERATING FLUIDS............................................65
8.6 CLEANING AND CARE.................................................................................................................67
8.7 SALT WATER MAINTENANCE AND CARE ...................................................................................68
SECTION 9–SUPPLEMENTS ........................................................................................................................................72
9.1 CONTINUED AIRWORTHINESS MAINTENANCE PROGRAM........................................................72
9.2 DOCUMENTATION .....................................................................................................................76
9.3 ABBREVIATIONS & DEFINITIONS................................................................................................76
9.4 AIRCRAFT PERFORMANCE & FLIGHT PLANNING TERMINOLOGY ..............................................77
9.5 OPERATION OF OPTIONAL EQUIPMENT OR ACCESSORIES ........................................................77
9.6 AIRPLANE FLIGHT TRAINING SUPPLEMENT (FTS) ......................................................................77
9.7 PLACARDS AND MARKINGS .......................................................................................................77
9.8 REPORTING IMPROVEMENTS OR CORRECTIONS.......................................................................86
9.9 CONTINUED OPERATIONAL SAFETY REPORTING.......................................................................86
9.10 OWNER CHANGE OF ADDRESS NOTICE .....................................................................................87

Searey LS –Pilot’s Operating Handbook Version 5.0, Revision 8 1
Pilot’s Operating Handbook - POH
PROGRESSIVE AERODYNE
3801 State Road 19
Tavares, Florida 32778
Introduction
0.1 ASTM STANDARDS
The design, construction, and continued airworthiness of the Searey LS
all comply with the following ASTM Standards:
F2245 –11 (S/N: 1LK556C) / F2245 –12d (S/N: 1002through S/N
1014) F2245-13b (S/N 1015 to 1048) F2245-14 (SN1049 and forward):
Standard Specification for Design and Performance of a Light Sport
Airplane
F2279 –06: Standard Practice for Quality Assurance in the Manufacture
of Fixed Wing Light Sport Aircraft
F2295 –06: Standard Practice for Continued Operational Safety
Monitoring of a Light Sport Aircraft
F2483 –12: Standard Practice for Maintenance and the Development of
Maintenance Manuals for Light Sport Aircraft
F2746 –12: Standard Specification for Pilot’s Operating Handbook
(POH) for Light Sport Airplane
0.2 MANUFACTURER CONTACT INFORMATION
PROGRESSIVE AERODYNE
3801 State Road 19
Tavares, Florida 32778
United States of America
Phone: [phone]
Fax: [phone]
Email: [e-mail]
Website: www.Searey.com

Searey LSA –Pilot’s Operating Handbook Version 5.0, Revision 8
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0.3 SUPPORT CONTINUATION INFORMATION
In the event that Progressive Aerodyne becomes unable to support the
Searey LSA, a bulletin will be issued including the new location for data
and the contact information for recovery of certification documentation
and for further continued operational support.

Searey LSA –Pilot’s Operating Handbook Version 5.0, Revision 8
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Section 1 –General Information
1.1 INTRODUCTION TO AIRPLANE
The Searey LSA aircraft is a two-place factory-built amphibian produced
to fully meet the ASTM Light Sport Airplane industry standards. It is
powered by a Rotax, 4 cylinder, 4-cycle internal combustion engine. The
physical size is:
Wingspan: 30’ 10”
Length: 22’ 5”
Height: 7’ 2”

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1.2 PERFORMANCE SPECIFICATIONS
Gross Weight (MTOW)
1430 lbs.
VNE - Never Exceed Speed
120 MPH
VH (Adventure configuration:
Powered by Rotax 912 ULS, 100
HP engine) –Max. Cruise Speed
at 5500 RPM at Sea Level
95 MPH
VH (Elite configuration:
Powered by Rotax 914 UL, Turbo
charged, 115 HP engine) –Max.
Cruise Speed at 5500 RPM at
Sea Level
105 MPH
Full Fuel Range (Adventure
configuration, Powered by
Rotax 912ULS engine) with 30
minute Day VFR reserves (as
required by FAA)
75% Power at 5250 RPM burns 5.5 Gal/hr at 91
MPH with 30 minute reserve yields 317 miles at Sea
Level
At 5500 RPM, 6.6 Gal/hr at 96 MPH with 30 minute
reserve yields 259 miles at Sea Level
55% Power at 4700 RPM burns 4.0 Gal/hr at 80
MPH with 30 minute reserve yields 398 miles at Sea
Level
At 5250 RPM, 6.1 Gal/hr at 91 MPH with 30 minute
reserve yields 264 miles at Sea Level
Full Fuel Range (Elite
configuration, Powered by
Rotax 914 UL engine) with 30
minute Day VFR reserves (as
required by FAA)
75% Power at 5000 RPM burns 5.3 Gal/hr at 98
MPH with 30 minute reserve yields 430 miles at Sea
Level
55% Power at 4500 RPM burns 3.0 Gal/hr at 81
MPH with 30 minute reserve yields 554 miles at Sea
Level
Adventure configuration:
Engine Power Output (Rotax
912ULS)
Max Power: 98.6 HP (73.5 KW) at 5800 RPM, max 5
minutes
Max Continuous Power: 92.5 HP (69 KW) at 5500
RPM

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Elite configuration:
Engine Power Output (Rotax 914
UL)
Max Power: 115 HP (84.5 KW) at 5800 RPM, max 5
minutes
Max Continuous Power: 99.9 HP (73.5 KW) at 5500
RPM
Vy –Best Rate of Climb Speed
63 MPH IAS with 10 degrees of flaps
Vx –Best Angle of Climb Speed
58 MPH IAS with 20 degrees of flaps
Vs - Stall Speed with Flaps not
Extended
47 MPH IAS
Vso –Stall Speed with Flaps
Extended
40 MPH IAS with Flaps 30°
Va –Maneuvering Speed at
gross weight
92 MPH KCAS 94 MPH IAS
Va (min) –Maneuvering Speed at
minimum weight
79 MPH KCAS 82 MPH IAS
Total Fuel Capacity
23 Gallons
Total Usable Fuel
22 Gallons
Approved Fuel Types
Premium 91 Octane Minimum (R+N)/2 method or
100 LL AvGas –No more than 10% Ethanol by
volume (no ethanol in fuel preferable)

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Section 2 –Limitations
2.1 AIRSPEED INDICATOR –SPEED RANGE MARKINGS
COLOR
IAS
DESCRIPTION
White Arc
40 –80 MPH
Full Flap Operating Range
Lower limit is at Gross Weight. VSO in landing
configuration.
Upper limit is maximum speed permissible with flaps
extended. Vfe
Green Arc
47 –94 MPH
Normal Operating Range
Lower limit is at Gross Weight. VSwith flaps retracted.
Upper limit is maximum structural cruising speed (Vno)
Yellow Arc
94 –120 MPH
Caution Range
Operations must be conducted with caution and only in
smooth air.
Red Line
120 MPH
Never Exceed Speed - Vne

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2.2 STALLING SPEEDS AT MAXIMUM TAKEOFF WEIGHT (VSto VSO)
VS: 47 MPH IAS
VSO: 40 MPH IAS
2.3 FLAP EXTENDED SPEED RANGE (VSO to VFE):
40 –80 MPH
2.3.1 FLAP LIMITATIONS
Flap setting for takeoff and landing on water is 30 degrees. Takeoff from
land use 10 degrees and landing on land use 10 to 30 degrees.
1. Maximum positive load factor with flaps +2g
2. Maximum negative load factor with flaps -1g
2.4 MANEUVERING SPEED (VA) AT GROSS WEIGHT AND MINIMUM WEIGHT
94 MPH IAS, Gross weight
82 MPH IAS, Minimum weight
2.5 NEVER EXCEED SPEED (VNE)
120 MPH IAS
2.6 SERVICE CEILING
With Rotax 912 ULS (100 HP): 13000 feet
With Rotax 914 UL (115 HP Turbo charged): 17000 feet
2.7 MANEUVERING LOAD FACTORS
1. Maximum positive limit load factor + 4g
2. Maximum negative limit load factor - 2g
3. Maximum positive load factor with flaps +2g
4. Maximum negative load factor with flaps -1g
2.8 APPROVED MANEUVERS
This aircraft is intended for non-aerobatic flight and the following
maneuvers are approved
1. Any maneuvers incidental to normal flying
2. Stalls (except whip stalls)
3. Lazy eights, chandelles and steep turns in which angle of bank
does not exceed 40 degrees

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General limitations for maneuvering in this aircraft are:
30 degrees pitch, 40 degrees angle of bank
WARNING: Aerobatic maneuvers, including spins, are not permitted.
2.9 TOTAL FUEL CAPACITY
23 Gallons
2.10 TOTAL USABLE FUEL
22 Gallons
2.11 APPROVED FUEL TYPES
The Rotax engine(s) requires a minimum of 91 AKI ("premium"). Rotax
manuals mention a rating of 95. This rating is calculated based on the
RON standards used in Europe and is equivalent to a rating of 91 under
the AKI standards used in North America. Use of 100LL AvGas is also
allowed though not preferred. For further information refer to Rotax 912
ULS and 914UL series Operator’s Manual supplied with the aircraft.
In China besides AvGas 100LL, the fuel that can be used is 97#.
In all cases, we recommend using as high an octane rating as possible,
since fuel evaporates and quickly loses its octane rating when it lies in an
aircraft's fuel tank or in a plastic jug. A "premium" fuel will see its octane
rating reduced to unusable levels after as little as three weeks. Fuel with
a lower octane rating has an even shorter usable life.
Too low an octane rating will cause pre-ignition and detonation, which can
damage the piston ring grooves, skirt and crown.
Ethanol in fuel is allowed though not preferred up to a maximum of 10%
(E10). Ethanol added fuel can reduce its octane rating faster and should
be used up within a shorter period of time. Storage over longer period of
time requires removal of fuel.
2.12 MAXIMUM ENGINE POWER OUTPUT AT STATED RPM
With ROTAX 912ULS (Adventure Configuration)

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Maximum
Power*
(5 minutes)
98.6 HP /
73.5KW @ 5800
RPM
Maximum
Power
(sustained)
92.5 HP /
69.0KW @ 5500
RPM
With ROTAX 914UL (Elite Configuration)
Maximum
Power*
(5 minutes)
115 HP /
84.5KW @ 5800
RPM
Maximum
Power
(sustained)
99.9 HP /
73.5KW @ 5500
RPM
2.13 ENVIRONMENTAL LIMITATIONS
2.13.1 SMOKING
Smoking is prohibited at all times.
2.13.2 CROSSWIND COMPONENT
Maximum demonstrated crosswind component for takeoff and landing on
land: 15 MPH
WARNING: Water takeoff and landings should be done into the wind as
much as possible. Significant crosswind component can increase
operational hazards in water takeoff and landings
2.13.3 HEADWIND COMPONENT
Maximum permissible headwind component for takeoff and landing: 20
MPH
2.13.4 TAILWIND COMPONENT
Maximum permissible tailwind component for takeoff and landing: 5 MPH

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2.13.5 AMBIENT TEMPERATURE
Flights are permitted only under no icing conditions. Operational
temperature range is -13 degrees to 120 degrees Fahrenheit.
2.13.6 ICING CONDITIONS
Flight into known icing conditions is prohibited.
2.13.7 CLOUDS, STORMS and OTHER WEATHER EVENTS
This aircraft is not certified for operation in IMC (Instrument
Meteorological Conditions) or heavy rain operation. Always stay clear of
clouds and have visual contact with the ground. Follow the airspace
classification regarding distance from clouds. Always evaluate weather
during your flight and try to get weather information from your destination
using radio whenever possible. When weather is deteriorating make a
diversion or turn back before the low cloud base and/or low visibility are
critical.
2.14 VFR NIGHT OR IFR USE LIMITATIONS
The aircraft is not intended for IFR. VFR night flight on clear nights with
operating lights is allowed. The landing lights should only be used while
takeoff or landing and not continuously. Water landings at night without
lighting assistance from the water are not allowed and can be very
dangerous.
2.15 REQUIRED EQUIPMENT
Do not operate this aircraft without at least the following equipment
operation except as allowed by local civil aviation authority regulation for
the purpose of flying to a repair facility or mechanic such as FAR 91.215
1. Air Speed Indicator
2. Altimeter
3. Magnetic Heading indicator (required for United States per Part 91.205)
4. Oil Temperature indicator
5. Oil Pressure indicator
6. Cylinder Head Temperature indicator (at least one, hotter cylinder)
7. Engine Tachometer or RPM indicator
8. Manifold Pressure Gauge (914UL Elite configuration only)
9. Fuel Level indication
10. Landing Gear Position indication (use visual if needed)

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Section 3 –Emergency Procedures
3.1 GENERAL INFORMATION ON EMERGENCY PROCEDURES
This section contains procedures for various emergencies that may occur.
Emergencies caused by aircraft or engine malfunctions are rare if proper
pre-flight inspections and maintenance are practiced. Not all emergencies
that may occur can be listed here in full; therefore their solution depends
on experience of the crew controlling the course of such events.
3.2 AIRSPEEDS FOR EMERGENCY PROCEDURES
SPEED
Engine Failure After Takeoff
Wing Flaps Up
65 MPH
Engine Failure After Takeoff
Wing Flaps Down 30°
60 MPH
Landing without Engine
Flaps Up
57 MPH
Landing without Engine
Flaps Down 30°
47 MPH
3.3 EMERGENCY CHECKLISTS
3.3.1 ENGINE FIRE DURING START
Due to the high-octane fuel carried by the aircraft, there is always the
possibility of a violent explosion occurring if an aircraft catches fire.
Personnel are therefore warned not to take undue risks in attempting to
save an aircraft that is obviously well alight. A small fire extinguisher is
only meant to be used on small fires. For large fires, trained personnel
with appropriate equipment are required.
Throttle
CLOSED
Ignition
OFF
Fuel
OFF
Master Switch
OFF
Evacuate the aircraft and move away
Extinguish fire (if possible)
Fire damage
INSPECT

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3.3.2 ENGINE FAILURE DURING TAKEOFF
3.3.2.1 ENGINE FAILURE DURING TAKEOFF RUN
If sufficient runway/strip/waterway is available, lower the nose and come
to a complete stop in a controlled manner. If there are obstacles in the
path of the aircraft a slight change in heading may be made to line up on
the most suitable area that is safe until aircraft slows down especially on
water.
Throttle
CLOSE
Brakes
APPLY
Ignition
OFF
3.3.2.2 ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF
If the altitude above ground is low, make an immediate plan for finding a
landing point to which a slow but controlled landing can be made with least
impact of the fuselage. Do not try to return to the runway unless there is
enough altitude to work with and a clear approach can be made. Consider
the effect of the wind, as a downwind landing will likely be made. If
possible, shut off the fuel supply valve and master switch. Once a safe
landing is assured, do not try to restart the engine, simply execute the
landing.
Airspeed –Flaps UP
65 MPH
Airspeed –Flaps DOWN
60 MPH
Fuel
OFF
Ignition
OFF
Wing Flaps
AS REQUIRED
3.3.3 LOSS OF ENGINE POWER DURING FLIGHT
Airspeed
60 MPH
Fuel (troubleshoot)
CHECK ON
Electric Fuel Pump
ON
Ignition –if propeller is stopped
START

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3.3.3.1 RESTARTING THE ENGINE DURING FLIGHT
It is unlikely that the engine will stop during normal maneuvers. However,
in the event of the engine stopping in flight, the following procedure will
normally allow the engine to be restarted without problems.
3.3.3.1.1 USING STARTER MOTOR
Throttle
OPEN 1/4
Fuel
CHECK ON
Electric Fuel Pump
ON
Master Switch
ON
Ignition
BOTH L & R ON
Starter
TURN KEY & START
CAUTION: Because of the high compression ratio of the Rotax four-cycle
engines, the propeller will not windmill, even in a steep dive. If the engine
cannot be restarted by using the starter motor, carry out the procedure as
set out in Section 3.3.4 of this document.
3.3.3.2 ENGINE FAILURE CHECKS
3.3.3.2.1 INITIAL CHECK
Clogged fuel line or filter or hole in fuel line?
Fuel
ON
Fuel Sump
CHECK CONTENTS
3.3.3.2.2 TROUBLESHOOT
Fuel
ON –Contents sufficient
Oil pressure & temperature
NORMAL
Ignition
CHECK L & R - Both
Switches ON
Throttle
OPEN - check for operation
Choke
OFF

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3.3.3.2.3 SAFETY CHECK
Brakes
OFF
Switches
OFF –Ignition and Master
Fuel Pumps / Fuel
OFF
Occupants
HARNESS SECURE
Canopies/Hatches
SET FOR LANDING
Undercarriage
SET FOR LANDING
3.3.3.3 CARBURETOR ICING
A gradual loss of RPM and eventual engine roughness may result from
the formation of carburetor ice. The chance of the formation of carburetor
ice is reduced by the use of a carburetor heater warmed by engine
coolant and is always on the Adventure Configuration (912ULS powered).
On Elite configuration with 914UL powered aircraft, the chance of
carburetor icing is reduced by the use of the turbo compressor and the
engine cowling where some hot air is directed to the air filters under the
cowling continuously. Thus no pilot action to turn on carburetor heat is
required.
3.3.3.4 SPARK PLUG FOULING
A slight engine roughness in flight may be caused by one or more spark
plugs becoming fouled. This may be verified by turning the ignition switch
from BOTH to either L or R position. An obvious power loss in a single
ignition operation is evidence of spark plug trouble.
3.3.4 EMERGENCY LANDING WITHOUT ENGINE POWER
Wing Flaps
20 Degrees
Airspeed
60 MPH
Fuel
OFF
Ignition
OFF
Radio, if available
Transmit Distress Call
Transponder, if available
Set code 7700
Sliding Canopies
Unlatched, Partially Open
Touchdown
LAND: Brake hard
WATER: As normal
IF SHORT: Back stick
3.3.4.1 OTHER PROCEDURES FOR LANDING WIHTOUT ENGINE POWER
Convert any excess speed to height and at the same time perform the
checks listed in paragraph 3.3.3.2.1.
Place the aircraft at optimum gliding angle/attitude/speed.

Searey LSA –Pilot’s Operating Handbook Version 5.0, Revision 8
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Select the most suitable field/waterway, bearing in mind height above
the ground, wind speed and direction and the availability of assistance
after landing.
Plan descent in relation to the selected field/waterway –aiming to
reach a base leg position –as for a normal glide approach.
Keeping within easy gliding distance of the field/waterway, carry out
the procedure listed in paragraph 3.3.3.2.2.
If the engine cannot be restarted, continue as planned, brief the
passenger and send distress signal, if radio is available.
During descent, use flaps intelligently. Aim to have 10of flap on
base leg –use 30when you are sure of making the field/waterway –
turn off all fuel and electrical switches at a time early enough not to
interfere with concentration over the final stages of the emergency
landing. Refer to paragraph 3.3.3.2.3.
NOTE: If intending to use the aircraft radio for communication, make a
thorough inspection to ensure that no fuel is spilled that would be likely to
cause a fire if the electrical circuits are reactivated.
3.3.4.2 DITCHING (Without power)
Landing Gear
UP POSITION
Radio, if available
TRANSMIT DISTRESS CALL
Transponder, if available:
SQUAWK 7700
Baggage, etc.
SECURE OR JETTISON
Approach
HIGH WINDS/HEAVY SEAS –Into Wind
LIGHT WINDS/HEAVY SWELL –Parallel to
swell
Wing Flaps
30
Airspeed
55 MPH
Passenger
Brief –Headset, Seat Belts, Canopy,
Orientation, Cockpit Exit, Life Jacket/Raft,
Face Protection, Clothing