ICON A5 FOUNDER’S EDITION Pilot Operating Handbook

PILOT’S
OPERATING
HANDBOOK

MODEL A5

FOUNDER’S EDITION

Publication ICA012347, Issue A3
Airplane Registration Number:_________________________
Airplane Serial Number:________________________________
Date: 22 August 2018

ICON Aircraft / 2141 ICON Way, Vacaville, CA 95688

ICON Aircraft, Inc.
2141 ICON Way
Vacaville, CA 95688
https://www.iconaircraft.com

All rights reserved. No part of this manual may be
reproduced or copied in any form or by any means
without written permission of ICON Aircraft, Inc.

II

RECORD OF MANUAL/HANDBOOK REVISIONS / ISSUE A3 III

RECORD OF MANUAL/HANDBOOK REVISIONS

This section gives a record of the Pilot’s Operating Handbook
revisions in the current issue series (Issue A, Issue B, etc.). Further
description of the revisions by issue and chapter can be found
below.

Issue Date Chapter(s) Added By

A 02 August 2017 All ICON Aircraft
A1 16 February 2018 3,4,7,9 ICON Aircraft
A2 11 April 2018 2,3,4,7,9 ICON Aircraft
A3 22 August 2018 2,4,7,8,9 ICON Aircraft

ISSUE A3

The following are a list of revisions for Issue A3.

Chapter 2

• Corrected typo in the word ‘supplying’ in the warning for
Minimum Load Rating of Cargo Restraints (Pilot Supplied)

• Updated text of Environmental Limitations

• Revised reference to FAA exemption number

• Corrected graphic font error in Secure Loose Objects placard

• Updated the ELT Remote Switch placard

Chapter 4

• Updated text of Step Taxi/Normal Takeoff—Water

Chapter 7

• Updated text of Flight Controls

• Updated placard in ELT Remote Control and Audio Alert Indi­cator

Chapter 8

• Updated text of Cleaning and Care related to Corrosion Inhib­itor

Chapter 9

• Updated FAA Exemption

ISSUE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

IV RECORD OF MANUAL/HANDBOOK REVISIONS / ISSUE A2

ISSUE A2

The following are a list of revisions for Issue A2.

Chapter 2

• Changed Complete Aircraft Parachute to ICON Parachute
System (IPS)

Chapter 3

• Changed Complete Aircraft Parachute to ICON Parachute
System (IPS)

Chapter 4

• Changed Complete Aircraft Parachute to ICON Parachute
System (IPS)

Chapter 7

• Changed Complete Aircraft Parachute to ICON Parachute
System (IPS)

Chapter 9

• Changed Complete Aircraft Parachute to ICON Parachute
System (IPS)

ISSUE A1

The following are a list of revisions for A1.

Chapter 3

• Small formatting changes

• Updated Electrical Fire in Flight

• Added Box-Canyon Reversal

Chapter 4

• Updated Before Cockpit Entry

Chapter 7

• Correct typos

• Updated ICON Parachute System

Chapter 9

• Updated ICON Parachute System

ICON A5 / PILOT’S OPERATING HANDBOOK ISSUE A3

RECORD OF MANUAL/HANDBOOK REVISIONS / ISSUE A V

ISSUE A

The following are a list of revisions for Issue A.

All Chapters

• Initial release of Founder’s Edition POH

ISSUE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

VI RECORD OF MANUAL/HANDBOOK REVISIONS / ISSUE A

ICON A5 / PILOT’S OPERATING HANDBOOK ISSUE A3

LIST OF EFFECTIVE CHAPTERS / VII

LIST OF EFFECTIVE CHAPTERS

The table below shows the current, effective chapters and dates in
this revision of the handbook (see previous section). The applicable
handbook issue is listed at the bottom corner of this page for
reference.

Chapter Change Date

0. Introduction A0 02 August 2017

1. General Information A0 02 August 2017

2. Limitations A2 22 August 2018

3. Emergency Procedures A2 11 April 2018

4. Normal Procedures A3 22 August 2018

5. Performance A0 02 August 2017

6. Weight, Balance, and
Equipment List

7. Description of Airplane
and Systems

8. Handling and Servicing A1 22 August 2018

9. Supplements A3 22 August 2018

A0 02 August 2017

A3 22 August 2018

ISSUE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

VIII LIST OF EFFECTIVE CHAPTERS /

ICON A5 / PILOT’S OPERATING HANDBOOK ISSUE A3

TABLE OF CONTENTS IX

Table of Contents

CHAPTER

Record of Manual/Handbook Revisions . . . . . . . . . . . . . . . . .

List of Effective Chapters . . . . . . . . . . . . . . . . . . . . . . . . .

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0

General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2

Emergency Procedures . . . . . . . . . . . . . . . . . . . . . . . . . .3

Normal Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4

Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5

Weight, Balance, and Equipment List . . . . . . . . . . . . . . . . . .6

Description of Airplane and Systems . . . . . . . . . . . . . . . . . . 7

Handling and Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . .8

Supplements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9

ISSUE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

INTRODUCTION / ASTM STANDARDS 0-2

CHAPTER 0

Chapter 00

INTRODUCTION

ASTM Standards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0-2

Contact Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0-3

Data Location Information. . . . . . . . . . . . . . . . . . . . . . . . . . . 0-3

Handbook Revisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0-3

Symbols. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0-4

0.1 ASTM STANDARDS

FAA-accepted consensus standards are utilized for the design,
construction, and continued airworthiness of the ICON A5. This
aircraft complies with the following ASTM standards:

F2245

Standard Specification for Design and Performance of a Light
Sport Aircraft

F2295

Standard Practice for Continued Operational Safety Moni­toring of a Light Sport Aircraft

F2746

Standard Specification for Pilot’s Operating Handbook (POH)
for Light Sport Airplane

F2972

Standard Specification for Light Sport Aircraft Manufacturer’s
Quality Assurance System

This Pilot’s Operating Handbook is in compliance with ASTM
Standard F2746.

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

0-3 INTRODUCTION / CONTACT INFORMATION

CHAPTER 0

0.2 CONTACT INFORMATION

The following is the name and contact information of the
manufacturer of the ICON A5.

ICON Aircraft, Inc.
2141 ICON Way
Vacaville, CA 95688
+001 707 564 4000

https://www.iconaircraft.com

0.3 DATA LOCATION INFORMATION

Below is the data location and contact information for recovery of
certification documentation, should ICON Aircraft lose its ability to
support the aircraft.

ICON Aircraft, Inc.
2141 ICON Way
Vacaville, CA 95688
+001 707 564 4000

0.4 HANDBOOK REVISIONS

This handbook utilizes section-level revision control. Each page of
the handbook contains a revision indication in the lower, inside
corner. Revision indicators are consistent within an entire section,
but can vary from section to section.

A major release of the handbook is called an “Issue”. The issue letter
and its effective date are listed on the title page of the handbook
using a letter code; for example, “Issue A”.

Updates and changes to the handbook are called “Revisions” and
are designated using an issue prefix followed by a number; for
example, “Revision A2” is the second revision of “Issue A”. These
revisions are listed on the Record of Manual/Handbook Revisions
page near the front of the handbook. Owners are responsible for
keeping this page updated when handbook revisions are issued by
ICON.

Updates and changes to sections of the handbook are called
“Changes” and are designated using the issue prefix followed by a
number; for example, “Change A0” is the original release of a

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

INTRODUCTION / SYMBOLS 0-4

CHAPTER 0

section in Issue A and “Change B3” is the third revision of a section
in Issue B of the entire handbook. The “List of Effective Sections”
near the front of the handbook documents the applicable section
“Changes” associated with a given handbook revision.

Revisions to this Pilot’s Operating Handbook will be distributed to all
owners of relevant aircraft registered with ICON. Distribution will
include new pages for the sections that have changed, a new List of
Effective Sections, and any necessary instructions. Revisions should
be examined immediately upon receipt and incorporated into this
handbook per the instruction provided.

It is the responsibility of the owner to maintain this POH in a current
state when it is being used for operational purposes. Owners should
contact ICON whenever the revision status of their POH is in
question.

0.5 SYMBOLS

For a full list of Symbols, Abbreviations, and Terminology, see
Chapter 9, Supplements.

This handbook uses the following symbols and definitions to
emphasize important information.

WARNING: Indicates a potentially hazardous situation

which, if not avoided, could result in serious
injury or death.

CAUTION: Indicates a potentially hazardous situation or

instruction which, if not avoided or followed,
may result in minor or moderate injury or
severely damage the aircraft.

NOTE: Indicates supplementary information that

may be needed to fully complete or under­stand an instruction.

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

GENERAL INFORMATION / AIRPLANE INTRODUCTION 1-2

CHAPTER 1

Chapter 01

GENERAL INFORMATION

Airplane Introduction. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2

Illustrations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3

Summary of Performance Specifications . . . . . . . . . . . . . . 1-4

1.1 AIRPLANE INTRODUCTION

The ICON A5 is a two-seat, single-engine, amphibious Light Sport
Aircraft. The A5 has a conventional high wing, tail-aft configuration
with ailerons, flaps, elevator, rudder and water rudder control
surfaces. The wings are manually foldable with the flight controls
(ailerons and flaps) connecting automatically. The tricycle landing
gear is retractable. The A5 is equipped with a Rotax 912iS Sport,
4-cylinder, horizontally-opposed, reciprocating engine of 100
horsepower. Installed equipment provides for flight in day and night
VFR conditions. Fuel is contained in a single fuselage-mounted tank.
Flight controls employ conventional push-pull tubes, torque tubes
and cables. The primary flight controls are conventional sticks and
rudders (with toe brakes) for each seat. An electrically operated
pitch trim tab is controlled from the pilot’s (left seat) stick only.

1.1.1 DESCRIPTIVE DATA

Parameter Val ue

Wing Span 34.8 ft

Wing Area

Aspect Ratio 9.0
Overall Length 23.0 ft
Overall Height at Ground Attitude 7.5 ft
Wheel Base 7.7 ft
Main Landing Gear Track Width 5.8 ft
Draft at Gross Weight, Landing Gear Up 14 in
Draft at Gross Weight, Landing Gear

Down

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

135 ft

26 in

2

1-3 GENERAL INFORMATION / ILLUSTRATIONS

CHAPTER 1

1.8' WING FOLD
EXTENSION

7.7' WITH TAIL
TIPS REMOVED

FOLDED WING
CONFIGURATION

R15.7'
WING FOLD AREA

FOLDED WING
CONFIGURATION

Ø68"

7.8' WINGS FOLDED

34.8'

5.8'

7.5' SEAWING
TIP REMOVED

8.0'

GROUND DATUM

8.3'

7.3'

8.1'

2.3"

2"

GROUND DATUM

23.0'
FOLDED WING
CONFIGURATION

1.2 ILLUSTRATIONS

FIGURE 1-1

AIRCRAFT 3-VIEW DRAWING

11.2'

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

7.7'

GENERAL INFORMATION / SUMMARY OF PERFORMANCE SPECIFICATIONS 1-4

CHAPTER 1

1.3 SUMMARY OF PERFORMANCE SPECIFICATIONS

Parameter Val ue

Gross Weight

Top Speed at SL, VH (MCP, 5500 RPM)

Cruise Speed, 5000 RPM, 8000 ft 84 KTAS
Range (5000 RPM, 8000 ft, including

takeoff and climb from SL)
Best Angle of Climb Speed, V

Best Angle of Climb Speed, V

(Flaps 0°)

X

(Flaps

X

15°/30°)
Best Rate of Climb Speed, V

Rate of Climb at V

Rate of Climb at V

Stall Speed, V

(SL)

X

(SL)

Y

(Flaps and landing gear

S

Y

up)
Stall Speed, V

(Flaps and landing gear

S0

down)
Total Fuel Capacity 20.1 US gallons
Total Usable Fuel 20 US gallons

Approved Types of Fuel

Max Engine Power at SL 100 hp at 5800 RPM (5 min max)
Max Demonstrated Direct Crosswind

Component—Land and Water (not a
limitation)

Service Ceiling at Gross Weight (100
ft/min Climb Rate)

1510 lb

f

95 KTAS

427 nm (with 45 min reserve)

54 KIAS

50 KIAS

58 KIAS

616 ft/min

629 ft/min

45 KIAS

39 KIAS

Unleaded automotive fuel with up to 10%
maximum ethanol content meeting ASTM
D4814 with minimum RON 95 (minimum
Anti-Knock Index 91)
Grade 100LL aviation gasoline (AVGAS)
meeting ASTM D910

12 knots

15,000 ft

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

LIMITATIONS / INTRODUCTION 2-2

CHAPTER 2

Chapter 02

LIMITATIONS

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-2

Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-2

Airspeed Indicator Markings. . . . . . . . . . . . . . . . . . . . . . . . . .2-3

Service Ceiling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-4

Human Load Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-4

Baggage/Cargo Limitations . . . . . . . . . . . . . . . . . . . . . . . . . .2-5

Load Factors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6

Water Speed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6

Approved Maneuvers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7

Fuel Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-7

Engine Oil Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9

Engine Coolant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9

Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-10

Environmental Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . .2-10

VFR and IFR Use Limitations . . . . . . . . . . . . . . . . . . . . . . . . 2-12

ICON Parachute System (IPS) Limitations . . . . . . . . . . . .2-12

Spin-Resistant Airframe (SRA) Limitations . . . . . . . . . . .2-12

Exemption Required Equipment Limitations . . . . . . . . . .2-13

Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-13

2.1 INTRODUCTION

This section includes the operating limitations necessary for the
safe operation of the airplane.

2.2 AIRSPEED LIMITATIONS

Speed KIAS Remarks

V

S0

V

S

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

Stall Speed, MTOW,
Flaps 30°

Stall Speed, MTOW,
Flaps 0°

39 Idle power

45 Idle power

2-3 LIMITATIONS / AIRSPEED INDICATOR MARKINGS

CHAPTER 2

Speed KIAS Remarks

VFE and V

V

O-min

V

O-max

V

N0

V

NE

LE

Maximum Flap and
Landing Gear
Extended Speed

Operating
Maneuvering
Speed, 1145 lb

, Min

f

Flight Weight

Operating
Maneuvering
Speed, MTOW

Max Structural
Cruising Speed

Never Exceed
Speed

75

76

87

95

120

Operation and
extended speeds
are the same.

Do not make full or
abrupt control
movements above
this speed.

Do not make full or
abrupt control
movements above
this speed.

Do not exceed this
speed except in
smooth air.

Do not exceed this
speed in any
operations.

2.3 AIRSPEED INDICATOR MARKINGS

FIGURE 2-1

AIRSPEED INDICATOR

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / SERVICE CEILING 2-4

CHAPTER 2

Marking KIAS Range Significance

Full flap operating range.
Lower limit is maximum
weight stall speed in

White Arc 39-75

Green Arc 45-95

Yel l o w A rc 9 5 -1 2 0

Red Line 120

landing configuration.
Upper limit is maximum
speed permissible with
flaps and landing gear
extended.

Normal operating range.
Lower limit is maximum
weight stall speed with
flaps retracted. Upper limit
is the maximum structural
cruising speed.

Operations must be
conducted with caution,
and only in smooth air.

Maximum speed for all
operations.

2.4 SERVICE CEILING

The service ceiling (the maximum altitude at which a climb rate of
100 ft/min can be maintained) is 15,000 ft at MTOW, standard
conditions.

2.5 HUMAN LOAD LIMITATIONS

Maximum Human Weight

250 lb

per person

f

The carbon structure of the A5 though strong, can be damaged if
loaded in an unintended manner. The A5 is designed to support a
person of up to 250 lb

total weight wearing normal soft-soled

f

shoes. High load concentrations that can be created by things such
as stylish shoes, heels, knees, and elbows must be avoided by all
people, particularly if heavy.

Surfaces approved for standing, sitting, or kneeling:

• Cockpit floors

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-5 LIMITATIONS / BAGGAGE/CARGO LIMITATIONS

CHAPTER 2

• Top surface of each Seawings™ forward of the aft limit of the
step pad

•Seats

•Canopy jambs

Surfaces approved for sitting only:

• Top surface of the left and right wings in the area bounded by
the wing leading edge, side of engine cowling, station of the
forward edge of the IPS cut out, and wing fold joint

All surfaces of the fuselage, Seawings™, wings, and horizontal tail
other than those specified above are not approved for standing,
kneeling, or sitting regardless of the weight of the individual.

CAUTION: The seats, interior, Seawings™ step areas

and safety restraints are designed to support
a person of 250 lb

maximum weight. Do not

f

exceed this limit. Exceeding the maximum
human weight limit or loading the aircraft in an
unapproved manner could result in an unsafe
condition and damage to the aircraft.

NOTE: The above limit makes no statement about

weight and balance. Always perform a weight
and balance procedure for any new loading
condition.

2.6 BAGGAGE/CARGO LIMITATIONS

Maximum Baggage/Cargo Weight

60 lb

f

WARNING

: Loading a concentrated weight fully aft in the

baggage area may cause an unsafe aft CG
condition.

Minimum Number of Anchor Loops

At least three (3) out of the six (6) provided anchor loops must
be used in order to safely restrain the full baggage/cargo load.

Minimum Load Rating of Cargo Restraints (Pilot Supplied)

1000 lb

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

f

LIMITATIONS / LOAD FACTORS 2-6

CHAPTER 2

WARNING: The pilot is responsible for properly

restraining the baggage/cargo. At least three
(3) out of the six (6) provided anchor loops
must be used in order to safely restrain the
load. The pilot is responsible for supplying a
properly rated cargo restraint to interface
with the anchor loops built into the A5.

2.7 LOAD FACTORS

Design Maneuvering Limit with flaps at 0° and 1510 lb

aircraft

f

weight

+4, -2 g

Design Maneuvering Limit with flaps at 15°/30° and 1510 lb
aircraft weight

+2 g

Landing Gear Extension/Retraction

+1.5 g

NOTE: Do not extend or retract the landing gear with

more than this load on the aircraft.

Engine

Limit of engine operation at zero gravity and in negative gravity
conditions.

Maximum of 5 seconds at maximum -0.5 g.

NOTE: These are not operational limits (-2 g is for

structural load purposes).

2.8 WATER SPEED LIMITATIONS

f

Maximum water speed for landing gear extension/retraction

4 knots (idle power setting)

Maximum water speed with water rudder extended

10 knots

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-7 LIMITATIONS / APPROVED MANEUVERS

CHAPTER 2

2.9 APPROVED MANEUVERS

2.9.1 IN FLIGHT:

All aerobatic maneuvers are prohibited. The aircraft is not certified
for aerobatics, inverted flight, or sustained zero ‘g’ or negative ‘g’
flight.

Intentional or attempted spins are prohibited.

Prolonged periods in stalled flight are to be avoided.

2.9.2 ON THE WATER:

Low speed taxiing turns on the water while off the step in
displacement or plowing modes are approved. Gentle turns while on
the step and up to takeoff speeds are also approved.

Aggressive turns while on the step and up to takeoff speeds should
be avoided and may induce a water loop. Water loops are not
approved and could cause damage to the nose gear doors or
Seawings™.

WARNING: Contacting the wing tip with the water while

in motion can create a dangerous situation
and must be avoided. The planing wing tip
design is intended as a safety precaution for
inadvertent wing tip water contact and should
never be used intentionally or relied upon for
safety.

2.10 FUEL LIMITATIONS

Total Fuel Capacity

20.1 US gallons

Total Usable Fuel

20 US gallons

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / FUEL LIMITATIONS 2-8

CHAPTER 2

Approved Types of Fuel

a) Unleaded automotive fuel with up to 10% maximum

ethanol content meeting ASTM D4814 with minimum
RON 95 (minimum Anti-Knock Index 91)

b) Grade 100LL aviation gasoline (AVGAS) meeting ASTM

D910

NOTE: Use of leaded gasoline decreases the mainte-

nance interval for changing the oil filter,
cleaning the oil tank, and replacing spark
plugs. See the A5 Maintenance Manual for
further information.

NOTE: Anti-Knock Index is (RON+MON)/2. RON is

Research Octane Number and MON is Motor
Octane Number.

CAUTION: Due to various environmental, economic, and

political reasons, fuels with different blends
of ethanol, oxygenators, and other additives
may be encountered when using automotive
gasoline. Be careful to use only fuel suitable
for your operational climate zone since there
is a risk of fuel vapor formation if using
winter-blend, or other high vapor pressure
fuel, in summer-type weather or at high alti­tude. Vapor formation can result in fuel pump
cavitation, low fuel pressure, and engine
power loss. This phenomenon is most likely
to be encountered in a full throttle climb at
high altitude and in hot weather. An occa­sional flash of the fuel pressure annunciator
light is acceptable, but if the fuel pressure
light flashes frequently, continuously, or if any
sort of power loss, stumbling or surging is
observed, land as soon as practical and
contact ICON Owner Support. The problem
may be poor fuel quality or an inappropriate
blend of automotive fuel. If these are the case
then 100LL Aviation fuel should be used until
a suitable type of automotive fuel can be
sourced.

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-9 LIMITATIONS / ENGINE OIL LIMITATIONS

CHAPTER 2

Mixing of Fuel Types

The A5 fuel system is designed to allow mixing of automotive
fuel and AVGAS.

2.11 ENGINE OIL LIMITATIONS

Approved Oil Specifications

Viscosity—SAE 10W-40 multi-grade

API classification SG or higher

Registered brand heavy-duty four-stroke motorcycle oil with
gear additives

CAUTION: Do not use oils containing friction modifier

additives as this could result in clutch slip­page.

CAUTION: Do not use conventional a.d. (ashless disper-

sant) aircraft oils.

CAUTION: Do not use oils intended primarily for diesel

engines.

CAUTION: Do not use any oil additives.

Recommended Oil

Shell brand AeroShell Sport Plus 4

2.12 ENGINE COOLANT LIMITATIONS

The engine coolant must be a mixture of 50% ethylene glycol based
antifreeze and 50% distilled water. The antifreeze portion of the
coolant mixture should be a low silicate and nitrite-free formula.

A list of approved antifreeze is included in the table below:

Brand Description

BASF Glysantin Protect Plus/G48
CASTROL Antifreeze All-Climate
CASTROL Antifreeze Anti-Boil
OMB OMB Coolant Plus
PETROL Antifreeze Concentrate/ Antifreeze G11

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / ENGINE 2-10

CHAPTER 2

Brand Description

PRESTONE DEX-COOL extended life

PRESTONE

SHELL DEX-COOL
SHELL Antifreeze Concentrate
TEXACO Havoline Extended Life Antifreeze
VELVANA FRIDXE G49
YACCO LR-35

50/50 prediluted DEX COOL extended
life

2.13 ENGINE

One Rotax 912iS Sport, 4-stroke, 4-cylinder horizontally opposed,
spark ignition

Maximum Rated Power at Sea Level, Standard Day

100 hp at 5800 RPM

NOTE: Per the Rotax Manual, the engine should only

be run at this setting for a maximum of 5
minutes.

Ignition Switch

Operate Starter for a no more than 10 seconds, continuous
cranking, followed by a cooling period of 2 minutes before next
attempt

Maximum Continuous Power

97 hp at 5500 RPM

Idle Speed

1700 ± 75 RPM (A5 requirement)

2.14 ENVIRONMENTAL LIMITATIONS

Aircraft Temperature Limitations

The design temperature ranges for the aircraft are as follows:
Storage: -40°F and 150°F
Operations in dry conditions: -20°F to ICAO+50°F (109°F at
sea level)

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-11 LIMITATIONS / ENVIRONMENTAL LIMITATIONS

CHAPTER 2

Operations in wet conditions: 40°F to ICAO+50°F (109°F at
sea level)

NOTE: The paint scheme was chosen to minimize

solar absorptivity to prevent critical struc­tures from exceeding 150°F.

NOTE: The low temperature limit in wet conditions is

to help avoid water freezing in critical
systems.

Visible Moisture

Avoid flying in visible moisture at air temperatures below
40°F/5°C. The air filter may ice up and ice may collect on the
aircraft and create an unsafe condition.

CAUTION: Do not operate the aircraft in freezing

temperatures if water is present on the
airframe. Freezing water can impair the func­tion of critical systems such as instrumenta­tion, flight controls, and landing gear.

Water Operations Limitations

Maximum suggested wave height (from crest to trough): 12
inches.

Salt water operations are approved. Rinse with fresh water
afterward per the procedure in Chapter 8.

The A5 uses aerospace paint, not marine paint. The paint can
withstand 96 hours of continuous direct contact with water.
Exceeding the 96 hours or securing aircraft where it may come
in contact with rocks or other abrasive objects may result in
visible degradation or permanent damage to paint and/or hull
structure.

During non-operational continuous direct contact with water
the aircraft should be checked at least every 24 hours for a
purge bilge light. If purge bilge light is illuminated, run the bilge
to remove acquired water. This is necessary as the A5 does
not have an automatic bilge pump and is not designed for
prolonged storage in water.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / VFR AND IFR USE LIMITATIONS 2-12

CHAPTER 2

Open Canopy Wind Limitations

The maximum design wind speed for opening the canopy is 25
knots.

NOTE: Be cautious when opening the cockpit

canopy in windy conditions to avoid losing
control of it. Do not leave the aircraft unat­tended with the canopy open.

2.15 VFR AND IFR USE LIMITATIONS

VFR Flight

This airplane is equipped for day and night VFR operations
only. Operate in VMC only.

IMC Flight

IMC flight is prohibited.

2.16 ICON PARACHUTE SYSTEM (IPS) LIMITATIONS

There are no restrictions on the use of the IPS. Optimal IPS
actuation is from level flight above 500 ft AGL.

2.17 SPIN-RESISTANT AIRFRAME (SRA) LIMITATIONS

The aircraft must be operated with the following items in place to
maintain SRA compliance:

Wing stall strips—quantity 2 (1 per side)

Wing vortex generators—34 pair (17 pair per side)

NOTE: Up to 3 wing vortex generators are allowed to

be missing on each wing so long as there are
at least 3 good vortex generators between
any two missing ones.

Fuselage vortex generators—quantity 10 (5 per side)

Flap fences—quantity 2 (1 per side)

When flying with side windows removed, a wind deflector must be
installed on each A-pillar, just above the lower window jamb. Install

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-13 LIMITATIONS / EXEMPTION REQUIRED EQUIPMENT LIMITATIONS

CHAPTER 2

one deflector on the left A-pillar and one on the right A-pillar. Flight
with only one side window installed is not approved.

2.18 EXEMPTION REQUIRED EQUIPMENT LIMITATIONS

Per FAA exemption number 10829B, all interior panels, floorboards,
and other covers must be installed for flight. In addition, the AOA
and ballistic recovery parachute systems must be functional.

2.19 PLACARDS

2.19.1 GENERAL INFORMATION

The placards shown in this section are safety, operational, or
standards-required placards and must be installed on the aircraft at
all times. Labels and markings on other instruments and controls are
not given.

2.19.2 INTERIOR

Fuel Shutoff

Located on the overhead console.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / PLACARDS 2-14

CHAPTER 2

Max Amperage for USB and 12V Accessory Port

Located inside of arm rest in center console.

Maneuvering Speed

Located on the left side above the ignition and master switch.

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-15 LIMITATIONS / PLACARDS

CHAPTER 2

Baggage Area

Located in the baggage compartment aft of the occupant seats.

Secure Loose Objects

Located on the window jamb beneath the removable windows (only
visible when window is removed). There are two per aircraft—one on
the right side and one on the left side.

Parking Brake

Located next to the parking brake.

Window Removal Procedure

Located on the removable window. There are two per aircraft—one
on the right side and one on the left side.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / PLACARDS 2-16

CHAPTER 2

K

E

E

P

H

A

N

D

S

C

L

E

A

R

Window Installation Procedure

Located on the window jamb beneath the removable windows (only
visible when window is removed). There are two per aircraft—one on
the right side and one on the left side.

Wind Deflector Alignment and Instructions

Located on the wind deflector. There are two per aircraft—one on
the right side and one on the left side (when installed).

Keep Hands Clear

Located on the canopy jamb. There are two per aircraft—one on the
right side and one on the left side.

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-17 LIMITATIONS / PLACARDS

CHAPTER 2

Open Canopy

Located above the occupant seats under the canopy latch handle.

Passenger Warnings and Kinds of Operation

Located near the front of the overhead canopy.

Registration Numbers

Located on center console of cockpit.

NOTE: Registration numbers are for illustration only.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

Your aircraft registration number will be
different.

LIMITATIONS / PLACARDS 2-18

CHAPTER 2

Fuselage Station

Located in cockpit above the baggage compartment on the forward
face of the wing spar and beneath the headliner panel.

Do Not Jump Start

Located under battery charging terminals on right, inside surface of
fuselage near passenger rudder pedals.

Fuses

Located on overhead console.

ELT Remote Switch

Located on overhead console on ELT remote control.

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-19 LIMITATIONS / PLACARDS

CHAPTER 2

Parachute Handle

Located on the parachute handle.

Parachute Activation Instructions

Located on the overhead console just in front of the parachute
activation handle.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / PLACARDS 2-20

CHAPTER 2

2.19.3 EXTERIOR

Canopy Handle

Located on the center of the canopy; top side, next to the canopy
release lever.

Danger Explosive

Located on the parachute egress panel adjacent to the engine on
the root of the right wing.

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-21 LIMITATIONS / PLACARDS

CHAPTER 2

Ballistic Parachute Passenger Warning

Located near each entrance to the cockpit.

Parachute Egress

Located around the perimeter of the parachute installation adjacent
to the engine on the root of the right wing.

Wing Release

Located on both wing tips near the trailing edge on top and bottom
surfaces (total of four locations).

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / PLACARDS 2-22

CHAPTER 2

Wing Lock

Located on bottom, center wing near wing fold joint forward of the
locking handle. There are two per aircraft—one on the right side and
one on the left side.

Tire Pressure

Located on main and nose landing gear legs.

Keep Static Port Clear

Located on both sides of the vertical tail.

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-23 LIMITATIONS / PLACARDS

CHAPTER 2

Aircraft Data Plate

Located on the left rear of the empennage below the vertical tail.

NOTE: Serial number is for illustration only. Your

aircraft serial number will be different.

Registration Numbers

Located on the left and right sides of the empennage.

NOTE: Registration numbers are for illustration only.

Your aircraft registration number will be
different.

Light Sport

Located on right and left sides of aircraft nose.

NOTE: Color shown for reference only.

Oil Type

Located on the inside of the oil door of the engine cowling.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / PLACARDS 2-24

CHAPTER 2

No Step Wing

Located on the upper center wing, left and right side toward the
leading edge.

Horizontal Stabilizer Tip Locks

Located on the underside of the horizontal tail tips, left and right
sides.

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

2-25 LIMITATIONS / PLACARDS

CHAPTER 2

Keep AOA Port Clear

Located next to the AOA ports on the left wing, top and bottom
leading edge.

Fueling Information

Located behind the canopy on the pilot side near the fuel filler cap.

Propeller Warnings

Located on either side of the propeller on the flap fence and on the
trailing edges of the Seawings™ below the propeller.

Left Hand Side

Right Hand Side

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

LIMITATIONS / PLACARDS 2-26

CHAPTER 2

On Right Hand, Top, Trailing Edge of Seawings™ Below Propeller

On Left Hand, Top, Trailing Edge of Seawings™ Below Propeller

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

EMERGENCY PROCEDURES / GENERAL INFORMATION 3-2

CHAPTER 3

Chapter 03

EMERGENCY PROCEDURES

General Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-2

Airspeeds for Emergency Operations . . . . . . . . . . . . . . . . 3-3

Annunciator Panel Caution Lights. . . . . . . . . . . . . . . . . . . . 3-4

Annunciator Panel Warning Lights . . . . . . . . . . . . . . . . . . . .3-5

Abnormal Engine Vibration . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6

ICON Parachute System (IPS) Actuation . . . . . . . . . . . . . 3-6

Coolant Temperature High . . . . . . . . . . . . . . . . . . . . . . . . . . .3-7

Emergency Rapid Descent . . . . . . . . . . . . . . . . . . . . . . . . . . 3-8

Engine Failure During Takeoff Prior to Liftoff . . . . . . . . . 3-8

Engine Failure After Takeoff. . . . . . . . . . . . . . . . . . . . . . . . . 3-8

Engine Failure In-Flight. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-8

Engine Fire on Ground/Start . . . . . . . . . . . . . . . . . . . . . . . . 3-9

Engine Fire in Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9

Electrical Fire in Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9

Inadvertent Spin . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9

Icing Encounter. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-10

Box-Canyon Reversal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-10

Landing Gear Fails to Retract—On Water . . . . . . . . . . . .3-10

Landing Gear Fails to Retract—In Flight . . . . . . . . . . . . . .3-10

Landing Gear Fails to Extend . . . . . . . . . . . . . . . . . . . . . . . . 3-11

Loss of Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-12

Loss of Primary Instruments. . . . . . . . . . . . . . . . . . . . . . . . .3-12

Oil Pressure-Low/High (In the Red) . . . . . . . . . . . . . . . . . .3-12

Oil Temperature High . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-12

Overvoltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13

Precautionary Landing With Engine Power . . . . . . . . . . . 3-13

Wheel Brake Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-13

3.1 GENERAL INFORMATION

This section provides checklists and procedures for coping with
emergencies that may occur. Emergencies caused by airplane

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

3-3 EMERGENCY PROCEDURES / AIRSPEEDS FOR EMERGENCY OPERATIONS

CHAPTER 3

malfunctions are rare if proper preflight inspections and
maintenance are practiced. En-route weather emergencies may be
minimized by careful flight planning and good judgment when
unexpected weather is encountered. Should an emergency arise,
the basic guidelines in this section should be considered and
applied as necessary to correct the problem.

The A5 has a series of annunciator lights that assist the pilot in
assessing the criticality of various situations. (See “Annunciator
Panel” on page 7-16.)

The following terminology is used to categorize the level of urgency
to land the aircraft during an abnormal or emergency situation:

Land as soon as practical

Extended flight is not recommended. The landing site and
duration of flight is at the discretion of the pilot. Flying to a
nearby airport with support services is recommended.

Land as soon as possible

Fly toward the nearest normal landing area (runway or water)
while being prepared to execute the “Engine Failure In-Flight”
on page 3-8 to an emergency landing site (e.g. road).

3.2 AIRSPEEDS FOR EMERGENCY OPERATIONS

Condition Airspeed

Engine Failure After Takeoff AOA-Pitch for white line (~60 KIAS)
Engine Failure In-Flight AOA-Pitch for white line (~60 KIAS)
Precautionary Landing with Engine

Power
Operating Maneuvering Speed—1510 lb

Operating Maneuvering Speed—1145 lb

Best Glide Speed AOA-Pitch for white line (~60 KIAS)
Emergency Descent Speed for Rapid

Descent

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

AOA-Pitch for white line (~60 KIAS)

87 KIAS

f

76 KIAS

f

Max 120 KIAS

EMERGENCY PROCEDURES / ANNUNCIATOR PANEL CAUTION LIGHTS 3-4

CHAPTER 3

3.3 ANNUNCIATOR PANEL CAUTION LIGHTS

The annunciator panel caution lights are amber in color.

Caution Cause/Remarks Corrective Action

BATTERY

ALTERNATOR

ENGINE

FUEL PRESS

1. Low battery voltage.

2. Battery not charging
with engine running.

3. Aircraft systems are
discharging battery.

1. Low voltage on main
bus.

2. If flying, ALT B failure.

3. Battery not charging
with engine running.

1. Engine compo­nent/sensor
failure/exceedance
detected.

2. Engine limits may have
been exceeded; check
gauges.

3. 10 hours max flight time
recommended.

1. Excessively low or high
fuel pressure.

1. Confirm Master Switch
ON.

2. Turn off non-critical
equipment.

3. If accompanied by
ALTERNATOR light,
consider lowering
landing gear while
battery is still strong.

1. Reset 30 Amp circuit
breaker if tripped. If
trips again then:

2. Turn off non-critical
equipment.

3. Consider lowering
landing gear while
battery is still strong.

1. Land as soon as prac­tical for trouble­shooting.

1. Land as soon as prac­tical for trouble­shooting.

2. Power reduction may
help.

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

3-5 EMERGENCY PROCEDURES / ANNUNCIATOR PANEL WARNING LIGHTS

CHAPTER 3

3.4 ANNUNCIATOR PANEL WARNING LIGHTS

The annunciator panel warning lights are red in color.

War nin g Cause/Remarks Corrective Action

PURGE BILGE

SECURE WING/TAIL

LAND AIRCRAFT

+ FUEL PRESS

LAND AIRCRAFT

+ ENGINE

LAND AIRCRAFT

+ ENGINE

+ ALTERNATOR

1. At least 1 gallon of
water in bilge.

2. Could create weight or
CG out of limits.

1. One or more sensors
indicate unlocked.

2. Does not identify
affected sensor.

1. Critically low or high
fuel pressure.

1. Critical engine compo­nent or sensor failure.

1. Low voltage on main
bus.

2. If flying, ALT A failure.

1. Bilge pump—ON.

If light remains on:

1. Do not takeoff.

On ground:

1. Do not takeoff.

2. Confirm wings/tails
locked.

In flight:

1. Minimize maneuvering.

2. Land as soon as prac­tical.

1. Land as soon as
possible.

1. Land as soon as
possible.

1. Turn off non-critical
equipment.

2. Land as soon as
possible.

3. Consider lowering
landing gear while
battery still strong.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

EMERGENCY PROCEDURES / ABNORMAL ENGINE VIBRATION 3-6

CHAPTER 3

War nin g Cause/Remarks Corrective Action

LAND AIRCRAFT

+ ALTERNATOR

+ BATTERY

LAND AIRCRAFT

+ ENGINE

+ ALTERNATOR

+ BATTERY

1. Excessively low
battery.

2. If flying, Alt B failure.

3. Battery not charging
with engine running.

4. ALT A may also have
failed.

1. Excessively low
battery.

2. If flying, Alt A failure.

3. Battery not charging
with engine running.

4. ALT B may also have
failed.

1. Confirm Master Switch
ON.

2. Turn off non-critical
equipment.

3. Land as soon as
possible.

4. Lower landing gear now
if land landing.

NOTE: Battery life may

limit engine run time.

1. Confirm Master Switch
ON.

2. Turn off non-critical
equipment.

3. Land as soon as
possible.

4. Lower landing gear now
if land landing.

NOTE: Battery life may

limit engine run time.

3.5 ABNORMAL ENGINE VIBRATION

1. Throttle—Reduce to minimum practical

2. Assess Vibration—Take action

Option Actions

If vibration stops. 1. Land as soon as practical

If vibration continues.

1. Land as soon as possible (suitable
landing area)

3.6 ICON PARACHUTE SYSTEM (IPS) ACTUATION

IPS actuation is recommended for any of the following:

• Loss of Aircraft Control

• Engine Failure and < 1000 ft AGL with NO SUITABLE landing
area

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

3-7 EMERGENCY PROCEDURES / COOLANT TEMPERATURE HIGH

CHAPTER 3

• Pilot Incapacitation or inability to cope with situation or flight
conditions

Parachute Deployment

1. Safety Pin—CONFIRM REMOVED, Remove if necessary

2. Parachute Handle—PULL HARD

3. Ignition Key—OFF

3.6.1 NOTES:

Approximately 48 lb

of force is required to actuate the IPS.

f

Optimal IPS actuation is from level flight above 500 ft AGL.

Descent rate under parachute will be approximately 1200 ft/min.

Landing gear will automatically extend following IPS actuation. Once
extended, it cannot be raised.

Seat belts should remain secure during descent until contact with
the surface and all motion stops.

At pilot’s discretion, consider unlocking canopy and removing
windows during descent.

Exit the aircraft after all motion stops.

The ELT may not activate during IPS deployment or touchdown. It is
therefore recommended to manually activate the ELT during the
descent.

3.7 COOLANT TEMPERATURE HIGH

3.7.1 GROUND

1. Throttle—ADVANCE to 3000-4000 RPM (if feasible)

If high coolant temperature persists:

2. Shutdown as soon as practical

NOTE: Use of cabin heater may help reduce coolant

temperature.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

EMERGENCY PROCEDURES / EMERGENCY RAPID DESCENT 3-8

CHAPTER 3

3.7.2 IN FLIGHT

1. Throttle—REDUCE power to minimum required

2. Airspeed—INCREASE

If high coolant temperature persists:

3. Land as soon as possible

3.8 EMERGENCY RAPID DESCENT

1. Throttle—IDLE

2. Flaps—UP

3. Airspeed—120 KIAS max in smooth air or 90 KIAS max in
rough air

3.9 ENGINE FAILURE DURING TAKEOFF PRIOR TO LIFTOFF

1. Throttle—IDLE

2. Brakes—AS REQUIRED

3.10 ENGINE FAILURE AFTER TAKEOFF

1. AOA—White line

2. Landing Area—Select, land within 45° of straight ahead unless
sure of sufficient altitude for a turn

3.11 ENGINE FAILURE IN-FLIGHT

1. AOA—white line

2. Landing Site—SELECT

3. Confirm:

a. Throttle—above idle
b. Master Switch—ON
c. Ignition—BOTH
d. Fuel Valve—ON

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

3-9 EMERGENCY PROCEDURES / ENGINE FIRE ON GROUND/START

CHAPTER 3

4. Evaluate Landing Site Options and Take Action

Option Actions

Suitable water or soft surface is available for
landing.

Suitable hard surface is available for landing. 1. Landing Gear—DOWN

Less than 1,000 ft AGL with no suitable landing
area.

1. Landing Gear—UP

2. Flaps—FULL (landing
assured)

1. IPS Handle—PULL HARD

2. Ignition Key—OFF

3.12 ENGINE FIRE ON GROUND/START

1. Ignition—OFF

2. Master Switch—OFF

3. Egress Airplane

3.13 ENGINE FIRE IN FLIGHT

1. Ignition—OFF

2. Master Switch—OFF

3. Fuel Valve—OFF

4. Land As Soon As Possible

3.14 ELECTRICAL FIRE IN FLIGHT

1. Master Switch—OFF

2. Alternator Circuit Breaker—PULL (in overhead console)

3. Land As Soon As Possible

3.15 INADVERTENT SPIN

1. IPS Handle—PULL HARD

2. Ignition Key—OFF

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

EMERGENCY PROCEDURES / ICING ENCOUNTER 3-10

CHAPTER 3

3.16 ICING ENCOUNTER

1. Exit Icing Conditions

CAUTION: The presence of even small amounts of ice on

the airframe may increase stall speed,
decrease stall angle of attack and reduce
performance including climb rate.

3.17 BOX-CANYON REVERSAL

1. Power—Full

2. Pitch—slightly up (~5-10° above horizon)

3. Immediately roll and pull (in most open direction)

4. AOA—pull mid yellow (or stall horn)

5. Keep nose above horizon (out of buffet)

3.18 LANDING GEAR FAILS TO RETRACT—ON WATER

1. Speed—Idle taxi

2. Landing Gear Handle—DOWN

3. Fuses—CHECK Landing Gear Fuses and REPLACE as
required

4. Landing Gear—CHECK nose wheel centered; debris/seaweed
clear of all landing gear

5. Landing Gear handle—UP

6. If Landing Gear Does Not Retract:

a. Landing Gear Handle—DOWN
b. Aircraft—SECURE on ramp, beach or dock for further

troubleshooting

3.19 LANDING GEAR FAILS TO RETRACT—IN FLIGHT

1. Landing Gear Handle—DOWN

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

3-11 EMERGENCY PROCEDURES / LANDING GEAR FAILS TO EXTEND

CHAPTER 3

2. Evaluate Landing Gear Position and Landing Site Options—
Take action

Option Actions

If the landing gear position indicates
down.

If the landing gear fails to extend.

If water landing is the only option and
the landing gear must be raised.

1. Land on suitable hard surface for
troubleshooting

1. Proceed to Landing Gear Fails to
Extend

1. Leave landing gear handle in DOWN
position

2. CHECK/REPLACE overhead
landing gear fuses as needed

3. Landing Gear Handle—UP

3.20 LANDING GEAR FAILS TO EXTEND

1. Landing Gear handle—UP

2. Evaluate Landing Gear Position and Landing Site Options—
Take action

Option Actions

If the landing gear position indicates up
and suitable water is available.

If no suitable water is available for
landing.

1. Land on water for further trouble­shooting

1. Landing Gear Handle—DOWN

2. CHECK/REPLACE overhead
landing gear fuses as needed

1. Landing Gear Handle—UP

If the landing gear fails to extend.

If the landing gear still fails to extend
and suitable water is unavailable.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

2. CHECK/REPLACE overhead
landing gear fuses as needed

3. Landing Gear Handle—DOWN

1. Perform gentle, minimum speed, full
flap, runway landing

NOTE: Use of a grass runway may

reduce hull damage if forced to land
with landing gear not fully down.

EMERGENCY PROCEDURES / LOSS OF CONTROL 3-12

CHAPTER 3

3.21 LOSS OF CONTROL

1. IPS Handle—PULL HARD

2. Ignition Key—OFF

3.22 LOSS OF PRIMARY INSTRUMENTS

1. Land as soon as practical

2. Use GPS for speed and altitude (if needed)

3.23 OIL PRESSURE-LOW/HIGH (IN THE RED)

3.23.1 GROUND

1. Throttle—IDLE

2. Ignition—OFF as soon as practical

3.23.2 IN FLIGHT

1. Throttle—Reduce

2. Land as soon as possible

3.24 OIL TEMPERATURE HIGH

3.24.1 GROUND

1. Throttle—ADVANCE to 3000-4000 RPM (if feasible)

If high oil temperature persists:

2. Shutdown as soon as possible

3.24.2 IN FLIGHT

1. Throttle—REDUCE

2. Airspeed—INCREASE

If high oil temperature persists:

3. Land as soon as possible

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

3-13 EMERGENCY PROCEDURES / OVERVOLTAGE

CHAPTER 3

3.25 OVERVOLTAGE

1. Land as soon as possible

NOTE: The A5 has no overvoltage indicator, but

smoke or an acid smell in the cockpit is an
indication of overvoltage. (See “Electrical Fire
in Flight” on page 3-9.)

3.26 PRECAUTIONARY LANDING WITH ENGINE POWER

1. AOA—White line (~60 KIAS)

2. Landing Area—SELECT

3. Landing Gear and Flaps—As required for type of landing

4. Communicate intentions (time permitting, as required)

5. AOA—mid-yellow prior to touchdown

3.27 WHEEL BRAKE FAILURE

NOTE: Wheel brakes are needed for steering at low

speeds. Failure in-flight would be indicated by
low or no brake pedal resistance.

1. If possible, land with cross wind from side of failed brake

2. Rudder Pedal—MAINTAIN directional control

3. Wheel Brake (Operable)—LIGHT APPLICATION as needed

4. Shut down engine and tow back

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A2

EMERGENCY PROCEDURES / WHEEL BRAKE FAILURE 3-14

CHAPTER 3

CHANGE A2 ICON A5 / PILOT’S OPERATING HANDBOOK

NORMAL PROCEDURES / PREFLIGHT INSPECTION 4-2

CHAPTER 4

Chapter 04

NORMAL PROCEDURES

Preflight Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-2

Before Cockpit Entry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-7

After Cockpit Entry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-7

Engine Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-8

Before Taxi. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-8

Taxiing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9

Engine Run-Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9

Before Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9

Normal Takeoff—Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-10

Step Taxi/Normal Takeoff—Water. . . . . . . . . . . . . . . . . . .4-10

Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-10

Cruise. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-11

Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-11

Normal Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-12

Balked Landing Procedures . . . . . . . . . . . . . . . . . . . . . . . . . 4-12

Before Beaching. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-12

Before Taxi From Water to Ramp . . . . . . . . . . . . . . . . . . . .4-12

Short Field Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-13

Soft Field Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-13

Short Field Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-13

Soft Field Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-14

Glassy Water Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-14

Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-14

Post-Flight Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-15

4.1 PREFLIGHT INSPECTION

Prior to flight, the aircraft should be inspected in accordance with
the following checklists and in the sequence shown in the diagram.
Carefully verify that the airplane is in a condition for safe operation.

CHANGE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

4-3 NORMAL PROCEDURES / PREFLIGHT INSPECTION

CHAPTER 4

10 2

9

8

7

6

5

4

3

1

11

FIGURE 4-1

PREFLIGHT INSPECTION PROCESS

4.1.1 (1) CABIN

1. Baggage Area—SECURE stored items

2. Throttle Lever—CHECK freedom of motion

3. Controls—CHECK freedom of motion to all stops

4. Landing Gear Switch—VISUALLY CHECK DOWN (land)/UP
(water)

5. Rudder Pedal Area and Parking Brake—CHECK clear and no
fluid leaks

6. Master Switch—ON

7. Strobe Lights—VERIFY all lights illuminate

8. Fuel Quantity—CHECK/CONFIRM

9. Landing Gear Position Indicator—VISUALLY VERIFY DOWN
(land)/UP (water)

10. Bilge Pump—ON (verify operation & bilge empty)/OFF

11. Water Rudder—VISUALLY inspect and VERIFY operation

12. Circuit Breakers and Fuses—CHECK IN and NONE LIT

13. Master Switch—OFF

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A3

NORMAL PROCEDURES / PREFLIGHT INSPECTION 4-4

CHAPTER 4

14. Canopy Frame, Seal, and Latch—CHECK CONDITION

15. Canopy/Windows—CHECK general condition

16. Fuselage Left Nose—CHECK CONDITION

17. Fresh Air Vent Scoop—CLEAR

18. Nose Gear Strut and Mechanism—CHECK CONDITION

19. Aft Nose Gear Doors—CHECK CONDITION and CONFIRM
locked in down position

20. Fuselage Right Nose—CHECK CONDITION

4.1.2 (2) RIGHT WING LE AND TIP

1. Seawings™ LE—CHECK CONDITION and SECURE

2. Wing Lock Handle—CHECK LOCKED and SECURE

3. Wing Inspection Panels (2)—CHECK SECURE

4. Wing Stall Strip—CHECK SECURE

5. Wing Tie Down Fitting—REMOVE

6. Wing LE and HT Hanger Fitting—CHECK CONDITION

7. Wing Vortex Generators (17 Pair)—CHECK SECURE

8. Wing Tip and Lights—CHECK CONDITION

4.1.3 (3) RIGHT WING TE

1. Aileron and Hinges—CHECK FREE and SECURE

2. Top of Wing—CHECK for DAMAGE

3. Flap, Hinges, and Root Fence—CHECK CONDITION

4.1.4 (4) RIGHT INBOARD WING AND ENGINE

1. Parachute Cover—CHECK SECURE

2. Main Landing Gear—CHECK CONDITION

3. Tires—CHECK CONDITION, wear

4. Brakes—CHECK CONDITION, wear, fluid leaks

5. Seawings™ and Hull Step—NO DAMAGE

6. Fuselage Vortex Generators (5)—CHECK SECURE

CHANGE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

4-5 NORMAL PROCEDURES / PREFLIGHT INSPECTION

CHAPTER 4

7. Aft Cowl and Exhaust—SECURE, NO CRACKS

8. Coolant Overflow Bottle—VERIFY LEVEL between min and
max

9. Propeller and Spinner—SECURE, NO NICKS

10. Cooling Outlet and Fan—CLEAR, GOOD CONDITION

4.1.5 (5) RIGHT TAIL BOOM

1. Firewall Drain—CHECK CLEAR

2. Top of Tail Boom Under Propeller—CLEAR OF
WATER/DEBRIS

3. Tail Boom and Hull—CHECK CONDITION and CLEAR OF
DEBRIS

4. Water Rudder and Access Panel—SECURE, NO DAMAGE

5. Tail One Access Panel—SECURE

6. Tail Tie Down—CHECK CONDITION and UNTIE

4.1.6 (6) TAIL SURFACES

1. Vertical Tail and HT/VT Joint—CHECK CONDITION and
SECURITY

2. Right HT and Tip—VERIFY CONDITON and LOCKED

3. Rudder—CHECK FREE and in GOOD CONDITION

NOTE: The rudder is spring-centered with a minor

offset to the right. This is normal and should
not be adjusted.

4. Static Ports (2)—CHECK CLEAN with CRESCENTS IN PLACE

5. Elevator, Hinges, and Pushrod—CHECK FREE and SECURE

6. Trim Tab and Pushrod—CHECK CONDITION and WITHOUT
EXCESSIVE PLAY

7. Left HT and Tip—VERIFY CONDITON and LOCKED

4.1.7 (7) LEFT TAIL BOOM

1. Tail Boom and Hull—CHECK CONDITION

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A3

NORMAL PROCEDURES / PREFLIGHT INSPECTION 4-6

CHAPTER 4

4.1.8 (8) LEFT INBOARD WING

1. Aft Cowl and Exhaust—SECURE, NO CRACKS

2. Seawings™ and Hull Step—NO DAMAGE

3. Fuselage Vortex Generators (5)—CHECK SECURE

4. Main Landing Gear—CHECK CONDITION

5. Tires—CHECK CONDITION, wear

6. Brakes—CHECK CONDITION, wear, fluid leaks

4.1.9 (9) LEFT WING TE

1. Flap, Hinges, and Root Fence—CHECK CONDITION

2. Top of Wing—CHECK for DAMAGE

3. Aileron and Hinges—CHECK FREE and SECURE

4.1.10 (10) LEFT WING TIP AND LE

1. Wing Tip and Lights—CHECK CONDITION

2. Wing Vortex Generators (17 pair)—CHECK SECURE

3. Wing LE and HT Hanger Fitting—CHECK CONDITION

4. AOA Ports (2)—CHECK CLEAR

5. Wing Tie Down Fitting—REMOVE

6. Wing Stall Strip—CHECK SECURE

7. Wing Inspection Panels (2)—CHECK SECURE

8. Fuel Vent—CHECK CLEAR

9. Wing Lock Handle—CHECK LOCKED and SECURE

10. Pitot Tube—CHECK CLEAR

11. Seawings™ LE—CHECK CONDITION

12. Bilge Outlet—CHECK CLEAR

4.1.11 (11) FUEL AND ENGINE OIL

1. Fuel Cap—REMOVE

2. Fuel—SUMP via access port and INSPECT fuel

3. Fuel Cap—SECURE (tab swings down)

CHANGE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

4-7 NORMAL PROCEDURES / BEFORE COCKPIT ENTRY

CHAPTER 4

4. Ignition Switch—OFF and key REMOVED

5. Oil Filler Cap—REMOVE via access door

6. Propeller—TURN SLOWLY CCW (behind prop facing forward)
several times by hand, holding pressure for several seconds
against each compression stroke, until oil ‘burps’

7. Oil Level—CHECK, SERVICE as necessary, then secure cap
and door

8. Cowling—CHECK condition/VERIFY secure

9. Engine Inlet—CLEAR

4.2 BEFORE COCKPIT ENTRY

1. Chocks and Tie Downs—VERIFY REMOVED

2. Aircraft Documents—VERIFY/REVIEW

3. Preflight Planning—COMPLETE

4. Takeoff Data—CALCULATE as required

5. Life Vest(s)—GOOD CONDITION/DON (as required)

6. Windows—BOTH IN or BOTH REMOVED

7. Wind Deflectors—BOTH INSTALLED (if windows removed)

4.3 AFTER COCKPIT ENTRY

1. Canopy—LOWERED to detent or CLOSED

2. Belts/Harnesses—FASTEN

3. Headsets—CONNECTED

4. Landing Gear Switch—DOWN (land)/UP (water)

5. Electrical Switches—ALL OFF (or as required)

6. Master Switch—ON

7. Annunciator Panel—PRESS to test; VERIFY all lights illuminate

8. Landing Gear Position Indicator—DOWN (land)/UP (water)

9. Bilge Pump—On (verify operation & bilge empty)/OFF

10. Fuel Valve—ON

11. IPS Safety Pin—REMOVE and stow

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A3

NORMAL PROCEDURES / ENGINE START 4-8

CHAPTER 4

4.4 ENGINE START

1. Strobes—ON

2. Brakes—TEST and SET

3. Throttle—OPEN 1/2”

4. Area Around Aircraft—CLEAR

5. Ignition Switch—SMOOTHLY ROTATE to start; RELEASE as
engine fires

NOTE: Max crank time is 10 seconds, followed by 2

minutes off

6. Throttle—ADJUST to 2000 RPM

7. Annunciator Panel—LAND AIRCRAFT and ENGINE lights OUT

NOTE: If lights not out, switch may have been

rotated too rapidly. Shutdown and restart.

8. Oil Pressure—MONITOR; shutdown if not up in 10 seconds

4.5 BEFORE TAXI

1. Throttle—ADVANCE above 2500 RPM until ALTERNATOR
light out

2. Radio and Transponder—ON ALT (VFR 1200)

3. AWOS — RECORD as required

4. Altimeter—SET/VERIFY

5. GPS—SET as required

6. Exterior Lights—ON as required

7. Engine Instruments—CHECK

8. Parking Brake—RELEASE

CHANGE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

4-9 NORMAL PROCEDURES / TAXIING

CHAPTER 4

4.6 TAXIING

4.6.1 LAND

1. Brakes—CHECK

2. Steering—CHECK

4.6.2 WATER

1. Steering—CHECK

2. Water Rudder—DOWN as necessary for improved authority

4.7 ENGINE RUN-UP

1. Throttle—ADVANCE TO 4000 RPM

2. Ignition Switch—B (pause until LAND AIRCRAFT AND ENGINE
lights illuminate)

3. Ignition Switch—A (pause 6 seconds)

a. RPM: 180 max drop from original
b. FUEL PRESSURE Annunciator—OUT

4. Ignition Switch—B (pause 6 seconds)

a. RPM—180 max drop from original
b. FUEL PRESSURE Annunciator—OUT

5. Ignition Switch—BOTH

6. Annunciator Panel—ALL LIGHTS OUT

7. Engine Instruments—CHECK

8. Throttle—RETARD to idle

NOTE: During the ignition check, the RPM may

increase when operating on a single lane.
This is normal; the original RPM will be
restored after a short time operating on both
lanes.

4.8 BEFORE TAKEOFF

1. Flight Controls—FREE and CORRECT

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A3

NORMAL PROCEDURES / NORMAL TAKEOFF—LAND 4-10

CHAPTER 4

2. Flaps—CHECK operation

3. Trim—SET for takeoff

4. Instruments—CHECK

5. Canopy—LATCHED

4.9 NORMAL TAKEOFF—LAND

1. Flaps—UP (0°)

2. Throttle—MAX

3. Stick—Rotate at 50 KIAS

4. Landing Gear—RETRACT when safely airborne (<75 KIAS)

4.10 STEP TAXI/NORMAL TAKEOFF—WATER

CAUTION: Takeoff distance will be extended with less

than full flap set.

WARNING: Contacting the wing tip with the water while

in motion can create a dangerous situation
and must be avoided.

1. Bilge Pump—ON (verify bilge empty) / OFF

2. Landing Gear—UP, indicating up

3. Flaps—FULL (30°)

4. Water Rudder—UP

5. Throttle—MAX

6. Stick—POSITION for minimum water drag

7. Flaps—RETRACT when safely airborne above 50 KIAS (<75
KIAS)

4.11 CLIMB

1. Airspeed—58 KIAS for best rate of climb

2. Instruments—MONITOR

CHANGE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

4-11 NORMAL PROCEDURES / CRUISE

CHAPTER 4

4.12 CRUISE

1. Cruise Power—SET

2. Fuel Quantity—MONITOR

3. Instruments—MONITOR

4.13 APPROACH

4.13.1 DESCENT

1. Throttle—AS REQUIRED

2. Landing Gear—AS REQUIRED

4.13.2 BEFORE LANDING—LAND

1. Landing Gear—DOWN for the runway (<75 KIAS), indicating
down

2. Flaps—UP (0°), or as desired for type of landing

3. Water Rudder—UP

4. Brakes—CHECK for firmness and parking brake OFF

5. AOA—WHITE LINE

4.13.3 BEFORE LANDING—WATER

WARNING: Confirm landing gear up for water landing.

Aircraft may flip inverted if landed on water
with landing gear extended.

1. Landing Gear—UP for water, indicating up

2. Flaps—FULL (30°, <75 KIAS)

3. Water Rudder—UP

4. AOA—WHITE LINE

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A3

NORMAL PROCEDURES / NORMAL LANDING 4-12

CHAPTER 4

4.14 NORMAL LANDING

4.14.1 LAND

1. Throttle—IDLE

2. Braking—MINIMUM REQUIRED

4.14.2 WATER

NOTE: Normal water landing and short field water

landing procedures are identical.

1. Throttle—IDLE

2. Stick—FULL AFT, after touchdown if desired for maximum
hydrodynamic braking

4.15 BALKED LANDING PROCEDURES

1. Throttle—MAX

2. AOA—white line

3. Flaps—RETRACT after positive rate of climb

4.16 BEFORE BEACHING

NOTE: Select a beaching surface that will not

damage the hull and arrive at the beach with
little or no speed.

1. Water Rudder—UP

2. Ignition—OFF

4.17 BEFORE TAXI FROM WATER TO RAMP

1. Throttle—IDLE taxi

2. Landing Gear—DOWN

CHANGE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

4-13 NORMAL PROCEDURES / SHORT FIELD TAKEOFF

CHAPTER 4

CAUTION: Ramping with landing gear not fully down will

damage the landing gear.

3. Water Rudder—UP

4.18 SHORT FIELD TAKEOFF

1. Flaps—HALF (15°)

2. Brakes—HOLD

3. Throttle—smoothly advance to MAX

4. Flight Instruments—CHECK

5. Brakes—RELEASE

6. Stick—ROTATE at 45 KIAS

7. Landing Gear—UP once safely airborne and climbing

8. Climb at V

(50 KIAS) until obstacles cleared (if required)

X

9. Flaps—UP climbing through 100 ft AGL

4.19 SOFT FIELD TAKEOFF

1. Flaps—HALF (15°)

2. Stick—FULL AFT

3. Throttle—smoothly advance to MAX

4. Flight Instruments—CHECK

5. At Nosewheel Liftoff—Modulate stick to avoid excessively
steep climb angle

6. Landing Gear—UP once safely airborne and climbing

7. Climb at V

(50 KIAS) until obstacles cleared (if required)

X

8. Flaps—UP climbing through 100 ft AGL

4.20 SHORT FIELD LANDING

1. Landing Gear—DOWN for the runway (<75 KIAS), indicating
down

2. Flaps—FULL (30°, <75 KIAS) before short final

3. Water Rudder—UP

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A3

NORMAL PROCEDURES / SOFT FIELD LANDING 4-14

CHAPTER 4

4. AOA—YELLOW LINE

5. After Touchdown—apply brakes as needed

4.21 SOFT FIELD LANDING

1. Landing Gear—DOWN for the runway (<75 KIAS), indicating
down

2. Flaps—FULL (30°, <75 KIAS) before short final

3. Water Rudder—UP

4. AOA—YELLOW LINE

5. After Touchdown—Apply back stick to hold nose off ground

6. Minimize braking and maintain AFT stick during roll out

4.22 GLASSY WATER LANDING

1. Locate suitable shoreline visual reference

2. GPS—Select HSI/panel display for VSI reference (if on-board
and desired)

3. Final Approach Path—as close to visual reference as practical

4. Wheels—UP for water, indicating up

5. Flaps—FULL (30°,<75 KIAS)

6. Water Rudder—UP

No later than last visual reference:

7. AOA—YELLOW LINE

8. Throttle—Set RPM to establish 100-150 ft/min decent (approx
3700-4000 RPM)

9. After Touchdown—throttle to idle

4.23 SHUTDOWN

1. Brakes—HOLD (on land)

2. Flaps—UP

3. Trim—SET takeoff

4. Engine—STABILIZE at idle (2 minutes in hot conditions)

CHANGE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

4-15 NORMAL PROCEDURES / POST-FLIGHT INSPECTION

CHAPTER 4

5. Ignition Switch—OFF

6. Radio and Transponder—OFF

7. Lights— ALL OFF

8. Master Switch—OFF

9. Parking Brake—SET (if desired)

10. IPS Safety Pin—INSTALL

4.24 POST-FLIGHT INSPECTION

1. Propeller—CHECK for nicks, water damage

2. Bilge Pump—RUN until no water; then confirm bilge pump and
master switch OFF

3. Tie Downs and Chocks—AS REQUIRED

4. General Aircraft Condition—INSPECT

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A3

NORMAL PROCEDURES / POST-FLIGHT INSPECTION 4-16

CHAPTER 4

CHANGE A3 ICON A5 / PILOT’S OPERATING HANDBOOK

PERFORMANCE / SUMMARY OF PERFORMANCE SPECIFICATIONS 5-2

CHAPTER 5

Chapter 05

PERFORMANCE

Summary of Performance Specifications . . . . . . . . . . . . . .5-2

Airspeed Calibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-3

Temperature Conversion Chart. . . . . . . . . . . . . . . . . . . . . . .5-4

Stall Speeds. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-4

Normal Runway Takeoff Performance . . . . . . . . . . . . . . . .5-5

Water Takeoff Performance. . . . . . . . . . . . . . . . . . . . . . . . . .5-6

Short Field Runway Takeoff Performance . . . . . . . . . . . . .5-7

Rate of Climb. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-8

Cruise Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-9

Time, Fuel, and Distance to Climb. . . . . . . . . . . . . . . . . . . .5-10

Range and Endurance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11

Normal Runway Landing Performance . . . . . . . . . . . . . . . 5-12

Water Landing Performance. . . . . . . . . . . . . . . . . . . . . . . . .5-13

Short Field Runway Landing Performance. . . . . . . . . . . . 5-14

5.1 SUMMARY OF PERFORMANCE SPECIFICATIONS

Parameter Val ue

Gross Weight

Top Speed at SL, VH (MCP, 5500 RPM)

Cruise Speed, 5000 RPM, 8000 ft 84 KTAS
Range (5000 RPM, 8000 ft, including

takeoff and climb from SL)
Best Angle of Climb Speed, V

Best Angle of Climb Speed, V
15°/30°)
Best Rate of Climb Speed, V

Rate of Climb at V

Rate of Climb at V

Stall Speed, V
up)

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

(SL)

X

(SL)

Y

(Flaps and landing gear

S

(Flaps 0°)

X

(Flaps

X

Y

1510 lb

f

95 KTAS

427 nm (with 45 min reserve)

54 KIAS

50 KIAS

58 KIAS

616 ft/min

629 ft/min

45 KIAS

5-3 PERFORMANCE / AIRSPEED CALIBRATION

CHAPTER 5

Parameter Val ue

Stall Speed, VS0 (Flaps and landing gear
down)
Total Fuel Capacity 20.1 US gallons
Total Usable Fuel 20 US gallons

Approved Types of Fuel

Max Engine Power at SL 100 hp at 5800 RPM (5 min max)
Max Demonstrated Direct Crosswind

Component—Land and Water (not a
limitation)

Service Ceiling at Gross Weight (100
ft/min Climb Rate)

39 KIAS

Unleaded automotive fuel with up to 10%
maximum ethanol content meeting ASTM
D4814 with minimum RON 95 (minimum
Anti-Knock Index 91)
Grade 100LL aviation gasoline (AVGAS)
meeting ASTM D910

12 knots

15,000 ft

5.2 AIRSPEED CALIBRATION

Conditions

Level flight

Assumed zero instrument error

Flap Setting Airspeeds

Flaps 0°

Flaps 15°

Flaps 30°

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

KIAS 50 60 70 80 90 100 110 120

KCAS 51 61 71 80 90 100 109 119

KIAS 45 50 55 60 65 70 75 —

KCAS 46 51 55 60 65 70 74 —

KIAS 45 50 55 60 65 70 75 —

KCAS 45 50 54 59 64 68 73 —

PERFORMANCE / TEMPERATURE CONVERSION CHART 5-4

CHAPTER 5

5.3 TEMPERATURE CONVERSION CHART

FIGURE 5-1

TEMPERATURE CONVERSION BETWEEN FAHRENHEIT
AND CELSIUS

5.4 STALL SPEEDS

Conditions

1510 lb

f

Power idle

Most forward center of gravity

Assumed zero instrument error

Flap Setting

0° KIAS 45 48 54 64
15° KIAS 41 44 49 58
30 KIAS 39 42 46 55

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

0° 30° 45° 60°

Angle of Bank

5-5 PERFORMANCE / NORMAL RUNWAY TAKEOFF PERFORMANCE

CHAPTER 5

5.5 NORMAL RUNWAY TAKEOFF PERFORMANCE

Conditions

1510 lb

f

Landing gear—DOWN

Level and dry asphalt runway

Zero wind

POH normal takeoff and climb technique except for full throttle
prior to brake release

Corrections

Decrease distances by 10% for each 8 knots of headwind.

Increase distances by 10% for each 4 knots of tailwind.

Increase ground roll distance by 15% for operation on grass
runway.

Press Alt (ft) Tem p (° F) Ground Roll (ft)

0 520 1220

20 560 1320

Sea Level

2000

4000

40 600 1410
60 640 1510
80 690 1620

100 740 1730

06401500
20 690 1630
40 750 1750
60 800 1890
80 860 2030

100 920 2180

0 810 1890
20 880 2060
40 950 2230
60 1030 2420
80 1110 2620

100 1200 2820

Tot al to Cl ear 50 ft

Obstacle (ft)

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

PERFORMANCE / WATER TAKEOFF PERFORMANCE 5-6

CHAPTER 5

Press Alt (ft) Tem p (° F) Ground Roll (ft)

-20 950 2240
0 1050 2460

6000

8000

20 1150 2700
40 1250 2950
60 1370 3220
80 1490 3520

-20 1280 3010
0 1420 3340

20 1570 3710
40 1740 4110
60 1930 4550
80 2140 5040

Total to Clear 50 ft

Obstacle (ft)

5.6 WATER TAKEOFF PERFORMANCE

Conditions

1510 lb

f

Full throttle from 4 knots water speed

Glassy water

Zero wind

POH step taxi/takeoff technique except for full throttle from 4
knots water speed and climb at 50 KIAS

NOTE: Normal Water Takeoff performance data is

the same as Short Field Water Takeoff
performance data.

Corrections

Decrease distance by 10% for each 8 knots of headwind.

Increase distances by 10% for each 4 knots of tailwind.

Water run distance may reduce slightly with wave conditions
more favorable than glassy.

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

5-7 PERFORMANCE / SHORT FIELD RUNWAY TAKEOFF PERFORMANCE

CHAPTER 5

Press Alt (ft) Tem p (° F) Wat er Run (ft )

20 720 1260
40 780 1360

Sea Level

2000

4000

6000

8000

60 840 1470
80 900 1580

100 970 1690

20 910 1590
40 990 1730
60 1070 1880
80 1160 2030

100 1250 2190

20 1190 2080
40 1300 2280
60 1430 2490
80 1560 2720

100 1700 2970

20 1630 2860
40 1810 3170
60 2010 3510
80 2220 3890

100 2460 4310

20 2420 4240
40 2750 4810
60 3120 5470
80 3560 6230

100 4070 7120

Tot al to Cl ear 50 ft

Obstacle (ft)

5.7 SHORT FIELD RUNWAY TAKEOFF PERFORMANCE

Conditions

1510 lb

f

Level and dry asphalt runway

Zero wind

POH short field takeoff technique

Corrections

Decrease distances by 10% for each 8 knots of headwind.

Increase distances by 10% for each 4 knots of tailwind.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

PERFORMANCE / RATE OF CLIMB 5-8

CHAPTER 5

Increase ground roll distance by 15% for operation on grass
runway.

Press Alt (ft) Tem p (° F) Ground Roll (ft)

0420920

20 450 990

Sea Level

2000

4000

6000

8000

40 480 1060
60 520 1130
80 550 1210

100 590 1290

05101120

20 550 1210
40 600 1310
60 640 1410
80 690 1510

100 740 1620

06401410

20 700 1540
40 760 1660
60 820 1800
80 880 1950

100 950 2100

-20 760 1670
0 830 1830

20 910 2010
40 1000 2190
60 1090 2390
80 1180 2610

-20 1010 2230
0 1120 2480

20 1250 2750
40 1380 3040
60 1520 3360
80 1680 3710

Total to Clear 50 ft

Obstacle (ft)

5.8 RATE OF CLIMB

Conditions

1510 lb

f

Flaps—0°

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

5-9 PERFORMANCE / CRUISE PERFORMANCE

CHAPTER 5

Full throttle

V

—58 KIAS

Y

Press Alt

(ft)

Sea Level 682 663 646 629 614 598

1000 644 626 609 592 577 562
2000 607 589 571 555 540 525
3000 569 551 534 518 503 488
4000 532 514 497 481 466 451
5000 494 477 460 444 429 415
6000 457 439 423 407 392 377
8000 381 363 346 330 314 300

10000 303 285 268 252 237 223
12000 224 207 191 175 160 146

0°F 20°F 40°F 60°F 80°F 100°F

5.9 CRUISE PERFORMANCE

Conditions

1510 lb

f

Windows installed

STD Temp - 20°F STD Temp STD Temp + 20°F

Press

Alt

RPM KTAS FF1Econ2KTAS FF1Econ2KTAS FF1Econ

(ft)

4000 76 3.54 21.5 75 3.41 22.1 75 3.29 22.8

Sea

5000 86 4.67 18.5 86 4.46 19.3 86 4.27 20.1

Level

5500 95 8.10 11.8 95 6.92 13.7 95 5.80 16.4
4500 75 3.35 22.4 75 3.22 23.1 74 3.07 24.0

2000

5000 86 4.37 19.7 86 4.16 20.6 85 3.97 21.4
5500 95 6.36 14.9 95 5.18 18.3 95 4.92 19.2
4500 74 3.15 23.6 73 2.99 24.6 73 2.84 25.6

4000

5000 85 4.07 21.0 85 3.87 22.0 85 3.68 23.0

5500955.0518.8944.7719.8944.5120.9
4500 73 2.91 25.1 72 2.76 26.2 71 2.65 26.9

6000

5000 85 3.77 22.5 84 3.57 23.6 84 3.41 24.6
5500 94 4.64 20.3 94 4.36 21.6 94 4.14 22.6

Rate of Climb (ft/min)

2

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

PERFORMANCE / TIME, FUEL, AND DISTANCE TO CLIMB 5-10

CHAPTER 5

STD Temp - 20°F STD Temp STD Temp + 20°F

Press

Alt

RPM KTAS FF1Econ2KTAS FF1Econ2KTAS FF1Econ

(ft)

4500 72 2.70 26.5 70 2.58 27.3 69 2.53 27.2

8000

5000 84 3.49 24.1 84 3.32 25.2 93 3.20 26.0
5500 94 4.26 22.1 94 4.02 23.3 93 3.85 24.3
4500 70 2.56 27.2 68 2.49 27.2 66 2.44 27.0

10000

12000

1. Fuel Flow (gal/hr)

2. Economy (nm/gal)

5000 83 3.26 25.6 83 3.13 26.5 82 3.00 27.4
5500 94 3.94 23.8 93 3.76 24.8 93 3.59 25.9
4500 67 2.47 27.1 65 2.41 26.9 63 2.35 26.8
5000 83 3.07 26.9 82 2.93 27.9 81 2.81 29.0
5500 93 3.67 25.4 93 3.49 26.6 93 3.32 27.9

5.10 TIME, FUEL, AND DISTANCE TO CLIMB

Conditions

1510 lb

f

Flaps—0°

Full throttle

V

—58 KIAS

Y

Zero wind

Standard temperature

2

Corrections

Add 0.2 gallons of fuel for engine start, taxi and takeoff allow­ance.

Increase time, fuel and distance by 5% for each 20°F above
standard temperature.

Press Alt

(ft)

Sea Level 59 0.0 0.0 0.0

1000 55 1.6 0.2 1.6
2000 52 3.4 0.3 3.3
3000 48 5.2 0.5 5.2

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

STD Temp

(°F)

Time (min)

From Sea Level

Fuel Used

(gal)

Distance

(nm)

5-11 PERFORMANCE / RANGE AND ENDURANCE

CHAPTER 5

Press Alt

(ft)

4000 4 5 7.1 0.6 7.2
5000 41 9.2 0.8 9.4
6000 37 11.5 0.9 11.8
8000 30 16.6 1.3 17.3

10000 23 22.9 1.6 24.3

12000 16 31.1 2.1 33.7

STD Temp

(°F)

Time (min)

From Sea Level

Fuel Used

(gal)

Distance

(nm)

5.11 RANGE AND ENDURANCE

Conditions

1510 lb

and Forward CG

f

Flaps—0°

Landing gear—UP

Windows installed

Zero wind

Includes 0.2 gal for engine start, taxi, and takeoff.

Includes fuel and distance to climb to the given altitude.

Includes 45 minutes fuel reserve at 4500 RPM at the given alti­tude.

STD Temp - 20°F STD Temp STD Temp + 20°F

Press

Alt

RPM KTAS

(ft)

4500 76 4.8 369 75 5.1 381 75 5.3 394

Sea

5000 86 3.7 317 86 3.9 332 86 4.1 348

Level

5500 95 2.1 202 95 2.5 237 95 3.0 284
4500 75 5.1 384 75 5.3 398 74 5.6 417

2000

5000 86 3.9 337 86 4.1 354 85 4.3 372
5500 95 2.7 257 95 3.3 316 95 3.5 334
4500 74 5.3 403 73 5.7 424 73 6.0 444

4000

5000 85 4.1 360 85 4.4 379 85 4.6 400
5500 95 3.3 322 94 3.6 343 94 3.8 364
4500 73 5.7 429 72 6.1 453 71 6.4 466

6000

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

5000 85 4.4 386 84 4.7 408 84 4.9 427
5500 94 3.6 350 94 3.8 374 94 4.1 395

Endur

ance
(hrs)

Range

(nm)

KTAS

Endur

ance

(hrs)

Range

(nm)

KTAS

Endur

ance
(hrs)

Range

(nm)

PERFORMANCE / NORMAL RUNWAY LANDING PERFORMANCE 5-12

CHAPTER 5

STD Temp - 20°F STD Temp STD Temp + 20°F

Press

Alt

(ft)

8000

10000

12000

RPM KTAS

4500 72 6.1 454 70 6.4 470 69 6.6 471
5000 84 4.7 414 84 5.0 435 83 5.2 451
5500 94 3.9 381 94 4.1 404 93 4.3 422
4500 70 6.4 465 68 6.5 466 66 6.7 467
5000 83 5.0 438 83 5.2 456 82 5.4 473
5500 94 4.1 409 93 4.3 429 93 4.5 449
4500 67 6.4 462 65 6.6 463 63 6.8 463
5000 83 5.2 460 82 5.4 478 81 5.7 498
5500 93 4.3 435 93 4.6 457 93 4.8 480

Endur

ance
(hrs)

Range

(nm)

KTAS

Endur

ance
(hrs)

Range

(nm)

KTAS

Endur

ance
(hrs)

Range

(nm)

5.12 NORMAL RUNWAY LANDING PERFORMANCE

Conditions

1510 lb

f

Flaps—0°

Level and dry asphalt runway

Reasonable braking

Zero wind

POH approach and normal landing technique except speed at
50 ft is 58 KIAS

Corrections

Decrease distance by 10% for each 8 knots of headwind.

Increase distances by 10% for each 3 knots of tailwind.

Increase ground roll distance by 30% on dry grass.

Tot a l Di st a nc e

Press Alt (ft) Tem p (° F) Ground Roll (ft)

05401620

20 560 1670

Sea Level

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

40 580 1720
60 590 1770
80 610 1820

100 630 1870

from 50 ft

Obstacle (ft)

5-13 PERFORMANCE / WATER LANDING PERFORMANCE

CHAPTER 5

Tot a l Di st a nc e

Press Alt (ft) Tem p (° F) Ground Roll (ft)

05701710

20 590 1760

2000

4000

6000

8000

40 610 1810
60 630 1870
80 640 1920

100 660 1980

0 600 1800
20 620 1860
40 640 1920
60 660 1980
80 680 2040

100 700 2090

-20 620 1840
0 640 1910

20 660 1970
40 680 2030
60 700 2100
80 720 2160

-20 650 1950
0 680 2020

20 700 2090
40 720 2160
60 740 2230
80 770 2290

from 50 ft

Obstacle (ft)

5.13 WATER LANDING PERFORMANCE

Conditions

1510 lb

f

Glassy water

Zero wind

POH approach and normal landing technique except speed at
50 ft is 50 KIAS

NOTE: Short field and normal landing data for water

are identical.

Corrections

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

PERFORMANCE / SHORT FIELD RUNWAY LANDING PERFORMANCE 5-14

CHAPTER 5

Decrease distances by 10% for each 8 knots of headwind.

Increase distance by 10% for each 3 knots of tailwind.

Pressure Altitude

(ft)

Sea Level

2000

4000

6000

8000

Tot a l Di st a nc e

Tem p (° F) Wat er Run (ft )

Obstacle (ft)

20 670 2020
40 690 2080
60 700 2140
80 720 2190

100 740 2250

20 700 2130
40 720 2190
60 74 0 2250
80 760 2310

100 780 2370

20 740 2240
40 760 2300
60 780 2370
80 800 2440

100 830 2500

20 780 2360
40 800 2430
60 830 2500
80 850 2580

100 870 2650

20 820 2500
40 850 2570
60 870 2650
80 900 2730

100 920 2800

from 50 ft

5.14 SHORT FIELD RUNWAY LANDING PERFORMANCE

Conditions

1510 lb

f

Level and dry asphalt runway

Reasonable braking

Zero wind

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

5-15 PERFORMANCE / SHORT FIELD RUNWAY LANDING PERFORMANCE

CHAPTER 5

POH short field landing technique except speed at 50 ft is 50
KIAS

NOTE: Short and normal landing data for water are

identical. See Water Landing Performance for
more information.

Corrections

Decrease distances by 10% for each 8 knots of headwind.

Increase distances by 10% for each 3 knots of tailwind.

Increase ground roll distance by 30% on dry grass.

Tot a l Di st a nc e

Press Alt (ft) Tem p (° F) Ground Roll (ft)

0 440 1460

20 450 1510

Sea Level

2000

4000

6000

40 460 1550
60 480 1590
80 490 1630

100 500 1680

04601540

20 470 1580
40 490 1630
60 500 1680
80 520 1720

100 530 1770

04901620

20 500 1670
40 510 1720
60 530 1770
80 540 1820

100 560 1870

-20 500 1650
0 510 1710

20 530 1760
40 540 1810
60 560 1870
80 570 1920

from 50 ft

Obstacle (ft)

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

PERFORMANCE / SHORT FIELD RUNWAY LANDING PERFORMANCE 5-16

CHAPTER 5

Tot a l Di st a nc e

Press Alt (ft) Tem p (° F) Ground Roll (ft)

from 50 ft

Obstacle (ft)

-20 520 1750
0 540 1800

8000

20 560 1860
40 570 1920
60 590 1970
80 610 2030

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

WEIGHT, BALANCE, AND EQUIPMENT LIST / INTRODUCTION 6-2

CHAPTER 6

Chapter 06

WEIGHT, BALANCE, AND EQUIPMENT LIST

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2

Aircraft Dimensional Data . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3

Weight and Balance Record . . . . . . . . . . . . . . . . . . . . . . . . . 6-4

Operating Weights and Loading . . . . . . . . . . . . . . . . . . . . . .6-5

Empty Weight and CG Measurement While on Gear . . .6-5

Weight and Balance Determination for Flight . . . . . . . . . .6-7

Installed Optional Equipment List . . . . . . . . . . . . . . . . . . . . 6-9

6.1 INTRODUCTION

This section describes the procedure and provides relevant
reference information to determine the weight and balance of the
ICON A5. Additionally, a discussion of the aircraft equipment list is
included.

The A5 design places the cockpit forward of the flight center of
gravity range. A change of occupant weight will therefore also
change the CG location. It is possible to be outside the forward CG
limit with a heavy total occupant weight and to be outside the aft CG
limit with a light occupant. It is therefore imperative for all pilots to
become familiar with the weight and balance of the specific aircraft
they will fly, and their own specific loading condition. Specific details
about weight, moment, and center of gravity for this airplane can be
found accompanying this POH.

WARNING: It is the responsibility of the pilot to make sure

the airplane is loaded properly. Operation
outside of the approved weight and balance
limitations could result in an accident and
serious or fatal injury.

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

6-3 WEIGHT, BALANCE, AND EQUIPMENT LIST / AIRCRAFT DIMENSIONAL DATA

CHAPTER 6

340

280

80

(FS)

Fuselage

Station

300

180

160

140

120

100

320

60

200

220

240

260

FS

294.63
Aft

Jackpoint

FS

153.0
Fuel

FS

84.5

Nose Gear Axle

(1g empty)

FS

147.7
Wing

Jackpoint

FS

154.75

Spar Datum

FS

128.5

Occupants

FS

176.0

Main Gear

Axle

FS

157.0

Baggage

6.2 AIRCRAFT DIMENSIONAL DATA

6.2.1 AIRCRAFT REFERENCE DATUMS

FIGURE 6-1

AIRCRAFT REFERENCE DATUMS

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

WEIGHT, BALANCE, AND EQUIPMENT LIST / WEIGHT AND BALANCE RECORD 6-4

CHAPTER 6

6.3 WEIGHT AND BALANCE RECORD

The aircraft empty weight and CG are determined prior to delivery.
The first entry is made in this Weight and Balance Record. For any
change of equipment, repair, or alteration that affects empty weight,
the CG position and moment of the net addition/removal must be
entered in the Weight and Balance Record included with this POH.
Always ensure that you are using the latest weight and balance
information when performing a weight and balance calculation.

ICON A5 Serial No.

Date Description of Changes

As Delivered

Weigh t Chan ge

Added (+) or Removed (-)

Wt (lbf) FS (in)

Moment

(lb

f

-in)

Running Totals

Wt (lbf)

Moment

(lb

f

-in)

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

6-5 WEIGHT, BALANCE, AND EQUIPMENT LIST / OPERATING WEIGHTS AND LOADING

CHAPTER 6

6.4 OPERATING WEIGHTS AND LOADING

Maximum Human Weight

250 lb

per person

f

Maximum Baggage/Cargo Weight

60 lb

f

WARNING

: Loading a concentrated weight fully aft in the

baggage area may cause an unsafe aft CG
condition.

Minimum Number of Anchor Loops

At least three (3) out of the six (6) provided anchor loops must
be used in order to safely restrain the full baggage/cargo load.

Minimum Load Rating of Cargo Restraints (Pilot Supplied)

1000 lb

f

Full Usable Fuel Weight

120 lb

(20 US gal at 6 lbf per US gal)

f

Removable Side Window Weight and Fuselage Station

7.18 lb

(total both windows)

f

FS 127.6

Removable Wind Deflector Weight and Fuselage Station

0.3 lb

(total both deflectors)

f

FS 113.4

6.5 EMPTY WEIGHT AND CG MEASUREMENT WHILE ON GEAR

The airplane empty weight includes engine oil and coolant, unusable
fuel, hydraulic brake fluid, and installed equipment for the aircraft.

The airplane must be weighed and leveled in a level area. The
weighing area should also be calm or indoors to prevent wind from
affecting the readings.

Check the calibration of the scales used to ensure accurate results.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

WEIGHT, BALANCE, AND EQUIPMENT LIST / EMPTY WEIGHT AND CG MEASUREMENT WHILE ON GEAR

CHAPTER 6

6-6

Check the oil dipstick to verify at least 3.17 quarts (three liters) of oil.
Service as necessary. The difference between the max and the min
marks is approximately 0.5 quarts (0.47 l).

Usable fuel must be pumped out of the fuel tank. See the
Maintenance Manual.

Retract flaps to the 0° position.

Center all controls to the neutral, static position.

Install removable side windows.

Close and latch the canopy.

Ensure all inspection covers and panels are installed.

1. Install three platform scales under the two main gear and nose

gear.

NOTE: Remove the floor boards as described in the

Maintenance Manual. Set the floor boards
back in place after leveling.

2. Shim or block up the aircraft so that the bubble level beneath

the right side floor board indicates a level condition.

3. Record the weight readings on the scales under the nose gear,

main gear RH, and main gear LH.

4. Complete the Empty Weight and CG Calculation Form and

perform the calculations to obtain the total empty weight and
CG position.

Fill out blank cells in table below.

Scale Position Weight, Wt (l bf) Arm, FS (in)

Nose Gear 84.5
Right Main Gear 176.0
Left Main Gear 176.0
To ta l

Tot a l We i g ht (l bf) CG Position—FS (in)

Moment, M=Wt x
Arm (lb

f

-in)

Calculate the FS location of the CG by dividing the total moment by
the total weight.

Total Wt (from above)=______ lbs

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

6-7 WEIGHT, BALANCE, AND EQUIPMENT LIST / WEIGHT AND BALANCE DETERMINATION FOR FLIGHT

CHAPTER 6

Aircraft CG Location, FS (Total M/Total Wt)=______ in

Verify that the above readings and calculations make sense by
comparing them with the Weight and Balance Record. Enter the
new weight and balance information as a new baseline into the
Weight and Balance Record.

6.6 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT

It is the pilot’s responsibility to ensure that the aircraft is properly
loaded and operated within the prescribed weight and CG limits.
The following steps should be used to calculate the airplane weight
and CG for flight. The Weight and Balance Loading Form gives one
method to complete this procedure.

Moment = Weight x FS

1. Empty Weight—Enter the empty weight and moment from the
airplane “Weight and Balance Record” on page 6-4.

2. Pilot—Enter the weight and calculate and enter moment of the
pilot.

3. Passenger—Enter the weight and calculate and enter moment
of the passenger or enter zero if there will be no passenger.

4. Usable Fuel—Enter the total weight and calculate and enter
moment of usable fuel loaded into the airplane.

NOTE: 1 gallon of fuel = 6 pounds

5. Baggage/Cargo—Enter the total combined weight and calcu­late and enter moment of baggage loaded into the baggage
area.

6. If side windows are removed (and completely out of the
airplane) and deflectors installed, include this line item in the
totals, which accounts for both items.

a. If side windows are to be carried as baggage for flight,

include their weight and moment arm (see Operating
Weights and Loading) as Baggage/Cargo in addition to
this line item.

7. Garmin aera 796 Accessory—If carrying the unit onboard,
include this line item in the totals.

8. Other—Additional space for other items, if needed. Note that
FS must be determined.

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

WEIGHT, BALANCE, AND EQUIPMENT LIST / WEIGHT AND BALANCE DETERMINATION FOR FLIGHT 6-8

CHAPTER 6

9. Other—Additional space for other items, if needed. Note that
FS must be determined.

10. Totals—Total the weights and moments and determine CG
Position (FS).

a. Transfer the weight total to the Total Weight box.
b. Calculate the CG Position (FS) by dividing Total Moment

by Total Weight and enter into the box.

11. Verify that the weight and CG are within acceptable limits as
depicted in. See Figure 6-2.

6.6.1 WEIGHT AND BALANCE LOADING FORM

Position

1.

2. Pilot 128.5

3. Passenger 128.5

4. Usable Fuel 153.0

5. Baggage/Cargo 157.0

6.

7. If Garmin 796 Will Be Used 1.7 109.7 186.5

8. Other

9. Other

10. To t a ls :

Tot a l We i g ht (l bf)

1. Not to exceed 1510 lb

2. See Weight and CG Envelope Limits

(See Weight & Balance Record)

If Side Windows Removed & Deflectors

Empty Weight

Installed (Net)

1

f

Wei gh t, Wt

(lb

-6.88 -882.1

CG Position—FS (in)

Arm,

)

f

FS

(in)

2

Moment

M=Wt x Arm

(lb

6.6.2 CG LIMITS AND STATION INFORMATION

Maximum Takeoff Weight (MTOW)

1510 lb

f

f

-in)

Reference Datum

FS 154.75 (located on forward face of wing spar carry-through)

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK

6-9 WEIGHT, BALANCE, AND EQUIPMENT LIST / INSTALLED OPTIONAL EQUIPMENT LIST

CHAPTER 6

Forward CG Limit

FS 153.0

Aft CG Limit

FS 159.2

NOTE: See the Weight and CG Envelope Limits

figure for further details on the acceptable
operating envelope.

6.6.3 CENTER OF GRAVITY LIMITS

FIGURE 6-2

WEIGHT AND CG ENVELOPE LIMITS

6.7 INSTALLED OPTIONAL EQUIPMENT LIST

At this time, the ICON A5 has no equipment options or maintenance
procedures allowed that affect weight and balance. Any
modifications to the aircraft equipment require the prior approval of
ICON Aircraft. Should such work be necessary, ICON will supply any
needed weight and balance information and instructions through

ICON A5 / PILOT’S OPERATING HANDBOOK CHANGE A0

WEIGHT, BALANCE, AND EQUIPMENT LIST / INSTALLED OPTIONAL EQUIPMENT LIST 6-10

CHAPTER 6

the Major Repair and Alteration (MRA) process, which is part of the
A5 maintenance program.

CHANGE A0 ICON A5 / PILOT’S OPERATING HANDBOOK