Symphony SA-160 Flight Manual

SA 160

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APPLICABILITY / REVISIONS

APPLICABILITY

i

Feb 25, 2005

This handbook contains information applicable to the model SA 160
aircraft designated by serial number and registration number shown on
thetitlepage.
All information is based on data available at the time of delivery of your
aircraftby SymphonyAircraft IndustriesInc.

NOTE: A current handbook must be in the aircraft during flight. It

is theoperator's responsibility to maintainthe handbook in
acurrentstatus.

The information in this handbook will be kept current by revisions
issuedby .
Revision materialwill contain information necessary toupdate the text,
figures,and chartsof thepresent handbookand /or addinformation.

1.Incorporating Revisions

Revisions must be incorporated as they are issued. Revision status is
noted on List of Revisions page and Log of Effective Pages table in this
section.
Revisionsshall beinserted intothe handbookas follows:

(a) Alwaysreplace pageswith revisionpages ofsame pagenumber.
(b) Insert additional pages in correct numerical order within each

section.

Revisions

SymphonyAircraft Industries

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APPLICABILITY / REVISIONS

2.Identification ofRevised Material

Revisions, additions and deletions will be identified by a vertical black
line alongthe outsideof thepage oppositeonly the portion ofthe printed
matterthat waschanged.

A line along the outside margin of the page beside the page number
indicatesthat non-changedmaterial hasa newphysical locationonly.

Thedate ofthe revisionis shownon eachrevised page.

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LIST OF REVISIONS

LIST OF REVISIONS

Description

Page
No.

Date

Rev.
No.

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Approval

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CONTENTS

CONTENTS

SECTION

GENERAL............................1

LIMITATIONS .........................2

EMERGENCY PROCEDURES ................3

NORMAL PROCEDURES ..................4

PERFORMANCE........................5

WEIGHT AND BALANCE

EQUIPMENT LIST.......................6

DESCRIPTION AND OPERATION

OF THE AIRCRAFT AND ITS SYSTEMS ..........7

HANDLING, SERVICING AND

MAINTENANCE ........................8

SUPPLEMENT .........................9

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SECTION 1

GENERAL

1-1

SECTION 1

GENERAL

TABLE OF CONTENTS

Page

Aircraft Views (3) ..............................................................................1-2

1.1 Introduction..........................................................................................1-4

1.3 Technical Data ......................................................................................1-5

Engine.................................................................................................1-5

Propeller.............................................................................................1-5

Fuel......................................................................................................1-5

Oil........................................................................................................1-6

Maximum Certificated Weights......................................................1-6

Typical Aircraft Weights...................................................................1-6

Cabin and Entry Dimensions .........................................................1-7

Baggage Space...................................................................................1-7

Specific Loadings..............................................................................1-7

Other Data .........................................................................................1-7

1.5 Symbols, Abbreviations and Terminology .......................................1-8

(a) General Airspeed Terminology and Symbols......................1-8

(b) Meteorological Terminology ................................................1-10

(c) Power Terminology................................................................1-11

(d) Engine Instruments ...............................................................1-11

(e) Aircraft Performance and Flight

Planning Terminology...........................................................1-11

(f) Weight and Balance...............................................................1-12

(g) Other Definitions ...................................................................1-14

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AIRCRAFT VIEWS

Abb. 1-1(1)

Aircraft Views

1-2

10.67 (35)

2.11 (6.92)

1.118 (3.67)

3.27 (10.75)

0.86 (2.82)

m (ft.)

SECTION 1
GENERAL

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Abb. 1-1(2)

Aircraft Views

1-3

2.82 (9.25)

1.72 (5.67)

6.960 (22.84)

SECTION 1

GENERAL

Notes:

The ground clearance of the propeller at maximum takeoff weight and
in the takeoff attitude is at least 0.180 m (7 in.). Maximum propeller
diameteris 1.854m (73in.).
Thewing areais 11.93m² (128.4sq.ft.).
A minimum turning radius of 6.6 m (21.7 ft) (Pivot point to the wing
tip) can be achieved.

Control Surface Deflections:

- Aileron Up 23° - Down 17°;

- Elevator Up 21° - Down 20°;

- Rudder Left 21°- Right 21°;

- Trim Tab Up 10° - Down 20°;

- Flaps - Down 0° to 40°.

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1-4

1.1 INTRODUCTION

SECTION 1
GENERAL

This manual constitutes a Transport Canada approved Airplane Flight
Manualfor Canadianregistered airplanesin accordancewith AWM 523.

In countries other than Canada, Transport Canada operating rules may
not apply. Operators must ensure that the aircraft is operated in
accordancewith nationaloperating rules.

The manual is divided into 8 sections and contains data for the pilot that
must be available in accordance with the CARs. Supplementary
specificationsof theaircraft manufacturerare alsoincluded.

The handbook is intended to familiarize the pilot with the aircraft,
operating limits, emergency procedures, normal procedures and
performance.

The handbook does not serve as a substitute for appropriate flight
training and knowledge of valid airworthiness advisories, the relevant
official aviation rules and the advisory circulars. It is not intended as
orientation for flight, basic training, or as a training manual, and it may
onlybe usedas thecurrentstatus for theoperationof theAircraft.

The handbook is divided into sections, which are numbered with Arabic
digits. Each section is divided by separator sheets for speedy reference.
The operating limitsand theemergency proceduresare placedbefore the
normal procedures, the performance data and the other sections. The
section "Emergency Procedures" is marked witha red tab divider so that
thissection canbe lookedup immediately.

Provision for an extension to the handbook is provided. Therefore, some
paragraph numbers, figure numbers, position numbers and pages are
deliberatelyomitted andannotated "Intentionally leftblank".

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1.3 TECHNICAL DATA

1-5

SECTION 1

GENERAL

Engine

Propeller

Fuel

(a) Number 1
(b) Engine Manufacturer Textron Lycoming.
(c) Engine Model O-320-D2A
(d) Engine Type Four cylinder, direct drive,

horizontally opposed,

air cooled engine with

a float type carburetor
(e) Rated Power 119 kW (160 BHP)
(f) Rated Speed 2700 RPM
(g) Bore 130.175 mm (5.125 in.)
(h) Stroke 98.425 mm (3.875 in.)
(i) Displacement 5.24 l (319.8 cu.in.)
(j) Compression Ratio 8.5:1

(a) Number 1
(b) Propeller Manufacturer MT-propeller
(c) Propeller Model MT 186 R 140-3D P-244-3
(d) Number of Blades 2
(e) Propeller Diameter 1860 mm, (73.2)
(f) Propeller Type Wood, fixed pitch

(a) Fuel Approved Fuel Grades

AVGAS 100 LL blue
(b) Total Capacity 122 l (32.2 U.S. Gal)
(c) Total Usable 110 l (29.1 U.S. Gal)

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SECTION 1
GENERAL

Oil

Maximum Certified Weights

Typical Aircraft Weights

(a) Oil Specification Aviation Grade Straight

Mineral Oil MIL-L-6082

and Aviation Grade Ashless

Dispersant Oil MIL-L-22851

(b) Oil Viscosity

Mean Environment- MIL-L-6082 MIL-L-22851
Temperature Ashless Dispersant

Above 16°C (60°F) SAE 50 SAE 40 or SAE 50

-1°C to 32°C SAE 40 SAE 40

-18°C to 21°C SAE 30 SAE 30 or SAE 40
Below -12°C SAE 20 SAE 30

(c) Max. Oil Capacity 7.6 l (8 qt)
(d) Recommended Oil Quantity 4.7 - 6.6 l (5 -7 qt)

(a) Maximum Ramp Weight 975 kg (2150 lbs)
(b) Maximum Takeoff Weight 975 kg (2150 lbs)
(c) Landing Weight 926 kg (2041 lbs)
(d) Maximum Weight in Baggage Compartment 75 kg (165 lbs)

but in the front or rear area maximum 45 kg (99 lbs)

(a) Empty Weight depending

630 - 660 kg (1389 - 1455 lbs)

(b) Maximum Useful Load 345 kg (761 lbs)

(30°F) (90°F)

(0°F) (70°F)

(10°F)

on installed equipment:

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SECTION 1

GENERAL

Cabin and Entry Dimensions

Baggage Spaces

Specific Loadings

(a) Maximum Cabin Width 1.10 m (43.3 in.)
(b) Maximum Cabin Length 1.22 m (48.0 in.)
(c) Maximum Cabin Height 1.14 m (44.8 in.)
(d) Maximum Entry Width 0.805 m (31.7 in.)
(e) Maximum Entry Height 0.80 m (31.5 in.)
(f) Maximum Sill Height 0.838 m (33 in.)

(a) Compartment Width 0.44 m (17.3 in.) - 0.87 m (34.3 in.)
(b) Compartment Length 1.255 m (49.4 in.)
(c) Compartment Height 0.45 m (17.7 in.) - 0.77 m (30.3 in.)
(a) Volume 870 l (30.72 cu.ft)

(a) Wing Area Loading 81.7 kg/m (16.73 lbs/sq.ft.)
(b) Power Loading Takeoff Power (N) / 975 x 9.81 (N) = 0.122

= 8.19 kg/kW (13.89 lbs/hp)

2

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SECTION 1
GENERAL

1.5 SYMBOLS, ABBREVIATIONS
AND TERMINOLOGY

The followingdefinitions arefor symbols,abbreviation, and terms which
are used in this handbook or are relevant for the pilot during the
operationof theAircraft.

means the indicated speed of an aircraft,
corrected for position and instrument error. CAS is equal to TAS in
standardatmosphere atsea level.

CalibratedAirspeed expressedin "knots”.

isthe speedrelative tothe ground.

is thespeed ofan aircraftas shownon the airspeed
indicator whencorrectedfor instrument error. IASvalues published
inthis Handbookassume zeroinstrumenterror.

IndicatedAirspeed expressedin "knots".

isthe ratioof true airspeedto thespeed ofthe sound.

is the airspeed of anAircraft relative to undisturbedair
which is the CAS corrected for altitude, temperature and
compressibility.

(a) General Airspeed Terminology and Symbols

CAS

KCAS

GS

IAS

KIAS

M

TAS

Calibrated Airspeed

Ground Speed

Indicated Airspeed

Mach Number

Tr ue Airspeed

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SECTION 1

GENERAL

V/V

AO

Maneuvering Speed

Maximum Flap Extended Speed

Never Exceed Speed

Maximum Structural Cruising Speed

Stall Speed

Stall Speed with flap

Best Angle-of-Climb Speed

Best Rate-of-Climb Speed

V

V/M

V

V

V

V

V

is the maximum speed at which application of

fullavailable aerodynamiccontrol willnot overstressthe Aircraft.

is the highest speed permissible with

wingflaps ina prescribedextended position.

or Mach Number is the speed limit that may not

beexceeded atany time.

is the speed that should not be

exceededexceptin smoothair andthen onlywith caution.

or the minimum steady flight speed at which the Aircraft

iscontrollable.

orthe minimumsteady flight speedat whichthe

Aircraftis controllablein thelanding configuration.

is the airspeed which delivers the greatest

gainof altitudein theshortest possiblehorizontal distance.

is the airspeed which delivers the greatest

gainin altitudein theshortest possibletime.

FE

NE NE

NO

S

SO

x

Y

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SECTION 1
GENERAL

(b) Meteorological Terminology

ISA

OAT

MSN

Indicated Pressure Altitude

Pressure Altitude

Station Pressure

International StandardAtmosphere

Outside Air Temperature

inwhich
(1) The airis adry perfect gas;
(2) The temperatureat sealevel is15° Celsius(59° Fahrenheit);
(3) The pressureat sealevel is29.92 inchesh g.(1013.2mb);
(4) The temperature gradient from sea level to the altitude at which

thetemperature is-56.5°C (-69.7°F) is- 0.00198°C
(- 0.003564°F)per footand zeroabove thataltitude.

is the free air static temperature, obtained
either from inflight temperature indications or ground
meteorological sources, adjusted for instrument error and
compressibilityeffects.

Mean Sea Level

The number actually read from an altimeter when the barometric
subscalehas beenset to29.92 inchesof mercury (1013.2mb).

Altitudemeasured fromstandardsea levelpressure(29.92 in.hg.)by
a pressure or barometric altimeter. It is the indicated pressure
altitude corrected for position and instrument error. In this
Handbook,altimeter instrument errorsare assumedto bezero.

Actualair pressureat fieldelevation.

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SECTION 1

GENERAL

(c) Power Terminology

(d) Engine Instruments

(e) Aircraft Performance and Flight Planning Terminology

Takeoff Power

Maximum Continuous Power

Cruise Climb Power

Maximum Cruise Power

EGT-Indicator

CHT-Indicator

Climb Gradient

Themaximum powerpermissible fortakeoff(may betime limited).

Highestpower setting,not limitedby time.

Powerrecommended forcruise climb.

The maximum power setting for which specific values of fuel flow

andairspeed arepresented.

ExhaustGas TemperatureIndicator

Cylinder Heat Temperature Indicator

The demonstrated ratio of the change in height during a portion of
a climb, to the horizontal distance traversed in the same time
interval

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1-12

SECTION 1
GENERAL

Demonstrated Crosswind Velocity

Accelerate-StopDistance

Route Segment

MEA

Reference Datum

Station

Arm

The demonstrated crosswind velocity is the velocity of the
crosswindcomponent forwhich adequatecontrol ofthe Aircraft
during takeoff and landing was actually demonstrated during
certificationtests.

The distance required to accelerate an Aircraft to a specified speed
and, assuming failure of an engine at the instant that speed is
attained,to bringthe Aircraftto astop.

A part of a route. Each end of that part is identified by: (1) a
geographical location;or (2) apoint at whicha definite radiofix can
beestablished.

Minimumenroute IFRaltitude.

An imaginary vertical plane from which all horizontal distances are
measuredfor balancepurposes.

A location along the Aircraft fuselage usually given in terms of
distancefrom thereference datum.

The horizontal distance from the reference datum to the center of
gravity(C.G.) ofan item.

(f) Weight and Balance

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SECTION 1

GENERAL

Moment

Center of gravity (C.G.)

C.G. Arm

C.G. Limits

Usable Fuel

Unusable Fuel

Standard Empty Weight

Basic Empty Weight

Useful load

,

The productof theweight ofan itemmultiplied byits arm.(Moment
divided by a constant is used to simplify balance calculations by
reducingthe numberof digits.)

The point at which an Aircraft would balance if suspended. Its
distance from the reference datum is found by dividing the total
momentby thetotal weightof theAircraft.

The arm obtained by adding the Aircraft's individual moments and
dividingthe sumby thetotal weight.

The extreme center of gravity locations within which the Aircraft
mustbe operatedat agiven weight.

Fuelavailable forflight planningpurposes.

Fuel remaining after a run out test has been completed in
accordancewith governmental regulations.

Weightof astandard Aircraftincluding unusablefuel, fulloperating
fluidsand fulloil.

Standardempty weightplus optionalequipment.

Difference between take off weight, or ramp weight if applicable
andbasic emptyweight.

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Payload

Maximum Ramp Weight

Maximum Takeoff Weight

Maximum Landing Weight

Maximum Zero Fuel Weight

Weightof occupants,cargo andbaggage.

Maximum weight approved for ground maneuvre. (It includes
weightof start,taxi andrun upfuel.)

Maximumweight approvedfor thestart ofthe takeoffrun.

Maximumweight approvedfor thelanding touchdown.

Maximumweight exclusiveof usablefuel.

Methods, proceduresor limitswhich must befollowed precisely
toavoid injury ordeath.

(g) Other Definitions

1-14

CAUTION !

WARNING !

SECTION 1
GENERAL

Methods, procedures or limits which must be followed to avoid
damageto equipment.

Additionalprocedures orinformation pertainingto thetext.

NOTE:

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SECTION 2

LIMITATIONS

2-1

SECTION 2

LIMITATIONS

TABLE OF CONTENTS

2.1 General..................................................................................................2-2

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

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

2.7 Power Plant Limitations .....................................................................2-4

2.9 Engine Parameter Color Markings...................................................2-5

2.11 Weight Limits .......................................................................................2-6

2.13 Center of Gravity Limits.....................................................................2-6

2.15 Maneuver Limits .................................................................................2-6

2.17 Flight Load Factor Limits ...................................................................2-7

2.19 Crew ......................................................................................................2-7

2.21 Kinds of Operations............................................................................2-7

2.23 Fuel Limitations...................................................................................2-8

2.29 Placards .................................................................................................2-9

2.25 Other Limitations ................................................................................2-8

(a) Airframe.....................................................................................2-8

2.27 Temperature Limitation ......................................................................2-8

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2.1 GENERAL

2.3 AIRSPEED LIMITATIONS

2-2

This section contains the operating limits (approved by the regulatory
authority), the instrument markings, the color coding and the most
important placards that are necessary for the safe operation of the
aircraft,engine, systems,and theaircraft's standardequipment.

The Chapter 4 "Airworthiness" of the SA 160 Maintenance Manual
containsthe prescribedlimitations concerning themaintenance.

The aircraft must be operated in compliance with these operating limits,
which areprovided inthe form ofmarkings andplacards aswell asin this
manual.
Operating limits for specific systems and equipment are incorporated in
section9, entitled"Supplements".

Airspeed KIAS KCAS

V

V

NE

NO

- 162 162
Do not exceed this speed in
any operation.

Maximum Structural Cruising 130 130
Speed - Do not exceed this
speed except in smooth air and
then only with caution.

975 kg (2150 lbs). Do not make 116 116
full or abrupt control movements
above this speed.

Maneuvering Speed at weightV/V

AO

SECTION 2
LIMITATIONS

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