Glasair Sportsman GS-2 Owner's Manual

Model GS-2

TAILDRAGGER

OWNER’S MANUAL

Serial #__________

P/N 063-03002-01

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Published by

GLASAIR AVIATION, LLC

18810 - 59th Avenue NE

Arlington, WA 98223

No part of this manual may be reproduced in any form without the

prior written permission of the publisher.

Copyright 2004 by

GLASAIR AVIATION, LLC

Printed in USA

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O

WNER’S MANUAL

TABLE OF CONTENTS

GENERAL INFORMATION........................................................ Section 1

LIMITATIONS.............................................................................Section 2

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

NORMAL OPERATING PROCEDURES....................................Section 4

WEIGHT AND BALANCE..........................................................Section 5

SYSTEMS DESCRIPTIONS .......................................................Section 6

HANDLING, SERVICE AND MAINTENANCE..........................Section 7

FLIGHT TEST .............................................................................Section 8

SAFETY INFORMATION ...........................................................Section 9

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LIST OF REVISIONS

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SECTION 1

G

ENERAL INFORMATION

Table of Contents

Subject: Page:

1-1 INTRODUCTION...........................................................................2

1-2 APPLICABILITY AND PURPOSE .................................................2

1-3 FAA REGULATIONS.....................................................................3

1-4 USE OF THE MANUAL ................................................................4

1-5 REVISIONS ...................................................................................5

1-6 WARNINGS, CAUTIONS AND NOTES.......................................5

1-7 AIRPLANE 3-VIEW.......................................................................6

1-8 SPECIFICATIONS .........................................................................8

1-9 PERFORMANCE DATA............................................................. 10

1-10 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY.............. 12

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1-1 INTRODUCTION

The sole purpose of this manual is to explain the safe and efficient operation of your Sportsman aircraft. Section 1 provides basic aircraft specifications and performance data as well as general information on the use of the manual. It also contains definitions of symbols, abbreviations and terminology used throughout the manual.

1-2 APPLICABILITY AND PURPOSE

The information contained in this manual refers to the Sportsman aircraft (Model GS-2) built according to the

Manual.

from the

Any homebuilder modifications to the aircraft that deviate

Assembly Manual

may alter the applicability of this manual to

your airplane.

This manual is not designed nor can it serve as a substitute for adequate and competent flight instruction. It is not intended to be a guide of basic flight instruction or a training manual.

This manual should be read thoroughly and carefully by the owner and/or operator in order to become familiar with the operation of the aircraft. It is intended to serve only as a guide under most circumstances, but cannot take the place of good, sound judgment during flight operations. Multiple emergencies, adverse weather, terrain, etc., may require deviation from the recommended procedures. Furthermore, this

Owner’s Manual

does not provide a discussion of all

possible dangerous situations an owner or operator may encounter.

Sportsman Assembly

Flying in itself is not inherently dangerous, but to an even greater

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GENERAL INFORMATION

extent than any other mode of travel, it is terribly unforgiving of any carelessness, incapacity or neglect. The builder/pilot is entirely responsible for the manufacture, inspection, maintenance, test flight and normal operation of the aircraft. Thorough, careful procedures, therefore, must be carried out in all these phases.

How well the plane is built, maintained and operated will determine how safely it performs. Maximum performance and safe operation can only be achieved by a skilled pilot and a good mechanic. Thorough, careful construction, continued maintenance and diligent practice during the early phases of flight familiarization are mandatory.

The performance data presented in this manual are estimates based on flight tests of Glasair Aviation’s own aircraft. Due to differences in the engine and propeller installed, quality of workmanship and many other variables, each airplane will vary somewhat in performance. Do not assume that your aircraft will have the same performance characteristics as presented in this manual.

1-3 FAA REGULATIONS

The owner and operator should be familiar with the Federal Aviation Regulations (FARs) applicable to the operation and maintenance of an airplane licensed in the experimental amateur-built category and with FAR Part 91, General Operating and Flight Rules. Further, the airplane must be operated and maintained in accordance with FAA Airworthiness Directives that may be issued against powerplants, propellers and any other parts of the aircraft not manufactured by Glasair Aviation. Additionally, mandatory service bulletins issued by

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Glasair Aviation must be complied with.

The Federal Aviation Regulations place the responsibility for maintenance of this airplane on the owner and operator. All limits, procedures, safety practices, time limits, servicing and maintenance requirements contained in this manual are considered mandatory for continued safe airworthiness and to maintain the airplane in a condition equal to that of its original construction.

NOTE

The Federal Aviation Regulations mentioned throughout this manual refer, of course, to regulations issued by the Federal Aviation Administration (FAA) in the USA. Owners and operators of Sportsmans in other countries must comply with the regulations issued by the controlling authorities in their own countries.

1-4 USE OF THE MANUAL

The

Sportsman Owner’s Manual

necessary for the safe and efficient operation of the aircraft. It is published in loose-leaf form for easy revision updates and in a convenient size for storage in the airplane. The manual is divided into nine major sections, which are listed in the Table of Contents. Each section also has its own individual Table of Contents.

is designed to maintain documents

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GENERAL INFORMATION

1-5 REVISIONS

Immediately following the Table of Contents page in the front of the manual is the “List of Revisions,” which lists all revisions to the

Manual

by the revision letter, date issued, section and page number. When you receive a revision, remove and discard all the obsolete pages, and insert the revised pages.

1-6 WARNINGS, CAUTIONS AND NOTES

The following definitions apply to WARNINGS, CAUTIONS and NOTES used throughout this manual.

WARNING Procedures, practices, etc., which may result in personal injury or loss of life if not carefully followed.

CAUTION Procedures, practices, etc., which if not strictly observed may result in damage to or destruction of equipment.

NOTE An operating procedure, condition, etc., which it is considered essential to emphasize.

Owner’s

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1-7 AIRPLANE THREE-VIEW

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GENERAL INFORMATION

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1-8 SPECIFICATIONS

Wing Span ...................................................................................... 35.0 ft.

Wings Folded/Tail Removed ..................................................8.25 ft.

Wing Area.....................................................................................131.0 ft.

Wing Aspect Ratio ..................................................................................9.6

Fuselage Length:

With Lycoming Engine............................................................23.0 ft.

Wings Folded (Lycoming engine)...........................................24.7 ft.

Maximum Height.............................................................................. 6.9 ft.

Wheel Base..................................................................................... 17.5 ft.

Wheel Span (track)........................................................................... 7.2 ft.

Cabin Width at Hips....................................................................... 44.0 in.

At Shoulders............................................................................ 46.0 in.

Front Door Width ..........................................................................37.0 in.

Height ......................................................................................31.5 in.

Sill to Ground .......................................................................... 33.0 in.

2

Rear Door Width............................................................................ 26.0 in.

Height ......................................................................................31.0 in.

Baggage Space............................................................................... 37.0 ft.

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3

GENERAL INFORMATION

Maximum Gross Weight: ............................................................ 2,350 lb.

Empty Weight (approx.) .............................................................. 1,350 lb.

Useful Load (approx.) .................................................................. 1,000 lb.

Baggage Capacity (maximum)........................................................ 300 lb.

Wing Loading, Gross................................................................. 17.5 lb./ft.

Fuel Capacity (total):

Main Wing Tanks (standard) .................................................... 30 gal.

Auxiliary Tip Tanks (standard) .................................................. 20 gal.

Fuel Capacity (usable):

Main Wing Tanks ...................................................................... 29 gal.

Auxiliary Tanks .......................................................................... 19 gal.

Seats........................................................................................................... 4

Tire Size:

Main Gear (standard)..............................................................6.00 × 6

Main Gear (optional)...............................................................8.00 × 6

Main Gear (optional)....................................................... 26.00 × 10.5

Tail Wheel...................................................................... 2.80/2.50 × 4

2

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1-9 PERFORMANCE DATA

NOTE

Performance numbers are the actual data from Glasair Aviation’s prototype Sportsman equipped with 8.00 × 6 tundra tires without wheel pants. The 180 h.p. numbers are for aircraft equipped with Lycoming O-360 engine and Hartzell constant-speed propellers. The performance of a different airplane will vary depending on engine horsepower, propeller choice, aircraft weight, airframe construction and pilot ability.

Top Speed (sea level, TAS):

180 h.p. ............................................................... 140 kts./161 m.p.h.

Cruise Speed (75% power @ 8,000 ft., TAS):

180 h.p. ............................................................... 135 kts./155 m.p.h.

Cruise Speed (65% power @ 8,000 ft., TAS):

180 h.p. ............................................................... 130 kts./149 m.p.h.

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GENERAL INFORMATION

Stall Speeds, Gross:

No Flaps (Vs).............................................................51 kts./58 m.p.h.

Full Flaps (Vso)..........................................................42 kts./48 m.p.h.

Best Rate of Climb Speed (Vy)........................................85 kts./97 m.p.h.

Best Angle of Climb Speed (Vx)......................................75 kts./86 m.p.h.

Best Glide Speed..............................................................80 kts./92 m.p.h.

Maneuvering Speed (Va) .............................................. 98 kts./113 m.p.h.

Maximum Structural Cruising Speed (Vno)...............144 kts./166 m.p.h.

Rate of Climb, Solo:

180 h.p.......................................................................... 1,950 ft./min.

Rate of Climb, Gross:

180 h.p.......................................................................... 1,000 ft./min.

Structural Limit Loads, Gross

Positive .......................................................................................3.8 Gs

Negative .....................................................................................1.5 Gs

Fuel Consumption at 65% power:

180 h.p............................................................................... 8.0 gal./hr.

Range at 65% power (no wind, VFR reserve):

180 h.p...................................................................747 n.m./859 s.m.

Service Ceiling (estimated):

180 h.p................................................................................ 20,000 ft.

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1-10 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

CAS

— Calibrated Airspeed is the indicated speed of an airplane, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level.

KCAS

— Calibrated Airspeed expressed in knots.

GS

— Ground Speed is the speed of an airplane relative to the ground.

IAS

— Indicated Airspeed is the speed of an airplane as shown on the

airspeed indicator when corrected for instrument error. IAS values published in this manual assume zero instrument error.

KIAS

— Indicated Airspeed expressed in knots.

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GENERAL INFORMATION

TAS

— True Airspeed is the airspeed of an airplane relative to undisturbed air, which is the CAS corrected for altitude, temperature and compressibility.

Va

— Maneuvering Speed is the maximum speed at which the abrupt

application of full available aerodynamic control will not over-stress the airplane.

Vfe

— Maximum Flap Extended Speed is the highest speed permissible

with wing flaps in a prescribed extended position.

Vne

— Never Exceed Speed is the speed limit that may not be exceeded at any time.

Vno

— Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution.

Vs

— Stalling Speed or the minimum steady flight speed at which the

airplane can maintain altitude.

Vso

— Stalling Speed or the minimum steady flight speed in the landing

configuration (i.e., full flaps).

Vx

— Best Angle-of-Climb Speed is the airspeed that delivers the

greatest gain of altitude in the shortest possible horizontal distance.

Vy

— Best Rate-of-Climb Speed is the airspeed that delivers the

greatest gain in altitude in the shortest possible time.

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SECTION 2

L

IMITATIONS

Table of Contents

Subject: Page:

2-1 AIRSPEED LIMITATIONS ............................................................3

2-2 AIRSPEED INDICATOR MARKINGS...........................................4

2-3 CONTROL SURFACE TRAVEL LIMITS .......................................4

2-4 POWERPLANT LIMITATIONS .....................................................5

2-4.1 S 2-4.2 O 2-4.3 O 2-4.4 F

2-4.5 CYLINDER HEAD TEMPERATURE ..........................................7

2-4.6 ENGINE CRANKSHAFT SPEED ..............................................8

2-5 VACUUM PRESSURE ..................................................................9

2-6 WEIGHT LIMITS...........................................................................9

UPPORTED ENGINES .........................................................5

IL PRESSURE ...................................................................6

IL TEMPERATURE .............................................................6

UEL PRESSURE .................................................................7

2-7 CENTER OF GRAVITY LIMITS ....................................................9

2-8 FLIGHT LOAD FACTORS.......................................................... 10

2-9 AEROBATIC MANEUVER LIMITATIONS................................. 10

2-10 INTENTIONAL SPINS ............................................................... 10

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2-11 FLIGHT IN ICING CONDITIONS ..............................................11

2-12 FLIGHT IN THE VICINITY OF THUNDERSTORMS .................11

2-13 REQUIRED EQUIPMENT .......................................................... 12

2-14 PLACARDS.................................................................................12

2-14.1 P

2-14.2 FUEL FILLER CAP PLACARDS ............................................ 13

2-14.3 BAGGAGE COMPARTMENT PLACARDS ...............................13

2-14.4 FUEL VALVE MARKINGS ...................................................13

LACARDS, MARKINGS REQUIRED BY FAR........................12

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LIMITATIONS

2-1 AIRSPEED LIMITATIONS

Vfe = 90 kts./103m.p.h. (maximum flap extended speed)

Do not extend flaps or operate with flaps extended above this

speed. If Vfe is inadvertently exceeded with the flaps extended, slow the aircraft to an airspeed below Vfe before retracting the flaps.

Va = 101 kts./116 m.p.h. (maneuvering speed) Do not make full or abrupt control movements above this speed.

Vno = 140 kts./161 m.p.h. (maximum structural cruising speed) Do not exceed this speed except in smooth air and then only

with caution.

Vne = 162 kts./186 m.p.h. (never exceed speed) Do not exceed this speed in any operation

NOTE

Definitions of these airspeeds are given in FAR Part 1, Paragraph 1.2. All airspeeds are calibrated airspeeds (CAS). During flight test, the airspeed indicator should be calibrated so as to distinguish indicated airspeeds (IAS) from CAS.

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2-2 AIRSPEED INDICATOR MARKINGS

*WHITE ARC ...............................................42–90 kts./48–103 m.p.h.

(full flap operating range)

*GREEN ARC............................................ 49–144 kts./56–166 m.p.h.

(normal operating range)

YELLOW ARC.......................................144–162 kts./166–186 m.p.h.

(operate with caution; only in smooth air)

RED LINE.................................................................162 kts./186 m.p.h.

(maximum speed for all operations)

* Indicated gross weight stall speed with flaps for the white arc and

indicated clean stall speed for the green arc are derived from tests of the Glasair Aviation Sportsman prototype. Slight variations may be experienced in customer-built aircraft. Actual stall speeds should be determined from flight test of each individual aircraft, and the airspeed indicator markings should be adjusted appropriately.

2-3 CONTROL SURFACE TRAVEL LIMITS

Elevator Travel........................................... 23° up and 20° down (±1°)

Rudder Travel .....................................................25° left and right (±1°)

Aileron Travel ........................ 22.5° (±2.5°) up and 17.5° down (±1°)

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LIMITATIONS

2-4 POWERPLANT LIMITATIONS

2-4.1 SUPPORTED ENGINES

Engines supported by Glasair Aviation for the Sportsman are:

1. Lycoming O-360-A1A, -A1F6 or -A4M engines.

Other engines may be installed on the Sportsman, but the above listed engines are the only ones that have been tested by Glasair Aviation and the only ones for which Glasair Aviation supplies propellers, engine mounts, cowlings and other firewall-forward accessories and installations.

NOTE

For new engines and engines returned to service following cylinder replacement or top overhaul of one or more cylinders, cruising should be done at not less than 65% to 75% power until a total of 50 hours has accumulated or oil consumption has stabilized. This is to insure proper seating of the piston rings. Use straight mineral oil for the 50 hour break-in period. See Section 8-2 in “SECTION 8: FLIGHT TEST” for a further discussion of this subject.

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NOTE

In the event of any discrepancy between the limitations given in this manual and those given in the engine manufacturer’s operating manual, the latter shall be observed. The pilot should be thoroughly familiar with the engine operating manual, which may contain additional limitations not discussed below.

2-4.2 OIL PRESSURE

Lycoming O-360:

Normal Operating.................................................................... 60–90 p.s.i.

Idling................................................................................................25 p.s.i

Start and Warm-up Maximum (red line) ..................................... 100 p.s.i.

Green Arc ................................................................................ 60–90 p.s.i.

2-4.3 OIL TEMPERATURE

Lycoming O-360:

Recommended .......................................................................82°C/180°F

Maximum (red line)..............................................................118°C/245°F

Green Arc ....................................................... 60°–104°C/140°–220°F

Yellow Arc .........................................................38°–60°C/100°–140°F

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LIMITATIONS

2-4.4 FUEL PRESSURE

Lycoming O-360 (at inlet to carburetor):

Maximum ..........................................................................................8.0 p.s.i.

Recommended..................................................................................3.0 p.s.i.

Minimum...........................................................................................0.5 p.s.i.

2-4.5 C

YLINDER HEAD TEMPERATURE

Lycoming O-360:

Maximum (red line) .............................................................260°C/500°F

Normal Operating (green arc)........................66°–204°C/150°–400°F

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2-4.6 ENGINE CRANKSHAFT SPEED

Lycoming O-360:

Maximum (red line)................................................................. 2,700 r.p.m.

Normal Operating (green arc) .......................................600–2,700 r.p.m.

NOTE

The Lycoming O-360-A1A has a restriction against continuous operation between 1,900 and 2,200 (± 50) r.p.m. when fitted with a Hartzell constant-speed propeller. This restricted range is inferred from similar engine/propeller combinations but can only be established definitively by a vibrational survey, which has not yet been conducted at this writing. The O-360- A1F6, on the other hand, has crankshaft counterweights that permit use of the Hartzell prop throughout the engine’s operating range without restriction. Both the

-A1A and the -A1F6 can also be used with a Sensenich fixedpitch propeller, but both engines have a restriction against continuous operation between 2,150 and 2,350 r.p.m. using the Sensenich prop. The O-360-A4M is a solid-crank engine that cannot be used with a constant-speed propeller, but has no r.p.m. restrictions for the Sensenich fixed-pitch propeller.

2-5 VACUUM PRESSURE

Operating Range .................................................................4.3–5.9 in. Hg

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LIMITATIONS

2-6 WEIGHT LIMITS

Maximum Gross Weight .............................................................. 2,350 lb.

Maximum Baggage Weight..............................................................300 lb.

W A R N I N G

The weight limit figures depend on the airplane being within safe center of gravity limits. Do not fly the airplane if its flight CG falls outside of the published limits. Variables such as fuel, passenger and baggage weights will affect the CG location. Before each flight, calculate the CG to determine whether the aircraft is within safe CG limits.

2-7 CENTER OF GRAVITY LIMITS

Forward Limit...........................................................................Station 95.6

Aft Limit..................................................................................Station 103.5

The reference datum is 58.0 in. forward of the cowling attach flange joggle. Stations are measured in inches from the datum. See “SECTION 5: WEIGHT AND BALANCE” for further information.

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2-8 FLIGHT LOAD FACTORS

At the 2,350 lb. gross weight, the G limits are:

Positive........................................................................................3.8 Gs

Negative...................................................................................... 1.5 Gs

2-9 AEROBATIC MANEUVER LIMITATIONS

The Sportsman is a standard-category aircraft. Aerobatic maneuvers are prohibited in the Sportsman. Maneuvers required for pilot certification, such as stalls, steep turns, lazy eights and chandelles, can be performed in the Sportsman, however. Do not attempt any maneuver that could impose high loads on the airframe. In performing any maneuver, avoid excessive airspeed or abrupt control movements that could result in excessive loads.

2-10 INTENTIONAL SPINS

Due to many variables that affect spin recovery and our lack of control over these variables, Glasair Aviation prohibits intentional spins in the Sportsman. Some of the variables are: pilot technique, the manner in which the spin is entered, slight differences in wing and horizontal stabilizer incidence angles, center of gravity location, number of turns into the spin, spin direction, aileron position, power carried and control rigging and adjustment.

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Glasair Sportsman GS-2 Owner's Manual

Specifications and Main Features

Frequently Asked Questions

User Manual