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PILOT´S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the Gavilan 358 Pilot’s Operating Handbook, El Gavilan Report 1208

REV No. Revised Pages Description of Revision Approval Signature

New First issue Rev. 1 ALL The following changes were made:

Spelling and presentation format checked. In Title Page P/N added, UAEAC approved signature added. Effective Pages Format changed to indicate effectivity of each page.

In Section 1. General: Added on footer “Rev 1” In page 1-4 Three View Added Approved Propeller Models added in page 1-7.

In Section 2. Limitations: Added on footer “Rev 1” In Page 2-2 VFE updated in conformity to TIR Report 1240-120. In Page 2-4 Propeller Models Added In Page 2-4 propeller caution note changed to: “Do NOT Operate above 38 inches of manifold pressure when propeller is between 2200 and 2400 RPM, if you are using a propeller with blades model F8468A” In Pages 2-10 through 2-13 frames added to placards.

In Section 3. Emergency Procedures: In Footer “Rev. 1” added Paragraph Nos. Revised

In Section 4. Normal Procedures: Frames added to Cautions and Warning Notes. Paragraph 4.3 Normal Procedures Checklist – Preflight Check revised in following pages: 4-16, 4-18, 4-19, 4-22, 4-23, 4-24, 4-25, 4-26, 4-27.

In Section 5. Performance: In Footer “Rev. 1” Added Tables 5-9, 5-14, 5-15 & 5-16 added.

In Section 6. Weight and Balance: In Footer added “Rev. 1” Paragraphs 6.6 to 6.11 added Figures 6.4 to 6.11 added

In Section 7. Aircraft and Systems Descriptions: In footer “Rev. 1” Added Spelling and Paragraph Nos. revised

EL GAVILAN S.A.

PILOT´S OPERATING HANDBOOK TABLE OF CONTENTS. SECTION

General 1

Limitations 2

Emergency Procedures 3

Normal Procedures 4

Performance 5

Weight and Balance 6

Aircraft and Systems 7

(Reserved)

8

Supplements 9

Report 1208 Page 1-3

EL GAVILAN S.A. Bogota Colombia

Model EL-1C

REVISED: Dec. 07, 2000 Rev. No. 1

PILOT´S OPERATING HANDBOOK

EL GAVILAN S.A.

GAVILAN 358 (MODEL EL-1C) Serial Number: Registration Number:

El Gavilán Report 1208 P/N G1208-002

This is an UAEAC required Airplane Flight Manual (AFM)

UAEAC Approved:

El Gavilán S.A. Bogotá, Colombia

ISSUED: February 16, 1998 REVISED: DEC. 07, 2000



Model EL-1C


SECTION 1

GENERAL Table of Contents

Para. Title Page

1.1 Introduction 2

1.2 Warnings, Cautions and Notes 3

1.3 General Data 6

1.4 Engine 6

1.5 Propeller 7

1.6 Fuel 7

1.7 Oil 8

1.8 Maximum Weights 9

1.9 Standard Airplane Weight 9

1.10 Specific Loading 9

1.11 Cabin and Entry Dimensions (Inches) 9

1.12 Baggage Space and Entry Dimensions 10

1.13 Cargo Space and Entry Dimensions 10

1.14 Symbols, Abbreviations and Terminology

11

Figures Page 1-1 EL-1C Three View 4

1-2 Turning Clearances 5



Model EL-1C


SECTION 1

GENERAL

1.1 INTRODUCTION This Pilot’s Operating Handbook presents operational information to the pilot that is clear, concise and provides all information required by the Colombian Aeronautical Regulations (R.A.C.) plus additional information found appropriate by the manufacturer. This manual is the U.A.E.A.C. Approved Pilot’s Operating Handbook required to be supplied with, and carried in, each Gavilan Model EL-1C airplane by R.A.C. and contains all information required by R.A.C. section 9.1.5. This handbook is not designed as, and its purpose is not intended to be, a flight instruction manual. It is not a substitute for adequate, competent flight training, knowledge of current Airworthiness Directives affecting the airplane or applicable aviation regulations. The manufacturer will occasionally supply revisions to this manual. The airplane may not be legally operated unless the manual is maintained in a current status by the insertion of revisions as periodically furnished by, and in accordance with, instructions supplied by the manufacturer. Assurance that the airplane is in an airworthy condition is the responsibility of the owner. The pilot in command is responsible for determining that the airplane is safe for flight. He is also responsible to see that all operations are conducted within the limitations defined by instrument markings, placards and those set forth in this manual. This manual is arranged to enhance its use in flight. However, it is not to be used solely as an occasional operating reference. The pilot must study this entire manua l and be familiar with all limitations, performance, procedures and operational handling characteristics of the airplane prior to flight. The information in this manual is divided into numbered (Arabic) sections, each of which is provided with a tab divider for quick reference to the desired section. LIMITATIONS, EMERGENCY and ABNORMAL PROCEDURES SECTIONS have been located ahead of NORMAL and PERFORMANCE SECTIONS and other sections so as to provide easier access to information that may be needed quickly in flight. Additionally, the EMERGENCY PROCEDURES SECTION is further identified with a RED divider tab to present instant reference to the section. Provisions for expansions have been made by the deliberate omission of certain paragraph numbers, figure numbers, item numbers and pages noted as being intentionally left blank.



Model EL-1C


1.2 WARNINGS, CAUTIONS AND NOTES

WARNINGS, CAUTIONS and NOTES are used to emphasize critical and important information, and are used as defined below:

WARNING

AN OPERATING PROCEDURE, PRACTICE OR A CONDITION WHICH, IF NOT CORRECTLY FOLLOWED OR CORRECTED, COULD RESULT IN SERIOUS PERSONAL INJURY OR LOSS OF LIFE.

Report 1208EL GAVILAN S.A. Bogota Colombia

Model EL


CAUTION

An operating procedure, practice or a condition which, if not strictly observed or corrected, could result in destruction of, or damage to equipment.

NOTE

An operating procedure, practice or condition which is important to emphasize.

EL GAVILAN S.A. Report 1208 Page 2-8 Bogota Colombia Model EL-1C




GAVILAN EL-1C THREE VIEW Figure 1-1



TURNING CLEARANCES Figure 1-2



1.3 GENERAL DATA

a. Wing Span (Feet) 42.0 b. Chord (Inches) 62.0 c. Wing Area (Square Feet) 206.6 d. Wing Loading (Pounds per square foot 21.8 e. Airfoil Section NACA 4412 f. Dihedral 1.5 degrees g. Twist (Geometric) 2.5 degrees h. Aspect Ratio 7.7 i. Aileron Area (Square Feet) 19.6 j. Flap Area (Square Feet) 24.0 k. Horizontal Tail Surface Span (Feet) 15.3 l. Horizontal Tail Surface Area (Square Feet) 50.6 m. Horizontal Tail Airfoil Section NACA 0012 n. Vertical Tail Surface Area (Square Feet) 25.5 o. Vertical Tail Airfoil Section NACA 0012

1.4 ENGINE

a. Manufacturer Textron L ycoming b. Model Number TIO540-W2A c. Rated Power (Horsepower) 350 d. Rated Speed (RPM) 2600 e. Maximum Manifold Pressure (In. Hg.) 50.6 f. Bore (Inches) 5.1 g. Stroke (Inches) 4.4 h. Displacement (Cubic Inches) 541.5 i. Compression Ratio 7.3:1 j. Weight (Pounds, dry) 567 k. Type Six Cylinder, Direct Drive, Fuel

injected, Turbocharger, Horizontally Opposed, Air Cooled



1.5 PROPELLER El Gavilan 358, has been tested and approved with the following propeller models:

a. Manufacturer Hartzell b. Model HC-C3YR-IRF/F8468A c. Number of Blades 3 d. Diameter (Inches) 86” e. Type Constant Speed, Controllable Pitch

f. Manufacturer Hartzell g. Model HC-C3YR-IRF/F8468A-6R h. Number of Blades 3 i. Diameter (Inches) 80” j. Type Constant Speed, Controllable Pitch

k. Manufacturer Hartzell l. Model HC-C3YR-IRF/F8468A-2R m. Number of Blades 3 n. Diameter (Inches) 84” o. Type Constant Speed, Controllable Pitch

1.6 FUEL (AVIATION GASOLINE ONLY)

a. Fuel Capacity Maximum total (U.S. Gallons)

107

b. Useable Capacity (U.S. Gallons) 104 c. Minimum Aviation Grade 100(Green) or 100LL(Blue) d. Alternate Fuels: Refer to latest revision of Lycoming

Service Instruction1070. Alcohol is NOT approved for use in this airplane.

1.7 OIL

a. Oil Capacity (U.S. Quarts) 12 b. Oil Specification: Refer to latest revision of Lycoming Service



Instruction 1014 (Latest revision). c. Recommended Seasonal Oil

Grades

MIL-L-22851 AVERAGE AMBIENT ASHLESS DISPERSANT TEMPERATURE SAE GRADES

All Temperatures 15W-50 or 20W-50 Above 80 deg. F 60 Above 60 deg. F 40 or 50 30 to 90 deg. F 40 0 to 70 deg. F 30, 40 or 20W-40

Below 10 deg. F 30 or 20W-30

NOTE

When operating temperatures overlap indicated ranges, use the next lighter grade oil.



1.8 MAXIMUM WEIGHTS

a. Ramp Weight (Pounds) 4500 b. Takeoff Weight (Pounds) 4500 c. Landing Weight (Pounds) 4500 d. Useful Load (Pounds, Approximate) 1700 e. Baggage 200

(See Section 6 for actual Useful Load or Section 8 for passenger and cargo configurations)

1.9 STANDARD AIRPLANE WEIGHT

Standard Empty Weight (Pounds, Approximate) 2800 (See Section 6 for actual Empty Weight) 1.10 SPECIFIC LOADINGS

a. Wing Loading (Pounds per square foot) 21.8 b. Power Loading (Pounds per horsepower) 12.8

1.11 CABIN AND ENTRY DIMENSIONS

a. Cabin Width (Inches, inside) 53.5 b. Cabin Length (Inches, Instrument Panel to rear Bulkhead)

135.0

c. Cabin Height inside (Inches) 53.0 d. Cabin Entry: Height (Inches) 44.5 Width (Inches, Maximum) 24.0 e. Cockpit Entry (Pilot): Height (Inches) 48.0 Width (Inches, Maximum) 30.0 f. Cockpit Entry (Copilot/Emergency Exit): Height (Inches) 48.0 Width (Inches, Maximum) 30.0



1.12 BAGGAGE SPACE AND ENTRY DIMENSIONS

a. Baggage Compartment: Height (Inches) 50.3 Width (Inches) 53.5 Length (inches) 24.0 Floor Loading (Pounds per Square Foot) 50.0

b. Baggage Compartment Entry: Height (Inches) 44.5 Length (Inches, Maximum) 24.0

1.13 CARGO SPACE AND ENTRY DIMENSIONS (Cabin Seats Removed)

a. Cargo Compartment: Height (Inches) 53.0 Width (inches) 53.5 Length (Inches) 102.0 Floor Loading (Pounds per Square Foot)

50.0

b. Cargo Compartment Entry (Both doors open) Height (Inches) 44.5 Length (Inches) 48.0



1.14 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

The following definitions are for symbols, abbreviations and terminology used throughout this manual and others, which may be of added operational assistance to the pilot:

a. General Airspeed Terminology and Symbols

CAS Calibrated Airspeed - The indicated speed of an aircraft, corrected

for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere a t sea level.

GS Ground Speed - The speed of an aircraft relative to the ground.

IAS Indicated Airspeed - The speed of an aircraft as shown on the airspeed indicator when corrected for instrument error. IAS values published in this manual assume zero instrument error.

KCAS Calibrated Airspeed (In Knots).

KIAS Indicated Airspeed (In knots).

KTAS True Airspeed in knots.

TAS True Airspeed - The speed of an aircraft relative to undisturbed air, which is CAS, corrected for altitude and temperature.

Vfe

Maximum Flap Extended Speed - (The maximum speed allowable with the wing flaps in a prescribed position).

Vne

Never Exceed Speed - The speed that may not be exceeded at any time.

Vno

Maximum Structural Cruising Speed – The speed that should not be exceeded except in smooth air, and then, only with caution.

Vo

Operating Maneuvering Speed - The maximum speed at which application of full available aerodynamic control will not overstress the airplane.

Vs Stalling Speed or Minimum Steady Flight Speed - The minimum speed at which the airplane is controllable.



1.14 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Cont.)

Vso Stalling Speed or Minimum Steady Flight Speed - The minimum speed at which the airplane is controllable in the landing configuration at maximum gross weight.

VX Best Angle of Climb Speed – The speed at which the greatest gain of altitude is obtained in the shortest possible horizontal distance.

VY Best Rate of Climb Speed – The speed at which the greatest gain of altitude is obtained in the shortest possible time.

b. Meteorological Terminology

IND. PRESS. ALT.

Indicated Pressure Altitude – The number actually read from an altimeter when the barometric sub-scale has been set to 1013.2 mb (29.92 in. Hg.).

ISA International Standard Atmosphere – Atmosphere in which: (1) The air is a dry perfect gas; (2) The temperature at sea level is 15 deg. C (59 deg. F); (3) The atmospheric pressure at sea level is 1013.2 mb (29.92 in. Hg); (4) The temperature gradient from sea level to the altitude at which the temperature is -56.5 deg. C (-69.7 deg. F) is -0.00198 deg. C(-0.003564 deg. F.) per foot and zero gradient above that altitude.

OAT Outside Air Temperature – Free air static temperature obtained

from in-flight temperature indications or ground meteorological sources.

PRESS. ALT.

Pressure Altitude - The altitude measured from standard sea level pressure, 1013.2 mb (29.92 in. Hg) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. In this manual, altimeter instrument errors are assumed to be zero.

STA. PRESS.

Station Pressure - Actual atmospheric pressure at a field elevation.




WIND The wind velocities recorded, as variables on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds.

c. Power Terminology

MAXIMUM CLIMB POWER

Maximum power permissible during climb.

MAXIMUM CRUISE POWER

Maximum power permissible during cruise.

M.C.P. Maximum Continuous Power – Maximum power permissible continuously during flight.

TAKEOFF POWER

Maximum power permissible for takeoff.

d. Engine Instruments

CHT Cylinder Head Temperature.

EGT/TIT Exhaust Gas Temperature/Turbine Inlet Temperature.

MP Manifold Pressure.

e. Airplane Performance and Flight Planning

BALKED LANDING

An aborted landing in which takeoff power is applied with the flaps in the landing configuration.

CLIMB GRADIENT

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

DEMON- STRATED CROSSWIND VELOCITY

The velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was demonstrated during certification flight tests.




f. Weight and Balance Terminology

ARM The horizontal distance along the airplane fuselage from the Ref. Datum to the Sta., or Center of Gravity (CG), of an item.

BASIC EMPTY WEIGHT

Standard Empty Weight plus optional equipment.

C.G. Center of Gravity - The point at which an airplane would balance if suspended. Its distance from the Ref. Datum is found by dividing the total moment by the total weight of the airplane.

C.G. ARM The Arm obtained by adding the airplane's individual moments and dividing the sum by the total weight

C.G. LIMITS The extreme center of gravity locations within which the airplane must be operated at a given weight.

MAX. LANDING WEIGHT

Maximum weight approved for the landing touchdown.

MAX. RAMP WEIGHT

Maximum weight approved for operating and maneuvering on the ground (It includes the weight of fuel for starting, taxiing and run-up).

MAX. TAKEOFF WEIGHT

Maximum weight approved for the start of the takeoff run.

MAX. ZERO FUEL WEIGHT

Maximum Weight exclusive of Usable Fuel.

MOMENT The product of the weight of an item multiplied by its arm. (Moment divided by a constant is used to simplify balance calculations by reducing the number of digits).

PAYLOAD Weight of occupants, cargo and/or baggage.



1.14. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Cont.)

REF. DATUM An imaginary vertical plane from which all distances are measured for balance calculation purposes.

STA. Station - A location along the airplane fuselage usually given in terms of distance from the Ref. Datum.

STANDARD EMPTY WEIGHT

Weight of a standard airplane including Unusable Fuel, full operating fluids and full oil

UNUSABLE FUEL

Fuel remaining after U.A.E.A.C. fuel run out tests has been conducted. Unusable Fuel cannot be safely used in flight and must never be included in range or endurance computations.

USABLE FUEL

Fuel available for flight planning purposes.

USEFUL LOAD

Difference between Maximum Takeoff Weight, or Maximum Ramp Weight if applicable, and Basic Weight.

g. Miscellaneous Terminology

RAC

Colombian Aeronautical Regulations

UAEAC Unidad Administrativa Especial de Aeronáutica Civil



SECTION 2 LIMITATIONS

Table of Contents

Para. Title

Page

2.1 General

2

2.2

Airspeed Limitations and Airspeed Instrument Markings

2

2.3 Power Plant Limitations and Power Plant Instrument Markings

3

2.4 Weight Limits

7

2.5 Center of Gravity Limits

7

2.6 Flight Load Limit

7

2.7 Flight Load Factor Limits

8

.2.8 Kinds of Operations Limits

8

2.9 Kinds of Operation Equipment List

8

2.10 Maximum Operating Altitude Limit

9

2.11 Maximum Passenger Seating Limits

9

2.12 Allowed Lateral Fuel Loading Limits

9

2.13 Other Limitations

10

2.14. Placards

10



SECTION 2

LIMITATIONS

2.1 GENERAL

This section provides the U.A.E.A.C. approved operating limitations, instrument markings, color-coding and basic placards necessary for operation of the airplane and its systems.

This airplane must be operated in compliance with the operating limitations stated in this section of the U.A.E.A.C. approved Pilot’s Operating Handbook.

Limitations associated with optional systems and equipment requiring Operating Handbook supplements will be provided separately, according to the configuration supplied by the manufacturer.

2.2 AIRSPEED LIMITATIONS AND AIRSPEED INSTRUMENT MARKINGS



Model EL-1C

REVISED: Dec 07,2000 Rev. No. 1

NOTE

Airspeeds listed in this manual are expressed in KIAS. Assume zero

instrument error unless otherwise noted.

SPEED KIAS

Never Exceed Speed (Vne) (Do not exceed this speed in any operation).

155

Operating Maneuvering Speed (Vo) (Do not make full or abrupt control movements above this speed).

123

Maximum Structural Cruising Speed (Vno) (Do not exceed this speed except in smooth air and then only with caution).

123

Maximum Flaps Extended Speed (Flaps – 15 Deg)

107

Maximum Flaps Extended Speed (Flaps – 30 Deg)

107

Maximum Flaps Extended Speed (VFE) (Do not exceed this speed with full flaps)

107



Model EL-1C


2.2 AIRSPEED LIMITATIONS AND AIRSPEED INSTRUMENT MARKINGS (Cont.)

CAUTION The "Operating Maneuvering Speed" presented above (123 KIAS)

is the maximum speed which is appropriate to the airplane at maximum gross weight. Do not exceed Operating Maneuvering Speed while operating in rough air.

AIRSPEED INDICATOR MARKINGS

Red Radial Line

155 KIAS

Yellow Arc

123 to 155 KIAS

Green Arc

63 to 123 KIAS

White Arc

58 to 107 KIAS

2.3 POWER PLANT LIMITATIONS AND POWER PLANT INSTRUMENT

MARKINGS Power Plant Limitations

Engine Manufacturer

Textron Lycoming

Engine Model Number TIO-540-W2A

Engine Operating Limits:

Maximum Continuous Power 350 BHP Rating

Maximum Engine Speed 2600 RPM

Maximum Manifold Pressure

50.6 Inches Hg.

Maximum Cyl. Head Temp 450 Degrees F

Maximum Oil Temp 245 Degrees F



Model EL-1C


2.3 POWER PLANT LIMITATIONS AND POWER PLANT INSTRUMENT MARKINGS (Cont.)

Oil Pressure

Minimum 25 PSI

Maximum 115 PSI

Fuel Pressure Maximum 65 PSI

Exhaust Gas temp.

1650 Degrees F

Propeller:

Propeller Manufacturer

Hartzell

Propeller Model(s) Number:

HC-C3YR-1RF/F8468A-6R Propeller Diameter: Maximum 80”

No Cut Off Allowed

HC-C3YR-1RF/F8468A-2R Propeller Diameter: Maximum 84”

Minimum 78”

HC-C3YR-1RF/F8468A Propeller Diameter: Maximum 86”

Minimum 85” Propeller Blade Angle at 30 inch station:

Low

12.4 Degrees

High

34.0 Degrees

CAUTION

“Do NOT operate the engine above 38 inches of manifold pressure when propeller is between 2200 and 2400 RPM, if you are using a propeller with blades model F8468A”

This is valid only for blades F8468A. 2.3 POWER PLANT LIMITATIONS AND POWER PLANT INSTRUMENT

MARKINGS (cont.)



Model EL-1C


Fuel:

Fuel Cap. Maximum total (U.S. Gallons)

107

Usable Capacity (U.S. Gallons) 104 Minimum Aviation Grade 100 (Green) or 100LL (Blue)

Alternate Fuels Refer to latest revision of Lycoming

Service Instruction1070. Alcohol is NOT approved for use in this airplane.

Oil:

Oil Capacity (U.S. Quarts) 12

Oil Specification Refer to latest revision of Lycoming Service Instruction1014. (Latest revision)

Recommended Seasonal Oil Grades:

AVERAGE AMBIENT TEMPERATURE

MIL-L-22851 ASHLESS DISPERSANT

SAE GRADES

All Temperatures SAE15W50 or SAE20W50

Above 80 deg. F SAE60

Above 60 deg. F SAE40 or SAE50

30 to 90 deg. F SAE40

0 to 70 deg. F SAE30, 40 or SAE20W40

0 to 90 deg. F SAE20W50 or SAE15W50

Below 10 deg. F SAE30 or SAE20W30

NOTE

When operating temperatures overlap indicated ranges, use the next lighter grade oil.

2.3 POWER PLANT LIMITATIONS AND POWER PLANT INSTRUMENT MARKINGS (cont.) Power Plant Instrument Markings:



Model EL-1C


Red Line Maximum and/or Minimum Yellow Arc Caution Range Green Arc Normal Operating Range a.)Tachometer:

Radial Red Line 2600 RPM Green Arc 500 - 2600 RPM b.)Manifold Pressure (MP):

Red Radial Line 50.6 In-Hg c.)Cylinder Head Temperature (CHT):

Radial Red Line

450 Deg F

Green Arc 250 - 400 Deg F Yellow Arc 400 - 450 Deg F

d.)Exhaust Gas Temperature (EGT)/(TIT): Radial Red Line

1650 Deg F

Green Arc 1200 to 1650 Deg F e.)Oil Temperature:

Radial Red Line 245 Deg F Yellow Arc 220 - 245 Deg F Green Arc 100 - 220 Deg F

f.)Oil Pressure:

Radial Red Line 115 PSI Yellow Arc 25 - 55 PSI Green Arc

55 - 95 PSI

g.)Fuel Pressure:

Radial Red Line 65 PSI

Green Arc 30 - 65 PSI



Model EL-1C


2.4 WEIGHT LIMITS

Maximum Ramp Weight

4500 Lbs.

Maximum Takeoff Weight

4500 Lbs.

Maximum Landing Weight 4500 Lbs. 2.5 CENTER OF GRAVITY LIMITS (Inches aft of datum)

Forward (At 4500 Lbs.)

120

(At 3350 Lbs. or less)

112

Rearward (At all weights) 126

NOTE

Straight line variation between points given. The datum is 105.80 inches ahead of the wing leading edge.

NOTE

The pilot in command is responsible for ascertaining that the airplane is properly loaded prior to conducting flight operations. Approved loading instructions are contained in Section 6 (Weight and Balance) and paragraphs 6.6 through 6.7 (Airplane Configurations and General Loading Recommendations) of this AFM.

WARNING

OPERATION BEYOND THE MANEUVERING AND LOAD LIMITS OF THE AIRCRAFT MAY RESULT IN COMPLETE STRUCTURAL FAILURE OF ONE OR MORE COMPONENTS.

2.6 MANEUVERING LIMITS This airplane is certificated in the normal category.

a. No acrobatic maneuvers, including spins, approved. b. Bank limits are 60 degrees and pitch limits are 30 degrees above and below

the horizon.



Model EL-1C


2.7 FLIGHT LOAD FACTOR LIMITS

c. Maximum Positive Load Factor 3.8 G. d. Maximum Negative Load Factor 1.52 G. e. Maximum Positive Load Factor with Flaps Extended 2.0 G.

2.8 KINDS OF OPERATIONS LIMITS

This airplane is approved for day, VFR flight only. Intentional flight into known icing conditions is prohibited.

NOTE

Intentional flight into known moderate turbulence, or into, or in the vicinity of

towering cumuliform clouds is NOT recommended. Severe turbulence can

cause high vertical gust velocities (positive and negative) with resultant high

rates of airplane climb and sink.

Turbulence can cause difficulty in maintaining airplane control.

Hazardous hail, lightning and icing conditions can be present in, and in the vicinity of,

cumuliform clouds.

2.9 KINDS OF OPERATION EQUIPMENT LIST

This airplane may be operated in day, VFR conditions when equipment appropriate to the intended flight is installed and operable.

The following equipment list identifies the systems and equipment upon which approval for

each kind of operation is predicated. This equipment must be installed and operable for the

kinds of operation indicated.

The following list summarizes the equipment required by R.A.C. section 9.5.6.5 (FAR 23) for airworthiness for the particular kind of operation. Those minimum items of equipment necessary under the operating rules are defined in R.A.C. Part 4 (IV) as applicable.



Model EL-1C


2.9 KINDS OF OPERATION EQUIPMENT LIST (Cont.).

INSTRUMENT, SYSTEM, or EQUIPMENT

KINDS OF OPERATION DAY VMC

Airspeed indicator 1 Alternate engine induction air system 1 Alternator 1 Altimeter 1 Ammeter 1 Anti-collision light 2 Approved Airplane Flight Manual 1 Auxiliary Electric Pump 1 Battery 1 Fire extinguisher 1 Circuit breakers A/R Pitot-static system 1 Safety restraint system (each occupant) A/R Trim indicator (elevator) 1 Trim indicator (rudder) 1 Trim system (elevator) 1 Stall warning system. 1 Compass, magnetic 1 Cylinder head temperature gage 1 Turbine inlet temperature gage (EGT) 1 Tachometer 1 Manifold pressure gage 1 Fuel flow indicator 1 Fuel pressure indicator 1 Fuel quantity-indicating system 1 Oil pressure gage 1 Oil temperature gage 1

2.10 MAXIMUM OPERATING ALTITUDE LIMIT

According to dispositions of RAC, fight over 10,000 feet is not approved without oxigen equipment.

2.11 MAXIMUM PASSENGER SEATING LIMITS

The maximum number of passengers approved is seven (7). Refer to Section 7 (Airplane Configurations and General Loading Recommendations).

2.12 ALLOWABLE LATERAL FUEL LOAD LIMITS The maximum lateral fuel unbalance permitted is 1/4 tank.



Model EL-1C


2.13 OTHER LIMITATIONS Flap Limitation

Approved takeoff range 0 to 15 Degrees Approved landing range: 0 to 40 Degrees

2.14 PLACARDS The following placards are required for Gavilan EL-1C

On instrument panel:

NO SMOKING Near the magnetic compass:

A calibration card giving the accuracy of the compass in

30 degree increments

Near the manifold pressure gage: (For aircraft with propeller diameter between 86 to 85 inches only)

DO NOT OPERATE ABOVE 38” MANIFOLD PRESSURE

BETWEEN 2200 AND 2400 RPM. Near the fuel selector:

BOTH USABLE FUEL 104 U.S. GAL.

LIFT AND LIFT AND ROTATE ROTATE POINTER TO POINTER TO DESIRED DETENT DESIRED DETENT LEFT RIGHT USABLE FUEL USABLE FUEL 52 U.S. GAL. 52 U.S. GAL LEVEL FLIGHT LEVEL FLIGHT ONLY ONLY LIFT POINTER LIFT POINTER OVER GATE TO OVER GATE TO PLACE IN OFF PLACE IN OFF POSITION POSITION

OFF



Model EL-1C


2.14 PLACARDS (cont.) In the cargo area:

MAX. WEIGHT 1200 LBS. MAX. FLOOR LOADING 50 LBS.

SEE POH FOR CARGO LOADING INFORMATION At each fuel filler cap:

AV GAS ONLY 100 OR 100LL

CAPACITY 52 U.S. GAL. At the oil filler:

OIL SPECIFICATION Average Ambient Temp. MIL-L-22851

Spec. Ashless Dispersant Grades All Temps. SAE15W50 or SAE20W50 Above 80 Deg. F SAE60 Above 60 Deg. F SAE40 or SAE50 30 Deg. F to 90 Deg. F SAE40 0 Deg. F to 70 Deg. F SAE30, SAE40 or SAE20W40 0 Deg. F to 90 Deg. F SAE20W50 or SAE15W50 Below 10 Deg. F SAE30 or SAE20W30

Capacity - 12 U.S. Quarts At emergency exit controls (rear doors) in red:

EMERGENCY EXIT PUSH RELEASE BUTTON ON FWD DOOR ROTATE FWD DOOR LATCH UPWARD PUSH FWD DOOR OPEN AS FAR AS POSSIBLE ROTATE AFT LATCH UPWARD FORCIBLY PUSH AFT DOOR OPEN

At external power connection:

EXTERNAL

POWER 28 VDC



Model EL-1C


2.14 PLACARDS (cont.) In clear view of the pilot:

OPERATING LIMITATIONS

THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN OPERATING LIMITATIONS THAT MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE NORMAL CATEGORY. OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THIS CATEGORY ARE CONTAINED IN THE PILOT’S OPERATING HANDBOOK AND U.A.E.A.C. APPROVED AIRPLANE FLIGHT MANUAL.

NO ACROBATIC MANEUVERS, INCLUDING INTENTIONAL SPINS, APPROVED.

MAXIMUM OPERATING ALTITUDE 12500 FEET. FLIGHT INTO KNOW ICING CONDITIONS PROHIBITED. THIS AIRPLANE APPROVED FOR THE FOLLOWING FLIGHT OPERATIONS: DAY VFR On/near rear bulkhead access panel:

EMERGENCY LOCATOR

TRANSMITTER INSIDE

Near the airspeed indicator:

Vo 123 KIAS AT 4500 LBS Near the parking brake control:

WARNING NO BRAKING WILL OCCUR IF AIRCRAFT BRAKES ARE APPLIED WHILE

PARKING BRAKE HANDLE IS PULLED OR HELD

PARKING BRAKE

SET: DEPRESS PEDALS, PULL HANDLE FULLY AFT

RELEASE: DEPRESS PEDALS, PUSH HANDLE FULLY FORWARD



Model EL-1C


2.14 PLACARDS (cont.) At each forward door handle:

TO OPEN PUSH BUTTON

ROTATE HANDLE On each seat back and frame:

DO NOT PLACE OBJECTS UNDER SEAT

Near flap handle:

DO NOT LOWER FLAPS WITH CARGO

DOORS OPEN Near flap control:

DO NOT LOWER FLAPS WITH CARGO

DOORS OPEN Near/on flap handle:

FLAP POSITIONS NOTCH 1 - 15 NOTCH 2 - 30 NOTCH 3 - 40

At each static port:

STATIC PORT DO NOT OBSTRUCT

KEEP CLEAN Near each fuselage sump drain:

FUEL DRAINS At each fueling tab:

GROUNDING TAB



Model EL-1C


Section 3 EMERGENCY PROCEDURES

Table of Contents Para. Title Page 3.1 General

3

3.2 Emergency Procedures Checklist

5

3.2a Engine Fire During Start (3.4)

5

3.2b Engine Power Loss (Takeoff) (3.5)

5

3.2c Engine Power Loss (In Flight) (3.6)

6

3.2d Power Off Landing (3.7)

7

3.2e Fire In Flight (3.8)

8

3.2f Cockpit/Cabin Smoke/Fumes (3.9)

9

3.2g Loss of Oil Pressure (3.10)

10

3.2h High Oil Temperature (3.11)

10

3.2i High Cylinder Head Temperature (3.12)

10

3.2j Loss of Fuel Flow/Pressure (3.13)

11

3.2k Alternator Failure (3.14)

11

3.2l Propeller Overspeed (3.15)

12

3.2m Engine Roughness (3.16)

12

3.2n Inadvertent Stall/Spin (3.17)

13

3.2o Emergency Descent (3.18)

13

3.2p Inadvertent Icing Encounter (3.19)

14



Model EL-1C


Section 3 AMPLIFIED EMERGENCY PROCEDURES

Table of Contents

Para. Title

Page

3.3 Amplified Emergency Procedures – General

15

3.4 Engine Fire During Start (3.2a)

15

3.5 Engine Power Loss (TAKE-OFF) (3.2b)

15

3.6 Engine Power Loss (In Flight) (3.2c)

16

3.7 Power Off Landing (3.2d)

17

3.8 Fire In Flight (3.2e)

18

3.9 Cockpit/Cabin Smoke/Fumes (3.2f)

19

3.10 Loss Of Oil Pressure (3.2g)

19

3.11 High Oil Temperature (3.2h)

20

3.12 High Cylinder Head Temperature (3.2i)

20

3.13 Loss Of Fuel Flow/Pressure (3.2j)

21

3.14 Alternator Failure (3.2k)

21

3.15 Propeller Overspeed (3.2l)

22

3.16 Engine Roughness (3.2m)

23

3.17 Inadvertent Stall/Spin (3.2n)

23

3.18 Emergency Descent (3.2o)

24

3.19 Inadvertent Icing Encounter (3.2p)

25

Fig. 3-1 Power-Off Landing

26



Model EL-1C


EMERGENCY PROCEDURES 3.1 GENERAL

This section provides the recommended procedures for coping with various emergency or critical situations. All of the emergency procedures required by the U.A.E.A.C. as well as those necessary for operation of the airplane, as determined by the operating and design features of the airplane, are presented. This section consists of abbreviated emergency procedures checklists, each of which supplies an action sequence with little emphasis on the operation of systems.

Pilots must familiarize themselves with the procedures given in this section and must be prepared to take the appropriate action should an emergency situation arise. The procedures are offered as a course of action for coping with the particular situation or condition described. These procedures are not a substitute for sound judgement and common sense.

Most basic emergency procedures are a normal part of pilot training. The information

presented in this section is not intended to replace that training. This information is intended

to provide a source reference for the procedures, which are applicable to the Gavilan Model

EL-1C airplane. The pilot should review standard emergency procedures periodically to

remain proficient.

Emergency procedures associated with optional systems and equipment which require flight manual supplements are provided in Section 9 (Supplements).

The pilot must always remember and adhere to the following basic steps during an emergency:

1 In all emergencies: MAINTAIN AIRPLANE CONTROL (FLY THE AIRPLANE). 2. Analyze emergency: TAKE APPROPRIATE ACTIONS. 3. Land: SOON AS EMERGENCY REQUIRES OR CONDITIONS PERMIT.



Model EL-1C


3.1 GENERAL (Cont.) 4. Airspeed for Emergency Operations: Engine Failure After takeoff:

Wing Flaps Up 85 KIAS Wing Flaps Down 75 KIAS Operating Maneuvering Speed (4500 lbs.) 123 KIAS Recommended Glide Speed 80-85 KIAS

Landing Without Power: Wing Flaps Up 85 KIAS Wing Flaps Down 75 KIAS

LAND IMMEDIATELY MEANS:

Land at the nearest location where personal survival can be assured, regardless of airplane damage or loss.

LAND AS SOON AS POSSIBLE MEANS:

Land without delay at the nearest suitable landing area. The primary consideration of the landing site is survival of persons onboard the airplane. It is accepted that the nature of the emergency may require landing at an off-airport site.

NOTE

Critical emergency procedures checklists are shown with BOLD face and underlined titles. The aircrew must be familiar enough with these procedures to execute them immediately as the situation dictates. Reference within a checklist or amplified procedural discussion to a separate checklist that is required for completion of the sequence is indicated by UPPER CASE lettering.



Model EL-1C


3.2 EMERGENCY PROCEDURES CHECKLIST

3.2a ENGINE FIRE DURING START (3.4)

Starter ...................................................................................... ENGAGE Mixture ............................................................................ IDLE CUT-OFF Throttle .......................................................................................... OPEN Fuel Selector ..................................................................................... OFF Aircraft ................................................. ABANDON IF FIRE CONTINUES

3.2b ENGINE POWER LOSS [TAKEOFF] (3.5)

If sufficient runway remains for a normal landing, land straight ahead.

If insufficient runway remains and the area ahead is rough or has obstructions that must be cleared:

Airspeed ...................................................................................... 85 KIAS Mixture ............................................................................. IDLE CUT-OFF Fuel Selector ..................................................................................... OFF Master Switch .................................................................................... OFF Aircraft .................................................. STEER TO AVOID OBSTACLES

If sufficient altitude has been gained to attempt a restart:

Aircraft ...................................... MAINTAIN AIRSPEED AND CONTROL Fuel Selector .............................................. SELECT DIFFERENT TANK Mixture .................................................................................. FULL RICH Electric Fuel Pump.......................................................... ON 5 sec. – OFF Induction Air ........................................................................ ALTERNATE

NOTE

If propeller has stopped the starter may be engaged while accomplishing above checklist.



Model EL-1C


3.2b ENGINE POWER LOSS ?TAKEOFF? (3.5) (Cont.)

CAUTION

If normal engine operation and fuel flow are not re-established, the lack of fuel flow indication could indicate a leak in the fuel system. If a fuel system leak is veri fied, switch fuel selector to OFF.

If power is not regained:

Aircraft ..................................... PREPARE FOR POWER OFF LANDING

3.2c ENGINE POWER LOSS [IN FLIGHT] (3.6)

Airspeed .............................................................................80 to 85 KIAS Fuel Selector .............................................. SELECT DIFFERENT TANK Mixture .................................................................................. FULL RICH

(Above 5000 feet may require leaning for restart) Induction Air ........................................................................ ALTERNATE Engine Gauges .................................................... CHECK INDICATIONS

If power is restored:

Induction Air ............................................................................. PRIMARY Mixture ............................................................................ AS REQUIRED Aircraft ..... LAND AS SOON AS PRACTICAL AND DETERMINE CAUSE OF POWER LOSS

CAUTION

If normal engine operation and fuel flow are not re-established, the lack of a fuel flow indication could indicate a leak in the fuel system. If fuel system leak is verified, switch fuel selector to OFF.



Model EL-1C


3.2c ENGINE POWER LOSS [IN FLIGHT] (3.6) (Cont.)

NOTE

If propeller has stopped the starter may be engaged while accomplishing above check list.

If power is not restored:

Aircraft ..................................... PREPARE FOR POWER OFF LANDING

3.2d POWER OFF LANDING (3.7)

Propeller ............................................................ FULL DECREASE RPM Airspeed ..............................................................................80 to 85 KIAS Landing Area .............................................. LOCATE BEST AVAILABLE Passengers .................................................................................... BRIEF Loose equipment ....................................................................... SECURE Seat belts/shoulder harnesses ................................SECURE & TIGHTEN

If altitude and nature of engine failure permit, attempt air start. If start not achieved:

Throttle ...................................................................................... CLOSED Mixture ............................................................................. IDLE CUT-OFF Magneto Switches ............................................................................. OFF Fuel Selector ..................................................................................... OFF Transponder ...................................................................... EMERGENCY Radio ......................................................................TRANSMIT MAYDAY Approach .............................................. ESTABLISH SPIRAL PATTERN (See Figure 3-1, Power Off, Off Airport Landing) Flaps ............................................................................... AS REQUIRED Master Switch ................................................................................... OFF Touch-down Speed ............................................. SLOWEST POSSIBLE



Model EL-1C

REVISED: Dec. 07,2000 Rev. No. 1

3.2e FIRE IN FLIGHT (3.8)

Type of Fire (Electrical or Other) ........................................ DETERMINE

If electrical and source of fire is apparent:

Defective equipment ......................................................................... OFF Defective equipment circuit breakers .............................................. PULL

If fire persists or sources of fire is not apparent:

Master Switch ................................................................................... OFF Alternator Switch .............................................................................. OFF Fire Extinguisher(s) ................................................................ ACTIVATE

If fire is extinguished and avionics are required:

Circuit Breakers (All) ...................................................................... PULL Master Switch .................................................................................... ON Alternator Switch ................................................................................ ON Avionics Circuit Breakers (One at a time)...................................... RESET

(One at a time for necessary equipment) If fire recurs:

Offending Circuit Breaker ............................................................... PULL

If fire is extinguished:

Land AS SOON AS POSSIBLE and correct problem.

If cockpit/cabin fire and not electrical:

Fire Extinguisher(s) ................................................................. ACTIVATE Cockpit/Cabin Smoke and Fumes ......................................... EVACUATE

Land AS SOON AS POSSIBLE and correct problem.



Model EL-1C


3.2e FIRE IN FLIGHT (3.8)(cont.) If fire persists:

EMERGENCY DESCENT, LAND IMMEDIATELY AND ABANDON AIRPLANE

If engine fire:

Throttle ..................................................................................... CLOSED Mixture ............................................................................. IDLE CUT-OFF Fuel Selector ..................................................................................... OFF Magneto Switches ............................................................................. OFF Cabin Heat Control ............................................................................ OFF Cockpit/Cabin Smoke and Fumes ......................................... EVACUATE

Proceed with POWER OFF LANDING procedure (3.2d).

If fire persists:

EMERGENCY DESCENT, LAND IMMEDIATELY AND ABANDON AIRPLANE

WARNING

DO NOT ATTEMPT AN ENGINE RESTART AFTER ANY ENGINE COMPARTMENT FIRE

3.2f COCKPIT/CABIN SMOKE/FUMES (3.9)

Cockpit Heat ...................................................................................... OFF Cockpit/Cabin Vents ....................................................................... OPEN Speed ........................................................................................ REDUCE Pilot and Copilot Doors .........................................................AJAR-TRAIL

If smoke/fumes persist:

Oxygen Masks [If installed] ................................................................ ON Oxygen ............................................................................................... ON DO NOT USE OXYGEN IF FLAMES ARE PRESENT Smoke Goggles [If installed] .............................................................. ON Pilot and Copilot Doors ................................................................. CLOSE Radio .................................................................. ADVISE EMERGENCY Transponder .................................................. SET EMERGENCY CODE

Conduct EMERGENCY DESCENT and LAND AS SOON AS POSSIBLE.



Model EL-1C


3.2g LOSS OF OIL PRESSURE (3.10)

Land AS SOON AS POSSIBLE and investigate. Be prepared for possible POWER OFF, OFF AIRPORT LANDING.

3.2h HIGH OIL TEMPERATURE (3.11)

Power ........................................................................................ REDUCE (Reduce Manifold Pressure and RPM)

Mixture ............................................................................. RICHEN Airspeed ................................................................................. INCREASE

If climbing:

Rate of Climb .................................................. REDUCE OR LEVEL OFF

If high oil temperature persists or other indications of engine malfunction occur:

Land AS SOON AS POSSIBLE and determine cause of excess temperature. Be prepared for possible POWER OFF LANDING.

If temperature subsides:

Continue flight but monitor temperature closely.

3.2i HIGH CYLINDER HEAD TEMPERATURE (3.12)

Power ........................................................................................ REDUCE Mixture ........................................................................................ RICHEN Airspeed ................................................................................. INCREASE

(If possible)

If high temperature persists:

Land AS SOON AS POSSIBLE and determine cause of excess temperature. Be prepared for possible POWER OFF LANDING.



Model EL-1C


3.2j LOSS OF FUEL FLOW/PRESSURE (3.13)

Fuel Selector .............................................................. CHECK-ON-BOTH Fuel Boost Pump ................................................................................. ON

If power is restored:

Mixture ............................................................................. AS REQUIRED

3.2k ALTERNATOR FAILURE (3.14)

Alternator output failure is indicated by the "Alternator Fail" light in the annunciator panel

and/or by a negative ammeter indication. Output failure may be the result of a mechanical

failure of the alternator, by failure of the alternator drive belt or by a momentary over voltage

condition.

Alternator Switch ............................................................................... OFF Circuit Breakers .....................................................................CHECK – IN If alternator drive belt failure is NOT obvious and NO circuit breakers are out:

Alternator Switch ................................................................................. ON

If drive belt failure is obvious, circuit breakers are out or electrical power is NOT restored:

Alternator Switch ............................................................................... OFF Alternator Control Circuit Breaker .................................................... PULL Electrical Load ........................................................................... REDUCE

NOTE

Drive belt failure may be accompanied by unusual sounds emanating from

the engine compartment.



Model EL-1C


3.2k ALTERNATOR FAILURE (3.14) (Cont.)

CAUTION

Battery life following alternator output failure is dependent on numerous factors such as battery condition at time of failure and the amount of electrical loads necessary for continued flight, therefore is not predictable. Prompt recognition of an alternator failure and reduction of electrical load by eliminating all non-essential equipment loads is essential to prolonging battery life. Safe flight is still possible without electrical power. Landing should be AS SOON AS POSSIBLE.

3.2l PROPELLER OVER SPEED (3.15)

Throttle ....................................................................................... RETARD Propeller Pitch Control ........................................................... DECREASE

(As required to remain below 2600 RPM) Oil Pressure ................................................................................. CHECK Airspeed .................................................................................... REDUCE Throttle ....................................................................................... ADJUST

(As required to remain below 2600 RPM)

Land AS SOON AS POSSIBLE to correct problem.

If engine shut-down is required due to excessively rough engine operation, be prepared for POWER OFF, OFF AIRPORT LANDING.

3.2m ENGINE ROUGHNESS (3.16)

Throttle and Mixture .................................................................... ADJUST (To obtain maximum smoothness)

Induction Air ......................................................................... ALTERNATE Fuel Selector ....................................................... DIFFERENT POSITION Magnetos ..................................................................................... CHECK

(Left, right and both) Magneto .............................................................................................. ON

(If single magneto operation is smoother than both)



Model EL-1C


3.2m ENGINE ROUGHNESS (3.16) (Cont.)

Land AS SOON AS POSSIBLE.

In the event that the engine must be shut down due to unacceptable roughness, be prepared for POWER OFF, OFF AIRPORT LANDING.

3.2n INADVERTENT STALL/SPIN (3.17)

Aileron Control ......................................................................... NEUTRAL Throttle ...................................................................................... CLOSED Rudder ......................................................................... FULL OPPOSITE

(Opposite to direction of spin) Elevator Control ...................................................................... FORWARD

(To break stall) Elevator and Throttle ........................................................ AS REQUIRED

(To smoothly resume level flight) 3.2o EMERGENCY DESCENT (3.18)

WARNING

1. DO NOT ALLOW AIRSPEED TO EXCEED 155 KIAS IN SMOOTH AIR (Flaps retracted).

2. DO NOT ALLOW AIRSPEED TO EXCEED 123 KIAS IN ROUGH

AIR (Flaps retracted).

3. DO NOT ALLOW AIRSPEED TO EXCEED 107 KIAS WITH FLAPS EXTENDED.

4. DO NOT PERFORM ABRUPT MANEUVERS AT SPEEDS IN EXCESS

OF 123 KIAS.

Throttle ......................................................................................... CLOSE Propeller ................................................................FULL INCREASE RPM Wing Flaps ............................................................... EXTENDED 40 DEG Speed ......................................................................................... ADJUST

(DO NOT exceed the above speed limitations)



Model EL-1C


3.2p INADVERTENT ICING ENCOUNTER (3.19)

WARNING

THIS AIRPLANE IS NOT APPROVED FOR FLIGHT IN ICING CONDITIONS FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED

Ice accumulation over engine induction air inlet can cause engine roughness and/or loss of power.

Ice accumulation over oil cooler inlet will cause high oil temperature.

Ice formations on the propeller may cause severe propeller/engine vibrations.

Ice accumulation on the wings and other airframe components will greatly increase the stall speed of the airplane and result in unpredictable flight characteristics. Ice accumulation over the static ports of the air speed indicating system will cause erroneous air speed indications. Ice build-up on the windshield will distort vision and probably obscure forward visibility.

Windshield Defroster ........................................................................... ON Outside Air Temperature .......................................................... MONITOR

If ice build-up is evident on windshield or lift struts:

Induction Air ......................................................................... ALTERNATE Mixture ........................................................................................ ADJUST

(For maximum smoothness) Propeller ....................................................................................... CYCLE

(To shed ice build-up)

Fly toward warmer air, clear of visible moisture or descend to lower altitude (If possible).

If ice build-up continues: Radio ............................................................. ADVISE OF EMERGENCY Land AS SOON AS POSSIBLE. Be prepared for possible POWER OFF, OFF AIRPORT LANDING.

3.3 AMPLIFIED EMERGENCY PROCEDURES – GENERAL



Model EL-1C


The following paragraphs furnish the pilot with additional, expanded information in order that he may better understand the reasons for the recommended emergency procedures indicated in this manual.

3.4 ENGINE FIRE DURING START (3.2a)

Engine fires during start are usually the result of over priming. The first effort to extinguish

the fire is an attempt to start the engine and draw the excess fuel and fire back into the

induction system.

If a fire is present before the engine has started, move the mixture control to idle cut-off, open the throttle and crank the engine. This is an attempt to draw the fire back into the engine. If the engine has started, continue operating to try to pull the fire into the engine induction system.

In either case, if fire continues more than a few seconds, the fire should be extinguished by the best available external means.

If an external fire extinguishing method is to be used, turn OFF the fuel selector valve, place the mixture control in the IDLE CUT-OFF position, place the master switch in the OFF position and ABANDON the airplane.

WARNING

IF A FIRE IS ON THE GROUND, UNDER THE AIRPLANE, DUE TO OVER PRIMING AND THE ENGINE HAS STARTED, TAXI AWAY FROM THE FIRE AS QUICKLY AS POSSIBLE. IF A FIRE IS ON THE GROUND BUT THE ENGINE HAS NOT STARTED, ABANDON THE AIRPLANE IMMEDIATELY.

3.5 ENGINE POWER LOSS [TAKE-OFF] (3.2b)

The proper course of action to be taken in the event of loss of power during take-off depends

primarily on the location along the length of the runway and the height attained above the

runway surface when the power loss occurs.

Land straight ahead if power loss occurs early in the take-off run and/or sufficient runway remains to land from the height attained.



Model EL-1C


3.5 ENGINE POWER LOSS [TAKE-OFF] (3.2b) (Cont.)

If the take-off has progressed to the point where a safe landing cannot be performed on the remaining runway, land as nearly straight ahead as possible. Moderate turns may be made when necessary, to avoid rough terrain or obstructions.

DO NOT attempt to return to the runway unless ample altitude has been gained to safely perform a 180 degree, power-off turn. (If a return to the runway is chosen, be aware of the increased stall speed during turns and be absolutely certain to maintain adequate airspeed during the turn).

If time permits, move the mixture control to IDLE CUT-OFF, turn OFF the fuel selector valve, turn OFF the magnetos and master switch and select full flaps. Touch down at the slowest controlled speed.

If sufficient altitude has been gained to attempt a restart, maintain a safe airspeed, select a different fuel tank, check mixture control FULL RICH, turn electric fuel pump ON 5 seconds then OFF, and select ALTERNATE induction air source. If power is not regained, proceed with POWER OFF LANDING procedure (refer to paragraph 3.9).

3.6 ENGINE POWER LOSS [IN FLIGHT] (3.2c)

Modern aircraft engines are extremely reliable and complete engine power loss is rare and usually caused by fuel flow interruption rather than mechanical failure of the engine. Power will normally be restored shortly (10 sec. or less) after fuel flow is restored.

The first step is to establish a trim speed of 80 to 85 KIAS. If altitude permits, turn fuel selector to a different fuel tank, ENRICH THE mixture, move induction air selector to ALTERNATE. Check engine gauges for a possible indication of the cause of the power loss. If no fuel flow is indicated, check the fuel selector valve to be assured that it is on a tank containing fuel or move it to the both position.



Model EL-1C


3.6 ENGINE POWER LOSS [IN FLIGHT] (3.2c) (Cont.) If power is restored, move the induction air to PRIMARY (unless induction ice is suspected), and adjust the mixture control as necessary. If the cause of the power loss was anything except fuel exhaustion (of one source with adequate fuel remaining in the other), land AS SOON AS POSSIBLE and investigate the cause.

If the preceding steps have not restored power, call ATC, declare emergency and intentions, set Transponder to Emergency Code or that assigned by ATC and prepare for a POWER OFF LANDING (Paragraph 3.9).

3.7 POWER OFF LANDING (3.2d)

If power is lost at altitude, trim the airplane to a gliding speed (80 to 85 KIAS) and look for the best available landing area. If time and altitude permit, check charts and/or calls ATC for the nearest airport in the immediate vicinity. Report the emergency and your intentions (It may be possible to land at an airport - if sufficient altitude is available).

Advise passengers to tighten seat belts harnesses and

secure all loose equipment.

When a suitable field (whether airport or off-airport) has been located, establish a spiral

pattern around the field. Attempt to be at 1200 to 1400 feet above the field at the downwind

position so that a normal landing approach may be conducted (Excess altitude can be lost

by widening the pattern, using flaps or slipping or a combination of these). When the field is

assured, slow the airplane to normal approach speed and deploy the flaps as required. Crew

should tighten seat belts and harnesses at this time. If the landing is to be made at an off-

airport field, it is normally best to make the final approach and touch-down at the slowest

practical speed consistent with good control of the airplane. If the field is suspected to be

excessively soft or when. landing in water of any significant depth, always hold the nose

wheel off as long as possible.

When committed to land CLOSE the throttle, move the mixture control to IDLE CUT-OFF, shut OFF the magneto switches, turn the fuel selector to OFF and turn OFF the alternator and master switches.



Model EL-1C


NOTE

With the master switch OFF landing lights and navigation lights will not be usable.



Model EL-1C


3.7 POWER OFF LANDING (3.2d)(cont.)

NOTE

With the airplane trimmed at a gliding speed (80 to 85 KIAS) and under no wind conditions, the airplane will travel approximately (TBA) miles for each 1,000 feet of altitude above terrain.

WARNING

BE EXTREMELY CAUTIOUS WHEN MANEUVERING FOR LANDING AT LOW ALTITUDES. MAINTAIN A SAFE MARGIN ABOVE STALL SPEED. SEE FIGURE 5-3FOR STALL SPEEDS VS. ANGLES OF BANK.

3.8 FIRE IN FLIGHT (3.2e)

Fire will be detected through the presence of smoke, odor and probably heat in the cockpit/cabin of the airplane. Since the action to be taken will be based on the type and location of the fire, it is imperative that the pilot quickly identify the type and source of the fire by the character of the smoke and possibly from instrument readings.

If the source of the fire is electrical equipment and the offending equipment is apparent, turn equipment OFF and PULL corresponding circuit breaker(s).

If the fire persists or the source is not apparent, turn Master Switch OFF, turn Alternator Switch OFF, turn OFF cabin heat and attempt to extinguish fire with fire extinguisher.

If fire is extinguished and avionics are required for navigation or communication, PULL all circuit breakers, turn ON, Master and Alternator Switches then reset appropriate circuit breakers (One-at-a-time). Allow sufficient time between resetting circuit breakers to determine which is the defective item of equipment. If fire recurs, PULL the circuit breaker of the offending equipment, land AS SOON AS POSSIBLE and correct the problem. If fire persists, conduct EMERGENCY DESCENT, LAND IMMEDIATELY and EVACUATE the airplane if necessary.



Model EL-1C


3.8 FIRE IN FLIGHT (3.2e) (Cont.)

If fire is in cabin/cockpit and is other than electrical in nature, fire extinguisher must be used in an attempt to extinguish the fire.

If fire is extinguished, land AS SOON AS POSSIBLE and correct problem.

If fire persists, conduct EMERGENCY DESCENT, LAND IMMEDIATELY and EVACUATE the airplane if necessary.

If an engine fire is indicated, CLOSE the throttle, select IDLE CUT-OFF on the mixture control, turn OFF the fuel selector valve, turn magneto switches OFF, turn OFF electric fuel pump, turn cabin heat OFF and proceed with POWER OFF LANDING.

If fire persists, conduct EMERGENCY DESCENT, LAND IMMEDIATELY and EVACUATE the airplane if necessary.

NOTE

It may be necessary to evacuate smoke/fumes (3.11).

3.9 COCKPIT/CABIN SMOKE/FUMES (3.2f)

Turn cockpit/cabin heat OFF, OPEN cockpit/cabin vents, REDUCE speed and, if necessary OPEN and allow pilot and copilot doors to trail.

3.10 LOSS OF OIL PRESSURE (3.2g)

Loss of oil pressure can be partial or total.

A partial loss usually indicates a malfunction in the oil pressure regulating system and a landing should be made AS SOON AS POSSIBLE to investigate the cause and to prevent possible engine damage.

A total loss of oil pressure and increased oil temperature probably indicates oil exhaustion. A total loss of oil pressure without a temperature increase may be the result of a faulty gauge. In either case, proceed toward the nearest airport, advise ATC of the nature of the problem and your intentions. Maintain altitude, at reduced power, until a POWER OFF LANDING can be accomplished or as long as possible. Make power changes only as required. Altering the power setting may hasten a complete power loss.



Model EL-1C


3.10 LOSS OF OIL PRESSURE (3.2g) (Cont.)

Circumstances may dictate an "Off-Airport" landing while power is still available. This is particularly true if actual oil pressure loss is indicated by a sudden increase in oil or cylinder head temperature, abnormal engine sounds or the odor of oil smoke and an airport is not nearby.

Be prepared for a possible POWER OFF, OFF AIRPORT LANDING (Paragraph 3.9).

3.11 HIGH OIL TEMPERATURE (3.2h)

An abnormally high oil temperature indication can be caused by low oil quantity, an obstruction in the oil cooler an obstructed oil cooler air inlet, damaged baffles, a defective gauge or other causes.

A steady, rapid rise in oil temperature is a sign of serious trouble. A rise in oil temperature will probably be accompanied by a loss of oil pressure (monitor the oil pressure gauge).

Power should be reduced as much as possible, enrich the mixture, if possible, increase the airspeed. Land AS SOON AS POSSIBLE at an appropriate airport and investigate the cause but be prepared for a possible POWER OFF, OFF AIRPORT LANDING.

3.12 HIGH CYLINDER HEAD TEMPERATURE (3.2i)

Excessively high cylinder head temperatures may accompany excessive oil temperature.

Reduce power, enrich the mixture as much as possible, and increase airspeed if possible or practical.

If high cylinder head temperature persists, LAND AS SOON AS POSSIBLE and investigate cause. Be prepared for a possible POWER OFF, OFF AIRPORT LANDING.



Model EL-1C


3.13 LOSS OF FUEL FLOW/PRESSURE (3.2j)

Loss of fuel flow/pressure is normally caused by depletion of fuel from the selected source or by engine driven fuel pump failure or, on rare occasion, by a failed fuel line.

If loss of flow/pressure occurs, the fuel selector should be set on the fuel source containing the most fuel or on the BOTH position and turn on FUEL pump.

If power is restored, turn the electric fuel pump OFF. If power is again lost, it is an indication that the engine driven pump has failed and the electric pump must be turned ON to continue flight. Adjust the throttle and mixture as required. A landing should be made at the nearest airport and repairs accomplished.

If turning the electric fuel pump on and selecting the other fuel source does not restore power, proceed with POWER OFF LANDING procedure (Paragraph 3.9).

CAUTION

If normal engine operation and fuel flow/pressure can not be reestablished, turn the electric fuel pump and fuel selector valve OFF. Lack of fuel flow/pressure may be an indication of a leak in the fuel system and if the fuel is left ON, presents a potential fire hazard.

NOTE

If flow/pressure loss is caused by fuel depletion, it will normally be restored in

10 seconds or less after selection of an adequate source of fuel.

3.14 ALTERNATOR FAILURE (3.2k)

Alternator output failure can be caused by a mechanical failure of the alternator, a momentary overvoltage condition, a failed alternator drive belt or other reasons. Alternator output failure will be indicated by the illumination of the ALT FAIL light in the annunciator panel and by a zero or negative reading on the ammeter. A momentary overvoltage or other condition may cause the alternator circuit breaker to "trip".



Model EL-1C


3.14 ALTERNATOR FAILURE (3.2k) (Cont.) Failure of the alternator drive belt or a mechanical failure of the alternator may be accompanied by unusual sounds emanating from the engine compartment, possibly accompanied by a hot rubber-like odor. The first step is to reduce the electrical load to minimum.

NOTE

Duration of the battery is dependent on the condition of the battery at the time of the failure and electrical load being supplied.

Turn the alternator switch OFF for at least one second, check circuit breaker and RESET if tripped. Turn the alternator switch ON, check ALT FAIL light EXTINGUISHED and that the ammeter shows a POSITIVE indication.

If alternator returns on line, continue flight, monitor ammeter and annunciator light and have system checked after landing.

If the alternator does not return on line, reduce electrical load to minimum required for safe flight by turning OFF switches and pulling circuit breakers for all nonessential electrical equipment (Maintain only that equipment required to provide information for safe flight).

Land AS SOON AS POSSIBLE and conduct appropriate repairs.

3.15 PROPELLER OVERSPEED (3.2 l)

Propeller overspeed is rare. If it should occur, it is normally the result of a malfunction of the governor or loss of oil pressure to the governor. The propeller control should be moved to the full DECREASE rpm position. RESET the propeller pitch control to the original setting and determine if any control is available.

If control is returned, land at the first available airport and investigate the cause of the overspeed.

If control is not returned, move the propeller pitch control to the full DECREASE rpm position, REDUCE power and airspeed in order to control propeller at no more than 2600 rpm.

If control is still not returned or if severe vibrations develop, the engine should be shut down and preparations made for a POWER OFF, OFF AIRPORT landing.

3.16 ENGINE ROUGHNESS (3.2m)



Model EL-1C


Engine roughness can be the result of numerous conditions such as dirt in the injector nozzles, induction filter icing, ignition problems, water contamination etc.

First adjust the mixture control to obtain the maximum smoothness (Rough operation can occur if the mixture is too lean or too rich).

If roughness persists:

Move the induction air control to ALTERNATE and switch the fuel selector valve to a different fuel source.

Check the engine gauges for any abnormal readings. If any gauge reading is abnormal take

corrective action as necessary.


Turn the left magneto OFF, check engine operation and then turn ON. Turn the right magneto OFF, check engine operation and then turn ON. If operation is satisfactory on only one magneto, proceed on the good magneto, at reduced power, and land at the first suitable airport for repairs.


Consider a precautionary landing while power is still available.

Prepare for a possible POWER OFF, OFF AIRPORT landing.

3.17 INADVERTENT SPIN (3.2n)

This airplane is prohibited from intentional spins.

If an inadvertent spin is entered, close throttle, neutralize ailerons and apply full rudder opposite to the direction of the spin. Move the elevator control full forward to break the stall after applying the rudder. When rotation stops, neutralize the rudder, relax forward pressure on the elevator control as required to smoothly regain level flight and return to initial power setting.



Model EL-1C


3.18 EMERGENCY DESCENT (3.2o)

An Emergency Descent should be initiated whenever a situation occurs at high altitude requiring a high rate of descent. This is done in order to minimize exposure of the crew and passengers to an uncontrolled fire or when smoke, toxic fumes or other cause threatens control of the airplane through incapacitation or restricted visibility for the pilot (See paragraphs 3.10, FIRE IN FLIGHT and 3.11, COCKPIT/CABIN SMOKE/FUMES).

Retard throttle to IDLE, advance propeller pitch to FULL INCREASE rpm and switch to a different fuel tank.

Trim airplane for maximum allowed indicated airspeed appropriate to the configuration

selected and the atmospheric conditions. Advise the control center if flight path is in an

airway.

WARNING

SCENT IS TO BE MADE USING FULL FLAPS, SLOW THE AIRPLANE TO 107 KIAS PRIOR TO FLAP EXTENSION AND PRIOR TO STARTING THE DESCENT. EXCEEDING THE FLAP EXTENDED SPEED (107 KIAS), CAN CAUSE DAMAGE TO THE WING STRUCTURE AND POSSIBLE FAILURE OF THE FLAP ATTACHMENTS.

IF THE DESCENT IS TO BE MADE WITH THE FLAPS RETRACTED, DO NOT EXCEED 155 KIAS (IN SMOOTH AIR) OR 123 KIAS (IN ROUGH AIR). DO NOT MAKE FULL ABRUPT CONTROL MOVEMENTS ABOVE 123 KIAS.EXCEEDING THE NEVER EXCEED SPEED (155 KIAS, IN SMOOTH AIR), OR THE DESIGN AND MANEUVERING SPEEDS (123 KIAS, IN ROUGH AIR), CAN CAUSE SEVERE DAMAGE TO AND POSSIBLY FAILURE OF THE AIRPLANE STRUCTURE.

Call ATC, report the nature of the emergency, your intentions and set transponder to EMERGENCY code. If the engine has been shut down due to fire, it may be necessary to slip the airplane in an attempt to divert flames away from the cockpit area. Be prepared for a POWER OFF, OFF AIRPORT LANDING.



Model EL-1C


3.19 INADVERTENT ICING ENCOUNTER (3.2p)

Icing conditions are very difficult to predict. Aviation Weather Service may predict light, moderate or severe icing conditions at certain locations and altitudes and no icing will be encountered. On the other hand, icing conditions may not be forecast and any of the above levels of icing may occur. As indicated above, icing conditions can be encountered in areas and at altitudes where no icing is forecast. Under these conditions, immediate action must be taken to divert from the icing conditions. It may be possible to descend to a lower, warmer altitude or it may be necessary to return to an area where no icing was present (At any time the flight is conducted in clouds or visible moisture, turn windshield defroster ON and MONITOR the outside air temperature gage.

If ice build-up becomes evident on the windshield and/or the lift struts or if engine operation becomes rough, select Alternate Air ON, if engine operation remains rough, adjust mixture control to obtain maximum smoothness. If engine operation continues to be rough it may indicate that ice is accumulating on the propeller and cycling the propeller from high to low rpm and return may shed the ice.

WARNING

ICING ENCOUNTERS CAN CAUSE ICE ACCUMULATION OVER THE ENGINE INDUCTION AIR INLET, RESULTING IN ROUGH ENGINE OPERATION. ACCUMULATION OVER THE OIL COOLER INLET WILL CAUSE HIGH OIL TEMPERATURES. ACCUMULATION ON THE PROPELLER MAY CAUSE SEVERE PROPELLER/ENGINE VIBRATION. ACCUMULATION ON WINGS, TAIL SURFACES AND OTHER AIRFRAME COMPONENTS CAN GREATLY INCREASE THE STALL SPEED OF THE AIRPLANE AND CAUSE UNKNOWN FLIGHT CHARACTERISTICS. ACCUMULATION OF ICE OVER THE STATIC PORTS WILL CAUSE ERRONEOUS AIR SPEED INDICATIONS. ACCUMULATIONS ON THE WINDSHIELD WILL DISTORT VISION AND PROBABLY OBSCURE FORWARD VISIBILITY.



Model EL-1C

REVISED: Dec 07, 2000 Rev. No. 1

If ice build-up continues:

Advise ATC of emergency, land AS SOON AS POSSIBLE. Be prepared for possible POWER OFF, OFF AIRPORT LANDING.



Model EL-1C


POWER-OFF LANDING

MAINTAIN BEST GLIDE AIR SPEED UNTIL NORMAL PATTERN CUES ARE OBTAINED. WHENEVER THIS OCCURS, FLY BEST GLIDE OR NORMAL PA TTERN AIRSPEEDS AS REQUIRED.

USE FLAPS ONLY AFTER ESTABLISHED IN A NORMAL PATTERN AND A SAFE LADING IS A SSURED.

Figure 3-1

? WIND

High Key Approximately 1200”-1400”

Low Key Approximately 700-900”

Final Min 300”AGL

Turn 45° from landing point



Model EL-1C


Section 4 NORMAL PROCEDURES

Table of Contents Para Title

Page

4.1 General

3

4.2 Airspeeds for Normal Operations

4

4.3 Normal Procedures Checklists

6

4.4 Amplified Normal Procedures (General)

27

4.5 Preflight Check

27

4.6 Before Starting Engine

31

4.7 Engine Start

32

4.8 Before Taxi

33

4.9 Taxi

33

4.10 Ground Run-Up

34

4.11 Before Takeoff

35

4.12 Takeoff

36

4.13

After Takeoff/Climb 38

4.13 (a)

Climb (Best Angle) 38

4.13 (b)

Climb (Best Rate) 38

4.13 (c)

Climb (Normal/Cruise) 39

4.14

Cruising Powerplant Management 39

4.15 Descent 41



Model EL-1C



Table of Contents Para Title Page

4.16 Approach to Landing (Normal)

41

4.16 (a)

Approach to Landing (Obstacle Clearance) 42

4.17

Landing 42

4.18

Parking 44

4.19

Practice Maneuvers 44

FIGURES Figure 4.1

Walk Around

5



Model EL-1C



4.1 GENERAL This section describes the recommended procedures for the conduct of normal operations in the Gavilan Model EL-1C at maximum gross weight. The first portion of this section provides abbreviated checklists, which supply an action, sequence for normal operation in the basic EL-1C airplane and are suitable for reference in the cockpit. The second portion of this section supplies amplified information and explanations of the basic checklists. It provides the pilot with detailed descriptions for a better understanding of the procedures and techniques presented. The second portion is not intended for use as an in-flight reference. Amplified information is not provided for those checklists which are self-explanatory. Refer to Section 9 (Supplements) for checklists which provide procedures for optional equipment in EL-1C airplanes. Pilots should familiarize themselves with the applicable procedures given in Section 9 in order to become proficient in the normal operations of their particular airplane.



Model EL-1C


4.2 AIRSPEEDS FOR NORMAL OPERATIONS

The following airspeeds are those which are significant to the safe and efficient operation of the airplane during performance of normal procedures contained in this section. The airspeeds presented are applicable to airplanes flown at maximum gross weight in standard atmospheric conditions.

Airplane performance and the best airspeed for normal operations vary from published figures depending upon actual aircraft weight, atmospheric conditions, engine performance and piloting techniques.

a. Never Exceed Speed (Vne)

155 KIAS

b. Operating Maneuvering Speed (Vo)

123 KIAS

c. Maximum Flap Speed (VFE)[Flaps 40 deg.]

107 KIAS

d. Cruise Climb Speed

90-100 KIAS

e. Best Rate of Climb Speed (Vy)@ SL

80 KIAS

f. Best Angle of Climb Speed (Vx)@ SL

70 KIAS

g. Final Approach Speed (Flaps 40 deg.)

80-85 KIAS

h. Balked landing speed (Flaps 40 deg.)

69 KIAS

I. Normal Rotation Speed (Vr)(Flaps 15 deg.)

60-65 KIAS

j. Short field obstacle clearance speed (Takeoff) (Flaps 15 deg.) (Landing) (Flaps 40 deg.)

72 KIAS

k. Maximum demonstrated cross wind component 14 KIAS



Model EL-1C


Figure 4-1. WALK-AROUND



Model EL-1C


4.3 NORMAL PROCEDURES CHECKLIST PREFLIGHT CHECK (fig.4.1)

a. COCKPIT

Parking Brake SET Flight Controls RELEASE – CHECK - FREEDOM/PROPER SENSE Fuel Selector SET – BOTH Static Sys tem Drain DRAIN - SET PRIMARY SOURCE Trim SET – TAKEOFF Wing Flaps EXTEND - 40 DEG

(ensure cargo doors are closed)

Oxygen Supply/Masks (If installed) CHECK – QUANTITY (Adequate for intended flight) Empty Seat SECURE – BELTS AND HARNESSES FASTENED

Airworthiness Certificate, Aircraft Registration, Radio Station License, Airplane Flight Manual, CHECK-ONBOARD/STOWED/COMPLETE Navigation/Approach Charts, Portable Equipment Weight & Balance

Magnetos CHECK - OFF Circuit Breakers CHECK - SET Battery Switch ON Fuel Quantity Gauges CHECK - INDICATED QUANTITY



Model EL-1C


4.3 NORMAL PROCEDURES CHECKLIST - PREFLIGHT CHECK (cont.)

Nav./Strobe/Landing/Taxi Lights ON – CHECK – O

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