Chapter 79 Oil System - extraaircraft.com · out through the overboard breather line. The top ball...

CHAPTER 79PAGE 1

SERVICE MANUAL EXTRA 300L

PAGE DATE: 4. June 2009

Chapter 79

Oil System

CHAPTER 79PAGE 2



TABLE OF CONTENTS

Chapter Title

79-00-00 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 379-00-10 Christen Inverted Oil System . . . . . . . . . . . . . . . . . . . . . 379-00-11 Valve Balls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

79-20-00 DISTRIBUTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 779-20-02 Fittings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 779-20-03 Flexible Hoses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 779-20-10 Single Oil Cooler System . . . . . . . . . . . . . . . . . . . . . . . 879-20-20 Dual Oil Cooler System . . . . . . . . . . . . . . . . . . . . . . . . 9

79-30-00 INDICATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1079-30-10 Oil Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1079-30-11 Oil Pressure Gauge . . . . . . . . . . . . . . . . . . . . . . . . . . . 1179-30-14 Oil Pressure Wet Line . . . . . . . . . . . . . . . . . . . . . . . . . 1179-30-15 Engine Fitting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1279-30-20 Oil Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1279-30-21 Oil Temperature Gauge . . . . . . . . . . . . . . . . . . . . . . . . 1279-30-25 Oil Temperature Sensor . . . . . . . . . . . . . . . . . . . . . . . . 12

CHAPTER 79PAGE 3



79-00-00 GENERAL

79-00-10 Christen Inverted Oil System

The EXTRA 300L is equipped with a modification of aChristen Inverted Oil System (CHRISTEN 801 series). Theneed for modification of the standard Christen 801 InvertedOil System results from installation requirements of theLycoming engine. Maintenance work or overhaul of thissystem requires consultation of the manufacturer. (Refer toChristen Product Manual and Lycoming Operaton andInstallation Manual (refer to Chapter 01).

Description and Operation

The standard Christen 801 Inverted Oil System is a kit-formaccessory for Lycoming aircraft engines which permitsnormal engine lubrication, with minimal oil loss, duringaerobatic flight. When installed, it becomes a self-containedextension of the normal aircraft engine oil and breathersystems. As the system control valves are gravity-operated,no connection to aircraft power sources is required (Referto Figure 1 and 2).

The system works in all inverted and negative-g flightconditions and is particularly suited to high-performanceaircraft used for unlimited-class aerobatic competitions.

CHAPTER 79PAGE 4



Normal flight

During normal flight, the weighted ball valve at the top of theoil separator is open, allowing blow-by gases from theengine crankcase to be vented from the breather port to thetop of the oil separator and out through the overboardbreather line. The top ball valve of the oil valve is closed andthe bottom ball valve is open, allowing oil to flow from thesump fitting to the oil pump and out to the engine lubricationpoints.

Inverted flight

When the aircraft is inverted, engine oil falls to the top of thecrankcase. the weighted ball valve in the oil seperator closes,preventing overboard loss of oil though the top of the oilseparator. Blow-by gasses from the engine crankcase arevented from the sump to the bottom of the oil separator andout through the overboard breather line. The top ball valve ofthe oil valve is open, and the bottom valve is closed, allowingoil to flow out from the breather port to the oil valve, throughthe sump fitting and the sump screen, to the oil pump and outto the engine lubrication points.

INVERTED OIL SYSTEM

Inverted Oil System, Normal FlightFigure 1

CHAPTER 79PAGE 5



Any oil in the lines which fails to return to the sump duringthe transition between normal and inverted flight drains intothe oil separator. This oil then returns to the sump from thebottom of the oil separator during periods of normal flight.

Maintenance Practices

The inverted oil system normally requires no maintenance.During major overhauls or when repairs require sumpremoval, inspect sump for excessive deposits of sludge,varnish, or foreign material. If sump is dirty, remove andthoroughly clean all hoses and components; then use com-pressed air blast for drying and cleanout before reassembly.

Cleaning

The inverted oil system must be flushed with a suitablepetroleum solvent, such as varsol, every 300 (three hundred)hours of engine operation or when there is evidence of theloss of oil through the breather line after normal flight.

Principles of OperationINVERTED OIL SYSTEM

Inverted Oil System, Inverted FlightFigure 2

CHAPTER 79PAGE 6



79-00-11 Valve Balls

Reseating

Marginal oil loss of valve may result from nicks in the valveseats which cause leakage when the valve should be closed.Such nicks can be caused by mishandling or by small chips ofmetal being caught between the ball and the seat as the valveoperates during initial run-in of a new or overhauled engine.For more information of the valves refer to LycomingOperaton and Installation Manual (see Chapter 01).

CHAPTER 79PAGE 7



79-20-00 DISTRIBUTION


The lubrication system of the EXTRA 300L features eithera single or dual oil cooler system both using flexible tubing.

The hose and fitting installation is modified with respect tothe standard Christen Inverted Oil System. The connectionsof the Inverted Oil System however still consist of AN(Army/Navy) Standard fittings.

The flexible tubing of the oil cooling system is connectedusing AN Standard fittings with equal size (8D), but differentconnection angles.

In operation the hot lubricating oil leaving the engine ispumped by an engine-driven pump to a hose connector on theengine mount which directs the oil to the oil cooler(s). Theoil is cooled in passing through the oil cooler(s) and returnedto the engine lubricating circuit through the return hosetubing.

Maintenance Practices

Before making installations and repairs to the aircraft plum-bing, it is important to make accurate identification ofplumbing materials.

79-20-02 Fittings

General information concerning fittings used in the EXTRA300L can be found in Chapter 20-10-08.

79-20-03 Flexible Hoses

General information concerning flexible hoses can be foundin Chapter 20-10-07.

CHAPTER 79PAGE 8



I M P O R T A N T If replacement of oil lines is necessary, cover the oillines of the engine compartment with AEROQUIPAE102 fire sleeves as per Chapter 20-10-07 except theAEROQUIP 637/MIL-H 6000 hoses.

79-20-10 Single Oil Cooler System


When the single oil cooler system is installed the oil cooleris located on the aft right hand engine side (see Figure 3).

Figure 3,Single Oil Cooler System

CHAPTER 79PAGE 9



Flexible Hose

Oil cooler Oil cooler

Figure 4,Dual Oil Cooler System

Engine

79-20-20 Dual Oil Cooler System


When the dual oil cooler system is installed the oil coolersare mounted on the left front and left rear engine baffles andare connected to the engine by flexible hose (refer to Fig. 4).The two oil coolers are produced by the STEWART WARNERSOUTH WIND Corporation.

CHAPTER 79PAGE 10



79-30-00 INDICATING

Oil pressure and oil temperature are sensed on the EXTRA300L engine and are indicated to the pilot in command.

Trouble Shooting

Trouble Possible Cause Remedy

No oil pressure indication Sensor defective Replace sensor.Gauge defective Replace gauge.

Oil pressure low Engine oil pressure low Check engine oil pressurewith calibrated equipment.

Orifice engine fitting Clean fitting.blockedSense line leakage Replace sense line.

Oil temperature high Sensor or cable defective Replace sensor.Repair cable defect.

Gauge defective Replace gauge.Incorrect engine oil Perform engine oil change.

79-30-10 Oil Pressure

The oil pressure gauge is located in the rear instrumentpanel. The gauge receives its data electrically from a pressuresensor located on the aft side of the firewall (refer toFigure 5). The pressure sensor is connected to a bulkheadfitting on the cold side of the firewall. A wet line connects thebulkhead fitting to the reducer fitting at the engine.

CHAPTER 79PAGE 11



Figure 5,Oil Pressure Sensor & Wet Line

79-30-11 Oil Pressure Gauge

Oil pressure indication is combined with the oil temperatureindication in one single unit.

Removal/Installation

Refer to Chapter 31.

79-30-14 Oil Pressure Wet Line


1 Remove upper cowling per Chapter 71

2 Disconnect the sense wet line at firewall bulkhead fittingand at engine fitting (refer to Figure 5).

CHAPTER 79PAGE 12



3 Install in reverse sequence of removal. Torque sense linefittings with 15.3 to 16.9Nm (135 to 150 in.lbs.) and applyinspection lacquer.

79-30-15 Engine Fitting


1 Remove upper cowling per Chapter 71.

2 Disconnect the sense wet line per Chapter 79-30-14.

3 Remove the engine fitting.

4 Install in reverse sequence of removal. Torque enginefitting with 15.3 to 16.9Nm (135 to 150 in.lbs.) and applyinspection lacquer.

79-30-20 Oil Temperature

The oil temperature gauge is located in the rear instrumentpanel. The gauge receives its data electrically from a sensorlocated on the engine in front of the oil filter screen (referto Figure 6).

79-30-21 Oil Temperature Gauge

Oil temperature indication is combined with the oil pressureindication in one unit.

79-30-25 Oil Temperature Sensor


The sensor can be easily removed and installed withoutspecial equipment.

1 Remove upper cowling per Chapter 71.

CHAPTER 79PAGE 13



2 Remove oil temperature sensor (refer to Figure 6).

3 Install in reverse sequence of removal.

Figure 6Oil temperature sensor location

Chapter 79 Oil System - extraaircraft.com · out through the overboard breather line. The top ball...

Documents

Transcript of Chapter 79 Oil System - extraaircraft.com · out through the overboard breather line. The top ball...