Section 28-40 % Fuel Quantity Indicating - Lycoming Engine
1.
General ..............................................1
2.
Description............................................1
3.
Operation.............................................6
Trouble-Shooting
1. General ............................................101
Maintenance Practices
1.
General ............................................201
2.
Remove/Install a Fuel Tank Sensor .......................201
3.
Remove/Install a Fuel Tank Probe........................203
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Rev. 4 09 Jan 2003
28-CONTENTS
AMM
% Section 28-41 % Fuel Quantity Indicating - TAE 125 Diesel Engine % 1. General ..............................................1 % 2. Description............................................1 % 3. Operation.............................................1 % Trouble-Shooting % 1. General ............................................101 % Maintenance Practices % 1. General ............................................201 % 2. Remove/Install a 'Low Fuel' Sensor .......................201 % 3. Remove/Install the 'High Fuel' Sensor .....................203 % 4. Remove/Install a Fuel Quantity Probe .....................205
28-CONTENTS
Fuel System
AMM
CHAPTER 28
FUEL SYSTEM
% Section 28-00 % Fuel System - Lycoming Engine
1. General
% This Section tells you about the DA 40 airplane fuel system with the Lycoming engine installed. It does not tell you about the engine fuel system. For more data on the engine fuel system refer to the Lycoming Maintenance Manual.
% The DA 40 has a fuel tank in each wing. Each wing tank is made of the following two or three
% chambers:
%) the inboard fuel chamber,
%) the outboard fuel chamber, and
%) the long range chamber (only if the Long Range Tank is installed, see O.M 40-071).
% All individual chambers are interconnected. The total usable fuel capacity of the fuel system is 152
% liters (40 US gal) with the Standard Tank and 182 liters (48 US gal) with the optional Long Range Tank
% installed. Two pumps supply fuel to the engine and a filter gives protection to sensitive components.
The pilot controls the fuel system with a selector valve and a switch for the electric fuel pump. A fuel quantity indicator shows the quantity of fuel in the left tanks and in the right tanks. Refer to these Sections for more data on these systems:
Section 28-10 Fuel storage.
Section 28-20 Fuel distribution.
Section 28-40 Fuel indication.
Note: Equipment which is certified for installation in the DA 40 is listed in Section 6.5 of the Airplane Flight Manual. Such equipment may be installed in accordance with the Airplane Maintenance Manual.
Any equipment which is not listed in Section 6.5 of the Airplane Flight Manual is called "Additional Equipment". The installation of Additional Equipment is a modification which must be handled in accordance with national regulations or a Service Bulletin.
Doc # 6.02.01 Page 1
Rev. 4 09 Jan 2003
28-00-00
AMM
Fuel Flow Divider
Finger Filter Finger Filter
% Figure 1: Fuel System Schematic Diagram, Standard Tanks Installed
28-00-00
Fuel System
AMM
2. Description
% A. Standard Tanks
% Figure 1 shows the fuel system schematic diagram for the DA 40 with the Lycoming engine and % the Standard Tanks installed.
% An inboard chamber and an outboard chamber in each wing hold the fuel. A flexible coupling % connects the inboard chamber to the outboard chamber. Each outboard chamber has a fuel filler % assembly and a vent connection. Each inboard chamber has a fuel drain and a finger-filter at the
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