BOEING 737
MAINTENANCE MANUAL
CHAPTER 74 TAB EFFECTIVE PAGES SEE LAST PAGE OF LIST FOR NUMBER OF PAGES CONTENTS 74 1 SEP 20/82 5802 MAY 20/82 553 74- 00 1 OCT 20/91 5692 OCT 20/91 5693 OCT 20/91 5694 NOV 15/78 5695 NOV 15/80 5696 NOV 15/78 5697 OCT 20/91 5698 OCT 20/91 5699 NOV 15/80 56910 BLANK 74- 00 101 FEB 20/88 500102 FEB 20/85 505103 SEP 20/82 505104 BLANK PAGE DATE CODE 74- 21- 11 (CONTINUED)402 FEB 01/96 569403 FEB 01/96 569404 OCT 20/90 569405 FEB 01/96 569406 NOV 15/80 569 74- 21- 11 501 FEB 15/79 500502 BLANK 74- 21- 21 401 FEB 20/91 500402 OCT 20/84 500403 FEB 20/91 500404 FEB 20/91 500405 FEB 20/91 500406 FEB 15/81 500 74- 31-0 1 JUN 20/83 5042 JAN 20/83 5043 NOV 15/80 5864 NOV 15/80 5865 MAY 15/79 5046 BLANK 74- 31- 11 401 MAY 15/79 504402 MAY 15/79 504 PAGE DATE CODE PAGE DATE CODE PAGE DATE CODE
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CHAPTER 74
IGNITION
TABLE OF CONTENTS
Subject Subject No.
IGNITION SYSTEM........................................................................................................ Description and Operation Electrical Power Supply Ignition Power Supply Igniter Exciter Distribution High Tension Distribution High Tension Leads Igniter Plugs Switching (Ref 74-31-0) Trouble Shooting Maintenance Practices Adjustment/Test Inspection/Check Cleaning/Painting
ELECTRICAL POWER SUPPLY
IGNITION POWER SUPPLY
Ignition Exciter ......................................................................................................... 74-11-11 Removal/Installation
DISTRIBUTION
HIGH TENSION DISTRIBUTION
High Tension Leads ................................................................................................. 74-21-11 Removal/Installation Adjustment/Test
Igniter Plugs ............................................................................................................. 74-21-21 Removal/Installation
580
Sep 20/82 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Contents 74 Page 1
Subject Subject No.
SWITCHING
ENGINE IGNITION CONTROL ................................................................................... Description and Operation Start Lever Actuated Switches 74-31-0
Start Lever Switches ................................................................................................ Removal/Installation Adjustment/Test 74-31-11
Engine Start Switch .................................................................................................. Adjustment/Test [1] 74-31-12
Engine Start Switch .................................................................................................. Adjustment/Test [2] 74-31-13
[1] [2] Airplanes with four position rotary start switch Airplanes with five position rotary start switch
Contents 74 May 20/82 Page 2
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
IGNITION SYSTEM - DESCRIPTION AND OPERATION
1. General
A. The purpose of the engine ignition system is to provide a means of initiating or sustaining combustion of the fuel - air mixture in nine can - annular combustion chambers in the combustion section.
B. There are two identical ignition systems, one for each engine consists of control switches, two ignition exciters, two high tension leads and two igniter plugs. Each ignition system shall be discussed in terms of electrical power supply, distribution and switching.
2. Electrical Power Supply
A. Ignition Power Supply
(1)
Airplanes with 20-4 Joule DC Starting and Continuous Ignition System: The 20-4 Joule single pack continuous ignition system is powered by two input voltage at the ignition exciter, 28 VDC and 115 V, 400 Hertz. The single unit housing incorporates one power input connection and two output connectors. A dual pack system is also available. The dual pack system has two exciters with a power input connection for each exciter. The two output connections supply the high tension voltage through the exciter cables to the igniter plugs. P&W SB 5880 installs the optional dual pack system.
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