BIT Manual 346116 s

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737 FMS

MAINTENANCE BITE MANUAL

HIGHLIGHTS of 2May 14/10

34-61-16

Formerly Smiths Aerospace

To: Holders of Flight Management Computer System Maintenance BITE Manual (737 Update10.4A and Later).

On May 4th, 2007 the Aerospace business of Smiths Group, formally known as Smiths Aerospace LLC, was sold to General Electric Corporation and became GE Aviation Sys-tems LLC, doing business as GE Aviation.

REVISION NO. 4 DATED MAY 14/10

This manual has been reformatted and is re−issued in full at this revision as part of GE Aviationpolicy to publish in accordance with ATA 100 Rev 21.

Incorporate the revision as follows:

Action Reason

Replace existing manual with this revision. Full re−issue of manual.

Pages which have been revised are outlined below together with the highlights of the revision.Change bars have been used to indicate revised material in this manual.

Page No. Description

of

Change Effectivity

General Inserted a “THIS PAGE INTENTIONALLY LEFTBLANK” page for all blank backup pages exceptthe title page.

All Models

Title Page Updated to reflect this revision. All Models

Record of RevisionsPage 1

Updated to reflect this revision. All Models

List of Effective PagesPages 1 thru 4

Revised to reflect this revision. All Models

ContentsPages 1 and 3 Updated to reflect relocated material and

corrected subject title.

All Models

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Page No. EffectivityDescription of Change

IntroductionPage 1

Pages 2 thru 8

Added LCD CDU identif icat ion definitions to theterminology paragraph.

Added new acronyms and relocated material asneeded.

All Models

Description and OperationPage 1 and 2

Pages 7, 14 thru 18,18.1 and 18.2, 19,25, 34 thru 38,38.1 and 38.2, and 42

Updated company name to reflect the correct us-age. Added new display model information.

Added coverage for the new display units,corrected minor errors, and relocated material asneeded.

All Models

Maintenance BITE PagesPages 151, 162, 162.1and 162.2, 163 thru 166,166.1 and 166.2, 168,and 169

Added coverage for new display models and relo-cated material as needed.

All Models

RepairPage 203 Added view of new units.

All Models

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Page T−1Basic Issue: Aug 29/03

Revision 4: May 14/1034-61-16

GEK 117273

CAGE CODE: 35351

For Europe, Africa, India and For Asia, Australasia and the Pacific For the AmericasMiddle East contact: contact: contact:GE Aviation GE Aviation GE AviationCustomer Services − Cheltenham 3 Hakea Street Customer Services − ClearwaterBishops Cleeve, Cheltenham, Brisbane Airport, QLD4007, P.O. Box 9013, Clearwater, FL 33758Glos. GL52 8SF, United Kingdom Australia United States of AmericaT: + 44 (0)1242 673355 T: + 61 7 3860 0700 T: + 1 (727) 539 1631F: + 44 (0)1242 669165 F: + 61 7 3860 0701 F: + 1 (727) 539 0680

Global Contact: [email protected]

MAINTENANCE BITE MANUAL

FLIGHT MANAGEMENT COMPUTER SYSTEMMAINTENANCE BITE MANUAL

(737 UPDATE 10.4A AND LATER)

UNITS COVERED BY THIS MANUAL

MODEL NO. BOEING PART NO. PART NO.

2907A4 10−62225−003 171497−05−01

2907C1 10−62225−004 176200−01−01

2584A SERIES S242A600 SERIES 174101 SERIES

Copyright (2010), GE Aviation Systems LLC, U.S.A.

The information contained in this document is GE Aviation Systems LLC proprietary information and is disclosed in confidence. It is the property ofGE Aviation Systems LLC and shall not be used, disclosed to others or reproduced without the express written consent of GE Aviation SystemsLLC, including, but without limitation, it is not to be used in the creation, manufacture, development, or derivation of any repairs, modifications,spare parts, design, or configuration changes or to obtain FAA or any other government or regulatory approval to do so. If consent is given forreproduction in whole or in part, this notice and the notice set forth on each page of this document shall appear in any such reproduction in whole orin part.

Destination Control StatementThis technical data is considered ITAR and/or EAR controlled pursuant to 22 CFR Part 120-130 and 15 CFR Parts 730-774 respectively.

Transfer of this data by any means to a non-U.S. Person, whether in the United States or abroad, without the proper U.S. Governmentauthorization (e.g., License, exemption, NLR, etc.), is strictly prohibited. ECCN#: 7E994, NLR

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GE Proprietary Information − subject to the restrictions on the cover or first page. 34-61-16

RECORD OF REVISIONS

REV

NO.

ISSUE

DATE

DATE

INSERTED

BY REV

NO.

ISSUE

DATE

DATE

INSERTED

BY

1 Sep 14/07 Sep 14/07 Smiths

2 Apr 3/09 Apr 3/09 GE

3 Jun 19/09 Jun 19/09 GE

4 May 14/10 May 14/10 GE

RETAIN THIS RECORD IN THE FRONT OF MANUAL OR CHAPTER.ON RECEIPT OF REVISIONS, INSERT REVISED PAGES INTO MANUAL AND ENTER DATE INSERTED ANDINITIALS.

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REV

NO.

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DATE

DATE

INSERTED

BY REV

NO.

ISSUE

DATE

DATE

INSERTED

BY

RETAIN THIS RECORD IN THE FRONT OF MANUAL OR CHAPTER.ON RECEIPT OF REVISIONS, INSERT REVISED PAGES INTO MANUAL AND ENTER DATE INSERTED ANDINITIALS.

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LIST OF EFFECTIVE PAGES

Total number of pages in this publication is 169 consisting of the following:

SUBJECT PAGE DATE SUBJECT PAGE DATE

0 Title T--1 May 14/10

1 Record of Revisions 1 Aug 29/03

2 2 May 14/10

3 Record of Temporary 1 Aug 29/03

4 Revisions 2 May 14/10

5 List of Effective Pages 1 May 14/10

6 2 May 14/10

7

3 May 14/108 4 May 14/10

9 Contents 1 May 14/10

10 2 Aug 29/03

11 3 May 14/10

12 4 Sep 14/07

13 5 Aug 29/03

14 6 May 14/10

15 Introduction 1 May 14/10

16 2 May 14/10

17

3 May 14/1018 4 May 14/10

19 5 May 14/10

20 6 May 14/10

21 7 May 14/10

22 8 May 14/10

23 Description and 1 May 14/10

24 Operation 2 May 14/10

25 3 Aug 29/03

26 4 May 14/10

27 5 Aug 29/03

28 6 May 14/10

29 7 May 14/10

30 8 Aug 29/03

31 9 Aug 29/03

32 10 Aug 29/03

33 11 Aug 29/03

34 12 Aug 29/03

35 13 Aug 29/03

36 14 May 14/10

37 15 May 14/10

38 16 May 14/10

39 17 May 14/10

40 18 May 14/10

41 18.1 May 14/10

42 18.2 May 14/10

43 19 May 14/10

44 20 Jun 19/09

45 21 Jun 19/0946 22 Jun 19/09

47 23 Jun 19/09

48 24 Jun 19/09

49 25 May 14/10

50 26 Jun 19/09

51 27 Aug 29/03

52 28 May 14/10

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54 30 May 14/10

55 31 Aug 29/03

56

32 Aug 29/0357 33 Aug 29/03

58 34 May 14/10

59 35 May 14/10

60 36 May 14/10

61 37 May 14/10

62 38 May 14/10

63 38.1 May 14/10

64 38.2 May 14/10

65 39 Aug 29/03

66 40 Sep 14/07

67 41 Sep 14/07

68 42 May 14/10

69 43 Aug 29/03

70 44 Aug 29/03

71 45 Aug 29/03

72 46 Aug 29/03

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76 50 Aug 29/03

77 51 Aug 29/03

78 52 May 14/10

79 Maintenance BITE 101 Aug 29/03

80 Pages 102 Aug 29/03

81 103 Aug 29/03

82 104 Aug 29/03

83 105 Aug 29/03

84 106 May 14/10

85 107 Aug 29/03

86 108 Aug 29/03

87 109 Aug 29/03

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110 Aug 29/0389 111 Aug 29/03

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91 113 Aug 29/03

92 114 Aug 29/03

93 115 Aug 29/03

94 116 Aug 29/03

95 117 Aug 29/03

96 118 Aug 29/03

97 119 Aug 29/03

98 120 Aug 29/03

99 121 Aug 29/03

100 122 Aug 29/03

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102 124 Aug 29/03

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107 129 Aug 29/03

108 130 Aug 29/03

109 131 Aug 29/03

110 132 Aug 29/03

111 133 Aug 29/03

112 134 Aug 29/03

113 135 Aug 29/03

114 136 Aug 29/03

115 137 Aug 29/03

116 138 Aug 29/03

117 139 Aug 29/03

118 140 Aug 29/03

119 141 Aug 29/03

120 142 Aug 29/03

121 143 Apr 3/09

122 144 Aug 29/03

123 145 Apr 3/09

124 146 Apr 3/09

125 146.1 Apr 3/09

126 146.2 Apr 3/09

127 147 Sep 14/07

128 148 Aug 29/03

129 149 Aug 29/03

130 150 Apr 3/09

131 151 May 14/10

132 152 Aug 29/03

133 153 Aug 29/03

134 154 Aug 29/03

135 155 Aug 29/03

136 156 Aug 29/03

137 157 Aug 29/03

138 158 Aug 29/03

139 159 Aug 29/03

140 160 Aug 29/03

141 161 Aug 29/03

142 162 May 14/10

143 162.1 May 14/10

144 162.2 May 14/10

145 163 May 14/10

146 164 May 14/10

147 165 May 14/10

148 166 May 14/10

149 166.1 May 14/10

150 166.2 May 14/10

151 167 Aug 29/03

152 168 May 14/10

153 169 May 14/10

154 170 Aug 29/03155 171 Aug 29/03

156 172 Aug 29/03

157 173 Aug 29/03

158 174 Aug 29/03

159 175 Aug 29/03

160 176 Aug 29/03

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162 178 Aug 29/03

163 Repair 201 Aug 29/03164 202 Aug 29/03

165 203 May 14/10

166 204 Apr 3/09

167 205 Aug 29/03

168 206 May 14/10

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CONTENTSPage 1

May 14/10


PART OF

CHAPTER 34

TABLE OF CONTENTS

SUBJECT PAGE

FLIGHT MANAGEMENT COMPUTER SYSTEM MAINTENANCE BITE MANUALINTRODUCTION

Scope 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Terminology 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Manual Layout 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Abbreviations, Symbols, and Acronyms 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DESCRIPTION AND OPERATION

Introduction 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Flight Management Computer System 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Aircraft Types 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS Configurations 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS Hardware Configurations 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Operational Flight Software 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Display and Keyboard 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Display Mapping 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Page Header Line 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Primary FMC Indicator 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMC Location 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Page Number 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Data Display Area 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Flight Displays 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Maintenance Displays 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Scratch Pad 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Key Usage 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Data Entry Keys 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Alpha−Numberic Keys 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Sign Key 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Slash Key 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Spare or Space Key 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Function/Mode/Activation Selection 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Function and Mode Keys 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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SUBJECT PAGE

Activation Key 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Navigation Keys 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Data Manipulation 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Line Select Keys 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CLR Key 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DEL Key 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Annunciators 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

EXEC 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Left Annunciator Block 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DSPY/CALL 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FAIL 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Right Annunciator Block 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MSG 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OFST 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

INDEX Prompt 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Operational Index Pages 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS Maintenance BITE Index Pages 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Power−Up 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMC Power−Up 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cold Power−Up 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Perform Power−Up BIT. 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ISB Communications Check. 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OFP Validity Check 13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Warm Power−Up 13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Glitch Power−Up 13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Invalid OFP 13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Display Unit Power−Up 13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cold Power−Up 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Warm Power−Up 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Glitch Power−Up 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Invalid OFP 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Source Select Switch 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

NAV Master 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Sub−System Interfaces 15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Initial Displays 15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Normal Displays 15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Invalid CDU Mode Display 15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Failed Display Unit Indications 17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Failed FMC Indications 17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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Single FMC Installations 17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Dual FMC Installations 17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Program Pin Errors 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Service Maintenance Messages 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Crossload Operation 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OP PROGRAM INVALID Page 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CROSSLOAD Pages 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OP PROGRAM CROSSLOAD Page 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DATABASE CROSSLOAD Page 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Analog discretes and Performance Factors Mismatch 24. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Special Conditions 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Data Load Operation 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMC Loading 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Display Unit Loading 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

File System Download 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMC Fault Record 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fault Record Contents 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Label Codes 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Hardware Generated Label Code 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Software Generated Label Codes 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Monitor Codes 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Hardware Generated Monitor Code 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Software Generated Monitor Codes 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS Display Fault Record 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Unit Code 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fault Description Codes 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Extended Fault Codes 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Discretes 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Discrete Inputs Monitored on ANALOG DISC Page 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Static State Discrete Inputs 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Conditional Discrete Inputs 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Complete Discrete List 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Software Options 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMC Software Options 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS Display Unit Software Options 42. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ARINC 429 Data 42. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MAINTENANCE BITE PAGES

Accessing the Maintenance BITE Pages 101. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS Display Unit BITE 101. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMC BITE 101. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Maintenance BITE Page Maps 102. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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Maintenance BITE Descriptions 107. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMC Maintenance BITE Pages 111. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Data Loader Page 111. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Menu Page 113. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Maintenance BITE Index Page 115. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS BITE Index Page (Dual Instl.) 117. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS BITE Index Page 119. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

In−Flight Faults Page (Single Instl.) 121. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

In−Flight Faults Page (Dual Instl.) 123. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Flight Select Page 125. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Flight Number Page 127. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS CDU Test Page 129. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS Key Test Page 130. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS Display Test Page 132. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Sensor Status Page (Single Instl.) 133. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Sensor Status Page (Dual Instl.) 135. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Sensor Data Page 137. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Analog Discretes Page (Single Instl.) 139. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Analog Discretes Page (Dual Instl.) 140. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fixed Outputs Page 142. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Model/Engine Configuration Page 143. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Software Options Page (FMC) 145. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Performance Factors Page 146.1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Inertial Reference System Monitor Page 148. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Hardware Configuration Page 149. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FMCS Display Unit Maintenance BITE Pages 151. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU Maintenance BITE Index Page 151. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU BIT Display Index Page 153. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cycle XX Faults Page 154. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CDU Key Test Page 156. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU Color Test Page 157. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU Display Test Page 158. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU Configuration Page 159. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Software Options Page (CDU) 160. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU Power Supply Sensors 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU Temperature Sensors Page 163. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU Light Sensors Page 165. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU Lamp Test Page 167. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CDU Calibration Page 168. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Alternate Navigation Fixed Outputs Page (UPDATE 2 Only) 169. . . . . . . . . . . . . . . . . . . . . . . . .

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FMS Sub−System Maintenance BITE Pages 170. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Digital Flight Control System BITE Test 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Autothrottle BITE Test Page 172. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Air Data Inertial Reference System BITE Index and Test Pages 173. . . . . . . . . . . . . . . . . . . . .

Common Display System BITE Index and Test Pages 174. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Engine and Engine Exceedance BITE Index and Test pages 175. . . . . . . . . . . . . . . . . . . . . . . .

Auxiliary Power Unit BITE Test Page 177. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fuel Quantity Indicating System BITE Test Page 178. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

REPAIR

Introduction 201. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LCD CDU Cleaning 201. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

File System Download 204. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Testing 204. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Replacing the FMC 204. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Replacing the FMCS Display Unit 205. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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FLIGHT MANAGEMENT COMPUTER SYSTEM (FMCS)

INTRODUCTION

1. Scope

This manual has been prepared in accordance with ATA Specification No. 100, Revision 21. It isintended for instruction in maintenance operation, checkout and system troubleshooting of theFlight Management Computer System (FMCS) while installed on the aircraft.

This document is intended as a guide for the aircraft level maintenance personnel, and may notbe all encompassing. When reference to the maintenance built−in−test−equipment (MAINTBITE) pages for other sub−systems of the aircraft is made, the technician should refer to theequivalent manual for the referenced sub−system.

2. Terminology

Some special terminology is used throughout this manual and is defined as follows:

Display Unit−

General reference to the GE Aviation display units used in the FMCS.These can be Control Display Units (CDU), Multi−Purpose ControlDisplay Units (MCDU), Future Air Navigation System (FANS) MCDUsor Alternate Navigation MCDUs (ALTNAV MCDU).

FMC − The Flight Management Computer only.

FMCS − The Flight Management Computer (FMC) plus the display units (DUs).

FMS − The Flight Management Computer System (FMCS) plus the aircraft sub−systems.

MCDUs − Refers to both MCDU and FANS MCDU.

MCDU (U2) − Refers to the ALTNAV MCDU.

The LCD CDU models are grouped and identified as follows throughout this manual to identifyfunctional differences in the two groups of models.

174101−xx−01 Units − refers to the models 2584A, 2584A1, and 2584A2(part numbers 174101−01−01, 174101−02−01,and 174101−03−01).

174101−xx−02 Units − refers to the models 2584A3, 2584A4, and 2584A5(part numbers 174101−01−02, 174101−02−02,and 174101−03−02).

3. Manual Layout

The content of this manual is divided into three sections. Section one provides a description of the FMCS and system level operations. Section 2 provides a descript ion of the FMCS MAINTBITE pages, operation of the page prompts, and a description of the data contained on them.The third refers to general maintenance and equipment replacement.

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4. Abbreviations, Symbols, and Acronyms

The following is a list of the abbreviations, symbols, and acronyms used in this manual along withtheir meanings. Abbreviat ions, symbols, and acronyms are listed in alphabetical order.

Abbreviation Meaning

± Plus or Minus

° Degrees

° C Degrees Celsius

° F Degrees Fahrenheit

A/C Aircraft

A/T Autothrott le

A/P Autopi lot

ACARS Aircraft Communications, Address ing, and Reporting System

ACARS MU ACARS Management Unit

ACK Acknowledge

ADC Air Data Computer

ALO Aloha Word

ALR Aloha Response Word

ALT Alti tude

ANG Angle

AOC Airline Operat ional Communicat ion

ANNUN Annunciator

ANP Actual Navigat ion Performance APP Approach

APTS Airports

ARINC Aeronautical Radio, Inc

ASSY Assembly

ATA Air Transport Association

ATC Air Traff ic Control

ATE Automatic Test Equipment

ATP Acceptance Test Procedure

ATS Air Traff ic ServiceBARO Barometric

BCD Binary Coded Decimal

BIT Built−In−Test

BITE Built−In Test Equipment

BK Back

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BNR Binary

BUFF Buffer

C Celsius

CAA Civil Aviation Authority

CAP Capacitor

CCU Computer Control Unit

CDS Common Display System

CDU Control Display Unit

CH or CHAN Channel

COD Coded (ARINC 429 Data)

COMM Communication

CP Control Panel

CPU Central Processing Unit

CRC Cyclic Redundancy Code

CRT Cathode Ray Tube

DAA Digital to Analog Adapter

DACK Data Acknowledge

DADC Digital Air Data Computer

DB Data Base

DEG Degrees

DEST Destination

DEU Display Electronics Unit

DFCS Digital Flight Control System

DFDAU Digital Flight Data Aquisition Unit

DISC or DISCR Discrete

DLA Display Light Assembly

DLDR Data Loader

DLU Data Loader Unit

DME Distance Measuring Equipment

DMT Deadman TimerDTG Distance To Go

E East

EADI Electronic Attitude Director Indicator

ECU Engine Control Unit

EDC or EDAC Error Correction and Detection

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EEC Electronic Engine Controller

EFC Expected Further Clearance

EFIS Electronic Flight Instrument System

EFIS CP Electronic Flight Instrument System Control Panel

EFIS SG Electronic Flight Instrument System Symbol Generator

EHSI Electronic Horizontal Situation Indicator

ENET_ Ethernet

ENG Engine

EOT End of Transmission

ESDS Electrostatic Discharge Sensitive Devices

ETA Estimated Time of Arrival

ETI Elapsed Time Indicator

F Fahrenheit

FAA Federal Aviation Authority

FACTR Factors

FANS Future Air Navigation System

Fc Foot−Candles

FCC Flight Control Computer

F/D Flight Director

FL Failure

FLT Flight

FMC Flight Management Computer

FMCS Flight Management Computer System

FMS Flight Management System

FOM Figure of Merit

FQIS Fuel Quantity Indicating System

FREQ Frequency

FUEL−SUM Fuel Summation Unit

GA Go Around

GMT Greenwich Mean TimeGND Ground

GPIRS Global Positioning Inertial Reference System

GPIRU Global Positioning Inertial Reference Unit

GPS Global Positioning System

GPSSU Global Positioning System Sensor Unit

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HYB Hybrid

HSI Horizontal Situation Indicator

Hz Hertz

I/O Input/Output

ICAO International Civil Aviation Organization

ID Identification

ILL Illegal

ILS Instrument Landing System

INERT Inertial

INH Inhibit

INST Instruction

INTEG Integrity

IP Internet Protocol

IPL Interrupt Priority Level

IRS Inertial Reference System

IRU Inertial Reference Unit

ISB Intersystem Bus

ISO International Statndard Organization

k Kilo

Kilo one thousand

lb(s) Pound(s)

L Left

LAT Latitude

LCD Liquid Crystal Display

LED Light Emitting Diode

LN Line

LNAV Lateral Navigation

LOC Localizer

LON Longitude

LRU Line Replaceable UnitLSB Least Significant Bit or Byte

LSK Line Select Key

m Mega

MAINT Maintenance

MACH Mach Number

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MAG Magnetic (North)

MBE Multiple−Bit Error

mbytes Mega−

bytes

MCDU Multi−Purpose Control Display Unit

MCP Mode Control Panel

MEDB Model Engine Data Base

MEM Memory

Mega one million

MFG Manufacturing

MICROCTL Microcontroller

MIPS Millions of Instructions Per Second

MLS Microwave Landing System

MSB Most Significant Bit or Byte

MSG Message

N North

N1 N1 Limit Mode Key

NA or N/A Not Applicable

NAV Navigation

NC Not Connected

NCD No Computed Data

ND Navigation Display

NDB Navigation Data Baseor

Non−Directional Beacon

NG New Generation Airplanes

NMI Non−Maskable Interrupt

OAT Outside Air Temperature

OFP Operational Flight Program

OP Operational

OSC Oscillator

p/o Part of

PDI Power Down Interrupt

PERF Performance

PFD Primary Flight Display

PGM Program

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POR Power On Reset

POS Position

POT Potentiometer

PPOS Present Position

PRI Primary

PROC Processor

PROG Program

PROM Programmable Read−Only Memory

PRSNT Present

PS Power Supply

PWR Power

QRH Quick Reference Handbook

R Right

RAM Random Access Memory

RCVR Receiver

RDY Ready

REF Reference

REG Register

RF Radio Frequency

ROM Read−Only Memory

RNP Required Navigation Performance

RST Reset

RTC Real Time Clock

RTP Resident Test Program

RX Receive

S South

SAL System Address Level

SAT Selected Air Temperature

SBE Single−Bit Error

SBFMC Single Board Flight Management ComputerSEC Secondary

SEL Select

SDI Source/Destination Identifier for ARINC 429 data

SID Standard Instrument Departure

SLF Self

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SOT Start of Transmission

SP or SPD Speed

SPR Spare

SRAM Static Random Access Memory

SSM Sign Status Matrix

STAR Standard Terminal Arrival Route

SUPP Supplemental

SW Software

SYN or SYNC Synchronization

SYS System

TAT Total Air Temperature

TEMP Temporary

TO or T/O Take Off

THRES Threshold

TOGA Take Off/Go− Around

TX Transmit

TX/RX Transmit/Receive

UART Universal Asynchronous Receiver Transmitter

UUT Unit Under Test

V Vertical

Vac Voltage, Alternating Current

Vdc Voltage, Direct Current

VEL Velocity

VHF Very High Frequency

VNAV Vertical Navigation

VOL Volitile

VOR VHF Omni−directional Radio−range

VRNP Vertical Required Navigation Performance

W West

W/ WithWO/ Without

WPT Waypoint

WXR Weather Radar

XMTR Transmitter

ZFW Zero Fuel Weight

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DESCRIPTION AND OPERATION

1. Introduction

This section provides an overall description of the units that make up the GE Aviation Systems LLC(doing business as GE Aviation) Flight Management Computer System (FMCS), the operation of thesystem, the required Flight Management Computer (FMC) software, and system interface with otheravionics equipment within the aircraft.

2. Flight Management Computer System

The GE Aviation FMCS is an integral part the complete Flight Management System (FMS) aboardthe Boeing 737 aircraft.

A “single” installation consists of one FMC and one or two liquid crystal display units (LCD CDUs).

A “dual” installation consists of two FMCs and two LCD CDUs. Figure 1 shows the two computers,and Figure 2 provides views of the three display units.

A. Aircraft Types

The FMCS is designed to operate in several aircraft configurations and provide varying func-tionality that may be tailored to an airline’s needs. General operational functional ity is dividedacross the Boeing 737 platform by the types of sub−systems contained within the aircraft.

The new generation group consists of the 737−600, 737−700, 737−800, and 737−900 airplanes.The sub−systems interconnected with the FMCS are as follows:

(1) Airline Communication and Reporting System (ACARS) (option)

(2) Air Data Inertial Reference System (ADIRS)

(3) Air Data Inertial Reference Unit (ADIRU)

(4) Air Data Computer (ADC)

(5) Autopilot/Flight Director System (AFDS)

(6) Autothrottle (A/T)

(7) Common Display System (CDS)

(8) Common Display System Display Electronics Unit (DEU)

(9) FMC Source Select Switch (Dual FMC Installations)

(10) Fuel Quantity Indicator System (FQIS)

(11) Global Positioning System (GPS) (option)

(12) GMT Clock

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(13) Mode Control Panel (MCP)

(14) Multi−Mode Radio (MMR)

(15) Printer (option)

B. FMCS Configurations

The FMCS may be configured with different equipment and software options depending on thefunctionality desired.

Software Options are available to the airline to alter the Operational Flight Program (OFP) op-eration and enable functional features of the FMS.

The FMCs may be any combinat ion of GE Aviation Model 2907A4 and 2907C1 computers. In adual configuration, both FMCs must have the same version of the OFP loaded in order to func-tion correctly. The crossload function will force this to happen if a computer is changed and itcontains a different version. The display units may be mixed as desired, however, at least oneunit must be an MCDU or FANS MCDU to allow the ACARS MU to control and ut ilize the dis-

play, and at least one unit must be a FANS MCDU to access the ATC function.

NOTE: When ACARS is activated in the airplane, any display unit (CDU, MCDU, FANSMCDU) will provide the ACARS prompts, and the prompts will function correctly.

(1) FMCS Hardware Configurations

The components listed below are all compatible with each other and will operate in bothsingle or dual system configurations, with any combination of units. Legal certified con-figurations are determined by the Boeing Company, and they should be contacted for ver-ification.

NOTE: When interchanging different units in a configuration, some functionality maybe unavailable to the users due to various versions of the software that may

be loaded.

NOMENCLATURE GE MODEL NO BOEING P/N

Flight Management Computer 2907A4 10−62225−003

Flight Management Computer 2907C1 10−62225−004

Control Display Unit* 2584A S242A600−1001

Control Display Unit** 2584A3 S242A600−1002

Multi−Purpose Control Display Unit* 2584A1 S242A600−2001

Multi−Purpose Control Display Unit** 2584A4 S242A600−2002

FANS Multi−Purpose Control Display Unit* 2584A2 S242A600−3001

FANS Multi−Purpose Control Display Unit** 2584A5 S242A600−3002

* These units may have LCD CDU Update 1 or LCD CDU Update 2 software loaded.

** These units will have LCD CDU Update 3 software loaded.

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2907A4 2907C1

Flight Management ComputersFigure 1

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CDU MCDU FANS MCDU

LINE SELECT KEYS(R1 THRU R6) (L1 THRU L6)

EXECUTE KEY

BRIGHTNESSCONTROL KNOB

RIGHT ANNUNCIATOR LEFT ANNUNCIATOR

ALPHA KEYS(SQUARE)

NUMERIC KEYS

(ROUND)

FUNCTION/MODE KEYS(RECTANGULAR)

BLOCK BLOCK

TITLE PAGE NO

OPS DATA LINE 1 / MAINT LINE 3

FMC





SCRATCH PAD

OPS HEADER LINE 1 / MAINT LINE 2







Liquid Crystal Display UnitsFigure 2

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(2) Operational Flight Software

This manual covers the equipment listed above when the FMCs are loaded with OFP Up-date version 10.4A (Boeing Part Number 549849--011) or later. When Model 2907A4FMCs are loaded with an earlier version, a crossload operation will be forced.

NOTE: The Model 2907C1 FMC cannot be loaded with OFP Update versionsU7/U8 Series or U10.3 and earlier.

3. Display and Keyboard

A. Display Mapping

The display area (regardless of the model in use) is mapped to provide distinct information tothe FMCS operator.

(1) Page Header Line (Ref. Figure 3)

The page header line will display the Primary FMC indicator, the selected FMC location,

page title, and, if applicable, page number of the page currently displayed.

(a) Primary FMC Indicator

The first position of the page header line is the Primary FMC indicator arrow. ThePrimary FMC indicator is an arrow symbol displayed only on the MAINT BITEpages. It is used to show the operator which FMC is the designated master as setby the FMC Source Select Switch. Regardless of which FMC is selected to viewthe maintenance pages, it will point to the primary. This indicator is only displayedin dual configurations.

PRIMARY FMCINDICATOR

HEADER LINE PAGE NUMBER

DATA DISPLAY AREA

SCRATCH PAD

DUAL FMC

ONLY( )

FMC LOCATION

Display Data MappingFigure 3

(b) FMC Location

BITE data is stored individually in each FMC. Most of the MAINT BITE pages pro-vide the operator with the source of the data via the FMC location indicator. Theformat displayed will vary depending on the page selected. The following are thedifferent types of indicators used.

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1 Single FMC installations will display one of the following:

FMCS or blanked

2 Dual FMC installations will display one of the following:

FMCS

FMC−L or FMC−R

LT or RT

(c) Page Number

Many MAINT BITE pages have multiple displays or are capable of having multipledisplays due to the quantity of data available. When this occurs, the page numberarea will show the page number currently displayed/total pages available (i.e., 2/4).

(2) Data Display Area

Data and selection prompts pertinent to the page title are displayed in this area. The fol-lowing general guidelines are used unless specified in the MAINT BITE Page Descrip-tions (Section 2) for a specific display page.

(a) F light Displays

1 Header lines are displayed in small font, and in some cases may be blankedwhen the sub−system or data is not available.

2 Data fields and prompts are located next to the line select keys. Prompts areactive when the caret (< on left side or > on right side) is displayed. Promptsare used to access various data and other MAINT BITE pages or functionsfrom the current page.

(b) Main tenance Displays

Maintenance displays vary greatly as to their layout. Each page is covered in detailin Section 2.

(3) Scratch Pad

The scratch pad area displays the applicable characters when the alphanumeric keys arepressed or copied from a data field (see data manipulation below). The entered data maythen be selected to a specific data field when entries are allowable. The majority of theMAINT BITE pages do not allow entries.

B. Key Usage

The display unit keyboards have the keys grouped and located around the display according totheir function. The basic functions include; data entry, function/mode selection, and data ma-nipulation.

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(1) Data Entry Keys

(a) A lpha−Numeric Keys

The alpha−numeric keys are located on the lower half of the display unit keyboard.These include alpha keys A through Z and numeric keys 0 through 9. Pressing anyone of these keys will display the appropriate character in the scratch pad area ofthe display.

(b) Sign Key

The sign (+/−) key inserts a minus sign on the first push. Subsequent presses(prior to any other key presses) will toggle the displayed sign.

(c) Slash Key

The slash ( / ) key is used to separate dual component entries such as wind speed/ direction. The MAINT BITE pages do not require dual component entries.

(d) Spare or Space Key

On the CDU keyboard, the spare alpha key (blank key to the right of the Z key) hasno action. The MCDU and FANS MCDU keyboards have a space (SP) key in thisposition. Pressing the space key inserts a space into the scratch pad allowing thecreation of text messages for ACARS or ATC Datalink messages. On all otherpages, this key will have no affect.

(2) Function/Mode/Activation Selection

(a) Funct ion and Mode Keys

The function and mode keys are located between the display and the data entrykeys. They are primarily used to access operational pages to monitor various por-

tions of the flight.

(b) Activation Key

The EXEC key activates a flight plan after being loaded by any of the variousmeans available, and activates flight plan modifications made by the air crew.

(c) Navigation Keys

The previous/next (PREV PAGE/NEXT PAGE) keys are used to navigate the dis-play pages when multiple pages exist. These keys work in a circular manner, i.e.,pressing NEXT PAGE from the last page displays the first page, and pressingPREV PAGE from the first display displays the last page.

(3) Data Manipulation

The data manipulation keys allow copying, moving, deleting data, and clearing advisorymessages.

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(a) Line Select Keys

The 12 keys on the top of the display unit keyboard (six per side) are the line selectkeys. These keys provide access to other pages via prompts when available, allowentering data into an editable field from the scratch pad, and copying displayeddata to the scratch pad. In this manual the term “line select” is used to refer to theuse of these keys. When a specific line select key is required, the key is referred toas line select key (LSK), the key number (1 through 6) referenced from the top keyin the row, and the left or right side of the display unit (L or R).

(b) CLR Key

The clear (CLR) key is used to clear the display scratch pad. A brief press willclear an advisory message displayed, or the last character of a manual entry. De-pressing and holding the CLR key will completely clear a manual entry from thescratch pad.

NOTE: The CLR key will only clear the top message in the message queue re-gardless of how long its depressed. As each message is cleared, the

next one appears when multiple messages are queued.

(c) DEL Key

The delete (DEL) key is used to delete entries in data fields. Pressing the DEL keybriefly places the word “DELETE” into the scratch pad. The scratch pad may thenbe line selected to the desired field. After deletion, the field returns to the defaultvalue or is blanked when a default value is not assigned to the field. When a field isselected that is not editable, the message “INVALID DELETE” is displayed in thescratch pad.

For the MCDU and FANS MCDU, the DEL key has a second function. Pressingand holding the DEL key for at least one second (referred to as the long deletefunction) will suspend ACARS and ATC Datalink uplink messages.

C. Annunciators

There are five annunciators located on the display panel; EXEC, DSPY/CALL, FAIL, MSG, andOFST.

(1) EXEC

The execute (EXEC) annunciator is located just above the EXEC key. This annunciator islit when a route is first entered or when changes are made to the active flight plan (includ-ing uplink data). Pressing the EXEC key activates the flight plan or incorporates thechanges.

(2) Left Annunciator Block

The left annunciator block contains two annunciators.

(a) DSPY/CALL

The top left annunciator on the CDU is DSPY (display). This annunciator is cur-rently not in use, and should only light during annunciator tests.

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The top left annunciator on the MCDU and FANS MCDU is CALL. This annunciatorlights when another sub−system in the FMS group requests control of the displayunit, and during annunciator tests.

(b) FAIL

The bottom left annunciator is FAIL. This annunciator lights when the primary FMChas failed, and during annunciator tests.

(3) Right Annunciator Block

The right annunciator block contains two annunciators.

(a) MSG

The top right annunciator is MSG (message). This annunciator lights when the dis-play unit receives an alerting message from the FMC and has it displayed in thescratch pad. When the message(s) is(are) cleared, the annunciator turns off.

(b) OFST

The bottom right annunciator is OFST (offset). This annunciator is only active inMCDU and FANS MCDU, and lights when a lateral offset is active. For all displayunits, this annunciator lights during annunciator tests.

D. INDEX Prompt

The INDEX prompt is displayed on many of the operational and Maintenance BITE pages. It isalmost always located at line 6 left (select using LSK 6L). The function of the INDEX prompt isto quickly return the operator to the next higher level index page.

(1) Operat ional Index Pages

(a) INIT/REF INDEX page − provides access to all operational areas including themaintenance BITE pages while on the ground.

(b) DEP/ARR INDEX page − provides access to the available departures and arrivals.

(c) ATC INDEX page − provides access to all of the ATC Datalink pages.

(2) FMCS Maintenance BITE Index Pages

(a) ADIRS BITE INDEX − provides access to the ADIRS test pages.

(b) CDS BITE INDEX − provides access to the CDS test pages.

(c) CDU BIT DSPLY INDEX − provides access to the power up cycles that contain dis-play unit BIT failures.

(d) CDU MAINT BITE INDEX − provides access to the FMCS display unit BITE pages.

(e) ENGINE/EXCEED BITE INDEX − provides access to the engine BITE test pages.

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(f) FMCS BITE − provides access to the individual FMC MAINT BITE INDEX page,provides FMC status, and provides access to the crossload pages (dual installa-tions only).

(g) IRS BITE INDEX − provides access to the IRS test pages.

(h) Maint BITE INDEX − provides access to the FMC maintenance BITE pages.

The INDEX prompt on a page will bring the operator to the index page used to get to the currentdisplay.

4. Power−Up

A. FMC Power−Up

The FMC firmware and software will perform power−up processing based on the type of power−up (cold, warm, or glitch) condition detected. In all cases when power is first applied, the FMCVALID discrete is set to the invalid state, the FMC FAIL discrete is set to the failed state, andthe ARINC Channels are disabled. These will remain in this state until all of the power−up test-

ing has been successfully completed.

(1) Cold Power−Up

A cold power−up is performed when any of the following conditions are detected by theFMC:

The FMC was receiving a crossload when it was reset or powered down.

The FMC machine state data stored in capacitor backed RAM from the last powerdown is not valid.

There has been a power loss of greater than 10 seconds (nominal) while on the ground.

The FMC then executes the following steps in the order listed.

(a) Perform Power−Up BIT

Power−up testing is performed automatically by the FMC firmware and software.All hardware within the FMC is tested for proper operation and functionality. Eachtest will continue to loop until it passes. When a test fails a major hardware area,the FMC hangs and never goes valid.

(b) ISB Communicat ions Check

In dual installations, after the hardware tests have successfully completed, theFMC attempts to establish communication with the second FMC.

1 A Model 2907A4 computer always attempts communication over the RS−422ISB channel.

2 A Model 2907C1 computer first attempts communication over the ISB Ethernetchannel. If successful, the FMC assumes it is working with another 2907C1computer and begins running at the higher internal processor speed (30 MHz).If communication on the ISB Ethernet channel is unsuccessful, the ISB

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RS−422 channel is attempted. If successful, the FMC begins running at thelower internal processor speed (20 MHz).

(c) OFP Va lidit y Check

A checksum check is performed to verify a valid executable OFP is available, thencontrol is transferred to the OFP and the FMC begins operating. The OFP staticdata is not preserved, and begins updating again. When communications withanother FMC could not be established, and the failure was not attributed to a failedchannel, the OFP assumes single FMC operational mode.

(2) Warm Power−Up

A warm power−up is performed when the FMC machine state data stored in capacitorbacked RAM from the last power down is valid after a power loss of greater than 10 sec-onds in flight or the reset was caused by a deadman timer (DMT) reset.

A warm power−up is identical to a cold power−up except that the RAM tests are omitted,and OFP static data is preserved and reused, allowing the flight plan to be used as it was

originally loaded and modified.

(3) G litch Power−Up

A glitch power−up is performed after a short duration power loss (10 second or less) witha saved machine state.

If the power−up type is determined to be glitch, the FMC restores the state of the systemas it was prior to the power loss, re−synchronizes the real time clock, and restarts the ap-plication from the point of power loss.

(4) Invalid OFP

When the OFP is not valid, two indications may be displayed on the display units. One

indication is the INVALID OP PROGRAM display in a single FMC configuration.

In a dual FMC configuration while on the ground, the CROSSLOAD PAGE is displayed ifone of the two FMCs contains a valid OFP, or the INVALID OP PROGRAM display if neth-er FMC contains a valid OFP. The FMC monitors the data loader discretes to check whena data loader is connected (Data Loader Operation is covered later).

In a dual FMC configuration while in the air, the first indication of an FMC going invalid ishalf of the cockpit displays blanking. When the FMC Source Select switch is changed tothe valid FMC, it will operate in single FMC mode, and re−establish all of the displays.

B. Display Unit Power−Up

The display unit software will perform power−up processing based on the type of power−up(cold, warm, or glitch) condition detected. In all cases when power is first applied, the key-board, annunciators and ARINC channels are disabled, and the CDU FAIL discrete is set to thefail condition. These will remain in this state until all of the power−up testing has been success-fully completed.

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(1) Cold Power−Up

The display unit will perform a cold power−up whenever the power has been removed formore than 10 seconds. The initialization software verifies the integrity of the OFP by per-forming a checksum check, and when valid, begins operating. The OFP determines whatmode the display is to operated as, enables the ARINC channels, and informs the FMC ofthe display mode (CDU, MCDU, or FANS MCDU). The five annunciators will flash brieflyto inform the operator that start up is complete. The display unit will then display a flightpage.

(2) Warm Power−Up

In the 174101−xx−01 units, the display unit will perform a warm power−up in one of twoways determined by the duration of the power outage. When the power outage is lessthan 10 seconds and more than 200 milliseconds, the initialization software checks themachine state stored in memory at shut down. If the machine state is valid, the OFP isexecuted, and the display unit displays the last page preserved in memory (requiresapproximately 7 seconds). When the duration of the power outage is between 200 milli-seconds and 50 milliseconds, the operator will notice a flicker in the display, and possibly

a page change. The 174101−xx−02 units will return to operation immediately.

(3) G litch Power−Up

The display unit will perform a glitch recovery operation when the duration of the poweroutage is less than 50 milliseconds. The operator will not notice the restart; however, inthe 174101−xx−02 units, there may be a brief change to the display brightness.

(4) Invalid OFP

When power up testing determines that the OFP is not valid, two indications are providedon the display unit; the display screen is blanked, and the FAIL annunciator is blinked.Blinking the FAIL annunciator indicates that the display unit is still alive and just requiresan operating program to be loaded. The display unit monitors the data loader discretes to

determine when a data loader is connected (Data Loader Operation is covered later).When the FAIL annunciator does not blink, the display unit is non−operational and re-quires replacement.

When the display unit completes the power−up cycle, the five annunciators are flashed to pro-vide the operator with an indication that the display unit is completing start−up.

C. Source Select Switch (Dual Installations Only)

The FMCS may be in any configuration when first checked. Several factors are required tomake a complete determination. First, know the position of the FMC Source Select Switch.This determines who’s who in the configuration set−up.

(1) NAV Master

Regardless of the type of airplane (Classics or NGs) the system is installed in, when theFMC Source Select Switch is in NORMAL or BOTH ON L position, the left FMC (FMC−L)is the navigation master and and the primary. The right FMC (FMC−R) is the secondary.When the FMC Source Select Switch is in BOTH ON R, FMC−R becomes the navigationmaster and FMC−L becomes the secondary.

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During flight, both FMCs compute a navigation solution simultaneously. The primaryFMC picks Navaids from the available Navaid list for itself and assigns Navaids to thesecondary FMC. The two navigation solutions are continuously being compared. Whenthe solutions are too far apart, the NAV master instructs the follower to perform a restartand recompute the navigation solution. This is allowed to happen three consecutivetimes before the primary FMC declares the follower FMC failed and drops to single mode.Under these conditions the FMCS display unit will have displayed the message SINGLEFMC OPERATION in the scratch pad.

This action does not necessarily indicate a failed FMC. This means the FMC solutionsdiffered by more than the allowable tolerance. This could be caused by bad data fromother FMS sources.

(2) Sub--System Interfaces

The FMC Source Select Switch also determines which FMC communicates with whichsub--systems.

(a) FMC Source Select Switch is in the NORMAL position.

1 All left side sub--systems interface with the left FMC.

2 All right side sub--systems interface with the right FMC.

3 The Data Loader, ACARS MU, and both CDUs interface with the left FMC.

(b) FMC Source Select Switch is in the BOTH ON L position.

1 All sub--systems interface with the left FMC.

2 The Data Loader, ACARS MU, and both CDUs interface with the left FMC.

(c) FMC Source Select Switch is in the BOTH ON R position.

1 All sub--systems interface with the right FMC.

2 The Data Loader, ACARS MU, and both CDUs interface with the right FMC.

5. Initial Displays

The are several types of displays that may be viewed when first entering the airplane cockpit.These displays will provide some initial insight into the health of the FMCS.

A. Normal Displays

The FMCS may display any number of pages depending on events that occurred and the FMCS

configuration. Figure 4 provides examples of some of the displays the ground crew might seewhen the system is operational.

B. Invalid CDU Mode Display

When a display unit has an INVALID CDU MODE display showing (ref Figure 5 and 5A), itmeans the unit doesn’t know what type of display (CDU, MCDU, FANS MCDU) it should be.Based on the type of keyboard present, and the type of display unit, select the appropriateprompt (LSK 2L, 3L, 4L, or 2R, 3R, 4R) to initialize the display unit in the correct mode. When

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the prompt is highlighted, select the EXIT prompt (LSK 6L) to continue to the normal displays.This display is not entered unless there is a problem with the display unit or keyboard, and acold power--up was performed.

POS I N I T 1 / 3

L A S T P O S

N 4 1 ° 5 7 . 9 W48 7 ° 54 . 3R E F A I R P O R T

KORD N 4 1 ° 5 8 . 7 W48 7 ° 54 . 2G A T E

-- -- -- -- --S E T I R S P O S

° . ° .G M T - M O N / D Y S E T I R S H D G

1 3 5 7 . 2 Z 4 6 / 1 7 -- -- -- °

-- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --

ANY SYSTEM C ONFIGURATION ANY AIRCRAFT TYPE

ANY FLIGHT PAGE MAY BE DISPLAYED

MENU

< FMC <ACT >

< AC AR S < H LD >

<DFDAU

ACAR S<LOGOFF

MCDU OR FANS MCDU WITH UPDATE 1 ANY AIRCRAFT TYPE

(ACARS OPTION ENABLED)

MENU

< FMC <ACT >

< AC AR S < H LD >

<DFDAU

ACA RS<A L T NAV LOGOFF >



Normal Displays

Figure 4

I N V A L I D C D U M O D E

S E L E C T D E S I R E D M O D E

C D U

< M C D U

< F A N S M C D U

< E X I T



< C D U

< M C D U

< F A N S M C D U

CURRENT FLIGHT PAGE MENU PAGE

SELECT THEDESIRED MODE



< C D U

M C D U

< F A N S M C D U

< E X I T



< C D U

< M C D U

F A NS M C DU

< E X I T

174101--xx--01 Unit Invalid CDU Mode DisplayFigure 5

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W I T H P O T W I T H B R T K E Y

< C D U C D U >

< M C D U M C D U >

< F A N S M C D U F A N S M C D U >

THE OPERATION OF

THIS PAGE IS THE

THIS SIDE IS DISPLAYED

BUT CURRENTLY NOT USEDSAME AS PREVIOUSLY DESCRIBED

174101−xx−02 Unit Invalid CDU Mode DisplayFigure 5A

The display unit will function at this point, however, this is an indication of a problem with thekeyboard, keyboard connector, or display unit keyboard interconnect wiring and needs to beinvestigated. Repairs may need to be performed on the display unit.

The selected operating mode will remain functional until the next cold power−up. If a problemcontinues to exist, the INVALID CDU MODE page will again be displayed.

C. Failed Display Unit Indications

When the display unit is blanked, annunciators are dark, and the keyboard is not lit up, verifypower is applied.

When a display unit fails, the ARINC channels are disabled, the display is blanked and the key-board backlights are lit.

D. Failed FMC Indications

Depending upon the FMCS configuration, a failed FMC indication could take several forms.Note that as previously stated in paragraph (2), both display units are driven by the primaryFMC. When both of the display units are the same type, the displays will be the same. If a mixis present, the displays may be different. Figure 6 provides some examples of failed FMC indi-cations.

(1) Single FMC Installat ions

In single FMC installations that include an MCDU, the MENU page is provided to view thedisplays user list. A failed FMC will cause the FMC prompt at LSK 1L to be blanked (refFigure 6).

NOTE: If any other subsystem fails to communicate with the MCDU, the accessprompt for that user is also blanked.

(2) Dual FMC Installations

Dual installations have several layers of functionality to sift through, however, two mainavenues of approach normally yield results in determining an appropriate action. Keep inmind that a non−operational FMC may be the result of one of the FMCs failing (hardwarefailure), or it may be that the navigation solution was not within acceptable limits.

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(a) One method to determine which FMC is not operating is to observe the position of the FMC Source Select Switch:

1 With any normal flight operating page displayed, the message “SINGLE FMCOPERATION” displayed in the scratch pad, and;

The Source Select Switch is BOTH--ON--R -- the left FMC is not operating.

The Source Select Switch is BOTH--ON--L or NORMAL -- the right FMC is notoperating.

2 With the display unit indicating a failed FMC and;

The Source Select Switch is BOTH--ON--L or NORMAL -- the left FMC is notoperating.

The Source Select Switch is BOTH--ON--R -- the right FMC is not operating.

MENU

< AC AR S < H LD >

<DFDAU

ACA RS<LOGOFF


ACARS OPTION ENABLEDSINGLE FMC

MENU

< FMC <ACT >

< AC AR S < HL D >

<DFDAU

ACAR S<LOGOFF


ACARS OPTION ENABLED

FMC

CDU ANY AIRCRAFT TYPE

DUAL FMC

MENU

< FMC <ACT >

< AC AR S < H LD >

<DFDAU

ACA RS<A L T NAV LOGOFF >


ACARS OPTION ENABLEDDUAL FMC

Failed FMC IndicationsFigure 6

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(b) Another method to determine which FMC is failed is to enter the maintenance BITEpages:

1 Select the INIT/REF INDEX page (select INDEX prompt (LSK 6L) on anypage).

2 On INIT/REF INDEX page − select the MAINT prompt (LSK 6R).

3 On MAINT BITE INDEX page − select the FMCS prompt (LSK 1L).

4 On FMCS BITE index page − failed FMC prompt indicates BITE INOP.

(c) When the CROSSLOAD page is displayed, one of the FMCs has a corrupted OFP/ database(s) or database(s) are not loaded. Follow the instructions on the displayto perform the crossload operation (also covered later).

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E. Program Pin Errors

Many discrete input pins are connected to the FMCs and display units at the aircraft connectors.Some of the discretes are used to inform the FMCS units what position they are installed at (leftor right), what options are installed in the airplane (ACARS, EFIS, GPS, etc.), and a group ofdiscretes are used to inform the FMCS of the airplane model and engine type configuration.This last group are referred to as the program pins. The program pins are read at cold power−up to allow the OFP to be configured for the aircraft/engine model. Note that because the pro-gram pins are only read during a cold start−up, this problem may not be detected until this hap-pens.

When the IDENT page is displayed, the MODEL/ENG RATING fields are blanked, and the mes-sage “PROGRAM PIN ERROR” (classic airplanes) or “PROGRAM PIN NOT IN DB” (NG air-planes) is displayed in the scratch pad, the following should be checked:

(1) A parity error for the Airframe/Engine program pin configuration at the FMC connectorhas been detected.

(2) The Airframe/Engine program pin configuration is invalid (classic airplanes).

(3) The Airframe/Engine program pin configuration is not contained in the loaded Perfor-mance Database (NG airplanes).

F. Service Maintenance Messages

For 174101−xx−01 units only.

There is one service maintenance message that may appear in the scratchpad area of theMCDU either at power up or during normal operation. The ”SERVICE BACKLIGHT SOON”message indicates the MCDU Backlight Assembly is reaching the end of its useful life and mayfail soon. If this message is displayed, the MCDU should be removed and repaired as soon aspossible.

6. Crossload Operation

A mismatch condition can only occur in a dual installation, and can only be corrected while the air-plane is on the ground. If a mismatch condition occurs while in the air after an FMC restart, the dualoperation is suspended (SINGLE FMC OPERATION displayed in display unit scratch pad).

The CROSSLOAD pages are the primary pages used to resolve program and database mismatchconditions. Discrete mismatch problems may not be readily correctable using the crossload opera-tion. Repairs may be required.

At power−up, the designated primary FMC requests data configuration information from the secon-dary FMC and compares it to its own information. When this data does not match, a mismatch con-dition is declared and an appropriate maintenance BITE page is displayed.

A mismatch condition will be declared when the following types of information are not the same inboth FMCs:

OFPs are not the same version (or not loaded in one FMC).

Databases are not the same (or not loaded in one FMC).

Airplane configuration discrete inputs do not match.

Performance parameters are not the same (or not loaded in one FMC).

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Mismatch conditions are prioritized for correction and queued when multiple mismatches exist. Aseach selection of the NEXT MISMATCH prompt (LSK 6L) is made, each mismatch type is identifieduntil all mismatch conditions are corrected. In the case of airplane configurat ion discretes, wiringand connector repairs may have to be performed before the mismatch condition can be cleared up.

The crossload operation also allows the crew to reload the second FMC without having to connectthe dataloader or get the disk set when one of the FMCs contains a valid OFP and databases.Crossloading provides a time savings because FMC−to−FMC transfers are much faster. When up-dating the software to a new version, use the dataloader to load the primary FMC, then use thecrossload function to load the secondary FMC. The CROSSLOAD page may be manually selectedfrom the dual FMCS BITE index page (ref Section 2, page 117).

A. OP PROGRAM INVALID Page

The OP PROGRAM INVALID page is automatically displayed as follows:

(1) In single FMC installations (ref Figure 7) when the OFP is declared invalid during BITtesting. The FMC must be manually loaded using a data loader and disk set.

OP PROGRAM I NVA L I D

SINGLE FMC INSTALLATION

OP PROGRAM INVALID Page − Single FMCFigure 7

(2) When the primary FMC in a dual installation (ref Figure 8) contains a corrupted OFP thedisplay unit will automatically display the OP PROGRAM INVALID page. IF the secon-dary FMC reports it’s OFP is valid, a crossload operation is enabled.

NOTE: This will also occur if the Source Select Switch position is changed, and thenewly selected primary FMC’s OFP is invalid and the other FMC’s OFP is val-id.

The OP PROGRAM INVALID page allows the crew to correctly set up the crossload op-eration. The crossload always transfers left FMC−to−right FMC, which means that theSource Select Switch may need to be changed when the desired FMC is selected. Whenchanges are required, instructions are displayed for the operator to follow.

After the required setup complete, the crossload operation will continue with the OPPROGRAM CROSSLOAD page.

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B. CROSSLOAD Pages

Two crossload pages are provided to perform the crossload operation.

NOTE: During a crossload operation, both display units will show the crossload page andother operations are not allowed.

OP PROGRAM I N VA L I D

SE T FMC SOURCE SE LECTTO BOTH−ON−R

DUAL FMC INSTALLATION

OP PROGRAM I N VA L I D

PRIMARY FMCDETERMINESOFP INVALID

SECONDARY FMCREPORTS OFP

VALID

NORMAL

BOTH−ON−R

FMC SOURCE SELECT

BOTH−ON−L

MASTER

TO OP PROGRAM CROSSLOAD PAGE

CHANGE SWITCHPOSITION

DISPLAYS

FMC−L IS PRIMARY AND FMC−R IS VALIDTO BOTH−ON−R

FMC−R IS PRIMARY AND FMC−L IS VALIDTO NORMAL

BOTH FMC−L AND FMC−R ARE INVALIDBLANKED

OP PROGRAM INVALID Page − Dual FMCFigure 8

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(1) OP PROGRAM CROSSLOAD Page

An OFP mismatch has the highest priority, and must be performed prior to loading orcrossloading databases because this operation re−maps the FMC memory.

NOTE: Performing this operation will erase previous flight history data, fault historydata, and the file system data.

The OP PROGRAM CROSSLOAD page (ref Figure 9) is displayed automatically when:

(a) The OFPs in both FMCs are valid but different versions.

(b) The required setting changes were made while on the OP PROGRAM INVALIDpage.

² OP PROGRAM CROSSLOAD 1 / 1

L E F T

5 4 9 8 4 9 −4 1 4

C O P Y F ROM

<LEFT



< I NDEX

INDICATES FMC−L IS PRIMARY

INDICATES OFP MISMATCH INDICATES SECONDARY FMC OFPNOT LOADED OR IS INVALID

OFP CROSSLOAD PageFigure 9

The OP PROGRAM CROSSLOAD page fields are as follows:

(c) Line 1L and 1R display the OFP software part numbers. When the secondary FMC(can be left or right depending on the Source Select Switch setting) does not havean OFP loaded or the OFP is invalid, the corresponding field is blanked.

During the crossload operation, the secondary FMC software part number field isblanked. Upon successful completion of the OFP crossload, both fields will displaythe same part number.

(d) The COPY FROM line allows selection of the designated primary FMC. When thesecondary FMC contains an invalid OFP or the OFP is not loaded, the correspond-ing LEFT (LSK 5L) or RIGHT (LSK 5R) prompt will be blanked.

When the designated primary FMC is selected, the EXECute annunciator lights,and the display transitions to the crossload pending state. The LEFT and RIGHTprompts are replaced with CROSSLOAD FMC−X to FMC−Y, and the INDEX prompt(LSK 6L) is replaced with a CANCEL prompt.

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(e) Line 6L displays one of three prompts; INDEX, CANCEL, or NEXT MISMATCH.These prompts are selected using LSK 6L. This field is blanked while a crossloadoperation is in progress.

Selecting the INDEX prompt displays the FMCS BITE index page. The INDEXprompt is displayed prior to starting a crossload operation, or during the operation ifthe secondary FMC stops communicating.

Selecting the CANCEL prompt or selecting another page prior to pressing the EX-ECute button will cancel the crossload operation. Once the EXECute button ispressed, key presses are ignored.

The NEXT MISMATCH prompt is displayed when an OFP crossload is not required,but a database or discrete mismatch is detected. Selecting this prompt displaysthe DATABASE CROSSLOAD page or the ANALOG DISCRETES page as ap-propriate.

As the crossload progresses, status of the operation is displayed. CROSSLOAD INPROGRESS is displayed in field 5 during the crossload operation. Header line 6 displays

additional information pertaining to the crossload. The OFP and databases are listed aseach is crossloaded, including a record block count showing the progress. After the OFPis crossloaded the status will indicate RESTARTING OTHER FMC. The secondary FMCmust be restarted before the databases can be crossloaded.

Other possible status messages include CROSSLOAD COMPLETE (successful termina-tion), CROSSLOAD FAIL (unsuccessful termination), and CROSSLOAD UNAVAILABLE(loss of communications with secondary FMC after Crossload page was displayed).

(2) DATABASE CROSSLOAD Page

The DATABASE CROSSLOAD page allows selection of the databases to be crossloaded.This page is automatically displayed when a database mismatch is detected and bothFMCs contain a valid OFP. The fields in this page operate the same as the OP PRO-

GRAM CROSSLOAD PAGE. Only databases indicating a mismatch are listed, and onlythose selected are crossloaded.

² DATABASE CROSSLOAD 1 / 1

SW O P T I O N S

BCG− 4 4 5 − 4 5 BCG− 4 4 5 − 4 2L E F T M O D E L / E N G I N E R I G H T

BCG− 4 4 5 − 4 4 DEFAULT 4 1O

C O P Y F R O M C O P Y F R OM

<LEFT R I GHT>

< I NDEX

DATABASE CROSSLOAD PageFigure 10

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When a database mismatch or an invalid database is detected, the the primary FMC willdisplay the DATABASE CROSSLOAD page. The databases are prioritized and will cross-load in the following sequence:

Source/Destination Indicator

Software OptionsModel/Engine

Navigation Data

Performance Defaults

In addition, the following databases will be crossloaded when the software options areenabled:

QRH Takeoff Speeds

Flight Plan Data

(3) Analog discretes and Performance Factors Mismatch

After any existing program and database mismatch conditions are corrected, analog dis-crete and performance factor mismatch conditions are dealt with in that order. Whenthese mismatch conditions exist, the ANALOG DISC or PERF FACTORS pages as ap-propriate are displayed automatically with the mismatched parameter highlighted.

C. Special Conditions

Two circumstances may exist that would prevent a mismatch from being indicated:

(1) A mismatch condition is not indicated if one of the FMCs are failed.

(2) The Source/Destination Identifier discrete pins (SDI pins 1 (MP−01K) and 2 (MP−03K))fail in such a way as to make both FMCs appear to be on the same side. Should a condi-tion occur where both FMCs believe they are on the same side (both indicate left or both

indicate right), the display will show single FMC operation on each computer, and theANALOG DISC page will not indicate a mismatch condition.

7. Data Load Operation

The display units and the FMCs are both in−aircraft loadable using an ARINC 615 Dataloader. Se-lecting the desired unit and connecting the data loader begins the communicat ions link. Inserting adisk begins the loading operation.

A. FMC Loading

When an FMC is selected on the data loader panel and the data loader is connected, the displayunit displays a blank page. The DATA LOADER page (ref Figure 11) will appear when the soft-ware disk is inserted. After successful complet ion of the load operation, the DATA LOADERpage will indicate the CURRENT RECORD count equal to the TOTAL RECORDS count, LOADCOMPLETE is displayed in line 7, and OPS LOADED in line 11. Ejecting the disk at this pointcauses the FMC to perform a cold start−up.

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B. Display Unit Loading

When the FMCS display unit is selected on the data loader panel and the data loader is con-nected, the display unit displays a blank page. The DATA LOADER page (ref Figure 11) will ap-pear when the software disk is inserted. After successful completion of the load operation, theDATA LOADER page will indicate the CURRENT RECORD count equal to the TOTAL RE-CORDS count, LOAD COMPLETE is displayed in line 7, and OPS LOADED in line 11. Ejectingthe disk at this point causes the display unit to perform a cold start−up.

When a load test disk is used, all of the displays and messages are the same, and the proce-dure functions the same. Several of the messages will include “TEST” to inform the operator ofthe difference.

8. File System Download

The File System Download function is a tool to help provide continuing support and improvements tothe operating software. Each time an FMC performs a restart, system data and software data arestored in the FMC File System. This data is available to download while the airplane is on theground, providing an OFP was not loaded The data can be sent to GE Aviation for analysis (Refer

to SIL−34−49 for additional information).

DATA LOADER

CURRENT RECORD 4 4 4 4

TOTAL RECORDS 4 3 9 6

− − − − LOAD IN PROGRESS − − − −

OPS LOAD I NG

INSERT DISK INTO DATA LOADER

174101−xx−01 UNITS 174101−xx−02 UNITS

WA I T I NG FOR AR I NC

DATA LOADER

Display Unit DATA LOADER PageFigure 11

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The File System Download function should be performed whenever possible if experiencing restartsof the FMC(s). Many restarts occur because of circumstances and events other than FMCS hard-ware failures and the File System Download data can be used to help determine the cause of therestarts.

Before the download can be accomplished, floppy disks need to be formatted using the GE AviationFMCPREP.BAT PC Utility. Data will not be downloaded to any other type of disk format.

To access the File System Download function (ref Figure 12), select the INDEX prompt (LSK 6L) onany flight page where its available or press the INIT/REF key on the keyboard and select the INDEXprompt on the page that is displayed. The display shows the INIT/REF INDEX page. Select theMAINT prompt (LSK 6R) to enter the FMC’s MAINT BITE INDEX page. On the MAINT BITE INDEXpage, select the FMC DOWNLOAD prompt (LSK 6R).

Figure 13 is a flowchart style representation of the File System Download function using the dis-plays that would be seen in the cockpit.

9. FMC Fault Record

Each FMC generates a fault record each time a fault or failure is detected or reported, and when onthe ground, makes this information available to the ground crew through the Maintenance BITEpages. The (FMC−X) FLIGHT n pages and (FMC−X) SENSOR DATA pages (ref Section 2, pages127 and 137 respectively) display the fault records. Each fault record consists of two lines to identi-fy the sub−system (LRU) to which the fault or failure is attributed to, an indicator as to weather thefault/failure is considered steady or intermittent, the time of first occurrence, a fault label code and amonitor code.

Each time a fault or failure is detected, the fault records are searched for the same fault/failure al-ready recorded. The first time the fault/failure is detected a new record is generated. Subsequentfaults/failures already recorded will not have new records generated.

/

/

² FMC−L F L I GHT 2 1 / 1

3 1 − A U G − 0 1

A D I R S − L A D R S 1 8 0 7 Z

B A R O A L T 1 S S M

DATE

FIRST OCCURRENCE

MONITOR CODELABLE CODE

FLIGHT NUMBER

ORFAILED TEST

STEADY/INTERMITTENTINDICATOR

² FMC− L SENSOR DA TA 1 / 1

A D I R S − L A D R S 1 8 4 7 Z


FIRST OCCURRENCE


SUB−SYSTEM CODE

ORFAILED TEST


SUB−SYSTEM CODE

There are two main differences between the FLIGHT n pages and the SENSOR DATA pages.

When aircraft have GPS installed, the FLIGHT n pages log GPS faults as they occur. On the(FMC−X) SENSOR DATA page, the first two fault record positions (lines 3/4 and 6/7) on page 1 arereserved for GPS entries. When there are no reported problems, these lines are blank, and theirpositions are preserved.

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POS I N I T 1 / 3

L A S T P OS

N4 1 ° 5 7 . 9 W0 87 ° 5 4 . 3R EF A I R P OR T

−−−−G A T E

−−−−−S ET I R S P O S

° . ° .GM T - MO N / D Y S ET I R S H D G

1 3 5 7 . 2 Z 0 6 / 1 7 −− − °

−−−−−−−−−−−−−−−−−−−−−−−−

INITREF

I N I T / R E F I ND EX 1 / 1



<POS MSG RECAL L >

<PERF AL TN DEST>

<TAKEOFF

<A PPROACH S EL CONF I G>

<OFFSET MA I NT>

MA I NT B I T E I NDEX 1 / 1

<FMCS ENG I NE>

<DFCS APU>

<A / T FQ I S>

<ADIRS

<CDS



*

*

* AIRLINES OPTION −MAY NOT BE DISPLAYED

/

/

WILL DISPLAY ONEOF THE FLOWING PAGES

FMC S D ATA L OADER

V ER I F Y T HE F OL L OWI N G∗D ATALOAD ER IS POWER ED∗NO D I SK I N DA TA LOADER∗FOR AD L S EL EC T F MC ON

D AT A L OA D S EL EC T P AN EL

< INDEX CONT I NUE>

FMC S D ATA L OADER

V ER I F Y T HE F OL L OWI N G∗D ATALOAD ER IS POWER ED∗NO D I SK I N DA TA LOADER∗FOR AD L S EL EC T F MC ON

D AT A L OA D S EL EC T P AN EL∗SO UR CE F MC S EL EC TE D V I A

FMC SOU RC E SEL SWITC H

< INDEX CONT I NUE>

FMC S D ATA L OADER

V ER I F Y T HE F OL L OWI N G∗D ATALOAD ER IS POWER ED∗NO D I SK I N DA TA LOADER∗SEL EC T SOU RC E FMC ON

D AT A L OA D S E LE CT P AN EL∗S OURCE F MC S EL EC TE D V I A

FMC SOU RC E SEL SWITC H

< INDEX CONT I NUE>

FMC S D ATA L OADER

V ER I F Y T HE F OL L OW I NG∗D ATAL OADER IS POWER ED∗NO D I SK I N DA TA LOADER∗SEL EC T SOU RC E FMC ON

D AT A L OA D S E LE CT P AN EL

< INDEX CONT I NUE>

TO FIGURE 13

CLASSIC AIRCARFTSINGLE INSTALLATION

CLASSIC AIRCARFTDUAL INSTALLATION

NG AIRCRAFTSINGLE INSTALLATION

NG AIRCRAFTDUAL INSTALLATION

Accessing the File System Download FunctionFigure 12

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WHEN INSERTED DISK IS FORMATTED BYTHE FMCPREP.BAT PC UTILITY ANDCONTAINS NONLOADABLE DATA ORDOWNLOAD DATA FROM THE CURRENTLYSELECTED FMC.

FMC S D ATA L OADER

F MCS F I L E S YS TE MD OWNL OAD U TI L I TY

I N SE RT I N TO D AT A L OA DE RD I S K F ORMA TT ED B Y T HE

f mc p r ep PC UT I L I T Y

ORPRESS HERE TO EX I T >

FMC S D ATA L OADER


DOWNLOAD IN PROGRESSFI L ENAM.TYP

38% COMPLETE

FMC S D ATA L OADER


DOWNLOAD COMPLETE

R EMO VE D I S K T HE NPRESS HERE TO EX I T >

INDICATES PERCENT COMPLETED FOR

ENTIRE (ALL FILES) DOWNLOAD OPERATION.

WHEN INSERTED DISK IS FORMATTED BYTHE FMCPREP.BAT PC UTILITY AND DOESNOT CONTAIN DATA OR CONTAINSDOWNLOAD DATA FROM THE OTHER FMCIN A DUAL FMC INSTALLATION.

THE SELECTED FMC WILLEXECUTE A COLD START.

THE SELECTED FMC WILLEXECUTE A COLD START.

FMC S D ATA L OADER


WAR N ING: D ISK U NU SABLEOF P OR DB D I SK I NSERT ED

R EMOVE D I SK

A

FMC S D ATA L OADER


D EVIC E N OT PRESENTD I S K WA S R EMO VE D O R

I N T ER FA CE H AS F A I L E D

P RE SS HERE TO R ET RY >

NORMALCOMPLETION.

DOWNLOADFAILED.

FMC S D ATA L OADER

F MC S F I L E S YS TE MD OWNL OAD U TI L I TY

WAR N ING: D ISK U NU SABLED I S K CO NT A I N S D AT A

R EMOVE D ISK THENPRE SS H ERE T O RE TRY >

A

REMOVE DISK FROMDATA LOADER.

IF DISK INSERTED IN THE DATA LOADER IS WRITE-PRO-TECTED, THE SYSTEM WILL NOT MOVE OFF THIS PAGE.REMOVE DISK FROM DATA LOADER, SET WRITE-PRO-TECT TAB TO THE WRITE POSITION, AND REINSERTDISK INTO THE DATA LOADER.

WHEN INSERTED DISK CONTAINS ANOFP OR DATABASE.

FMC S D ATA L OADER

F MCS F I L E S YS T EMD OWNL OAD U TI L I TY

WAR N ING: D ISK U NU SABL EF ORMAT D I S K U S I NG T HE

f mc p r e p PC UT I L I T Y

R EMOVE D I SK THENP RE SS H ER E T O R ET RY >

WHEN INSERTED DISK IS BLANK AND NOTFORMATTED BY THE FMCPREP.BAT PC U



FROM FIGURE 12

File System Download OperationFigure 13

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The FLIGHT n pages maintain a fault log containing records which occur during a particular flight,and these fault records cannot be cleared. The FMC will maintain them for ten flights. The SEN-SOR DATA pages display faults instantaneous, can be cleared manually, and are cleared at the endof each flight.

A. Fault Record Contents

DATE ((FMC−X) FLIGHT n page only) − displays the date that the first fault for the indicatedflight was recorded. During ground periods (FLIGHT G) the date may not be determinable, andis blanked.

SUB−SYSTEM CODE − displays the LRU the fault record pertains to.

STEADY INTERMITTENT INDICATOR − displays “S” or “I” to indicate the state of the fault/fail-ure. On the first occurrence of a fault or failure, the fault record is generated and the state islisted as “I” (intermittent). When the fault/failure occurs again the state is changed to “S”steady. Once the state is set to steady, it will not be changed back to intermit tent.

FIRST OCCURRENCE − displays the time the fault/failure was first logged. The time is not up-

dated once recorded.

LABEL CODE/FAILED TEST − displays the label code of the FMCS detected fault/failure orprovides failed test indication from a sub−system if reported to the FMCS.

MONITOR CODE − displays a monitor code (if one exists) to further define an indication of theproblem.

B. Label Codes

Label codes provide a broad category indication to identify the type of fault or failure that wasdetected by or reported to the FMC. Status provided on the (FMC−X) FLIGHT n pages and(FMC−X) SENSOR DATA pages provide this code on the line directly below the sub−system(LRU) identifier.

(1) Hardware Generated Label Code

The following label codes are derived from the FMC hardware testing and result in theFMC FAIL discrete set active. These hardware failures are reason to remove the FMCfrom service.

ARINC BUS TIMEOUT EDAC FAIL MEM CFG REG PROCESSOR

ASIC CPU ETHERNET−n MICROCODE UART

BACKPLANE DISCR OUTLOOP

GLITCH TIMER NAV DB VOL RAM

BUS ERROR DMA CHAN INT TIMER CLK OFP WDT TEST FAIL

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(2) Software Generated Label Codes

Many label codes are generated as a result of data checking performed by the FMC orfrom ARINC status words sent to the FMC. In most cases, it is doubtful if removing theFMC from service is going to help. Two of the most common software label codes are:

DATA SYNC ERR − the FMCs are sending different data to a sub−system.

PGM FAULT − FMC OFP faulted and must restart.

C. Monitor Codes

Monitor codes provide a specific fault or failure indication to further define the specified fault/ failure. Status provided on the (FMC−X) FLIGHT n pages and (FMC−X) SENSOR DATA pagesprovide the monitor code to the right of the label code in the fault record.

NOTE: Not all label codes have monitor codes associated with them.

(1) Hardware Generated Monitor Code

The following monitor codes are derived from the FMC hardware testing and result in theFMC FAIL discrete set active. These hardware failures are reason to remove the FMCfrom service.

COMM DISC−O MICROCTL REG

CACHE FAIL OSC USER 1

CRC INH RAM RAM USER−2

DISC−I INST RAMDAT WRAP

(2) Software Generated Monitor Codes

Many monitor codes are generated as a result of data checking performed by the FMC orfrom ARINC status words sent to the FMC. In most cases, it is doubtful if removing theFMC from service is going to help. Four of the most common software monitor codesare:

RATE − ARINC data word type was not received when expected.

REASON − ARINC data received from a sub−system contained data that was not withinexpected tolerances.

PARITY − ARINC data word received with incorrect parity set.

SSM − ARINC word Sign Status Matrix code was not as expected.

The RATE monitor code must be checked. Rate errors are logged against a specific sub−systems ARINC word type. When the FMC expects to receive a specific data word type,and the data is not received, the FMC performs a channel wrap−around test on that chan-nel. If the test fails, the FMC fails that ARINC input channel. If the test passes, the FMCfails the sending sub−system. Due to the internal hardware set up, there is a case whenthe FMC can be at fault and still pass the test. If only one or two monitored word typesare logged against a sub−system with rate errors, suspect the sub−system. When all

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monitored word types from a sub−system are logged with rate errors, suspect the FMCwhen it is known that the specific sub−system is powered up and running.

10. FMCS Display Fault Record

Each FMCS display unit generates a fault record each time a fault or failure is detected or reported,and when on the ground, makes this information available to the ground crew through the Mainte-nance BITE pages. The CDU BIT DSPLY INDEX and CDU BIT DISPLY pages (ref Section 2, pages153 and 154 respectively) display the fault records. Each fault record consists of two lines to identi-fy the sub−system (LRU) to which the fault or failure is attributed to, an indicator as to weather thefault/failure is considered steady or intermittent, the display unit elapsed time reading of first occur-rence, a failure description and an extended fault code.

Each time a fault or failure is detected, the fault records are searched for the same fault/failure al-ready recorded. The first time the fault/failure is detected a new record is generated. Subsequentfaults/failures already recorded will not have new records generated.

The display unit fault records are maintained for the last ten power−up cycles (cold starts). BITEdata for cycles older than that are not available. For each cycle, only the last five faults recorded

are displayed.

A. Unit Code

The unit code is an abbreviation for the function the display unit has determined the fault/failurecondition applies to. In the CDU mode, these are limited to the FMC or the CDU. When inMCDU or FANS MCDU modes, the five user channels are also included (USER 1 through USER5).

B. Fault Description Codes

The fault description codes provide an indicat ion of what the detected fault is. There are twogroups of fault descriptions, one group points to another sub−system or unit, and the secondgroup points to FMCS display unit hardware/software problems.

(1) Other sub−system or unit failure descriptions are FMC FAULT, 429 FAULT, and SUBSYS-TEM FAULT. When faults or failures are detected, the appropriate test is performed toverify the display units functionality. When the test passes, the fault/fai lure is recordedand attributed to an external unit.

(2) FMCS display failure descriptions point to faults and failures detected by the display unitsBITE testing. This set of fault/failure descriptions are as follows:

FAILUREDESCRIPTION

DEFINITION

ADC A failure was detected in the display unitanalog−to−digital circuitry.

ANNUN FAULT A failure was detected in the display unit an-nunciator circuitry.

EDC A failure was detected in the display unit er-ror detection and correction function.

FONTROM A failure was detected in the display unit fontgeneration circuitry.

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FAILUREDESCRIPTION

DEFINITION

KEYBOARD A failure was detected in the display unit key-board or keyboard matrix circuit ry.

LCD A failure was detected in the display unit liq-uid crystal display circuitry.

LIGHT SENSOR A failure was detected in the display unit am-bient light sensor or control circui try.

MEMORY A failure was detected in the display unitmemory circuitry.

POWER SUPPLY A failure was detected in the display unitpower supply outputs.

PROCESSOR A failure was detected in the display unitprocessor.

R/C TIMER A failure was detected in the display unit realtime clock function.

SOFTWARE FAULT An undef ined sof tware exception fault wasdetected in the display unit.

TEMP SENSOR A failure was detected in the display unitLCD and backlight temperatu re control cir-cuitry.

WATCHDOG TIMER A bus t ime−out was detected in the d isplayunit circuitry.

429 FAULT A failure was detected in the display unitARINC input/output circuitry.

C. Extended Fault Codes

The extended fault codes further define the fault/failure. There are a total of 100 extended faultcodes including spares for future use, and in general, these codes point to a functional test.

FAULTCODE

APPLIES TO

174101−xx− FAULT TITLE

01 02

00 X X PROC FAIL

01 X X RAM FAIL

02 X X PROG CRC FAIL

03 X X EDC SINGLE BIT FAIL

04 X X EDC MULTIPLE BIT FAIL

05 X X CPU WDT FAIL

06 X X HW WDT FAIL

07 X X ARINC 1 CHANNEL FAIL



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FAULTCODE

FAULT TITLE

APPLIES TO

174101−xx−FAULTCODE

FAULT TITLE

0201





14 X X ARINC 1 DATA FAIL






20 X X ARINC 7 DATA FAIL21 X X ARINC 1 RATE FAIL

22 X X ARINC 2 RATE FAIL






28 X X ARINC RCV 1 WRAP FAIL







35 X X ARINC XMT 1 WRAP FAIL

36 X X ARINC XMT 2 WRAP FAIL

37 X X ARINC EXTERN 1 WRAP FAIL







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FAULTCODE

FAULT TITLE

APPLIES TO


FAULT TITLE

0201

44 X X DISCRETE EXTERN WRAP FAIL

45 X X FONT ROM FAIL

46 X X VIDEO RAM FAIL

47 X BACKLIGHT BUSY FAIL

48 X BACKLIGHT CHANNEL FAIL

49 X X GPS FAILURE

50 X +1.2 V POWER SUPPLY FAIL



53 X REFL HETSNK DIF FAIL

54 X X ROW COL DIF FAIL55 X X LCD BCKLGHT DIF FAIL

56 X X AMB LT SENSOR 25 FAIL



59 X VIDEO FPGA CHECKSUM FAIL

60 X X PI ADC FAIL

61 X X PWR SUPPLY VCC FAIL

62 X X PWR SUPPLY POS 12 FAIL

63 X X PWR SUPPLY NEG 12 FAIL

64 X PWR SUPPLY P26V DC FAIL

65 X X PWR SUPPLY P28V DC FAIL

66 X X PWR SUPPLY SW 28 FAIL

67 X X PWR SUPPLY KBD ANN FAIL

68 X LCD HEATER FAIL

69 X TEC FAIL

70 X RC 200MS TIMER FAIL

71 X X RC 10SEC TIMER FAIL

72 X X KEYBOARD FAIL

73 X ARC DAC FAIL

74 X LAMP FIL FAIL*

75 X LAMP DRV FAIL*

75 X LED DRV FAIL

76 X LCD ADC FAIL

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FAULTCODE

FAULT TITLE

APPLIES TO


FAULT TITLE

0201

76 X BACKLIGHT CAL DATA FAIL

77 X X Start of Software Exception Faults

78 X X CPU WDT TIMEOUT

79 X X HW WDT TIMEOUT

80 X X EDAC SINGLE BIT FAIL

81 X X EDAC MULTIPLE BIT FAIL

82 X X FRAME OVERRUN

83 X X DIV ZERO FAULT

84 X X DEBUG EXCEPTION

85 X X NMI INTERRUPT

86 X X BREAKPOINT87 X X INTO DETECTED OVERFLOW

88 X X BOUND RANGE EXCEEDED

89 X X INVALID OP CODE

90 X X COPROCESSOR NOT AVAILABLE

91 X X DOUBLE FAULT

92 X X COPROCESSOR SEGMENT OVERRUN

93 X X INVALID TASK STATE SEGMENT

94 X X SEGMENT NOT PRESENT

95 X X STACK FAULT

96 X X GENERAL PROTECTION FAULT

97 X X PAGE FAULT

98 X X COPROCESSOR ERROR

99 X X SPARE INTERRUPT ERROR

100 X X SPURIOUS INTERRUPT ERROR

101 X X End of Fault Code Marker

NOTE: * These faults will result in the SERVICE BACKLIGHT SOON mes-sage being displayed in the scratchpad. BIT testing indicates the BacklightAssembly will fai l soon and needs to be replaced as soon as possible.

11. Discretes

The discrete inputs provide the FMC with information of varying types. These are divided into cate-gories covering aircraft configuration, optional equipment installations, FMCS configuration, equip-ment status, and software functionality.

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A. Discret e Inputs Monitored on ANALOG DISC Page

Many of the discrete inputs are displayed on the (FMC--X) ANALOG DISC pages (ref pages 139and 140) and are indicated in the last column. The following paragraphs discuss those dis-cretes that are indicated on the (FMC--X) ANALOG DISC pages.

(1) Static State Discrete Inputs

The static state discretes are used to provide the FMC with operating environment infor-mation to allow the FMC software to determine how functions and operations are con-trolled. The FMC reads these discretes only at power up while on the ground, and storesthem. These discrete states are not sampled again until the next on--ground power--up.

DISCRETENAME

STATES ANALOGDISC

PAGE*TRUE FALSE

A/ C & ENG TYPE 1 0 3/5

A/ C & ENG TYPE (PARIT Y) ODD EVEN 3/5

A/ C & ENG TYPE 1 1 0 3/5

A/ C & ENG TYPE 2 1 0 3/5

A/ C & ENG TYPE 3 1 0 3/5

A/ C & ENG TYPE 4 1 0 3/5

A/ C & ENG TYPE 5 1 0 3/5

A/ C & ENG TYPE 6 1 0 3/5

A/ C & ENG TYPE 7 1 0 3/5

A/ C & ENG TYPE 8 1 0 3/5

ACARS INSTALLED NOTINSTALLED

4/11

ASPI RATED TAT PROBE INSTALLED NOTINSTALLED

2/8

ASSUMED TEMPERATURE ENA BLED DISABLE D 2/3

CAA/JAA FLIGHT RULES CAA/JAA FAA 2/4

DEGREES C/ F DEFAULT °F °C 2/10

FAA/CAA QRH TAKEOFF SPEEDS CAA FAA 4/7

F LI GHT NUMBER ENT RY O PT IO N ENABLED DI SABLED 4/ 4

KILOGRAM OPTION KILOGRAM POUNDS 2/5

* -- Dis pla y pag e no. /l ine no. whe n dis crete is lis ted on the dis pla y pag es.

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DISCRETENAME

STATES ANALOGDISC

PAGE*TRUE FALSE

NAVAID SUPPRESSION ON DIS-PLAY

SUP-PRESSED

NOTSUPPRES-

SED

4/9

PERFORMANCE OPCODE 0 1 2/12

RUNWAY POSITION UPDATE TOGASWITCH

ENABLED

TOGASWITCH

NOTENABLED

4/5

SELECTED COARSE INHIBITEDON DISPLAY

INHIBITED NOTINHIBITED

4/10

SOURCE/DESTINATIONINDICATOR 1

0 1 2/7

* -- Dis play page no. /l ine no. when dis crete is lis ted on the dis play pages.

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DISCRETENAME

STATES ANALOGDISC

PAGE**TRUE FALSE

TAKEOFF PROFILES ENABLED DISABLED 4/6

TAKEOFF SPEEDS CALCU-LATED

NOTCALCULA-

TED

4/8

VOR INHIBIT INHIBITED NOTINHIBITED

4/3

* − Display page no./line no. when discrete is listed on the display pages.

(2) Conditional Discrete Inputs

The conditional discrete states change in response to sub−system setting changes,switch changes made by the flight crew, or component failures. These discretes aresampled after power up is complete, and on a periodic rate thereafter.

DISCRETENAME

STATES ANALOGDISC

PAGE*TRUE FALSE

ACARS INSTALLED INSTALLED NOTINSTALLED

4/11

COWL ANTI−ICE−L OFF ON 1/6

COWL ANTI−ICE−R OFF ON 1/6

ECS PACK−L OFF ON 1/3

ECS PACK−R OFF ON 1/3

ECS PACK H/L−L OFF ON 1/4

ECS PACK H/L−R OFF ON 1/4

ENGINE BLEED NO. 1 OFF ON 3/8

ENGINE BLEED NO. 2 OFF ON 3/8

ISOLATION VALVE CLOSED OPEN 1/5

FREQ AGILITY MODE DME−L ENABLED NOTENABLED

1/11

FREQ AGILITY MODE DME−R ENABLED NOTENABLED

1/11

MAG/TRUE TRUENORTH

MAGNETICNORTH

2/6

OLEO STRUT SWITCH SQUAT NOTSQUAT

1/8

WING ANTI−ICE OFF ON 1/7

* − Display page no./line no. when discrete is listed on the display pages.

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B. Complete Discrete List

The complete list of the input and output discretes Including the signal type and FMC or displayunit connector pin assignments can be found in Figure 14.

12. Software Opt ions

Software options allow the airlines to modify the FMCS basic functionality. The Option Code dis-played on the Software Options page (See FMC Maintenance BITE Pages section, paragraph 4T orFMCS Display Unit Maintenance BITE Pages section, paragraph 5H) is a summation of the individu-al hex codes for each enabled option. Many of these options require specific discrete inputs to theFMC to be placed in the enabled state as well as having the software options disk to enable the soft-ware.

A. FMC Software Options

The FMC software options are controlled via the loadable Software Options Database which isavailable from the airplane manufacturer. The FMC options currently available are as follows:

OPTION CODE(hex)

DESCRIPTION NOTES

0000 0000 0001 High Idle Descent Requires Runway Position Updateoption installed in aircraft. In Classicgroup, default option if SW OptionsDB is not loaded.

0000 0000 0002 Runway Remaining in Meters Requires Runway Posit ion Updateoption installed in aircraft.

0000 0000 0004 Runway Offset in Feet Requires Runway Position Updateoption installed in aircraft.

0000 0000 0006 Runway Remaining in Feet Requires Runway Posit ion Updateoption installed in aircraft.

0000 0000 0008 Manual Takeoff Speeds Requires Takeoff Speeds optioninstalled in aircraft.

0000 0000 0010 Missed Approach Color Requires Electronic displays (EHSIor CDS) installed in aircraft.

0000 0000 0020 VNAV Alt Option code 0000 0001 0000 also re-quired.

0000 0000 0040 GPS Advisory Requires GPS/MMR installed in air-craft.

0000 0000 0080 GPS without Integrity Requires GPS/MMR installed in air-craft.

0000 000000C0 GPS with Integrity Requires GPS/MMR installed in air-craft.

0000 0000 0100 Direct GPS Input Requires GPS/MMR installed in air-craft.

0000 0000 0200 Manual RNP Entry Default option if SW Options DB isnot loaded.

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OPTION CODE(hex)

NOTESDESCRIPTION

0000 0000 0400 ATS Datalink Requires ACARS option installed inaircraft.

0000 0000 0800 Fixed Outputs ATS Test Requires ACARS option installed inaircraft and option code 0000 00000400 (ATS Datalink) enabled.

0000 0000 1000 ATC Message on XXXX Requires ACARS option installed inaircraft , option code 0000 0000 0400(ATS Datalink) enabled, and eitherEFIS or CDS installed. (XXXX is thedisplay type, EFIS or CDS)

0000 0000 2000 Abeam Waypoints

0000 0000 4000 AOC Datalink Requires ACARS option installed inaircraft.

0000 0000 8000 Alternate Destination

0000 0001 0000 Altitude/Speed Intervention

0000 0002 0000 Cert if ied Takeoff Speeds Requ ires Takeoff Speeds opt ioninstalled in aircraft.

0000 0004 0000 Message Recall

0000 0008 0000 Plan Fuel Entry

0000 0010 0000 QFE Altitude Reference Requires NG aircraft with PFN/NDdisplay format.

0000 0020 0000 CDU Color

0000 0040 0000 Geometr ic Path Descent Defau lt opt ion i f SW Opt ions DB isnot loaded (U10.6 and later)

0000 0080 0000 Pilot Defined Company Route

0000 0100 0000 Quiet Climb System Requires Takeoff Profile optioninstalled in aircraft.

0000 0200 0000 Optional Noise Gradient Requires option code 0000 01000000 and Takeoff Profile optioninstalled in aircraft.

0000 0400 0000 Engine Out SIDS

0000 0800 0000 Common Instrument ApproachProcedure

0000 1000 0000 GLS Procedures

0000 2000 0000 Gross Weight Inhibit

0000 4000 0000 Takeoff Derate Inhibit

0010 0000 0000 Manual Position Update

0020 0000 0000 Common VNAV

0040 0000 0000 Speed Propagation

0080 0000 0000 Additional Fix Pages

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OPTION CODE(hex)

NOTESDESCRIPTION

0100 0000 0000 Default DME Update Off

0200 0000 0000 Intent Data On ACARS Requires ACARS option installed on

aircraft and option code 0000 00004000 (AOC Datalink) enabled.

0400 0000 0000 Intent Data On Dedicated

0800 0000 0000 TO Thrust Auto Select

Note: Leading zeros for 16 digit hex codes not shown.

B. FMCS Display Unit Software Options

The FMCS display units have the software options loaded as an integral part of the OFP. Theoptions may be enabled or disabled as desired using the CDU Software Options maintenanceBITE page. The software options for the CDU are as follows:

OPTIONCODE(hex)

UPDATE DESCRIPTION NOTES

0000 0000 1 & 2 Default Setting Software options are not enabled.

0000 0001 1 & 2 Switching Mode Enables a dual sub−system to beconnected to an MCDU or FANSMCDU user channels 1 and 5, andboth will be selected by LSK 2L.When one sub−system is not avail-able, the other is automatically con-nected.

0000 0002 1 & 2 ARINC 739 Color

Usage

When enabled, allows the sub−sys-

tems connected to an MCDU orFANS MCDU to use color in the dis-play pages.

0000 0004 2 ALT NAV − GPS Enables the alternate navigationfunction using GPS in an MCDU orFANS MCDU.

0000 0008 2 Reserved

0000 0010 2 WXR Map Enables display of uplink map data.Requires additional equipment to beinstalled (174101−xx−01 Units).

13. ARINC 429 Data

The FMC communicates with the sub−systems of the FMS using various ARINC 429 word formats.Figure 15 lists the ARINC words by label code.

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DISCRETE NAME I/OCONNECTOR PIN STATES

FMC DISPLAY GND 28V/OPEN

AIR−GROUND DISCRETE I J1−07 ON GROUND IN AIR

ATC CHIME O MP−14D CHIME NO CHIME

ATC MESSAGE ALERT O TP−15K ATC MESSAGE ALERT NO ATC MESSAGES

ACARS I MP−10A INSTALLED NOT INSTALLED

ASPIRATED TAT PROBE I MP−14F INSTALLED NOT INSTALLED

CAA FLIGHT RULES OPTION I MP−13C CAA RULES FAA RULES

CDU−L FAIL WARNING I MP−06F DISPLAY UNIT OPERATIONAL DISPLAY UNIT FAILED

CDU−R FAIL WARNING I TP−13J DISPLAY UNIT OPERATIONAL DISPLAY UNIT FAILED

CDU FAIL WARNING O J1−13 DISPLAY UNIT OPERATIONAL DISPLAY UNIT FAILED

CDU MESSAGE ALERT O TP−13K MESSAGE ALERT NO ALERT

COWL ANTI−ICE (LEFT AND RIGHT INPUTS ARE CROSS−TIED)

I MP−13FMP−13G

OFF ON

DATA LOADER I J1−10 ENABLED NOT ENABLED

DATA LOADER FUNCTION 2 I MP−11A ENABLED NOT ENABLED

DEGREES C/DEGREES F DEFAULT I MP−10D DEFAULT TO DEGREES F DEFAULT TO DEGREES C

ECS PACK−L I MP−13J OFF ON

ECS PACK−L I MP−14A LOW HIGH

ECS PACK−R I MP−14B OFF ON

ECS PACK−R I MP−14C LOW HIGH

ENGINE 1 BLEED I MP−13H BLEED OFF BLEED ON

ENGINE 2 BLEED I MP−14H BLEED OFF BLEED ON

FAA/CAA QRH SPEEDS I MP−10B CAA QRH SPEEDS FAA QRH SPEEDS

FLIGHT NUMBER ENTRY I MP−10G ALLOWED NOT ALLOWED

FMC FAIL WARNING O MP−07K FMC OPERATIONAL FMC FAILED

FMC SOURCE SELECT SWITCH BIT 1 (USED IN CONJUNCTION WITH FMC SOURCE SELECT SWITCH BIT 2)

(BINARY 0 = SINGLE FMC INSTALLATION)

(BINARY 1 = FMC−L IS MASTER)

(BINARY 2 = FMC−R IS MASTER)

(BINARY 3 = NORMAL DUAL OPERATION)

I MP−12E LOGIC 1 LOGIC 0

FMC SOURCE SELECT SWITCH BIT 2 (USED IN CONJUNCTION WITH FMC SOURCE SELECT SWITCH BIT 1)

(BINARY 0 = SINGLE FMC INSTALLATION)

(BINARY 1 = FMC−L IS MASTER)

(BINARY 2 = FMC−R IS MASTER)

(BINARY 3 = NORMAL DUAL OPERATION)

I MP−12G LOGIC 1 LOGIC 0

FMCS Discrete Inputs and OutputsFigure 14 (Sheet 1)

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DISCRETE NAMESTATESCONNECTOR PIN

I/ODISCRETE NAME28V/OPENGNDDISPLAYFMC

I/O

ISOLATION VALVE I MP−04K VALVE CLOSED VALVE OPEN

KILOGRAM OPTION I MP−13B KILOGRAMS POUNDS

LAMP TEST I J1−23 ANNUNCIATOR LAMP TEST MODE NORMAL OPERATION MODE

LATERAL OFFSET INHIBIT I MP−13D OFFSETS INHIBITED OFFSETS ENABLED

MAG/TRUE SWITCH I TP−04K TRUE MAGNETIC

MCDU LOCATION BIT 1 I J1−11 LOGIC 1 LOGIC 0

MCDU LOCATION BIT 1 I J1−12 LOGIC 1 LOGIC 0

MODEL ENGINE CODE BIT 1 I MP−11C LOGIC 1 LOGIC 0

MODEL ENGINE CODE BIT 2 I MP−11D LOGIC 1 LOGIC 0

MODEL ENGINE CODE BIT 3 I MP−11E LOGIC 1 LOGIC 0

MODEL ENGINE CODE BIT 4 I MP−11F LOGIC 1 LOGIC 0MODEL ENGINE CODE BIT 5 I MP−11G LOGIC 1 LOGIC 0

MODEL ENGINE CODE BIT 6 I MP−11H LOGIC 1 LOGIC 0

MODEL ENGINE CODE BIT 7 I MP−12C LOGIC 1 LOGIC 0

MODEL ENGINE CODE BIT 8 I MP−12D LOGIC 1 LOGIC 0

MODEL ENGINE CODE BIT NEWGEN I MP−12A LOGIC 1 LOGIC 0

MODEL ENGINE CODE BIT PARITY I MP−12B ODD PARITY EVEN PARITY

NAVAID SUPPRESSION ON EFIS I MP−10H AUTOTUNED NAVAIDS SUPPRESSED NOT SUPPRESSED

OLEO STRUT I TP−01K ON GROUND IN AIR

PERFORMANCE OPTION CODE I MP−15F OPTION CODE 1 OPTION CODE 0

RUNWAY POITION UPDATE I MP−10J TOGA SWITCH UPDATE BASIC UPDATE

S/W DISPLAY ENABLE I TP−09F ENABLED NOT ENABLED

SDI CODE BIT 1 (USED IN CONJUNCTION WITH SDI CODE BIT 2)

(BINARY 1 = LEFT POSITION)

I MP−01K LOGIC 1 LOGIC 0

SDI CODE BIT 2 (USED IN CONJUNCTION WITH SDI CODE BIT 1)

(BINARY 2 = RIGHT POSITION)

I MP−03K LOGIC 1 LOGIC 0

SELECTED CONFIGURATION MODE I TP−08K SELECTED CONFIGURATION MODE NOT SELECTED CONFIGURATION MODE

SELECTED COURSE INHIBIT ON EFIS I MP−10C SELECTED COURSE NOT DISPLAYED SELECTED COURSE DISPLAYED

TAKEOFF PROFILE I MP−12H ACTIVE NOT ACTIVETAKEOFF SPEEDS I MP−12F FMC COMPUTED TAKEOFF SPEEDS TAKEOFF SPEEDS NOT COMPUTED

VOR INHIBIT I MP−10F INHIBIT VOR FOR NAVIGATION USE VOR FOR NAVIGATION

WING ANTI−ICE I MP−14J OFF ON

FMCS Discrete Inputs and OutputsFigure 14 (Sheet 2)

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LABLE BUS SOURCE SIGNAL NAME NOTES DATA TYPERATE

NOM MIN MAX

001 FMC−01, FMC−02 FMC−PRIMARY DISTANCE TO GO (WAYPOINT) BCD 200

001 FMC−08, FMC−09 FMC−PRIMARY DISTANCE TO GO (WAYPOINT) BCD 200

012 FMC−01, FMC−02 FMC−PRIMARY GROUND SPEED BCD 200

012 FMC−08, FMC−09 FMC−PRIMARY GROUND SPEED−D BCD 200

017 FMC−01, FMC−02 FMC−PRIMARY FRONT COURSE BCD/DISC 400 200 400

017 FMC−08, FMC−09 FMC−PRIMARY FRONT COURSE BCD 500

033 I LS−2 ILS−1, ILS−2 ILS FREQUENCY BCD/COD

033 I LS−2 MMR−L, MMR−R ILS FREQUENCY BCD/COD 167 333

033 ILS−2 MMR−L, MMR−R GLS ENCODED CHANNEL 2 COD 167 333

034 FMC−01, FMC−02 FMC−PRIMARY VOR FREQUENCY FMC−01 TO VOR−L, FMC−02 TO VOR−

R

BCD 167 333

034 VOR−2 VOR−L, VOR−R VOR/ILS TUNING BCD/DISC 167 333

035 DME−1, DME−2 DME−L, DME−R DME FREQUENCY BCD/DISC/COD 200

035 FMC−01, FMC−02 FMC−PRIMARY DME FREQUENCY BCD/DISC/COD 100 200

040 MCDU−1 MCDU−L, MCDU−R DISPLAY DATA SFMT

041 F MC−01, FMC−02 FMC−PRIMARY SET LATITUDE BCD 500

042 FMC−01, FMC−02 FMC−PRIMARY SET LONGITUDE BCD 500

043 FMC−01, FMC−02 FMC−PRIMARY SET MAGNETIC HEADING BCD 500

050 MCDU−1 MCDU−L, MCDU−R DISPLAY DATA SFMT

056 FMC−08, FMC−09 FMC−PRIMARY ETA BCD 500

061 F MC−01, FMC−02 FMC−PRIMARY ORIG/DEST−1 ISO 500



064 FMC−01, FMC−02 FMC−PRIMARY DESTINATION RUNWAY ISO 500

065 FMC−01, FMC−02 FMC−PRIMARY DESTINATION ETA BCD 500

070 F MC−01, FMC−02 FMC−PRIMARY VREF SPEED BNR 1000

070 F MC−08, FMC−09 FMC−PRIMARY VREF SPEED BNR 1000

071 FMC−08, FMC−09 FMC−PRIMARY V2 SPEED BNR 1000

072 FMC−08, FMC−09 FMC−PRIMARY VR SPEED BNR 1000073 FMC−08, FMC−09 FMC−PRIMARY V1 SPEED BNR 1000

075 FMC−01, FMC−02 FMC−PRIMARY GROSS WEIGHT BNR 1000

100 MCP−3 AFDS LOCAL SELECTED COURSE SDI 1 = FCC−A, SDI 2 = FCCB BNR 50 8 52

ARINC Data in Label Code SequenceFigure 15 (Sheet 1)

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LABLERATE

DATA TYPENOTESSIGNAL NAMESOURCEBUSLABLEMAXMINNOM

DATA TYPENOTESSIGNAL NAMESOURCEBUS

102 FMC−01, FMC−02 FMC−PRIMARY FMC ALTITUDE BNR 200

102 MCP−3 AFDS SELECTED ALTITUDE SDI 1 = FCC−A, SDI 2 = FCC−B BNR 100 98 102

103 FMC−01, FMC−02 FMC−PRIMARY FMC AIRSPEED BNR/DISC 200

103 GNSS DATA 1 MMR−L GNSS TRACK ANGLE BNR 100 200 1200

103 GNSS DATA 2 MMR−R GNSS TRACK ANGLE BNR 100 200 1200

103 MCP−3 AFDS SELECTED AIRSPEED SDI 1 = FCC−A, SDI 2 = FCC−B BNR 100 98 102

104 FMC−01, FMC−02 FMC−PRIMARY VERTICAL SPEED COMMAND BNR 100

106 FMC−01, FMC−02 FMC−PRIMARY FMC MACH BNR/DISC 200

106 MCP−3 AFDS SELECTED MACH SDI 1 = FCC−A, SDI 2 = FCC−B BNR 100 98 102

110 FMC−08, FMC−09 FMC−PRIMARY GNASS DATA LATITUDE BNR 1000 200 1200

110 GNSS DATA 1 MMR−L GPS DATA GNSS LATITUDE − COARSE BNR 1000 200 1200

110 GNSS DATA 2 MMR−R GPS DATA GNSS LATITUDE − COARSE BNR 1000 200 1200

110 MCP−3 AFDS FOREIGN SELECTED COURSE SDI 1 = FCC−A, SDI 2 = FCC−B BNR 100 98 102

111 FMC−08, FMC−09 FMC−PRIMARY GNASS DATA LONGITIUDE BNR 1000 200 1200

111 GNSS DATA 1 MMR−L GPS DATA GNSS LONGITUDE (COARSE) BNR 1000 200 1200

111 GNSS DATA 2 MMR−R GPS DATA GNSS LONGITUDE (COARSE) BNR 1000 200 1200

114 FMC−01, FMC−02 FMC−PRIMARY DESIRED TRACK BNR 200

114 FMC−08, FMC−09 FMC−PRIMARY DESIRED TRACK BNR 50

114 MCDU−1 MCDU−L (U2 ONLY) DESIRED TRACK BNR

115 FMC−01, FMC−02 FMC−PRIMARY WAYPOINT BEARING BNR 100

115 FMC−08, FMC−09 FMC−PRIMARY WAYPOINT BEARING BNR 100

115 MCDU−1 MCDU−L (U2 ONLY) WAYPOINT BEARING BNR

116 FMC−01, FMC−02 FMC−PRIMARY CROSS−TRACK DEVIATION BNR 100

116 FMC−08, FMC−09 FMC−PRIMARY CROSS−TRACK DEVIATION BNR 50

116 MCDU−1 MCDU−L (U2 ONLY) CROSS−TRACK DEVIATION BNR

117 FMC−01, FMC−02 FMC−PRIMARY VERTICAL DEVIATION BNR 100

117 FMC−08, FMC−09 FMC−PRIMARY RANGE TO ALTITUDE BNR 50

120 FMC−08, FMC−09 FMC−PRIMARY GNASS DATA

SDI = 0 RANGE TO ALTITUDE BNR 50

SDI = 1 LATITUDE − FINE BNR 1000 200 1200SDI = 2 LATITUDE − FINE B BNR 1000 200 1200

120 GNSS DATA 1 MMR−L GPS DATA GNSS LATITUDE − FINE BNR 1000 200 1200

120 GNSS DATA 2 MMR−R GPS DATA GNSS LATITUDE − FINE BNR 1000 200 1200


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LABLERATE



121 FMC−01, FMC−02 FMC−PRIMARY HORIZONTAL COMMAND SIGNAL BNR/DISC 100

121 FMC−08, FMC−09 F MC−PRIMARY GNASS DATA LONGITUDE − FINE BNR 1000 200 1200

121 GNSS DATA 1 MMR−L GPS DATA LONGITUDE − FINE BNR 1000 200 1200

121 GNSS DATA 2 MMR−R GPS DATA LONGITUDE − FINE BNR 1000 200 1200

124 DUE−FMC IRNAV DISPLAY SDI 1 = DEU−1, SDI 1 = DEU−2 DISC 1000 990 1010

125 CLK−1 CLK−CAPT GMT (TO FMC−L ONLY) BCD 100 200

125 CLK−1 CLK−COPLT GMT (TO FMC−R ONLY) BCD 100 200

125 FMC−01, FMC−02 FMC−PRIMARY GMT BCD 200

126 FMC−08, FMC−09 FMC−PRIMARY VERTICAL DEVIATION (WIDE) BNR 50

127 FMC−08, FMC−09 FMC−PRIMARY SET LANDING ALTITUDE BNR 1000

130 FMC−08, FMC−09 FMC−PRIMARY DME ELEVATION SDI 1 = USE LEFT VOR, SDI 2 = USE

RIGHT VOR

BNR 200 200 1000

130 G NSS DATA 1 MMR−L GPS DATA BNR/DISC 1000 200 1200

130 G NSS DATA 2 MMR−R GPS DATA BNR/DISC 1000 200 1200

135 FMC−08, FMC−09 FMC−PRIMARY VERTIACAL RNP BNR 500 200 100

136 FMC−08, FMC−09 FMC−PRIMARY VERTIACAL ANP BNR 500 200 100

137 MCP−3 AFDS FLAPS POSITION SDI 1 = FCC−A, SDI 2 = FCC−B BNR 100 98 102

150 G NSS DATA 1 MMR−L GPS DATA BNR/DISC 1000 200 1200

150 G NSS DATA 2 MMR−R GPS DATA BNR/DISC 1000 200 1200

152 FMC−08, FMC−09 FMC−PRIMARY TRANSITION ALTITUDE BNR 1000 990 1010

167 FMC−08, FMC−09 FMC−PRIMARY ANP BNR 200 100 2000

171 FMC−08, FMC−09 FMC−PRIMARY RNP BNR 200 100 2000

172 ACARS−1 SDU−L SYSTEM ID BNR

173 DAA−2 DAA−l, DAA−R

173 FMC−01, FMC−02 FMC−PRIMARY ANGULAR LATERAL DEVIATION BNR 100 50 100

173 FMC−08, FMC−09 FMC−PRIMARY ANGULAR LATERAL DEVIATION BNR 100 50 100

173 ILS−2 ILS−1, ILS−2 LOCALIZER DEVIATION BNR/DISC 34 67

173 ILS−2 MMR−L, MMR−R LOCALIZER DEVIATION BNR/DISC 34 67

174 FMC−01, FMC−02 FMC−PRIMARY ANGULAR VERTICAL DEVIATION BNR 100 50 100

174 FMC−08, FMC−09 FMC−PRIMARY ANGULAR VERTICAL DEVIATION BNR 100 50 100

200 ADR−4 ADIRU−l, ADIRU−R ALTITUDE (UNCORRECTED) BNR 62.5

200 FMC−01, FMC−02 FMC−PRIMARY DRIFT ANGLE BCD 100 200

202 DME−1, DME−2 DME−L, DME−R DME DISTANCE BNR/DISC 167


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202 FMC−08, FMC−09 FMC−PRIMARY EM CLEAN BNR 100

203 ADR−4 ADIRU−L, ADIRU−R ALTITUDE UNCORRECTED ALTITUDE BNR 62.5

203 FMC−08, FMC−09 FMC−PRIMARY EM SPEED BRAKES BNR 100

204 ADR−4 ADIRU−L, ADIRU−R ALTITUDE BARO CORRECTED NO. 1 BNR 62.5

205 ADR−4 ADIRU−L, ADIRU−R AIRSPEED MACH BNR 125

206 ADR−4 ADIRU−L, ADIRU−R AIRSPEED CAS BNR 125

210 ADR−4 ADIRU−L, ADIRU−R AIRSPEED TAS BNR 125

211 A DR−4 ADIRU−L, ADIRU−R TEMPERATURE TAT BNR 500

213 A DR−4 ADIRU−L, ADIRU−R TEMPERATURE SAT BNR 500

213 FMC−01, FMC−02 FMC−PRIMARY TEMPERATURE SAT BNR 500

214 FMC−01, FMC−02 FMC−PRIMARY SELECTED TEMPERATURE BNR 500

220 ACARS−1 SDU−L ACARS DATA ISO

220 ADR−4 ADIRU−L, ADIRU−R ALTITUDE BARO CORRECTED NO. 2 BNR 62.5

221 ACARS−2 SDU−L ACARS DATA ISO

222 VOR−2 VOR−L, VOR−R VOR DATA OMNIBEARING BNR 50 100

233 FMC−01, FMC−02 FMC−PRIMARY FLIGHT NUMBER WORD 1 ISO 800 1000




245 FMC−01, FMC−02 FMC−PRIMARY MINIMUM AIRSPEED BNR 1000

246 FMC−08, FMC−09 FMC−PRIMARY MAX VNAV SPEED BAND BNR 1000

247 FMC−01, FMC−02 FMC−PRIMARY TOTAL FUEL POUNDS OF FUEL BNR 500 1000

247 FMC−08, FMC−09 FMC−PRIMARY MIN VNAV SPEED BAND BNR 1000

247 FQPU−5 FQIS TOTAL FUEL POUNDS OF FUEL BNR 500 1000

247 GNSS DATA 1 MMR−L GPS DATA HORIZONTAL FIGURE OF MERIT BNR 1000 200 1200

247 GNSS DATA 2 MMR−R GPS DATA HORIZONTAL FIGURE OF MERIT BNR 1000 200 1200

250 FMC−01, FMC−02 FMC−PRIMARY CONTINUOUS N1 LIMIT SDI 1 = ENG 1, SDI 2 = ENG 2 BNR 50 200

251 FMC−01, FMC−02 FMC−PRIMARY DISTANCE TO GO BNR 200

251 FMC−08, FMC−09 FMC−PRIMARY DISTANCE TO MISSED APPROACH POINT BNR 200 100 400

251 MCDU−1 MCDU−L (U2 ONLY) DISTANCE TO WAYPOINT BNR

253 FMC−01, FMC−02 FMC−PRIMARY GO−AROUND N1 LIMIT SDI 1 = ENG 1, SDI 2 = ENG 2 BNR 50 200

254 FMC−01, FMC−02 FMC−PRIMARY CRUISE N1 LIMIT SDI 1 = ENG 1, SDI 2 = ENG 2 BNR 50 200

255 FMC−01, FMC−02 FMC−PRIMARY CLIMB N1 LIMIT SDI 1 = ENG 1, SDI 2 = ENG 2 BNR 50 200


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260 CLK−L−1 CLK−CAPT DATE (TO FMC−L ONLY) BCD 100 1000

260 CLK−R−1 CLK−COPT DATE (TO FMC−R ONLY) BCD 100 1000

260 FMC−01, FMC−02 FMC−PRIMARY CLOCK DATE BCD 100 1000

260 GNSS DATA 1 MMR−L GPS DATE BCD 1000 200 1200

260 GNSS DATA 2 MMR−R GPS DATE BCD 1000 200 1200

261 FMC−01, FMC−02 FMC−PRIMARY FLIGHT NUMBER BCD 1000

263 FMC−01, FMC−02 FMC−PRIMARY NDB EFFECTIVITY DATE BCD 1000

265 FMC−01, FMC−02 FMC−PRIMARY MIN BUFFET AIRSPEED BNR 50 200

267 FMC−01, FMC−02 FMC−PRIMARY MAX BUFFET AIRSPEED BNR 50 200

270 A/T−1 A/T A/T DISCRETE WORD DISC 50

270 ACARS−1 SDU−L COMMUNICATIONS LINK STATUS DISC 1000

270 FMC−01, FMC−02 FMC−PRIMARY FMC DISCRETE WORD NO. 1 DISC 1000

270 FMC−05 FMC−BOTH SYSTEM STATUS DISC/COD 1000

270 IR−3 ADIRU−L, ADIRU−R IR DISCRETE WORD NO. 1 SDI = 0 DISC 500

270 MCP−3 AFDS AFDS DISCRETE WORD NO. 2 SDI 1 = FCC−A, SDI 2 − FCC−B DISC 100 98 102

271 A/T−1 A/T A/T DISCRETE WORD 2 DISC 1000


271 FMC−08, FMC−09 FMC−PRIMARY FMC DISCRETE WORD NO. 2 DISC/COD 500


272 DEU−FMC CDS CDS EFIS CP MODES NO. 1 SDI 1 = DEU−1, SDI 2 = DEU−2 DISC 50 40 60



273 DEU−FMC CDS CDS EFIS CP MODES NO. 2 SDI 1 = DEU−1, SDI 2 = DEU−2 DISC/COD 50 40 60

273 GNSS DATA 1 MMR−L GNSS SENSOR STATUS BNR/DISC/COD 1000 200 1200

273 GNSS DATA 2 MMR−R GNSS SENSOR STATUS BNR/DISC/COD 1000 200 1200


274 MCP−3 AFDS AFDS DISCRETE WORD NO. 3 SDI 1 = FCC−A, SDI 2 − FCC−B DISC/COD 100 98 102



275 CDU/MCDU−1 FMC PRIMARY TO−FROM ARROW DISPLAY SDI = 0 COD

275 MCDU−1 MCDU−L (U2 ONLY) LRN STATUS WORD − GAMA DISC/COD

276 FMC−01 FMC−PRIMARY FMC DISCRETE WORD NO. 4 ENGINE THRUST RATING COD 1000

277 FMC−08, FMC−09 F MC−PRIMARY FMC NAVIGATION SOURCE SDI = 0 DISC/COD 1000


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LABLERATE



301 FMC−08, FMC−09 FMC−PRIMARY SOT MAP BACKGROUND BNR

302 FMC−08, FMC−09 FMC−PRIMARY EOT MAP BACKGROUND BNR

303 FMC−08, FMC−09 FMC−PRIMARY MAP (DYNAMIC) DATA 50

304 FMC−05 FMC−PRIMARY ACARS DATA SFMT 1000

304 FMC−08, FMC−09 F MC−PRIMARY APPROACH DATA BLOCK BCD/BNR/DISC/ ISO

5000

310 FMC−08, FMC−09 FMC−PRIMARY PRESENT POSITION LATITUDE BNR 100

310 IR−3 ADIRU−L, ADIRU−R PRESENT POSITION LATITUDE BNR 100 200

311 FMC−08, FMC−09 FMC−PRIMARY PRESENT POSITION LONGITUDE BNR 100

311 IR−3 ADIRU−L, ADIRU−R PRESENT POSITION LONGITUDE BNR 100 200

312 FMC−01, FMC−02 FMC−PRIMARY GROUND SPEED BNR 200

312 F MC−08, FMC−09 FMC−PRIMARY GROUND SPEED BNR 50

312 IR−3 ADIRU−L, ADIRU−R GROUND SPEED BNR 50 100

313 FMC−08, FMC−09 FMC−PRIMARY TRACK ANGLE (TRUE) BNR 50

314 IR−3 ADIRU−L, ADIRU−R TRUE HEADING BNR 25 50

315 FMC−08, FMC−09 FMC−PRIMARY WIND SPEED BNR 100

316 FMC−08, FMC−09 FMC−PRIMARY WIND DIRECTION (TRUE) BNR 100

317 FMC−01, FMC−02 FMC−PRIMARY TRACK ANGLE (MAGNETIC) BNR 25 100

317 FMC−08, FMC−09 FMC−PRIMARY TRACK ANGLE (MAGNETIC) BNR 50

320 I R−3 ADIRU−L, ADIRU−R MAGNETIC HEADING BNR 25 50

321 F MC−01, FMC−02 FMC−PRIMARY DRIFT ANGLE BNR 200

321 FMC−08, FMC−09 FMC−PRIMARY DRIFT ANGLE BNR 50

322 FMC−08, FMC−09 FMC−PRIMARY FLIGHT PATH ANGLE BNR 50

324 IR−3 ADIRU−L, ADIRU−R PITCH ANGLE BNR 10 20

325 IR−3 ADIRU−L, ADIRU−R ROLL ANGLE BNR 10 20

341 FMC−01, FMC−02 FMC−PRIMARY TARGET N1 SDI 1 = ENG 1, SDI 2 = ENG 2 BNR 50 200

342 FMC−01, FMC−02 F MC−PRIMARY N1 BUG DRIVE SDI 1 = ENG 1, SDI 2 = ENG 2 BNR 50 200

350 ACARS−1 SDU−L STATUS DISC 1000

351 DEU−FMC DEU−1, DEU−2 CP & DU MAINT WORD

354 FMC−08, FMC−09 FMC−PRIMARY ALPH−NUMERIC TET BNR/ISO 200

355 GNSS DATA 1 MMR−L GNSS FAULT SUMMARY DISC 1000 200 1200


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LABLE BUS SOURCE SIGNAL NAME NOTES DATA TYPERATE

NOM MIN MAX

355 GNSS DATA 2 MMR−R GNSS FAULT SUMMARY DISC 1000 200 1200

356 A/T−1 A/T BITE RESPONSE (XMT ONLY DURING BITE) ISO NOT SENDING DATA −10 MIN, 200 MAX

SENDING DATA − 8MIN,10 MAX

356 DEU−FMC DEU−1, DEU−2 BITE RESPONSE (XMT ONLY DURING BITE) ISO NOT SENDING DATA −10 MIN, 200 MAX


356 DLDR−1 DLDR SELECTED CONFIGURATION ISO

356 FQPU−5 FQIS BITE RESPONSE (XMT ONLY DURING BITE) ISO NOT SENDING DATA −10 MIN, 200 MAX


356 IR−3 ADIRU−L, ADIRU−R BITE RESPONSE (XMT ONLY DURING BITE) ISO NOT SENDING DATA −10 MIN, 200 MAX


356 MCP−3 FCC−A, FCC−B BITE RESPONSE (XMT ONLY DURING BITE) ISO NOT SENDING DATA −10 MIN, 200 MAX


356 SELCONFIG−1 DLDR SELECTED CONFIGURATION DATA ISO

357 FMC−01, FMC−02 FMC−PRIMARY BITE TEST WORD BNR/COD/ISO NOT SENDING DATA −10 MIN, 200 MAX


360 FMC−08, FMC−09 FMC−PRIMARY FLIGHT INFORMATION WORDS 1−7 BNR/ISO 1000

361 IR−3 ADIRU−L, ADIRU−R INERTIAL ALTITUDE BNR 20 40

365 IR−3 ADIRU−L, ADIRU−R INERTIAL VERTICAL SPEED BNR 20 40

366 IR−3 ADIRU−L, ADIRU−R N−S VELOCITY BNR 50 100

367 IR−3 ADIRU−L, ADIRU−R E−W VELOCITY BNR 50 100

377 MCDU−2 MCDU−L, MCDU−R MCDU ID DECIMAL 93 BCD

377 P RINTER−1 PRINTER PRINTER ID DECIMAL 40 BCD 1000


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MAINTENANCE BITE PAGES

1. Accessing the Maintenance BITE Pages

There are several Maintenance BITE pages and sub−system test pages available to the groundcrew via the FMCS display units while the aircraf t is on the ground. These pages provide a greatdeal of information that the ground crew can use to make determinations concerning the health ofthe FMS. When the ACARS option is available, the BITE data may also be downloaded.

The sub−systems included are as follows:

NEW GENERATION (NG) AIRPLANES(737−600/700/800)

FMC

Display Units(CDU, MCDU, FANS MCDU, ALT NAV MCDU)

DFCS

A/T

ADIRS

CDS DEU

EEC

APU

FQIS

These units perform their own BITE testing, and share the FMCS to display the information.

A. FMCS Display Unit BITE

The FMCS display units contain their own individual Maintenance BITE pages that can be ac-cessed by the ground crew. Provisions have been made to allow accessing the display unitBITE whether the FMC is operational or failed.

(1) When the FMC is operational, the FMCS display unit BITE is accessed from the FMCSBITE INDEX page LCD CDU prompt (LSK 5R).

(2) When the FMC is failed, enter “BIT” into the scratch pad, and press LSK 5R.

The FMCS display unit software configuration data is also available at this top level. During the

same conditions indicated above, enter CRC and press LSK 5L. The CDU SW CONFIG pagewill be displayed.

B. FMC BITE

The FMC BITE is accessed from the INIT/REF INDEX page (ref Figure 101) MAINT prompt(LSK 6R), and are only available while the aircraft is on the ground. The INIT/REF INDEX page

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may be displayed from most operational flight page displays by selecting the INDEX prompt(LSK 6L).

Another option is to press the INIT REF key and then select the INDEX prompt on the page thatis displayed (most likely an initialization page).

In an MCDU or FANS MCDU, the MENU page may be displayed. Selecting the FMC prompt(LSK 1L) will display the IDENT page. Selecting the INDEX prompt on the IDENT page will dis-play the INIT/REF INDEX page.

I N I T / REF I NDEX 1 / 1



<POS MSG RECAL L >

<PERF ALTN DEST>

<TAKEOFF

<APPROACH SEL CONF I G>

<OFFSET MA I NT>

(737−600/700/800/900)

INIT/REF INDEX PAGE ON THE GROUND

* INDICATES OPTIONS

*

*

*

*

Initalization/Reference Index PageFigure 101

2. Maintenance BITE Page Maps

Figures 102 through 104 provide flowchart style maps of the FMCS Maintenance BITE pages.These maps can be used as a guide to manuever through the pages.

Page titles are listed in the boxes, prompts are shown next to the flow lines, and keys are showngraphically.

Figure 102 maps the display unit BITE pages.

Figure 103 maps the FMCS BITE pages with single FMC installations.

Figure 104 maps the FMCS BITE pages with dual FMC installations.

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FMCMENU

FLIGHT PAGECDU MCDU/FANS MCDUWITH

INDEX PROMPT

C

CDU SW

CDU MAINTCONFIG

BITE INDEX

FMC FAILEDFMC

INIT/REFINDEX

EXIT

EXIT

MAINT

CDU MAINTBITE INDEX

EXIT

R C B I TMAINT BITE

INDEX

LCD CDU

FMCS

OR

(LSK 5L) (LSK 5R)

FMCS BITE

CDU DISPLAYCDU COLORCDU KEYCDU BIT

TEMPP/SCDU SWCDU

CDU BIT

CDUCDU LAMPLIGHT

DSPY INDEX

DSPY CYCLEXX FAULTS

FAULTS KEY TEST COLOR TEST DISPLAY TEST

CONFIG SW OPTIONS P/S TEMP

CONFIGURATION OPTIONS SENSORS SENSORS

TEST TEST TEST

SENSORS TEST CALIBRATION

LIGHT LAMP TEST CALIBRATION

OPERATIONAL

Display Unit Maintenance BITE Pages MapFigure 102

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ADIRS CDS

ADIRS BITE

CDS BITE

INDEX

INDEX*

*

* − SELECTING THE INDEX PROMPT RETURNS THE DISPLAY TO THE MAINT BITE INDEX PAGE.** − SELECTING THE INDEX PROMPT RETURNS THE DISPLAY TO THE FMCS BITE PAGE.

MODEL/ENG

FMCSMODEL/ENG

CFG**

ENGINE

ENGINE/EXCEEDBITE INDEX

*

APU

APU BITETEST

*

FGIS

FQIS BITETEST

*

FMCMENU

FMCOR

FMCPROMPTBLANKED

FMC BITE NOT AVAILABLE

MCDUFANS MCDU CDU

ANYFLIGHTPAGE

MENU

MCDUFANS MCDU

INDEX

INIT/REFINDEX

MAINT

MAINT BITEINDEX

FMC

FMCS DATALOADER

FMCS

DFCSA/T

FMCS BITE

DFCS BITEA/T BITE

INDEX

TESTTEST* *

1/2

*

FIXED

FMCS FIXED

DISCRETES

ANALOG

SENSORS

SENSOR

CDU

FMCS CDU

INFLT

FMCS IN FLT

SW

FMCS

FAULTTESTOUTPUTS OPTIONS

TEST**

FMCS DSPLYTEST

FMCS KEYTEST

STATUS**

1 0 0

(LSK 6R)

SENSORDATA

DISC**

OUTPUTS**

PERF

FMCS PERF

FACTRIRS

FMCS IRS

MONITR

FACTORS**

MONITOR**

FAULTS**

3 0 0

(LSK 6R)

FMCS FLTSELECT

FMCSFLIGHT n

SW OPTIONS

DOWNLOAD

DSPLYTEST

KEYTEST

*

FMCS BITE2/2*

NEXTPAGE

PREVPAGE

H/WCONFIG

FMCS H/WCONFIG

**

**

CDS DEU 1

ENGINE 1

MAINT/BITECDS DEU 2MAINT/BITE

DEU 1 DEU 2

BITE TESTENGINE 2BITE TEST

ENGINE 1BITE TEST

ENGINE 2BITE TEST

ENGINEEXCEEDANCES

EXCEEDANCESENGINE 2CH A ONLY

ENGINE 1CH A ONLY

ENGINE 2ENGINE 1

Single FMC Maintenance BITE Pages MapFigure 103

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FMC

ANYFLIGHTPAGE

MENU

MCDUFANS MCDU

INDEX

INIT/REFINDEX

MAINT

MAINT BITEINDEX

FMCS

XX FMCS

INDEX

BITE

* − SELECTING THE INDEX PROMPT RETURNS THE DISPLAY TO THE MAINT BITE INDEX PAGE.** − SELECTING THE INDEX PROMPT RETURNS THE DISPLAY TO THE FMCS BITE PAGE.

FIXED

FMCS FIXED

DISCRETES

ANALOG

SENSORS

SENSOR

CDU

FMCS CDU

INFLT

FMCS IN FLT

SW

FMCS

FAULTTESTOUTPUTS OPTIONS

TEST**

FMCS DSPLYTEST

FMCS KEYTEST

STATUS**

1 0 0

(LSK 6R)

SENSORDATA

DISC**

OUTPUTS**

PERF

FMCS PERF

FACTRIRS

FMCS IRS

MONITR

FACTORS**

MONITOR**

FAULTS**

3 0 0

(LSK 6R)

FMCS FLTSELECT

FMCSFLIGHT n

SW OPTIONS

DSPLYTEST

KEYTEST

1/2

NEXTPAGE

PREVPAGE

H/WCONFIG

FMCS H/WCONFIG

**

**

FMCS BITE*

*

XX FMCSBITE2/2*

CROSSLOAD

OP PROGRAMCROSSLOAD

DATABASECROSSLOAD

FMC LEFT

FMC RIGHTOR

INDICATES WHICH FMCBITE IS ACCESSED BASEDUPON PROMPT SELECTED

INDEX

INDEX

FMC LEFT

FMC RIGHTOR

DISPLAYED WHENBITE IS AVAILABLE

FMC LEFT BITE INOP

FMC RIGHT BITE INOPOR

DISPLAYED WHENBITE IS NOT AVAILABLE

ADIRS CDS

ADIRS BITE

CDS BITE

INDEX

INDEX*

*

ENGINE

ENGINE/EXCEEDBITE INDEX

*

APU

APU BITETEST

*

FGIS

FQIS BITETEST

*

DFCSA/T

DFCSA/T BITETETEST

* *

CDS DEU 1

ENGINE 1

MAINT/BITECDS DMAINT

DEU 1 DEU 2

BITE TESTENGINE 2BITE TEST

ENGINE 1BITE TEST

ENGINE 2BITE TEST

ENGINEEXCEEDANCES

EXCEEDANCESENGINE 2CH A ONLY

ENGINE 1CH A ONLY

ENGINE 2ENGINE 1

FMC

FMCS DATALOADER

*

DOWNLOAD

Dual FMC Maintenance BITE Pages MapFigure 104

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3. Maintenance BITE Descriptions

The maintenance BITE display pages are divide in groups covering FMC BITE, FMCS display unitBITE, and FMS sub−system BITE that is accessible via the FMC.

Figure 105 contains a mini−index table to rapidly locate the display descriptions in this manual. Themini−index table is listed in display page name sequence and includes the page title (displayed inpage header), indicators for single or dual type of installation, aircraft type, and the sub−system.

PAGE DISPLAY NAME − name of the page display.

TITLE − page title displayed in line 1 when the page is viewed. When the title begins with“FMC−X”, the page refers to dual installations only. When the title begins with “(FMC−X)”, thepage refers to both dual and single installations, and in most cases the title is the only difference.

INST TYPE (Installation Type);

S − single.

D − dual.

B − both.LRU (Line Replaceable Unit) − Acronym of FMS sub−system the page display applies to.

PAGE − manual page number that the description begins on.

PAGE DISPLAY NAME TITLE INSTTYPE

LRU PAGE

Autothrottle BITE Test A/T BITE TEST B A/T 172

Air Data Inertial ReferenceSystem BITE Index

ADIRS BITE INDEX B ADIRS 173

Air Data Inertial Reference

System X BITE

ADIRS X BITE B ADIRS 173

Air Data Inertial ReferenceSystem L & R Inertial Refer-ence Ground BITE Test

ADIRS−IR L+R BITE B ADIRS 173

Air Data Inertial ReferenceSystem L & R Air Data Refer-ence Ground BITE Test

ADIRS−ADR L+R BITE B ADIRS 173

Air Data Inertial ReferenceSystem Maintenance CodesBITE Test

ADIRS MAINT CODES B ADIRS 173

Analog Discretes ANALOG DISC S FMCS 139

Analog Discretes FMC−X ANALOG DISC D FMCS 140

Auxiliary Power Unit BITETest

APU BITE TEST B APU 177

Display Page IndexFigure 105 (Sheet 1)

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PAGE DISPLAY NAME PAGELRUINSTTYPE

TITLE

CDU BIT Display Index CDU BIT DSPLY INDEX B FMCS Display 153

CDU Calibration CDU CALIBRATION B FMCS Display 168

CDU Color Test CDU COLOR TEST B FMCS Display 157

CDU Configuration CDU CONFIGURATION B FMCS Display 159

CDU Display Test CDU DSPLY TEST B FMCS Display 158

CDU Key Test (CDU) CDU KEY TEST B FMCS Display 156

CDU Lamp Test CDU LAMP TEST B FMCS Display 167

CDU Light Sensors LIGHT SENSORS B FMCS Display 165

CDU Maintenance BITE In-dex

CDU MAINT BITE INDEX B FMCS Display 151

CDU Power Supply Sensors P/S SENSORS B FMCS Display 162

CDU Software Options CDU SW OPTIONS B FMCS Display 160

CDU Temperature Sensors TEMP SENSORS B FMCS Display 163

Common Display SystemBITE Index

CDS BITE INDEX B CDS 174

Common Display SystemDisplay Elect ronics Unit BITEand Maintenance

CDS DEU X BITE/MAINT B CDS 174

Cycle XX Faults CDU BIT DISPLAYCYCLE XX FAULTS

B FMCS Display 154

Data Loader FMCS DATA LOADER B FMCS 111

Digital Flight Control SystemBITE Test

DFCS BITE TEST B DFCS 171

Engine and Engine Excee-dance BITE Index

ENGINE/EXCEED BITE IN-DEX

B EEC 175

Engine Exceedances BITETest

ENGINE/EXCEEDANCES B EEC 175

Engine X BITE Test ENGINE X BITE TEST B EEC 175

Fixed Outputs (FMC−X) FIXED OUTPUTS B FMCS 142

Flight Select (FMC−X) FLIGHT SELECT B FMCS 125

Flight Number (FMC−X) FLIGHT n B FMCS 127

FMCS BITE Index FMCS BITE D FMCS 117


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PAGE DISPLAY NAME PAGELRUINSTTYPE

TITLE

FMCS BITE Index (XX) FMCS BITE D FMCS 119

FMCS CDU Test FMCS CDU TEST B FMCS 129

FMCS Display Test FMCS DSPLY TEST B FMCS 132

FMCS Key Test FMCS KEY TEST B FMCS 130

Fuel Quantity Indicating Sys-tem BITE Test

FQIS BITE TEST B FQIS 178

Hardware Configuration (FMC−X) H/W CONFIG B FMCS 149

In−Flight Fault IN FLT FAULTS S FMCS 121

In−Flight Fault FMC−X IN FLT FAULTS D FMCS 123

Inertial Reference SystemMonitor

(FMC−X) IRS MONITOR B FMCS 148

Maintenance BITE Index MAINT BITE INDEX B FMCS 115

Menu (MCDUs) MENU B FMCS Display 113

Model/Engine Configuration FMC−X MODEL/ENG CFG B FMCS NO TAG

Performance Factors (FMC−X) PERF FACTORS B FMCS NO TAG

Sensor Status SENSOR STATUS S FMCS 133

Sensor Status FMC−X SENSOR STATUS D FMCS 135

Sensor Data (FMC−X) SENSOR DATA B FMCS 137

Software Options (FMC−X) SW OPTIONS B FMCS NO TAG


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The following descriptions provide detailed information as well as required and elective buttonpushes to maneuver through the displays. When the line select keys are shown next to the displayand are not shaded, they are for line reference only. They are shaded gray to indicate that the but-ton is pressed. Whenever possible, the displays are grouped by access sequence (i.e., an indexpage is followed by all of the displays accessible from that index page).

Software options are included in the descript ions provided. These options are identified as “AirlinesSelected Options” and are blanked on the displays when not subscribed to.

The FMC Maintenance BITE pages begin on page 111.

The FMCS display unit Maintenance BITE pages begin on page 151.

The FMS Sub−system Maintenance BITE pages begin on page 170.

NOTE: The maintenance BITE pages for any given unit are only accessible when the unit is ishealthy enough to operate (could be at reduced capability). The maintenance BITEfunction for one unit cannot be directly accessed from another unit.

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4. FMC Maintenance BITE Pages

A. Data Loader Page

The DATA LOADER page provides control and status of the loading operation.

(1) Page Access

Automatically displayed when the FMC or display unit is selected and the software disk isinserted into the data loader.

DATA LOADER

CURRENT RECORD 4 4 4 4

TOTAL RECORDS 4 3 9 6

− − − − LOAD IN PROGRESS − − − −

OPS LOAD I NG

(2) Prompt Selections

None

(3) ACARS Prompt

None

(4) Next Higher Level

None

(5) Data Fields

Data fields provide status of the operation as follows:

(a) CURRENT RECORD − displays the number of records that have been successfullystored in the FMC or FMCS display unit memory.

(b) TOTAL RECORDS − displays the total number of records to be transferred from thedisk.

(c) Line 7 displays the status of the load operation.

1 LOAD IN PROGRESS − displayed while all of the records are being trans-ferred to the FMC or FMCS display unit.

2 LOAD VALIDATING − displayed after all records are transferred and the datais being validated.

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3 LOAD COMPLETE − displayed after validation check determines the trans-ferred data is correct.

4 LOAD FAILURE − displayed whenever the load operation failed.

(d) Line 9 − displays DATA LOAD INOP when the transfer operation fails.

(e) Line 10 − displays status information about the data loader.

1 LOADING FONTROM (FMCS display unit only) − displayed when the FON-TROM character set is being transferred. The record count will not updateand a graphical representation of the load progress is displayed in the scratchpad.

2 EXCEEDS CDU MEMORY (FMCS display unit only) − displayed when thecontents of the disk inserted into the data loader requires more memory stor-age than is currently available in the display unit.

3 CHECK DBL OR INTERFACE − displayed when communications with the data

loader is lost after the transfer has started.

4 RESET COUNT EXCEEDED − displayed after five unsuccessful attempts atloading.

5 OPS INCOMPATIBLE − displayed when incorrect OFP or data is contained onthe disk inserted into the data loader.

6 CHECK MEDIA − displayed when a portion of the data on the disk is unusable.

(f) Line 11 − displays general status of the data being loaded.

1 OPS LOADING − displayed during the load operation.

2 OPS LOADED − displayed after the load operation is completed.

3 OPS FAIL − displayed when the load operations failed to complete.

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B. Menu Page (MCDUs Only)

The MENU page provides a selectable list of the FMS sub−systems that can make use of theFMCS display unit (must be connected to MCDU). The FMC is the default active (<ACT>) sub−system (unless FMC is failed). The other sub−systems must be selected.

In the independent mode (Switching mode not enabled in MCDU), up to 5 FMS sub−systemsmay be connected to the FMCS display unit. When the Switching Mode is enabled, one of thesub−systems may be paired. Pairing a sub−system allows both the left and right units to beconnected and accessed via one prompt. Selecting the prompt for a paired sub−system causescommunications to begin with the primary unit. If communications with the primary fails, thesecondary unit is automatically selected.

Only one sub−system may be active at any time. When a sub−system is placed on hold(<HLD>), the MCDU maintains communications with that sub−system and keeps the storeddata current.

Prompts are blanked when communications with a sub−system fails. In dual systems, theprompts are not blanked unless both LRUs fail.

(1) Page Access

Automatically displayed when the FMC has failed and another sub−system is not active.

MENU key on MCDUs.

MENU

<FMC <ACT >

<ACARS <HLD>

<DFDAU

ACARS<LOGOFF

MCDU OR FANS MCDU WITH UPDATE 1ANY AIRCRAFT TYPE


MENU

<FMC <ACT >

<ACARS <HLD>

<DFDAU

ACARS<ALT NAV LOGOFF>

MCDU OR FANS MCDU WITH UPDATE 2ANY AIRCRAFT TYPE



FMS sub−systems (LSK 1L through LSK 5L) when displayed

(LSK 6L or LSK 6R)

LOGOFF − displayed for any sub−system placed on hold.

HOLD − displayed when a sub−system (not FMC) is active

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(3) ACARS Prompt

None


None

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C. Maintenance BITE Index Page

The Maintenance BITE Index page is the main access page for the MAINT BITE displays. Itallows access to maintenance functions, FMS systems status, systems tests.

(1) Page Access

MAINT prompt (LSK 6R) on INIT/REF INDEX page.

INDEX prompt (LSK 6L) on any page access from this page.

MA I NT B I TE I NDEX 1 / 1

<FMCS ENG I NE>

<DFCS APU>

<A / T FQ I S>

<ADIRS

<CDS




(a) FMCS (LSK 1L)

1 single instl. − displays the FMCS BITE Index (pg. 119)

2 dual instl. − displays the FMCS BITE Index (PG. 117)

(b) DFCS (LSK 2L) − displays the DFCS BITE Test (ref pg. 171)

(c) A/T (LSK 3L) − displays the A/T BITE Test (ref pg. 172)

(d) ADIRS (LSK 4L) − displays the ADIRS BITE INDEX (ref pg. 173)

(e) CDS (LSK 5L) − displays the CDS BITE INDEX (ref pg. 174)

(f) ENGINE (LSK 1R) − displays the ENGINE/EXCEED BITE INDEX (ref pg. 175)

(g) APU (LSK 2R) − displays the APU BITE TEST (ref pg. 177)

(h) FQIS (LSK 3R) − displays the FQIS BITE TEST (ref pg. 178)

(i) FMC DOWNLOAD − initiates the FMC File System Download function(ref Section 1)

(3) ACARS Prompt

None

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INDEX (LSK 6L) − returns display to INIT/REF INDEX page

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D. FMCS BITE Index Page (Dual Instl.)

In the dual installation, this page allows the ground crew to determine which FMC is available,allows selection of the of the desired FMC’s BITE data for display, and also provides access tothe crossload function allowing program and database transfers to the secondary FMC via theISB or Ethernet buses. This is the first page to display the primary FMC indicator in the firstposition of the title line. This will inform the operator which FMC is the designated primary asdetermined by the Source Select Switch.

(1) Page Access

FMCS prompt (LSK 1L) on the MAINT BITE INDEX page.

INDEX prompt (LSK 6L) on the MAINT BITE page.

Automatically when on any FMCS BITE page when the secondary FMC BITE data is se-lected and is not available.

² FMCS B I TE 1 / 1

< FMC L EF T

< FMC R I GHT



When the BITE data is not available for an FMC, selection of that FMC is not allowed.

The prompt selection caret is removed, and the prompt is changed to a status line as indi-cated below.

² FMCS B I TE 1 / 1

< FMC L EF T

F M C R I GH T B I T E I N O P

< I NDEX


(a) FMC LEFT (LSK 1L) − displays the FMCS BITE index page 1 for the leftFMC (ref pg. 119)

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(b) FMC RIGHT (LSK 2L) − displays the FMCS BITE index page 1 for the rightFMC (ref pg. 119)

(c) CROSSLOAD − initiates the FMC crossload function (ref Section 1). This promptis blanked when an FMC is failed.

(3) ACARS Prompt

None


INDEX (LSK 6L) − returns to the MAINT BITE INDEX page (ref pg. 115)

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E. FMCS BITE Index Page

The FMCS BITE index page 1 provides access to the different FMCS BITE data and functional-ity tests for the FMCS. This includes access to the FMCS display unit BITE.

(1) Page Access

FMCS prompt (LSK 1L) on the MAINT BITE INDEX page (single FMC instl.).

FMC LEFT (LSK 1L) prompt on the dual FMCS BITE page (dual FMC instl.).

FMC RIGHT (LSK 2L) prompt on the dual FMCS BITE page (dual FMC instl.).

NEXTPAGE or PREV

PAGE key from the FMCS BITE index page 2.

FMCS B I TE 1 / 2



<CDU TEST SW OPT I ONS>

<SENSORS PERF FACTR>

<D I SCRETES I RS MONI TR>

<F I XED OUTPUTS LCD CDU>







< I NDEX

FMCS B I TE 2 / 2

<H / W CONF I G

< I NDEX

³ RT FMCS B I TE 2 / 2

<H / W CONF I G

< I NDEX

SINGLE INSTALLATIONS DUAL INSTALLATIONS


(a) INFLT FAULT (LSK 1L)

1 single instl. − displays the IN FLT FAULTS (ref pg. 121)

2 dual instl. − displays the FMC−X IN FLT FAULTS page (ref pg. 123)

(b) CDU TEST (LSK 2L) − displays the FMCS CDU TEST page (ref pg. 129)(This test is driven from the FMC.)

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(c) SENSORS (LSK 3L)

1 single instl. − displays the SENSOR STATUS page (ref pg. 133)

2 dual instl. − displays the FMC−X SENSOR STATUS page (ref pg. 135)

(d) DISCRETES (LSK 4L)

1 single instl. − displays the ANALOG DISC page (ref pg. 139)

2 dual instl. − displays the FMC−X ANALOG DISC page (ref pg. 140)

(e) FIXED OUTPUTS (LSK 5L) − displays the (FMC−X) FIXED OUTPUTS page(ref pg. 142)

(f) MODEL/ENG (LSK 1R) − displays the FMC−X MODEL/ENG CFG page (ref pg.NO TAG)

(g) SW OPTIONS (LSK 2R) − displays the (FMC−X) SW OPTIONS page (ref pg.

NO TAG)

(h) PERF FACTR (LSK 3R) − displays the (FMC−X) PERF FACTORS page(ref pg. NO TAG)

(i) IRS MONITR (LSK 4R) − displays the (FMC−X) IRS MONITOR page (ref pg. 148)

(j) LCD CDU (LSK 5R) − displays the CDU MAINT BITE INDEX page (ref pg. 151)

NOTE: When selected, the BITE data and functionality are generated by theFMCS display unit.

² LT FMCS B I TE 1 / 2



(3) ACARS Prompt

When ACARS is installed and the airlines has a user defined maintenance prompt, theACARS prompt (LSK 6R) is displayed on page 1 of the designated primary FMC. Selec-tion will downlink the selected FMC maintenance BITE data.


INDEX (LSK 6L) − returns to the MAINT BITE INDEX page (ref pg. 115)

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F. In−Flight Faults Page (Single Instl.)

The (FMC−X) IN FLT FAULTS page presents an overview of the fault data collected for the lastnine flights and the current on−ground period for the FMCS and the sub−systems connected tothe FMC(s). These pages provide a top level picture of the FMS health, and access to moredetailed information concerning faults and failures detected.

When faults or failures occur, the FMC logs the detailed information and tags the sub−system orequipment with the flight number it was detected in. This includes the FMCs fault/failure dataproviding it is healthy enough to perform the task.

(1) Page Access

INFLT FAULT prompt (LSK 1L) on the FMCS BITE page (ref pg. 119)

NEXTPAGE key from the IN FLT FAULTS page 3

PREVPAGE key from the IN FLT FAULTS page 2

INDEX prompt (LSK 6L) on the (FMC−X) FLIGHT SELECT page (ref pg 125)

I N FLT FAULTS 3 / 3

L R U

A C A R S

C D U L E F T

C D U R I G H T

F M C

A / T

ACARS>< I NDEX


L R U

A D I R S L E F T

A D I R S R I G H T

D F C S

D M E L E F T

D M E R I G H T 3

F Q I S

9

C D S D E U L E F TC D S D E U R I G H T

< I NDEX


L R U

V O R L E F T

V O R R I G H T 2

I L S / M M R L E F T

I L S / M M R R I G H T

MM R L E F T

MM R R I G H T

C L O C K

< I NDEX

NOTE: The CLOCK (on page 2/2) refers to the captains clock. If the clock fails, the FMC willuse the last time data received and update it from the FMC computed time. The CLOCKstatus line will indicate the fault status.

The display of some sub−system status lines will depend on equipment installation, air-craft features, and software option codes. When the criteria for the display line is notmet, that line will be blanked, but its position preserved.

(a) ILS/MMR is not displayed when GPS is installed.

(b) MMR in−flight status is only displayed when GPS is installed.

(c) ACARS is displayed only when the ACARS MU is installed.

(d) A/T is displayed only when the aircraft is configured with the Quiet Climb feature.

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Entering code “300” into the scratch pad and selecting LSK 6R displays the (FMC−X)FLIGHT SELECT page (ref pg. 125).

(3) ACARS Prompt



INDEX prompt (LSK 6L) − displays the FMCS BITE index page 1 (ref pg. 119).

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G. In−Flight Faults Page (Dual Instl.)

The (FMC−X) IN FLT FAULTS page presents an overview of the fault data collected for the lastnine flights and the current on−ground period for the FMCS and the sub−systems connected tothe FMCs. These pages provide a top level picture of the FMS health, and access to more de-tailed information concerning faults and failures detected.

When faults or failures occur, the FMC logs the detailed information and tags the sub−system orequipment with the flight number it was detected in. This includes the FMCs fault/failure dataproviding it is healthy enough to perform the task. The header in line 1 lists the current groundperiod (G) and the last nine flights (1 through 9) with 9 being the oldest flight. The faults areindicated according to which FMC detected the problem (L=left, R=right, and B=both).

(1) Page Access

INFLT FAULT prompt (LSK 1L) on the FMCS BITE page (ref pg. 119)

NEXTPAGE key from the IN FLT FAULTS page 3

PREVPAGE key from the IN FLT FAULTS page 2

INDEX prompt (LSK 6L) on the (FMC−X) FLIGHT SELECT page (ref pg 125)

²FMC−L I N F LT FAULTS 1 / 3

L R U G 1 2 3 4 5 6 7 8 9

A D I R S L E F T

A D I R S R I G H T

D F C S

D M E L E F T

D M E R I G H T

F Q I S B

C D S D E U L E F T

C D S D E U R I G H T



< I NDEX


L R U G 1 2 3 4 5 6 7 8 9

V O R L E F T

V O R R I G H T R



MM R L E F T

MM R R I G H T

C L O C K L E F T

C L O C K R I G H T

< I NDEX

The display of some sub−system status lines will depend on equipment installation, air-craft features, and software option codes. When the criteria for the display line is notmet, that line will be blanked, but its position preserved.

(a) ILS/MMR is not displayed when GPS is enabled.

(b) MMR in−flight status is only displayed when GPS is installed.

(c) ACARS is displayed when ACARS is installed.

(d) A/T is displayed when the aircraft is configured with the Quiet Climb featureinstalled.

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Entering code “300” into the scratch pad and selecting LSK 6R displays the (FMC−X)FLIGHT SELECT page (ref pg. 125).

(3) ACARS Prompt



INDEX prompt (LSK 6L) − displays the FMCS BITE index page 1 (ref pg. 119).

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H. Flight Select Page

The (FMC−X) FLIGHT SELECT page provides access to more detailed failure/fault data per-taining to the indications displayed on the (FMC−X) IN FLT FAULTS pages.

The flights and ground period are separately selectable to obtain the data pertaining to the peri-od selected. Only the periods that recorded failure/fault data are displayed, all other promptsare blanked.

FLIGHT G prompt refers to the current ground period.FLIGHT 1 is the last flight flown.FLIGHT 9 is the ninth flight prior to this ground period.

(1) Page Access

Single instl. − entering code “300” into the scratch pad and selecting LSK 6R on the INFLT FAULTS pages (ref pg. 121)

Dual instl. − entering code “300” into the scratch pad and selecting LSK 6R on the FMC−X

IN FLT FAULTS pages (ref pg. 123)

²FMC−L F L I GHT SE LECT 1 / 1

<F L I GHT G FL I GHT 5 >

<F L I GHT 1 FL I GHT 6 >






F L I GHT SE LECT 1 / 1

<FL I GHT G FL I GHT 5 >

<FL I GHT 1 FL I GHT 6 >






SINGLE INSTALLATION DUAL INSTALLATION


(a) FLIGHT X prompts (LSKs 1L − 5L, and 1R − 5R)

When a fault is detected and displayed on the (FMC−X) IN FLT FAULTS page, thecorresponding flight select prompt is displayed.

1 Selecting a prompt displays the (FMC−X) FLIGHT n page (ref pg. 127).

2 All flights without fault data are blanked.

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In the following example, faults/failures were detected by the left FMC in flights 2,5, and 9 as shown on the FMC−L IN FLT FAULTS pages. The correspondingFMC−L FLIGHT SELECT page is shown. The operator may then select the de-sired FLIGHT n prompt (LSK 3L, LSK 1R, or LSK 5R) to display the detailed infor-mation.

²FMC−L F L I GHT SE LECT 1 / 1

FL I GHT 5 >

<FL I GHT 2

FL I GHT 9 >



RESULTS IN


L R U G 1 2 3 4 5 6 7 8 9

A D I R S L E F T

A D I R S R I G H T

D F C S

D M E L E F T

D M E R I G H T

F Q I S B

C D S D E U L E F T

C D S D E U R I G H T



< I NDEX


L R U G 1 2 3 4 5 6 7 8 9

V O R L E F T

V O R R I G H T R



MM R L E F T

MM R R I G H T

C L O C K L E F T

C L O C K R I G H T

< I NDEX

(3) ACARS Prompts



INDEX prompt (LSK 6L) − returns display to:

(a) single instl. − the IN FLT FAULTS page(ref pg. 121)

(b) dual instl. − the FMC−X IN FLT FAULTS page (ref pg. 123)

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I . Flight Number Page

The (FMC−X) FLIGHT n page displays a detailed status record for each of the faults and fail-ures logged during the flight selected on the (FMC−X) FLIGHT SELECT page. Each sub−sys-tem a fault or failure was logged for is listed along with details of the problem. The number offollow−on pages will vary with the number of fault or failure records generated.

(1) Page Access

FLIGHT n prompt (LSKs 1L − 5L, or 1R − 5R) on the (FMC−X) FLIGHT SELECT page (refpg. 125)

NEXTPAGE or PREV

PAGE key when multiple pages exist

/ /

² FMC−L F L I GHT 2 1 / 1

3 1 − A U G − 0 1A D I R S − L A D R S 1 8 0 7 Z


MM R − R I L S I 1 8 3 5 Z

L O C D E V I A T I O N S S M

A D I R S − R I R S 1 8 3 5 Z

P I T C H A N G L E R E A S O N



SINGLE INSTALLATION DUAL INSTALLATION

/

/

² FMC− L F L I GHT 2 1 / 1

3 1 − A U G − 0 1

A D I R S − L A D R S 1 8 0 7 Z


DATE

FIRST OCCURRENCE


FLIGHT NUMBER

ORFAILED TEST


SUB−SYSTEM CODE

/ /

FL I GHT 2 1 / 1

3 1 − A U G − 0 1A D I R S − L A D R S 1 8 0 7 Z


MM R − R I L S I 1 8 3 5 Z


A D I R S − R I R S 1 8 3 5 Z

P I T C H A N G L E R E A S O N



(a) FLIGHT NUMBER − indicates the FMC flight number from the (FMC−X) FLIGHTSELECT page.

(b) DATE − the date the first fault was listed for this flight number page. In the case ofFLIGHT G page, the date may not be determinable. If this occurs, the date field

will be blanked.

(c) SUB−SYSTEM CODE − the sub−system the fault is listed against.

(d) STEADY/INTERMITTENT INDICATOR − indicates whether the FMC assumes thefault listed to be steady or intermittent (refer to section1).

(e) FIRST OCCURRENCE − the time the fault was logged the first time it occurred.

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(f) LABEL CODE/FAILED TEST − refer to section 1.

(g) MONITOR CODE − refer to section 1.

Fault records are listed in chronological order according to the time of occurrence.


None

(3) ACARS



INDEX prompt (LSK 6L) − returns to the (FMC−X) FLIGHT SELECT page (ref pg. 125)

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J. FMCS CDU Test Page

The FMCS CDU TEST page allows the ground crew to select between an active test of the dis-play units key operation and interpretation, or to verify the FMC character set. This test is driv-en by the selected FMC.

(1) Page Access

CDU TEST (LSK 2L) prompt on the FMCS BITE index page 1 (ref pg. 119)

FMCS CDU TEST 1 / 1

<KEY TEST DSPLY TEST>



< I NDEX


(a) KEY TEST prompt (LSK 5L) − displays the FMCS KEY TEST page(ref pg. 130)

(b) DSPLY TEST prompt (LSK 5R) − displays the FMCS DSPLY TEST page

(ref pg. 132)

(3) ACARS Prompt

None


INDEX prompt (LSK 6L) − returns to the FMCS BITE index page 1 (ref pg. 119)

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K. FMCS Key Test Page

The FMCS KEY TEST page provides an active test of the display unit key functions. Keys maybe checked to verify they are functional and do not stick. Selecting any key (except as notedbelow) will cause that character to be highlighted, and is displayed in the scratch pad.

INIT REF key − when pressed the first time, will cause INI (line 1) to be highlighted. A secondpress of the key will display the INIT REF INDEX page and exit FMC BITE.

MENU key (MCDU/FANS MCDU) − when pressed displays the MENU page. Select the FMCprompt (LSK 1L) to return to this page.

(1) Page Access

KEY TEST prompt (LSK 5L) on the FMCS CDU TEST page (ref pg. 129)

SINGLE FMC INSTALLATIONS

DUAL FMC INSTALLATIONS

CDU DISPLAY

FMCS KEY TEST 1 / 1

I N I RTE CLB CRZ DESD I R LEG DEP HOL PRO EXE

1 L N1 F I X ABCDE 1R2 L PRE NEX FGH I J 2R3 L 1 2 3 KLMNO 3R4 L 4 5 6 PQRST 4R5 L 7 8 9 UVWXY 5R6 L . 4 + Z D / C 6R−−−−−−−−−−−−−−−−−−−−−−−−

PUSH KEYS TO TESTKEY³ KEY I ND I CAT ES VA L I D<CDU TES T

“ A “ KEY PUSHED

MCDU DISPLAY

FMCS KEY TEST 1 / 1

I N I RTE CLB CRZ DESLEG DEP HOL PRO EXE


PUSH KEYS TO TESTKEY³ KEY I ND I CATES VA L I D<CDU TES T


FANS MCDU DISPLAY

FMCS KEY TEST 1 / 1

I N I RTE FMC ATC VNALEG DEP HOL PRO EXE


PUSH KEYS TO TESTKEY³ KEY I ND I CAT ES VA L I D<CDU TES T


CDU DISPLAY

² FMCS KEY TEST 1 / 1

I N I RTE CLB CRZ DESD I R LEG DEP HOL PRO EXE


PUSH KEYS TO TESTKEY³ KEY I ND I CAT ES VA L I D

<CDU TES T“ A “ KEY PUSHED

MCDU DISPLAY


I N I RTE CLB CRZ DESLEG DEP HOL PRO EXE


PUSH KEYS TO TESTKEY³ KEY I ND I CATES VA L I D


FANS MCDU DISPLAY


I N I RTE FMC ATC VNALEG DEP HOL PRO EXE


PUSH KEYS TO TESTKEY³ KEY I ND I CAT ES VA L I D



None

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(3) ACARS Prompt

None


CDU TEST prompt (LSK 6L) − when pressed two consecutive times, returns to the CDUTEST page (ref pg. 129)

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L. FMCS Display Test Page

The FMCS DSPLY TEST page displays a full screen of the usable characters in both large andsmall font size.

(1) Page Access

DSPLY TEST prompt (LSK 5R) on the FMCS CDU TEST page (ref pg. 129)

−−−FMCS−DSPLY−TEST−− 1 / 1 −´ & ° ³ ± 4 1 2 3 4 5 6 7

8 9 ! ” °F °%°C ’ ( ) * + , − . / 4 1 2 3 4 5 6 7 8 9 : ; < = >? ABCDE FGH I J K LMNOPQRSTUVWXYZ [ \ ] _

A B C D E F G H I J K L M NO P QR S T U V W

X Y Z ²ł ´ & ° ³ ±4 1 2 3 4 5 6 7 8 9 ! ” °F °%°C ’( ) * + , − . / 4 1 2 3 4 5 6 7 8 9 : ; < = > ?

ABCDEFGHI JK LMNOPQRSTUVWXYZ [ \ ] _ A B C D E F G H I J K L M N O

P Q R S T U V W X Y Z ²ł ´ &<CDU−TEST−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−


²−−FMCS−DSPLY−TEST−− 1 / 1 −´ & ° ³ ± 4 1 2 3 4 5 6 7

8 9 ! ” °F °%°C ’ ( ) * + , − . / 4 1 2 3 4 5 6 7 8 9 : ; < = >? ABCDE FGH I J K LMNOPQRSTUVWXYZ [ \ ] _

A B C D E F G H I J K L M NO P QR S T U V W

X Y Z ²ł ´ & ° ³ ±4 1 2 3 4 5 6 7 8 9 ! ” °F °%°C ’( ) * + , − . / 4 1 2 3 4 5 6 7 8 9 : ; < = > ?

ABCDEFGHI JK LMNOPQRSTUVWXYZ [ \ ] _ A B C D E F G H I J K L M N O

P Q R S T U V W X Y Z ²ł ´ &<CDU−TEST−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−−


None

(3) ACARS Prompt

None


CDU TEST prompt (LSK 6L) − returns to the FMCS CDU TEST page (ref pg. 129)

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M. Sensor Status Page (Single Instl.)

The SENSOR STATUS page displays the high level status of the sub−systems providing theFMC with data. Four status indicators are used to represent the FMS health; OK, FAIL, TEST,and − − − −.

The status “OK” indicates that the FMC has not had problems communicating with the sub−system.

The status “FAIL” indicates that the FMC has stopped using the sub−system due to the unitdeclaring itself failed, or communications with the sub−system has ceased, or the data re-ceived from the sub−system is unusable.

The status “TEST” indicates that the sub−system is performing self−test.

The status “− − − −” indicates that the sub−system is not connected to the FMC. For exam-ple, there is one ACARS MU which is connected to the FMC. Dashes are displayed for theright side on the ACARS line (page 2) because it is not in the aircraft, and is not expected tobe connected.

The SENSOR STATUS page also provides access to specific fault/failure data logged by the

FMC. Unlike the In Flight Faults pages, the information listed on these pages will only be cur-rent data.

(1) Page Access

SENSORS prompt (LSK 3L) on the FMCS BITE index page 1 (ref pg. 119)

NEXTPAGE or PREV

PAGE key from the SENSOR STATUS page 2.

SENSOR STATUS 1 / 2

L R U L E F T R I G H T

V O R O K O K

D M E T E S T O KI L S / MM R O K O K

A D I R S O K O K

MM R O K O K

D F C S O K −−−−

F Q I S O K −−−−C L O C K O K −−−−

< I NDEX

The display of some sub−system status lines will depend on equipment installation, air-craft features, and software option codes. When the criteria for the display line is not

met, that line will be blanked, but its position preserved.

PAGE/LINE LRU NOTES

1/3 VOR

1/4 DME

1/5 ILS/MMR ILS/MMR IS BLANK WHEN GPS ISENABLED.

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PAGE/LINE NOTESLRU

1/6 (BLANK)

1/7 ADIRS

1/8 MMR MMR IS DISPLAYED WHEN GPS IS

ENABLED.1/9 DFCS

1/10 (BLANK)

1/11 FQIS

1/12 CLOCK Captains CLOCK ONLY.

2/3 A/T A/T DISPLAYED WHEN QUIETCLIMB FEATURE INSTALLED.

2/4 (BLANK)

2/5 ACARS ACARS IS DISPLAYED WHENACARS FEATURE IS INSTALLED.

2/6 (BLANK)

2/7 CDS DEU


Entering code “100” into the scratch pad and selecting LSK 6R displays the SENSORDATA page (ref pg. 137)

(3) ACARS Prompt

When ACARS is installed and the airlines has a user defined maintenance prompt, theACARS prompt (LSK 5R) is displayed on page 2. Selection will downlink the selectedFMC maintenance BITE data.



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N. Sensor Status Page (Dual Instl.)

The FMC−X SENSOR STATUS page displays the high level status of the sub−systems provid-ing the FMC with data. Four status indicators are used to represent the FMS health; OK, FAIL,TEST, and − − − −:

The status “OK” indicates that the FMC has not had problems communicating with the sub−system.

The status “FAIL” indicates that the FMC has stopped using the sub−system due to the unitdeclaring itself failed, or communications with the sub−system has ceased, or the data re-ceived from the sub−system is unusable.

The status “TEST” indicates that the sub−system is performing self−test.

The status “− − − −” indicates that the sub−system is not connected to the FMC. For exam-ple, there is one ACARS MU which is connected to the FMC. Dashes are displayed for theright side on the ACARS line (page 2) because it is not in the aircraft, and is not expected tobe connected.

The SENSOR STATUS page also provides access to specific fault/failure data logged by the

FMC. Unlike the In Flight Faults pages, the information listed on these pages will only be cur-rent data.

(1) Page Access

SENSORS prompt (LSK 3L) on the FMCS BITE index page 1 (ref pg. 119)

NEXTPAGE or PREV

PAGE key from the SENSOR STATUS page 2.

²FMC−L SENSOR STATUS 1 / 2


V O R O K O K

D M E T E S T O K

I L S / MM R O K O K

A D I R S O K O K

MM R O K O K

D F C S O K −−−−

F Q I S O K −−−−C L O C K O K −−−−

< I NDEX

In a dual installation, the status displayed is the status stored in the FMC indicated in thepage title line (FMC−L or FMC−R).

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The display of some sub−system status lines will depend on equipment installation, air-craft features, and software option codes. When the criteria for the display line is notmet, that line will be blanked, but the position is preserved.

PAGE/LINE LRU NOTES

1/3 VOR1/4 DME

1/5 ILS/MMR ILS/MMR IS BLANK WHEN GPS ISENABLED.

1/6 (BLANK)

1/7 ADIRS

1/8 MMR MMR IS DISPLAYED WHEN GPS ISENABLED.

1/9 DFCS

1/10 (BLANK)

1/11 FQIS

1/12 CLOCK LEFT CLOCK ONLY.2/3 A/T A/T DISPLAYED WHEN QUIET

CLIMB FEATURE INSTALLED.

2/4 (BLANK)

2/5 ACARS ACARS IS DISPLAYED WHENACARS FEATURE IS INSTALLED.

2/6 (BLANK)

2/7 CDS DEU

2/8 FMC

When a sub−system is not connected to the FMC and is not expected to be (i.e., CAPT-CLOCK is connected to the left FMC only), dashes are displayed for status.


Entering code “100” into the scratch pad and selecting LSK 6R displays the SENSORDATA page (ref pg. 137)

(3) ACARS Prompt




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O. Sensor Data Page

The (FMC−X) SENSOR DATA page lists current detailed fault/failure information pertaining tosub−systems with a “FAIL” status listed on the (FMC−X) SENSOR STATUS pages. Unlike the(FMC−X) FLIGHT n page, the data displayed on this page is not retained in history. Oncecleared, or a new flight is started, the data is gone.

When GPS is installed, display lines 3 and 4 are reserved for GPS−L (or GPSSU−L) and lines 6and 7 are reserved for GPS−R (or GPSSU−R). If the GPS maintenance discrete word containsmaintenance status, the status is displayed in the monitor code field. When normal status isindicated, the appropriate lines are blank but remain reserved for the GPS.

(1) Page Access

Enter code “100” into the scratch pad and select LSK 6R on the SENSOR STATUS page(ref pg. 133) or the FMC−X SENSOR STATUS page (ref pg. 135)

Use NEXTPAGE and PREV

PAGE keys to maneuver pages when multiple pages exist.

² FMC− L SENSOR DA TA 1 / 1

A D I R S − L A D R S 1 8 4 7 Z


SENSOR DATA 1 / 1

A D I R S − L A D R S 1 8 4 7 Z


I L S / MM R − R I 1 8 3 4 Z


A D I R S − L I R S 1 8 3 5 Z

P A R I T Y



³ FMC−R SENSOR DATA 1 / 2

MM R − L G P S

G P S M A I N T 4 4 4 4 4 1

A D I R S − L A D R S 1 8 4 7 Z




SINGLE INSTALLATION

DUAL INSTALLATION

FIRST OCCURRENCE

MONITOR CODELABLE CODEOR

FAILED TEST


SUB−SYSTEM CODE

TITLE LINE

TITLE LINE

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(a) SUB−SYSTEM CODE − the sub−system the fault/failure is listed against.

(b) STEADY/INTERMITTENT INDICATOR − indicates whether the FMC assumes thefault listed to be steady or intermittent (refer to section1)

(c) FIRST OCCURRENCE − the time the fault/failure was logged the first time it oc-curred.

(d) LABEL CODE/FAILED TEST − refer to section 1.

(e) MONITOR CODE − refer to section 1.


CLR DSPLY (LSK 6R) − clears the data currently displayed on the page. Once cleared,new faults/failures will be displayed as they are detected. In a dual installation, this op-eration will only clear the sensor data on the selected FMC. The second FMCs BITE datawill remain unaffected.

(3) ACARS Prompt

None.


INDEX prompt (LSK 6L)

(a) single instl. − returns to the SENSOR STATUS page (ref pg. 133)

(b) dual instl. − returns to the FMC−X SENSOR STATUS page (ref pg. 135)

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P. Analog Discretes Page (Single Instl.)

The ANALOG DISC pages list the program discrete inputs read by the FMC at its aircraft con-nector, and provides an indication of the status of each. Refer to Section 1 for detailed discreteinformation.

(1) Page Access

DISCRETES prompt (LSK 4L) on the FMCS BITE index page 1 (ref pg. 119)


PAGE keys to maneuver between pages.

ANA LOG D I SC 1 / 4

L E F T R I G H T

E C S P A C K O N O F F

E C S P A C K H / L L O H I

I S O L V A L V E O P

C OW L A / I C E O F F O N

W I N G A / I C E O F FO L E O SW I T C H G N D

< I NDEX


J A A F L T R U L E S D I S A B L E

K I L OG R A M O P T I O N D I S A B L E

M A G / T R U E M A G

S R C E / D E S T I D E N T L E F T

A S P I R A T E D T A T E N A B L E

° C / ° F D E F A U L T ° C

P E R F C O D E 1

< I NDEX


M O D E L / E N G V A L I D

N O . 1 N O . 2E N G I N E B L E E D O F F O N

S E L C O N F I G M O D E D I S A B L E

< I NDEX


V O R I N H I B I T E N A B L E

F L I G H T N U M B E R E N A B L E

T O G A RW P O S U P D D I S A B L E

T A K E O F F P R O F I L E D I S A B L E

T A K E O F F S P E E D S D I S A B L E

N A V A I D S U P P R E S S E N A B L E

S E L C R S I N H I B I T E N A B L EA C A R S I N S T A L L E D O N




None

(3) ACARS Prompt

When ACARS is installed and the airlines has a user defined maintenance prompt, the

ACARS prompt (LSK 6R) is displayed on page 4. Selection will downlink the selectedFMC maintenance BITE data.


INDEX prompt (LSK 6L) returns display to the FMCS BITE index page 1 (ref pg. 119)

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Q. Analog Discretes Page (Dual Instl.)

The FMC−X ANALOG DISC pages list the program discrete inputs read by the FMC at its air-craft connector, and provides an indication of the status of each. The discretes and status dis-played pertain to the FMC listed in the title line. Refer to Section 1 for detailed discrete informa-tion.

(1) Page Access

DISCRETES prompt (LSK 4L) on the FMCS BITE index page 1 (ref pg. 119)

Automatically when a discrete mismatch is detected (on the ground only and no otherhigher priority mismatch exists)



² FMC− L ANA LOG D I SC 1 / 4

L E F T R I G H T

E C S P A C K O N O F F

E C S P A C K H / L L O H I

I S O L V A L V E O P

C OW L A / I C E O F F O N

W I N G A / I C E O F F

O L E O SW I T C H G N D

< I NDEX



K I L OG R A M O P T I O N D I S A B L EM A G / T R U E M A G



° C / ° F D E F A U L T ° C

P E R F C O D E 1

< I NDEX


M O D E L / E N G V A L I D

N O . 1 N O . 2

E N G I N E B L E E D O F F O N

S E L C O N F I G M O D E D I S A B L E






T O G A RW P O S U P D D I S A B L E

T A K E O F F P R O F I L E D I S A B L E



S E L C R S I N H I B I T E N A B L E

A C A R S I N S T A L L E D O N



When the FMCs determine that adiscrete mismatch exists, the sta-tus of that discrete is highlighted.

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A unique situation may occur when there is a problem with the Source/Destination Identification(SRCE/DEST IDENT on display page 2) discretes. If the discrete inputs are incorrectly readsuch that both FMCs believe they are in the same aircraft location, both FMCs will drop to singleoperating mode (both think they are left, and there is no right). The SRCE/DEST IDENT dis-crete status will not be highlighted when displayed by either FMC as shown below.







° C / ° F D E F A U L T ° C

P E R F C O D E 1

< I NDEX

² FMC−R ANA LOG D I SC 2 / 4






° C / ° F D E F A U L T ° C

P E R F C O D E 1

< I NDEX

LEFT FMC RIGHT FMC


None

(3) ACARS Prompt

When ACARS is installed and the airlines has a user defined maintenance prompt, theACARS prompt (LSK 6R) is displayed on page 4. Selection will downlink the selectedFMC maintenance BITE data.

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R. Fixed Outputs Page

The FMCS FIXED OUTPUTS pages cause the FMC to transmit data to verify specific basicfunctionality. The outputs to the sub−systems listed are active as soon as the pages are se-lected and displayed, then deactivated when the page is left. Each page displays the targetLRU, the annunciator and the state it should be in. These outputs are live data and should beverified in the flight deck.

(1) Page Access

FIXED OUTPUTS prompt (LSK 5L) on the FMCS BITE index page 1 (ref pg. 119)



² FMCS F I X ED OUT PUT S 1 / 2

C H E C K F L T D E C K V A L U E SS E L E C T M A P M O D E O N C P ’ S

T M A “ C R Z “ O F F

“ C L B “ O F F

“ −− − “ O N

“ C O N “ O F F

“ T O “ O F F

“ G A “ O F F

C D S “ F M C I N T E R F A C E O K “

< I NDEX

² FMCS F I X ED OUT PUT S 2 / 2

C H E C K A NN UN C I A T OR S

C D U − “ M S G “ O N

“ F A I L “ O N

“ O F S T “ O N

A A − “ F M C “ A L E R T O N

< I NDEX


None

(3) ACARS Prompt

None

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S. Model/Engine Configuration Page

The (FMC−X) MODEL/ENG CFG page displays the current aircraft and engine configurationstatus. The A/C & ENG TYPE discrete pins are read at power−up and looked up in the loadableperformance data base to obtain the information displayed. When takeoff derates (TO−1/TO−2)do not exist for a configuration, the value is displayed as “NONE”.

When the discrete combination cannot be found in the performance data base or the perfor-mance data base is not loaded, the data fields and headers are blanked with error status dis-played in line 7 (examples shown on next page).

The page examples below reflect updates 10.4A through 10.6 (fixed format). Update 10.7 andlater provides for the display of this page in either a fixed format or a variable text format asdefined within the Model/Engine Data Base (MEDB). If the MEDB is configured for variable for-mat, the headers, text, and font size for the left and right side of the page (columns 2−12) aredisplayed as defined within the data base. Because the page configurat ion is dependent uponthe specific MEDB loaded, an example of the variable text format is not given. When the pageis being displayed in variable text format, the header text ”CONFIG” will be displayed at LSK 4Lwith a 3 − digit configurat ion identifier directly below. When the MEDB is configured for fixed

format, the page will be displayed as shown below.

The only difference in the display between single and dual installations is the page title.

(1) Page Access

MODEL/ENG prompt (LSK 1R) on the FMCS BITE index page 1 (ref pg. 119)

WITHOUT THRUST BUMP WITH THRUST BUMP

²FMC− L MODEL / ENG C FG 1 / 1

M O D E L E N G I N E

7 3 7 − 7 4 4C CFM5 6 −7B

B R A K E O P T E N G I N E O P TCAT _B SACE N G R A T I N GS

F U L L 2 4 K

T O − 1 2 2 K

T O − 2 2 4 K

B U M P 2 6 K

< I NDEX


M O D E L E N G I N E

7 3 7 − 6 4 4 CFM56−7BB R A K E O P T E N G I N E O P T

CAT _B DACE N G R A T I N GS

F U L L 2 6 K

T O − 1 2 4 K

T O − 2 NONE

< I NDEX


None

(3) ACARS Prompt

None

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(5) Error Status

Four status messages are used to identify problems concerning the model and engineconfiguration.

NOTE: Regardless of the types of errors that may exist concurrently, a parity errorhas the highest priority and will be displayed first.

(a) PARITY ERROR − displayed when the A/C & ENG TYPE discrete pins are read bythe FMC, and the parity is incorrect.


PAR I TY ERROR

< I NDEX

(b) INVALID − displayed when a performance data base is not loaded in the FMC.


I N VA L I D

< I NDEX

(c) PROGRAM PIN NOT IN MODEL/ENGINE DATA BASE − displayed when a perfor-mance data base is loaded in the FMC and the A/C & ENG TYPE discrete pin codecannot be found.


PROGRAM P I N NOT I NMODEL / ENGI NE DA TA BA SE

< I NDEX

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T. Software Options Page (FMC)

The (FMC−X) SW OPTIONS pages provide detailed information about the airlines selectableoptions loaded in the FMC. Many of the options available must have equipment installed, ana-log discrete pins configured correctly, and the software option enabled, while others just requirethe option enabled. Display pages are expanded as required with subsequent pages displayingthe enabled options in plain English. Refer to the Descript ion and Operation section paragraph12 for more information about software options.

The information on this page differs slightly depending on the update version installed. Update10.5 and 10.5A added VRNP. The Option Code, beginning with update U10.6 changed from a12 − digit to a 16 − digit hexidecimal code. Version 10.7 and later updated the default RNP time− to −alarm values and also displays them for each environment. The updated default valuesare listed below:

ENVIRONMENTU10.6 ANDEARLIER

U10.7 ANDLATER

Oceanic 80 Seconds 60 Seconds

Enroute 80 Seconds 30 Seconds

Terminal 60 Seconds 10 Seconds

Approach 10 Seconds 10 Seconds

Note: Time−to−alarm values are only displayed and modifiable forU10.7 and later.

If a software options database is not loaded, the default code is as follows: U10.5A and earlier:For 737−300/400/500 − 000000000201 − manual RNP and high idle descent.

For 737−600/700/800 − 000000000200 − manual RNP.

U10.6 and later:For 737−300/400/500 − 0000 0000 0040 0201 − Manual RNP, high idle descent and geometricpath descent.For 737−600/700/800 − 0000 0000 0040 0200 − Manual RNP and geometric path descent.

(1) Page Access

SW OPTIONS prompt (LSK 2R) on the FMCS BITE index page 1 (ref pg. 119)



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² FMC− L SW OP T I O NS 1 / 2

N D B S I Z E O P T I O N C O D E

3 5 8 4 KW O R D S 4 4 4 4 4 4 4 4 4 2 4 4

D E F A U L T R N P / V R N PO C E A N I C 1 2 . 6 4 4 4

E N R O U T E 2 . 4 4 4 4 4

T E R M I N A L 1 . 0 0 4 4 4

A P P R O A C H 4 . 3 5 4 4 4

N E T A C K

5 . 4 M I N

< I NDEX



3 5 8 4 KW O R D S 4 4 4 4 4 4 4 5A3C3D E F A U L T R N P

O C E A N I C 1 2 . 6

E N R O U T E 2 . 4 4

T E R M I N A L 1 . 0 0

A P P R O A C H 4 . 3 5

< I NDEX



4 4 9 6K 4 4 4 4 4 4 4 4 4 4 4 4 4 2 4 4

D E F A U L T R N P / V R N PO C E A N I C 1 2 . 6 4 4 4

E N R O U T E 2 . 4 4 4 4 4

T E R M I N A L 1 . 0 0 4 4 4

A P P R O A C H 4 . 3 5 4 4 4

N E T A C K

5 . 4 M I N

< I NDEX



4 4 9 6K 4 4 4 4 4 4 4 4 4 4 4 4 4 2 4 4

R N P V R N P T I M E R

O C E A N I C 1 2 . 6 4 4 4 6 4 S

E N R O U T E 2 . 4 4 4 4 4 3 4 S

T E R M I N A L 1 . 0 0 4 4 4 1 4 S

A P P R OA C H 4 . 3 5 4 4 4 1 4 S

< I NDEX N E T A C K 5 . 4 M I N

Page 1 U10.4 Page 1 U10.5A

Page 1 U10.6 Page 1 U10.7 and later


E N A B L E D O P T I O N S

H I G H I D L E D E C E N T

RW Y R E M A I N I N G I N M E T E R SG P S W I T H I N T E G R I T Y

D I R E C T G P S I N P U T

M A N U A L R N P

A B E A M W A Y P O I N T S

A L T ER N A T E D E S T I N A T I O N

A L T / S P D I N T E R V EN T I O N

M E S S A G E R E C A L L

< I NDEX

Enabled Options Page (all versions)


None

(3) ACARS Prompt

None

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U. Performance Factors Page

The (FMC−X) PERF FACTORS page displays performance optimization parameters which maybe used to alter the aircraft characteristics slightly. The display is static until enabled (exceptthe INDEX prompt).

WARNING: THESE PARAMETERS ARE NOT TO BE ALTERED WITHOUT DIRECTIONAND APPROVAL FROM AN AUTHORIZED ENGINEERING FACILITY. THEYAFFECT THE FMC COMPUTATIONS AND PREDICTIONS FOR THE FLIGHTAND MAY PROVIDE MISLEADING INDICATIONS WHEN INCORRECT VAL-UES ARE USED.

(1) Page Access

single instl. − PERF FACTR prompt (LSK 3R) on the FMCS BITE index page 1 (ref pg.119)

dual instl.:

(a) Automatically at power−up when only a performance factor mismatch condition ex-ists

(b) Selecting the NEXT MISMATCH prompt (LSK 6R) on a crossload page and no oth-er mismatch of a higher priority exists

(c) PERF FACTR prompt (LSK 3R) on the FMCS BITE index page 1 (ref pg. 119)

² FMC− L PER F FAC TORS 1 / 1

D R A G F A C T O R

+ 4 . 4 M I N R / CF − F F A C T O R C L B

+ 4 . 4 3 4 4

M N V R M A R G I N C R Z

1 . 3 4 1 4 4

M I N C R Z T I M E E N G O U T

1 1 4 4

< I NDEX − −−

PERF FACTORS 1 / 1

D R A G F A C T O R


+ 4 . 4 3 4 4


1 . 3 4 1 4 4


1 1 4 4

< I NDEX −− −

² FMC− L PER F FAC TORS 1 / 1

G E O D E S

FU L L / A P P

D R A G F A C T O R


+ 4 . 4 3 4 4


1 . 3 4 1 4 4


1 1 4 4

< I NDEX −− −

SINGLE INSTALLATION U10.6 AND EARLIER DUAL INSTALLATION U10.6 AND EARLIER

PERF FACTORS 1 / 1

G E O D E S

FU L L / A P P

D R A G F A C T O R


+ 4 . 4 3 4 4


1 . 3 4 1 4 4


1 1 4 4

< I NDEX − −−

SINGLE INSTALLATION U10.7 AND LATER DUAL INSTALLATION U10.7 AND LATER

http://c/desktop.ileaf/34-61-16_R1.ilfdr/34-61-16.ilboo/Section_100.ilboo/2_111.ildoc

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None

(3) ACARS Prompt

None



(5) Data Fields

These fields will contain parameters which may originate from several different sources.They may be the factory default settings, they may be loaded from a loadable perfor-mance data base disk, or they may be manually loaded.

(a) Geometric Path Descent (GEO DES) mode selection (U10.7 and later). The de-

fault profile is FULL (geometric path descent construction applies to the entire de-scent, from the first altitude restriction to the end of descent). An option in theloadable performance database can change the default selection to APP (descentprofile applies only to the approach and approach transitions). If the loaded perfor-mance database allows access to this field, the default can be changed throughline selection after arming.

(b) The DRAG FACTOR and F−F FACTOR parameters provide a −9.9 to +9.9 percentchange in the drag and fuel flow computations used by the FMC to predict ETA,RTA, and fuel remaining.

(c) The MNVR MARGIN parameter affects the flight envelope and bank angle limitcomputations as follows:

1 For 737−300/400/500:

If FAA Flight Rules − range is 1.30 to 1.60If CAA Flight Rules − range is 1.20 to 1.60

2 For 737−600/700/800, the range is determined by the loadable performancedata base.

(d) MIN CRZ TIME allows a range of 1 to 20 minutes as a lower limit to the minimumcruse time for computing the trip altitudes.

(e) MIN R/C CLB and CRZ allows a rate of climb margin range of 0 to 999 for the flightenvelope computations of each of these phases of flight.

(f) MIN R/C ENG OUT allows a rate of climb margin range of 0 to 500 for the flight en-velope computations for an engine out condition in flight.



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(6) Data Field Access

To access the allowable data fields, enter “ARM” in the scratch pad and select the dashprompt (LSK 6R).

WARNING: THESE PARAMETERS ARE NOT TO BE ALTERED WITHOUT DIREC-TION AND APPROVAL FROM AN AUTHORIZED ENGINEERING FA-CILITY. THEY AFFECT THE FMC COMPUTATIONS AND PREDIC-TIONS FOR THE FLIGHT AND MAY PROVIDE MISLEADINGINDICATIONS WHEN INCORRECT VALUES ARE USED.

The ARMED condition is cancelled when the display page is exited.

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V. Inertial Reference System Monitor Page

The (FMC−X) IRS MONITOR page displays the positional error rate (NM/hour) of each IRS forthe previous flight.

These fields are blanked under the following conditions:

The IRS is not in NAV Mode.The IRS is not aligned providing the FMC with valid data.The FMC has not performed a two dimensional update within the last hourwhile on the ground.The FMC performed a cold restart (powered down for more than 10 minutes).

(1) Page Access

IRS MONITR prompt (LSK 4R) on the FMCS BITE index page 1 (ref pg. 119)


² FMC− L I RS M0N I TOR 1 / 1

I R S L

2 . 5 N M / H R

I R S R

2 . 9 N M / H R



I RS M0N I TOR 1 / 1

I R S L

2 . 5 N M / H R

I R S R

2 . 9 N M / H R




None

(3) ACARS Prompt

When ACARS is installed and the airlines has a user defined maintenance prompt, theACARS prompt (LSK 6R) is displayed. Selection will downlink the selected FMC mainte-nance BITE data.

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W. Hardware Configuration Page

The (FMC−X) H/W CONFIG page provides basic information and status concerning itself.

(1) Page Access

H/W CONFIG prompt (LSK 1L) on the FMCS BITE index page 2 (ref pg. 119)


² FMC− L H / W C0NF I G 1 / 1

H AR DW A R E P / N

1 7 6 2 4 4 − 4 1 − 4 1S E R I A L N O

5 6E T I P R O C S P E E D

1 7 9 . 3 6 4 MH Z

R S 4 2 2 −−−−− I S B − −− E T H E R N E T

VAL I D ACT I VE

< I NDEX

SINGLE FMC INSTALLATION

H / W C0NF I G 1 / 1

H AR DW A R E P / N

1 7 1 4 9 7 − 4 5 − 4 1S E R I A L N O

1 7 2 9E T I P R O C S P E E D

5 4 8 8 . 1 4 4 MH Z

< I NDEX

BOTH COMPUTERS ARE2907C1

COMPUTER IS2907A4


² FMC− L H / W C0NF I G 1 / 1

H AR DW A R E P / N

1 7 6 2 4 4 − 4 1 − 4 1S E R I A L N O

5 6E T I P R O C S P E E D

1 7 9 . 3 6 4 MH Z

R S 4 2 2 − − − − − I S B −− − E T H E R N E T

ACT I VE N / A

< I NDEX

ONE COMPUTER IS2907A4


None

(3) ACARS Prompt

None

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(5) Data Fields

The data fields are defined below. When the specified data is not available “UNAVAIL-ABLE” is displayed in the field. In a dual installation, the data displayed pertains to theFMC specified in the page title (FMC−L or FMC−R).

(a) HARDWARE P/N − displays the GE Aviation assembly number of the unit (stored inmemory).

(b) SERIAL NO − displays the units serial number (stored in memory).

NOTE: The internal hardware number and serial number are to match the unitslabel.

(c) ETI − displays the internal elapse time indicator of the unit.

(d) PROC SPEED − displays the FMCs internal processor clock speed. In a dualinstallation, the processor clock speed is determined by the model of computersinstalled.

1 Both Model 2907A4 computers − PROC SPEED is 40 MHz.

2 One Model 2907A4 computer and one Model 2907C1 computer − PROCSPEED is 40 MHz.

3 Both Model 2907C1 computers − PROC SPEED is 60 MHz.

(e) ISB − displays the status of the RS422 and ETHERNET buses in a dual installation.The header and status is not present in a single installation. The ISB status is de-fined as follows:

1 ACTIVE − displayed when the bus is used as the ISB.

2 VALID − displayed when the bus is operational and is not being used as theISB.

3 INVALID − displayed when communication with the other FMC cannot be per-formed and built−in−testing has not detected a failure on this channel.

4 FAIL − displayed when built−in−testing has detected a failure on this channel.

5 N/A − (ETHERNET status only) displayed when at least one of the FMCs in adual installation is a model 2907A4.

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5. FMCS Display Unit Maintenance BITE Pages

A. CDU Maintenance BITE Index Page

The LCD CDU MAINT BITE INDEX page provides access to the display units BITE mainte-nance pages and functions. When the LCD CDU prompt is selected, the FMC BITE access issuspended. The CDU maintenance BITE pages, operations and data pertain to the display unitcurrently in use. Select the LCD CDU prompt on the other display unit to access its mainte-nance BITE function. The CDU BITE pages do not provide ACARS access.

(1) Page Access

LCD CDU prompt (LSK 5R) on the FMCS BITE index page 1 (ref pg. 119)

Enter BIT into scratch pad and select LSK 5R on the MENU page

For UPDATE 2 use NEXTPAGE and PREV


CDU MA I NT B I TE I NDEX

<FAULTS SW OPT IONS>

<KEY TEST P / S>

<COLOR TEST TEMP>

<D I SPLAY TEST L IGHT>

<CONF I G LAMP TEST>

<EX I T CAL I BRAT I ON>

UPDATE 1 UPDATE 2 OR 3

CDU MA I NT B I TE I NDEX 1 / 2

<FAULTS SW OPT IONS>

<KEY TEST P / S>

<COLOR TEST TEMP>

<D I SPLAY TEST L IGHT>

<CONF I G LAMP TEST>

<EX I T CAL I BRAT I ON>

CDU MA I NT B I TE I NDEX 2 / 2

< AL TNAV F I X ED OUT PUT S


(a) Page 1 (LCD CDU UPDATE 1 and 2)

1 FAULTS (LSK 1L) − displays the CDU BIT DSPLY INDEX page (ref pg. 153)

2 KEY TEST (LSK 2L) − displays the CDU KEY TEST page (ref pg. 156)

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3 COLOR TEST (LSK 3L) − displays the CDU COLOR TEST page (ref pg. 157)

4 DISPLAY TEST (LSK 4L) − displays the CDU DSPLY TEST page (ref pg. 158)

5 CONFIG (LSK 5L) − displays the CDU CONFIGURATION page (ref pg. 159)

6 SW OPTIONS (LSK 1R) − displays the CDU SW OPTIONS page (ref pg. 160)

7 P/S (LSK 2R) − displays the P/S SENSORS page (ref pg. 162)

8 TEMP (LSK 3R) − displays the TEMP SENSORS page (ref pg. 163)

9 LIGHT (LSK 4R) − displays the LIGHT SENSORS page (ref pg. 165)

10 LAMP TEST (LSK 5R) − displays the CDU LAMP TEST page (ref pg. 167)

11 CALIBRATION (LSK 6R) − displays the page (ref pg. 168)

(b) Page 2 (LCD CDU UPDATE 2 only)

ALTNAV FIXED OUTPUTS (LSK 1L) − displays the ANCDU FIXED OUTPUTSpage (ref pg. )


EXIT prompt (LSK 6L) exits the display BITE and returns display control to the FMCSBITE index page 1 (ref pg. 119)

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B. CDU BIT Display Index Page

The CDU BIT DSPLY INDEX page provides access to the display unit BIT status over the last10 full power−up cycles (cold starts).

(1) Page Access

FAULTS prompt (LSK 1L) on the CDU MAINT BITE INDEX page (ref pg. 151)

CDU B I T DSPLY I NDEX

<CYCLE 4 1

<CYCLE 4 2

CYCLE 4 9 >

< I NDEX


CYCLE 01 through CYCLE 10 prompts (LSK 1L thru LSK 5L and LSK 1R thru LSK 5R) −displays CDU BIT DISPLAY page for the selected cycle (ref pg. 154).

When fault/failure data is not logged during a particular cycle, the prompt for that cycle isnot displayed, and the cycle is not selectable.


INDEX prompt (LSK 6L) returns the display to the CDU MAINT BITE INDEX page (ref pg.151)

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C. Cycle XX Faults Page

The CDU BIT DISPLAY CYCLE XX FAULTS page provides CDU BIT history data for a desig-nated cold power−up cycle selected on the CDU BIT DSPLY INDEX page. The last five faultrecords are displayed for each selectable cycle.

(1) Page Access

CYCLE XX prompt (LSK 1L thru LSK 5L or LSK 1R thru LSK 5R) on the CDU BIT DSPLYINDEX page (ref pg. 153)

CDU B I T D I SPLAYCYCLE 4 9 FAUL TS

U S E R 5 1 3 S 9

4 2 9 F A U L T 4 4 4 1 4 9 . 3

CDU B I T D I SPLAYCYCLE 4 9 FAUL TS

U S E R 5 1 3 S 1

4 2 9 F A U L T 4 4 1 4 9 . 3

F M C 7 I 1

F M C F A U L T 4 4 1 4 7 . 4

F M C 1 4 I 1

F M C F A U L T 4 4 1 4 7 . 2

< I NDEX

NUMBER OF OCCURENCES

ETI

FAILURE DESCRIPTION

EXTENDED FAULT CODE


SUB−SYSTEM CODE

POWER−UP CYCLE


None


INDEX prompt (LSK 6L) returns the display to the CDU BIT DSPLY INDEX page (ref pg.153)

(4) Data Fields

(a) POWER−UP CYCLE − displays the power−up cycle this display page correspondsto.

(b) SUB−SYSTEM CODE − displays the abbreviation of the unit the fault is attributedto.

(c) FAILURE DESCRIPTION − provides a brief description of the type of fault detected(refer to Section 1 for a list of CDU Failure Descriptions). The failure descriptionworks similar to the fault label code in the FMC.

(d) EXTENDED FAULT CODE − provides a more specific indication of the type of faultdetected (refer to Section 1 for a list of CDU Extended Fault Codes). The extendedfault code works similar to the fault monitor code in the FMC.

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(e) STEADY/INTERMITTENT INDICATOR − indicates if the display unit considers thefault to be Steady or Intermittent.

(f) NUMBER OF OCCURRENCES − displays the number of times this fault was de-tected during this cycle. The maximum count is 9, and after nine the count is notrecorded.

(g) ETI − displays the display units Elapse Time Indicator count when this fault wasfirst detected.

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D. CDU Key Test Page

The CDU KEY TEST page provides an interactive test of the display unit key operation and in-terpretation. Pressing a key will cause the appropriate character or function switch indicator tobe highlighted and the key annunciated in the scratch pad. Multiple key presses can help identi-fy dead or sticking keys.

The LSK 6L position is tied to the INDEX prompt. The first time it is pressed, the 6L functionswitch indicator on the display will highlight. A second press in succession will return the dis-play to the CDU MAINT BITE INDEX page.

On a CDU display, the blank key is non−operational.

This test is driven by the display unit, not the FMC.

(1) Page Access

KEY TEST prompt (LSK 2L) on the CDU MAINT BITE INDEX page (ref pg. 151)

CDU KEY TESTI N I RTE CLB CRZ DESD I R LEG DEP HOL PRO EXEN1 F I XPRE NEX ABCDE

1 L FGH I J 1R2 L 1 2 3 KLMNO 2R3 L 4 5 6 PQRST 3R4 L 7 8 9 UVWXY 4R5 L . 4 + Z D / C 5R6 L 6R− − −PUSH KEYS TO TEST − −− −

< I NDEX ( PUSH TWI CE )“ R TE “ PRESSED

RTE

CDU

CDU KEY TESTI N I RTE CLB CRZ DESMEN LEG DEP HOL PRO EXEN1 F I XPRE NEX ABCDE

1 L FGH I J 1R2 L 1 2 3 KLMNO 2R3 L 4 5 6 PQRST 3R4 L 7 8 9 UVWXY 4R5 L . 4 + Z D / C 5R6 L 6R− − −PUSH KEYS TO T EST − −− −


MCDU

CDU KEY TESTI N I RTE DEP ATC VNAF I X LEG HOL FMC PRO EXEMEN N1PRE NEX ABCDE

1 L FGH I J 1R2 L 1 2 3 KLMNO 2R3 L 4 5 6 PQRST 3R4 L 7 8 9 UVWXY 4R5 L . 4 + Z D / C 5R6 L 6R− − −PUSH KEYS TO T EST − −− −


FANS MCDU


None


Two consecutive presses of the INDEX prompt (LSK 6L) returns display to the CDUMAINT BITE INDEX page (ref pg. 151)

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E. CDU Color Test Page

The CDU COLOR TEST page allows selection of color and gray scale verification pages toverify all positions of the display can generate the correct color, and that all allowed gray scalelevels are interpreted and generated correctly.

(1) Page Access

COLOR TEST prompt (LSK 3L) on the CDU MAINT BITE INDEX page (ref pg. 151)

CDU COLOR T ES T 1 / 1

<RED CYAN>

<GREEN WHI TE>

<BLUE GRAY SCALE>

<AMBER CHECKERBOARD>

<MAGENTA

< I NDEX


(a) LSKs 1L through 5L, 1R, and 2R

The RED, GREEN, BLUE, AMBER, MAGENTA, CYAN, and WHITE prompts pro-vide a solid display in the color selected. Each position of the display can bechecked to verify the color is visible at all positions on the screen.

Press any key to return to the CDU COLOR TEST page.

(b) LSK 3R

Displays seven lines of gray scale representing the seven different brightness lev-els.


(c) LSK 4R

Displays a black and white checkerboard pattern.



INDEX prompt (LSK 6L) returns display to the CDU MAINT BITE INDEX page (ref pg.151)

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F. CDU Display Test Page

The CDU DSPLY TEST pages provide a display of the units character set in large and small fontsizes, including special characters. Eight pages are available, one for each of the supportedcolors. Page colors are as follows:

1/8 − White 5/8 − Amber

2/8 − Black 6/8 − Green

3/8 − Cyan 7/8 − Magenta

4/8 − Red 8/8 − Blue

(1) Page Access

DISPLAY TEST prompt (LSK 4L) on the CDU MAINT BITE INDEX page (ref pg. 151)



−−−−CDU−DSPLY−TEST−− 1 / 8 −

3´# & °³± 4 1 2 3 4 5 6 7 8 9 ! “ °F ° %°C

’ ( ) *+ , − . / 4 1 2 34 5 67 8 9 : ; < =>?VABCDEFGH I JK LMNOPQRSTUVWXYZ [ \ ] A B C D E F G H I J K L M N OP

Q R S T U V W X Y Z²# & °³± “ 3´ ! °F °

%°C ’ ( ) * + , − . / : ; < = > ? V [ \ ] ΔΔ

²

< INDEX−−−−−−−−−−−− −−−−−−−−−−−−−−−−−−−−−−−−−−−−−−


None

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G. CDU Configuration Page

The CDU CONFIGURATION page provides current information about the display and its loca-tion within the aircraft.

(1) Page Access

CONFIG prompt (LSK 5L) on the CDU MAINT BITE INDEX page (ref pg. 151)

CDU CONF IGURA TI IONS O F TW A R E P / N

3 4 6 3 − SM I − 4 4 1 − 4 2C D U M O D E

MCDUC D U L OC A T I O N

LEFTE T I H R S

4 7 8 2 6 . 9S E R I A L N O

4 4 4 42 6

< I NDEX

UPDATE 1

CDU CONF IGURA TI IONC D U O P S

3 4 6 2 − SM I − 4 4 1 − 4 3C D U O P C

U2−LCD−BLACKC D U M O D E

FANS MCDUC D U L OC A T I O N

R IGHTE T I H R S S E R I A L N O

4

5 8 1 6 . 24 4

1 3 2 6< I NDEX

UPDATE 2


None



(4) Data Fields

Data fields provide the following information:

(a) SOFTWARE P/N or CDU OPS − displays the Boeing software part number.

(b) CDU OPC (Update 2 only) − displays update information.

(c) CDU MODE − displays the operational mode of the display unit (CDU, MCDU, orFANS MCDU).

(d) CDU LOCATION − Displays the location as determined by the MCDU location discretepins at the display unit connector (left or right).

(e) ETI HRS − displays the operational elapsed time stored internally.

(f) SERIAL NUMBER − displays the unit serial number stored internally.

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H. Software Options Page (CDU)

The CDU SW OPTIONS page displays the software options enabled in the display unit. TheOPTION CODE field must have a code entered to enable the options. To enable or disable op-tions, enter ARM into the scratch pad and select the dash prompt (LSK 6R). While ARM is dis-played at location 6R, valid option codes may be entered. The option code value must be eightdigits including the leading zeros.

The options are automatically enabled when entered and displayed in plain English under theENABLED OPTIONS header. The ARM condition expires when leaving the page.

(1) Page Access

SW OPTIONS prompt (LSK 1R) on the CDU MAINT BITE INDEX page (ref pg. 151)

CDU SW OP T I O NS 1 / 1

O P T I O N C O D E

4 4 4 4 4 4 4 4

ENABLED OPT IONS

NONE

< I NDEX −− −


Dash prompt (LSK 6R) − ARM

Enter ARM into the scratch pad and select LSK 6R to allow entry of an eight−digit code inline 1R, which defines the option(s) that is(are) to be enabled.

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O P T I O N C O D E

4 4 4 4 4 4 4 4

ENABLED OPT IONS

NONE

< I NDEX −− −

0 30 0 0 0 0 0


O P T I O N C O D E

4 4 4 4 4 4 4 4

ENABLED OPT IONS

NONE

< I NDEX −− −ARM

A R M


O P T I O N C O D E

4 4 4 4 4 4 4 4

ENABLED OPT IONS

NONE

< I NDEX ARM4 4 4 4 4 4 4 3


O P T I O N C O D E

4 4 4 4 4 4 4 4

ENABLED OPT IONS

NONE

< I NDEX ARM


O P T I O N C O D E

4 4 4 4 4 4 43

ENABLED OPT IONS

SWITCH ING MODEAR I NC 7 3 9 COLOR USAGE

< I NDEX ARM

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I. CDU Power Supply Sensors Page

The operating power outputs of the power supply are continually monitored and displayed. Thedisplay values are not static because they are the instantaneous values read at each iteration ofthe continuous monitoring test.

(1) Page Access

P/S prompt (LSK 2R) on the CDU MAINT BITE INDEX page (ref pg. 151)

P / S SENSORS

SENSOR VALUE+ 5 4 4 . 9 8 V

+ 1 2 1 2 . 5 1 V

− 1 2 −1 2 . 8 1 V

+ 2 6 2 7 . 2 4 V

+ 2 8 2 7 . 3 7 V

SW 2 8 2 7 . 2 5 V

ANNUN 4 4 . 7 9 V

< I NDEX

174101−xx−01 UNITS

P / S SENSORS

SENSOR VALUE+ 1 . 2 4 1 . 1 8 V

+ 2 . 5 4 2 . 4 6 V

+ 3 . 3 4 3 . 3 8 V

+ 5 . 4 4 4 . 9 8 V

+ 1 2 . 4 1 2 . 5 1 V

− 1 2 . 4 − 1 2 . 8 1 V

+ 2 8 . 4 2 7 . 3 7 V

SW 2 8 2 7 . 2 5 V

ANNUN 4 4 . 7 9 V< I NDEX

174101−xx−02 UNITS


None


INDEX prompt (LSK 6L) returns display to the CDU MAINT BITE INDEX page (ref pg.

151)

(4) Data Fields


(a) +1.2 − displays the output of the positive 1.2 volt supply. The value is 1.08 to 1.32Vdc. This is used by the 174101−xx−02 units only.

(b) +2.5 − displays the output of the positive 2.5 volt supply. The value is 2.375 to2.625 Vdc. This is used by the 174101−xx−02 units only.

(c) +3.3 − displays the output of the positive 3.3 volt supply. The value is 2.97 to 3.63Vdc. This is used by the 174101−xx−02 units only.

(d) + 5 − displays the output of the positive five volt supply line. The value is 4.85 to 5.3Vdc.

(e) + 12/−12 − displays the output of the positive and negative twelve volt supply lines.The value is 12.1 to 13.3 Vdc.

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(f) + 26 − displays the output of the positive five volt supply line. The value is 25.8 to29.0 Vdc (This is used by the 174101−0xx−01 units only).

(g) + 28/SW 28 − displays the output of the positive five volt supply line. The value is16.0 to 32.0 Vdc. When the display heater is OFF (TEMP SENSORS page − refpage 163), the SW 28 value is blanked.

(h) ANNUN − displays the annunciator lamp supply line. The value is:

When light ing input is 28 Vdc − 4.7 to 5.0 Vdc.When lighting input is 14 Vdc − 2.1 to 2.3 Vdc.

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J. CDU Temperature Sensors Page

The TEMP SENSORS page displays the current temperature values of the display (LCD andBacklight Assemblies), the TEC (thermal electric cooler) mode, and the heater status. The dis-play values are the values obtained at each iteration of the continuous monitoring BITE test.

NOTE: When BIT failures are logged against the LCD or backlight assemblies, and the tem-perature indicated on this are high, check the display unit chassis vents for dust anddirt, and verify the aircraft cooling systems is operational.

(1) Page Access

TEMP prompt (LSK 3R) on the CDU MAINT BITE INDEX page (ref pg. 151)

TEMP SENSORS

SENSOR VALUELCD TEMP R + 3 2 . 9 1°C

LCD TEMP C + 3 4 . 7 9°C

BK L I GHT R + 4 1 . 1 2°C

BK L I GHT H + 3 9 . 5 8°C

TEC MODE COOLT EC CMD 4 4 4

HEATER OFF< I NDEX

174101−xx−01 UNITS

TEMP SENSORS

SENSOR VALUELCD TEMP R +3 2 . 9 1°C

LCD TEMP C +3 4 . 7 9°C

BACK L I GHT +4 1 . 12°C

HEATER 4 3%

< I NDEX

174101−xx−02 UNITS


None



(4) Data Fields


(a) LCD TEMP R/LCD TEMP C − displays the LCD assembly row and column temper-ature. The difference between the two values must be less than 20° C for the174101−xx−01 units, and less than 15° C for the 174101−xx−02 units.

(b) BK LIGHT R/BK LIGHT H − displays the backlight assembly reflector and heatsinktemperatures. The difference between the two values must be less than 45° C.This applies to the 174101−xx−01 units only.

NOTE: The average LCD temperature and the average backlight temperaturemust have less than a 62° C difference.

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NOTE: When the tolerances indicated in (a) and (b) are exceeded, the heater is dis-abled, however status will not be sent to the FMC.

(c) TEC MODE − displays the current backlight thermal electric cooler operating mode.The two modes are HEAT and COOL.

NOTE: This applies to 174101−xx−01 units only.

(d) TEC CMD − displays the TEC command code sent to the TEC controls in the back-light assembly to command the TEC to heat or cool to a specific temperature level.This command is driven by the backlight reflector and heatsink temperatures. Therelationship between the command code and backlight temperatures is as follows:

NOTE: This applies to 174101−xx−01 units only.

TEMP TEC CMD(HEX)(DEG C)

40 000

41

42

43

44

45

46

47

48

49

5051

52

53

066

0CC

133

19A

200

266

2CC

333

399

400466

4CC

533


54 599

55

56

57

58

59

60

61

62

63

6465

66

67

600

666

6CC

733

799

800

866

8CC

933

999A00

A66

ACC


68 B33

69

70

71

72

73

74

75

76

77

7879

80

B99

C00

C66

CCD

D33

D99

E00

E66

ECC

F33F99

FFF

(e) HEATER − displays the state of the LCD heater mode (ON or OFF) as follows:

1 The heater is full on at −5° C.

2 The heater is on at a 50% duty cycle between 0° C and 20° C.

3 The heater is off above 20° C.

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K. CDU Light Sensors Page

The LIGHT SENSORS page displays the outputs of the light sensors and luminance values.The display values are the values obtained at each iteration of the continuous monitoring BITEtest.

(1) Page Access

LIGHT prompt (LSK 4R) on the CDU MAINT BITE INDEX page (ref pg. 151)

L IGHT SENSORS

SENSOR VALUEAMB I ENT LT 6 . 6F C

D I MMER POT 8 3 . 9%

DES LUM 1 4 . 9 ( FT− L )SPOT BRT 4 3 3 9 ( FT− L )ARC H I GH 4 4 F4 ( HEX )ARC LOW 4 4 4 4 (HEX)

< I NDEX

174101−xx−01 UNITS 174101−xx−02 UNITS

L IGHT SENSORS

SENSOR VALUEAMB I ENT LT 6 . 6F C

BRT 8 3 . 9%

DES LUM 1 4 . 9 ( FT− L )SPOT BRT 4 3 3 9 ( FT− L )L ED CMD 4 4 F4 ( HEX )

< I NDEX


None


INDEX prompt (LSK 6L) returns display to the CDU MAINT BITE INDEX page (ref pg.

151)

(4) Data Fields


(a) AMBIENT LT − displays the flight deck ambient light detected by the photo sensorsin the display keyboard. The range can be 0.3 Fc to 8000.0 Fc.

(b) Line 5.

1 In the 174101−xx−01 units; DIMMER POT − displays the percentage of themanual brightness range set by the manual brightness control on the displaykeyboard. The range can be from 0.0% to 100.0%.

2 In the 174101−xx−02 units; BRT − displays the percentage of the manualbrightness range set by the manual brightness control on the display key-board. The range can be from 0.0% to 100.0%. In addition, a level indicat ingbar is displayed in the scratch pad when a keyboard with brightness controlkeys is installed on the LCD CDU.

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(c) DES LUM − displays the desired luminance of the display. It is determined by theambient flight deck light, temperature inside the display unit, and the position of themanual brightness control on the display keyboard. The range can be from 0.1 FT−L to 95.0 FT−L.

(d) SPOT BRT − displays the allowable spot brightness level of the backlight assem-bly. The value range is dependent upon the reflector temperature. The minimumand maximum values shown below provide the allowable range that is controlled bythe manual brightness control and the flight deck ambient light.

TEMPMAX

(FT−L)

(DEG C)

−40 3200

−20

0

2055

60

65

70

75

3200

3200

32003200

3200

3000

2000

1500

REFLECTOR SPOT LUMINANCE

MIN

333

333

66.67

1.3361.336

1.336

1.336

1.336

1.336

For 174101−xx−01 units.

(e) ARC HIGH/ARC LOW − displays the commands sent to the backlight assembly tocontrol the intensity of the backlight lamp. The ARC HIGH command is used when

the display is operating in the brighter ranges, and the ARC LOW command is usedat the dimmer ranges. Note that in the crossover fringe, both ARC HIGH and ARCLOW commands have values.

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H

ARC COMMAND

(FT−L)

3333.33 939

1666.67

426.67

213.33

179.00

148.63

106.67

53.33

26.67

4BA

134

098

07E

061

000

000

000

SPOT BRT

L

000

000

000

000

000

FFF

B7C

5A8

2E7

13.33

6.67

3.33

1.671.336

0.00

000

000

000

000000

000

19E

0E2

080

05504A

000

For 174101−xx−02 units.

(f) LED CMD − displays the current hexidecimal command sent to the display to con-trol the intensity of the LED backlight in the DLA.

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L. CDU Lamp Test Page

The CDU LAMP TEST page is an annunciator self test page. When accessed, the five annun-ciators are to be lit. When leaving the page, the annunciators are turned off unless driven fromthe FMC.

(1) Page Access

LAMP TEST prompt (LSK 5R) on the CDU MAINT BITE INDEX page (ref pg. 151)

CDU L AMP TEST

ANNUNC I ATORS A L L L I T

< I NDEX


None

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M. CDU Calibration Page

The CDU CALIBRATION page displays the LCD constants stored in memory during the calibra-tion process. These values are used to correct deviations injected due to component tolerancedifferences and will not change until the unit is re−calibrated.

(1) Page Access

CALIBRATION prompt (LSK 6R) on the CDU MAINT BITE INDEX page (ref pg. 151)

CDU CA L I B RA T I O NGS DEF L TR I M4 4 4 . 4 V 2 . 4 V

1 6 2 . 1 4 V 2 . 6 V

3 2 3 . 2 V 2 . 6 V

4 8 3 . 9 V 2 . 6 V

6 3 4 . 5 V 2 . 6 V

VC 3 . 9 V 1 . 2 V

VE 4 . 4 V 4 . 4 V

LT SENS B I AS − 4 4 5 8 MV

SCALE FACTOR 4 . 4 3 2

< I NDEXCAL I BRATED

174101−xx−01 UNITS 174101−xx−02 UNITS


None


INDEX prompt (LSK 6L) returns display to the CDU MAINT BITE INDEX page

(ref pg. 151)

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N. Alternate Navigation Fixed Outputs Page (UPDATE 2 and 3 Only)

The ANCDU FIXED OUTPUTS page performs the same function as the FMC generated FIXEDOUTPUTS page with the EHSI/EFIS/CDS displays. When the page is accessed the test infor-mation displayed on this page is transmitted to the ESAI and displayed. The ESAI test informa-tion is removed when the page is exited.

(1) Page Access

ALTNAV FIXED OUTPUT prompt (LSK 1L) on the CDU MAINT BITE INDEX page 2 (refpg. 151)

ANCDU F I XED OUTPU TS

C H E C K F L T D E C K V A L U E S

ESA I −XTRK R I GHT 1NMESA I −DES I RED TK 3 7 . 5 °

ESA I −WPT BEAR I NG 2 2 . 5 °

ESA I −DS TO NX WPT 3 8 8ESA I −MSG MSG

< I NDEX


None


INDEX prompt (LSK 6L) returns display to the CDU MAINT BITE INDEX page 2 (ref pg.

151)

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6. FMS Sub−System Maintenance BITE Pages

Unless otherwise stated in the individual display descriptions, the following operational guidelinesapply to all sub−system BITE pages.

During execution of the sub−system BITE tests, the FMC maintains control of the title line and thescratch pad of the display. Lines 2 through 13 are under control of the selected sub−system usingthe FMC to perform the data transfers between the sub−system and the display unit. The FMC per-forms integrity checks on the blocks of data received from the sub−system and ignores a transmis-sion if the data is determined to be corrupted (returns a NAK to the sending sub−system).

During sub−system testing, the alphanumeric keys, line select keys, and page manipulation keysare active. The function/mode keys are inactive.

When a sub−system BITE test page is selected and displayed, the FMC begins transmitting a BITErequest to the sub−system every 200 ms, and looks for a reply. If the FMC does not receive a returntransmission, the display changes to a status display indicating the BITE function is inoperable.

DFCS B I T E TEST

D F C S B I T E I N O P

C H E C K F C C O R I N T E R F A C E

At normal completion of a test, the sub−system sends an end−of−transmission (EOT) code to the

FMC which in turn responds by switching the display to the MAINT BITE INDEX page (ref pg. 115).

Press INITREF key to return to the MAINT BITE INDEX page (ref pg. 115) when communications fail

or early termination of test is desired.

The INDEX prompt on any of the sub−system BITE pages returns the display to the MAINT BITEINDEX page (ref pg. 115)

An ACARS prompt is not available for any of the sub−system BITE access pages.

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A. Digital Flight Control System BITE Test Page

For detailed information concerning DFCS BITE testing, refer to the FCC supplier manuals.

(1) Page Access

DFCS prompt (LSK 2L) on the MAINT BITE INDEX page (ref pg. 115)

In the Classic airplane group, when the FMC Source Select Switch (dual FMC installations) is inany other position but BOTH−ON−L as the DFCS BITE TEST page is accessed, the operatorwill be provided with instructions to continue with the test.

DFCS B I T E TESTMO V E FMC TRANS FER SWI TCHT O BOTH ON L F O R A L L

DFCS B I TE T E S T S . DO NOTC H A N G E SW P O S I T I O N WH E N

T H E S E M E S S A G E S A P P E A R :

* MOVE A LL I NST SWI T CHES

TO NORMAL*MOVE AL L I NST AND NAVSWITCHES TO NORMAL / FMC

I NDEX>

DFCS B I T E TESTMO V E FMC TRANS FER SWI TCHT O BOTH ON L F O R A L L

DFCS B I T E T E S T S . DO NOTC H A N G E SW P O S I T I O N WH E N

T H E S E M E S S A G E S A P P E A R :

* MOVE A LL I NST SWI T CHES

TO NORMAL*MOVE AL L I NST AND NAVSWI TCHE S TO NORMAL / FMC

<PUSH I F NO RESPONSE

DFCS B I T E TEST

FMC TRANS FER SWI TCH N O T

D E T E C T E D I N BOTH ON L .

DFCS B I T E T E S T I N G M A Y

N O T WO R K P R O P E R L Y I F

B O T H FCC S A R E P OW E R E D

<CONT I NUE I NDEX>

INSTRUCTION PAGE WARNING PAGE

DFCS B I T E TEST

DFCS BITE ACCESS PAGE


PUSH IS NO RESPONSE (LSK 6L) − displays the DFCS BITE TEST WARING page.(Only displayed for 15 seconds after page access and not when

INDEX prompt is present.)

CONTINUE (LSK 6L) − displays the DFCS BITE TEST access page.

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B. Autothrottle BITE Test Page

For detailed information concerning A/T BITE testing, refer to the A/T supplier manuals.

(1) Page Access

A/T prompt (LSK 3L) on the MAINT BITE INDEX page (ref pg. 115)

A / T B I TE TEST


None

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C. Air Data Inertial Reference System BITE Index and Test Pages

The ADIRS BITE INDEX page provides access to the ADIRS BITE pages. When accessing theindividual left or right ADIRS, communication is with the selected unit only. When accessing theother tests, the FMC switches to the left ADIRS for BITE data if it becomes valid. The BITEINOP status page is only displayed when both ADIRSs fail to communicate.

For detailed information concerning ADIRS BITE testing, refer to the ADIRS supplier manuals.

(1) Page Access

ADIRS prompt (LSK 4L) on the MAINT BITE INDEX page (ref pg. 115)

AD I RS B I TE I NDEX

<AD I RS L

<AD I RS R

<AD I RS− I R L +R GND TEST

< AD I RS −ADR L +R GND TEST

<AD I RS MA I N T CODES

< I NDEX


ADIRS X (LSK 1L through 5L) prompts − display the appropriate ADIRS BITE TESTpages (examples on next page)

AD I RS L B I TE AD I RS R B I TE

AD I RS− I R L +R B I TE AD I RS−ADR L +R B I TE

AD I RS MA I N T CODES

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D. Common Display System BITE Index and Test Pages

The CDS BITE INDEX page provides access to the CDS DEU BITE pages.

For detailed information concerning CDS BITE testing, refer to the CDS DEU supplier manuals.

(1) Page Access

CDS prompt (LSK 5L) on the MAINT BITE INDEX page (ref pg. 115)

CDS B I TE I NDEX

<DEU 1

<DEU 2

< I NDEX

CDS DEU 1 MA I NT / B I TE



DEU X prompt (LSK 1L or 2L) − displays the appropriate CDS DEU X MAINT/BITEpages.

When the DEU X MAINT/BITE page is selected the FMC begins transmitting to the selectedDEU. When a response is not received from that DEU, the FMC displays the DEU status page.


D E U S E L F T E S T ( 3 M I N )

O R D E U 2 B I T E I N O P

C H E C K D E U 2 O R I N T E R F A C E

The selected DEU may be performing self−test. If the allotted time (line 3) has expired, assumethe DEU is not able to respond.

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E. Engine and Engine Exceedance BITE Index and Test pages

The Engine/Exceed BITE INDEX page provides access to the EEC BITE pages. The EEC andFMC do not communicate directly, but use the CDS DEUs to relay the transfers back and forthfor all BITE testing. If the communication failure status is displayed, both the EEC and DEUmust be checked.

For detailed information concerning EEC BITE testing, refer to the EEC supplier manuals.

(1) Page Access

ENGINE prompt (LSK 1R) on the MAINT BITE INDEX page (ref pg. 115).

ENG I NE / EXCEED B I TE I NDEX

<ENG I NE 1

<ENG I NE 2

<ENG INE 1 CH A ONLY

<ENG INE 2 CH A ONLY



ENG INE 1 B I TE TEST


ENG I NE EXCEEDANCES


(a) ENGINE X (LSK 1L or 2L) prompts − display the appropriate ENGINE X BITETEST page.

(b) ENGINE X CH A ONLY (LSK 3L or 4L) prompts − display the appropriate ENGINEX BITE TEST page.

(c) EXCEEDANCES prompt (LSK 6R) − displays the ENGINE EXCEEDANCES page.

(3) ENGINE 1 (LSK 1L) or ENGINE 2 (LSK 2L) BITE test initialization

The FMC sends a BITE request for EEC channel A of the selected engine to both DEUs,then waits for a reply from ether DEU.

While the FMC waits for a response, the initialization status is displayed.

After a reply is received, the FMC responds by displaying the ENGINE X BITE TEST

page for the selected engine. Once a reply is received from one DEU, that DEU will beused for the remainder of the access. If that DEU stops responding the FMC displays theBITE INOP status and does not switch to the other DEU.

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I N I T I AL I Z I NG EEC1

If a reply is not returned within 10 seconds, the FMC terminates the channel A request,and sends a BITE request for EEC channel B of the selected engine to both DEUs, thenwaits for a reply. If a reply is not received in 5 seconds, the FMC terminates the channelB request, and sends a request for channel A only. The FMC waits for a response for anadditional 5 seconds. If a response is not received, the communication fail status is dis-played and the FMC continues sending a BITE request for channel A only.


E N G I N E 1 B I T E I NO P

C H E C K E E C 1 O R I N T E R F A C E

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F. Auxiliary Power Unit BITE Test Page

The FMC only provides the access interface to the APU. During access of the APU BITE TESTthe FMC controls the information displayed in the title line and the scratch pad line. Lines 2through 13 are under control of the APU. For detailed information concerning APU BITE test-ing, refer to the APU supplier manuals.

(1) Page Access

APU prompt (LSK 2R) on the MAINT BITE INDEX page (ref pg. 115)

APU B I TE TEST


None

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G. Fuel Quantity Indicating System BITE Test Page

The FMC only provides the access interface to the FQIS. During access of the FQIS BITETEST the FMC controls the information displayed in the title line and the scratch pad line. Lines2 through 13 are under control of the FQIS. For detailed information concerning FQIS BITEtesting, refer to the FQIS supplier manuals.

(1) Page Access

FQIS prompt (LSK 3R) on the MAINT BITE INDEX page (ref pg. 115)

FQ I S B I TE TEST


None

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REPAIR

1. Introduction

Aircraft level repair consists of cleaning the LCD CDUs and replacing defective units in the aircraft.

CAUTION: CONNECTING AND DISCONNECTING ELECTRONIC EQUIPMENT WHILE POW-ER IS APPLIED WILL DAMAGE INTERNAL COMPONENTS AND ELECTRICALCONNECTOR PINS. TURN OFF POWER AT THE POWER SOURCE BEFORECONNECTING OR DISCONNECTING ELECTRONIC EQUIPMENT TO PREVENTDAMAGE.

CAUTION: FAILURE TO OBSERVE ELECTROSTATIC DISCHARGE PRECAUTIONARY PRO-CEDURES WHEN TOUCHING, REMOVING, OR INSERTING PARTS OR ASSEM-BLIES MAY RESULT IN DEGRADED PERFORMANCE OR FAILURE OF THEEQUIPMENT.

2. LCD CDU Cleaning

CAUTION: CLOGGED COOLING VENTS IN THE LCD CAUSES OVERHEATING AND PRE-MATURE FAILURE OF THE LCD BACKLIGHT ASSEMBLY CLEANING THECOOLING VENTS IS RECOMMENDED TO PREVENT PREMATURE FAILURE.

It has been noticed that many LCD CDU return units have considerable dust, lint, and cloth fibrepacked into the unit’s central cooling chamber and backlight cooling camber, causing the backlightassemblies to overheat and fail prematurely. Cleaning the cooling vents is recommended on a regu-lar basis along with general aircraft maintenance and new airplanes should be checked quarterly forthe first year.

Figure 201 shows an LCD backlight cooling vent that is plugged, compared to one that is clean. It isimperative that this cooling chamber maintains unrestricted air flow down to the LCD backlight’sthird set of cooling fins.

If the plugged cooling chambers cannot be cleaned, the unit should be sent to a repair facility to bedisassembled and cleaned.

A. Remove power to the LCD display units.

B. Disengage six turnlock fasteners securing the unit to the equipment mounting rail on each dis-play unit.

C. Disconnect the aircraft wiring connector from the display units and remove the units from the

airplane.

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PLUGGED LCD BACKLIGHTCOOLING VENT

CLEANED LCD BACKLIGHT COOLING VENT

THIRD SET OFCOOLING FINS

LCD Cooling Vent LocationsFigure 201

WARNING: USING LOW PRESSURE AIR CAN CAUSE DEBRIS TO FLY INTO THE AIRCREATING INHALATION IRRITATIONS AND EYE INJURIES. USE A DUST MASKAND FACE SHIELD TO PREVENT INHALATION OF, OR EYE CONTACT WITH,FLYING DEBRIS. DO NOT USE LOW PRESSURE AIR WHILE UNPROTECTED

PEOPLE ARE IN THE WORK AREA.

D. Use low pressure air (40 to 90 PSI), on the top and bottom ventilation ports to dislodge and ex-tract the build up of material in the central cooling chamber (Ref Figure 202).

NOTE: Alternately using a vacuum source and the low pressure air on the ventilation portsmay also help extract material.

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E. Repeat several times to remove material.

F. Using low pressure air (40 to 90 PSI), alternate blowing air into the LCD backlight top coolingvents and rear chamber vent to dislodge and extract the build up of material in the LCD CDUbacklight cooling chamber (Ref Figure 202).

NOTE: Alternately using a vacuum source and the low pressure air on the LCD backlightcooling vents and rear chamber vent may also help extract material.

G. Repeat several times to remove material.

(174101−xx−01 UNITS) (174101−xx−02 UNITS)

CENTRAL CHAMBERTOP COOLING VENT

(BOTTOM VENT NOT SHOWN)

REAR CHAMBER VENT(LOCATED AT THIS CORNER ON BOTH UNITS)

BACKLIGHT COOLING VENT

LCD Cooling Vent LocationsFigure 202

H. Connect the aircraft wiring connector to the display units and install them into the equipmentmounting rail.

I. Engage six turnlock fasteners securing each unit to the equipment mounting rail.

J. Restore power to the FMCS display units.

K. With the FMCs and LCDs powered up, verify the display units are operational using the displayBITE pages (refer to the MAINTENANCE BITE PAGES Section of this manual).

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3. File System Download

When an FMC is healthy enough to complete BITE testing, perform the File System download op-eration using the FMC DOWNLOAD function, a portable ARINC 615 Dataloader (or equivalent) andthe FMC download function pre−formated diskettes. Send the downloaded diskettes to GE Aviationin accordance with the latest version of GE Aviation SIL−34−49.

4. Testing

Testing is normally performed using the FMCS Maintenance BITE pages to determine if the FMCsand FMCS displays are functioning correctly.

An alternate method of testing the Model 2907A4 FMC is available using the Return to Service(RTS) tester. The RTS tester can be used to test the FMC hardware on the bench, providing apass/fail indication in a short time.

When the FMC is inserted into the test adapter sled, the RTS tester will verify the FMC hardwareoperational status using BITE testing. The RTS tester can also be used to load the OperationalFlight Program. For more information about the tester, refer to CMM 34−61−12 or 34−61−15.

NOTE: The RTS tester will not test the Operational Flight Program or any of the flight data.

For detailed set up and operation, refer to the Ideal Aerospace User’s Manual for FMCS Return toService Test Program 553757.

5. Replacing the FMC

A. Turn off aircraft power at the circuit breaker for the FMC.

B. Loosen two lockdown screws securing the FMC to the electrical mounting frame.

C. Pull the FMC free of the electrical connector and mounting frame using the FMC handle.

D. Slide replacement FMC into electrical mounting rack and seat rear connector.

E. Mate the two lockdown screws on the electrical mounting rack with the support hooks on theFMC and tighten the lockdown nuts.

F. Restore power to the FMC.

G. Verify the FMC PWR indicator is lit.

H. Verify the FMC VALID indicator lights after approximately 10 seconds.

I. Check the FMCS display unit to verify that a valid display page is shown.

J. If a crossload page is displayed in a dual installation, perform the crossload after verifying theOFP and database versions.

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6. Replacing the FMCS Display Unit

A. Turn off aircraft power at the circuit breaker for the display unit.

B. Loosen six screws securing the display unit to the equipment rack.

C. Lift the display unit handle to the upright position.

D. Raise the display unit out of the equipment rack to gain access to the electrical connector on therear side of the display unit.

E. Disconnect the connector and completely remove the display unit.

F. Connect the aircraft connector to the replacement display unit.

G. Lift the replacement display unit handle to the upright position and lower the unit into the equip-ment rack.

H. Tighten six screws securing the display unit to the equipment rack.

I. Restore power to the FMCS display unit.

J. Verify that a valid display page is shown.

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