3 4  LOC tuned (DDF6) R CWS O/D (DD7E)  X X  R A/P G/A (DD56) R Dual Cont. (DD74)  A/P G/A (DD66) Ail Actr Det (DD77) 
NOTE:  X means the discrete is not tested and counted as a logical 1. 

512 
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Display Test No. Name
2.1 Discretes
  Data Subtest Nominal
5 HFDF6  1XXX XX0X XX11 01X0 1 Flare APP (7DF6) X X X BIT 15 0 2 X X Elev. Actr Eng X 1 234 FFF6

3 X X P A/P G/A G/S ENG (FDD6) (FDE6) 4 P CWS O/D APP (FDF2) X Elev. Act Det (FDFE) Pressure (FDF7)
6 HFFFF XXXX 1XXX 111X X1X1 1 X X X X 2F LIM X X X CLUTCH ENG (F7FF) 3 F LIM A/P RELEASE TRIM/FLAP X CLUTCH ENG SW INTERLOCK (FF7F) (FFBF) (FFDF) X 4 X COMPASS XFR X V.G. XFR (FFFB) (FFFE)
7 HF7DF

X111 0XXX X10X XXXX 1 X WHEEL LIM IN TRIM WARN ILS DEV (B7DF) (D7DF) (E7DF)
2 A/SWARN X X X RESET (FFDF)
3 X 28 VDC Valid NAV INTERRUPT X (F7BF) (F7FF) X 4X X X X
NOTE: X means the discrete is not tested and counted as a logical 1.
512 
Jun 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  22-11-01 Page 141 

BITE TEST RESULTS TABLE BITE TEST RESULTS TABLE
Display No.  Library/Sub Test No.  Nominal  LL  UL  Description  Notes 
2.2 2.3  66 Single Chan App. Ann 66.1 66.2 67 ILS DEV WARN 67.1 67.2 67.3  H 0080 H 0000 H 0300 H 0000 H 0000  LOC tuned APP LOC DEV, & GS DEV LOC DEV GS DEV  812-7=1 813-2=0 815-8,9=1 815-8,=0 815-9,=- J2A-59 INT INT INT INT 
NOTE: "INT" = Internal (inside FCC) 

512 
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Display Library/Sub No. Test No. Nominal LL UL Description Notes
2.7  39 MCP F/D Switch
39.1  H 2000 LCL & FGN ON J2A-23, 807-9, -13, =1 J2B-4F
39.2  H 0000 LCL & FGN F/D J2A-23, 807-9, -13, =0 J2B-4F
2.18  2 ADI Test
2.1  -6.2 -7.36 -5.44 Pitch A/D 8E Pitch Bar Bias.
2.2 -6.2 -7.36 -5.44  Roll A/D 16 Roll Bar Bias.
2.3  0.0 -0.06 0.06 Pitch   8E Pitch Bar centered.
2.4  0.0 -0.06 0.06 Roll 16 Roll Bar centered.
2.5  [1] 0.412 0.350 0.473 Pitch 8E Pitch Bar down.

2.6 [1] 0.251 0.182 0.283  Roll 16 Roll Bar left.
2.19  3 MASI
3.1  4.8 4.32 5.28 A/S BUG 2E 440 Kts
3.2 0.0 -0.06 0.08  213 Kts 2E
3.3 -3.9 -4.29 -3.51  2E
[1] The nominal and tolerances shift for different F/D bar gradient options
Option 1 Shown  Option 2 ST5 =.493 .566 Option 3 ST5  =1.503 1.75
.419  1.28
Gnd J4A 36 & 39  Gnd J4A36  ST6  =.013 7  .161 .097  Gnd 4A39  ST6  =.993  1.14 .84 
*Note “INT” = Internal (inside FCC). 

Jun 20/83  22-11-01
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

BITE TEST RESULTS TABLE
Display  Library/Sub 
No.  Test No.  Nominal  LL  UL  Description  Notes 
5 CWS Interlocks 
2.20  5.1  H 2000  AIL ACT ENG  J4A-47 
812-13=1 
5.2  H 0200  ELEV ACT   J4A-61 
ENG
813-9=1 
5.3  H 0020  LCL CWS  810-5=1 J4A-53 
5.4  H 0000  LCL CMD  810-6=0 J4B-8 
5.5  H 0008  R CWS O/D  812-3=1 INT 
5.6  H 0008  P CWS O/D  812-3=1 INT 
5.7  H 0008  R CWS O/D  812-3=1 INT 
5.8  H 0008  P CWS O/D  813-3=1 INT 
2.21  6 ENG Interlocks 
6.1  H 2000  Ail Act Eng  812-13=1 J4A-47 
6.2  H 0200  Elev Act Eng  813-9=1 J4A-61 
6.3  H 0040  LCLCMD  810-6=1 J4B-8 
6.4  H 0000  LCL CWS  810-5=10 J4A-53 
6.5  H 0008  Foreign  810-3=1 J2a-17 
(CWS + CMD) 
6.6  H 0000  FGN CMD  810-4=0 J3A-35 
and FGN 1sr 
up 
6.7  H 0014  FGN CMD  810-4=1 J3A-35 
and 1st up 
6.8  H 0000  LCL CWS and  810-6=0 J4B-8 
LCL CMD 
2.22  7 AP Diseng. 
Warning 
7.1  H 0000  LCL CMD  810-6=0 J4B-8 
7.2  H0000  CWS Warn  812-12=1 BA Only 
Reset 

22-11-01 Jun 20/83
Page 144
　
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