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 D. The system receives instrument landing system data from the VHF NAV.Standby Horizon Indicator (Fig. 1)
_________________________
 A.  The indicator is of the conventional mechanical type. Attitude is provided by a 3-phase vertical gyro suspended in a two degree-of-freedom gimbal system. This system is connected to a drum-type roll and pitch attitude display. The system displays approximately 85 degrees of freedom in climb, 85 degrees of freedom in dive and 360 degrees of freedom in roll.
 B.  The gyro system utilizes a spinning pendulum and counterweight device to automatically erect the gyro at turn-on. The quick caging knob on the front face is used to mechanically accelerate the erection process. The fast erection process stabilizes the display drum to the reference vertical position determined by indicator orientation.
 C.  An integral static inverter converts the 28v dc input to three-phase 400Hz ac voltage for the gyro motor. It also monitors the power supplies and the speed of the gyro.
 D.  The ILS display consists of the LOC and G/S deviation bars. The bars indicate deviation from their respective centerlines and are driven by signals from the VHF NAV receiver (AMM 34-31-00, or AMM 34-31-01, or AMM 34-31-02, or AMM 34-31-03, or AMM 34-31-04).
 E.  ILS display modes are controlled by a three-position rotary mode select switch on the indicator's front face.
 F.  Three warning flags are provided for failure indication. The LOC or G/S failure flags appear in view in the event of invalid LOC or G/S signals or for internal failures in ILS logic or power supplies. The gyro failure flag appears in view in the event of a power failure or if gyro rotor speed is low.
Operation (Fig. 2)
_________
 A.  Within 3 minutes of power application the gyro reaches operational speed and the gyro failure flag retracts from view. The normal rate of gyro erection is 3 degrees per minutes, but a fast erection device is fitted to bring about erection within a few seconds. The mechanism for fast erection is actuated by pulling gently on the quick caging knob, located in the lower right-hand corner of the indicator front face. After power has been removed, the gyro takes approximately 9 minutes to come to rest.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

737-300/400/500
MAINTENANCE MANUAL

ROLL POINTER

ROLL SCALE
GLIDE SLOPE FAILURE FLAG
HORIZON BAR
FIXED AIRPLANE SYMBOL GYRO
FAILURE
FLAG
PITCH
SCALE
GLIDE SLOPE DEVIATION BAR
LOCALIZER
DEVIATION
BAR
LOCALIZER

OFF  FAILUILS 
MODE SELECT  ILS  B/CRS  KNOB QUICK CAGING FLAG RE 

STANDBY HORIZON INDICATOR
A

Standby Attitude Reference System Component Location
Figure 1

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 34-25-02

 ú ú 01 Page 2 ú Feb 25/87
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

737-300/400/500
MAINTENANCE MANUAL

28V DC FROM STBY/HORIZ CB (P18) (34-24-00)
G/S-1
S FLAG

G/S-1 DEV
LOC-1 DEV
VOR/LOC-1 S FLAG
+5V LIGHTING
SFENA P/N H341ANM

Standby Attitude/ILS Indicator Schematic
Figure 2

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A
737-300/400/500MAINTENANCE MANUAL
 B.  ILS functions are controlled by the mode select switch located in the lower left-hand corner of the indicator front face. The three selectable modes operate as follows:
 (1)  
OFF - ILS pointers and failure flags (LOC and G/S) retract out of view.

 (2)  
ILS - ILS operation normal for front course approach.
　
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