1. General
_______
A. Both captain's and first officer's F/D computer select relays (R288 and R289) are located in flight instrument relay panel P73. The P73 panel is installed on the left outboard side of the main electronic equipment center in the lower 41 section of the airplane.
B. The relay panel cover is held in place by two wing screws. The relays are installed with four screws and each terminates into three cable connectors.
2. Referenced Procedures
_____________________
A. 24-22-00, Manual Control - Maintenance Practices (Apply Power)
B. 34-41-00, Inertial Navigation System - Adjustment/Test (Operational Test)
3. Remove Relay
____________
A. Open the following circuit breakers: AFC WARN DC (P6 panel) A/P F/D SYS A AC (P7 panel) A/P F/D SYS A PITCH DC (P7 panel) A/P F/D SYS A ROLL DC (P7 panel) A/P F/D SYS B AC (P7 panel) A/P F/D SYS B PITCH DC (P7 panel) A/P F/D SYS B ROLL DC (P7 panel) F/D SYS C AC (P7 panel)(Airplanes without P126 panel) F/D SYS C DC (P7 panel)(Airplanes without P126 panel) A/P F/D SYS C AC (Airplanes with P126 panel) A/P F/D SYS C PITCH DC (Airplanes with P126 panel) A/P F/D SYS C ROLL DC (Airplanes with P126 panel) CAPT FLT INST SW RELAYS - F/D (P7 panel) F/O FLT INST SW RELAYS - F/D (P7 panel)
B. Open P73 panel.
C. Remove electrical connectors from relay.
D. Remove relay mounting screws and remove relay.
4. Install Relay
_____________
A. Hold relay on mounting and install mounting screws. XA XA NOTE:____On A/C incorporating AEB 34-162, indexing pins preclude XA installation of inappropriate relays. XA
B. Connect electrical connectors to relay.
C. Close P73 panel.
D. Test Relay
(1)
Close circuit breakers opened in step 3.A.
(2)
Provide electrical power. Refer to 24-22-00.
(3)
Verify that INS-1, INS-2, and INS-3 are operative and have aligned through code 8; if not, align INS. Refer to 34-41-00.
(4)
Position captain's and first officer's FLT DIR switches on AP-FD mode select panel to ON. Observe that F/D (or CMPTR) flag in captain's and first officer's ADI's are out of view.
EFFECTIVITY
ALL EXCEPT: LH 011-030,
051-070, 082-099; IB 406-
499; AZ 212-299;
SN 351-399; AT ALL 22 Page 401 Aug 25/8634-26-02
(5) Alternately position captain's FLT DIR CMPTR select switch to A, B,
then C. Observe that F/D (or CMPTR) flag remains retracted and
corresponding position light illuminates as each position is
selected.
(6) Alternately position first officer's FLT DIR CMPTR select switch to
A, C, then B. Observe that F/D (or CMPTR) flag in first officer's
ADI remains retracted and corresponding position light illuminates
as each position is selected.
(7) Position both FLT DIR switches to off.
(8) Turn off INS if no longer required. Refer to 34-41-00.
(9) Remove electrical power if no longer required. Refer to 24-22-00.
CAUTION:_______ IF ELECTRICAL POWER IS STILL REQUIRED TO PERFORM TESTS ON
SYSTEMS OTHER THAN AUTOPILOT/FLIGHT DIRECTOR OR YAW DAMPER
OPEN THE FOLLOWING CIRCUIT BREAKERS TO PREVENT UNNECESSARY
WEAR OF RATE GYROS.
A/P F/D SYS A AC YAW DAMP UPR RUD AC
A/P F/D SYS B AC YAW DAMP LWR RUD AC
A/P F/D SYS C AC
EFFECTIVITY
ALL EXCEPT: LH 011-030,
051-070, 082-099; IB 406-
499; AZ 212-299;
SN 351-399; AT ALL 19 Page 402 Aug 25/8634-26-02
VOR/ILS NAVIGATION SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________
1. General
_______
A. Two VOR/ILS (VHF omnidirectional range/instrument landing systems) navigation systems and a switchable 3rd receiver are installed. A system consists of a VHF NAV control panel, a VOR/ILS receiver, transfer switching, antenna switching, and displays on flight instruments. A VOR antenna, two localizer antennas, and either three, four or six glide slope antennas provide radio frequency inputs to the receivers. Either the VOR or the LOC antenna is selected by means of the A/P-F/D mode logic circuits. Figure 1 shows the location of each of the units associated with the VOR/ILS navigation systems. On LH 011-099; AF 152-154, 172-173, 191-194; GN ALL and MD ALL plus airplanes incorporating SB 34-2069 and LH airplanes incorporating SB 34-2069 or SB 34-2076, glide slope deviation information is also provided to the ground proximity warning system computer.
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