- artificial feel and trim unit
2. Job Set-up Information
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A. Referenced Information
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REFERENCE DESIGNATION
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AMM 27-23-00-710-001 Operational Test of the Rudder Artificial-Feel Loads AMM 27-23-17-000-001 Removal of the Artificial Feel Unlocking Solenoid 16CA AMM 27-23-17-400-001 Installation of the Artificial Feel Unlocking
Solenoid 16CA AMM 27-23-41-000-001 Removal of the Artificial Feel and Trim Unit AMM 27-23-41-400-001 Installation of the Artificial Feel and Trim Unit
3. Fault Confirmation
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A. Test Do the operational test of the rudder artificial-feel loads (Ref. AMM TASK 27-23-00-710-001).
4. Fault Isolation
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A. If during the test, after activation of the rudder artificial-feel solenoid, the force to move the rudder pedals does not increase.
(1) Replace the SOLENOID-RUDDER ARTF FEEL (16CA) (Ref. AMM TASK 27-23-17-000-001) and (Ref. AMM TASK 27-23-17-400-001).
(2) If the fault continues:
- replace the artificial feel and trim unit (Ref. AMM TASK 27-23-41-000-001) (Ref. AMM TASK 27-23-41-400-001).
B. Do the test given in para. 3.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : ALL ∞∞27-20-00∞∞∞∞∞∞∞∞∞∞Page 216
May 01/05 CES Fluctuation of the Pointer of the RUD Indicator on the lower ECAM DU.
1. Possible Causes
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- SDAC-1 (1WV1)
- SDAC-2 (1WV2)
- XDCR UNIT-RUDDER POS (42WV)
- DMC-2 (1WT2)
- DMC-1 (1WT1)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
31-32-00-810-933 Failure of the Analog Links AMM 27-25-17-000-001 Removal of the Rudder Position Transducer Unit 42WV AMM 27-25-17-400-001 Installation of the Rudder Position Transducer Unit
42WV
AMM 31-55-34-000-001 Removal of the SDAC (1WV1,1WV2)
AMM 31-55-34-400-001 Installation of the SDAC (1WV1,1WV2)
AMM 31-63-34-000-001 Removal of the DMC (1WT1,1WT2,1WT3)
AMM 31-63-34-400-001 Installation of the DMC (1WT1,1WT2,1WT3)
ASM 31-54/04
ASM 31-54/08
3. Fault Confirmation
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A. Not applicable, the fault is evident on the F/CTL page of the lower ECAM DU.
4. Fault Isolation
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A. Table of the circuit breakers used in this procedure:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU SDAC/1/SPLY 3WV F04 49VU SDAC/2/26VAC SYNC/AC ESS BUS 6WV F03 49VU SDAC/1/26VAC SYNC/AC ESS BUS 5WV F02 121VU EIS/SDAC1 AND 2/BUS2/28VDC 44WV P03 121VU EIS/SDAC/2/SPLY 2WV Q06 121VU EIS/SDAC/1/BUS2/26VAC SYNC AC 7WV Q03 121VU EIS/SDAC/2/BUS2/26VAC SYNC AC 8WV Q02
May 01/05R CES
R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-299, 301-302,
B. If there are fluctuations of the pointer of the RUD indicator on the F/CTL page:
(1) Open the circuit breakers 3WV, 5WV, 7WV and 44WV.
(a) If the fluctuations of the pointer continue:
- see para.(2).
(b) If the fluctuations of the pointer stop:
- replace the SDAC-1 (1WV1) (Ref. AMM TASK 31-55-34-000-001) and (Ref. AMM TASK 31-55-34-400-001).
- do a check of the wiring from the SDAC 1 to the first terminal block (Ref. ASM 31-54/08) (RUD POS XDCR unit side).
- do a check of the wiring from the SDAC 1 to the first terminal block (Ref. ASM 31-54/04) (DMC side).
(2) Close the circuit breakers 3WV, 5WV, 7WV and 44WV.
(3) Open the circuit breakers 2WV, 6WV, 8WV and 44WV.
(a) If the fluctuations of the pointer continue:
- see para.(5).
(b) If the fluctuations of the pointer stop:
- replace the SDAC-2 (1WV2) (Ref. AMM TASK 31-55-34-000-001) and (Ref. AMM TASK 31-55-34-400-001).
- do a check of the wiring from the SDAC 2 to the first terminal block (Ref. ASM 31-54/04) (RUD POS XDCR unit side).
- do a check of the wiring from the SDAC 2 to the first terminal block (Ref. ASM 31-54/04) (DMC side). 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 1(34)
