E190 Reset Guide

QUICK-REFERENCE RESET GUIDE

FOR REFERENCE USE ONLY The data contained herein is intended to assist troubleshooting only and is not a substitute for Embraer and/or operator’s manuals. Fault correcting maintenance and the aircraft’s “return to service” testing shall be accomplished in full accordance with proper Embraer and/or operator’s manuals. All inquires regarding this material should be addressed to: [email protected]

JANUARY 2006

REVISION 10 – May 2010

Copyright 2010 by EMBRAER - Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced, whether in whole or in part, in any form or by any means

without the express written authorization of Embraer. The information, technical data, designs and drawings disclosed in this document are property information of Embraer or third parties and shall not be

used or disclosed to any third party without permission of Embraer.

May 10

TABLE OF CONTENTS

INTRODUCTION......................................................................... 8 MAU AND SPDA RESET SAFETY PROCEDURES ................. 10 GENERAL INFORMATION....................................................... 15 ACARS FROZEN...................................................................... 16 ADS 1 FAIL............................................................................... 17 ADS 1 HTR FAIL ...................................................................... 17 ADS 1 HTR FAULT................................................................... 18 ADS 2 FAIL............................................................................... 18 ADS 2 HTR FAIL ...................................................................... 19 ADS 2 HTR FAULT................................................................... 20 ADS 3 FAIL............................................................................... 21 ADS 3 FAIL............................................................................... 22 ADS 3 SLIPCOMP FAIL ........................................................... 23 ADS 4 HTR FAIL ...................................................................... 24 ADS 4 SLIPCOMP FAIL ........................................................... 25 ADS PROBE 1 FAIL ................................................................. 26 ADS PROBE 2 FAIL ................................................................. 27 ADS PROBE 3 FAIL ................................................................. 28 ADS PROBE 4 FAIL ................................................................. 29 AFCS FAULT............................................................................ 30 A-I ENG 1 FAULT ..................................................................... 31 A-I ENG 2 FAULT ..................................................................... 32 A-I WING FAIL.......................................................................... 33 AMBER "X" ON RECIRC FAN INDICATION (ECS SYNOPTIC PAGE) .......................................................... 34 AOA LIMIT FAIL ....................................................................... 35 APPR 2 NOT AVAIL ................................................................. 35 APU FAIL.................................................................................. 36 APU FUEL SOV FAIL ............................................................... 36 AT FAIL .................................................................................... 37 AURAL WRN SYS FAIL ........................................................... 38 AURAL WRN SYS FAULT........................................................ 38 AUTOBRAKE FAIL................................................................... 39 AVNX MAU 1A FAIL................................................................. 39 AVNX MAU 1A FAULT ............................................................. 40 AVNX MAU 1B FAIL................................................................. 41 AVNX MAU 1B FAULT ............................................................. 42 AVNX MAU 2A FAIL................................................................. 43

May 10

AVNX MAU 2A FAULT .............................................................44 AVNX MAU 2B FAIL .................................................................45 AVNX MAU 2B FAULT .............................................................46 AVNX MAU 3A FAIL .................................................................47 AVNX MAU 3A FAULT .............................................................48 AVNX MAU 3B FAIL .................................................................49 AVNX MAU 3B FAULT .............................................................50 BLEED 1 FAIL...........................................................................51 BLEED 1 OFF ...........................................................................52 BLEED 2 FAIL...........................................................................53 BLEED 2 OFF ...........................................................................54 BRK CONTROL FAULT............................................................55 BRK LH FAULT ........................................................................55 BRK LH FAULT ........................................................................56 CAS MSG INDICATION ON PFD..............................................56 CENTER EBAY FANS FAIL......................................................57 CHIMES NOT AVAILABLE - ALL POSITIONS.........................58 CMF 1 FAIL...............................................................................58 "CMC IN AIR" OR "CMC CONNECTION FAILED" MESSAGES ON CMC SCREEN ...............................................59 COPILOT DAP PROBLEMS - DISPLAY, VOLUME AND CONTROLS ..............................................................................60 CVR AFT FAIL ..........................................................................60 CVR FWD FAIL .........................................................................61 DATALINK TIMEOUT SHOWS ON THE MCDU 1 SCRATCHPAD..........................................................................61 DATALINK TIMEOUT SHOWS ON THE MCDU 2 SCRATCHPAD..........................................................................62 EICAS FAULT...........................................................................62 ELEVATOR FAULT...................................................................63 ELEVATOR LH FAIL.................................................................63 ELEVATOR RH FAIL ................................................................64 ENG 1 FADEC FAULT ..............................................................65 ENG 1 FUEL SW FAIL .............................................................66 ENG 2 FADEC FAULT ..............................................................67 ENG 2 FUEL SW FAIL .............................................................68 ENG TLA TRIM FAIL ................................................................69 FDR AFT FAIL ..........................................................................70 FDR FWD FAIL .........................................................................70 FLAP FAIL ................................................................................71

May 10

FLAP LO RATE ........................................................................ 72 FLT CTRL BIT EXPIRED.......................................................... 73 FLT CTRL FAULT..................................................................... 74 FLT CTRL NO DISPATCH........................................................ 75 FLT CTRL NO DISPATCH/FLT CTRL FAULT/FLT CTRL BIT EXPIRED, AUTO CONFIG TRIM FAIL (ALTERNATE PROCEDURE) .......................................................................... 76 FMS 1 FAIL............................................................................... 77 FMS 2 FAIL............................................................................... 78 FMS1 TIMEOUT SHOWS ON THE MCDU 1 SCRATCHPAD ......................................................................... 79 FMS1-2 TIMEOUT SHOWS ON THE MCDU 1 SCRATCHPAD ......................................................................... 80 FMS1-2 TIMEOUT SHOWS ON THE MCDU 2 SCRATCHPAD ......................................................................... 81 FMS2 TIMEOUT SHOWS ON THE MCDU 2 SCRATCHPAD ......................................................................... 82 FUEL DC PUMP FAIL............................................................... 83 FUEL EQUAL-XFEED OPEN.................................................... 83 FWD EBAY FANS FAIL............................................................ 84 GND PROX FAIL ...................................................................... 85 GROUND SPOILERS FAIL....................................................... 86 HUD 1 FAIL .............................................................................. 86 HUD 2 FAIL .............................................................................. 87 HUD FAIL ................................................................................. 88 ICE DETECTOR 1 FAIL ............................................................ 89 ICE DETECTOR 2 FAIL ............................................................ 90 INPH AUDIO (BETWEEN DAPS) - NOISY OR NOT AVAILABLE ............................................................... 91 INVERTER FAIL ....................................................................... 91 IRS 1 FAIL ................................................................................ 92 IRS 2 FAIL ................................................................................ 92 IRS PRES POS INVALID .......................................................... 93 LAV SMOKE............................................................................. 94 LAV SMOKE DET FAIL ............................................................ 95 LG NO DISPATCH.................................................................... 96 LG NOSE DOOR OPEN............................................................ 96 LG WOW SYS FAIL.................................................................. 97 MFD 1 FAULT........................................................................... 97 MFD 2 FAULT........................................................................... 98

May 10

NAVCOM 1 FAIL.......................................................................98 NAVCOM 2 FAIL.......................................................................99 NO LEFT FUEL QTY INDICATION ON EICAS .........................99 NO RIGHT FUEL QTY INDICATION ON EICAS .....................100 NO TOTAL FUEL QTY INDICATION ON EICAS ....................100 OBSERVER DAP PROBLEMS - DISPLAY, VOLUME AND CONTROLS....................................................100 PACK 1 FAIL ..........................................................................101 PACK 2 FAIL ..........................................................................101 PFD 1 FAULT..........................................................................102 PFD 2 FAULT..........................................................................102 PILOT DAP PROBLEMS - DISPLAY, VOLUME AND CONTROLS ............................................................................103 PITCH TRIM BKUP FL............................................................103 PITCH TRIM FAIL ...................................................................104 PITCH TRIM SW 1 FAIL..........................................................105 PITCH TRIM SW 2 FAIL..........................................................106 POTABLE WATER OR WASTE SYSTEM INOPERATIVE. ....107 PRESN AUTO FAIL ................................................................108 PRESN AUTO FAULT.............................................................109 PRESN MAN FAIL ..................................................................110 RADIOS TIMEOUT SHOWS ON THE MCDU 1 SCRATCHPAD........................................................................111 RADIOS TIMEOUT SHOWS ON THE MCDU 2 SCRATCHPAD........................................................................111 RALT 1 FAIL ...........................................................................112 RALT 2 FAIL ...........................................................................112 RAM AIR FAULT.....................................................................113 RAT FAIL ................................................................................114 RECIRC SMK DET FAIL .........................................................115 RECIRC SMOKE.....................................................................115 REFUEL PG TIMEOUT SHOWS ON THE MCDU 1 SCRATCHPAD........................................................................116 REFUEL PG TIMEOUT SHOWS ON THE MCDU 2 SCRATCHPAD........................................................................117 REMOTE CB TRIP ..................................................................118 RUDDER FAIL ........................................................................119 RUDDER FAULT.....................................................................119 SETUP PG TIMEOUT SHOWS ON THE MCDU 1 SCRATCHPAD........................................................................120

May 10

SETUP PG TIMEOUT SHOWS ON THE MCDU 2 SCRATCHPAD ....................................................................... 120 SHAKER 1 FAIL ..................................................................... 121 SHAKER 2 FAIL ..................................................................... 122 SLAT FAIL.............................................................................. 123 SLAT LO RATE ...................................................................... 124 SLAT-FLAP LEVER DISAG.................................................... 125 SPDA FAIL ............................................................................. 125 SPDBRK LEVER DISAG ........................................................ 126 SPOILER FAULT.................................................................... 126 STEER FAIL ........................................................................... 126 STEER FAULT........................................................................ 127 TAT 1 FAIL ............................................................................. 127 TAT 2 FAIL ............................................................................. 127 TCAS FAIL ............................................................................. 128 TERRAIN FAIL ....................................................................... 129 TERRAIN NOT AVAILABLE................................................... 130 TEST PG TIMEOUT SHOWS ON THE MCDU 1 SCRATCHPAD ....................................................................... 131 TEST PG TIMEOUT SHOWS ON THE MCDU 2 SCRATCHPAD ....................................................................... 131 THRUST MGT TIMEOUT SHOWS ON THE MCDU 1 SCRATCHPAD ....................................................................... 132 THRUST MGT TIMEOUT SHOWS ON THE MCDU 2 SCRATCHPAD ....................................................................... 133 TRU 1 FAIL............................................................................. 134 TRU 2 FAIL............................................................................. 134 TRU ESS FAIL........................................................................ 135 UNCOMMANDED CHIME GENERATION – ALL POSITIONS............................................................................. 135 UNCOMMANDED HF COMM TRANSMISSION – ALL POSITIONS............................................................................. 136 UNCOMMANDED VHF COMM 1 TRANSMISSION - ALL POSITIONS............................................................................. 136 UNCOMMANDED VHF COMM 2 TRANSMISSION - ALL POSITIONS............................................................................. 137 UNCOMMANDED VHF COMM 3 TRANSMISSION - ALL POSITIONS............................................................................. 137 WATER SYSTEM FAULT INDICATION ON AFT FLIGHT ATTENDANT PANEL ............................................................. 138

May 10

WINDSHEAR FAIL..................................................................139 WINDSHIELD 1 HTR FAIL ......................................................140 WINDSHIELD 2 HTR FAIL ......................................................140 WX FAIL MESSAGE ON THE MFD ........................................141 XPDR 1 FAIL...........................................................................142 XPDR 2 FAIL...........................................................................142

May 10

INTRODUCTION

The purpose of this quick-reference guide is to provide information to help users in the troubleshooting routine and elimination of some faults detected on the aircraft through rest procedure. This guide does not cover all the messages/faults that may be detected on the aircraft. If the message/fault is not given in the quick-reference guide, refer to the FAULT ISOLATION MANUAL. The guide is organized in a three-column table, disposed as follows:

• ATA column: Gives the ATA number for the related fault/message.

• MESSAGE/FAULT column: Gives the messages/faults, alphabetically ordered.

• MAINTENANCE ACTION column: Gives the corrective action (PROCEDURE). It may also inform the EFFECTIVITY and/or FAULT CONDITION.

• “IS THE FAULT REMOVED?” column: Gives the results of the procedure indicated in the Maintenance Action column.

When the reset procedure does not remove the message/fault, refer to the FAULT ISOLATION MANUAL and do as follows:

1. On the “CAS MESSAGE LIST” or “OBSERVED FAULTS LIST”, in the front matter of the chapter, find the related FAULT CODE (FAULT CODE column).

2. Go to the “FAULT CODE INDEX”, and use the related FAULT CODE to do a check for correlated CMC messages:

(a) If there are correlated CMC messages, in the “CORRELATED MAINTENANCE MESSAGE CODE” column, look for the correlated maintenance messages on the CMC (AMM TASK 45-45-00-970-803-A/200) to find the task that you must do.

May 10

(b) If there are no correlated CMC messages go directly to the task given in the “GO TO FIM TASK” column.

If you have any doubts about how to use the FIM, refer to FAULT ISOLATION MANUAL USAGE section. Every effort has been made to ensure that the information presented in the Quick-Reference Reset Guide is in accordance with the Fault Isolation Manual. However, in the event of conflict between them, the Fault Isolation Manual shall prevail. NOTE: The Quick-Reference Reset Guide will be reissued on all revisions.

May 10

MAU and SPDA RESET SAFETY PROCEDURES

MAU - MAINTENANCE SAFETY PROCEDURES

(1) EFFECTIVITY: PRE-MOD SB 170-24-0017 (ON ACFT

WITH SPDA BLOCK 6.1)

If the aircraft is energized with APU and you need to do the reset of the MAU 1 and MAU 3, you must open the following SSPC to avoid the RAT deployment:

•RAT DEPLOY-SPDA1 (CBMENU/CB BY SYS/ELEC)

(2) If the aircraft is energized with APU and you open the

circuit breaker MAU 3 PWR 1, the APU will shutdown.

NOTE: To avoid power interruption, you must energize the aircraft with an AC external power supply.

(3) Before you reset MAU 1 or MAU 3 power supplies, make sure that all switches on the HYDRAULIC CONTROL PANEL are set at the OFF position.

(4) If you do the MAU reset procedure with the engines in

operation, engine related messages can show on the EICAS. We recommend that you stop the engines before the power-supply circuit-breaker cycling procedure.

(5) If it is necessary to open the MAU 1 and/or MAU 3 circuit

breakers, the message “SPOILER FAULT” “and “A-I WING FAIL” will show on the EICAS.

(6) EFFECTIVITY: ON ACFT WITH ‘MAU2 PWR2 PRI’

CIRCUIT BREAKER ON DC ESS BUS 2

If it is necessary to open the MAU 2 PWR 2 PRI-RHCBP (DC ESS BUS 2) circuit breaker, the message “RAT FAIL” will show on the EICAS.

May 10

(7) This procedure must be done to prevent the integrated pitot/static/AOA and TAT system heating in any of these situations:

- If you open one of these MAU 1 circuit breakers: • MAU 1 PWR 2-LHCBP (DC ESS BUS 1) • MAU 1 PWR 3-LHCBP (DC BUS 1)

- If you open one of these MAU 3 circuit breakers: • MAU 3 PWR 1-RHCBP (DC ESS BUS 2) • MAU 3 PWR 2-RHCBP (DC BUS 2) • MAU 3 CUST I/O 2A-RHCBP (DC ESS BUS 2) • MAU 3 CUST I/O 2B-RHCBP (DC BUS 2)

WARNING: THE INTEGRATED PITOT/STATIC/AOA AND TAT HEATING SYSTEMS MUST BE OFF DURING MAINTENANCE. THIS IS BECAUSE SYSTEMS THAT INTERFACE WITH MAU 1, MAU 3 AND SPDA 2 CAN CAUSE THE INTEGRATED PITOT/STATIC/AOAAND TAT SENSORS TO BECOME HOT. THESE SENSORS OPERATE AT HIGH TEMPERATURE. IF YOU TOUCH THEM, THEY WILL CAUSE INJURIES TO YOU.

(a) Open this circuit breaker and put a circuit breaker ring and tag (inoperative - do not operate) on it: • PROBE 3 HEATER PWR-RHCBP (DC ESS BUS 3 NAV). (b) On the MCDU, use the sequence in parentheses to open these SSPCs: • TAT 1 HEAT-SPDA1 (CBMENU/CB BY SYS/ICE/RAIN). • TAT 2 HEAT-SPDA1 (CBMENU/CB BY SYS/ICE/RAIN).

May 10

(c) Open these circuit breakers and put a circuit breaker ring and tag (inoperative - do not operate) on each one of them: • ADS PROBE 1 HTR-LICC (DC BUS 1) • ADS PROBE 2 HTR-LICC (DC BUS1) • ADS PROBE 4 HTR-RICC (DC BUS 2)

(8) To restore the systems affected by the MAU safety

procedures to their initial condition, do as follows:

(a) Remove the circuit breaker ring and tag (inoperative - do not operate) from this circuit breaker, and close it: • PROBE 3 HEATER PWR-RHCBP (DC ESS BUS 3 NAV) (b) On the MCDU, use the sequence in parentheses to close these SSPCs: • TAT 1 HEAT-SPDA1 (CBMENU/CB BY SYS/ICE/RAIN) • TAT 2 HEAT-SPDA1 (CBMENU/CB BY SYS/ICE/RAIN) (c) Remove the circuit breaker ring and tag (inoperative - do not operate) from each of these circuit breakers, and close them: • ADS PROBE 1 HTR-LICC (DC BUS 1) • ADS PROBE 2 HTR-LICC (DC BUS1) • ADS PROBE 4 HTR-RICC (DC BUS 2)

May 10

SPDA - MAINTENANCE SAFETY PROCEDURES

(1) Before you reset SPDA 1 or SPDA 2 power supplies,

make sure that all switches on the HYDRAULIC CONTROL PANEL are set at the OFF position.

(2) This procedure must be done to prevent the integrated

pitot/static/AOA and TAT system heating if you open one of these SPDA 2 circuit breakers:

• SPDA2 PWR SPLY 1-RICC (DC BUS 2) • SPDA2 PWR SPLY 3-EICC (DC ESS BUS 1) • SPDA2 PWR SPLY 2-RICC (DC ESS BUS 2) • SPDA2 PWR SPLY 4-LICC (DC GND SVC BUS) • SPDA2 I-O MOD 11-RICC (DC ESS BUS 2)

WARNING: OBEY ALL THE SPDA SAFETY PROCEDURES. IF YOU DO NOT OBEY THESE PROCEDURES, INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT CAN OCCUR. WARNING: THE INTEGRATED PITOT/STATIC/AOA AND TAT HEATING SYSTEMS MUST BE OFF DURING MAINTENANCE. THIS IS BECAUSE SYSTEMS THAT INTERFACE WITH MAU 1, MAU 3 AND SPDA 2 CAN CAUSE THE INTEGRATED PITOT/STATIC/AOA AND AT SENSORS TO BECOME HOT. THESE SENSORS OPERATE AT HIGH TEMPERATURE. IF YOU TOUCH THEM, THEY WILL CAUSE INJURIES TO YOU.

(a) On the MCDU, use the sequence in parentheses to open these SSPCs: • TAT 1 HEAT-SPDA1 (CBMENU/CB BY SYS/ICE/RAIN) • TAT 2 HEAT-SPDA1 (CBMENU/CB BY SYS/ICE/RAIN)

(b) Open these circuit breakers and put a circuit breaker ring and tag (inoperative - do not operate) on each one of them:

May 10

• PROBE 3 HEATER PWR-RHCBP (DC ESS BUS 3 NAV)

• ADS PROBE 1 HTR-LICC (DC BUS 1) • ADS PROBE 2 HTR-LICC (DC BUS1) • ADS PROBE 4 HTR-RICC (DC BUS 2)

(3) To restore the systems affected by the SPDA safety

procedures, do as follows:

(a) On the MCDU, use the sequence in parentheses to close these SSPCs: • TAT 1 HEAT-SPDA1 (CBMENU/CB BY SYS/ICE/RAIN) • TAT 2 HEAT-SPDA1 (CBMENU/CB BY SYS/ICE/RAIN)

(b) Remove the circuit breaker ring and tag (inoperative - do not operate) from these circuit breakers, and close them: • PROBE 3 HEATER PWR-RHCBP (DC ESS BUS 3 NAV) • ADS PROBE 1 HTR-LICC (DC BUS 1) • ADS PROBE 2 HTR-LICC (DC BUS1) • ADS PROBE 4 HTR-RICC (DC BUS 2)

May 10

General Information

The purpose of this section is to provide some standard procedures and general information.

(1) The Quick-Reference Reset Guide must be used only

with the aircraft on the ground.

(2) To perform the procedures that follow, refer to AMM TASK 45-45-00-970-805-A: • MAU module reset test; • Initiated BIT; • PBIT; • Clear Inhibit.

(3) To open and/or close a SSPC on the MCDU, refer to SDS

34-61-00.

May 10

ATA MESSAGE /

FAULT MAINTENANCE ACTION IS THE FAULT

REMOVED?

23 ACARS

FROZEN

EFF: [ON ACFT WITH CMF] PROCEDURE: CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS, AND STATIC PORT HAVE NO COVERS ON THEM BEFORE YOU DO THE MAINTENANCE PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THE MAINTENANCE PROCEDURE. AS A RESULT, DAMAGE TO THEM WILL OCCUR IF YOU DO NOT REMOVE THE COVERS. Open this circuit breaker and, after approximately 5 seconds, close it: • MAU 3 PWR 2-RHCBP (DC BUS 2)

Yes. FIM TASK 23-24-00-810-868-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

34 ADS 1 FAIL

Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 1 PROBE 1A-2A-LHCBP (DC BUS 1 NAV) • ADS FC PROBE 1B-2B-LHCBP (DC BUS 1 NAV)


30 ADS 1 HTR

FAIL

FAULT CONDITION: During power-up PROCEDURE: Open these circuit breakers and, after 30 seconds, close them: • ADS 1 PROBE 1A-2A-LHCBP (DC BUS 1/NAV) • ADS FC PROBE 1B-2B-LHCBP (DC BUS 1/NAV)


May 10

ATA MESSAGE /


REMOVED?

30 ADS 1 HTR

FAULT

FAULT CONDITION: During power-up PROCEDURE: Open these circuit breakers and, after 30 seconds, close them: • ADS 1 PROBE 1A-2A-LHCBP (DC BUS 1/NAV) • ADS FC PROBE 1B-2B-LHCBP (DC BUS 1/NAV)


34 ADS 2 FAIL

EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 2 NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV) • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV) EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 3 NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV) • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV)


May 10

ATA MESSAGE /


REMOVED?

30 ADS 2 HTR

FAIL

FAULT CONDITION: During power-up EFF: 170 - [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after 30 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3/NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 2/NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2/NAV) • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2/NAV) EFF: 170 - [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] 190 - [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] PROCEDURE: Open these circuit breakers and, after 30 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3/NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 3/NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2/NAV) • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2/NAV)


May 10

ATA MESSAGE /


REMOVED?

30 ADS 2 HTR

FAULT

FAULT CONDITION: During power-up EFF: 170 - [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after 30 seconds, close them: - ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3/NAV) - ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 2/NAV) - ADS 2 PROBE 4A-RHCBP (DC BUS 2/NAV) - ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2/NAV) EFF: 170 - [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] 190 - [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] PROCEDURE: Open these circuit breakers and, after 30 seconds, close them: - ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3/NAV) - ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 3/NAV) - ADS 2 PROBE 4A-RHCBP (DC BUS 2/NAV) - ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2/NAV)


May 10

ATA MESSAGE /


REMOVED?

30 ADS 3 FAIL



May 10

ATA MESSAGE /


REMOVED?

34 ADS 3 FAIL

EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 2 NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV) • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV) EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 3 NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV) • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV)


May 10

ATA MESSAGE /


REMOVED?

34

ADS 3 SLIPCOMP

FAIL

EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 2 NAV) • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV) EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 3 NAV) • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV)


May 10

ATA MESSAGE /


REMOVED?

30 ADS 4 HTR

FAIL



May 10

ATA MESSAGE /


REMOVED?

34

ADS 4 SLIPCOMP

FAIL

EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 2 NAV) • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV) EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 3 NAV) • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV)


May 10

ATA MESSAGE /


REMOVED?

34 ADS PROBE 1

FAIL

EFF: [ON ACFT WITH PRIMUS EPIC LOAD UP TO 21.5] FAULT CONDITION 1: The CAS message shows from the moment in which the aircraft is at the gate until the takeoff. ADS 1 FAIL does not show on the EICAS display. PROCEDURE: De-energize the aircraft and energize it again. FAULT CONDITION 2: The CAS message shows as soon as the aircraft lands. PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 1 PROBE 1A-2A-LHCBP (DC BUS 1 NAV) • ADS FC PROBE 1B-2B-LHCBP (DC BUS 1 NAV) EFF: [ON ACFT WITH PRIMUS EPIC LOAD 23.1 AND ON] FAULT CONDITION: The CAS message shows as soon as the aircraft lands. PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 1 PROBE 1A-2A-LHCBP (DC BUS 1 NAV) • ADS FC PROBE 1B-2B-LHCBP (DC BUS 1 NAV)

Yes. FIM TASK 34-15-00-810-852-A No. Refer to the correspondent chapter of the FIM for troubleshooting. Yes. FIM TASK 34-15-00-810-801-A No. Refer to the correspondent chapter of the FIM for troubleshooting. Yes. FIM TASK 34-15-00-810-801-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

34 ADS PROBE 2

FAIL

EFF: [ON ACFT WITH PRIMUS EPIC LOAD UP TO 21.5] FAULT CONDITION 1: The CAS message shows from the moment in which the aircraft is at the gate until the takeoff. ADS 1 FAIL does not show on the EICAS display. PROCEDURE: De-energize the aircraft and energize it again. FAULT CONDITION 2: The CAS message shows as soon as the aircraft lands. PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 1 PROBE 1A-2A-LHCBP (DC BUS 1 NAV) • ADS FC PROBE 1B-2B-LHCBP (DC BUS 1 NAV) EFF: [ON ACFT WITH PRIMUS EPIC LOAD 23.1 AND ON] FAULT CONDITION: The CAS message shows as soon as the aircraft lands. PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 1 PROBE 1A-2A-LHCBP (DC BUS 1 NAV) • ADS FC PROBE 1B-2B-LHCBP (DC BUS 1 NAV)


May 10

ATA MESSAGE /


REMOVED?

34 ADS PROBE 3

FAIL

EFF: [ON ACFT WITH PRIMUS EPIC LOAD UP TO 21.5] FAULT CONDITION 1: The CAS message shows from the moment in which the aircraft is at the gate until the takeoff. ADS 2 FAIL and ADS 3 FAIL do not show on the EICAS display. PROCEDURE: De-energize the aircraft and energize it again. FAULT CONDITION 2: The CAS message shows as soon as the aircraft lands. EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 2 NAV) EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 3 NAV) EFF: [ON ACFT WITH PRIMUS EPIC LOAD 23.1 AND ON] FAULT CONDITION: The CAS message shows as soon as the aircraft lands. EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 2 NAV) EFF: [ON ACFT WITH ADS 3/STBY PROBE 3B CIRCUIT BREAKER ON DC ESS BUS 3] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 3A-RHCBP (DC ESS BUS 3 NAV) • ADS 3/STBY PROBE 3B-RHCBP (DC ESS BUS 3 NAV)


May 10

ATA MESSAGE /


REMOVED?

34 ADS PROBE 4

FAIL

EFF: [ON ACFT WITH PRIMUS EPIC LOAD UP TO 21.5] FAULT CONDITION 1: The CAS message shows from the moment in which the aircraft is at the gate until the takeoff. ADS 2 FAIL and ADS 3 FAIL do not show on the EICAS display. PROCEDURE: De-energize the aircraft and energize it again. FAULT CONDITION 2: The CAS message shows as soon as the aircraft lands. PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV) • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV) EFF: [ON ACFT WITH PRIMUS EPIC LOAD 23.1 AND ON] FAULT CONDITION: The CAS message shows as soon as the aircraft lands. PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV) • ADS 3/STBY PROBE 4B-RHCBP (DC ESS BUS 2 NAV)


May 10

ATA MESSAGE /


REMOVED?

22 AFCS FAULT

On the CMC, in the ACTIVE MAINTENANCE MESSAGES and PRESENT LEG areas, look for any message correlated to the CAS messages below that may be causing the AFCS FAULT. • FLT CTRL NO DISPATCH • FLT CTRL FAULT • FLAP LO RATE • SLAT LO RATE • ADS PROBE 1 FAIL • ADS PROBE 2 FAIL • ADS PROBE 3 FAIL • ADS PROBE 4 FAIL • TAT 1 FAIL • TAT 2 FAIL • AP FAULT • AFCS FAULT Proceed accordingly. If there is not a correlated message, reset the aircraft.


May 10

ATA MESSAGE /


REMOVED?

30 A-I ENG 1

FAULT

FAULT CONDITION 1: "A-I ENG 1 FAULT" CAS message can come into view approximately 30 seconds after landing, if the respective bleed system remains off for 10 seconds during any flight phase; OR FAULT CONDITION 2: Bleed System 1 or 2 is off and the cross bleed valve is closed. EFF: [EMBRAER 190 and 195] PROCEDURE: On the ICE PROTECTION control panel, unlatch (off) the ENGINE 1 and ENGINE 2 switches (lights come on). Note: After 10 seconds, "A-I SWITCH OFF (advisory)" message shows on the EICAS. On the ICE PROTECTION control panel, latch (on) the ENGINE 1 and ENGINE 2 switches (lights go off). Note: "A-I SWITCH OFF (advisory)" message goes out of view.


May 10

ATA MESSAGE /


REMOVED?

30 A-I ENG 2

FAULT

FAULT CONDITION 1: "A-I ENG 2 FAULT" CAS message can come into view approximately 30 seconds after landing, if the respective bleed system remains off for 10 seconds during any flight phase; OR FAULT CONDITION 2: Bleed System 1 or 2 is off and the cross bleed valve is closed. EFF: [EMBRAER 190 and 195] PROCEDURE: On the ICE PROTECTION control panel, unlatch (off) the ENGINE 1 and ENGINE 2 switches (lights come on). Note: After 10 seconds, "A-I SWITCH OFF (advisory)" message shows on the EICAS. On the ICE PROTECTION control panel, latch (on) the ENGINE 1 and ENGINE 2 switches (lights go off). Note: "A-I SWITCH OFF (advisory)" message goes out of view.


May 10

ATA MESSAGE /


REMOVED?

30 A-I WING FAIL

FAULT CONDITION: "A-I WING FAIL" CAS message shows during the BIT (Built-in Test) PROCEDURE: On the overhead panel: • On the ICE PROTECTION control panel, turn the TEST switch to the WING position. • Unlatch the WING switch (light comes on). • After 10 seconds, "A-I SWITCH OFF (advisory)" message shows on the EICAS. • Latch the WING switch (light goes off). • "A-I SWITCH OFF (advisory)" message goes out of view. Wait for 60 seconds and verify if message does not show again on the CAS. FAULT CONDITION:"A-I WING FAIL" CAS message shows on EICAS with the letters CAS MSG displayed inside a cutout box on both PFDs. PROCEDURE: On the overhead panel: • On the ICE PROTECTION control panel, turn the TEST switch to the WING position. • Unlatch the WING switch (light comes on). • After 10 seconds, "A-I SWITCH OFF (advisory)" message shows on the EICAS. • Latch the WING switch (light goes off). • "A-I SWITCH OFF (advisory)" message goes out of view. Wait for 60 seconds and verify if message does not show again on the CAS


May 10

ATA MESSAGE /


REMOVED?

21

AMBER "X" ON RECIRC

FAN INDICATION

(ECS SYNOPTIC

PAGE)

FAULT CONDITION: RECIRC switch is set to AUTO, batteries are set to ON/AUTO, and the GPU is OFF for more than one minute PROCEDURE: On the overhead panel, on the AIR COND/PNEUMATIC control panel, set the RECIRC pushbutton to the unlatched (off) position. Wait 60 seconds and set it back to the latched (auto) position. If it does not work, reset the aircraft (power down/up).

Yes. FIM TASK 21-24-00-810-805. No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

27 AOA LIMIT

FAIL On the maintenance panel, make sure the FCS MAINT switch is in the OFF position.

Yes. FIM TASK 27-03-00-810-89L-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

22 APPR 2 NOT

AVAIL

Make sure that the same ADS and IRS sources are not selected on PFD 1 and PFD 2, the indications of RALT/IRS/ADS/FD are correct and there are no messages related to these systems on the EICAS.


May 10

ATA MESSAGE /


REMOVED?

49 APU FAIL

On the MCDU, open these SSPCs and close them after 10 seconds to confirm that the failure has occurred: • APU FADEC (CB/CB BY SYS/APU) • ABC CMD PWR (CB/CB BY SYS/APU) • ASC CMD PWR (CB/CB BY SYS/APU) Start the APU again.


28 APU FUEL SOV FAIL

FAULT CONDITION: The APU FUEL SOV FAIL CAS message was displayed during power-up and an APU start has not been attempted PROCEDURE: On the APU CONTROL panel set the EMER STOP pushbutton to the latched in (on) and latched out (off) position. NOTE: The resetting is valid only if the failure message occurred during power-up.


May 10

ATA MESSAGE /


REMOVED?

22 AT FAIL

FAULT CONDITION 1: "ENG TLA TRIM FAIL" message is active on the EICAS; AND FAULT CONDITION 2: The following maintenance messages are active on the CMC: 22310005TA1 - ENGINE DATA [TRSA1] FAULT 22310005TA2 - ENGINE DATA [TRSA2] FAULT 22310023TA1 - FADEC1/FADEC2 [ATA1] WRG FAULT 22310023TA2 - FADEC1/FADEC2 [ATA2] WRG FAULT 22310079TA1 - LEFT FADEC [ATA1] FAULT 22310079TA2 - LEFT FADEC [ATA2] FAULT 22310080TA1 - RIGHT FADEC [ATA1] FAULT 22310080TA2 - RIGHT FADEC [ATA2] FAULT NOTE: The recording of "RIGHT FADEC [ATxx] FAULT" or "LEFT FADEC [ATxx] FAULT" maintenance message on the CMC depends on the faulty FADEC. The left FADEC refers to engine 1 and the right FADEC refers to engine 2. EFF: [ALL] PROCEDURE: On the CMC, use the sequence that follows to get access to the ENGINE 1 GENERAL STATUS PAGE: • 73 - ENGINE FUEL AND CONTROL • 21 - ENGINE FADEC 1A • ENGINE 1 GENERAL STATUS PAGE If the CHANNEL IN CONTROL status is the same for both channels, go to the FIM TASK 22-31-00-810-821-A. On the CMC, use the sequence that follows to get access to the ENGINE 2 GENERAL STATUS PAGE: • 73 - ENGINE FUEL AND CONTROL • 21 - ENGINE FADEC 2A • ENGINE 2 GENERAL STATUS PAGE If the CHANNEL IN CONTROL status is the same for both channels, go to the FIM TASK 22-31-00-810-821-A.


May 10

ATA MESSAGE /


REMOVED?

31 AURAL WRN

SYS FAIL

On the CMC, use the sequence that follows to do the PROC module 1 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - PROC MODULE 1 (MAU 1 SLOT NIC 1) • MAU1 PROC1 MODULE RESET TEST On the CMC, use the sequence that follows to do the PROC module 4 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - PROC MODULE 4 (MAU 2 SLOT NIC 2) • MAU2 PROC4 MODULE RESET TEST

Yes. FIM TASK 45-45-00-810-81B-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

31 AURAL WRN SYS FAULT

On the CMC, use the sequence that follows to do the PROC module 1 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - PROC MODULE 1 (MAU 1 SLOT NIC 1) • MAU1 PROC1 MODULE RESET TEST On the CMC, use the sequence that follows to do the PROC module 4 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - PROC MODULE 4 (MAU 2 SLOT NIC 2) • MAU2 PROC4 MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

32 AUTOBRAKE

FAIL On the CMC (System Diagnostics/ 32 - Landing Gear), run the RESET TEST for AUTOBRAKE MODULE.


31 AVNX MAU 1A

FAIL

CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORT HAVE NO COVERS ON THEM BEFORE YOU DO THE MAINTENANCE PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THE MAINTENANCE PROCEDURE. AS A RESULT, DAMAGE TO THEM WILL OCCUR IF YOU DO NOT REMOVE THE COVERS. Open these circuit breakers and, after approximately 5 seconds, close them: NOTE: If power is removed from the CMC module for more than 10 seconds, the CMC module will start its shutdown procedure. When power is supplied to the CMC module again, it will start its power-up procedure. The full process takes approximately 5 minutes. • MAU 1 PWR 1-LHCBP (DC ESS BUS 1) • MAU 1 PWR 2-LHCBP (DC ESS BUS 1) • MAU 1 PWR 3-LHCBP (DC BUS 1) On the CMC, use the sequence that follows to do the MAU 1 NIC module 1 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - MAU 1 NIC 1 • MAU1_NIC1 MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 1A

FAULT


Yes. FIM TASK 31-41-00-810-88S-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 1B

FAIL



May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 1B

FAULT

CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORT HAVE NO COVERS ON THEM BEFORE YOU DO THE MAINTENANCE PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THE MAINTENANCE PROCEDURE. AS A RESULT, DAMAGE TO THEM WILL OCCUR IF YOU DO NOT REMOVE THE COVERS. Open these circuit breakers and, after approximately 5 seconds, close them: NOTE: If power is removed from the module for more than 10 seconds, the CMC module will start its shutdown procedure. When power is supplied to the CMC module again, it will start its power-up procedure. The full process takes approximately 5 minutes. • MAU 1 PWR 1-LHCBP (DC ESS BUS 1) • MAU 1 PWR 2-LHCBP (DC ESS BUS 1) • MAU 1 PWR 3-LHCBP (DC BUS 1) On the CMC, use the sequence that follows to do the MAU 1 NIC module 2 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - MAU 1 NIC 2 • MAU1_NIC2 MODULE RESET TEST

Yes. FIM TASK 31-41-00-810-88Y-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 2A

FAIL

EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC ESS BUS 2) EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC ESS BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC BUS 2) EFF: ALL PROCEDURE: On the CMC, use the sequence that follows to do the MAU 2 NIC module 3 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - MAU2 NIC 1 • MAU2_NIC3 MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 2A

FAULT

EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC ESS BUS 2) EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC ESS BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC BUS 2) EFF: ALL PROCEDURE: On the CMC, use the sequence that follows to do the MAU 2 NIC module 3 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - MAU 2 NIC 1 • MAU2_NIC3 MODULE RESET TEST

Yes. FIM TASK 31-41-00-810-89F-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 2B

FAIL



May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 2B

FAULT


Yes. FIM TASK 31-41-00-810-89M-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 3A

FAIL

CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORT HAVE NO COVERS ON THEM BEFORE YOU DO THE MAINTENANCE PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THE MAINTENANCE PROCEDURE. AS A RESULT, DAMAGE TO THEM WILL OCCUR IF YOU DO NOT REMOVE THE COVERS. Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 3 PWR 1-RHCBP (DC ESS BUS 2) • MAU 3 PWR 2-RHCBP (DC BUS 2) On the CMC, use the sequence that follows to do the MAU 3 NIC module 5 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - MAU 3 NIC 1 • MAU3 NIC5 MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 3A

FAULT


Yes. FIM TASK 31-41-00-810-89T-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 3B

FAIL



May 10

ATA MESSAGE /


REMOVED?

31 AVNX MAU 3B

FAULT

CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORT HAVE NO COVERS ON THEM BEFORE YOU DO THE MAINTENANCE PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THE MAINTENANCE PROCEDURE. AS A RESULT, DAMAGE TO THEM WILL OCCUR IF YOU DO NOT REMOVE THE COVERS. Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 3 PWR 1-RHCBP (DC ESS BUS 2) • MAU 3 PWR 2-RHCBP (DC BUS 2) On the CMC, use the sequence that follows to do the NIC + PROC module 6 reset test: • 31 - INDICATING/RECORDING SYSTEMS • 41 - MAU 3 NIC 2 • MAU3 NIC6 MODULE RESET TEST

Yes. FIM TASK 31-41-00-810-90A-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

36 BLEED 1 FAIL

FAULT CONDITION: With the letters CAS MSG shown in a cutout box on both PFD or during the BIT (Built-in Test). PROCEDURE: On the overhead panel, reset the BLEED 1 pushbutton. EFF: 170 - [ON ACFT WITH BLACK LABEL 6 AND ON] OR [POST-MOD SB 170-21-0016] 190 - [ON ACFT WITH BLACK LABEL 6 AND ON] OR [POST-MOD SB 190-21-0002] FAULT CONDITION: The BLEED 1 FAIL message shows on the CAS, but the BLEED 1 OFF message does not show. PROCEDURE: On the overhead panel, reset the BLEED 1 pushbutton.

Yes. FIM TASK 36-10-00-810-804A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

36 BLEED 1 OFF

FAULT CONDITION: The message BLEED 1 OFF comes into view on the EICAS. PROCEDURE: Make sure that the bleed 1 pushbutton is in the AUTO position (pushed - light goes off).


May 10

ATA MESSAGE /


REMOVED?

36 BLEED 2 FAIL

FAULT CONDITION: With the letters CAS MSG shown in a cutout box on both PFD or during the built-in test. PROCEDURE: On the overhead panel, reset the BLEED 2 pushbutton. EFF: 170 - [ON ACFT WITH BLACK LABEL 6 AND ON] OR [POST-MOD SB 170-21-0016] 190 - [ON ACFT WITH BLACK LABEL 6 AND ON] OR [POST-MOD SB 190-21-0002] FAULT CONDITION: The BLEED 2 FAIL message shows on the CAS, but the BLEED 2 OFF message does not show. PROCEDURE: On the overhead panel, reset the BLEED 2 pushbutton.


May 10

ATA MESSAGE /


REMOVED?

36 BLEED 2 OFF

FAULT CONDITION: The message BLEED 2 OFF comes into view on the EICAS. PROCEDURE: Make sure that the bleed 2 pushbutton is in the AUTO position (pushed - light goes off).


May 10

ATA MESSAGE /


REMOVED?

32

BRK CONTROL

FAULT

FAULT CONDITION: After the aircraft power-up PROCEDURE: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


32 BRK LH FAULT

FAULT CONDITION: The messages BRK LH FAULT and BRK RH FAULT are displayed at the same time on the EICAS after landing, before takeoff and during taxi. EFF: All 190 and 195 PROCEDURE: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

32 BRK LH FAULT

FAULT CONDITION: The messages BRK RH FAULT and BRK LH FAULT are displayed at the same time on the EICAS after landing, before takeoff and during taxi. EFF: All 190 and 195 PROCEDURE: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


31

CAS MSG INDICATION

ON PFD

• If the message does not go out of view do the power-down/up procedure to reset the SPDAs. To do this, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200).

Compare the two CAS message lists and do the related fault isolation task.

May 10

ATA MESSAGE /


REMOVED?

21 CENTER EBAY

FANS FAIL

EFF: [ON ACFT WITH SPDA BLOCK 6.1 (MICRO/COMM PN 1705540D)] FAULT CONDITION: Aircraft changes directly from Ground Service Mode to any other operating mode such as: • Ground Service to Batteries • Ground Service to GPU • Ground Service to APU Gen PROCEDURE: Reset the aircraft (power down/up). EFF: [LDI UP TO V02] PROCEDURE: On the CMC, use the sequence that follows to run the ebay fans BIT (Built-in Test): • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM A (B) • EBAY FAN INITIATED BIT CH A (B) EFF: [LDI FROM V03 TO LDI V05.1] PROCEDURE: On the CMC, use the sequence that follows to run the ebay fans BIT (Built-in Test): • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM A (B) • AVIONICS COMPARTMENT FANS IBIT CH A (B) EFF: [LDI V06 AND ON] PROCEDURE: On the CMC, use the sequence that follows to run the ebay fans BIT (Built-in Test): • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM A (B) • AVIONICS COMPARTMENT FANS IBIT CH 1 (2)

Yes. FIM TASK 21-26-00-810-833-A . No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

23 Chimes not

available - All Positions

PROCEDURE: On the CMC, use the sequence that follows to do the MRC 1 NIM reset test (AMM TASK 45-45-00-970-805-A/200): • 34 - NAVIGATION • 02 - MODULAR RADIO CABINET 1 - NIC • MRC1 NIM [NIC] MODULE RESET TEST Afterwards, on the CMC, use the sequence that follows to do the MRC 2 NIM reset test (AMM TASK 45-45-00-970-805-A/200): • 34 - NAVIGATION • 02 - MODULAR RADIO CABINET 2 - NIC • MRC2 NIM [NIC] MODULE RESET TEST


23 CMF 1 FAIL

EFF: [ON ACFT WITH CMF] PROCEDURE: CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS, AND STATIC PORT HAVE NO COVERS ON THEM BEFORE YOU DO THE MAINTENANCE PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THE MAINTENANCE PROCEDURE. AS A RESULT, DAMAGE TO THEM WILL OCCUR IF YOU DO NOT REMOVE THE COVERS. Open this circuit breaker and, after approximately 5 seconds, close it: • MAU 3 PWR 2-RHCBP (DC BUS 2)


May 10

ATA MESSAGE /


REMOVED?

45

"CMC in air" or "CMC

connection failed"

messages on CMC screen

FAULT CONDITION: The messages "CMC in air" or "CMC connection failed" are displayed when the airspeed is less than 50 kts (AMM SDS 34-15-00/1) and the TLA is less than 50° (AMM SDS 76-00-00/1). PROCEDURE: Open this circuit breaker and, after approximately 5 seconds, close it: • MAU 1 PWR 3-LHCBP (DC ESS BUS 1)

Yes. FIM TASK 45-45-00-810-89P-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

23

Copilot DAP Problems -

Display, Volume and

Controls

PROCEDURE: Open this circuit breaker and, after approximately 5 seconds, close it: • COMM AUDIO 2-RHCBP (DC ESS BUS 2)


31 CVR AFT FAIL

On the MCDU, use the sequence in parentheses to open these SSPCs. After approximately 10 seconds, close them: • FDR ACCEL-SPDA2 (CBMENU/CB BY SYS/FDR/CVR) • DVDR 2-SPDA2 (CBMENU/CB BY SYS/FDR/CVR)


May 10

ATA MESSAGE /


REMOVED?

31 CVR FWD FAIL

On the MCDU, use the sequence in parentheses to open these SSPCs. After approximately 10 seconds, close them: • FDR ACCEL-SPDA2 (CBMENU/CB BY SYS/FDR/CVR) • DVDR 1-SPDA1 (CBMENU/CB BY SYS/FDR/CVR)


23

DATALINK TIMEOUT

Shows on the MCDU 1

Scratchpad

PROCEDURE: 1) On the MCDU 1, push the CLR key as necessary until you clear the scratchpad; 2) On the MCDU 1, push the MENU function key and then, the DLK function key; 3) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

23

DATALINK TIMEOUT

Shows on the MCDU 2

Scratchpad

PROCEDURE: 1) On the MCDU 2, push the CLR key as necessary until you clear the scratchpad; 2) On the MCDU 2, push the MENU function key and then, the DLK function key; 3) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


31 EICAS FAULT Open this circuit breaker and, after approximately 5 seconds, close it: • EICAS-LHCBP (DC ESS BUS 1 DISPLAY/CONTROL)

Yes. FIM TASK 31-61-00-810-88G-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

27 ELEVATOR

FAULT

Make sure that the hydraulic systems are on. On the FLIGHT CONTROLS panel, push the ELEVATORS pushbutton. After 3 seconds, push it again.


27 ELEVATOR LH

FAIL

FAULT CONDITION: Hydraulic systems are OFF PROCEDURE: Pressurize No. 1, No. 2, and No. 3 hydraulic systems (AMM TASK 29-10-00-863-802-A/200). FAULT CONDITION: Hydraulic systems are ON PROCEDURE: On the FLIGHT CONTROLS panel, push the ELEVATORS pushbutton. After 3 seconds, push it again.

Yes. No maintenance action. No. Refer to the correspondent chapter of the FIM for troubleshooting. Yes. FIM TASK 27-03-00-810-90Y-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

27 ELEVATOR RH

FAIL

FAULT CONDITION: Hydraulic systems are OFF PROCEDURE: Pressurize No. 1, No. 2, and No. 3 hydraulic systems (AMM TASK 29-10-00-863-802-A/200). FAULT CONDITION: Hydraulic systems are ON PROCEDURE: On the FLIGHT CONTROLS panel, push the ELEVATORS pushbutton. After 3 seconds, push it again.

Yes. No maintenance action. No. Refer to the correspondent chapter of the FIM for troubleshooting. Yes. FIM TASK 27-03-00-810-92K-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

73 ENG 1 FADEC

FAULT

PROCEDURE: Open these circuit breakers and close them after 5 seconds to confirm that the failure has occurred: • FADEC 1A-LHCBP (DC ESS BUS 1 ENGINE) • FADEC 1B-RHCBP (DC ESS BUS 2 ENGINE)

Yes. FIM TASK 73-21-00-810-82C-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

73 ENG 1 FUEL

SW FAIL

FAULT CONDITION: If there is a CMC message correlated to the EICAS message. PROCEDURE: Make sure that all fuel pumps are off and the engines are not running. Do the steps that follow: NOTE: Do not perform this procedure during the refueling procedure. • On the FUEL panel, set the XFEED switch to the LOW1 position; • Open the access door of the refueling panel (616HB); • On the refueling panel, set the DEFUELING switch to the OPEN position; • Wait for 30 seconds; • On the refueling panel, set the DEFUELING switch to the CLOSED position; • Close the access door of refueling panel (616HB); • On the FUEL panel, set the XFEED switch to the OFF position; • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A). FAULT CONDITION: If there is NO CMC message correlated to the EICAS message. PROCEDURE: Do the steps that follow: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

73 ENG 2 FADEC

FAULT

PROCEDURE: Open these circuit breakers and close them after 5 seconds to confirm that the failure has occurred: • FADEC 2A-LHCBP (DC ESS BUS 1 ENGINE) • FADEC 2B-RHCBP (DC ESS BUS 2 ENGINE)


May 10

ATA MESSAGE /


REMOVED?

73 ENG 2 FUEL

SW FAIL

FAULT CONDITION: If there is a CMC message correlated to the EICAS message. PROCEDURE: Make sure that all fuel pumps are off and the engines are not running. Do the steps that follow: NOTE: Do not perform this procedure during the refueling procedure. • On the FUEL panel, set the XFEED switch to the LOW1 position; • Open the access door of the refueling panel (616HB) ; • On the refueling panel, set the DEFUELING switch to the OPEN position; • Wait for 30 seconds; • On the refueling panel, set the DEFUELING switch to the CLOSED position; • Close the access door of refueling panel (616HB); • On the FUEL panel, set the XFEED switch to the OFF position; • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A). FAULT CONDITION: If there is NO CMC message correlated to the EICAS message. PROCEDURE: Do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

22 ENG TLA TRIM

FAIL

FAULT CONDITION: The following maintenance messages are active on the CMC: 22310005TA1 - ENGINE DATA [TRSA1] FAULT 22310005TA2 - ENGINE DATA [TRSA2] FAULT 22310023TA1 - FADEC1/FADEC2 [ATA1] WRG FAULT 22310023TA2 - FADEC1/FADEC2 [ATA2] WRG FAULT 22310079TA1 - LEFT FADEC [ATA1] FAULT 22310079TA2 - LEFT FADEC [ATA2] FAULT 22310080TA1 - RIGHT FADEC [ATA1] FAULT 22310080TA2 - RIGHT FADEC [ATA2] FAULT NOTE: The recording of "RIGHT FADEC [ATxx] FAULT" or "LEFT FADEC [ATxx] FAULT" maintenance message on the CMC depends on the faulty FADEC. The left FADEC refers to engine 1 and the right FADEC refers to engine 2. EFF: [ALL] PROCEDURE: On the CMC, use the sequence that follows to get access to the ENGINE 1 GENERAL STATUS PAGE: • 73 - ENGINE FUEL AND CONTROL • 21 - ENGINE FADEC 1A • ENGINE 1 GENERAL STATUS PAGE If the CHANNEL IN CONTROL status is the same for both channels, go to the FIM TASK 22-31-00-810-821-A. On the CMC, use the sequence that follows to get access to the ENGINE 2 GENERAL STATUS PAGE: • 73 - ENGINE FUEL AND CONTROL • 21 - ENGINE FADEC 2A • ENGINE 2 GENERAL STATUS PAGE If the CHANNEL IN CONTROL status is the same for both channels, go to the FIM TASK 22-31-00-810-821-A.


May 10

ATA MESSAGE /


REMOVED?

31 FDR AFT FAIL

On the MCDU, use the sequence in parentheses to open these SSPCs and, after approximately 10 seconds, close them: • FDR ACCEL-SPDA2 (CBMENU/CB BY SYS/FDR/CVR) • DVDR 2-SPDA2 (CBMENU/CB BY SYS/FDR/CVR)


31 FDR FWD FAIL

On the MCDU, use the sequence in parentheses to open these SSPCs and, after approximately 10 seconds, close them: • FDR ACCEL-SPDA2 (CBMENU/CB BY SYS/FDR/CVR) • DVDR 1-SPDA1 (CBMENU/CB BY SYS/FDR/CVR)


May 10

ATA MESSAGE /


REMOVED?

27 FLAP FAIL

On the CMC, use the sequence that follows to do the SF-ACE CLEAR INHIBITS procedure for both flap channels: • 27 - FIGHT CONTROLS • 53 - FLAP ACTUATOR CNTL ELECTRONICS 1 • FLAPS-ACE1 CLEAR INHIBITS Afterwards, on the CMC, use the sequence that follows to do the FLAPS-ACE1 BIT (Built-in Test): • 27 - FLIGHT CONTROLS • 53 - FLAP ACTUATOR CNTL ELECTRONICS 1 • FLAPS-ACE1 BUILT IN TEST On the CMC, use the sequence that follows to do the FLAPS-ACE2 BIT (Built-in Test): • 27 - FLIGHT CONTROLS • 53 - FLAP ACTUATOR CNTL ELECTRONICS 2 • FLAPS-ACE2 BUILT IN TEST


May 10

ATA MESSAGE /


REMOVED?

27 FLAP LO

RATE

On the CBP, open these circuit breakers and, after approximately 5 seconds, close them: • FLAP ACE 1-LHCBP (DC ESS BUS 1 FLIGHT CONTROLS) • FLAP ACE 2-RHCBP (DC ESS BUS 3 FLIGHT CONTROLS) On the CMC, use the sequence that follows to do the SF-ACE CLEAR INHIBITS procedure for both flap channels: • 27 - FIGHT CONTROLS • 53 - FLAP ACTUATOR CNTL ELECTRONICS 1 • FLAPS-ACE1 CLEAR INHIBITS Afterwards, on the CMC, use the sequence that follows to do the FLAPS-ACE1 BIT (Built-in Test): • 27 - FLIGHT CONTROLS • 53 - FLAP ACTUATOR CNTL ELECTRONICS 1 • FLAPS-ACE1 BUILT IN TEST On the CMC, use the sequence that follows to do the FLAPS-ACE2 BIT (Built-in Test): • 27 - FLIGHT CONTROLS • 53 - FLAP ACTUATOR CNTL ELECTRONICS 2 • FLAPS-ACE2 BUILT IN TEST


May 10

ATA MESSAGE /


REMOVED?

27 FLT CTRL BIT

EXPIRED

Do the flight control electrical P-BIT (Power-up Built-in Test). To do this test, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200). NOTE: • The flight control electrical built-in test is complete three minutes after the AC power is connected to the aircraft. If you set the hydraulic pump to ON before that, the flight control electrical built-in test is canceled. • You must not move the flight control commands. If you move the flight control commands with the hydraulic pressure off, a CAS message will show. Pressurize No. 1, No. 2 and No. 3 hydraulic systems (AMM TASK 29-10-00-863-802-A/200) to do the flight control hydraulic P-BIT (Power-up Built-in Test). NOTE: • You must not move the flight control commands until the flight control actuators engages in the daily switch configuration. • Make sure that the rudder surface is not fully deflected to the LEFT position (due to wind action, for instance). If the fault is not removed, do the flight control electrical P-BIT (Power-up Built-in Test) again. To do this test, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200). NOTE: • The flight control electrical built-in test is complete three minutes after the AC power is connected to the aircraft. If you set the hydraulic pump to ON before that, the flight control electrical built-in test is canceled. • You must not move the flight control commands. If you move the flight control commands with the hydraulic pressure off, a CAS message will show.


May 10

ATA MESSAGE /


REMOVED?

27 FLT CTRL

FAULT

Make sure that the hydraulic systems are on. On the FLIGHT CONTROLS panel, push the ELEVATORS, RUDDER and SPOILERS pushbuttons. After 3 seconds, push them again. Do the P-BIT (Power-up Built-in Test). To do this test, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200). Do the return-to-service test of the flight control system (AMM TASK 27-00-00-070-801-A/200).

Yes. FIM TASK 27-03-00-810-91A-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

27 FLT CTRL NO

DISPATCH

FAULT CONDITION: During power-up PROCEDURE: On the maintenance panel, make sure the FCS MAINT switch is in the OFF position. Make sure that the hydraulic systems are on. On the FLIGHT CONTROLS panel, push the ELEVATORS, RUDDER, and SPOILERS pushbuttons. After 3 seconds, push them again. Do the P-BIT (Power-up Built-in Test). To do this test, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200). Do the return-to-service test of the flight control system (AMM TASK 27-00-00-070-801-A/200). FAULT CONDITION: After landing PROCEDURE: Make sure that the hydraulic systems are on. On the FLIGHT CONTROLS panel, push the ELEVATORS, RUDDER, and SPOILERS pushbuttons. After 3 seconds, push them again.


May 10

ATA MESSAGE /


REMOVED?

27

FLT CTRL NO DISPATCH/FLT

CTRL FAULT/FLT CTRL BIT EXPIRED,

AUTO CONFIG TRIM FAIL (Alternate

procedure)

FAULT CONDITION: During power-up PROCEDURE: On the maintenance panel, make sure the FCS MAINT switch is in the OFF position. Pressurize the No. 1, No. 2, and No. 3 hydraulic systems (AMM TASK 29-10-00-863-802-A/200). NOTE: • Wait 1 minute until the FCS PCUs engage in the daily switch configuration. • You must not move the flight control commands until the flight control PCUs engage in the daily switch configuration. • Make sure that the rudder surface is not fully deflected to the LEFT position (due to wind action, for instance). On the FLIGHT CONTROLS panel, push the ELEVATORS, RUDDER, and SPOILERS pushbuttons. After 3 seconds, push them again. Do the return-to-service test of the flight control system until you push the CLEAR RAM button (CMC Page 2) (AMM TASK 27-00-00-070-801-A/200). Set the FCS MAINT switch to the OFF position. Examine the message window on the EICAS display and make sure that there are no FLT CTRL NO DISPATCH/FLT CTRL FAULT/FLT CTRL BIT EXPIRED messages: 1) If there are none of these error messages, continue the return-to-service test of the flight control system (AMM TASK 27-00-00-070-801-A/200); 2) If there are any of these error messages, on the HYDRAULIC control panel, set the SYS 1, SYS 2 and SYS 3 - ELEC PUMP switches to OFF and do the P-BIT (Power-up Built-in Test). To do this test, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200). NOTE: • The flight control electrical built-in test is completed three minutes after the AC power is connected to the aircraft. If you set the hydraulic pump to ON before that, the flight control electrical built-in test is cancelled. • You must not move the flight control commands. If you move the flight control commands with the hydraulic pressure off, a CAS message will show.

Yes.. FIM TASK 27-00-00-810-801-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

34 FMS 1 FAIL

EFF: [ON ACFT WITH FMS2 AND ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC ESS BUS 2) EFF: [ON ACFT WITH FMS2 AND ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC ESS BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC BUS 2) EFF: ALL PROCEDURE: On the CMC, use the sequence that follows to do the reset test of the PROC module 3: • 31-INDICATING/RECORDING SYSTEMS • 41 - PROC MODULE 3 (MAU 2 SLOT NIC 1) • MAU2 PROC3 MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

34 FMS 2 FAIL

CAUTION: MAKE SURE THAT THE INTEGRATED PITOT/STATIC/AOA SENSORS, TAT SENSORS, ICE DETECTORS AND STATIC PORT HAVE NO COVERS ON THEM BEFORE YOU DO THE MAINTENANCE PROCEDURE. THESE COMPONENTS CAN BECOME HOT DURING THE MAINTENANCE PROCEDURE. AS A RESULT, DAMAGE TO THEM WILL OCCUR IF YOU DO NOT REMOVE THE COVERS. Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 3 PWR 1-RHCBP (DC ESS BUS 2) • MAU 3 PWR 2-RHCBP (DC BUS 2) On the CMC, use the sequence that follows to do the reset test of the PROC module 5: • 31-INDICATING/RECORDING SYSTEMS • 41 - PROC MODULE 5 (MAU 3 SLOT NIC 1) • MAU3 PROC5 MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

34

FMS1 TIMEOUT

Shows on the MCDU 1

Scratchpad

PROCEDURE: 1) On MCDU 1, push the CLR key as necessary until you clear the scratchpad; 2) On MCDU 1, push the MENU function key and then the applicable FMS function key; 3) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

34

FMS1-2 TIMEOUT

Shows on the MCDU 1

Scratchpad



May 10

ATA MESSAGE /


REMOVED?

34

FMS1-2 TIMEOUT

Shows on the MCDU 2

Scratchpad



May 10

ATA MESSAGE /


REMOVED?

34

FMS2 TIMEOUT

Shows on the MCDU 2

Scratchpad



May 10

ATA MESSAGE /


REMOVED?

28 FUEL DC

PUMP FAIL

On the FUEL overhead panel, set DC PUMP to ON. Wait 10 seconds and set it back to AUTO.


28 FUEL EQUAL-XFEED OPEN

Make sure that the XFEED switch is in the OFF position.


May 10

ATA MESSAGE /


REMOVED?

21 FWD EBAY FANS FAIL

EFF: [ON ACFT WITH SPDA BLOCK 6.1 (MICRO/COMM PN 1705540D)] FAULT CONDITION: Aircraft changes directly from Ground Service Mode to any other operating mode such as: • Ground Service to Batteries • Ground Service to GPU • Ground Service to APU Gen PROCEDURE: Reset the aircraft (power down/up). EFF: [LDI UP TO V02] PROCEDURE: On the CMC, use the sequence that follows to run the ebay fans BIT (Built-in Test): • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM A (B) • EBAY FAN INITIATED BIT CH A (B) EFF: [LDI FROM V03 TO LDI V05.1] PROCEDURE: On the CMC, use the sequence that follows to run the ebay fans BIT (Built-in Test): • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM A (B) • AVIONICS COMPARTMENT FANS IBIT CH A (B) EFF: [LDI V06 AND ON] PROCEDURE: On the CMC, use the sequence that follows to run the ebay fans BIT (Built-in Test): • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM A (B) • AVIONICS COMPARTMENT FANS IBIT CH 1 (2)


May 10

ATA MESSAGE /


REMOVED?

34 GND PROX

FAIL

EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC ESS BUS 2) EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC ESS BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC BUS 2) EFF: ALL PROCEDURE: On the CMC, use the sequence that follows to do the self-test of the EGPWM module: • 34 - NAVIGATION • 41 - ENHANCED GROUND PROXIMITY WARN SYS • EGPWM SELF TEST


May 10

ATA MESSAGE /


REMOVED?

27

GROUND SPOILERS

FAIL

Do the return-to-service test of the flight control system (AMM TASK 27-00-00-070-801-A/200).


34 HUD 1 FAIL

EFF: [ON ACFT WITH DUAL HEAD-UP GUIDANCE SYSTEM] Open these circuit breakers and, after a minimum of 60 seconds, close them: • COMPUTER - RHCBP - DC BUS 2/HUD 1 • OVHD UNIT - RHCBP - DC BUS 2/HUD 1


May 10

ATA MESSAGE /


REMOVED?

34 HUD 2 FAIL

EFF: [ON ACFT WITH DUAL HEAD-UP GUIDANCE SYSTEM] Open these circuit breakers and, after a minimum of 60 seconds, close them: • COMPUTER - LHCBP - DC BUS 1/HUD 2 • OVHD UNIT - LHCBP - DC BUS 1/HUD 2


May 10

ATA MESSAGE /


REMOVED?

34 HUD FAIL

EFF: [ON ACFT WITH SINGLE HEAD-UP GUIDANCE SYSTEM] Open these circuit breakers and, after a minimum of 60 seconds, close them: • COMPUTER - RHCBP - DC BUS 2/HUD • OVHD UNIT - RHCBP - DC BUS 2/HUD


May 10

ATA MESSAGE /


REMOVED?

30

ICE DETECTOR 1

FAIL

EFF: 170 - [ON EMBRAER 170 ACFT WITH PRIMUS EPIC LOAD 17.1 AND ON] OR [POST-MOD 170-31-0010/01] 190 - [ON EMBRAER 190 ACFT WITH PRIMUS EPIC LOAD 4.2 AND ON] PROCEDURE: WARNING: DO NOT OPERATE THE ENGINE OR PRESSURIZE THE BLEED AIR SYSTEM. THE BLEED AIR WILL FLOW OUT OF THE BLEED AIR LINE AND CAUSE INJURIES TO PERSONS. WARNING: DO NOT TOUCH THE INTEGRATED PITOT/STATIC AOA SENSOR, TAT SEN-SOR, STATIC PORT AND ICE DETECTORS IMMEDIATELY AFTER THE HEATER WAS SET TO OFF TO PREVENT INJURY TO PERSONS. On the overhead panel: • On the ICE PROTECTION control panel, turn the TEST switch to the WING or ENG position. • Hold the TEST switch at WING or ENG positions for 3 seconds. • Wait for 60 seconds and check if the message does not show on the CAS again.


May 10

ATA MESSAGE /


REMOVED?

30

ICE DETECTOR 2

FAIL

EFF: 170 - [ON EMBRAER 170 ACFT WITH PRIMUS EPIC LOAD 17.1 AND ON] OR [POST-MOD 170-31-0010/01] 190 - [ON EMBRAER 190 ACFT WITH PRIMUS EPIC LOAD 4.2 AND ON] PROCEDURE: WARNING: DO NOT OPERATE THE ENGINE OR PRESSURIZE THE BLEED AIR SYSTEM. THE BLEED AIR WILL FLOW OUT OF THE BLEED AIR LINE AND CAUSE INJURIES TO PERSONS. WARNING: DO NOT TOUCH THE INTEGRATED PITOT/STATIC AOA SENSOR, TAT SEN-SOR, STATIC PORT AND ICE DETECTORS IMMEDIATELY AFTER THE HEATER WAS SET TO OFF TO PREVENT INJURY TO PERSONS. On the overhead panel: • On the ICE PROTECTION control panel, turn the TEST switch to the WING or ENG position. • Hold the TEST switch at WING or ENG positions for 3 seconds. • Wait for 60 seconds and check if the message does not show on the CAS again.


May 10

ATA MESSAGE /


REMOVED?

23

INPH audio (Between

DAPs) - Noisy or not

Available



24 INVERTER

FAIL

To reset the inverter, do as follows: • On the MCDU, push the CB key. Then, push the MAINT key to enter the MAINT screen. • On the MAINT screen, push the related key to select the INV RESET. Then, push the key related to INV RESET. • After the message IN PROGRESS appears, if the reset is confirmed, the message INV RESET shows on the MCDU display. If the reset is not confirmed, the message INV NOT RESET shows on the MCDU display. • After the reset, push the key related to INV RESET. Then, push the key related to MAINT.


May 10

ATA MESSAGE /


REMOVED?

34 IRS 1 FAIL

Open these circuit breakers and, after approximately 5 seconds, close them: • IRS 1 PWR 1-LHCBP (DC ESS BUS 1 NAV) • IRS 1 PWR 2-RHCBP (DC ESS BUS 2 NAV)


34 IRS 2 FAIL

Open these circuit breakers and, after approximately 5 seconds, close them: • IRS 2 PWR 1-RHCBP (DC BUS 2 NAV) • IRS 2 PWR 2-LHCBP (DC BUS 1 NAV)


May 10

ATA MESSAGE /


REMOVED?

34 IRS PRES POS

INVALID

On the MCDU, do the steps that follow to get access to the POS SENSORS page: • Push the NAV function key to show the NAV INDEX page 1/2. • Push the LSK (NAV IDENT) to show the NAV IDENT page. • Push the LSK (POS INIT) to show the POSITION INIT page. • Push the LSK (POS SENSORS) to show the POS SENSORS page. If the GPS 1/2 is not available on the POS SENSORS page of the MCDU, put the aircraft out of the hangar or in a place where the GPS signal is available. Note: "IRS PRES POS INVALID" CAS message comes into view if the GPS signal is not available.


May 10

ATA MESSAGE /


REMOVED?

26 LAV SMOKE

FAULT CONDITION: CMC indicates a failure in the forward lavatory smoke detector during the test PROCEDURE: On the CMC, use the sequence that follows to do the generic I/O 1 module reset test: • 31-INDICATING/RECORDING SYSTEMS • 41 - GENERIC I/O (DUAL) MODULE 1A • MAU1 GIO1A MODULE RESET TEST FAULT CONDITION: CMC indicates a failure in the aft lavatory smoke detector during the test PROCEDURE: On the CMC, use the sequence that follows to do the generic I/O 1 module reset test: • 31-INDICATING/RECORDING SYSTEMS • 41 - GENERIC I/O (DUAL) MODULE 1B • MAU1 GIO1B MODULE RESET TEST On the CMC, use the sequence that follows to do the generic I/O 3 module reset test: • 31-INDICATING/RECORDING SYSTEMS • 41 - GENERIC I/O (DUAL) MODULE 3A • MAU3 GIO1B MODULE RESET TEST

Yes. FIM TASK 26-14-00-02-810-801-A No. Go to the correspondent chapter of the FIM for troubleshooting. Yes. FIM TASK 26-14-00-02-810-802-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

26 LAV SMOKE

DET FAIL

FAULT CONDITION: CMC indicates a failure in the forward lavatory smoke detector PROCEDURE: On the CMC, use the sequence that follows to do the generic I/O 1 module reset test: • 31-INDICATING/RECORDING SYSTEMS • 41 - GENERIC I/O (DUAL) MODULE 1A • MAU1 GIO1A MODULE RESET TEST FAULT CONDITION: CMC indicates a failure in the aft lavatory smoke detector PROCEDURE: On the CMC, use the sequence that follows to do the generic I/O 1 module reset test: • 31-INDICATING/RECORDING SYSTEMS • 41 - GENERIC I/O (DUAL) MODULE 1B • MAU1 GIO1B MODULE RESET TEST On the CMC, use the sequence that follows to do the generic I/O 3 module reset test: • 31-INDICATING/RECORDING SYSTEMS • 41 - GENERIC I/O (DUAL) MODULE 3A • MAU3 GIO1B MODULE RESET TEST

Yes. FIM TASK 26-14-00-02-810-801-A No. Go to the correspondent chapter of the FIM for troubleshooting. Yes. FIM TASK 26-14-00-02-810-802-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

32 LG NO

DISPATCH

FAULT CONDITION: During power-up PROCEDURE: Reset MAU 1 PWR 1-LHCBP (DC ESS BUS 1). • If it does not clear the message, reset MAU 3 PWR 1. • If it does not clear the message, reset the aircraft power.


32 LG NOSE

DOOR OPEN



May 10

ATA MESSAGE /


REMOVED?

32 LG WOW SYS

FAIL



31 MFD 1 FAULT Open this circuit breaker and, after approximately 5 seconds, close it: • MFD 1-RHCBP (DC ESS BUS 2 DISPLAY/CONTROL)

Yes. FIM TASK 31-61-00-810-88E-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

31 MFD 2 FAULT Open this circuit breaker and, after approximately 5 seconds, close it: • MFD 2-LHCBP (DC BUS 1 DISPLAY/CONTROL)

Yes. FIM TASK 31-61-00-810-88F-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

34 NAVCOM 1

FAIL

Open this circuit breaker and, after approximately 5 seconds, close it: • MRC 1-LHCBP (DC ESS BUS 1 COMM)


May 10

ATA MESSAGE /


REMOVED?

34 NAVCOM 2

FAIL

On the MCDU, use the sequence in parentheses to open the SSPC below. After a minimum of 10 seconds, close it: • MRC 2-SPDA2 (CBMENU/CB BY SYS/NAV)


28

NO LEFT FUEL QTY

INDICATION ON EICAS

Open this circuit breaker and, after approximately 5 seconds, close it: • FUEL QTY 1 - LHCBP - DC ESS BUS 1 .


May 10

ATA MESSAGE /


REMOVED?

28

NO RIGHT FUEL QTY

INDICATION ON EICAS

Open this circuit breaker and, after approximately 5 seconds, close it: • FUEL QTY 2 - RHCBP - DC ESS BUS 2


28

NO TOTAL FUEL QTY

INDICATION ON EICAS

Open these circuit breakers and, after approximately 5 seconds, close them: • FUEL QTY 1 - LHCBP - DC ESS BUS 1 • FUEL QTY 2 - RHCBP - DC ESS BUS 2


23

Observer DAP Problems -

Display, Volume and

Controls

PROCEDURE: Open this circuit breaker and, after approximately 5 seconds, close it: • COMM AUDIO 3-LHCBP (DC BUS 1)


May 10

ATA MESSAGE /


REMOVED?

21 PACK 1 FAIL

FAULT CONDITION: PACK 1 FAIL and PACK 2 FAIL CAS messages come into view simultaneously with the aircraft on the ground, without any correlated maintenance message PROCEDURE: On the CMC, check if there is any active message and do the correspondent troubleshooting. If there is no active messages, do as follows: • On the overhead panel, on the AIR COND/PNEUMATIC control panel, set the PACK 1 pushbutton to the unlatched (off) position. Then, set it back to the latched (auto) position.


21 PACK 2 FAIL

FAULT CONDITION: PACK 1 FAIL and PACK 2 FAIL CAS messages come into view simultaneously with the aircraft on the ground, without any correlated maintenance message PROCEDURE: On the CMC, check if there is any active message and do the correspondent troubleshooting. If there is no active messages, do as follows: • On the overhead panel, on the AIR COND/PNEUMATIC control panel, set the PACK 2 pushbutton to the unlatched (off) position. Then, set it back to the latched (auto) position.


May 10

ATA MESSAGE /


REMOVED?

31 PFD 1 FAULT Open this circuit breaker and, after approximately 5 seconds, close it: • PFD 1-LHCBP (DC BUS 1 DISPLAY/CONTROL)


31 PFD 2 FAULT Open this circuit breaker and, after approximately 5 seconds, close it: • DISPLAY PFD 2-RHCBP (DC BUS 2)

Yes. FIM TASK 31-61-00-810-88D-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

23

Pilot DAP Problems -

Display, Volume and

Controls

PROCEDURE: Open this circuit breaker and, after approximately 5 seconds, close it: • AUDIO 1-LHCBP (DC ESS BUS 1 COMM)


27 PITCH TRIM

BKUP FL

• On the TRIM control panel, push the SYS 1 CUTOUT and SYS 2 CUTOUT pushbuttons to the OFF position at the same time. • On the TRIM control panel, push the SYS 1 CUTOUT and SYS 2 CUTOUT pushbuttons to the ON position at the same time. • Do the return-to-service test of the flight control system (AMM TASK 27-00-00-070-801-A/200). • Push and hold the BACKUP PITCH TRIM switch to the nose-up position for 3 to 5 seconds. Make sure that the leading edge of the horizontal stabilizer moves down a short distance and then stops, and that the PITCH trim indication on the EICAS moves up. • Push and hold the BACKUP PITCH TRIM switch to the nose-down position for 3 to 5 seconds. Make sure that the leading edge of the horizontal stabilizer moves up a short distance and then stops, and that the PITCH trim indication on the EICAS moves down.


May 10

ATA MESSAGE /


REMOVED?

27 PITCH TRIM

FAIL

• On the TRIM control panel, push the SYS 1 CUTOUT and SYS 2 CUTOUT pushbuttons to the OFF position at the same time. • On the TRIM control panel, push the SYS 1 CUTOUT and SYS 2 CUTOUT pushbuttons to the ON position at the same time. • If the fault is not removed, do the return-to-service test of the flight control system (AMM TASK 27-00-00-070-801-A/200). • Push and hold the BACKUP PITCH TRIM switch to the nose-up position for 3 to 5 seconds. Make sure that the leading edge of the horizontal stabilizer moves down a short distance and then stops, and that the PITCH trim indication on the EICAS moves up. • Push and hold the BACKUP PITCH TRIM switch to the nose-down position for 3 to 5 seconds. Make sure that the leading edge of the horizontal stabilizer moves up a short distance and then stops, and that the PITCH trim indication on the EICAS moves down.


May 10

ATA MESSAGE /


REMOVED?

27 PITCH TRIM SW 1 FAIL

• On the TRIM control panel, push the SYS 1 CUTOUT and SYS 2 CUTOUT pushbuttons to the OFF position at the same time. • On the TRIM control panel, push the SYS 1 CUTOUT and SYS 2 CUTOUT pushbuttons to the ON position at the same time. • Do the return-to-service test of the flight control system (AMM TASK 27-00-00-070-801-A/200). • Push and hold the pilot control-yoke pitch-trim switch to the nose-up position for 3 to 5 seconds. Make sure that the leading edge of the horizontal stabilizer moves down a short distance and then stops, and that the PITCH trim indication on the EICAS moves up. • Push and hold the pilot control-yoke pitch-trim switch to the nose-down position for 3 to 5 seconds. Make sure that the leading edge of the horizontal stabilizer moves up a short distance and then stops, and that the PITCH trim indication on the EICAS moves down.


May 10

ATA MESSAGE /


REMOVED?

27 PITCH TRIM SW 2 FAIL

• On the TRIM control panel, push the SYS 1 CUTOUT and SYS 2 CUTOUT pushbuttons to the OFF position at the same time. • On the TRIM control panel, push the SYS 1 CUTOUT and SYS 2 CUTOUT pushbuttons to the ON position at the same time. • Do the return-to-service test of the flight control system (AMM TASK 27-00-00-070-801-A/200). • Push and hold the copilot control-yoke pitch-trim switch to the nose-up position for 3 to 5 seconds. Make sure that the leading edge of the horizontal stabilizer moves down a short distance and then stops, and that the PITCH trim indication on the EICAS moves up. • Push and hold the copilot control-yoke pitch-trim switch to the nose-down position for 3 to 5 seconds. Make sure that the leading edge of the horizontal stabilizer moves up a short distance and then stops, and that the PITCH trim indication on the EICAS moves down.


May 10

ATA MESSAGE /


REMOVED?

38

POTABLE WATER OR

WASTE SYSTEM

INOPERATIVE.

During servicing, draining or when the passenger use the lavatory or the flight attendant use the galleys. PROCEDURE: Reset the WWSC. Open these circuit breakers and, after approximately 5 seconds, close them: • WATER WASTE CTRL1 - LICC - DC GND SVC BUS • WATER WASTE CTRL2 - LICC - DC BUS 1 • WATERWASTE CTRL3 - AICC - HOT BATT BUS 3

Yes. FIM TASK 38-00-00-810-801A. No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

21 PRESN AUTO

FAIL

On the overhead panel, on the PRESSURIZATION control panel, turn the MODE switch from the AUTO to the MAN position. Wait 5 seconds and turn it back to the AUTO position. Note: As an alternative procedure to reset this message, do as follows: Open these circuit breakers and, after a few seconds, close them: • PRESN CPCS CTRL 1A (RHCBP) • PRESN CPCS CTRL 1B (LHCBP) • PRESN CPCS CTRL 2A (LHCBP) • PRESN CPCS CTRL 2B (LHCBP)


May 10

ATA MESSAGE /


REMOVED?

21 PRESN AUTO

FAULT

On the overhead panel, on the PRESSURIZATION control panel, turn the MODE switch from the AUTO to the MAN position. Wait 5 seconds and turn it back to the AUTO position. Note: As an alternative procedure to reset this message, do as follows: Open these circuit breakers and, after a few seconds, close them: • PRESN CPCS CTRL 1A (RHCBP) • PRESN CPCS CTRL 1B (LHCBP) • PRESN CPCS CTRL 2A (LHCBP) • PRESN CPCS CTRL 2B (LHCBP).


May 10

ATA MESSAGE /


REMOVED?

21 PRESN MAN

FAIL

On the overhead panel, on the PRESSURIZATION control panel, turn the MODE switch from the AUTO to the MAN position. Wait 5 seconds and turn it back to the AUTO position. Note: As an alternative procedure to reset this message, do as follows: Open these circuit breakers and, after a few seconds, close them: • PRESN CPCS CTRL 1A (RHCBP) • PRESN CPCS CTRL 1B (LHCBP) • PRESN CPCS CTRL 2A (LHCBP) • PRESN CPCS CTRL 2B (LHCBP).


May 10

ATA MESSAGE /


REMOVED?

23

RADIOS TIMEOUT

Shows on the MCDU 1

Scratchpad

PROCEDURE: 1) On MCDU 1, push the CLR key until you clear the scratchpad; 2) On MCDU 1, push the MENU function key and then, the RADIO function key; 3) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


23

RADIOS TIMEOUT

Shows on the MCDU 2

Scratchpad

PROCEDURE: 1) On MCDU 2, push the CLR key until you clear the scratchpad; 2) On MCDU 2, push the MENU function key and then, the RADIO function key; 3) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

34 RALT 1 FAIL On the MCDU, use the sequence in parentheses to open this SSPC. After approximately 10 seconds, close it: • RALT 1-SPDA2 (CBMENU/CB BY SYS/NAV)


34 RALT 2 FAIL On the MCDU, use the sequence in parentheses to open this SSPC. After approximately 10 seconds, close it: • RALT 2-SPDA1 (CBMENU/CB BY SYS/NAV)


May 10

ATA MESSAGE /


REMOVED?

21 RAM AIR FAULT

On the MCDU, use the sequence in parentheses to open these SSPCs. After 10 seconds, close them: • RAM AIR VLV CLS-SPDA2 (CBMENU/CB BY SYS/ECS DIST) • RAM AIR VLV OPN-SPDA2 (CBMENU/CB BY SYS/ECS DIST EFF: [ON ACFT WITH SPDA BLOCK 9 AND AMS BLACK LABEL UP TO 4.0] FAULT CONDITION: Aircraft changes directly from Ground Service Mode to any other operating mode such as: • Ground Service to Batteries • Ground Service to GPU • Ground Service to APU Gen PROCEDURE: On the overhead panel, on the AIR COND/PNEUMATIC control panel, set the PACK 1 pushbutton to the unlatched (off) position. Wait 5 seconds and then set it back to the latched (auto) position.


May 10

ATA MESSAGE /


REMOVED?

24 RAT FAIL

FAULT CONDITION: The following maintenance messages are not active on the CMC: • 24230007EP1 • 24230010AI1 • 24230024EP1 • 24230025EP1 • 24230026EP1 • 24510011EP1 • 24610009SP1 • 24610016SP1 • 24610029EP1 • 24230023EP1 • 24510012EP1 • 24610006SP1 • 24510003EPM PROCEDURE: Do the power-down/up procedure to confirm that the failure has occurred. To do this, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200).


May 10

ATA MESSAGE /


REMOVED?

26 RECIRC SMK

DET FAIL

FAULT CONDITION: If there is a CMC message correlated to the EICAS message PROCEDURE: On the CMC, use the sequence that follows to do the initiated IBIT of the recirculation bay smoke detector: • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM A (1) • SMOKE DETECTOR IBIT CH A (1) And: • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM B (2) • SMOKE DETECTOR IBIT CH B (2)

Yes. FIM TASK 26-16-00-02-810-801-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

26 RECIRC SMOKE

FAULT CONDITION: 3 minutes after landing PROCEDURE: On the overhead panel, on the AIR COND/PNEUMATIC panel, latch and unlatch the RECIRC button. On the CMC, use the sequence that follows to do the initiated IBIT of the recirculation bay smoke detector: • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM A (1) • SMOKE DETECTOR IBIT CH A (1) And: • 21 - AIR CONDITIONING • 00 - ECS AND CREW O2 SYSTEM B (2) • SMOKE DETECTOR IBIT CH B (2) On the overhead panel, on the AIR COND/PNEUMATIC panel, latch and unlatch the RECIRC button.

Yes. FIM TASK 26-10-00-02-810-801-A No. Refer to the correspondent chapter of the FIM for troubleshooting.

May 10

ATA MESSAGE /


REMOVED?

34

REFUEL PG TIMEOUT

Shows on the MCDU 1

Scratchpad

PROCEDURE: 1) On MCDU 1, push the CLR key as necessary until you clear the scratchpad; 2) On MCDU 1, push the MENU function key; 3) On MCDU 1, push the LSK adjacent to MISC to get access to the MISC MENU page; 4) On MCDU 1, push the LSK adjacent to REFUEL; 5) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

34

REFUEL PG TIMEOUT

Shows on the MCDU 2

Scratchpad

PROCEDURE: 1) On MCDU 2, push the CLR key as necessary until you clear the scratchpad; 2) On MCDU 2, push the MENU function key; 3) On MCDU 2, push the LSK adjacent to MISC to get access to the MISC MENU page; 4) On MCDU 2, push the LSK adjacent to REFUEL; 5) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

24 REMOTE CB

TRIP

EFF: [ON ACFT WITH SPDA S/W BLOCK UP TO 10.2 OR PRE-MOD SB 170-24-0043] PROCEDURE: If the message is related to a system that was intentionally deactivated, do the thermal CB/SSPC status acknowledgement to clear the message on the MCDU (AMM TASK 24-60-00-910-801-A/200). If the REMOTE CB TRIP continues to show on the EICAS, it is necessary to do a power-down/ power-up of the aircraft as follows: NOTE: The thermal CB must stay open during the aircraft power down / power-up procedure. • De-energize the aircraft (AMM TASK 24-42-02-860-802-A/200). • After a minimum of 30 seconds, energize the aircraft (AMM TASK 24-42-02-860-801-A/200). • Do the thermal CB status acknowledgment to clear the message on the MCDU (AMM TASK 24-60-00-910-801-A/200). EFF: [ACFT WITH SPDA S/W BLOCK 11.1 AND ON, AND WITH CMC LDI V08 AND ON] PROCEDURE: If the message is related to a system that was intentionally deactivated, do the thermal CB/SSPC status acknowledgement to clear the message on the MCDU (AMM TASK 24-60-00-910-801-A/200).


May 10

ATA MESSAGE /


REMOVED?

27 RUDDER FAIL

FAULT CONDITION: Hydraulic systems OFF PROCEDURE: Pressurize No. 1, No. 2 and No. 3 hydraulic systems (AMM TASK 29-10-00-863-802-A/200).

Yes. No maintenance action. No. Refer to the correspondent chapter of the FIM for troubleshooting.

27 RUDDER FAULT

Make sure that the hydraulic systems are on. On the FLIGHT CONTROLS panel, push the RUDDER pushbutton. After 3 seconds, push it again.


May 10

ATA MESSAGE /


REMOVED?

34

SETUP PG TIMEOUT

Shows on the MCDU 1

Scratchpad

PROCEDURE: 1) On MCDU 1, push the CLR key as necessary until you clear the scratchpad; 2) On MCDU 1, push the MENU function key; 3) On MCDU 1, push the LSK adjacent to MISC to get access to the MISC MENU page; 4) On MCDU 1, push the LSK adjacent to SETUP; 5) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


34

SETUP PG TIMEOUT

Shows on the MCDU 2

Scratchpad

PROCEDURE: 1) On MCDU 2, push the CLR key as necessary until you clear the scratchpad; 2) On MCDU 2, push the MENU function key; 3) On MCDU 2, push the LSK adjacent to MISC to get access to the MISC MENU page; 4) On MCDU 2, push the LSK adjacent to SETUP; 5) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

27 SHAKER 1

FAIL

FAULT CONDITION: CMC maintenance message with A1 on its text PROCEDURE: On the CMC, use the sequence that follows to do the reset test of the AIOP 1A: • 31 - INDICATING/RECORDING SYSTEMS • 41 - ACTUATOR I/O MODULE 1A (MAU 1 SLOT 2) • MAU1 AIOPA1 MODULE RESET TEST FAULT CONDITION: CMC maintenance message with B1 on its text PROCEDURE: On the CMC, use the sequence that follows to do the reset test of the AIOP 1B: • 31 - INDICATING/RECORDING SYSTEMS • 41 - ACTUATOR I/O MODULE 1B (MAU 1 SLOT10) • MAU1 AIOPB1 MODULE RESET TEST FAULT CONDITION: CMC maintenance message with A2 on its text PROCEDURE: On the CMC, use the sequence that follows to do the reset test of the AIOP 2A: • 31 - INDICATING/RECORDING SYSTEMS • 41 - ACTUATOR I/O MODULE 2A (MAU 2 SLOT14) • MAU2 AIOPA2 MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

27 SHAKER 2

FAIL

FAULT CONDITION: CMC maintenance message with B1 on its text PROCEDURE: On the CMC, use the sequence that follows to do the reset test of the AIOP 1B: • 31 - INDICATING/RECORDING SYSTEMS • 41 - ACTUATOR I/O MODULE 1B (MAU 1 SLOT10) • MAU1 AIOPB1 MODULE RESET TEST FAULT CONDITION: CMC maintenance message with A2 on its text PROCEDURE: On the CMC, use the sequence that follows to do the reset test of the AIOP 2A: • 31 - INDICATING/RECORDING SYSTEMS • 41 - ACTUATOR I/O MODULE 2A (MAU 2 SLOT14) • MAU2 AIOPA2 MODULE RESET TEST FAULT CONDITION: CMC maintenance message with B2 on its text PROCEDURE: On the CMC, use the sequence that follows to do the reset test of the AIOP 2B: • 31 - INDICATING/RECORDING SYSTEMS • 41 - ACTUATOR I/O MODULE 2B (MAU 3 SLOT 6) • MAU3 AIOPB2 MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

27 SLAT FAIL

On the CMC, use the sequence that follows to do the SF-ACE CLEAR INHIBITS procedure for both slat channels: • 27 - FLIGHT CONTROLS • 83 - SLAT ACTUATOR CNTL ELECTRONICS 1 • SF-ACE1 SLATS CLEAR INHIBITS Afterwards, on the CMC, use the sequence that follows to do the SLATS-ACE1 SYSTEM TEST: • 27 - FLIGHT CONTROLS • 83 - SLAT ACTUATOR CNTL ELECTRONICS 1 • SLATS-ACE1 SYSTEM TEST On the CMC, use the sequence that follows to do the SLATS-ACE2 BUILT IN TEST: • 27 - FLIGHT CONTROLS • 83 - SLAT ACTUATOR CNTL ELECTRONICS 2 • SLATS-ACE2 BUILT IN TEST


May 10

ATA MESSAGE /


REMOVED?

27 SLAT LO

RATE

On the CBP, open these circuit breakers and, after approximately 5 seconds, close them: • SLAT ACE 1-LHCBP (DC BUS 1 FLIGHT CONTROLS) • SLAT ACE 2-RHCBP (DC ESS BUS 2 FLIGHT CONTROLS) On the CMC, use the sequence that follows to do the SF-ACE CLEAR INHIBITS procedure for both slat channels: • 27 - FLIGHT CONTROLS • 83 - SLAT ACTUATOR CNTL ELECTRONICS 1 • SF-ACE1 SLATS CLEAR INHIBITS Afterwards, on the CMC, use the sequence that follows to do the SLATS-ACE1 SYSTEM TEST: • 27 - FLIGHT CONTROLS • 83 - SLAT ACTUATOR CNTL ELECTRONICS 1 • SLATS-ACE1 SYSTEM TEST On the CMC, use the sequence that follows to do the SLATS-ACE2 BUILT IN TEST: • 27 - FLIGHT CONTROLS • 83 - SLAT ACTUATOR CNTL ELECTRONICS 2 • SLATS-ACE2 BUILT IN TEST


May 10

ATA MESSAGE /


REMOVED?

27 SLAT-FLAP

LEVER DISAG

On the control pedestal, set the SFCL to the 0 (UP) position. Move the SFCL to the 1 position and wait until the surfaces reach the final position. • Move the SFCL to the 2 position and wait until the surfaces reach the final position. • Move the SFCL to the 3 position and wait until the surfaces reach the final position. • Move the SFCL to the 4 position and wait until the surfaces reach the final position. • Move the SFCL to the 5 position and wait until the surfaces reach the final position. • Move the SFCL to the FULL position and wait until the surfaces reach the final position. • Move the SFCL to the 0 (UP) position and wait until the surfaces reach the final position.


24 SPDA FAIL

FAULT CONDITION: The SPDA FAIL CAS message was displayed during flight and the CMC maintenance message is related to the SPDA MICRO/COMMS module(s) (Fault Codes: 24610004SP2, 24610016SP2, 24610004SP1 and/or 24610017SP1) PROCEDURE: Do the power-down/up procedure to reset the SPDAs. To do this, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200).


May 10

ATA MESSAGE /


REMOVED?

27 SPDBRK

LEVER DISAG Make sure that the speed brake lever and the surfaces are in the closed position.


27 SPOILER

FAULT

Make sure that the hydraulic systems are on. On the FLIGHT CONTROLS panel, push the SPOILERS pushbutton. After 3 seconds, push it again.


32 STEER FAIL PROCEDURE: Open this circuit breaker and, after 5 seconds, close it: • MAU 2 PWR 1-RHCBP (DC BUS 2)


May 10

ATA MESSAGE /


REMOVED?

32 STEER FAULT PROCEDURE: Open this circuit breaker and, after 5 seconds, close it: • MAU 2 PWR 1-RHCBP (DC BUS 2)


34 TAT 1 FAIL Open this circuit breaker and, after approximately 5 seconds, close it: • ADS 1 PROBE 1A-2A-LHCBP (DC BUS 1 NAV)


34 TAT 2 FAIL Open this circuit breaker and, after approximately 5 seconds, close it: • ADS 2 PROBE 4A-RHCBP (DC BUS 2 NAV)


May 10

ATA MESSAGE /


REMOVED?

34 TCAS FAIL On the MCDU, use the sequence in parentheses to open this SSPC and, after a minimum of 10 seconds, close it: • TCAS-SPDA1 (CBMENU/CB BY SYS/NAV)


May 10

ATA MESSAGE /


REMOVED?

34 TERRAIN FAIL

EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC ESS BUS 2) EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC ESS BUS 2] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC ESS BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC BUS 2) EFF: ALL PROCEDURE: On the CMC, use the sequence that follows to do the self-test of the EGPWM module: • 34 - NAVIGATION • 41 - ENHANCED GROUND PROXIMITY WARN SYS • EGPWM SELF TEST


May 10

ATA MESSAGE /


REMOVED?

34 TERRAIN NOT AVAILABLE

EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC BUS 2)] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC ESS BUS 2) EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC ESS BUS 2)] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC ESS BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC BUS 2) EFF: ALL PROCEDURE: On the CMC, use the sequence that follows to do the self-test of the EGPWM module: • 34 - NAVIGATION • 41 - ENHANCED GROUND PROXIMITY WARN SYS • EGPWM SELF TEST


May 10

ATA MESSAGE /


REMOVED?

34

TEST PG TIMEOUT

Shows on the MCDU 1

Scratchpad

PROCEDURE: 1) On MCDU 1, push the CLR key as necessary until you clear the scratchpad; 2) On MCDU 1, push the MENU function key; 3) On MCDU 1, push the LSK adjacent to MISC to get access to the MISC MENU page; 4) On MCDU 1, push the LSK adjacent to TEST; 5) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


34

TEST PG TIMEOUT

Shows on the MCDU 2

Scratchpad

PROCEDURE: 1) On MCDU 2, push the CLR key as necessary until you clear the scratchpad; 2) On MCDU 2, push the MENU function key; 3) On MCDU 2, push the LSK adjacent to MISC to get access to the MISC MENU page; 4) On MCDU 2, push the LSK adjacent to TEST; 5) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A).


May 10

ATA MESSAGE /


REMOVED?

76

THRUST MGT TIMEOUT

shows on the MCDU 1

scratchpad

PROCEDURE: 1) On MCDU 1, push the CLR key as necessary until you clear the scratchpad; 2) On MCDU 1, push the MENU function key and then, the TRS function key; 3) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A)


May 10

ATA MESSAGE /


REMOVED?

76

THRUST MGT TIMEOUT

shows on the MCDU 2

scratchpad

PROCEDURE: 1) On MCDU 2, push the CLR key as necessary until you clear the scratchpad; 2) On MCDU 2, push the MENU function key and then, the TRS function key; 3) If the message persists, do the steps that follows: • De-energize the aircraft (AMM TASK 24-42-02-860-802-A); • Energize the aircraft (AMM TASK 24-42-02-860-801-A)


May 10

ATA MESSAGE /


REMOVED?

24 TRU 1 FAIL Cycle the TRU1 toggle switch from AUTO to OFF. Then, return it to AUTO again.


24 TRU 2 FAIL Cycle the TRU2 toggle switch from AUTO to OFF. Then, return it to AUTO again.


May 10

ATA MESSAGE /


REMOVED?

24 TRU ESS FAIL Cycle the TRU ESS toggle switch from AUTO to OFF. Then, return it to AUTO again.


23

Uncommanded chime

generation - All Positions



May 10

ATA MESSAGE /


REMOVED?

23

Uncommanded HF COMM

Transmission - All Positions

EFF: ON ACFT WITH HF COMM PROCEDURE: On the CMC, use the sequence that follows to do the MRC 1 NIM reset test (AMM TASK 45-45-00-970-805-A/200): • 34 - NAVIGATION • 02 - MODULAR RADIO CABINET 1 - NIC • MRC1 NIM [NIC] MODULE RESET TEST


23

Uncommanded VHF COMM 1


PROCEDURE: On the CMC, use the sequence that follows to do the MRC 1 NIM reset test (AMM TASK 45-45-00-970-805-A/200): • 34 - NAVIGATION • 02 - MODULAR RADIO CABINET 1 - NIC • MRC1 NIM [NIC] MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

23



PROCEDURE: On the CMC, use the sequence that follows to do the MRC 2 NIM reset test (AMM TASK 45-45-00-970-805-A/200): • 34 - NAVIGATION • 02 - MODULAR RADIO CABINET 2 - NIC • MRC2 NIM [NIC] MODULE RESET TEST


23



EFF: ON ACFT WITH VHF-3 COMM PROCEDURE: On the CMC, use the sequence that follows to do the MRC 2 NIM reset test (AMM TASK 45-45-00-970-805-A/200): • 34 - NAVIGATION • 02 - MODULAR RADIO CABINET 2 - NIC • MRC2 NIM [NIC] MODULE RESET TEST


May 10

ATA MESSAGE /


REMOVED?

38

Water System FAULT

Indication on Aft Flight Attendant

Panel

PROCEDURE: In the middle avionics compartment, open these circuit breakers and, after approximately 10 seconds, close them: •WATER WASTE CTRL1-LICC (DC GND SVC BUS) •WATER WASTE CTRL2-LICC (DC BUS 1) In the aft avionics compartment, open this circuit breaker and, after approximately 10 seconds, close it: •WATERWASTE CTRL3-AICC (HOT BATT BUS 2) On the CBP, make sure that these circuit breakers are closed: • MAU 3 PWR 1-RHCBP (DC ESS BUS 2) • MAU 3 PWR 2-RHCBP (DC BUS 2)


May 10

ATA MESSAGE /


REMOVED?

34 WINDSHEAR

FAIL

EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC BUS 2)] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC ESS BUS 2) EFF: [ON ACFT WITH ’MAU2 PWR2 PRI’ CIRCUIT BREAKER ON DC ESS BUS 2)] PROCEDURE: Open these circuit breakers and, after approximately 5 seconds, close them: • MAU 2 PWR 1-RHCBP (DC BUS 2) • MAU 2 PWR 2 PRI-RHCBP (DC ESS BUS 2) • MAU 2 PWR 2 SEC-RHCBP (DC BUS 2) EFF: ALL PROCEDURE: On the CMC, use the sequence that follows to do the self-test of the EGPWM module: • 34 - NAVIGATION • 41 - ENHANCED GROUND PROXIMITY WARN SYS • EGPWM SELF TEST


May 10

ATA MESSAGE /


REMOVED?

30 WINDSHIELD 1

HTR FAIL

FAULT CONDITION: WINDSHIELD 1 HTR FAIL set at same time or not with WINDSHIELD 2 HTR FAIL, with no CMC correlation. PROCEDURE: • On the Ice/Rain overhead panel, unlatch (lights come on) the pushbuttons Windshield 1 and 2 and latch (lights go off) them again. After 120 seconds, check if the message goes out of view. • If the message does not go out of view do the power-down/up procedure to reset the SPDAs. To do this, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200).


30 WINDSHIELD 2

HTR FAIL

FAULT CONDITION: WINDSHIELD 1 HTR FAIL set at same time or not with WINDSHIELD 2 HTR FAIL, with no CMC correlation. PROCEDURE: • On the Ice/Rain overhead panel, unlatch (lights come on) the pushbuttons Windshield 1 and 2 and latch (lights go off) them again. After 120 seconds, check if the message goes out of view. • If the message does not go out of view do the power-down/up procedure to reset the SPDAs. To do this, you must de-energize the aircraft (AMM TASK 24-42-02-860-802-A/200) and energize it again (AMM TASK 24-42-02-860-801-A/200).


May 10

ATA MESSAGE /


REMOVED?

34

WX FAIL MESSAGE ON

THE MFD

On the MCDU (AMM SDS 34-61-00/1), use the sequence in parentheses to open this SSPC and, after a minimum of 10 seconds, close it: • WX RADAR-SPDA1 (CBMENU/CB BY SYS/NAV)


May 10

ATA MESSAGE /


REMOVED?

34 XPDR 1 FAIL On the MCDU, use the sequence in parentheses to open this SSPC. After a minimum of 10 seconds, close it: • TRANSPONDER 1-SPDA1 (CBMENU/CB BY SYS/NAV)


34 XPDR 2 FAIL On the MCDU, use the sequence in parentheses to open this SSPC. After a minimum of 10 seconds, close it: • TRANSPONDER 2-SPDA2 (CBMENU/CB BY SYS/NAV)


E190 Reset Guide

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