maintenance tips load 19.3

8/10/2019 Maintenance Tips Load 19.3

1/38and shall not be copied or used any manner, except with Embraers written consent.

EMBRAER 170 / 190

Issue: May, 20The information contained herein is the property of Embraer S.A.

MAINTENANCE TIPS

PRIMUS EPIC LOAD 19.3



EMBRAER 170 / 190


FOR TRAINING PURPOSES ONLY

IT DOES NOT SUPERSEDE EMBRAER

OFFICIAL DOCUMENTATION


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MAU FAIL / FAULT MESSAGES

DESCRIPTION: The MAUs are cabinets thosecontains the main modules of the avionics systems.All 3 MAUs have 2 channels: A and B, for supplying

/ retrieving data and power supply to the modules.

An MAU channel consists of one power module, one

NIC/PROC module, one MAU data communications

backplane and various modules connected to thatbackplane.

AIRCRAFT COMMUNICATION BUS

PROCESSOR

NETWORK

INTERFACE

CONTROLLER

POWER

SUPPLY

I/OMODULE

MAU CHANNEL ( EXAMPLE )

BACKPLANE B (BOTTOM)



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MAU FAIL / FAULT MESSAGES (CONT.)

Whenever messages like these comes on in th

EICAS display :

- , it mean

that all functions in the associated channel hav

failed. Usually there is a lot of EICAS message

being displayed simultaneously with this message.

- ,it mean

the associated MAU channel suffered a failu

condition that does not affect its functionality, b

could cause a loss of redundancy.

Independently of the message, its important to follo

the instructions contained in the Aircraft Maintenanc

Manual (AMM), the Fault Isolation Manual (FIM) an

the CMC.



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BLEED LEAK POINT OF LEAKAGE

DESCRIPTION: The bleed leak loops used on the

Embraer 170/190 are resistive type.

A sensing element consists in a continuous

coaxial assembly filled with an euthetic salt.

The thin wall sensor loops include outer and

inner conductive materials which are independent

electrical circuits. The area between the outer andinner wall of the loops are filled with salt. If the

temperature rises above the alarm temperature, the

circuit develops a short.

SENSING ELEMENT SECTION



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For bleed leakage

troubleshooting refer to

FIM TASKS 36-21-00-

810-XXX and 36-22-00-

810-XXX for Embraer

170/175, and FIM

TASKS 36-21-00-990-

XXX and 36-22-00-990-

XXX for Embraer190/195.

FIM TASK

For Bleed leakage

location table of

Engine lines:

- FIM Task Support

36-21-00/301

For Bleed leakage

location table of

APU lines:

- FIM TASK Support

36-22-00/301



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On the CMC OVERHEAT DETECTION

PARAMETERS screen, look at BLEED 1, BLEED or APU OVERHEAT LOCATION VALUES t

identify the bleed leakage point.

Record the values and check the Table for acces

panel and XYZ coordinates of the leakage spot. (se

example below)

Leakage values to be compared with the

values read in the CMC

To find out the leakage spots, in case of different

values recorded from the CMC, take as referencethe closest value printed at the Table and remove

the respective access panel.

NOTE: The CMC may not refer precisely to

the values as shown on the table.


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ForWASTE SYSTEM FAULT a failure of one of

the WWSC components may occur. See tablebelow:

CMC FIM TASK

1 Overheat condition in the vacuum generator

(38300326WWSC)

1.1 Failure of vacuum generator

1.2 Defective Harness

2 Continuous operation of the vacuum generator after activated(38300322WWSC)

2.1 Failure of the VWS MOTOR STARTING RELAY

2.2 Failure of the WWSC


3 The WWSC is not available for system operation

(38000218WWSC)

3.1 Failure of WWSC

3.2 Transitory condition of the WWSC


FAULT INDICATIONS FLIGHT ATTENDANT PANEL



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CMC FIM TASK

1 - The WWSC senses that the fill/drain valve is not in the positio

(open/closed) set in the fill/drain switch after 5s (38100227WWS)

1.1 Failure of the FILL/DRAIN VALVE

1.2 Defective HARNESS1.3 Failure of the WWSC

2 The WWSC senses that the FWD drain valve is not in the

position (open/closed) set in the fill/drain switch after 5s

(38100226WWS)

2.1 Failure of the FORWARD DRAIN VALVE

2.1 Defective HARNESS

2.3 Failure of the WWSC

ForWASTE SYSTEM FAULT a failure of one of

the WWSC components may occur. See tablebelow:




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3 Failure of the FWD drain mast sensed by the WWSC. This

failure occurs if the signal from the temp sensor in the drainmast does not agree with expected value. (38000221WWS)

3.1 - Failure of the FWD drain mast

3.2 - Defective HARNESS

4 Failure of the AFT drain mast sensed by the WWSC. This

failure occurs if the signal from the temp sensor in the drain

mast does not agree with expected value (38000220WWS)

4.1 Failure of the AFT drain mast

4.2 Defective HARNESS

NOTE: This is a quick guide that makes

reference to the Embraers official

documentation. For complete T/S procedures

always refer to the Fault Isolation Manual (FIM)

and the Aircraft Maintenance Manual (AMM)



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The pack bypass valve torque motor has a

continuous air flow on its air inlet port. This inlet porhas a filter that could get clogged by dust or other

contaminants. Due to this continuous air flow the

filter gets clogged faster than the other filters.

One of the steps of the troubleshooting

shown on the FIM TASK 21-60-00-810-801-A

(Problems to control cockpit and cabintemperature) is cleaning the Pack Bypass Valve

filter (refer to AMM TASK 21-51-10-100-801-A)

Using the AIR BLAST METHOD

NOTE: MAKE SURE OF SAFE CONDITIONS

FOR PROCEDURES AND WEAR PROTECTIVE

EQIPMENTS. SET THE PRESSURE TO 25 PSIG

OR LESS TO CLEAN THE FILTER OTHERWISE

DAMAGE TO THE COMPONENTS MAY OCCUR

CABIN TEMPERATURE DIFFICULTIES TO CONTROL



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DESCRIPTION: See the procedure below for PAX

& SERV DOORS EICAS message displayed

For Service Doors Warning Sensor

Adjustment always refer to AMM ll 52-74-20-05 and 52-

74-20-05.

For Pax Door Warning Sensor Adjustment

always refer to AMM II 52-72-20-05 and 52-72-21-05

NOTE: For Adjustment Values always

refer to the respective AMM II

PAX AND SERVICE DOOR EICAS INDICATION



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Pax & Serv Door Eicas Indication

MAKE SURE THE EMERGENCY EVACUATION-SLIDE PIN AND THE

EMERGENCY OPENING SYSTEM PIN ARE INSTALLED BEFORE

YOU START THIS PROCEDURE.

- Open the CB according to the respective task.

- For sensor access see procedure at AMM

- Start the adjustment procedure according AMM task.

CAUTION: PAY ATTENTION FOR

DIFFERENCES ON THE ADJUSTMENT VALUE(Y) AND OTHER ASSEMBLIES FOR PAX AND

SERVICE DOORS.



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PAX AND SERV DOOR EICAS INDICATION

CAUTION: PAY ATTENTION FOR DIFFERENCES

ON THE ADJUSTMENT VALUE (W) AND OTHER

ASSEMBLIES FOR PAX AND SERVICE DOORS.



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DESCRIPTION: Technicians are facing problems tobuild up a fail code according to the code dataprovided from the synoptic page of the enginesdisplayed at the MFD.

For Eng no Dispatch or Eng short Dispatch message on

the EICAS field refers to the FAULT REPORTING

INDEX in the FAULT REPORTING MANUAL (FIM).

NOTE: TO PERFORM THE APPLICABLE T/S ALWAYS

REFER TO THE FIM - FAULT ISOLATION MANUAL AND

EMM - ENG MANUFACTURE MANUAL

OBS: THERE ARE FOUR KINDS OF FAULT CODE (see below)

1) CAS MSG FAULT CODE 8 CHARACTERS 720 001 51

2) OBSERVED FAULT CODES 8 CHARACTERS 720 501 48

3) CABIN MESSAGE FAULT CODE 8 CHARACTERS G03 36 000

4) MAINTENANCE FAULT CODE 11 CHARACTERS 73211541E1A

In this T/S only CAS MSG FAULT CODE and

MAINTENANCE FAULT CODE will be used.

ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH



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If or

EICAS messages are displayed on the EICASperform the follow procedure:

1) Go to CMC MAIN MENU pages on MFD 2 andclick on the MAINTENANCE MESSAGES:


GO TO

MAINTENANCE

MESSAGES



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2) On the MAINTENANCE MESSAGES pages you canstart performance the T/S clicking on Historical By Date or

Actives option.

IF CAS MESSAGE IS NOT AVAILABLE

WHEN ENG OUT - PERFORM T/S USING

HISTORICAL BY DATE


GO TO ACTIVE

or

HISTORICAL BYDATE



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EICAS message

Correlated maintenance message

3) Clicking on ACTIVE option. A page with WARNING,

CAUTION and ADVISORY CAS MSG will be displayed. So

them select the correlated CAS message and click on it.


See example of a CMC page below



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4) The CMC will display the FDE (Flight Deck Effect) DETAIL

page and MAINTENANCE FAULT CODE for correlated CAS

MSG.


FDE NAME: The title of the FDE

the same title as CAS message

FAULT CODE: The code of the

fault. To troubleshoot using theFIM (Fault Isolation Manual),

you will need this number

POSSIBLE LRU(S) AT

FAULT: Displays the

possible LRUs at fault, the

most probable cause first

SYMPTOM: What is the

aircraft behavior face to this

message

DOCUMENTS: Displays the

applicable FIM TASK. When

you are using a notebook PC

with the Digital Technical Data

provided by Embraer, onceyou click on this task number,

automatically the associated

FIM TASK will be displayed



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5) Record the CAS message and the Maintenance Fault

Code, so them refers to the Fault Isolation Manual.

6) Open the Fault Isolation Manual in the Fault Reporting

Section

7) On the CAS Message List find the CAS Message

displayed at the EICAS Field, click on the correlated CAS

Message Fault Code in blue color.

CAS MSG Fault

Code with 8

characters




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8) Find in the table the correlated Maintenance Message Code,

the same code showed in the CMC Maintenance Messageand click on the correlated FIM Task.

9) Performance the task to solve the failure.

MAINTENANCE

MSG Fault Code

with 11

characters

In some cases the FIM Task will guide you to the ENG

MAINTENANCE MANUAL.




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1) When an engine related EICAS message was reported by

the pilots and the EICAS message disappears when theengines are off, choose HISTORICAL BY DATE, to retrieve

data related to a message when occurred on a determined

date.

Using Historical By Date all the CAS MSG

not latched are displayed




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2) Choose the date of the occurrence and click on it.

Choose the date of the occurrence and click over Year,

Month, Day and Leg step by step.




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3) Click over the warning, caution or advisory to view theCAS MSG and correlated Maintenance MESSAGE.

See example of a CMC page below


EICAS message

Correlated maintenance message



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FDE NAME: The title of the FDE

the same title as CAS message

FAULT CODE: The code of the

fault. To troubleshoot using theFIM (Fault Isolation Manual),

you will need this number

POSSIBLE LRU(S) AT

FAULT: Displays the

possible LRUs at fault, the

most probable cause first

SYMPTOM: What is the

aircraft behavior face to this

message

DOCUMENTS: Displays the

applicable FIM TASK. When

you are using a notebook PC

with the Digital Technical Data

provided by Embraer, onceyou click on this task number,

automatically the associated

FIM TASK will be displayed

4) Click over the correlated Maintenance MSG to enter in theMaintenance Message Detailed page.



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5) Go to the respective chapter in the Fault Isolation Manua

enter in the Maintenance Message Index and find the

appropriate FIM TASK.

6) Perform troubleshooting task

Maintenance Fault Code



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2) Use this table on the FIM, in the appropriate ATAchapter, to find the applicable maintenance procedure.

All FADEC code

initials refers to

the chapter and

sub-chapter

These codes are the

same of the EngineMaintenance Data page.

Fault code

to be used

on the FIM

E = Engine

1 or 2 = eng 1 or 2

A or B = FADEC Channel




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In some cases the FIM Task will refer to the

ENGINE MAINTENANCE MANUAL

Maintenance message fault

code, with 11 characters

3) Perform troubleshooting task according FIM.




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AILERON PCU FORCE FIGHT - ADJUSTMENT / TEST

Aileron control is accomplished by means of a dual

conventional cable system, using dual hydro-

mechanical actuators for each aileron surface.

Commands are provided through the control-yokes,

and are transferred to the actuators mechanically by

means of the cables, the aft mounted

interconnect/force override mechanism, torquetubes, and quadrants.

AileronsPCUs

location


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5) With the recorded values, calculate the PCU pressure

difference in the neutral position for the LH aileron

4) Record the delta pressure values of the LH INBD, LH OUTBD

RH INBD and RH OUTBD ailerons PCUs in the neutral position

Ex: -300

For instance consider:

A = - 300 psi Formula ( A B )B = - 250 psi P = -300 - (-250)

P = -300 + 250

P = -50 psi

First of all dissolve the parentheses.Consider the rule for equation:

Same signals = adds (+)

Diferente signals = subtraction (-)

- 50

Less than 400 psi:

WITHIN the limits

AILERON PCU FORCE FIGHT ADJUSTMENT / TEST

Ex: -250



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AILERON PCU FORCE FIGHT ADJUSTMENT / TESTAnother example, but now with different values:

With the recorded values, calculate the PCU pressure difference

in the neutral position for the RH aileron

950

EX: +150

EX: - 800

For instance consider:

C = + 150 psi Formula ( C D )D = - 800 psi P = +150 - (-800)

P = +150 + 800

P = 950 psi

First of all dissolve the parentheses.

Consider the rule for equation:

Same signals = adds (+)

Diferente signals = subtraction (-)

More than 400 psi:

OUT of the limits


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If the ailerons differential pressure values arewithin the limits (less than 400 psi in neutral

position and less than 600 psi in deflected

position) theres no need to adjust the force fight

If values are out the limits perform the procedurefor aileron PCU force fight adjustment, according

to AMM MPP TASK 27-12-01-820-821-A

AILERON PCU FORCE FIGHT ADJUSTMENT / TEST

NOTE 1: Use the lowest possible value toadjust the Aileron PCU Force Fight to have

the smaller differential pressure at the PCUs.

NOTE 2: the way to calculate the P for

NEUTRAL POSITION and DEFLECT POSITIONis the same, but its important to remember

that the maximum P values are different.

maintenance tips load 19.3

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