Maintenance Tips Load 19.3
Short Description
Descripción: Maint. tips EPIC...
Description
MAINTENANCE TIPS
EMBRAER 170 / 190
PRIMUS EPIC LOAD 19.3
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
EMBRAER 170 / 190
FOR TRAINING PURPOSES ONLY IT DOES NOT SUPERSEDE EMBRAER OFFICIAL DOCUMENTATION
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
PURPOSE EMBRAER 170 / 190
The purpose of this pocket book is to show some maintenance tips those could help on the day-by-day maintenance procedures.
All the procedures shown herein are available on the Embraer’s Official Technical Publications
Always refer to the latest version of AMM (Aircraft Maintenance Manual) and the FIM (Fault Isolation Manual) for detailed procedures and explanations.
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
MAU FAIL / FAULT MESSAGES EMBRAER 170 / 190
DESCRIPTION: The MAUs are cabinets those contains 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 that backplane.
AIRCRAFT COMMUNICATION BUS
I/O MODULE
POWER SUPPLY
NETWORK INTERFACE CONTROLLER
PROCESSOR
BACKPLANE B (BOTTOM) MAU CHANNEL ( EXAMPLE )
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
MAU FAIL / FAULT MESSAGES (CONT.) EMBRAER 170 / 190
Whenever messages like these comes on in the EICAS display : , it means that all functions in the associated channel have failed. Usually there is a lot of EICAS messages being displayed simultaneously with this message. ,it means the associated MAU channel suffered a failure condition that does not affect its functionality, but could cause a loss of redundancy. Independently of the message, it’s important to follow the instructions contained in the Aircraft Maintenance Manual (AMM), the Fault Isolation Manual (FIM) and the CMC.
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
BLEED LEAK – POINT OF LEAKAGE EMBRAER 170 / 190
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 and inner wall of the loops are filled with salt. If the temperature rises above the alarm temperature, the circuit develops a short.
SENSING ELEMENT SECTION
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
BLEED LEAK – POINT OF LEAKAGE EMBRAER 170 / 190
For bleed leakage troubleshooting refer to FIM TASKS 36-21-00810-XXX and 36-22-00810-XXX for Embraer 170/175, and FIM TASKS 36-21-00-990XXX and 36-22-00-990XXX for Embraer 190/195.
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
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
BLEED LEAK – POINT OF LEAKAGE EMBRAER 170 / 190
On the CMC OVERHEAT DETECTION PARAMETERS screen, look at BLEED 1, BLEED 2 or APU OVERHEAT LOCATION VALUES to identify the bleed leakage point. Record the values and check the Table for access panel and XYZ coordinates of the leakage spot. (see 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 reference the 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. The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
FAULT INDICATIONS – FLIGHT ATTENDANT PANEL EMBRAER 170 / 190
DESCRIPTION: This section covers the functions of the faul indication lights on the AFT flight attendant panel.
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
FAULT INDICATIONS – FLIGHT ATTENDANT PANEL EMBRAER 170 / 190
Indicates a failure on the waste system. Refer to FIM TASK 38-00-00-810-804-A
Indicates waste tank 100% full. Both toilets are disabled until tank is serviced. Refer to FIM TASK 38-00-00-810-805-A
Indicates waste tank at 75%. Both toilets operate normally. Refer to FIM TASK 38-00-00-810-806-A
Indicates a failure on the water system. Refer to FIM TASK 38-00-00-810-807-A
Indicates a failure on the lavatories. Refer to FIM TASK 38-32-00-810-801-A and 38-32-00-810-802
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
FAULT INDICATIONS – FLIGHT ATTENDANT PANEL EMBRAER 170 / 190
For WASTE SYSTEM FAULT a failure of one of the WWSC components may occur. See table below: FIM TASK
CMC
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 2.3 – Defective Harness 3 – The WWSC is not available for system operation (38000218WWSC) 3.1 – Failure of WWSC 3.2 – Transitory condition of the WWSC 3.3 – Defective Harness The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
FAULT INDICATIONS – FLIGHT ATTENDANT PANEL EMBRAER 170 / 190
For WASTE SYSTEM FAULT a failure of one of the WWSC components may occur. See table below: FIM TASK
CMC
1 - The WWSC senses that the fill/drain valve is not in the position (open/closed) set in the fill/drain switch after 5s (38100227WWS) 1.1 – Failure of the FILL/DRAIN VALVE 1.2 – Defective HARNESS 1.3 – 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
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
FAULT INDICATIONS – FLIGHT ATTENDANT PANEL EMBRAER 170 / 190
3 – Failure of the FWD 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. (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 Embraer’s official documentation. For complete T/S procedures always refer to the Fault Isolation Manual (FIM) and the Aircraft Maintenance Manual (AMM)
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
CABIN TEMPERATURE - DIFFICULTIES TO CONTROL EMBRAER 170 / 190
DESCRIPTION: The cabin temperature control in Embraer 170/190 aircrafts is achieved by two Pack Bypass Valves, located on the LH and RH ECS (Environmental Control System) bays. The pack bypass valve is a pneumatically actuated butterfly valve controlled by a torque motor mounted on the valve body. This valve mixes the hot air directly from the pack flow control valve outlet with cold air coming from the second stage of turbine of the ACM (Air Cycle Machine). P T
hot air
Pressure-actuated torque motor symbol
ACM shaft
To ECS system
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
CABIN TEMPERATURE – DIFFICULTIES TO CONTROL EMBRAER 170 / 190
The pack bypass valve torque motor has a continuous air flow on its air inlet port. This inlet port has 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 cabin temperature) 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.
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
PAX AND SERVICE DOOR EICAS INDICATION EMBRAER 170 / 190
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 5274-20-05. 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
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
Pax & Serv Door Eicas Indication EMBRAER 170 / 190
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.
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
PAX AND SERV DOOR EICAS INDICATION EMBRAER 170 / 190
CAUTION: PAY ATTENTION FOR DIFFERENCES ON THE ADJUSTMENT VALUE (“W”) AND OTHER ASSEMBLIES FOR PAX AND SERVICE DOORS.
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
DESCRIPTION: Technicians are facing problems to build up a fail code according to the code data provided from the synoptic page of the engines displayed 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).
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.
NOTE: TO PERFORM THE APPLICABLE T/S ALWAYS REFER TO THE FIM - FAULT ISOLATION MANUAL AND EMM - ENG MANUFACTURE MANUAL
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
If or EICAS messages are displayed on the EICAS perform the follow procedure: 1) Go to CMC MAIN MENU pages on MFD 2 and click on the MAINTENANCE MESSAGES:
GO TO MAINTENANCE MESSAGES
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 190MAINTENANCE 2) 170 On / the
MESSAGES pages you can start performance the T/S clicking on Historical By Date or Actives option.
GO TO ACTIVE or HISTORICAL BY DATE
IF CAS MESSAGE IS NOT AVAILABLE WHEN “ENG OUT” - PERFORM T/S USING
HISTORICAL BY DATE
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER / 190on 3) 170 Clicking
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
Correlated maintenance message
EICAS message
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
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 the FIM (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, once you click on this task number, automatically the associated FIM TASK will be displayed
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
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
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
8) Find in the table the correlated Maintenance Message Code, the same code showed in the CMC Maintenance Message and 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.
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
1) When an engine related EICAS message was reported by the pilots and the EICAS message disappears when the engines 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 The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
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.
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
3) Click over the warning, caution or advisory to view the CAS MSG and correlated Maintenance MESSAGE.
See example of a CMC page below
Correlated maintenance message
EICAS message
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
4) Click over the correlated Maintenance MSG to enter in the Maintenance Message Detailed page.
FDE NAME: The title of the FDE, the same title as CAS message
FAULT CODE: The code of the fault. To troubleshoot using the FIM (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, once you click on this task number, automatically the associated FIM TASK will be displayed
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
5) Go to the respective chapter in the Fault Isolation Manual enter in the Maintenance Message Index and find the appropriate FIM TASK. 6) Perform troubleshooting task
Maintenance Fault Code
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190
In case of CMC FAIL you can use the ENG MAINTENANCE DATA to find out the fail code.
It is recommended an engine run-up procedure before accessing this page (engine-related CAS messages are only displayed when engines are running) 1) In the menu of the MFD click over engine synoptic page to access the ENGINE MAINTENANCE DATA.
CAS message field
This field shows 4-number fail codes. These codes are necessary to find the maintenance procedures on the Fault Isolation Manual (FIM) The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 190 2) 170 Use / this
table on the FIM, in the appropriate ATA chapter, to find the applicable maintenance procedure.
All FADEC code initials refers to the chapter and sub-chapter These codes are the same of the Engine Maintenance Data page.
E = Engine 1 or 2 = eng 1 or 2 A or B = FADEC Channel Fault code to be used on the FIM
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
ENG 1 (2) NO DISPATCH AND ENG 1 (2) SHORT DISPATCH EMBRAER 170 / 190 3) Perform troubleshooting
task according FIM.
Maintenance message fault code, with 11 characters
In some cases the FIM Task will refer to the ENGINE MAINTENANCE MANUAL The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
AILERON PCU FORCE FIGHT - ADJUSTMENT / TEST EMBRAER 170 / 190
Aileron control is accomplished by means of a dual conventional cable system, using dual hydromechanical 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, torque tubes, and quadrants.
Ailerons PCUs location
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
AILERON PCU FORCE FIGHT - ADJUSTMENT / TEST EMBRAER 170 / 190
FOR THE COMPLETE PROCEDURE REFER TO AMM PART II TASK 27-12-01-820-821-A
1) Make sure that the aileron control cables are correctly tensioned, rigged, and adjusted before you do this task. 2) Pressurize Hydraulic Sys No. 2 and No. 3 3) On the CMC go to the AILERON STATUS PAGE
To NEUTRAL position the max value is ∆P = 400 To DEFLECTED position the max value is ∆P = 600
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
AILERON PCU FORCE FIGHT ADJUSTMENT / TEST EMBRAER 170 / 190 4) Record the
delta pressure values of the LH INBD, LH OUTBD, RH INBD and RH OUTBD ailerons PCUs in the neutral position Ex: Ex:
-300 -250
5) With the recorded values, calculate the PCU pressure difference in the neutral position for the LH aileron
- 50 Less than 400 psi: WITHIN the limits
For instance consider: A = - 300 psi B = - 250 psi
Formula ( A – B )
∆P = -300 - (-250)
First of all dissolve the parentheses. Consider the rule for equation: ∆P Same signals = adds (+) Diferente signals = subtraction (-)
= -300 + 250
∆P = -50 psi
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
AILERON PCU FORCE FIGHT ADJUSTMENT / TEST Another example, but now with different values:
EMBRAER 170 / 190
With the recorded values, calculate the PCU pressure difference in the neutral position for the RH aileron
EX:
+150
EX:
- 800
950 More than 400 psi: OUT of the limits
For instance consider: C = + 150 psi D = - 800 psi
Formula ( C – D )
∆P = +150 - (-800)
First of all dissolve the parentheses. ∆P Consider the rule for equation: Same signals = adds (+) Diferente signals = subtraction (-) ∆P
= +150 + 800 = 950 psi
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
AILERON PCU FORCE FIGHT ADJUSTMENT / TEST EMBRAER 170 / 190
If the ailerons differential pressure values are within the limits (less than 400 psi in neutral position and less than 600 psi in deflected position) there’s no need to adjust the force fight. If values are out the limits perform the procedure for aileron PCU force fight adjustment, according to AMM MPP TASK 27-12-01-820-821-A
NOTE 1: Use the lowest possible value to adjust 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 POSITION is the same, but it’s important to remember that the maximum ∆P values are different.
The information contained herein is the property of Embraer S.A.
Issue: May, 2007
and shall not be copied or used any manner, except with Embraer’s written consent.
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