Operator E-jets News Rel 08

Issue N# 00 - Month 2006

Issue No. 08 – July2007

Issue No. 08 July 2007

Page 1

From the Editor

E-JETS NEWS is a publication that presents EMBRAER 170/190 aircraft technical items. This newsletter, compiled by EMBRAER Fleet Technical Center (EFTC), brings the latest developments and shares in-service knowledge and maintenance best practices. It also provides troubleshooting tips to optimize aircraft utilization and efficiency in daily operation.

E-JETS NEWS addresses Operator’s concerns with maintenance support and dispatchability of EMBRAER 170/190 aircraft. It has relevant information to be shared with the technical departments, such as Engineering and Maintenance. Recipients are encouraged to distribute this newsletter to EMBRAER Customers.

Earlier editions of E-JETS NEWS publication can be found at CIS / Aerochain at

http://www.aerochain.com

- Login (enter username and password);

- Select “Technical Services” and then “EMBRAER Customer Services”;

- Select “Maintenance Support”;

- Select “E-JETS NEWS;

- Click on desired E-JETS NEWS.

If any additional information regarding the in-service items covered in the E-JETS NEWS is needed, please contact the local EMBRAER Field Service Representative. General questions or comments about the E-JETS NEWS publication can be addressed to:

E-JETS NEWS

Tel: +55 12 3927 5762

Fax: +55 12 3927 5996

E-mail: [email protected]

PROPRIETARY NOTICE

The articles published in E-JETS NEWS are for information only and are an EMBRAER S/A property. This newsletter must not be reproduced or distributed in whole or in part to a third party without EMBRAER’s written consent. Also, no article published should be considered authority-approved data, unless specifically stated.


Page 2

CF34-8E Combustor Liner – Update

Effectivity: EMBRAER 170

EMBRAER was informed about engine removals due to cracks in the combustor liner (refer to E-Jets NEWS Release No. 6 and 7). After a borescope inspection, damage exceeding limits described on EMM (Subtask 72-00-00-220-065 (Page 843) – For the inspection limits, refer to Table 803) was found. HPT stage 1 nozzle missing material was also found.

Testing on the removed engine indicated acceptable operability margin. In HPC, significant deposits were observed along leading edges of all blades and vanes from stage 4 and up, not silt-like, as found in the hot section. This is related to operation in sandy environments. Some components and materials are still under investigation and EMBRAER is following up this issue with GE. The final findings and recommendations will soon be properly communicated.

Non-Latched Engine Short Dispatch Messages during Engine Start – Update


An update from the article published in the E-Jets NEWS Release No. 06 and during the GE Customer Support Operators Telecon held on April 17

th,

which EMBRAER highlighted about Engine Short Dispatch nuisance and non-latched messages due to LPT CMD - POSITION DISAGREE (Fail Code 73215321) during Engine Start.

As described during the EOC 2007 presentation in June/2007, as interim solution the engine manual troubleshooting will state that LPT CMD Disagree faults during engine start with FADEC 10Ev5.20 software or lower may be ignored. The next FADEC software version 10Ev5.30 is expected to be available by Dec/2007 and will solve the nuisance fault during start.

In the meantime, EMBRAER would like to highlight that any Engine Short Dispatch message latched after flight and caused due to LPT CMD - POSITION DISAGREE fault will require an LPTACC Valve replacement.

RAT Bearing Issue

Effectivity: EMBRAER 170 / 190

EMBRAER released SNL 170-24-0023 and 190-24-0017 to provide information about the RAT bearing issue, the root cause and also the action that must be taken with respect to the affected part number/ serial number range.

The Brazilian Certification Authority (ANAC) issued an AD and the proposed time for accomplishment is 26 months or 6.000 flight hours after the effective date of the AD, whichever occurs first.

A retrofit campaign has been planned, taking into account the rotables available and the Operator’s fleet size. This activity is being coordinated by the Fleet Performance Team.

Instructions regarding the technical accomplishment can be found in SB170-24-0041 and 190-24-0012.

MCDU "Timeout" scratchpad messages


Some MCDU "timeout" scratchpad messages were introduced on EPIC LOAD 4.5/17.5 to identify an application that became unresponsive.

RADIO TIMEOUT is one of those messages that have been lately reported by the Operators.

SNLs 170-34-0015 and 190-34-0014 contain further information with all expected "timeout" messages and the procedure to be followed in order to recover the required application.


Page 3

FGCS Channels Engagement Verification will no longer be necessary with Epic Load 19.3


Operators who incorporated Primus EPIC Load 19.3 (SB170-31-0019 and 190-31-0009R01) in their fleet will no longer be required to comply with SB 170-22-0003 and 190-22-002 FGCS (Flight Guidance and Control System) Channels Engagement Verification, according to AD 2006-11-02 and 2006-11-03, as soon as these ADs are revised.

EMBRAER has recently sent a fax to the Authorities Department addressing this issue. The fax is about a proposal to include in the AD an option to install Load 19.3 in lieu of the repetitive verification on FGCS.

EMBRAER is waiting a response for this request about this issue and, as soon as it is received, operators will be advised accordingly.

Air Cycle Machine Investigation


EMBRAER and Hamilton Sundstrand are conducting an investigation to fully understand the cause for premature Air Cycle Machine failure in the EMBRAER 170 / 190 fleet.

As part of this investigation, EMBRAER developed an Aircraft Condition Monitoring Function (ACMF) specifically to improve the ability to acquire aircraft level information. EMBRAER is requesting the Operator's help to install this application and to provide the download whenever possible.

In case of ACM failure, it is very important that all available data (DFDR, FHDB, ACMF and Pilot Report) be sent to EMBRAER representatives and also that the recommendations outlined in the SNL 170-21-0021 and 190-21-0014 be followed.

CMC messages erroneously correlated with BLEED 2 OVERPRESS CAS message


EMBRAER has identified that LDI V05 and V05.1 erroneously introduced the following Maintenance Messages correlation to the BLEED 2 OVERPRESS CAS message:

•LH HPSOV [C1]/WRG FAULT

•LH HPSOV [C2]/WRG FAULT

•LH NACELLE PRSOV (OPEN) [C1]/WRG

•LH NACELLE PRSOV (OPEN) [C2]/WRG

•LH BLD PRESS SNSR [C1]/WRG FAULT

•LH BLD PRESS SNSR [C2]/WRG FAULT

•LH BLD PRESS SNSR (DRIFT) [C1]/WRG

•LH BLD PRESS SNSR (DRIFT) [C2]/WRG

In case the above messages are active in the CMC, they will be correlated to the CAS message whenever a BLEED 2 OVERPRESS event occurs. The BLEED 2 OVERPRESS CAS message should be troubleshot according to FIM Task 36-14-00-810-809-A.

The solution is available through SB 190-31-0009 Primus EPIC Field-loadable Software System Load 19.3 upload (CMC LDI Database V06) released in May 2007.


Page 4

ACMP 2B AUTO MODE TEST


On the CMC System Diagnostic Page, it was identified that, the Auto Mode Test of the ACMP 2B on the Hydraulic Power Control 1, has a wrong link. It means that, when the ACMP 2B AUTO MODE TEST is selected, the link will open the page ACMP 1B AUTO MODE TEST. Thus, the ACMP 2B can not be tested by the CMC AUTO MODE TEST.

The correction for the EMBRAER 170 will be available in the next LDI version. Meanwhile, EMBRAER recommends for the EMBRAER 170 to perform the AMM Task 29-11-02-710-801-A - No. 1 and No. 2 Hydraulic System Alternating-Current-Motor Driven Pump - Operational Test and AMM Task 29-11-02-720-801-A - No. 1 and No. 2 Hydraulic System Alternating-Current-Motor Driven Pump - Functional Test, when the ACMP 2B test is required.

SNL 170-29-006 will be issued to cover this subject.

Concerning the EMBRAER 190, the link of the ACMP 2B AUTO MODE is correct.

New SPDA Block 10.1 improves APU starting performance


SPDA Block 9.2 presents a condition where a logic lock prevents the APU start contactors to supply energy for APU starting. This logic lock can be identified by the fault code 24610021EP2 - BUS ON (APU START NOT COMMANDED), that drives the fault code 49425518APU - APU FAIL TO CRANK (ASC) which will be triggered for all subsequent APU start attempts. The applicable maintenance action for this issue is performing an aircraft reset.

The last SPDA Block 10.1 software update, released in January 2007, addresses this issue and brings a significant improvement in APU starting.

For more information about SPDA upgrade, please refer to EMBRAER Service Bulletin 170-24-0038 for E170/175 and 190-24-0009 for E190/195.

Additional APU start logic improvements will be incorporated in SPDA Block 11 expected for November 2007.


Page 5

APU ESC Mod K released


A new modification was incorporated to APU Electronic Starter Controller (ESC) (PN 4505005B AIPC 49-42-01) in June 2007. According to Hamilton Sundstrand Power Systems, the new ESC Mod K adds sealant to leak paths in order to help prevent liquid contamination of internal circuitry.

All production units after SN 420 and repair units manufactured since June 2007 are Mod K. Operators should contact Hamilton Sundstrand Power Systems for ordering new Mod K units.

CAS messages during data loading process


EMBRAER has received a report of NAVCOM2 FAIL CAS message being displayed when the DATA LOADER button is selected on the CMC main page.

After pressing that button, the data loading process is started with a system configuration check which compares the existing hardware with the optional one. This comparison is made by the reading of MLF enclosed on the APMs (a non-volatile memory).

There are four APMs: APM1, APM2, APM3 and APM4. Their contents are accessed by their corresponding timing NICs: NIC2, NIC5, NIM1 and NIM2, respectively.

As far the design is concerned, the first APM to be consulted is the APM4 and, because of it, NAVCOM2 FAIL (also with APM FAULT and AURAL WARNING SYS FAULT) is displayed on the EICAS, as NIM2 is put on download mode to read the APM contents.

Even if an effective data loading is not performed, this start event will require a complete PD/PU (which is a required procedure after a software loading task).

HS-ACE – Pitch Trim indication


According to the Horizontal Stabilizer Control System architecture, EICAS (Caution) message FLT CTRL NO DISPATCH should be displayed in case of any HS-ACE channel failure.

The possibility of having one HS-ACE channel failed without the FLT CTRL NO DISPATCH message on the EICAS and with pitch trim position indication being shown by two amber dashes (“- -“) was detected;

With the pitch trim position dashed, the flight crew will have the maintenance action for this report as described in MMEL 27-41-01 (Pitch Trim Position Indication on EICAS), (M) Maintenance and (O) Operational procedures, which must be performed to verify the Horizontal Stabilizer Control System with pitch trim position indication inoperative on the EICAS.

Primus EPIC Load 21 will map the new HS-ACE No-Response Fault Monitor (FR15 Bit25) in ASCB displaying EICAS (Caution) message FLT CTRL NO DISPATCH in case of the on HS-ACE channel fail. However, as an interim solution, performing FIM TASK 27-40-00-810-802-A is recommended.

An SNL and an FOL will be issued to address this report.


Page 6

Strip Lights


Some operators have observed that the photoluminescent strip lights may have the end caps detached during operation, which could increase the dust penetration into the sleeve.

Figure 1 – Strip Lights location

Figure 2 – Strip Lights

It was also observed that on long strip lights (the ones which have two photoluminescent inserts inside one sleeve) overlapping may occur between these two inserts due to the sliding movement generated by the usual aircraft movement and vibration.



In view of the scenarios outlined above, SNLs 170-33-0015 and 190-33-0021 were issued to inform about the proper way to attach the end caps back to the sleeve and rework the inserts of the longer strip lights.

Static Inverter - New Supplier


EMBRAER has recently certified another supplier for the Static Inverter to be used on EMBRAER 170/175/190/195.

The new available part number SPC-10(Y) is two-way interchangeable with the current one in use.

The next AIPC revision will contain such information. Meanwhile, PIL 170-24-0030/ 190-24-0035 allows the Operators to install this new Static Inverter.


Page 7

Acronyms

ACM = Air Cycle Machine

ACMF = Aircraft Condition Monitoring Function

ACMP = Alternating-Current Motor-Driven Pump

AD = Airworthiness Directive

AIPC = Aircraft Illustrated Parts Catalog

AMM = Aircraft Maintenance Manual

ANAC = Agência Nacional de Aviação Civil (Brazilian Civil Aviation Authority)

AOM = Airplane Operations Manual

APM - Aircraft Personality Module

APU = Auxiliary Power Unit

CAS = Crew Alerting System

CMC = Central Maintenance Computer

CMM = Component Maintenance Manual

DLS = Data Load System

DVDR = Digital Voice-Data Recorder

EMM = Engine Maintenance Manual

EOC = EMBRAER Operators Conference

ESC = Electronic Starter Controller

FADEC = Full-Authority Digital Engine-Control

FGCS = Flight Guidance and Control System

FHDB = Fault History Database

FIM = Fault Isolation Manual

FOL = Flight Operations Letter

HPC = High Pressure Compressor

HPSOV = High Pressure Shutoff Valve

HPT = High Pressure Turbine

LDI = Loadable Diagnostic Information

LH = Left-Hand

LPT = Low Pressure Turbine

MCDU = Multifunction Control Display Unit

MLF - Master Loading File

MMEL = Master Minimum Equipment List

NIC - Network Interface Controller

NIM - Network Interface Module

OB = Operational Bulletins

HS-ACE = Horizontal Stabilizer Actuator Controls Electronics

PN = Part Number

RAT = Ram Air Turbine

RH = Right-Hand

SB = Service Bulletin

SN = Serial Number

SNL = Service Newsletter

SPDA = Secondary Power Distribution Assembly

Note: All abbreviations used in EMBRAER Maintenance Manuals can be found in the Introduction to AMM Part II.

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Operator E-jets News Rel 08