ADVISORY WIRE
AW700-27-0373
DATE: January 30, 2012 PAGE: 1 OF 5
FROM: BOMBARDIER CUSTOMER SERVICES BUSINESS AIRCRAFT
ADVISORY WIRE
REFERENCE NO: AW700-27-0363
SUBJECT : SFCU -17: “SLAT-FLAP HALFSPD” EICAS Nuisance
Message
EFFECTIVITY: Global Express aircraft (9002 to 9153)
Global 5000 aircraft (9127 to 9413, 9415 to
9442, 9998)
Global Express XRS aircraft (9159 to 9431)
Global 5000 GVFD aircraft (9386, 9401,9445 to 9997)
Global 6000 aircraft (9313,9381, 9432 to 9997)
ATA: 27-51
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. If you require technical information concerning this wire, please call your Field Service Representative.

ADVISORY WIRE
AW700-27-0373
DATE: January 30, 2012 PAGE: 2 OF 5
1.0 REFERENCES:
1.1 Airplane Flight Manual (AFM) Non-Normal Procedure, Chapter 05-10
1.2 Aircraft Maintenance Manual (AMM) TASK 27-51-05-400-801
Installation of Slat/Flap Control Unit (SFCU)
1.3 AMM TASK 27-51-00-710-801 “Operational Test of the Slat/Flap
Control System (SFCS)”
1.4 SMARTFIX™ Plus troubleshooting tool
1.5 Detailed GX SFCS Troubleshooting Report (available in
SMARTFIX™Plus for all SFCS EICAS messages)
1.6 AMM TASK 45-45-00-970-822 “Access to NVM Management”
2.0 INTRODUCTION:
This Advisory Wire (AW) is to keep Operators informed about all latest nuisances messages identified in service and in production, since the introduction of the SFCU P/N GT415-5900-17.
Additionally, while the SFCU is part of the “TOP 10 NFF”, this AW provides technical instructions in order to prevent unnecessary removals.
3.0 DESCRIPTION:
Following the introduction of the -17 SFCU, the number of units returned to
Hamilton Sundstrand and No Fault Found (NFF) has increased.
The most frequent cause of recent NFF removals is the appearance of
“SLAT-FLAP HALFSPD” advisory message, as described below: o Installation of a new SFCU. o On Aircraft power-up. o After a SFCU swap for troubleshooting. o In-flight.

ADVISORY WIRE
AW700-27-0373
DATE: January 30, 2012 PAGE: 3 OF 5
A “SLAT-FLAP HALFSPD” advisory message may be displayed on the
Engine Indication and Crew Alerting System (EICAS).
This advisory message should be considered a nuisance message if a SFCU
“internal fault” (2751064STD or 2752064STD) is verified with the Central
Aircraft Information and Maintenance System (CAIMS) or the Onboard
Maintenance System (OMS).
Per SFCS design, an “Internal Fault” is a summary fault indication for detected Built-in Test (BIT) on power-up and in continuous mode; this condition can be successfully cleared by cycling DC input power to the affected SFCU.
4.0 ACTION:
Until the root cause for the transitory external corruption of interfaces to the
SFCU is understood and a final corrective action becomes available,
Bombardier and Hamilton Sundstrand recommend the following procedure to avoid unnecessary LRU removals:
4.1 “SLAT-FLAP HALFSPD” EICAS message occurs in-flight
The Crew must follow AFM instructions (Ref 1.1).
Upon Landing, on ground condition, confirm which SFCU is reporting the “Internal Fault” on CAIMS or OMS.
The “Internal Fault” can be cleared by a successfully completing power
Built-In Test (BIT) in cycling DC input power source of the affected
SFCU, via Electrical Management System Control Display Unit (EMS
CDU).
4.2 “SLAT-FLAP HALFSPD” EICAS posted on Ground Power-up
Maintenance shall confirm which SFCU is reporting the “Internal Fault” on CAIMS or OMS.
The “Internal Fault” can be cleared by a successfully completing power
Built-In Test (BIT) by cycling DC input power source of the affected
SFCU, via EMS CDU.

ADVISORY WIRE
AW700-27-0373
DATE: January 30, 2012 PAGE: 4 OF 5
Note: A “Full Memory Fault” CAIMS or OMS fault may also be observed in the case of a software lock-up condition.
4.3 Should one of the above conditions remain, perform a dual electronic rigging of the affected SFCU, as follows : a. Execute two consecutives Slats and Flaps electronic rigging in using CAIMS /OMS as per AMM TASK (Ref 1.2).
Note: EICAS messages and CAIMS/OMS Active faults related to the SFCS must be disregarded until completion of the dual electronic rigging process. b. Once the two SFCS electronic rigging are completed, perform a complete aircraft power shut down. c. At the next aircraft power up, do an Operational Test of the SFCS as per AMM TASK (ref 1.3).
4.4 If the EICAS message persists, continue troubleshooting in accordance with the SMARTFIX™ Plus troubleshooting tool (ref 1.4).
In the case where the SFCU is confirmed faulty and must be replaced,
Bombardier is requesting that a GX SFCS Troubleshooting Report
(Ref 1.5) sheet be filled and forwarded to your Field Service
Representative (FSR) or the Bombardier Customer Response Center
(CRC) at ac.yul@aero.bombardier.com
.
The information contained in this questionnaire will allow Bombardier to gather data on the reported issues and assist in the troubleshooting if required.
All troubleshooting related to the SFCS remains available via
CAIMS/OMS active faults, ground and flight faults history menus.
In some cases where NVM data must be retrieved, downloading NVM from the SFCU #2 may stop inadvertently with corrupted or incomplete data. For such cases, follow the alternate procedure listed

ADVISORY WIRE
AW700-27-0373
DATE: January 30, 2012 PAGE: 5 OF 5 below : a. On EMS CDU, select “DAU 4 CH A” circuit breaker to “OUT”.
(For Global Vision Flight Deck select DCU 2 A PRI and SEC)
This action will force the SFCU #2 to upload its NVM data via
“DAU 4 CH B” (or DCU 2B) b. Download the NVM file as per AMM task (Ref 1.6) c. Once NVM download complete, select “DAU 4 CH A” (DCU 2 A
PRI and SEC) circuit breaker back to “IN” on EMS CDU.
Should you have any technical questions or need technical assistance, do not hesitate to communicate with :
-CRC Team of Montreal (24/7/365)
North America : 1-866-JET-1247 (1-866-538-1247)
International: +1-514-855-2999
-Your assigned FSR
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