Advisory Wire: In-Flight engine fire indication
Effectivity: Global 7500 aircraft
ATA: 72-00
1. REFERENCES:
1.1 General Electric (GE) Fleet All Operator Wire (AOW) – 25-PASSPORT-001 Rev 1
1.2 Airplane Flight Manual (AFM) – Sections 03-05-12 & 03-05-14
1.3 Flight Crew Operating Manual (FCOM) Volume 1 – Sections 03-05-14 & 03-05-17
1.4 Quick Reference Handbook (QRH) Volume 2 – Sections ENG 05-12 & ENG 05-15
1.5 GE Vendor Service Bulleting (VSB) PASSPORT20-A-72-00-0166-00A-930A-D – Start Bleed Valve (SBV) fuel tube replacement for containment action
1.6 GE AOW - 25-PASSPORT-001-Rev 2 - Passport corrective action for investigation into engine fire indication
1.7 GE VSB PASSPORT20-A-72-00-0168-00A-930A-D – Start bleed valve (SBV) fuel tube redesign
2. INTRODUCTION:
This Advisory Wire (AW) is to inform operators of the release of the corrective action for the ongoing ICAO ANNEX 13 investigation, into a fire indication within the fire zone of the engine core compartment on a Passport engine installed on the Global 7500 aircraft.
3. DESCRIPTION:
During this event, the operator reported that they observed the L ENG FIRE (Warning) CAS message during the climb phase of flight. Engine parameters indicated no anomalies, the fire detection system worked as designed and the aircraft returned to base without incident. The use of the fire extinguishing bottles to put out the fire were not required.
Post-flight inspections on the affected engine revealed evidence of fire that was contained within the fire zone of the engine core compartment. The decision was made to return the impacted engine back to GE for detailed inspection.
GE initially released AOW 25-PASSPORT-001 (Ref. 1.1) which contained the latest investigation status:
“Root Cause Investigation to date: The engine was removed from the aircraft and sent to the GE Aerospace MRO facility. Engine investigation found that a fuel leak occurred within the engine core compartment on tube Part Number (PN) 2721M52G01. This tube supplies fuel control pressure to the Nacelle Anti-Ice/Booster Anti-Ice/Start Bleed Valve (SBV). Further investigation on this engine and six additional engines in the field found that an air leak, which does not impact engine performance parameters, can form at the High-Pressure Compressor (HPC) case split line flange intersection with the HPC extension case. This air can impinge on the tube and cause surface erosion. Over time the erosion can degrade the tube wall thickness and potentially lead to a fuel leak. This is a wear out mode driven by engine flight hours”
Corrective Action:
GE redesigned the SBV fuel tube to avoid the local air impingement, eliminating the possibility of surface erosion. The redesigned tube has been released in Service Bulletin PASSPORT20-A-72-00-0168-00A930A-D – Start bleed valve (SBV) fuel tube redesign (Ref 1.7). This VSB was released on June 30, 2025.
GE’s All-Operator Wires (AOW) 25-PASSPORT-001 (Ref. 1.1 & 1.6) and Service bulletins (SB) PASSPORT20-A-72-00-0166-00A-930A-D (Ref. 1.5 & 1.7) can be obtained on the GE portal (https://my.geaerospace.com).
4. ACTION:
In the unlikely event that an (L/R) ENG FIRE (Warning) CAS message is observed, it is important that the crew follow the flight manual procedures (Ref. 1.2 – 1.4).
Bombardier recommends operators to familiarize themselves with the instructions and recommended compliance time included in the GE SB (Ref.1.5 & 1.7).
NOTE:
For those Operators that have previously complied with the field containment SB 72-00-0166 (Ref. 1.2), you have 2,500 flight hours since implementing that SB to comply with the Corrective Action SB 72-00-0168 (Ref. 1.7).
As this is a total fleet retrofit, it is recommended to adhere to the 2,500 FH guidance to retrofit the SBV fuel tube.
Should you have any questions pertaining to this AW or require additional information, please contact your Bombardier Field Service Representative (FSR) or the Customer Response Center (CRC 24/7) team.