Message Name:

GSSV FAIL

Message Code:

B3-006823

Associated CAS:

SPOILERS FAULT
(Caution)

SPOILERS FAULT
(Advisory)

The Spoiler Electronic Control Unit 1 (SECU1) has detected a Ground Spoiler Select Valve (GSSV) 1 Fault.

• Ground-Spoiler Selector Valve 1 (GSSV1) (MPE34)
• Spoiler Electronic Control Unit 1 (SECU1) (A118)
• Associated Wiring

Advisory Wire/Service Bulletin:

• AW300-27-0123 - No Fault Found Reduction Initiative And Troubleshooting Information - Spoiler Fault Cyan Message (20501 - 20999)
• AW300-29-0251 - Recent failures of the Engine Driven Pump (EDP) (20501 - 20999)

Forum Articles/Infoservice/Newsletter: None

Latency Check:

The system continuous monitoring includes a "Latency Check" which verifies that both GSSV command solenoid valves are not failed in the open position. This test is carried out automatically at every landing, but it also can be easily interrupted at anytime if one of the pre-requisite conditions is not met (for example, if pilots are engaging the spoilers too early, etc.). If the Latency Check has not successfully been performed automatically or manually at least one time since the last 100 landings, the SECU will post a fault message in the MDC.

1. Aircraft has been weight on wheels for 40 seconds and wheel speed has been lower than 45 kts for 10 seconds.
2. All spoilers have completed a deploy and retracted cycle.
3. Left and right throttle levers valid and less than maximum take-off.
4. Ground Spoiler (GS) switch at AUTO or MAN.
5. No GS failure messages.
6. Left and right hydraulic greater than 1,500 psi.
7. Control Wheel centered.

The test duration is 17 seconds. If any of the above conditions change during the test sequence, the test will abort. If the test is run and a failure is detected, or if the test conditions were not met for 100 consecutive flight cycles, the cyan 'SPOILERS FAULT' advisory EICAS message is displayed.

1. Check aircraft panel operation. PLD, ROLL, GLD. If no loss of spoiler functionality, run latency check as follows:

   1. Get Hydraulic by using Aircraft EDPs or a mule.
   2. Pull C/B of the SECU Not under test.
   3. Center control wheels.
   4. Confirm FSCL at 0.
   5. Select GSSS to Manual, wait 5 seconds. Verify all spoiler surfaces deployment.
   6. Select GSSS to Auto. Verify all spoiler surface retraction.
   7. Listen to the spoilers until three clicks are heard in fifteen seconds.
   8. Select GSSS to Off.
   9. Pull Spoiler C/B under test.
   10. Reset both Spoiler C/Bs.
       NOTE: IF FAULT IS CLEARED AFTER LATENCY CHECK HAS BEEN COMPLETED, THEN NO FURTHER TROUBLESHOOTING IS REQUIRED AND AIRCRAFT CAN BE RETURNED TO SERVICE. DO CLOSE OUT.

2. If fault remains, continue with next step.
3. Visually inspect the back of the box for pin damage or in the rack. If damaged, repair pin.
4. Interchange SECU 1 with SECU 2.

   1. If problem follows, replace SECU 1.
      NOTE: Perform electronic rigging of both SECUs when either SECU is swapped or replaced. The intent is if a SECU that is being installed was previously rigged in a different location in the same aircraft or it is being installed in a different aircraft or the SECU is a spare part it requires electronic rigging (AMM 27-61-05-820-802) per the instructions in AMM TASK 27-61-05-400-801 Installation of the Spoiler Electronic-Control Unit (SECU).
   2. If system checks are good, do close out.
   3. If fault remains, continue with next step.

5. Perform wiring check between GSSV 1 and SECU 1 per AWM 27-62-05. If damaged, repair wiring and run latency check (see step 1 of the Troubleshooting Recommendation).

   1. If system checks are good, do close out.
   2. If fault remains, continue with next step.

6. Check GSSV 1 coil values. Pins 8 to 9, 10 to 11, 12 to 13 = 62 to 74 Ω. If damaged, replace GSSV 1.
7. Do close out.