# SDR 2023FA0000199

- Type: Service difficulty report (as reported; unverified)
- Difficulty date: April 6, 2023
- Submitted: April 6, 2023
- Operation: General aviation
- Aircraft: [N6922L](https://openairdocs.org/aircraft/N6922L), registered now
- Make and model: Cessna 310K
- Registry model: [Cessna 310K](https://openairdocs.org/model/cessna-310k) (OpenAirDocs)
- Engine: IO470
- System (JASC): [7300 · Engine Fuel and Control](https://openairdocs.org/jasc/7300)
- Part: Flow Divider
- Condition: Perforated
- Location: Engine Spine
- Component: Flow Divider
- Stage of operation: IN
- How discovered: O
- Nature of condition: K
- Precautionary procedure: K
- FAA source: FAA Service Difficulty Reporting System (https://sdrs.faa.gov/)
- Page: https://openairdocs.org/sdr/2023FA0000199

## Discrepancy

THE FLOW DIVIDER ON TOP OF THE ENGINE AT THE SPINE HAS A SMALL COMPENSATION HOLE ABOVE THE DIAPHRAGM. IF THE DIAPHRAGM HAS A PERFORATION, RAW FUEL WILL RISE ABOVE THE DIAPHRAGM AND SPEW FROM THIS HOLE AND THUS CAUSE AND EXTREME FIRE HAZARD. I HAVE OBSERVED THIS EFFECT ON TWO ENGINE RUNS WITH DIFFERENT FLOW DIVIDERS. I KNOW OF NO STC/AD TO CORRECT THIS CONDITION. A SMALL TUBE LEADING TO BELOW THE ENGINE BAY WOULD CORRECT THIS UNSAFE CONDITION.I SUSPECT THIS CONDITION IS PRESENT ON MANY AIRCRAFT---I ALSO OBSERVED THIS HOLE ON A BARON FLOW DIVIDER. THE SERVICE MANUAL DOES NOT SPECIFY A TIME COMPLIANCE CHANGE.

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