# SDR 2026FA0000303

- Type: Service difficulty report (as reported; unverified)
- Difficulty date: April 28, 2026
- Submitted: April 29, 2026
- Operation: General aviation
- Aircraft: DIBET
- Make and model: Cessna 525A
- Registry model: [Cessna 525A](https://openairdocs.org/model/cessna-525a) (OpenAirDocs)
- Aircraft serial: 0229
- Aircraft time: 6,366 hours, 4,603 cycles
- Engine: FJ442C
- Engine time: 6,269 hours, 4,521 cycles
- System (JASC): [7230 · Turbine Engine Compressor Section](https://openairdocs.org/jasc/7230)
- Part: Compressor
- Part number: 69986
- Part serial: HW17563
- Condition: Damaged
- Location: Engine
- Part time: 6,269 hours, 4,521 cycles
- Component: Engine, Wilint, FJ442C
- Component part number: 60500
- Stage of operation: IN
- How discovered: V
- Nature of condition: O
- Precautionary procedure: K
- FAA source: FAA Service Difficulty Reporting System (https://sdrs.faa.gov/)
- Page: https://openairdocs.org/sdr/2026FA0000303

## Discrepancy

ENGINE MODEL FJ44-2C, WAS RETURNED TO OUR REPAIR STATION FOR UNSCHEDULED REPAIR.  ENGINE SERIAL NUMBER 126312 WAS INSTALLED IN THE RIGHT-HAND (NR 2) POSITION OF THE AIRCRAFT.  FLT CREW REPORTED HEARING AN ABNORMAL NOISE DURING CLIMB, ACCOMPANIED BY LIGHT VIBRATIONS, ALL ENGINE PARAMETERS REPORTED TO REMAIN WITHIN NORMAL LIMITS.  ON SUBSEQUENT ENG START, ANOTHER ABNORMAL NOISE NOTICED BY FLT CREW;  THEY PROCEEDED WITH TAKEOFF.  DURING TAKEOFF ROLL, LOUD BANGS WERE REPORTED, ACCOMPANIED BY LACK OF PERFORMANCE ON NR 2 ENGINE. POST-FLT INSP REVEALED FAN ROTOR HAD CONTACTED THE INLET CASE SHROUD.  PRODUCT SUPPORT DIRECTED A BORESCOPE INSP OF ENG’S COMPRESSOR SECTION, WHICH REVEALED FOD DAMAGE TO THE INTERMEDIATE PRESSURE COMPRESSOR ROTOR & THE HPC ROTOR.  DUE TO LEVEL OF ENG DISASSEMBLY REQUIRED TO FACILITATE REPAIRS,  PRODUCT SUPPORT DIRECTED REMOVAL OF ENG FOR RETURN TO OUR REPAIR STATION FOR REPAIR.   AFTER INDUCTION INTO OUR REPAIR STATION, DISASSEMBLY OF ENG REVEALED ONE LIBERATED 2ND-STAGE I.P. COMPRESSOR ROTOR BLADE.  DAMAGE TO THE DOWNSTREAM HPC ROTOR BLADES ARE EVIDENCE OF SECONDARY DAMAGE RESULTANT FROM THE LIBERATED I.P. ROTOR BLADE.

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.