# SDR UATA5120205265301

- Type: Service difficulty report (as reported; unverified)
- Difficulty date: January 27, 2026
- Submitted: February 6, 2026
- Operation: Air carrier
- Aircraft: [N707RA](https://openairdocs.org/aircraft/N707RA), registered now
- Make and model: Cessna 208B
- Registry model: [Cessna 208B](https://openairdocs.org/model/cessna-208b) (OpenAirDocs)
- Aircraft serial: 208B5120
- Aircraft time: 9,227 hours, 17,090 cycles
- System (JASC): [5340 · Fuselage Main, Attach Fittings](https://openairdocs.org/jasc/5340)
- Part: Attach Fitting
- Part number: 261111356
- Condition: Corroded
- Location: Zone 100
- Part time: 9,227 hours, 17,090 cycles
- 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/UATA5120205265301

## Discrepancy

RIGHT FUSELAGE STRUT FITTINGS FAILED SID 53-20-07-250. LIFT STRUT FITTINGS. REMOVED FLOOR PANELS 2611127-18, 2611127-22 AND PULLY BRACKET 2612112-2 REMOVED FOR ACCESS. CAP ASSEMBLY 2611011-66 RIVETS REMOVED TO OUTBOARD SEAT RAIL FOR ACCESS. REMOVED LIFT STRUT FITTINGS 261113-6 AND 2611113-5. FITTED LIFT STRUT FITTINGS IN PLACE, ALL -3 HOLES REAMED IN PLACE TO 0.,188", ALL -4 BOLT HOLES REAMED IN PLACE TO 0.248". INSTALLED NEW LIFT STRUT FITTINGS 2611113-6 AND 2611113-5, USING NEW BOLTS,, RIVETS, AND SUBSTITUTED ONE RIVET  PIN. APPLIED PS870 B1/2 TO EXTERIOR OPENING EDGES. LIFT STRUT TO FUSELAGE FITMENT FOUND SATISFACTORY. REINSTALLED: FLOOR PANELS 2611127-18, 2611127-22, PULLY BRACKET 2612112-2, AND CAP ASSEMBLY 2611011-66. MATERIALS USED; RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM ORIGINAL INSTALLATION AS WELL AS: MM D2078-13 REVISION-42: SRM 51-40-00, TURBOPROP STANDARD PRACTICES MANUAL (REV 4) 20-10-65, AC43.13-1 B: 4-60B.1 (P4-40), AND 4-57E (P4-19).

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