68A112285-2011: PLATE,STRUCTURAL,AIRCRAFT.
The PLATE,STRUCTURAL,AIRCRAFT is a the manufacturer industrial component. Key specifications include material: ALUMINUM ALLOY 2024, overall_length: 6.880 INCHES NOMINAL IN, special_features: REQUESTEDNAME:SILL;P/N 68A112285-2012 IS THE OPPOSITE CONFIGURATION, aircraft_location: COVER-WING/FUSELAGE,LOWER,FS550 TO FS566, material_thickness: 0.050 INCHES NOMINAL IN, aircraft_mission_design_series: F-15I. This part is cataloged in the U.S.
Government catalog under NSN 1560-01-436-5337, indicating validated use in U.S. government and defense logistics supply chains. Available through authorized enterprise resellers and TPM (Third Party Maintenance) channels.
Verify compatibility with your specific system configuration before ordering.
| material | ALUMINUM ALLOY 2024 |
| overall_length | 6.880 INCHES NOMINAL IN |
| special_features | REQUESTEDNAME:SILL;P/N 68A112285-2012 IS THE OPPOSITE CONFIGURATION |
| aircraft_location | COVER-WING/FUSELAGE,LOWER,FS550 TO FS566 |
| material_thickness | 0.050 INCHES NOMINAL IN |
| aircraft_mission_design_series | F-15I |
| material_document_and_classification | QQ-A-250/4,T62 FED SPEC SINGLE MATERIAL RESPONSE |
| surface_treatment_document_and_classification | PS13201 TYPE 2 CLASS 1 MFR REF SINGLE TREATMENT RESPONSE |
| NSN | 1560-01-436-5337 |
| SURFACE TREATMENT DOCUMENT AND CLASSIFICATION | PS13201 TYPE 2 CLASS 1 MFR REF SINGLE TREATMENT RESPONSE |
| MATERIAL DOCUMENT AND CLASSIFICATION | QQ-A-250/4,T62 FED SPEC SINGLE MATERIAL RESPONSE |
| OVERALL LENGTH | 6.880 INCHES NOMINAL IN |
| MATERIAL THICKNESS | 0.050 INCHES NOMINAL IN |
| SPECIAL FEATURES | REQUESTEDNAME:SILL;P/N 68A112285-2012 IS THE OPPOSITE CONFIGURATION |
| AIRCRAFT LOCATION | COVER-WING/FUSELAGE,LOWER,FS550 TO FS566 |
| MATERIAL | ALUMINUM ALLOY 2024 |
| AIRCRAFT MISSION DESIGN SERIES | F-15I |
No substitute or cross-reference records for this part.