| Alternative NSN: 9535-01-531-7800 |
| Item Name: Plate Metal |
| FSG: 95 Metal Bars Sheets and Shapes |
| Federal Supply Class (FSC): 9535 Plate Sheet Strip and Foil Nonferrous Base Metal |
| NIIN: 015317800 |
| NCB Code: USA (01) |
| Manufacturers: Sae International, Society Of Automotive Engineers Inc |
Browse NSN parts of NSN 9535-01-531-7800 and get lowest price for your requested parts in 15 minutes. Just ordered part of NSN 9535-01-531-7800 like AMS-QQ-A-250 5, AMS-QQ-A-250 5, AMS-QQ-A-250 5-CDT351-1 0X6X24, AMS-QQ-A-250 5-T351-1.000X6X24, AMS-QQ-A-250-5-T351-1-000X6X24 described as Plate Metal from industry leading manufactures such as Society Of Automotive Engineers Inc, Sae International. We are proud to offer an inventory of over 2 billion ready-to-ship parts, 24/7 availability, and key locations in the U.S./abroad. These attributes allow us to meet all aircraft on ground (AOG) requirements with ease.
| Part No | Manufacturer | Item Name | QTY | RFQ |
|---|---|---|---|---|
| AMS-QQ-A-250 5 | Society Of Automotive Engineers Inc | plate metal | Avl | RFQ |
| AMS-QQ-A-250 5 | Sae International | plate metal | Avl | RFQ |
| AMS-QQ-A-250 5-CDT351-1 0X6X24 | Society Of Automotive Engineers Inc | plate metal | Avl | RFQ |
| AMS-QQ-A-250 5-T351-1.000X6X24 | Sae International | plate metal | Avl | RFQ |
| AMS-QQ-A-250-5-T351-1-000X6X24 | Society Of Automotive Engineers Inc | plate metal | Avl | RFQ |
| MRC | Criteria | Characteristic |
|---|---|---|
| AARN | FABRICATION METHOD | ROLLED |
| ABGL | WIDTH | 6.000 INCHES NOMINAL |
| ABRY | LENGTH | 24.000 INCHES NOMINAL |
| ADVM | CROSS-SECTIONAL THICKNESS | 1.0000 INCHES NOMINAL |
| AGAV | END ITEM IDENTIFICATION | FUSELAGE F4F JET AIRCRAFT |
| AGTA | BASIC SHAPE STYLE | SOLID |
| ALBY | USAGE DESIGN | AIRCRAFT |
| CQBC | MINIMUM TENSILE STRENGTH | 62000 POUNDS PER SQUARE INCH |
| CQHQ | MINIMUM YIELD STRENGTH | 42000 POUNDS PER SQUARE INCH |
| FEAT | SPECIAL FEATURES | THIN LAYERS APPROXIMATELY EQUAL THICKNESS, OF ALUMINUM ALLOY 1230 ANODIC TO THE CORE ARE BONDED TO BOTH SURFACES; NOMINAL CLADDING THICKNESS FOR EACH LAYER TO BE 2.5 PERCENT OF COMPOSITE THICKNESS OR 2.0 PERCENT OF FINISHED PLATE THICKNESS |
| HEAT | HEAT TREATMENT | T-351 SOLUTION HEAT TREATED |
| MATL | MATERIAL | ALUMINUM ALLOY, QQ-A-250/5 |
| AARN | FABRICATION METHOD | ROLLED |
| ABGL | WIDTH | 6.000 INCHES NOMINAL |
| ABRY | LENGTH | 24.000 INCHES NOMINAL |
| ADVM | CROSS-SECTIONAL THICKNESS | 1.0000 INCHES NOMINAL |
| AGAV | END ITEM IDENTIFICATION | FUSELAGE F4F JET AIRCRAFT |
| AGTA | BASIC SHAPE STYLE | SOLID |
| ALBY | USAGE DESIGN | AIRCRAFT |
| CQBC | MINIMUM TENSILE STRENGTH | 62000 POUNDS PER SQUARE INCH |
| CQHQ | MINIMUM YIELD STRENGTH | 42000 POUNDS PER SQUARE INCH |
| FEAT | SPECIAL FEATURES | THIN LAYERS APPROXIMATELY EQUAL THICKNESS, OF ALUMINUM ALLOY 1230 ANODIC TO THE CORE ARE BONDED TO BOTH SURFACES; NOMINAL CLADDING THICKNESS FOR EACH LAYER TO BE 2.5 PERCENT OF COMPOSITE THICKNESS OR 2.0 PERCENT OF FINISHED PLATE THICKNESS |
| HEAT | HEAT TREATMENT | T-351 SOLUTION HEAT TREATED |
| MATL | MATERIAL | ALUMINUM ALLOY, QQ-A-250/5 |
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9505-00-061-1592 (9505000611592) |
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