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AIRBUS REFERENCE STANDARD-99D51107295000 (Inch Version) Airbus Reference Standard A318-A321 51-10-11 Fig 604 Fastener (Ln9199). Includes Test Report And Certificate Of Conformance. SHEET A: THICKNESS: MIN – 0.055" / MAX - 0.12" SHEET B: THICKNESS: MIN – 0.063"/ MAX – 0.16" SHEET C: ANY THICKNESS Block Contains 9 Rivet Shank Hole Diameters (D) 0.16" – 0.22" mm STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99D51107295000 MATERIAL – SHEET A and SHEET B is ALUMINUM−ALLOY, WITH CONDUCTIVITY RANGE 16−26 MS/m SHEET C is ALUMINUM−ALLOY OR TITANIUM SHEET/STIFFENER. NOTE: For special alloy request by mail.
AIRBUS REFERENCE STANDARD-99D51107295000 (Metric Version) Airbus Reference Standard A318-A321 51-10-11 Fig 604 Fastener (Ln9199). Includes Test Report And Certificate Of Conformance. SHEET A: THICKNESS: MIN − 1.4 mm / MAX-3mm SHEET B: THICKNESS: MIN − 1.6 mm/MAX - 4mm SHEET C: ANY THICKNESS Block Contains 9 Rivet Shank Hole Diameters (D) 4 mm − 5.6 mm STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99D51107295000 MATERIAL – SHEET A and SHEET B is ALUMINUM−ALLOY, WITH CONDUCTIVITY RANGE 16−26 MS/m SHEET C is ALUMINUM−ALLOY OR TITANIUM SHEET/STIFFENER. NOTE: For special alloy request by mail.
AIRBUS REFERENCE STANDARD-99A51107299001 (Inch Version) Airbus Reference Standard A300-600 51-10-13 Fig 4 Fastener (Nas5410-48). Includes Test Report And Certificate Of Conformance. OVERALL DIMENSION -PLATE (1) – 6.5" (L) X 1.6" (W) X 0.08" (T) PLATE (2) – 6.5" (L) X 4" (W) X 0.071" (T) PLATE (1) & (2) - ASSEMBLED WITH SEALANT PLATE (3) – 6.5" (L) X 1.6" (W) X 0.08" (T) Block Contains (5) BOREHOLE WITH RIVET, DIA 0.19" (2) BOREHOLE WITHOUT RIVET, DIA 0.19" (1) BOREHOLE WITHOUT RIVET, DIA 0.16" (11) ENGRAVED NUMBERS DEPTH 0.006", ENGRAVED RANGE LINES DEPTH 0.002" ENGRAVE WIDTH – 0.04" (3) CORNER NOTCH – 0.2" (1) BORE NOTCH – 0.12" (1) CORNER NOTCH – 0.12" (2) SCREW, WASHER, NUT STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99A51107299001 MATERIAL: 2024 ALUMINUM ALLOY. RIVET MATERIAL - CSK 100 - NSA 5410−48 SEALENT MATERIAL - PR 1422B NO. 09−002 NOTE: For special alloy request by mail.
AIRBUS REFERENCE STANDARD-99A51107299001 (Metric Version) Airbus Reference Standard A300-600 51-10-13 Fig 4 Fastener (Nas5410-48). Includes Test Report And Certificate Of Conformance. OVERALL DIMENSION -PLATE (1) - 160mm (L) X 40mm (W) X 2mm (T) PLATE (2) - 160mm (L) X 100mm (W) X 1.8mm (T) PLATE (1) & (2) - ASSEMBLED WITH SEALANT PLATE (3) - 160mm (L) X 40mm (W) X 2mm (T) Block Contains (5) BOREHOLE WITH RIVET, DIA 4.8 mm (2) BOREHOLE WITHOUT RIVET, DIA 4.8 mm (1) BOREHOLE WITHOUT RIVET, DIA 4.0 mm (11) ENGRAVED NUMBERS DEPTH 0.15 mm, ENGRAVED RANGE LINES DEPTH 0.05 mm ENGRAVE WIDTH - 1mm (3) CORNER NOTCH - 5mm (1) BORE NOTCH - 3mm (1) CORNER NOTCH - 3mm (2) SCREW, WASHER, NUT STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99A51107299001 MATERIAL: 2024 ALUMINUM ALLOY. RIVET MATERIAL - CSK 100 - NSA 5410−48 SEALENT MATERIAL - PR 1422B NO. 09−002 NOTE: For special alloy request by mail.
AIRBUS REFERENCE STANDARD-99A53307292001 (Metric Version) Airbus Reference Standard A318-A321 51-10-15-991-004-A Fasteners: (Nas5410-48). Includes Test Report And Certificate Of Conformance. OVERALL DIMENSION - TOP SKIN – 9" (L) X 4" (W) X 0.06" (T) TOP SKIN DOUBLER -9" (L) X 2.5" (W) X 0.024" (T) BOTTOM SKIN - 9" (L) X 5" (W) X 0.06" (T) BOTTOM SKIN DOUBLER - 9" (L) X 2" (W) X 0.024" (T) Block Contains: (28) RIVET HOLE DIA – 0.19", Note - NSA5410−48 (8 Rivet as modified length). (4) PILOT HOLE DIA – 0.06". (10) A CORNER NOTCH – 0.12" (L) X 0.006" (W) X 0.06" (D) (2) B CORNER NOTCH - 0.2" (L) X 0.006" (W) X 0.06" (T) (4) C CORNER NOTCH – 0.28" (L) X 0.006" (W) X 0.06" (T) (4) THRU NOTCH – 0.4" (L) X 0.02" (W) X 0.06" (D) STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99A53307292001 MATERIAL: 2024 ALUMINUM ALLOY. STRINGER - DAN21 AK 28 x22 x 1.6 SEALENT MATERIAL - PR 1422B, NO. 09−002 NOTE: For special alloy request by mail.
AIRBUS REFERENCE STANDARD-99A53307292001 (Metric Version) 2024 ALUMINUM ALLOY Airbus Reference Standard A318-A321 51-10-15-991-004-A Fasteners: (Nas5410-48). Includes Test Report And Certificate Of Conformance. OVERALL DIMENSION - TOP SKIN - 230mm (L) X 100mm (W) X 1.6mm (T) TOP SKIN DOUBLER -230mm (L) X 64mm (W) X 0.6mm (T) BOTTOM SKIN - 230mm (L) X 125mm (W) X 1.6mm (T) BOTTOM SKIN DOUBLER - 230mm (L) X 50mm (W) X 0.6mm (T) Block Contains: (28) RIVET HOLE DIA - 4.8mm, Note - NSA5410−48 (8 Rivet as modified length). (4) PILOT HOLE DIA - 1.5mm. (10) A CORNER NOTCH - 3mm (L) X 0.15mm (W) X 1.6mm (D) (2) B CORNER NOTCH - 5mm (L) X 0.15mm (W) X 1.6mm (T) (4) C CORNER NOTCH - 7mm (L) X 0.15mm (W) X 1.6mm (T) (4) THRU NOTCH - 9.5mm (L) X 0.5mm (W) X 1.6mm (D) STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99A53307292001 MATERIAL: 2024 ALUMINUM ALLOY. STRINGER - DAN21 AK 28 x22 x 1.6 SEALENT MATERIAL - PR 1422B, NO. 09−002 NOTE: For special alloy request by mail.
AIRBUS REFERENCE STANDARD-99A51107300000 (Inch Version) ALUMINUM ALLOY Airbus A330 Reference Standard For Subsurface Cracks In Al-Alloy 51-10-16-991-011-A. Part 6, Page 615 Figure 610procedure B. Includes Test Report And Certificate Of Conformance. OVERALL DIMENSION - 4" (L) X 2.5" (W) X 0.07" (T) 1. NOTCH - RADIUS 1" X DEPTH 0.04". 2. NOTCH – 2.5" (L) X 0.006" (W) X 0.05" (Deep) (2) ACRYL 5.1411 - Sq.0.4" X 0.4", 4" (L) (8) SCREW - DIN84 M4 or LOCAL PROCUREMENT STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99A51107300000 MATERIAL: ALUMINUM ALLOY. NOTE: For special alloy request by mail.
AIRBUS REFERENCE STANDARD-99A51107300000 (Metric Version) ALUMINUM ALLOY Airbus A330 Reference Standard For Subsurface Cracks In Al-Alloy 51-10-16-991-011-A. Part 6, Page 615 Figure 610procedure B. Includes Test Report And Certificate Of Conformance. OVERALL DIMENSION - 100mm (L) X 60mm (W) X 1.8mm (T) 1. NOTCH - RADIUS 25mm X DEPTH 1mm 2. NOTCH - 60mm (L) X 0.15mm (W) X 1.2mm (Deep) (2) ACRYL 5.1411 - Sq.10mmX10mm, 100mm (L) (8) SCREW - DIN84 M4 or LOCAL PROCUREMENT STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99A51107300000 MATERIAL: ALUMINUM ALLOY. NOTE: For special alloy request by mail.
AIRBUS REFERENCE STANDARD-99A53307274000 (Inch Version) 2024-T351 ALUMINUM AIRBUS A318/A319/A320/A321 REFERENCE STANDARD 51-10-16-991-005A, PAGE 10. MATERIAL: 2024-T351 ALUMINUM. Includes Test Report and Certificate of Conformance. OVERALL DIMENSION - 4" (L) X 2.5" (W) X 0.07" (T) 1. NOTCH - RADIUS 1" X DEPTH 0.04". 2. NOTCH – 2.5" (L) X 0.006" (W) X 0.05" (Deep) (2) ACRYL 5.1411 - Sq.0.4" X 0.4", 4" (L) (8) SCREW - DIN84 M4 or LOCAL PROCUREMENT STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99A53307274000 MATERIAL: 2024-T351 ALUMINUM. NOTE: For special alloy request by mail.
AIRBUS REFERENCE STANDARD-99A53307274000 (Metric Version) 2024-T351 ALUMINUM AIRBUS A318/A319/A320/A321 REFERENCE STANDARD 51-10-16-991-005A, PAGE 10. MATERIAL: 2024-T351 ALUMINUM. Includes Test Report and Certificate of Conformance. OVERALL DIMENSION - 100mm (L) X 60mm (W) X 1.8mm (T) 1. NOTCH - RADIUS 25mm X DEPTH 1mm 2. NOTCH - 60mm (L) X 0.15mm (W) X 1.2mm (Deep) (2) ACRYL 5.1411 - Sq.10mmX10mm, 100mm (L) (8) SCREW - DIN84 M4 or LOCAL PROCUREMENT STANDARD/MANUFACTURE REFERENCE/PART NUMBER - 99A53307274000 MATERIAL: 2024-T351 ALUMINUM. NOTE: For special alloy request by mail.
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