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Wings (aircraft)

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Image
Published: 30 June 2023
Fig. 11 Schematic diagram of building-block test for a fixed-wing aircraft, or the pyramid of testing. Reprinted from Ref 8 with permission from the European Union Aviation Safety Agency (EASA) More
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Published: 01 January 2002
Fig. 4 Fatigue cracking in an aircraft wing fitting for the F-111 Aircraft 94 that crashed in 1969. (a) and (b) Location of the left wing-pivot box fitting. The 22 mm (0.91 in.) material defect was not observed during inspection, and a fatigue crack initiated and grew for only about 0.38 mm More
Image
Published: 30 August 2021
Fig. 4 Fatigue cracking in an aircraft wing fitting for the F-111 aircraft 94 that crashed in 1969. (a) and (b) Location of the left wing pivot box fitting. The 23 mm (0.91 in.) material defect was not observed during inspection, and a fatigue crack initiated and grew for only approximately More
Image
Published: 01 January 2006
Fig. 14 Galvanic corrosion of an F/A-18 aircraft wing substructure resulting from composite doors attached to aluminum substructure with titanium and steel fasteners in the presence of moisture. Courtesy of S. Long, Naval Air Depot—North Island More
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Published: 01 November 1995
Fig. 9 Backside of mandrel for aircraft wing More
Image
Published: 01 January 1987
Fig. 1027 Surface of a crack in an aircraft wing-spar carry-through forging of aluminum alloy 7075-T6. The crack was discovered during inspection after 5269 h of service and was opened up. The external surface at edge C-C had been machined after forging. The regions marked A contain fatigue More
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Published: 01 January 2001
Fig. 5 Laser ply outline projection system in use on aircraft wing and fuselage fairing tool. Courtesy of Assembly Guidance Systems More
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Published: 01 January 2002
Fig. 10 4140 steel slat track from a military aircraft wing. The track bent because one end did not become fully austenitic during heat treatment, producing a low-strength structure of ferrite and tempered martensite. More
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Published: 01 January 2002
Fig. 12 Cadmium-plated 8740 steel aircraft-wing assembly nut that failed by hydrogen embrittlement. The nut was not baked after electroplating to release hydrogen. (a) Overall view. 5×. (b) Fracture surface. 9×. (c) Scanning electron micrograph of typical intergranular fracture shown in box More
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Published: 30 November 2018
Fig. 9 Resistance seam welding of an aircraft integral wing fuel tank using continuous electrode motion. Dimensions given in inches More
Image
Published: 15 January 2021
Fig. 10 4140 steel slat track from a military aircraft wing. The track bent because one end did not become fully austenitic during heat treatment, producing a low-strength structure of ferrite and tempered martensite. More
Image
Published: 30 August 2021
Fig. 12 Cadmium-plated 8740 steel aircraft-wing assembly nut that failed by hydrogen embrittlement. The nut was not baked after electroplating to release hydrogen. (a) Overall view. Original magnification: 5×. (b) Fracture surface. Original magnification: 9×. (c) Scanning electron micrograph More
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003477
EISBN: 978-1-62708-195-5
... military aircraft applications use carbon-fiber-reinforced epoxy composites. About 26% of the structural weight of the U.S. Navy's AV-8B is carbon-fiber-reinforced composites. Components include the wing box, forward fuselage, horizontal stabilizer, elevators, rudder and other control surfaces...
Series: ASM Handbook Archive
Volume: 12
Publisher: ASM International
Published: 01 January 1987
DOI: 10.31399/asm.hb.v12.a0000621
EISBN: 978-1-62708-181-8
... gear wheel and actuator beam, an aircraft wing spar, a fractured aircraft propeller blade, shot peened fillet, an aircraft lower-bulkhead cap, and clevis-attachment lugs. aircraft components corrosion fatigue fatigue crack propagation fatigue cracks fatigue fracture fatigue striations...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003452
EISBN: 978-1-62708-195-5
... million ( Ref 2 ), with a successful history of over 25 years of service. The USAF has installed bonded composite repairs on a number of aircraft types, including C-141, C- 130, C-5, B-52, and F-16. The most notable application is the “weep hole” crack repair for the C-141 aircraft wings. This application...
Image
Published: 01 January 2024
. These resulted from immersion in the sea after the wing separated from the aircraft. Source: Ref 11 More
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003467
EISBN: 978-1-62708-195-5
... deal mainly with structures that exhibit an initial material and/or manufacturing defect or failures that are most prevalent and most easily solved. The components include helicopter rotor blade, composite wing spar, and aircraft rudder. aircraft rudders composite wing spar helicopter rotor...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003457
EISBN: 978-1-62708-195-5
... & Co., Wilmington, DE) honeycomb. The configurations of the center-engine fairing, under-wing fillet, and wing-to-body fairing are shown in Fig. 5 , along with the various types of damage incurred. During the ten-year service evaluation period, the Kevlar 49-epoxy fairings installed on L-1011 aircraft...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002393
EISBN: 978-1-62708-193-1
... failure of the lower wing skin root region at 1900 h caused loss of aircraft. F-111 Safe-Life 4000 h: Fatigue failure of the center wing box at 105 h caused loss of aircraft. Almost without exception, initial manufacturing or in-service accidental damage is the cause of fatigue cracking...
Series: ASM Handbook
Volume: 12
Publisher: ASM International
Published: 01 January 2024
DOI: 10.31399/asm.hb.v12.a0006848
EISBN: 978-1-62708-387-4
... representing gust loads on transport aircraft wings. Fig. 10 SEM fractographic and optical metallographic characteristics of fatigue crack growth in 8090-T81 aluminum-lithium alloy sheet under constant-amplitude (CA) and variable-amplitude (VA) loading ( Ref 47 ). R s , surface roughness profile...