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fuselage frames

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Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006741
EISBN: 978-1-62708-210-5
... Abstract The aluminum alloy 7099 is a Kaiser aluminum high-strength Al-Mg-Zn-Cu alloy with zirconium that offers a less quench-sensitive alloy for properties in thicker sections for airframe structures such as wing ribs, spars, and skins, as well as fuselage frames and floor beams...
Image
Published: 01 January 2006
Fig. 26 Examples of local and widespread corrosion on fuselage structures. (a) Local corrosion involves nonadjacent frame bays. (b) Local corrosion—involves nonadjacent stringers. (c) Widespread corrosion—involves adjacent stringer frame bays. (d) Widespread corrosion—involves adjacent frame More
Image
Published: 01 January 1990
Fig. 16 Prealloyed HIP Ti-6Al-4V aerospace parts produced by the Crucible ceramic mold method. (a) F-14 fighter plane fuselage brace. (b) F-18 fighter plane engine mount support fitting. (c) Cruise missile engine impeller. (d) Four-section welded nacelle frame structure. (e) Titanium aluminide More
Book Chapter

By Don O. Evans
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003410
EISBN: 978-1-62708-195-5
... facesheets inclose a Nomex (DuPont) honeycomb core for a total thickness of 20.6 mm (0.81 in.). This design creates a fuselage shell free of frames and stiffeners. The shells are also free of rivets and skin joints. Because the shells do not contain frames, there is more usable space for passengers or cargo...
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
...). Figure 5(a) illustrates a fatigue-critical location in a fuselage skin at the first fastener in a circumferential frame shear clip cutout. The cutout, which allows continuous axial stiffeners to pass through the frame, creates a stress concentration in the skin, which is aggravated by increased skin...
Series: ASM Handbook
Volume: 13C
Publisher: ASM International
Published: 01 January 2006
DOI: 10.31399/asm.hb.v13c.a0004169
EISBN: 978-1-62708-184-9
... that is determined by the operator to be an urgent airworthiness concern Fig. 26 Examples of local and widespread corrosion on fuselage structures. (a) Local corrosion involves nonadjacent frame bays. (b) Local corrosion—involves nonadjacent stringers. (c) Widespread corrosion—involves adjacent stringer...
Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006731
EISBN: 978-1-62708-210-5
... 6.2–7.0 Other (each), max 0.05 0.05 Other (total), max 0.15 0.15 Al bal bal The 7040 plate alloy was introduced by Pechiney for use in fuselage applications, such as integrally machined main frames, cockpit window frames, beams, and fittings ( Ref 1 ). The over-aged T7651 temper...
Series: ASM Handbook
Volume: 2
Publisher: ASM International
Published: 01 January 1990
DOI: 10.31399/asm.hb.v02.a0001080
EISBN: 978-1-62708-162-7
... and titanium alloys Applications area Typical uses Aerospace  Airframes Fittings, bolts, landing gear beams, wing boxes, fuselage frames, flap tracks, slat tracks, brake assemblies, fuselage panels, engine support mountings, undercarriage components, inlet guide vanes, wing pivot lugs, keels...
Book Chapter

Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006740
EISBN: 978-1-62708-210-5
... corrosion cracking in aerospace applications such as wing-box ribs and spars; fuselage primary structural elements such as frames, bulkheads, windshield surrounds; and structural components in landing-gear bays. Plate product has excellent flatness, consistency, and low residual stress that facilitate...
Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006711
EISBN: 978-1-62708-210-5
.... Source: Ref 2 Applications include engine nacelles, cowling, aircraft inner door structures, seat components, fuselage skin, wing components, forged aircraft wheels, automotive structural forgings, drawn hydraulic tubing, recreational products, and welded plate. Alloy 6013 has been evaluated...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002416
EISBN: 978-1-62708-193-1
... are vertical tails of the Airbus A300-340 series and the Boeing 777 transports and the wings and fuselages of the B-2 bomber. NASA and its contractors have completed two of three phases of the Advanced Composite Technology (ACT) program to develop composite wings and fuselages for commercial transport...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002392
EISBN: 978-1-62708-193-1
... of component failure within a specified time frame is very remote. Component life estimates using these methods are typically based upon material and load data gathered from axial loading tests, material component tests, and full-scale testing. In axial loading tests, test samples of the material are subjected...
Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006516
EISBN: 978-1-62708-210-5
... a commercial success as a passenger plane as well as a cargo carrier ( Ref 19 ). Alclad 2024-T351 remained the alloy of choice for the fuselage of virtually every airplane built until the 1990s, when other 2 x 24 alloy variants became available. Fig. 5 1930s vintage Douglas DC-3 aircraft...
Series: ASM Handbook
Volume: 14B
Publisher: ASM International
Published: 01 January 2006
DOI: 10.31399/asm.hb.v14b.a0005124
EISBN: 978-1-62708-186-3
... a hardness of Durometer A 80 to 85. The second piece, which was replaceable, was 25 mm (1 in.) thick and had a hardness of Durometer A 70 to 75. Example 1: Shallow Drawing of a Fuselage Tail Cap by the Guerin Process The fuselage tail cap shown in Fig. 2 was rubber-pad formed at 140 MPa (20 ksi...
Book Chapter

By R. Kopp, J. Schulz
Series: ASM Handbook
Volume: 14B
Publisher: ASM International
Published: 01 January 2006
DOI: 10.31399/asm.hb.v14b.a0005132
EISBN: 978-1-62708-186-3
... materials. Typical Applications Aerospace Industry In the aircraft and aerospace industries, shot peen forming has been successfully used for many years to form numerically controlled milled components, such as airplane wings, stringer-strengthened fuselages (Alpha Jet, Airbus), or structural...
Series: ASM Handbook
Volume: 12
Publisher: ASM International
Published: 30 January 2024
DOI: 10.31399/asm.hb.v12.a0006844
EISBN: 978-1-62708-387-4
.... Photographs that have nonsequential frame numbers or that have been digitally edited for clarity can invite unfounded accusations of evidence tampering by a plaintiff’s attorney who is determined to cast doubt on an investigation’s integrity. For that reason, a master file of all photographs taken...
Book Chapter

By Frank K. Ko
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003361
EISBN: 978-1-62708-195-5
... U.S. Composites New York Applications of braided fabrics and composites Table 4 Applications of braided fabrics and composites Aircraft fuselage frames Aircraft interiors Aircraft propellers Artificial limbs, tendons, bone Automotive parts Boats Boat masts Bridge components Chemical...
Series: ASM Handbook
Volume: 14B
Publisher: ASM International
Published: 01 January 2006
DOI: 10.31399/asm.hb.v14b.a0005122
EISBN: 978-1-62708-186-3
... produce parts with sharp contours or depressions. It is primarily used to make aircraft skin panels, window frames, and automotive door panels. The four methods of stretch forming are: Stretch draw forming ( Fig. 1a and b ) Stretch wrapping, also called rotary stretch forming ( Fig. 1c...
Series: ASM Handbook
Volume: 13C
Publisher: ASM International
Published: 01 January 2006
DOI: 10.31399/asm.hb.v13c.a0004127
EISBN: 978-1-62708-184-9
... and stress-corrosion cracking. Aluminum cladding is used on sheet products, such as fuselage skins, fuel tank divider webs, and other components. Cladding alloys are selected to be anodic to the core alloy and provide cathodic protection to the core. Cladding materials are metallurgically bonded via...
Series: ASM Handbook
Volume: 13A
Publisher: ASM International
Published: 01 January 2003
DOI: 10.31399/asm.hb.v13a.a0003706
EISBN: 978-1-62708-182-5
... crevice corrosion pitting corrosion damage tolerance crack growth crack initiation structural integrity CORROSION FATIGUE has been identified as a significant safety issue in the world aircraft fleets. The in-flight failure of a large section of fuselage on an Aloha Airline Boeing 737 in 1988...