By W. A. Harrison, Andrew Probert, Richard Hudson, Don Greer
Fairey Swordfish In motion КНИГИ ;ВОЕННАЯ ИСТОРИЯ Fairey Swordfish In motion (Aircraft quantity 175)ByW.A. HarrisonPublisher:Squadron/Signal courses Inc.2001 fifty two PagesISBN: 089747421XPDF15 MBThe British Fleet Air Arm (FAA) operated 3 major varieties of airplane through the Twenties and Thirties: the fleet fighter, the torpedo-bomber, and the spotter-reconnaissance airplane. those aircraft operated from the Royal Navy's fleet of airplane providers, which totaled six via 1930. In 1933. the Fairey Aviation corporation submitted a layout which mixed a few of these 3 roles and met different standards already issued by way of the British Air Ministry. The ensuing aircraft, by way of Fairey clothier Marcclle Lunelle, was once often called the TSR I (Torpedo-Spotter-Reconnaissancc). It was once to be powered by means of a 525 horsepower (hp) Rolls-Royce Kestrel v-12. liquid-cooled in-line engine. The plane will be in a position to simply switching from a wheeled undercarriage to floats for waterbome operations.sharingmatrix letitbit zero
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Extra info for Fairey Swordfish In Action
4 • Flap, aileron, k ~ nacelle \\\~contact Fig. 11 Pitch and roll limitation diagram. ~ 2 m 0 0 m i 2 4 Aircraft t. / I1. :. , m z..... J ~F--. IF- T¢: 41 I el 42 AIRCRAFT LANDING GEAR DESIGN The following checks are suggested: I) Are the nose and main gear shock struts operating properly and the tires at normal inflation? 2) Is the nose gear shock strut fully compressed and the tire flat? Is the main gear shock strut fully compressed and the tire flat on one side, with static deflection and normal tire inflation on the other side?
During taxi tests, the normal and emergency brake systems are evaluated along with the skid control and steering system. Stop distances are compared with predictions and the aircraft is maneuvered to examine steering and damping with normal and emergency systems. Shimmy tests are also conducted. Demonstrations are conducted to show how towing, jacking, and mooring requirements have been met and, then, with the aircraft on jacks, a thorough 24 AIRCRAFT LANDING GEAR DESIGN inspection is made again of the landing gear and its proper functioning before first flight.
The report that accompanies these drawings shall indicate tire sizes, tire inflation pressures, design sink speeds, total air volume, and isothermal pressure in the extended, static, and compressed shock absorber positions at maximum takeoff gross weight, as well as the preliminary loads imposed upon the landing gear (USN). The shock strut efficiency obtained during the drop test shall not be less than 75% using the following formula: Efficiency, % - A LxS where A is the energy absorbed by the strut during its stroke (obtained by integrating the area beneath the strut Ioadstroke curve), L the maximum load (in pounds) obtained during the stroke, and S the maximum stroke obtained during the test (USAF/USN).