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ATA Chapters

Air transportation Association (ATA) published a numbering system to learn and understand the technical features of an Aircraft The standard numbering system was published by the   Air Transport Association   on June 1, 1956.  While the   ATA 100   numbering system has been superseded, it continued to be widely used until it went out of date back in 2015, especially in documentation for   general aviation   aircraft, on aircraft Fault Messages (for Post Flight Troubleshooting and Repair) and the electronic and printed manuals. This commonality permits greater ease of learning and understanding for   pilots ,   aircraft maintenance technicians , and   engineers . The Joint Aircraft System/Component (JASC) Code Tables was a modified version of the Air Transport Association of America (ATA), Specification 100 code. It was developed by the FAA's, Regulatory Support Division (AFS-600). This code table was constructed by using the new JASC code four digit format, along with an abbreviate
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Lockheed Martin F-35 Lightning II

Ø   The Lockheed Martin F-35 Lightning II is a family of single-seat, single-engine, all-weather stealth multirole fighters. Ø   The fifth-generation combat aircraft is designed to perform ground attack and air superiority missions. Ø   It has three main models: ·        the F-35A conventional takeoff and landing (CTOL) variant, ·        the F-35B short take-off and vertical-landing (STOVL) variant, ·        the F-35C carrier-based Catapult Assisted Take-Off But Arrested Recovery (CATOBAR) variant.                                      Role Stealth   multirole fighter National origin United States Manufacturer Lockheed Martin Aeronautics First flight 15 December 2006 (F-35A) Introduction F-35B: 31 July 2015 ( USMC ) F-35A: 2 August 2016 ( USAF ) F-35C: 2018 ( USN ) Status In service Primary users United States Air Force United States Marin
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Gas Turbine Compressor

PURPOSE OF COMPRESSOR                                     The compressor section of the gas turbine engine has many functions. Its primary function is to supply air in sufficient quantity to satisfy the requirements of the combustion burners. Specifically, to fulfill its purpose, the compressor must increase the pressure of the mass of air received from the air inlet duct, and then, discharge it to the burners in the quantity and at the pressures required.                               A secondary function of the compressor is to supply bleed-air for various purposes in the engine and aircraft. The bleed-air is taken from any of the various pressure stages of the compressor.                              The exact location of the bleed ports is dependent on the pressure or temperature required for a particular job. The ports are small openings in the compressor case adjacent to the particular stage from which the air is to be bled                                Air is often bled
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