| タイトル | Aircraft Design Considerations to Meet One Engine Inoperative (OEI) Safety Requirements |
| 本文（外部サイト） | http://hdl.handle.net/2060/20120016833 |
| 著者（英） | Scott, Mark W. |
| 著者所属（英） | Sikorsky Aircraft Corp. |
| 発行日 | 2012-08-01 |
| 言語 | eng |
| 内容記述 | Commercial airlines are obligated to operate such that an aircraft can suffer an engine failure at any point in its mission and terminate the flight without an accident. Only minimal aircraft damage is allowable, such as brake replacement due to very heavy application, or an engine inspection and/or possible removal due to use of an emergency rating. Such performance criteria are often referred to as zero exposure, referring to zero accident exposure to an engine failure. The critical mission segment for meeting one engine inoperative (OEI) criteria is takeoff. For a given weight, wind, and ambient condition, fixed wing aircraft require a balanced field length. This is the longer of the distance to take off if an engine fails at a predetermined critical point in the takeoff profile, or the distance to reject the takeoff and brake to a stop. Rotorcraft have requirements for horizontal takeoff procedures that are equivalent to a balanced field length requirements for fixed wing aircraft. Rotorcraft also perform vertical procedures where no runway or heliport distance is available. These were developed primarily for elevated heliports as found on oil rigs or rooftops. They are also used for ground level operations as might be found at heliports at the end of piers or other confined areas. |
| NASA分類 | Air Transportation and Safety |
| レポートNO | ARC-E-DAA-TN5707
NASA/CR-2012-216037 |
| 権利 | Copyright, Distribution under U.S. Government purpose rights |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/240033 |
