ASTM F2242-2005 Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft《动力伞降飞行器的生产验收试验系统的标准规范》.pdf

《ASTM F2242-2005 Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft《动力伞降飞行器的生产验收试验系统的标准规范》.pdf》由会员分享，可在线阅读，更多相关《ASTM F2242-2005 Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft《动力伞降飞行器的生产验收试验系统的标准规范》.pdf（2页珍藏版）》请在麦多课文档分享上搜索。

1、Designation: F 2242 05Standard Specification forProduction Acceptance Testing System for PoweredParachute Aircraft1This standard is issued under the fixed designation F 2242; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year

2、 of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon (e) indicates an editorial change since the last revision or reapproval.1. Scope1.1 The following requirements apply for the manufacturepowered parachute aircraft. This specification includes thepr

3、oduction acceptance test requirements for powered parachuteaircraft.1.2 This specification applies to powered parachute aircraftseeking civil aviation authority approval, in the form of flightcertificates, flight permits, or other like documentation.1.3 This standard does not purport to address all

4、of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory requirements prior to use.2. Terminology2.1 Definitions:2.1.1 powered parachute, naircraft

5、 comprised of a flex-ible or semi-rigid wing connected to a fuselage in such a waythat the wing is not in position for flight until the aircraft is inmotion. This aircraft has a fuselage with seats, engine, andwheels (or floats), such that the wing and engine cannot beflown without the wheels (or fl

6、oats) and seat(s). Unique to thepowered parachute is the large displacement between thecenter of lift (high) and the center of gravity (low), which ispendulum effect. Pendulum effect limits angle of attachchanges, provides stall resistance and maintains flight stability.3. Significance and Use3.1 Th

7、e purpose of this specification is to provide theminimum requirements for the establishment of a ground andflight test program for verifying the initial (first run) productionaircraft meets certain operational performance requirementsthat have been set forth by the manufacturer in its AircraftOperat

8、ing Instructions.3.2 In addition, this specification provides minimum re-quirements to verify that each subsequent production airplanehas no obvious defects that would prevent the safe operation ofthe airplane.4. Production Acceptance Testing, Ground Testing4.1 Inspection VerificationThere shall be

9、a written proce-dure in effect to verify all top-level inspections have beencompleted and no discrepancies remain open.4.2 Engine Break-InThere shall be a written procedure ineffect to perform the engine break-in. This procedure mayinclude all engine gage verification of operation. All enginereading

10、s shall achieve the normal accepted range of readingscommensurate with a new engine. If not performed duringengine break-in, then this verification must be performed underseparate procedures. All engine gages shall be verified to beoperating.5. Production Acceptance Testing, Flight Testing5.1 Every

11、production aircraft shall be flight tested to thefollowing minimums:5.1.1 Powered ParachutesFifteen minutes flight time,including at least one takeoff and landing, trimming of flightcontrols, and verification of control for left turn, right turn, andflare (flare only is so equipped).5.2 Instrument V

12、erificationThere shall be a written proce-dure in effect to verify that all other instruments are operatingwithin normal ranges. If equipped with a compass, the compassvariation card data shall be developed with the engine running.6. Post Flight Acceptance6.1 There shall be a written procedure in ef

13、fect to performpost flight inspection that will review all flight critical attach-ments and structures.6.2 The reviewing personnel shall sign all post flight reviewdocuments.1This specification is under the jurisdiction of ASTM Committee F37 on LightSport Aircraft and is the direct responsibility of

14、 Subcommittee F37.30 on PowerParachute.Current edition approved March 1, 2005. Published March 2005. Originallyapproved in 2003. Last previous edition approved in 2003 as F 2242 03.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.7. D

15、ocumentation7.1 There shall be a written procedure in effect to properlydocument and store the production acceptance test results suchthat they are correlated to the specific aircraft for futurereference.7.2 Test Failures:7.2.1 There shall be a written procedure in effect to reviewthe causes for any

16、 aircraft failures in the production acceptancetests phases. Aircraft may only be released for retest aftermanufacturing review of the discrepant articles and writtenrelease for retest.8. Keywords8.1 light sport aircraft; powered parachute aircraft; specialairworthiness certificateASTM International

17、 takes no position respecting the validity of any patent rights asserted in connection with any item mentionedin this standard. Users of this standard are expressly advised that determination of the validity of any such patent rights, and the riskof infringement of such rights, are entirely their ow

18、n responsibility.This standard is subject to revision at any time by the responsible technical committee and must be reviewed every five years andif not revised, either reapproved or withdrawn. Your comments are invited either for revision of this standard or for additional standardsand should be ad

19、dressed to ASTM International Headquarters. Your comments will receive careful consideration at a meeting of theresponsible technical committee, which you may attend. If you feel that your comments have not received a fair hearing you shouldmake your views known to the ASTM Committee on Standards, a

20、t the address shown below.This standard is copyrighted by ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959,United States. Individual reprints (single or multiple copies) of this standard may be obtained by contacting ASTM at the aboveaddress or at 610-832-9585 (phone), 610-832-9555 (fax), or serviceastm.org (e-mail); or through the ASTM website(www.astm.org).F2242052