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A U.S. Government Specification

A U.S. Government Specification 224 AIRCRAFT ENGINEERING August, 1934 Details of Requirements in a 100 Horse-Power Two- Seater Aeroplane for Inspectors' Use S no doubt most readers of AIRCRAFT glide. It shall also be capable of being flight path, and two vertical planes diverging ENGINEERIN G are aware, during the easily landed with the fuselage at any angle 100 deg. from the flight path, one to the right pas t year or so, discussion, originated with the horizontal from minus 5 deg. to and one to the left; (2) a downward cone of b y the Aeronautics Branch of the U.S. Depart­ th e angle of maximum lift with immediate vision having an included angle of 30 deg., the men t of Commerce, has been proceeding on the an d full application of the brakes. There axis of which lies between vertically downward, possibilities of the production of a really cheap shall be no. tendency to "ground loop" an d 45 deg. forward of vertically downward, "light " aeroplane for the use of private unde r any landing condition. The landing an d (3) an upward cone of vision having an owners. conditions specified herein shall be attain­ included angle of 45 deg. the axis of which able by any pilot having a private pilot's lies between vertically upward and 45 deg. to I n view of this it is interesting to record licence. th e rear of vertically upward. Maximum th e issue by the department of the specifica­ visibility in all other directions is, of course, tion reprinted below, which is backed by an (e) Taxying. The aeroplane shall be desired. invitation for tenders for 25 aeroplanes to the easily controllable on the ground and shall specification for the use of the department's be capable of being brought to a stop from (h) Windshield and windows shall be of a Inspectors. Various details are of interest; a ground speed of 45 m.p.h. in 150 ft. materia l no more inflammable than doped particularly those in regard to the take-off and fabric. landing runs; view and power—which is limited Safety Features Power Plant t o 100 rated horse-power. (a) With power on and power off and with (a) The engine may be cooled in any manner an y possible combination of settings of the and have any arrangement of cylinders but General Specification horizontal stabilizer and elevator, full lateral shall not have less tha n four cylinders. It may (a) Any aircraft purchased under these control shall be provided and there shall be no operate on the four stroke or two stroke cycle. specifications shall meet the airworthiness tendenc y to side slip or spin under these condi­ I t may or may not be geared. It shall not requirements effective July 1st, of the Aero­ tions of flight. develop over 100 h.p. at rated speed. nautics Branch, Department of Commerce, (b) From the maximum nose-up attitude (b) I t must be inherently free from excessive pertainin g thereto. which can be maintained with any and all vibration. (b) The aeroplane design shall be such that settings of the horizontal stabilizer with full (c) I t shall require no servicing at less than maintenance and replacement costs will be as power, sudden loss of power and full upward 50 hour intervals. low as possible. movemen t of the elevator shall not cause the (d) I t shall be capable of operation on any (c) The seating arrangement shall be side by longitudinal axis of the plane to assume a good grade of aviation or automobile fuels and side or staggered not to exceed 45 deg. nose-down attitude exceeding 10 deg. below the oils. (d) The cockpit shall be closed or convertible. horizontal. (e) Dual controls with provision for readily (e) I t shall idle satisfactorily and accelerate (c) Any normal flight attitude shall be making one set ineffective shall be provided. smoothly from all speeds on slow or rapid attainabl e with power on or power off by use (f) The fuselage shall be of all metal con­ opening of the throttle both on the ground and of the elevators, regardless of the setting of the struction. horizontal stabilizer. after long glides. (d) The landing gear shall be capable of Performance ( f) Single ignition may be accepted. accommodating a vertical velocity component The minimum performance with a pilot and (g) Prior to delivery and acceptance of the of 20 ft. per second without overstressing the one passenger (170 lb. each), two parachutes of first aeroplane the engine shall hav e successfully landing gear or other parts of the aeroplane. 20 lb. each and baggage of 40 lb., and fuel and passed all tests required for the attainment of (e) Operation of auxiliary high-lift devices oil sufficient for a cruising range of 300 miles a n approved type certificate. shall not require an independent readjustment against a 10 mile per hour head wind shall be : of the horizontal stabilizer. (a) Maximum speed at rated r.p.m. not Equipment ( f) The aeroplane shall be capable of normal less tha n 110 m.p.h. The following equipment will be provided manœuvrin g including right and left hand (b) Minimum controlled flying speed level for each aeroplane:— turn s up to 20 deg. bank without the use of flight not more than 35 m.p.h. (a) Instruments:—(1) Fuel gauge; (2) alti­ th e rudder and without appreciable skidding or (c) Take off. The aeroplane must be meter ; (3) oil pressure gauge (if required); slipping and without nosing up or down. capable of clearing an obstacle 35 ft. high (4) oil temperature gauge (if required); (5) from a standing start 800 ft. away with no (g) I n all flying attitudes, both pilot and compass ; (6) tachometer; (7) bank and turn wind, at sea level. passenger by movement of the head and indicator ; (8) air speed indicator. (d) Landing. The aeroplane shall be shoulders only shall have an unobstructed view capable of being brought to a stop within in the following sectors: (1) A forward sector (b) Accessories:—(1) Navigation lights; (2) 400 ft. of a 35 ft. obstacle, which it has bounded by a plane inclined 5 deg. below the liquid battery ; (3) engine starter ; (4) genera­ cleared, in a straight and fully controlled flight path, a plane inclined 20 deg. above the tor ; (5) parking brake. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

A U.S. Government Specification

Aircraft Engineering and Aerospace Technology , Volume 6 (8): 1 – Aug 1, 1934

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029834
Publisher site
See Article on Publisher Site

Abstract

224 AIRCRAFT ENGINEERING August, 1934 Details of Requirements in a 100 Horse-Power Two- Seater Aeroplane for Inspectors' Use S no doubt most readers of AIRCRAFT glide. It shall also be capable of being flight path, and two vertical planes diverging ENGINEERIN G are aware, during the easily landed with the fuselage at any angle 100 deg. from the flight path, one to the right pas t year or so, discussion, originated with the horizontal from minus 5 deg. to and one to the left; (2) a downward cone of b y the Aeronautics Branch of the U.S. Depart­ th e angle of maximum lift with immediate vision having an included angle of 30 deg., the men t of Commerce, has been proceeding on the an d full application of the brakes. There axis of which lies between vertically downward, possibilities of the production of a really cheap shall be no. tendency to "ground loop" an d 45 deg. forward of vertically downward, "light " aeroplane for the use of private unde r any landing condition. The landing an d (3) an upward cone of vision having an owners. conditions specified herein shall be attain­ included angle of 45 deg. the axis of which able by any pilot having a private pilot's lies between vertically upward and 45 deg. to I n view of this it is interesting to record licence. th e rear of vertically upward. Maximum th e issue by the department of the specifica­ visibility in all other directions is, of course, tion reprinted below, which is backed by an (e) Taxying. The aeroplane shall be desired. invitation for tenders for 25 aeroplanes to the easily controllable on the ground and shall specification for the use of the department's be capable of being brought to a stop from (h) Windshield and windows shall be of a Inspectors. Various details are of interest; a ground speed of 45 m.p.h. in 150 ft. materia l no more inflammable than doped particularly those in regard to the take-off and fabric. landing runs; view and power—which is limited Safety Features Power Plant t o 100 rated horse-power. (a) With power on and power off and with (a) The engine may be cooled in any manner an y possible combination of settings of the and have any arrangement of cylinders but General Specification horizontal stabilizer and elevator, full lateral shall not have less tha n four cylinders. It may (a) Any aircraft purchased under these control shall be provided and there shall be no operate on the four stroke or two stroke cycle. specifications shall meet the airworthiness tendenc y to side slip or spin under these condi­ I t may or may not be geared. It shall not requirements effective July 1st, of the Aero­ tions of flight. develop over 100 h.p. at rated speed. nautics Branch, Department of Commerce, (b) From the maximum nose-up attitude (b) I t must be inherently free from excessive pertainin g thereto. which can be maintained with any and all vibration. (b) The aeroplane design shall be such that settings of the horizontal stabilizer with full (c) I t shall require no servicing at less than maintenance and replacement costs will be as power, sudden loss of power and full upward 50 hour intervals. low as possible. movemen t of the elevator shall not cause the (d) I t shall be capable of operation on any (c) The seating arrangement shall be side by longitudinal axis of the plane to assume a good grade of aviation or automobile fuels and side or staggered not to exceed 45 deg. nose-down attitude exceeding 10 deg. below the oils. (d) The cockpit shall be closed or convertible. horizontal. (e) Dual controls with provision for readily (e) I t shall idle satisfactorily and accelerate (c) Any normal flight attitude shall be making one set ineffective shall be provided. smoothly from all speeds on slow or rapid attainabl e with power on or power off by use (f) The fuselage shall be of all metal con­ opening of the throttle both on the ground and of the elevators, regardless of the setting of the struction. horizontal stabilizer. after long glides. (d) The landing gear shall be capable of Performance ( f) Single ignition may be accepted. accommodating a vertical velocity component The minimum performance with a pilot and (g) Prior to delivery and acceptance of the of 20 ft. per second without overstressing the one passenger (170 lb. each), two parachutes of first aeroplane the engine shall hav e successfully landing gear or other parts of the aeroplane. 20 lb. each and baggage of 40 lb., and fuel and passed all tests required for the attainment of (e) Operation of auxiliary high-lift devices oil sufficient for a cruising range of 300 miles a n approved type certificate. shall not require an independent readjustment against a 10 mile per hour head wind shall be : of the horizontal stabilizer. (a) Maximum speed at rated r.p.m. not Equipment ( f) The aeroplane shall be capable of normal less tha n 110 m.p.h. The following equipment will be provided manœuvrin g including right and left hand (b) Minimum controlled flying speed level for each aeroplane:— turn s up to 20 deg. bank without the use of flight not more than 35 m.p.h. (a) Instruments:—(1) Fuel gauge; (2) alti­ th e rudder and without appreciable skidding or (c) Take off. The aeroplane must be meter ; (3) oil pressure gauge (if required); slipping and without nosing up or down. capable of clearing an obstacle 35 ft. high (4) oil temperature gauge (if required); (5) from a standing start 800 ft. away with no (g) I n all flying attitudes, both pilot and compass ; (6) tachometer; (7) bank and turn wind, at sea level. passenger by movement of the head and indicator ; (8) air speed indicator. (d) Landing. The aeroplane shall be shoulders only shall have an unobstructed view capable of being brought to a stop within in the following sectors: (1) A forward sector (b) Accessories:—(1) Navigation lights; (2) 400 ft. of a 35 ft. obstacle, which it has bounded by a plane inclined 5 deg. below the liquid battery ; (3) engine starter ; (4) genera­ cleared, in a straight and fully controlled flight path, a plane inclined 20 deg. above the tor ; (5) parking brake.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Aug 1, 1934

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