SAE ARP 4101 1-1990 Seats and Restraint Systems for the Flight Deck《飞行甲板座椅和约束系统[代替 SAE ARP 682C SAE ARP 682B]》.pdf

1、AEROSPACE RECOMMENDED PRACTICEARP4101/1Issued 1990-03Reaffirmed 2007-07Seats and Restraint Systems for the Flight DeckFOREWORDChanges in this reaffirm are format/editorial only.1. SCOPE:This document establishes the minimum requirements for seats and restraint systems for the flight deck.Due to limi

2、tations that it would place upon basic aircraft design, it is not considered practical for these requirements to apply fully to the observer seat. However, it is emphasized that every effort should be made to provide the observer seat position with an equivalent level of comfort and safety.This docu

3、ment is also intended to make recommendations for flight crew restraint systems. A properly designed crew restraint system will minimize injury or debilitation during a survivable crash and enable post crash assistance to occupants and escape from the aircraft.Crew member safety is the primary objec

4、tive, with appropriate provisions for crew comfort taken into consideration. The criteria established herein are designed to standardize restraint systems without hindering the development of new, improved systems.2. REFERENCES:2.1 Documentation:- ARP4101, Flight Deck Layout and Facilities- ARP4102,

5、 Flight Deck Panels, Controls and Displays- ARP4105, Nomenclature and Abbreviations for Use on the Flight Deck- AS8043, Torso Restraint Systems- MIT PRESS 1975 Cambridge, MA, Henry Dreyfuss Association, “Human Scale 1, 2, and 3”- JAR/FAR 25.853(b), Fire Blocking RequirementsSAE Technical Standards B

6、oard Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising therefrom, is the sole responsib

7、ility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2007 SAE International All rights reserved. No part of this publication may be reproduced, stored in

8、 a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: 724-776-4970 (outside USA) Fax: 724-776-0790 Email: C

9、ustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org RATIONALE This document has been reaffirmed to comply with the SAE 5-Year Review policy. SAE ARP4101/1 - 2 -2.2 Definitions:2.2.1 Seat Reference Point: The intersection of a tangent to the surface of the bottom of a seated persons buttocks and

10、 a line through the seat back cushion representative of a back tangent line when in a compressed state under the load of a 50th percentile, 175 cm, 77 kg (59“, 170 lb) person.3. OPERATIONAL REQUIREMENTS:3.1 Construction:The surfaces of the seat shall be free from sharp edges or projections which may

11、 cause damage to the safety belt, shoulder harness or the clothing of the occupant. The exterior surfaces of the seat shall be free from sharp edges or any projections which might scratch the hands or the clothing of the occupant while moving his/her arms about the sides of the seat to handle equipm

12、ent within reach to the rear and to the sides, and to operate the seat-adjustment mechanisms.No seat position or portion of the seat shall in any way interfere with the full range of any flight control handle, column, or other controlling device.3.2 Cushion:The cushion shall be constructed to provid

13、e optimum comfort (either by contouring and/or by variation of stiffness of the cushion material) and durability. Cushion material shall also provide adequate ventilation to minimize discomfort due to body perspiration and meet the requirements of JAR/FAR 25.853(b), with respect to fire blocking. Th

14、e cushion material should be of such firmness as to provide a stable platform for seating. It should not be possible to feel any structure through the cushion. The cushion shall not touch the control column when it is in the full rear position and the seat is fully forward. The combination of the se

15、at bottom and seat cushion shall be such that the seat will not “bottom“ while occupied by a 90 kg (198 lb) person.It is desirable that the cushion be covered by a material such as sheepskin to optimize comfort.3.3 Dynamics:The seat cushions, seat and seat-to-aircraft attach structure shall be desig

16、ned such that for all reasonable crew member weights (using normal lap restraint and shoulder harness restraint provisions), there is no resulting amplification of crew member motion particularly at the basic aircraft response frequencies generated by turbulent flight conditions. The cushion materia

17、l shall be selected for resistance to permanent deformation and excessive compaction.SAE ARP4101/1 - 3 -3.4 Seat Adjustment:3.4.1 Vertical Adjustment: The seat shall be adjustable vertically through a range of at least 180 mm (7 in) in increments of no greater than 12 mm (1/2 in) throughout the enti

18、re range. The lowest adjustment shall place the seat reference point at least 876 mm (34.5 in) below the design eye position as shown in Figure 1, and the highest adjustment point no more than 700 mm (27.5 in) below the design eye position. It shall be possible to achieve the eye level position equi

19、valent adjustment with the seat cushion depressed. The vertical adjustment shall incorporate a means of raising the seat freely to the maximum up-position. If a mechanical system is employed, it should not require a lifting force of greater than 23 kg (50 lb) (less is desirable) to lift a 90 kg (198

20、 lb) person, and no additional force to lower a 57 kg (125 lb) person. An appropriate hand-hold should be installed. Up and down travel shall be free with no binding and the mechanism should be of such a design that it is easy to keep free. Adjustment through the full vertical range shall be easy wh

21、ile seated and shall not restrict the fore or aft adjustment range.3.4.2 Angular Adjustment of Back: The seat back shall be adjustable throughout an angle of from at least 95 degrees from seat bottom to 115 degrees as shown in Figure 1. The back should be adjustable in no greater than 2 degree incre

22、ments from the most erect position to the 105 degree position, and in no greater than 5 degree increments for the remainder for the total aft adjustment range.3.4.3 Head Rest: None required, but provisions should be made for a vertically adjustable head rest for recline angles greater than 30 degree

23、s.3.4.4 Angular Adjustment of Seat: The seat shall support the body so that there is no tendency to slide forward. The angle between the body and the upper leg should not be less than 90 degrees to prevent cramping of the anterior muscles.3.4.5 Fore and Aft Adjustment: The seat shall be adjustable i

24、n the fore and aft direction for a distance of not less than 150 mm (6 in) 250 mm (10 in) is desirable in increments of not more than 25 mm(1 in). In all cases, the travel shall be sufficient to permit easy access to the seat and clearance with normal control movements in cruise for a 315 mm (12.4 i

25、n) flight manual place on the lap. Inboard-outboard adjustment may be included to improve access to the seat. Such adjustment should occur only at the most aft position.Emergency egress shall be possible when the seat is jammed in any position. Movement through the total fore and aft adjustment rang

26、e shall not restrict the full vertical adjustment range. The seat in the full forward and up position shall not restrict the full range of the primary flight controls.3.4.6 Kidney Support: Kidney support in the lumbar area, curved slightly to fit across the back of the seat occupant, shall be provid

27、ed. It should be easily adjustable while seated. Both forward and rearward adjustment relative to the seat back and 76 mm (3 in) of vertical adjustment should be provided.SAE ARP4101/1 - 4 -3.4.7 Thigh Support: The seat shall have an adjustable thigh support on the forward part. It should have a con

28、tinuously adjustable range of 102 mm (4 in) in the vertical plane.3.4.8 Power Operated Seats: The speed of movement in any direction shall not exceed 42 mm/s(1.65 in/s) when motorized. An immediately accessible master on/off or stall force clutch switch or other means should be provided to rapidly s

29、top a runaway seat.3.4.9 Arm Rests: Arm rests shall be provided on each side of the seat and shall fold to a position and remain where they will minimize interference with egress or ingress of the occupant. When in extended or folded position, the arm rests shall not interfere with the normal moveme

30、nts or view of the instrument panels by the pilot in the operation of the aircraft. The forward part of the arm rests should be adjustable in the vertical plane in increments of not more than 12 mm (1/2 in) from a position 203 mm (8 in) to 318 mm (12.5 in) above the seat reference point. The arm res

31、ts shall be padded for a minimum length of 279 mm (11 in) forward of the vertical plane through the seat reference point. The top surface of the arm rests should have a flat or slightly concave padded elbow bearing surface not less than 64 mm (2.5 in) wide. The arm rest adjustment should be a simple

32、 one-hand operation.4. NOT APPLICABLE:5. CONTROLS:5.1 Seat Adjustment and Locking:All adjusting and locking controls shall be easily accessible to the occupant and these controls should be grouped together. They should be easily operable with the use of only one hand while seated in the seat, or fro

33、m outside the seat when occupied or not occupied. All adjustment controls shall be positive actuating to prevent unlocking or slipping. The controls shall not interfere with ingress or egress.Individual adjusting levers should be appropriately labeled and shape coded to indicate their function to th

34、e seat occupant (for example, fore-aft, up-down, recline). When a mechanical lever-type control is utilized, the movement of the lever shall not exceed 50 degrees and the mechanism shall automatically lock when the lever is released. This type of locking mechanism shall be released by an upward move

35、ment of the lever. Remotely actuated devices shall have the controls located so as to permit access to the seat.5.2 Power Controls:The controls shall be protected from inadvertent operation and the direction of movement of the control switch(es) shall result in seat movement in the same direction.Me

36、ans shall be provided to permit adjusting the seat in case of failure of the power operated device(s). Such alternate means should be readily accessible to the pilot although they need not necessarily be located in accordance with this paragraph.SAE ARP4101/1 - 5 -5.3 Location:For either mechanical-

37、 or electrical-type locking mechanism, the location of the actuating handle or switch should be as follows (except that in case of an electrically adjusted seat, a unitary-type switch control may be used, in which case it should be centrally located on the side of the seat bottom):Fore and Aft Adjus

38、tment: At approximately the fore and aft midpoint of the seat and as high as possible so as to minimize the need for bending in order to reach the controls.Vertical Adjustment: Towards the forward corner of the seat bottom.Back Angle Adjustment: Towards the back edge of the seat bottom, the most aft

39、 control.Thigh Support Adjustment: The most forward control.Kidney Support Adjustment: Towards the back of the seat, above the back angle adjustment.These mechanisms shall positively lock the seat in position without seat wobble or fore and aft motion.5.4 Restraint System:5.4.1 General:5.4.1.1 All s

40、traps and hardware (adjusters, releases, attaching end fittings, structural attachments, etc.) in the restraint system shall be designed and installed to avoid bodily injury to crew members under all normal and emergency conditions and not cause significant wear or damage to clothing. Placement of h

41、ardware against skeletal or other easily injured parts of the body shall be especially avoided.5.4.2 Shoulder Harness:5.4.2.1 Operation: Seat back height specifications of Figure 1 are based on considerations of comfort and convenience. If the seat back incorporates provision for shoulder harness at

42、tachment, this attachment height shall be great enough to prevent the shoulder harness from imposing dangerous down loads on the occupant under survivable crash conditions, and from imposing uncomfortable down loads under routine operating conditions. The shoulder harness leads from the seat back ar

43、ea shall be such that the harness will not slide off the pilots shoulders or chafe the neck.The harness should be easy to don, adjust and remove, yet should not be susceptible to inadvertent release during the dynamics of the crash impact. The device should permit ample upper torso freedom so that t

44、he crew member can efficiently and comfortably carry out the regular duties under all operating conditions.SAE ARP4101/1 - 6 -5.4.2.2 Installation: The shoulder harness should be installed in such a manner as to prevent snagging of the straps. Strap splices should pass freely through harness guides

45、or fittings. The point from which the harness comes over the shoulder should be at or above the shoulder level of the occupant while sitting in a normal position; however, the harness should not exceed 45 degrees above the horizontal plane through the shoulder level.The adjustment should be positive

46、, simple, and easy to operate. The load imposed on the body by the retraction tension of the device shall be negligible when the occupant is sitting in a normal position. Stowage of the shoulder harness should be automatic so as to prevent entanglement with the seat itself or with any adjacent struc

47、ture. The harness shall be installed to accommodate the ranges of body component dimensions.5.4.2.3 Harness Reel: When required as a function of flight deck design, an inertia reel or a similar device shall be provided to allow ample torso movement of the crew member thereby permitting full operatio

48、n of the aircraft under all conditions. Single or dual reels may be used; however, dual reels shall be designed for simultaneous lockup within a 1.0 g lockup tolerance. Acceleration forces of more than 2.0 g and less than 3.0 g (or equivalent accelerations or strap “payout“ rate) applied in any dire

49、ction, causing the torso of the crew member to move away from the seat back, shall activate the lock device within 60 ms. The crew member shall be automatically and positively restrained when the aforementioned accelerations occur.If the crew member is leaning away from the seat during acceleration in any direction, the devices should automatically reel in when returning to a normal sitting position and relock if the force or acceleration is still being applied or is later reapplied. When the shoulder harness is released, the component design and/or the ret