1、 SAE Technical Standards Board 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 there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions.Copyright 2013 SAE International All rights reserved. No part of this pu
3、blication may be reproduced, stored in 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: +1 724-776-4970
4、 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/ARP1409CAEROSPACERECOMMENDED PRACTICEARP1409 REV. CIssued 1978-01 Revised 2003-03 R
5、eaffirmed 2013-08 Superseding ARP1409B (R) Aircraft On Board Weight and Balance System Requirements RATIONALEARP1409C has been reaffirmed to comply with the SAE five-year review policy. 1. SCOPE:This SAE Aerospace Recommended Practice (ARP) establishes requirements for the function, characteristics,
6、 and installation of an aircraft On Board Weight and Balance System (OBWBS) for use on civil transport aircraft. This document is not intended to specify design methods, mechanisms, or material to accomplish the requirements set forth.2. REFERENCES:2.1 Applicable Documents:The following publications
7、 form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited h
8、erein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.2.1.1 SAE Publications: Available from SAE, 400 Commonwealth Drive, Warrendale, PA 15096-0001.ARP4102/1 On Board Weight and B
9、alance SystemCopyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2.1.2 ARINC Publications: Available from ARINC, 2551 Riva Road, Annapolis, MD 21401-7465.ARINC 429ARINC 537ARINC 573ARINC 717ARINC/AEEC 73
10、7ARINC NIC 600Radio Technical Commission for Aeronautics (RTCA) Document No DO-160D, changes 1 and 2, Environmental Conditions and Test Procedures for Airborne Electronic/Electrical and Instruments2.2 Other Reference Documents:2.2.1 ISO Publications: Available from ANSI, 25 West 43rd Street, New Yor
11、k, NY 10036-8002.ISO 6702-1 AircraftRequirements for on-board weight and balance systems - Part 1: General (corresponds to the present ARP)ISO 6702-2 AircraftRequirements for on-board weight and balance systems - Part 2: Design, performance and interface characteristics (corresponds to the ARINC/AEE
12、C 737 document)2.2.2 EUROCAE Documents: Available from EUROCAE, European Organization for Civil Aviation Equipment, 11 rue Hamelin, F-75783 Paris CEDEX 16, France:EUROCAE/ED-14D (corresponds to the RTCA DO-160D document)3. DESCRIPTION:The aircraft OBWBS shall provide a direct accurate measurement an
13、d display of the actual aircraft weight and center of gravity location under ground, preferably static, conditions. Optional functions, such as noted herein, may be included. The system shall function independent of any system external to the aircraft with the exception of ground electrical power wh
14、en ships power is not available.This document establishes requirements for three classes of aircraft OBWBS:a. Class I system shall be high accuracy/performance, very high level of confidence, systems capable of measuring and displaying both aircraft weight and aircraft balance condition.b. Class II
15、systems shall be high level of confidence systems that do not meet the accuracy requirements of Class I systems, while capable of measuring and displaying both aircraft weight and aircraft balance condition.c. Class III systems shall be high level of confidence systems that do not meet the accuracy
16、requirements of Class I systems, capable of measuring and displaying only the aircraft balance condition.SAE INTERNATIONAL ARP1409C Page 2 of 20_Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3. (Co
17、ntinued):“Level of confidence“, in the context of this document, is intended to mean the overall measurement validity resulting from the following factors:a. Measurement accuracyb. Statistical interval of confidencec. Probability of undetected system failure at dispatch (including the effect of any
18、built-in redundancies/duplications)4. WEIGHT AND BALANCE SYSTEM OBJECTIVES:The objective of Class I OBWBS shall be to provide at least as accurate weight and balance information as can be provided by established ground procedures and equipment for weight and balance control.The objective of Class II
19、 or Class III OBWBS shall be to provide a reliable means of detecting major errors in the weight and balance condition determined by ground procedures and equipment, before aircraft takeoff. Class II or Class III systems may not be used to meet the requirements of Class I systems.The general objecti
20、ve for the overall level of confidence, as defined in Section 3, shall be:a. 99.7% minimum for Class I OBWBS (very high level of confidence)b. 95% minimum for Class II or Class III OBWBS (high level of confidence)5. PART I: REQUIREMENTS FOR CLASS I ON BOARD WEIGHT AND BALANCE SYSTEM:The system shall
21、 determine actual aircraft weight and center of gravity location as follows:5.1 Range of Operation:5.1.1 Weights: The system shall determine and display the aircraft weight at least throughout a range from 10% less than aircraft empty weight to 15% greater than maximum taxi gross weight. Overflow in
22、dication shall be provided if calculated weight exceeds maximum displayable value.5.1.2 Center of Gravity: The system shall determine and display the aircraft center of gravity location throughout a system range determined as follows:Determine aircraft maximum center of gravity range expressed in Pe
23、rcent of Reference Chord such as mean aerodynamic chord (MAC) or equivalent by subtracting most forward limit from most aft limit. Extend most forward aircraft limit forward by an amount equal to 50% of the aircraft range or 20% MAC forward of the forward design limit, whichever is further forward.E
24、xtend most aft aircraft limit aft by an amount equal to 50% of the aircraft range, or 20% aft of the static aft tipping point, whichever is further aft.SAE INTERNATIONAL ARP1409C Page 3 of 20_Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networkin
25、g permitted without license from IHS-,-,-5.1.2.1 Lateral Center of Gravity: Where required for a specific aircraft usage the system shall be capable of determining the lateral center of gravity of the aircraft throughout a symmetric envelope 10% greater than the aircraft certified lateral center of
26、gravity limits.5.2 Mode of Operations:The system shall determine the aircraft weight and center of gravity location in both the ground static mode and the taxiing mode and shall automatically compensate for the following factors:5.2.1 Any combination of ramp slopes up to 3%, aircraft pitch and/or ro
27、ll attitude changes up to +3% in excess of the established range of aircraft ground handling attitude excursion.5.2.2 Aircraft brakes locked or released.5.2.3 Landing gear steering set for zero to minimum turning radius.5.2.4 Continuous aircraft brakes temperature variations from 20 C (68 F) above m
28、aximum temperature permitted for dispatch through cool down to ambient.5.2.5 The 50% variations of normal landing gear oleo strut pressure for any permissible degree of strut extension.5.2.6 The 60 kt wind, or aircraft maximum ground operations limit, whichever is lower, through an azimuth of 360. T
29、he system shall provide steady weight/center of gravity indications under wind gusts up to a minimum 10 kt differential. Manual input of average wind and azimuth is acceptable.5.2.7 Any combination of operating engines from zero to ground taxiing/maneuvering thrust, over the aircrafts approved range
30、 of airport elevation.5.2.8 Any effect of loading or unloading aircraft, or transferring load or fuel on board.5.2.9 Landing gear tilt hydraulic system on or off.5.3 Accuracy:The system shall be capable of determining and displaying actual aircraft weight and center of gravity within 1.0% of actual
31、aircraft weight and 1.0% of Reference Chord (MAC or equivalent).Lateral center of gravity if required shall be determined and displayed within 3.0% of the lateral center of gravity range.As an objective, the above accuracy shall be guaranteed within 3 standard deviations.5.4 Response Time:The system
32、 shall respond to a command to continuously display weight and center of gravity location within 1 min after initial self-test.SAE INTERNATIONAL ARP1409C Page 4 of 20_Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without licen
33、se from IHS-,-,-5.5 System Components:The system shall consist of the minimum components required to perform the functions defined by this document. A typical system may consist of four subsystems, eventually duplicated, plus connecting lines or cabling; the Display Unit, the Computer Unit, the Cali
34、bration Unit and the Sensors. No external equipment, ramps, stabilizer or temporary aircraft-to-ground supports shall be required.5.5.1 Component Description:5.5.1.1 Display Unit: The unit shall display a continuous digital readout of aircraft weight to nearest 100 kg or 100 lb in four lighted digit
35、s of 6.3 mm (0.25 in) minimum size. It shall display a continuous digital readout of aircraft center of gravity location to nearest 0.1 % of Reference Chord (MAC or equivalent) in three lighted digits of 6.3 mm (0.25 in) minimum size. The readout shall be visible in conditions of full sunlight to to
36、tal darkness intensity shall be controlled by normal cockpit instrument lighting controls, unless individual controls are provided.The display unit shall contain all controls necessary to operate and self-test the system. If controls are required for in-flight adjustment, they shall be located on th
37、e display unit. The display unit shall provide separate indication when preset weight and center of gravity location limits are exceeded, or the system is operating in degraded mode, if these options are exercised (see Section 6).The display unit location, actuation and integration into flight deck
38、controls shall comply with ARP4102/1 requirements.5.5.1.2 Computer Unit: The computer unit shall perform the operations required by the system functions. The unit shall have provisions for signal outputs to additional remote display units and signal outputs when preset weight and center of gravity l
39、imits are exceeded. The computer shall provide at the display unit or through a centralized display system a malfunction warning indication whenever a system failure occurs or the error on either aircraft weight or center of gravity location exceeds preset limits. It shall include controls or provis
40、ions for malfunction troubleshooting. The unit shall have provisions for ARINC 429 outputs for use by external monitoring equipment such as AIDS.It shall be possible to replace the computer unit without requiring system recalibration.5.5.1.3 Sensors: The sensors shall detect changes in aircraft weig
41、ht and attitude and transmit them to the computer unit. Number, mounting, and location of sensors shall be determined by the specific aircraft and system design. Devices to overcome landing gear system friction if required and attitude sensors shall be considered a part of the sensor subsystem.5.5.1
42、4 Calibration Unit: All calibration data shall be stored in a calibration unit, which shall remain with the aircraft when other components are replaced, to prevent the need for recalibration. The calibration unit shall contain the controls necessary to adjust the system to read within the specified
43、 accuracy limits on a particular aircraft. These controls shall be protected from unauthorized or inadvertent use.SAE INTERNATIONAL ARP1409C Page 5 of 20_Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,
44、5.5.2 Component Dimensions, Compatibility and Interface: The OBWBS components shall meet the dimensions, compatibility, interface, and interchangeability criteria set forth in ARINC/AEEC 737 specification.5.5.3 Power Supply Requirements: The system shall operate from aircraft electrical power. Th
45、e system shall also operate when the aircraft is powered from a ground power source, and shall continue to operate without interruption after normal system transients or power interruptions (e.g., changeover from ground power to aircraft power).5.5.4 Weight: System weight shall be minimized consiste
46、nt with function, maintenance, and reliability requirements. Design objective of the system weight, less connecting lines or cables, shall not exceed 22.7 kg (50 Ib).5.6 Environmental and Functional Requirements:The system shall meet the requirements of Radio Technical Commission for Aeronautics (RT
47、CA) Document No DO-160D as follows:5.6.1 All components within the pressurized fuselage shall meet DO-160D equipment category A-2 requirements for temperature and altitude.5.6.2 All other components shall meet DO-160D equipment category D-2 and E-2 requirements for temperature and altitude.5.6.3 All components shall meet the requirements for DO-160D category B “Severe Humidity“ requirements.5.6.4 All components shall meet all other DO-160D requirements except that components within the pressurized fusel
