SAE AS 943A-1986 Starter Pneumatic Aircraft Engine General Specification for.pdf

1、The Engineering Society For Advancing Mobility Land Sea Air and Space400 COMMONWEALTH DRIVE, WARRENDALE, PA 15096AEROSPACESTANDARDCopyright 1986 Society of Automotive Engineers, Inc.All rights reserved.Printed in U.S.ASAE Technical Standards Board Rules provide that: “This report is published by SAE

2、 to advance the state of technical andengineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use , includingany patent infringement arising therefrom, is the sole responsibility of the user.”SAE reviews each technical report at le

3、ast every five years at which time it may be reaffirmed, revised, or cancelled. SAE invit esyour written comments and suggestions.Submitted for recognition as an American National StandardIssued 1-31-68Revised 12-31-86Supersedes AS 943AS 943ATABLE OF CONTENTSPage Number1. SCOPE . . . . . . . . . . .

4、 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32. APPLICABLE DOCUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33. REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5、 . . . . . . . . . . . . . . . . . . . . . . . . 33.1 Qualification Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33.2 Model Specification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6、 33.3 Mockup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43.4 Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53.5 Materials . . . . . . . . . . . .

7、. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53.6 Design and Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53.7 Inspection Processes and Certification . . . . . . . . . . . . . . . . . . . .

8、. . . . . . . . . . . . . . . 103.8 Reliability and Maintainability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103.9 Performance Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113.10 Environmental Requi

9、rements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 123.11 Details of Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 143.12 Interchangeability . . . . . . . . . . . . . . . . . . . . . . . . . . . .

10、 . . . . . . . . . . . . . . . . . . . . . . . . 173.13 Drawings and Diagrams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 173.14 Identification of Product . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

11、73.15 Workmanship . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174. QUALITY ASSURANCE PROVISIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174.1 Responsibility for Inspection . . . . . . . . . . . . .

12、. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174.2 Classification of Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 184.3 Test Condition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

13、 . . . . . . . 184.4 Acceptance Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204.5 Qualification Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22STARTER, PNEUMATIC, AIRCRAFT

14、 ENGINE, GENERAL SPECIFICATION FORENTIRE STANDARD REVISEDIAS 943A Page 2TABLE OF CONTENTS (continued)5. PREPARATION FOR DELIVERY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.1 Preservation and Packaging . . . . . . . . . . . . . . . . . . . . . . . . . .

15、. . . . . . . . . . . . . . . . . . 265.2 Packing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.3 Marking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

16、. . 265.4 Packing List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 266. NOTES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 276.1 Intended Use . . . . .

17、 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 276.2 Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 276.3 Symbols . . . . . . . . . . . . . . . . . . . . . . . . . .

18、 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33FIGURESFigure 1 Air Turbine Starter Performance; Torque vs. Speed . . . . . . . . . . . . . . . . . . . . . . . . . 35Figure 2 Air Turbine Starter Performance; Airflow vs. Speed . . . . . . . . . . . . . . . . . . . . . . . . . . 3

19、6APPENDICESAppendix A Specifications, Standards List. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37Appendix B Requirements/Verification Index. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39IIAS 943APage 31. SCOPE :The starters covered by this specification shall be des

20、igned to operate on compressed air from ground support equipment, engine interbleed or on board air supply, for the purpose of starting aircraft jet engines. 2. APPLICABLE DOCUMENTS :The documents listed in Appendix A, unless obsoleted, shall form a part of this specification to the extent specified

21、 herein. The applicable issue of each shall be that in effect on the date of issue of this AS, unless otherwise specified. Buyer or contractor specifications may be used, provided a clear relation to existing similar military specification is available. For additional information, a listing of appli

22、cable SAE documents (ARPs, AIRs, AS) is included in Appendix A. 3. REQUIREMENTS3.1 Qualification Testing :This specification makes provision for qualification testing.3.2 Model Specification :When required by the purchaser, a starter model specification in accordance with the outline and instruction

23、s for preparation specified herein shall be prepared by the starter contractor and submitted to the purchaser for approval. The appropriate approval status shall be shown on page 1. After specification approval, changes shall be submitted as amendments. Each amendment shall be approved and shall inc

24、lude and supersede the previous amendment. A model specification may be revised only to incorporate previously approved amendments. Such a revision must be complete or alternately must include a “revision status“ listing, showing the current issue of each page of the document.AS 943A Page 43.2.1 The

25、 headings and numbering of sections and paragraphs in the model specification shall correspond to those in this specification. Data required by this specification and such other additional data as may be required to completely describe the unit, shall be included in the model specification. (Omissio

26、n of reference in the model specification to a particular requirement of this specification by the starter manufacturer shall be interpreted as compliance therewith, unless otherwise noted by the detail specification.) When departures from the requirements of this specification are necessary, the de

27、tails of such departures shall be stated as specific requirements bearing the same section, paragraph heading and numbering as in this specification. In the event of conflict, the model specification shall govern.3.2.2 All applicable documents shall be listed in numerical order in section 2 of the m

28、odel specification and shall include the applicable revision and date of issue. 3.2.3 The model specification shall be assigned a model number and a part number by the starter manufacturer. When a revised model specification is submitted, it shall be designated by the use of the model number and the

29、 part number with the part number followed by a dash and a number. Date of the revision shall be shown on page 1 only. The model number and the part number followed by a dash and the revision suffix number shall be shown on subsequent pages. 3.2.4 For purposes of permitting preliminary evaluation of

30、 a proposed starter design, or for release of approved starter performance characteristics in connection with a design competition, the starter manufacturer shall submit a preliminary model specification to serve until superseded by a complete coordinated model specification which will be required f

31、or a production contract.3.2.5 All curves shall be presented on graph paper having an adequate number of subdivisions to permit easy interpolation.3.2.6 Definitions and Symbols :Terms, their definitions and symbols used in the model specification shall be in accordance with 6.2 and 6.3 herein.3.2.7

32、A cross reference of Requirements and Verification Means is included in Appendix B herein.3.3 Mockup :When required by the customer, a full scale mockup shall be prepared for examination and approval by the customer. At completion of the qualification test, the mockup of the final configuration shal

33、l be furnished to the customer.AS 943APage 53.3.1 Changes :Changes to the starter features requiring changes in the vehicle or ground support equipment made after approval of the mockup shall be submitted to the purchaser for approval in accordance with DOD-STD-480. Any changes required by the purch

34、aser shall be subject to negotiation as provided in the contract. Unless otherwise authorized, the mockup shall be kept current with approved changes.3.4 Components :Normally, the complete starter shall consist of the following assemblies and systems:a. Energy conversion and speed reduction assembly

35、 (3.11.1 herein)b. Clutch and output assembly (3.11.2 herein)c. Control System (3.11.3 herein)d. Lubrication System (3.11.4 herein)e. Containment Provisions (3.6.1 herein)3.5 Materials3.5.1 Metals :Metal parts in storage or service use as defined by the purchaser, shall be of the corrosion resistant

36、 type or suitably treated to resist corrosion due to fuels, oil, hydraulic fluid, combustion gases or residue, or atmospheric conditions likely to be met in storage or service use. Any corrosion resistant protective coating used shall have adequate resistance to cracking, chipping and scaling with a

37、ge, use or extremes of atmospheric conditions.3.5.2 Dissimilar Metals : Unless protected against electrolytic corrosion, dissimilar metals shall not be used in contact with each other. Dissimilar metals are defined in MIL-STD-889B.3.5.3 Synthetic Rubber Parts :Age of synthetic rubber parts shall be

38、controlled in accordance with MIL-STD-1523.3.5.4 Castings :Castings shall be classified and inspected in accordance with MIL-C-6021.3.5.5 Organic Materials :Materials that are nutrients for fungi shall not be used where it is practical to avoid them. If used, nutrient materials and their associated

39、fungicidal treatment shall be identified in the model specification.3.6 Design and Fabrication :The starter shall be designed for operational use with pneumatic energy sources. The design shall be amenable to production processing methods.3.6.1 Overspeed Protection :When not provided as part of the

40、aircraft system, the starter shall incorporate both the following features:AS 943A Page 63.6.1 Continueda. Except for particles emitted from the exhaust, which do not contain sufficient energy to cause harm to equipment, structure or personnel, the starter shall be capable of containment of all star

41、ter fragments within its envelope and remain on its mount should a failure at free run speed occur with air at the worst combination of pressure and temperature possible in the system from sea level to the maximum aircraft operational altitude. The starter shall be designed to provide containment of

42、 maximum energy hub burst (3 piece 120 segments) of the turbine wheel at a speed not less than the maximum cutout speed or the maximum free running speed as specified in the detail specification. Containment shall also be provided for a turbine blade separation or a rim separation, if the turbine ro

43、tor is fused at the separation speed. Containment demonstration of all high speed rotating components shall be required. b. The starter shall incorporate a speed limiting feature which will safely limit the starter speed, either loaded or unloaded. The speed limiting feature(s) shall limit rotation

44、of all high speed components to less than 100% of the minimum burst speed(s). The limiting feature shall not require manual resetting and shall function, as necessary, throughout the overhaul life of the starter without maintenance or adjustment. The speed limiting feature(s) shall be described in d

45、etail in the model specification. The containment requirement shall address nacelle structural and design considerations, such as fuel line proximity and location of other critical engine equipment, as will be made available by the airframe manufacturer.3.6.2 External Surface Temperature :The extern

46、al surface temperature of the starter shall not exceed the value specified in the detail specification during or following any operating condition, throughout the ambient temperature range specified. This temperature is exclusive of any external influences such as engine radiated heat. Provisions ne

47、cessary to meet this requirement shall be integral with the starter.3.6.3 Emergency Disengagement :When required by detail specification, an automatic emergency starter drive disengagement mechanism shall be incorporated external of the starter gear section to effect emergency disengagement of the s

48、tarter from the engine in the event normal disengagement does not occur. The disengaging mechanism shall be so designed that removal of the starter from the engine pad shall be required to effect re-engagement of the starter drive. An attempted start, after an emergency disengagement has been experi

49、enced, shall not cause damage to the starter or engine. The disengagement mechanism shall be described in detail and its operating limits specified in the model specification.AS 943APage 73.6.4 Loads and Forces :The starter shall withstand the required number of operational cycles as specified in the detail specification, without permanent deformation or degradation of the performance, when subjected to the maximum normal forces resulting from the combination of loads and rotational accelerations specified in the detail specification. The starter shall not rupture and shall remain on