SAWE Technical Papers

@inproceedings{3494,

title = {3494. An Error Propagation Analysis of Small Engine Mass Properties Measurements},

author = {P. E. Anthony Primozich},

url = {https://www.sawe.org/product/paper-3494},

year  = {2010},

date = {2010-05-01},

booktitle = {69th Annual Conference, Virginia Beach, Virginia},

pages = {16},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Virginia Beach, Virginia},

abstract = {This paper investigates the impact of measurement error propagation on the accuracy of calculated weights and centers of gravity of small turbofan engines. Three variations of the two-load-cell crane-and-cable weighing technique were explored. The potential sources of measurement error were identified and analytical expressions for calculating the total error in the weight and center of gravity calculations were derived. A generic engine example was used to conduct a sensitivity analysis to illustrate the magnitude of error that could result from various weighing configurations. Results show that incorrect mass properties values can have an effect on modern aircraft flying qualities, such as fuel burn, aircraft handling, and trim.},

keywords = {03. Center Of Gravity, 08. Weighing, 17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3497,

title = {3497. New Mass Properties Engineers' Aerospace Ballasting Challenge Facilitated by the SAWE Community},

author = {Amanda Cutright and Brendan Shaughnessy},

url = {https://www.sawe.org/product/paper-3497},

year  = {2010},

date = {2010-05-01},

booktitle = {69th Annual Conference, Virginia Beach, Virginia},

pages = {27},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Virginia Beach, Virginia},

abstract = {The discipline of Mass Properties Engineering tends to find the engineers; not typically vice 

versa. In this case, two engineers quickly found their new responsibilities deep in many aspects 

of mass properties engineering and required to meet technical challenges in a fast paced 

environment. As part of NASA's Constellation Program, a series of flight tests will be conducted 

to evaluate components of the new spacecraft launch vehicles. One of these tests is the Pad Abort 

1 (PA-1) flight test which will test the Launch Abort System (LAS), a system designed to provide 

escape for astronauts in the event of an emergency. The Flight Test Articles (FTA) used in this 

flight test are required to match mass properties corresponding to the operational vehicle, which 

has a continually evolving design. Additionally, since the structure and subsystems for the Orion 

Crew Module (CM) FTA are simplified versions of the final product, thousands of pounds of 

ballast are necessary to achieve the desired mass properties. These new mass properties 

engineers are responsible for many mass properties aspects in support of the flight test, including 

meeting the ballasting challenge for the CM Boilerplate FTA. SAWE expert and experienced 

mass properties engineers, both those that are directly on the team and many that supported via a 

variety of Society venues, significantly contributed to facilitating the success of addressing this 

particular mass properties ballasting challenge, in addition to many other challenges along the 

way. This paper discusses the details regarding the technical aspects of this particular mass 

properties challenge, as well as identifies recommendations for new mass properties engineers 

that were learned from the SAWE community along the way.},

keywords = {17. Weight Engineering - Procedures, 19. Weight Engineering - Spacecraft Estimation},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3503,

title = {3503. Carefree Handling for Current Aerodynamically Instable Fighters — Resulting Requirements on Mass Properties as Well as In-Service Operation},

author = {Gregor Lehnertz},

url = {https://www.sawe.org/product/paper-3503},

year  = {2010},

date = {2010-05-01},

booktitle = {69th Annual Conference, Virginia Beach, Virginia},

pages = {22},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Virginia Beach, Virginia},

abstract = {Modern fighters face high level mission requirements as well as complex combat scenarios. Additionally their agility has significantly grown, especially by the introduction of aerodynami- cally instable flight performance designs. This demands for solutions to reduce the pilots work- load in the field of aircraft flight control. It could be achieved by the application of a principle called Carefree Handling. This principle transfers the aircraft trim control together with the flight envelope limits observation to the aboard Flight Control System (FCS). Applying this, both tasks are completely and autono- mously performed by the FCS. The trim control is a permanent background process during flights. The flight envelop limit con- trol triggers FCS reactions at limit approach or exceedance. At limit approach the FCS poten- tially indicates warnings to the pilot(s). At limit exceedance the FCS initiates adequate counter measures. The risk potential at limit exceedance defines the safety requirements on accuracy and reliability of fundamental FCS input parameters. Basic technologies such as Fly-by-Wire and FCS architecture with powerful operating units are already available - hence Carefree Handling is technically feasible. The application of the Carefree Handling principle generates additional technological, logistical and operational effort. However it must be considered that for aerodynamically instable fighters the aircraft trim control must be performed by the FCS anywhere. In this paper basic aspects of the Carefree Handling principle with emphasis on their impact on mass properties handling are briefly outlined.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3479,

title = {3479. Managing and Controlling Weight and Center of Gravity for Combat Ground Vehicle Development Programs},

author = {Scott Kaiser},

url = {https://www.sawe.org/product/paper-3479},

year  = {2009},

date = {2009-05-01},

booktitle = {68th Annual Conference, Wichita, Kansas},

pages = {16},

address = {Wichita, Kansas},

abstract = {BAE Systems Inc. is the U.S, subsidiary ofBAE Systems pIc, an intcmational company engaged in the development, delivery and support of advanced defense and aerospace systems in the air, on land, at sea and in space. US Combat Systems, one of BAE Systems Inc.'s Land & Armaments lines of business is a leader in designing, rapidly prototyping and manufacturing protected fighting vehicle plattbrms and survivability solutions that support and protect the current and future forces. Improving and increasing military transformation capabilities, that is increasing the speed with which the military forces deploy and engage by reducing the logistics tail is directly related to the successes of managing and controlling the development and fielded weight of combat ground vehicles. This paper discusses methods of controlling and managing weight of complex design combat vehicle solutions tbr the customer that has various design constraints such as high level of component commonality, low cost, high reliability, speed to market, and increased performance capabilities over the current force systems. The mass properties control and management methods presented in this paper focus on developing an accurate estimate, reconciling this estimate with the customer's requirements, advocating a program mass properties and control plan, establishing and enforcing weight allocations/targets, monitoring and mitigating development weight, organizing and presenting data. The final conclusions of this paper will include lessons learned based on implementation ofthese methods.},

keywords = {17. Weight Engineering - Procedures, 25. Weight Engineering - System Estimation, 31. Weight Engineering - Surface Transportation},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3437,

title = {3437. Development and Implementation of a Space Systems Mass Properties Process},

author = {Jesse Peterson and Otto G. Ratz and Dr. Angela Trego},

url = {https://www.sawe.org/product/paper-3437},

year  = {2008},

date = {2008-05-01},

booktitle = {67th Annual Conference, Seattle, Washington},

pages = {10},

address = {Seattle, Washington},

abstract = {ATK Launch Systems is the world leader in solid rocket motor design and manufacturing. The Systems Engineering and Integration (SE&I) team within the Advanced Programs group was tasked with developing a mass properties process for very large and complex systems. This process was to include a definition of what mass properties information needed to be tracked, how the information was going to be calculated and tracked, and where the information would be stored. The SE&I team chose to use the AIAA S-120-2006 [1] standard as a basis for the new process. This standard provided suggestions for what information should be tracked, and what the mass growth allowance (MGA) and mass margin (MM) depletion schedule should look like for a space system, including mass assessment Technical Performance Measure (TPM) guidelines. With the AIAA guidelines [1] in mind, the SE&I team developed a new mass properties control plan. This control plan included the process for calculating MGA and MM depletion schedules, and mass assessment roll ups, including TPMs, for assemblies with components in various design stages. The traditional roll up as outlined in the AIAA standard [1] suggests components within assemblies follow the same schedule with different percentages based on maturity. ATK chose to develop an approach to allow different schedules for each component / assembly based on the component / assembly specific development schedule and maturity. The mass properties process also included the method for tracking detail part changes real time, and calculating and reporting TPMs for mass assessment, the number of component mass changes, and the time sequenced mass properties. All of the knowledge contained within the control plan was then captured within a MATLAB application which calculated the time sequenced mass properties, the mass depletion schedule of the system, and output the required TPMs programmatically. The MATLAB application also created a formatted mass properties report, and a data file containing all of the time sequenced mass properties information for use by other groups. This process and application can be used on any large system, and it is ideal for systems which implement the AIAA approach [1] to mass properties control. With little time and effort on the part of the mass properties engineer, a great deal of data can be created programmatically.},

keywords = {17. Weight Engineering - Procedures, 24. Weight Engineering - System Design},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3440,

title = {3440. E-Standards For Mass Properties Engineering},

author = {Jeffrey Cerro},

url = {https://www.sawe.org/product/paper-3440},

year  = {2008},

date = {2008-05-01},

booktitle = {67th Annual Conference, Seattle, Washington},

pages = {19},

address = {Seattle, Washington},

abstract = {A proposal is put forth to promote the concept of a Society of Allied Weight Engineers developed voluntary consensus standard for mass properties engineering. This standard would be an e-standard, and would encompass data, data manipulation, and reporting functionality. The standard would be implemented via an open-source SAWE distribution site with full SAWE member body access. Engineering societies and global standards initiatives are progressing toward modern engineering standards, which become functioning deliverable data sets. These data sets, if properly standardized, will integrate easily between supplier and customer enabling technically precise mass properties data exchange. The concepts of object-oriented programming support all of these requirements, and the use of a Java based open-source development initiative is proposed. Results are reported for activity sponsored by the NASA Langley Research Center Innovation Institute to scope out requirements for developing a mass properties engineering e-standard. An initial software distribution is proposed. Upon completion, an open-source application programming interface will be available to SAWE members for the development of more specific programming requirements that are tailored to company and project requirements. A fully functioning application programming interface will permit code extension via company proprietary techniques, as well as through continued open-source initiatives.},

keywords = {16. Weight Engineering - Organization, 17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3453,

title = {3453. Modernizing Inclining Experiment Tools and Methods},

author = {David Tellet},

url = {https://www.sawe.org/product/paper-3453},

year  = {2008},

date = {2008-05-01},

booktitle = {67th Annual Conference, Seattle, Washington},

pages = {14},

address = {Seattle, Washington},

abstract = {The purpose of this paper is to propose new, more modern tools and methods for performing an inclining experiment on ships and submarines. The paper describes the process of an inclining experiment and the current tools and methods used. New tools are proposed and described for the weight survey and inventory of load items, determining the density of liquid load items, and measuring the density of the water in which the ship is floating. Reading draft marks and weighing inclining weights is discussed briefly. The move to electronic range finders and inclinometers is discussed and examples of each are shown. A discussion of error analysis follows; this is missing in the current inclining experiment reports and requirements. Finally a common inclining experiment computer application is discussed and an information display mockup shown.},

keywords = {13. Weight Engineering - Marine, 17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3456,

title = {3456. Level or Not to Level: The Analysis of a Single Engine Weighing Process},

author = {Johnathan Kaufman},

url = {https://www.sawe.org/product/paper-3456},

year  = {2008},

date = {2008-05-01},

booktitle = {67th Annual Conference, Seattle, Washington},

pages = {24},

address = {Seattle, Washington},

abstract = {With Cessna growing at a rate unprecedented in the company's history, and facilities bursting at the seams to accommodate the 18 different models of aircraft currently produced, every line is reviewed and evaluated to simplify and accelerate line flow. Cessna's Independence facility decided to evaluate the weighing process for the current production single engine aircraft (172, 182, and 206). 

How can a process developed 10, 20, or even 30 years ago compare to one developed using the latest technologies? This paper discusses the analytical process used to develop a new weighing process for Cessna's single engine aircraft. This new process allows the aircraft to be weighed in unlevel conditions, translates the center-of-gravity to level conditions and decreases cycle time by more than one hour per weighing. These equations have been tested and show an improvement in repeatability, reproducibility and comparability between different units. This paper evaluates Cessna's previous single engine weighing process on safety, accuracy, reproducibility, repeatability, cycle time and cost. Anyone who has ever observed a weighing process and thought, 'there must be a better way,' will enjoy this paper.},

keywords = {08. Weighing, 17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3458,

title = {3458. Methods of Determining the Longitudinal Weight Distribution of a Ship},

author = {David Laurence Hansch},

url = {https://www.sawe.org/product/paper-3458},

year  = {2008},

date = {2008-05-01},

booktitle = {67th Annual Conference, Seattle, Washington},

pages = {24},

address = {Seattle, Washington},

abstract = {Approximation methods for weight distribution of ships are surveyed. Grouping methods such as the 'Bucket' and station method are also explored. Detail based methods are explained. Finally, an improved method of distribution based on details is proposed. Guidance for the requirements of a weight database for this method is given and an alternative summary method is suggested to overcome difficulties caused by failure to meet certain database requirements of the detail method. Extensive appendices provide necessary figures and equations for using these methods.},

keywords = {13. Weight Engineering - Marine, 17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3407,

title = {3407. Genetic Algorithm Applied to Weight Estimation},

author = {Jorge Torres and Juan Victoria},

url = {https://www.sawe.org/product/paper-3407},

year  = {2007},

date = {2007-05-01},

booktitle = {66th Annual Conference, Madrid, Spain},

pages = {18},

publisher = {Society of Allied Weight Engineers},

address = {Madrid, Spain},

organization = {Society of Allied Weight Engineers},

abstract = {Fast and accurate rear fuselage weight estimations are an important process in aircraft design tasks. After modeling geometry and obtaining the load distribution, an optimized sizing must be obtained to calculate the rear fuselage weight. In this paper, optimization will be performed using a genetic algorithm. It will be integrated in the global weight estimation process, and its configuration and settings will be analyzed in order to improve convergence time and results obtained.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3385,

title = {3385. Reproducible Research in Mass Properties Engineering: A Modest Proposal},

author = {David Tellet},

url = {https://www.sawe.org/product/paper-3385},

year  = {2006},

date = {2006-05-01},

booktitle = {65th Annual Conference, Valencia, California},

pages = {46},

publisher = {Society of Allied Weight Engineers},

address = {Valencia, California},

organization = {Society of Allied Weight Engineers},

abstract = {These days of diminishing resources - especially in the mass properties industries - demand that we find and use the most efficient and effective paths to do our jobs. We also have a responsibility to provide a corporate memory legacy to future weight engineers. The current trend toward bulletized presentations and undocumented spreadsheets will not provide future engineers with the data, methodology, or rationale needed to prevent future wasteful re-work and uncertainty. This paper proposes one path to move back toward meaningful, useful, and effective technical reports while increasing the efficiency of producing those reports. This path borrows from the Academic model for papers and theses in the use of proven open-source programs like LATEX and R. A practical example of the use of these programs is shown in Part II of this paper as a short study on an Exploratory Data Analysis of the FF 1040 Weight and Stability. This study shows how an ascii file can contain the data, methods, discussion, and results (both text and graphics) of a subject and how this file can be used far into the future to either recreate the original study or revise or expand on it as needed. The study shows that a better legacy than anemic PowerPoint slides can be provided for future weights engineers and that the tools used to do so can improve efficiency and effectiveness of current weights engineers.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3375,

title = {3375. Methods to Measure and Track Technical Performance Measures},

author = {Amy McDonald},

url = {https://www.sawe.org/product/paper-3375},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {16},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {This research paper was done to determine the best way to measure and track Technical Performance Measures (TPM) in a marine industrial setting. Technical Performance Measures are plans of expected technical achievement in which actual progress is assessed relative to goals which are measured against a documented timeline. This researcher was looking for better ways to track these performance measures. 

The goal of this researcher was achieved. By doing extensive research, this researcher found that TPMs need to be measured in the following ways: 

1. Assess requirements 

2. Determine goals and thresholds 

3. Create a plan to meet those goals 

4. Track progress against a strict timeline (in graphic format) 

5. Report Risks 

6. Devise a plan to mitigate risks 

7. Implement plan 

8. Report results to management},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3146,

title = {3146. Predictive Weight Accounting Within a Multidiciplinary Engineering Organisation},

author = {Douglas Smith and Cheeseman},

url = {https://www.sawe.org/product/paper-3146},

year  = {2001},

date = {2001-05-01},

booktitle = {60th Annual Conference, Arlington, Texas, May 19-23},

pages = {21},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Arlington, Texas},

abstract = {There is an obvious requirement to maintain and document Aircraft weight at all stages of an Aircraft project. The standard of information available to the weight engineer changes, becoming gradually more detailed as the project continues. Different weight capturing methods are suited to particular phases of a project and provide subtly different types of weight data. 

In the early phases of a project there is no particular specific design available. Data takes the form of a list of project requirements and some engineering solutions which detail how certain aspects of that design are to be realised. In this phase of a project, the weight engineer is providing a predicted weight, not the weight of a particular design instance. He is telling the project what a design should weigh, not what a particular design does weigh. This activity is supported by a varied selection of weight prediction methods, which are examined in this paper.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3005,

title = {3005. X-35 Weight Control},

author = {Glen Maijala},

url = {https://www.sawe.org/product/paper-3005},

year  = {2000},

date = {2000-06-01},

booktitle = {59th Annual Conference, St. Louis, Missouri, June 5-7},

pages = {17},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {St. Louis, Missouri},

abstract = {Effective weight control is mandatory for any successful short takeoff/vertical landing (STOVL) aircraft. The demanding task is made more difficult when the aircraft has a high degree of commonality with variants designed as replacements for high performance Air Force and Navy fighters. 

This challenge was placed squarely in front of a Lockheed Martin led team when, in November 1996, it was selected as one of two participants for the concept development phase (CDP) of the Joint Strike Fighter (JSF) program. Each contractor was to develop two aircraft that would demonstrate technologies it deemed critical to being able to produce a multi-service fighter to replace the F-16, F/A-18, and the AV-8. Lockheed Martin?s demonstrator aircraft, which are designated the X-35A, X-35B and X-35C, are currently undergoing final assembly and system checkout testing at its Palmdale, California location and are schedule to fly before year end. 

This paper describes and examines the weight management aspects of the X-35 program that contributed to the achievement of the healthy weight margin its STOVL variant now enjoys. The effectiveness, strengths, and weaknesses of the aspects are explained. Some of the aspects addressed include: the roles of the mass properties engineer, subcontractor weight management, weight ?plan-to-perform? profiles, weight reduction programs, definition and use of target weights, ?value of a pound,? the ?weight czar,? and program management?s role in weight control. Following the examination of the weight control processes are recommendations for improvements.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3025,

title = {3025. Tracking Aircraft Basic Weight Using Microsoft Access Relational Database},

author = {H Rogers},

url = {https://www.sawe.org/product/paper-3025},

year  = {2000},

date = {2000-06-01},

booktitle = {59th Annual Conference, St. Louis, Missouri, June 5-7},

pages = {30},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {St. Louis, Missouri},

abstract = {The objective of this paper is to provide the reader with an appreciation of some of what can be achieved with MS Access database in the field of aircraft weight and balance tracking, and to inspire the reader to investigate applications in their own field. This paper describes the background, reasoning, construction, operation, and features of the Microsoft Access database developed for recording and tracking aircraft basic weight and balance for Air New Zealand. Tracking aircraft basic weight between weighs is a process of recording modification weight changes, in an accurate and organised manner, and identifying when their cumulative effect requires republication of basic weight. Over the years there have been many methods of achieving this, some more or less complicated than others. Air New Zealand has operated over the years a variety of recording systems, from paper records to main frame databases. The difference between the previous methods and the current MS Access Weight and Balance database is that the MS database combines the benefits of all the previous methods, without many of the drawbacks. The problem with paper or spread sheet records for a fleet of aircraft of ten and above is the difficulty faced when researching whether a modification has been accounted for or not, and which revisions have been included. It quickly becomes a laborious task searching through all records. The database is the perfect form of weight record data management. Mainframes have been the only available databases of sufficient capability to manage aircraft weight records efficiently until recently. Unfortunately if enhancements were required, it was often difficult if not impossible to make these changes to the mainframe. Now with the modern PC based databases available, it is now reasonable for powerful weight and balance data management databases to be developed by the end user. Thereby allowing the recording medium to evolve with the changing requirements of the weights engineer. The Air New Zealand weight and balance database is developed in Microsoft Access because Air New Zealand chose to use Microsoft products. Initially the data was transferred from Paradox as flat file records, and then stripped down to tables and relational links created. The weight and balance database has been developed using common sense logic and terminology in a manner understandable for operators unfamiliar with Microsoft Access. MS Access allowed creation of simple forms for operation of the database which resulted in the database being simple and easy to use. The database records modification accomplishments, and alerts the weights engineer when change limits are exceeded. Other features include maintaining historical weight publication records for all aircraft, maintaining all records regarding inactive aircraft, a search capability for specific modifications, and modification status comparison between aircraft. It also records weigh dates, and forecasts upcoming weighs. The MS Access aircraft weight and balance tracking database has proven to be an efficient and accurate record keeping system which reduces the time required to manage weight and balance records for a fleet of aircraft. It?s strength is that it can be developed by persons unfamiliar with more advance programming languages, thereby allowing the developer the opportunity to evolve the database in keeping with changing requirements.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{2418,

title = {2418. Mass Properties Process Improvements},

author = {W McKeighan and M Vanderpool and T Reed and P Chronister and D Kemp and S Jones and J Vanscyoc and M A Tice},

url = {https://www.sawe.org/product/paper-2418},

year  = {1998},

date = {1998-05-01},

booktitle = {57th Annual Conference, Wichita, Kansas, May 18-20},

pages = {22},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Wichita, Kansas},

abstract = {In the course of the last two years the weight and balance group has initiated several process improvement projects with the object in mind of reducing response time and improving the quality of the data which we supply to our customers. This paper discusses four of these projects. The first is a function developed on CATIA which automates distribution of mass properties by section for solid models of individual aircraft parts, which is one of our most time consuming tasks. This function splits solid models along section boundaries and transports the resultant data to a UNIX file for further processing. The second improvement is a CATIA function which determines fuel mass properties and the associated fuel burn curve from a CATIA solid model of the fuel tank. Process improvement number three is a program which calculates avionics and electrical system wire bundle weights by developing CATIA solid models which use splines representing the routing which these wire bundles take through the aircraft. The program extracts the wire type and quantity from the desired wiring schematic model located in a PROCADAM file and adjusts the density of the CATIA solid models proportionately, yielding distributed mass properties. These three improvements are the result of a collaborative effort between the weight and balance group and computer support group. The final project is a program run on Microsoft Excel which streamlines the process of creating preliminary aircraft loading profiles. As requests for these studies proliferated, the demand became apparent for a mechanism that would allow marketing personnel to run scenarios for various loading and optional equipment selections, and demonstrate the feasibility of loading the resultant aircraft for specified missions. This program is a response to that demand.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{2419,

title = {2419. FAR 25.571 Impact on Weight Control},

author = {B L Anderson},

url = {https://www.sawe.org/product/paper-2419},

year  = {1998},

date = {1998-05-01},

booktitle = {57th Annual Conference, Wichita, Kansas, May 18-20},

pages = {15},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Wichita, Kansas},

abstract = {FAR 25.571 and advisory guidelines require that damage tolerance evaluations be made for all commercial aircraft designs. Simply put, damage tolerance refers to the ability of a structure to prevent preexisting or developing cracks from causing structural failure, which threaten the integrity of the aircraft. Traditionally this has been accomplished through the use of redundant or fail-safe designs where the inspection interval is set to provide at least two opportunities for inspection in the time it would take for a visually detectable crack to grow large enough to cause failure. As the industry and the regulatory agencies gained understanding of how aircraft structure behaves in the commercial environment, changes have been made to FAR 25.571 to reflect operators' in-service experience. These changes, (specifically those, associated with amendment level 45 of FAR 25.571), have presented new challenges to the weight control community. This paper covers the impact of damage tolerance on weight control and provides some basis from which Weight Control Engineers can estimate or even offset the impact of these increasing structural requirements.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{2348,

title = {2348. A Weight Status Report for All Audiences},

author = {D K Jones},

url = {https://www.sawe.org/product/paper-2348},

year  = {1997},

date = {1997-05-01},

booktitle = {56th Annual Conference, Bellevue, Washington, May 19-21},

pages = {17},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Bellevue, Washington},

abstract = {This paper will present the content and format of a monthly weight status report that was generated to accomplish three goals: 1) provide a comprehensive monthly weight status of the aircraft for senior management, 2) provide the data in a format such that any audience can easily understand, and 3) create a report that is easy to generate and distribute. Before the report content and format were finalized several meetings occurred with different levels of management to determine what data was important and how the data would be presented to satisfy the needs of the report. The result of the meetings generated a report whose format is predominantly graphical and bullet type narrative. This paper will also discuss items of importance that were considered in determining what the content of the report would be, how it would be presented, how it would be generated, and how it would be distributed. After publishing fourteen such status reports, it is felt that the status report presented here has been optimized for accomplishing the three goals listed above. That is, senior management receives a status report that satisfies their needs, is easy to understand, and easy for the weights group to generate and distribute.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{2239,

title = {2239. IPD Weight Control and Management Plan for Commercial Aircraft},

author = {R Fox},

url = {https://www.sawe.org/product/paper-2239},

year  = {1995},

date = {1995-05-01},

booktitle = {54th Annual Conference, Huntsville, Alabama, May 22-24},

pages = {16},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Huntsville, Alabama},

abstract = {An effective weight control management process is crucial during the aircraft development phase. Historically, it has been shown that without proper weight control the aircraft weight can grow two to ten percent from program launch to certification. The objective of this plan is to identify weight problems before design release. The plan must have effective weight management from the start of the program. It must implement weight control/weight reduction throughout development and flight test to insure a balanced weight/cost configuration for production. The top level weight commitment is the Specification Manufacturers Empty Weight (MEW) as defined in the Detail Specification. This specification and the Aircraft Baseline Configuration Definition (ABCD) provide the design features that are included in the weight evaluation for the derivation of the MEW. This weight control and management plan has been developed to encompass the basic elements of a traditional weight control plan but had several fundamental improvements over conventional programs. It assumes the commitment of an Integrated Product Development (IPD) process including the use of solid modeling. The plan establishes a ?Must Weigh? level for each Product Center and a requirement to track this weight through the design process. This ?Must Weigh? will also be imposed on the supplier procurement packages within the Product Centers. Suppliers must institute a weight control plan compatible with the IPD plan. It establishes a Weight Control Board staring at Configuration Definition (ABCD approval) and continuing through production. It also establishes a weight reduction/improvement program to offset growth and configuration changes to maintain balanced design, weight, and cost. Finally, the plan establishes a weight status reporting system to compare the Product Center ?Must Weigh? with its current weight.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{2270,

title = {2270. Integration of Cost Reduction Initiatives Into a Weight Improvement Program},

author = {K H Klink and R W Rankin},

url = {https://www.sawe.org/product/paper-2270},

year  = {1995},

date = {1995-05-01},

booktitle = {54th Annual Conference, Huntsville, Alabama, May 22-24},

pages = {38},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Huntsville, Alabama},

abstract = {Many processes and activities are being conducted by the F-22 Team to control weight and cost. This paper describes only one of those processes and specifically focuses on the unique aspects of how we integrated cost reduction initiatives into our existing Weight Improvement Program to create the F-22 Cost/Weight Improvement Program. The purpose of this paper is to inform the weight and cost control communities of our success with this initiative. The paper also provides examples of forms, process descriptions, and operating instructions, etc. in Appendices B and C which can be utilized by the readers as a framework to create and tailor a fully integrated Cost/Weight improvement Program for their projects.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}