the determination of operational and support
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NASA-CR-140626
THE DETERMINATION OF OPERATIONAL ANDSUPPORT REQUIREMENTS AND COSTS
DURING THE CONCEPTUAL DESIGNOF SPACE SYSTEMS / ^v<r ^ £ /
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Prepared for
National Aeronautics and Space Administration
Langley Research Center
under
Grant No. NAG-1-1327
V
Prepared by
Charles EbelingKenneth Beasley
University of Dayton
Engineering Management and Systems Department
300 College Park
Dayton, Ohio 45469-0236
https://ntrs.nasa.gov/search.jsp?R=19920022016 2018-02-13T14:13:05+00:00Z
Table of Contents
List of Figures iv
List of Tables v
List of Attachments vi
Chapter I - Introduction 1Background 1Related Efforts 1Scope of Research 4
Chapter II - Data Sources 5Reliability and Maintainability Data 5Military R&M Data Systems 6Commercial Aircraft R&M Data 9Aircraft Performance and Design Specifications . . . 10Initial Data Base 11
Chapter III - Methodology 16Parametric Analysis 16Computation of MTBM 17Maintainability Estimates . 21Spare Parts Requirements 22Vehicle Turn Times 23
Chapter IV - Analysis and Results 24Preliminaries 24Regression Analysis 26Analysis of Weights and Secondary Variables 27MTBM Equations 31MHMA Equations 36Scheduled Maintenance 39Removal Rates 39Crew Sizes 41Repair Distribution 43
PRECEDING PAGE BLANK NOT FILMED
Chapter V - Implementation 47Introduction 47Modes of Operation 47Additional Input Parameters 50Computations 55Output Report 58Validation 61User Options 63
Chapter VI - Conclusions 64
Bibliography 65
APPENDIXA. AFALDP 800-4 Format A-lB. MODAS Report Format B-lC. Navy 3-M Report Format C-lD. R&M Data Sources D-lE. Data Generation Programs (BASIC) E-lF. Variable Definitions F-lG. Design/Performance/Weight Values G-lH. Dependent Variable Values H-lI. Subsystem Weight Percentage 1-1J. MTBM Regression Analysis J-lK. MHMA Regression Analysis K-lL. POFF Regression Analysis L-lM. Removal Rate Data & Regression M-lN. Abort Rate Data & Regression N-lO. Crew Size Data & Regression O-lP. Scheduled Maintenance Data P-lQ. Learning Curve Data & Regression Q-lR. Technology Growth Data R-lS. R & M Model - BASIC Program Listing S-l
in
List of Figures
1. AF R&M Summary Format 142. Navy R&M Summary Format 153. Mission Profile 484. Driver & System Variables 485. Weight Menu 496. Secondary Variable Menu 507. Calibration Menu - MTBM 518. Calibration Menu - MH/MA 529. Mission Profile Menu 53
10. Subsystem Operating Times 5411. Technology Factor Display Menu 5512. Reliability Report 5813. Maintainability Report 5914. Subsystem Spares Report 6015. Vehicle Turn Time Report 60
IV
List of Tables
1. Aircraft Design/Performance Variables 112. AF/NAVY Aircraft 123. Aircraft Subsystems 2-Digit Work Unit Codes (WUC) 134. WUC to WBS Conversions 255. WUC 11XXX Maintenance Actions 266. Subsystem Weight Equations 287. Secondary Variable Equations 298. Weight Distribution 309. MTBM Equations 32
10. Learning Curve Results 3311. Technology Growth Rates 3412. Critical Failure Rate Equations 3513. MHMA Equations 3714. Percent Off Equipment Equations 3815. Scheduled Maintenance Manhours 3916. Removal Rate Equations 4017. Crew Size Data 4118. Crew Size Regression Equations 4219. Crew Size Probability Distribution 4220. Repair Time Data 4421. Goodness of Fit Tests 4522. Model Validation - F16 6223. Model Validation - C141B 62
List of Attachments
1. USAF APR 66-1 Data
2. Navy 3-M Data
3. AF/Navy Regression Models
4. WUC 11XXX Breakdown Data
5. Removal Rate Data
6. Scheduled Maintenance Data
7. Commercial Data Systems
VI
Chapter I
Introduction
A. Background
This report documents the first year of research conducted by the University of Dayton forthe National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC)under NASA research grant NAG-1-1327. The purpose of the grant is to provide support toNASA in predicting operational and support parameters and costs of proposed space systems.Specific research objectives include: (1) the development of a methodology for derivingreliability and maintainability parameters and based upon their estimates determine operationalcapability and support costs, and (2) the identification of data sources and the establishment ofan initial data base to implement the methodology. Implementation of the methodology isaccomplished through the development of a comprehensive computer model. A third objective,not documented in this report, is to assist NASA in the development of a simulation modelwhich will provide an integrated view of the operations and support of proposed spacetransportation systems.
B. Related Efforts
Several previous studies provide insight and motivation for this research. These studies arediscussed briefly below.
The Supportability Assessment Model (SAM) developed by Rockwell International [21]provided much of the motivation for the development of the parametric equations as part of thisresearch. SAM projects maintenance action rates as a function of the dry (empty) weight of avehicle. Dry weight is considered a surrogate for complexity. This projection is then modifiedby factors which consider the environment (e.g. space vs. ground), technology (developmentyear) and reliability procurement policies (high or low reliability specifications). Using AirForce Maintenance Data Collection (MDC) data (AFM 66-1) pertaining to the C-9A, C-141Aand the C-5A, Rockwell derived a regression equation with maintenance actions per flying houras a dependent variable and empty weight as an independent variable. Predictions from thisequation for estimating spacecraft reliability are then adjusted by an environmental factor derivedfrom MIL-HDBK-217, Reliability Prediction of Electronic Equipment and a technology factorrelated to the development year.
An enhancement to the original Rockwell SAM model is the Reliability/Maintainability(R/M) Analysis Methodology used by Rockwell in assessing the R&M of the Personnel LaunchSystem, Advanced Manned Launch System (PLS/AMLS). [19] This analysis establishedregression equations between unscheduled maintenance actions and vehicle dry weight for severalaircraft subsystems such as avionics, powerplants, electrical, hydraulic, structural and landinggear. Eight different aircraft including a bomber, fighters and airlift (cargo) are used to generateexamples of the correlations obtained between subsystem weight and maintenance actions per
flying hour or per landings. Component removals are computed as a percent of the componentmaintenance actions in order to determine requirements for spares. Both a bottom-up and atop-down analysis is performed using Air Force, airline and orbiter data.
In a discussion on life cycle costing, Earles [7] presents one of the first successfulparametric models for estimating maintenance manhours per flying hour (MH/FH). An estimateof the MH/FH for on-aircraft propulsion is obtained from a regression equation with thethrust/engine and number of engines as independent variables. Five tactical aircraft and the T-38provided the source of data.
Another early study by Harmon, Pates, and Gregor [9] developed maintenance manhoursper flying hour (MH/FH) estimates for tactical aircraft for use during conceptual anddevelopment design phases. Again, using AFM 66-1 data, MH/FH estimating relationships werederived using aircraft design and performance parameters. Using ten tactical aircraft, a database covering maintenance manhours over a 6 month period was developed at the two-digit workunit code (WUC). Different independent variables were selected for each subsystem. Forexample, landing gear maintenance manhours was assumed to be related to kinetic energy andaircraft weight while the fuel system maintenance manhours was related to weight, number ofengines and fuel quantity. Correlations above .90 were reported for each of the examples,however, only 5 to 7 data points (aircraft) were used in the analysis. Technology improvementfactors are given for each WUC but details on their derivations are not provided.
Norris and Timmins [16] present another early study which focused on spacecraftperformance during its orbital life. Component failure rates over time of 57 unmannedspacecraft were analyzed. Both a Duane reliability growth curve and a Weibull hazard ratefunction provided an adequate fit to the data. A decreasing failure rate over time and a four-foldincrease in failures during the first day following launch were observed from the data.
Decreasing failure rates were also reported in a study by Hecht and Florentine [10] andHecht and Hecht [11] which focused on electronic systems of over 300 spacecraft. The studyconcluded that design and environmental causes of failures contributed the most to a decreasingfailure rate. They computed Weibull shape and scale parameters for each of several failureclassifications. Causes of spacecraft failures, their distribution by subsystem and criticality andmission type are also presented. A reliability prediction method is developed for electronicequipment operating in a space environment which is consistent with MIL-HDBK-217.
Peacore [18] discusses some reliability results pertaining to the Air Force's AW ACS (E-3A)system. In flight failure rates were found to be decreasing with flight time which he believesto be characteristic of large multi-engine transport type aircraft. A model, developed by BoeingAerospace Corporation and based upon B-52 data, has high early failure rates which decreaseto a relatively constant rate after 10 hours of flight. The high early failures are attributed toenvironmental stresses during takeoff, failures occurring when initiating (e.g. turning on) andstabilizing equipment, failures undetected during testing, andmaintenance induced failures.
One of the few papers addressing failure time and repair time probability distributions ispresented by Ostrofsky [17]. However, only graphical examples of these distributions areprovided with no results on fitted theoretical distributions reported.
A comprehensive report prepared for the Goddard Space Flight Center (NASA) byBloomquist and Graham [5] describes the study of 44 unmanned orbital spacecraft. In fact, thisstudy is an update of earlier studies conducted by the Planning Research Corporation (PRC)which addressed 350 spacecraft. In addition to providing an extensive data base of the 44spacecraft, the report classified anomalies by satellite mission, subsystem, effect, and incidenttype (e.g. electrical or mechanical). Subsystem survival times were also computed in units ofthe spacecraft design life.
A report prepared by Hughes Aircraft for the Rome Air Development Center [14] addressesdifferences between predicted and demonstrated reliability and the observed field values(primarily MTBF). Prediction models for estimating the field MTBF were derived. The studycontains a detailed description of the Air Force's MDC (AFM 66-1) and D056 data systems.The relationship between predicted and observed MTBF was established using multipleregression techniques. Of interest in this report is the derivation of a "K" factor (equipment usefactor) to account for the differences between equipment flying hours and equipment operatinghours. Equipment operating hours varied from 1.2 to 2.4 times the flying hours depending uponthe aircraft.
Maintenance policies may have a significant effect on the maintenance manhours expendedin supporting a space vehicle. Barnard and Matteson [4] describe a test conducted by the Navyto perform aircraft maintenance similar to that of the commercial airlines. Both scheduledmaintenance manhours and aircraft downtime were significantly reduced while the quality ofmaintenance increased. Similar changes in maintenance policies may be contemplated as NASAtransitions from the Shuttle to the next generation of space transportation vehicles.
C. Scope of Research
This initial effort is limited to the prediction of reliability and maintainability (R&M)parameters and their effect on the operations and support of space transportation vehicles. Thefocus is on the failure and repair of major subsystems and their impact on vehicle turn times,maintenance manpower, and repairable spares requirements. Other system components such asbooster rockets, expendables (e.g. fuels and oxygen), ground support facilities, softwaredevelopment and maintenance, and overhead staff would be subjects for future researchactivities.
Chapter II discusses various sources of R&M data and documents the data utilized in thisstudy. Chapter III develops the general methodology for estimating R&M parameters and forrelating these parameters to the logistics support requirements of the proposed vehicle. ChapterIV presents the analysis and results of applying the methodology to the initial data base whileChapter V describes the implementation of the methodology through the use of a computermodel and provides some validation of the model. The report concludes with a summary of theresearch findings and results.
Chapter II.
Data Sources
The principle approach to be used in establishing R&M estimates of new space systems isbased upon comparability with existing systems. In this regard, many of the subsystems definedfor manned space vehicles may be favorably compared to corresponding aircraft systems.Therefore, a primary source of data to support this analysis are commercial and military aircraftfailure and repair data.
A. Reliability and Maintainability Data
Data requirements consist of the following R&M data pertaining to all relevant aircraftsubsystems.
The primary R&M data are:
(1) Mean time between maintenance (MTBM). This is defined to be the length oftime in flying hours between maintenance actions on a particular subsystem or component. Onlyunscheduled maintenance actions are included. A distinction is made between maintenanceactions and failures. Maintenance actions include inherent failures (internal subsystem failures),induced failures (external failure causes) and no defect.
(2) Maintenance manhours per maintenance action (MH/MA). This is the primarymeasure of maintainability used in this study. Along with the number of maintenance actionsper mission (obtained from the MTBM), it becomes the basis of the maintenance cost estimates.
(3) Maintenance Task Times. The length of time (usually in hours) to perform aparticular task such as troubleshoot, remove and replace, perform minor maintenance, etc. Thismaintainability parameter is usually summarized at the subsystem or component level as theMean Time to Repair (MTTR). In this study, task times are obtained by dividing the MH/MAby an average crew size. Task Times include both on and off vehicle times.
(4) Maintenance crew sizes. The number of maintenance personnel required toperform a particular task. This number may vary depending upon the task, the particularcomponent involved and the skill level of the personnel. An average crew size was determinedby subsystem.
(5) Removal rates (RR). This is the percent of maintenance actions which resultsin a removal and replacement of a component from the aircraft. It is the basis for establishingdemand rates for spare components.
(6) Abort rates (AB). This is the percent of maintenance actions as a result of aground or air abort. This rate is used to establish a critical failure rate which in turn is used tocompute a mission reliability.
(7) Percent off equipment (POFF). This is the percent of the total unscheduledmaintenance manhours performed on components removed from the aircraft. These hours donot delay processing the vehicle. Therefore 1-POFF, or the percent of on-aircraft work, is usedin determining the vehicle turnaround time.
Secondary R&M data which were collected and documentedinclude:
(1) Maintenance manhours per flying hours (MH/FH). This is sometimes referredto as the maintenance index (MI) and may be broken down into off-equipment (aircraft) andon-equipment (aircraft) manhours. When it differs from flying hours, subsystem operating hoursshould be used.
(2) Mean sorties between maintenance actions (MSBMA). This is the averagenumber of sorties flown between unscheduled maintenance actions.
B. Military R&M Data Systems
(1) US Air Force data systems
Reliability and maintainability data for USAF aircraft originates with the MaintenanceData Collection (MDC) system as described in AFM 66-1. This data is collected at the base(squadron/wing) level (AFTO Form 349) and transmitted periodically to AF Logistics Command(AFLC). AFR 65-110 data (aircraft status reporting) reports flying hours and sorties for thesame bases monthly. The D056 Product Performance System processes this data producingseveral R&M reports. D056 also provides data to the Maintenance and Operational Data AccessSystem (MODAS) for on-line viewing and retrieval. AFALD Pamphlet 800-4, AircraftHistorical Reliability and Maintainability Data summarizes the worldwide R&M data at thetwo-digit work unit code (WUC) in 6-month intervals (see Appendix A for an example ofAFALDP 800-4 data). Currently Volumes I through VI covering the years 1972 through 1989have been published.
The current Office of Primary Responsibility (OPR) for AFALDP 800-4 isALD(AFLC)/LSR, Wright-Patterson AFB, Ohio. However, with the consolidation of AFLCand the Air Force Systems Command (AFSC) scheduled for July 1992, this office may no longerexist. With the eventual implementation of REMIS (Reliability and Maintainability InformationSystem), the D056 system along with MODAS will also be eliminated. It is not certain at thistime what the final configuration and capabilities of REMIS will be.
The MOD AS system (G063) is currently sponsored by AFLC/MMES, Wright-PattersonAFB, Ohio 45433. MOD AS provides the user with access to various data bases through aninteractive menu driven system. It is a Data Base Management System (DBMS) with someautomated analytical capability. R&M information may be displayed by aircraft (MDS), WUC,level of WUC, base and by month. Examples of MODAS reports may be found in AppendixB.
In addition, to the above systems, a unique representation of aircraft R&M data exist inthe form of Logistics Composite Model (LCOM) data bases. LCOM is a computer simulationmodel which simulates the operation of a squadron or wing of aircraft with random failurestimes and repair times of aircraft subsystems and components. LCOM data bases exist for mostof the aircraft in the Air Force inventory although many of these data bases are several yearsold. This data is unique in that the failure times may be based upon several years of (AFM66-1) data and repair times and crew sizes are often based upon field audits conducted at theunit's themselves. This data, which is usually collected at the 3 or 4 digit WUC level, is arefinement of the MDC data. LCOM data bases may be obtained from ASD/ENSSC,Wright-Patterson AFB, Ohio. LCOM data bases were not used in developing the parametricequations because of the more readily available and more relevant MODAS and AFALDP 800-4data.
(2) US Navy
The primary source of R&M data pertaining to Navy aircraft is the Aviation 3-MInformation reports. The Navy Maintenance Support Office (NAMSO), is the central data bankfor Aviation 3-M data (Maintenance and Material Management system). NAMSO is part of theNaval Sea Logistics Center. Although preformatted reports are published monthly, quarterlyand annually, and are available on request, a potential user may also request the developmentof a new report. Most reports can be obtained on either hard copy or microfiche. Magnetictape may be obtained under a special request.
The following R&M reports have been identified as relevant to this research. Examplesof each report may be found in Appendix C.
Report Title Report Number
Reliability and Maintainability Summary NAMSO 4790.A7142-01WUC System R&M Summary NAMSO 4790.A7142-02R&M Summary for selected WUCs NAMSO 4790.A7142-03R&M Trend Analysis Summary NAMSO 4790.A7142-045-Digit WUC R&M Trend Analysis Summary NAMSO 4790.A7142-05R&M Summary for Selected Equipments NAMSO 4790.A7298-01
The R&M Summary Report provides data similar to that available from the MODASsystem. Summary statistics are reported by aircraft type at the 5-digit WUC and include meanflying hours between maintenance actions, maintenance manhours per flying hour, maintenancemanhours per maintenance action, and elapsed maintenance time per maintenance action.
Of particular interest in this research is the WUC System R&M Summary. This reportprovides mean flying hours between maintenance actions, maintenance manhours per flyinghour, maintenance manhours per maintenance action, and elapsed maintenance time permaintenance action by system level WUC (2-digit) for all appropriate aircraft. Similar R&Minformation is provided in the R&M Summary for selected WUCs. However, this report is atthe 4-digit WUC and pertains only to engines and avionic components.
The two trend analysis reports provide MTBF and MH/FH information at the 4-digit and5-digit WUC respectively. Multiple time periods may be displayed to produce trend data, anda comparative failure ranking of the WUC relative to all WUCs for the aircraft is computed.
The final report, R&M Summary for Selected Equipments, allows for R&M data to bepresented at the 2nd and 4th level WUC by activity. This report would not add any newinformation not already available on the other reports other than the activity breakdown.
(3) Reliability Analysis Center
The Reliability Analysis Center (RAC) is one of 21 DOD Information Analysis Centers(IAC). It is operated by IIT Research Institute in Rome, New York. As an IAC, RACmaintains data bases and studies concerning component reliability particularly that of electronicsystems. The Center also conducts special studies, publishes newsletters, and offers trainingcourses. In general, the items contained in RAC's data bases are individual parts rather thanan entire component. Therefore, this data was not used in this research.
C. Commercial Aircraft R&M Data
Commercial data sources were investigated but not used in developing the initial database for reasons discussed below. However, examples of the reports and types of data availablefrom these sources is documented in Attachment 8.
(1) Federal Aviation Agency (FAA)
Commercial sources of R&M data include both the airlines and the aerospacecontractors. In addition, the Federal Aviation Agency (FAA) in Oklahoma City maintains a database consisting of component failures by Airline Transport Association (ATA) code whichcorresponds to the military's WUC. The data base is very detailed with significant variabilityin reporting by the individual airlines. A narrative on each incident is included, but there is noquantitative data for estimating MTBF or MTTR. This data is of limited use since there is nopractical way to obtain failure rates or times of failure without additional information.
(2) Commercial Airlines
Each airline maintains R&M data in a form useful to them. However, they onlymeasure reliability in terms of failures which cause schedule delays (usually of 15 minutes ormore) or aborts. Therefore total maintenance activities are generally not captured in their datasystems. R&M reports from three different carriers were obtained and analyzed for theirrelevance to this research. Because of major differences in reporting compared to the militarydata systems, it was concluded that this data would be of very limited use. For example, USAirproduces a monthly reliability assurance program report [22] which focus schedule departuredelays and cancellations. Flying hours between events and maintenance hours are not reported.
(3) Aerospace Contractors
Examples of the type of data maintained by the major aerospace corporations may befound in Attachment 7. These contractors are dependent upon the airlines for reporting failuresand, as a result, their reports focus on those events which significantly affect scheduled flightsresulting in delays (again exceeding 15 minutes), cancellations, diversions, and air turn backs.While this information is very useful in identifying problem areas, failure times cannot becomputed from this report. For example, scheduled interruptions are Boeing's major measureof reliability. They maintain very little data on MTBF, MTTR or maintenance MH/FH.McDonnell Douglas maintains a Data Exchange Program which reports various reliabilityinformation which is then provided to commercial aircraft customers. Information contained inthis report is obtained from participating airlines. Like the Boeing report, it focuses on eventswhich result in excessive delays and cancellations. However, a component removal summarycontains some MTBF information.
(4) Other Sources
A secondary source of reliability data consists of subcontractors involved in themanufacture of particular aircraft subsystems and components. For example, HughesCorporation which, among other things, makes radar systems for various aircraft. We were ableto obtain the system specifications and reliability test results on four of their radar systems. Asadditional information like this on other radar sets is obtained, a parametric estimation of MTBFis possible. We have requested similar input from other subcontractors including HarrisCorporation (digital map generators, global positioning system) and E-Systems (electronicsystems). This level of detail may be beneficial during the follow-on effort when componentlevel R&M analysis is anticipated.
Other sources which had been pursued include Airbus Industries (Europe), The Society ofAutomotive Engineers (SAE) which has published a guidebook on rocket booster reliability, theAeronautical Systems Division (Air Force Systems Command) concerning a comparative studyon competing radar systems, and the Air Force Logistics Command's Reliability andMaintainability Information System (REMIS). Some of the information gathered is beyond thescope of this task and has not been incorporated into this report.
Various points of contact for the data sources identified above are summarized in AppendixD.
D. Aircraft Performance and Design Specifications.
In addition to R&M data, aircraft performance and design specifications (Table 1) werenecessary to support the parametric analysis. A primary source of this data for military aircraftwas a technical report titled "Modular Life Cycle Cost Model for Advanced Aircraft SystemsPhase HI," prepared by the Grumman Aerospace Corporation [15] for the Flight DynamicsLaboratory, Wright-Patterson AFB, Ohio. This report documents the data base used indeveloping a life cycle cost model for the proposed aircraft.
10
Table 1Aircraft Design/Performance Variables1
(Potential Drivers)
VEHICLE DRY WEIGHTVEHICLE LENGTHWETTED AREAVEHICLE WING SPANFUSELAGE VOLUMESUBSYSTEM WEIGHTSFUSELAGE SURFACE AREALANDING DISTANCECREW SIZENUMBER PASSENGERSNUMBER ENGINES
NUMBER INTERNAL FUEL TANKSMISSION LENGTHOPERATING CEILINGNUMBER OF WHEELSNUMBER ACTUATORSNUMBER CONTROL SURFACESMAXIMUM ELECTRICAL OUTPUTNUMBER HYDRAULICS SYSTEMSNUMBER AVIONICS SYSTEMSBTU COOLING CAPACITYAVIONICS INSTALL WEIGHT
The primary source for subsystem weights used in this study was Design Branch of the Plansand Programs Directorate of the Wright Laboratories at Wright-Patterson AFB (WL/XPAD).Secondary data sources included all volumes of Jane's All The World's Aircraft [13], "AviationWeek & Space Technology" [3], and Observer's Directory of Military Aircraft [8].
E. Initial Data Base
The primary source of military R&M data is the Air Force AFM 66-1 Maintenance DataCollection (MDC) system and the Navy 3-M data system. The initial data base consisted of AFMDC data as reported in Volume V (October 1985 to September 1987) of AFALDP 800-4 andNavy data reported in the July 1990 - June 1991 R&M Summary Report. Volume VI ofAFALDP 800-4 (October 1987-September 1989) and the MOD AS on-line system (January1990-December 1991) were secondary sources. AFALDP 800-4 summarizes R&M data at6-month intervals. Four 6-month periods were averaged together in order to provide moreaccurate measures. The Navy data is presented by quarters. Four quarters were averagedtogether also to provide for more accurate MTBM's and manhours. Table 2 lists the 37 AirForce and Navy aircraft used in the study and Table 3 identifies the 26 major aircraft subsystemswhich were included. These subsystems are identified by two-digit work unit codes (WUC).
1 Variable definitions of those used in the models are found in Appendix F.
11
Table 2AF/NAVY Aircraft
TACTICAL BOMBER
A-7D/E B-1B
A-10A B-52G
F-4C/D/E FB-111A
F-5E
F-14A
F-15A/C
F-16A/B
F-18A
F-106
F-111A/D/F
CARGO/TANKER
C-2A
C-5A
C-9A
KC-10A
C130B/E/H
KC-135A
C-140A
C-141B
COMMAND/CONTROL/TRAINER
E-2C
E-3A
EA-6B
T-38
12
Table 3Aircraft Subsystems
2-Digit Work Unit Codes (WUC)
WUCSYSTEM
11
12
13
14
23
24
41
42
44
45
47
49
51
52
55
61
62
63
64
66
71
72
91
93
96
97
SYSTEM NOUN
STRUCTURES/AIRFRAME
EQUIP/FURNGS/CREW COMPARTMENT
LANDING GEAR
FLIGHT CONTROLS
POWER PLANT SYSTEM
AIRBORNE AUXY PWR (APU)
AIR CONDITIONING/ENVIRONMENTAL CONTROL
ELECTRICAL POWER
LIGHTING SYSTEM
HYDRAULIC POWER
OXYGEN
FIRE PROTECTION/MISC UTILITIES
INSTRUMENTS
AUTO FLIGHT
MAL ANLY RECORDING
COMMUNICATIONS
VHP COMMUNICATIONS
UHF SYSTEM
PASS ADDRESS SYS
EMERG LOCT XMTR
NAVIGATION
RADAR NAVIGATION
EMERG EQUIP
DRAG CHUTE EQUIP
PERSONNEL EQUIP
EXP DEV & COMP
13
Figure 1AF R&M Summary Format
OUTPUT RESULTS FOR F-15
TOT FLYING-HRS 172258TOT SORTIES 130501TOT LANDINGS 146896AVG MISSION LENGTH 1.319975
WUC 13
TOTAL MAINTENANCE EVENTS 13223.61TOTAL MAINTENANCE MANHOURS 125632
TOTAL ON-EQUIP MAINT 89678TOTALOFF-EQUIPMAIHT 35954PERCENT OFF EQUIPMENT HRS .2861851
MEAN FLYING HR BTWN MAINT 13.02655MEAN SORTIES BTWN MAINT 9.868786MEAN LANDINGS BTWN MAINT 11.10861MAN-HOURS PER FLY-HR .7293246MAN-HOURS PER SORTIE .9626899
MAN-HOURS PER MAINT ACTION 9.500581ON-EQUIP MAN-HRS/MAINT ACTION 6.781657OFF-EQUIP MAN-HRS/MAINT ACTION 2.718924
ECHO CHECK OF INPUT DATA
PERIOD MTBM ON-EQUIP MH OFF-EQUIP MH
131 9.276 30658 115482 13.707 28229 117073 14.368 16776 69764 16.831 14015 5723
VALIDATION CHECK
PERIOD ON-EQUIP MH/FH OFF-EQUIP MH/FH
131 .7647485 .28805912 .6180946 .25633343 .3967458 .16497974 .3169811 .1294386
14
Two computer programs, written in interactive Microsoft0 BASIC, were utilized for processingthe data. The data was aggregated into two years (AF) or one year (Navy) and various R&Mparameters computed as illustrated in Figures 1 and 2. These programs are listed in AppendixE; the AF processed data is in Attachment 1; and the Navy processed data is in Attachment 2.These data provided the MTBM and MH/MA dependent variable values used in the subsequentregression analysis.
Values for the independent variables (Table 1) and subsystem weights used in the analysisare found in Appendix G. R&M (Dependent) variable values are summarized in Appendix H.
Figure 2Navy R&M Summary Format
OUTPUT RESULTS FOR F-14AWUC 45XXX
TOT FLYING-HRS 92011TOT MAINT ACTIONS 8943TOT MAN-HRS 56868TOT ELAPSED TIME 32224.9
MEAN FLYING HR BTWN MAINT 10.28861MAN-HOURS PER FLY-HR .6180566AVG ELAPSED MAIN TIME 3.603366AVE CREW SIZE 1.764722MAN-HOURS PER MAINT ACTION 6.35894
SUMMARY STATS FOR 45XXX HYDRAULICS/PNEUMATIC PWR
AVG TASK TIME 3.38761AVG CREW SIZE 1.747144
15
Chapter III
Methodology
A. Parametric Analysis
The primary objective is to develop a methodology for estimating reliability andmaintainability parameters for use in life cycle costing, supportability requirements determinationand the assessment of operational capabilities and constraints of proposed space vehicles. Thismethodology utilizes the available data sources identified in the previous chapter. The approachis based upon a comparability analysis with similar aircraft subsystems. By estimating aircraftequipment failure and repair parameters as a function of performance and design specifications,then, with suitable adjustments to account for the differences in operating environment, theR&M parameters of a conceptual space vehicle may be estimated based upon its design andoperating specifications. Adjustments are also necessary to account for technological innovationover time. This chapter presents the mathematical foundation for the analysis performed on thedata base and described in the following chapter.
Parametric R&M equations are derived using regression analysis. In general, let
Y = B0 + Bt Xi + B2 X2 + ... + Bk Xk (1)
where Y = R&M parameter of interest (e.g. MTBF or MH/MA)
and Xj = jth design or performance specification(e.g. vehicle dry weight), j = 1, 2, ... k,
thenB0, BI, ... , Bfc. are the regression coefficients.
These are estimated by performing a least-squares fit of the equation against known paired valuesfor Y and the corresponding X1? X2, ... , Xk obtained from the data base.
The following R&M parameters have been estimated using this approach:
MTBM - Mean Flying Hours between Maintenance Actions
MH/MA - Maintenance Manhours per Maintenance Actions
RR - Subsystem removal rate
POFF - Percent off-equipment (vehicle) manhours
CREW - Average crew size per maintenance task
AB - Abort Rates (Critical Failure Rate)
16
In addition to the above R&M parameters, regression equations were derived to estimatesubsystem weights and design/performance variables (see Table 1) as functions of the vehicledry weight (DRY WT) and length + wing span (LEN+WING). These variables are classifiedas secondary variables while the dry weight and length + wing span are classified as primaryvariables. Using these equations, it is possible to estimate all of the necessary R&M parametersusing only a small number of primary (driver) variables. First subsystem weights aredetermined from the regression equations, then the secondary variables are computed from theirequations, and finally the MTBM, MH/MA and other R&M parameters are estimated from theirregression equations. The latter equations will include subsystem weights and those secondaryvariables which were found to significantly improve upon their prediction capability.
B. Computation of MTBM
An initial MTBM is obtained by subsystem from the derived parametric estimatingequations. The MTBM is in units of operating (flying) hours between maintenance actions andreflects a subsystem operating in an aircraft (air/ground) environment.
(1) Technology Growth Factor
In order to account for increased reliability as a result of technological change over time,a growth factor was computed. First, the learning curve effect on the reliability of a subsystemover time was estimated. The learning curve accounts for engineering changes, modifications,and other reliability burn-in phenomena associated with a system maturing over time. This wasaccomplished by fitting an equation of the form:
MTBM = a T" (2)
where: T = cumulative calendar time or cumulative operating (flying) hours and "a" and "b"are parameters estimated using least-squares.
Next, a technology adjustment factor was found by averaging several pairwise comparisonsbetween aircraft developed during different technology periods but having similar missions andrequirements. An MTBM for both aircraft was obtained from the data set (generally a two-yearaverage value). The MTBM of the newer aircraft was modified using the learning curve growthrate (b) to account for the differences in age between the two systems. That is,
Mod MTBM = a x (1986 - Dev YR Old ACFT)b (3)
where solving Equation (2) for "a" provides:
a = NEW ACFT MTBM/(1986-DEV YR NEW ACFT)b (4)
17
The baseline year of the data is 1986 and the MTBM reflects the baseline year. The "a"parameter defines the units (e.g. operating hours or years) while the "b" parameter describesthe rate of growth.
The adjustment factor was then found by solving the compound growth rate curve:
MOD MTBM = OLD ACFT MTBM x (1+ADJ FAC)AGEDIFF (5)
That is,
ADJ FAC = [MOD MTBM/OLD ACFT MTBM](1/AGEDIFF) -1 (6)
This factor was then used in adjusting the initial MTBM to account for technological growth inreliability between the baseline year of the data and the expected development year of theproposed system. That is
ADJ MTBM = MTBM x (1+ADJ FAC)(yr'1986) (7)
(2) Environmental Adjustment
A further adjustment to the MTBM was then made to account for the change in failure rates(from those of the aircraft air/ground environment) during launch and orbit. During the air(non-booster launch and re-entry phase) and ground phase, failure rates are assumed to beconstant (exponential) with a MTBM based upon the ADJ MTBM defined above. However,during launch under booster rockets, the failure rate may increase dramatically as a result of theincreased vibration and stresses. On the other hand, while in orbit, the failure rate is assumedto decrease over time based upon results found in related work cited in Chapter 1. A Weibullfailure rate function was assumed for this portion of the mission. Previous studies have showna decrease in component failure rates occurring in the somewhat more benign spaceenvironment. Two approaches have been identified to quantify this change. The first is toinclude an environmental factor in the regression model. This would require obtaining historicaldata on comparable components operating in space. This data is quite limited and may beexplored during the follow-on effort. An alternate approach is to make use of the earlierresearch which concluded failure rates in space were decreasing with the Weibull failuredistribution providing a reasonable model. This study utilizes the latter approach.
18
For each subsystem, a mission profile curve was assumed having the following form:
Figure 3Mission Profile
Mission ProfileFailure Rate
Ground Launch OrbitProcessing Booster Time
Recovery
19
This failure rate curve may be expressed mathematically as:
A. ( t) =
A, for 0 <. t < t0for t0 £ t< tj_
A. for ; t< t^(-\ for t, s t< t,a \ a l 2 3
X for t3 ^ t< t4
(8)
where:
K=LAUNCH FACTOR
and a, and b are the Weibull scale and shapeparameters respectively
Since, in general, a reliability function is given by
R ( t)= e - ^ M £ ) d £ (9)
the reliability function may be obtained from (8) using (9):
R(t) = * t -Jb / *•» \ b
-T - -T -^t-^)
forforfor
for
for
(10)
Since the mission profile is repetitive over time, a steady-state MTBM may be computed fromequation (11).
SS MTBM = (11)
20
The use of the Weibull failure distribution in defining R(t) requires a numerical integration tocompute the MTBM from Equation (11). In the implementation of the model discussed inChapter V, Simpson's rule was used to perform the integration.
(3) Critical MTBM
Using aircraft air and ground abort rates (AB), subsystem regression equations were derivedto provide estimates of critical failure rates. A critical MTBM was then obtained from
CRIT MTBM = SS MTBM/AB (12)
A vehicle MTBM is calculated from the subsystem MTBM's using:
VEH MTBM = 1/[1/MTBM! + 1/MTBM2 + ... + 1/MTBMJ (13)
where 1/MTBM; is the failure rate of the ith subsystem.
With critical failure rates replacing 1/(ADJ MTBM), approximate mission reliabilities are foundusing Equation (10) for each subsystem. A Vehicle reliability is computed by multiplyingsubsystem reliabilities (Rj)
Rv* = R ! x R 2 x ... xRk (14)
Equation (14) assumes no explicit redundancy at the subsystem level. Some componentredundancy may be implicitly taken into account by the critical MTBM.
C. Maintainability Estimates
The primary maintainability parameter used in this study is the maintenance manhours permaintenance action (MH/MA). This parameter is estimated from the parametric regressionequations for each subsystem. Then using
TOT MA = 1/(SS MTBM) x OPER HRS (15)
total maintenance actions per mission is obtained and from
TOT MANHRS = MH/MA x TOT MA (16)
total maintenance manhours per mission is found. Manhours are then split into on-vehicle andoff-vehicle manhours using the percent off-equipment hours (POFF) obtained from regressionequations:
TOT ON-VEH MH = (1-POFF) x TOT MANHRS (17)TOT OFF-VEH MH = POFF x TOT MANHRS (18)
21
Maintenance manpower requirements are determined by computing the total manhours of workper month and dividing this total by the number of hours per month available per technician todo direct maintenance work.
Let N = number of mission per month,
AV = available hours per month per individual
IND = percent of indirect work (work not included in the MH/MA)
then,
PER ~
Scheduled maintenance manhours per mission are found by multiplying the unscheduledmanhours by a percentage estimated from a regression equation giving scheduled maintenanceas a percent of the unscheduled maintenance.
C. Spare Parts Requirements
In order to estimate spare parts requirements, it is necessary to distinguish between a failureresulting in a remove and (if a spare is available) replace action versus other maintenance actionssuch as on-aircraft troubleshoot and repair. The MODAS system identifies maintenance actionsby an action taken code one of which is a removal code.
Using regression equations or an estimated mean value, a removal rate (RR) per maintenanceaction was determined and used to obtain the mean number of demands (failures) for spares(MFAIL) per mission as follows:
MFAIL = RR x (TOT MA) (20)
Under the common assumption that the number of failures in a given time period follows aPoisson process, a spare parts level can now be found which will satisfy demands a specifiedpercent of the time. This is the frequently used fill rate criterion which represents the percentof time a demand (failure) can be immediately satisfied from the on-hand stock.
Let S = spare parts level to support a given mission andp = desired percent of time demands are satisfied (fill rate), then find the smallest value for Ssuch that F(S) > = p where
SF(S) = % Exp(-MFAIL) x MFAILj/i! (21)
i=0F(S) is the cumulative probability of demands not exceeding the spares level (S).
22
D. Vehicle Turn Times
In order to determine the time required to perform maintenance on the vehicle, estimates ofaverage repair crew sizes for typical on- vehicle tasks by subsystem must first be obtained. Oncethe average crew size has been determined from regression equations or averages from the database, an average repair time can be obtained by
REPAIR TIME = (1-POFF) X (MH/MA)/AVG CREW (22)
Average on-vehicle subsystem repair time per mission may be found from
MSN REPAIR TIME = TOT ON-VFH MH _ (23)AVG CREW
Assuming all tasks are performed sequentially (a worst case), then total vehicle mission repairtime is the sum of the subsystem repair times:
VEH REPAIR TIME = ^ SUBSYSMSN REPAIR TIME (24)
Scheduled maintenance time may then be added to obtain a total vehicle maintenance time:
TOT VEH TASK TIME = VEH REPAIR TIME + srw MHPS (25)AVG CREW SIZE
Mission time must be included in order to obtain a vehicle turn-around time. Therefore, vehicleturn-around time in working days is:
VEH TURNAROUND = MSN TIME/24 + TOT VEH TASK TIME/8 (26)
Equation (26) assumes a single 8-hour maintenance shift per day. Dividing the vehicleturnaround time into the number of working days per month gives an estimate of the number ofmissions per month per vehicle:
MSN/MO/VEH = wnpinNO HA/MO (27)VEH TURNAROUND
Dividing the required number of mission per month by the number of missions per month pervehicle provides an estimate of the required fleet size:
23
Chapter IV
Analysis and Results
A. Preliminaries
Both Navy and Air Force aircraft were initially selected for deriving the parametricequations. However, Air Force subsystem data was utilized primarily in the current modelbecause it was more comprehensive and consistent. In many cases, there was a significantdifference in failure times between Navy and Air Force systems due, in part, to the morestressful environment found on carrier based aircraft. The first set of R&M equations alsocontained variables such as mission length and maximum ceiling which could not accurately beextrapolated to values representative of space vehicles. Finally, these equation were not weightbased making them difficult to use in those cases where vehicle design had not progressed muchbeyond the determination of subsystem weights. Nevertheless, many of these equations resultedin a good fit to the data (e.g. high R-squared values) and are presented in Attachment 3. Theremainder of this chapter is based primarily upon the Air Force data base presented in ChapterII.
Table 4 identifies the subsystems by military aircraft work unit code (WUC) and shows themapping of WUC's to NASA's Work Breakdown Structure (WBS) for space vehicle subsystems.The mapping in some cases is only approximate. For example, WUC 14XXX, flight controls,includes control surfaces whereas WBS 1.12, actuators, does not. Miscellaneous utilities (WUC49XXX) and Personal Equipment (WUC 96XXX) may include oxygen masks, communications,goggles, maintenance crane, fire protection and warning devices, water systems, flashlights,ladder, cooler, toilets, etc., while WBS 1.15 personnel provisions includes food, water, wastemanagement and seats.
Similarly, WBS 1.16, recovery and auxiliary systems, includes parachutes, escapesystems, separation systems, docking system and manipulator system, which, in turn, is mappedto emergency equipment (survival kit, emergency oxygen system, emergency lights, search andrescue systems, parachute system, life raft, life vest, evacuation system, escape slide), dragchute, explosive devices (ejection seats devices, escape initiating systems, and canopy removalsystem). During implementation of the equations, adjustments can be made to the parametersto account for the approximate nature of the match between the WBS and WUC structure. Todevelop a complete match would involve developing equations at a much lower level of both theWBS and WUC structures.
24
Table 4WUC to WBS Conversions
WBS
1.1
1.2
1.3
1.4
1.5
1.6
1.7
1.8
1.9
1.10
1.11
1.12
1.13
1.14
1.15
1.16
Wing Group
Tail Group
Body Group
Thermal Protection System
Landing Gear
Propulsion
Propulsion, RCS
Propulsion, OMS
Prime Power
Electrical
Hydraulics/Pneumatics
Actuators
Avionics
Environmental Control
Personnel Provisions
Recovery & Auxiliary Sys
WUC
11XXX
12XXX
13XXX
23XXX
24XXX
42XXX
44XXX
45XXX
14XXX
51XXX
52XXX
55XXX
61XXX
62XXX
63XXX
64XXX
66XXX
71XXX
72XXX
41XXX
47XXX
49XXX
96XXX
91XXX
93XXX
97XXX
Airframe
Crew Compartment
Landing Gear
Propulsion System
Aux Power Units-APU
Electrical
Lighting System
Hydr/Pneumatics
Flight Controls
Instruments
Autopilot
Malfunc Anal Rec
HF Comm
VHFComm
UHF Comm
Interphone
Emergency Comm
Radio Navigation
Radar Navigation
Environ Control
Oxygen System
Misc Utilities
Personnel Equipment
Emerg Equipment
Drag Chute Eqpt
Explosive Devices
25
WUC 11XXX (airframe) was mapped into WBS's 1.1 (wing group), 1.2 (tail group), 1.3(body group), and 1.4 (TPS). The distribution of failures was based, in part, upon thebreakdown of aircraft maintenance actions of WUC 11XXX to the wing, tail, and body usingthe data in Table 5. WUC 12XXX (crew compartment) was also mapped into the body group.The allocation of failures and manhours to the thermal protection system (TPS) was proportionalto its weight to the total weight of WBS 1.1, 1.2, 1.3 and 1.4.
Table 5WUC 11XXX Maintenance Actions
AIRCRAFT
B-52
KC-10A
F-15E
F-4E
F-16C
F-16A
TOTAL
PERCENT
TAIL
417
37
-
32
787
272
945
.014
WING
7417
212
203
1225
2430
2109
13,393
.202
BODY
22,501
1,427
2,388
5,575
8,809
13,116
52,028
.784
TOTAL
30,335
1676
2591
6832
12,026
15,497
66,366
1.000
In many cases, work unit codes were combined into a single WBS using Table 4 before derivinga regression equation. WUC's 42XXX (electrical) and 44XXX (lighting) were combined underWBS 1.10 (electrical distribution). WUC's 41XXX (environmental) and WUC's 47XXX(oxygen systems) were combined under WBS 1.14 (environmental control system). All avionicsWUC's were combined under WBS 1.13 (avionics). WUC 23XXX (propulsion system) wascomputed separately for WBS 1.6 (propulsion), 1.7 (RCS), and 1.8 (QMS) using theircorresponding weights.
B. Regression Analysis
Multiple linear regression procedures were used to develop each of the parametric equations.A "best fit" was defined as the simplest mathematical model having a significant Rvalue, a largeR-squared value, and a small standard error. Generally, only independent variables which weresignificant (based upon a t-test) were included in the final model. Several models weremarginally significant but retained nevertheless. A secondary criterion for model selection was
26
the practical test that the model would provide reasonable results over the anticipated range ofindependent variable values. Because of the difference between aircraft and space vehicleparameters, extrapolations outside the domain of the input data were expected. Nonlineartransformations of the independent variables were also included in the model if they significantlycontributed to the prediction power of the equation. Generally these transformations consistedof squaring, taking logarithms or square roots of the variables.
An investigation of the residuals would, on occasion, identify one or more data points asoutliers (two or more standard deviations from the mean). At times these outliers were deletedfrom the data base. This was based upon the strong possibility that the AFALDP 800-4 datawas incomplete. This is particularly true for the Vol VI data which contains a warning to thiseffect. In processing AFM 66-1, the monthly tapes from the bases may not contain all of thefailures logged for that month. On the other hand, the monthly flying hours and sorties reportedthrough a different data system is almost always complete. The net result is an overstatementof the MTBF. This was normally the case when outliers were observed.
C. Analysis of Weights and Secondary Variables
Several variables were identified as primary or "driver" variables. These include (1)vehicle dry weight in pounds, (2) the sum of the vehicle length and wing span in feet, (3) crewsize, and (4) number of passengers. Values for these independent variables were based uponreferences [8] and [13] and are found in Appendix G. Using these four driver variables,regression equations were derived to estimate subsystem weights and secondary variables. Table6 displays the weight equations and Table 7 displays the secondary variable equations. As aconceptual vehicle becomes better defined, it is expected values for these variables will beobtained from the design specifications and will need not be estimated from the "driver"variables. With the exception of Prime Power (WBS 1.9) and Avionics (1.13), there areexcellent least-squares fits to the data. The number of aircraft in the data base having an APUweight is quite small and its weight is not as dependent with vehicle size as are othersubsystems. The engine weight equation was not used since aircraft engines are not comparableto spacecraft engines. Instead, a percentage of dry weight was allocated to each propulsionsystem and the TPS. Avionics weight is not as highly correlated with vehicle size as are theremaining subsystems. Observe that the secondary variable equations must be evaluated in aparticular order since several of these equations require values derived from the previoussecondary variable equations. Correlation of these equations vary from under 60 percent to over99 percent.
27
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Table 8Weight Distribution
WBS
1.1
1.2
1.3
1.4
1.5
1.6
1.7
1.8
1.9
1.10
1.11
1.12
1.13
1.14
1.15
1.16
SUBSYSTEM
WING
TAIL
BODY
TPS
LANDING GEAR
PROPULSION
PROPULSION, RCS
PROPULSION, QMS
APU (PRIME POWER)
ELECTRICAL
HYDRAULICS/PNEU
ACTUATORS
AVIONICS
ECS
PERSONNEL PROV
RECOVERY & AUX
AVE VEHICLE
AVERAGE
.091
.003
.140
.099
.053
.019
.029
.017
.151
.059
.021
.007
.061
.083
.070
.097
1.00
30
D. MTBM Equations
Based upon the "driver" variables, subsystem weights, and the secondary variables,regression equations were derived to estimate MTBM. These equations are summarized in thefollowing table with the regression analysis provided in Appendix J. The estimated MTBMrepresents an unadjusted number and reflects aircraft reliability as captured in the data base.With the exception of Propulsion (WBS 1.6-1.8), acceptable correlations were obtained with theregression models. Aircraft engine failures were estimated exclusively from engine weight inorder to utilize the equation for each Propulsion WBS and to provide a reasonable approach forextrapolating aircraft engine results to space vehicle propulsion systems. It is expected that thisequation will be replaced as data on space propulsion systems becomes available.
31
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The estimated MTBM is adjusted for technological change. In deriving the adjustmentfactor, a learning curve of the form given by Equation (2) is determined by using least-squares.These curves are summarized by subsystem in Table 10. Three separate equations were derivedusing historical data from the F-16B, B-l, and F-15A. Appendix Q summarizes the results ofthe regression analysis and Table 10 depicts the average growth rate (b parameter) for eachsubsystem. Only statistically significant growth rates from among the three aircraft wereaveraged. A separate analysis was performed for the overall aircraft.
Table 10.Learning Curve Results
WBS
1.1
1.2
1.3
1.4
1.5
1.6-1.8
1.9
1.10
1.11
1.12
1.13
1.14
1.15
1.16
SUBSYSTEM
WING
TAIL
BODY
TPS
LANDING GEAR
PROPULSION
APU (PRIME POWER)
ELECTRICAL
HYDRAULICS/PNEU
ACTUATORS
AVIONICS
ECS
PERSONNEL PROV
RECOVERY & AUX
VEHICLE
AVE GROWTHRATE (b)
.1534
.1534
.1534
—.1480
.2305
.1927
.1333
.1703
.1608
.2427
.1555
.0683
.3592
.1370
Using the methodology discussed in the previous chapter, technology adjustment factors werethen derived. These factors, displayed in Table 11, represent an average annual growth ratebased upon a compound growth curve derived from the pairwise comparisons shown inAppendix R. One subsystem, electrical, resulted in a negative growth rate which was set equalto zero. A combined avionics growth rate of .42 appeared to be excessive and was replacedwith an adjusted rate obtained by deleting the F-4E - F-16A comparison which had a 0.978
33
annual growth rate. The rates shown in Table 11 represent the default values used in theimplementation phase. In implementation, the TPS subsystem defaulted to the structuralsubsystems (WBS 1.1, 1.2, 1.3) growth rates. The APU growth rate was not computed becauseof insufficient data. The aircraft rate was used as a default value.
Table 11Technology Growth Rates
WBS
1.1
1.2
1.3
1.4
1.5
1.6-1.8
1.9
1.10
1.11
1.12
1.13
1.14
1.15
1.16
SUBSYSTEM
WING
TAIL
BODY
TPS
LANDING GEAR
PROPULSION
APU (PRIME POWER)
ELECTRICAL
HYDRAULICS/PNEU
ACTUATORS
AVIONICS
ECS
PERSONNEL PROV
RECOVERY & AUX
AVE TOTAL
AVERAGE
.08184
.08184
.08184
—.03352
.01116
.0557
-0.02090
.09222
.05622
.41915 (.22)
.00617
.03571
.08358
.0557
Regression equations for subsystem critical failure rates were derived from MODASobtained aircraft air/ground abort rates found in Appendix N and displayed in Table 12. ForWUC's 24XXX, 49/96XXX, and 91/93/97XXX, averages were used since the number of datapoints were insufficient to properly fit a regression curve. Regression results may also be foundin Appendix N. Because of the processing time required to obtain the abort rates, theseequations are based upon a smaller sample size consisting of 13 aircraft. Each subsystem andeach aircraft data point had to be retrieved separately from the MODAS ABORT SUMMARYREPORT. In general, there is a high correlation between vehicle size as measured by DRYWEIGHT or LENGTH plus WING SPAN and abort rates.
34
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Predicted maintenance manhours per maintenance action were obtained from regressionequations using primary, secondary and subsystem weight variables. These equations arepresented in Table 13. Appendix K contains the regression analysis.
Marginal correlations were obtained for several subsystems including electrical, andoxygen subsystems. For those subsystems average manhours per maintenance action remainssomewhat constant across aircraft. However, except for landing gear and oxygen, the fittedequations were significant at the 10 percent level and therefore partly explain the variation foundin this parameter. In order to separate the on and off vehicle work being performed, the percentof off-equipment (POFF) manhours was also estimated from regression equations. Theseequations are identified in Table 14.
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Limited data is maintained on military aircraft pertaining to scheduled maintenance.These tasks fall into two categories: preflight/postflight inspections and periodic maintenance.For AF aircraft, total maintenance manhours expended in both areas are recorded in AFALDP800-4. Using this data pertaining to 27 different data points, a regression analysis wasperformed with the results summarized in Table 15. Scheduled maintenance manhours ispredicted as a percent of the unscheduled maintenance manhours. Once total unscheduledmaintenance is computed, then the predicted percentage is applied to obtain the total scheduledmaintenance.
Table 15.Scheduled Maintenance Manhours
As a percentage of UNSCHEDULED Maintenance Manhours:
%UNSCH = 0.844224 + .002638 X (LENGTH + WING)+ .00003379 X (WETTED AREA) - .005231 SQRT (DRY WT)
(R = 0.922)
SCH MANHOURS = % UNSCH x UNSCH MANHOURS
G. Removal Rates
Removal rates were based on data pertaining to six aircraft: C-5A, C-130E, C-141B, F-15D, F-111A, and T-38A. Since it was not possible to obtain adequate least-square fits forWBS's 1.11 and 1.15, mean values were used. Results are depicted in Table 16 with the dataand regression analysis found in Appendix M.
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H. Crew Sizes
Average (mean) crew sizes for performing unscheduled maintenance are predicted fromderived regression equations. The input data for this analysis was obtained from the MODASmaintenance summary reports which provided by aircraft and by subsystem total maintenancemanhours and total elapsed time. The crew size analysis may be found in Appendix O and issummarized in Table 17. By dividing the maintenance manhours by elapsed time, an averagecrew size was obtained. For this analysis, crew sizes were estimated at the one digit (or higher)level. Because of the difficulty and time in extracting this data from MODAS, the data wasobtained at the higher level. The resulting equations are in Table 18. No significant fit couldbe obtained for WUC's 2XXXX and avionics (5XXXX, 6XXXX and 7XXXX). Therefore themean value was used. Neither propulsion repair crew size nor avionics repair crew size seemto be related to aircraft size.
Table 17Repair Crew Size Data
(by WUC)
AIRCRAFT
A7DF111E
F4E
F15C
F16A
C130E
KC135
C141B
C5B
1XXXX
1.66
2.66
1.80
2.03
1.90
2.12
1.90
2.30
2.09
2XXXX
2.44
2.85
2.37
2.26
2.37
2.00
2.53
2.99
2.11
4XXXX
1.58
2.73
2.04
2.18
2.02
2.21
2.39
2.26
2.22
AVIONICS
2.01
2.42
2.28
2.21
2.21
1.98
2.42
1.98
2.10
9XXXX
1.762.87
1.88
2.00
2.17
2.02
2.03
2.12
2.42
41
Table 18Crew Size Regression Equations
wuc1XXXX
2XXXX
4XXXX
AVIONICS
9XXXX
WBS
1.1-1.5, 1.12
1.6-1.9
1.10, 1.11, 1.14
1.13
1.15, 1.16
EQUATION
1.5 -3.m*E-5(WET AREA)+ 9. 1722£-3 JWET AREA
AVE = 2.44
-1.48 -2S33E-3(LEN + WING)+ M466LOG(LEN + WING)
AVE = 2.18
1. 78933 +9.8722£-4v/D/?r WT
R
.737
™
.774
—.759
An empirical crew size distribution was obtained from the MODAS Detail Maintenance Datareport which identifies the start and stop time of each maintenance activity along with theassigned crew size. The crew size distribution and average (mean) crew size were found (Table19). Since this distribution was based on over 130 individual maintenance tasks, it is assumedto be representative of the crew size requirements for this particular component (AC powersystem) on B-1B.
Table 19Crew Size Probability Distribution
AIRCRAFT ISWORK UNIT CODE ISNOMENCLATURE IS
CREW SIZE PROB CUM PROB
B-1B42B**AC POWER SYSTEM
1.002.003.004.005.006.007.008.00
0.110.520.330.030.010.010.000.00
0.110.630.960.990.991.001.001.00
AVERAGE CREW SIZE IS 2.326485
42
I. Repair Distribution
Using August 1990 data from the Bl-B bomber, MOD AS provided start and stopmaintenance times for each failure record in the system (see Table 20). Using the repair timescomputed from these values, a Chi-square goodness of fit test was conducted to determine asuitable distribution. Because of the tendency to report times in whole hours (or 30 minuteperiods), the data had to be aggregated into four intervals. A significant fit was obtained usingeither the Weibull or lognormal distributions (see Tables 21). Follow-on research will attemptto analyze repair distributions more fully.
43
Table 20Repair Time5 Data
Repair Time Observations
NASA Bl-B WUC 42B TIHE-TO-RKPAIR
UBIBiBII ARIIAT OP OBSERVATIONS
5 5 5 $ 55 5 10 10 IS20 20 20 20 2025 25 30 10 JOSO 30 30 30 3030 30 30 30 3030 30 30 30 3030 30 30 30 3030 30 30 30 3040 58 (0 10 1010 10 10 10 fO(0 «0 CO «0 fO(0 (0 (0 (0 10<0 SO SO 60 SOso to so so soSO SO SO SO SOso so so so so•0 SO SO 00 •••0 00 SO 00 SO00 00 »0 00 (0•o to to to to•o to to in tn118 1*0 120 ISO ISO1X0 110 1X0 1X0 1X01X0 120 120 1X0 1X01X0 1X0 120 1X0 1X01X0 1X0 1X0 1X0 1X0ISO 1X0 120 120 ISO1«0 110 ISO ITS ITSISO 110 110 ISO ISOISO 110 100 ISO 240240 240 240 240 240240 240 240 240 240240 240 2TO 2TO JSI300 300 300 300 300300 330 300 301 420420 410 410 400 410
DUUUIMITE STATISTICS
SAMPLE SIZE 1SSMEAN 1124432Amttnt so* COIF INTERVAL IOOLSOST i2S.srrtMEDIAN , SOVARIANCE 1 OSTO.STSTARDAU DETIATIOM 10X4131VARIANCE/MEAN RATIO 1344)400cuifFitmrr or VARIATION .totooxs
4TSM) 1.000341
10* CRITICAL VALUES FOR 81-0 -.1003412 .2002412HimiUSIS-fB2> S.2SST1310* cxrr VALUES FOR B2-J <NORMAU 2.iorso4 3.103407
'Time is in minutes.
44
Table 21Goodness of Fit Tests
Repair Time Distributions
CBI-SQVARE COMPUTATION
WBBOLL WITH SCALE PARAMETER* 120 AND SHAPE PARAMETER* 1.17
CELL LOVER UPPER OBS ED? <O-EJ»2/E1.00 0.00 41.37 48.00 4ff«S8 0.002.00 41.37 37.T3 Si.OO 41.26 0.4*3.00 37.73 ! 31.04 46.00 48JS 0.004.00 158.84 9900.00 42.00 48.18 0.38
CHX-SQVABZ STATISTIC* .8810111 OEOREES OF FREEEDOM- 198* CRITICAL VALUE- 3.S4 90* CRITICAL VALUE- 2.71
CANNOT REJECT AT IDS LEVEL
MEAN OF LOONORMAL- 121.80tt WTTB STND OEV- .9832414
CELL LOWER UPPER OBS EXP (O-EV2/E1.00 -9900.00 3.08 48^0 48^8 0.032.00 3.88 4.32 52.00 48^8 0.713.0O 4^2 4.08 49.00 4U8 0^84^0 4.08 9900.00 4MO 48^8 0.00
CRI-SQUABE STATISTIC- 1.140*41 DECREES OF FHEEEDOM- 198* CRITICAL VALUE* 3.84 90* CRITICAL VALUE- 2.71
CANNOT REJECT AT 10* LEVEL
45
An attempt to derive a failure time distribution from the MODAS data was more difficult.MODAS provides the Julian date and time (although time does not appear to be very accurate)of each failure. However flying hours (and sorties) are reported monthly. Therefore it isimpossible to determine from this data set the actual flying hours between failures. However,it may be possible to show in some cases that the number of failures per flying hour is Poissonby taking failures per month and converting to failures per flying hour. Therefore the time(flying hours) between failures would be exponential. This approach will be investigated in thefollow-on effort.
46
CHAPTER V
Implementation
I. INTRODUCTION
This chapter describes the PC based model for evaluating the reliability and maintainabilityequations derived in the previous chapter. Because of the large number of equations to beevaluated and the large number of additional calculations, the only practical way to implementthe results of this research is on a computer. This PC based model is completely menu drivenwith all parameters computed at the subsystem (WBS) level and then rolled up to reflect overallvehicle performance.
Flying hours between maintenance actions, maintenance manhours per maintenance action,critical failure (abort) rates, percent on/off vehicle hours, removal rates, and crew sizes areestimated using the multiple regression models derived from aircraft data. Lower bounds (andin some cases upper bounds) are set if the equations predict values outside the limits of the inputdata. In addition to predicting failures and repair manhours, estimates of mission reliability,spares support, manpower requirements, and fleet size are also made.
The computer model is design to evaluate all 16 major subsystems as defined by the NASAwork breakdown structure (WBS). Upon execution of the model, the user may elect to deleteany number of these subsystems from the analysis.
II. Modes of Operation
A. The model operates in one of three modes: PRECONCEPTUAL, WEIGHTDRIVEN, & WEIGHT/VARIABLE DRIVEN. In mode 1, PRECONCEPTUAL, the user mustspecify 4 driver variables and 10 system parameters. The driver variables are used to estimatesubsystem weights and secondary variable values from the multiple regression models derivedfor this purpose. These 4 variables and the 10 system parameters are listed below as theyappear on the first menu. When operating in Mode 1, the user will bypass the weight andsecondary variable menus shown below. However, changes to the primary variables will resultin both weights and secondary variables being recomputed. The user has the option of havingweights computed by the regression (aircraft) equations or by the weight distribution presentedin Table 8. The user must specify the average crew size for scheduled maintenance activity.However, the model will compute crew sizes for unscheduled maintenance based upon theregression equations in Table 18. The default value for the technology growth factor is theestimated factor (see Table 11) for the overall vehicle. The user may elect to replace asubsystem growth factor with this value on a subsequent menu. The Weibull shape parameterdefault value is based upon a previous study [11] and is used in determining the MTBM adjustedfor the time in orbit. The launch factor applies to the booster phase of the mission. Availablehours per month is the average number of working hours a month, and the percent indirect work
47
refers to all work accomplished by the individual which is not accounted for in the maintenancemanhour equations.
Figure 4Driver & System Variables
INPUT MODULE - PRIMARY INDEP VARIABLESNBR
1234
567891011121314
VARIABLE
VEHICLE DRIVER VARIABLES
DRY WGT (LBS)LENGTH+WING SPAN (FT)CREW SIZENBR PASSENGERS
SYSTEM PARAMETER VALUES
TECHNOLOGY YRDEFAULT TECH GROWTH FACTOR"TEBUTfT- SHAPE PARAMETERLAUNCH FACTORAVAIL MANHRS /MONTHPERCENT INDIRECT WORKSPARE FILL RATE OBJAVG CREW SIZE-SCHD MAINTPLANNED MISSIONS /MONTHWGT IND O-PCT/1-EQS
CURRENT VALUE
900010028
1994.0557.2820144.15.951.811
48
B. In Mode 2, WEIGHT DRIVEN, the user may input/change subsystem weights.This should result in more accurate estimates. Secondary variables may be recomputed fromthese weights, however, the secondary menu will not be displayed and the user cannot updateit. As subsystem weights are updated, the total weight is recomputed. The overall vehicledry-weight is set equal to this new total weight regardless of the initialvalue on the first menu. The subsystem weight menu is shown below:
Figure 5Weight Menu
NBR
1 .2345678910111213141516
TOTAL
SUBSYSTEM WEIGHTSSUBSYSTEM
1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIHE POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS
WGT
WEIGHT IN LBS
1846.976364.95962319.57849.7662347.247777.25148309.0059154.503114.4622263.2065253.3027429.6665501.S043348.434247.32994772.5147
9000
49
C. Mode 3, WEIGHT/VARIABLE DRIVEN, allows the user to specify and changeboth subsystem weights and 12 secondary variables. These secondary variables provide for moreaccurate regression equations as measured by the R value (MultipleCorrelation coefficient) and the standard error of the estimate (a measure of the variability ofthe estimated value. This mode, therefore, should result in the most accurate assessments.However, the vehicle must be sufficiently defined to enable theuser to assign values to these variables. Definitions of these variables may be found inAppendix F. Default values are computed values from the regression equations. These are thesame values which would be used in Modes 1 and 2. The user may run the model in Mode 3,and by not changing the weight or secondary variable values, generate the same results as Mode1.
Figure 6Secondary Variable Menu
SECONDARY INDEP VARIABLES
NBR
123456789101112
VARIABLE
FUSELAGE AREAFUSELAGE VOLUMEWETTED AREANBR m"UBT.sNBR ACTUATORSNBR CONTR SURFACESKVA MAXNBR HYDR SUBSYSNBR FUEL TANKS ( JJ»u:i5«ilAL)TOT NBR AVIONICS SUBSYSNBR DIFF AVIONICS SUBSYS3TU COOLING
CURRENT VALUE
4781185.1831996.13135724.1249184161686.46997
III. Additional Input Parameters
A. Subsystem Calibration
To provide sufficient flexibility to transition from the aircraft system to the space vehiclesystem, a calibration factor is included. This factor is used in modifying the aircraft computedMTBM AND MH/MA where CALIBRATED MTBM = CAL FACTOR x AIRCRAFT MTBMand CALIBRATED MH/MA = CAL FACTOR x MH/MA. The default value is one. Withthese two factors, the R&M parameters may be calibrated by subsystem based upon non-aircraft
50
data (e.g. Shuttle data) in order to account for those differences between aircraft and spacevehicles which are not accounted for by the variables in the aircraft generated equations.
Figure 7Calibration Menu - MTBM
SUBSYSTEM MTBM CALIBRATION
NBR
12345678910111213141516
SPACE VEH-MTBM = CAL FACSUBSYSTEM
1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS
XFACTORACPT-MTBM
.CAL FACTOR
1111111111111111
51
Figure 8Calibration Menu - MH/MA
SUBSYSTEM MH/MA CALIBRATION FACTORCAL MH/MA - CAL FAC X COMPUTED-MH/MA
NBR
12345678910111213141516
SUBSYSTEM
1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROFULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS
CAL FACTOR
1111111111111111
B. Mission Profile and Subsystem Operating Hours
In order to adjust for the time spent in space and to account for ground operating times,the following mission profile menu is provided (see Figure 4):
52
Figure 9Mission Profile Menu
MISSION PROFILE
NBR TIME IN HOURS
1 GROUND TIME PRIOR TO LAUNCH 2
LAUNCH TIME AT T=0
2 BOOSTER COMPLETION TIME .143 ORBIT INSERTION TIME 14 ORBIT COMPLETION TIME 715 GROUND RECOVERY TIME 72
From the selected profile, subsystem operating times are determined and displayed in thefollowing manner:
53
Figure 10Subsystem Operating Times
SUBSYSTEM OPERATING TIMESTOTAL MISSION TIME " HRS MAX GROUND TIME;IBR
12345673910111213141516
SUBSYSTEM GROUNDTIME
1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TFS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS
2222222222222222
BOOSTERTIME
.14
.14
.14
.14
.14
.14
.14
.14
.14
.14
.14
.14
.14
.14
.14
.14
2 HRSREM TIMETO -ORBIT
.86
.86
.86
.86
.86
.86
.86
.86
.86
.36
.86
.86
.86
.86
.86
.86
ORBITTIME
70707070707070707070707070707070
RECOVERYTIME
1111111111111111
The user may then uniquely adjust each subsystem based upon its mission profile. In computingspace adjusted MTBM's, the ground segment, non-booster time to orbit, and recovery segmentshave constant failure rates based upon the calibrated MTBM as adjusted for technology and thesteady-state ground/air/space environment. During the launch (booster) segment, the failure rateis increased by the launch factor (system parameter number 8). During the orbit segment, thefailure rate is assumed to be decreasing based upon the Weibull shape parameter (systemparameter number 7).
54
C. Technology Factor
The default technology factors used by the model are those presented in Table11. The user may replace any one of these with the system value displayed on the first menu.
Figure 11Technology Factor Display Menu
OPTION TO USE DEFAULT RATE
MBR
12345678910111213141516
FOR ANNUAL RELIABILITY
SUBSYSTEM
1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OHS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS
GROWTH FACTOR
ANNUAL GROWTH RATE
.082
.082
.082
.082
.033
.011
.011
.011
.0540.092.056.22.0062.036.083
IV. Computations
A. MTBM (mean operating hours between maintenance actions)
An aircraft MTBM is first computed by evaluating the regression equations. Then thecalibration factor is applied to obtain the calibrated MTBM. A technology adjustment to accountfor increases in reliability in obtained by:
ADJ MTBM = (1+TECH GROWTH FAC)(tech ***> x CAL MTBM
where 86 reflects the baseline year of the input data.
55
The primary MTBM used in subsequent calculations is based upon the adjustment foroperating in the launch and space environment (SS MTBM). This adjustment uses the subsystemmission profiles as previously discussed. As a result of the decreasing failure rate, a numericalintegration must be performed for each subsystem. Therefore, this process may take severalseconds to a minute to complete.
A critical MTBM is based upon a critical failure or abort rate and is found from:
CRIT MTBM = SS MTBM / ABORT RATE
Corresponding to and computed from the subsystem critical MTBM is a subsystem missionreliability. This reliability may be interpreted as the probability the subsystem will complete themission without a critical failure. This reliability also depends upon the subsystem missionprofiles (operating times). A vehicle mission reliability is obtained by multiplying the subsystemreliabilities.
B. Maintainability Parameters
The initial calculation is the determination of the subsystem maintenance manhour permaintenance action (MH/MA) obtained by evaluating the corresponding regression equations.This value is then adjusted by the maintainability calibration factor. Total maintenance actionsper mission (TOT MA) is found by
TOT MA = TOT OPER HRS / SS MTBM
Then total manhours per mission (MH) is calculated by:
TOT MH = MH/MA x TOT MA
These manhours are then split into on-vehicle and off-vehicle manhours using the regressionestimated percent of off/on-vehicle manhours. Scheduled maintenance manhours per missionis based upon a regression estimated percent of unscheduled maintenance applied to the totalunscheduled maintenance manhours. Scheduled maintenance is also broken down into on andoff-vehicle work.
To convert total manhours into manpower requirements, the following calculations areperformed:
MANHRS/MO = TOT MH x MISSIONS/MO
Then
NBR PERSONNEL = MANHRS/MO / {AVAIL MANHRS/MO x (1-% INDIRECT)}
56
and NBR PERSONNEL is rounded up to the nearest integer if the fraction portion exceeds .001.This is done by subsystem.
C. Spares
Spares levels for each subsystem are determined using a single mission fill rate goalspecified on the first menu. Fill rate refers to the percent of time a spare will be available whena demand (failure) is generated. The average number of demands (MFAIL) are determined froman estimated removal rate (RR) as follows:
MFAIL = RR x TOT MA
This becomes the mean of a Poisson probability distribution. The spares level is iterativelyincreased by one unit until the probability of demands not exceeding the spares level reaches orexceeds the fill rate objective (system variable number 11). The achieved fill rate and computedspares level are then retained for display.
D. Vehicle Turn Time
For each subsystem, an average task time is found from:
AVG TASK TIME = MH/MA / AVG CREW SIZE
Average hours (clock time) on-vehicle time per mission becomes:
ON-VEH HRS/MSN = TOT ON-VEH MH /AVG CREW
The subsystem on-vehicle times are summed together in order to obtain a maximum vehicle turntime. This assumes each task must be accomplished sequentially. Since this is probably not thecase, it provides an upper bound on vehicle turn time. On-vehicle scheduled maintenance is alsoadded to this sum to obtain a total turn time. By adding the mission time (including groundprocessing time) to this total, a complete vehicle turnaround time is obtained. This is convertedto days under the assumption that the mission time will occur on a 24 hour/day basis but thescheduled and unscheduled work would occur on a 8 hour/day basis. For a given vehicle, thenumber of missions per month is found by
VEH MSN/MO = (WORKING DAYS/MO) /TURNAROUND TIME IN DAYS
The fleet size is computed from:
FLEET SIZE = (MSN/MO) / (MSN/MO/VEH)
rounded up to the nearest integer.
57
V. Output Reports
The following figures are examples of the output displays resulting from running the modelSeparate screen displays are found for the reliability calculations, maintainability calculations^spares levels, and vehicle turn time analysis.
VEHICLE IS TEST VEH
WBS
Figure 12Reliability Report
RELIABILITY REPORTDATE: 06-11-1992
CALIBRATED MTBM
1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OHS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS
VEHICLE
34.72139500.98294.63618537.401936.25531831.4318228.9158730.37121121.27745.1546.9502622.5884627.1306228.538232S9.32253.802
1.140834
TECH ADJ
65.22554941.11138.70921270.260643.11057934.306731.5606333.14908184.7165.1594.9334134.92995133.149229.984784325.19480.311
1.558437
TIME: 16:25:32
SPACE ADJ
333.58875072.35730.29372360.785427.23173166.8098152.0331160.5794979.675412.77312494.1188170.1649700.7554143.558323383.492S78.978
5.248452
VEHICLE IS TEST VEHWBS
1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPSI'.S LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS
VEHICLE
RELIABILITY REPORT - page 2DATE: 06-11-1992
CRITICAL CRITICALFAIL RATE MTBM
1.831055E-021.831055E-O21.895309E-021.831055E-024.266358E-02.035484.035484.035484.064.00248.000845.542377E-02.023764.817755E-02.0185.004678
18218.39277018.31598.35319703.69638.28984700.9884284.5544525.40415307.435150.451588236.63070.25129493.072979.7761263973551299.3
254.6037
TIKE: 16:25:43SUBSYSMSH RELIABILITY
.9992496
.9999506
.9914805
.9993061
.9788026
.9970951
.9968133
.9969826
.999107
.9973483
.9999768
.9955556
.9995364
.9954211
.9999891
.9999752
.9477038
58
Figure 13Maintainability Report
VEHICLE IS TEST VEHWBS
MAXHTAZHABZLT? REPORTDATE: 06-11-1992
MAHHR/MA TOT HA
1.1 WING GROUP1.2 TAIL CROUP1.3 BODY GROUP1.4 TPS1.5 LAUDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-QMS1.9 PRIME POWER1.10 ELECTRIC COHV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTDATORS1.13 AVIOaiCS1.14 mv.nujhimre'AL CONTROL1.13 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTERS
SCHEDULEDTOTALS
TIME: 16:26:08TOT HANHRS
9.0976289.09762812.18929.0976284.37683249.3434145.9953647.880925.24.4990228.4466172.1S.4404916.1236596.89484.051671
14.35193 (AVG)
.22183011.4588B8E-022.442751.20510812.717419.443619.4867361.46083127.S53S23E-025.793417.1497616.4348724.1056003.51547013.164626B-032.869354E-02
14.0994
2.018128.132724229.775171.86599712.4371721.8453122.387622.06502.392783226.041541.264979.9132319.57491763.1S6S632.087008E-02.1162968
77.19669222.2046
VEHICLE IS TEST VEHWBS
1.1 HXRC GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPSl.S LAUDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-QMS1.9 PRIME PUMUt1.10 ELECTRIC COHV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 EMVIKONMEHTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY I AUX SYSTEMS
MAXBXAZKABZLTY REPORT - paqa 2DATE: 06-11-1992
OH-VEH MH
1.849614.121641727.221951.7101868.8058346.007466.1565896.06788.380999720.123331.212454.69*3355.42915392.9123911.7837S7E-027.680828E-02
TOTALS75.65276159.4392
! TIME: 16:26:35•VEH MH PERCENT ON-VEH
.16891361.108247E-022.553221.13581073.63133515.8378516.2310115.99714.01178355.9182075.232423E-02.2168965.1493637.24417223.032502E-033.944849E-02
1.54393462.76932
.9165
.9165
.91425
.9169
.7080296
.279
.279
.279
.97
. 7727397
. 9584781
. 7624958
.740019
.9226462
. 3946961
. 660678
.7399081
WBS
MAIHTAINABTLTY REPORT - pag» 3IS TEST VEH DATE: 06-11-1992
MMBBS/KSB MAKBRS/MO
1.1 N1N6 GROUP1.2 TAIL GROUP1.3 BODY uKuur1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-QMS1.9 t'klRE PONER1.10 FTJU.TKIC COHV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIOHieS1.14 fcitv j KOHHEHTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS
77.19669TOTAL
77.19669145.0079
TUBS 16:27:26NBR PERSONNEL
2.018128.132724229.779171.86999712.4371721.8453122.387622.06502.393783226.041541.264979.9132319.57451763.1369632.087008E-02. 1162968
2.018128.132724229.775171.86999712.4371721.8493122.387622.06902.392783226.041541.264979.9132319.57431763.1963632.087008E-02.1162968
1111111111111100
115
59
w
Figure 14Subsystem Spares Report
VEHICLE IS TEST VEHwas
SUBSYSTEM SPARES REPORTDATE: 06-11-1992 TIME: 15:27-37
REM RATE AVG DEMAND SPARES RQMT FILL RATE
1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS
TOTALS
.1919366
.1919366
.2227305
.194
.22
.5992393
.5773786
.5901843
.5077349
.5007281
.368
.38593
.4140355
.5070317
.274
.747236
4.257731E-022.800139E-03.54407513.979097E-02.5978321.2658339.281031.27197543.835187E-022.9009275.511226E-02.16783034.372229E-02.26135968.671074E-O42.144084E-02
.4057564 (AVG) 5.535527
0020211106I10100
16
.9820489
.9820489
.9770984
.9703458
.9671848
.9690837
.9690837
.9712413
.9985361
.9873974
.9873974
.9712519
.9712519
.9712519
Figure 15Vehicle Turn Time Report
VEHICLE IS TEST VEH
WBS
VHHierr.f TURN TIME REPORTDAXE: 06-11-1992 TIKE: 16:28:03
AVG CREW SIZE AVG (ON) TASK TIME (HRS)AVG ON-VEH CLOCK HRS
1.1 WING GROUP 1.845915 4.5169871.2 TAIL GROUP 1.845915 4.5169871.3 BODY GROUP 1.845915 6.0370991.4 TPS 1.845915 4.5169871.5 LANDING GEAR 1.845915 1.7555051.6 PROPULSION 2.43 5.5728131.7 PROPULSION-RCS 2.43 5.2052351.8 PROPULSION-OMS 2.43 5.4186221.9 PRIME POWER 2.43 2.075721.10 ELECTRIC CONV/DISTR 1.98833 1.7469351.11 HYDRAULICS/PNEUMATICS 1.98833 4.0717081.12 ACTUATORS 1.845915 .86745091.13 AVIONICS 2.18 1.8468191.14 ENVIRONMENTAL CONTROL 1.98833 2.8415661.15 PERSONNEL PROVISIONS 1.935642 2.911981.16 RECOVERY & AUX SYSTEMS 1.882954 1.421622
1.0020046.589777E-O214.74713.92647054.7704432.4722062.5335762.49707.1567910.12072.6097854.3772304.19502471.4647429.215327E-034.079137E-02
60
VEHICLE TURN TIME REPORT - page 2VEHICLE IS TEST VEH DATE: 06-11-1992 " TIME: 16:28:36
MAX TURN TIMES
AVG VEH TASK TIME 3.457753 HRSSCHD MAINT MSN TASK TIME 42.02931 HRSMAX TURK TIME NO SCH MAINT 41.9891 HRSMAX TORS TIME WITH SCH MAINT 84.0184 HRSMISSION TIME -INC GROT TIME 74 HRSTOT VEHICLE TURNAROUND TIME 116.0293 HRSTOT vi-'HTPT-T? TURNAROUND TIME 8.336997 DAYSMISSIONS /MONTH/VEHICLE 2.518893FLEET SIZE 1
VI. Validation
Some model validation was accomplished by running the computer model for differentaircraft having known R&M parameters. The R&M parameters were obtained from AFALDP800-4 Volume VI, and therefore, were not part of the input data to the model. Since the averagedate of the data in Volume IV is 1988, this date was used for the technology year. The spaceadjusted feature of the model was not utilized since it obviously does not apply to aircraft.Mission profiles reflected the average mission of the aircraft.The model was run in all three modes. Table 22 and 23 compare the results of the computedMTBM values in each model with reported values from Volume VI for the F-16A and C-141Brespectively.
61
Table 22Model Validation - F16
SUBSYSTEM
STRUCTURAL
LANDING GEAR
PROPULSION
APU
ELECTRICAL
HYDRAULICS
ACTUATORS
AVIONICS
ECS
PERSON PROV
REC & AUX SYS
AIRCRAFT
MODE 1
6.2
14.0
20.7
22.8
19.9
96.8
17.4
19.9
29.7
784
88.5
1.8
MODE 2
7.8
14.2
19.2
37.0
17.3
84.9
14.1
16.1
29.7
1539
88.5
1.9
MODE 3
7.8
14.2
19.2
50.4
21.5
100.3
13.3
14.7
29.7
1539
88.5
1.9
OCT87MAR 88
7.4
11.4
20.2
23.4
16.6
58.7
13.7
16.4
36.0
493
117
1.8
APR 88SEP 88
7.5
10.1
17.8
21.5
14.4
64.8
15.2
15.6
33.5
476
224
1.7
Table 23Model Validation - C141B
SUBSYSTEM
STRUCTURAL
LANDING GEAR
PROPULSION
APU
ELECTRICAL
HYDRAULICS
ACTUATORS
AVIONICS
ECS
PERSON PROV
REC & AUX SYS
AIRCRAFT
MODE 1
3.6
1.5
9.6
147
37.3
5.6
11.1
1.7
16.6
210
120.7
.50
MODE 2
1.3
3.6
9.6
60.7
46.1
5.6
3.1
1.8
16.6
50.1
120.8
.43
MODES
1.7
7.8
9.6
54.1
39.1
5.6
5.0
1.7
16.6
50.1
120.8
.52
OCT87MAR 88
2.7
6.8
3.3
41.5
8.9
15.6
4.9
4.0
10.7
30.8
96.7
.57
APR 88SEP 88
2.3
6.3
2.6
32.0
7.6
14
4.5
3.2
9.9
23.3
87.0
.48
62
VII. User Options
At the conclusion of a run, the user has the option of repeating the analysis after changingone or more of the input parameters. Regardless of the mode, the primary variable screen willbe displayed for update. If in mode 2 or 3, the subsystem weight menu will be available forupdate, and if in mode 3, the secondary variable menu will also appear. The calibration andmission/subsystem profile menu and technology growth rates will also be available for update.
The user may also save all of the current input menus for use at a later time. The calculatedMTBMs (both space adjusted and critical operating hours between failures) may also be savedfor a more detailed reliability calculation.
63
Chapter VI
Conclusion
This report describes the data, methodology, and results of a one year research effort todevelop a model for predicting R&M parameters for conceptual space transportation systems foruse in determining operational capabilities and support costs. Whilethe model appears to work reasonable well when applied to aircraft systems, its accuracy whenused for space systems has not as yet been demonstrated.
The model is dynamic and should be updated as new data becomes available. It isparticularly important to integrate the current aircraft data base with data obtained from theShuttle and other space systems. Subsystems unique to a space vehicle such as the TPS,propulsion systems, and docking systems require data not available from aircraft. Although thisstudy has included these subsystems in a rationale way using comparabilitywith aircraft subsystems, their uniqueness requires the use of R&M parameters obtained fromsimilar subsystems in order to insure a higher degree of accuracy. As the model is used overtime, those features which seem to work should be retained while those which do not providereasonable results should be replaced. The model is modularized in the sense that any regressionequation may be easily replaced without affecting other areas of the model.
Finally, this research addressed only the major subsystems on the vehicle. The spacetransportation system includes booster rockets, launch and recovery facilities, software, andexpendable fuels, oxygen, etc. Therefore, follow-on research efforts should focus on theseaspects of the system. Much work remains as well in refining the subsystem analysis. Betteraccuracy may be achieved by analyzing component (rather than subsystem) failures and repair.Subsystems may then be defined in terms of their individual components. This would alsopermit a more explicit determination of redundancy and its effect on mission reliability.
64
BIBLIOGRAPHY
1. Aircraft Historical Reliability and Maintainability Data, Vols. V & VI, J. Osmanski, ed.Air Force Acquisition Logistics Center, Pamphlet 800-4. Dayton: Department of the"Air Force, 1988, 1990.
2. Aviation 3-M Information Reports, NAVSEALOGCEN INSTR 4790.1.Mechanicsburg: Department of the Navy, 1988.
3. Aviation Week and Space Technology, Vol. 134, No. 11. March 18, 1991.
4. Barnard, R. A. and T. D. Matteson. "Military Aircraft Maintenance - A NewConcept." Proceedings 1975 Annual Reliability and Maintainability Symposium pp. 596-600. New York: Institute of Electrical and Electronic Engineers, 1975.
5. Bloomquist, C. and W. Graham. Analysis of Spacecraft On-orbit Anomalies andLifetimes. For Goddard Space Flight Center Contract No. NAS 5-27279. Los Angeles:PRC Systems Service, 1983.
6. Brussell, E. R., K. R. Pope, and K. M. Tasugi. "Cost of Ownership - IndustryViewpoint: Parametric Analysis of Operating and Support Costs." Proceedings 1975Annual Reliability and Maintainability Symposium pp. 217-220. New York: Instituteof Electrical and Electronic Engineers, 1975.
7. Earles, D. R. "LCC - Commercial Application: Ten Years of Life Cycle Costing."Proceedings 1975 Annual Reliability and Maintainability Symposium pp. 74-85. NewYork: Institute of Electrical and Electronic Engineers, 1975.
8. Green, W. and G. Swanborough. Observer's Directory of Military Aircraft. New York:Arco Publishing, Inc., 1982.
9. Harmon, D. F., P. A. Pates, and D. Gregor. "Maintainability Estimating Relationships."Proceedings 1975 Annual Reliability and Maintainability Symposium, pp. 18-25. NewYork: Institute of Electrical and Electronic Engineers, 1975.
10. Hecht, H. and E. Florentino. "Reliability Assessment of Spacecraft Electronics." 1987Proceedings Annual Reliability and Maintainability Symposium pp. 341-345. New York:Institute of Electrical and Electronic Engineers, 1987.
11. Hecht, H. and M. Hecht. Reliability Prediction for Spacecraft. Rome Air DevelopmentCenter Final Technical Report No. 85-229, 1985.
65
12. Hintle, Jerry. "Number Cruncher Statistical System, Version 5.03." Kaysville, UT,September 1991.
13. Jane's All the World's Aircraft, J. W. R. Taylor, ed. New York: McGraw-Hill BookCompany, 1971-1990.
14. Kern, G. A. and T. M. Drnas. Operational Influences on Reliability. For Rome AirDevelopment Center Contract No. RADC-TR-76-366. Culver City: Hughes AircraftCompany, 1975.
15. "Modular Life Cycle Cost Model for Advanced Aircraft Systems, Phase III", GrummanAerospace Corp., Bethpage, NY. Contract No. AFF DC-DC-TR-78-40, Vol. IV, Rev.3, September 1986.
16. Norris, H. P. and A. R. Timmins. "Failure Rate Analysis of Goddard Space FlightCenter: Spacecraft Performance During Orbital Life." Proceedings 1976 AnnualReliability and Maintainability Symposium pp. 120-125. New York: Institute ofElectrical and Electronic Engineers, 1976.
17. Ostrofsy, B. "Development of I.L.S. Models from R and M Data." Proceedings 1975Annual Reliability and Maintainability Symposium pp. 130-138. New York: Instituteof Electrical and Electronic Engineers, 1975.
18. Peacore, E. J. "Reliability Developments - AWACS." Proceedings 1975 AnnualReliability and Maintainability Symposium pp. 383-389. New York: Institute ofElectrical and Electronic Engineers, 1975.
19. Personnel Launch System Advanced Manned Launch System (AMLS): PLSReliability I Maintainability Analysis, Ehrlich, Jr., C. F., ed. For Langley ResearchCenter Contract No. NAS1-18975. Los Angeles: Rockwell International Space SystemsDivision, 1990.
20. Personnel Launch System (PLS) Advanced Manned Launch System Study (PLS/AMLS):Final Oral Review. For Langley Research Center Contract No. NAS1-18975. LosAngeles: Rockwell International Space Systems Division, 1990.
21. Report on the Development of a Spacecraft Supportability Assessment Model. LosAngeles: Rockwell International Space Systems Division, n.d.
22. "USAir Reliability Assurance Program Monthly Report," prepared by The Reliability andMaintenance Programs Department, Pittsburgh, PA, May 1991.
66
APPENDIX A
AFALDP 800-4 Format
AFALCF 800-4 Volime 7 Attachment 3 20 April 1988
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APPENDIX B
MODAS Report Format
Operational SummaryDate Range = January, 1990 TO December, 1991 , Base Code = ****MDS/CMD = F004E /***
Date
123456789101112123456T89101112
909090909090909090909090919191919191919191919191
FlightHours
483246075185497449954932445954343392442939683003270227773374338126582096193016749821175816619
Poss. Avg.Hours Sorties Landings Inv.
164606179401139978186269194349167411249048246912237120243360234000241800241080217728238920227580229728221304226776211698198336196536180888181536
40393757415339273986395036174481292537373399258623652342256123842095172015071205739847607521
470443364483453443684255410547633121439835842710273225072696272522541802179813387921076724640
220266190258261232335332330325325325323324320316311307305284276264252244
Percnt PercntFMC PMC
646864696866798381828086888485869092919295969798
.76
.59
.92
.08
.83
.10
.18
.59
.05
.89
.04
.26
.23
.38
.97
.62
.80
.52
.91
.99
.98
.41
.24
.04
667679334453222100000000
.68
.97
.35
.88
.85
.97
.34
.57
.72
.19
.05
.17
.38
.41
.03
.40
.73
.33
.27
.38
.16
.29
.23
.25-
PercntNMC
28:5624.4527.7224.0423.3223.9417.4812.8414.2312.9214.9110.569.3913.2112.0011.978.477.157.826.633.863.302.531.71
78394 5056364 63450 70445
B-l
Summary Maintenance Data - ManhoursDate Range = January/ 1990 TO December, 1991 , Base Code = ****MDS/WUC = F004E /ll***
Flight Hours Maintenance ManhoursOn-Eq
Date Mo Cum On-Eq; Off-Eq Sup Total Events
1 902 903 904 905 906 907 908 909 9010 9011 9012 901 912 913 914 915 916 917 918 919 9110 9111 9112 91
483246075185497449954932445954343392442939683003270227773374338126582096193016749821175816619
78394
4832943914624195982459329525339843941842810472395120754210569125968963063664446910271198731287480275784769597777578394
On-Eq
89055358824880466444454853324323425554437135490659331961308229036641127252594410281154422550
Off-Eq
2592595097165502183401986662092291776317902417133181195517
Sup
00000.00000000000 -00-000000
Total
91645617875787626994476656724342434155097344513561102024309929936881144265896210391249427567
95236 4127 99363
2203.1216182716931521110311319389859711290838928319399633246212314247254342124141
19875
MMHTK
3.563.794.224.343.863.704.283.704.034.944.954.895.665.095.074.102.624.956.813.513.723.443.023.64
B-2
Abort Summary - ON EquipmentDate Range = January, 1990 TO December, 1991 , Base Code = ****MDS/WUC = F016A /ll***
1234567
90909090909090
8 909 9010 9011 9012 901 912 913 914 915 916 917 918 919 9110 9111 9112 91
Flight
Mo
11801109321232711936116811246610915127651003311958107619011969612238115041179611696978793001030298181093688697693
Hours
Cum J
1180122733350604699658677711438205894823104856116814127575136586146282158520170024181820193516203303212603222905232723243659252528260221
;
\ir GI
i00001412102110402411002
&ort Coui
round T<
83753817425571040523543358
it
3tal
937539215465911509259543510
Cum
9121924273657626672778697102102111113118127132136139144154
Sort
MO
861876848910895386189222787594867473872678856477681785908088780480127326718079797315808966795902
:ies
Cum
86181630225212341654278352005598806936676839855659345099927106744115334123422131226139238146564153744161723169038177127183806189708
260221 28 126 154 189708
B-3
Summary Maintenance Data - FailuresDate Range = January, 1990 TO December, 1991 , Base Code = ****MDS/WUC = F004E /ll***
Flight Hours On-Equipment Failures
1 902 90345
909090
6 907 908 909 9010 9011 9012 901 912 913 914 915 916 917 918 919 9110 9111 91.12 91
MO
483246075185497449954932445954343392442939683003270227773374338126582096193016749821175816619
78394
Cum
4832943914624195982459329525339843941842810472395120754210569125968963063664446910271198731287480275784769597777578394
Tl
61037549248929225517928119767538307416408018583504410258532141.
T2
113606845672434402021723156121121196151013314
T6
1671141281201321601879587124106794729666318182312191493
Total
89054968865449143940041630421271641751981157269120748212490703148
5255 766 1820 7841
Removals
558302414370183144771499030310128215114783
: '.': 483122502320
' 710
3322
B-4
System Summary - ReliabilityDate Range = July, 1991 TO July, 1991 , Base CodeMDS/WUC = F015A /****»
Failure Count
= *ts*
MTBM
System
2 = POWER PLAN33=LOOK PH SC34=SPECIAL IN11=AIRFRAME12=CKPT &. FUS13=LANDING GE14=FLIGHT CON32=NOT DEFINEU=AIR COND P42=ELECTRICAL43=NOT DEFINE44=LIGHTING Si5=HYD AN PNE16=FUEL SYSTE47=OXYGEN SYSi9=MISC UTILI51= INSTRUMENT52=AUTOPILOT53=NOT DEFINE54=NOT DEFINE55=MALF ANAL57=INTER GUID32=NOT DEFINE53=UHF COMMUN55=IFF?1=RADIO NAVI74=FIRE CONTR75=WPN DLVRY76=TAC ELEC W31=EMERG EQUI32=TOW TARGET37=EXPLOSIVE
Removal
86500
374630281038360
3166851319149390117180898911241591116190
123
MTBR
700
17113721780
1661760
2049674487333421620
63433733520
717156156954
3330
51
Tl
68200
21543306118053300
3888771411150390119661
16917411344790163103
T2
4500
203171003101131130000405815200.01
T6
131700
24796119120899605
25731479
361625910123109091120560373116200
124
Total
204400
4821424422488
155915
6416222724483159811
31101
12642732341012465279210
128
Tl
9002914720530
1192110
16672.82453576421620
634333396
6343373656147038
63430
2114
T2
14100
31721143736340
21146343
0634363432114634363432114
0000
15850
1268792
634312683171
000
6343
T6.
4 —0 •0^
2566-5352-
792 -64-1051268253864370417639-1076343
-. o .528204
o-7069,52:111754 -3170
51.
Total
3001344-1425-7924069
12689939272641322064
6343634320462
63432423276
1322302049
TOTAL 2897 3111 135 4120 7366
B-5
System Summary - MaintainabilityDate Range = August. 1989 TO July, 1991MDS/WUC = F015B /***** F015A /**«*«
Maintenance Manhours
, Base Code = ****
On Equip. Off Equip.^IM^»«»M
MHTCSystem
01=NOT DEFINE2 = POWER PLANOSsLOOK PH SC04sSPECIAL INOSsNOT DEFINE06sNOT DEFINE07sNOT DEFINEOSsNOT DEFINEOSsNOT DEFINElOsNOT DEFINE11=AIRFRAME12=CKPT i FUS13sLANDING GE14=FLIGHT CONISsNOT DEFINE16sNOT DEFINE17=NOT DEFINEISsNOT DEFINE31=NOT DEFINE32sNOT DEFINE33sNOT DEFINE34sNOT DEFINE36sNOT DEFINE39sNOT DEFINE40sNOT DEFINE41sAIR COND P42sELECTRICAL43sNOT DEFINE44sLIGHTING S45sHYD AN PNE46=FUEL SYSTE47=OXYGEN SYS48sNOT DEFINE49sMISC UTILISOsNOT DEFINESlsINSTRUMENT5 2s AUTOPILOT53sNOT DEFINE54sNOT DEFINESSsMALF ANAL56sNOT DEFINE57sINTER GUID59sNOT DEFINE61sNOT DEFINE62sNOT DEFINE63sUHF COMMUN64sNOT DEFINE65sIFF66sNOT DEFINE69=NOT DEFINETOsNOT DEFINE71sRADIO NAVI
On-eq
0599911
00000006
268809500577059331141
5325967619233335 -
213
4653731397335
33792535461385506246103313409528
43838196604334152
79082
9441126
2912677
2651913111
34342
Off-eq
0239764
00000040
64274522418319679
226021002418000
839125912
15519562773471316
07900
1474111820
221
50970
509101619
2520443
406023300
28190
Supp
549874173219721345544554
44777327444121034
1952250000000000000000000000000000000000000000000
Total
5498741062894721345544554
44777327444121034
1952296
2752365457911242490820
75853067619437515
213
5492857309336
39311591731458977562103314199528
58579314804356153
130052
135321
1825
54330120
6712146111
62532
MH/FH
3.4646.6974.5453.4310.0030.4870.2800.0071.2300.0001.7340.3440.7080.5720.0000.0010.0000.0000.0000.0010.0000.0000.0000.0000.0000.3460.3610.0020.2480.3730.9190.0480.0070.0890.0030.3690.1980.0270.0010.0820.0000.0850.0000.0000.0000.3420.0010.4230.0000.0000.0000.394
MMHTR
0.0009.3340.0000.0000.0000.0000.0000.0000.0000.6003.8465.7785.0946.6704.4171.3332.2502.0003.4553.1765.2004.8335.0002.0000.0005.9456.4652.6293.1265.96113.4173.73913.8008.2141.0004.6787.9986.4145.5004.2240.0003.4711.0000.0002.0003.3164.7143.1402.0000.0001.0004.096
MHTR
040376
00 .o •-o -~0^OT-02or
38173389192385387"11-600 •Or:o -Ox.0*83F0 =OtOJL
678722499
04080351016605280
3170
47117613
70
28680 -
31470
13 -12-
1697941
3220527"00
13382
0000000o .0004010000000000o00o;Oi000,00000000000001000000
B-6
Maroon IndustriesRecord Type: AMDS: B001B
*«* M 0 D A S II ***Detail Maintenance Data Report
TotalTime
Summary ReportAUG 90
Cum.CrewSize
TotalMan-hours
TotalUnits
Produced
214.8 247 520.8Hit <RETURN> to continue, or "$" to end output:MO DAS II *** Page: 1Record Type: A Detail Maintenance Data ReportMDS: BOOIB
101Marcon Industries
Summary ReportSEP $0
TotalTime
Cum.CrewSize
TotalMan-hours
TotalUnits
Produced
162.0 180 306.8Hit <RETURN> to continue, or "$" to end output:Marcon Industries **t MO DAS II ***Record Type: A Detail Maintenance Data ReportMDS: BOOIB
88
Summary ReportOCT 30
TotalTime
Cum.CrewSize
TotalMan-hours
295.9 349 757.6Hit <RETURN> to continue, or "$" to end output:
TotalUnits
Produced
141
B-7
Failures selected are All FailuresReliability - MTBM (by type)
Date Range = August, 1989 TO July, 1991 , Base Code = ****MDS/WUC = F015A /74F** F015B /74F**
Flight Hours Mean Time Between Maint.Failure
Date Mo Cum Count
8 899 8910 8911 8912 891234567
90909090909090
8 909 9010 9011 9012 901 912 913 914 915 916 917 91
TOTAL
Mo
778253277402606653946587610071337369690868615732742851277004682154496182613570436757776868957449
i -
Cum
77821310920511265773197138558446585179159160660687292978661860899121698220105041110490116672122807129850136607144375151270158719
' '158719
949615845750589111262591955389779411637419611092703726955792830936916691707
19861
Monthly
8.208.668.768.099.165.929.767.76
13.337.708.644.9310.025.346.419.707.516.477.758.497.228.489.9810.54
3mo avg
8.208.388.518.508.647.367.777.469.829.049.426.837.426.387.006.887.657.747.187.517.798.048.429.56
Cum
8.208.388.518.418.537.938.148.098.508.418.438.028.167.927.797.897.877.787.787.827.797.827.907.99
B-8
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APPENDIX D
R&M Data Sources
Government:
FAAOperations Systems Branch, AVN-120PO Box 25082Oklahoma City, Oklahoma 73125
US Air Force:
Rome Laboratory/ERSR (MIL HNDBK-217)Griffiss AFB, NY 13441-5700
Aeronautical Systems Division/ENACR (System Reliability)Wright-Patterson AFB, OH 45433
HQ Air Force Logistics Command/ENIS (MODAS & REMIS)WPAFB, OH 45433
Acquisition Logistics Division (ALD Pamphlet 800-4)WPAFB, OH 45433
Aeronautical Systems Divisiou/ENSSC (LCOM)WPAFB, OH 45433
Reliability Analysis Center (RAC)PO Box 4700Rome, NY 13440-8200
Naval Air Systems Command (AIR-4114)Washington, DC 20361
Naval Maintenance Support OfficeNaval Sea Logistics Center, Code 615450 Carlisle PikePO Box 2060Mechanicsburg, PA 17055-0795
Commerciah
Airbus Industrie of North America593 Herndon ParkwayHeradon, VA 22070
American Institute of Aeronautics and Astronautics (AIAA)37 UEnfant Promenade SWWashington, DC 20024
D-l
Commercial (continued)
Boeing Commercial Air PlanesPO Box 3707Seattle, WA 98124
Boeing Computer Services7990 Boeing CourtVienna, VA 22182-3999
Douglas Aircraft Company3855 Lakewood Blvd.Long Beach, CA 90846
E-SystemsPO Box 1056Greenville, TX 75401
Harris Corporation4141 CoL GlennDayton, OH 45431
Harris CorporationGovernment Aerospace Systems DivisionPO Box 9400Melbourne, FL 32902
Hughes Aircraft CompanyRadar Systems GroupPO Box 92426Los Angeles, CA 90009
Society of Automotive Engineers (SAE), Inc.400 Commonwealth Dr.Warrendale, PA 15096-0001
United AirlinesSan Francisco International Airport (MOC/SF Airport)San Francisco, CA 91428
US Air173 Industry Dr.Pittsburgh, PA 15275
D-2
APPENDIX E
Data Generation Programs (BASIC)
Basic Program for Data Analysis
AFALDP 800-4
'PROGRAM COMBINES 6 MONTH DATA FROM ALDP 800-4'COMPUTES RiM STATS FOR VARIOUS 2 -DIGIT WUC'SKEY OFF : CLS : COLOR 3PRINT TAB (20) "CALCULATION OF AIRCRAFT R4OOM PARAMETERS'PRINT: PRINTDIM MTBM(10,10) ,MMH( 10,10 ) ,WUC$( 10)FOR J=l TO 5READNEXT
AIRCRAFT" ; ACSNUMBER OF 6-MONTH INTERVALS "; MUM
FOR 1=1 TO NUMPRINT "ENTER FLYING HOURS FORINPUTPRINTINPUTPRINT
WUC$(J)J
INPUT "ENTER. INPUT "ENTER
SORTIES FOR
LANDINGS FOR
";I;"6-MONTH PERIOD"
; I; "6 -MONTH PERIOD"
"; I; "6-MONTH PERIOD"
MTBM FOR" J WUC$ ( J )J)ON-EQUIP MMH FOR";WUC$(J)
MMH(I.J)"ENTER OFF-EQUIP MMH FOR";WUC$(J)OMMH(I,J)
FH(I)"ENTERS(I)"ENTER
INPUT L(I)FOR J=l TO 5PRINT "ENTERINPUT MTBM (IPRINT "ENTERINPUTPRINTINPUTPRINTNEXT JNEXT ICLS: COLOR 2PRINT TAB (20)LPRINT TAB (20)PRINTLPRINTFOR 1=1 TO NUMTFH=TFH+FH(I)TS=TS+S(I)TL=TL+L(I)NEXT IPRINT TAB (10) "TOT FLYING-HBS" ; TAB (40) TFHLPHINT TAB (10) "TOT FLYING-HRS" J TAB (40 ) TFHPRINT TAB(IO) "TOT SORTIES" ; TAB (40) TSLPHINT TAB (10) "TOT SORTIES" ; TAB (40 ) TSPRINT TAB (10) "TOT LANDINGS" ; TAB (40) TLLPRINT TAB (10) "TOT LANDINGS" ; TAB (40) TLPRINT: LPRINTFOR J=l TO 5FOR 1=1 TO NUM
OUTPUT RESULTS FOR"OUTPUT RESULTS FOR
;ACS";ACS
E-l
TMAINT(J)=TMAINT(J)+<1/MTBM(I,J))*FH(I)TMMH(J)=TMMH(J)+MMH(I,J)TOMMH(J)=TOMMH(J)+OMMH(I,J)NEXT ITOTMH{J)=TMMH{J)+TOMMH{J)MFHBMC J)=TFH/TMAINT(J)MSBM(J)=TS/TMAINT(J)MLBM(J)=TL/TMAINT(J)MHFH{J)=TOTMH{J)/TFHMHS(J)=TOTMH(J)/TSPRINT:PRINTLPBINT:LPRINTPRINT TAB(10) "WUC ";WUCS(J):PRINTLPRINT TAB (10) "WUC " ; WUCS ( J ) : LPRINTPRINT TAB(15) "TOTAL MAINTENANCE EVENTS"; TAB(50) TMAINT(J)LPRINT TAB(15) "TOTAL MAINTENANCE EVENTS"; TAB(50) TMAINT(J)PRINT TAB(15) "TOTAL MAINTENANCE MANHOURS";TAB(50) TOTMH(J)LPRINT TABUS) "TOTAL MAINTENANCE MANHOURS"; TAB ( 5 0 ) TOTMH(J)PRINT TAB(20) "TOTAL ON-EQUIP MAINT";TAB(50) TMMH(J)LPRINT TAB(20) "TOTAL ON-EQUIP MAINT";TAB(50) TMMH(J)PRINT TAB(20) "TOTAL OFF-EQUIP MAINT";TAB(50) TOMMH(J)LPRINT TAB(20) "TOTAL OFF-EQUIP MAINT";TAB(50) TOMMH(J)PRINT:COLOR 12LPRINTPRINT TABU5) "MEAN FLYING HR BTWN MAINT" ; TAB(50) MFHBM(J)LPRINT TAB(15) "MEAN FLYING HR BTWN MAINT";TAB(50) MFHBM(J)PRINT TAB{15) "MEAN SORTIES BTWN MAINT";TAB(50) MSBM(J)LPRINT TABUS) "MEAN SORTIES BTWN MAINT" ;TAB< 50) MSBM(J)PRINT TABUS) "MEAN LANDINGS BTWN MA1NT";TAB{50) MLBM(J)LPBINT TABUS) "MEAN LANDINGS BTWN MAINT"; TAB (50) MLBM(J)PRINT TABUS) "MAN-HOURS PER FLY-HR" ;TAB( 50) MHFH(J)LPBINT TABUS) "MAN-HOURS PER FLY-HR" ; TAB ( 50 ) MHFH(J)PRINT TABUS) "MAN-HOURS PER SORTIE" ; TAB (50) MHS(J)LPBINT TABUS) "MAN-HOURS PER SORTIE" ; TAB ( 50 ) MHS(J)PRINT:LPRINTMHPF(J)=TOTMH(J)/TMAINT(J)MHPFON(J)=TMMH(J)/TMAINT(J)OMHPF(J)=TOMMH(J)/TMAINT(J)PRINT TABUS) "MAN-HOURS PER MAINT ACTION" ; TAB ( 50 ) MHPF(J)LPBINT TABUS) "MAN-HOURS PER MAINT ACTION" ; TAB ( 50 ) MHPF(J)PRINT TAB(20) "ON-EQUIP MAN-HRS/MAINT ACTION";TAB(50) MHPFON(J)LPBINT TAB (20) "ON-EQUIP MAN-HRS/MAINT ACTION" ; TAB ( 50 ) MHPFON (J)PRINT TAB(20) "OFF-EQUIP MAN-HRS/MAINT ACTION" ; TAB( 50 ) OMHPF(J).LEBINT TAB(20) "OFF-EQUIP MAN-HRS/MAINT ACTION" ; TAB ( 50 ) OMHPF(J)PRINTLPBINT: LPRINTNEXT JCOLOR 3GOSUB 1000END
E-2
10 'PROGRAM COMBINES 4 QUARTERS OF DATA FROM NAVY 3M SYSTEM20 "COMPUTES R&M STATS FOR A PARTICULAR 2-DIGIT WUC30 KEY OFF:CLS:COLOR 340 PRINT TAB(20) "CALCULATION OF AIRCRAFT R&M PARAMETERS"50 PRINT:PRINT !
60 DIM MTBM(IO),MMH(10),ACFT$(10)70 FOR 1=1 TO 980 READ ACFT$(I)90 NEXT I100 INPUT "ENTER WUC";WUC$105 LPRINT TAB(IO) "NAVY 3M DATA SYSTEM - R&M SUMMARY REPORT COMPOSITE"106 LPRINT:LPRINT110 LPRINT TAB(10) "WUC ";WUC$:LPRINT120 NUM=4130 FOR J=l TO 9135 TFH=0:TMA=0:TMMH=0:TET=0:TFAIL=0140 PRINT TAB(5) "FOR AIRCRAFT ";ACFT$(J)145 LPRINT:PRINT150 FOR 1=1 TO NUM160 PRINT "ENTER DATA FOR QTR";I170 READ FH(I)180 INPUT "ENTER MAINT ACTIONS FOR QTR";MA(I)190 INPUT "ENTER UNSCH MAINT MAN-HRS - QTR";MMH(I)210 INPUT "ENTER ELASPSED MAINT TIME":EMT(I)220 PRINT230 NEXT I240 CLS:COLOR 2250 PRINT TAB(20) "OUTPUT RESULTS FOR ";ACFT$(J)260 LPRINT TAB(20) "OUTPUT RESULTS FOR ";ACFT$(J)270 PRINT280 LPRINT290 FOR 1=1 TO NUM300 TFH=TFH+FH(I)310 TMA=TMA+MA(I)320 TMMH=TMMH+MMH(I)330 TET=TET+MA(I)*EMT(I)350 NEXT I360 PRINT TAB(IO) "TOT FLYING-HRS";TAB(40) TFH370 LPRINT TAB(10) "TOT FLYING-HRS";TAB(40) TFH380 PRINT TAB(IO) "TOT MAINT ACTIONS";TAB(40) TMA390 LPRINT TAB(IO) "TOT MAINT ACTIONS";TAB(40) TMA400 PRINT TAB(10) "TOT MAN-HRS";TAB(40) TMMH410 LPRINT TAB(IO) "TOT MAN-HRS";TAB(40) TMMH440 PRINT TAB(IO) "TOT ELAPSED TIME";TAB(40) TET450 LPRINT TAB(IO) "TOT ELAPSED TIME";TAB(40) TET460 PRINT:LPRINT470 MFHBMA=TFH/TMA480 MMHFH=TMMH/TFH490 AVEMT=TET/TMA500 AVCREW=TMMH/TET520 PRINT .'PRINT540 PRINT:COLOR 12550 LPRINT560 PRINT TABUS) "MEAN FLYING HR BTWN MAINT";TAB(50) MFHBMA570 LPRINT TAB(15) "MEAN FLYING HR BTWN MAINT";TAB(50) MFHBMA580 PRINT TAB(15) "MAN-HOURS PER FLY-HR";TAB(50) MMHFH590 LPRINT TABUS) "MAN-HOURS PER FLY-HR" ; TAB ( 50 ) MMHFH600 PRINT TABUS) "AVG ELAPSED MAIN TIME" ; TAB (50 ) AVEMT610 LPRINT TABUS) "AVG ELAPSED MAIN TIME" ;TAB( 50) AVEMT620 PRINT TABUS) "AVG CREW SIZE" ;TAB( 50) AVCREW630 LPRINT TABUS) "AVG CREW SIZE" ; TAB ( 50 ) AVCREW
E-3
PRINT TAB(15)LPRINT TAB (15)PRINTLPRINT: LPRINT
660670680690691695700710711712720 END1000 DATA10101020103010401050106010701080
NEXT JCOLOR 3LPRINT:LPRINTLPRINT:LPRINTLPRINT TAB(20;
MAN-HOURS PER MAINT ACTION";TAB(50) TMMH/TMA"MAN-HOURS PER MAINT ACTION";TAB(50) TMMH/TMA
= SUM2-1-TMMH:SUM3 =
TAB(IO) "SUMMARY STATS FOR ";WUC$TAB(20) "AVG TASK TIME";TAB(40) SUM1/SUM3"AVG CREW SIZE";TAB(40) SUM2/SUM1
1090
DATADATADATADATADATADATADATADATADATA
" A4-E" , "A-4F" , "EA-6B" , "A-6E" , "A--7E1
1579,1598,1770,13982335,2384,2625,25277444,6080,8517,598217022,14906,16840,153284624,5404,4989,5562751,3794,3871,17777341,9143,9738,603617856,15592,17214, 1518421649,19976,30652,19734
"C-2A","E-2C","F-18A","F-14A"
E-4
'PROGRAM COMBINES 6 MONTH DATA FROM ALDP 800-4'COMPUTES SCHEDULED MAINT AS A PERCENT OF TOTAL MAINTKEY OFF:CLS:COLOR 3PRINT TABJ20) "CALCULATION OF AIRCRAFT SCHEDULED MAINT"
PRINT"ENTER AIRCRAFT TYPE";AC$"ENTER TIME PERIOD";TIM$"ENTER NUMBER OF TIME PERIODS";NUMTO NUM
PRINT:INPUTINPUTINPUT
102030405060708090 FOR 1=1100 PRINT
PRINTINPUTINPUTINPUTINPUTINPUTINPUTINPUTINPUT
110112113120130140150160170180190200210220230231232240250260270280290300310320330340350360370380390400410420430440450460500
"FOR TIME PERIOD";!"ENTER TOT FLY HRS";FLY(I)"ENTER TOT SORTIES";SORT(I)"ENTER SCHED INSP-03 HRS";SCH3(I)"ENTER SCHED INSP-03 HRS OFF";OSCH3(I)"ENTER SCHED INSP-04 HRS ON";SCH4(I)"ENTER SCHED INSP-04 OFF HRS";OSCH4(I)"ENTER TOT ON EQ MHRS";TOTON(I)"ENTER TOT OFF EQ MHRS";TOTOFF(I)
SUM1=SUM1+SCH3{I)+OSCH3(I)+SCH4(I)+OSCH4(I)SUM2=SUM2+TOTON(I)+TOTOFF(I)SUM3=SUM3+SCH3(I)+SCH4(I)SUM4=SUM4+OSCH3(I)+OSCH4(I)SUM5=SUM5+TOTON(I)SUM6 =SUM6+TOTOFF(I)TFLY=TFLY+FLY(I)TSORT=TSORT+SORT(I)NEXT IPERSCH=SUM1/SUM2PERON=SUM3/SUM5PEROFF=SUM4/SUM6CLS:COLOR 3LOCATE 5,10:PRINT TAB(20) "AIRCRAFT TYPE";TAB(45)PRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTEND
TAB(20) "TIME PERIOD IS";TAB(45) TIM$AC$
TAB(10) "SCHEDULED MAINTENANCE PERCENTS"TAB(10) "OF TOTAL MAINTENANCE";TAB(40) PERSCHTAB(lO) "OF ON-EQ MAINTENANCE";TAB(40) PERONTAB(lO) "OF OFF-EQ MAINTENANCE";TAB(40) PEROFF
TAB(lO) "AS A PERCENT OF UNSCHEDULED MAINTENANCE"
TAB(10)TAB(10)TAB(lO)
TAB(IO)TAB(lO)TAB(10)TAB(IO)
"TOTAL";TAB(40) SUM1/(SUM2-SUM1)"ON-EQ";TAB(40) SUMS/(SUMS-SUMS)"OFF-EQ";TAB(40) SUM4/(SUM6-SUM4)
"SCH MAINT HRS PER FLY HR";TAB(40)"SCH MAINT HRS PER SORTIE";TAB(40)"% SCHED ON-EQUIP";TAB(40) SUMS/SUMl11 % SCHED OFF-EQUIP";TAB(40) SUM4/SUM1
SUM1/TFLYSUM1/TSORT
E-5
APPENDIX F
Variable Definitions
INDEPENDENT VARIABLE
Variable Name
ACT
ACTWT
AV INSTA
AVWT
AVS
BODYWT
BTU COOL
CONTS
CREW
DIP SUBS
DRYWT
ECS WT
ELECT WT
Definition
Total number of actuators to operate all vehicle movableflight surfaces.
Weight of the actuator subsystem in pounds.
Weight in pounds of brackets, shelves, wiring and plugsused on avionics equipment.
Weight in pounds of avionics equipment uninstalled (doesnot include wiring, shelves, ducts, fasteners, etc.).
Total number of avionics (AN nomenclature) subsystems.
Weight of the body (fuselage) in pounds.
Total cooling capacity of air conditioning equipment usedfor personnel and equipment cooling. Measured inBTU/HR/1000.
Total number of control surfaces - ailerons, rudders,elevator tabs, flaps, spoilers and slats.
Total number of crew members (repair or flyingdepending upon context).
Total number of different avionics subsystems (two ormore identical units count as one).
Empty weight (without fuel) of vehicle in pounds.
Total weight of the environmental control systemincluding heating, cooling and anti-icing equipment inpounds.
Weight of electrical subsystems in pounds.
F-l
ENG
ENG WT
FUEL TK
FUS AREA
FUS DENS
FUS VOL
HYD WT
KVAMAX
L.GEAR WT
LEN + WING
MSN LEN
PASS
SUB WT
SUBS
WET AREA
WHEELS
Number of primary engines.
Weight of the engine in pounds.
Number of separate internal fuel cells, bladders andtanks.
External area of fuselage including canopy in square feet.
Fuselage density (weight/volume).
Total volume of fuselage, excluding any engine inlet ductvolume, in cubic feet.
Weight of Hydraulic subsystems in pounds.
Total electrical power of engines, motors, and APUdriven generators/alternators in kVA (thousands of voltamps).
Landing gear weight in pounds.
Aircraft length plus wing span in feet.
Mission length in hours. May be adjusted by/forsubsystem utilization.
Maximum number of passengers.
Total subsystem weight in pounds.
Total number of aircraft subsystems requiring use ofhydraulic or pneumatic power.
Total external surface area of vehicle in square feet.
Total number of wheels.
WING LEN Length of the wing in feet.
F-2
APPENDIX G
Design/Performance/Weight Values
DRY WGT LEN WINGA-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A
96241016925558177921854620822152293474802400043032443414434128545287022966394593903726768274251444714447230506710071990739629703021450140882313693200836179024061337498321626673
188000
69691088585
11134414410813713713797971017512610710780829423123123226711432813847121234713811272299
WETAREA10721094218017031703260017645316422303117311731011989198919899473105263226431385139820508899889988991095427341535037293371262482110131502295971
FUS VOL571581
1231813813793
12447188913211889188918891270127012706601822149517165965969649060906090601155017101967827128661076474130013461361806
G-l
A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A
FUS AREA4784988987497497114942958985961961961100010009615831647140514687355518903460346034604420105066831336166463221911510431017533
CREWS I ZE1121116212222221211121444445353454223
PASSENGR ENGINES
929292800
2092836040750
1.001.002.001.001.002.008.002.001.002.002.002.002.002.002.002.002.002.002.001.001.002.004.004.004.004.004.004.002.004.002.003.002.002.002.00
G-2
A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A 8.20
MSN LEN2.502.504. 101.504.001.706.703.201.502.202.302.401.201.301.200.903.701.301.301.301.302.402.402.402.803.001.903.30
3.901.204.405.103.101.20
WHEELS334443844444444343333466610610428610443
ACTUATOR14.0014.0023.0026.0026.0023.0042.0031.009.0031.0031.0031.0024.0027.0027.0019.0041.009.009.0014.0014.0012.0015.0015.0015.0029.00
29.0025.00115.0024.0039.0025.0024.000.00
CONT SUR13.0013.0019.0012.0012.0014.0032.0028.006.0028.0028.0028.0017.0017.0017.0012.0023.009.008.0011.0011.0011.0014.0014.0014.0024.0016.00
18.0043.0020.0052.0018.0019.00
G-3
A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A
ECSWT63.0063.00420.00263.00263.00210.00670.00631.00407.00631.00631.00631.00392.00397.00403.00143.001048.00669.00669.00230.0023.00
1526.001836.001836.001473.00608.002648.00656.003636.001538.002186.00510.00585.00325.00
KVA MAX11.0011.0065.0027.5027.5060.00160.00130.0028.30130.0062.4057.4063.0063.0063.0055.00126.5050.00130.0050.0050.0080.00190.00190.00190.00120.0028.00252.00123.00484.00112.00360.00123.0092.0016.00
SUBSYS17.0017.0034.0038.0038.0020.0076.0038.0025.0038.0022.0035.0039.0033.0033.0016.0045.0028.0030.0020.0020.0014.0020.0020.0020.0012.008.00
i 33.00! 31.0072.0012.0030.0027.0034.0014.00
FUEL TK2.002.006.007.007.00
4.007.004.006.004.009.009.009.003.00
5.005.007.004.008.006.006.006.0010.006.0012.002.0012.00
*
15.00
6.004.00
AV WGT
1178.00
1153.008823.00
2135.00
303.00
1910.001938.001103.001103.00
3249.003249.00
2323.004240.00
4015.002143.004181.00
493.002353.00
G-4
A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BO130EC-130HKG- 135 AO140AC-141BC-2AC-5AO9AKC-10AE-2CEA-6BT-38AE-3A
TOTSUBS14.0015.0027.0031.0037.0016.0019.0026.0016.0026.0028.0025.0014.0027.0028.0010.0033.0025.0025.0018.0018.0016.0023.0027.0030.0022.0020.0025.0018.0033.0018.0036.0029.0026.00
9.00
AV INSTA203.00
70.00663.00523.00506.00203.00
2949.001080.00801.00874.00
1089.00992.00434.00496.00626.00207.00619.00393.00364.00250.00336.00329.00658.00851.00800.00654.00556.00
1241.00425.00
1377.00800.00
1389.00965.00
59.00
DIF SUBS14.0015.0021.0031.0037.0016.0019.0022.0014.0024.0023.0025.0014.0027.0028.0010.0031.0025.0025.0018.0018.0014.0022.0025.0025.0022.0020.0018.0017.0025.0015.0025.0027.0023.00
5.00
BTU COOL"' 25.00
25.00130.0075.0075.0015.80
180.00127.4095.0095.50
142.2095.5040.0040.0040.0035.00
174.00153.00155.0040.0040.00
106.0078.00
105.0078.00
130.0034.00
118.0050.00
318.00200.00145.00195.00130.00
G-5
A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A
WGT WING
3269
510737369
4688468846881349
339936421808
11626116261162625305295435092
1000121139259202
79532654
WGT TAIL
832
9676030
913913913328
10981104719
34103410341055658805907
12719279114636
3026310
WGT BODY
3302
474526731
4801480148012617
616062453118
14338143381433820732373636822
1212591182246987
214035193
G-6
A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A
WGT13
1267
148612992
196219621962768
130513439241067
48734873487311023108110850
38282429526211
52713330
WOT 14
1196.00
836.002591.00
ENG WGT
4497
428336554
WGT 2 4
157.00
1001.001001.001001.00422.00
800.00810.00718.00718.00
1693.001693.001693.002287.00939.003701.00
7263.001639.005773.00
9968996899682247
604960913671
166961669623386380425471
390911053543162
481.00482.00164.00170.40
451.00460.00460.00945.00
535.00367.001080.00832.001486.00
394.003214.00
176723321 500.00
G-7
A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BO2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A
WGT42
1094.00
732.006047.00
536.00536.00536.00310.00
583.00607.00441.00441.00
2299.002299.002299.004152.001937.002823.00
4046.001766.004862.00
327.00
WGT45
210.00
373.001915.00
601.00601.00159.00
431.00433.00309.00309.00
666.00666.00666.00880.00338.001605.00
4484.00756.004170.00
147.00
WGT51/72
1178.00
1153.008823.00
2135.00
303.00
1910.001938.001103.001103.00
3249.003249.00
2323.004240.00
4015.002143.004181.00
493.002353.00
G-8
APPENDIX H
Dependent Variable Values
FHBMA11 MH/MA11A-4EA-4FA-6EA-7D 10.00 5.80A-7EA-10A 11.30 5.20B-52G 3.00 6.90FB-111A 1.10 3.90F-106A 10.10 7.40F-111A 2.90 4.30F-111D 2.50 4.40F-111F 2.30 4.30F-4C 5.10 6.20F-4D 3.60 5.40F-4E 4.20 6.70F-5E 7.90 7.60F-14AF-15A 3.00 5.70F-15C 2.68 9.00F-16A 8.32 5.20F-16B 6.50 4.10F-18AC-130B 3.40 5.70C-130E 5.30 8.10C-130H 4.70 9.80KC-135A 4.00 6.00C-140A 9.40 9.20C-141B 3.63 6.30C-2AC-5A 1.37 5.40C-9A 10.30 4 .40KC-10A 41.90 5.10E-2CEA-6BT-38A 6 .20 7 .70E-3A 4.80 2.90
H-l
%OFF12 FHBMA12 MH/MA12A-4EA-4FA-6EA-7D 0.06 46.00 7.60A-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38A 0.16 29.40 4.60E-3A 8.90 7.90
0.070 .040.060.000.040.040.010.130.090.070.05
0. 100.050.100.11
0.180.300.090.270.440.39
0.180.290.05
22.8015.30
9.1041.3011.0018.4028.10
5.606.206.20
32.50
18.5026 .4028.8014.90
13.6014.7021.4024.9020.8010.00
1.908.90
4 .504 . 2 04 .003.205.005.306.005.405.204.703.80
8.5010.00
7.006.50
6 .408.80
11.9010.20
7.3010.40
7.705.007.70
H-2
FHBMA13 MH/MA13 %OFF EQPA-4EA-4FA-6EA-7D 14.40 9.90 0.34A-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10A 4.80E-2CEA-6BT-38A 12.70 6.60 0.33E-3A 7.90
18.50
11.208.70
10.70
11.308.40
12.0018.00
13.0015.3012.4010.30
12.8013.3012.30
6.2010.60
7.50
1.4015.70
3.506 .206 .406.80
10.1011.509.60
11.507.30
10.6011.90
9 .5013.606.004.30
10.909.40
11.709.10
10.906.60
5.905.90
0.390. 140.340 .260.340.300.270.540.310.410.50
0 .290.280.450.29
0.320.230.130.490.470.19
0.230.31
H-3
A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A
FHBMA143.932.764.2814.567.28
17. 147.084.3622.496.027.219.619.359.809.65
21.704.4812.9514.3515.5314.347.4714.3818.9418.326.6011.806.808.573.8021.98
6.704.2417.534.78
MH/MA14
10.60
6.005.706.009.709.909.309.6011.309.8011.9011.40
10.9015.107.305.80
6.607.309.406.307.706.50
6.303.906.10
8.902.10
%OFF EQP
0. 15
0. 130.18
0.080.160. 140.070.040.060. 130.22
0.080.080.200. 16
0.040.030.190.120.06
0.090.090.05
0.290.07
H-4
FHBMA23 MHMA23 %OFF EQPA-4EA-4FA-6EA-7D 21.70 22.60 0.54A-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38A 20 .20 25 .00 0.68E-3A 8.60 4.10 0.00
20.404 .606.20
13.205.705 .209.30
16.5020.5016.5022.10
11.2011.0022.0020.50
7.606.806.405.007.104 . 4 0
1.4026 .2028.40
29 .8013.7019.302 4 . 2 017.2013.7024 .7025.5031.5041.9058.80
36.0031.5032.9011.70
10.2012.8013.9014.1012.2014.20
11.406 .40
10.70
0.730 . 6 20.660.450 .430.360.630.450.520.630.82
0.620.560.690.21
0.240.420.200.580.340.55
0.64
H-5
FMA41/47 MHMA4147 %OFF EQP-41 %OFF EQP-47A-4EA-4FA-6EA-7D 29 .20 6.50 0 .22 0.12A-7E ,A-10A 17.50 4.50 0.17 0.08B-52G 18.30 6.20 0 .04FB-111A 5.90 5.20F-106A 22.10 7.20 0.12 0.05F-111A 8.80 6.50 0.26 0.33F-l l lD 9.90 10.40 0.31 0.23F-111F 10.00 10.80 0.24 0.32F-4C 16.60 6.90 0.03 0.10F-4D 19.90 9.20 0.03 0.17F-4E 19.40 9.20 0.04 0.20F-5E 35.80 6.70 0 .47F-14AF-15A 17.70 8.60 0.19 0.15F-15C 19.40 12.50 0.25F-16A 28.60 4.90 0.16F-16B 21.10 4.40 0.16 0.13F-18AC-130B 11.00 6.10 0.07 0.05C-130E 12.80 6.60 0.06 0.05C-130H 11.10 0.07 0.02KC-135A 28.50 8.20 0.15 0.070140A 19.80 7.00 0.19 0.06C-141B 9.30 5.30 0.14 0.11C-2AC-5A 4.20 5.90 0.10 0.02C-9A 5.00 0.04KC-10A 38.70 5.20E-2CEA-6BT-38A 41.60 7.30 0.34 0.12..
H-6
FMA42/44 MHMA4244 foOFF EQP - 42 %0FF EQP - 44A-4EA-4FA-6EA-7D 26.30 6.40 0.38 0.22A-7EA-10A 24.40 6.50 0.48 0.17B-52G 9.00 6.10 0.30 0.04FB-111A 9.00 7.30 0.31F-106A 18.80 4.60 0.20 0.12F-111A 7.90 6.80 0.15 0.26F-111D 9.40 9.90 0.16 0.31F-111F 17.90 5.20 0.30 0.24F-4C 16.00 9.40 0.33 0.03F-4D 15.70 6.70 0.35 0.03F-4E 16.30 8.20 0.31 0.04F-5E 36.30 7.90 0.47F-14AF-J5A 12.60 6.10 0.23 0.19F-15C 14.90 0.16 0.25F-16A 14.50 5.70 0.52 0.16F-16B 13.20 4.90 0.53 0.16F-18AC-130B 12.80 4.50 0.11 0.07C-130E 14.40 5.80 0.15 0.06C-130H 12.40 8.30 0.05 0.07KC-135A 10.00 7.30 0.36 0.15C-140A 20.20 5.70 0.25 0.19C-141B 39.80 0.28 0.14C-2AC-5A 2.50 4.10 0.29 0.10C-9A 20.70 4.40 0.19KC-10A 81.70 4.70E-2CEA-6BT-38A 31.20 6.60 0 .47 0.34E-3A 8.50 4.60
H-7
FHBMA45 MH/MA45 SOFFEQPA-4EA-4FA-6EA-7D 44.40 9.10 0.13A-7EA-10AB-52GFB-1 HAF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT_38A 91.60 5.90 0.18E_3A 17.60 2.40 0.17E-3A
95.809.60
12.3035.2020.5018.5028.2030.4026.3044.70
183.00
19.7025.4075.7062.70
17.0018.7019.4014.3027.3016.00
4.7073.8060.50
9.804.606.008.308.208.607.108.708.30
11.909.50
8.90
4.504.00
5.405.809.006.204.505.00
4.904.105.70
0.180.080.290. 120.110.130. 140.070.090.190.11
0.080.090.100.17
0.070.050.030.110.040.04
0.050.010.33
H-8
FMA49/96 MHMA4996 %OFF EQP-96 *0OFF EQP-49A-4EA-4FA-6EA-7D 234 .00 8.50 0.98 0.09A-7EA-10A 235.00 7.60 0.98 0.06B-52G 55.50 7.60 0.08FB-111A 40.10 3.60 0.47 0.01F-106A 60.30 13.80 0.08F-111A 95.00 5.30 0.05F-111D 108.40 10.50 0.00F-111F 121.80 5.70 0.05F-4C 236.60 5.00 0.02F-4D 236.80 4.90 0.00F-4E 262.10 . 0.00F-5E 610.80 6.40 0.00F-14AF-15A 83.60 7.20 0.03F-15C 131.10 13.20 0.02F-16A 561.10 7.70 0.96 0 15F-16B 492.70 4.00 0.24F-18AC-130B 34.70 4.00 0.23 0.05C-130E 48.80 7.10 0.57 o!o8C-130H 34.20 6.60 0.72 0.04KC-135A 46.70 3.40 0.31 0.13C-140A 70.50 4.10 0.05C-141B 34.60 8.70 0.45C-2AC-5A 10.00 6.40C-9A 201.40 5.70 0.03KC-10A 175.90 4.30E-2CEA-6BT-38A 331.50 4.50 0.69 0.00E-3A 45.30 2.20 0.14 0.13
H-9
AVIONICS
FHBMA MH/MA %OFF EQPA-4EA-4FA-6EA-7D 13.80 7.30 0.40A-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38A 14.40 4.60 0.23E-3A 4.80 8.50 0.29
11.703.603.205.305.704.506.504.603.002.30
13.40
7.206.80
17.1010.90
4.704.403.202.60
11.304.40
1.50
9.60
7.806.80
10.205.70
13.8013.0011.208.709.008.808.20
12.6013.604.704.90
8.709.60
11.008.00
11.807.00
8.005.005.30
0.310.290.520.280.360.410.480.380.430.360.35
0.400.460.290.19
0.410.440.230.350.530.31
0.29
H-10
NASA - WBS SUBSYSTEM ROLL-UP
FLY HRS ME42 MH42 ME44 MH44 FHBMA MH/MA ME41
A-7DA-10B-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-15AF-15CF-16AF-16BC-130BC-130EC-130HKC-135AC-140AC-141BC-5AC-9AKC-10AT-38E-3A
NAVY A/C
A4-EA-4FEA-6BA-6EA-7E
C-2AE-2CF-18AF-14A
150,924442,398136,04040,12721,83616,14940,11431,04830,998153,424204,99347,034172,258103,690350,10267,00288,133514,59542,802278,0125,783
572,817109,29040,07067,738460,85032,693
6,3459,87128,02364,09615,573
12,19332,25865,84692,011
2,49011,1158,3572,005519629
1,952607920
3,7174,795633
4,6062,157
13,6722,6273,73217,2161,70713,331
11913,38217,043
352829
6,7572,165
1,1419,8717,54828,5501,432
1,2464,3743,270
13,954
21,32892,78662,35212,6773,6164,22018,3904,50813,42739,74462,7725,89341,37637,844112,95718,90918,797118,82119,013128,443
930100,29991,0174,6323,86950,91713,129
5,6555,58246,800163,8018,481
8,31521,30126,99496,743
3,2527,0236,7882,474644
1,4132,3011,1271,0146,0677,789662
9,0784,78010,5012,4543,13818,6431,73114,335
1671,01427,2031,583
8,0031,672
1,040834
4,19513,4741,552
1,9975,4832,74214,216
15,30124,57330,30519,8371,7729,64123,8494,5534,67226,08340,9774,33642,65446,70525,7245,90012,05290,8009,47673,488
689157,42488,9383,804
46,2564,614
2,7222,63610,04236,8324,867
4,2779,24711,92940,522
26.324.49.09.018.87.99.417.916.015.716.336.312.614.914.513.212.814.412.410.020.239.82.520.781.731.28.5
2.90.92.41.55.2
3.83.311.03.3
6.46.56.17.34.66.89.95.29.46.78.27.96.112.25.74.94.55.88.37.35.717.94.14.44.76.64.6
3.80.84.84.84.5
3.93.16.54.9
4,21217,1565,0705,950536
1,5783,4872,6661,1444,7857,0091,0938,2394,6328,6142,1236,37932,2612,7112,711237
48,92319,9721,132983
8,0284,389
312123
2,2135,539769
1,0764,9564,5109,695
H-ll
MH41 ME47 MH47 FHBMA MH/MA ME49 MH49 ME96 MH96 FHBMA MH/MA
A-7DA-10B-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-15AF-15CF-16AF-16BC-130BC-130EC-130HKC-135AC-140AC-141BC-5AC-9AKC-10AT-38E-3A
NAVY A/C
A4-EA— 4F"•AEA-6BA-6EA-7E
C-2AE-2CF-18AF-14A
2883343351038309536677661441038218112481
264125565916
,254,967,123,600,594,554,546,908,977,379,431,143,389,708,539,883,827,207,940,834,728,346,125,901,143,693,598
82
23
1
311817
126
3
1,772406
8,15618,8182,979
5,20,24,52,
429960310846
951,184,376876450266559440725,906,564219,480722,618,051,645,070,142,05155
,809,143453769,042569
460148
1,7202,478262
1,
2,
649484736108
5,26530,98212,1702,0801,4601,3953,5532,4972,93417,20430,8721,5947,1195,25515,5353,0809,833
46,1538,69931,158
30761,81229,3882,0852,93920,7741,507
1,006476
5,2638,2591,180
2,5285,6282,4397,914
291718522891016191935171928211112112819942538416
.2
.5
.3
.9
.1
.8
.9
.0
.6
.9
.4
.8
.7
.4
.6
.1
.0
.8
.1
.5
.8
.3
.2
.3
.7
.6
.6
8.236,7,8.15.
7.5.12.7.
.4
.1
.0,1
1068
6.54.56.25.27.26.510.410.86.99.29.26.78.612.54.94.46.16.631.68.27.05.35.95.05.27.33.7
3.63.33.43.44.0
4.64.15.15.1
6281,8412,45298716017035925513164878277
2,060791578115
2,53410,4271,2175,917
8216,57911,047
199385
1,377631
Tj
9183
31
36
14102
1073720
144711161
,940,675,576,611909839,838,373623,029,267482,870,422,642450,095,915,820,440339,805,029,129,637,199,492
1742
14202
11
46218
1283540
1,5494,631
404,078
63347730159
2,66110
2,154963971348770
1391
78118
,1,3
234.0234.955.540,60.95.0108.4121.8236.6236.8262.1610.883.6131.1561.1492.734.748.834.246.770.534.69.9
201.4175.9331.545.3
3.57.67.63.613.85.310.55.75.04.911.46.47.213.27.74.04.07.16.63.44.18.76.45.74.34.52.2
H-12
NASA - AVIONICS SUBSYSTEM ROLL-UP
FLY HRS ME51 MH51 OMH51 ME52 MH52 OMH52 MESS
A-7DA-10B-52G
150,924442,398136,040
FB-111A 40,127F-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-15AF-15CF-16AF-16BC-130BC-130EC-130H
21,83616,14940,11431,04830,998153,424204,99347,034172,258103,690350,10267,00288,133514,59542,802
KC-135A 278,012C-140AC-141BC-5AC-9AKC-10AT-38E-3A
MH55
16,0582,7872,9231,807920380678447
10,56625,765
88817,86715,8183,314407766
4,813854
17,950
5,783572,817109,29040,07067,738460,85032,693
2,901 14,23116,636 127,10016,062 89,0323,825 29,184329 3,264938 11,008
2,344 20,5481,372 13,6501,510 15,1107,629 71,91911,678 110,6671,544 11,4235,914 59,5432,619 33,1195,515 30,8941,652 9,3662,895 14,68913,375 77,1491,353 14,94439,657 230,067
84 42831,309 189,6319,869 68,871470 1,875858 3,014
19,736 75,4631,358 7,374
12,97,80,20,2,8,16,9,9,40,65,7,49,20,22,7,12,67,14,199,
155,52,1,3,62,7,
OHB55 ME61 MH61 OMH61
10,2152,551 11,5181,672857357 1508385
9,00414,259
72911,57011,9073,193391690 1
4,583 5825
2
17,672 9163,369 127,165 3
447753
388749
,027 12,026 8867 12,161 3
274 4,026 2,321 21,053 7641 8,769 3
,019,870
,035,794,367
130617309193771503062552224052896239310647630978071103113714393418376698000897255
2,7595,9762,506886779
2,8481,489604
3,1254,159404
1,3801,132
2,41214,7251,49418,767
7820,23512,900
3681,4972,576458
31434331652229
337542424
199917136
160116
39173
ME62 MH62
1,s,410 13,770 42,
928925
,026 20,136 29,979 16,110 5,999 9,300 27,900 10,176 6,218 25,104 50,925 3,959 12,917 13
,299 14,807 82,797 15,080 96406,470 113,122 98,823 3,520 9,710 11,903 3
OMH62
5,34927,071
,634,842,586,890,047,019,403,699,015,584,309,312,875
,000,100,390,870324,106
2,1088975563919888
1251,5604,087141
1,2381,76323112091885
4,800,948 25,744,805,520,636,903
ME63
1,9715,4423,8712,922505248
1,011634829
7,02310,645
,350 15,060 6,332 66,100 28777 9,274 4,811 33,875 1934 783
,362 116,661 51,097 32,479 2287 276171 937
590 6,445 4
,967,334,551,617276,049,939267937
,229
3,
2,1,
6,
17
622 16,998 4,441 4,378 18,533 4,382 1,22493 42,523 3,18710018102 1,
122
51901014171208341142173128561145256018
78
11,1572,9062,18511,0583,302762135
29,7172,57057635953633
6236,8154,2196,2861,080498
5,161243
5,45927
5,4121,060173399
3,158944
15486
MH63
15,13739,03930,58925,1202,0841,7529,0584,1575,71337,63173,9164,83363,64948,26228,9666,1603,96627,8851,97758,092
29328,1737,076434
2,06916,22911,673
OHH63
92114911613255423627193216126
174
2107
,277,329,837,943,584,329,236,990,487,045,727,945,555,053,238,559,428,507,454,523174,850,759434,069,167,174
H-13
NASA - AVIONICS SUBSYSTEM ROLL-UP
ME64 MH64 OMH64 ME66 MH66 OHH66 ME71 MH71 OMH71 ME72 MH72
7261,2575,7771,309
303710466
201
917477
2,21412,2591,4317,678
6218,6585,556384
1,3331,8941,337
OMH72
6,705262
7,947599
7158,61917,397
31,958277,55441,376152,334
44365,54146,8431,2532,197
2,567
5,645 4,2587,380 4,37241,505 25,6199,636 7,286
2,300 1,6265,479 5,0731,903 1,433
1,218 1,218
4,795 4,4642,457 2,36513,036 10,68,764 54,16,403 14,66,147 35,
65374,723 65,35,931 25,1,119 1,5,138 5,11,025 10,9,714 5,
TOT ME
10,97537,83637,44112,7244,0832,8418,8984,8006,75351,83089,3143,50123,92215,29620,4176,13318,869116,828 113,295106,825
511128,87171,8012,4277,02031,9446,803
363963716042370856396001133090804
TOT
8029425312923391155358467786283002089530163,1241468506
897576123714557
2881,317166
1,7291,99416527
101
3,
7,23,
1,
MH TOT
,266,534,684,763,459,332,666,946,536,703,741,774,929,781,188,286,253,261,546,505,052,663,062,017,321,463,861
47
953978697
024704674117
281
OMH
,826202,188180621625672836264503181791126724976341125542
623411103711141
,079,364,979,240,648,157,505,769,205,602,277,219,686,451,124,604,380,120,835,284,673,916,208,463,323
8673,723626
5,98414,227
556117
853
FHBMA
13.811.73.63.25.35.74.56.54.63.02.313.47.26.817.110.94.74.43.22.6
. 11.34.41.516.59.614.44.8
2,4153,7552,490617
1,472201576198
3,47030,71455,240
5719,8136,0882,3141,6952,77214,0511,9853,641110
20,0052,464347
2,1774,4081,377
MH/MA
7.37.86.810.25.713.813.011.28.79.08.88.212.613.64.74.98.79.611.08.011.87.08.05.05.34.68.5
18,20030,73019,8645,9298,1942,3276,8481,88922,413290,204468,8725,365
134,91186,66510,7007,88627,985253,85722,03944,4721,513
161,36629,0451,68013,87624,53312,192
%OFF EQ
0.4040.3140.2900.5190.2760.3580.4150.4780.3760.4340.3600.3540.4040.4630.2890.1930.4050.4360.2330.3480.5320.3060.2850.0920.0030.2340.286
10,20,10,2,5,1,5,
15,157,300,
3,69,38,7,7,15,88,16,23,
101,16,1,13,16,3,
107 1,552688 109955 1,341369 122062843107904995 215034 1,779342 3,505084530737004252595 5,879679 47,312027 4,228258 28,430720 94091 10,868450 8,594326 246876 458232156 450
13,125276
14,745831
5,67724,16532,417
63,358503,19658,478280,3611,55598,93496,1801,5252,198
3,508
MH/FH
001312211330120012331150001
.53
.67
.86
.23
.07
.44
.88
.74
.89
.05
.84
.61
.75
.01
.27
.45
.85
.18
.42
.06
.05
.57
.27
.30
.55
.32
.77
H-14
APPENDIX I
Subsystem Weight Percentage
WEIGHT DISTRIBUTION ANALYSIS
PLS AMLS AVG
WINGTAILBODYTPSLANDINGPROP 6,7,8PRIME PWRELECTRICACTUATORSAVIONICSECSPERS ACCOMRECOV & AUX
TOTAL
1,86969
2,2382,1241,1611,3662,8721,216
1731,3371,5991,4341,961
0.0960.0040.1150. 1090.0600.0700.1480.0630.0090.0690.0820.0740.101
1,73962
2,9071,555
8291,1382,720
999123956
1,4781,1951,634
0.1000.0040.1680.0900.0480.0660.1570.0580.0070.0550.0850.0690.094
0.0980.0040.1410.1000.0540.0680.1520.0600.0080.0620.0840.0710.098
19,419 1.000 17,335 1.00 1.00
1-1
APPENDIX J
MTBM Regression Analysis
Multiple RegressionDate/Time 04-01-1992 15:05:42Data Base Name C:\NASA\WUC11Description Backup of NASAMSTR created 12-18-1991
Multiple Regression Report
Dependent Variable: FHBMA11Independent Parameter Stndized StandardVariable Estimate Estimate ErrorIntercept 15.23085 0.0000 3.994154WGT TAIL .6057E-02 2.8217 .5551E-03SQR TW -.1375748 -1.7464 .5844E-01WETAREA -.723E-03 -0.7205 .6747E-03
t-value(b=0)
3.8110.91-2.35-1.07
Prob.Level0.00150.00000.03170.2997
Seq.R-Sqr
0.24390.88360.8914
SimpleR-Sqr
0.24390.04460.0343
Analysis of Variance Report
Dependent Variable: FHBMA11
Source df Sums of Squares(Sequential)
Constant 1 1114.525Model 3 1254.958Error 16 152.9258Total 19 1407.884
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
1114.525418.31959.55786174.09917
3.0915797.465.4141432
0.89140.8710
F-Ratio Prob. Level
43.77 0.000
J-l
Multiple RegressionDate/Time 04-01-1992 15:06:00Data Base Name C:\NASA\WUC11Description Backup of NASAMSTR created 12-18-1991
Residual Analysis
Row
1234567891011121314151617IS1920212223242526272829303132333435
Durbin
ActualY..,
10.
11.331.110.12.92.52.35.13.64.27.9,
32.688.326.5•
3.45.34.749.43.63,
1 .3710.341.9,
,
6.2- Watson
PredictedValue,..
7.201859•
4.8981232.562452•
•
*
•
•
5.2914075.2914075.2914077.517668.
5.7760295.5835818.247961•
•
5.8715765.8715765.8715769.7660436.6141831.53145.
1.3440415.4327140.8043•
»
8.530637
Std Errof Fred*
.
•
.8609902•
.87151371.713773
t
•
•
•
t
1.0275271.0275271.0275271.150616
*
.836188
.86195951.022725•
•
.8064643
.8064643
.80646431.3919221.1036231.63013•
2.4764081.1493043.042678•
•
1.529309
Lower95%Mean•
.«
5.376893•
3.050851-1.070084
*
•
•
•
•
3.1134473.1134473.1134475.078806•
4.0036343.756566.08018•
•
4.1621834.1621834.1621836.8157054.27493-1.923795
*
-3.9049852.9966334.355•
•
5.289094
Upper95%Mean.•
.9.026825•
6.7453956.194987•
•
•
•
t
7.4693687.4693687.4693689.95653•
7.5484247.41060210.41574' «
•
7.5809687.5809687.58096812.716388.9534374.986695•
6.5930677.86879147.2536•
•
11.77218
Residual
•
•
•
2.798142•
6.401877.4375482•
•
•
t
•
-.1914072-1.691407-1.091407.3823323•
-2.776029-2.903581.7204E-01•
•
-2.471576-.5715756-1.171576-5.7660432.7858162.09855
t
.02595894.867291.095703•
•
-2.330637Statistic 1.213496
J-2
Multiple RegressionD.ate/T.ime 04-02-1992 14:43:23Data Base Name C:\NASA\WUC12ADescription Merge of WUC11 and WUC12 created 04-01-1992
Multiple Regression Report
Dependent Variable: FHBMA12IndependentVariableInterceptDRY WGTLN DRYWTSQR WOTCREWS I ZESQR CREWWGT BODYSQRWTBODCREW+TRP
ParameterEstimate3428.487-.142E-01-423.959411.05028111.5669-360.7212.1865E-01-4.835661-.2578509
StndizedEstimate0.0000
-99.4395-49.6111125.888548.0205
-28.120544.7105
-31.1615-2.1322
S tandardError889.042.4057E-02112.35143.05327229.2030491.78398. 5565E-021.462995.1338993
t-value(b=0)
3.86-3.50-3.773.623.82
-3.933.35
-3.31-1.93
Prob.Level0.00270.00500.00310.00400.00280.00240.00650.00700.0804
Seq.R-Sqr
0.26650.31940.33950.36890.5711,58527243
0,0,0.7938
SimpleR-Sqr
0.26650.31230.31780.11510.19750.21260.27110.1739
Analysis of Variance Report
Dependent Variable: FHBMA12
Source df Sums of Squares Mean Square(Sequential)
Constant 1 6581.192Model 8 1873.412Error 11 486.516Total 19 2359.928
F-Ratio Prob. Level
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
6581.192234.176544.22873124.2067
6.65046818.14.366619
0.79380.6439
5.29 0.007
J-3
Multiple RegressionDate/Time 04-02-1992 14:43:48Data Base Name C:\NASA\WUC12ADescription Merge of WUC11 and WUC12 created 04-01-1992
Residual Analysis
Row
123456789101112131415161718192021222324252627282930313233343536
Durbin
ActualY...
46.
22.815.39.141.31118.428.15.66.26.232.5.
18.526.428.814.9•
13.614.721.424.920.810,
1.98.9•
.
.
29.48.9- Watson
PredictedValue,.,
35.40208•
18.0293414.40029.•
•
*
•
8.1983698.77435812.2691139.88201•
20.5776222.0104829.78044•
•
16.1278319.440720.3578120.1924810.508987.176239•
2.42415315.85721-282.9091•
•
31.9359.461346
Std Errof Pred•
.
•
4.578885•
3.3349616.470281
t
•
.
•
•
3.4281573.3624683.1766133.990315•
3.8283423.7858723.131097•
•
3.2145993.2214163.5564373.8471124.8397756.234165•
6.6419272.94807389.58411•
•
5.3706066.644016
Lower95%Meant
•
,
25.33262•
10.6954.1714525•
•
t
•
•
.65948491.3799315.28339731.10688•
12.1586913.6849422.89483•
•
9.05858412.3564612.5368311.73227-.1342001-6.533356.
-12.182169.374085-479.9141•
•
20.12446-5.149556
Upper95%Mean...
45.47154•
25.3632828.62913•
•
•
t
•
15.7372516.1687919.2548248.65714•
28.9965630.3360136.66606•
•
23.1970826.5249328.178828.6526921.1521620.88583,
17.0304622.34034-85.90405•
•
43.7455424.07225
Residual
•
•
*
10.59792•
4.77066.8997078•
•
•
•
•
-2.598369-2.574358-6.069109-7.382008•
-2.0776224.389523-.9804421•
•
-2.52783-4.7406971.0421894.7075210.291022.823762•
-.5241526-6.957213•
•
•
-2.535002-.5613461
Statistic .5828236
J-4
"Huitioie Kearessiori-Oate.' Time O4-12-1992 19:23:26Data Sase Name B:WUC13Description BacKuo of WUC13 created 03-27-1992
Multiple Regression Report
Dependent VariableIndependentVariableInterceptWHEELSLEN .WINGLN DRYWT3QRWHEELWGT13LOGWGT13
FHBMA13ParamererEstimate72.4115914.5682.9942E-01-12.41028-65.6-.568E-0218.59791
StndizedEstimate020oA*
_2-13-125
.0000
.6183
.6360
.9632
.8090
.0906
.0203
Standard t-valueError ( b=O )17.391414.177294-2670E-014.37050716.95416-1661E-026.412072
433-2-3—32
.16
.49
.72
.84
.87
.42
.90
Prob.Level0o00o00
.0013
.0045
.0029
.0149-OO22.0051.0133
Seq.R-Sqr
000000
-5762.5780.6106.6747.7200.8354
SimpleR-Sqr
O00OO0
.5762
.4303
.3896
.6015
.5508
.4365
Analysis of Variance Report
Dependent Variable: FHBMA13
Source df Sums of Squares Mean Square(Sequential)
Constant 1 269O.59Model 6 248.1326Error 12 48.88739Total 18 297.02
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdiusted R Squared
2690.5941.355434.07394916.50111
2.01840311.9.1696137
0.83540.7531
F-Ratio Prob. Level
10.15 O.OOO
J-5
HuitiDle Rear ess i on-Date/Time 04-12-1992 1.9:23:27Data Base Name 8:WUC13Oescriotion Backuo of WUC13 created 03-27-1992
Residual Analysis
Row
1234567a91011121314151617181920212223242526272829303132333435
Durbi
ActualY,
.
..
14.4m
18.5.
..
11.28.710.7
„
11.3S.412.18
—
1315.312.410.3
m
12.813.312.36.210.67.5
„
1.415.7
„
.
.12.7
n - Watson
PredictedValue.
.
.
12.1383911.6232917.5O248-8.098694
„
m
„
.
.
11.6314111.5633411.6218915.52705
„
12.579712.596813.2817213.56009
„
14.37613.5030113.326715.2OO3710.494217.232115.1.53793414.52365-68.25033.
.
13.9O354
3td Errof Pred....8063493.78459611.1677026.455153
„
m
m
.
.
.9716528
.9720188
.89829581.127848,
1.2302381.223564.7411884.7361409.
.9899314
.8845586
.89131861.6429391.9O2811.476327.
2.O154741.04949522.92037.
.
1.488O36
Lower95?;Mean...
10.332189.91445614.95926-22.15785
m
m
m
a
.
9.5151759.4463079166542213.07O63•
9.900279.-93190811.6674311.95679
* ,
12.2199511.5764711.385441.6220916.3499354.016712.
-2.85171912.23788-118.1703.
m
10.66263
Uoper955Mean,
._
13.8945913.332122O. 045715.960466
„
—_
m
m
13.7476413.6803713.5783517.98348
—
15.2591215.2616914.8960115.16339
<•
16.5320415.4295615.267988.7786514.6384810.44752
—
5.92758716.80943-18.33034•
.17.14444
Residual
.„
.2.261614..9975166
m
w
.—
B
—
-.3314095-3.163341.37811182.472947
—
.42030332.7032-.8817177-3.26OO91•
-1.575998-.203O125-1.026712.9996295.105792.2678852
m
-.1379341.176345.
•
„
-1.203537Statistic 1.1842
J-6
Date/TJLnieData Base NameDescription
Sum of Functions Regression05-18-1992 15:20:40C:\NASA\WUC23Merge of WUC11 and WUC51 created 04-27-1992
Estimation Summary Report
Y: FHBMA23 X: ENG WGTModel: A+B*(X)+C*(SQR(X))
Term Coefficient EstimateA 34.10401387922342B 9.853047097031215D-04C -.3122318101760727
Std. Error10.237317.461445E-04.1872512
T-Value3.31.3
-1.7
SourceModelErrorTotal
df21719
Sum-Sqr338.017964.6731302.69
Mean Square169.008556.7454768.56263
SQR(M.S.13.000337.5329598.280255
Prob(!t!>TJ0.00400.20420.1137
F-Ratio3.0
R-Squared0.25947618
Prob(f>F)0.0778
J-7
Sura of Functions RegressionDate/Time 05-18-1992 1 5 : 2 0 : 4 9Data Base Name C : \ N A S A \ W U C 2 3Description Merge of WUC11 and WUC51 created 04-27-1992
Residual Analysis
Row123456789101112131415161718192021222324252627282930313233343536
ActualX,
,
t
4497,
428336554,
,
,
,
f
9968996899682247
*
604960913671,
,
t
166961669623386380425471
$
390911053543162
,
t
176723321
ActualY...
21.7.
20.44.66.213.25.75.29.316.520.516.522.1.
11.2112220.5.
7.66.86.457.14.4.
1.426.228.4..
20.28.6
PredicteY...
17.59677.
17.8901810.42493.....
12.7523512.7523512.7523521.51742.
15.7801915.7374218.80332...
10.2102510.210259.39835718.594729.369648.
10.8878212.4366811.76412..
22.720179.400715
Value Value Residual
17.59677 .9983463 34.19518 4.103235
17.89018 1.253127 34.52723 2.509822-7.081947 27.9318 -5.824929
-3.882895 29.38759-3.882895 29.38759-3.882895 29.387593.922633 39.1122
-.6974329 32.25782-.7396602 32.21452.009699 35.59695
-6.638539 27.05904-6.638539 27.05904-7.390118 26.186831.841787 35.34766-7.407126 26.14642
-7.082106 28.85775-4.230335 29.10369-7.23429 30.76253
4.610004 40.83033-7.388428 26.18986
3.7476537.7476533.747653.582585
-4.580194-4.7374173.196676
-3.410251-3.810252-4.398357-11.49472-4.969648
-9.48782313.7633216.63588
-2.520164-.8007144
J-8
Residual Plot
rMultiple Regression-Date/Time 04-02-1992 17:08:31Data Base Name A:WUC24Description Backup of WUC24 created 03-13-1992
Multiple Regression Report
Dependent VariableIndepenaentVariableInterceptKVA MAXSQR KVAWGT24SQR WT24LOG WT24
: FHBMA24ParameterEstimate4996.525-1.90606146.34963-2.735048284.5488-1642.986
StndizedEstimate0.0000-4.27203.7415
-18.411038.6879-20.2179
StandardError1764.139.596856717.272031.063313102.2125575.155
t-value(b=0)
2.83-3.192.68
-2.572.78-2.86
Prob.Level0.02530.01520.03140.03690.02710.0245
Seq.R-Sqr
0.01510.12010.5197'0.53380.7847
SimpleR-Sqr
0.01510.00410.13600.134O0.1154
Analysis of Variance Report
Dependent Variable: FHBMA24
Source df Sums of Squares(Sequential)
Constant 1 54639.37Model 5 32075.44Error 7 8798.53Total 12 40873.97
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
54639.376415.0871256.9333406.164
35.4532564.83077.5468584
0.78470.6310
F-Ratio Prob. Level
5.10 0.027
J-9
MultiPle Regress i on-Date /T ime 04-02-1992 17:08:41Data Base Name A:WUC24Description Backup of WUC24 created 03-13-1992
Residual Analysis
3W
1234567a91011121314151617181920212223242526272829303132
ActualY.
,
.
100.
.
.
.
,
.
.
B
27.131.622.624
B
52.549.644. 12339853.2
f
14.599.790.9
333435
Durbin - Watson
Predicted Std ErrValue of Prea
69.82757
Lower95%Mean
22.92636 15.78379
Upper95%Mean
Resio.ua!
123.8713 30.17243
7.18551955.763145.4095735.43O1
41.5939344.5107444.51074181.7857
48.6821621.1045415.26921158.485594.35203
33.3694814.6383820.4951919.86587
17.0438516.7257316.7257326.3202
18.1014119.3458734.7541323.5097335.24929
-71.4755921.2564-2.903259-11.39926
1.4168555.0835725.083572119.7417
6.012123-24.49903-66.65589103.066611.25969
85.846639O. 2698193.7223982.25946
81.7710183.9379183.93791243.8297
91.3521966.7081197.19431213.9044177.4444
19.91448-24.1631-22.80956-11.4301
10.906075.089256-.410743751.21433
4.517845m
-.7692118-58.78552-3.452026
Statistic 1.276503
J-10
Date/Ti.me 04-07-1992 14Data Base Name A:WUC42Description Backup of WUC4;
••'-lultipie Reqression-T C- C "I
: createa 03-27-1992
Multiple Regression Report
Dependent VariableIndependentVariableInterceptWGT42SQR WT42LEN WINGLN DRYWTSQR WGTLOG KVAKVA SOD
FMA42/44ParameterEstimate1193.127-.755E-016.758773-.7155964-167.24012.230829.10236-.127E-02
StndizedEstimate0-77-5-10171
-4
.0000
.6982
.6694
.0081
.6606
.6804
.5538
.2703
StandardError117.0389.9180E-02.3034786.3059E-0116.50279.20853124.96025. 1504E-03
t-value(b=0)10-8a-a-10105-8
.19
.22
.41
.88
.13
.70
.87
.46
Prob.Level00000000
.0000
.0000
.0000
.0000
.0000
.0000
.0001
.0000
Sea.R-Sqr
0000000
.0233
.0363
.0384
.0391
.3664
.4321
.9126
SimpleR-Sqr
0000000
.0233
.0170
.0094
.0091
.0320
.0100
.0290
Analysis of Variance Report
Dependent Variable: I-MA42/44
Source df Sums of Squares Mean Square(Sequential)
Constant 1 9425.524Model 7 5013.7J7Error 13 480.0486Total 20 5493.766
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
9425.524716.245336.92682274.6883
6.07674421.18571.2868321
0.91260.8656
F-Ratio Prob. Level
19.40 0.000
J-ll
Multiple Reg re ESI on-14:36:04Date/Time 04-07-1992
Data Base Name A:WUC42Description Sackuo of WUC42 created 03-27-1992
ROW ActualY
Predicted'.Value
Residual Analysis
3td Errof Pred
Lower95%Mean
Upper95%Mean
Residual
34567891011121314151617181920212223242526272829303132333435
Durbin
26.3.
24.49918.87.99 . 417.91615.716.336.3,
12.614.914.513.2
12.814.412.41020.239.8
2.520.781.7.
.
31.2- Watson
29.8017
14.950136.211584
3.488953
1.7404275.541101
22.26824
11.19215-5.752943
37.33516
18.7081218.17611
-3.501701
9.4498672.788416
16.7053116.8231414.2268633.83958
6.69112818.0953221.8323919.82873
4.7349313.6565916.1345919.8094817.4475339.02169
5.14978522.9655177.70444
2.3485492.8728242.9729564.143581
2.9379483.4580872.1832442.184684
3.2329782.7588872.6519552.9714534.4988684.757357
5.9562063.217155.775562
10.5546310.620047.80755524.89262
.347414510.628517.1182615.11149
-2.2458217.69951110.408413.393437.73343328.74945
-7.7110516.0189365.23366
22.8559923.0262320.6461642.78654
13.0348425.5621326.5465224.54597•
11.7156819.6136721 . 8607826.2255427.1616449.29393
18.0106229.912089O. 17522
-.705307-1.1231362.073142.460419
5.908873-3.195318-7.332394-6.628732
8.065071. 7434092-3.734589-9 . 8094852.752466. 7783089
-2.649785-2.2655053.99556
29.27219 4.585095Statistic .9728374
19.37191 39.17248 1.927809
J-12
—^Multiple Regression-Date/Time 04-03-1992 14:10:20Data Base Name A-.WUC45Description Backup of WUC45 created 03-13-1992
Multiple Regression Report
Dependent VariableIndependentVariableInterceptWETAREA3U8SYSSQR SUBSLOG SUBSSQR WT45LOG WT45
FHBMA45ParameterEstimate396.2586-.622E-0235.63519-779.8318975.56658.812898-105.7279
StndizedEstimate0.-1.14.
-27.12.3.-2.
0000253492055569848116243344
Standard t-valueError (b=O)158.0882.2952E-0213.60838293.7664372.15572.21449925.46246
O4.
-22-223-4
.51
.11
.62
.65
.62
.98
.15
Prob.Level0000000
.0263
.0552
.0212
.0198
.0211
.0016
.0011
Seq.R-Sqr
000000
.1895
.2126
.2190
.3287
.3724
.7302
SimpleR-Sqr.
0.0.0.0.0.0.
189516061578137716462943
Analysis of Variance Report
Dependent Variable: FHBMA45
Source df Sums of Squares Mean Square(Sequential)
Constant 1 43300.82Model 6 25232.66Error 13 9321.665Total 19 34554.32
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SauaredAd.justed R Squared
43300.824205.443717.05121818.648
26.7778146.53.5754956
0.73020.6057
F-Ratio Prob. Level
5.86 0.004
J-13
flu 1 tide Regression-Date/Time 04-03-1992 14:10:30Data Base Name A:WUC45Description Backup of WUC45 created 03-13-1992
Residual Analysis
Row
1234567891011121314151617181920212223242526272829303132333435
Durbin
ActualY.
.
.
44.4.
95.89.612.335.220.518.528.230.426 . 344.7183.
19.725.475.762.7.
1718.719.414.327.316
f
4.773.860.5,
m
91.6- Watson
Predicted Std ErrValueB
m
m
43.68098.
71.948197.946936
m
m
.
.
.
.
30.6770130.67701121.2529.
43.5881937.1987584.1158684.03505,
28.7947728.7198628.7198623.1532433.6419-19.23709,
8.60784249.3537368.67876
„
,
125.0493Statistic .
of Predm
.
.
18.99137.
9.O1718723.73618,
.
.
.
.
.
13.3297913.3297915.21319
B
8.8641459.7463299.8133089.798325•
11.8298411.8342911.8342914.2364224.3488816.0961
»
22.3944514.3985524.75348.
.
16.280757553009
Lower95?sMean.
.
. .
2.674194.
52.47798-43.30499.
.
.
.
m
.
1.8949031.89490388.404O7•
24.4484416.1541562.9266462.87819.
3:.2513913 . 1668823.166882-T: 586506-18.93301-53.99232•
-39.7469818.2639115.23025.
•
89.89542
Upper95%Mean,
.
.
84.68777.
91.418459.19886.
m
B_
.
.
59.4591259.45912154.1017•
62.7279458.24334105.3051105.1919
m
54.3381554.2728454.2728453.8929936.2168115.51813
m
56.96266SO. 44355122.1273
w
a
16O.2033
Residual
B
.7190208a
23.851811.653065...f
.•
-4.37701414.0229961.74712•
-23.88819-11.79875-8.415863-21.33505
m
-11. 79477-10.01986-9.319861-8.853242-6.341935.23709
9
-3.90784224.44627-8.178764,
m
-33.44935
J-14
--_ Multiple Regression-Dace/Time 04-02-1992 16:26:05Data Base Name A:WUC14Description Backup of WUC14 created 03-27-1992
Multiple Regression Report
Dependent VariableIndependentVariableIntercept3QR WT14ACTUATORCONT SURLEN WINGWETAREA
FHBMA14ParameterEstimate26.29027-1.11361.9516068-1.899484.3505284--357E-02
StndizedEstimate0.0000-3.12674.4096-3.21127.4989-5.6737
Standard t-valueError (b=0)5.516686.2823322.2070737.3542125.0697234.8842E-03
4.77-3.944.6O-5.365.03-4.04
Prob.Level0.00060.00230.00080.00020.00040.0019
Seq.R-Sqr
0.31190.36650.42570.58700.8338
SimpleR-Sqr
0.31190.36350.41770.19620.2781
Analysis of Variance Report
Dependent Variable: FHBMA14
Source df Sums of Squares Mean Square(Sequential)
Constant 1 3124.495Model 5 368.186Error 11 73.38562Total 16 441.5716
F-Ratio Prob. Level
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
3124.49573.637196.6714227.59822
2.58290913.55706.1905213
0.83380.7583
11.04 0.001
J-15
Multiple Regression-Date./ Time 04-02-1992 15:26:14Data Base Name A:WUC14Description Backup of WUC14 created 03-27-1992
Residual Analysis
Row
12345678910111213141516171819202122232425262728293031323334
Durbin
ActualY
3.932.764.2814.567.2817.147.084.3622.496.027.219.619.359.89.6521.74.4812.9514.3515.5314.347.4714.3818.9418.326.611.86.88.573.821.98.
6.74.24- Watson
Predicted Std ErrValue.
m
m
13.36487.
18.932956.314134.
.
.
.
»
8.35759511.2124212.859921.57O82,
14.2221915.8861211.7961712.73119
»
17.1457817.1457817.706639.488832...
3.59049218.14413-73.75688.
•
Statistic 1
of Prea.m
B
1.540009.
1.2720042.212739•
.
.
.
•
1.3603071.1548891.1451792.105001.
1.2014211.2103351.1776661.058403•
1.2704081.2704081.299221.438714...
2.5524061.8166115.50723..
.453594
Lower95%Mean.
m
m
9.978226.
16.135681.448084•
m
B
.
m
5.3661368.67269210.3415316.9417.
11.5801413.224469.20635610.40365•
14.3520214.3520214.84956.324945•
.
.
-2.02252114.14921-107.8589.
.
Upper95?sMean..f
16.75151,
21.7302211.18018.
.
•
.
.
11.3490613.7521415.3782726.19994.
16.8642518.5477814.3859815.05873•
19.9395419.9395420.5637512.65272.
.
,
9.20350522.13905-39.65482.
•
Residual
1.19513.
-1.792948- 7658658
m
.
.
.9924049-1.412416-3.209903.129179.
-1.272195-1.5361193.7338311~. 608809
*
-2.7657791.794222.6133728-2.888832,
^
^
.20950823.835873•
•
^
J-16
rtultioie Rearession-1-4:10:02Oate/Time O4-O5-1992
Data Base Name B:AVIONIC3Oescrionon Sackuo of AVIONICS created 03-27-1992
Multiple Regression Report:
Dependent VariableI ndependentVariableInterceptTOTSUBSSQR TSUBAVG WT/3WQT51/72SQR51/72
FHBMAParameterEstimate-36.91729-4-496O1645.75636-.1230886.2360E-01-2.453409
StndizedEstimate0-73-210-9
.0000
.2132
.1287
.2612
.1898
.6786
Standard t-valueError (b=O )27.717371.79898518.14795.4387E-01. 7750E-02.7582701
-1-22-23-3
.33
.SO
.52
.81
.05
.24
Prob.Level000O00
.2124
.0315
.0303
.0186
.0124
.0089
3eq.R-Sqr
00000
.3061
.3499
.5039
.5524
.7813
SimpleR-Sqr
00000
.3061
. 3269
.1876
.4244
.5377
Analysis of Variance Report
Dependent Variable: FHBMA
Source df 3ums of Squares Mean Square(Sequential }
Constant 1 1161.106Model 5 277.7397Error 10 77.7247Total 15 355.4644
F-Ratio Prob. Level
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
1161.10655.547937.7724723.69763
2.7879158.51875.3272681
0.78130.6720
7.15 O.OO4
J-17
nuitioie Recression-.14:10:02Oate/Time U4-O5-1992
Data Base Name B:AVIONICSDescription Backup of AVIONICS created O3-27-1992
Residual Analysis
Row Actual Predicted 3td Erry Value of Pred Mean
Upper95%Mean
Residual
34567a9
1011121314151617181920212223242526272829303132333435
Durbi
,13.8
„
11.73.63.25.35.74.56.54 .632.313.4.
7.26.817.110.9
_
4.74.43.22.611.34.4.
1.5
9.6„
14.4n - Watson
_
11.47413.
13.29583.321389
„
„
„
„
«
.,
3.347O25^
14.37355„
9.2150O68.96962113.6941812.69238.
„
4.354426.210011,
5.7701875.542498.
2.12689-.32241687.683124.
.
14.22974Statistic 1.
.2.163948.1.3918162.734361....-.1.895034.2.05159..9867181.96925661.4210321.256933..1.1187571.03621.1.5473291.320705.1.6367263.2934022.278235..2.211951
486O22
. -'6.654596.
10.19595-2.768568......
-.8735862.
9.804258.
7.0173926.81089710.529279.892949..1.8627313; 902168.
2.3239832.601031.
-1.51842-7.6574662.609049..9.303292
.
16.29367.
16.395649.411346......7.567636
m
18.94284.
11.4126211.1283416.859115.49182.
„
6.8461098.517853.
9.2163928.483965.
5.7721997.O1263212.7572•
m
19.15619
m
2.325869m
-1.595797.2786114
m
^
„
m
..
,
- . 3470249m
-.9735508m
-2.015006-2.1696213.4O5816-1.792384...4558E-01-3.010011
m
5.529813-1.142498.
- . 6268895m
1.916876.
m
.1702614
J-18
Multiple RegressionDate/Time 03-17-1992 15:46:03Data Base Name C:\NASA\PRECONDescription Merge of WUC12 and WUC11 created 03-17-1992
Multiple Regression Report
Dependent Variable: ECS FHMAIndependent Parameter StndizedVariableInterceptDRY_WGTLEN_WINGLN LENTH
Estimate454.3876-.547E-03.8210209-107.5185
Estimate Error0.0000 73.06644-2.7882 .1174E-036.3884 .1587219-4.3668 18.67703
t-value(b=0)
6.22-4.665.17-5.76
Prob.Level0.00000.00010.00000.0000
Seq.R-Sqr
0.22680.24120.7057
SimpleR-Sqr
0.22680.23990.3295
Analysis of Variance Report
Dependent Variable: ECS FHMA
Source
ConstantModelErrorTotal
df Sums of Squares Mean Square F-Ratio Prob. Level(Sequential)
1 158763 2878.971 959.6572 16.78 0.000
21 1200.84924 4079.82
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
15876959.657257.18326169.9925
7.56196225.2.3000779
0.70570.6636
J-19
Multiple RegressionDate/Time 03-17-1992 15:46:20Data Base Name C:\NASA\PRECONDescription Merge of WUC12 and WUC11 created 03-17-1992
Residual Analysis
1 Std Errof Fred4.1182184.0854651.8288522.38572.369651.740723.8954842.9132071.7796172.6957682.8021192.8021192.115572.1239112.1004313.4870542.5337461.8862331.9164422.8438522.6477591.9964512.9614032.7142972.6823542.8266841.7491753.5578132.0402797.2512642.6218018.3792092.2909142.1521253.978719
564765
Lower95%Mean42.186141.9559921.8893531.8999531.5207324.1758817.408996.2004322.757278.7091017.7717127.77171222.2579722.1547520.4285539.38911.2141821.3262820.9039735.3652934.3502426.4742715.8312713.6693113.2265913.8963723.3564416.4876116.49411-11.19213.34383-38.7122712.6440416.9285341.95843
Upper95%Mean59.3124958.9461729.4949741.8213441.3753731.4149933.609118.3155630.1581519.9199619.4248619.4248631.0559730.9874329.1635953.8905821.7512429.1705428.8738647.1919945.3614534.7768928.1468324.9572324.3816725.6516730.6307231.2834524.9789918.9637524.24709-3.86573222.1712425.8785558.50468
Residual
(
.t
-1.060646•
-1.9954381.290951-5.55799314.24229-4.114533-2.098285-1.998284.44303515.528914.403929-3.639786
*
-4.34841-2.488913-.6786423-8.255842•
-8.189052-3.413271-3.00413214.32598-2.593578-12.18553•
1.61412416.60454•
•
•
7.168446
J-20
ResidMultiple Regression
Date/Time 03-18-1992 16:24:35Data Base Name C:\NASA\PRECONDescription Merge of WUC12 and WUC11 created 03-17-1992
Multiple Regression Report
Dependent Variable:IndependentVariableInterceptLEN_WINGLN DRYLDRY SQDWGT/LEN
FHBMA47Parameter StndizedEstimate Estimate6613.119 0.0000-1.484938 -3.7671-1358.298 -31.405573.58044 36.8273-.7258523 -2.5758
S tandardError2618.338.824043574.823432.95623
t-value(b=0)
2.53-1.80-2.362.23
Prob.Level0.01860.08410.02660.0352
Seq.R-Sqr
0.18440.38880.4523
SimpleR-Sqr
0.18440.31310.2908
.3997296 -1.82 0.0819 0.5185 0.2127
Analysis of Variance Report
Dependent Variable: FHBMA47
Source df Sums of Squares Mean Square(Sequential)
Constant 1 157445.3Model 4 24456.88Error 24 22715.22Total 28 47172.1
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
157445.36114.22946.46751684.718
30.7647173.68276.4175293
0.51850.4382
F-Ratio Prob. Level
6.46 0.001
J-21
Multiple RegressionDate/Time 03-18-1992 16:24:54Data Base Name C:\NASA\PRECONDescription Merge of WUC12 and WUC11 created 03-17-1992
Residual Analysis
Row
123456789101112131415161718192021222324252627282930313233343536
Durbin
ActualYt
,
,
•
59.45457.345.848.560.771.870.642.852.857.521543.6116.4143.696.863.889.553.663.837.539.410544.7,
17.888.588.1
t
•
15157.5- Watson
Predicted Std ErrValue141.1113135.105874.5027489.1327186.2055181.109750.205965.3828676.7792265.5499265.0115165.0115164.5768264.2231765.46734142.090165.1792372.5086471.52433103.5267103.856675.7008252.1328956.595157.4500257.7234179.3160152.8481667.6524726.0277956.8467961.1599467.1311366.90881183.777669.05804
Statistic 1
of Pred14.827813.739577.3882898.8569168.979489.00659913.074869.3737517.5358398.5896798.9946818.99468110.6924210.800149.71571515.253398.3947647.5620077.6797189.6274649.6126768.6973611.785611.0587711.0708511.895239.22261212.597338.16292727.4912910.5645919.69377.371018.1796824.3162519.9642
.776327
Lower95XMean110.5091106.749559.2544970.8534567.6732962.5215223.2214946.0369361.2264647.822246.4479246.4479242.5093741.9334145.41566110.609547.8537856.9018655.6746283.6571884.0176157.7508627.8092833.7715834.6015633.1735560.2820126.8492850.8055-30.7098435.0431720.5152851.9185550.02726133.592727.85511
Upper95%Mean171.7135163.462189.75098107.412104.737799.6978877.1903284.7287892.3319983.2776483.5750983.5750986.6442786.5129285.51902173.570682.5046888.1154187.37404123.3963123.695793.6507876.456579.4186380.2984882.2732698.3500178.8470384.4994582.7654178.65041101.804682.3437283.79037233.9624110.261
Residual
,(
•
•
-26.8055-27.10977.094097-19.58286-28.27922-4.8499186.7884985.588493-21.. 77682-11.42317-7.96733972.90994-21.5792343.8913772.07568-6.726723-40.0566413.799181.467117.204895-19.95002-18.3234125.68399-8.148155
t
-8.22778731.6532126.94006•
•
-32. .77757-11.55804
J-22
Multiple RegressionDate/Time 04-06-1992 11:25:48Data Base Name C:\NASA\WUC96Description Merge of WUC47 and WUC12 created 02-11-1992
Multiple Regression Report
Dependent VariableIndependentVariableInterceptDRY WGTCREWSIZELEN WINGPERSONSSQR PERWGT49/96SQRWT49/LOGWT49/
FMA49/96ParameterEstimate17952.73.5793E-02169.962-10.1356821.14998-461.3335-1.892708421.331-4O54.064
StndizedEstimate021
-610
-13-3771-29
.0000
.6703
.5299
.6007
.7670
.7798
.9819
.9834
.7305
Standard t-valueError (b=0)2610.109.1051E-0234.799771.4932223.98022986.43541.315461168.4356615.40O6
654-65-5-66-6
.88
.51
.88
.79
.31
.34
.00
.16
.59
Prob.Level000000000
.0000
.0002
.0005
.0000
.0002
.0002
.0001
.0001
.0000
Seq.R-Sqr
00000000
.2448
.4510
.5271
.5287
.5324
.5328
.6250.
.9242
SimpleRr-Sqr
00000000
.2448
.4508
.4064
.2572
.3662
.3246
.4239
.5188
Analysis of Variance Report
Dependent Variable: FMA49/96
Source df Sums of Squares(Sequential)
Constant 1 770752.3Model 8 534015.3Error 11 47919.77Total 19 631935
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
770752.373001.914356.34233259.74
66.00259196.31.3362162
0.92420.8690
F-Ratio Prob. Level
16.76 0.000
J-23
Multiple RegressionDate/Time 04-06-1992 11:26:00Data Base Name C:\NASA\WUC96Description Merge of WUC47 and WUC12 created 02-11-1992
Residual Analysis
Row
1234567S9101112131415161718192O212223242526272829303132333435
Durbi
ActualY.
„
„
234B
23555.54O. 160.395108.4121.8236.6236.8262.1610.8.
83.6131.1561.1492.7.
34.748.834.246.770.534.6
m
10201.4175.9,
a
331.5n - Watson
Predicted Std ErrValue.
m
.
296.2767»
213.767647.42839.
.
.
.
„
258.4744259 . 3846217.3143454 . 2334.129.978132.4468630.444452.9334.
.367659226.3637521.5707873.3337878.9325984.06O72.
-7.931614•
179.8266.
.
376.9937Statistic .
of Pred*
m
.
23.31404•
36.6763165.27004.
.
.
.
B
36.7633236.8095934.7252228.79348•
36.8856236.6277446.6696440.21066
B
32.3759631.5515231.5928763.020853.7456649.07781•
64.03231.
65.26067.
.
33.911248255058
Lower95%Mean»
m
m
245.0067m
133.1125-96.10739
m
m
m
m
m
177.628178.4363140.9498390.9134
—
48.8625351.8985527.8124364.5058
• *
-70.83053-43.0214-47.90533-65.2557-39.25987-23.86664.
-148.7455m
36.31137m
•
302.4193
Upper95%Mean,
m
m
347.5468•
294.4228190.9642.
B
m
m
m
339.320934O . 3328293.6787517.5533
—
211.0934212.9951733.0755541.3609
m
71.5658595.7489191.0469211.9232197.125191.9881
—
132.8823a
323.3418.
•
451.5682
Residual
•
.
.-62 . 27673
m
21.232388.07161
m
.B
m
m
-21.87442-22.5845844.78574156.5666
m
-46.37795-1.346802-69.3439939 . 76666
m
34.3323422.4362512.62922-26.63378-8.432587-49.46072•
17.93161.
-3.926575.
.
-45.49371
J-24
—. Multiple Reqression-•Date/Time 04-20-1992 12:59:29Data Base Name B:WUC97Description Backup of WUC97 created 03-13-1992
Multiple Regression Report
Dependent Variable: FMA91397Independent Parameter Stndized StandardVariable Estimate Estimate ErrorIntercept 7549.095 0.0000 204O.461DRY_WGT -.165E-01 -4.8461 .7514E-02LEN_WING 4.00187 2.6090 1.085099LN DRYWT -999.7649 -6.7243 276.4O953QR WGT 16.8468 10.9600 6.396186PERSONS -4.224915 -2.1475 .862487
value=0)3.70-2.203.69-3.622.63-4.9O
Prob.Level0.00210.04420 . 00220.0025O.O1880.0002
Seq.R-Sqr
0.11830.29450.30540.62560.8560
SimpleR-Sqr
0.11830.18600 . 08310.12140.0506
Analysis of Variance Report
Dependent Variable: FMA91397
Source df Sums of Squares Mean Square(Sequential)
Constant 1 6O3369.1Model 5 2055O8.5Error 15 34579.43Total 20 240087.9
F-Ratio Prob. Level
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
603369.141101.72305.295120O4.4
48.01349169.5048.2832575
0.85600.8080
17.83 O.OOO
J-25
Multiple Regression-Date /Time O4-20-1992 12:59:29Data Base Name B:WUC97Description Backup of WUC97 created 03-13-1992
Residual Analysis
ActualYw
„
.
104_
122.4m
249.241146.8175.219972.174.896.9125.4
i»
58109.5
-• i*
*
„189.9281.2140.8452.8128.596
„
385 . 3.
- Watson
Predicted Std ErrValue143.8382125.92597.2693653.5772846.76052134.22921031.059237.2138108.7047204.3625205.5599205.559945.6894545.4324562.84465174.4325159.903793.4960392.0333873.5501980.5303653.35607211.3269212.3031220.6398425.021893.45365104.506988.O2855-533.9526339.3272505.O987194.987895.26366289.9013
Statistic l.
of Pred25.8281724.4618216.0448418.0265217.8945526.72573205.203521.5065218.6879617.8731719.511219.511220.2745620.5197418.4420225.8818216.5136914.8038914.5377419.2375619.636716.5085529.4641226.6347525.4620135.3164225.0448246.2821222.05599436.025525.87459327.400915.9200515.4212841.4184
8O4476
Lower95%Mean88.805873.8039963.0824615.167988.63240177.28436593.8298191.389668.88611166.2799163.9872163.98722.49O2311.71081523.55004119.2859124.717861.9532261.0576732.5605238.6902318.18113148.5473155.5521166.3876349.77284O.09O395.89305941.03361-1462.997284.1959-192.498161.066862.40537201.6507
Upper95%Mean198.8705178.O461131.456391.9865884.88863191.1741468.288283.038148.5234242.4451247.1326247.132688.8886789.15409102.1393229.5792195.0896125.0388123.0091114.5399122.370588.53101274 . 1064269.054274 . 892500.2709146.8169203.1207135.0235395.0914394.45841202.695228.9089128.1219378.152
Residual
.
.50.42272.-11.82916.11.98621-67.70474-57.5625-30.35989-6.55989126.4105529.3675534.05535-49.03252
—
-35.4960317.46662
m
m
m
-21.4268668.89696-79.8397827.7781735.04635-8.506867
m
m
45.97281•
•
„
20.89865
J-26
APPENDIX K
MHMA Regression Analysis
Multiple RBgsedaaonDate/T,ime 04-01-1992 15:46:03Data Base Name C:\NASA\WUC11Description Backup of NASAMSTR created 12-18-1991
Multiple Regression Report
Dependent Variable: MH/MA11Independent Parameter Stndized StandardVariable Estimate Estimate ErrorIntercept 16.57323 0.0000 3.446548FUS DENS -.3511567 -0.7189 .8338E-01LN DRYWT -.7455627 -0.4292 .2965363
value:=0)4.81-4.21-2.51
Prob.Level0.00010.00030.0194
Seq.R-Sqr
0.29260.4451
SimpleR-Sqr
0.29260.0172
Analysis of Variance Report
Dependent Variable: MH/MA11
Source df Sums of Squares Mean Square(Sequential)
Constant 1 982.1554Model 2 30.41182Error 23 37.9128Total 25 68.32462
F-Ratio Prob. Level
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
982.155415.205911.6483832.732985
1.2838946.146154.2088938
0.44510.3969
9.22 0.001
K-l
Multiple RegressionDate/Time 04-01-1992 15:46:19Data Base Name C:\NASA\WUC11Description Backup of NASAMSTR created 12-18-1991
Row
1234567891011121314151617181920212223242526272829303132333435
Durbin
ActualY,
,
.
5.8,
5.26.93.97.44.34.44.36.25.46.77.6,
5.795.24.1
t
5.78.19.869.26.3,
5.44.45.1
f
t
7.7- Watson
PredictValue7.5689377.5651485.9721216.1180946.0871484.1100455.1510784.2515176.811384.6304664.6081254.6081256.0160826.0014865.9183147.374845.0970786.467176.7717155.7643465.7643465.8053037.1687767.1420277.1218796.4155677.3629026.254596.7449766.2516037.0082646.0111435.5941745.3583828.696106
Statistic :
Residual Analysis
of Pred.530663.5209367.2885803.339687.3332928.6046.4670056.5098779.3165508.4368744.4402585.4402585.2735671.2736548.2748418.5128313.3557626.280771.3012482.40291.40291.3146783.393468.3987096.3993941.3622405.397073.4301723.290952.6268806.3578876.5460897.2865999.3272913.7472628
.591353
Lower95%Mean6.4712856.4876155.3752075.4154675.3977482.8594584.1850993.1968596.156613.7268123.6974713.6974715.4502225.4354445.3498166.3140734.3611995.8864096.1485974.9309454.9309455.1544056.3549066.3173156.2957515.666296.5415755.3647996.1431564.9549296.267994.8815825.0013564.6813957.150428
Upper95%Mean8.6665888.6426816.5690366.820726.7765495.3606316.1170575.3061767.466155.534125.5187795.5187796.5819436.5675286.4868118.4356085.8329567.0479327.3948336.5977466.5977466.45627.9826467.966747.9480077.1648458.1842297.1443827.3467977.5482767.7485387.1407046.1869936.03536810.24178
Residual
•
•
9
-.3180933a
1.0899551.748922-.3515172.5886202-.3304658-.2081251-.308125.1839175-.6014857.7816863.2251596•
-.76717042.228285-.5643458-1.664346•
-1.468776.9579732.678121-.41556741.837098. 4541E-01*
-.8516026-2.608264-.9111433•
t
-.9961062
K-2
T Sum of Functions RegressionDate/Time 04-02-1992 15:39:30Data Base Name C:\NASA\WUC12ADescription Merge of WUC11 and WUC12 created 04-01-1992
Estimation Summary Report
Y: MH/MA12 X: LOG PERSModel: A+B*(1/SQR(X))+C*(X*X)
Term Coefficient EstimateA 7.085547889120501B -1.66660693023797C .0987784700042235
Std. Error2.5541922.2571517.185552E-02
T-Value Prob(!t!>T)2.8 0.0130-0.7 0.47041.4 0.1871
SourceModelErrorTotal
df21719
Sum-Sqr52.4533342.9846895.438
Mean Square26.226662.528515.023053
SQR(M.S.)5.1211981.5901292.241217
F-Ratio10.4
R-Squared0.54960626
Prob(f>F)0.0011
K-3
Sum of Functions RegressionDate/Time 04-02-1992 15:39:39Data Base Name C:\NASA\WUC12ADescription Merge of WUC11 and WUC12 created 04-01-1992
Residual Analysis
Row123456789101112131415161718192021222324252627282930313233343536
ActualX00.69314720001•
.79175969314720•
•
•
•
,
.
0•
000•
0444425353411•
3
693147269314726931472693147269314726931472
6931472
6931472
.564348
.564348
.564348
.430817
.397895
.365976
.433987
.899898
.7612
.369448
.609438
.3862946931472.135494
ActualY
7.6
4.4.43.55.65.5.4.3..
8.1076..
6.8.11107.10.
7.57.,.
4.7.
52
2
3
4278
5
5
48.9.23.4
7
7
69
Predicted Lower95%Y Value
5.131208 1.596899
65
555555
5
5
88886979786557
.
.157598
.131208
.
.131208
.131208
.131208
.131208
.131208
.131208
.
.131208
.
.
.
.131208
.
.363339
.363339
.363339
.233025
.577252
.210281
.351009
.837771
.62358
.174137
.027713
.859896
.131208
.115475
21
111111
1
1
44442535442213
,.453058.596899..596899.596899.596899.596899.596899.596899,.596899....596899,.840035.840035.840035.714607.839643.483817.732269.766802.054166.655851.355306.240462.596899.450584
Upper95%Value
8.665516
.9.8.,
8.8.8.8.8.8.
t
3.,,.
8.,
111111111012101311119.9.8.10
862137665516
665516665516665516665516665516665516
665516
665516
.88664
.88664
.88664
.75144
.31486
.93675
.96975
.90874
.19299
.692427001247933665516.78037
Residual
*
*
,
-1.957598-1.131207
*
-.1312074. 1687928.8687926.2687927.0687924-.4312076,,,,.
1.368793.
-1.963338.43666193.5366611.966975.72274821.189718
*
-2.137771-2.62358-.4741375
^9
-.5312075.7845255
K-4
Residual P--. • Sum of Functions Regression-Date/Time 04-02-1992 16:08:13Data Base Name C:\NASA\WUC13,-Description Backup of NASAMSTR created 12-20-1991
Estimation Summary Report
Y: MH/MA X: LOGWGT13Model : A+B*(X)+C*(X*X)-l-D*(X~3)
Term Coefficient EstimateA -156.94627814436718 55.98411332035852C -6.095157233287962D .2128174813014896
Std. Error175.319563.685287.631809.3017441
T-Value Prob(!t!>T)-0.9 0.38250.9 0.3909-0.8 0.43490.7 0.4897
R-Squared0.27491117
SourceModelErrorTotal
df Sum-Sqr3 39.0643818 103.033821 142.0982
Mean Square13.021465.72416.76658
SQR(M.S.3.6035262.. 3925092.601265
F-Ratio2.3
Prot>(f>F)0.1146
K-5
Sum of Functions Regression-Date / Time 04-02-1992 16:08:18Data base Name C : \ N A S A \ W U C 1 3Description Backup of NASAMSTR created 12-20-1991
ActualRow X
1234 7.1444075 .6 7.3038437 9.4720898 .9 .10 .1112 .13 7.5817214 7.5817215 7.5817216 6.6437917 .18 7.17395819 7.20266120 6.82871221 6.97260622 .23 8.49146524 8.49146525 8.49146526 9.30773927 6.98564228 9.29192129 .30 10.5527431 8.36520732 10.1739333 .34 .35 6.26720136 9.497772
ActualY,
«
.
9.9m
8.56.26.46.810.111.59.611.57.310.611.9
m
9.513.664.3•
10.99.411.79.110.96.6.
5.95.94.8.
.
6.67.9
Residual Analysis
Predicted Lower95% Upper95%Y Value Value Residual
9.522524 4.266597 14.77845 .3774756
9.720329 4.451412 14.989257.340721 1.897937 12.78351
9.8941269.8941269.8941268.370622
9.564929.6035648.8958049.221945
9.2529119.2529119.2529117.7002859.2480737.734547
5.1746969.430365.845793
6.9005557.284155
4.605783 15.132474.605783 15.182474.605783 15.182472.906784 13.83446
4.307173 14.822674.34368 14.863453.592491 14.199123.961608 14.48228
3.9501933.9501933.9501932.2692833.9893992.305128
14.5556314.5556314.5556313.1312914.5067513.16397
-1.452819 11.802214.138935 14.72179.1736933 11.51789
-1.220329-1.140721
.4045451.840164
13.3965612.72815
1.605874-2.594126.70587443.529378
-.649E-013.996436-2.895804-4.921945
1.647089.14708942.447091.3997151.651927-1.134547
.7253048-3.53036-1.045793
-.3005549.6158446
K-6
Sum of Functions RegressionDate/Time 05-18-1992 15:22:42•'Data "Base Name C:\NASA\WUC23Description Merge of WUC11 and WUC51 created 04-27-1992
Estimation Summary Report
Y: MHMA23 X: ENG WGTModel: A4-B*(X)+C*(SQR(X) )
Term Coefficient EstimateA 52.6323670458033B 9.122120994236714D-04C -.393600323202448
Std. Error14.947581.089452E-03.273407
T-Value Prob( !tJ >T)3.5 0.00260.8 0.4140-1.4 0.1681
SourceModelErrorTotal
df Sum-Sqr2 1509.60817 2056.60219 3566.21
Mean Square754.8038120.9766187.6953
SQR(M.S.27.4736910.9989413.70019
F-Ratio6.2
R-Squared0.42330867
Prob(f>F)0.0093
K-7
Sum of Functions RegressionDate/Time 05-18-1992 15:22:51Data Base Name C:\NASA\WUC23Description Merge of WUC11 and WUC51 created 04-27-1992
Residual Analysis
Row123456789101112131415161718192021222324252627282930313233343536
ActualX
•
•
4497,
428336554•
*
,
•
^
9968996899682247,
604960913671
»
,
t
166961669623386380425471,
390911053543162,
•
176723321
ActualY
•
•
.22.
2913192417132425314158. .36313211.
101213141214•
116.10•
•
254.
.6
.8
.7
.3
.2
.2
.7
.7
.5
.5
.9
.8
.5
.9
.7
.2
.8
.9
.1
.2
.2
.44.7
1
PredictedY
.30.
3010•
•
•
•
•
22222236•
272732•
•
t
1717133113•
102110•
*
3713
.33987
.78034
.72453
.42829
.42829
.42829
.02446
.53795
.47017
.13334
.00438
.00438
.7741
.8265
.05014
.47118
.84333
.23296
.69898
.79851
Lower95%Value
•
6
6
.•
•
•
104384
488446-14.83741
---1
337
e
•
.•
•
1110.•
•
•
•
•
•
-7-7
.860969
.860969
.860969
.33417
47882641185612824
.596682
.596682-10.738897•365395-11.44577
-•
1-25.76686.492323
-17.50677
1
•
•
1.25618-10.71545
Upper95%Value
*
.54.,
55.36.,
•
•
•
•
46.46.46.61..
51.51.56.
*
•
•
41.41.38.56.37..
36.46.37.•
•
64.38.
57537
0722428647
71755717557175571475
597075284965385
605446054428712876154605
70923178979727
1417831248
Residual
•
-7.739875•
-.98034352.975473•
.•
•
•
3.0717089.07170919.4717122.77554•
8.4620524.029831.7666664•
•
•
-4.204381-3.104381.325899-19.62651.14986•
.9288171-15.44333.4670366•
•
-12.69898-9.698515
K-8
Residual Plot
-Multiple Regression-Date/Time 04-02-1992 17:09:45Data Base Name A:WUC24Description Backup of WUC24 created 03-13-1992
Multiple Regression Report
Dependent Variable: MH/MA24IndependentVariableInterceptKVA MAXSQR KVAWGT24SQR WT24LOG WT24
ParameterEstimate-451.3954.9054E-01-2.965429.265695-26.09953150.5043
StndizedEstimate0.00003.4559-4.002730.0350-58.211929.6631
StandardError118.7124.4055E-011.175478.7173E-016.88959138.72723
t-value(b=0)-3.802.23-2.523.70
-3.793.89
Prob.Level0.00890.06700.04510.01000.00910.0081
Seq.R-Sqr
0.00720.01660.04120.07490.7370
SimpleR-Sqr
0.00720.01010.00250.00430.0098
Analysis of Variance Report
Dependent Variable: MH/MA24
Source
ConstantModelErrorTotal
df Sums of Squares Mean Square F-Ratio Prob. Level(Sequential)
1 1164.275 95.682116 34.147911 129.83
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
1164.2719.136425.69131611.80273
2.3856489.85.2421977
0.73700.5178
3.36 0.086
K-9
Multiple Regression-Date/Time 04-02-1992 17:10:05Data Base Name A:WUC24Description Backup of WUC24 created 03-13-1992
Residual Analysis
Row
1234567891011121314151617181920212223242526272829303132333435
Durbin
ActualY.•
,
•
f
8.7,
•
•
,
,
.
,
•
•
,
,
17.213.87•
.
7.97.512.7rrt
129.
7.76.713•
•
,
- Watson
PredictedValue.t,.,
6.741755.......,...
17.0495311.434049.05177610.05459.10.2929410.1549710.154976.877838.
8.31726913.15047.6492337.56062812.91464...
Std Errof Pred.,,.,
1.770797,..........
2.276696.98696531.6565091.613951.
1.1469991.1254871.1254871.776137.
1.2217661.3222752.338621.5856652.372941...
Lower95%Meant
^9
t
,
2.411969,t
,,,,,,,«,
11.482779.0208075.0014386.108312,
7.4884117.4030357.4030352.534996,
5.3299249.91731.9310613.683517.112551...
Upper95%Mean9
9
.
t
t
11.07154t
§
9
t
f
t
t
t
9
9
t
22.6162913.8472713.1021114.00087
%
13.0974812.906912.906911.22068.
11.3046216.383513.367411.4377518.71673,9
t
Residual
.
.,
1.958245.
.
.t
.,.t
•
t
.15047262.365959-2.051776,"«-2.392944-2.6549692.545031,1221623
t
.6827307t
.5077E-01-.8606281.8536E-01.,9
Statistic 1.731521
K-10
Sum of Functions RegressionDate/Time 03-20-1992 16:11:05Data Base Name C:\NASA\PRECON2Description Merge of WUC12 and PRECON created 03-19-1992
Estimation Summary Report
Y: MH/MA42 X: LN DRYModel: A+B*(X)+C*(X*X)
Term Coefficient EstimateA -95.16097482423832B 20.31584606137617C -.983565860822489
SourceModelErrorTotal
df Sum-Sqr2 52.3716424 184.280226 236.6519
Std. Error57.2112910.63598.4916664
Mean Square26.185827.6783429.101995
T-Value Prob(ItJ>T)-1.7 0.10931.9 0.0681
-2.0 0.0569
SQR(M.S.5.1172082.7709823.016951
F-Ratio3.4
R-Squared0.22130247
Prob(f>F)0.0497
K-ll
Sum of Functions RegressionDate/Time 03-20-1992 16:11:14Data Base Name C:\NASA\PRECON2Description Merge of WUC12 and PRECON created 03-19-1992
Residual Analysis
Row123456789101112131415161718192021222324252627282930313233343536
ActualX9.1720159.227099109.9.9.1110101010101010109.1010109.9.1011111111
.1487178650482801943766.93356.76806.08581.6697.69967.69967.25924.26472.29766154722.57227.19496.21921578242578242.04542.11394.18428.21131.48278
9.9734811101211121010
.85568
.35358
.67634
.0315
.39095
.53204
.378548.80582512.1442
ActualY
.8..
8.7.6.76.9.7.1410139..
9178.7..
56.119.7.7..
5.134...
7.6.
6
353
744.6.7.13
.532
9.1685
3.27
51
Predicted Lower95%Y Value8.432947 2.1181088.555184 2.3042719.9.9.9.7.9.9.9.9.9.9.9.9.8.9.9.9.9.9.9.9.9.8.8.9.7.9.4.9.5.9.9.7.6.
714996458464500953601545209922555716688965631414610364610364741886742595745605393341687634729173734923194108194108668145138396024733978465434091623115449983745828320797259225559242705401743942468602500862
3.3.3.3.1.3.3.3.3.3.3.3.3.2.3.3.3.3.3.3.3.3.3.2.3.1.3.-23.*" •
3.3.
837769547251598363715425198005653239811125732719710418710418862651863181865008057032793509851511856787211594211594789035229833115607069075515919739674466471862843.4646393513537975169813326859775
.5409592
.3732426
Upper95%Value14.7477914.806115151515131515151515151515141515151515151514141415131511151115151412
.59222
.36968
.40354
.48767
.22184
.45819
.5668
.53011
.51031
.51031
.62112
.62201
.6262
.72965
.58176
.60683
.61306
.17662
.17662
.54726
.04696
.93386
.88786
.35226
.50656
.43349
.62881
.10623
.1671
.916
.59747
.62811
.39624
.62848
Residual
,-.8584635,
-1.301545.2900778-3.255715-2.688964-2.931413-.2103646-2.2103644.858114.95740553.354396.9066593
*
-.72917237.765077-.8941078-1.994108,
-4.138396-2.1247322.1215351.16591-1.823115. 5002E-01
m
.97920363.940775-.8592423
9
g
.3140E-01-.4008624
K-12
Multiple RegressionDate/Time 06-08-1992 12:05:32Data Base Name C:\NASA\PRECON2Description Merge of WUC1.2 and PRECON created 03-19-1992
Multiple Regression Report
Dependent Variable:IndependentVariableInterceptLN DRYLN LENTH
WGT/LENSQRLGDRY
SQRLGLEN
MH/MA44ParameterEstimate2300.043474.1092-452.2954
-.1462855-2769.85
1788.391
Stndized StandardEstimate Error0.0000 900.3793
231.8082 165.1477%-125.2645
148.6725-11.0183 .5235E-01%-206.6015
966.0448109.4917 593.9519
value= 0)2.552.87
-3.04-2.79
-2.873.01
Prob.Level0.01850.0091
0.00620.0109
0.00920.0067
Seq.R-Sqr
0.0274
0.05880.0979
0.09830.3702
SimpleR-Sqr
0.0274
0.04180.0312
0.02530.0393
Analysis of Variance Report
Dependent Variable: MH/MA44
Source df Sums of Squares(Sequential)
Constant 1 630.75Model 5 38.57628Error 21 65.62372Total 26 104.2
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
630.757.7152573.1249394.007692
1.767754.833334.3657413
0.37020.2203
F-Ratio Prob. Level
2.47 0.066
K-13
Multiple RegressionDate/Time 06-08-1992 12:05:53Data Base Name C: \NfASA\PRECO.\'2Description Merge of WUC12 and PRECON created 03-19-1992
Row
123456789101112131415161718192021222324252627282930313233343536
Durbin
ActualYt
.
.4.7.
3.54.582.86.810.344.64.35.36.5
t
4.79.82.43.3•
3.84.95 . 55.14. 14.4.
3 .32.43.3
,
5.42.8- Watson
PredictValue4.4761424.2799735.1616384.3674974.3897143.6530585.0351936.9205124.8122596.6819516.7876646.7876645. 1065885.0992645.4466584.5054466.4760195.3922335.4749974.1343344.1503094.922563.3767574.4480464.6672455.1861513.4811115.1796414.215461.8614274.1576762.8497575.787185.9288246.1064574.827341
Statistic :
Residual Analysis
of Pred1.0335741.061601.4341575.7106825.749886.8042564.9830074.7419165.4654595.6717756.7033455.7033455.7295298.7355821.6352148.8628373.6235349.4540576.469175.7652015.6651328.6141115.8575392.656988.6337518.6777176.8803259.9178398.7478251.275647.71845621.251661.5418295.53776281.5192211.041613
458488
Lower 9 5%Mean2.3269842.0725384.2588752.8897432.8304421.9807312.9911825.3778123.8444085.2850975.3251665.3251663.5896443.5697354.1258272.7113095. 1794754.4480914;499422.5432162.7672693.645611.5936373.0819423.3494563.7769421.650613.2711352.660474-.79108232.663758.24712284.6605294.810632.9474732.661469
Upper 9 5%Mean6.62536.4874086.0644025.8452525.9489865.3253847.0792058.4632135.780118.0788048.2501618.2501616.6235326.6287936.7674896.2995837.7725646.3363756.4505735.7254525.533356.199515.1598775.8141515.9850346.595365.3116127.0881465.7704474.5139375.6515945.4523926.913837.0470199.2654416.993213
Residual
.t
t
.3325024(
-.1530578-.53519341.079488-2.012259. 11804963.512337-2.787664-.506588-.7992635-. 14665791.994554(
-.69223314.325004-1.734334-.8503091•
.4232426
.4519539
.8327551-.862E-01.6188891-.7796407,
1.438573-1.757676.4502428•
•
-.7064567-2.027341
K-14
. Multiple Regression—Date/Time 03-18-1992 20:48:06Data Base Name C:\NCSS\FILES\preconDescription Backup of PRECON created 03-18-1992
Multiple Regression Report
Dependent Variable: MH/MA45Independent Parameter StndizedVariable Estimate EstimateIntercept 0LN DRYLDRY SQD
2.412351 3.4617-.1630653 -2.5469
Standard t-valueError (b=0)
.4730937
.04346585.10-3.75
Prob.Level
0.00000.0009
Seq.R-Sqr
0.85570.9077
SimpleR-Sqr
0.85570.8116
Analysis of Variance Report
Dependent Variable: MH/MA45
Source df Sums of Squares(Sequential)
ConstantModelErrorTotal
02
2527
01365.137138.8831504.02
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
682.56855.55532155.70445
2.3569737.022222.3356449
0.90770.9040
F-Ratio Prob. Level
122.87 0.000
K-15
Multiple Regression—Date/Time 03-18-1992 20:48:06Data Base Name C:\NCSS\FILES\preconDescription Backup of PRECON created 03-18-1992
Residual Analysis
Row
123456789101112131415161718192021222324252627282930313233343536
Durbin
ActualY^.f
9.1t
9.84.668.38.28.67.18.78.311.99.5•
8.913.24.54•
5.45.896.24.55
f
4.94.15.7•
.5.92.4- Watson
PredictedValue8.4081128.3757297.6871177.9907987.9581687.8642065.5658367.0687477.7429297.1753027.1431557.1431557.5859347.5808237.5498248.4180767.2777367.6452787.6230488.146038.146037.7780876.6689536.5828856.5493646.1996377.8393825.6800657.4964124.3768776.7677774.8549767.3191527.4722548.5982425.246937
Std Errof Pred.7703225.7559537.5271578.6106086.6002989.5723715.7595165.4573211.5403237.4587896.4578761.4578761.5059632.5049864.4992655.7748201.4644312.5179666.5133272.6638971.6638971.5491371.4888824.5022931.5080413.5824589.5654381.7250962.49022121.14514.4761021.986229.4678913.4864747.8634986.8591117
Statistic 1.444019
Lower 95%Mean6.8217256.8189346.6014996.7333236.7219256.6854764.0017036.1269496.6301986.230486.2002146.2002146.5439636.5408656.5216476 8224276.3212966.5785886.5659126.7788136.7788136.6472055.6621595.5484735.5031155.0001336.6749314.1868176.4868612.0185995.7873032.8239566.3555876.4704196.8199713.477701
Upper95%Mean9.9944979.9325248.7727369.2482729.1944119.0429367.1299698.0105448.855668.1201238.0860958.0860958.6279048.6207828. -57800110.013728.2341768.7119688.6801839.5132469.5132468.9089687.6757487.6172977.5956147.3991419.0038347.1733138.5059636.7351557.7482526.8859958.2827188.47409110.376517.016174
Residual
.•
1.109203•
1.935794-.9658361-1.068747.55707121.0246981.456846-.432E-011.114066.71917734.3501761.081924•
1.2547225. 576952-3.64603-4.14603
*
-1.268953-.78288512.450636. 3629E-03-3.339382-.6800647
^
.5231233-2.667778.8450241
*
•
-2.698242-2.846937
K-16
Resiauai --lot
Multiple Regression-Date/Time 04-02-1992 16i:29:08Data Base Name A:WUC14Description Backup of WUC14 created 03-27-1992
Multiple Regression Report
Dependent VariableIndependentVariableInterceptACTUATORCONT SURWETAREADRY WOTLOG WG14SQR ACT
: MH/MA14ParameterEstimate26.23825-1.106748-1.66585-.328E-02.6018E-03-6.28269214.28908
StndizedEstimate0.0000-8.9169-6.7252-9.741217.3149-1.54988.4616
StandardError16.15215.5413623.6519315.1091E-02.2159E-033.4293736.916294
t-value(b=0)
1,-2,-2-32
-1,
620456017983
2.07
Prob.Level0.13260.06560.02670.01190.01770.09410.0632
Seq.R-Sqr
0.09250.21500.255545894688
0,0,0.6173
SimpleR-Sqr
0.09250.21210.21390.18550.25220.1272
Analysis of Variance Report
Dependent Variable: MH/MA14
Source df Sums of Squares(Sequential)
Constant 1 1278.494Model 6 91.62071Error 11 56.7954Total 17 148.4161
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
1278.49415.270125.1632188.730359
2.2722728.427778.2696169
0.61730.4086
F-Ratio Prob. Level
2.96 0.057
K-17
Multiple Regression-Date/Time 04-02-1992 16:29:30Data Base Name A:WUC14Description Backup of WUC14 created 03-27-1992
Residual Analysis
Row
12345678910111213141516171819202122232425262728293031323334
Durbin
ActualY...
10.6.
65.769.79.99.39.611.39.811.911.4
*
10.915.17.35.8,
6.67.39.46.37.76.5,
6.33.96.1.
•
- Watson
PredictedValue...10.92807•
7.7142343.419895.....
8.604839.62538810.2037212.11051•
9.62702711.574128.7157748.673118
t
6.1286969.07150710.258264.962518.•.
6.7099266.5405986.831707•
•
Std Errof Pred•
•
•
1.527894•
.9371691.746283•.....9662351.0130471.0631921.982511•
1.3312171.2638721.002661.009739.
1.2229411.2369831.4748211.105857...
2.2635691.0021212.216654.•
Lower95%Mean•
•
,
7.568065•
5.653299-.420368•
*
•
•
•
6.4799767.3975897.8656467.750756•
6.6995388.7947296.5108186.452595•
3.4393186.3512497.0149712.53062
• -
•
•
1.7320964.3368261.957047•
•
Upper95%Mean•
t
•
14.28807*
9.7751687.260158•
•
•
•
•
10.7296811.8531912.5417916.47026•
12.5545214.3535110.9207310.89364•
8.81807511.7917613.501557.394416
*
,
%
11.687768.74437111.70637•
•
Residual
t
§
.-.3280668
t
-1.7142342.280105•
•
•
•
•
2.69517.1746121.69628-.7105103•
1.2729733.525882-1.415773-2.873117•
.4713035-1.771506-.85825921.337482•
,
•
-.4099255-2.640598-.7317071.
•
Statistic 1.432175
K-18
Huitipie Regression--1.4 : LA : 45Date/rime U4-O5-1992
Data Base Name B:AVIONICSDescription Backup of AVIONICS createa O3-27-1992
Multiple Repression Report
Dependent VariableI ndepenaentVariableInterceptDIP SUBSSQR T3UBWGT51/723QR51/72LOG5172
: MH/MAParameterEstimate131.39541.039403-9.035161-.154E-012.864137-26.19323
itndizedEstimate0.00002.3979-2.6722-10.994518.6286-7.6260
Error45.66148.26467632.627782-4954E-02-95541259.767553
value=0 )2.883.93-3.44-3.113.OO-2.68
Prob.Level0.01500 . 00240.00550 . 00990 . 01210.0213
Seq.R-Sqr
0 . 21560 . 30660 . 30660.4O870 . 6425
SimpleR-Sqr
0 . 21560.09180.0000O.OO790.0289
Analysis of Variance Report
Dependent Variable: hH/MA
Source df 3ums of Squares Mean Square(Sequential)
Constant 1 1107.285Model 5 84.03074Error 11 46.76455Total 16 130.7953
F-Ratio Prob. Level
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdiusted R Squared
1107.28516.8O6154-.2513238.174706
2.0618748.070588.25548
0.64250.4799
3.95 0.027
K-19
Multiple rtearession•14:1-4:45uate/Time O4-O5-1992
Data Base Name B:AVIONICSDescription Backup of AVIONICS created 03-27-1992
Residual Analysis
Row
1234567a91011121314151617181920212223242526272329303132333435
Ourbi
ActualY..
-,
7.3.
7.86.810.25.713.81311.23. 79
3.88.2
„
12.613.64.74.9
m
3.79.611811.8-7
„855.3.
„
4 . 6n - Watson
PredictedValue.
-.
8.218O63.
6.69O7496.7421
„
m
„
._
„
11.1196,
8.739O8„
10.0327710.133886.3776O36.377603..11.776419.236857.10.979O57.258468,7.6897097.2882745.474031..
3.O66015
3td Errof Pred.-.1.581274•
.92692022.056123
»......8945798.
1.94O782..7545902.7599139.8949887.8949887..1.044804.7690271.1.1040181.111545.
1.0303311.O848991.464335..1.443832
Lower95?>Mean„
-_
4.740672„
4.6523522.220465_
m
^
«
„
M
9.152324w
4.471093„
8.3733448.4627444.4O94274.409427.
•
9.4787727.545684
m
8.5511944.814O61
„
5.42394.9O24662.253802,
B
-.1091256
Upper 955Mean„
.
m
11.69545„
8.72914611.26373
^
„
„
M
-
^
13.08688w
13.00707-
11.6921911.805018.3457798.345779•
„
14.O74O410.92803
„
13.40699.7O2875
—
9.9555199.6740828.694262
m
—
6.241155
Residual
-.9180632m
1.109251.579OE-O1...m
[4
m
-2.1196.
- . 539O8O6—
2.5672323.466125-1.677603-1.477602•
.
-2.1764071.763144
„
.8209524-.2584677
„
. 3102908-2.288274-.174O313
m
„
1.533985Statistic 1.204315
K-20
Multiple RegressionDate/T.ime 03-20-1992 15:55:14Data Base Name C:\NASA\PRECON2Description Merge of WUC12 and PRECON created 03-19-1992
Multiple Regression Report
Dependent Variable: MH/MA41Independent Parameter Stndized Standard t-value Prob.Variable Estimate Estimate Error (b=0) LevelIntercept 0LN DRY .6886774 0.9419 .4914E-01 14.01 0.0000
Seq.R-Sqr
SimpleR-Sqr
0.8871 0.8871
Analysis of Variance Report
Dependent Variable: MH/MA41
Source
ConstantModelErrorTotal
df
01
2526
Sums of Squares(Sequential)01409.219179.37091588.59
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
1409.2197.17483461.09961
2.6785887.442308.3599137
0.88710.8871
F-Ratio Prob. Level
196.41 0.000
K-21
Multiple RegressionDate/Time 03-20-1992 15:55:28Data Base Name C:\NASA\PRECON2Description Merge of WUC12 and PRECON created 03-19-1992
Row
123456789101112131415161718192021222324252627282930313233343536
Durbin
ActualY,•.
6.7.
4.56.75.610.46.71111.68.711.19.56.5•
9.313.35.25.1
t
6.16.7
*
7.27.35.4,
6.35.26.2,
,
7.43.8- Watson
PredictValue6.316566.3544966.9891856.7397456.7683296.8480478.2183747.4157236.9458697.3479827.3686187.3686187.0653057.0690837.0917646.3046517.2808817.0210417.037746.596326.596326.9180557.653927.7023637.7209747.9079296.8685118.1647387.1302748.7299067.5971438.5333657.2531817.1474676.0643748.363435
Statistic :
Residual Analysis
of Fred.4507101.4534169.4987044.4809059.4829455.4886337.5864117.5291395.4956136.5243059.5257784.5257784.5041359.5044054.5060238.4498603.519518.5009774.502169.470672.470672.493629.5461357.5495923.5509203.5642602.4900939.5825845.5087717.6229114.5420845.6088874.5175415.5099984.4327157.5967622
144088
Lower95%Mean5.3883775.4207385.9621635.7493775.7737615.8417657.010736.3260245.9252126.2682376.2858416.2858416.0270986.0303216.0496695.3782186.2109965.9893386.0035845.6270285r.6270285.9014856.5292196.5705446.586426.7459035.8592226.9649756.0825217.4470956.4807857.2794356.1873676.0971875.1732487.134475
Upper95%Mean7.2447437.2882538.0162077.7301137.7628977.854339.4260198.5054227.9665268.4277268.4513958.4513958.1035128.1078448.1338597.2310848.3507658.0527448.0718977.5656127.5656127.9346248.7786218.8341828.8555289.0699557.8778019.36458.17802810.012728.7135019.7872958.3189958.1977476.9554999.592395
Residual
•
t
•
-.397E-01•
-2.348047-1.518374-1.8157233.454131-.64798163.6313824.2313821.6346954.0309182.408237.1953492•
2.2789596.26226-1.39632-1.49632•
-1.55392-1.002363•
-.7079291.431489-2.764738•
-2.429906-2.397143-2.333365•
•
1.335627-4.563435
K-22
Sum of Functions RegressionDate/Time 03-20-1992 16:45:57Data Base Name C:\NASA\PRECON2Description Merge of WUC12 and PRECON created 03-19-1992
Estimation Summary Report
Y: MH/MA47 X: DRY_WGTModel: A+B*(LOG(X))+C*(SQR(X))
Term Coefficient EstimateA 5.743205009617056B 1.852806289238006D-02C -3.36575286114062D-03
Std. Error10.811721.2160179.676912E-03
T-Value0.50.0-0.3
Prob(
SourceModelErrorTotal
df2
2426
Sum-Sqr4.08758660.1190864.20667
Mean Square2.0437932.5049622.469487
SQR(M.S.1.4296131.5827071.57146
0.60020.98800.7310
F-Ratio0.8
R-Squared0.06366295
Prob(f>F)0.4541
K-23
Sum of Functions RegressionDate/Time 03-20-1992 16:46:06Data Base Name C:\NASA\PRECON2Description Merge of WUC12 and PRECON created 03-19-1992
Residual Analysis
Row123456789101112131415161718192021222324252627282930313233343536
ActualX96241016925558177921854620822152293474802400043032443414434128545287022966394593903726768274251444714447230506710071990739629703021450140882313693200836179024061337498321626673188000
ActualY
5
35235654587
4742
657454
443
62
.
.5
.
.8
.1
.4
.2
.2
.4
.7
.9
.7
.3,.8.3.3.9.
.7
.6
.4
.6
.8
.
.8
.6
.8
.
.
.8
.6
Predicted Lower95%Y Value5.582958 1.9953985.574758 2.0163225.5.5.5.4.5.5.5.5.5.5.5.5.5.5.5.5.5.5.5.5.5.5.4.5.4.5.4.5.4.5.5.5.4.
39316247558446693944177265083520932240865524269723271223271236463636317635431958548274093814337516251612251612241833107727204736503558907539435052699558338918073869110952321806286585331893631417508858
2.2.2.2.1.1.2.1.1.1.2.2.2.1.1.2.2.2.2.2.1.1.1.1.2.1.1.
04284209688109428208178522206583658805687875322863689863689014288012752003306988315912002031468025169093327093327064947689793658048645656513019077402283092986443
.8264E-011.726151.68052121.1.1.1.
926579978597792076019374
Upper95%Value9.1705179.1331938.8.8.8.8.8.8.8.8.8.8.8.8.9.8.8.8.8.8.8.8.8.8.8.8.8.8.8.8.7.8.8.9.7.
743483854286839595801758079604582056760441610072601735601735714984713670533118264563617973139172515593891793891777171546474943668242550430205879270311602369139406510249575296309646591685188470758998342
Residual
,
-,-
,2442E-01,
1.64177144916532.809322-2.208655
—1,-.31
—1
—-
,,2
—B,
.
—-
1-
.427E-01
.16728846728751.3646365368242.345681.71452.
.5814293
.9248381.2161222.6161224
92272876526353.56442.507538616494771004426.
7261315.5109522.5218055t
,
.1685831.908858
K-24
Mul tide RegressionOats/Time 04-06-1992 12:01:53(fata 6'ase Name C:\NASA\WUC96Description rtsrge of WUC47 and WUC12 r^reatea 02-11-1992
Multiple Regression Report
Dependent Variable: MHMA4996Independent Parametervariable EstimateIntercept 9.513174LEN WING .3508E-01WGT49/96 -.721E-03SQR CREW -4.520094
tndizedstimate01
— \_-0
.0000
.7971
.1406
.9904
Standard t-valueError (b=0)1.68657-1022E-01-2665E-031.519629
53-2-2
.64
.43
.70
.97
Prob.Level000o
.0000
.0037
.0163
.0095
Seq.R-Sqr
000
.0031
.2029
.4986
SimpleR-Sqr
000
.0031
. 0600
.1043
Analysis of Variance Report
Dependent Variable: MHMA4996
Source df Sums of Squares Mean Square(Sequential)
Constant 1 773.1284Model 3 49.7196Error 15 49.99197Total 18 99.71158
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
773.123416.57323.3327985.539532
1.8255956.378947.2861907
0.49860.3984
F-Ratio Prob. Level
4.97 0.014
K-25
MultiDle RegressionD a t e / T i m s 04-06-1992 12:02:07Data Sase Name C:\NASA\WUC96Description Mercie of WUC47 and WUC12 created 02-11-1992
Residual Analysis
Row
1
34567891011121314151617181920212223242526272329303132333435
Durbin
ActualY
8.5
7.67.63.613.85.310.55.754.9
6.4,
7.213.27.74
B
47. 16.63.44. 13.7.
6.45.74.3
„
.
4.5- Watson
PredictedValue
7.669556
8.6436373.664033
3td Errof Pred
.6735326
.77303321.549436
Lower95%Mean
6.234453
6.9965275.362634
Upper95%Mean
9.104659
10.2907511.96543
Residual
8304439
-1.043637-1.064033
5.8436695.8436696.0085497.366797
8.4357598.4350387.577325.767948
5.0312775.0312775.0874073.1774093.3830246.748656
6.771239
6.378088
.5503315
.5503315
.5307801
.6628822
.7450752
.7449992
.667131
.604834
.5793074
.5793074
.57312911.1431381.089339.7755465
1.310955
.8124059
4.6710734-.6710734.877615.954387
6.8482196.847666^1558574. -479221
377969413:7969413.866234.74171191.0619585.096191
3.977974
4.647086
7.0162667.0162667. 1394888.779207
10.023310.022428.9987837.056674
6.2656146.2656146.3085795.6131055.7040898.401121
9.564504
3.10909
-.8436694-.9436693
-.9667969
-1.2357594.764962. 1226802-1.767948
-1.0312772.0687231.512593.2225916.71697641.951344
-.3712387
-2.078087
5.344202Statistic 1
.6632126490154
3.931088 6.757316 -.8442016
K-26
Residual P-urn or Functions Neoression-1.5:05: OSOate/ Time O4-2O-1992
Data Base Name B:WUC97Description Backup of WUC97 created 03-13-1992
Estimation Summary Report
Y: MHMA9137 X: DRY...WGTModel : A+B*(X )+C*(LOG(X ) )+D*(SQR(X ) )
Term Coefficient EstimateA -57.90084944513313 1. 4638806 795145O9D-04C 8.2373209437452080 -.1514356975659418
Std. Error20.626654.060194E-052.6343794.433468E-O2
T-Vaiue Prob(!t|>T )-2.8 0.01093.6 0.00183.1 O.O053
-3.4 0.0027
R-Squared0.41108948
SourceMode 1ErrorTotal
df Sum-Sqr3 18.6634620 26.7365423 '45.4
Mean Square6.2211541.3368271.973913
3QRCM.S. )2.4942241.1562121.4O496
F-Ratio4.7
Prob(f0.0126
K-27
Sum of Functions Regression-Date/Time 04-20-1992 13:05:06Data Base Name 6:WUC97Oescriotion GacKup of WUC97 created 03-13-1992
Residual Analysis
ROW
1
3456789101112131415161718192021222324252627282930313233343536
ActualX962410169255581779218546208221522934748024OOO43O324434144341285452S702296639459390372676827425144471444723050671007199073962970302145014O882313693200836179024061337498321626673188000
ActualY
6
5442354
654
55
554154
835
32
—
.4„
.8
.4
.7
.9
.1
.1m
.8
.7
—
.2
.2m
m
m
.6
.5
.7
.7
.3
.5,
.6
„
„
.3
.3
PredictedY4.204684.3233515555345444555445544544435357455533
.228855
.118762
.147458
.205316
.596225
.751958
.232194
.874202
.838446
.838446
.20O963
.198863
.184861
.165978
.980506
.220557
.214257
.911157
.911157
.229442
.243475
.134512
.O93051
.718819
.214932
.541364
.155697
.698452
.371178
.107493
.O19613
.140531
.241859
.994804
Lower95SValue1.479104I. 6318932222
.
,
.
„
7148O2587104619209683981
.963184122222222122222211112
„
»
„
.
•
._
„
.
.
.
.
•
.
.
.
.
.
.
.
254687162363755634O3663403666901316881946751774287684794117078570225435027435027471216733176616941572236153953694923
.9148228241222
.
.
.
.
.
.
647732475865867238418397517318633351
.16361221.35635
Upper95%Value6.9302567.014809T
77767777777767777776666767
.742908
.650419
.675707
.726651
.229265
.249236
.74815
.372845
.336525
.336525
.711795
.709533
.694546
.903187
.481602
.733264
.72626
.47204
.47204
.746725
.753775
.652083
.613867
.283685
.734942
.167904
.66366210.92104677766
.875117
.796589
.521908
.64771
.320105
.633258
Residual
.1.281238.
-.20531581.203776-.3519578-2.532193-.9742023.2615545-.7384455.
1.601137.5151388-.1659774.
- . 206E-0.1-.143E-01....
1.3565251.365488. 6O69483-2.018819.8507E-01. 9586363.. 30154855-.7711777-.107493...5814E-01-1.694804
K-28
APPENDIX L
POFF Regression Analysis
Date/Time 02-06-1992•-Descriptive Statistics-IBM?: 28
Data Base Name C:\NASA\WUC11Description Backup of NASAMSTR created 12-18-1991
Detail Report
Variable: %OFF EQUMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Testfbl 1.00 Skew-Z
8.916666E-02.068566.10976735.475333E-024.879119E-022.38058E-03.54719091.0646711.1786170.113522.18 Pr 0.0291
No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=0T prob levelKurtosisReject if > 1.182(10%)Reject if > 0.162(10%)b2. 4.33 Kurt-Z
D'Agostino-Pearson Omnibus K} Normality Test100-%tile75-%tile50-%tile25-%tile0-%tile
r\ -I n __
1 1
( Maximum )
(Median )
( Minimum )
12 1111 1
.235
.1245
.0835
.052
.013
1 2 1
90-%tile10-%tileRange75th-25th %tileC.L. Median(95%;
Line Plot / Box Plot11 1 2 2 11
3511242.149.959459E-038.9529630.00001.9510671.289(5%)0.178(5%)
1.78 Pr 0.07517.9 Pr-0.0189
.14
.042
.222
.0725.053, .124
2351
Distribution & Histogram
Variable: %OFFBin Lower1 .0132 3.318E-023 5.336E-024 7.354E-025 9.372E-026 .11390917 .13409098 .15427279 .174454510 ,194636411 .2148182
EQUUpper3.318E-025.336E-027.354E-029.372E-02.1139091.1340909.1542727.1744545.1946364.2148182.235
Count16433330001
Prcnt4.2
25.016.712.512.512.512.50.00.00.04.2
Total-17
111417202323232324
Prcnt4.229.245.858.370.883.395.895.895.895.8100.0
Histogram* ' . • - ' •******-***** t * ;*********
j
*
L-l
Date/TimeData Base NameDescription
Descriptive Statistics02-06-1992 17:03:16C:\NASA\WUC12Data base created at 16:18:28 on 12-19-1991
Detail Report
Variable: %OFF EQPMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality TestA>1 1.31 Skew-Z
.12876928.176091E-02. 1757775.3386806. 11639251.354722E-02.90388481.392012.0534020.217902.79 Pr 0.0052
No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=0T prob levelKurtosisReject if > 1.169(10%)Reject if > 0.156(10%)
359263.3482.282646E-025.6412270.00001.1751611.265(5%)0.171(5%)
D'Agostino-Pearson Omnibus K/ Normality Testb2 3.74 Kurt-Z
9.6100-%tile (Maximum) .43875-%tile .17850-%tile (Median) .08825-%tile .0490-%tile (Minimum) .002
90-%tile10-%tileRange75th-25th %tileC.L. Median(95%)
1.33 Pr 0.1835Pr- 0.0083.298.037.436
.05,. 129
. 16.002 Line Plot / Box Plot .4381 1 12212 11 11111 1 1 11- 111 1 1
Variable: %OFFBin Lower1 .0022 4.163E-023 8.127E-024 .12090915 .16054556 .20018187 .23981828 .27945459 .319090910 .358727311 .3983636
Distribution & Histogram
EQPUpper Count I4.163E-028.127E-02.1209091.1605455.2001818.2398182.2794545.3190909.3587273.3983636.438
39.5-220 •120 .11
^rcnt Total11.534.619.27.77.70.03.87.70.03.83.8
312171921212224242526
Prcnt Histogram.* 11.5; 46.2
- 65.4- 73.180.880.884.692.392.3
- 96.2100.0
*********************
***
**
Lr2
Multiple RegressionDate/Time 04-16-1992 12:01:35Data Base Name C:\NASA\WUC13Description Backup of IMASAMSTR created 12-20-1991
Multiple Regression Report
Dependent Variable: %OFF EQPIndependent ParameterVariable EstimateIntercept .2774E-O1DRY WGT -.407E-05LEN WING -.194E-02SQRWHEEL5QRW13
.1931569
.7156E-02
tndizedstimate0.0000-2.5518-1.85141..37712.5413
StandardError.1396931. 1497E-05.6558E-03.8535E-01.3463E-02
t-valuefb=0)
0.20-2.72-2.962.262.07
Prob.Level0.84530.01590.00970.03890.0565
Sep.R-Sqr
0.22630.32590 . 56790.6636
SimpleR-Sqr
0.22630.30370.10790.1937
Analysi:
Dependent Variable: %OFF EQP
of Variance Report
Source df Sums of Squares(Sequential)
Constant 1 2.203816Model 4 .1751109Error 15 8.875405E-02Total 19 .263865
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
2.2038164.377772E-025.916937E-031.388763E-02
7.692163E-02.33195.2317265
0.66360.5739
F-Ratio
7.40
Prob. Level
0.002
L-3
oate/TimeData Base NameDescription
04-27-1992C:\NASA\WUC23Merae of WUC11 and
cf Functions Regression-42: 16
created 04-27-1992
Estimation Summary Report
Y: %OFF EQP X: ENG WGTModel: A+B*(X)+C*(SQR(X))
Term Coefficient EstimateA 1.146330127496948B 4.572100568624601D-05C -1.145581687278943D-O2
SourceModelErrorTotal
df Sum-Sqr2 .151861113 .201946615 .3538078
Std. Error.19059651.54087E-053.70415E-03
T-Value Prob(!t|>T)6.0 0.00003.0 0.0109
-3.1 0.0086
Mean Square7.593055E-021.553436E-022.358718E-02
3QR(M.S..275555.1246369.1535812
F-Ratio4.9
R-Sauared0.42921925
Prob(fO.0261
Date/Time 04-16-1992Data Base Name A:WUC24
Multiple Regression-12:38:01
Description Backup of WUC: :reated 03-13-1992
Multiple Regression Report
Dependent Variable:IndependentVariableInterceptLN DRYWTKVA MAXSQR KVA
LOG KVAWGT24SQR WT24
%OFF EQPParameterEstimate-109.8302-.1645163.1426994-6.151774
15.75077.6602E-01-5.683191
LOG WT24 29.07148
Estimate0.0000-1.0364 .80.9389 .%-159.2671
178.4592 3113.1754 .?i-247.6460
1133.8745 6
Standard t-valueError (b=0)4.7688 -4.434566E-01 -3.602812E-01 5.07
.26376
.3776481467E-01
..273395
.480136
-4.874.66
-4.464.49
Prob.Level0.04730.06910.0367
0.03970.04300.0460
0.04670.0463
3eq.R-Sqr
0.14030.4907
0.51060.51250.9286
0.94390.9949
SimpleR-Sqr
0.14030.3695
0.37290.36740.0362
0.02000.0089
Analysis of Variance Report
Dependent Variable: %OFF EQP '. '.
Source
ConstantModelErrorTotal
df Sums of Squares Mean Square(Sequential)
1 .26146897 .154171
F-Ratio Prob. Level
2 7.851048E-049 .1549561
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
.26146892.202443E-023.925524E-041.721735E-02
56.11 0.018
1.981294E-02.1617.122529
0.99490.9772
L-5
Multiple RegressionDate/Time 04-16-1992 13:06:22Data Base Name C:\NASA\WUC42Description Merge of WUC41 and WUC13 created 12-27-1991
Multiple Regression Report
Dependent VariableIndependentVariableInterceptKVA MAXWGT42SQR WT42LOG WT42
%OFF EQPParameterEstimate-26.56543--271E-02.5143E-02-.74877886.621144
StndizedEstimate0
-236-6430
.0000
.1024
.0501
.7482
.6361
Standard t-valueError (b=0)5.705455. 1020E-02.8676E-03.13497851.325087
-4-25
-55
.66
.66
.93
.5S
.00
Prob.Level0.0.0.0.0.
00160288000400050011
Seq.R-Sqr
0.0.0.0.
1454203642318600
SimpleR-Sqr
0000
.1454
.1952
.2289
.2395
Analysis
Dependent Variable: %OFF EQP
of- Variance Report
Source
ConstantModelErrorTotal
df- Sums of Squares(Sequential)
1 1.0553554 .24945588 4.060512E-0212 .2900609
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
1.0553556.236395E-025.07564E-032.417175E-02
7.124353E-02.2849231.2500448
0.86000.7900
F-Ratio
12.29
Prob. Level
0.002
Residual Plot
• Multiple Regress ion-Date/Time 04-16-1992 13:10:12Data Base Name A:WUC44Description Backup of WUC44 created 03-13-1992
Multiple Regression Report
Dependent Variable: %OFF EQPIndependentVariableInterceptDRY_WGTWETAREALN DRYWTSQR WING
ParameterEstimate3.061047.1178E-04-.127E-03-.4239174.1346839
StndizedEstimate0.00007.3057-8.7046-3.52604.4295
StandardError.6213115.3256E-05.3581E-04.0959754.3769E-01
t-value(b=0)
4.933.62
-3.56-4.423.57
Prob.Level0.00010.00200.00230.00030.0022
Seq.R-Sqr
0.11000.14600.33590.6115
SimpleR-Sqr
0.11000.12410.26550.1742
Analysis of Variance Report
Dependent Variable: %OFF EQP
Source df Sums of Squares Mean Square(Sequential)
Constant 1 .6311348Model 4 .1681584Error 18 .1068569Total 22 .2750152
F-Ratio Prob. Level
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
.63113484.203959E-025.936492E-031.250069E-02
7.704864E-02.1656522.465123
0.61150.5251
7.08 0.001
L-7
Multiple Regression-Date/Time 04-16-1992 13:17:33Data Base Name A:WUC45Description Backup of WUC45 created 03-13-1992
Multiple Regression Report
Dependent Variable: %OFFEQPIndependent Parameter StndizedVariable Estimate EstimateInterceptLEN WING
.7614E-01 0.0000-.1S1E-02 -2.6037
Standard t-value Prob.Error (b=0) Level.0283886 2.68 0.0130.5151E-03 -3.52 0.0018
SQR WGT .1543E-02 2.5598 .4460E-03
Seq.R-Sqr
SimpleR-Sqr
0.0119 0.01193.46 0.0020 0.3406 0.0005
Analysis of Variance Report
Dependent Variable: %OFFEQP
Source df Sums of Squares(Sequential)
Constant 1 .3719467Model 2 4.866481E-02Error 24 9.420949E-02Total 26 .1428743
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
.3719467
.02433243.925395E-035.495166E-03
6.265298E-O2.1173704.5338057
0.34060.2857
F-Ratio Prob. Level
6.20 0.007
Lr8
Residual Plot
Multiple Regression-Date/Time 04-16-1992 12:33:56Data Base Name A:WUC14Description Backup of WUC14 created 03-27-1992
Multiple Regression Report
Dependent Variable: %OFF EQPIndependentVariableInterceptACTUATORWGT14LOG WG14SQR WT14
ParameterEstimate5.512466.2663E-02-.566E-03
StndizedEstimate0 . 00000.8745
-14.4189
StandardError1.372817.llllEr-02.1722E-03
t-value(b=0)
4.022.40-3.29
Prob.Level0.00130.03110.0054
Seq.R-Sqr
0.02930.1397
SimpleR-rSqr
0 .02930.1041
-1.193089 -13.1531..3157466.1055595 25.9373 .3051E-01
-3.78 0.0020 0.3424 0.23223.46 0.0038 0.6455 0.1545
Analysis of Variance Report
Dependent Variable: %OFF EQP
Source df Sums of Squares Mean Square(Sequential)
Constant 1 .2719226Model 4 6.115096E-02Error 14 3.358546E-02Total 18 9.473642E-02
F-Ratio Prob. Level
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
.27192261.528774E-022.398961E-035.263134E-03
4.897919E-02.1196316.4094169
0.64550.5442
6.37 0.004
L-9
CLSOk
Multiple Reqression-11 :34:54Date/Time 04-16-1992
Data Base Name A:AVIONICSDescription Backup of AVIONICS created 03-27-1992
Multiple Regression Reoort
Dependent VariableIndependentVariableInterceptDIP SUBSWGT51/72SQR51/72LOG5172WGT/TSUB
%OFF EQPParameterEstimate7.166202.2090E-01-.128E-02.1773785-1.734067.6700E-02
StndizedEstimate0.1.
-28.35.-15.7.
000045990442200538262109
Standard t-valueError (b=0)1.777114.4766E-02.2910E-03.4246E-01.4300031.1521E-02
44-44-44
.03'
.39
.40
.18
.03
.40
Prob.Level000000
.0030
.0018
.0017
.0024
.0030
.0017
Seq.R-Sqr
00000
.1874
.2205
.2212
.2358
. 7578
SimpleR-Sqr
00000
..1874
.0064
.0000
.0091
.0131
Analysis of Variance Report
Dependent Variable: %OFF EQP
Source df Sums of Squares Mean Square(Sequential)
Constant 1 1.782616Model 5 .1003Error 9 3.204889E-02.Total 14 .1323489
Root Mean Square ErrorMean of 'Dependent VariableCoefficient of Variation
R SauaredAd.justed R Squared
1.7826162.006001E-02-3.560988E-039.453496E-03
F-Ratio
5.63
Prob. Level
0.013
5.967401E-02.3447333.1731019
0.75780.6233
L-10
•Descript ive Stat is t ics-Date /TimeData 03.se NameDescription.
02-10-1992 i UC: \ .N 'ASA\WUC41Merge of WUC42
15:0"
and. WUC11 created 02-05-1992
Detail Report
Variable: %OFF EQPMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAd.i sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test(bl 1.01 Skew-ZD'Agostino-Pearson Omnibus
.09326.419662E-02.1222034.1184947.026557E-024.93725E-03.75392241.079831.1240250.19816
2.24 Pr 0.0249K;
No. observationsNo. missing valuesSum of frequenciesSum of observations
100-%tile75-%tile50-%tile25-%tile0-%tile
0 1 r _ _
1 11131 1
(Maximum)
(Median)
( Minimum)
1 4
.27
.13
.08
.03
.015
12 1
Std.error of meanT-value for mean=0T prob levelKurtosisReject if > 1.176(10%)Reject if > 0.159(10%)b2 3.15 Kurt-Z 0.74
Normality Test 5.690-%tile10-%tileRange75th-25th %tileC.L. Median<95%)
Plot / Box Plot2 1
035
3510252.331.405311E-026.6319820.0000.47104651.276(5%)0.174(5%)Pr 0.4604Pr 0.0615.2.026.2559.999999E-02. 11
1271
234567891011
.1772727
.2004546
.2236364
.2468182
Distribution & Histogram
Variable: %OFFBin Lower1 .015
3.818E-026.136E-028.454E-02.1077273.1309091.1540909
EQPUpper3.818E-026.136E-028.454E-02. 1077273.1309091.1540909.1772727.2004546.2236364.2468182.27
Count81533102011
Prcnt32.04.0
20.012.012.04.00.08.00.04.04.0
Total89141720212123232425
Prcnt32.036.056.068.080.084.084.092.092.096.0100.0
Histogram*********************
**
**
L-ll
Residual Plot
Multiple RegressionDate/Time 04-16-1992 12:59:43Data Base Name C:\NASA\WUC47BDescription Merge of WUC47 and WUC47 created 04-16-1992
Multiple Regression Report
Dependent Variable:IndependentVariableInterceptLEN WINGLN DRYWTLDWGTSQDWGT./LEN
%OFF EQPParameterEstimate Estimate Error23.85198 0.0000 6.959501-.902E-02 -10.1204-5.247019 -50.4282.3009554 62.2695-.212E-02 -2.7734
StandardError.959501.2212E-021.523853.8677E-01.S730E-03
value=0)3.43-4.08-3.443.47-2.42
Prob.Level0.00370.00100.00360.00340.0284
Seq.R-Sqr
0.17480.34740.60960..7196
SimpleR-Sqr
0.17480.05600.06370.0097
Analysis of Variance Report
Dependent Variable: %OFF EQP
Source df Sums of Squares Mean Square(Sequential)
Constant 1 .2930621Model 4 .1118034Error 15 4.357554E-02Total 19 .155379
F-Ratio Prob. Level
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
.29306212.795085E-022.905036E-038.177839E-03
5.389838E-02.12105.4452572
0.71960.6448
9.62 0.000
L-12
Residual PlotMultiple Regression-- -——
Date/Time 04-16-1992 14:07:39Data Base Name C:\NASA\WUC49Description Merge of WUC24 and WUC13 created 02-12-1992
Multiple Regression Report
Dependent Variable: %OFF EQPIndependentVariableInterceptDRY WGTSQR WGTKVA MAX
ParameterEstimate.1988856.4938E-05-.205E-02.4877E-03
StndizedEstimate0.00002.0439-1.77430.3383
StandardError.114326-2131E-05. 1098E-02.4481E-03
t-value(b=0)
1.742.32-1.87L.09
Prob.Level0.09810.03180.07710.2900
Seq.R-Sqr
0.33040.40320.4382
SimpleR-Sqr
0.33040.26060.2504
Analysis of Variance Report
Dependent Variable: %OFF EQP
Source
ConstantModelErrorTotal
df Sums of Squares(Sequential)
1 .09365843 8.434577E-0219 .108127322 .1924731
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
.09365842.811526E-025.690911E-038.748776E-03-
7.543813E-02;.6.381305E-02..1.182174
0.43820.3495
F-Ratio Prob. Level
4.94 0.011
Resiaual •Multiple Regression
Date/Time 04-16-1992 14:11:10Data Base Name C:\NASA\WUC96Description Merge of WUC47 and WUC12 created 02-11-1992
Multiple Regression Report
Dependent VariableIndependentVariableInterceptLEN WINGWETAREAPERSONSSQR PERSQRWT49/
%OFF EQPParameterEstimate-5.46864. 1683579-.448E-02.3652105-4.152794.1779732
StndizedEstimate0.44.-59.56.-59.17'.'
000047558242949562249140
Standard t-valueError (b=0)1.728256.3631Er01.9387E-03.4935E-01.5515564.3293E-01
-34-47-75
.16
.64
.77
.40
.53
.40
Prob.Level000000
.0507
.0189
.0175
.0051
.0049-0124
Seq.R-Sqr
00000
.2583
.2815
.2901
.7208
.9740
SimpleR-Sqr
00000
.2583
.2633
.2636
.2901
.3109
Analysis of Variance Report
Depenaent Variable: %OFF EQP
Source
ConstantModelErrorTotal
df Sums of Squares Mean Square(Sequential)
1538
3.584711.76330672.038224E-02.7836889
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
3.584711.15266136.794081E-03-9.796111E-OZ:
8.242621E-02,.6311111.1306049
0.97400.9306
F-Ratio Prob. Level
22.47 0.014
L-14
Data Base Name C:\NASA\WUC91Description Backup of WUC49 created 02-13-1992
Multiple Regression Report
Dependent Variable: %OFF EQPIndependent Parameter Stndized StandardVariable Estimate Estimate ErrorIntercept 4.653976 0.0000 2.156753LN DRYWT -.4571863 -2.0304 .2379916SQR WGT .2421E-02 1.4973 .1709E-02
valuei=0)2.16
-1.921.42
Prob.Level0.04760.07390.1770
Seq.R-Sqr
0.31400.3950
SimpleR-Sqr
0.31400.2461
Analysis of Variance Report
Dependent Variable: %OFF EQP
Source df Sums of Squares(Sequential)
Constant 1 1.664096Model 2 .3243408Error 15 .4968562Total 17 .821197
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
1.664096.16217043.312375E-024.830571E-02
.1819993
.3040555
.5985725
0.39500.3143
F-Ratio Prob. Level
4.90 0.023
L-15
Descriptive StatisticsDate/Time 02-14-1992 14:38:09Data Ease Xame C:\NASA\WUC93Description Data base created, at lr: 14:42 en 02-13-1992
Detail Reoort
Variable: %OFF EQPMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test
0.44 Skew-Z
.2877375
. 1127736
.4627014
.3085063
.20993414.407232E-02.7296028.54452961.07360. 18167
0.73 Pr 0
No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=0T prob levelKurtosisReject if > 1.548(10%)Reject if > 0.264(10%)
D'Agostino-Pearson Omnibus100-%tile75-%tile50-%tile25-%tile0-%tile
O 1 R A -
1 1 1fY5
( Maximum)
(Median)
( Minimum)
:YYYYYYYYYY5
.644
. 44
.265
. 10075
.0464
1nnnrYYYYXj
4631 b2 1.98Normality Test
90-%tile10-%tileRange75th-25thC.L. Median
Line Plot / Box Plot1 1
8082.30197.422291E-023.8766670.0061-.74861942.421(5%)0.288(5%)
Kurt-Z0.7
tile
-0.41 Pr 0.6818Pr 0.7024.5625.0464.5976.33925
.0464, .644
1 1
Variable: %OFFBin Lower1 .04642 .13177143 .21714294 .30251435 .38788576 .47325727 .5586286
EQPUpper.1317714.2171429.3025143.3878857.4732572.5586286.644
Distribution & Histogram
Count Prcnt Total Prcnt Histogram3020111
37.50.0
25.00.012.512.512.5
3355678
37.37.62.62.75.87.
100.
5555050
**»
**
***
L-16
Descriptive Statistics-Date/Time 02-14-1992 15:16:51Data -2ase Name C:\NASA\WUC97Description Backup of -WUC91- created 02-14-1992
Detail Report
Variable: %OFF EQPMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Testfbl 4.03 Skew-Z
1 .003704E-02-9.861112E-042.106019E-02.020-18922.786589E-027.765078E-042.7763064.268697192.59250.352385.70 Pr 0.0000
Mo. observationsNo. missing valuesSum of frequenciesSum of observationsStcUerror of meanT-value for mean=0T prob levelKurtosisReject if > 1.164(10%)Reject if > 0.153(10%)b2 19.00 Kurt-Z
D'Agostino-Pearson Omnibus K/ Normality Test 55.8100-%tile75-%tile50-%tile25-%tile0-%tile
0D422 11 1
(Maximum) .14 90-%tile.0048 10-%tile
(Median) .0013 Range0 75th-25th %tile
(Minimum) 0 C.L. Median(95%)Line Plot / Box Plot
36927.2715.362793E-031.8716060.072619.667711.254(5%)0.168(5%)
4.83 Pr 0.0000Pr 0.0000.0330.14.0048
0, .0047
1. 14
1
Distribution & Histogram
Variable: %OFFBin1234567891011
Lower01.272E-022.545E-023.818E-025.090E-026.363E-027.636E-028.909E-02. 1018182. 1145455. 1272727
EQPUpper1.272E-022.545E-023.818E-025.090E-026.363E-027.636E-028.909E-02. 1018182. 1145455.1272727.14
Count231110000001
Prcnt85.23.73.73.70.00.00.00.00.00.03.7
Total2324252626262626262627
Prcnt85.288.992.696.396,96,96,96,96,96,
,3,33333
Histogram***********************
**
100.0
APPENDIX M
Removal Rate Data & Regression
REMOVAL RATE
ANALYSIS SUMMARY
! WUC11121314
1234
24 541 6 .
1 42 7
IMEAN I C-5A0.194 0.1160.319 I 0.3980.4420.30403210385
02200.1310.1870.168
0.344 I 02301 44 8 0.716
C-130E0.168022503140247030603130305
C-141B0.177036203440263026903780332
0.767 0.530 0.69645 i 9 ! 0.368 I 0.234 0.257 0.30846 10 0572 ! 0.17847 i 1149 | 125152616263646566
1314151617181920
69 i 21
0.415 I 02370274 I 0.1500.5070.4580299024503680.4560.47203960.455
i 71* i 22: 1 0.44272 ; 23 0.475
0.45303750317027502990.518038203090.0000.3950.455
! 91 - i 24 0.461 I 0.179; 97 I 25 0.555 I 0.192
0.199037503130.4140.4830307032703060.4430.551055702950.411
0.1640.31303890.4450.5140.5390388027503210.44503220.4190.424
0.542 0.4270.1890.707
03920.128
F-15D0207
F-111A0.309
0235 0.0000.663 i 0.6200390 0.4290.521 0.0000345 0.6360.381 0.5390.694 0.8720.593 : 0.515-0.366 i 0.3890.514 0.53503680.5100.3450.0000.0000.4050.0000.3500.0000.000
0.1380.7260.70803300.0000.54603070.4220.0000.652
0.426 0.4330.000 0.0000.658 0.0000.911 0.421
T-38A0.18503770.49003630.0000.4680.2750.7340.3030.3590.51702880.49403220.0000235037502920.6800.0000.0000.5600.0000.8870.968
M-l
REMOVAL RATE
wuc
1112
13 .
, 14
24-
41
42
44
45
46
47
49
51
52-
61
62
63
64
65
66 -
69
71
72
91
97
MEAN
0.194
0319
0442
0304
0321
0385
0344
0.716
0368
0272
0.415
0274
0.507
0458
0299
0245
0366
0456
0.472
0396
0455
0442
0475
0.461
0355
MEDIAN
0.181
0362
0.417
0313
-02875
0.3615
0.3185
0.715
03055
0279
0.4445
03005
04735
0429
0317
0275
0.3405
0.507
0.4335
0322
0419
0425
0455
0392
0364
STDDEV
6.407E-2
.0826818
.1778206
.1107797
.1424603
.1573603
.1084576
.1120169
.1485499
.101439
.1231341
.10/3/73
.1127367
.1445094
.1925806
.1484907
.1003549
9.713E-2
.1230586
.1395815
.1812522
5.959E-2
5.997E-2
.3076337
.3612372
VARIANCE
4.105E-3
6.836E-3
3J62E-2
1227E-2
2J3E-2
2476E-2
1.176E-2
1.255E-2
2207E-2
1.029E-2
1.S66E-2
1.153E-2
1271E-2
2JBBE-2
3.7096-2
.02205-
.01007
9434E-3
1.514E-2.
1.948E-2
328SE-2-
3J51E-3
3.596E-3
9464E-2
.13049
VAR/MEAN II COEFF VARRATIO 9
2.119E-2
2.14E-2
7.1566E-2
4.0391E-2
63Z7E-2
6.4373E-2
3.4228E-2
1.7537E-2
5.991E-2
3.7784E-2
3.77163E-2
42029E-2
2.506BE-2
4.56126E-2
0.1242
8.999BE-2
2.73919E-2
iOB78E-2
32106E-2
4.91995E-2
7.215E-2
8.04246E-3
7.57649E-3
02062895
023533
03308
025887
0.40246
03646
0.44415
0.40908
0.31559
0.1566
0.4033
037248
03014
039141
022236
0315838
0.64495
0.60608
027295
02129
02609.
0.35248
0398
0.13497
0.12634
0.66732
0.66147
M-2
REMOVAL RATE ANALYSIS - WUC 23
REMOVALS MISSIONSACCOMPLISHED
PERCENT
F-4E
F-15C
F-16C
C-5A
C-130E
KC-135
1
8
16
6
12
1
,988
,653
,978
,845
,205
,787
5
16
39
43
36
10
,921
,891
,635
,508
,836
,354
0.3358
0.5123
0.4284
0.1573
0.3313
0.1726
TOTALS 48,456 153,145 0.3164
M-3
Date/TimeData Base NameDescription
Sum of Functions Regression-06-04-1992 15:34:59C:\nasa\WUCllBackup of NASAMSTR created 12-18-1991
Y: REMRAT11Model: A+B*(X)
Estimation Summary Report
X: WGT BODY
Term Coefficient EstimateA .1934133385777032B -6.308858923946157D-07
Source df Sum-SqrModel 1 3.888923E-03Error 3 6.722772E-04Total 4 .0045612
Std. Error8.649185E-031.514432E-07
T-Value Prob(|t!>T)22.4 0.0002-4.2 0.0252
Mean Square3.888923E-032.240924E-04.0011403
SQR(M.S.)6.236123E-021.496972E-023.376833E-02
F-Ratio17.4
R-Squared0.85260957
Prob(f>F)0.0252
°l. I snotionsData Base Name C:\nasa\WUCllDescription Backup of NASAMSTR created 12-18-1991
Estimation Summary Report
Y: REMRAT13 X: LEN_WINGModel: A+B*(SQR(X))
Term Coefficient EstimateA .8639022023186406B -2.962998410898014D-02
Source df Sum-SqrModel 1 .1111809Error 4 4.691989E-02Total 5 .1581008
Std. Error.14404729.624203E-03
T-Value Prob(|t|>T)6.0 0.0039-3.1 0.0370
Mean Square.11118091.172997E-023.162017E-02
SQR(M.S..3334381.108305.1778206
F-Ratio9.5
R-Squared0.70322806
Prob(f>F)0.0370
M-4
Sum of Functions Regression-Date /Time 06-04-1992 15:17:11Data Base Name C:\nasa\WUCllDescription Backup of NASAMSTR created 12-18-1991
Y: REHEAT14Model: A+B*(X)
Estimation Summary Report
X: LEN_WING
Term Coefficient EstimateA .453905563751608B -6.676834926788542D-04
Source df Sum-SqrModel 1 5.185439E-02Error 4 1.003094E-02Total 5 6.188534E-02
Std. Error3.872833E-021.468313E-04
T-Value Prob(!t!>T)11.7 0.0003-4.5 0.0104
Mean Square5.185439E-022.507735E-031.237707E-02
SQRM.S.).22771565.007729E-02.1112523
F-Ratio20.7
R-Squared0.8379108!
Prob(f>F)0.0104
Sum of Functions Regression-Date/Time 06-04-1992 15:23:55Data Base Name C:\nasa\WUCllDescription Backup of. NASAMSTR created 12-18-1991
Estimation Summary Report
Y: REMRAT24 X: DRY_WGTModel: A+B*(SQR(X))
Term Coefficient EstimateA .5789757975531332B -7.51193706208044D-04
Source df Sum-SqrModel 1 4.949569E-02Error 2 1.138906E-02Total 3 6.088475E-02
Std. Error
2.547987E-04
T-Value Prob(!t!>T)6.1 0.0261-2.9 0.0984
Mean Square4.949569E-025.694529E-032.029492E-02
SQR(M.S..2224763.0754621.1424602
F-Ratio8.7
R-Squared0.81294072
Prob(f>F)0.0984
M-5
Sum of Functions RegressionDate/Time 04-27-1992 14:28:07Data Base Name C:\NASA\WUC23Description Merge of WUC11 and WUC51 created O4-27-1992
Estimation Summary Report
Y: REM RATE X: ENG WGTModel: A+B*(SQR(X))
Term Coefficient EstimateA .62110674490679298 -2.48722869S927137D-03
Source df Sum-SqrModel 1 7.983025E-02Error 4 1.631308E-02Total 5 9.614334E-02
Std. Error7.217704E-025.62173E-04
T-Value Prob( j t',>T)8.6 0.0010-4.4 0.0115
Mean Square7.983025E-024.07827E-031.922867E-02
SQR(M.S.).28254256.386133E-02.1386675
F-Ratio19.6
R-Squared0.83032542
Prob(f>F)0.0115
Sum of Functions RegressionDate/Time 06-04-1992 16:03:23Data Base Name C:\nasa\WUC41Description Merge of WUC42 and, WUC11 created 02-05-1992
Estimation Summary*Report
Y: REMRAT12Model: A+B*(X)
X: BTU COOL
Term Coefficient EstimateA .2026788301027799B 5.880527005587363D-04
Source df Sum-SqrModel 1 .0100263Error 2 .0131717Total 3 .023198
Std. Error -9.232288E-024.765976E-04
T-Value Prob(!t!>T)2.2 0.15931.2 0.3426
Mean Square.01002636.585851E-037.732667E-03
SQR(M.S.).10013148;:il5325E-028V793558E-02
F-Ratio1.5
R-Squared0.43220529
Prob(f>F)0.3426
M-6
Sum of Functions RegressionDate/Time 06-04-1992 16:06:33Data Base Name C:\nasa\WUC41Description Merge of WUC42 and WUC11 created 02-05-1992
Y: REMRAT41Model: A+B*(X)
Estimation Summary Report
X: ECSWT
Term Coefficient EstimateA .529437162022918B -8.913524598640413D-05
Source df Sum-SqrModel 1 6.933792E-02Error 4 5.447341E-02Total 5. .1238113
Std. Error7.991302E-023.950266E-05
T-Value Prob(!t!>T)6.6 0.0027-2.3 0.0870
Mean Square6.933792E-021.361835E-022.476227E-02
SQRfM.S.).263321.1166977.1573603
F-Ratio5.1
R-Squared0.56002885
Prob(f>F)0.0870
Sum of Functions RegressionDate/Time O5-O3-1992 11:11:02Data Base Name C:\NCSS\REMAVDescription Data base created at 10:48:48 on O5-O3-1992
Estimation Summary Report
Y: REM42 X: LEN+WINGModel: A+B*(X)+C*(LOG(X))Filter: REM42Term Coefficient EstimateA -.3853306486485544B -1.0061057835372460-03C .1771478107273882
Std. Error.55208916.318003E-04.1326407
T-Value Prob(|t{>T)-O.7 0.5574-1.6 0.25231.3 0.3134
R-Squared0.6231614
Source df Sum-SqrModel 2 8.119295E-O3Error 2 4.909905E-O3Total 4 .0130292
Mean Square4.059648E-032.454952E-03.0032573
SQR(M.S.)6.371536E-024.954748E-025.707276E-02
F-Ratio1.7
Prob(f>F0.3768
M-7
Sum of Functions RegressionDate/Time 05-O3-1992 11:12:43Data Base Name C:\NCSS\REMAVDescription Data base created at 10:48:48 on O5-O3-1992
Estimation Summary Report
Y: REM44 X: LEN+WINGModel: A+B*(X)+C*(LOG(X))Filter: REM42Term Coefficient EstimateA 2.365083753788492B 2.014026317131226D-03C -- 4115210829205226
Source df Sum-SqrModel 2 2.494925E-02Error 2 8.399552E-O3Total 4 .0333488
Std. Error.72210558.263639E-O4.1734875
T-Value Prob(|t|>T)3.3 0.08192.4 0:1351-2.4 0.1411
Mean Square1.247462E-O24.199776E-03.0083372
SQR(M.S.).11168996.48O568E-029.130827E-02
F-Ratio
R-Squared0.74813O3:
Prob(f>F0.2519
Sum of Functions RegressionDate/Time 06-04-1992 16:16:45Data Base Name C:\nasa\WUC47Description Merge, of WUC45 and WUC42 created 01-03-1992
Estimation Summary Report
Y: REMRAT47 X.: DRY_WOTModel: A+B*(SQR(X))
Term v Coefficient EstimateA .6026214260605686B -6.758594018545932D-04
Source df Sum-SqrModel 1 6.784252E-02Error 4 1.045031E-02Total 5 7.829283E-02
Std. Error4.229213E-021.326294E-04
T-Value Prob(!t!>T)14.2 0.0001-5.1 0.0070
Mean Square6.784252E-022.612577E-031.565857E-02
SQR(M.S.).2604665.111338E-02.1251342
F-Ratio26.0
R-Squared0.86652279
Prob(f>F)0.0070
M-8
Sum of Functions RegressionB'ate/Time 06-04-1992 16:23:15Data Base Name C:\nasa\AVIONICSDescription Merge of WUC71 and WUC61 created 03-25-1992
Estimation Summary Report
Y: REMRAT91 X: LEN_WINGModel: A+B*(LOG(X))
Term Coefficient EstimateA 2.348927831791845B -.3585188334562223
Source df Sum-SqrModel 1 .3137073Error 3 6.484672E-02Total 4 .378554
Std. Error.49991449.410941E-02
T-Value Prob(!t!>T)4.7 0.0182-3.8 0.0318
Mean Square.31370732.161557E-02.0946385
SQR(M.S..5600958.1470224.3076337
R-Squared0.82869887
F-Ratio14.5
Prob(f>F)0.0318
Sum of Functions RegressionDate/Time 06-04-1992 16:31:52Data Base Name C:\nasa\WUC42Description Merge of WUC41 and WUC13 created 12-27-1991
Estimation Summary Report
Y: REMRAT97 X: WETAREAModel: A+B*(LOG(X))
Term Coefficient EstimateA 2.532197071458078B -.2283679845742844
SourceModelErrorTotal
df Sum-Sqr1 .43941214 .21304945 .6524615
Std. Error.69496387.950773E-02
T-Value Prob(!t|>T)3.6 0.0219-2.9 0.0454
Mean Square.43941215.326235E-02.1304923
SQR(M.S..6628817.2307864.3612372
F-Ratio8.2
R-Squared0.67346829
Prob(f>F)0.0454
M-9
Sum of Functions Regression •- '•<-Date/Time 05-O3-1992 11:00:51Data Base Name C:\NCSS\REMAVDescription Data base created at 10:48:48 on O5-03-1992
Estimation Summary Report
Y: REMAV X: DRY WGTModel: A+B*(X)+C*(SQR(X))Filter: REMAVTerm Coefficient Estimate Std. Error T-Value Prob(|t|>T) R-SquaredA .3973471291561014 .0219378 18.1 O.OO30 0.75776649B -4.265886102584761D-07 2.39473E-07 -1.8 0:2168C 2-163532620527512D-04 1.603619E-O4 1.3 0.3097
Source df Sum-Sqr Mean Square SQR(M.S.) F-Ratio Prob(f>F)Model 2 1.121494E-03 5.607472E-04 .02368O1 3~1 0.2422Error 2 3.585056E-O4 1.792528E-O4 1.338853E-O2Total 4 .00148 .00037 1.923538E-02
M-10
APPENDIX N
Abort Rate Data & Regression
ABORT RATES - ABORTS PER MAINTENANCE ACTION
F-4D-A F-4D-F F-4D B-52G-A B-52G-F B-62G B-52H-A B-52H-F
WUC11WUC12WUC13WUC14WUC41WUC42WUC44WUC45WUC47WUC51WUC52WUC61WUC62WUC63WUC64WUC71WUC72
1611172441662311012
13
60
7751,154758405207217218281102388144
2233
97154
0.020650.009530.022430.059260.019320.073730.027520.081850.009800.025770.08333•0.000000.05579
0.006180.00000
392248137
16-6184224-
01-400
3052520362
211
111
222
,437,850,000,649,284,620,248,306,719,280,681
22,428,024,251712
00000000000
00000
.00128
.00376
.00192
.00063
.00213
.00242
.00267
.00084
.00233
.00195
.00238
.00000
.00041
.00198
.00000
.00000
2341210783.2..0-23o,04-2;0.0
2031513261
10191
111
,234,933,326,144,734,023,507,481,324,941,054
3,787,991,720645
KC-10A-A KC-10A-F KC-10 C-130A-A C-130A-F C-130B-A C-130B-F C-130B C-130E-A
WUC11WUC12WUC13WUC14WUC41WUC42WUC44WUC45WUC47WUC51WUC52WUC61WUC62WUC63WUC64WUC71WUC72
5 -0191035 -7
17-363
0-0122
1,695 0.002952,041 0.000006,016 0.003162,056 0.004861,280 0.002341,011 0.004953,105 0.002251,707 0.00996884 0.00339956 0.00628
1,990 0.00151• •
196 0.00000473 0.00000
1,231 0.000812,509 0.00080529 0.00378
71176101403-0,11
00332
1,32916974642228237913234867262228
4330105226477
2755029305862821212
321025
11,395 0.002372,663 0.001885,087 0.009833,394 0.008541,718 0.017461,397 0.04152580 0.01034
2,380 0.01176382 0.00524
2,063 0.005821,802 0.00666
421 0.00713255 0.00784105 0.09524
1,130 0.001772,244 0.00223
77281546286101106094437
83241080
legend:
A - aborts
F - maintenance actions
N-l
ABORT RATES - ABORTS PER MAINTENANCE ACTION
C-130E-F C-130E C-130H-A C-130H-F C-130H F-4D-A F-4D-F F-4D F-4G-A F-4G-F
40,51512,25018,71112,00410,4456,1884,77710,7632,2159,2897,416
2,3992,1333,6116,63019,270
0.001900.002290.008230.005160.008230.016320.002090.005570.004060.004740.00499
0.003330.001410.006650.001510.00415
40138551418464561229
4262
25
14,5046,1679,3506,7344,0083,0551,8844,9901,2473,0163, .715
1,9381,3032,0322,6477,244
0.002760.002110.009090.007570.010230.027500.003180.009020.004810.003980.00781
0.002060.001530.002950.000760.00345
947819636356206484311850134
01060961
77542113
31
2
10
,841,917,115,727,127,164,176,570732,033,449
1,571
0,965787
00000000000
00
00
.01199
.00985
.03832
.07679
.02633
.17698
.04082
.12073
.02459
.01649
.09248
.00000
.04123
.00876
.00127
40691201422310031233144161
481
242
2,5633,3961,2391,776956492456
1,309292
1,514645
1,7300
5,681485
F-16A-A F-16A-F F-16A F-16C-A F-16C-F F-15A-A F-15A-F F-15A F-15B-A
154125737
1,200191884108375281730
2613430120
15,8449,85623,83117,6545,71911,6545, '1684,3001,9075,297
5
2 ,'3685,557896
2,3014
0.009720.012680.030930.067970.033400.075850.020900.087210.014680.032660.00000
0.010980.024110.033480.005220.00000
162153
1,0601,05148691914938651
2550
1417842221
11,8417,75426,31012,9307; 57210,5116,1433,1462,7126,996
9
2,0999,895891
3,56818
0.0.0.0.0.0.0.0.0.0.0.
0.0.0.0.0.
0136801973040290812806418087430242612270018810364500000
0066701799047140061705556
20352243236215289955606
196158
0510530
13,0884,1538,1376,6774,2712,6963,2364,293924
7,1082,239
26,489
86,451
0.0.0.0.0.0.0.0.0.0.0.
'0.0.0.0.
0155101252029860353505034107200293613044006490275707057
.•tt00000007860000000822
22316279414219
1153
3519
1.30110
N-2
ABORT RATES - ABORTS PER MAINTENANCE ACTION
F-15B-F F-15C-A F-15C-F F-15C F-15D-A F-15D-F F-15E-A F-15E-F F-111E-A
2,8101,3461,3311,271761361803641253
1,760419
1,516
1,359
142742702742102799652115
336150
40
63
15,3254,2387,2837,5186,3433,2514,9484,9501,4247,6612,594
8,506
7,636
00000000000
0
0
.00927
.01746
.03707
.03645
.03311
.08582
.01940
.10525
.01053
.04386
.05783
.00470
.00825
211656393136216723219
011
7
21111
1
1
1
,773,017,363,174,087558750851288,674385
,478
,217
322090115111641.2643
69162
21
.. 70
21211
22
2
1
,397,257,355,528,622795976421565,305,053
,072
,303185
29760147595915742
6298008100
ABORT RATES - ABORTS PER MAINTENANCE ACTION
F-111E-F F-111E KC-135A-A KC-135A-F KC-135A KC-135R-A KC-135R-F
5,5571,173752
3,4682,6411,3451,1361,822911
2,7912,2443089
1,120608411
0.005220.005970.079790.042390.022340.043870.013200.040610.002200.022210.043670.000000.000000.007140.016450.00000
415
413265713254 i374012r017
30,0654,65722,16021,4134,2388,4643,84911,3612,32617,0866,911911207
2,0132,3261,30110,650
0.001360.001070.001850.001490.001420.006730.003380.002200.001720.002170.000580.000000.004830.000990.003010.000000.00160
347"303315131493
51812431
15
22,6015,78033,01224,6944,8594,4383,8019,4902,54615,2635,606707405
1,8122,0681,15310,140
N-3
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N-6
Sum of Functions RegressionDate/Time O3-21-1992 13:18:31Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992
Estimation Summary Report
Y: AWUC11 X: DRY WTModel: A+B*(X)+C*(SQR(X))
Term Coefficient EstimateA 3.1212954054979310-02B 1.956O10750103666D-07C -1.5455S3903781419D-04
Source df Sum-SqrModel 2. 3.120985E-04Error 10 1.737278E-O4T Ota1 124.858263E-04
Std. Error7.319232E-039.48912E-O85.629948E-05
T-Value Prob(|t|>T)4.3 O.O0172.1 O.O662-2.7 0.0206
Mean Square1.560493E-O41.737278E-O54.O48552E-O5
SQR(M.S-)1.249197E-O24.168066E-O36.362824E-03
F-Ratio9.0
R-Squareo0.6424076
Prob(f>FO.OO58
Sum of Functions RegressionDate/Time O3-21-1992 13:23:44Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992
Estimation Summary Report
Y: AWUC12 X: DRY WTModel: A+B*(X)+C*(SQR(X))Filter: AWUC12Term Coefficient EstimateA .0423204OO2592303B 3.877491472986547D-07C -2.518829377924677D-O4
Source df Sum-SqrModel 2 3.7558O5E-04E rro r 9 7.379731E-O5Total 11 4.493778E-04
Std. Error7.036862E-031.259424E-O76.22464E-05
T-Value Prob(!tJ>T)6.0 O.OOO2311- 0.0132'-4.0 O.O029
Mean Square1.877903E-048.199701E-O64.085253E-05
SQR(M.S.)1.370366E-022.863512E-036.391598E-03
F-Ratio22.9
R-Squared0.8357789
Prob(f>FO.0003
N-7
Sum of Functions RegressionDate/Time 03-21-1992 13:31:13Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992
Estimation Summary Report
Y: AWUC13 X: LEN+WINGModel: A+B*(X)+C*(LOG(X))+D*(SQR(X))
Term Coefficient EstimateA -2.432076284094683B 5.911218731680826D-03C 1.145696021259627D -.3392548733540112
Source df Sum-SqrModel 3 3.731493E-03Error 9 2.191311E-03Total 12 5.922804E-03
Std. Error1.3856853.564697E-03.6458694.1946242
Mean Square1.243831E-032.43479E-044.93567E-04
T-Value Prob(|t|>T)-1.8 0.11311.7 0.13161.8 071098-1.7 0.1153
SQR(M.S.)3.526799E-021.560381E-022.221637E-02
R-Squarec0.6300212
F-Ratio5.1
Prob(f>F0.0246
Sum of Functions RegressionDate/Time 05-O6-1992 15:15:57Data Base Name C:\NASA\WUC23Description Merge of WUC11 and WUC51 created 04-27-1992
Estimation Summary Report
Y: ABTRATE X:Model: A+B*(X)
LEN WING
Term Coefficient EstimateA 4.816425031610672D-02B -1.268146378348553D-04
Source df Sum-SqrModel 1 1.050443E-O3Error 2 6.902844E-O4Total 3 1.740727E-03
Std. Error1.836541E-027.~269126E-O5
T-Value Prob(! t |>T)2.6 0.1198
-1.7- 0.2232
Mean Square1.050443E-033.451422E-O45.802425E-04
SQR(M.S.)3.241054E-02.0185782.408822E-02
F-Ratio3;0
R-Squared0.60345060
Prob(f>F)0.2232
N-8
Sum of Functions Regression'Oate'/Time 03-22-1992 10:27:44Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992
Estimation Summary Report
Y: AWBS10 X: LN DRYModel: A+B*(X)+C*(X*X)+D*(X~3)
Term Coefficient EstimateA -39.95984549060828B 11.092141439OO919C -1.017822607855107D 3.0907587294699490-02
Source df Sum-SqrModel 3 1.531093E-O2Error 9 6.74579E-O3Total 12 2.205672E-02
Std. Error17.157764.735571.43417151.322297E-02
T-Value Prob(|t|>T)-2.3 0.04482.3 0.0439
-2.3 O.O4372.3 0.0442
Mean Square5.103644E-037;495322E-041.83806E-03
SQRCM-S.).07143982.737758E-02.0428726
R-Squared0.6941617
F-Ratio6.8
prob(f>FO.O1O8
Date/TimeData Base NameDescription
Sum of Functions Regression ------03-21-1992 13:44:33C:\NCSS\FILES\ABORTData base created at 12:22:06 on 03-21-1992
Estimation Summary Report
Y: AWUC45 X: LN DRYModel: A+B*(1/SQR(X))+C*(X)+D*(X*X)+B*(X"3)Filter: AWUC45Term Coefficient Estimate Std. ErrorA 5000.25349948818B -7578.183026428647C -453.6120878012779D 24.60056275019885E. -.5276227079707911
Source df Sum-SqrModel 4 .0281919Error 7 1.759745E-03Total 11 2.995164E-02
2535.2523806.867234.465712.97183.2839331
Mean Square7.047974E-032.513922E-042.722876E-03
T-Value Prob({t J >T)2.0 0.0892
-2.0 0.0868-1.9 0;09431.9 0.0997
-1.9 0.1055
SQR(M.S.)8.395221E-021.585535E-025.218119E-02
R-Squared0.94124711
F-Ratio28.0
Prob(f>F)0.0002
N-9
Sum of Functions RegressionDate/Time 03-21-1992 13:37:30Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992
Estimation Summary Report
Y: AWUC14 X: LEN+WINGModel: A+B*(LOG(X))+C*(SQR(X))
Term Coefficient EstimateA .7119536461928977B -.1881388279494333C 2.098824012629048D-02
Source df Sum-SqrModel 2: 1.015222E-02Error 10 9.66868E-04Total 12 1.111908E-02
Std. Error.18466385.986314E-029.148882E-03
T-Value Prob(!t|>T)3.9 0.0032
-3.1 0.01052 3 0.0447
Mean Square5.076109E-039.66868E-059.265904E-04
SQR(M.S.)7.124681E-029.832945E-033.043995E-02
F-Ratio52.5
R-Squared0.9130442:
Prob(f>P0.0000
Sum of Functions RegressionDate/Time 03-22-1992 10:24:15Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on O3-21-1992
Estimation Summary Report
Y: AWUCAV X: DRY WTModel: A+B*(X)+C*(SQR(X))
Term Coefficient EstimateA 5.027494869365O81D-02B 2.605132300912917D-07C -2.2881974939125510-04
Source df- Sum-SqrModel 2 9.871627E-O4Error 10 2.069475E-O4Total 12 1.19411E-03.
Std. Error7 . 988421Err031.03567E-076.144687E-05
T-Vaiue Prob(!t|>T)6.3 O.O0012.5 0.0306-3.7 O.O039
Mean Square4.935814E-042.O69475E-O59.95O918E-05
SQR(M.S.)2.221669E-024.549148E-O39.975429E-O3
F-Ratio23.9
R-Squared0.8266931L
Prob(f>F0.0002
N-10
Sum of Functions Regression* Date/Time 03-22-1992 10:45:38Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 oh 03-21-1992
Estimation Summary Report
Y: AWBS14 X: DRY WTModel: A+B*(X )+C*(SQR(X))
Term Coefficient Estimate Std. Error T-Value Prob(Jt!>T) R-SquaredA 8.2198986530845460-02 1.398155E-02 5.9 O.OO02 O.78927531B 5.0072044718141130-07 1.812657E-07 2.8 0.02OOC -4.0612509035796350-04 1.07546E-04 -3.8 O.O036
Source df Sum-Sqr Mean Square SQR(M.S.) F-Ratio prob(f>FModel 2 2.374444E-03 1.187222E-O3 3.4456O9E-O2 18.7 O.0004Error 10 6.339409E-O4 6.3394O9E-05 7.962041E-O3Total 12 3.008385E-03 2.506987E-O4 1.583347E-02
N-ll
APPENDIX O
Crew Size Data & Regression
Descriptive StatisticsDate/Time 05-O3-1992 08:56:17Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on O5-O3-1992
Detail Report
Variable: CREW1Mean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test/bl 0.81 Skew-Z
2.0511111.8237042.278518.7O10889.2960348.763611E-02.1443286.9848181.1876070.185771.39 Pr 0.1653
No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2 3.11 Kurt-Z
D'Agostino-Pearson Omnibus KJ Normality Test-100-%tile (Maximum) 2.6675-%tile 2.1250-%tile (Median) 2.0325-%tile 1.90-%tile (Minimum) 1.66
1.661 1 2 - .
9O-%tile10-%tileRange75th-25th %tileC.L. Median(95%)
Line Plot / Box Plot ------i : i l 1
9o918.469.867799E-0220.7859O.OOOO1.3483142.151(5%)0.275(5%)
1.05 Pr 0.29483'.0 Pr 0.2207
2.481.661.2199999
1.8, 2.3•2.66
1
Detail Report
Variable: CREW2Mean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSKewnessNormality Test ValueK.S. Normality Test/bl 0.48 Skew-Z
2.4355562.1891362.681975.8232222.3207846.1029028.131709.58114421.0594250.1620O0 83 Pr 0.4077
No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2 2.29 Kurt-Z
D'Agostino-Pearson Omnibus K} Normality Test 0.7100-%tile (Maximum)75-%tile50-%tile (Median)25-%tile0-%tile (Minimum)
2-1
2.99 90-%tile2.53 • • * • - 10-%tile2.37 Range2.26 75th-25th %tile2 C.L. Median(95%)
Line Plot / Box PlotI" 2'- 1 1CXXXXXXXXmXXXXaXXXXXXX J
9O9"21.92.106928222.77748O.OOOO-.2131622.151(5%)0.275(5%)
0.02 Pr 0.9819Pr 0;70962.92
:' ' 2 :.99.27 •"
11, 2.85-2.99
1
0-1
Descriptive StatisticsDate/Time 05-03-1992 08:56:18Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992
Detail Report
Variable: CREW4Mean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test
-0.22 Skew-Z
2.1811111.9442352.417987.7606889.30836049.508611E-02.1413776-.26932981.2448260.17682
-O.39 Pr 0.6998
No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2 3.49 Kurt-Z.
D'Agostino-Pearson Omnibus KJ Normality Test 2.1100-%tile (Maximum) 2.7375-%tile 2.2650-%tile (Median) 2.2125-%tile 2.040-%tile (Minimum) 1.58
I CO - ___ .HIT Ull 1_
• ,30—"——•————•—i
90-%tile10-%tileRange75th-25th %tileC.L. Median(95%)
-Line Plot / Box Plot11 1_2 1,CXXXXXXXXXaXmXX]
Detail Report
90919.63.102786821.219760.00002.075O352.151(5%)0.275(5%)
1.41 Pr 0.1580Pr 0.34272.561.581.15.22 .
2.02, 2.39-2.7:
Variable: CREW567Mean - AverageLower 95% c.i.1imitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test#>1 0.20 Skew-ZD'Agostino-Pearson Omnibus
2.422.282.212.011.98
2.1788892.0452032.312574.2422889.174O2913.O28611E-027.987055E-02.24651881.0710840.16743
No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2. 1.66 Kurt-Z
1.40.35 Pr 0.7241
7 Normality Test100-%tile (Maximum) 2.42 90-%tile75-%tile 2.28 10-%tile5O-%tile (Median) 2.21 Range25-%tile 2.01 75th-25th %tile0-%tile (Minimum) 1.98 C.L. Median(95%)
1.98 Line Plot / Box Plot21 1 2. 1.
CXXXXXXXXXXXXXXXXXXXXXXXXXXXXXaXXXXXmXXXXXXXXXXXD -
9O :-.=.,919.61,5.80O968E-0237.560780.0000-1.4037312.151(5%)0.2.75(5%)
-1.14 Pr 0.2528Pr O.48862.42-1.98 ..44OOOO1.27
1.98, 2.42
0-2
-—•* Descriptive StatisticsDate/Time 05-O3-1992 08:56:18Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992
Detail Report
Variable: CREW9Mean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test
1-22 Skew-Z
2.1411111.8876862.394536.87O6889.3299032.1088361.15408041.4763571.9679540.242892.04 Pr 0.0415
No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean-OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2 3.74 Kurt-Z
D'Agostino-Pearson Omnibus K.7 Normality Test 6.8100-%tile (Maximum) 2.87 90-%tile75-%tile 2.17 10-%tile50-%tile (Median) 2.O3 Range25-%tile 2 75th-25th ttile0-%tile (Minimum) 1.76 C.L. Median(95%)
1.76 Line Plot / Box Plot1 1 111 11 1
CXmXXXXXXXaX]
9o919.27.109967719.47036O.OOOO2.5475032.151(5%)0.275(5%)
1.62 Pr 0.1048Pr 0.03362.6451.761.11.1700001
88, 2.42-2.87
1
0-3
Sum of Functions RegressionDate/Time 05-03-1992 08:23:49Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992
Estimation Summary Report
Y: CREW1 X: WET AREAModel: A+B*(X)+C*(SQR(X))Filter: CREW1Term Coefficient EstimateA 1.500658209569604B -3.198838553665343D-05C 9.172174012957018D-03
SourceModelErrorTotal
df; Sum-Sqr2 .15434995 .12965017" .284
Std. Error.24366762.614986E-055.589843E-03
T-Value Prob(!t|>T)6.2 0.0016
-1.2 0.27571.6 0.1617
Mean Square7.717495E-022.593002E-024.057143E-02
SQR(M.S.).2778038.161028.2014235
F-Ratio3.0
R-Squared0.5434855
Prob(f>F0.1408
ActualRow X
1 17032 .3 19894 26435 13856 88997 109548 153509 33712
ActualY.,1.66
2.031.92.121.92.32.09
Residual Analysis
Predicted Lower95% Upper95%Y Value Value Residual1.824694 1.359004 2.290384 -.164694
1.8460961.8876551.7977022.0812462.110232.1460242.106353
1.3875031.4379041.3205821.6088781.6324211.6664361.525632
2.3046892.3374062.2748222.5536142.5880382.6256122.687073
-.461E-01.1423445.1022978.3875E-01-.2102297.1539759-.164E-01
O-4
Sum of Functions Regression-Date/Time 05-03-1992 08:32:04Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992
Estimation Summary Report
Y: CREW4 X: LEN+WINGModel: A+B*(X)+C*{LOG(X))Filter: CREW4Term Coefficient EstimateA -1.48042021491415B -2.832923203920881D-03C .8146558480412586
SourceModelErrorTotal
df Sum-Sqr2 .2526895 .1690617 .42175
Std. Error1.8986062.211458E-03.4565359
T-Value Prob( ,'t|>T)-0.8 0.4708-1.3 0.25641.8 0.1344
Mean Square.1263445.0338122.06025
SQRfM.S.).3554497.1838809.2454588
F-Ratio3.7
R-Squared0.599144K
Prob(f>F0.1017
ActualRow X
1 852 .3 1014 1075 806 2317 2678 3289 471
ActualY1.58
2,2,2,
.04,18.02
2.212.392.262.22
Residual Analysis
Predicted Lower95% Upper95%Y Value Value1.898013 1.. 358883 2.437143
Residual-.3180131
1.9931892.0232041.862792.2988722.3148742.3096932.199364
1.4748241.5065641.3099791.7453911.7690781.7762171.547251
2.5115552:. 5 3 984 52V41562.8523532.860672.8431692.851477
.0468105
.1567957
.1572104-.0888719.7513E-01-.0496934. 2064E-01
O-5
Sum of Functions RegressionDate/Time 05-03-1992 08:52:24Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992
Estimation Summary Report
Y: CREW9 X: DRY WGTModel: A+B*(SQR(X))Filter: CREW9Term Coefficient EstimateA 1.789334628455685B 9.872173912348861D-04
Std. Error.10351513.452152E-04
T-Value Prob(|t|>T)17.3 0.00002.9 0.0288
SourceModelErrorTotal
df Sura-Sqr1 .15746876 .11553137 .273
Mean Square.1574687l;925522E-02.039
SQR(M.S..3968232.1387632.1974842
F-Ratio8.2
R-Squared0.5768083.
Prob(f>F0.0288
ActualRow X
1 177922 .3 296634 274255 144476 719907 970308 1408829 320083
ActualY1.76
lies2.27172.022.032.122.42
Residual Analysis
Predicted Lower95% Upper95%Y "• Value Value Residual1.921016 1.544625 2.297407 -.1610163
1.9593631.9528231.9079942.0542152.0968492.1598792.347862
1.5912411.5834831.5281911.6943241.7347551.7879461.90699
2.3274842.3221622.2877972.4141052.4589442.5318122.788734
-.794E-01.4718E-01.2620062-.342E-01-.668E-01-.0398794.7214E-01
0-6
APPENDIX P
Scheduled Maintenance Data
SCHEDULED MAINTENANCE DATA BASEREGRESSION FUNCTION & ANOVA FOR % OF UNSCH
% OF UNSCH = 0.844224 + 0.002638 LGTH+WING+ 3.379129E-05 WET AREA- 0.005231 SQR DRY WT
R-Squared = 0.849869Adjusted R-Squared = 0.830287Standard error of estimate = 0.048856Number of cases used = 27
Source
RegressionResidual
Total
Analysis of Variance
SS df MS : F Value
43.399860.31077 30.05490 23
0.36567 26
Ov103590.00239
Sig Prob
O..OOOOOO
Variable
ConstantLGTH+WINGWET AREASQR DRY WT
SCHEDULED MAINTENANCE DATA BASEREGRESSION COEFFICIENTS FOR % OF UNSCH
Coefficient,
0.84422.0.00264
3I37913E-05-0.00523
Std Error
0.047745.41478E-O44.82356E-065.44648E-04
t-Value
17.682674.871917~. 00547-9.60423
Two-SidedSig Prob
0.0000000.0000640.0000000.000000
Standard error of estimate = 0.048856Durbin-Watson statistic = 2.325117
P-l
SCHEDULED MAINTENANCE DATA BASESTANDARDIZED RESIDUALS TABLE FOR % OF UNSCH
CaseActual Predicted
% OF UNSCH % OF UNSCH
A-7DA-10AB-52GB-52G-2FB-111AF-106AF-111AF-111DF-111FF-4EF-5EF-15AF-15CF-16AC-130BC-130B-2C-130EC-130HC-130H-2KC-135AC-140A-2C-141BC-141B-2C-5AC05A-2C-9AT-38A
0.48400 . 46600.25900.33000.17000.48800.23600.25200.18100.2580O.63200.27900.34900.47200.38400.47000.32100.28800 . 4020O.29600.39100.25100.30300.25700.27200.27300.5850
0.42770.46960.30660.30660.19010.39490.22450.20820.20760.27770.56510 . 35850.34850 . 47200.39800.39800.34950.33460.33460.28930.47180.26560.26560.26510.26520.31510;6389
Residual
0.0563-3.562E-03-4.760E-02
0.0234-2.015E-02
0.09310.01150.0438
-2.661E-02-1.975E-02
0.0669-7.955E-025.1859E-04-1.384E-05-1.400E-02
0.0720-2.849E-02-4.662E-02
0.06746.6864E-03-8.076E-02-1.460E-02
0.0374-8.147E-036.8484E-03-4.212E-02-5.388E-02:
Std Dev
0.04620.04660.04590.04590.04420.0472O.04520.04460.04460.0452O . 04380.04680 . 04660.04580 . 04640 . O4640.04710.04710.04710.04650.04660.0455O.O455O.03560 . 03560.04610 . 0404
StdResidual
1.2168-7.641E-02
-1.0370.5097-0.4561.97080 ; 25360 . 9826-0.597-0.4371.5287-1.7010.0111
-3.020E-O4-O.3021.5514-O.605-0 . 9891 . 42950.1437-1.733-0.321_0.8221-0.2290.1926-0.914- 1 . 333
Durbin-Watson statisticPRESS statistic
= 2.325117= 0.07127
P-2
Descriptive Statistics •Date/Time 03-23-1992 13:50:42Data Base Name C:\NASA\MAINTDescription Merge of WUC51 and WUC11 created 02-21-1992
Detail Report
Variable: %UNSCHMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test
0.55 Skew-Z
.3731923
.3193155
.4270691
.444882
.1333991.779528E-02.3574537.58886641.0154850.123701.33 Pr 0.1846 b2
No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=0T prob levelKurtosisReject if > 1.169(10%)Reject if > 0.156(10%)
D'Agostino-Pearson Omnibus K/ Normality Test100-%tile (Maximum) .665 90-%tile75-%tile .472 10-%tile
2.49 Kurt-Z1.8
.3515 Range
.272 75th-25th %tile
.17 C.L. Median(95%).17 Line Plot / Box Plot11 1 12 21 11 1 11 11 1 1 1111 1
50-%tile (Median)25-%tile0-%tile (Minimum)
359269.7032.616169E-0214.264840.0000-.35604981.265(5%)0.171(5%)
-0.25 Pr 0.8000Pr 0.4016.585.236.495.2
.273, .4666651
Variable: %UNSCHBin Lower1 .172 .215
26305353954448553
34567891011
.5750001
.62
Upper.215.26.305.35.395.44.485.53.5750001.62.665
Distribution & Histogram
Count24523232012
Prcnt- 7.715.419.27.7
11.57.711.57.70.03.87.7
Total26111316182123232426
Prcnt. 7.723.142.350.061.569.280.888.588.592.3100.0
Histogram***********************
***
P-3
APPENDIX Q
Learning Curve Data & Regression
_ Multiple RegressionDate/Time 01-08-1992 16:07:40Data Base Name C:\NASA\learnDescription Data base created at 15:46:10 on 01-08-1992
Aircraf t : F-16BMultiple Regression Report
Dependent Variable: LOG MTBMIndependent Parameter Stndized Standard t-valueVariable Estimate Estimate Error (b=0)Intercept -1.826819 0.0000 .2906916 -6.28LOG CUM .1441237 0.7799 .2726E-01 5.29
Prob.Level0.00000.0001
Seq.R-Sqr
0.6082
SimpleR-Sqr
0.6081
Analysis of Variance Report
Dependent Variable: LOG MTBM
Source df Sums of Squares(Sequential)
Constant 1 1.973916Model 1 1.468497Error 18 .9458253Total 19 2.414322
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
1.9739161.4684975.254585E-02.1270696
.2292288-.3141589-.7296589
0.60820.5865
F-Ratio Prob. Level
27.95 0.000
Row MTBM FLY HRS LOG MTBM CUM
1234567891011121314151617181920
.315
.459
.587
.651
.801
.679
.953
.724
.48
.574
.63
.687
.633
.825
.779
.9391.1721.1121.411.076
106138729844735542861338907983193691004412787155311577516248159751642417726168771648112657
-1.155183-.7787051-.5327305-.4292457:-.2218943-.3871342-4.81E-02-.3229639-.7339692-.5551259-.4620355-.375421-.4572849-.1923719-.2497442-.0629398.1587117.1061602.34358977.325E-02
1061493447792121464020773296803951148880589247171187242103017119265135240151664169390186267202748215405
LOG CUM
4.6634397.3085438.4067099.1282639J5915139:94140910.2982310.5843310.7971210.98411.180411.3764411.5426511.689111.8148111.9294212.0399612.1349412.2197212.28028
Q-l
Multiole RegressionDate/Time 01-08-1992 16:14:52Data Base Name C:\NASA\learnDescription Data base created at 15:46:10 on 01-08-1992
Multiple Regression Report
Dependent Variable: LOG MTBMIndependent Parameter StndizedVariable Estimate EstimateIntercept -2.229546 0.0000LOG CUM .1271822
Standard t-valueError (b=0),2569398 -8.68
0.8949 .2836E-01 4.49
Aircraft: B-l
Prob.Level0.00030.0065
Seq.R-Sqr
SimpleR-Sqr
0.8009 0.800C
Analysis of Variance Report
Dependent Variable: LOG MTBM
Source df Sums of Squares(Sequential)
Constant 1 8.427293Model 1 .3213427Error 5 7.987001E-02Total 6 .4012127
Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Mean Square
8.427293.3213427.0159746.686879E-02
.1263883-1.097223-.1151892
0.80090.7611
F-Ratio Prob. Level
20.12 0.006
Row MTBM FLY MRS LOG MTBM CUM
12345678
.236
.266
.288
.396
.339
.238
.498
.382
36711672786651583O4110OO1242711676
-1.443923-1.324259-1.244795-.9263411.-1.081755
-.6971552-.9623347
367153443201083519139301394256654242
LOG CUM
5:9053627.3356348:3710119.2905379185948410.3135810.6588110.90121
Q-2
Multiple RegressionDate/Time 01-08-1992 16:25:06Data Base Name C:\NASA\learnDescription Data base created at 15:46:10 on 01-08-^1992 Aircraft: F-15A
Multiple Regression Report
Dependent Variable: LOG MTBMIndependent Parameter StndizedVariable Estimate EstimateIntercept -2.517107 0.0000LOG CUM .1403061 0.8265
StandardError.2322152.1912E-01
t-value<b=0)-10.847.34
Prob.Level0.00000.0000
Seq.R-Sqr
0.6830
SimpleR-Sqr
0.6830
Analysis of Variance Report
Dependent Variable: LOG MTBM
Source df Sums of Squares(Sequential)
Constant 1 18.84179Model 1 2.070925Error 25 .9610558Total 26 3.031981
Root Mean Square Error •Mean of Dependent VariableCoefficient of Variation
R SquaredAdjusted R Squared
Row, MTBM FLY HRS
1 .23 4222 .186 15793 .242 36104 .343 89745 .217 83176 . 484 208867 .43 267628 .521 360229 .491 4028110 .482 4839611 .499 4599312 .5 4034913 .483 4210114 .449 4O42715 .424 3912616 .475 4196017 .423 4296018 .38 4169419 .438 4292520 .496 44157
21 .404 4077822 .492 4019823 .514 4008924 .687 4567125 .704 4228426 .74 4421427 1 3881728 .582 3736629 1.073 42941
Mean Square F-Ra
18.841792.070925 533.844223E-02.1166146
.1960669
.8353705
.2347065
0.68300.6703
LOG MT8M CUM
-1.469676 422-1.682009 2001-1.418818 5611-1.070025 14585-1.527858 22902-.7256704 43788-.8439701 70550-.6520053 106572-.7113112 146853-.7298112 195249-.6951492 241242-.6931472 281591-.7277386 323692-.8007324 364119-.8580218 403245-.7444405 445205-.8603831 488165-.967584 529859-.8255364 572784-.7011793 616941-.90634O4 657719-.7092766 697917-.665532 738006-.375421 783677-.3509769 825961-.3011051 870175
908992-: 5412849 946358
989299
Prob. Level
0.000
LOG CUM
6.045O057.6014023.6324849.58774910.0389810.6871111.1640811.5765811.8971912.1820312.3935612.5482112.6875512.8052412.907313.0O62913.0984113.1803713.2582613.3325313.3965313.4558613.5117113.5717513.624313.6764513.720O913.7603813.80475
Q-3
Learning Curve
SUMMARY OF REGRESSION ANALYSIS OF WUC FOR F15A
WUC R-SQUARED F-RATIO PROB(f>F)
11121314232441424445464749515255576365717475769197
.4986
.2419
.6682
.0051
.8615
.1733
.3939
.5006
.0571
.5544
.0484
.2858
.1241
.7441
.5637
.8064
.5747
.6388
.0588
.7474
.6896
.0001
.0347
.0043
.0849
26.88.654.40.1
168.05.7
17.527.11.6
32.21.3
10.43.7
75.633.6108.335.146.01.6
76.957.80.00.90.12.4
.0000
.0067
.0000
.7135
.0000
.0247
.0003
.0000
.2209
.0000
.2604
.0034
.0660
.0000
.0000
.0000
.0000
.0000
.2139
.0000
.0000
.9573
.3424
.7405
.1325
-1.915372.058404-.1265132.320406-1.157162.0835291.4757401.6287903.469018.71487622.0356953.1693163.582417.4074346.8766071.48106991.8363965.783D-22.294958-.280821-1.371032.0108363.7017416.5566561.856478
B
.2076786.85051D-2.1985811.35424D-2.2604547.37557D-2.111258.132691-3.5174D-2.1581114.59528D-2.1141946.83186D-2.217907.246037.304793.186201.2181413.60766D-2.227016.221936-2.5339-4.7932D-2-3.1327D-2.186038
Q-4
Learn ing Curve
SUMMARY OF REGRESSION ANALYSIS OF WUC FOR F16B
WUC R-SQUARED F-RATIO P R O B ( f > F )
111213142324414244454647495155626364657174757691939697
.1059
.36829
.32299
.52673
.60731
.61054
.51493
.142337
.000168
.596262
.383556
.006646
.003831
.006221
.152934
.295669
.391082
.694946
.009315
.380828
.733988
.705648
.249363
.167479
.861299
.012051
.007545
2.311.19.1
21.129.429.820.23.20.0
28.111.80.10.10.13.27.612.241.00.2
11.752.445.56.33.6
31.00.20.1
.15
.0035
.0072
.0002
.0000
.0000
.0003
.0918
.9555
.0000
.0028
.7254
.7955
.7340
.0882
.0132
.0024
.0000
.6773
.0029
.0000
.0000
.0212
.0732
.0026
.6450
.7081
1.06010.8958701.18406.68128.52739.1432431.0961762.3528413.3012241.9055431.1165094.0804916.4613573.4176077.7507617.0489222.1408831.1891824.4754612.109804-1.15588-.3489292.1966884.3369794.3793667.1128114.651410
B
6.46444D-02.165848
9.746065D-2.160767.200457.244629.205497
6.748413D-2-3.30773D-2
.182393
.1452481.689806D-2-2 .7 978 3D-21.448673D-2-.182029-.242943.1653402.3180727-2.87638D-2
.133664
.280784
.258164
.101590
.293534
.4249086.728099D-23.790276
Q-5
Learning Curve
SUMMARY OF REGRESSION ANALYSIS OF WUC FOR BIB
WUC R-SQUARED F-RATIO P R O B ( f > F )
11121314161923242739414243444546474849515255597375:7697
.3889
.5187
.0437
.0128
.5717
.2123
.2637
.7642
.0458
.1926
.2466
.3047
.1248
.6880
.0114
.1802
.4963
.2795
.6084
.5936
.3803
.6044
.2483
.6457
.1214
.2454
.3654
3.86.50.30.18.01.32.119.40.31.42.02.60.9
13.20.11.35.92.39.38.83.79.22.0
10.90.82.03.5
.0985
.0439
.6194
.7895
.0300
.2981
.1931
.0045
.6109
.2767
.2106
.1560
.3907
.0109
.8012
.2945
.0511
.1780
.0224
.0253
.1035
.0232
.2089
.0163
.3977
.2119
.1124
A
-.4813981.3397571.6275071.856759-1.288142.964628.514386.702416
3.8852552.4230091.040726.986220
3.072291.597645
1.8871972.8177221..8596262.6790965.9605211.0156084.465351,255066,752438
-.6095651.7397761.1279137.623481
11
B
.107564
.2182973.24288D-2-1.8648D-2.533732.1590607.03474D-2.259668-.07045.1585998.32289D-28.57397D-2.104326.199826.016278-.09968.191071.142582-.20272.415428-.10694.1771148.51324.169980.0822627.49415-.22974
Q-6
AVERAGE SLOPE FROM SUMMARY OF REGRESSION ANALYSIS OF WUC
PLANESF15AF16BBIB
USED:
WUCs11 &13142341 &42 &
12
4744
4549 & 9651 - 72*91, 93, & 97
AVERAGE.153578.148021.160767.230456.155505.133334.170252.068319.242701.359221
SLOPE NUMBER OF VALUES AVERAGED5212432182
51 - 72 IS COMPOSED OF 51, 52, 61, 62, 63, 64, 69, 71, & 72
Q-7
APPENDIX R
Technology Growth Data
TECHNOLOGY ADJUSTMENT FACTOR DATA
. 'i : LJ Mi -jM '- ALC w i_.-i i • 0 . • C
FLY HOURSMTBM/PERIOD
wucwucwucwucwucwucwucwucKUCVUCwucwucwucwucwucwucwucwucwucwucwucwucwuc
* ••%
± 1 '3L <J
14•> o_ o
41421445474931526162636469717291939697"
GROUPED11 i 1213
234142
4744
-rO4951 - 7291 & 97
WUCs
0/85-3/86
4,200
7.67338. £211.86711.03217.96229.75543.019
3634.721
1.36.2251.95.42939.265
83.S2455.019156.381
3,109.09151.42983.824152.679
4/86-9/86
10, 164
8.52540.43813.77412.93919.09829.25358.20348.56644.936168.050218.28352.571
89.45269.972193.096
2,868.85760.67196.317161.952
1C/86-3/37
3S.C27
12.33650.24715.30217.52327.35544.47873.37546.97146.188164.507259. 18760.754
133.92986.396251.S37'
1,896. 15365.743103.229232.432
4/37-9/87
40.533
12.58458.4031G. 18119.22724.79146.06078.70557.25054.774
167. 492311.79260.227
142.72289.280
258. 1722,533.313
75". 061107.230268.43
10/35-9/87
120,924
10.740448.154115.144315.811522.863837.740567.456249.996147.7059165.4609254.849956.5869
114.935280.1036226.1225
2.401.626766.0188101.2675207.9488
183.371 196.882 184.754 455:427 236.7149
8151522302847
25414
110
,78171443,81153638,73107142,70593499,55247007
WUCs 51, 62, 63, 64, 69 & 72
r~ < T PT*T \ TL.-.i-L >. i-.-ii
MTBM/PERIODwuc : iWUC 12WUC 13WUC 14WUC 23WUC 41WUC 42WUC 44WUC 45WUC 47WUC 49WUC 5 1WUC 52WUC 61WUC 52WUC v3WUC 6 IWUC 69WUC 71WUC 72WUC 91WUC 93WUC 96WUC 97
GROUPED11 & 12131423414245495191
4744
967297
10/85-3/86
106,021
3.47524.88220.33818.59425.02929. 16745.89765.083113.87958.285285.77128.960220.418
96.47091.793391.221
2,255. 7661.53.210
9,638.273302.054
4/86-9/86
113,267
6.95520. 11:216.35615.50118.49622.99437.90760.44194.46847.792230.68623.876143.014
64.83569.660337.104845.276106.354
3,146.306207.069
10/86-3/87
104, '537
6.48920.27515.82914.70917.74522.12433.30351.93177.723'43.179188.69524.054138.276
64.89070.112313.925
1,005. 16395.468
3,167.788244.245
4/87-9/87
118,573
3. 18527.46722.86020.80221.66130.63944.27778.681103.64875.332278.99530.521162.429
90.307101.344374.047513.303131.310
4,088.724334.008
10/85-9/87
442,293
7.451722.347818.491117.136520.363625.786939.802162.992595.778154.0563240.303026.5931160.3472
76.672281.2932351.9473857.3603117.8159
4,058.6975263.1751
WUCs
10,602.100 7,079.188 17,422.833 11,857.300 10,533.2860199.663 203.718 234.915 296.433 228.9848
5.619118.491117.136520.363617.458524.390795.7781234.943112.2062 WUCs 51, 52, 62, 63, 64, 69, 71, 72.
122.4462
R-2
10/85-3/36 4/36-3/86 10/86-3/87 4
FLY HOURSMTBM/PZRIODWUC :. 1VUC 12WUC 13
51,56" 54,718
WUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUC
140 Oi. U
4142444547495152SI62S38469717291939697
GROUPED11131422414245495191
& 12
&. 47& 44
- 72, 93,
WUCs
97
3.3166.96211.45910.33817.92433.79245.87825.29047.44059.069334.85118.56351.006
23.145
4.14462.963991.673170.188
2,242.043537. 156
2.094312.16019.942316.925619. 123616.813644.1927226.89652.577592.0627
2.6765.85911.6878.45715.59825.65339.91126.43442.91657.841279. 17316.84746.808
16.032
3.37446.371816.687144.757
2,379.043353.019
WUCs 51,
49 ,583
36121.01531412544512451749
,264021
, 578.102, 558,968.488, 585,629,703,460,086.533
/87-3/S7 1
491
3612101727432843622131750
,240
. 187
.208
.253
.083
. 140
.306
.357
.200
.979
.499
.583
.863
.229
.0/85-9/87
647
3.6 .12.9.16.27.43.27.44.60.226.17.49.
, ioa
1535215516019423925639230824575419278301896576399273
18.412 21.257 20.5800
3.338 4.190 4.025458.817 74.094 68.3182708.329 1,116.455 1,028.7890156.413 156.446 156.3819
MTBM NOT CALCULATED378.496 261.298 286.0779
52, 63, 71, & 72
R-3
10/85-3/86 4/86-9/86 10/86-3/87 4/37-9/87 10/85-9/87
FLY HOURSMTBM/PERIOD
40,089 45,571 2 0, .-00 - 44,214 179 ° ~ Qx I £ , «d w o
WUC*ucWUCwucWUCwucwucWUCwucwucwucwucWUCwucWUCwucwucwucwucwucwucwucwucwuc
:. 1•« n- w
13142341.'1 <~>-r t*
4445474951526162636469717291939697
GROUPED WUCs11 &.13142341 &42 &.454951 -91 &.
12
4744
7197
1 .9161 2 . 5 7 39.2769.8029.833
15.93429.91715. 16215.59399.47659.21625.024120.387
2.55920.26213.70714.04810.89720.22642.64320.12824.984135.92683.49431.849153.774
2.73622.69714.36814.17011.81823.76836.48319.45920.506
120.467107.04827.245126.599
3.09722.26216.83114.83212.28126.22442.67822.19619.350
113.369100.03233.34473.081
2.539518.540413.026512.945911.173120.907637.398518.975319.6957
116.390483.580129.1272109.7883.
20.633
41.934
2.233613.026512.945911.173117.723812.588219.695783.58017.1444
58.0187
28.349 25.094 28.055
84.420 127.746 56 i 180
WUCs 51, 52;: 63, 69, &. 71
25.2764
15.077 23.713 16.263 16.824 17.5541
331.314 496.424 671.175 566.846 486.6045
65.8729
R-4
'ISA
10/85-3/86 4/86-9/86 10/86-3/37 4/87-9/87 10/85-9/37
FLY HOURSMTBM/PERIODWUC 11
33,311 85, C2' 39.041 92,692 350, 102
WUCWUCWUCWUCwucwucWUCwucWUCwucwucwucWUCWUCwucwucwucwucwucwucwucwucwuc
121 *}1 sJ
14234142444547495 1- o*J &.
6162636469717291939697
625121421382230758064150
• O O *>
.699
.757
.362
.309
.637
.124
.833
.014
. 757
.085
.571
826,1115,25,35.22,34.74,90.488.64.
.350
.521
.210,756.008,019.943,410,324.551,661610
9341 OL 0
182351303779
10270676
.250.! - q• ~t *j j.489.010.432.469.619.085.359.938.675.627
3.29.12.14.19.40.28.31.74.118.626.66.
655690348470315O i QO i. J
166679333533304734
328121522402533759660563
30 r r:4. *J \J
.8032
.4037
.5285
.0051
.6432
.6072
.3399
.7139
.7670
.7130
.4818
85. 74252.219324.284
78.51151 .500397.322
38.42261.535418.033
73.44958.224397.324
80.967255.6955381.7905
150.707 140.773 170.250 146.203 151.2970
2,604.406 5,001.588 1,141.551 648.203 1,296.67427,576.455 28,342.333 22,260.250 92,693.000 18,426.421711,905.857 5,314.188 8,094.636 7,724.417 7,610.9133
2.13.695 228.567 57.483 50.159 84.1798
GROUPED WUCs11 & 1213
41 i 4742 St. 444549 & 9651 - 72 *91, 93, & 97
61215222814755611878
4587403752850051621848327139061008757103
WUCs 51, 62, 63, 64, fc 71
R-5
F4C MTBM CALCULATION'S
10/85-3/36 4/86-9/86 10/86-3/87 4/87-9/87 10/85-9/87
FLY HOURSMTBM/PERIODWUC 1 1WUC 12WUC 13WUC 14WUC 23WUC 41WUC 42WUC 44WUC 45WUC 47WUC 49WUC 51WUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUC
526162S36469717291939697
18,421
39.959
8.536139.553877.190214.198708.500103.489
12,577 9.944
34.177
9.586151.530483.731196.516
44.995
12..864284.114904.000320.774
40 ,942
5.48205.613011.69609.783017.072025.656033.432029.616033.013046.2840224.646021.749051 . 4550
4.5575.48310.6958.77715.62429.52334.08432.08427.34138.462256.67318.97051.126
6.3959.48915.48912.47719.65238.99650.22243.61431.97454.339621.50028.99160.634
5.33436.181212.06689.954517.130529.265036.620832.964630.806645.0905278.516622.095253.3097
228.673 261.684
38.9925
9.6492163.7679705.8966226.1992
151.0777:
GROUPED WUCs11131423414245495191,
& 12
& 47&. 44
- 72 *, 93, & 97
2.12.9.17.17.17.30.278.
5.80.
8633066895451305746834838066516601492785
WUCs 51, 52, 63, 71, & 72
R-6
352G MTSM CALCULATIONS
10/85-3/86 4/86-9/86 1
FLY HOURSMTEM/PERIODWUCwucWUCwucwucWUCwucwucwucwucwucwucwucwufWUCwucwucwucwucwucwucwucwucwuc
111 O
13142341424445474951526162636459717291939697
GROUPED11 & 12
WUCs
131423414245495191
4 47& 44
- 72, 93,
*&
.32.742 34,536
97
3.32714. 1375.2437. 1743.588
2.3.96914.01619.6069.210
55.30759.6397.92019.443
134.741
39.40124.674
40.12583.739696.63884.170
85.712
2.54794.73647.08174.592518.30958.98249.621055.48103.7226
41.3999
2.37716.2605.0257.3224.851
25.35717.28521.5049.95656.99051.6238.61922.543124.679
36.08825.227
85.274101.279986.743100.104
54.994
WUCs 5 1 ,
0/86-3/87
33,363
2.87215.3924. 1076.6365.132
28.26617.24217 . 5558.968
- 50.54254.9728.51722.819132.277
30.72922.234
52.017109.235891.132103.874
;/87-3/87
34,899
3.07419.7954.7427.2315. 148
30.93916.94922.04610.44968.69956.4718.84627.350139. C40
35.57522.400
56.471116.719
1,125.774192.812
10/85-9/87
136,040
3.023816. 18934.73647.08174.5925
26.917216.278320.04129.6210
57.255955.48108.469622.7644L32.4636
35. 143623.5485
54.6346101.4466900.9271109.6212
159.731 51.933 71.8270
52, 61, 63, 64, 71, & 72
R-7
SIB MTBM CALCULATIONS
10/87-3/88 4/88-9/88 10/88-3/89 4/89-9/89 10/87-9/89
FLY HOURSMTBM/PERIODWUC 11WUC 12WUC 13WUC 14WUC 23WUC 41WUC 42WUC 44WUC 45WUC 17WUC 49WUC 51WUC 32WUC 61WUC 62WUC 63WUC 64WUC 69WUC 71WUC 72WUC 91WUC 93WUC 96WUC 97
8,304
1.90523.7946.4525.6073.0076.1015.08512.1947.152
35.03851.900159.69243.937
296.571
11,001
1.23521.5714.5843.4592.4734.0944.3678.8934.779
22.87128.42660.44522.314
139.253
12,427
2.42869.42511.C567.6104.6728.3129.37219.88311.31868.28046.894
225.94534.329
203.721
11,676
1.90051.8937.9655.8943.4296.8767.33017.4798.68169.08943.567
353.81819.299
93.408
43,408
1.769634.36936.91565.24543.27085.99456.138813.51847:349840.606140.1923134.807326.3237
148.1501
GROUPED WUCs11 & 1213142341 & 4742 & 44454951 & 5297
1.68296.91565.24543.27085.22344.22177.3498
40.192322.0232148.1501
R-8
Li!CD<ro:HI.
sr CN CN >o r% o CN ^ in CD INCD in CN <-" •rt &• CN N ^ in If}1-1M »O *-i »0 O CN in 0s K" M03 M in •-« O M 0- r-0 -H CD No o o o o o o o <t o ao o o o d o o o a o d
COf*
-iCDCNin04 :
iU
CD in CD CD to 0* 0s hO D* fN Q*Nt1 *"* 0s 0* 0s &* C''i M * " *™* ^o IIT o ~* •** o ^ o in o Hio o o o o o o o «$• •*• 13-O O O O O O O O O O •""•
! I I
(N o in CD t'~i •«-• fN in i-« tN ^in CN O «*" t-> OQ CD O KI •*•' K*t''J •** -O " N O in O 0- CN Ch^ O O O O O ~« <•« CN O CN
O O O O O O O O O O •""
s_o
oS_cs
C7)o
u(U
U.I
UJ
\n1-«li.
IUJ
u.
?1-*
I
i
Ch W N K) «O tN ^ ^ N »-«r i *^ o- >o m r-j CN h> ow o o o o o ^ CM o* oo o o o do o o o o
III CN CM O rt CD O
CM CM N in o <t o w ch inO O O O O O *-i M O
o o o d d d d d d c"I I ! I I I
r-s CD TI TH «j- c> in T-I jxn >o r>i ^ r-4 o to in N wCD vO K) -• O M IN ^H r-4 LOO O O O « O C-4 O O O
i i i i i
aUl-HUI
UJQ.
-0 CN NO K 0--
Uiu «r M -^
i
1-4
SiT
R-9
TECHNOLOGY ADJUSTMENT FACTOR
Overall Aircraft
Perform pairwise comparison between similar aircraftdeveloped at different times (i.e. different technologies).
Determine the annual growth rate in reliability (FHBMA).
Average annual growth rate over several comparisons.
Model: Compound Growth Curve
ADJ FHBMA = FHBMA x {1+ADJ
ACFT
A-7DA-10A
F-4EF-15A
F-4EF-16A
F-4CF-16A
B-52GB-l
FHBMA
1.271.34
.507
.652
.5071.110
.6561.110
.406
.338
DEV YR
6872
6772
6774
6374
5885
DISCOUNTED FHBMA'
1.271.387
.507
.680
1.182
1.224
.534
AVERAGE =
ADJ FAC s
.0220
.0604
.128
.058
.0102
.0557
Notes:
1. 86 represents the baseline year of the data
2. Discounted FHBMAa = A x ( 86-yn+yrz )»
where B = .137 and A = FHBMA2 /(86-YR2)B
(based upon reliability growth curve)
3. ADJ FAC = (DISC FHBMAz/FHBMAi ) 1 / < r r « - y r i > -l
(by solving for the ADJ FAC in the compound growth curve)
R-10
APPENDIX S
R & M Model - BASIC Program Listing
10 'NASA, LANGLEY RESEARCH CENTER20 'MTBM COMPUTATIONAL MODEL - NASA RESEARCH GRANT -30 'DEVELOPED BY C. EBEUNG, UNIV OF DAYTON 2/10/9235 ' »******« COMBINED PRE/CONCEPTUAL MODEL **»*««**«*40'50 'SAVE AS "MTB3.BAS" Mean Time Between Maintenance - MODIFIED60'70 DIM WBS$(2S) 100),NAM$(100),THRS(20) IHMA(20) 1H(20) IP(20),ON1H(20) MH(20)72 DIM GOH(20)OX)H(20),TOH(20),OOH(20),ROH(20),R(20),TSKT(20)73 DIM V(15),SNAM$(15) JTV1AT(20)4'MACX20),FMAS(20),S(20)74 DIM MW(20),C(20),CM(20),OP$(20),TG(20),PWTS(20)75 DIM FMA(20)^F(20)^A(25)^(500),Y(SOO),RR(20),W(20)^IR(20)4'R(20)76RFLG=0 'REPEAT FLAG80'85 GOSUB 1000 'OPENING BANNER87 INPUT "DO YOU WISH TO INPUT FROM A FILE-(Y/N)";ANS$88 IF ANS$="Y" OR ANS$="y" THEN GOSUB ITOthGOTO 10090 GOSUB 500 INITIALIZATION95 GOSUB 12300 'OPTION TO DELETE SUBSYSTEMS100 GOSUB 1050 INPUT MODULE102 IF RFLG=0 OR MODE=0 THEN GOSUB 1500 ELSE GOSUB 1400 'SUBSYS WGTS103 IF RFLG=0 OR MODE-0 OR MODE=1 THEN GOSUB 11120 ELSE GOSUB 11000 'SECONDARY VARIABLES104 GOSUB 1200 'ESTABLISH SUBSYSTEM MTBM CALIBRATION FACTORS105 GOSUB 1600 'DETERMINE MISSION PROFILE110 GOSUB 1300 'DETERMINE SUBSYSTEM HRS111 GOSUB 12400 'ESTABLISH TECH GROWTH FACTORS112 CL&LOCATE 10,20:PRINT "COMPUTING MTBM'S ....."113P1 = .202:P2=.014:P3=.784 . . .114 'ADD=W(l)+W(2)+W(3):P1=W(1)/ADD:P2=W(2)/ADD:P3=W(3)/ADD115 GOSUB 3000 'EVALUATE REGRESSION EQS; DETERMINE UNADJUSTED MTBM & MH/MA120 GOSUB 2500 'PERFORM TECHNOLOGY ADJUSTMENT130 GOSUB 2000 'DETERMINE SPACE ADJUSTMENT140 GOSUB 2700 'DETERMINE CRITICAL FAILURES-MTBM145 GOSUB 2800 'DETERMINE CRTT FAIL RELIABILITY150 GOSUB 9000 'DISPLAY RELIABILITY PARAMETERS160 GOSUB 7000 'COMPUTE MANPOWER REQUIREMENTS170 GOSUB 7500 'DISPLAY MAINTAINABILrrY PARAMETERS175 CLS:LOCATE lO^ftPRINT "COMPUTING SPARES "180 GOSUB 8000 'COMPUTE SPARES REQUIREMENTS190 GOSUB 8500 'DISPLAY SPARES REQUIREMENTS200 GOSUB 9700 'DISPLAY VEHICLE TURN-TIME310TMA12=2257.4-687.44'LOG(W(3))+70.118»LOG(W(3))"2-2J8<LOG(W(3))"3400 CLS405 LOCATE 10^0:INPUT "DO YOU WISH ANOTHER ANALYSIS-<Y/N)";ANS$408 IF ANS$='V OR ANS$=y THEN RFLG=1:GOTO 100409CLS410 LOCATE 10,lfcINPUT "DO YOU WISH TO SAVE FHBMA'S FOR RELIABILITY ANALYSIS - (Y/N)";ANS$420 IF ANSS="Y" OR ANS$="y" THEN GOSUB 9500430 CLS435 LOCATE lO.lftlNPUT "DO YOU WISH TO SAVE INPUT FOR LATER USE - (Y/N)";ANS$440 IF ANS$="Y" OR ANS$=Y THEN GOSUB 9600470 LOCATE 15,25:PRINT "HAVE A NICE DAY"480 COLOR 3490 END500' INITIALIZATION MODULE520 FOR 1=1 TO 16525MW(I)=1526CM(I)=1527 OP$(i)="COMPUTE"
S-l
530 READ WBS$(I)540NEXTI580 FOR 1=1 TO 14590 READ NAM$(I)600NEXTI610 FOR 1=1 TO 12620 READ SNAM$(I)630 NEXT I640 FOR 1=1 TO 16:READ TG(1):NEXT I TECH GROWTH RATES650 FOR 1=1 TO 16:READ PWTS(I):NEXT I WGT DISTR PERCENTS690 ' •••• DEFAULT VALUES700 X(l)=9000! 'DRY WEIGHT - LBS710 X(2) = 100 'LENGTH + WING SPAN - FT720X(3)=2 'CREW SIZE730X(4)=8 'NBR PASSENGERS750 X(5)=1994 TECHNOLOGY YR760 X(6)=.0557 T>EFAULT TECH GROWTH FACTOR770X(7) = .28 -WEIBULL SHAPE PARAMETER780 X(8)=20 'LAUNCH FAILURE RATE FACTOR790 X(9)=144 ' AVAIL HRS PER MONTH800X(10) = .15 'PERCENT INDIRECT WORK810X(11) = .95 'SPARES FILL RATE GOAL815X(12)=1.8 'AVG CREW SIZE816X(13)=1 'PLANNED MSN PER MONTH817 X(14)= 1 "WGHT INDICATOR820T(0)=2:T(1)=.14:T(2) = 1:T(3)=71:T(4)=72830 'PI = J9:P2 = .01:P3=.6 'PRORATION FACTORS FOR WUC11 (WBS 1 A3)
900 'INrriALIZE SUBSYSTEM MSN PROFILES910 FOR 1=1 TO 16920 GOH(I)=T(0):LOH(I)=T(1):TOH(I)=T(2>T(1):OOH(I) =T(3>T(2):ROH(I) =T(4>T(3)921 NEXT I922 TOR 1=1 TO 3:OOH(I)=ftNEXT I923 'GOH(5)=0:OOH(5)=0924 'OOH(12)=0
999'1000 'INPUT MODULE1010 KEY OFRCL&COLOR 111015 IP RFLGS="YES" THEN GOTO 10501020 LOCATE 6,15:PRINT "VEHICLE REUABOJTY/MAINTAINABILrrY MODEL"1030 PRINT.PRINT TAB(20) "NASA - LANGLEY RESEARCH CENTER'1040 LOCATE 14,20:INPUT "ENTER VEHICLE NAME";VNAM$1042 PRINT:PRINT TAB(20) "ANALYSIS MODE"1043 PRINT:PRINTTAB(20) "PRECONCEPTUAI 1"1044 PRINT TAB(20) "SUBSYSTEM WEIGHT DRIVEN™2"1045 PRINT TAB(20) "WEIGHT/VARIABLE DRIVEN_-3"1046 PRINT:INPUT "ENTER CHOICE";MODE
1049 "PRIMARY MENU1050 CL&PRINT TAB(5) "INPUT MODULE - PRIMARY INDEP VARIABLES"1060 PRINT TAB(1) "NBR";TAB(10) "VARIABLE";TAB(35) "CURRENT VALUE"1065 PRINT:PRINTTAB(5) "VEHICLE DRIVER VARIABLES":PRINT1070 FOR 1=1 TO 141075 IF 1=5 THEN PRINT:PRINT TAB(5) "SYSTEM PARAMETER VALUES':PRINT1080 PRINT TAB(1) I;TAB(7) NAM$(I);TAB(35) X(I)1090 NEXT I1100 PRINT:INPUT "ENTER NBR OF VARIABLE TO BE CHANGED - 0 IF NONE";NBR1110 IF NBR=0 THEN GOTO 11351120 INPUT "ENTER NEW VALUE";X(NBR)1130 GOTO 10501135 YR=X(5):B=X(7):LF=X(8):X1=X(1):X2=X(2)
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1137' -1200 'MODULE TO INPUT MOD FACTOR1205 CLS:PRINT TAB(20) "SUBSYSTEM MTBM CALIBRATION FACTOR"1206 PRINT TAB(20) "SPACE VEH-MTBM = CAL FAC x ACFT-MTBM"1210 PRINT TAB(3) "NBR SUBSYSTEM';TAB(45) "CAL FACTOR"1220 PRINT1230 FOR 1=1 TO 161235 IF OP$(I) = "DELETE" THEN GOTO 12501240 PRINT TAB(3) I;TAB(10) WBS$(I) TAB(45) MW(I)1250 NEXT I1260 PRINT:INPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR1265 IF NBR> 16 THEN GOTO 12051270 IF NBR=0 THEN GOTO 12951280 INPUT "ENTER NEW FACTOR";MW(NBR)1290 GOTO 12051295 GOSUB 12200 'ESTABLISH CAL FACTOR FOR MAINT
1300 T>ISPLAY SUBSYSTEM OPERATING TIMES1301 CL&PRINT:PRINT TAB(5) "SUBSYSTEM OPERATING TIMES"1305 PRINT TAB(1) TOTAL MISSION TIME";TAB(20) T(4);" HRS";TAB(30) "MAX GROUND TIME";TAB(50) T(0);" HRS"1306 PRINT TAB(1) "NBR SUBSYSTEM";TAB(30) "GROUND",TAB(38) "BOOSTER";TAB(46) "REM TIME";TAB(S5)"ORBrT;TAB(65) "RECOVERY"1310 PRINT TAB(31) TIME";TAB(40) "nME";TAB(46) "TO-ORBn*;TAB(56) "nME";TAB(65) TIME"1320 PRINT1330 FOR 1=1 TO 161335 IF OP$(I)="DELETE" THEN GOTO 13501340 PRINT TAB(1) I;TAB(7) WBS$(I) TAB(35) GOH(I);TAB(42) LOH(I);TAB(50) TOH(I);TAB(58) OOH(I);TAB(65) ROH(I)1350 NEXT I1360 PRINTiINPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR1365 IF NBR> 16 THEN GOTO 13011370 IF NBR=0 THEN GOTO 13951380 INPUT "ENTER NEW VALUES SEPARATED BY COMMAS";GOH(NBR)^OH(NBR),TOH(NBR),OOH(NBR),ROH(NBR)1390 GOTO 1300
1400 -WEIGHT MENU MODULE1402 IF MODE=1 THEN RETURN1405 CL&PRINT TAB(20) "SUBSYSTEM WEIGHTS"1410 PRINT TAB(3) "NBR SUBSYSTEM";TAB(45) "WEIGHT IN LBS"1420 PRINT1430 FOR 1=1 TO 161435 IF OP$(I)="DELETE" THEN GOTO 14501440 PRINT TAB(3) L-TAB(IO) WBS$(I) TAB(45) W(I)1450 NEXT I1455 PRINT:PRINTTAB(3) "TOTAL WGT";TAB(45) ADD:PRINT1460 PRINTINPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR1465 IF NBR> 16 THEN GOTO 14051470 IF NBR=0 THEN GOTO 1495 C'.':1480 INPUT "ENTER NEW WEIGHT";W(NBR)1484ADD=01485 FOR 1=1 TO 16:ADD=ADD+W(I):NEXT I1486 X1=ADD:X(1)=ADD1490 GOTO 1405
1500 ' MODULE TO COMPUTE SUBSYSTEM WEIGHTS1505 IF X(14)=0 THEN GOTO 15671510W(l)=-«485026.7#+135102i5#*LOG(Xl)-135432!'(LOG(Xl))'>2+4522.4»(LOG(Xl))'>31511 IF W(l)< =0 THEN W(l)=7951515W(2)=-290909.9+91929.4*LOG(X1)-9709.901*(LOG(X1))'>2+343J*(LOG(X1))"31516 IF W(2)< =0 THEN W(2)=3021520W(3)=39713145^+1417950.4#'LOG(X1H04722(»#/SQR(IX>G(X1)>12993808^#»SQR{LOG(X1))1523 IF W(3)< =0 THEN W(3)=21401525 W(5)=^9535!+.282563'XH-6873.7*LOG(X1)-160.1'SQR(X1)
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1526 IF W(5)< =0 THEN W(5)=5271530 W(12)=-9849.5 + .0459666*X1 + 1364.8'LOG(X1>26.248*SQR(X1)1531 IF W(12)< =0 THEN W(12)=1001535 W(9)=-910.4+100.22'LOG(X1)+ 13835*SQR(X1)1536 IF W(9)< =0 THEN W(9) = 1571540 W(14)=-719.15+5.56265*X2+56.882<SQR(X2)1541 IF W(14)< =0 THEN W(14)=631545 W(10)=-757.97+11.222'SQR(X1)1546 IF W(10)< =0 THEN W(10)=3101550 W(ll)=575.27+.022216*X1-5.0608*SQR(X1)1551 IF W(ll)< =0 THEN W(ll) = 1471555 W(15)=6625S.6-14720.4'LOG(X1)+818.19'(LOG(Xl)r21556 IF W(15)< =0 THEN W(15)=2841560 W(13)=-10901.5+ 1261.52'LOG(X1)1561 IF W(13)< =0 THEN W(13)=3031563 W(4)=.ll'Xl:W(6) = .01*X1:W(7)=.04*X1:W(8)=.02*X1:W(16)= .1*X11564 WENG=-7141.92+89.1053*SQR(X1)1565 -W(6)=WENG1567 FOR 1=1 TO 161568 IF OP$(I)=-DELETE" THEN W(I) = 11569 NEXTI1570 -WEIGHT RECONCILIATION1572 ADD=01575 FOR 1=1 TO 16:ADD=ADD+W(I):NEXT I1580 PCT=X1/ADD1586TX1=X11587 SMI=01588 FOR 1=1 TO 161589 IF OP$(I) = 'DELETE" THEN GOTO 15921590 IF X(14)=l THEN W(I)=PCT*W(I) ELSE W(I)=PWTS(I)*TX11591 SM1=SM1+W(I)1592NEXTI1593 DIF=X1-SM11594 IF DIF>1 AND X(14)=0 THEN TX1=TX1 + DIF:GOTO 15871595 ADD=SM11596 GOSUB 1400
1599'1600 -MODULE TO ESTABLISH MISSION PROFILE1615 CL&COLOR 10-.KEY OFF1630 NBR=01635 LOCATE 3,25:PRINT "MISSION PROFILE"1640 LOCATE 7,10:PRINT "NBR";TAB(50) TIME IN HOURS"1645 LOCATE 9,10:PRINT "I" ;TAB(25) "GROUND TIME PRIOR TO LAUNCH";TAB(55) T(0)1650 LOCATE 1L5:PRINT "LAUNCH TIME AT T=0"1655 LOCATE 13,10:PRINT "2" ;TAB(25) "BOOSTER COMPLETION TIME";TAB(55) T(l)1660 LOCATE 14,10:PRINT "3" ;TAB{25) 'ORBrT INSERTION TIME",TAB(55) T(2)1665 LOCATE 15,10: PRINT "4" ;TAB(25) "ORBir COMPLETION TTME-jTABCSS) T(3)1670 LOCATE 16,10:PRINT "5' ;TAB(25) "GROUND RECOVERY TIME";TAB(55) T(4)1675 PRINTiPRINT1680 INPUT -ENTER NUMBER TO BE CHANGED OR 0 IF NONE";NBR1685 IF NBR> 16 THEN GOTO 16151690 IF NBR>0 THEN NBR=NBR-1:INPUT "ENTER NEW TIME";T(NBR):GOTO 16151694 IF RFLG=O THEN GOSUB 900
1699'1700 'MODULE TO READ FROM A FILE1705 INPUT "ENTER FILE NAME";DNAM$1707 LOCATE 5,10:PRINT "INPUT DATA WILL BE READ FROM AN FILE"1708 PRINT1710 OPEN DNAMS FOR INPUT AS #31720 FOR 1=1 TO 16
1725 INPUT #3,WBS$(I),W(I),MW(I),CM(I)1730 INPUT #3,GOH(I),LOH(I),TOH(I),OOH(I),ROH(I)1731 INPUT #3,OP$(I)1735 NEXT I1740 FOR 1 = 1 TO 131745 INPUT #3,NAM$(I),X(I),SNAM$(I),V(I)1750 NEXT I1755 FOR 1=0 TO 41760 INPUT #3,T(I)1765 NEXT I1770 CLOSE #31780 LOCATE 15,10:PRINT "DATA SUCCESSFULLY READ"1785 RFLG=1
1999'2000 'MODULE TO DETERMINE SPACE ADJ MTBM2010YZ=fcYX=l2020 FOR J=l TO 162030 TO=GOH(J):T1=TO+LOH(J):T2=TH-TOH(J)2040 T3=T2+OOH(J):T4=T3+ROH(J)2050 IF OP$(J) = "DELETE" THEN GOTO 21002060 L1 = 1/FMAT(J):L2=LF'L12070 GOSUB 22002080 FMAS(J)= MEAN2090 YZ=YZ+ I/MEAN2095 YX=YX*RT42100 NEXT J2110 SVFMA=1/YZ:VR=YX
2200 'MODULE TO COMPUTE SPACE ADJUSTED MTBM2210 A= (BT(2r(B-l)/Lir(l/B)2220 Al = (1-EXP(-L1*TO))/L12230 A2=EXP(-L1TO)'(1-EXP(-L2*(T1-TO)))/L22240A3=EXP(-U'(Tl-TO))'(EXP(-L2nT))/L2-EXP(-L2'(T2+TO-Tl))/L2)2255 GOSUB 2320 TIND A4 USING SIMPSON'S RULE2260 A4=EXP(-Ll*(T2+TO-Tl>L2*(Tl-TO)+(T2/ArB)*AREA2270 AS = EXP(-L1*(T2 +TO-Tl>L2*(Tl-TOKI3/ArB + (T2/ArB)»(l-EXP(-Ll*(T4-T3)))/Ll2280 MEAN=A1+A2+A3+A4+A52290RT4=EXP(-Ll«(T2+TO-Tl)-L2'(Tl-TO)-(T3/ArB+(T2/ArB-Ll*Cr4-T3))2300 MEAN=MEAN/(1-RT4)
2320 N=INT((T3-T2)/^)2330 IF N=0 THEN AREA=0
2340DX=(T3-T2)/N2350 FX=42360Z(0)=T2:Y(0)=EXP(-(Z(0)/ArB):SUM=Y(0)2370 FOR 1=1 TON
2390 Y(I)=EXP(-(Z(I)/ArB)2400 IF I=N THEN FX=12410 SUM=SUM+FX'Y(I)2420 IF FX=4 THEN FX=2 ELSE FX=42430 NEXT I2440 AREA=DX'SUM/3
2500 TECHNOLOGY ADJUSTMENT MODULE2510 Y=02520 FOR 1=1 TO 162530 IF OP$(I) = "DELETE" THEN GOTO 25602540 FMAT(I) = FMA(I)*(l+TG(I)r(YR-1986)2550 Y=Y+1/FMAT(I)
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2560NEXTI2S70TVFMA=1/Y
2700 'DETERMINE CRITICAL FMA2710 YY=02720 FOR 1 = 1 TO 162730 IF OP$(I) = "DELETE" THEN GOTO 27602740 FMAC(I) = FMAS(I)/PA(I)2750 YY=YY+1/FMAC(I)2760 NEXT I2770 CVFMA=1/YY
2800 'MODULE TO DETERMINE RELIABILITIES - CRITICAL FAILURES ONLY2810 VR=12820 FOR J=l TO 162830 TO=GOH(J):T1 =TO+LOH(J):T2 =T1 +TOH(J)2840 T3=T2+OOH(J):T4=T3+ROH(J)2850 IF OP$(J) = "DELETE" THEN R(J) = 1:GOTO 29002860L1 = 1/FMAC(J):L2=LF'L12870 A=(BT(2r(B-l)/Lir(l/B)2880 R(J)=EXP(-Ll'(T2+TO-Tl)-L2'Cn-TOKr3/ArB+(T2/ArB-Ll-(T4-T3))2890 VR=VR'R(J)2900 NEXT J
3000 'MTBM CALCULATIONS BY WUC3005 PROR=W(4)/(W(1) + W(2)+W(3)+W(4)):PP=1-PROR3010 *WBS 1,2 & 3 AIRFRAME "••3020 FMA11 = 15^3H-.006057»W(2>-.137575'SQR(W(1)+W(2)+W(3)+W(4)>.000723'V(3)3022 EPFMA11<1.4 THEN FMA11 = 1.4302SFMA(I) = FMAH/CPP*P1):FMA(2) = FMA11/(PP*P2) '="3030 MH11 = 16J732-3511567*W(3)/V(2>-.74556«LOG(X1)3031 IF MH1K 3.9 THEN MH=3.9 '- .3032MHMA(1)=MH11:MHMA(2)=MH11 ' C,.:.3040 ABU = .031213+1.956E-07*X1-1.54S6E-04*SQR(X1)3041 IF AB11<=0 THEN AB11=.00128 • . . . • -3042 IF AB11>.02065 THEN AB11=.02065 ; -•3045 PA(1)=AB11:PA(2)=AB11 -3050PF(l)=.0835:PF(2)=.0835:PF(3)=(.0835+.088)/23054 Rll = .1934-6309Bfl7»W(3)3055 R12=.20268+.000588'V(12)3060 RR(1)=R11:RR(2)=R11:RR(3)=(Rll+R12)/23100 -WUC12 AIRCREW COMPARTMENT .............3 1 1 0FMA12 = 3428.49-.0142*XW23.96*LOG(Xl) + 11.05'SQR(X1) + 111J67»X(3>360.72'SQR(X(3))+.01865*W(3>4-83566«SQR(W(3)>^5T85'(X(3)+X(4))3112 IF FMA12<5.6 THEN FMA12=5.6 ' 25TH PERCENTILE RANGE3115TP=P3'PP/FMA11+1/FMA12:FMA(3)=1/TP 'CHECK LINE 3715 FOR FMA(3)3120 MH12=7.0855-1.6667/SQR(X(3) + X(4)) + .098778*(X(2)+X(4))3121 IF MH12<3^ THEN MH12=3.23123 MHMA(3)=((1/FMA11)'MH11+(1/FMA12)*MH12)/(1/FMA11+1/FMA12) -3130AB12=.04232+33775EWX1-2^1883E-04*SQR(X1)3131 IF AB12>.02 THEN AB12=.023135 PA(3)=(AB11/FMA1H-AB12/FMA12)/(1/FMA11+1/FMA12)3200 WUC13/WBS5 LANDING GEAR SYSTEMS ••••••••••••••••3210 SMA13=22J723-.00313*V(3)+.19511'X2^S.47476'SQR(V(4))+.003161*W(5)- 171441*SQR(W(5))3211 TMA(5)=SMA13*(GOH(5)+LOH(5) +TOH(5)+OOH(5)+ROH(5))3212 IF SMA12<.4 THEN SMA12=.43213 FMA(5)=72.4+14J68*V(4)+.0994»X2-1Z41<LOG(X1>65.6»SQR(V(4)>.00568»W(5)+18J98'LOG(W(5))3214 IF FMA(5) < 1.4 THEN FMA(5)=1.43215 TMA(5)=SMA13'(GOH(5)+LOH(5) +TOH(5) + OOH(5)+ROH(5))3220 MHMA(5)=-156.95 -h55.984'LOG(W(5))-6.095'(LOG(W(5)))"2+^12817'(LOG(W(5)))'>33221 IF MHMA(5) < 1.9 THEN MHMA(5)=1.9
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3230 AB13=-2.4321 + .0059112«X2+1.1457'LOG(X2)-33925*SQR(X2)3231 IF AB13<0 THEN PA(5) = .0018S ELSE PA(5)=AB133232 IF PA(5)>.08 THEN PA(5) = .083250 PF(5) = .02774-4.07E-06*X1-.00194'X2+.19316*SQR(V(4)) + .OOT156'SQR(W(13))3251 IF PF(5)<.134 THEN PF(5) = .1343252 IF PF(5) > .54 THEN PF(5) = 343260 RR(5) = .8639-.02963'X23261 IF RR(S)<.22 THEN RR(5) = .223300-WUCM WBS 12 FLIGHT CONTROLS ••••3310 FMA(12) = 26.29-1.1136*SQR(W(12)) + .9516»V(5)-1.9'V(6) + 3S05'X2-.00357*V(3)3312 IF FMA(12)<2.8 THEN FMA(12)=2.83320 MHMA(12)=26-238-1.1067*V(5>1.6658*V(6>.00328»V(3) + .0006018'X2-6J827*LOG(W(12)) + 14.289»SQR(V(5))3321 IF MHMA(12)<2.1 THEN MHMA(12)=2.13330 AB14=.7119S3-.1881388*LOG(X2) + .0209882*SQR(X2)3331 IF AB14<0 THEN PA(12)=6.000001E-04 ELSE PA(12)=AB143332 IF PA(12) > .08128 THEN PA(12) = .081283350 PF(12)=5.51246+.002663*V(5)-.000566'W(12)-1.193*LOG(W(12))+-105S6*SQR(W(12))3351 IF PF(12)<-04 THEN PF(12) = .043352 IF PF(12) > 39 THEN PF(12) = 293360 RR(12) = .4527-.0006677*X23361 IF RR(12)<0 THEN RR(12) = .073400 "ffVC2A APU3410 FMA(9) =4996-525-1.906'V(7)+4635'SQR(V(7)>2.735*W(9)+284^49'SQR(W(9))-1642.99'LOG(W(9))3411 IF FMA(9)<14.5 THEN FMA(9) = 1433420 MHMA(9)=^51.4+.09054*V(7>2.9654»SQR(V(7)) + -2657«W(9>26.1'SQR(W(9)) + 1503*LOG(W(9))3421 IF MHMA(9)<5.2THEN MHMA(9)=523440 PA(9) = .0643 4 5 0PF(9)=-109£3-.1645'LOG(Xl)+.1427*V(7)-6.1517*SQR(V(7)) + 15.751*LOG(V(7))+.066'W(9)-5.6832'SQR(W(9))+29.071 «LOG(W(9))3451 IF PF(9) < .03 THEN PF(9) = .033452 IF PF(9) > 39 THEN PF(9) = 393460 RR(9)=^79-.0007512*SQR(X1)3461 IF RR(9)<0 THEN RR(9)=.013500'WUC41/47 WBS14 ENVIRONMENTAL CONTROL •••••••3510'FMA(14)=34.08071-.42487*W(14r2 ;
3511 FH41=454J87-.000547*XH- 21'X2-1073185<LOG(X2)3512FH47=6613.12-1.485*X2-13583'LOG(X1)+73J8'(LOG(X1))'>2-.72S852*X1/X23513 Z=1/FH41-H/FH47:FMA(14) = 1/Z3515 IF FMA(14)<7.68 THEN FMA(14)=7.683520 MH41=.6886774'LOG(X1)3521 MH47=5.7432+.018525'LOG(X1>3J6575E-03'SQR(X1)3522 MHMA(14)=(MH41/FH4H-MH47/FH47)/(1/FH41-H/FH47)3523 IF MHMA(14)<1! THEN MHMA(14)=1!3530 PA(14)=.082199+5.0072E-07'XW.0612B04*SQR(X1)3531 IF PA(14) < 0 THEN PA(14)=.001523532 IF PA(14)>.05222 THEN PA(14) = .052223550 PF47=23.852-.00902*X2-5 J47*LOG(X1)+J01'LOG(X1)"2-.00212'X1/X23551 IF PF47< .02 THEN PF47=.023552 IF PF47>33 THEN PF47=333553 PF(14)=(.0932/FH41 + PF47/FH47)/(1/FH41+1/FH47)3555 R41 = J294-8.914E4)5*W(14)3556 IF R4KO THEN R41 = .1683557 R47=.6026-.0006758'SQR(X1)3560 RR(14)=(R41/FH41 + R47/FH47)/(1/FH41+1/FH47)3600 •WUC 42/44 WBS 10 ••• ELECTRICAL SYS ••••••3 6 1 0FMA(10)=1193.13-.0755»W(10)+6.758773*SQR(W(10))-.715596*X2-167.24'LOG(X1)+2^308*SQR(X1)+29.10236'LOG(V(7))-.00127'VC7T23611 FH44=13613FH42=13614 IF FMA(10)<5.15 THEN FMA(10)=5.153620'MHMA(10)=-183923+1694.6'LOG(Xl)-92Atl2'(LOG(Xl))"2+27629/SQR(LOG(Xl))+2*LOG(Xl)'v3
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3621 MH42 = -95.161 + 20 J158'LOG(X1>.98356'(LOG(X1))"23622MH44=2m04+474.11'I^G(XlM52395'IX>G(X2>.146285*Xl/X2-2769^^3623 MHMA(10)=(MH42+MH44)/23624 IF MHMA(10)<1! THEN MHMA(10)=4.13630 PA(10) =-39.95984 + 11.09214'LOG(X1)-1.0178226#*LOG(X1)'S2 + .0309075«LOG(X1)"33631 IF PA(10)< =0 THEN PA(10)=. 002483632 IF PA(10)>.142 THEN PA(10) = .1423650PF42=-26^65-.00271'V(7)+.005143'W(10)-.74878*SQR(W(10))+6.62irLOG(W(10))3651 IF PF42<.054 THEN PF42=.0543652 IF PF42>.53 THEN PF42=.533653 PF44 = 3.061 + 1.178E-05'X1-.000127* V(3)-.42392*LOG(X1) + .13468*SQR(X2)3654 IF PF44<.03 THEN PF44=.033655 IF PF44>.47 THEN PF44 =.473656 PF(10)=(PF42/FH42+PF44/FH44)/(1/FH42-H/FH44)3660RR42=-38533-.001»X2 + .17715'LOG(X2) -3661 IF RR42<.23 THEN RR42=.23:IF RR42>.539 THEN RR42=.5393662RR44=2.3651+.00201»X2-.41152*LOG(X2)3663 IF RR44<.S3 THEN RR44=.53:IFRR44>.872 THEN RR44=.8723665RR(10)=(RR42/FH42+RR44/FH44)/(1/FH42-H/FH44)3700 ""'WBS4 THERMAL PROTECTION SYSTEM .........3710 FMAC4)=FMA11/PROR3720 MHMA(4) = MH113730 PA(4) =AB11:PF(4) = .0835:RR(4) = ,1943800 WUC45 WBS11 HYDRAULICS SYS ..................381<FMA(11) = 396.2S8-.00622*V(3) + 35.635'V(8>779.83'SQR(V(8)) +975 -56'LOG(V(8)) + 8.812899*SQR(W(11))-105.728'LOG(W(11))3812 IF FMA(11)<4.7 THEN FMA(11)=4.73820 MH45=2.41235'LOG(X1)-.16306'LOG(X1) 23821 MHMA(11)=MH453822 IF MHMA(11)<2.4 THEN MHMA(11)=2.43830 PA(ll)=5000J535#-7578.183/SQR(IX)G(Xl)H53.612*LOG(Xl)+24^005*LOG(Xl)A2- 276227'LOG(Xl)/<33831 IF PA(11) < =0 THEN PA(11) = .000843832 IF PA(11) > .1304 THEN PA(11) = .130438SOPF(11) = .07614-.00181*X2+.001543*SQR(X1) . . . . . .3851 IF PF(11)<. 014 THEN PF(11)=. 0143852 IF PF(11)>33 THEN PF(11)=333860 RR(11)= 3683900'WBS13 AVIONICS «•••••«•««•»«••••3910 FMA(13)=-36.917-4J*V(10)+45.756*SQR(V(10)>.123088*W(13)/V(10)-h.0236«W(13>2.4534'SQR(W(13))3912 IF FMA(13) < 15 THEN FMA(13) = 153920 MHMA(13) = 131395 + 1.0394*V(11)-9.035'SQR(V(10))-.01S4*W(13) + 2 64*SQR(W(13)>26.193'LOG(W(13))3921 IF MHMA(13)<4.6 THEN MHMA(13)=4.63930 PA(13) = .0502749+1605132E-07»X1-2J88197E-04'SQR(X1)3931 IF PA(13)<0 THEN PA(13)=. 001523932 IF PA(13) > .02376 THEN PA(13) = .023763950 PF(13) = 7. 1662 + .0209* V(l 1)-.00128*W(13) + .1774*SQR(W(13))-L734*LOG(W(13)) + .0067 V(13)/V(10)3951 IF PF(13)<. 193 THEN PF(13)=. 1933952 IF PF(13) > .532 THEN PF(13) = 5323960 RR(13) = 3973£4.2659E-07*X1+2.163S&O4*SQR(X1)3%1 IF RR(13)<0 THEN RR(13)= J353962 IF RR(13)>.726 THEN RR(13)=.7264000 WUC49 MISC UmJTIES .......................4010 ' WUC49/96 WBS15 PERSONNEL PROVISIONS ................4 0 2 0
054'LOG(W(15))
4023 IF FMA(15) <46.7 THEN FMA(15) =46.74030MHMA(15)=951317+.03508»X2-.000721*W(15H-52'SQR(X(3))4031 1MH49=.0831*LOG(X1)"2-.0116*X1/X24033 IF MHMA(15)<23 THEN MHMA(15)=2J4040 PA(15)=. 01854050PF49=.19888+4.938&fl6'Xl-.00205*SQR(Xl)+.0004877*V(7)
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4051 IF PF49<.002 THEN PF49 = .0024052 IF PF49>.45 THEN PF49=.454053 PF96=-5.4686+ .1683S'X2-.00448*V(3) + .36521 •X(4>4-1528*SQR(X(4)) +• .178*SQR(W(15))4054 IF PF96<.23 THEN PF96=.234055 IF PF96>.98 THEN PF96=.984057 PF(15) = (PF49 + PF96)/24060 RR(15) = .2744100 •• ..... WUC23 PROPULSION SYSTEM *"* WBS 6, 7 & 8 ........4160 FOR 1=6 TO 84161 RR(I) = .6211-.0024872*SQR(W(I))4162 IF RR(I)<.157 THEN RR(I)=.1574163 'IF RR(D>.5120001 THEN RR(I) = .51200014165 PF(I) = 1.14633 +4.572E-05*W(I)-.0114S6*SQR(W(I))4166 IF PF(I)< 2 THEN PF(I) = .24167 IF PF(I)>.725 THEN PF(I)=.7254170 FMA(I)=34.H-9.853001E-04*W(I)-.312232'SQR(W(I))4171 IF FMA(I) < 1.4 THEN FMA(I) = 1.44175 MHMA(I)=52.6324+.0009122*W(I>3936'SQR(W(I))4176 IF MHMA(I)<4.1 THEN MHMA(I)=4.14178 PA(I)=.048164-.0001268'X24179 IF PA(I)<.0013 THEN PA(I)=.00134180 NEXT I4200 ' WUC91/93/97 WBS 16 ..... RECOVERY & AUX SYS ••••••••4210 FMA(16) = 7549.1-.0165«X1 +4*X2-999.76*LOG(X1) + 16.847*SQR(X1>4-225*(X(3) + X(4))4211 IF FMA(16)<17.9 THEN FMA(16) = 17.94220 MHMA(16) = -57.9 + 1.4639E-04*X1 + 8.23732*LOG(X1)-.151436*SQR(X1)4221 IF MHMA(16)<1.7 THEN MHMA(16) = 1.74230 PA( 16) = .0046784253 PF91=4.654-.45718*LOG(X1)+.00242'SQR(X1)4254 IF PF9K.011 THEN PF91=.0114255 IF PF91:>.84 THEN PF91=At4256 R97=2.532-.22837*LOG(V(3))4257 PF(16) = (PF91 + .287+ .01)/34258 IF R97<0 THEN R97=.1284260 R91=23489-35852»LOG(X(2))4261 IF R9KO THEN R91 = . 461 'SET EQUAL TO MEAN VALUE4262 IF R91>1 THEN R91 = .4614263 IF R97>1 THEN R97=.9684265 RR(16)=KR91 + R97)/24300 'APPLY MTBM & MHMA CALIBRATION FACTORS4310 FOR 1 = 1 TO 16
4325 MHMA(I) = CM(I)<MHMA(I)4330 NEXT I5500 'SCHEDULED MAINTENANCE MODULE5540 SCHP = -3.861213-.0449'X2 + 3^794'LOG(X1) + .02297*SQR(X1)-.0176»LOG(X1)'>3-7.289«LOG(X2) + 2J6973'SQR(X2)5550 IF SCHP<.17THEN SCHP=.175560 IF SCHP>.665 THEN SCHP=.6655569'5570 •VEHICLE ROLL-UP - UNADJUSTED MTBM5575 Y=05580 FOR 1=1 TO 165590 IF OP$(I)= "DELETE11 THEN GOTO 56105600Y=Y + 1/FMA(I)5610 NEXT I5620VFMA=1/Y
6999'7000 "MANPOWER COMPUTATION MODULE ......7005 TMA=ftVMH=fcAMHMA=ftIK=ftTOMH=0:TFMH=0-.APF=0:TMP=07010 MANF=(4.348'5'8)/(X(9)'(1-X(10))) 'HRLY AVAIL FACTOR7020 FOR 1=1 TO 16
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7030 IF OP$(I) = -DELETE" THEN GOTO 71407035KK=KK+17040 THRS(I)=GOH(I)+LOH(I)+TOH(I)+OOH(I) + ROH(I)7045 MA=THRS(I)/FMAS(I)7046 TMA=TMA+MA7050 MH(I)=MA'MHMA(I)7055 AMHMA=AMHMA+MHMA(I)7060 VMH=VMH+MH(I)7070 MEN=(MH(I)'X(13))/(X(9)*(1-X(10)))7080 MP(I)=INT(MEN+.999)7085 TMP=TMP+MP(I)7090 OMH(I)=(1-PF(I))*MH(I)7100 FMH(I)=PF(I)'MH(I)7110 TOMH=TOMH+OMH(I)7120 TFMH=TFMH+FMH(I)7130APF=APF+1-PF(I)7135 VMOH=VMOH+MH(I)*X(13)7140 NEXT I7150 APF=APF/KK7160 AMHMA=AMHMA/KK7170 SMP=(SCHP*VMH*X(13))/(X(9)*(1-X(10)))7180 SMP=INT(SMP+.99)7190 TMP=TMP+SMP
7499'7500 ' DISPLAY MODULE FOR MAINTAINABILrrY REPORT7510 CLS:COLOR 147520 PRINT TAB(25) "MAINTAINABILTY REPORT"7530 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE ";DATE$;TAB(60) TIME: ";TIME$7548 COLOR 77550 PRINT TAB(1) "WBS";TAB(32) "MANHR/MA";TAB(50) TOT MA";TAB(65) TOT MANHRS"7555 PRINT7570 FOR 1=1 TO 167580 IF OP$(I)="DELETE" THEN GOTO 75927590 PRINT TAB(1) WBS$(I);TAB(32) MHMA(I);TAB(50) THRS(I)/FMAS(I);TAB(65) MH(I)7592 NEXT I7593 PRINT:COLOR 117594 PRINT TAB(5) "SCHEDULED";TAB(65) SCHP'VMH7595 COLOR 157600 PRINT TAB(5) TOTALS";TAB(32) AMHMA;"(AVG)";TAB(50) TMA;TAB(65) VMH+SCHP'VMH7610 COLOR 147620 INPUT "ENTER RETURN TO CONTINUE_";RET7640 CL&COLOR 147650 PRINT TAB(25) "MAINTAINABILTY REPORT - page 2"7660 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE: ";DATE$;TAB(60) TIME: ";TIME$7680 COLOR 77690 PRINT TAB(1) "WBS";TAB(32) "ON-VEH MH";TAB(47) "OFF-VEH MH";TAB(60) "PERCENT ON-VEH"7700 PRINT7710 FOR 1=1 TO 167720 IF OP$(I)='DELETE" THEN GOTO 77407730 PRINT TAB(1) WBS$(I);TAB(32) OMH(I);TAB(50) FMH(I);TAB(65) 1-PF(I)7740 NEXT I7750 PRINTiCOLOR 77755 PRINT TAB(5) "SCHEDULED";TAB(32) .98«SCHP*VMH;TAB(50) .02'SCHP*VMH7760 COLOR 157770 PRINT TAB(5) TOTALS";TAB(32) TOMH+.98»SCHP*VMH;TAB(50) TFMH+.02'SCHP*VMH;TAB(65) APF;"(AVG)"7780 COLOR 147790 INPUT "ENTER RETURN TO CONTINUE_",-RET7800 CL&COLOR 147810 PRINT TAB(25) "MAINTAINABILrV REPORT - page 3"7820 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB{35) "DATE: ";DATE$;TAB(60) TIME: ";TIME$7830 'PRINT TAB(1) "MNHR ADJ FAC";MANF
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7840 COLOR 77850 PRINT TAB(1) "WBS";TAB(30) "MANHRS/MSN";TAB(45) "MANHRS/MO";TAB(60) "NBR PERSONNEL"7860 PRINT7870 FOR 1=1 TO 167880 IF OP$(I) = "DELETE" THEN GOTO 79007890 PRINT TAB(1) WBS$(I);TAB(30) MH(I);TAB(45) X(13)'MH(I);TAB(60) MP(I)7900NEXTI7910 PRINT:COLOR 117915 PRINT TAB(5) "SCHEDULED";TAB(30) SCHP*VMH;TAB(45) X(13)'SCHP*VMH;TAB(60) SMP7920 COLOR 157930 PRINT TAB(5) "TOTAL";TAB(45) VMOH;TAB(60) TMP:COLOR 147932 'PRINT TAB(5) "AVAIL HRS/MO = ";X(9);TAB(40) "INDIRECT WORK=";X(10)7940 COLOR 147950 INPUT "ENTER RETURN TO CONTINUE...";RET
7999'8000 'SPARES CALCULATIONS8010 ARR=0:TS=0:KK=0:TNR=08020 FOR 1=1 TO 168030 IF OP$(I)="DELETE" THEN GOTO 81808040NR(I) = RR(I)«(THRS(I)/FMAS(I)) ' MEAN NBR REMOVALS8045MN=NR(I)8050 GOSUB 8300 'COMPUTE FILL RATE RQMT - POISSON DISTR8055S(I)=STK:FR(I) = F8060 TNR=TNR+NR(I)8150 ARR=ARR+ RR(I)8160TS=TS+S(I)8170KK=KK+18180 NEXT I8190 ARR=ARR/KK
8300 ' COMPUTE SPARES USING POISSON DIST8310 P=EXP(-MN)8320 IF P> =X(11) THEN JD=1:GOTO 83708330JD = 1:F=P8340P=P'MN/JD8350JD=JD+1:F=F+P8360 IF F<X(11) THEN GOTO 83408370STK=JD-1
8499'8500 ' DISPLAY SPARES RESULTS8510 CL&COLOR 148520 PRINT TAB(25) "SUBSYSTEM SPARES REPORT"8530 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE: ";DATE$;TAB(60) "TIME: ";TIME$8545 COLOR 78550 PRINT TAB(1) "WBS":TAB{25) "REM RATE";TAB(38) "AVG DEMAND";TAB(50) "SPARES RQMT";TAB(65) "FILL RATE"8555 PRINT8570 FOR 1=1 TO 168580 IF OP$(I)="DELETE" THEN GOTO 86008590 PRINT TAB(1) WBS$(I);TAB(30) RR(I);TAB(41) NR(I);TAB(56) S(I);TAB(65) FR(I)8600NEXTI8610 PRINT8620 COLOR 158630 PRINT TAB(5) TOTALS";TAB(27) ARR;"(AVG)";TAB(43) TNR;TAB(55) TS8640 INPUT "ENTER RETURN TO CONTINUE_.";RET
8999'9000 •••••• DISPLAY MODULE FOR RELIABILITY REPORT ••9010 CL&COLOR 149020 PRINT TAB(25) "RELIABILITY REPORT"9030 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE: ";DATE$;TAB(60) TIME: ";TIMES
S-ll
9048 COLOR 79050 PRINT:PRINTTAB(1) "WBS*;TAB(2S) "CALIBRATED MTBM";TAB(48) TECH ADJ";TAB(61) "SPACE ADr9055 PRINT9070 FOR 1 = 1 TO 169080 IF OP$(I) = "DELETE' THEN GOTO 90929090 PRINT TAB(1) WBS$(I);TAB(35) FMA(I);TAB(48) FMAT(I);TAB(61) FMAS(I)9092NEXTI9093 PRINT9095 COLOR 159100 PRINT TAB(5) "VEfflCLE";TAB(35) VFMA;TAB(48) TVFMA;TAB(61) SVFMA9105 COLOR 149110 INPUT "ENTER RETURN TO CONTINUE_";RET9120 CL&COLOR 149130 PRINT TAB(20) "RELIABILrry REPORT - page 2"9140 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE ";DATE$;TAB(60) "TIME: ";TIME$9160 COLOR 79170 PRINT TAB(1) "WBS";TAB(33) "CRrnCAL";TAB(48) "CRrnCAL";TAB(65) "SUBSYS"9171 PRINT TAB(33) "FAIL RATE";TAB(48) "MTBM";TAB(65) "MSN RELIABILITY"9180 PRINT9190 FOR 1 = 1 TO 169200 IF OP$(I)="DELETE" THEN GOTO 92209210 PRINT TAB(1) WBS$(I);TAB(33) PA(I);TAB(48) FMAC(I);TAB(65) R(I)9220NEXTI9230 PRINT9240 COLOR 159250 PRINT TAB(5) "VEfflCLE";TAB(48) CVFMA;TAB(6S) VR9260 COLOR 149270 INPUT "ENTER RETURN TO CONTINUE.»";RET
9500 "MODULE TO WRITE FHBMA TO A FILE9520 INPUT "ENTER FILE NAME";DNAM$9530 OPEN DNAMS FOR OUTPUT AS #19540 FOR 1=1 TO 169550 WRITE #1,FMAT(I),FMAS(I),FMAC(I)9560NEXTI9570 CLOSE #1
.:-?
9600'MODULE TO WRTTE INPUT DATA TO A FILE9605 INPUT "ENTER FILE NAME";DNAM$9610 OPEN DNAMS FOR OUTPUT AS #29615 FOR 1=1 TO 169620 WRITE #2,WBS$(I),Wa),MW(I),CM(I)9621WRTTE #2,GOH(I) JX)H(I),TOH(I)IOOH(I),ROH(I)9622 WRITE #2,OP$(I)9625 NEXT I9630 FOR 1 = 1 TO 139635 WRITE #2J<IAM$(I),X(I),SNAMS(I),V(I)9640NEXTI9645 FOR 1=0 TO 49650 WRITE #2,T(I)96S5NEXTI9690 CLOSE #2
9700 'MODULE TO DISPLAY VEHICLE TURN TIME9703 GOSUB 12000 'COMPUTE CREW SIZES9705 TT=09706 SUM=0:CT=09710 FOR 1=1 TO 169715 IF OP$(I) = "DELETE" THEN GOTO 97359716 CT=CT+19720TSKr(I)=(l-PF(I))'MHMA(I)/C(I) 'ON-EQUIP TASK TIME9730 TT=TT+(THRS(I)/FMAS(I))'TSKT(I)
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9733 SUM=SUM+TSKT(r)9735NEXTI9740 SCHT=.98*SCHP*VMH/X(12)9750 GTr=TT+SCHT:ATSK=SUM/CT9800 ' DISPLAY VEHICLE TURN TIME9810 CL&COLOR 149820 PRINT TAB(25) "VEHICLE TURN TIME REPORT"9830 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE ";DATE$;TAB(60) "TIME: ";TIME$9840 PRINT9845 COLOR 79850 PRINTTAB(1) "WBS";TAB(22) "AVG CREWSEZE";TAB(40) "AVG (ON) TASK TIME (HRS)";TAB(57) "AVG ON-VEH CLOCKHRS"9855 PRINT9870 FOR 1=1 TO 169880 IF OP$(I)="DELETE" THEN GOTO 99009885 TEMP=(THRS(I)/FMAS(I))TSKT(I)9890 PRINT TAB(1) WBS$(I);TAB{30) C(I);TAB(45) TSKT(I);TAB(59) TEMP9900NEXTI9910 PRINTiINPUT "ENTER RETURN.....";RET9920 CL&COLOR 149921 PRINT TAB(25) "VEHICLE TURN TIME REPORT - page 2"9922 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE: ";DATE$;TAB(60) "TIME: ";TIME$9923 PRINT9924 COLOR 15:PRINT:PRINT TAB(52) "MAX TURN TIMES":PRINT9925 PRINT TAB(5) "AVG VEH TASK TIME";TAB(55) ATSK;"HRS"9930 PRINT TAB(5) "SCHD MAINT MSN TASK TIME";TAB(55) SCHT.'HRS"9931 PRINT TAB(5) "MAX TURN TIME NO SCH MAim*;TAB(55) TT;"HRS"9932 PRINT TAB(5) "MAX TURN TIME WITH SCH MAINT";TAB{55) TT+SCHT;"HRS"9940 PRINT TAB(5) "MISSION TIME -INC GRND TIME";TAB(55) T(0)+T(4);"HRS"9945 VTT=T(0)+T(4)+OTT+SCHT9946 DVTT=(T(0)+T(4))/24+(OTr+SCHT)/89950 PRINT TAB(5) TOT VEHICLE TURNAROUND TIME";TAB(55) VTT;'HRS"9951 PRINT TAB(5) "TOT VEHICLE TURNAROUND TIME";TAB(55) DVTT;"DAYS"9955 PRINT TAB(5) "MISSIONS/MONTH/VEHICLE";TAB(55) 21/DVTT9960 PRINT TAB(5) "FLEET SIZE ";TAB(55) INT(X(13)/(21/DVTr)+.99)9985 LOCATE 21,10:INPUT "ENTER RETURN TO CONTINUE...";RET
10000 'INPUT DATA10005 DATA 1.1 WING GROUP.1.2 TAIL GROUP.13 BODY GROUP,1.4 TPS10010 DATA 1.5 LANDING GEAR.1.6 PROPULSION,1.7 PROPULSION-RCS10020 DATA 1.8 PROPULSION-OMS,1.9 PRIME POWER.1.10 ELECTRIC CONV/DISTR10030 DATA 1.11 HYDRAULICS/PNEUMATICS,1.12 ACTUATORS,1.13 AVIONICS10040 DATA 1.14 ENVIRONMENTAL CONTROL.1.15 PERSONNEL PROVISIONS10050 DATA 1.16 RECOVERY & AUX SYSTEMS10150 DATA DRY WOT (LBS),LENGTH+WING SPAN (FT),CREW SIZE^BR PASSENGERS10152 DATA TECHNOLOGY YR10155 DATA DEFAULT TECH GROWTH FACTOR, WffiBULL SHAPE PARAMETER10160 DATA LAUNCH FACTORAVAIL MANHRS/MONTILPERCENT INDIRECT WORK10170 DATA SPARE FILL RATE OBJAVG CREW SEE-SCHD MAINT,PLANNED MISSIONS/MONTH10180 DATA WGTIND O-PCT/1-EQS11000 CLS:PRINT:PRINT TAB(5) "SECONDARY INDEP VARIABLEy:PRINT11005 IF MODE=1 OR MODE=2 THEN RETURN11010 PRINT TAB(1) "NBR";TAB(10) "VARLABLE";TAB{35) "CURRENT VALUE'11020 PRINT11040 FOR 1=1 TO 1211050 PRINT TAB(1) I;TAB(7) SNAM$(I);TAB(35) V(I)11060 NEXT I11070 PRINT:INPUT "ENTER NBR OF VARIABLE TO BE CHANGED - 0 IF NONE";NBR11075 IF NBR>16 THEN GOTO 1100011080 IF NBR=0 THEN RETURN11090 INPUT "ENTER NEW VALUE";V(NBR)11100 GOTO 11000
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11110 '11120 'SUBROUTINE TO COMPUTE SECONDARY VARIABLES11122'WETTED AREA11123 V(3)=486.026+.1510165'X(2)*211130 'NBR WHEELS11140 V(4)=2.189572+6.66297E-OS*X(1)-138718E-10'X(1)*211150 V(4)=CINT(V(4))11160 IF V(4)<3 THEN V(4)=311170 'NBR CONTROL SURFACES11180 V(6)=3.588737+.0005281 *X(1) + .09493*X(2>.00517«V(3)11190 IF V(6)<6 THEN V(6)=611200 V(6)=INT(V(6))11210 "NBR ACTUATORS11220 V(5)= l-.001425'Xl+2.0752E 'Xrc+.007467*V(3H.0377*SQR(11230 IF V(5) <5 THEN V(5) =511240 V(5)=INT(V(5))11280 'KVA MAX11290 V(7)=-214.812-K001098*X(1)+25.1571'LOG(X(1))11300 IF V(7)<11 THEN V(7) = ll11340'NBR AVIONICS SYSTEMS (TOTSUBS)11350 V(10)= 0.4242-1.879E-05»X(1)+6.192823*U>G(X(1))11360 IF V(10)<9 THEN V(10)=911370 V(10) = ONT(V(10))11420 "NBR DIFFERENT AVIONICS SUBSYSTEMS11430 V(ll)=9.674-1.858»LOG(X(l)) + .87684* V(10)+1.4557*LOG(W(13))11440 IF V(ll)<5 THEN V(11)=5:IF V(ll)>V(10) THEN V(ll)=V(10)11450 V(ll) = ONT(V(11))11460 'BTU COOLING11470 V(12)=-1114.52-12.0178*X2+.0094G5'X2*2+230.872*SQR(X2)11480 IF V(12)<25 THEN V(12)=2511490 "MAX PERSONS = CREW + PASSENGERS11500 X(62)=X(7)+X(8) -11510 "NBR HYDRAULICS SUBSYSTEMS11520 V(8)=13.48-.56854'X2+.002409»V(3)+.433276>SQR(X1) ' ~' '11530 IF V(8)<8 THEN V(8)=811540 V(8)=ONT(V(8)) :11550'NBR INTERNAL FUEL TANKS11560 V(9)=-13.2236+1.851772*LOG(X(1))11570 IF V(9)<2 THEN V(9)=211580 IF V(9)>12 THEN V(9) = 1211590 V(9)=CINT(V(9))11620 "FUSELAGE AREA11630 V(l)=-«832.74+.082862'X(l) + 1274.76«LOG(X(l)).32.456'SQR(X(l))11640 IF V(l) <478 THEN V(l) =47811650 'FUSELAGE VOLUME11660 V(2)=-47618^+22143'LOG(X(2)>5743.09»SQR{X(2)) + .42623'X(2)"211670 IF V(2) <571 THEN V(2) =57111680 GOSUB 11000 'DISPLAY MENU
11700 DATA FUSELAGE AREA^FUSELAGE VOLUME,WETTED AREAlino DATA NBR WHEELSJJBR ACTUATORS,NBR CONTR SURFACESJCVA MAX11720 DATA NBR HYDR SUBSYSJMBR FUEL TANKS (INTERNAL) l"11730 DATA TOT NBR AVIONICS SUBSYS ;
11740 DATA NBR DIFF AVIONICS SUBSYS3TU COOLING ;
11750 TECH GROWTH RATES r
11760 DATA .082 082 082 082 033 011 011 011 054,0 092 05611770 DATA .2i.0062,036,.08311780 "WGT DISTRIBUTION PERCENTAGES11790 DATA .091,.003r140,.099,.053,.019,.029,.017,.151r.05911800 DATA .021,.007,.061,.083,.070,.09712000 'CREW SIZE CALCULATIONS12110 C(l)=1 -.000032'V(3)+.009172*SQR(V(3))
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12120 C(2)=C(1):C(3)=C(1):C(4)=C(1) ,12130 C(12)=C(1):C(5)=C(1)12140 C(6)=2.43:C(7)=2.43:C(8)=2.4312150 C(9)=2.4312160 C(10)=-1.48-.002833*X2-t-.814656*LOG(X2)12170 C(ll) = C(10):C(14) = C(10)12180 C(13)=2.1812190 C(16) = 1.7893+9.871999E-04'SQR(X1)12195 C(15)=(C(10)+C(16))/2
12199'12200 'MODULE TO INPUT MOD FACTOR FOR MAINTENANCE12202 COLOR 912205 CL&PRINT TAB(20) "SUBSYSTEM MH/MA CALIBRATION FACTOR"12206 PRINT TAB(20) "CAL MH/MA = CAL FAC x COMPUTED-MH/MA"12210 PRINT TAB(3) "NBR SUBSYSTEM";TAB(45) "CAL FACTOR"12220 PRINT12230 FOR 1 = 1 TO 1612235 IF OP$(I) = "DELETE' THEN GOTO 1225012240 PRINT TAB(3) I;TAB(10) WBS$(I) TAB(45) CM(I)12250 NEXT I12260 PRINT:INPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR12270 IF NBR=0 THEN GOTO 1229512280 INPUT "ENTER NEW FACTOR";CM(NBR)12290 GOTO 12205
12300 ' MENU TO DELETE A SUBSYSTEM12305 CLS:PRINT TAB(20) "OPTION TO DELETE A SUBSYSTEM":PRINT12310 PRINT TAB(3) "NBR SUBSYSTEM";TAB(45) "OPTION"12320 PRINT12330 FOR 1=1 TO 1612335 IF OP$(I)="DELETE" THEN COLOR 4 ELSE COLOR 312340 PRINT TAB(3) I;TAB(10) WBS$(I) TAB(45) OP$(I)12350 NEXTI12360 PRINT:INPUT "ENTER NBR OF SUBSYSTEM TO BE DELETED - 0 IF NONE";NBR12365 IF NBR>16 THEN GOTO 1230512370 IF NBR=0 THEN GOTO 1239512380 OP$(NBR)="DELETE"12390 GOTO 12305
12400 ' MENU TO DEFAULT ON TECH GROWTH FACTOR12403 COLOR 1312405 CLS:PRINT TAB(25) "OPTION TO USE DEFAULT RATE"12406 PRINT TAB(20) "FOR ANNUAL REUABUJTY GROWTH FACTOR":PRINT12410 PRINT TAB(3) "NBR SUBSYSTEM";TAB(45) "ANNUAL GROWTH RATE"12420 PRINT12430 FOR 1=1 TO 1612435 IF OP$(I)="DELETE" THEN GOTO 1245012440 PRINT TAB(3) I;TAB(10) WBS$(I) TAB(45) TG(I)12450 NEXTI12460 PRINT:INPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR12465 IF NBR>16 THEN GOTO 1240512470 IF NBR=0 THEN GOTO 1249512480 TG(NBR)=X(6)12490 GOTO 12405
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