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Produced by the NASA Center for Aerospace Information (CASI)
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(NASA-CR-175.356) Wi:1138T AND BALANCE FUR THE N84-16163

AIEMASS INCOh Pp 'RATED SUNFURST MODEL C

ULTLALIGHT (Kar.sas Univ. CenteL for

hesearch, Inc.) 92 p HC AC5/dF A01 CSLL 01C Unclas

G3/05 00543

1,^^^g2021

1 ^00%^0

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T;yE UNIVERSITY/ of KANSAS CENTER fOR RESEARCfi, INC.

2291 Irving Hill Drive-Campus West Lawrence, K.!nsas 66045
a

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WEIGHT AND BALANCE FOR THE

A!W4ASS INCORPORATED SUNBURST

MODEL 'C' UL'TRALIGHT

M KU-FRL-6135-2

Ts

Jahn A. Woltkamp, Project Engineer

L, Carlos L. Blacklock, Project Manager

Dr. Jan Roskam, Principal Investigator

Prepared under NASA Grant NAG1-345

for

National Aeronautics and Space Administratiou

Langley Research Center

Flight Research Laboratory

University of Kansas Center for Research, Inc.

Lawrence, Kansas 66045

m

November 1983
SUMMARY

This report presents the results of the weight and balance

determination done for an Airmass Incorporated Sunburst Model 'C'

ultralight. The tests were done at the University of Kansas Aerospace

Engineering hangar facilities at the Lawrence Municipal Airport in

Lawrence, Kansas. -The weight and balance determination encompassed

* finding weight: and C.G. of each component

* determining the center of gravity of the ultralight

in an X,Y,Z reference plane

* calculating the mass moments ai,d products of

inertia ( I XX , Iyy, I

zz' I xy' I xz' Izy).

The above relations were calculated for various pilot weights

and fuel loadings. The fuel varied from empty to five gallons (31.05 lbs),

and the pilots ranged from 90 to 260 pounds. The weighings of components

total 277.48 lbs (no F.Llot and no fuel). The centers of gravity and

inertias of the empty vehicle are listed below:

Center of Gravity

X cage - 

48•.73 % MGC, 110.02 in. from reference

(c - 50.34 in.)

Yc.g. - 233.77 in. from reference

2 - 58.91 in. from reference

c.g.

Moments of Inertia

I= - 303.9 slugs-ft.2

Iyy - 16.4 slugs-ft.2

IZZ - 352.3 slugs-ft.2

IXy - -2.5 slugs-ft.2

IXz - 3.2 slugs-ft.2

I zy - -0.43 slugs-ft.2

i
TABLE OF CONTENTS

Section Page

Summary . . . . . . . . . . . . . . . . . . . . . . . . . i

Table of Contents . . . . . . . . . . . . . . . . . . . . . .

List o f Figures . . . . . . . . . . . . . . . . . .

1. Introduction. . . . . . . . . . . . . . . . . . . . . . . . . 1.1

2. Methods Implemented . . . . . . . . . . . . . . . . . . . ' . . 2.1

2.1 Weighings . . . . . . . . . . . . . . . . . . . . . 2.1

2.2 Materials . . . . . . . . . . . . . . . . . . . . . . 2.3

2.3 Calculations. . . . . . . . . . . . . . . . . . . . . 2.5

2.3.1 Locating Components in Reference Axis System . . . 2.5

2.3.2 Center of Gravty . . . . . . . . . . . . . . . . . 2.19

2.3.3 Inertial Quantities. . . . . . . . . . . . . . . 2.19

2.4 Weighing Check and Error Analysis . . . . . . . . . . . . 2.22

3. Presentation and Discussion of Test Results . . . . . . . . . . 3.1

4. Conclusions . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1

5. References. . . . . . . . . . . . . . . . . . . . . . . . 5.1

6. Appendices. . . . . . . . . . . . . . . . . . . . . . . . 6.1

A. Weight and Balance Computer Program. . . . . . . . . . . A.i

B. Parts List with Description. . . . . . . . . . . . . . . B.i

C. Weighing Oheck and Error Analysis. . . . . . . . . . . . C.i

D. Principal Inertial Quantities. . . . . . . • . • . • D,i

ii
Page

1.2

1.3

1.3

1.3

2.2

2.2

2.4

2.5

2.6

2.6

2.20

2.21

3.3

3.3

3.4

3.4

3.5

3. 5

3.6

LIST OF FIGURES

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Number

1.1 Airmass Incorporated Sunburst Model 'C' ultralight. . . . . .

1.2 Sunburst ultralight front-view drawing. . . . . . . . . .

1.3 Sunburst ultralight side-view drawing. . . . . . . . . . . .

1.4 Sunburst ultralight top-view drawing . .. . . . , . . . . .

2.1.1 The typical marking convention for components . . . . . . .

2.1.2 Wing skin C.G. location and reference rib. . .

2.2.1 Manufacturer ultralight specification listing for Sunburst

Model 'C'.

2.3.1 Measurement reference axis system for establishing X,Y,

Z coordinate# . '

2.3.2 Distance measurements 'tieing taken using a vertical distance

tool, plumb line, and tape measure.

2.3.3 Measurement technique used to determine coordinates. . .

2.3.2.1 Center of gravity in the defined reference X-Z plane. . .

2.3.2.2 Center of gravity in the defined X-Y reference plane. . .

3.1 Computer output listing for empty aircraft; zero fuel and

no pilot.

3.2 Computer output listing for aircraft loading; aero fuel and

90 pound pilot.

3.3 Computer output listing for aircraft loading; zero fuel and

175 pound pilot.

3.4 Computer output listing for aircraft loading; zero fuel and

260 pound pilot.

3.5 Computer output listing for aircraft loading; 2.5 gallons

fuel and no pilot.

3.6 Computer output listing for aircraft loading; 2:5 gallons

fuel and 90 pound pilot.

3.7 Computer output ,Listing for aircraft loading; 2.5 gallons

fuel and 175 pound pilot.

3.8 Computer output listing for aircraft loading; 2.5 gallons

fuel and 260 pound pilot.
_ T OF IS 'r"TGURES (continued)

r

*± Number Page

3.9 Computer output listing for aircraft loading; 5.0 gallons 3.7 fuel and no pilot.

3.10 Computer output listing for aircraft loading; 5.0 gallons 3.7 fuel and 90 pound pilot.

3.11 Computer output listing for aircraft loading; 5.0 gallons 3.8

t and 75 pound pilot. 

3.12 Computer output listing for aircraft loading; 5.0 gallons 3.8 a fuel and 260 pound pilot.

3.13 Ultralight longitudinal experimental flight envelope for 3.9

pilot and fuel loadings.

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1.0 INTRODUCTION

This report will address the weight and balance analysis of an

ultralight aircraft, shown in Figures 1.1-1.4.

In recent years inflation, labor costs, complexity, and government

regulations have driven up the cost of privately owned single engine

general aviation aircraft. Previously, many of these airplanes had

been used for recreational, or nonessential, use; but recently the

cost has driven such users out of the market. Dome-built aircraft

have absorbed some of this market, but the time and inconvenience in

construction have dampened its development. Enter: the ultralight

aircraft.

Originally, the ultralight was a powered derivative of a hangglider; but it has evolved into a more complex aircraft of many bizarrre

configurations. Currently the Federal Aviation Administration (FAA)

has few regulations that apply to this class of airplan.4, one exception

being a 254 pound empty weight limit. The rece ►it 'zcom 1,i this industry

has gotten the attention of the Federal government and, namely, the FAA.

This interest has been aroused by numerous fatal accidents that might

have been avoided if some safety regulations had applied. The National

Aeronautics and Space Administration (NASA) has, in response to this

concern, granted the University of Kansas Center for Research, Incorporated,

a contract to conduct tests and analyses of a typical ultralight aircraft

to gain a better understanding of its characteristics and of the

technologies used.

The Center for Research, Inc. (CRINC), in turn obtained a Sunburst

Model. 'C o ultralight from Airmass, Incorporated, in Olathe, Kansas.

Currently a three-year research program is planned. This program will

involve the fallowing analyses:

* power plant test and analysis

(Report # KU-FRL-6135-1, dd October 1983)

* weight and balance

(this report, # KU-FRL-6135-2, dd December 1983)

lel
* drag analysis

(Report # KU-FRL-6135-3 0 dd December 1983)

* description of the assembly in process

(Report # KU-FRL-6135-4, dd Decc.mber 1983)

* stability and control

(Report # KU-FRL-6135-5, planned dd February 1984)

* load analysis

(Report # KU-FRL-6135-6, planned dd February 1984)

* stress analysis

t (Report # KU-FRL-6135-7, planned dd February 1984)

* nondestructive loads testing

(Report # KU-FRL-6135-8, planned dd April 1984)

* flight test and analysis

(Report it KU-FRL-6135-9, planned dd August 1984).

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2.0 METHODS IMPLEMENTED

To complete the specified goal of this weight and balance

document, each individual component had to be weighed and its center

of gravity determined relative to some reference axis system. This

was necessary to determine the ultralight's center of gravity (C.G.),

its mass moments of inertia, and the products of inertia.

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2.1 WEIGHINGS

All weighings were done at the University of Kansas Department

of Physics on m combination of two scales. The components that

weighed less than two pounds were weighed on a triple-beam balance,

while the items that weighed more were done on a larger scale.

The triple-beam balances measured the mass of each item, which

then had to be converted into pounds-weight. Each item was marked

ig with a part number and a. C.G. was determined. The center of gravity

of each item was found by placing the component on a knife-edged

support and adjusting until a satisfactory balance point was found.

The balance point was assumed to be the center of gravity and was

marked accordingly. The typical marking convention for part number

and C.G. location is shown in Figure 2.1.1. The only exception to

this was the C.G. determination of the wing skin. To find its C.G., 

a rib was assumed to simulate the actual cross section of the airfoil.

Using this reference rib (located halfway outboard on the wing), the

underside of the airfoil was assumed to be a straight line from the

leading edge to the trailing edge of the rib location; the center of

gravity was chosen to be located halfway between the upper and lower

skin surface, and half the distance of the upper and lower rib lengths

n

aft of the leading edge (see Figure 2.1.3).

After marking and identifying of all the components, the ultralight

was assembled. Upon completion of assembly, many parts were left over

and determined t e o be superfluous. p The parts list that was com fled for. P

IT the ultralight includes only those items which were used for assembly.

The compiled parts list is given in Appendix B, Table B-2.

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2.1
ORIGINAL PAGE [^

OF POOR QUALITY

An error analysis was performed for the weighings and the results

are presented in Chapter 2.4; this analysis is critical because the

weighing results will later be used to calculate the aircraft weight,

C.G., aad inertias.

Figure 2.1.1 The typical marking convention for components.

TILT

Ar

Figure 2.1.2 Wing skin C.G. location and reference c'ib.

2.2

O
2.3

2.2 MATERIALS

The majority of the structure on'the Sunburst ultralight was

made up of anodized aluminum tubing, as is the case on most ultralights.

It was observed that the mixer assembly, and wing spar tubes were not

anodized. The aluminum used for these, components was 6061-T6 stock

(.049 11 and .058 1, thick) which was pre-cv,'t,bent, drilled, and processed

upon arrival from Airmass Incorporated( the only exception to this was

that the upper and lower boom tubes which had to be drilled in actor- 

dance with the Assembly Manual, Reference 1). Other materials used

were:

* 3/32 11 and 1/8" plastic coated stainless steel cable

( the upper flying wires were not coated)

* AN-aircraft grade standard hardware

( bolts, lock-nuts, washers)

* 3.9 ounce stabilized dacron wing and tail fabric

* propeller-541 'x27" laminated 2 ply birch wood

* fiberglas bucket seat

* two large, one small fiber spoked wheels

* assorted plastic caps,plugs,saddles,and spacers

The actual manufacture's specification sheet for the ultralight is 

shown in Figure 2.2.1. 
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ORIGINAL PAGE Ifis

OF POOR QUAI.V,

ii

SUNBURST

The ultralWd aircraft d4syned for the discriminating pilot who

demands the bast In skai um alloy end deaott design.

contra*

A truly three axis design incorporating coordinated controls with stick

and rudder inputs thru a mixer operated inverted Mail end wing

mounted spoilers.

sbuco"

8uik with top quality aircraft hardware and components. It's

triangulated main frame, substantial wing spars and rugged suspended

landing gear give notice the Sunburst's element of structural integrity, In

fact, the entire structure has been overbuilt and designed for the eon.

tainmitnt and safety of the pig. Steerable rose gear and loge diameter

wheels facilitate the Sunburst's use in an all terra.n environment.

Power System

A strong and reliable twin cylinder 43000 Cuyuna engine developing

30hp is the heart of the Sunburst power system, k features dual CDI it

notion, forced air cooling and midair "arting capabilities. The power

system package with smooth planetary gear reductan;kive —tuming a

54" x 27" laminated hard wood propeller provides a power and car

fclerce unparalleled by others in its dam

ARMAWN

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operating conditions. Once aloft, you experience the responsive cor

trds and its wide range of speeds and soaring capabilities. Stalls are

mild and are preceded by a gentle warning. The Sunburst has spiral

stability and will not enter a stabilized flat spin condition. Landing is

effected by po ry setting the throttle to fly the Sunburst on the run

way at a minimum cruising speed.

Comfort

Longrangeupholsteredeomfortis pmvidedby af'rvepoint suspend

bucket sestadjustable to arangetilt and keglengthpositions.

Adjustable rudderpeddss also improve the pilots comfort settings. Th

throttle and control stick are located in natural low fatigue positions t

further enhance the ease of operation. ,

Fktlsh

Bright blue anodized tubing, black coated stainless steel cables and

color coordinated wheels and wind coverings combine to convey a

elegant finish.

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Overall; the performance, quality, comfort and finish are only hints

Performertce that the Sunburst is the ultimate personal flying machine designed to

The Sunburst's impressive ground handling abilities a" with its give the pilot what he. eeds, the exhilaration and case of ultralight

quick take off and rapid rate of climb allows its use in a wide variety of flight. 

STANDARD FtATURES gMENSIONS Height 9 ft. Length 16 ft. Width 36 ft.

Tubing 6061 •T6 bri8ht blue anodized aluminum tubing, cut,

bent, drilled and processed. Ready for assembly. PWORMANt t SPECIFICATIONS

Nerdwwe Al+aircraft grade hardware and fittings. VNiis(never exceed speed)

Guise Speed

35 50 m.

35.50 m.p.h. 

Cables 3/32" and 1/8" black coated stNmless steel cables, fac• Stall speed 23 m p.h

tory pre-swagged on jig. Glide ratio 10/1

Mel ng 36' span,156 sq, ft., 8.3 aspect ratio 4'4" chord, oes• ^ d

Takeoff distance

landing distance

75'•100'

501•100' ble surfaced. Rate of climb 800 f.p.m.

M'Ing 3.9 oz. stabilized dacron, wing coverings are precision Fuel Row 1,6 g.p.h.

Coverings and are ready for mounting. Ten standard color Fuel capacity 5 gallons

schemes. Custom wing cola schemes available. Endurance 3 hour

Average range' 100 nautical miles 

E ngine Cuyuna 430cc, 30hp, 2 cycle, recoil starter, quiet Drhpty weight 240 pounds multichambered muffler, freed air cooling and dual Wing loading 2,8 lbs. tm 170 lb, pike w/5 gal. fuel CDI ignition— factory assembled components ready to Pilot Weight range 90.260 pounds bolt on.

DO" Wine 2.1 ratio planetary gear reduction drive factory OPT1ONAt tOUIPMOiT 

Train assembled ready to bolt on. knourawft Od*M

Aft speed indicates bags Propeller Drive shaft dmyen, pusher mounted, 54"x 27" Altimeter Pns

ontoo

bntoo laminated 12 ply birch. Variorneter Parachute system

Canktrge Upholstered fiberglass bucket seat with five point Tach Kin eta Wheel brake

Assembly suspended comfort adjustment system, positive retetr EGT Front fender

tian shoulder harness, large diameter fiber spoked CHT Wheel pants

wheels, with shock cord suspensi6n system. Wheels instrument pod AG spaying system

available in red, blue, yellow or black. 2-way radio Strobe light

Figure 2.2.1 Manufacturer's ultralight specifications listing for the

Sunburst Model'C',

2.4
ORIGINAL PAGp.

OF POOR QUALITY

2.3 CALCULATIONS

7.3.1 LOCATING COMPONENTS IN A REFERENCE AXIS SYSTEM

To determine the center of gravity and moments of inertia the

location of each component had to be referenced to an axis system.

Because no technical drawings could be obtained from the manufacturer,

y

these locations had to be determined by measurements. These measurements were taken relative to a reference axis that was arbitrarily

chosen to be 'off' the aircraft to allow possible future test modifications to remain within the current axis system. The ultimate

s goal was to have the X,Y, and Z coordinate for each component. The

coordinate system is shown in Figure 2.3.1 and in Figures 1.2, 1.3,

and 1.4.

/UYIS SYM

COMPONENT Z

C.G.

ZDIRM I Y

I

f

m HDIST

X P I 1 ..

Figure 2.3.1 Measurement reference axis system for establishing X,

Y, and Z coordinates.

' The coordinates were found by using a vertical measurement tool,

tape measure, plumb-bob, and transit( Figure 2.3.2). The measurements

taken were (Figure 2.3.3):

* vertical distance

*, horizontal distance to plumb-line

* hoizontal angle from reference axis using the transit

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Figure 2.3.3 Measurement techniques used to determine coordinates.

^'. Vertical•=

Dist

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 vertical distance tool, plumb line, and

tape measure.

2.6

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The measurements, or raw data, taken are listed in Table A-1,

Appendix A. The measurements are assumed to be accurate, or were

read, to the nearest 1/8 inch and the angle to the nearest 10 minutes.

The errors in these measurements and their effects are discussed in

Section 2.4.

Once the measurements had been taken, the data were reduced to the

reference coordinates desired. This was accomplished using a computer

program subroutine that converted thei:a raw data into usable material.

The data taken, vertical height (Z-DIR), horizontal distance ( RDIST),

and horizontal angle (PSI) were reduced to X, Y, and Z coordinates

as follows:

Xref ' HDIST x COS(PSI)

Y

ref u HDIST x COS(PSI)

Zref is measured as vertical height, Z-DIR.

These reference coordinates are listed in Table 2 . 3.1. With these

data, the C . G. and moments of inertia can be calculated.

2.7

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Table 2.3.1 Reference coordinates for each component according to part

number(583 components including pilot and fuel).

THIS FILE COORD CONTAINS k,Y.AND 1 COORDINATES

VNERE Y AND 1 ME CALCULATED

1T[II NREF YREF tREf YEIGH7(LIS J

96-62 91.445 18.187 90.250 .237600

AN4-24A 2Fr27 88,172 16.071 90.250 .054590

-

EC-9 17,717 13.466 90.620 .012790

96-07 105.500 15.447 88.875 1.146000

EC-9 118.641 15.262 17.875 .012790

AN4-24A 3T 117.564 15.133 17.375 .052380

96-63 116.899 17.125 87.750 .218500

NC-57 136.641 21.031 15.250 .007253

96-66 112.368 55.609 17.175 .255900

96 -37 118.351 56.451 15.500 2.354000

Y6-37 16.251 55.841 17.250 2.354000

AN4-30A 2T 16.033 78.367 15.625 .057180

96-35 86.033 78.367 85.625 .005952

Y6-5. 91.412 11.360 15.375 .048670

AN4-144 IT 91.412 11.360 85.375 .031670

CS-30 95.051 11.181 15.375 .014770

"c Y6 -93 1 94 94.087 78.251 15.250 .281000

'

96-47 96.493 14.861 84.500 .288500

96 -77 112.257 77.876 14.625 .023530

AN3-16A 2F 112.694 77.604 83.750 .026370

- AN4-14A IT 113.032 77.192 83.175 .031670

96-53 113.367 76.691 13.875 .046677

AN4-26A 2F 115.389 76.314 83.875 .056790

x. AN4-24A 2F 115.702 76.581 14.000 .053260

96-66 108.195 16.063 15.625 .255900

Y6-33 116:426 117.447 10.150 2.115000

96-33 85.155 117.207 82.000 2.115000

96 -57 90.222 124.958 80.375 .215004

Y6 -57 90.222 124.958 80.375 .215000

96-66 109.208 122.015 80.625 .255900

96-35 85.300 158.221 75.625 .005952

AN4-30A 3F 15.355 151.192 11.625 .059380

96-53 16.513 155.562 78.625 .048670

AN4-144 IT 16.513 155.562 78.500 .031670

46-46 105.013 156.690 17.500 .278300 

96-66 108.692 155.230 79.750 .255900

AN4-14A IT 112.759 156.172 17.375 .031670

AN4-24A IT 86.157 155.426 78.625 .049730

96-93 91.672 153.599 78.250 .268300

96-53 114.340 155.484 77.250 .048670

AN4-264 2F ' 116.061 157.317 77.375 - .056790

AN4-24A 2F 116.436 157.355 77.375 .053260

4 96-97 117.655 156.134 77.250 .065480

AN4-11S iF1TYR 117.655 156.134 77.250 .050500

CS-40 111.706 134.978 79.500 .343800

96 -754 72.452 190.433 54.125 .687500

96-56 100.087 193.666 74.315 .200000

IT Y6-92 100.017 193.666 74.315 .112500

96-66 107.663 111.914 76.500 .255900

96-27 115.038 189.577 74.000 2.330000

96-27 85.275 189.305 76.250 2.380000

96-66 109.963 222.985 14.000 .255900
ORIGINAL

Table 2.3.1 continued OF POOR QUALITY

171 MREf 11RE1 i4E/ Yt1GNT(LIS.)

AN3-7A ST 113.503 225.971 66.375 .020784 AN3-7A ST 118.626 235.747 66.375 .020780

CS-33 114.606 227.375 61.750 .073520 CS-42 114.164 226.048 $9.625 .006596

AN5-1241 5F 114.184 226.048 69.625 .062090

CS-32 113.925 225.338 70.625 ,047950

A03-24A mr 113.839 226.641 11.375 .032730 AN3-244 1T2f 114.606 227.375 71.375 .032730

11?1 115.130 229,110 70.875 .375900

AN4

. 24A iF1T 115.859 230.662 70.675 .052160

112

AN4-248 2F

14.106

14.106

227.981

2?7.911

73.500

73.500

.100300

.053260 ' 96-71 104.368 117.749 92.500 .812500 06-74 105.414 169.117 56.150 1.562500

EC-9 16,759 453.526 92.000 1012790

AN4-248 3F 16.595 452.667 91.625 .055690

96-62 86.510 450.519 91,625 .237600 MS-17 ' 105.145 "429.698 89.375 1„146000

EC-9 119.210 453.061 89.000 .011790

A04-24A 3F 118.440 451.473 86.625 .655690

Y643 1181567 451.956 88.625 .2;18500 NC-57 136,079 449.869 85.875 .001253

96-66 110.582 415.020 86.875 .25W4 N6-37 118.144 412.021 85.615 2.354000 i 116-37 87.419 414.124 $8.250 2.354000 06-35 14.152 317.100 06.250 .405952

AN4-30A 2F 83.626 377.217 86.250 .059380

Y6°53 18.968 393.115 15.875 .048670

AN4-14A IT 88.968 393.185 85.875 .031670

1 W93 95.162 388.901 85.300 .278900

CS-31 91.877 387.764 05.500 .014770 Y6-47 107.353 389.216 14.625 .288500

96-77 114.435 390.581 84.750 .023530

AN3-16A 2F 114.435 390.581 84.150 .026370

A14-14A IT 109.7$9 391.272 84.000 .031670

N6-53 116.571 389.297 84.000 .048670

-

AN4-24A 2F 117.549 388.611 84.000 .053260

AN4-25A 2F 118.305 388.904 84.000 .053260

96-66 111.476 382.460 85.625 .255900 M6-57 102.302 349.149 81.625 .215000

Y6-57 102.302 349.849 81.625 .215000

96-33 85.662 348.759 82.625 2.115000

96-33 118.722 351.359 10.625 2.115000 

96-66 110.751 $47.661 82.815 ..255900

96-66 110.308 314.464 79.750 .255900

06-35 15.526 311.990 79.125 .005952

M AN4-30A IF 06.451 311.135 19.125 .056950 W6-53 17.631 309.00 78.875 .048670

A04-14A IT 87.631 309.U? 78.875 .031670

96-93 94.143 301.930 76.500 .267800

116-K 105.617 306.939 77.750 .278300

AN4-14A ST 115.790 311.021 17.250 .031670

96-53 116.224 310.859 77.250 .048670

A04-28A 2F 117.213 308.081 77.250 .056290

AN4-264 2F 117.213 308.081 77.250 .056790

2.9
ITEM NAEF w r 2REF OEIGHT(L1S O

ANi-17^^ 1F1TUR 119.445 301.429 16.750 .00500

UA-; 7 15.720 217.434 76.500 1.330000

UG 92 101.057 277.756 74.500 1112500

UG 56 101.057 272.756 74.500 0200000

MG-66 15.627 215.955 76.500 .255900

U6. 27 116.350 276.313 74.175 2.330000

06 . 66 110.225 247.571 74.000 .255900

191 16.539 238.103 73.375 .100309

AN4 . 240 2F 16.539 238.003 73.375 .053260

163 117.371 237.172 71.000 .100300

AN4-24A 2F 161.725 326.797 71.000 1053260

CS-39 117.673 335.460 79.500 .343100

06-75 72.239 275.951 55.625 .687500

U6-74 106.479 302.031 53.375 .562500

96-7? 105.022 219.107 94.500 .112500

U6-213 100.200 231.019 96.750 3.660000

AN365-524 109.191 234.107 117.175 .011270

AN4-50• iT 11.131 .,232.713 74.375 .155000

06-13 11.351 232.954 73.625 .075620 U6-1 12.516 231.350 73.375 .103600

06.8 63.621 237.192 73.375 .103604

AN4-26A 2F 81.096 231.189 72.000 .056794

AN4-26A 2F 12.425 230.586 71.115 .056790

AN4-24A 2F 11.573 230.351 73.000 .053260

AN4-240 2F 801197 229.650 74.125 .053260

AN4-24A 2F 82.662 230.235 74.040 *053240

AN4-21A 2F 15.167 231.153 73.96 .058290

AN4-2iA 2f ►4.478 232.104 73.750 .058290

AN4-25A IF 95.189 233.043 73.375 .052970

AN4-17S 2FUR 82.783 233.115 76.006 .051630

CS-28 83.110 233.660 76.000 .000661

CS-21 12.457 233.191 76.000 .000661

EN6,AEO,MOUNT 102.273 233.319 65.375 78.375000

SPARK PLU6 100.640 233.346 57.500 .124000 

SPARK PLU6 103.999 231.733 $7.500 .124000

V-PIPE 104.285 229.614 64.125 1.643500

J-PIPE 96.692 225.929 63.000 1.010400

MUFFLER 102.014 223.151 60.125 5.000000

MUFFLER SPR 100.934 224.066 64.625 .012130

MUFFLER SPR 100.768 226.331 66.250 .012130

MUFFLER SPR 95.777 225.639 59.175 .012130

MUFFLER SPA 95.183 227.765 59.8?5 .012130

AN4-12A 99.766 228.140 57.500 .035780

RU8i816 MASHER 99.766 221.140 57.500 .024690

AN4-12A 2F 106.031 229.159 57.250 - .035780

RU86016 RASHER 106.031 229.159 57.250 .024690

A04-28A 2T 99.299 232.019 72.250 .056090

AN4-21A 2T 10.330 231.499 72.250 .056090

EN-26 103.233 241.213 61.625 2.000000

06-36 125.645 232.184 70.175 .068830

AN5-42A 2F 125.210 232.311 69.756 .121000

AN3-25A 2F 125.969 232:001 70.500 .031310

AN3-25A 2F 124.956 232.555 70.625 .031310

AN4-20A 2F 125.210 232.3x1 72.750 .044450

06-36 126.229 234.141 72.750 .068830

^t

IT

P

^p

r

^, L

2.10 

-, L 

Table 2.3.1 continued
{ 2.1I

F

ORIGINAL PACE IS

Table 2.3.1 continued OF POOR QUALITY,

In" NREr MIFF iAEr VE1GHT(M.)

CS-28 125,443 232.293 72.750 .000611

CS-21 121.064 236.649 12.750 .400b61

PROPe.SHAFT 136.326 235.369 66.250 8.875000

EN-12 138.229 235.418 66.250 1.160000

EN-95

EN-95

135.116

139.013

232.075

232.920

66.250

66.125

.110900

.110900

AN4-35A 2F 135.334 231.319 65.000 .OG8420

AN4 . 35A 2F 136.959 230.942 67.625 .066420

EN-90 138.176 232.255 61,625 .262600

EN-94 138.995 237.577 67.625 .282600

EN-92 116 MASH 138.995 237.511 69.125 .100100

EN-92 138.116 231.411 69.250 1104100

EN-99 138.490 236.114 69.125 .057540

EN-99 131.629 232.276 69.250 .057540

06-50A 138.177 234.579 69.125 .172000

ANS-168 2P 113,154 232.001 66.625 .065280

TS-4 161.144 185.316 73.875 1.760000

TS-2 119.259 187.092 47.500 1.875000

TS-22 156.120 219.521 41.750 1.250000 TS-3 160.467 285.955 73.625 1.160000

TS-1 195.969 221.504 47.250 1.815000

PUSH CLEVIS 115.898 222.640 26.000 .149740

AN3- IA 2T 116.520 221.468 26.500 .019770

03-11A 2T 195.944 216.325 71.750 .019770

PUSH CLEVIS 195.033 214.114 12.375 .149700

CS-47 i3tl.264 241.167 35.000 1.437500

NOSE CLAMP $H 120.661 247.393 33.750 .053790

NOSE CLAMP 50 125.555 264.112 45.125 .053790

wr AN3-6A 2T 114.582 222:477 25.400 .016510

!N3-SA 2T 199.011 215.194 73.125 .016580

AN4-145 1FUR 191,469 211.945 66.500 .043730

AN4-14S 1FAR 199..641 209.133 71.400 .043730

AN4-14S 1FMR 196.629 256.253 66.000 .043730

AN4-14S iFYR 197.016 256.148 70.625 .043734

AN3-liA 2T 200.245 209.166 69.500 .019770

NSA-4 199.622 210.359 69.500 .006944

PISA-18 200.605 210.804 69.500 .011900

TS-36 203.650 212.737 71.250 .152600

"SA-i 200.370 212.405 69.500 .030090

NSA-108 202.642 215.416 71.625 .096;160

AN3-120 2T 200.802 214.058 69.500 ,021360

AN3-12A 2T 200.807 214.738 69.504 .021300

AN3-SA 2T 203.372 215.587 74.500 .016580

"SA-5 201.171 216.411 69.500 .010690

NSA-18 201.568 211.4" 69.500 .011900

NSA-2 201.214 211.284 69.500 .128200

NSA-11 201.653 217.537 12.290 .047000

AN3-51 IT 202.552 217.212 11.250 .014310

A03-'A IT 203.282 216.101 71.250 .914310

NSA-26 199.950 224.656 65.625 1.023404

NSA-16 199.713 224.474 66.625 .021210

AN4 -14A 2T 199.713 224.470 67.500 .022050

AN3-130 2T 201.013 223.315 69.500 .021380

A03-13A 2T 201.013 223.315 69.504 .021380

HSA-91 200.996 2?:.791 64.750 .084880
Table 2.3.1 continued

1TER

AM3-5A IF

AM3-5A IF

AN3 -6AIT

• RSA^12

A03-12A S1

RSA-13

HSA-8

RSA-7

RSA-23

^^ ry

RSA-15

AN3-64 !T

RSA-9A

AN4-13A 2T

A04-13A 2T

RSA-11

AM3 . 5A IF

F 3-SA IF

W-1e

RSA-4

AN3-11A 2T

RSA-3

AN3-12A 2T

AN3-120 2T

RSA-10A

RSA•1

RSA-1/

TS-36

AN3-11A 2T

t

ASA-4

AN3-14A 2T

AN3-14A 2T

A03-15A 27

AN3-15A 2T

AN3-15A 2T

AM3-15A 2T

AN3-15A 2T

AN3-15A 2T

TS-37

75-38

TS-114

TAIL TUIE ii

TS-1

FAIRIMAIL)

TS-19

AN3-6A 3T

TS-29

TS-31

AN31158 2T

75-3!

AN3-154 2T

TS-20

AN3-14A 2T

TS-26

TS-26

OF POOR QUAL"

MAEf VKF zNtF NEIGHT<LIS.)

201.709 222.066 71.544 .015300

202.046 222.436 70.815 .015300

203.943 222.566 67,675 1017770

203.159 222.474 70.504 .060300

243.191 223.071 73.750 .0249bu

203.979 224.564 U .Su0 .021940

205.111 222.r-11 74.250 .096320

207.516 273.863 70.625 .025350

207.516 223.163 70.625 .031160

200.409 223.911 72.875 .060300

206,212 223.706 74.625 .253200

196.715 224.617 72.125 1017770

199.701 224.376 70.750 .084110

200.346 224.470 69.500 .021310

200.346 224.470 61.500 .021384

200.864 225.684 69.500 .011900

201.678 225.962 70.875 .015300

201.671 22b.962 71.625 .015304

199.904 231.347 69.500 .011900

200.071 2 M IS2 69.500 .006944

200.071 239.852 6!.500 .019770

200.783 241,917 69.500 .345800

199.889 253.560 69.375 .021380

199.189 253,560 69.375 .421310

199.967 253.6se 71.250 .096560

201.157 255.902 69.375 .020090

200.705 256.892 69.335 .011900

202.015 257.011 71.250 .152600

201.399 2L9.362 69.313 .419770

201.399 259.362 69.375 .006944

202.393 257.475 68.750 .022050

202.231 211.845 68.754 .022050

207.156 208.972 67.250 .023150

207.040 209.439 67.750 .023150

206.492 211.310 68.875 .023150

205.705 213.015 71.250 .023150

207.101 216.348 72.000 .023150

207.496 217.360 72.500 .023150

206.514 212.513 70.125 .104600

207.120 213.210 69.250 .248200

203.534 223.41 79.250 .313444

201.294 219.059 59.750 .875000

214.110 205.034 63.500 1.010000

225.859 215.610 71.315 •.718800

219.714 214.703 73.625 .260000

233.164 213.656 73.625 .017770

229.079 215.296 72.375 .015700

232.311 216.705 72.000 .004299

232.317 216.705 71.500 .023150

229.102 219.911 72.000 .042990

229.102 219.911 71.500 .023150

236.569 215.411 71.500 .225600

231.287 216.966 71.500 .022050

227.04 221.110 72.250 .017360

230.70 216.453 70.750 .017360

..

2.12
r

^a

1

i

a I.^7

i

a

t7

I

NVr

ORIGINAL PAGE fS

OF POOR QUALITY

Table 2.3.1 continued

ITEM xqr VREF ZIEF NEIGHT(LIS.)

TAIL TUBE 14 221.650 202.531 71.075 .66750

AN3-13A 2F* 242.002 215.996 74.375 .021376

403-119 it 243,144 216.406 70.250 .0195'10

TS-28 243.144 216.406 74.250 .052360

AN3-11A 3T 230,168 190.929 57.500 .020960

T$-26 230.590 199.251 57.750 .017360

AN392. 13 AYE' 227.167 197,474 54,750 .003960

AN42-113 fl y 227,167 199.474 56.750 .025930

T5-21 226.979 197.310 56.000 ;452360

A03-1IA 17 227.137 196.311 $5.750 .010580

ANMIA 3T 230.441 231.121 15.250 .020960

TS-26 230336 231.909 14.500 .017360

ANMIA 2F 229.110 233.157 16.625 .021160

7S -21 229.110 233.157 86.375 .052360

ANMIA IT 229.810 233.157 16.500 .018580

TS-23 201.702 233.421 87.750 .022320

AN3-ITA NO IT 201.102 "233.428 17.250 .013640

T5-34 199.864 234.675 88.000 .00455

ANMIA IF 200.866 233.100 87.500 .019570

AN3-15A 2T 206.755 261.517 66.625 .023150

AN3-15A 2T 206.304 260.759 67.000 .023150

ANMSA 2T 206.440 261.161 68.500 .023150

AN3-15A 2T 205.224 255.105 71.500 .023150

AN3-15A 2T 205.267 255.029 71.375 .023150

ANMSA 2T 205.181 254.127 72.375 .023150

TS-37 205.726 257.065 69.875 .104600

TS-39 206.663 251.236 69.000 .251500

AN3-6A V 199.922 254.330 14.375 .016580

TS-34 201.572 236.011 17./71 .004255

A03-11A NO 202.352 235.507 17.175 .012650

TS-23 201,120 235.635 11.625 .022320

ANMIA 2F 202.546 237.152 87.000 .021760

TS-11 203.306 246.631 78.250 .333000

TAIL TUBE 81 212.372 247.169 77.000 .875000

TS-7 213.024 263.064 63.250 1.010000

TS-3 218.541 268.246 59.375 1.760000

TAIL FABRIC LF 224.533 255.313 71.000 .718800

AN392-13 A 226.350 272.138 55.250 .003960

A042-113 221.350 272.138 55.250 .041560

AN3-!1A NO 228.510 272.329 54.625 .012650

51-38 228.510 272.329 54.625 .052360

ANMIA 3T 230.398 271.390 56.000 .020960

TS-26 230.560 271,580 56.750 .017360

AN3-14A 2T 230.621 253.895 70.500 .022050

TS-26 229 .??fS 251.117 11.750 .017360

TS-26 228.924 252.735 70.250 .017360

TS-20 237.335 254.511 71.375 .225600

TAIL TUBE 84 239.740 254.141 72.750 .687500

ANMIA 2F 244.103 254.595 72.250 .014830

TS-21 244.459 254.654 12.250 .052360

ANMIA IF NO 244.459 254.654 72.250 .014830

TS-19 217.108 255.021 74.375 .260000

TS-34 232.218 254.959 72.875 .085700

AN3-6A 3T 232.575 255.329 14„375 .017770

AN3-11A 2T 231.396 254.035 71.750 .019770

2.13
Table 2.3.1 continued

~

ITER MREf vur zotr VEIGHT(LIS.)

A03-114 27 23?,900 252.657 71.750 .019770

TS-31 231.396 254.035 72,000 .004299

TS-31 232.900 252.657 72.000 .004?99

TS-26 231.147 239.361 14.625 .017360

ANMIA 3T 23.379

IT NO 220.459 235.177 86.375 .013840

►S-28 227.760 235.854 85.875 .05.2360

AN3-11A 2F 227.934 236.034 85.750 .014830

{ AN4-12A 2F 225.761 235.176 17.250 .035780

004-12A 2F 225.104 235.805 17.250 .035780

AN4-12S 2FYA 226.458 234.505 17.250 .043080

TS-25 225.761 235.176 87.625 .041450

TS-21 228.808 235.536 54.875 .120000

AN4-26A IF 1116.568 233.102 70.750 .054360

AN3-6A 2T 114.602 229.056 69.250 .016580

CS-46 116.902 229.434 50.000 ,.563000

NC-3 119.371 226.889 50.875 .965800

HC-3 120.476 243.445 50.875 .965800

NC-2 97.167 226.920 52.000 1.156000

HC-i 71.455 226.627 $3.000 1.000000

HC-1 73.649 243.480 53.000 1.000000

EN-94 68.809 242.684 42.375 .381800

- NC-2 99.574 244.367 51.875 1.156000

N6-20 71.560 236.276 51.675 .192000

A14-24A IF 42.344 230.264 12.175 .050830

NC-11 42.344 230.264 12.875 .000683

N6SA-12 42.127 232.972 13.500 1010360

N65A=10 42.229 231.683 13.250 .047620

N6SA-10 41.935 237.831 13.500 .047820

N6SA-11 42.430 232.790 13.500 .000680

NOSE 906TIRE 41.764 234.942 13.500 3.120000

06SA-11 42.005 236.296 13.500 .000880

N6SA-12 42.005 236.296 13.50" .010360

NC-88 42.304 239.924 13.250 .000683

,, y 06SO-9 41.764 234.942 13.500 .496000

AN4-24A IF 42.304 239.924 13.500 .050830

06SO-8 48.014 237.699 18.750 .434600

N6SA-1 48.390 232.646 19.000 .434600

= NSSA-7 54.213 234.823 23.875 1.250000

NSSA-18 52.667 234.278 12.375 .169900

USA-% 52.832 235.010 23.375 .058820

NOSA-13 51.463 235.441 20.625 .058310

06SA-13 51.972 234.433 21.125 .058310

NGSO-13 53.543 235.105 22.750 .058310

NOSA-13 54.044 234.092 23.375 .050310

N6SA-6 53.377 234.315 20.875 .095990

N6SA-19 52.161 235.207 22.625 .069550

06SA-19 54.241 234.945 24.175 .069550

i NC-57 55.365 236.609 25.500 .007253

NC-57 55.110 237.011 25.500 .007253

AN4-7A IT NO 52.103 238.372 22.250 .019160

N6-27 53.197 238.386 22.000 .015980

.% N6-53 55.014 238.599 21.500 .039080

AN4 iMLF NUT 53.709 238.912 21.875 .004630

AN4 HALF NUT 55.820 231.556 21 X00 .004630

2.14

w
4

Table 2.3.1 continued

Enn

06.27

04 -140 2F

403-IOA 2T

AN3-10A 2T

NGSA-14

AN4-7A IT NO

N6-27

AN4-16A 2F

N6SA-1

N6SA-2

N6SA-3

NGSA-4A

NGSA-3

NGSA-2

-

N6SA-5

N65A-2

N6SA-3

06SA-48

N6SA-3

° NGSA-2

°( NGSA-1

AN4-16A 2F

CS-50

A4391-61 R

N6-5$

AN4 HALF NOT

AN4 HALF NUT

N6-27

AN4-14A 2F

NC-99

MC-57

AN4-35A iF1T

HC-5

- MC-12

AN4-16A 2F

NC-57

NG-18

404-35A iT1F2'

U&-35

CS-42

AN392-13 R

AN392-13 R

AN4-15A 2F

AN4-24A 2F

HC-11

NC-11

AN4-17A 2F21

EC-9

NC-8

AN4-15A 2F

EC-9

AN4-17A 2F?,'I

NC-11

MC-11

OG

FU

OF POOR QUALITY

NREf VKr 2REF UEIGHT(LIS.)

56.544 230.643 21.75 .015980

46.84' ;,10.990 21.250 .039080

53.051 1:1Mo 22.375 .010200

52.496 23:1010 22.250 .018200

53.294 ?34.000 24.250 .058870

52.461 230.352 22.000 1019180

53.200 ?10 439 21.875 1015980

56.609 4717.049 24.250 .030290

56.025 24.250 .036380

55.915 77IMS 24.250 .009700

35.74; '?29.193 24.250 .033510

56.772 230.615 24.875 1.009700

56.000 231.832 24.250 .032520

55.497 232.596 24.250 .009700

$5.740 235.115 24.250 .572600

56.419 238.672 24.125 .009700

56.297 239.080 74.125 .033510

56.659 '239.129 24.750 1.042300

56.191 240.138 24.125 .033510

55.926 240.714 24.125 .009700

55.615 2,11.766 24.125 .36380

55.897 243.671 24.125 .042900

55.703 241.279 29.375 .051,1910

55.430 IM AM 29.250 .011630

55.120 231.015 23.625 .0?,9080

54.613 230.493 21.750 .004300

56.128 230.773 21.315 .0114300

56.802 230.736 21.250 .015980

%0 7 ._4g 230.567 21.125 .039064

62.720 242.521 30.940 .06376

64.528 242.176 32.450 .001187

64.159 243.696 31.850 .067320

64.009 244.511 31.850 .009458

64.104 244.073 31,.850 .037170

63.339 245.821 31.850 .042900

63.252 245.995 32.050 .007187

61.690 241.495 30.000 .021270

61.413 243.242 29.900 .068640

61.413 243.242 29.900 .004299

62.532 241.795 29.900 .004299

61.690 241.495 30.000 .008598

62.069 241.398 30.150 .003960

62.069 241.390 29.520 .003960

M.357 246.092 32.100 ..040810

61.628 244.090 32.100 .053260

61.244 244.187 30.300 .065480

60307 244.287 33.100 .065460

61.028 244.090 34.200 .045790

60.059 243.966 32.100 .012790

61.334 235.441 32.000 .820800

$I Q3 217.776 31.900 .040810

60.466 225.66S 21.500 .412790

61.897 225.795 34.150 .045190

61.897 225.795 33.404 .065480

61.197 225.795 30.700 .065480

f^

C

2.15 i 
OF POOH; QUALITY

Table 231 continued . . R

IM vREf "EF wr YE16MT(IIS.)

A04-114 2F2P 61.197 225.795 29.800 .045790

NC-12 64.223 223.974 31.900 .0371'10

AM4-164 2F 64.085 223.494 31.900 .042900

MC-5 64.013 224.424 31.900 .009458

Hf-57 63.113 223.583 31.900 .00763

AN4 . 25A SFiT 64.070 225.968 31.900 .054300

MC-6 11.203 225.181 31.400 2.540000

NC-13 12.796 225.399 30.500 .130000

AN3-23A iT1F 12.796 225.399 31.400 .030440

A04-24A 2F 82.796 225.399 29.300 .053260

AN3-6A 2T 12.765 224.345 30.000 .016580

Jj

CS-24 13.299 223.747 29.750 .097220

CS-21 13.528 222.461 29.750 .033680

CS-30 83.528 222.461 29.750 .008973

AN4-16A 2F2P 12.339 22.231 29.850 .04+1220

CS-22 11.144 222.942 31.650 .60,9800

AN4-6A 2T 12.116 26.600 .016580

HC-107' 87.526

.122.586

25.010 14.300 .562500

CS-38 94.149 223.453 14.300 .014770

NC-27 91.136 221.992 21.500 1.540000

CS-25 96.696 222.389 25.900 .450000

CS-26 98.119 222.993 28.900 .767400

r. NC-10 99.764 227.595 30.400 .439400

FT-1 108.669 229.580 22.900 2.021000

EN-92 108.612 232.921 22.900 .281500

k.; FT-2 108.202 236.553 22.900 2.021000

MC-120 108.760 235.058 29.000 .070000

NC-91 108.760 233.058 29.000 .197100

NS-35420-14 A 108.644 226.962 29.000 .013870

TANK TANG 108.644 226.962 29.500 .018300

TANK TANG 108.395 243.460 29.500 .018300

AN365-428 108.395 243.460 29.000 .008179

AM4-234 IF 107.681 225.760 30.050 .046570

AN4-234 2F 109.306` 225.810 30.050 .051000

NC-109 109.306 225.810 3.050 .464500

AN4-30A 2F 111.483 221.950 2!.800 .059380

MC-12 111.470 222.795 31.S00 .037170

MC-5 111.410 222.195 31.000 .009458

A04-24A 2F 111.470 222.795 30.200 .053260

' AN4-26A 2F 111.595 222.173 30.200 .056790

` NC-12 111.595 222.173 30.200 .037170

NC-5 111.595 222.173 31.000 .009458

MC-5 111.595 222.173 28.900 .009458

NC-12 111.595 222.173 28.500 -.437170

AN4-16A 2F 111.595 222.173 28.000 .042900

AM4-20 2F 111.905 222.017 30.200 .053260

NC-5 112.384 222.195 30.200 .009458

NC-12 113.157 222.014 30.400 .037110

AN4-11S 2FYR 111.256 219.964 30.200 .051630

06-105 111.256 219.964 30.200 .005842

AN3-6A 2T 114.215 222.525 25.200 .016580

CS-23 114.100 222.303 26.100 .051860

ti AN3-6A 2T 112.779 222.976 28.95u .016510

NC-110 113.615 226.194 29.050 .104200

ANS-23A IF 112.664 225.971 29.800 .075760

Eul

2.16

1
n

OF POOR QUALITY

Table 2.3.1 continued

171n IIRV VKF tRE ► Yi16HMIS.)

05-23A IF 112.571 226.576 29.800 .075760

MC-35 112.664 225.111 29.800 .009480

} MC-35 112.571 226.576 29.800 .009480

CS-21 111.995 224.629 20.000 .033680

CS-30 111.716 224.069 26.800 .008973

CS-27 112.862 223.915 28.000 .019250

CS-30 112.805 223.103 28.000 .006973

( HC-47 114.077 225.542 28.000 .138400

AN4-16A 2F 114.001 223.754 28.000 .042900

HC-57 115.384 224.033 26.000 .007253

AM3 -6A 2T 115.092 227.549 27.700 .016580

MHEELITIRE RT 111.651.1 205.643 15.100 5.430000

AXLE STRIP 129.670 240.523 13.700 .055660

AXLE STRIP 121.131 245.631 13.700 .055660

AN4 , 14A 2T 106.820 223.954 13.500 .036880

AN4 LONG 24 110.516 224.106 15.400 .060560

AN4-160 2F 101.393 .224.725 23.100 . .042900

MC-84 107.799 237.423 19.900 .250000

NC-14 107.799 231.4[3 19.904 .250000

REAR AXLE 110.341 237.494 15.500 7.007200

HC-9 106.236 237.716 30.000 2.021300

MC-25 99.860 237.212 30.200 .333000

NC-67 '100.316 228.854 30.200 .005842

AN4-244 1TSF

AN4-16A 2F

99.931

100.307

227.112

229.813

30.200

30.200

.052150

.042900

NC-12 100.417 229.083 30.200 .037170

AN4-16A 2F 99.480 244.135 30.200 .042900

NC-12 99.519 245.333 30.200 .037170

r MC-17 99.598 246.515 30.200 .005842

AM4-244 iT1F 99.645 246.631 30.200 .052150

NC-97(SEAT) 87.494 238.189 23.900 8.710000

.< NC-111 13.651 239.563 24.100 .975100

AM4-16A 2F 106.669 251.298 28.100 .042900

AM4-16A 2F 107.216 251.609 24.000 .042900

AM LONG 24 108.362 251.253 15.600 .060560

AM4-14A 2F 105.680 251.037 13.400 .039080

MHEELITIRE LF 109.292 269.427 15.200 5.460000

AN4-22S ITNR 105.668 251.992 30.000 .053240

`` 1 96-105 105.668 251.992 30.000 .005C42

AM4-264 2F 123.047 243.277 30.000 .056790

HC-12 123.047 243.277 26.600 .0371,70

HC-5 123.047 243.277 29.300 .0094,58

"C-5 123.047 243.277 30.900 103T170

t HC-12 105.936 249.572 31.300 -.037170

MC-5 105.936 249.572 30.900 .009458

AM4-24A 2F 105.936 249.572 30.000 .053260

004-24A 2F 105.928 250.526 30.000 .053260

MC-28 107.119 250.291 30.800 .037170

HC-5 107.070 250.176 30,400 .009458

AN4-17S 2FOR 107.768 249.876 30.600 .051630

AN5 3/4 24 106.235 247.210 30.000 .063710

AN5 3/4 24 106.432 246.177 30.000 .063710

#. NC-35 106.214 247.315 30.000 .009480

NC-35 106.283 246.433 30.000 .009480

NC-149 103.590 247.035 30.150 .465000

.t

2:17
Table 2.3.1 continued

ITEN NNEF VK F ZwEF MEIGHT(LIS.)

AN4-23A 2F 103.692 246.314 30.150 .051000

#N4-23A 2F 102.159 746.257 30.150 ,051000

NC-10 97.946 246.504 30.450 .439400

NC-27 92.106 249.215 20.150 1.540000

CS-38 97.595 244.625 14.600 .014770

NC-107 12.154 246.679 14.400 .562500

NC-7 76.322 245.798 31,500 2.540000

EN-95 70.097 240.493 40.200 .766800

NOSE CLAMP L6 70.218 244.182 32.700 .062170

NOSE CLAAP L6 73.363 245.002 32.200 .062170

CS-35 102.122 75.392 19.250 .747400

CS-34 102.663 15.142 18.150 .090170

AN3-5A 2T 100.961 15.221 18.150 .015500

AN3-5A 2T 104.459 16.109 18.150 .015500

ANI-5244 99.115 14.261 17.150 .013230

AN3-5A 2T 102.139 11.612 18.150 .015500

CS-37 101.111 91.671 18.750 .110900

AN3-5A 2T 101.517 1195.498 17.150 .015500

CS-36 101.599 101.647 16.950 .749600

CS-35 91.638 396.934 90.150 .747400

CS-34 92.050 388.494 19.850 .090170

AN3-5A 2T 90.936 388.627 19.850 .015500

AN3-5A 2T 93.832 398.453 19.850 .015500

ANO-524A 11.462 388.429 18.150 .013230

AN3-5A 2T 92.239 384.208 19.650 .015500

CS-37 92.042 381.041 89.450 .110900

AN3-5A 2T 92.598 376.145 18.950 .015500

CS-36 92.937 363.117 17.450 .749600

9IN6 FAO AT 106.384 129.054 79.100 8.125000

9IN6 FAB LF 100.808 345.850 79.800 1.125000

FUEL LINE ASS. 99.574 244.367 51.875 .435000

FUEL BULB 99.433 244.019 53.000 .106000

96-1 101.894 231.574 72.250 5.312500

PILOT 13.658 239.563 24.100 .000000

FUEL N16HT 108.669 229.580 22.900 .000000

FUEL LEFT 106.202 236.553 22.900 .000000

2.18
2.19

A

4 ^

R*

;, •

R

y .II

a

a

k

is

-

ORIGINAL PAGE 19

F POOR QUALITY

2.3.2 CENTER OF GRAVITY

The center of°gravity of the ultralight was calculated using a

computer program, listed in Appendix A, that used the coordinates and

weights of each item to sum moments about the reference axes and solve

for its moment arm. This moment arm was the location of the C.G.

relative to the reference axis. The component build-up method C.G.

locations are shown in Figures 2.3.2.1 and 2 . 3.2.20 The empty weight

C.G. is shown in these figures. Centers of gravity were also determined

for various loading conditions ( pilot weight and fuel on board). The

errors in measurement are addressed in Chapter 2.4.

2.3.3 INERTIAL QUANTITIES

The moments of inertia and products of inertia were calculated for

a body-fixed axis system with the origin passing through the C.G. and

parallel to the X, Y, and Z reference axis system shown in Figures

2.3.2.1 and 2.3.2.2. The inertias were calculated as follows:(slugs-ft.2)

Ixx' Ixx + W x ( Z2 + Y2)

p

Iyy Iyyp + ^: x (Z2 + X2)

IzZ• Izz + W x (X2 + Y2)

p

* subscript I p' represents principal inertia

IxyWx (X Y)

IXz• W x (X 4 Z)

I zy W x (Z x Y)

The principal inertias ofcomponents, which are defined here as

the contribution to inertia about its own C.G., were calculated by

hand knowing the component weight and individual geometry. This is

shown in Appendix D and the assumptions made are outlined there.

The results are presented in Figures 3.1-3.12.
2.20

W

W

a

1

e

W

C 4 .-i

O rl

(+ -4 N In

^ 0 N N N aCi U

^

00

• . 00 1

d

C

a ORIGINAL PACE IS

ry OF POOR QUALITY

tic

co

IL

N

1

^C

O

u

c

v

w

v

w

v

N

b

v

C

V4 w

vb

v

u

G

co

M

00

O

14

d

C

v

v

r+

N'

N

v

00 ,4W
a

/a

O

w

O

L^

V

C

V

v

WW

1

K

ORIGINA!' PlAfnE r

OF POOR QUALIV

.0

wd

O

M

N

C II

r-1 C

d 0

C c0

41 LI V y

.

. •

W4 V4 c" ol

V

C p n C u ^n W4 • • O^ +f 0000

O

O

fn 00 C N in fn W N

V M• N • ^•

u^1 .9 0 • 00 eo

^!u

M e b

V i+ u Nu '1 u r a y

w

w

a

as

C

a

d

u

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w

41

w

r~

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.d

X

W

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00

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2.21
r

2.4 WEIQ!UNG CHECK AND ERROR ANALYSIS

a

The build-up method outlined in the previous sections was checked

by weighing the assembled ultralight. This was done , to establish a

basis for comparison of the results}

The aircraft was placed on three scales at the same attitude as

the reference axes. The main gear scales leveled and zeroed prior to

setting the ultralight upon them. They were also calibrated by placing

known weights on them with the conclusion that within the expected 'range

of loading (100-150 pounds each) the scales were within 1 /2 pound or

0.33%. This was considered to be negligible for these purposes. The,

nose gear scale was also checked for accuracy and found to be within

1/50 of one pound, and was also assumed to be negligible.

} The ultralight was carefully weighed with the following results:

Attitude Nose Reaction Left Gear Right Gear

parallel to

reference axis 11.49 lb. 127.0 lb. 133.2 lb.

'. tilted nose

down 16 deg, --

102.5 lb. 103.2 lb.

ra` By summing the reactions measured by the scales, an aircraft weight

j

^

of 271.69 pounds was established. ' This differed from the component

r

build-upp ethod empty p weight of 277.48 g pounds, but as outlined i,n Appendix

` C the expected error is ¢ 7.183 pounds. The component build-up weight

w is within this error band.

The aircraft was tilted to determine the vertical C.G.. This

method is very sensitive to angle measurement and is very difficult to

measure accurately. A convenient angle of 16 degrees nose down was

' selected because without a pilot the tip-over ( on the tail) angle died

not allow the nose to be tilted upward. The experimental results are

ylisted below:

F± XC og 112.39 in. from reference axis

.-

Y - 234.27 in. from reference axis c.g.

Z - 56.89 in. from reference axis C. g.

2.22
}

2.23

ti

f

A^

^x

^r

'M

k

u Q

I5

The center of gravity as determined from component build-up

calculations is shown here with the error term listed alongside:

X 110.02 + 3.78 inches from reference axis

cogs -

Y 233.77 + 6.38 inches from reference axis

-

Z 58.91 + 1.74 inches from reference axis

cogs -

The build-up method errors due to measurements and inaccuracies

were calculated in Appendix C. Within the computed error bands the

C.G. locations as obtained from the two methods are in agreement.
4 3.0 DISCUOSION OF EXPERIMENTAL RESULTS

This chapter presents a detailed discussion of the results

L

x

achieved through the component build -up method for determining the

Sunburst ultralight C.G. and moments of inertia.

The center of gravity calculated from the build-up method compared

very well with that obtained from the entire vehicle weighing, with the

exception of the vertical C.G. ( Zc.g. ). The two methods results differed

by 2.02 inches but the expected error was only + 1.76 inches. This

is probably due to the weighing check procedure which calls for a

very accurate tilt angle measurement, Reference 3; also, the tilting

, f

method assumes a rigid aircraft which the ultralight is definitely not.

I' The X and Y reference C.G.'s (p. 3.2) were within the range of expected

error. The 

Xc.g. 

differed by 2.37 inches which is less than the predicted*

+ 3.78 inches, The 

Yc.

differed by only 0.5 inches considerably

%.

leas than the predicted + 6.38 inches.

The C.G.'s were computed with,the computer program of Appendix A

for different pilot weights and fuel loadings. The computer print-

►» out of these conditions are shown in Figures 3.1-3.12. The longitudinal

C.G. envelope, created by these various loadings, are shown in Figure 3.13.

It can be seen that the specified pilot weight range of 90 -260 pounds,

' from Figure 2.2.1, shifts the C.G. from 35.9% MGC to 23.4% respectively; 

w

a shift of 12.5% due to the pilot. This large C.G. range will probably

change the trim and control characteristics of the aircraft.

The vertical C.G. also changes from 50.38 inches for the 90 pound

pilot to 42.07 inches for the 260 pound pilot. The C.G.'s and inertias

a

are summarized in Table 3.1, page 3.2.

Predictions of expected errors are resented p p in Appendix C.

3.1
ORiGINAV P ^I-: d

OF POOR QUALITY

k

4

Measured Calculated

Aircraft pilot Fuel X

,

z

Aircraft Moment of nert 

Weight Weight Quan. c•g• e.g.g (slugs-ft.2)

lbs. lbs. gal. in. %MGC in. I

xx Iyy Izz 

277.48 01 0. 110.02 48.73 58.91 303.9 16.4 352.3 

293.00 ,0 2.5 109.93 48.56 57.00 308.1 16.5 352.3 

308.54 0 5.0 109.86 55.28 48.4 1 311.8 16.6 352.4 

1^3 5W T57 U 37o-. 3 '9 -37272 - 17.E 3E2.9 --

383.00 90 2.5 103.76 36.29 49.27 324.6 17.0 363.0 -

398.54 90 5.0 103.94 36.66 48.24 326.9 17.1 326.9 -

- $57.48 175- - a.

_

T9781 78:47 4574 37277 17.3- - '.675.1 -

468.00 175 2.5 100.11 29.04 44.70 334.5 17.3 369.4 -

483.54 175 5.0 A 100.38 29.57 44.00 336.1 17.4 369.7 -

537.48 260 0. 97.27 23.40 42.07 340.0 17.5 373.4 -

553.00 260 2.5 97.58 24.02 41.53 341.3 17.5 373.8 -

568.54 260 5.0 97.88 24.61 41.02 342.5 17.6 374.3 -

m

3.2

Table 3.1 C.G. and inertia summary.

R

X ^r

k

'c - 50.34 inches

L.E. Station - 85.49 inches

Centerline - 235.0 inches from axis

i

i
OR16INAL PAGE, fq

Y OF POOR QUAL17Y

E

—.r--^.r--rrrwrr ^r rr^.nr^------.err-rrrL ---------------

ULTRALIGHT WEIGHT- 277.461 (LOS) 

— --.— 

------------- ----------------------

1^---------.^

M f 

XCG IS i1A.036 IN. FROM X-REF

YCG IS 233.771 IN. FROM Y-REF.

s

ZCG IS $8.909 IN. FROM Z-REF.

C.G. IN PERCENT MGC 48.7259

***** INERTIAL QUANTITIES *******

. SLUG-SQ.FT.

IXX 303.096 IYY 16.383 IZZ 352.254 . ... •

Yi4Y -2. 458: IX2' 31. L5e^• IZY . -.429- ,.

Figure 3.1 Computer output listing for empty aircraft;

zero fuel and no pliot.

.

ULTRALIGRT. WEIGHT. 367.461 C LHS )

— —1 — — — — ----------- -- -- - — — — ------ ----r — -- --- —

XCG IS 103.562 IN. FROM X-REF

YCG LS 235.190 IN. FROM Y-FIEF.

ZCG IS 50.384 IN. FROM Z-REF.

C.G. IN PERCENT MGC 35.901% 

****** INERTIAL QUANTITIES ******

SLUG-SQ.FT.

IXX 322.162 IYY 16.951 IZZ 362.937

IXY -4.698 IXZ -6.991 IZY -3.386

Figure 3.2 Computer output listing for aircraft loading;

zero fuel and 90 pound pilot.

3.3
f

ORIGINAL CAGE W

OF POOR QUALITY

--------------------------------------------------

ULTRALIGHT WEIGHT- 452.481 (LBS)

---------- --rr----- wwr-------------w-----r-ww------R-

.

y

XCG IS 99.8,;3 IN. FRC'M X-REF'

YCG I5 236.011 IN. FROM Y-REF.

ZCG IS 45.447 IN. FROM Z-REF.

C.G. IN PERCENT MGC 28.473%

m***** INERTIAL QUANTITIES *******

E

SLUG-SQ.FT.

IXX 332.742 IYY 17.280 IZZ 369.125 '

"., IXY -5.995 IXZ -9.061 IZY -5.099

4 ^

Figure 3.3 Computer output listing for aircraft loading;

zero fuel and 175 pound pilot.

E^^,,r f

r

ULTRALIGHT WEIGHT= 537.481 (LBS)

- -- - - ----- --- - - - -- - -- - -- - -- - - w----------

XCG IS 97.267 IN. FROM X-REF

YCG IS 236.573 IN. FROM Y-REF.

2CG IS 42.071 IN. FROM Z-REF.

C.G. IN PERCENT MGC 23.395%

. * ***** INERTIAL QUANTITIE",, ; *******

SLUG-SA-FT.

t

IXX 339.974 IYY 111.505 IZZ 373.356 

IXY -6.881 IXZ -8.870 IZY -6.270

Figure 3.4 Computer output Listing for aircraft loading;

zero fuel and 260.pound pilot.

3.4
3.5

OF POOR QUALITY

------------------------ —'-----------1 r.+:s+------------

ULTRALIGHT WE GHT- 1

293.001 CLBS)

XCG IS 109. 921 IN. FROM X-REF

YCG IS 233.734 IN. FROM Y-REF.

ZCG I5 57.002 IN. FROM 2-REF.

C.G. IN PERCENT MGC 48.559%

 ^ INERTIAL QUANTITIES ** * ***

. SLUG-SQ.FT.

° IXX 348.05i IYY 16.513 I2Z 352.304

IXY -2 . 458 IXZ 2 . 875 IZY -.349

Figure 3.5 Computer output listing for aircraft loading;

2.5 gallons fuel and no pilot.

Y ^

W

'. ^. . 1,' • .' s ^ • i•.,, • '.• .• • i•I,•t ' ,• ... 1•'x,•1 

•

', •• •,'. 1• • •' • ,• • •

_ y s^/—r.i--o---.-----------tea--•--- -----------------------

.

ULTRALIGHT

-----------------

WEIGHT_

•

383.O01 (LBS)

-------------------------------- xco Ie 103.760 IN. FROM' X=REF

M

YCG I s 235 . 104 IN. FROM Y-REF.

2CG IS 49.271 IN. FROM Z-REF.

C.G. IN PERCENT MGC 36.293%

***** INERTIAL QUANTITIES a*****

SLUG-SQ . FT .

I X)C 324.645 IYY 17.028 I2Z 363.069

IXY -4.734 IXZ -6.737 IZY -3.199

Figure 3.6 Computer output listing for aircraft loading;

2.5 gallons fuel and 90 pound pilot.

a ^. a

G

F.

r

..
OF POOR QUALITY

—-------------------^---------------------------

ULTRALIGHT WEIGHT= 468.001 tLBS)

-------------------f---------------------------------

XCG IS 100.109 IN. FROM X-REF

YCG IS 235.914 IN. FROM Y-REF.

ZCG IS 44.699 IN. FROM Z-REF.

C.G. IN PERCENT MGC 29.040%

****** INERTIAL QUANTITIES*****

a SLUG-SQ.FT.

d• ^.w

IXX 334.456 IYY 17.333 IZZ 369.432

IXY -6.079 IXZ -8.905 IZY -4.884

F^

Figure 3.7- Computer output listing for aircraft loading;

*; r 2.5 gallons fuel and 175 pound pilot.

Y

•^• -- — — — ---- ----- ---^--- — -- -- — —r ------------------- --

ULTRALIGH Y wr.IGHTa 553.001 tLBS)

—•-----------• -------- -------

XCG " IS 97.580 IN'. FROM X-REF

YCG IS 236.474 IN. FROM Y-REF.

=3 2CG IS 41.533 IN. FROM Z-REF.

C.G. IN PERCENT MGC 24.017%

****** INERTIAL QUANTITIES *******

SLUG-S©.FT.

IXX 341.251 IYY 17.544 IZZ 373.842

IXY -7. 012 IXZ -8.848 IZY -6.051

F Figure 3.8 Computer output listing for aircraft loading;

2.5 gallons fuel and 260 pound pilot.

k

b

3.6

le4

39

1
0

NAL PAGe t,7

OF POOR QUAL17";+

— — — — — — — — -------------------- - — -- — -- — — — —

 -----------

ULTRALIGHT WEIGHT= 308.541 (LBS)

— — — — — — — — — — — — — -- T ------------------------------------

XCG IS 109.859 IN. FROM X—REF

YCG IS 233 . 709 IN. FROM Y—REF.

ZCG IS 55.284 IN. FROM Z—REF.

C.G. IN PERCENT MGC 48.408%

****** INERTIAL QUANTITIES *******

SLUG—SQ.FT.

IXX 311.800 IYY 160,629 IZZ 352.354

IXY —2.457 IXZ 2.625 IZY —.276

Figure 3.9 Computer output listing for • aircraft loading;

5,0 gallons fuel and no pilot.

f

Et

$

.m YYY

^b

^ tiu

-------------------------------------------------- 

ULTRALIGHT WEIGHT- 398.541 (LBS) 

XCG IS .103.942 IN. FROM X—REF

YCG IS 235.024 IN. FROK Y—REF.

ZCG. IS. 48.•242 • IN. FROM Z.-REF,•.. z •• .

C'. G: -IN 'PERCENT MGC .• 

******* INERTIAL QUANTITIES **a 

SLUG— SQ.FT. . 

IXX 326.942 IYY 17.100 I22 363.194

IXY -4 . 767 IXZ —6.540 IZY —3.025

Figure 3.10 Computer output listing for aircraft loading;

5.0 gallons fuel and 90 pound pilot.

Y4.0 

3.7

s+

bk
OF POOR QUALITY

--•------------------------------------------------

ULTRALIGHT WEIGHT= 483.541 (LBS)

47

------------------ -r --------------------------------

XCG IS 100.377 IN. FROM X-REF

YCG IS 235,822 IN. FROM Y-REF.

ZCG IS 43.998 IN. FROM Z-REF.

C.G. IN PERCENT MGC 29.572%

** ***** INERTIAL QUANTITIES ******

r SLUG-SQ.FT.

IXX 336.067

-6.159

IYY 17.383 IZ7. 369,726

IXY IXZ -8.750 IZY -4.6e2

s

Figure 3.11 Computer output listing for aircraft loading;

5.0 gallons fuel and 175 pound pilot.

Tv

jx

-- - - - - -- - -- - -- - - - - -- - - - 0 ► -- - -- - - - - -- - - - - -- - -- - -- - --

ULTRALIGH•T WEIGHT='- 568.341 (LBS)

.► ^-r'^^^^r3,1^^^rr-i^j.rrrrrr^r^^r,^-.^rr^r,r rr-err-rr,rr-rr- . 

XC'G 15 97.877 IN. FROM'. X-REF

YCG, IS 236 . 381 IN. FROM Y-REF.

ZCQ•:; I:S;,.',:,_ ' ^.1: 023., Uk. ,: f ROM. ; Z--REF :.

C.G. IN PERCENT MGC 24.607%

***** INERTIAL QUANTITIES*****

SLUG-50 FT

IXX 342. 463 IYY 17.582 IZZ 374.306

IXY

-7.135 IXZ -8.814 IZY -5.844

T

Figure 3.12 Computer output listing for aircraft loading;

5.0 gallons fuel and 260 pound pilot.

,d

.f

3.8
k ORIGINAL PAGE IS

OF POOR QUALITY

590

260 LS PILOT SUNBURST ULTRALIGHT

550 1 COMPONENT BUILD— UP

CENTER OF GRAVITY

ENVELOPE

1 MAKWUM FUEL. 54AL =31.0SLV.

510 1 c =4. 195 Fr,

ITS LS, PILOT

CL 470

,y 1

V^

430

W

90 LS. PILOT \

Sgt "' 390 ^^ \ FULL FUEL

i ^ \

h

' EMPTY

Q

U 350 \ 

310 No PILOT N\

EMPTY 27T. 48 WE14 HT

w" 2 TO

tO 2O 30 40 5fl

CENTER OF GRAV ITY s.4.ev MCC

m

A eALt ll1o l>< ka • 10 83 *8VlS[D OAT[ Figure 3.13 Ultralight longitudinal

CMSCK AW 12-20-81 experimental flight envelope for

APeO pilot and fuel loadings.

APrD

rAG9 

3.9 K.U. Center for Research Inc.

w 

vna^'
v

4

pn

^, x

4,' r a

n

1

1

4.1

A

r

4.0 CONCLUSIONS

The first and most critical conclusion is that the Airmass Inc.

Sunburst Model ' C' ultralight is in fact not an ultralight as defined

by the FAA regulation of maximum empty weight of 254 pounds. This

ultralight was found to have an empty weight of 277.48 pounds ( component

build-up method) and 271.69 pounds measured weight. These differ

substantially from the published weight by Airmass Inc. of 240 pounds

empty, see Figure 2.2.1.

The center of gravity location of this aircraft is greatly

affected by the pilot ' s weight. A stability and control report that is

planned for the future will give a detailed analysis of the effect of

C.G. on controllability. 
5.0 REFERENCES

1. Airmass Incorporated assembly manual furnished with the Sunburst

Model 'C I ultralight f 1983.

2. Beer, F.P., Johnston, E.R.,Jr., " Vector Mechanics for Engineers:

Dynamics," 3 rd Edition, McGraw-Hill, 1977, pp.9321-951.

3. Schweikhard, W.G., Kohlman, D.L., " Flight Test Principles and

Practices", University of Kansas,1983.

4. Tipler,P.A.,"Physics",Vol. 1, 2nd Edition, Worth,New York,1982,

pp. 274-387.

5. Peery, D.J., Azar, J.J.,"Aircraft Structures', 2 nd Edition,McGrawHill, 1982, pp. 409-424.

5.1
APPENDICES

6.1
APPENDIX A

WEIGHT AND BALANCE

COMPUTER PROGRAM
0001.000

0002.000

0003.000

0004.000

0005.000

000b. out$

0007.000

0008.000

0009.000

0010,000

0011.000

0012.000

0013.000

0014.000

0013. 000

0016.000

0017.000

0018.000

0019.Ono

0020.000

0021.000

0022.000

0023.000

OOc^_3.100

0024.000

0026.000

0027.000

0026.000

0029.000

0030.000

0031.000

0032.000

0033.000

0034.000

0035.000

0036.000 E

0037.000

0038.000 i

0039.000 1

0040.000

0041.000

0042.000

004 3.000

0044.000

0045.000

0046.000

0047.000

0045.000

0049.000

0050.000 i

0051.000

0052.000

0053.000

0054.000

0055.000

^a

yI

ORIGINAL PAGE 19

OF POOR QUALITY

C THIS PROGRAM COMPUTES THE ULTRALIGHT CENTER OF GRAVITY AND

C MASS MOMENTS OF INERTIA.

C 1. IT READS FROM A DATA-FILE P MEASURE' AND OUTPUTS TO 'COORDP

C 2. SUBROUTINE REDUCE CONVERTS THESE INTO XPYIZ COORDINATES

C 3. THIS MAIN PROGRAM COMPUTES THE WEIGHT AND BALANCE

C ( C.G.PIXKPIYYPIZZPIXZPIXYPIZY)

C

C *wwrwwww»,^wMwrrrwwrrwrrr*w**wrw*rwr*rrrw*rr**s:r, ► Mwrwr**wMww*wrrwww

C

C THIS PROGRAM WAS DEVELOPED BY JOHN A. WOLTKAMP(SUMMER 1983).

C THIS VERSION WAS WRITTEN FOR THE GOULD BEL 32/77 COMPUTER

C WITH DUEL PROCESSOR AND SHARED MEMORY WHOSE SERVICES WERE

C GRACIOUSLY MADE AVAILABLE BY KOHLMAN SYSTEMS RESEARCH IN

C LAWRENCE KANSAS.

C *wwwwwr+rww»wwwwwwwwwr*rwrwwwwrwwwwwwaa.wwww*www*wwwwe*wwwwwwww.*ww*ww

C DECLARE REALS AND INTEGERS

REAL W(600)PXWC600)PYW(600)PZW(600)PWXSUMPWYSUMPWZSUMPWSUM

REAL MARGIHPCSARPCO

REAL CENTXPCENTZPCENTYPXC600)PY(600)PZ(600)PZDIRMl600)P

i HDIST(600)PPSI(600)

REAL*4 IXXPIYYPIZZ.IXZPIXYPIZYPIXXPOIYYPOIZZPOIXZP

INTEGER NUMPTS

CHARACTER ITEM(600)*iSPSETNAME*4PFILENAME*SOFILECORD*5

sPFILEOUT*5

CHARACTER*2 ANS

REAL*4 DUMMY(60005)

C

C INITIALIZE ARRAYS

C

C TYPE*P'HOW MANY MEASUREMENTSCITEMS) T >>>p

C ACCEPT*ONUMPTS

CBARx4.195 1 FROM S/C ESTIMATION REPORT

DO I:101000

X(I):0.0

Y(I)z0.0

Z(I):0.0

W(I):0.0

XW(I):0.0

YW(I):0.0

ZW(I):O.O

END DO

C

TYPE * P'WHAT INPUT FILE TO OPEN >>'

ACCEPT i11PFILENAME

SETHAME:PPREP'

OPEH4UNIT:5PFORM:'FORMATTED'PSTATUSx'OLD'PIOSTAT:IIPERR:5150

iSLOCKED:.TRUE.PUSER:SETNAMEPFILE:FILENAMEPFILESIZEa70)

xt r W, 00 TO 13

s1s TYPE*P'******* ERROR IN OPEN *******'

1 STOP

C LOAD MEASUREMENTS INTO DUMMY ARRAY TO DECLARE THE REAL **

c

13 DO 3:103

READ(5P510)

END DO

d.

a

A.l 

A
ti

ORIGINAL PAGE IS

OF POOR QUALITY

g'

,-e

v

510 FORMAT(' P)

DO I:101000

READ(5 ► 102PEND:600)ITEM(I)

102 FORMAT(5X#A1S)

END DO

a00 REWIND(UNIT:S)

DO J:1 ► 3

READ(5#5l0)

END DO

DO Iz1.3000

READ(5#105PEND:900)(DUMMY(I#J)*J:2#5)

10:5 FORMAT(20X#4(F10.7))

DO J:205

C TYPE * #DUMMY (I#J)

C TYPE 102PITEM(I)

END DO

END DO

900 CLOSE(UNIT:5)

NUMPTS:I-1

C

C ASSIGN VALUES TO Z-DIRM#HDIST #PSI.AHD WT

C

DO Kei#NUMPTS

ZDIRM(K):DUMMY(K#2)-/12

NDIST(K):DUMMY(K#4)/12

PSI(K):DUMMY(K#3)

W(K):DUMMY(K#S)

C TYPE*#'ZDIRM:'#ZDIRM(K)

C TYPE*#'HDIST :'PHDIST(K)

C TYPE*#'PSI:'#PSI(K)

C TYPE*#'WEIGHT-'PW(K)

C TYPE*.'ITEM:'#ITEM(K)

END DO

TYPE* ► "FILE NAME TO STORE REFERENCE COORDINATES ?'

ACCEPT lii#FILECORD

OPEN(UNIT:3#FORMr#FORMATTED'#STATUS:'UNKNOWN'PERR:315

&P.SLUCKED:.TRUE.#USER:'PREP'#FILE:FSLECORD ► FILESI2Es70)

CALL REDUCE(NUMPTS#ITEM#W#ZDIRM#NDIST#PSIPX#Y)

111 FORMAT(A)

CLOSE(UHITs3)

C ***r INITIALIZE INERTIA ARRAYS ****

C

WSUM:0.0

WxSUM:0.0

WYSUM:0.0

.WZSUM:b.O

IxxxO.O

IYY:0.0

IZZ:0.0

IXZ=0.0

IXY:0.0

IZY:0.0

C

C CALCULATE VALUES OF WSUM#XW(K)#YW(K)PZW(K)#WXSUM

C WYSUM#WZSUM

0050.000

0057.000

0058.000

0059.000

0060,000

0061.000

0062,000

0063.000

0064.000

0065.000

0066.000

0067.000

0068.000

0069.000

007 0. 000

0071.000

0072.000

007 3. Wo

0074. 000

0075.000

0076.000

0077.000

0078,000

0079.000

0060.000

0061.000

0002. 000

0083.000

0084.000

0065.000

0086.000

0087.000

0088.000

0089.000

0090.000

0091.000

0092.000

0093.000

0094.000

0095.000

0096.000

0097.000

0098.000

0099.000

0100.000

0101.000

0102.000

010 3.000

0104.000

0105.000

0106.000

0107.000

0108.000

0109.000

0110.000

A.2
ORIGINAL 

OF p00R QR^pl.i'i'Y .,

C 011).000

DO lzl,NUMPTS 0112.000

WSUM:WSUM+W(I) 0113,000

XWtI):X(I)

YW(I):Y(I)*W(I)

*W(I)

0114.000

0115.000

' Z(I):ZDIRM ( I) 0116.000

ZW(I):Z ( I)*W(I) 0117.000

WXSUMZWXSUM+XW(I) 01181000

WYSUM:WYSUM+YW(I) 0119.000

WZSUM:WZSUM+ZW(I) 0120,000

END DO 0121,000

TYPE M ,'ULTRALIGHT WEIGHT-'PWSUMP'(POUNDS)' 0122.000

C 0123.00u

C ** CALCULATE CENTER OF GRAVITY ** 012 4,000

C 0125,000

CENT)(:WXSUM/WSUM 0126,000

CENTY:WYSUM/WSUM 0127.000

CENTZ%WZSUM/WSUM 0128.000

CG:((CENTX-85.49/12)/C3AR)*100 0129.000

TYPE*,'CGX;'rCENTX,'CGY:'PCENTY,'CGZ:',CENTZ,' C.G,. 'PCG 0130.000

F` C****w*r* *rr*rsr*****ra*r**r*rra* * rrr**r*r*rr*r ** w*s**rk .w*srr*****r* n 0131.000 y

C CALCULATE MOMENTS OF INERTIA ABOUT STABILITY AXIS 0132.000

- ` C 0133.000

DO I:1,NUMPT6 0134.000

IXX:IXX+W ( I)*((Z(I) - CENTZ)**2+(Y(T)-CENTY )**2) 0135.000

C 0136.000

IYY:IYY*W(I)*((Z(I)-CENTZ)**2+(X(I)-CENTX)**2) 0137.000

0138.000

IZZ:IZZ+W(I) *((X(I) -CENTX)**Z+(Y(I)-CENTY)**2) 0139.000

o C 0140.000

C PRODUCTS OF INERTIA ( IXY,IXZPIZY) 0141.000

C 0142,000

IXY:IXY+WtI )*(( X(I)-CENTX )*( Y(I)-CENTY)) 0143.000

IXZ:IXZ+W(I)*((X(I)-CENTX)*(Z(I)-CENTZ)) 0144.000 f

IXZ:-IXZ ! CHANGE SIGN OF Z-AXIS 0145.000

k» IZYsI2Y+W(I)*((Z(I)-CENTZ)*(YtI)-CENTY)) 0146.000

w END DO 0147.000

C 0146.000

C TYPE*P'DO YOU WISH TO ADD PRINCIPAL INERTIAS?>N' 0149.000

C 0150.000

C ACCEPT 111PANS 0151.000

3

". C IFtANS.E©.'N')THEN 0152.000

C IXXP:O. 0153.000

C IYYPaO. 01.54.000

C IZZP:O. 0155.000

C IXZP:O. 0156.000

.?r' C ELSE 0157.000

C TYPE*.'ENTER IXX SUM OF ALL COMPONENTS CONSIDERED(SLUG-FT**2)>' 0158.000

C ACCEPT*PIXXP 0159.000

C TYPE*.'ENTER IYY SUM OF ALL COMPONENTS COMSIDERED(SLUG-FT**2)>' 0160.000

C ACCEPT*,IYYP 0161.000

C TYPE*P'ENTER IZZ SUM OF ALL COMPONENTS CONSIDERED(SLUG-FT**Z)>' 0162.000

C ACCEPT*PIZZP 0163.000

C TYPE*,'ENTER IXZ SUM OF ALL COMPONENTS CONSIDERED ( SLUG-FT*92)>' 0164.000

C ACCEPT*PIXZP 0165.000

f

I i

a

f

A.3

m
is

L"

ORIGINAL, PAGE 19

OF POOR QUALITY

C ENU Ir 01E.E1000

C CONVERT TO SLUG-FT**Z AND ADD PRINCIPAL INERTIAS 0167.000

l y,P %(10/32,170+52.569 0160.000

IYYr(IXX/3Z.174t +1.9311 0169.000

IZZ :(xZZ00 3Z.174)+i2.564 0170.000

IXY=IXY/32.17.1 0171.000

iXZa(IXZ/32.174)+,276 01720000

IZY:IZY/32.174 0173,000

TYPE* ► 'IXXs'PIXXO' IYYs'OIYY 0174.000

TYPE*P'IZZ:'0I2ZP' IXYs' ► IXY 0175,000

TYPE* ► O IXZZ'PIXZ ► ' IZYs'OIZY 01760000

C A******* OUTPUT TO FILL ++ Mrw** rr 0177.000

C 0170.000

TYPE*0'CNTER FILENAME TO OUTPUT INCRTIA FILE) >' 0179.000

ACCEPT 1i10FILEOUT 01601000

C rILEOa'FILEOUT' 0181,000

OPEN(UNIT: 9 ► FORMe'FOROATTED'PSTATUSe'UNKNOWN'P9LOCXED: 0162.000

i.TRUC.PFILE:FILEOUTPUSER:'PREP'.IOSTATzliPERR:5i5.rILCSIZEcTO) 0163.000

c 0184, 000

C ***»* FORMAT FOR OUTPUT OF ALL CALCULATIONS 0195.000

C 0196.000

TYPE 100P WSUM.CENTXOCENTYOCCNTZPCG PIXXPIYY*IZZP 0167.000

6IXY,IXZrIZY 01061000

0196,000

CENTXsCESTX*12 0199.100

CENTY:CENTY*i2 0199.200

CENTZsCCNTZ*12 0199.300

WRITE(6 ► 100) WSUMPCENTX.CENTY.CENTZ ► CG.IXXi%YY02ZZPtXYPIXZ ► 14', 0190.000

C &lxY.IXZ ► IZY 0191.000

100 FORMAT(liX.'--------------------------------------------------to/ 0192,000

1 ► 1OX.'ULTRALIGHT WEIGHT:' ► ri0.3 ► ' (LBS)' ► / 0193.000

2 .SOe{P ----------------------------------------------------- ' ► / 019 4.000

30/PiZX 'XCG IS '0r10.3P' IN. FROM X-REF 'P/ 0195.000

4012X ► 'YCO IS 'PF10.3.'•IN, FROM Y-REF. './ 0196.000

5012X.'ZCO IS '.F10.3 ► ' IN. FROM Z-REF. './ 0197.000

601ZXP'C.O. IN PERCENT MOC 'PF10.3P'%G'. // 0199.000

7012X ► ' ******* INERTIAL QUANTITIES './ 0199.000

9012X0' SLUG-SG.FT. ' ► .1 0200.000

90.1 012X ► ' IXX ' ► !10.3 0 t. IYY ' ► F10.3 ► ' IZZ '0F10.3 P.1 0201.000

101ZX.' IXY ',F10.3 P' IXZ ' ► r10.3 P' IZY ' ► F10.3 P/) 0202,000

C 0203.000

CLOSE(UNITci) 0204.000

STOP 0203.000

END 0206.000

Err*•rrM+ rrr#r*rr*rr*rrrrrr*rr*r**r**r**rr *******r***nrs**r*r****nM*****0207.000

C ******** SUBROUTINE REDUCE THAT CONVERTS TO X ► Y ► Z COORD.* ******** 0209.000

C ***rr,r +** *rw*********** rrr*******rr**r**r***rr***rr**r***0r**** 0209.000

SUBROUTINE REDUCE(HUMPTSOITEMPWPZDIRMPHDISTPPSI.XDIR.YDIR) 0210.000

C 0211.000

C *+* READ INPUT DATA ****y+*** 021Z.000

C THIS SUBROUTINE CONVERTS THE Z-DIRECTION MEASUnEMENT.HORIZONTAL 0213.000

C ANGLE(PSI) THE MEASURED HORIZONTAL DISTANCE(HDIOT) INTO X.YPAND Z 0214.000

C COORDINATES (REFERENCED TO AN ARBITRARY AXIS). 0215.000

REA6*4 ZOIRM(600). HOIST(600) ► PSI(600) ► W(i00)POUMMY(i00.S) 0216.000

REAL*4 XDIR(600)PYDIR(600) 0217.000

A.4
4.

;

a'

t

^ zr

w ^

^Y

r

E.I OF R©QR Q

h .

C 0216.000

'

INTEGER NUMPTS 0219.000

C 0220.000

CHARACTER ITEM(200)*15 ► MEA$URE(600 ► 5) 0221.000

C 0222.000

C 022 3.000

C an BEGIN CALCULATIONS *+ 0224.000

DTOR:3.1415/160 0225.000

C REMEMBER TO READ PAST BANNER • 0226.000

WRITE(3 ► S4) 0227.000

54 FORMAT(SX ► 'THIS FILE COORD CONTAINS X ► Y ► AND Z COORDINATES'. 0226.000

S/.'WHERE Y AND Z ARE CALCULATED • . 3 ► ' ITEM '.5X► ' XREF OR29.000

L '.SX► ' YREF '.5X ► ' ZREF '.6X ► 'WEIOHT(L2S.)') 0230,000

DO Ks1rNUMPTS 0231.000

XDIR(k):HDIST(k)*COS(PSI(K)*DTOR) 0232.000

YDIR(K):HDIST(K)*SIN(PSI(K)*DTOR) 0233.000

C 0234.000

C *+ !FEND THE NEW COORDINATES ZDIRM ► XDIR ► YDIR TO FILE 'COORD' ** 0235.000

@4RITE(3 ► 55)ITEM(K) ► XDIR(K)*12 ► YDIR(K)*12 ► ZDIRM(K)*12 ► W(K) 0236.000

SS FORMAT(SX ► A1SriX ► F10.3 ► 3X ► F10.3 ► 3X ► F10.3 ► 3X ► F10.6) 0237.000

0236. ,400

END DO 0239.000

RETURN 0240.000

END 0241.000

r Y

1
^^ I \

^^ ^

r ^ ]\

^ ^ /\

/ ^^

APPENDIX B

PARTS LIST WITH

DESCRIPTION

B. i

[\ ^^

/ ^

<

\ ^
This appendix presents the parts list of all components (Table B-1)

and the actual assembled ultralight parts list (Table B-2).

Table B-1 was compiled of all parts received, with a corresponding 

description. Table B-2 consists of only those components used for

,k

assembly.

k

t

{•

t

L•

t

K

v

I

L
i

,^V

z

f

t•^

ORIGINAL. PAGE 19

OF POOR QUALITY Tables Preassembly parts list

(includes all parts received).

Part Number Name (ivan_ Descrinti.on,_

HC-6,7 Hang, cage frame ( 1 each) 50.5 ":s 1 .75"

tube assemblies

HC-10 :-sang cage frame (2) 14" x 1.875 11

tube sleeves

1:C-13 Control Stick (1)

Clamp

HC,-109 ' T' Brackets (2)

HC -8 ?rout Carry-thrn (1) 22'.8751@ x 1.125 1 ) o 

Tube

EC-11 'U' shaped radius (6)

based brackets

HC-12 'U' shaped scuare (10)

• based brackets

EC-87 Black Plastic M Designed to

Saddles fit 1 . 875 11 'tube

:iC -9 Rear Carry-thru (1) 30":c1 .875" GD

tube assembled with 1.75 11 OD tube

inside

i

i

rt

M

EC-28 Lower Boon Square (2)

'U' shaped brackets

HC-5 r luminum Saddles (10)

HIC-110 Rear Control Stick (1

Bracket with ' L'

Shaped Flange

HC-35 Aluminum Saddles (4)

HC- 1

Front Vertical (2)

Strut Tube

KC-88 Black Plastic (8)

Washers

HC-3 Rear Vertical (2)

Strut Tube

B.2

Designed ,.to fi t

1.875" 0D tube 

0.25" hole in c

Designed to fit

1.875 " CD tube 

0.3125" hole in 

' 43.5"x1." GD

0.625" CD x 0.2

43 11 x i ll GD
Rear Diagonal (2) 51.75"x1" CD

S tru.+ Tubes

main Gear Support (2) 72 11x1" OD with

Strut Tubes *"x1.12511 OB Slee

Cross Support (1) 36"x1" OD

Tube,

train Gear Cross (2) 28.2511 center to

Support Cables center of tangs

Black Elastic (4) 1" OD 0.9375" ID

Elug

Root Tube (1) 57.751lx2" Square

Front King Post (2)

Brackets

Rear King Post (2)

Brackets

Inboard Section (1 each) 78.5 "x1 .?5" CD wi

of Spars 1.875" OD sleeve

Outboard Section (2 each) 84"x1.75" CD with

of Spars a wooden plug

Center Section (1 each) 70.5625"x1.75" CD

of Spars with 1.875 1 ' sleev

I Shaped U (8)

Bracket

Inboard Cable (2) 82.75 " Center to

Assembly Center of Tangs

Cutboard Cable (4) 85" Center to

Assembly Center of Tangs

Slide Tube (4) 10"x1" CD with.

:assemblies Slotted Tube and

Knob Attached

WJZ-94 Compression (4)

Springs

W%-92 Inboard Cable (2) 80.75 " Center to

Assemblies Center of Tangs

B.3

Table B-1 continued

Fart Number

HC-2

EC-27

HC-53

HC-84

HC-5 7

';JG-1

WG-8

G-36

WG-279WG-42

(A11E19C1,D1)

WG-37 9 WO-38

WG-33 9 43T-40

(2,B2, C2,D2 )

`*-5 3

WG-5 6

WG-5 7

WG-93

ORIGINAL. PAGE IS

OF POOR QUALITY

Name (ouant.) Description
ORIGINAL PAGZ IS

Table B-1 continued OF POOR QUALI TY

Part Number Name (Cuant.) Description

'SIG-46 Compression (2) 17.75 "x1" OD

Strut Tube

WG-47 Compression (2) 17.75"x1" CD

Stmt Tube

WG-77 Spoiler Pulley (2)

Assembly

WG-54 Black Plastic (20) 0.625" CD 0.25" ID

Washers

WG-21 PTP pin (1)

WG-62 Leading .Frdge Rib (2) 6"x1 .875" CD

Tip Sleeve

'dG-63 Rear Spar Tip (2) 6"x1.875" CD

Sleeve

#IG-87 Tip Rib Tubes (2) 50"x1" CD at

Center Line

'fG-60 Black Plastic (10) 1" OD 0.875" ID

Plugs

WG-66 Batten Tubes (12) 61.75"x0.5" CD

with black plastic

tips

gv-1 Tail Section (2)

Fabric

KU- 2 'rail Frame (2) 4 Fi ec es (3 surface

- frames, 1 elevator

frame)

TS-11 Leading Edge (2) 25.5"x0.75" CD

• Stabilizer Tube

TS-23 Aluminum Insert (2) 1" long x 0.625" C

for TS-11

TS-39,38 Stabilizer Mounting (leach) 9.125"x1"x0.1875"

Bracket aluminum Angle

TS-37 Stabilizer Mounting (2) 9.125"x1 "x0.1G-75"

Bracket Back-Up Flat Aluminum

Plate plate

B.4
Table B-1 continued ORIGINAL PAGE 19

OF POOR QUALITY

Part Number Name ant.)

TS-28

t

Aluminum Inserts (6)

y /

S-8,7 Upper Diagonal ( 1 each)

Tail Tubes

TS-6 0 5 Lower Diagonal (1 each)

Tail Tubes

TS-36 NLtxer Assembly (2)

Mounting Brackets

TS-20 Ac tuator firm (2)

Control

TS-26 ' L' Shar eed Stainless (8)

Steel Brackets

TS-29 00 Bell Crank (2)

TS-31 Black Plastic (4)

Saddle

TS-21 Spreader Bar (1)

Assembly

TS-66 Range Grip Clevis (2)

Pin

T3 -33 Ring Pin (12)

TS-25 Triangle Shaped (2)

Tang

TS-49 Wing Nuts (28)

M-34 Black Plastic caps (2)

TS-69 Mixer assembly (1)

KU - 3 gear :axle' Assembly (1)

IIC-67 Bungee Chords (2)

KC-107 ,Landing sear (2)

Suspension Cables

B.5

Descrintio.__n__

Designed to fit

0.875" CD Tubes

4 5.5', x 1 l' CD with

Large Bend

44.5 "x 1 " GD with

Small Bend

13.75"x1" CD

1.625"x0.7511x0.5"

Designed to fit

TS-'9', 30 

72"x0.625" CD 

0.1875"x0.625"

Designed to fit

0.625" ID Tube

0. 375"x36"
Table B-1 continued ORIGINAL PAGE iS

OF POOR QUALITY

Part Number Name 'want. Description

HC-58 Main wear Wheel, (2 each) 20" in Diameter

Tire, and Tube

ICU-4

M

Nose gear (1 ) 'Assembled at the 

Assembly Factory

NC;- 17 Cable Mounting (1) Cast Aluminum,

Bracket 'L' Shaped with

Small Diagonal

Slot

NG-21 Black Plastic (2) 0.625"x0.25" ID

Washers

NG-49 Nose Gear; Tire (1) 16" in Diameter

DIG-50 Nose Gear Tube (1 ) 16x2.125

HC- t

97 _t <,. u eati ^+l,j ^ ( 1 )

HC -25 Seat Sling Back ( 1 ) 15.751°x1" C.D

Rest Tube

HC-91 All Threaded Rod (1) 17.875"x0.25"

28 threads

HC-120 Sleeve Tube (1) 16.511x0.5" CD 

ET-22 ,Fuel Tanks (2) 2.5 gal lons/tank

NG-5 3 Threaded Rods (2) 3"x0.25 "-28 thread

Ns-27 'Heim'-Ball Swivel (4) Joints

CS-24 'L'-Shaped Torque (1)

Tube P:ounting

Bracket

CS-21 'PVC' 'white Plastic (2)

Bushings

CS-26 Torque Tube (1) 3311x1" CD

B.6
Table B-1 continued ORIGINAL PAGE IS

OF POOR QUALITY

Part Number Name (Qaan.t. De_s_ riiotion

CS-21 (Steel) Rear fiorque Tube ( 1) 1"x1.125" CD

Sleeve Bushing

CS-30 Large Plat Washers (3)

CS-22 Joy Stick Control (1)

:assembly

CS-28 Black Plastic (5)

Washers

HC-47 Rear Torque Tube (1 )

Bracket

CS-23 Swing Arm Bracket (1)

CS-25 Short Control Tube (1)

WG-2,3 King Post Tubes ( leach)

^4G-5 2 :zing Pins (8)

W11-71 Inboard wound (1)

Cable assembly

.,/G-72 Cutboard wound M

Cable Assembly

WG- 35 Black Plastic L4)

Saddles

CS-35936 Spoiler Flap (2 each)

Stiffeners

CS-37 Spoiler Joining (2)

Plates

CS-34 Spoiler :activator (2)

Arms

.T.'-73,74 Flying Cable (2 each)

Assembly

W41 -105 Shackel Spacers (2)

i!G-75 Forward Cable (2)

Assemblies

'1" ID x 1.25" CD

0.525" Cy x 0.25" I

one end has swivel cl evi s

48"x1" CD assembly

includes wrap

brackets

Designed to fit

1.875" OD Tube

4.751lx31.75"

Plat Steel

2.5 "x9"

0.2511x0- 5 "x7-5"

Slightly Bent

1.1875"x0.5" CD

77.75 1, length

B.7
Table B-1 cont«tued ^. ORIGINAL PAGE IS

OF POUR QUALITY

Part Number Name truant, Description

NG-20 Nose ,Grear Cable ( 1) 50.75 length

•&ssembly

'+^^ -13 Root' Tube Plug (1)

n

WQ -67 Black Plastic (12)

Batten Tube

Protective Caps

TS,-3 9 4 Upper Boom Tube (1 each) 93"x1.125" CD

WG-97 Radius Based 'U' (2)

Shaped Bracket

TS-1,2 Lower Boom Tube (1 each) 97"x1.125" CD

TS-33 Ring Pin (1)

TS-19 Rudder/Elevator (2) 32" Long x 0.5" CD

Control Rod

TS-22 Long Elevator (1) 88.75"x0.75" OD

Control Rod

CS-46

.A

Spoiler Control (1) 43.5"x0.625" OD

Rod

P. CS-33 'L' Shaped Spoiler (1)

Bracket

CS-32 Spoiler Triangle (1)

counting Plate

CS-42 Stand -Off Bushing (1)

CS-39940 Spoiler Cables ( 1 each) Cable bushing at

one end and nothin

on the other end

CS-38 Long Bun-gee Chords (2) 0.12511x20"

CS-47 Spoiler Cable Assem. (1)

( N:^-18 Brass Lisconnect (1) Desi„ned to fit

Lever JG-17

B.8
Zescription

30 HE 2-Stroke

Cuyuna Engine

Clear Plastic

Preassembled

Short Sleeve to

fit over engine

output shaft

Chrome-holy Steel

Set includes mount

kit for the Root

Tube

•%luminum cast fram

flange mounted bea

assembly, 2-turnbu

assemblies, 4 gro

pulley bearing, an

shaft assembly 

Pulley belts

541l x27" pitch

Connected to

Lever

Table B

-1 .continued

. . ORIGINAL. PAGC 19

OF POOR QUALITY

rr

h+

dt'

r. .

^J

F:

4

G

^, m

w

^R

k4

i

Fart lumber Name ' iant,. I

03-50 ' Heim'' Ball Swivel (1)

Joint Connector „/

NG-51 Ring Fin (2)

EN-24 Engine (1)

KU- 5

Fuel Line -

EN-6 9 8 Engine Mounting (291)

Bracket Assem.

EN-17 Engine Drive Shaft (1)

Coupling

EN-12 Drive Shaft (1)

K^-6 Eccentric Bearing (1)

Block for. Drive

Shaft

EN-55

Reduction Drive (1)

Assembly

KU- 7 Q-belts (4)

E9-16 Propeller (1)

EN-15 Propeller Hub Plate (1)

EN-14 Propeller Hub (1)

EN-25 Engine Fuffler (1)

EN-48 Manifold Header k2)

Pipes

L-N-96 Muffler Mounting (1 Kit)

Bolt Kit

EI1-26 Carburetor assembly (1)

ED-7-95 Throttle Cable (1)

B.9
Table B-1 continued ORIGINAL. PAGE 19

OF POOR QUALITY

Fart Number :ame ,( u a t. _ Descriiation

KU-8 adjustable Clamps (2)

EN-94 Ignition Switch (1)

Assembly

EN-29 Squeeze Bulb (1) In-Line

EN-44 Fuel Filter (1) Id-Line

KU -9 Nylon I T , (1) Connects fuel line

to both tanks

EN-92 Bungee Chord (1) Straps fuel tanks 

vehicle

HC-111 Seat Sling Harness (1)

IM. 10 'ding Fabric (1)

B.10
N^

I

{

F

Note Regarding Compiled Parts List (Table B-21:

Table B-2 contains the raw data that had to be input into the

computer before processing. This raw data table contains the measured

parameters Z coordinate, horizontal angle (PSI), horizontal distance 

(SDIST), and component weight. All the components listed are actually

^- 

used on the ultralight.

The following naming convention was adopted to distinguish the nut, 

r=

bolt, and washer that were used:

Example:

AN4-24A 2F2T

bolt washer type and quantity

i Note: This convention assumes the standard size nut

unless otherwise states (W).

Convention:

S - safety bolt

F - thick washer 

T - thin washer

W - wing nut

R - safety ring.

The complete listing is shown in Table B-2.

4

L

B.11
t

€tt

ht

Tab1^2 Compiled parts list and coordinate C.G. locations.

THIS FILE INEASURE' CONTAINS All THE AEASUAEMENTS TAKEN

ON THE VASE CONFUUAATION.

COMOMENI t-COOAO PSI DISTANCE VE16NT

116-,> 90.25 11.67 93.375 .2376

AM-244 2Fr2T 90,25 10.33 19.625 .05459

EC-9 90.62 9.13 71.:115 .01219

Nb 17 19,115 1.33 106.625 1.146

EC-9 17.175 7.33 119,625 .01279

A04. 24A 3T 17.375 7.67 111.625 805231

N6-63 17.75 1.67 111.25 .2185

NC-57 15.25 1.75 131.25 .007253

9646 17.175 26.33 125.375 .2559 16-37 15.5 25.5 131.125 2.354

M6-37 11.25 32.92 102.75 2.354 04-30A 2T 15.625 42,33 116.315 .05711 N6-35 15.625 42.33 116,375 .005952

06-53 15.375 41.67 122.375 .04167

AN4-14A 17 15,375 41.67 122.375 .03167

CS-31 15.375 40.5 125.0 .01471

N6-93 9 94 15.25 39.75 122.375 .211

16-47 14.5 41.33 121.5 .2185

16-77 14.625 34.75 136.625 .02353 AN3-16A 2F 13.15 34.51 136,115 .02637

T° AN4-14A IT 13.175 34.33 136.175 .03167

16-53 13.175 34.01 136.175 1041611

AN4-264 2F 13.175 33.5 131.375 .05679

AN4-24A 2F 14.0 33.5 130.75 .05326

i N6-66 15.625 38.5 131.25 .2559

-a 16-33 10.15 45.25 165.375 2.115

96-33 12.0 54.0 144.175 2.115

16-57 10.375 54.17 154.125 .2150

116-57 10.375 54,17 154.125 .2150

16-66 10.625 41.17 163.75 .2559

16-35 75.625 61 AT 179.75 .005952

a AN4-30A 3F 11 71.625 61.65 119.75 .05931

6-53 78.625 60.92 171.0 .04867

AN4-14A IT 71.50 60.92 171.0 .03167

Fj 16-46 77.5 56.17 111.625 .2713

r 414`14A IT 77.375 54.17 192.625 .03167

9 AN4-24A IT 78.625 60.13 171.0 .04973

96-93 78.25 59.17 178„475 .2613 96-53 77.25 53.67 11.210 .04867 AN4-26A 2F 77.375 $3.51 19'5.5 .05679

AN4-24A 2F 77.375 53.5 195.75 .05326

16-97 11.25 53.0 195,5 .06548 AN4-1?S iFiTUR 71.25 53.0 195.5 .0505

CS-40 79.5 41.67 179.15 .3438

16-75A 54.125 69.17 203.75 .6175

96-56 74.375 62.67 218.0 .2000

.. 16-92 74.375 62.67 211.0 .1125

N6-66 76.5 60.33 217.5 .2559 16-27 74.0 51.15 221.75 2.330

116-27 16,25 65.75 207.125 2.310

96-66 74.0 63.15 241.625 .2559

4_

1
Ii

Fa

OF POOR QUALITY

CONPONEN7 2-000AO PSI DISTANCE UEI6NT

".iii• 7i".

rii ,."75 6=.22 AN3-7A 51 66.375 63.25

CS-33 68.75 63.25 CS-42 69.625 63.20

AN5-12A 5F 69.625 63.2

0-32 70.625 63.18

AN3-24A 172F 71.375 63.33 AN3-24A 172F 71.375 63.25

IBK 70.875 63.33 AN4-24A 1F1T 70.875 63.33

112 13.5 69.75

A04-24A 2F 73.5 69.75

V6-71 92,5 59.58 06-74 58.75 58.17 EC-9 92.0 79.17 AN4-24A 3F 91.625 79.17

96-62 91.625 79.13 96-17 89.375 76.25

EC-9 89.0 75.25 AN4-24A 3F 18.625 75.30

96-63 81.625 75.3 NC-57 85.875 73.17

96-66 18.875 75.08 96-37 15.625 74.0

Y6-37 88.25 78.08 96-35 86.25 77.42

AN4-30A 2F 86.25 77.50 16-53 15.875 77.25

AN4-14A IT 85.875 77.25 96-93 15.5 76.25 CS-38 85.50 76.67 96-47 14.625 74.58

06-77 84.75 73.67 AN3-16A 2F 84.75 73.67

AN4-14A IT 14.0 74.33 06-53 84.0 73.33

AN4-24A 2F 84.0 73.17

404-25A 2F 94.0 73.08 â 6-66 85.625 73.75 06-57 81.625 73.70

06-57 81.625 73.70 96-33 82.625 76.20

YF-33 10.625 71.33 96-66 12.175 72.33

96-66 19.75 70.67 96-35 79.125 74.67

AN4-30A IF 79.125 74.50 96-53 78.875 74.17

AN4-10 IT 78.175 74.17 96-99 78.5 73.0

96-46 77.7` 71.0 AN4-140 IT 77.25 69.58

96-53 77.25 69.50

AN4-21A 2F 77.25 69.17

AN4-26A 2F 77.25 69.17

611 I' ll .875

264.0

254.625

253.25

253.25

252.5

253.625

254.625

256.5

258.125

243.0

243.0

206.125

199.875

461.75

460.875

456.75

442.375

468.5

466.75

467.25

470.0

429.5

428.625

423.25

386.375

386.315

403.125

403.125

400.375

396.50

403.75

407.0

407.0

406.375

406.375

406.0

406.5

398.375

364.5

364.5

359.125

370.875

364,875

333.25

323.5

323.5

321.25

321.25

322.0

324.625

331.175

331.875

329.625

329.625

MOW

.01079

.07352

.008598

.06209

.04795

.03273

.03273

.3759

.05116

.1003

.05326

.1125

1.5625

.01279

.05569

.2376

1.146

.01279

.05569

.2185

.007253

.2559

2.3540

2.3540

.005952

.05938

.04867

.03167

.2789

.01477

.2885

.02353

.02637

.03167

.04867 j

.05326

.05326

.2559

.2150

.2150

2.115

2.1150

.2559

.2559

.005952

.05695

.04867

.03167

.2678

.2783

.03167

.04867

.05629

rr

isi

B.13
T•1,1

^ g•^

►^► n'

r ► n^^t.t

► ORIGINAL PAGE 19

OF POOR QUALITY

tOMON[NI t-COORO PSI DISTANCE 0E16NT

004 . 11S 1F1TUR 76.15 66.83 330.75 .0505

96• :7 16.5 7'1.13 290.375 2.330

96 . 9? 74.50 69,67 290.175 .I1?S Y6-56 74.5 69.67 290.175 .7000 116 . 66 16.$ 73.33 296 .:, 11?559

96-?7 74.075 67.17 299.875 2,330 96 66 74.0 66.0 271.0 .2559

161

04-20 2F

13.315

73,375

70.08

70.06

254.0

254.0

.1 M3

.05326

163 11.0 63.67 264.625 .1003 AN4 . 24A 2F 71.0 63.67 364.625 ',85326

CS-39 79.5 70.67 355.5 .,3438

96-75 55.625 75.33 215.25 .6875

U6-14 53.375 70.56 320.25 1.5625 06 . 72 94.5 70.08 308.25 .81?5 96-210 96.75 67.17 258.25 3.660

AN365-524 117.175 64.92 259.25 .01127

AN4-5A 17 74.375 70.63 20.75 .1550

06-13 73.625 70.75 246.75 .07562

96-1 73.375 70.37 245.625 .1036

0b-8 73.375 70.58 251.5 .1036

AN4 . 2CA 2F 72.0 70.67 245.0 .05679

AN4. 26A 2f 71.115 70.33 244.815 .05679

A04-24A 2F 13.0 70.5 244.315 .05326

AM4-24A 2F 74.1.25 70.75 243.23 .05326

AM4-24A 2F -14.0 70.25 244.625 .05326

AN4- 28A 2F 73.25 69.83 247.0 .05629

AN4-210 2F 73.75 70.0 247.0 .05629

AM4-25A IF 73.375 69.92 248.125 .05297

AM4-17S 2FUR 76.0 70.5 248.0 .05163 CS-26

( CS-28

76.0

76.0

70.42

70.58

248.0

248.0

.000661

.000661 EM PRED.ROUNT 65.315 66.33 254.75 76.375

SPARK PLUS 51.5 66.67 254.125 .1240

SPARK PLU6 57.5 65.83 234.0 1240 ( Y-PIPE 64.125 65.58 252.25 1.64 35

7-PIPE 63.0 66.83 245.75 1.0104

RUFFLER 60.125 65.5 246.0 5.000

RUFFLER SPR 64.625 65.75 245.75 .01213

1 RUFFLER SPR 66.25 66.0 247.75 .01213

RUFFLER SPR 59.875 67.0 245.125 .01213

RUFFLER SPR 59.875 67.17 247.125 .01213

AN4-120 2F 57.5 66.38 249.0 .03578

RUBS016 OASNER 51.5 66.38 249.0 .02464 AM4-12A 2F 57.25 65.17 252.5 .03578

RU91816 9ASNER 57.25 65.17 252.5 -. .02469 AN4-21A 2T 12.25 66.13 252.375 .05609

AM4-28A ?T 72.25 65.33 254.75 .05609 EN-26 61.625 66.83 262.315 2.00 06-36 70.175 61.58 264.0 .06883

AN5-42A 2F .69.75 61.67 264.0 .1210

AN3-25A 2F 70.5 61.5 264.0 .03131

AN42F -20A 72.755 61.67 264.0 .04445 V6-36 72.75 61.67 266 .0 .06883

4y

kl

f

2a

B-14

L 
r

^J

k

t

1

1

DISTANCE VEI6NT

264.0 .000661

266.0 ,100661

272.0 x,.,,:75

273.0

268.175 .1109

271.25 .1109

268.0 .06842

268.5 .06842

270.25 .2826

275.25 .1826

275.25 .1001

269.5 .1001

274.25 .05754

270.5 .05754

272.25 .1720

258.125 .06528

245.625 1.760

266.125 1.875

269.0 S 1.760

321.

251.05

1.1497

250.25 .01977

291.875 .01977

289.625 .1497

278.0 1.4375

275.25 .05379

292.5 .05379

250.25 .01651

293.625 .01658

289.0 .04373

289.125 .04373

323.0 .04373

323.75 .04373

290.0 .01977

290.0 .006944

291.0 .01190

294.5 .1526

292.0 .03009

295.75 .09656

293.5 .0; i 38

294.0 .02138

296.375 .01658

296.0 .01069

296.5 ..01190

296.875 .1282

296.625 .04700

297.0 .01431

297.125 .01431

300.75 1.0234

300.5 .02127

300.5 .02205

300.5 .02138

300.5 .02138

299.25 .06468

B. 15

i

ORIGINAL PAGE 19

OF POOR QUALITY

r

Table X-2 CONTINUED

COMPONENT Z-000RO PSI

CS-28 72.15 61.63

CS-28 72.75 62.83

PROPIBHAFT 66.25 59.92 EN-12 66.25 59.58

EN-95 66.25 59.67

E0-95 66.125 59.17

AN4-35A 2F 65.0 59.67

AN4-35A 2F 67.625 59.33

EN-90 67.625 59.25

EN-90 67.625 59.67

EN-92 116 MASH 69.125 59.67

EN-92 69.25 59.17

EN-99 69.125 59.67

EN-99 69.25 59.17

AN6-504 69.125 59.5

ONS-16A 2F 66.625 64.0

TS-4 73.875 49.0

TS-2 47.5 44.61 TS-23 0.75 •54.51

TS-3 73.625 60.67

TS-3 47.25 48.50

PUSH CLEVIS 26.0 62.5

AN3-11A 2T 26.5 62.25 AN3-11A 2T 71.75 47.83

PUSH CLEVIS 72.375 47.67 CS-47 35.0 60.17

NOSE CLAMP SH 33.75 64.0

HOSE CLAMP SM 45.125 64.58

AN3-6A 27 25.0 62.75

AN3-64 2T 73.123 47.33

AN4-14S 1FUR 66.5 47.17

AN4-14S IFYR 71.0 46.33

AN4-14S 1FUR 66.0 52.50

AN4-14S iFNR 70.625 52.50

AN3-11A 2T 69.5 46.33 NSA-4 69.5 46.5

11SA-11 69.5 46.42 TS-36 71.25 46.25 "SA-1 69.5 46.67

USA-140 71.625 46.75

AN3-12A 2T 69.5 46.83

AN3-120 2T 69.5 46.92 AN3--? ?T 74.5 46.67 NSA- 69.5 47.0 NSA-18 69.5 47.11

NSA-2 69.5 41.53 NSA-11 72.25 47.17 A03-50 IT 71.25 47.0

AN3-5A IT 71.25 46.83

NSA-26 68.625 48.33 NSA-%,6 66.625 48.33

AN4-14A 2T 67.5 48.33

A113-18A 2T 69.5 48.0 AN3-13A 2T 69.5 48.0

NSA-98 68.75 47.83
ORIGINAL PAGE 19

OF POOR QUALITY

DISTANCE UEI6NT

Table B-2 CONTINUED

t4

COMPONENT t-00040 PSI

B. 16

MA

r,

yx(I

11

4

w

ANMA IF 71.5 47.75

AN3-5A IF 70.175 47.75

AN3 , 6A 37 67.625 47.5

NSA-12 70.5 47.5

#03-124 ST 73.75 47.67

NSA-13 72.5 47.75

MSA-8 74.25 47.33

05A-7 70.625 47.11

MSA-23 10.625 47.17

MSA-12 72275 48,17

NSA-15 70.625 47.33

AN3-6A 37 72.125 48.5

MSA-94 70.75 48.33

AN4-13A 2T 69.5 41.25

A#4-13A 2T 69.5 48.25

MSA-18 69.5 48.33

AN3-5A IF 70.815 48.25

AN3-54 IF 111.625 48.25

11SA-18 69.5 49.17

MSA-4 69.5 49.33

AN3-11A 27 69.5 49.33

NSA-3 69.5 50.25

A#3-12A 2T 69.375 51.15

AN3-12A 2T 69.375 51.75

NSA-!0A 11.25 51.75

NSA-1 69.375 51.83

050-18 69.375 52.0

TS-36 71.25 51.83

ANMIA 2T 69.375 52.17

NSA-4 69.375 52.17

AN3-144 2T 68.75 51.83

403-144 2T 68.15 46.33

ANMSA 2T 67.25 45.25

ANMSA 2T 67.75 45.33

AN3-15A 2T 68.875 45.67

A03-15A 2T 71.25 46.0

AN3-iSA 2T 72.0 46.25

AN3-15A 27 72.5 46.33

TS-37 70.125 45.83

TS-38 69.25 45.13

TS-11A 79.25 47.67

TAIL THE 81 59.75 47.42

TS-8 63.5 43.75

FABRIC (TAR) 71.375 43.67

TS-19 73.625 44.33

AN3-6A 3T 73.625 42.5

TS-29 72.375 43.75

TS-31 72.0 43.0

AN3-1SA 2T 71.5 43.0

TS-31 72.0 43.75

AN3-15A 27 71.5 431.75

75-20 71.5 42.33

4113-14A 27 71.5 43.17

TS-26 72.25 44.25

73-26 70.75 43.17

300.0

300.5

301.115

301.75

301.75

303.375

302.625

305.25

305.25

300.5

304.25

300.0

300.375

300.115

300.815

302.125

302.115

302.875

305.15

307.0

307.0

314.0

322.875

322.875

323.0

325.5

326.0

327.0

328.375

328.375

327.5

292.815

294.25

294.5

295.5

296.125

299.5

300.5

296,375

297.25

302.25

297.5

296.5

312.25

307.25

316.25

317.125

317.75

311.75

318.125

318.125

320.0

317.125

317.815

316.315

.01530

.01530

.01177

.06030

.02495

.02194

.09632

.02535

.03186

.06030

.2532

.01777

.08488

.02138

.02138

.0119

.01530

.01530

.01190

.006944

.01977

.3458

.02138

.02138

.09656

.03009

.01190

.1526

.01911

.006944

.02205

.02205

.02315

.02315

.02315

.02315

.02315

.02315

.2482

.3130

.8750

1.010

.1188

.2600

.01777

.08570

.004299

.02315

.04299

.02315

.2256

.02203

.01736

.01736

l

s

^n

l

Nμ^

4

r

0
.Table B-2 CONTINUED

co"PONENT i-000RD PSI

ORIGINAL PAGE 1,9

OF POOR QUALITY

DISTANCE UE16NT

I

M

r

rt

f r '

m

TAIL TUBE 14 11.115 42.42

AN3-13A 2F 70.375 41.75 AN3-11A IF 70.25 41.67

TS-21 70.25 41.67

AN3-IIA 3T 37.5 40.75

TS-26 $7.75 40.13

AN392-13 RING 56.75 41.0

AN42-113 IIF $6.75 41.0

TS-28 56.0 41.0

ANMIA IT 55.75 40.15

ANMIA 3T 15.25 45.17

TS-26 14.5 45.17

AN3-IIA 2F 46.625 45.5

TS-28 16.375 45.5

ANMIA IT 16.5 45.5

TS-23 17.75 49.17

ANMIA NO IT ,11.25 49.17

TS-34 11.0 49.58

ANMIA IF 17.5 49.33

AN3-15A 2T 66.625 51.67

AN3-15A 2T 67.0 51,65

AN3-15A 2T 68.5 51.66

AN3-1SA 2T11.5 51.25

t AN3-1SA 2T 11.375 51.17

AN3-1SA 2T 72 375 51.0

TS -37 69.175 51.33

TS-39 69.0 51.33 ( AN3-4A 2T 74.375 51.83

TS-34 17.175 49.5

ANMIA NO 17.175 49.33

TS-23 87.625 49.42 ANMIA 2F 17.0 49.5 TS-11 78.25 $0.5 TAIL TUBE It 77.0 49.33

TS-7 63.25 51.0

TS- 3 59.375 50.83

TAIL FABRIC LF 71.0 48.67

AN392-13 A 55.25 50.0

AN42-113 55.25 50.0

t ANMIA NO 54.625 50.0

ANMIA 3T 56.0?5 49.67

75-26 56.75 49.67

AN3-14A 2T 70.5 41.75

TS-26 71.75 47.67

TS-26 70.25 47.13

TAIL TUBE 94 72:75 46.67 ANMIA 2F 72.25 46.25

73-21 72.25 46.17

AN3-11A IF NO 72.25 46.17 15-19 74.375 a.5

T5-30 72.875 47.67

AN3-6A 3T 74.375 47.67

AN3--11A 2T 71.75 47.67

300.25 .6875

324.375 .0,2337

325.5 .01957

325.5 .05236

304.75 .02096

304.75 .01736

30110 .00396

301.0 .02533

300.75 .05236

300.75 .01158

326.875 .02096

327.0 .01736

327.875 .02176

327.175 .05236

327.873 .01858

301.5 .02232

308.5 .01384

308.25 .004255

308.25 .01957

333.375 .02315

332.50 .02315

331.875 .02315

327.175 .02315

327.375 .02315

327.0 .02315

329.25 .1046

330.75 .2515

323.5 .01651

310.375 .044255

310.5 .0-1265

310.25 .02232

311.875 .02176

319.6I5 .333

325.875 .875

338.5 1.01 346.0 1.76

340.0 .71Bb

355.25 .00396

355.25 .04156

355.5 .01265

355.5 .05236

356.0 .02096

356.25 .01736

343.0 - .02205

340.625 .01736

341.4 .01736

348.0 .2256 349.375 .6175

353.0 .01483

353.0 .05236

353.0 .01483

335.315 .260

344.175 .0857

345.375 .01777

343.625 .01977

B.17

' 
ORIGINAL PAGE IS

Table B-2 CONTINUED

OF POOR QUALITY

gq

k

P

V,

AF;

v0

g

t.

1

a

COMPONENT 2-000AO

AN3 , 11A 2T 71.15

TS-31 72.0

TS -26 84.625

ANMIA 3T 15.0

4013 -114 IT NO 16.375

ANMI5.75 A 2F 1 

5

AN4-12A 2F 11.25

A1114-12A 2F 17.25

TS-2525 2FUA $7.625

TS-21 54.87

 IF 10.755

AN3-0 2T 69.25

CS-46 50.0

NC-3 •50.115

MC-3 50.875

NC-1 53.0

EN-94 42.375

NC-2 51.175

146-20 51.175

A1114-14A IF 12.875

NC-18 12.175

N65A-12 13.5

( 1116SA-10 13.25

1116SA-10 13.5

N6SA-11

13.5

NOSE UNATIRE 13.5

( N6SA-1! 13.5

NC

S1/i2 13.25

N6SA-9 13.5

AN4-24A IF 13.5

N6SA-8 18.75

N6SA-8 19.0

N6SA-7 23.875

1116SA-18 22.375

116SA-14 23.375

1116SA -1320.625

1116SA -13 21.125

116SA-13 22.75

1116SA -13

23.375

N6SA-6 20.875

1116SA-19 22.625

NGSA-19 24.875

NC-57 25.5

NC-57 25.5

N`

5

42TA IT NO 22:0

N6-53 21.5

AN4.NALF NUT 21.875

AN4 NALF NUT 21.5

PSI DISTANCE UE16NT

47.33 343.625 .01977

47.67 343.625 .004299

47.33 343.625 .004299

46.0 332.75 .01736

45.13 333.5 .02096

45.83 327.875 .01384

46.0 327.875 .05236

41.0 328.125 .01483

46.17 326.0 .03578

46.33 326.0 .03578

46.0 326.0 .04308

46.17 326.0 .04145

45.83 328.375 .72

63.5 261.25 .05436

63.42 256.125 .01658

63.0 257.5 .563

62.25 256.375 .9658

63.67 271.625 .9658

66.67 247.125 1.1560

72.5 237.625 1.00

73.17 254.375 1.00

74.17 252..25 .3818

67.13 263.875 1.156

73.15 246.875 .1$20

79.58 234.125 .05083

79.58 234.125 .000683

79.75 236.75 .01036

79.67 235.5 .04782

80.0 241.5 .04782

79.67 236.625 .00086

79.92 238.625 3.120

79.92 240.0 .00088

79.92 240.0 .01036

80.0 243.625 .000683

1932 238.625 .4960

80.0 243.625 .05083

78.58 242.5 .4346

78.25 237.625 .4346

17.0 241.0 1.250

77.33 240.125 .1699

77.33 240.875 .05682

77.67 241.0 .05831

77.5 240.125 .05831

77.17 241.135 - 105831

77.0 240.25 .05831

77.17 240.376 .09899

77.5 241.0 .06955

77.0 241.125 .06955

76.83 243.0 .007253

76.75 243.5 .007253

77.67 244.0 .01918

77.42 244.25 .01598

77.0 244.875 .03908

77.33 244.875 .004130

76.83 245.0 .004630

B.18
^.3

i

AO PSI

76.67

79.0

77.33

77.25

77.17

77.17

77.0

76.0

76.17

76.25

76.33

76.17

76.42

16.58

76.67

76.70

76.75

76.67

76.13

76.92

11.0

77.08

77.0

77.0

76.58

76.67

76.33

76.17

76.0

75.50

75.08

75.25

75.33

75.33

75.42

75.58

75.67

75.83

75.13

75.5

75.67

75.58

75.58

76.0

75.13

75.92

76.0

75.13

76.17

75.33

69.5

75.0

74.67

74.67

74.67

C

Table B-2 CONTINUED

COMPONENT 2-000

N6-27 21.375

AN4-14A 2F 21.25

AN310A 27 22.375

AN3-10A 2T 22.25

N6SA-14 24.25

AN4-7A 17 NO 22.0

N6-27 21.875

AN4-16A 2F 24.25

N6SA-1 24.25

N6SA-2 24.25

06SA-3 24.25

N6SA-4A 24.175

N6SA-3 24.25

N6SA-2 24.25

N6SA-5 24.25

M65A-2 24.125

N6SA-3 24.125

N65A-48 24.75

N6SA-3 24.125

N6SA-2 24.125

MESA-1 24.125

AN4-164 2F 24.125

CS-50 29.375

AN393-61 R 29.25

N6-53 21.625

AN4 HALF NUT 21.?S

N6421ALF NUT 21

.255

NC-99 2F 30.95

NC-575A iF1T 31.15

HC-5 31.85

NC-12 31.85

AN4-16A 2F 31.85

NC-57 32.05

AN4135A IT IM 29.9

N6-39 29.9

AN3 2-13 R 30.15

AN392-13 R 29.52

AN4-15A 2F 32.10

AN4-24A 2F 32.10 NC-11 30.3

AN4117A MP 34.20

MC-1 32.4

EC4'i5A 2F

31.9

AN4-17A 2F2P 34.15

NC-11 33.40

NC-11 30.7

B.19

ORIGINAL PAGE f.

OF POOR QUALITY

DISTANCE ME160T

245.25 .01596

245.5 .03908

241.875 .0182

237.875 .0182

240.0 .05882

236.25 .01918

236.5 .01598

234.0 .03029

234.375 .03638 j 235.25 .0097

235.175 .03351

237.5 1.0097

238.5 .03252

239.125 .0097

241.625 .5726

245.25 .0097

245.625 .03351

245.75 1.0423

246.625 .03351

247.125 .0097

248.125 .03638

250.0 .0429

247.625 .05997

246.5 .01763

237.5 .03908 

236.875 .00430

237.5 .00430

237.625 .01598

237.625 .03908

250.5 .063';6

250.625 .007187

252.0 .06732

252.75 .009458

253.125 .03717

254.0 .04290

254.0 .007187

249.25 .02127

250.875 .06864

250.875 .004299

249.75 ,,004299

249.25 .008598

249.25 .00396

249.25 : 00396

253.625 .0400l

251.75 .05326

251.75 .06548

251.765 .06548

251.75 .04579

251.25 .01279

243.375 .8208

232.w .0400

233.425 .012?9

234.125 .04579 r 

23#4125 .06548

234.125 .06541
ORIGINAL PAGE ig

Table 

B-2 CONTINUED OF POOR QUALMY

COMONENT t-000AO PSI DISTANCE NE16NT

AN4-17A MP 29.8 74.67 234.125 .04579 NC-12 31.9 74.0 233.0 .03717 004-160 2F

NC-5

31.9 74.0 232.5 .0429 31.9 74.08 233.375 .009458 NC-57 31.9 74.08 232.5 .007253 AN4-154 1F1T 31.9 74.17 234.875 .0543 MC-6 31.4 70.17 239.375 2.540

`

NC-13 30.5 69.83 240.125 .1300 AN3-23A 171F 31.4 69.83 240.125 .03044 A04-244 2F 29.3 69.83 240.125 .05316 AN3-6A 2T 30.0 69.75 239.125 .01658

' CS-24 29.75 69.58 236.75 .09722 CS-21 29.75 69.42 237.625 .03368 CS-30 29.75 69.42 231.625 .008973 AN4-164 2F2P 29.65 69.67 237.0 .04422 CS-22 31.65 10.0 237.25 .6098 AN4-6A 2T 26.6 69.75 237.25 .01656 {*.

NC-107 -143 68.75 241.5 .5625 CS-31 14.3 61.0 242.75 .01477 NC-27 21.5 66.0 243.0 1.54 CS-25 25.9 66.5 242.5 .458 CS-26 28.9 66.25 243.625 .7674 NC-10 30.4 66.33 248.5 .4394 FT-1 22.9 64.67 254.0 2.021 EN-92 22.9 65.0 257.0 .2815 F7-2 22.9 65.42 260.125 2.021 NC-120 29.0 65.17 259.0 .0700

u-. NC-91 29.0 65.17 259.0 .1971 NS-35QQ-14 A 29.0 64.42 251.625 .01387 TANK TAN6 29.5 64.42 251.625 .01830 TANK TAN6 29.5 66.0 266.5 .01830 A0365-428 29.0 66.0 266.5 .008179

AN4-23A IF 30.05 64.5 250.125 .04857 AN4-234 2F 30.05 64.17 250.875 .05100

AN4

130A 2F 31.85 63.33 248.375 .05938 NC -12 31.5 63.42 249.125 .03717 NC-5 31.0 63.42 249.125 .009458 AN4-24A 2F 30.2 63.42 249.125 .05326

k AN4-26A 2F 30.2 63.33 248.625 .05679 NC-12 30.2 63.33 248.625 .03717 NC-5 31.0 63.33 246.625 .009458 NC-5 28.9 63.33 248.625 .009458 NC-12 28.5 63.33 248.625 .03717

AN4-16A 2F 28.0 63.33 246.625 '.04290 A04-24A 2F 30.2 63.25 248.625 .05326 NC-5 30.2 63.17 249.0 .009458 MC -12 30.4 63.0 249.25 .03717 

AN4-17S 2FYA 30.2 63.17 246.5 .05163 96-105 30.2 63.17 246.5 .005842 AN3-6A 2T 25.2 62.83 250.125 .01658 CS-23 26.7 62.83 249.175 .05886 AN3-6A 27 28.95 63.17 249.875 .01658 NC-110 29.05 63.33 2$3.125 .1042

Y ANS-23A IF 29.8 63.5 252.3 .07576

B.20 i
ORIGINAL PAGE 13

Table g-2 CONTINUED OF POOR QUALITY

COIN'ONENT MOM PSI DISTANCE MEI6HT

ANS-23A iF

HC-35 29.8

29.0 63.58 253.0 .07576 63.5 15215 .00948

CS-21

CS-30

21.0

28..80

63.51

63.5

251.0

250,375

.03368

.008913 CS-27 28.0 63.25 250.75 .01925 CS-30

MC-47

28.0

28.0

63.25

63.17

250.625

252.75

.006973

.1384

< AM4-16A 2F

MC-57

28.0

21.0

tare

62.75

251.125

252.0

.0429

.007253 rt AM3-6A 27

VNEELATIRE AT

21.1

15.1

63.17

61.5

355.0

234.0

.01651

5.43

•• AXLE STRIP 15.7 i .1

6137

63.75

213.25

273.875

.05566

.05566 • AN4-14A 2T

AM4 LONG 24

13.5

15.4

64.5

63.75

248 425

20.815

.03681

.06056 AM4-16A 2F

MC-14

23.1

.19.9

64.25

65.5

3

249.5

260.75

.0429

.250

^99

MC-14

REAR AGILE

MC-9

19.9

15.5

30.0

63,58

65.08

65,52

260.75

261.175

260.375

.250

7.0072

NC-25 30.2 67.17

2.0213

MC-87 30.2 66.33

257.375

249.175

.333

.005842 AN4-24A iTiF 30.2 66.25 248.125 .05215 AM4-16A 2F

NC-12

30.2

30.2

66.42

66.33

250.75

250.125

.0429

.03717 404-16A 2F

MC-12

30.2

30.2

67.13

67.92

263.625

264.75

.0429

.03717

° MC-17

AM4-24A mr

30.2

30.2

68.0

68.0

265.875

266.0

,005842

.05215 HC-97(SEAT)

MC-111

23.9

24.1

69.83 253.75 1.71

AM4-16A 2F 28.1

70.75

67.0

253.75

2734

.9751

.0429 A114-16A 2F 24.0 66.92 273.5 .0429 AN4 LON6 24

r A04-14A 2F

15.6

13.4

66.67

67.17

273.625

272.375

.06056

.03908

VNEELITIRE LF

AM4-22S ITHR

15.2

30.0

67.92

67.25

290.25

273. 505824 H6-105

A04-26A 2F

30.0

30.0

67.25

63.17

273.25

272.625

.005842

.05679 MC-12

MC-5

21.6

29.3

63.17

63.17

272.625

212.6?5

.03717

.009451 MC-5

NC-12

30.9

31.3

63.17

67.0

272.625

271.125

.03717

.03717 NC-5

AN4-24A 2F

30.9

30.0

67.0

67.0

271.125

271.125

:009451

.05326

Wit

AM4-24A 2F

OL-28

30.0

30.8

67.08

66.13

272.0

272.?5

.05326

.03717 NC-5

AM4-17S 2FMA

30.4

30.6

66.13

66.67

272.125

272.125

.009458

.05163

-

ANS 3/4 24

AN5 3/4 24

30.4

30.0

66.75

66.67

269.125

261.15

.06371

.06371 NC-35

NC-35

30.0

30.0

66.75

66.67

269.25

268.373

.009410

.00941 NC-109 30.15 67.25 267.175 .46500

B.21
ORIGINAL. PAGE 13

a

Table B-2 CONTINUED OF POOR QUALITY

Y COMPONENT t-000AO PSI DISTANCE ME16NT

AN4-23A 2^ 30.15 67.33 266.175 .0510 NC-10

NC-27

30.45

20.15

68.33

69.58

265.25

266.0

.4394

1.540

CS-38

NC-107

14.6

14.4

61.25

71.51

263.375

260.0

.01477

.5625

EP-35 40.2 73.75 250.515 .7668

kr

NOSE CLAMP L6

NOSE CLAMP L6

32.7

32.2

74.0

73.33

254.75

255.15

.06217

.06217

'.

CS-35

CS-34

19.25

88.85

36.25

39.67

127.5

133.375

.7474

.09017

'

AN3-SA 2T

AN3-SA 2T

8a .85

18.15

40.17

39.5

132.125

135.375

.01550

.01550 ANO . 3244

AN3-54 2T

17.15

18.15

40.17

40.75

130.625

135.75

.01323

.01550 CS-37

AW3-54 2T

.18.75

17.15

42.0

43.25

137.0

13!.375

.110!

.01550 CS-36

CS-35

16.95

90.15

46.92

77.0

148.75

407.375

.7496

.7474 CS-34

AN3-5A 2T

19.15

19.15

76.67

76.83

39!.25

39!.125

.09017

.01550 AN3-54 2T

ANI-5244

19.15

88.15

76.42

77.17

399.625

391.375

.01550

.01323 -

AN3. 5A 2T

CS-37

19.015

19.45

76.5

16.42

395.125

392.0

.01550

AN3-54 2T

CS-36

18.95

81.45

76.17 387.375

.1109

.01550

9I16 FAB AT 74,8 75.67

50.50 375.5

167.,25

.7496

8.125 NIN6 FAB LF 79.8' 73.75 360.25 1.125

FUEL BULB W.

53i0TS

67.83 263.515 .1060 96-1

PILOT

72.25

24.1

66.25 253.0 5.3125 Y

FUEL 4160T 22.9

70.75

64.67

253.75

254.0

0.000

0.000

u

FUEL LEFT 22.9 65.42 260.125 0.000

d

t

B.22
E | ^

\.^ APPENDS C

WEIGHING CHECK

. !

\: { AND

/ ERROR ANALYSIS

:

\\ .

^§ |j

L9

/7 }.

( 

C.i [ y , 

^^^ .-.. . ....,^..^^^.^^^...: ... . . . ... ...
y

^R

ORIGINAL. PAGE 19

C.G. CHECK OF POOR QUALITY

C.1 WEIGHING CHECK AND ERROR ANALYSIS WEIGHING CHECK:

To determine the C.G. by weighing, the aircraft was placed on three

scales; the left and right chain gear on two large scales and the nose gear

on a smaller scale.

Tilt anglew 16 deb,

n.

right and left- nose `ear

main gear reactions ruction

FIGURE C.1 Reaction Diagram of Weighing Check.

Two Measurements were taken:

1) Level. Right 133.2 lb Nose = 11.49 lb

Left 127.0 lb

Total = 271:69 pounds

2) 160 Tilted: Right = 103.2 lb RN = 65.99 lb

Left = 192.5 lb

Total ;e ,271 ms_ .7 pounds

CENTER OF GRAVITY

The C.G. was calculated as follows

Level: SM = 'fix WTOT - 73.75 (% + RML) = 0

'Rose C.G.

Gear

- 73.75 (133.2 + 127.0)

xC'G, 271.69

= 70.63 in from ,nose gear

xC.G

zxC.G. _ 112.39 in from reference

C.1

I
ORIGINAL PAGE IV

OF POOR QUALITY

It

* fl

'^ Rtfcrenu X•ixis

Rri Rat

'uS

Weight and horizontal position of center of gravity,

^ Re(ere^te ?;-axis

ti1

h

1 •

a

s

IVMght and vertical and hori;ontal positions o; centc,r of gravity.

FIGURE C.2.

Experimental Techniques for Determining Weight and Center-of-Gravity Positions

P

+

r,

C.2
C.3

The vertical center of gravity was calculated using techniques outlined

in Ref. 3. Flight Test Principle and Practices.

Where RHd - W (xcose - zsine

See FIGURE C.1 and C.2

However, the ultralight was tilted nose gear down therefore;

Rrlose RMain (Total)

RMd - W (xcose - zsine )

d - 73.75 cos(16) - 70.89 111

x - 70.63 in

W - 271.69

e - 16 deg.

RM - (103.2 + 102.5) - 205.7 lb

FIGURE C . 3 Tilt Angle for Vertical C.G.

and

-z sine - RMd - x cose

W

z (xcose - RMd)

W /sine

• [70.63cos(16)- 205..7(70.89) ]

271.69 /sin(16)
♦ R

ORIGINAL PAGE iii

OF POOR QUALITY

z 51.59 in from ground

- 51.59 + 5.3 in from reference.

z 56.39 in from reference

Y-Direction C.G.:

nose

gear

73.75"

left right

main main

]2.0"

64.0"

FIGURE C.4 Top-view of Ultralight Gear Geometry.

37 (R) + 64(

LAC RM ) - 'Y (WA/C) Main T. C.G.

R.0 - 11.49

133.2

T.

WA/C - 271.69

32(11. 49) + 64(133.2)

C.G. 271.69

lyC. G. W 

32.73 ir* from left main

+0.73 in from r

C.G.

"Y

to CL - 235.0 in

C.G.

C.4
ty 

C.G.

234.27 in from reference

TOTALS:

112.39 in. from reference axis

C.G.

234.27 in. from reference axis

C.G.

t - 56.89 in. from reference axis

ZC.G.

C.5
ERROR ANALYSIS

Weighing: All weighing was done using scales and balances at the

University of Kansas Department of Physics.

The pieces which weighed less than 2 pounds were weighed on a 'poundsweight' balance that could handle the heavier items; the other components

were weighed on two standard triple-beam balances.

Error 'Reason for Error

Triple Beam ±0.10 grams = ±.00022 pounds Reading Balance

Balance

±0.05 grams = ±.00011 pounds Balance Accuracy

Lar a ±0.15 pounds Reading Error

Scale

±0.10 pounds Accuracy

TOTALS: 28 parts weighed on large scale

555 parts weighed on triple beam balance

Weight = 555(.00022) + 555(.00011)

+ 0.15(28) + 0.10(28)

Weight 

err= 

±7.183 pounds

Center of Gravity (3-axes)

The center of gravity was calculated using reference coordinates that were

calculated from a horizontal distance, vertical height, and horizontal angle.

Error Reason

Weight = ±7.183

Measurements:

n

±1.0 x,y direction Non-stable Plumb Line

±0.5 inches Vertical Height Error

due to C.G. Location

error.

C.S
Error Reason

* 10 minutes - 0.167 deg. Transit Reading

a tW -2+ - 2

x.G.

(X)[(QwIw) (x/x) o

C -

WTOT + oWTOT

Where:

vW 7.183 = .01232 lb.: 7.183 weight error

r each 583 583 number of items

a `±1.0± .167Tr sin (psi)

180

W - - component weight

x - - x coordinate

WTOT -- aircraft weight (empty): 277.48

` vW -- average weight ovvor - ±7.183 lb

TOT

The ay

and 

a

are identical to this except the coordiate Y

C.G. C.G.

or Z is interchanged with X 1 and i

a-Y = ±1.0± .1677 cos (psi)

ISO

v- _ x-0.5

z

These errors were computed to be:

Q _ ± 3.78 inches

GI ,

ar, _ ± 6.38 inches

QZ = + 1.74 inches

XC.G. = 110.02 ± 3.78 inches

empty

YC.G. = 233.77 t 6.38 inches

empty

K

ZC.G. = 53.91 ± 1.74 inches

empty C.7
APPENDIX D

PRINCIPAL INERTIAL

QUANTITIES
t

V,

r

P

rr

♦ v

D.1 PRINCIPAL INERTIAL QUANTITIES

This chapter presents the methods, assumptions, and results of the

principal inertia calculations. The principal inertias are defined here

as the inertial contribution to the total aircraft inertia due to the

contribution of the larger components many components such as nuts,

bolts, and many other small items' principal contribution was assumed

negligible, but however were not excluded from the 'MR 2 ' term in the

inertia calculations performed within the computer program in Appendix A.

To simplify the task of computing the principal inertia calculations

the following assumptions were made:

* Each wing and tail half were considered to be rectangular

prisms usii ng the sum of the masses of its components

* Inertia of the tubes were calculated as if they were slender

rods (see example calculation)

* Tires and wheels were considered to be circular cylinders

The following example problem justifies the slender rod assumption

for the tubeing :

I

R

a

ga

6

n

1

D.1

Ll

r
Y

1.6i

0.05

(not to scale)

30" ---

ORIGWAL PAGE ''r

OF POOIR QUALMY

SAMPLE CALCULATION:

Part HC - 9, see FIGURE D.1, Hang Cage Primary Structural Member.

(1.875" x .098" Aluminum Tubing)

M

HC-9 - 0.06282 slugs

Figure D.1 Hang cage primary structural member.

* IYy - MR2 - 0.06262(.07813) 2 - 0.000383 slug/ft2

* I zz = I 

xx - 

1/12 ML 2 + 1/2 MR2

- 0.03272 + 0.000192 - 0.0329 slug/ft2

* assume member to be a cylindrical shell (Ref. 1, p 276).

Now assume member to be a slender rod:

Iyy = 0; Ixx IZ2 1/12 ML2 = 0.03272 slug/ft 2 (Ref. 1, p 276)

It can be seen that the results of the two methods are quite close.

Part HC-9 was chosed for this Example because it is one of the largest

diameter, thick tubes on the aircraft.

Because the difference between the solutions is small all round

tube members are assumed to be slender rods for the calculation of their

individual moments of inertia.

D.2
(not to scale)

Y

Y'

'XI

ORIGINAL PAGE 19

OF POOR QUALITY

SAMPLE CALCULATION OF THE TAIL PLANES:

Tail Planes - assume solid rectangular parallelepiped

b = 50", c 40", 0= Tan-1 3/4 - 36.89 9 , Figure D.2.

Figure D.2 Tail plane sample axis system for calculations.

Iz , = 1/2M(b 2+' • c2) 1/12(0.21695)( (50)2+(40)2)

12 12

Iz , = 0.51474 slug/ft2 (Ref. 1, r.. 276)

Iy , 1/12 Mc2 = 1/12 (.21695)(40/12) 2 = 0.20088 slug/ft2

Ixx=Ix' =

1/12Mb 2 =1/12(.21695)(50/12) 2 = 0.31387

Iyy and Izz are found using the inclined axes method.

(Ref. 2, p 419).

The products of inertia 

Ix'x " Ix'z " Iy, z , are assumed zero

due to symmetry.

The above assumption will be applied to all components unless

otherwise noted.

Iyy = Iy , Cos 2 6 - Iy , z ,sin2e + I z , sin 20

1 z = Iy , sin 2 0 + Iy , z ,sin26 + 1z , Cos 26

D.3
i

i

t:

D.4

L

ti

x=

A^.,a

fF -

f

Iyz w Iy1z^cos20 + I - Iz , sin26

2

SAMPLE MOMENT OF INERTIA CALCULATIONS

Substitution of the previously obtained values of 0, Ty

and I yields:

Iyy 0.31387

Izz 0.40175

The results o,' these calculations are listed in Table D.1.
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