TWR-17591, Volume IV

Solid Rocket Motors

Thioko! Corporation

QM-8 FINAL PERFORMANCEEVALUATIONREPORT - SEALS

June 1989

Prepared for:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

GEORGE C. MARSHALL SPACE FLIGHT CENTER

MARSHALL SPACE FUGHT CENTER, ALABAMA 35812

Contact No. NAS8-30490

DR. No. 5-3

WBS.No. HQ302-10-10

SPA CE OPERA T/ ONS

CORPORA T/ON

PO Box 707,Brigham CItV,UT 84302-0707 (801)863-3511

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TITLE

VOL REV

TVR-17591, Volume 4

0M-8 FINAL PERFORMANCE EVALUATION REPORT (SEALS)

June 1989

Prepared by:

L. V. Nelsen

Joints and Seals Design

_upervisor__ "_'_

Joints and Seals Design

Syste_%0___&*'_4_Integ_lOn Englneering_.7..-

Syst%m Safe(y

Approved by:

J. V. Daines, Manager

_-/ _etalllc Component Design

R. B. Crosbie

Program Management

Re]_i li ty

Released by:

Data _anagemen t

ECS No.

_051

_ CORPORATION

SPACE OPERATIONS

PO Box 707, Brigham C_tK UT 84302-0707 (801) 863-3511

FORM TC N'O. 1810
1.0

2.0

3.0

4.0

CONTENTS

INTRODUCTION ...................................................

SUMMARYAND CONCLUSIONS ........................................

2.1 Motor Performance Per Instrumentation ......................

2.2 Motor Performance Per Disassembly Inspection ...............

DISCUSSION .....................................................

3.1 Test Objectives ............................................

3.1.1 Structural ...........................................

3.1.2 Adjustable VentPort Plug Installation Fixture .......

3.1.3 Leak Check ...........................................

3.2 QM-8 Field Joint Assembly Procedure ........................

3.2.1 Grease Application ...................................

3.2.2 V-2 Filler Installation ...............................

3.2.3 O-ring Installation ..................................

3.2.4 FJAF Installation and Mating .........................

3.3 Nozzle-to-Case Joint Assembly ..............................

3.4 Leak Check Tests ...........................................

3.4.1 Leak Test Introduction ...............................

3.4.2 Leak Check Conclusions and Recommendations ...........

3.4.3 Leak Check Results and Discussion ....................

3.5 Adjustable Vent Port Plugs .................................

3.6 Squeeze Calculations .......................................

TEST RESULTS ...................................................

4.1 Instrumentation ............................................

4.2 Field Joint Performance ....................................

4.2.1 Field Joint Girth Gages ..............................

4.2.2 QM-8 Field Joint Radial Growth Comparisons ...........

4.2.3 LVDT Gages ...........................................

4.3 Factory Joints .............................................

4.3.1 Forward Segment Factory Joint Girth Gage Response ....

4.4 Case Membrane Girth Gage Response ..........................

4.4.1 QM-8 Case Membrane Radial Growth Comparison ..........

4.5 Case Biaxial Stresses ......................................

4.5.1 Aft-to-Center Segment Case Line Load .................

4.5.2 Aft FieldlET Attach Joint ............................

4.6 Nozzle-To-Case Joint Performance ...........................

4.6.1 Nozzle-To-Case Joint .................................

4.6.2 Nozzle-To-Case Girth Gage ............................

4.6.3 Nozzle-To-Case Joint Comparison ......................

4.6.4 Nozzle-To-Case BiaxialStrain Gages ..................

4.6.5 Nozzle-To-Case Strainsert Gages ......................

4.6.5.1 Axial Bolts ...................................

4.6.5.2 Radial Bolts ..................................

4.7 Head End Pressure and Joint Temperature ....................

4.8 Axial Growth Deflections ...................................

1

5

5

7

8

12

12

14

18

22

23

23

24

24

24

25

25

26

27

30

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TI/R-17591, Vol IV
CONTENTS (Continued)

5.0

6.0

5.1

5.2

DISASSEMBLY INSPECTION RESULTS .................................

External Walk Around .......................................

Field Joint Disassemblles ..................................

5.2.1 Forward Field Joint ..................................

5.2.2 Center Field Joint ...................................

5.2.3 Aft Field Joint ......................................

5.3 Nozzle-to-Case Joint .......................................

5.4 Igniter Joints .............................................

5.4.1 Safe and Arm Joint. ..................................

5.4.2 Outer Joint ..........................................

5.4.3 Inner Joint ..........................................

5.5 Internal Nozzle ............................................

5.5.1 Aft Exit Cone Field Joint (Joint 1) ..................

5.5.2 Forward End Ring-to-Nose Inlet Housing (Joint 2) .....

5.5.3 Nose Inlet Housing-to-Throat Support Housing (Joint 3)

5.5.4 Forward Exit Cone-to-Throat Support Housing (Joint 4)

5.5.5 Fixed Housing-to-Aft End Ring (Joint 5) ..............

5.6 Factory Joints .............................................

5.6.1 Disassembly of 0M-8 Forward Dome and

Forward Segment Factory Joints .......................

5.6.1.1 Forward Doze-to-Cylinder Factory Joint .........

5.6.1.2 Forward Segment Cyllnder-to-Cylinder

Factory Joint ..................................

5.6.2 Disassembly of 0M-8 Center Forward Factory Joint .....

5.6.3 Disassembly of 0M-8 Center Aft Factory Joint .........

5.6.4 Disassembly of 0M-8 Aft Factory Joints ...............

5.6.4.1 Aft Segment Dome-to-Stiffener Joint ............

5.6.4.2 Stiffener-to-Stiffener Factory Joint ...........

5.6.4.3 ET-to-Stiffener Factory Joint ..................

5.7 Port Flue Evaluation .......................................

5.8 Seals Component Program Team Recomendations ...............

5.8.1 Remains Observation ..................................

5.8.2 Minor Anomalies ......................................

5.8.3 Major Anomalies ......................................

5.8.4 Critical Anomalies ...................................

5.9 RPRB Position ..............................................

REFERENCES .....................................................

69

71

71

72

73

74

75

76

79

79

8O

8O

86

86

87

87

88

88

88

88

89

90

90

91

92

92

93

94

95

95

95

96

96

96

98

Table 1

Table 2

TABLES

QM-8 Case Field Joint Primary 0-Ring Movement .............

QM-8 Internal Nozzle Joint Leak Test Results ..............

20

22

TYR-17591, Vol IV

ii
Table 3

Table 4

Table 5

Table 6

Table 7

Table 8

Table 9

Table I0

Table 11

Table 12

Table 13

Table 14

Table 15

Table 16

Table 17

Table 18

Table 19

Table 20

TABLES (Continued)

ON-8 Seal Leak Testing .................................... 26

OH-8 Case Field Joint Leak Test Results ................... 27

QN-8 Ignition System Leak Test Results .................... 28

QH-8 Nozzle-to-Case Joint Leak Test Results ............... 29

ON-8 Vent Port Plugs LeakTest Results .................... 29

OH-8 Forward Field Joint Girth Gage Response

(Zero - 120 Seconds) ...................................... 34

QM-8 Center Field Joint Girth Gage Response

(Zero to 120 Seconds) ..................................... 35

Forward Field Joint Radial Grovth Comparisons to OH-8 ..... 36

Center Field Joint Radial Grovth Comparisons to OH-8 ...... 36

O-Ring Sealing Gap Openings, OH-Y, OH-6, JES,

NJES, TPTA ................................................ 40

QH-8 Forward Segment Factory Joint Girth Gage Response

(Zero to 100 Seconds) ..................................... 43

ON-8 Case Radial Deflection Case Girth Gage Response

(Zero to 120 seconds) ..................................... 44

Case Hembrane Radial Grovth Comparisons to OH-8 ........... 45

QH-8 Aft-to-Center Segment (Station 1196.48) Case Line Load

Homent Biaxials (Zero to 120 seconds) ..................... 49

QH-8 Aft-to-Center Segment (Station 1466.00) Case Line Load

Moment Biaxials (Zero to 120 seconds) ..................... 49

QH-8 Aft-to-Center Segment (Station 1196.48) Case Line Load

Homent Biaxials, Haximum Hoop Stress

(Zero to 120 seconds) ..................................... 50

OH-8 Aft-to-Center Segment (Station 1466.00) Case Line Load

Homent Siaxials, Haximum Hoop Stress

(Zero to 120 seconds) ..................................... 50

ON-8 Aft Field-to-ETAttach (Station 1498.00)

Joint Biaxial Gages (Zero to 120 seconds) ................. 52

TI/R-17591, Vol IV

iii
Table 21

Table 22

Table 23

Table 24

Table 25

Table 26

Table 27

Table 28

Table 29

Table 30

Table 31

Table 32

Table 33

Table 34

TABLES (Continued)

QH-8 Aft Field-to-ET Attach (Station 1501.00).

Joint Biaxial Gages (Zero to 120 seconds) .................

QH-8 Aft Field-to-ET Attach (Station 1511.00)

Joint Biaxial Gages (Zero to 120 seconds) .................

QH-8 Aft Field-to-ET Attach (Station 1498.00)

Joint Biaxial Gages Maximum Hoop Stress

(Zero to 120 seconds) .................. : ..................

QH-8 Aft Field-to-ET Attach (Station 1501.00)

Joint Biaxial Gages Naximum Boop Stress

(Zero to 120 seconds) .....................................

QH-8 Aft Field-to-ET Attach (Station 1511.00)

Joint Biaxial Gages Maximum Hoop Stress

(Zero to 120 seconds) .....................................

QM-8 Aft Dome, Fixed Housing Nozzle-to-Case Joint

Girth Gages (18 to 22 seconds) ............................

Nozzle-to-Case Joint Radial Grovth Comparisons to QH-8 ....

QM-8 Aft Dome, Fixed Housing Nozzle-to-Case Joint

Biaxial Gages (Zero to 120 seconds) .......................

QH-8 Aft Dome, Fixed Housing Nozzle-to-Case Joint

Biaxial Gages (18 to 22 seconds) ..........................

QH-8 Aft Dome, Fixed Housing (Strainsert)

Radial Station 1874.3, Axial Station 1875.2

(Zero to 120 seconds) .....................................

QH-8 Forward Dome Chamber Pressure

(Zero to 120 seconds) .....................................

QH-8 Forward, Center, Aft Field Joints and Nozzle-to-case

Joint and Heater Temperatures (-10.0 to Zero seconds) .....

QH-8 Axial Grovth Deflections (Zero to 120 seconds) .......

Criteria for Classifying "Potential Anomalies n ............

52

53

53

54

54

57

58

61

62

63

65

66

67

97

Figure 1

Figure 2

FIGURES

QN-8 Test Article ........................................

Olq-8 Assembled Field Joint ...............................

TVR-17591, Vol. IV

iv
Figure 3

Figure 4

Figure 5

Figure 6

Figure 7

Figure 8

Figure 9

Figure 10

Figure 11

Figure 12

Figure 13

Figure 14

Figure 15

Figure 16

Figure 17

Figure 18

Figure 19

Figure 20

Figure 21

Figure 22

APPENDIX A

FICURES (Continued)

QM-8 Assembled Nozzle-to-Case Joint ...................... 4

P-8 Strut Load Duty Cycle ................................ 9

P-9 Strut Load Duty Cycle ................................ 10

P-10 Strut Load Duty Cycle ............................... Ii

Adjustable Vent Port Plug ................................ 16

Bottom Plug Installation Setup ........................... 17

OM-8 V2 Filler ........................................... 23

Forward Field Joint Radial Growth Comparisons ............ 37

Center Field Joint Radial Growth Comparisons ............. 38

Forward Field Joint LVDT Measurement (Gap Opening) ....... 41

Case Membrane Radial Growth Comparisons .................. 46

Case-to-Nozzle Joint Radial Growth Comparisons ........... 59

0N-8 Longwire Locations .................................. 68

Ignition Systems Seals ................................... 77

Igniter Cross Section .................................... 78

Forward Exit Cone-to-Aft Exit Cone Joint Interface ....... 81

Nose Inlet Housing/Flex Bearing Joint .................... 82

Nose Inlet/Throat Housing Joint .......................... 83

Throat/Forward Exit Cone Joint ........................... 84

Flex Bearing/Fixed-Housing Joint ......................... 85

APPENDICES

Inspection Forms ........................................ A-i

TWR-17591, Vol. IV
ACKNOWLEDGMENTS

Contributions to this report were made by the following people:

Chris Rice

Joints and Seals Design

Joe Hemen

Joints and Seals Design

Dave Gurney

Joints and Seals Design

Kelly Baker

Joints and Seals Design

Alan Carlisle

Joints and Seals Design

Jeff Curry

Post Fired Hardware Engineering

Joe Lohrer

Metal Component Design

TWR-17591, Vol IV

vi
1.0 INTRODIICrlON

The Space Shuttle Redesigned Solid Rocket Motor (RSRH) static test of Qualification Motor-8 (QM-8) vas conducted 20 January 1989 at Morton Thiokol,

Inc., Space Operations. The QM-8 test article (see Figure 1) was the fifth

full-scale, full-duration test, and the third qualification motor to

incorporate the redesigned case field joint and nozzle-to-case joint as

illustrated fn Figures 2 and 3, respectively. This vas the second static

test conducted in the T-97 test facility, vhich is equipped with actuators

for inducing external side loads to a 360 degree External Tank (ET) attach

ring during test motor operation, and permits heating/cooling of an entire

motor. The QM-8 motor vas cooled to a temperature which ensured that the

maximum propellant mean bulk temperature (PNBT) of 40 ° F vas achieved at

firing. QN-8 vas tested per Morton Thiokol, Inc. Test Plan CTP-0060,

Revision D (see Reference 1).

This final report does not include all test results, but rather, addresses

the performance of the metal case, field joints, and nozzle-to-case joint.

It focuses on the involvement of the Structural Applications and Structural

Design Groups vith the QN-8 test vhich includes: assembly procedures of

the field and nozzle-to-ease joints, joint leak check results, structural

test results, and post-test inspection evaluations.

The final test report vhich addresses all objectives is TI/R-17591, Volume I

(see Reference 2).

Ti/R-17591, Vol IV

1
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oocNo. TWR-17591 VOL IV

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2.0 SUMMARY AND CONCLUSIONS

2.1 Motor Performance per Instrumentation

The girth gage measurements from QM-8 field, factory, case, and

nozzle-to-case joints compare closely to pretest predictions. The highest

percentage differences were 8.5 percent on the FWD field joint, 6.9 percent

on the CTR field joint, 10.6 percent on the FWD cylinder to cylinder

factory joint, 5.7 percent on case segment (station 1411.5), and 19.6

percent on the nozzle-to-case joint girth gages. The overall maximum

radial growth occured in the case membrane at station 931.5, and had a

value of 0.271 inch. Several of the gage readings are questionable, or

produced no data.

The biaxial gage measurements were not consistently comparable with pretest

predictions which are discussed in more detail in the test results

sections. The included tables can more clearly depict similarities and

differences. The maximum stress experienced by the case membrane (stations

1196 and 1466) occured in the hoop direction, 270 degrees, at station 1466,

and had a value of 145.1KSI. In the aft field joint/ET region, a

comparison between biaxial gage test data and predicted values can be found

in TWR-19506 (Reference 3).

TWR-17591, Vol IV

5
The 0H-8 maximum head end pressure of 872.6 psia occurred in the forward

dome at 0.656 seconds following motor ignition (see Table 31). The joint

and heater temperatures ranged between 84.9 OF to 106.7 OF prior to

ignition (see Table 32), well above the 75 °F minimum required.

The gap opening aft of the primaryO-ring was measured with an LVDT via the

45 degree leak check port for the forward field joint. LVDTs were also used

on the center and aft field joints, unfortunately the deflection data was

not generated. The forward field joint Linear Variable Displacement

Transformer (LVDT) measured a radial growth of 0.004 inch, which is the

same as the pretest predictions.

The maximum axial growth was 1.06 inches between stations 527.0 to 1505.0

inches which is a typical value. (see Table 33) Negative values were

experienced in the gages which spanned the joints. Evaluation of the

placement of these gage locations which experienced negative values

supports that these values are in error. In other words, the instrument

measured a negative value but the joint did not go negative. The

measurement was that of of instrument, and not the joint.

TWR-17591, Vol IV

6
2.2 Notor Performance Per Disassembly Inspection

The detailed results of the post-test inspection of OH-8 can be found in

Section 5.0. In summary, the most significant observations made from

post-test inspection vhere:

O

O

I/hlte colored material, vhich ran circumferentially, vas

found on the aft edge of the forvard field joint capture

feature O-ring at 169 degrees. Nore thin lines of the vhite

colored material vere found intermittently on the aft edge

from 164 to 167 degrees. Also small thin lines of the vhite

colored material vere found on the capture feature metal-toJ-leg interface (aft of the capture feature groove on the

tang J-leg) at intermittent degree locations. Lab analysis

indicated the vhite material vas Teflon tape adhesive.

Teflon tape is used to mask the J-leg during grease

application and O-ring installation processes.

Inspection of the radial bolt Stat-O-Seals by the O-ring

inspection team revealed that 35 of 100 had unacceptable flov

line conditions vhich should have been rejected by Receiving

Inspection. Draying No. 1U75374 defines the Stat-O-Seals to

be inspected per HIL-STD-413, vhich allows circumferential

flov lines no greater than 0.180 inch in length. No radial

flov marks are alloyed.

At the present time there is a Stat-0-Seal inspection test

designed to qualify each inspector. This test was not in

force at the time the 0N-8 Stat-O-Seal inspection occurred.

Inspection of the nose-to-forward end ring revealed one very

small pressure path through the RTV of the joint interface at

355 degrees flowing circumferentially to 350 degrees before

penetrating into the metal interface. The primary O-ring

experienced no damage as a result of the pressure path. The

RTV backfill of this joint vas much better than the current

application of RTV to this joint ('buttering application').

No soot or evidence of blov by vas present past the primary

O-ring.

TI/R-17591, Vol IV
Con_|dertn g these ease and sea] observations were the mo_t R]Kn]f_eant

found, QM-8 represents the fifth successful assembly and firing of a

full-scale capture feature RSRH in a horizontal configuration.

3.0 DISCUSSION

The following sections provide a discussion on the assembly of the field

joints and nozzle-to-case joint. A summary of the QB-8 configuration

follows:

0 Field Joints

o RSI_ design with fluorocarbon 0-rings

o No intentional flaws

o Joint protection system with heaters and weather seal

installed

o Adjustable vent port plugs and vent valves installed

o LVDTs installed in leak check ports

0 Case-To-Nozzle Joint

o Axial and radial bolt configuration with fluorocarbon

O-rings

o No intentional flaws

o Adjustable plug installed in vent port and a pressure

transducer installed in the leak check port

o Temperature sensors of 105 °F, + 5 °F

0 Side load actuators for inducing external side loads to the 360

degree external tank attach ring which follow the curves shown

in Figures 4, 5, and 6.

0 Three stiffener rings installed on the aft segment

0 Weather seals installed on all factory joints

TI/R-17591, Vol IV
_CORPORA_ON

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_c_. TWR-17591 I voL IV

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REVISION OOCNO. TWR-17591 J_L IV

s,c I_, 10
3.1 Test Objectives

Test objectives, as outlined in CTP-O060, Revision D (see Reference 1)

which apply to any structural or seal issue, are addressed here. Explanation of how each objective was met is discussed.

3.1.1 Structural

The test objectives from CTP-0060, Revision D regarding structural performance and the corresponding results are as follows:

"H. Certify that all RSI_ seals, including adjustable vent port plug

seals in the field joints, experience no erosion or blow-by

throughout the static test" (Section 3.2.1.2, CTP-O060, Revision

D).

Post-test inspection shoved that no motor gas pressurization went

past any primary seal and no erosion or heat effects were found

(see Section 5.0). Objective H was met.

"J. Certify that the case field joint and nozzle-to-case joint seals,

if pressurized, accommodate static test motor and side load

induced structural deflections" (Section 3.2.1.2.1.a, CTP-O060,

Revision D).

Post-test inspection of the field and nozzle-to-case joints shoved

that no motor gas pressurization went past the J-Leg or polysulfide insulation respectively (see Section 5.1.2). Objective J was

met.

"K. Certify that the case field joint and nozzle-to-case joint seals,

if pressurized, operate when PMBT is at 40 ° F" (Section

3.2.1.2.1.b, CTP-0050, Revision D).

No pressure was seen to any field or nozzle-to-case joint seal

(see Section 5.1.2). Objective K was met.

TWR-17591, Vol IV

PRECEDING PAGE BLANK NOT FILED9

12
"M. Cert{fy thnt the nozxle-to-ease joint O--ring temperRt_mre _

maintained prior to static firing" (Section 3.2.1.2.1.f, CFP-U060,

Revision D).

Temperature gages located on the nozzle-to-case joint heater gave

a temperature range of 87.4 °F to 106.7 °F (see Section 4.7).

Objective N was met.

"W. Certify that the ignition system seals, if pressurized,

accommodate static test motor structural deflectlons" (Section

3.2.1.2.4.a, CTP-0060, Revision D).

Post-test inspection of the igniter joints (see Section 5.3)

showed there was no blow by past any primary gasket seal.

Objective W was met.

"X. Certify that the ignition system seals, if pressurized, operate

when PMBT is at 40 "F" (Section 3.2.1.2.4.b, CTP-O060, Revision

n).

Post-test inspection of igniter joints (see Section 5.3) showed

there was no blow by past any primary gasket seal. Objective X

was met.

"Z. Certify that the nozzle internal seals and the aft exit cone field

joint seals, if pressurized, accommodate static-test motor

structural deflections" (Section 3.2.1.2.5.a, CTP-O060, Revision

D).

Post-test inspection of all internal nozzle seals, which includes

the aft exit cone-to-forward exit cone field joint seals, (Section

5.4) showed there was no blow by past any primary O-rlng.

Objective Z was met.

"AA. Certify that the nozzle internal seals and the aft exit cone field

joint seals, if pressurized, operate when PMBT is at 40 °F"

(Section 3.2.1.2.5.b, CTP-0060, Revision D).

Post-test inspection of all Internal nozzle seals, which includes

the aft exit cone-to-forward exit cone field joint seals (see

Section 5.4) showed there was no blow by past any primary O-ring.

Objective AA was met.

"AD. Certify that the case is capable of containing the static-test

internal pressure" (Section 3.2.1.3.a, CTP-0060, Revision D)

TWR-17591, Vol IV

13
WA.

Pn_t-te_t inspection of the ON-8 hardvar? (_ee Section 5.0) and

structural evaluation from strain gage instrumentation (see

Section 4.0) indicated no anomalous conditions. Objective AD vas

met.

(Development Objective) Acquire engineering data for model

validation."

Comparisons of test data to predicted model data shov a close

correlation except in the nozzle-to-case biaxial strain gages.

Discrepancies in this joint are explained in Section 4.2.2.4.

3.1.2 Adjustable Vent Port Plug Installation Fixture

Figure 7 illustrates the components vhich make up the adjustable vent port

plug. Figure 8 shovs hov the installation fixture is used to install the

bottom section of the plug into the vent port. The qualification test

objectives regarding the vent port plug installation fixture and hov the

objectives vere set are discussed in this section.

"CO. Certify the performance of the Adjustable Vent Port Plug

Installation Tool as a means of installing, rotating, and torquing

the bottom section of the adjustable vent port plug" (Section

3.2.1.1, CTP-O060, Revision D).

All bottom sections of the plugs vere installed correctly vith the

installation tool. Bovever, three bottom sections had to be

replaced vhen the tool slipped causing raised metal on the bottom

section. This problem vas a result of inadequate training in the

use of the tool, not the tool design (see Section 3.5). Objective

CQ was met.

WCR. Certify that the installation fixture is efficient and does not

require special and additional tooling" (Section 3.2.1.1,

CTP-0060, Revision D).

No addition tooling vas required to install the Adjustable Vent

Port Plugs (see Section 3.5). Objective CR vas met.

"CS. Certify that the use of the adjustable vent port plug installation

tool does not affect the safe and reliable use and reusability of

TVR-17591, Vol IV

14
the RSRH" (Section 3.2.1.1, CTP-O060, Revision D).

Post-test inspection of the ON-8 field and nozzle-to-case joint

vent ports revealed no anomalous conditions (see Section 5.0).

Objective CS was met.

"CT. Certify that the tool allows for a threaded installation to the

bottom section of the adjustable vent port plug" (Section

3.2.1.2.1, CTP-0060, Revision D).

There were no problems associated with the threaded installation

to the bottom section of the adjustable vent port plug (see

Section 3.5). Objective CT was met.

"CU. Certify that the interlocking allows for rotation and torquing of

the bottom section of the adjustable vent port plug" (Section

3.2.1.2.2, CTP-O060, Revision D).

All bottom sections of the plugs were torqued correctly with the

interlocking feature of the installation tool (see Section 3.5).

Objective CU was met.

"CV. Certify the capability of interlocking the installed installation

tool with the bottom section of the adjustable vent port plug, and

the utilization of the notch in the bottom section of the

adjustable vent port plug" (Section 3.2.1.2.2, CTP-O060, Revision

D).

All bottom sections of the plugs were installed correctly with the

installation tool. Bowever, three bottom sections had to be

replaced when the tool slipped, causing raised metal on the bottom

section. This problem was a result of inadequate training in the

use of the interlocking feature, not the tool design (see Section

3.5). Objective CVwas met.

"CW. Certify that the tool is capable of applying a minimum torquing

force of 70 inch pounds to the bottom section of the adjustable

vent port plug" (Section 3.2.1.2.4, CTP-O060, Revision D).

The tool was capable of applying the minimum required torque of 70

inch pounds (see Section 3.5). Objective CW was met.

"CX. Demonstrate that the tool is capable of being transported to the

work site" (Section 3.2.8, CTP-OO60, Revision D).

The tool size and weight are acceptable (see Figure 8).

TIIR-17591, Vol IV

15
_ CORPORATION

SPACE OPERATIONS

Closure Plug

i

I

I

Shoulder O-ring

(1U50228-25)

- HotPatch Nylon

Locking Device

¢

w,

cI Top

Plug

I

/

Secondary O-ring

(1u50228-15)

Bottom

Plug

Primary O-ring

(1U50228-44)

Figure 7 Adjustable Vent Port Plug

REVISION Doc.o. TWR-17591 I_L IV

s=c I pAaE16
"__4_ CORPORATION

SPACE OPERATIONS

Retract

Key

Thumb Nuts

(direction)

Primary

O-ring • I X ." ""

Bottom Plug

Vent Port

Figure 8 Bottom Plug Installation Setup

REVISION _CNO. TWR-17591 I_ IV

s_c I _°E 17
3.1.3 l,eak Check

The qualification test objectives regarding leak test performance are as

follovs:

"I. Certify the verifiability of the RSRH seals (except for the

nozzle-to-case joint primary seal, the factory joint primary seal,

the fixed housing to aft end ring primary seal, the igniter dual

seal plugs (5 places) and the operational pressure transducer

(OPT) primary and secondary seals)" (Section 3.2.1.2, CTP-O060,

Revision D).

"L. Certify that the case field joint and nozzle-to-case joint seal

verification does not degrade the performance or integrity of the

sealing system" (Section 3.2.1.2.1.c, CTP-O060, Revision D).

"H. Certify that the bore seals for the center field joints are

verifiable in the proper direction n (Section 3.2.1.2.1.d, CTP-O060

Revision D).

"¥. Certify that the ignition system seal verification does not

degrade the performance or integrity of the sealing system"

(Section 3.2.1.2.4.c, CTP-O060, Revision D).

"AB. Certify that the nozzle internal seals and the aft exit cone field

joint seals verification does not degrade the performance or

integrity of the sealing system" (Section 3.2.1.2.5.c, CTP-0060,

Revision D).

"AC. Certify that the bore seals for the nozzle are verifiable in the

proper direction" (Section 3.2.1.2.5.e, CTP-0060, Revision D).

"BD. Certify the field joint, nozzle-to-case joint, and igniter-to-case

joint leak test compatibility" (Section 3.2.1.8.1.1.b, CTP-0060,

Revision D).

The following is a discussion of the test objectives and test results

relating to leak testing, and evidence that the current specifications meet

the requirements of the CEI Specification.

TVR-17591, Vol IV

18
Objective I requires that all RSP,H seals be verifiable, vhich, by definition in the CEI Specification, means that a leak test must be performed.

The seals not meeting this requirement have been previously identified in

Deviations RDV0526 and RDW0541 (see Reference 4). These seals include the

nozzle-to-case joint primary seal, the factory joint primary seal, the

fixed housing-to-aft end ring primary seal, the igniter dual seal plugs

(five places) and the OPT primary and secondary seals. All leak tests vere

completed successfully. The leak test results are provided and discussed

in Section 3.4. Objective I vas met.

Objective L requires the certification that the case field joint and

nozzle-to-case joint seal verification (leak test) does not degrade the

performance or integrity of the sealing system. This is verified by

post-test inspection. The completed inspections ahoy no damage or degradation to the system (see Section 5.0). This objective vas met.

Objective H requires the certification that the bore seals in the field

joints are verifiable in the proper direction. These data are gathered

during the leak test. llhen the primary-to-secondary seal cavity (V4) is

pressurized to 1000 psig, the secondary seal is seated in the proper

direction. It is already in that configuration because of assembly, but

that is assured vith pressure. The primary seal is moved into the "wrong"

position. I/hen the primary seal-to-capture feature O-ring cavity (V2) is

TI/R-17591, Vol IV

19
subsequently pressurized to 100 ps_ff, the primary sea] is moved and seated

in the proper sealing direction. This seal movement is evidenced by a

pressure rise in the V4 volume, which is monitored by a pressure transducer

during the test. The pressure rise must be a minimum of 0.5 psi. Table 1

contains the results of the final leak tests, shoving the pressure rises

recorded.

Based on above data, all field joint bore seals were seated and verified in

the proper direction. Objective N was met.

TABLE 1

0M-8 CASE FIELD JOINT PRIMARY O-RING MOVEMENT

FIELD _*INITIAL PRESSURE *FINAL PRESSURE

JOINT (psig) (pslg)

FORVARD 0.036 3.573

CENTER 0.059 3.982

AFT 0.063 3.366

* PRESSURE IN PRIMARY-TO-SECONDARY SEAL CAVITY DURING PRIMARY

SEAL-TO-CAPTURE FEATURE O-RING CAVITY PRESSURIZATION TO I00 psig

Objective Y requires the certification that the ignition system seal verification does not degrade performance or integrity of the sealing system.

This is verified by post-test inspection of the seals, detailed in Section

5.4. No damage was seen because of leak testing. Objective Y was met.

Objective AB requires the certification that the nozzle internal seals and

the aft exit cone field joint seal verification does not degrade the performance or integrity of the sealing system. This is verified by post-test

inspection of the seals detailed in Section 5.5. Completed inspections

show no damage caused by leak testing. This objective was met.

TWR-17591, Vol IV

20
Objective AC requires the certification that the bore seals for the nozzle

are verifiable in the proper direction. This is verified by the successful

completion of a leak test. Nozzle joints 2 and 4 have the only bore seals.

The bore seals are both secondary seals, so pressurization between the

seals verifies them In the proper direction. The pressures used for leak

testing are 920 psig and 144 psig for joints 2 and 4, respectively.

Full-scale testing on a field joint with a minimum 21 percent squeeze has

shown that approximately 65 psig is sufficient to move and seat an 0-ring

In the proper direction after it was seated in the opposite direction with

1000 psig. The internal nozzle joints are designed with minimum ten percent squeeze, resulting in easier movement. With the application of 144

psig and greater, it is assured the seal is seated in the proper direction.

Results of the leak tests are given in Table 2. This objective was met.

Objective BD requires the certification of the field joint, nozzle-to-case

joint and ignlter-to-case Joint leak test compatibility. This is accomplished by performing post-test inspections to determine that no damage to

the insulation was caused by leak testing, and that the insulation performed acceptably. These inspections and analyses were performed with no

anomalous conditions found. Detailed inspection reports are found in

Section 5.0. This objective was satisfied.

TVR-17591, Vol IV

21
TABLE 2

ON-8 INTERNAL NOZZLE JOINT LEAK TEST RESULTS

JOINT #

#1

#2

t3

#4

#5

MAX TEST

PRESSURE

83

920

740

144

920

*ALLOVABLE LEAK

RATE, HI/LO(sccs)

0.029/0.0082

0.084/0.0082

0.070/0.0082

0.053/0.0082

0.084/0.0082

ACTUAL LEAK RATE

HI/L0 (sccs)

0.0067/ 0.0011

0.0140/ 0.0053

0.0060/ 0.0000

0.0142/ 0.0004

0.0065/ 0.0072

* HI = MAX TEST PRESSURE, LO = 30 psig

(#1) => _ / AFT EXIT CONE

(#2) => _ END RING / NOSE INLET HOUSING

(#3) => NOSE INLET HOUSING / THROAT SUPPORT HOUSING

(#4) => THROAT SUPPORT HOUSING / IrgD EXIT CONE

(#5) => AFT END RING / FIXED HOUSING

3.2 0M-8 Field Joint Assembly Procedure

Assembly of the field joints proceeded in the folloving order:

I.

2.

3.

4.

5.

6.

7.

8.

Cleaning and greasing the joint

V-2 filler installation

O-ring cleaning, greasing, and installation

Field Joint Assembly Fixture (PJAF) installation

Application of J-seal adhesive

Joint mating

Pin Installation and FJAF removal

Installation of shims

9. Leak test procedure

TVR-17591, Vol IV

22
3.2.1 Grease Application

Grease application was accomplished per STI/7-2999

Rational for the method of grease application can be

Revision A, Section 3.1.1 (see Reference 6).

3.2.2 V-2 Filler Installation

(see Reference 5).

found in TVR-18135,

The V-2 filler installation is fully described in T_-18135, Revision A,

Section 3.1.2 (see Reference 6). However, the starting locatlons for the

lengths at 91 and 136 degrees were changed to 90 and 137 degrees to alloy a

larger V-2 gap where the vent port is located. This was done to ensure the

vent port was not obstructed.

For the purpose of convenience, a cross-section drawing shoving some fundamental dimensions is shown in Figure 9.

0.120

"-0.075

0.295

0.275

1

0.390

Figure 9

014-8 V2 Filler

TI/R-17591, Vol IV

23
3.2.3 O--Ring Installation

O-rings were installed per STW7-2999 (see Reference 5) which details the

O-ring installation procedures.

3.2.4 FJAF Installation and Mating

Installation procedures for the FJAF are detailed in ETP-0228, Revision A

(see Reference 6), which discusses how the FJAF is used to mate the joints

to full pin Installation.

3.3 Nozzle-to-Case Joint Assembly

Assembly of the nozzle-to-case joint proceeded in the following order:

lu

2.

3.

4.

5.

6.

Fixed housing metal parts were cleaned and regreased

The pregreased O-rings were installed.

The fixed housing was covered to keep it clean

Aft dome metal parts were cleaned

Radial bolt hole plugs were installed in the aft dome

Teflon tape was applied to the aft dome metal surface

from the insulation to approximately half way across the

radial hole plugs

TVR-17591, Vol IV

24
.

8.

.

Details

Polysulfide was mixed and applied to the aft dome.

Teflon tape was removed and aft dome metal surface was recleaned

then greased. Radial bolt hole plugs were checked for proper

alignment.

The joint was assembled vertically.

of the assembly procedure and radial bolt

found in TWR-18135, Section 3.2 (see Reference 7).

hole plug design can be

3.4 Leak Check Tests

3.4.1 Leak Test Introduction

After each RSRM joint is assembled, a leak test is performed to determine

the integrity of the seals (excluding the factory joint seal and the flex

bearing). The leak tests usually consist of a joint volume determination

and a pressure decay test. The volume and pressure information is combined

with temperature and time data, which is collected during the test, and

used in the calculation of a leak rate, expressed in terms of standard

cubic centimeters per second (SCCS). Each leak test has a maximum leak rate

allowed. Some specifications require only a maximum pressure decay over

time. This method has been determined as sufficient based on the small,

constant volumes, and the equivalent leak rates, which are conservative

when using all worst-case variables.

Table 3 contains a list of all joints, the Thiokol Corporation leak test

specifications, and the equipment used to test the joints. The leak tests

will be discussed in detail in Section 3.4.3

TWR-17591, Vol IV

25
.

2.

.

.

5.

6.

7.

TABLE 3

QN-8 SEAL LEAK TESTING

Joint

Case Field Joints

Forvard-to-Aft Exit

Cone Joint

Nozzle Internal

- Joint 2

- Joint 3

- Joint 4

- Joint 5

Vent Port Plug

Nozzle/Case Joint

Case Factory Joints

Ignition System

- Inner/Outer Gaskets

and Special Bolt

Installation

- S&AJoint

- X-ducer Assembly

- Barrier Booster

Specification

STW7-3447

STW7-3475

S'1"I/7-3476

STI/7-3477

STI,/7-3478

STE7-3320

STV7-3661

STW7-3448

STW7-2747

STI/7-3632

STW7-3633

STV7-2853

STW7-2913

Equipment

8U75902

8076248

20129718

2U129718

20129718

20129718

7076357

20129718

2U129718

20129718

8076500

2U65686

2065848

3.4.2 Leak Check Conclusions and Recommendations

Based

3.1.3,

joints

on the satisfaction of all 0M-8 objectives as discussed in Section

it is concluded that all leak tests currently performed on the RSRH

are certified for use on flight motors. These certification objectives were also satisfied during DN-9, QM-6, QM-7, and PV-1, except for the

igniter inner gasket leak test, vhich was certified on QM-7 and PV-1. No

further conclusions or recommendations are reached.

T_TR-17591, Vol IV

26
3.4.3 Leak Check Results and Discussion

The case field joint leak test results are shown in Table 4. All tests

were performed with the 8U75902 leak test system. The "8U" system was used

to test the fllght motor field joints (360L001, 360L002, and 360L003),

aft-to-forward exit cone joints_ and the S_A-to-igniter joint. The results

from the QM-8 field joint leak tests were nominal.

TABLE 4

0M-8 CASE FIELD JOINT LEAK TEST RESULTS

PRESSURE

(psig)

1000

30

IO0

**0

3O

**0

CAVITY*

P-S

P-S

P-C

P-S

P-C

P-S

MAXIMOMLEAK

RATE (sccs)

ACTUAL LEAK RATES (sccs)

CTR AFT

0.0002

0.0005

0.0102

-0.0005

0.0006

-0.0002

0.0693

0.0002

0.0124

-0.0006

0.0006

-0.0002

0.10

0.0082

0.037

-0. 037

O. 0082

-0.0082

0.0081

-0.0003

0.0163

-0.0006

0.0001

-0.0002

* P-S PRIMARY-TO-SECONDARY SEAL

P-C PRIMARY SEAL-TO-CAPTURE FEATURE O-RING

** MONITOR PRESStrRE RISE IN P-S CAVITY

The 0M-8 ignition system leak test results are shown in Table 5. The tests

were performed with a variety of equipment as shown in Table 3. The equipment was identical to that used on the flight motors. All results were

well within limits.

TNR-17591, Vol IV

27
TARLR 5

0M-8 IGNITION SYSTEM LEAK TEST RESULTS

JOINT SEAL

IGNITER

INNER

OUTER

TRANSDUCER

ALLOWABLE LEAK RATE

(sees), HI/L0*

0.10 / 0.0082

0.10 / 0.0082

0LIO / 0.0082

ACTUAL LEAK RATE

(sees), BI/LO

0.0017 / 0.0055

0.0123 /-0.0004

-0.0009 / 0.0000

INSTALLATION

OPT **

BARRIER"

BOOSTER

S&A

10 psi IN 10 sin/

1 psi IN 10 min

1 psi IN 20 min

0.10 / 0.0082

3.0/0.0

3.0/0.0

3.0/0.0

3.0/0.0

O.OPSI

0. 0303 /-0. 0005

HI ffi 1000 psig, LO = 30 psig

OPT's TESTED AT 1024 psigAND 30 psig, ACTUAL LEAK RATE UNITS

ARE psi/lO min

BARRIER BOOSTER TESTED AT 55-60 psig

Table

2U129718 equipment was used.

the nozzle-to-case joints of

within limits.

6 lists the results of the QM-8 nozzle-to-case joint leak test. The

This equipment is identical to that used on

the flight motors. All results were well

TWR-17591, Vol IV

28
TABLE 6

0N-8 NOZZLE-TO-CASE JOINT LEAK TEST RESULTS

PRESSURE

(pslg)

920

30

25

25

STAT-O-SEAL

CAVITY*

P-S

P-S

P-W

P-S"

P-W

NAXINUN ALLOWABLE

LEAK RATE (sccs)i

0.084

0.0082

-0.0082

0 BUBBLES/SEC

ACTUAL LEAK

RATE (sccs)

0.0213

-0.0002

0.140 psi/min

-0.0002

0

* P-S = PRIHARY-TO-SECONDARY SEAL

P-W = PRIMARY SEAL-TO-VIPER O-RING

** 5 psi DROP IN 5 MINUTES

MONITOR PRESSURE RISE RATE WITH P-W PRESSURIZED

Table 2 shovs the results of the internal nozzle joint leak tests. Joint

No. 1 vas tested vith the 8U75248, SIN 006 equipment, vhile Joints 2

through 5 vere tested vith the 2U129718 equipment. The "8U" vas used on

all flight motor No. 1 joints. The "2U" vas used on the all flight motor

nozzle internal joints. All data vere yell vithin limits.

Table 7 shovs results of leak test performed on the vent port plugs used on

0N-8. All results vere rill vithin limits.

TABLE 7

011-8 VENT PORT PLUGS LEAK TEST RESULTS

PRESSURR

(psig)

ALLOWABLE

LEAK RATE

(sccs)

ACTUAL LEAK RATE (sccs)

AFT CENTER FORWARD NOZZLE/CASE

1000 0.10 -0.0055 0.0051 0.0015 -0.0015

TVR-17591, Vol IV

29
3.5 Adjustable Vent Port Plugs

The adjustable vent port plug (AVPP), illustrated in Figure 7, was tested

in QM-8. Four AVPPs vere successfully installed in the case field joints

and the nozzle-to-case joint vent ports at 135 and 43.2 degrees, respectively. A 2U132133 (8U76549) installation tool, shorn in Figure 8, yam

used to install the bottom portion of the AVPPs in the vent ports. Each

AVPP yam installed per ST_/7-3499 (see Reference 8) and leak checked per

STW7-3661 (see Reference 9).

No major problems occurred during the installation of the AVPPs. Three

bottom portions vere replaced vhen the AWP tool slipped causing raised

metal on the bottom plug. This anomaly yam caused from the incorrect use

of the installation tool. After training technicians in the use of the

tool, no additional problems vith the tool occurred. Training should be

implemented to teach the correct use of the tool to prevent further problems vith raised metal on the bottom plug. TWR-18838 (see Reference 10),

documents the procedure for correct use of the AVPP installation tool.

The AVPP installation tool vorked as designed to install the bottom portion

of the AVPP into the port to the 70 in.lb maximum torque. The removal of

the tool did not affect the installed plug. In addition, the installation

process using the AVPP installation tool did not cause any damage to the

tool. Two bottom portions vere replaced because the installation torques

exceeded the requirements (too much locking device). The installation

1"VR-17591, Vol IV

3O
specification STV7-3499 (see Reference 8) has provisions to remove any

plugs that exceed the initial installation torque.

Each AVPP successfully passed leak check. All were below the 0.1 sccs

allowable leak rate. Actual leak rates are given in Table 7. Post-test

inspection results indicate all AVPPs were nominal. No motor pressure

reached the AVPPs, thus, no assessment of blow by or erosion can be made on

the seals.

3.6 Squeeze Calculations

No DRs were generated on the 0M-8 0-rings addressing the minimum squeeze.

All O-rings were within the drawing tolerances, therefore, all 0M-8 O-ring

squeezes were within limits outlined in TVR-18811, Revision A (see

Reference 11).

4.0 TEST RESULTS

The test results monitored by Structural Applications and Structural Design

are described in this section. In most cases, actual test data are compared to predicted values for each location and are shown in the Data

Summary Tables, Tables 8 through 33. Test data from each joint are summarized in these tables. Biaxial gages are presented in two tables - one to

show the maximum strain and a comparison with predictions (where applicable), and another to show the maximum calculated hoop and axial stress.

TWR-17591, Vol IV

31
The predictions included in the_e tab].es are ratioed to OH-8 pressure with

respect to gage location. The ratios were determined by multiplying the

original prediction by the ratio of the estimated QM-8 pressure to the

prediction pressure. This is done because each set of predictions were

calculated assuming a common pressure, which in most cases is somewhat

larger

using

made.

than the actual pressure for the specific location. Therefore, by

the ratio of the predictions to QM-8 values, a comparison can be

The calculation of the pressure ratio works as follows:

Maximum radial growth, e.g., girth strain, for a particular

location is found from test data, and the time at which it

occurred. The head end pressure at this time is determined,

and a predicted pressure drop to the gage location at this

time is found. For QH-8, the predicted pressure drops were

given in TI/R-18990 (see Reference 12). Therefore, the

pressure ratio is:

Pr°r ° E ad dPre P-d°ePdedPurD°

The percent difference between analysis and measured strain data is

given by:

(Prediction)*(Pressure Ratio) - Measured Measured x i00

4.1 Instrumentation

Instrumentation gages were placed on and close to the field and nozzle-tocase joints to characterize joint performance. Following is a list of

gages used and their function.

Tb'R-17591, Vol IV

32
Joint Girth Gages- Neasures the hoop strain for the entire 360

degree circumference. From the averaged hoop

strain, radial deflections are determined from

the product of measured (average) girth strain

and the nominal hardware radii at the corresponding gage location.

Biaxial Gages- Neasures local, rather than average (girth

gages) axial and hoop strains incurred in the

case during pressurization. From the strains,

stress canbecalculated.

StrainsertsLinearly VariableDifferential

Transducer (LVDT)

Added to the hollowed out heads of the nozzle-tocase radial and axial bolts to measure initial

and final loads on the bolts in pounds.

Used to measure 0-ring gap opening for the field

joints via the 45 degree leak check port.

Pressure Transducer- Installed in the igniter to measure head end

pressure.

Thermocouple- Instrumented on the field and nozzle-to-case

joints to monitor temperature.

Measures axial growth across the joint(s), gages

and membrane.

Axial Deflection4.2 Field Joint Performance

OM-8 instrumentation on the field joint consisted of four girth gages

(except on the aft joint where there were none) and one LVIYr per joint.

Deflection gages were placed across each field joint to measure axial

growth (see Section 4.8). Test results at these locations are compared to

analytical results. To predict QM-8 field joint response, a three-dimensional finite element model was used for pretest predictions. The basic

model represented a one degree cyclic-symmetric slice of the case and used

friction interface elements to simulate the contact surfaces. A detailed

'r'iR-17591, Vol IV

33
degcrJption of the mode] can he fo.nd in TVR-]7118, S.pplement B, Revision

A (see Reference 13).

4.2.1 Field Joint Girth Gages

Tables 8 and 9 list the girth gage response (i.e., strain and radial

growth) of the forward and center field joints, and compare it with the

predictions. The results shova strong correlation between analysis and

test data. Field joint predictions come within 8.5 percent of measured

values.

Close study of the field joint growth behavior shows the joint is moving

outward with the areas furthest from the pin centerline moving the most.

This can be seen from the higher radial growth values at the forward and

aft ends of each joint, and the lover values closer to the pin centerline.

TABLE 8

QM-8 FORWARD FIELD JOINT GIRTH GAGE RESPONSE (Zero to 120 "seconds)

TEST NAME: QM-8

JOINT: _ FIELD

DESCRIPTION: JOINT GIRTH Cg_3ES

THE TIME RANGE IS 0.0 TO 120.0 S_

GIRTH

GAGE GAGE RADIUS

LOCATION NUMBER STATION (IN)

RADIAL

(XN)

TEST

STRAIN

(U_N/IN)

ADu'USTU)

ADJUSTED ANALYSIS DIFF IN

ANALYSIS RADIAL RADIAL

STRAIN GROWTH GROWTH

(UIN/IN) (IN) ( % DIFF)

1 R303 848.5 73.1 h_) ND hE) _ I_)

2 S677 850.2 73.5 ND hD hD hD 5D

3 S965 852.6 73.5 0.157 2140 1959 0.144 -8.5

4 S621 855.0 73.1 0.175 2400 2441 0.178 1.7

TWR-17591, Vol IV

34
TABLE9

QM-8CENTERFIELD JOINTGIRTHGAGERESPONSE(zero to 120 Seconds)

TEST NAME: _q-8

JOINT: CTR FIELD

DESCRIPTION: JOINT GIRTH GAGES

THE TIME RANGE IS 0.0 TO 120.0 SEC_M_

GIRTH RADIAL TEST

GAGE GAGE RADIUS G_CWTH STRAIN

LOCATI(DN NUMBER STATION (IN) (IN) (UIN/IN)

A/_LYSIS DIFF IN

A/_.LYSIS RADIAL RADIAL

STRAIN GRCWTH GROWTH

(UIN/IN) (IN) ( % DIFF)

1 R304 1168.5 73.1 0.155 2118

2 $682 1170.2 73.5 0.136 1853

3 $966 1172.6 73.5 0.151 2056

4 $635 1175.0 73.1 0.169 2316

1973 0.144 -6.9

1880 0.138 1.4

1915 0.141 -6.8

2385 0.174 3.0

4.2.2 0M-8 Field Joint Radial Growth Comparisons

Tables I0 and II, and Figures 10 and 11 compare OM-8 field joint radial

growth to that on previous flights 360L001 and 360L002; and, full-scale

static tests PV-1, 0M-7, 0M-6, DM-9, DH-8, and analysis. All values are

pressure ratioed to the estimated 0M-8 joint pressures. Radial growth

values compare closely, considering the differences between each configuration. Actual radial growth at Location 3 on all three joints is much

higher than the predictions, which is caused by the case thickness being

smaller than the thickness used in the model. Figures 10 and 11 graphically illustrate data presented in Tables 10 and 11.

TWR-17591, Vol IV

35
TABLE10

FORWARDFIELD JOINTRADIALGROWTHCOMPARISONS TO 0M-8

Fwd Field Girths AVerAGE JOINT _ AT _X SIRAIN - 827

s'm-27 s't_-26 tV_L_ GR_m {Incl.)

Loc. G_Z _ _ _GUT Ln'T RIGHT UnrT t_'-I _t-7 _ m-9 _ Prod

1 R303 NO NO ND NO NO NO NO 0.182 0.151 0.153 0.158 0.154

2 $677 ND ND ND 0.146 ND 0.145 ND 0.140 0.132 0.146 0.142 0.141

3* $965 2150 0.157 NO 0.162 NO 0.164 NO 0.157 0.154 ND 0.155 0.144

4 $621 2400 0.175 0.175 0.174 NO 0.180 NO 0.174 0.173 0.166 0.177 0.178

* _ is 1/3 Inch _ce Fwd than the other rotors

Note: All Test Radial Gcuwths Are Ratios of _ Test Pressure

TABLE 11

CENTER FIELD JOINT RADIAL GROWTH COMPARISONS TO QM-8

Ctr Field Girths AVn%q]E JOINT PRESS[_E AT _%X _ - 799

S'IRA.U4 _27 STS-26 RRDIAL (3FCJW_ (Inches)

LOC. G_E _ _ RIGHT LEFT RIGST LEFT PV-1 QM-7 _ U_-9 _

1 R304 2118 0.155 ND NO NO NO NO NO ND 0.146 0.151 0.143

2 $682 1853 0.136 0.134 0.139 ND 0.140 NO 0.140 0.132 0.150 0.141 0.138

3* $966 2056 0.151 NO 0.156 0.158 NO 0.154 0.155 0.149 0.135 0.155 0.141

4 $635 2316 0.169 0.165 0.166 ND NO 0.173 0.171 0.167 0.165 0.176 0.174

* _ is 1/3 Inch _re Fwd than the other motors

Note: All Test Radial Gcuwths Are Ratios of _ _st Pressure

TVR-17591, Vol IV

36
_ CORPORATION

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TWR-17591 IV

J_GE 37
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TWr-17591 I voL IV

I_A_ 38
4.2.3 LVDT Gages

The O-ring gap opening for QM-8 was

center and aft field joints via the 45

were lockwlred, torque painted, and

ports. These measurements were also

measured directly for the forward,

degree leak check ports. The LVDTs

fitted tight into their respective

taken on the JES and TPTA tests.

Figure 12 shows the actual test data for the forward field joint LVDT. The

center, and aft field joint LVDT gages produced no data. Note that a

negative value on the plot corresponds to gap opening and positive value to

gap closing. Table 12 lists the maximum measured O-ring gap openings; the

flaw, if any, to the joint; and the test pressure for QM-8, OM-7, QM-6,

TPTA-I.I, JES-3A, and JES-3B. For QM-8, the maximum field joint gage

pressure was estimated to be 833 psig, which occurred at the forward field

joint between 9 to II seconds.

For the JES and TPTA tests, O-ring gap measurements were taken at more than

one Location around the circumference, whereas qM-8 produced only one data

point at 45 degrees on the forward field joint. Thus, it is probable the

reading for QM-8 was not a maximum. On JES and TPTA, up to 12 LVDT

readings were taken on a particular joint. The values used in Table 12 for

the JES and TPTA tests are the measured maximums from these readings. The

largest field joint O-ring gap measured (flawed or unflawed) was 0.007 inch

(QM-6). The 0.004 inch gap opening on the QM-8 forward field joint at the

45 degree Location was the same as predicted by analysis.

TWR-17591, Vol IV

39
TABLE 12

O-RING SEALING GAP OPENINGS, 0M-7, 0M-6, JES, NJES, TPTA

Max. Hax.

O-ring Gap Test Pressure ETA

Test Joint (in.) Defect (psig) Ring

Field

Joints

0M-8 Fwd 0.004 None 833 360

0H-7 Fwd 0.004 None 877 360

0M-6 Fwd 0.007 None 854 360

0M-6 Aft 0.002 None 816 360

JES-3A A 0.006 None 939 270

JRS-3A B 0.005 J Seal Vave 939

JES-3B A 0.004 Channel to 907 None

Feature O-ring

JES-3B B 0.005 Pressure to 907

Primary O-ring

TPTA 1.1 A 0.001 None 901 360

TPTA 1.1 B 0.006 None 901

Nozzle NJES-2A Primary 0.007 Flaw to Viper 1025

to O-ring (saw no pres.)

Case

NJRS-2A Secondary No Data " 1025

O-ring

NJES-2B Primary 0.005 Flaw to Viper 847

O-ring (say pressure)

NJES-2B Secondary 0.002" " 847

O-ring

TPTA 1.1 Primary 0.006 " 901

O-ring

TPTA I.I Secondary 0.004 " 901

* Maximum Gap Aft of Secondary

TVR-17591, Vol IV

40
_ CORPORATION

SPACE OPERATIONS

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ooc No. TWR-17591

s.c I _'A°_ 41
Therefore the value measured on 0M-8 falls within the TPTA and JES data base

which demonstrates that the O-rings would of remained sealed if motor pressure

reached the primary O-ring. Also resiliency testing, which is an on-going study

at this time, has shown that fluorocarbon will track 0.018 inch gap opening (see

TWR-17991, Reference 14), given the following conditions:

o Assembled with 16.5 percent squeeze for 180 days. O-ring at 75

°F at the time of test.

o Assembled with 18 percent squeeze for 365 days. O-ring at 75

°F at the time of test.

o O-rings stored at ambient temperatures.

The lowest calculated percent squeeze for the OH-8 field joints was 21.0

percent (TWR-18811, Reference ii). Also the joint heater temperatures (see

Table 32) were in the appropriate range to assure a minimum 0-ring

temperature of 75 °F. None of the field joints or the nozzle-to-case joint

were assembled beyond 365 days before the static test was conducted.

There was no evidence of gas reaching the forward and aft field joint

O-rings because of the effectiveness of the J-Seal insulation. Therefore,

the performance of these field joint O-rings cannot be fully evaluated.

4.3 Factory Joints

4.3.1 Forward Segment Factory Joint Girth Gage Response

QM-8 instrumentation on the forward segment factory joint consisted of four

girth gages. Table 13 lists the girth gage response for the zero through

TWR-17591, Vol IV

42
120 second range, and compares measured strain and corresponding radial

grovth vith predicted values. Predictions vere vithin 10.6 percent of

measured test data. As expected, the pattern of joint rotation is the same

as seen on the field joints. Hovever, note the values of radial grovth are

generally higher than the field joints. This happens because this factory

joint is nearer to the head end pressure, and the capture feature, vhich

limits joint rotation, is not included in the factory joint design. Radial

grovth at Location 3 is higher than predicted, vhich vas also the case in

the field joints.

TABLE 13

ON-8 FORWARDSEGMENT FACTORY JOINT GIRTH

GAGE RESPONSE (Zero to 120 seconds)

rEST NAME: QH-8

JOINT: FWD SEGM_2_T FACTORY JOINT

DESCRIPTION: GIRTH GAGES

THE TIME RANGE IS 0.0 TO 120.0 SECONDS

{ ¢

GIRTH

GAGE GAGE RADIUS

LOCATION NUMBER STATION (IN)

RADIAL

GROWTH

(IN)

TEST

STRAIN

(UIN/IN)

ADJUSTED

ADJUSTED ANALYSIS DIFF IN

ANALYSIS RADIAL RADIAL

STRAIN GROWII4 GROWTH

(UIN/IN) (IN) ( % DIFF)

1 Sll00 688.5 73.1 0.181 2472

2 $1101 690.2 73.5 0.168 2292

3 SII02 692.6 73.5 0.174 2369

4 S1103 695.0 73.1 0.181 2480

2360

2179

2117

2354

0.173 -4.5

0.160 -4.9

0.156 -10.6

0.172 -5.1

TWR-17591, Vol IV

43
4.4 Case Membrane Girth Gage Response

OH-8 instrumentation on the ease membrane consisted of eight girth gages.

Table 14 lists the girth gage response and compares the measured strain and

calculated radial growth vith predicted values. Every prediction is vithin

5.7 percent of measured test data. The forward segment is made of standard

weight cylinders, whereas the center and aft segments are made of thinner,

ltghtveight cylinders, which affect radial growth. (The attach cylinder is

standard weight, but there were no girth gages on this cylinder).

TABLE 14

OH-8 CASE RADIAL DEFLECTION, CASE GIRTH GAGE RESPONSE (Zero to 120 seconds)

TEST NAME: Qi_8

JOINT: CASE RADIAL DEFLECTION

DESCRIPTION: CASE GIRTH

THE TIME RANGE IS 0.0 TO 120.0 S_ l'( i i l?

f i l "f"f i,',J,',@

GIRTH

GAGE GAGE RADIUS

LOCATION NUMBER STATION (IN)

RADIAL

GROWTH

(IN)

ADYOSTED

AIkTu_STED ANALYSIS DIFF IN

TEST ANALYSIS RADIAL RADIAL

STRAIN S'rl_AN _ GRON'm

(UIN/IN) (UIN/ZN) (IN} ( % DIFF}

1 S584 611.5 73.0 0.270

2 S585 771.5 73.0 0.258

3 S586 931.5 73.0 0.271

4 $587 1091.5 73.0 0.268

5 $588 1251.5 73.0 0.265

6 $589 1411.5 73.0 0.268

7 $591 1637.5 73.0 0.249

8 $592 1757.5 73.0 0.251

3701 3699 0.270 -0.1

3539 3637 0.266 2.8

3712 3574 0.261 -3.7

3676 3533 0.258 -3.9

362B 3494 0.255 -3.7

3665 3456 0.252 -5.7

3407 3434 0.251 0.8

3432 3445 0.252 0.4

TVR-17591, Vol IV

44
r

4.4.1 QH-8 Case Membrane Radial Grovth Comparison

Analysis and data from 360L001, 360L002, QH-7, QN-6, and DH-8 (see Table 15

and Figure 13) shov that radial grovth for the forvard segment reduces from

the value at Station 1 to the value at Station 2, illustrating the pressure

drop down the bore of the motor. Also, a comparison vith these motors

shov that the radial grovth increases from Station 2 to Station 3. Factually, even though there is a pressure drop from Station 2 to 3, the transition from a standard veight segment to a ltghtveight segment overpovers the

pressure drop, and a net increase in radial grovth occurs. From Station 4

to 8 there is a drop of radial grovth, vhich is illustrated in Figure 13.

TABLE 15

CASE MEMBRANE P_IALGRO_rI_ COMPARISONS TO OH-8

d/, fl [,[,","l,,

I,_mbrar_Girths

SIBAIN bTS-27 SIS-26 RADIALGSU¢IH(IncUs)

U_C. _ 04-8 04-8 RIGS_ LEFT IUGSZ UmT F4-1 O_-7 Or-6 U_t-9 m-8 m_D

1 S584 3701 0.270 0.280 0.279 ND ND ND 0.289 0.275 0.268 0.284 0.270

2 S585 3539 0.258 0.266 0.270 ND 0.275 ND 0.275 0.262 0.271 0.282 0.266

3 S586 3712 0.271 0.284 ND ND ND ND 0.287 0.279 0.283 0.291 0.261

4 $587 3676 0.268 0.270 biD 0.281 0.279 ND 0.288 0.273 0.279 0.292 0.258

5 s588 3628 0.265 0.268 0.268 ND ND ND 0.279 0.264 ND 0.285 0.255

6 S589 3665 0.268 0.265 0.260 0.276 ND ND 0.278 0.268 ND ND 0.252

7 $591 3407 0.249 0.243 ND 0.261 0.260 ND 0.266 0.253 0.253 0.260 0.250

8 S592 3432 0.251 ND ND E_R ND ND 0.268 0.250 ND ND 0.251

NOTE: Only the predictions are pressure ratioed to

Nozzle to Case Joint Radial G_owth C_mparisons to

T'u'R-17591, Vol IV

45
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sEc I_ 46

IV
4.5 Case Btaxial Stresses

4.5.1 Aft-to-Center Segment Case Line Load

OH-8 biaxial gage instrumentation consisted of two sets of gages on the

center aft segment (one on Station 1196.48 and one on Station 1466.00).

Tables 16 and 17 show the moment biaxtal strains with the corresponding

predictions for the 120 second burn time. Tables 18 and 19 show the

maximum hoop with the corresponding axial stress, and maximum axial stress

with the corresponding hoop stress for this same time frame.

Hoop predictions compared more closely with the measured values than the

gages in the axial direction, especially at zero and 188 degrees. The

majority of this discrepancy can be attributed to the attempt to predict

the pretest sag effects of the motor in the test stand, and the subsequent

lessening of the sag during motor pressurization. This sagging effect,

known as column bending, would theoretically change motor stresses at the

zero and 188 degree locations as described:

When the SRN chocks are removed, a sag in the motor

results. This causes an induced tensile axial strain at

zero degrees (bottom of the motor), and an induced compressive axial strain at 188 degrees (top of the motor).

Then, just before the static-test, the biaxial gages in

these areas are set to zero. Therefore, when the motor

is fired, and the sag is lessened, an incorrect reading

in both the zero and 188 degree area results.

1_TR-17591, Vol IV

47
The maximum measured stress occurred in the hoop direction at Location 2,

270 degrees. The measured value was 145.1 ksi. Using biaxial improvement,

the ultimate case strength increases from 200 ksi to 214.2 ksi (i.e., 200 x

1.071 = 214.2), giving a safety factor of 1.48. No local yielding was

measured.

There was relatively little difference in maximum hoop stress and the time

it occurred between Locations 1 and 2. Maximum axial stress was affected

by the induced strut loads (those occurring during the initial second of

burn time), whereas maximum hoop stress was not.

A comparison of the QM-8 strain versus time plots with those of OH-6 (which

did not have strut loads applied) shows the 0M-8 strain was greatly affected by the induced strut loads. The QM-8 axlal and hoop gage plots followed

the same trend as in ON-6. Between about 51 and 60 seconds, the axial

strain shows a definite down spike at zero and 90 degrees, and an up spike,

of the same magnitude, at 188 and 270 degrees. Because gages were zeroed

prior to ignition, the propellant induced strains were ignored, thus, the

gages do not return to zero following burn time. Upon the completion of

the test, negative (compression) strain results at 200 degrees, with positive (tension) strain at 180 degrees.

T_-17591, Vol IV

48
TABLE 16

0M-8 AFT-T0-CENTER SEGMENT (STATION 1196.48) CASE LINE LOAD

MOMENT BIAXIALS (Zero to 120 seconds)

TEST NAME: QM-8

JOINT: AFT/CTR SE:(_'_ITr (STATION 1196.48)

DESCRIPTION: CASE LINE LOAD/ _ BIAXIALS

THE TIME RANGE IS 0.0 TO 120.0 SECONDS

_Ii J I fJf f,fI[_

TEST DATA ADJUSTI_ A_%LYSIS

AXIAL HOOP AXIAL IKX)P

AXIAL HOOP STRAIN STRAIN STRAIN STRAIN %DIFF %DIFF

LOCAT LOCATION GAGE GAGE (UIN/IN) (UIN/IN) (UIN/IN) (UIN/IN) AXIAL HOOP

0.0 R680 R679 -845 3610 288 3103 -134.0 -14.0

90.0 R740 R739 688 3506 740 3463 7.6 -1.2

188.0 R720 R719 1148 3666 -142 3777 -112.4 3.0

270.0 R686 R685 726 3550 747 3459 2.8 -2.6

AVERAGE: 429 3583

TABLE 17

QM-8 AFT-TO-CENTER SEGMENT (STATION 1466.00) CASE LINE LOAD

MOMENT BIAXIALS (Zero to 120 seconds)

TEST NAME:

JOINT:

DESCRIPTION: CASE LINE LOAD/ _ BIAX/ALS

THE TIME RANGE IS 0.0 TO 120.0 SECONDS

C_I-8

AFT/CTR SEGMENT (S_%TIGN 1466.00)

(I I I I I I i,i,,I,,l_

• TEST _ ADJUSTED ANALYSIS

AXIAL HOOP AXIAL B00P

AXIAL HOOP STRAIN STRAIN STRAIN STRAIN %DIFF %DIFF

LOCAT LOCATION GAGE GAGE (UIN/IN) (UIN/IN) (UIN/IN) (UIN/IN) AXIAL HOOP

0.0 R780 R779 -896 4193 298 3075 -133.3 -26.7

90.0 R782 R781 682 4126 715 3404 4.8 -17.5

188.0 R788 R787 983 3497 -145 3688 -114.8 5.5

270.0 R786 R785 781 4197 712 3404 -8.9 -18.9

AVERAGE: 387 4003

TWR-17591, Vol IV

49
TEST bE%ME: QM-8

JOINT: AFT/CTR S_ (STATION 1196.48)

DESCRIPTION: CASE LINE LOAD/ MOMENT BIAXIALS

THE TIME RANGE IS 0.0 TO 120.0 S_

TABLE 18

0M-8 AFT-TO-CENTER SEGMFRT (STATION 1196.48) CASE LINE LOAD

MOMENT BIAXIALS, MAXIMUM HOOP STRESS (Zero to 120 seconds)

I /2

I J I I I IIII 

MAX TEST DATA MAX TEST DATA

_oP AXIAL _OP AXIAL AXIAL _P AZ_AL _P

ANGULAR HOOP AXIAL STRESS STRESS STRAIN STRAIN STRESS STRESS STRAIN STRAIN

LOCAT LOCATION GAGE GAGE (KSI) (KSI) (UIN/IN) (UIN/IN) (KSI) (KSI) (UIN/IN) (UIN/IN)

0.0 R679 8680 122.7 49.4 3610 342 55.1 112.9 640 3220

90.0 R739 8740 121.1 54.1 3506 520 55.6 110.0 688 3116

188.0 R719 8720 127.8 60.8 3661 671 60.9 98.5 991 2671

270.0 R685 8686 122.9 55.5 3550 548 57.8 113.4 726 3207

AVERAGE: 123.6 54.9 3582 520 57.3 108.7 761 3053

TABLE 19

OH-8 AFT-TO-CENTER SEGMENT (STATION 1466.00) CASE LINE LOAD

MOMENT BIAXIALS, MAXIMUM HOOP STRESS (Zero to 120 seconds)

TEST NAME:

JOINT:

DESCRIPTION: CASE LINE LOAD/ _ BIAXIALS

THE TIME RANGE IS 0.0 TO 120.0 SECONDS

ca-8

AFT/UI_ SEG_NT (S'E_,TION 1466.00)

//I q I I I I I

TEST l_q_q MAX TEST DATA

800P AXIAL _)OP AXIAL AXIAL I_]OP AXIAL HOOP

ANGULAR HOOP AXIAL STRESS STRESS STRAIN STRAIN STRESS STRESS STRAIN STRAIN

LOCAT LOCATION GAGE GAGE (KSI) (KSI) (UIN/IN) (UIN/IN) (KSI) (KSI) (UIN/qN) (UIN/IN)

0.0 8779 8780 143.1 59.3 4193 456 61.1 139.9 554 4064

90.0 8781 8782 142.2 62.7 4126 580 63.8 140.8 634 4067

188.0 8787 8788 122.1 58.0 3497 641 58.2 122.0 647 3491

270.0 R785 8786 145.1 65.2 4197 634 65.3 145.0 640 4192

AVERAGE: 138.1 61.3 4003 578 62.1 136.9 618 3954

TWR-17591, Vol IV

50
4.5.2 Aft Field-to-Er Attach Joint

QH-8 biaxial gage instrumentation on the aft field-to-gT attach joint

consisted of 54 gages on the aft field joint and ET attach areas. Tables

20 through 22 list the naximun hoop and axial strains measured from biaxial

gages for the zero to 120 second burn time. Tables 23 through 25 list the

maximum hoop and axial stresses for this same time frame. The biaxial

strain gages at Locations 1, 2, and 3 are at Stations 1498, 1501, and 1511,

respectively.

The maximum measured stress occurred at Station 1498.0, Location 1 in the

hoop direction at 188 degrees, measuring a local stress o£ 109.8 ksi. This

maximum measured stress results in a 1.95 safety factor. The yield

strength of D6AC is 180 ksi, therefore, no local yielding vas measured in

this area. A fev select axial gages (R650, R714, R668, R674, R676, R716,

R678, $1182, and $1188) indicate that naximum axial stress is highly

affected by the induced strut loads.

Because of the complex nature of this area, no comparison to predictions is

given in this report, a detailed comparison is given in TWR-19506 (see

Reference 3).

T',_-17591, Vol IV

51
TABI.R 20

QH-8 AFT FIELD-TO-ET ATTACH (STATION 1498.00)

JOINT BIAXIAL GAGES (Zero to 120 seconds)

TEST NAME:

JOINT:

DESCRIPTION: JOINT BIAXIAL GAGES

THE TIME RANGE IS 0.0 TO 120.0 SEC(_DS

QN-8

AFT FIELD / ET AT]InCH (S'I_TIC_ 1498.00)

TEST DA_I_

AXIAL BOOP

STRAIN STRAIN

(tUN/m) (tUN/n_ )

ANGULAR AXIAL HOOP

LOC._T LOCATI(_'4 GAGE GAGE

0.0 R644 R643 1634 2413

90.0 R744 R743 1836 2432

188.0 R726 R725 2420 2556

220.0 R650 R649 2232 2460

255.0 R656 R655 2068 2424

270.0 R654 R653 1854 2460

285.0 R658 R657 2021 2400

300.0 R714 R713 1979 .2389

320.0 R660 R659 1896 2342

AVERAGE: 1993 2431

TABLE 21

0M-8 AFT FIELD-T0-ET ATTACH (STATION 1501.00)

JOINT BIAXIALGAGES (Zero to 120 seconds)

TEST NAME: QM-8

JOINT: AFT FIELD / ET ATI_.CR (STATION 1501.00)

DESCRIPTION: JOINT BIAXIAL C._K3_S

THE TIME RANGE IS 0.0 TO 120.0

TEST DATA

AXIAL BOOP

STRAIN STRAIN

( UL,_/m ) (U_N/m)

AXIAL HOOP

LOCAT LOCATION GAGE GAGE

0.0 R662 R661 597 2108

90.0 R746 R745 539 228I

188.0 R728 R727 744 2262

220.0 R668 R667 863 2193

255.0 R674 R673 714 2170

270.0 R672 R671 671 2248

285.0 R676 R675 754 2138

300.0 R716 R715 735 2192

320.0 R678 R677 790 2101

AVER_: 712 2188

TgR-17591, Vol IV

52
TABLE22

ON-8 AFT FIELD-TO-ET ATTACH (STATION 1511.00)

JOINT BIAXIAL GAGES (Zero to 120 seconds)

TEST NAME:

JOINT:

DESCRIPTION: JOINT BIAXIAL C_JNGES

THE TIME RANGE IS 0.0 TO 120.0 S_

_m-8

AFT FIELD / ET ATI_CH (SZkTION 1511.00)

TEST [_%_%

AXIAL S00P

AN_JLAR AXIAL HOOP STRAIN

LOCAT LOCATICN GAGE CAGE (UIN/IN)

STRAIN

(um/n_)

0.0 SI176 31175 997 2060

90.0 SI178 31177 940 2276

188.0 SI180 SI179 1237 2062

220.0 81182 31181 1327 2049

255.0 $1188 31187 1112 2095

270.0 SI186 31185 1019 2076

285.0 Sl190 31189 1098 1981

300.0 31184 $1183 1127 2106

320.0 SI192 Si191 1084 2083

AVERAGE: 896 2087

rEST NAME:

JOINT:

DESCRIPTION: JOINT BIAXIAL

THE TIME RANGE IS 0.0 TO 120.0 S_

TABLE 23

0M-8 AFT FIELD-TO-ET ATTACH (STATION 1498.00)

JOINT BIAXIAL GAGES MAXIMUM HOOP STRESS (Zero to 120 seconds)

@4--8

AFT FIELD / ET ATTACH (STATION 1498.00}

_/

,5

MAX TEST INk'I_ _ TEST DATA

IK)OP AXIAL IKX)P AXIAL AXIAL IK)OP AXIAL HOOP

ANGULAR HOOP AXIAL STRESS STRESS STRAIN STRAIN STRESS STRESS STRAIN STRAIN

LOCAT LOCATION GAGE GAGE (KSI) (KSI) (I/IN/IN) (UIN/IN) (ESI) (ESI) (I/IN/IN) {UIN/IN)

0.0 R643 R644 96.3 77.5 2413 1579 78.8 95.2 1634 2364

90.0 R743 R744 99.1 85.7 2421 1825 86.0 98.9 1836 2410

188.0 R725 R726 109.8 106.8 2556 2420 106.8 109.8 2420 2556

220.0 R649 R650 101.3 88.9 2460 1909 93.3 85.0 2232 1864

270.0 R653 R654 100.6 86.7 2460 1843 87.0 100.5 1854 2454

255.0 R655 R656 101.7 93.8 2424 2068 93.8 101.7 2068 2424

285.0 R657 R658 i00.I 90.3 2400 1971 90.5 99.8 1977 2395

300.0 R713 R714 98.9 88.1 2389 1908 88.6 97.8 1935 2345

320.0 R659 R660 96.1 83.6 2342 1785 84.8 89.7 1896 2114

AVERAGE: 100.4 89.1 2429 1923 89.9 97.6 1983 2325

TWR-17591, Vol IV

53
TAB[_ 24

OH-8 AFT FIELD-TO-ET ATTACH (STATION 1501.00)

JOINT BIAXIAL GAGES MAXIMUM HOOP STRESS (Zero to 120 seconds)

JOINT: AFT FIELD / ET AT_ (S_TICN 1501.00)

DESCRIPTION: JOINT BIAXIAL GN_.S

TIRE RANGE IS 0.0 TO 120.0

- l%a.X TEST II_TA _ TEST 11%TA

HOOP AXIAL HOOP AXIAL AXIAL HOOP AXIAL HOOP

ANGULAR HOOP AXIAL STRESS STRESS STRAIN STRAIN STRESS STRESS STRAIN STRAIN

LOCAT LOCATION GAGE GAGE (KSI) (KSI) (UIN/IN} (UIN/IN) (KSI) (KSI) (OIN/IN) (UIN/IN)

0.0 R661 R662 75.1 39.8 2108 532 40.6 73.6 576 2049

90.0 R745 R746 80.6 40.8 2281 506 41.5 79.9 539 2249

188.0 R727 8728 81.8 46.4 2262 684 46.5 81.5 689 2252

220.0 R667 R668 77.7 39.8 2193 507 45.6 62.7 863 1624

270.0 R671 R672 80.8 44.4 2248 627 44.4 80.8 627 2248

255.0 R673 8674 78.9 45.6 2170 689 45.6 78.9 689 2170

285.0 R675 R676 77.7 45.1 2138 683 45.2 76.4 699 2095

300.0 R715 R716 79.1 44.5 2192 648 45.0 72.8 735 1972

320.0 R677 R678 76.1 43.4 2101 643 46.8 73.0 790 1961

AVERAGE: 78.6 43.3 2188 613 44.6 75.5 690 2069

TABLE 25

0H-8 AFT FIELD-TO-ET ATTACH (STATION 1511.00)

JOINT BIAXIALGAGES MAXIMUM HOOP STRESS (Zero to 120 seconds)

AFT FIELD / ET ATI_.CH (S'I_TION 1511.00)

JOINT BIAXIAL GAGES

0.0 TO 120.0 SE_

._EST NAME:

JOINT:

DESCRIPTION:

THE TIME RANGE IS

MAX TEST _ _ TEST DA_%

B00P AXIAL BOOP AXIAL AXIAL HOOP AXIAL HOOP

ANGULAR HOOP AXIAL STRESS STRESS STRAIN STRAIN STRESS STRESS STRAIN STRAIN

LOCAT LOCATION GAGE GAGE (KSI) (KSI) (bIN/IN) (bIN/IN) (KSI) (KSI) (UIN/IN) (biN/IN)

0.0 Si175 SI176 77.9 53.0 2060 948 53.8 76.9 986 2017

90.0 Si177 SI178 65.6 -5.6 2276 -897 -9.0 57.3 -924 2034

188.0 Si179 Si180 81.0 62.4 2062 1232 62.4 81.0 1232 2062

220.0 SI181 Si182 78.7 56.5 2049 1059 58.2 59.1 1327 1368

300.0 SI183 SI184 80.7 57.2 2106 1062 57.6 79.7 1083 2069

270.0 SI185 SI186 78.8 54.3 2076 981 54.3 78.8 981 2076

255.0 81187 SI188 80.6 58.0 2095 1090 58.0 80.6 1090 2095

285.0 SI189 SI190 76.4 55.5 1981 1049 55.5 75.0 1066 1932

320.0 S1191 $1192 79.2 54.9 2083 997 55.8 74.1 1084 1900

AVERN3E: 77.7 49.6 2087 836 49.6 73.6 881 1950

TWR-17591, Vol IV

54
4.6 Nozzle-to-Case Joint Performance

4.6.1 Nozzle-to-Case Joint

QM-8 instrumentation on the nozzle-to-case joint consisted of seven girth

gages, three biaxial gage locations, and eight strainserted axial and

radial bolts. Test results at these locations are compared to analytical

results acquired from a three dimensional finite element analysis (see

Reference 15).

The analysis was performed with the finite element code ANSY5 using a 1.8

degree model of the nozzle-to-case joint. Near the joint region, the model

was three-dimenslonalj transitioning into two-dimensional away from the

joint.

The following assumptions and parameters were included in the model:

O Nominal values for material properties and hardware

dimensions

0 Preload of 140 kips in the axial bolts and 47 kips in the

radial bolts

Internal pressure of 909 psig applied to the backside of the

primary O-ring groove

o Frictionless joint behavior

o Zero vectoring nozzle condition

o Propellant was not modeled

T_R-17591, Vol IV

55
Because the model is cyclic-symmetric, any circumferential variation

indicated by test data will not be taken into account. The analysis was

performed at 909 psig_ which was linearly scaled to the estimated 792 pslg

nozzle stagnation pressure that involves approximately five percent error

caused by the nonlinear analysis. The estimated pressure corresponds to

the maximum strain gage readings at the time interval of 20 seconds after

ignition.

4.6.2 Nozzle-to-Case Girth Gages

Radial deflection is an important parameter to characterize, since it is

proportional to joint hoop stress and bolt hole stress concentration.

Table 26 shows the girth gage response from 18 to 22 seconds. This tile

frame was selected to minimize the effects of vectoring. The results

compare closely to the analytical results, ranging from 10.5 to 19.6

percent. Also included in the table is the maximum radial growth for the

full duration of the test (zero to 120 seconds).

As expected, calculated radial growths indicated a "prying open" action and

outward rotation of the joint. The maximum measured hoop strain (1778

in./in.) and radial growth (0.097 in.) occurred at Location 3.

Comparing QN-8 strain versus time plots to QN-6_ it can be concluded that

the strut loads had little effect on strain at this location (also see

Table 27).

TVR-17591, Vol IV

56
\

TABLE 26

QH-8 AFT DOME, FIXED HOUSING NOZZLE-T0-CASE JOINT

GIRTH GAGES (18 to 22 seconds)

I 2

TEST NAME: QN-8

JOINT: AFT DONE, FIXED HOUSING

DESCRIPTION: NOZZLE CASE GIRTH GAGES

THE TIME RANGE IS 18.0 TO 22.0

2

ADJUSTED

ADJ'D'STI_) A_LYSI S DIFF IN NAXINON

GIRTH RADIAL TEST IM_LYSIS RADIAL RADIAL RADIAL

GAGE GAGE RADIUS GROWTH STRAIN STRAIN GR_t'H _ GROWTH

LOCATION _._ER S_TION (IN) (IN) (UIN/IN) (UIN/IN) (IN) ( % DIFF) 0-120 SECONDS

4.6.3

1 $880 1873.0 50.4 0.081 1598 1431 0.072 -10.5 0.087

2 $878 1876.3 50.5 ND _ ND NO h_ ND

3 S877 1876.3 54.4 0.097 1778 2126 0.116 19.6 0.126

4 S884 1875.7 54.4 0.092 1689 1999 0.109 18.4 0.120

5 $887 1874.9 54.8 0.083 1520 1784 0.098 18.1 0.110

6 $875 1874.2 54.8 0.076 1394 1622 0.089 16.4 0.i00

7 S874 1872.5 55.2 0.066 1193 1345 0.074 12.7 0.105

Nozzle-to-Case Joint Comparison

Table 27 and Figure 14 compare the radial grovth of the OH-8 nozzle-to-case

joint vith the same joint configuration (radial bolt design) used in

360L001, 360L002, PV-1, QM-7, fiN-6, DM-9, DM-8, and analysis. Data from

QH-8 radial grovth compares closely to the other motors vhich again confirm

the minimal effect strut loads have on this joint as far as gap grovth is

concerned. Since the O-ring sealing surface gap grovth vas not directly

measured, it is assumed the grovth is similar to that measured from

NJES-2A, NJES-2B, and TPTA-I.1 testing, and predicted by analysis.

Tb-R-17591, Vol IV

57
Table 12 above lists the maximum measured O-ring gap openings, the flaw to

the joint, and the test pressure for NJES-2A, NJES-2B, and TPTA-I.I. For

QM-8, the maximum nozzle-to-case joint pressure did not exceed any maximum

NJES and TPTA test pressures listed in Table 12 for the respective joints.

The maximum measured gap opening for the nozzle-to-case joint was 0.007

inch (primary NJES-2A). Analysis predicts 0.006 inch for the primary

O-ring.

TABLE 27

NOZZLE-TO-CASE JOINTRADIALGROWTH COMPARISONS TO QM-8

Nozzle to Case Girths AVERAGE JOINT _ AT-_%X _ - 793

SIRAIN $IS-27 STS-26 RADIAL GRC_?_ (Inches)

LOC. G_Z (_m-8 _ RIGHT LEFT RIGIIZ LEfT I_-I _-7 _-6 us-9 uN-a RP_D

1 $880 1193 0.066 0.059 0.060 ND 0.051 0.086 0.067 0.080 0.072 ND 0.071

2 $878 ND ND 0.097 0.096 0.096 0.096 0.127 0.127 0.129 0.115 ND 0.1/7

3 $877 1778 0.097 ND ND ND ND 0.117 0.125 0.125 ND 0.124 0.114

4 $884 1689 0.092 0.091 0.090 0.I00 0.100 0.124 0.120 0.118 0.114 NO 0.107

5 S887 1520 0.083 0.083 0.081 NO NO 0.107 0.108 0.106 0.086 0.110 0.096

6 $875 1394 0.076 NO NO 0.090 0.087 0.108 0.i00 0.102 0.101 0.103 0.087

7 $874 1598 0.081 0.065 0.063 0.072 0.069 0.083 0.086 0.085 0.085 0.090 0.073

Note: All Test Radial Growths Aze Ratlos of _ Test Pressure

TWR-17591, Vol

58

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OOC NO. TWR-17591 I v°'- IV

sEc I "QE 59
4.6.4 Nozzle-to-Case Biaxtal Strain Gages

Previous static tests have shown the nozzle-to-case joint biaxial gages do

not compare as closely to analytical data as gages on other parts of the

motor. The reason for the variation is:

o The girth gage at Location 1 is at the neck of the fixed

housingJthe 3-D model grid may not be fine enough to

accurately predict circumferential strain.

o Analytical data was linearly scaled to test data.

o Nozzle stagnation pressure was estimated to be 792 psig, but

not measured.

o Nominal materials were used for the finite element model.

o A slight variation in gage placement can greatly alter the

expected results.

Two biaxial strain gages were placed on the fixed housing and one on the

aft dome. Table 28 contains the test results for the burn time of zero to

120 seconds. Table 29 compares the test results between 18 and 22 seconds

to analytical results to eliminate effects of nozzle vectoring. As

previously mentioned, the analysis was cyclic-symmetric, which means

analytical results will be identical at 90 degree increments about the

circumference.

As shown in Table 29, hoop strain correlated better for the gage Locations

1 and 3 than gage Locations 2. Gage readings at Locations I and 3 ranged

from 2.5 to 33.3 percent difference with the predictions. Gages readings

at Location 2 ranged from 18.8 to 41.0 percent difference. Meridional

strains at the three locations also varied, with the most favorable

TI/R-17591, Vol IV

60
correlation at LncRtlo. I (rsnge of 2.5 to 9.3 percent difference) _nd the

least favorable at Location 2 (range of 18.8 to 41.0 percent difference).

Stresses were calculated from the biaxial strains (see Table 28). The

maximum calculated hoop stress was 41.2 ksi, and occurred at Location 3,

270 degrees. The maximum calculated meridional stress was -32.9 ksi, and

occurred at Location 2, zero degrees. Based on the maximum calculated

stress of 41.2 ksi and an ultimate material strength of 200 ksi, the safety

factor is 4.85.

TEST NAME: C_-8

JOINT: FIXED HOUSING, AFT D(3_

DESCRIPTICN: NOZZLE / CASE BIAXIAL C_

THE TIME RANGE IS 0.0 TO 120.0 SECC_DS

TABLE 28

QM-8 AFT DOME, FIXED HOUSING NOZZLE-TO-CASE JOINT

BIAXIAL GAGES (Zero to 120 seconds)

I

ANGULAR HOOP MERID

LOCAT LOCATION GAGE GAGE

NAX TEST [m._% NAX

BOOP NERID 8_OP NERID N]_ID HOOP

STRESS STRESS STRAIN STRAIN STRESS STRESS

(KSI) (KSI) (UIN/IN) (UIN/IN) (KSI) (KSI)

TEST

NERID HOOP

STRAIN STRAIN

(tuN/rs) (tUN/m)

0.0 R528 R527 -11.9

90.0 R530 R529 -14.9

180.0 R532 R531 -11.2

270.0 R534 R533 -8.6

AVERAGE: -11.7

0.0 R520 R519 28.5

90.0 R522 R521 35.0

180.0 R524 R523 32.9

270.0 11526 11525 29.2

AVERAGE: 31.4

0.0 R602 R601 39.9

90.0 R604 R603 40.6

180.0 R606 R605 40.3

270.0 R608 R607 41.2

AVERAGE: 40.5

13.6 -550 589 14.3 -10.8 600

9.9 -611 495 14.6 -3.0 526

13.3 -521 572 14.5 -10.3 603

11.5 -416 481 13.9 -6.7 540

12.1 -525 534 14.3 -7.7 567

-30.3 1290 -1331 -32.9 26.9 -1404

-17.0 1367 -952 -19.5 32.4 -1010

-20.0 1328 -1032 -22.4 31.5 -1098

-29.5 1306 -1312 -31.9 27.2 -1370

-24.2 1323 -1157 -26.7 29.5 -1220

-16.5 1525 -989 -17.6 37.3 -999

-15.7 1542 -968 -17.2 34.5 -955

-16.2 _36 -981 -18.2 35.9 -1002

-15.6 1560 -971 -17.2 37.1 -981

-16.0 1541 -977 -17.5 36.2 -984

TWR-17591, Vol IV

-520

-259

-505

-376

-415

1265

1306

1305

1263

1285

1452

1353

1410

1440

1414

61
TABLR 29

0M-8 AFT DOME, FIXED HOUSING NOZZLE-TO-CASE JOINT

BIAXI GAGES (18 to 22 seconds)

TEST NAME: QM-8

JOINT: FIXED HOUSING, AFT DONE

DESCRIPTION: NOZZLE / CASE BIAXIAL CJM_ES

THE TIME RANGE IS 18.0 TO 22.0

I

TEST DAb MXXUb'TE) AI_LYSIS

HOOP MERID HOOP MERID

AN(YJLAR HOOP MERID STRAIN STRAIN STRAIN STRAIN %DIFF

LOCAT LOCATION GAGE GAGE (UIN/IN) (UIN/IN) (UIN/IN) (UIN/IN) IK)OP

%DIFF

NERID

4.6.5

0.0 R528 R527 -513 551 -554 571 7.9 3.6

90.0 R530 8529 -465 523 -554 571 19.1 9.3

180.0 R532 R531 -482 558 -554 571 15.1 2.5

270.0 R534 R533 -415 540 -555 570 33.3 5.5

AVERAGE: -469 543

0.0 R520 R519 1276 -1404 1036 -829 -18.8 -41.0

90.0 R522 R521 1356 -1021 1034 -828 -23.7 -18.9

180.0 R524 R523 1309 -1098 1036 -829 -20.9 -24.5

270.0 R526 R525 1288 -1370 1037 -829 -19.5 -39.5

AVERAGE: 1307 -1223

0.0 R602 R601 1525 -1006 1649 -848 8.1 -15.8

90.0 R604 R603 1542 -989 1651 -848 7.1 -14.2

180.0 R606 R505 1529 -1002 1650 -850 7.9 -15.2

270.0 R608 R607 1540 -985 1653 -849 7.4 -13.8

AVERAGZ: 1534 -996

Nozzle-to-Case Strainsert Gages

The Strainserts for QN-8 were added to eight radial and eight axial bolts.

As Table 30 shows, the Strainserts at preload ranged from 40 to 54.9 kips

for the radial bolts, and 122.6 to 139.2 kips for the axial bolts. The

specification tolerances for QM-8 were 45.0, + 4.5 kips for

bolts and 140.0, + 14.0 kips for the axial bolts.

the radial

TWR-17591, Vol IV

62
TABLE 30

ON-8 AFT DONE, FIXED HOUSING (STRAINSERT)

RADIAL STATION 1874.3, AXIAL STATION 1875.2 (Zero to 120 seconds)

TEST _J4E: _-8

JOINT: FIXED IKXJSING, AFT DO#_ (STRAINSERT)

DESCRIPTION: RADIAL - STA 1874.3, AXIAL - S_% 1875.2

THE TIME RANGE IS 0.0 TO 120.0

I AL

0-i SEC. 12-22 SEX:.' 120-130 SEC. @920 PSIG

PRE_ PRELOAD MEAS . MEAS. MEAS . MEAS. MEAS . MEAS. ANAL. ANAL.

ANGULAR STRESS LOAD STRESS LOAD STRESS LOAD STRESS LOAD PRELOAD LOAD

LOCAT GAGE LOCATION (KSI) (KIPS) (KSI) (KIPS) (KIPS) (KIPS) (KIPS) (KIPS) (KIPS) (KIPS)

RADIAL R150 358.2 78.6 40.0 75.2 30.3 75.6 38.5 77.0 39.2 46 44

RADIAL RISI 45.0 85.4 43.5 80.9 41.2 00.7 41.1 84.4 42.9 46 44

RADIAL R152 88.2 81.2 41.3 75.3 38.4 75.9 38.6 80.3 40.9 46 44

RADIAL R153 135.0 81.9 41.7 76.9 39.1 76.2 38.8 80.0 40.7 46 44

RADIAL 8154 178.2 80.9 41.2 72.8 37.0 75.2 38.3 82.0 41.7 46 44

RADIAL R155 225.0 80.4 40.9 73.6 37.5 75.2 38.3 80.0 40.7 46 44

RADIAL R156 268.2 81.0 41.2 72.7 37.0 73.6 37.4 80.8 41.1 46 44

RADIAL R157 315.0 107.7 54.9 90.7 50.2 98.1 49.9 107.8 54.9 46 44

AXIAL S397 O.0 98.7 129.7

AXIAL S401 46.8 96.6 127.0

AXIAL S398 90.0 94.6 124.4

AXIAL S399 180.0 94.2 123.9

AXIAL S4O0 270.0 94.6 124.4

AXIAL S402 136.8 93.2 122.6

AXIAL S403 226.8 98.1 129.1

AXIAL $404 316.8 105.8 139.2

90.7 119.2 91.1 119.8 100.1 131.7 140.0 130.9

89.6 117.8 89.0 117.0 96.1 126.4 140.0 130.9

88.2 115.9 87.4 114.9 94.1 123.8 140.0 130.9

87.2 114.6 87.1 114.6 94.5 124.3 140.0 130.9

87.5 115.1 87.1 114.6 94.4 124.1 140.0 130.9

86.3 113.6 86.5 113.7 94.2 123.9 140.0 130.9

91.7 120.6 91.5 120.3 97.2 127.8 140.0 130.9

99.6 131.0 99.0 130.2 104.9 138.0 140.0 130.9

4.6.5.1 Axial Bolts

Eight axial bolts were replaced with Strainsert bolts (see Table 30) to

measure a tension load in the bolts. Therefore, the change in bolt load

resulting from motor pressurization was monitored during the firing. All

shoved a bolt load decrease in the range of 8.2 to 10.5 kips from zero to 1

second, 8.8 to 10.0 kips from 12 to 22 seconds, and -2.0 (positive load

recovery) to 1.3 kips from 120 to 130 seconds.

Tb'R-17591, Vol IV

63
An

bolts. The analysis predicts a load decrease of 9.1 kips at 920 psig.

bolt load drops off because of thinning of the fixed housing flange.

flange thinning is attributable to Poisson's effect resulting from

flange displacing radially

actual measured data.

analysis was performed using a preload value of 140 kips in the axial

The

The

the

outward. The results correlate closely with

4.6.5.2 Radial Bolts

The radial bolts were a primary concern of the QN-8 (see Table 30) nozzleto-case Joint because the amount of preload in these bolts governs the

amount of delta gap opening of the joint. Delta gap controls the amount of

dynamic O-ring squeeze and consequently, the sealing of the joint.

Strainserts were added to eight radial bolts. Table 30 indicates the

radial Strainsert bolts decreased in load during pressurization. The load

decreased in a range between 1.7 to 4.7 kips from zero to one second, 1.5

to 5.0 kips from 12 to 22 seconds, and -0.5 (positive load recovery) to 0.8

kips from 120 to 130 seconds. The analysis, using a preload value of 46

kips, predicted the radial bolt loads would decrease by 2 kips at 920 psig.

This correlates closely with actual measured data.

T_/R-17591, Vol IV

64
4.7 Head End Pressure and Joint Temperature

Table 31 lists the maximum measured head end pressures and the time at

which they occurred. Table 32 gives the joint heater temperatures for the

field and nozzle-to-case joints immediately prior to static test.

TABLE 31

QH-8 FORWARDDOME CHAMBER PRESSURE (ZERO TO 120 SECONDS)

CIRCUMFERENTIAL MAXIMUM TIME OF

GAGE LOCATICN PRESSURE NAXPRES

NUMBER (DEG) (PSIA) (SEC)

P001 40.0 863.7 0.664

P002 270.0 872.6 0.656

P003 180.0 871.7 0.656

TABLE 32

QM-8 FORWARD, CENTER, AFT FIELD JOINTS AND NOZZLE-TO-CASE

JOINT AND _TERTEMPERATiH_ES (-10.0 to Zero seconds)

CIRCUMFERENTIAL MAXIMUM TIME OF

TEMPERATURE GAGE LOCATION TEMPERATURE ,MAX TEMP

LOCAT ,_K/MBER (DEG) (DEG F) (SEC)

FWD TI001 15.0 90.4 -6.968

TI002 .135.0 85.1 -4.984

TI003 195.0 101.1 -9.784

TI004 285.0 92.2 -7.576

CTR TI005 " 15.0 86.2 -2.840

TI006 135.0 84.9 -4.280

TI007 195.0 97.7 -6.680

TI008 285.0 105.7 -9.848

AFT TI009 15.0 92.0 -4.248

T1010 135.0 87.4 -3.736

T1011 195.0 101.7 -8.984

T1012 285.0 106.7 -9.768

NOZ T0807 0.0 82.0 0.0

T0808 120.0 78.5 0.0

T0809 240.0 85.0 0.0

TWR-17591, Vol IV

65
4.8 Axial Growth Deflections

Several long wire gages were installed along the length of the motor (see

Figure 15), and across joints to measure the axial growth experienced in

different areas of the motor during pressurization. Table 33 shows the

maximum deflection experienced by each gage for the duration of the test.

Locations 5, 7, and 8 are all across joints, and all show a negative

deflection. Evaluation of the placement of these gage locations which

experienced negative values supports that these values are in error. In

other words, the instrument measured a negative value but the joint did not

go negative. The measurement was that of of instrument, and not the joint.

The aft field joint does not show a negative value because it has a higher

stiffness due to the stiffener rings and struts.

The largest measured axial growth was 1.002 inches and occurred between

stations 527.0 and 1505.0 (270 degrees).

It is interesting to note that on the other side of the motor (90 degrees)

between stations 527.0 and 1829.0, the measured axial growth was 0.406

inch. The maximums for both of these gages occurred during the ignition

transient. Since the struts

case, they had some influence

sides of the motor.

are located on the 270 degree side of the

in causing this difference between the two

TWR-17591, Vol IV

66
TABLE 33

ON-8 Axlal Grovth Deflectlons (Zero to 120 seconds)

TEST NAME: QM-8

DESCRIPTION: AXIAL GROWTH DEFLECTIONS

THE TIME RANGE IS 0.0 TO 120.0 SE(rIqDS

FR0Pl TO GAGE AN(YJI2kR DEII_ECTION DEFLECTION

LOCAT STATION STATION NUMBER IX)CATION (IN) Atq_YSIS DIFFERENCE

1 527.0 1505.0 D196 270.0 1.002 t_) I_

2 527.0 1829.0 0027 92.0 0.406 ND

3 756.0 786.0 D169 80.0 0.021 0.017 0.004

4 756.0 786.0 D175 260.0 0.016 0.017 0.001

5 850.0 850.0 D321 86.0 -0.018 N_ _D

6 916.0 946.0 D168 80.0 0.028 0.014 0.014

7 1010.0 O386 86.0 -0.004 0.004 0.008

8 1170.0 D352 86.0 -0.012 0.023 0.035

9 1236.0 1266.0 P170 80.0 0.028 0.013 0.015

10 1490.0 D383 82.0 0.006 0.021 0.015

TWR-17591, Vol IV

67
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LISEC I P,GE 68
5.0 DISASSF, MBI,¥ INSPF.CTTON RESULTS

Structural Applications Design Engineering performed a post-fire evaluation

of the OH-8 external case, field joints, internal nozzle joints, nozzle-tocase joint, the igniter and safe and arm joints, and the factory joints.

The case and seals post-fire condition will be discussed with references

made to the inspection forms found in the Evaluation Plan (see Reference

16), and the engineering evaluation limits plan (see Reference 17).

Following the initial O-ring inspection at time of disassembly, the O-rings

were inspected by a specifically organized team made up of personnel from

Structural Applications, Liaison/Problem Reporting, and Quality Assurance.

The team function was to inspect the O-rings for damage which may have

occurred during the static-test, assembly, or disassembly; and damage which

may have gone undetected during disassembly inspection. Records are kept

on each O-ring and gasket so that the seals may be tracked for possible

reuse.

The following gnidelines have been established to classify O-ring,

Stat-O-Seal and corrosion damage found from post-flight test inspections.

These gnidelines were established so that each inspection database will be

consistent and not be confusing or misleading. Some of these definitions

are used in this document.

TNR-17591, Vol IV

69
O-RXNCS AND STAT-O-SEALS

Cut:

Scratch:

Nick:

Gouge:

Circumferential

or Radial Flovline:

(i) Closed:

(ii) Separable:

(iii) Open:

Width, essentially zero (have to

open up to find the damage), and

depth greater than 0.005 inch.

Width less than 0.005 inch and

depth less than 0.005 inch.

Width less than 0.020 inch, but

greater than 0.005 inch; and depth

less than 0.010 inch, but greater

than 0.005 inch.

Width greater than 0.020 inch and

depth greater than 0.010 inch.

Visible evidence of incomplete flov

or knit of the material.

Tightly adhered, not separable,

does not open vhen lightly probed.

Visually appears closed. Separates

vhen lightly probed.

Obvious separation or gap.

Hard Inclusion:

Porosity/Soft Inclusion:

Extrusion Damage:

Heat Effect:

Erosion:

Foreign material enclosed in the

seal material.

An air pocket enclosed in the seal

material.

Seal material pinched and/or cut

due to an overfill condition.

Glossy and/or hardened seal surface

due to hot gas impingement.

Seal material missing due to hot

gas impingement or blov by.

TWR-17591, Vol IV

70
\

CORROSION

Light Corrosion:

Medium Corrosion:

Heavy Corrosion:

Can be wiped off by hand. Surface

discoloration.

Cannot be wiped off by hand without

the use of a Scotch-Brite material,

methyl chloroform, or grease soaked

rag.

Starting to penetrate into the

metal surface such that pitting

and/or metal nmterial is

significantly eroded.

The following sections contain the details of each joint at disassembly and

subsequent seals examination by the Inspection Team.

5.1 External Walk Around

The external inspection of the fully assembled hardware at T-97 yam performed on 21 January 1989 (see pages A-1 through A-5, Appendix A). The

inspection included the case acreage, all field and factory joints, the

igniter, and nozzle-to-case joint. The stiffeners and ETA ring bolts were

also inspected. No anomalous conditions were encountered.

5.2 Field Joint Disassemblies

The QM-8 field joint configuration is shorn in Figure 2. Joint conditions

were as expected; there was no field joint O-ring damage found by

inspection at the time of disassembly. The V2 filler did not obstruct the

TqR-17591, Vol IV

71
"\

leak vent ports at 135 degrees. No corrosion was found on any field

joint. Detailed inspection results are documented below.

5.2.1 Forward Field Joint

The QH-8 forward field joint was disassembled on 8 February 1989 (see pages

A-6 through A-10, Appendix A). The overall condition of the joint was

excellent. No hot gas or soot was observed past the J-leg. There was no

evidence of damage to the O-rings while in the grooves. Inspection of the

O-rings by the O-ring Inspection Team revealed a 13.5 inch circumferential

scratch running from 1.6 to 12.6 degrees (see page A-10, Appendix A). The

depth of this scratch is indeterminable (very shallow). Scratches of this

nature have been found on FV-1, Flight 360L001 and 360L002 O-rings. The

cause is suspected to be from cleaning the 0-rings before final inspection.

No damage was found by the O-ring Inspection Team on the primary or

secondary O-rings.

There was no corrosion found on either the tang or clevis. The grease

condition was per STW7-2999 on the sealing and non sealing surfaces. The

V2 volume filler was in a nominal condition. Hetal pinhole slivers were

found in the bottom of the inner clevis leg pinholes in the following

locations: 52, 54, 58, 60, 62, 232, 282, 286, 288, 290, and 292 degrees.

This is a common occurrence. No other metal damage was found in the joint.

TVR-17591, Vol IV

72
A long thin line of vhlte colored material vas found on the aft edge of the

capture feature O-ring at 169 degrees. More thin lines of the vhite

colored material were found intermittently on the aft edge from 164 to 167

degrees. The long thin llne at 169 degrees was approximately 0.400 Inch

long. All thin lines of the white colored material ran circumferential on

the O-ring. Lab analysis of a sample of the material indicated that it was

Teflon tape adhesive. Teflon tape is used to mask the J-leg insulation

during grease application and O-ring installation processes.

Small thin lines of Teflon tape adhesive vere also found on the capture

feature metal-to-J-leg interface (aft of the capture feature groove on the

tang J-leg) at 153, 178, 180, 227, 228, and from 230 to 233 degrees. All

thin lines of Teflon tape adhesive ran circumferentially on the joint

except for the lines at 178 degrees. On the clevis, Teflon tape adhesive

was found on the top of the J-leg (near the inner clevis leg metal) at 138,

150, 152, 178, 180, and from 162 to 165, 167 to 170, 230 to 234, and 252 to

254 degrees. As on the tang, all Teflon tape adhesive ran circumferentially on the joint except for the lines at 178 degrees.

5.2.2 Center Field Joint

The QN-8 center field joint was disassembled on 7 February 1989 (see pages

A-11 through A-14, Appendix A). The overall condition of the joint was

excellent. No hot gas or soot vas observed past the J-leg. There vas no

evidence of damage to the 0-rings while in the grooves. Inspection of the

'rYR-17591, Vol IV

73
O-rings by the O-ring Inspection Team revealed a similar 13.5 inch circumferential scratch as on the forward fleld joint capture feature O-ring.

This scratch is also located on the capture feature O-ring and ranges from

4.7 to 15.7 degrees (see Page A-14, Appendix A). A series of radial

scratches measuring 0.150 inch long was found on the capture feature 0-ring

at 345.8 degrees. The depth of these scratches is approxlmately 0.001

inch. No damage was found by the O-ring Inspection Team on the primary or

secondary 0-rings.

There was no corrosion found on either the tang or clevis with the exception of what appeared to be a very light thin line of corrosion which

crossed the landing between the O-ring grooves at 134 degrees. The grease

on the O-rings was intermittently heavier than prescribed in STW7-2999.

However, the grease was heavier on the aft side of the primary and secondary O-rings. It was determined this grease was wiped from the inner tang

(pin hole region) during disassembly. The grease condition was per STW7-

2999 on the seallng and nonsealing surfaces. The V2 filler was nominal.

There was no joint metal damage observed. A metal pin hole sliver was found

in the 268 degree pin hole. This is a common occurrence.

5.2.3 Aft Field Joint

The 0M-8 aft field joint was disassembled on 4 February 1989 (see pages

A-15 through A-17, Appendix A). The condition of the joint was excellent.

No hot gas or soot was observed past the J-leg Insulation. There was no

TWR-17591, Vol IV

74
evidence of damage to the O-rlngs while in the grooves or foond by the

O-ring Inspection Team. There was no corrosion found on either the tang or

clevis. The pin hole at 136 degrees had a small metal pin hole sliver in

it, which fell on the

disassembly operations.

during the inspection.

aft face of the secondary 0-ring during joint

Otherwise, no apparent metal damage was found

The grease on the 0-rings and sealing areas was as prescribed in STW7-2999,

except not enough grease covered the clevis root from 232 to 282 degrees.

There was a small amount of foreign material which had fallen onto the

joint during or after disassembly.

5.3 Nozzle-to-Case Joint

The 0M-8 nozzle-to-case joint (see Figure 3) was disassembled on 13 February 1989 (see pages A-18 through A-22, Appendix A). The overall condition

of the joint was excellent. No hot gas or soot was observed past the

polysulflde. There was no corrosion or metal damage found.

No O-ring damage was found during the in-groove inspection. A heavy rub

mark was found on the primary O-ring at 354.6 degrees. This occurred on

disassembly because the radlal bolt hole plug at 354.6 degrees was in the

bottom of the bolt hole. A heavy impact mark was found on the top of the

plug. The plug appeared to be in this condition before disassembly. Inspection of the O-rings by the 0-ring Inspection Team revealed one scratch

Tk'R-17591, Vol IV

75
on the primary O-ring and one scratch, one cut, and one nick on the vqper

O-ring (see pages A-20 and A-21, Appendix A). This damage was caused by

disassembly; these are located within close proximity to radial bolt hole

locations. Also, the charred surface of the nozzle was not covered with

plastic prior to 0-ring removal. No damage was found on the secondary

0-ring by the 0-ring Inspection Team.

Polysulfide migrated past the wiper O-ring through the vent slots around

the entire circumference of the joint. The grease condition was per

STW7-2999 on the O-rings and sealing surfaces.

Inspection of the radial bolt Stat-0-Seals revealed that 35 of 100 had

unacceptable flow line conditions which should have been rejected by

Receiving Inspection. Drawing No. 1U75374 defines the Stat-0-Seals to be

inspected per MIL-STD-413, which allows circumferential flow lines no

greater than 0.180 inch in length. No radial flow marks are allowed.

Presently there is a Stat-0-Seal TRACS class and inspection test each

inspector must pass to qualify to perform an inspection. This class was

not in force at the time of the QM-8 Stat-0-Seal inspection.

5.4 Igniter Joints

Figures 16 and 17 illustrate the Igniter and S & A seals and components,

respectlvely. Post-test inspections were performed on the ignition system

1_TR-17591, Vol IV

76
_'_-__ CORPORATION

SPACE OPERA_ONS

g_ket_. All gaskets (Tnner, O_]ter, and Safe & Arm) performed vith no

signs of heat effect or sooting past the primary seals, and all sealing

surfaces were free of soot.

Figure 16 Ignition System Seals

OF _0_,=,_ Q_jAL_TY

REVISION

DO(::NO. TWR-17591

SEC I _.QE 7 7
!

REVISION

%%

%.\

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N

x _

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_CNO. TWR-17591

SEC

I PAGE

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Oq

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_,RiG!'_',_AL PAGE IS

OF POOR QUALITY

Jvo= IV

78
5.4.1 Safe and Arm Joint

The post-fire evaluation

conducted on 9 February 1989 (see pages A-23 through A-26, Appendix A).

evidence of hot gas or soot was observed past the primary seal. The

gasket and all sealing surfaces were visually inspected. No erosion

of the 0M-8 Safe and Arm-to-Igniter joint was

No

S_A

or

heat effects were observed. Soot was found around the circumference of the

gasket retainer, inward of the primary seal, but not past. Detailed

inspection at also shoved the gasket to be in excellent condition with no

seal damage observed. The sealing surfaces were in good condition with no

evidence of contamination or corrosion. No corrosion or damage was found

on the Barrier-Booster (S_a_) or igniter adapter.

5.4.2 Outer Joint

The ON-8 igniter adapter-to-forward dome joint was disassembled on 1 March

1989 (see pages A-27 through A-29, Appendix A). A blowhole occurred through

the igniter exterior putty at 15 degrees. No seal erosion or heat effects

were observed. No soot was found to or past the primary seal. No soot was

found on either side of the gasket retainer. Heavy soot deposits were found

on the inside edge of the gasket, covering the entire circumference. No

corrosion or joint contamination was found upon inspection of the sealing

surfaces. Detailed inspection of the gasket by the O-ring Inspection Team

T_rR-17591, Vol IV

79
revea]ed mlsslng materla] in the outer void area and a nick on the inner

bottom edge of the primary seal at 337 degrees (see page A-29, Appendix A).

Bovever, the nature of this damage suggested disassembly or handling after

dlsassembly as the cause. Another nick vas found on the crovn of the

secondary seal at 359 degrees (see page A-29, Appendix A). This nick is

vlthin the acceptable limits set forth by STV7-2790 (see Reference 18).

5.4.3 Inner Joint

The QM-8 adapter-to-chamber joint vas disassembled on 5 Nay 1989 (see pages

A-30 through A-32, Appendix A). No soot vas found on either side (top and

bottom) of the gasket retainer. Heavy sooting vas present on the outside

edge of the gasket because of the blovhole in the outer joint putty lay-up

at 15 degrees. No blovhole vas present in the inner putty lay-up, and no

contamination vas found on the sealing surfaces. Typical disassembly

detorque damage vas observed on the star-o-seals. No damage vas observed

on the gasket seals.

5.5 Internal Nozzle

The internal nozzle joints are illustrated in Figures 18 through 22.

TVR-17591, Vol IV

80
__J_ CORPORAT/ONSPACE OPERATIONS

CARBON

_ CLOIH

PItENOLIC

/

FWD EXIT CONE I /

ASSEMBLY

CARBON

CLOTH

PHENOLIC

GLASS

CLOTH

PHENOLIC

STEEL

AFT EXIT CONE

ASSEMBLY

GLASS

CLOTH

PHENOLIC

ALUMINUM

Figure q8 Forward Exit Cone-to-Aft Exit Cone Joint Interface

REVISION

DOC NO.

SEC

i _L IV

TWR-17591 _oE 81
_ CORPORATION

SPACE OPERATIONS

_ FWD ENDRIN_DIAMET__

I _ _r STEEL

_GLASS CLOTi_'|

HOUSING

CARBON CLOTH

PHENOLIC

CARBON CLOTH

PHENOLIC.

BEARING PROTECTOF

OUTER RING

PRECAST

COWL SEGMENT

ii|

I

I

SILICA CLOTH

PHENOLIC

COWL

Figure 19 Nose Inlet Bousing/Flez Bearing Joint

REVISION .o¢.o. TWR-17591 I v°L IV

s=c I PAOE82
__/_ CORPORAT/ON

SPACE OPERATIONS

BY

CARBON CLOTH

PltENOLIC

FACE SEALS

ALUMINUM

GLASS CLOTH

PHENOLIC

\

F

THROAT ASSEMBLY

CARBON CLOTH

PHENOLIC

STEEL

GLASS CLOTH

PHENOLIC

Figure 20 Nose Inlet/Throat Housing Joint

REVISION Doc.o. TWR-17591 I vo' IV

sEc l"aE 83
_ coRpORAT_ON

co_e _o_t
_ CORPORATION

SPACE OPERATIONS

FACE SEAL

I

!

I

I

I

0

FACE SEAL j

"___ FIXED HOUSING (STEEL)

Figure 2;) Flex Bearing/Fixed-Housing Joint

REVISION OOC NO.

SEC

TWR-17591 I voLIV

I_,3_ 85
5.5.1 Aft Exit Cone F_e]d Joint (Joint 1)

The aft exit cone-to-forvard exit cone of 0M-8 vas disassembled and

inspected on 30 January 1989 (see pages A-33 through A-34, Appendix A).

The seals and case inspection included the sealing surfaces, seals, and

joint metal components. No anomalous conditions vere encountered. There vas

no evidence of damage to the O-rings while in the grooves, or found by the

O-ring Inspection Team. There were no voids in the RTV vhich vould alloy

pressure to reach the primary O-ring. The grease application vas per design

vith no areas of corrosion found.

5.5.2 Forvard End Ring-to-Nose Inlet Housing (Joint 2)

1989 (see

experienced pressure, but

Inspection of the O-rings

inch indeterminable depth

The nose-to-forvard end ring vas disassembled and inspected on 15 February

pages A-35 through A-37, Appendix A). The primary O-ring

no apparent damage to the O-ring vas found.

by the O-ring Inspection Team revealed a 2.67

circumferential scratch on the primary O-ring

similar to the scratches found on the forvard and center field joint

capture feature O-rings (see page A-37, Appendix A). No damage vas found on

the secondary O-ring by the Inspection Team.

Inspection of the joint revealed one very small pressure path through the

RTV of the joint interface. The pressure path started at 355 degrees and

flowed circumferentially to 350 degrees before penetrating into the metal

T_rR-17591, Vol IV

86
interface of the joint. The RTV backfill of this joint was much better than

the current application of RTV to this joint ("buttering applicationn). No

soot or evidence of blow by was present past the primary O-ring. The

sealing surfaces suffered no assembly or disassembly damage.

5.5.3 Nose Inlet Housing-to-Throat Support Housing (Joint 3)

The nose-to-throat was disassembled and inspected on 15 February 1989 (see

pages A-38 through A-41, Appendix A). There was no joint pressurization,

and the 0-rings did not have any apparent damage at the time of disassembly. Inspection of the 0-rings by the 0-rlng Inspection Team revealed two

scratches on the primary 0-ring and one on the secondary O-ring (see pages

A-40 and A-41, Appendix A). This joint showed no signs of pressure past the

RTV; i.e., heat-effected grease, soot_ or an RTV void. The sealing surfaces

showed no assembly or disassembly dmmage.

5.5.4 Forvard Exit Cone-to-Throat Support Housing (Joint 4)

The forward exit cone-to-throat

14 February 1989 (see pages A-42

O-ring experienced pressure, but

support housing was disassembled on

through A-44, Appendix A). The primary

no damage to the O-ring was found. No

damage to the primary or secondary O-rings was found during the in grooves

inspection or by the O-ring Inspection Team. Inspection of the joint

revealed one pressure path through the RTV backfill at 205 degrees. The

sealing surfaces suffered no assembly or disassembly damage.

'rk'R-17591, Vol IV

87
5.5.5 Fixed Housing-to-Aft End Ring (Joint 5)

The aft end ring-to-fixed housing joint vas disassembled on 14 February

1989 (see pages A-45 through A-47, Appendix A). There vas no joint

pressurization_ and the in-groove 0-ring inspection revealed no damage.

Inspection of the O-rings by the 0-ring Inspection Team also revealed no

damage. This

heat-effected

damage.

joint shoved no signs of pressure past the RTV; i.e.,

grease_ sootp or an RTV void. There vas no sealing surface

5.6 Factory Joints

Post test inspection findings of the QM-8 factory joint O-rings and joint

metal components are discussed in this section.

5.6.1 Disassembly of OM-8 Forvard Dome and Forvard Segment Factory Joints

The forward segment of OH-8 vas disassembled on 24 April 1989 (see pages

A-48 through A-53, Appendix A).

5.6.1.1Forvard Dome-to-Cylinder Factory Joint

No corrosion vas observed on the outer clevis leg or in the joint areas

including the tang. No scratches vere observed in any joint area.

TYR-17591, Vol IV

88
Very excessive insulation and Chemlok were on the land forward of the

primary O-ring groove intermittently throughout the circumference of the

joint. The leak check port plug was removed in the previous log, therefore

the break-away torque was not observed or a preliminary inspection

completed. Inspection of the port threads revealed they were in nominal

condition but had no grease on them. Preliminary inspection of the O-rings

showed nominal condition. The O-ring Inspection Team reported no O-ring

damage.

5.6.1.2 Forward Segment Cylinder-to-Cylinder Factory Joint

No corrosion was observed on the outer clevis leg or in the joint areas

including the tang. No scratches were observed in any joint area.

Very excessive insulation and Chemlok were on the land forward of the

primary O-ring groove Intermittently throughout the circumference of the

joint. The leak check port plug break-away torque was not recorded. The

port plug head was partially covered with residual weather seal. Also,

scratches were present on the port plug head, which is typical due to the

weather seal removal. The port plug and port threads were in nominal

condition with a light coat of grease on them. Preliminary inspection of

the O-rings showed nominal condition. The O-ring Inspection Team reported

no O-ring damage.

TgR-17591, Vol IV

89
5.6.2 Disassembly of QM-8 Center Forward Factory Joint

The 0H-8 center forvard factory joint vas disassembled on 9 May 1989 (see

pages A-54 through A-56, Appendix A). No corrosion vas observed on the

outer clevis leg or in the joint areas including the tang. No scratches

vere observed in any joint area.

Insulation and Chemlok vere on the land forward of the primary O-ring

groove intermittently throughout the circumference of the joint.

The leak check port plug break avay torque vas not recorded because the

port plug had been removed in the previous log. Inspection of the port

hole vas difficult because of the amount of grease in the port, but it

shoved a nominal condition. The excessive amount of grease yam present in

the port as a normal preservative operation during the disassembly effort.

Preliminary inspection of the O-rings shoved nominal condition. The

O-ring Inspection Team reported no O-ring damage.

5.6.3 Disassembly of 0N-8 Center Aft Factory Joint

The ON-8 center aft factory joint vas disassembled on 14 April 1989 (see

pages A-57 through A-59, Appendix A). Inspection of the outer clevis leg

shoved no corrosion. Light corrosion vas observed downstream of the

secondary O-ring groove through the clevis root and up the inside surface

T'_-17591, Vol IV

90
.f the ollter clevis ]eg in the entire circumference of the joint. Light

corrosion was observed on the tang dovnstream of the sealing surface on the

entire circumference of the joint. No scratches were observed in any joint

areas.

A particle of foreign material was observed between the forvard wall of the

primary O-ring groove and the primary O-ring at seven degrees. A laboratory analysis showed the particle to be aluminum oxide material with residual combustion by-products. It was determined that this particle fell

into the joint during disassembly and remains an observation. A presentation was made to the EHT and RPRB for concurrence with this conclusion.

Insulation and Chemlok were on the land forvard of the primary O-ring

groove intermittently throughout the circumference of the joint. The leak

check port plug was removed in the previous log so the break-away torque

was not observed or an inspection done. The port threads were in nominal

condition but had no grease on them. Preliminary inspection of the O-rings

showed a nominal condition. The O-ring Inspection Team also revealed no

findings.

5.6.4 Disassembly of OH-8 Aft Segment Factory Joints

The OH-8 aft segment was disassembled on 2 and 3 Hatch 1989 (see pages A-60

through A-68, Appendix A).

¢VR-17591, Vol IV

91
5.6./,.1 Aft Segment Dome-to-Stiffener Joint

Intermittent spots of light to medium corrosion vere observed on the

outside of the outer clevis leg. No corrosion vas observed in the joint.

Scratches vere observed on the land betveen the O-ring grooves at 8, 22,

24, 26, 28, 30, 34, 36, 38, 40, 44, 304, 306, 308 to 316 and 346 degrees.

Scratches and pits vere observed on the inside of the tang dovnstream of

the seal surface to the chamfer at 302 to 346 degrees. Insulation and

Chemlok vere on the land forvard of the primary O-ring groove and in

contact vith the forvard edge of the primary O-ring intermittently

throughout the circumference of the joint.

The initial inspection of the port hole vas difficult because of the amount

of grease in the port but it shoved a nominal condition. The excessive

amount of grease vas present because the port plug had been removed in the

previous log. Thus the grease vas put in the port as a normal preservative

operation during the disassembly effort.

Preliminary inspection of the O-rings shoved a nominal condition. The A-2

O-ring Inspection Team also revealed no findings.

5.6.4.2 Stiffener-to-Stiffener Factor 7 Joint

Intermittent spots of light to medium corrosion vere observed on the

outside of the outer clevis leg betveen 271 to 137 degrees. Light

TW-R-17591, Vol IV

92
corrosion was observed downstream of the secondary groove at ]7 to 2], 32,

36 to 45, 84, and 147 to 175 degrees. Scratches were observed on the land

between the O-ring grooves at 358 degrees.

Insulation and Chemlok were on the land forward of the primary O-ring

groove and in contact with the forward edge of the primary O-ring

intermittently throughout the circumference of the joint.

The initial inspection of the port hole was difficult because of the amount

of grease in the port but it showed a nominal condition. The excessive

amount of grease was present because the port plug had been removed in the

previous log. Thus, ffD-2 grease was put in the port as a normal

preservative operation during the disassembly effort.

Preliminary inspection of the O-rings showed a nominal condition.

O-ring Inspection Team also revealed no O-ring damage.

The

5.6.4.3 ET-to-Stiffener Factory Joint

Intermittent spots of light to medium corrosion were observed on the

outside of the outer clevis leg. Light corrosion was observed in the

clevis bottom at 101 to 107 degrees. Scratches were observed on the land

between the O-ring groove at 18, 24, 38, and 316 degrees. Scratches were

also observed on the land forward of the primary O-ring groove at 38 and

316 degrees.

T'#R-17591, Vol IV

93
Insulation and Chemlok were on the land forward of the prJmar_ O-ring

groove and in contact with the forward edge of the primary O-ring

intermittently throughout the circumference of the joint.

The initial inspection of the port hole was difficult because of the amount

of grease in the port, but it showed a nominal condition. The excessive

amount of grease was present because the port plug had been removed in the

previous log. Thus HD-2 grease was put in the port as a normal

preservative operation during the disassembly effort.

Preliminary inspection of the O-rings showed a nominal condition.

O-ring Inspection Team also revealed no Oaring damage.

The

5.7 Port Plug Evaluation

Only recently, a detailed evaluatlon of all port plugs and port plug seals

have been evaluated by the O-ring Inspection Team (see pages A-69 through

A-98, Appendix A). On past full-scale static tests (PV-1, QH-7, QH-6) the

emphasis was focused mainly on the custom and adjustable plugs which were

in the design and qualification phases. Inspection forms and engineering

evaluation limits have since been added to the PEEP and PEEL documents,

respectively (see References 17 and 18). Since there are so many port plugs

in the RSRR, no attempt is made to discuss the post-test inspection

findings of each plug. However, it can be stated that no gross unexpected

conditions were encountered.

Tb'R-17591, Vol IV

94
Copies of the completed PFORs (Post Fire Observation Records) are presented

in Appendix A.

It should be noted that there were no port plugs installed in the 45 degree

leak check ports of the field joints, and the 262.5 degree leak cheek port

of the fixed h.using-to-aft end ring (Nozzle Joint 5). There were pressure

transducers installed in these ports. Also the leak check port plugs from

the igniter inner and outer joints were not received.

5.8 Seals Component Program Team Recommendations

The Seals Component Program Team has reviewed all observations presented in

this document and have determined that the following observations are

potential anomalies, classified as critical, major, minor, or observation,

as defined under Table 34 criteria.

5.8.1 Remains Observation

i. The aluminum oxide, combustion by-product particle observed

between the forward wall of the primary O-ring groove and the

primary O-ring at seven degrees on the center aft factory joint.

It was determined that this particle fell into the joint during

disassembly and remains an observation.

•r_-17591, Vol IV

95
5.8.2 Hinor Anolalies

. The white colored material, which ran circumferentially found on

the aft edge of the forvard field joint capture feature O-ring at

169 degrees. Nore thin lines of the vhite colored material vere

found intermittently On the aft edge from 164 to 167 degrees.

Also small thin lines of the white colored material vere found on

the capture feature metal to J-leg interface (aft of the capture

feature groove on the tang J-leg) at intermittent degree

locations. Lab analysis indicated the material vas Teflon Tape

adhesive.

2. Thirty five of I00 nozzle-to-case Stat-O-Seals had unacceptable

flov line conditions.

5.8.3 Hajor Anomalies

There vere no major anomalies.

5.8.4 Critical Anomalies

There vere no critical anomalies.

5.9 RPRB Position

The RPRB has accepted as presented.

TNR-17591, Vol IV

96
Table 34

Criteria for Classifying nPotential Anomalies n

Anomaly

Remains

0bserva t i on Hi nor Haj o r Cr i t i ca1

Requires no

Specific

Action

Requires corrective action,

but has no

impact on:

- Hotor Performance

- Program Schedule

Does not reduce

usability of part

for its intended

function

Could cause damage

preventing reuse

of hardware in

combination with

other anomaly

Significant departure from the historical database

Could cause failure

in combination vl

other anomaly

Could cause damage

preventing reuse

of hardware

Program acceptance

of cause, corrective action, and

risk assessment required before subsequent static test

or flight

Violates CEI Spec.

requirements

Could cause failure

and possible loss

of missionllife

Handatory resolution

before subsequent

static test/flight

Note: These criteria to be applied to the specific observed Wpotential

anomaly" as it relates to the observed article and as it relates to

subsequent articles.

Tl/R-17591, Vol IV

97
6.0 REFERENCES

APPLICABLE DOCUI_NTS

I. Hugh P.J., CTP-0060 Revision D, "Space Shuttle Qualification Motor |8

(QM-8) Static Fire Test Plan', Morton Thiokol, Inc., 19 January 1989.

2. Carecht D. ft., TI/R-17591Vol. 1, "Space Shuttle Qualification Motor 8

(QM-8) Final Test Report', Morton Thiokol, Inc., March 1989.

3. TI/R-19506 Has Not Been Released At This Time.

4. Svopes, C., TI/R-16459, Rev. E., "CPV1-3600 Specification Deviations',

Morton Thiokol, Inc., 7 October 1988.

. Furgeson J. V., STI/7-2999, "Calcium Grease, Field Joint, Factory Joint,

Nozzle Joints Assembly, Application o£, and Component Installation,

Space Shuttle SIOl', Morton Thiokol, Inc., March 1988.

. Ferney D. G., ETP-0228, Revision A, "Horizontal Assembly Requirements

for RSILq Segments vith 7U75170 Field Joint Assembly Fixture', Morton

Thiokol, Inc., January 1988.

7. Nelsen L. V., T_/R-18135, Revision A, "DN-9 RSRM Structural Test

Report', Morton Thiokol, Inc., 30 June 1988.

. Tarbet G. F., STW7-3499, "Installation Procedure, Leak Check and Vent

Port Plug, Space Shuttle Redesigned Solid Rocket Motor", Horton

Thiokol, Inc., 25 July 1988.

. Tarbet G. F., STI/7-3661, Revision B, "Leak Testing, Field Joint and

Nozzle-to-Case Vent Port Plugs, Space Shuttle, Redesigned Solid Rocket

Motor', Morton Thiokol, Inc., 7 September 1988.

10. TIIR-18838, Installing' "The Adjustable Vent Port Plug', Morton

Thiokol, Inc., (A Presentation, Publications No. 89268)

11. Dean H. C., Ash R., I_R-18811, Revision A, "O-ring Squeeze Calculations

and Temperature Requirements QH-8", Morton Thiokol_ Inc., 13 December

1988.

12. Hutchison B. J., TI/R-18990, "Predicted Ballistic Performance

Characteristics for QM-8", Morton Thiokol, Inc., 15 December 1988.

TVR-17591, Vol IV

98
13. Structural Design Section, TVR-17118, Supplement B, Revision A, "RSRH

Case Structural Analysis Summary', Norton Thiokol Inc., April 1988.

14. St. Aubin, B. K., TVR-17991, "RSRH Seal Design Summary Report', Morton

Thiokol, Inc., 1 September 1988.

15. Structural Design Section, T_/R-17118, Supplement D, Revision A, "RSRN

Case Structural Analysis Summary', Morton Thiokol Inc., April 1988.

16. Performance and Advanced Design, et. al., Tb-R-16473, Revision B, Volume

4, "0ualification and Production Verification Motor Postfire

Engineering Evaluation Plan', Morton Thiokol, Inc., 13 January 1989

17. Performance and Advanced Design, et. al., Tb'R-17198, Revision A, Volume

4, "Postfire Engineering Evaluation Limits', Morton Thiokol, Inc., 18

April 1988

18. V. J. Straley, STV7-2790, Revision B, "Ignition System Gaskets,

Reusable Acceptance Criteria For', Morton Thiokol, Inc., 20 November

1987.

APPLICABLE DRA_FINGS

o

o

Drawing 8U76500, "Leak Test System, Safe and Arm Device,

Installation', Morton Thiokol, Inc., 16 May 1988.

Drawing 8U75902, "Leak Check System, Installation', Morton Thiokol,

Inc., 11 December 1987.

3. Drawing 7U76357, "Vent Port Plug Leak Test Fixture', Morton Thiokol,

Inc., 15 March 1988.

4. Drawing 2U65686, "Transducer Leak Test Fixture', Morton Thiokol, Inc.,

17 January 1989.

5. Drawing 2U129718, "Auxiliary Leak Test Equipment', Morton Thiokol,

Inc., 18 May 1988.

T_/R-17591, Vol IV

99
APPENDIX A

INSPECTION FORMS

TI/R-17591, Vol. IV

A-i
=

l_lorton Thiokol Inc.

Space Operations

Joint External Walk Around - Evaluation Checkoff Worksheet

MotorNo.:,__ _ IDa"::_ =_t Iq8 9

Inspector(s): _)/_JE _OI._O$ELL . 3-EF F CoI_P_._

Evidence of Combustion Product Leakage (SOOT)?

A. Forward Dome Factory Joint (Sta. 531.5,

FDS, CLEVIS)

B. Forward Segment Factory Joint (Sta. 691.5,

FFS, CLEVIS)

C. Forward Field Joint (Sta. 851.5, FWD, CLEVIS)

D. Forward Center Segment Factory Joint (Sta.

1011.5, FCS, CLEVIS)

E. Center Field Joint (Sta. 1171.5, CTR, CLEVIS)

F. Aft Center Segment Factory Joint (Sta. 1331.5,

ACS, CLEVIS)

G. Aft Field Joint (Sta. 1491.5, AFT, CLEVIS)

H. Aft Segment Factory Joint (Sta. 1577.5, FSS,

CLEVIS)

I. Aft Segment Factory Joint (Sta. 1697.5, ASS,

CLEVIS)

J. Aft Dome Factory Joint (Sta. 1817.6, ADS,

CLEVIS)

K. Nozzle to Case Joint (Sta. 1875.2, NOZ, AFT)

I Time: / L__ C)

Comment

Number

no

no

J

yes no

yea L,/ no

yes

yes

no

7 no

yes _ no

yes --'7 no

yes W'" no

yes no

_. yes L_ no

If yes, record the indicated data below:

REV.

Dec

NO. TWR-17591 IVOL IV

sEc [P^as A-1
Morton Thiokol Inc.

Space Operations

External Igniter Interfaces - Evaluation Checkoff Worksheet

Motor No.: (_)f___ ! Date: _'/_t_ o_l |c_

Inspector(s): DAVE P...OL,O_.%ELL... _'E_I:: C_L.)t"4,t'_._

Evidence of Combustion Product Leakage (SOOT)?

A. Adapter I Forward Dome Interface (IGN, AFT)

B. Adapter To Forward Dome Bolts (IGN, FWD)

C. Adapter I Chamber Interface (IGI, AFT)

D. Adapter To Chamber Bolts (IGI, FWD)

E. S&A I Adapter Interface (S&A, AFT)

F. S&A To Adapter Bolts (S&A, FWD)

|

I Time: [L_O0

Comment

Number

yes ._ no

yes no

yea _ no

yes _ no

yes no

yes _" no

If yes, record the Indicated data below:

REV. ooo No. TWR-17591 , [VOL IV

eEc [ F,^Qe A-2
MORTON THIOKOL INC.

External Walk Around - Evaluation Checkoff Worksheet

Inspector(s): "_/_V_ _0oj.)SFL L I.. , _J_ F"_" _ L._I_ r',

MotorNo.:

Hotspots (Heat Affected Paint)?

1. Aft Segment

2. Aft Center Segment

3. Forward Center Segment

4. Forward Segment

II. Loose or Cracked ETA bolts?

III. Loose or Cracked Stiffener Ring Bolts?

IV. Additional Observations?

!Date: ,,._/ J'7'_,"/ F"_

yes _ no

yes _ no

yes _ no

yes _ no

yes _ no

yes /_ no

yes _ no

If yes, record the indicated data below:

Axial Degree

Segment Location Location

(1 - 4) Condition (In.) (Deg.)

Axial Circumferential

Length (In.) Width (In.)

If Applicable If Applicable

Degree Arc

If Applicable

Notes I Comments

Note: Clarify any observations on an OCF if necessary

Rev. DOC

NO. TWR-17591 VOL IV

SEC Page_ A-3
Morton Thiokol, Inc.

Space Operations

7,

<

{LI

6

"G

!

o

.7.

c

_< _--

,,- _ C n

j --_.

• _ _

c

-_ _ <_--

_ _ - - .__ o

_ _ _ _ _ -

_ - _ _:_ :_ > = <

o

_._T "_

_, ,

ed

uJ

td

L

',,9

.j

._ {.Q

_c2

.3

kn

_ tk

!o

Rev. DOC

NO. TWR-17591 VOL IV

SEC Page A-4
Morton Thiokol, Inc.

Space Operations

!

r3-

°,

v o

_- 0

0 :-

4,-

U w.

0

n

o

E

E

o

C_

m

S

Z

Rev. DOC

NO. TWR-17591 VOL IV

SEC Page A-5
Morton Thlokol Inc.

Space Operations

Case Field Joint Condition - Evaluation Checkoff Worksheet

Motor No.: q/_-_ [Date: _ l:"_'& _:_"

Joint: [[[Forward (FWD) I--)Center (CTR) [] Aft (AFT)

Inspector(s): -_(_V_ /_l/,/5 _LJ--- , .TErF ('.L,_/_ _

Case Field Joint Observations:

A. Soot In Proximity to I Pelt O-rlng Groove (SPINS, SICOR Yes I"'_ No

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Volume 2 Filler Damage (V2FD)?

E. Leak Check Port Obstructed (LPOBS)?

F. Vent Port Obstructed (VPOBS)?

G. Foreign material In the sealing area during motor operation

(FMIJ) ?

H. Rust on sealing surfaces (SSCOR)?

I. Rust on metal parts (PITCO)?

J. Heat affected metal (HTAFF)?

K. Damaged metal aealing surface (SSMET)?

Yes _ No

Yes _-_ho

Yes _C,--"_o

Yea L---"_O

_j_e. v'_o

es No

Yea L"i:No

Yes _ No

Yes

Comment

Number

m

If any of the above conditions exist, record applicable dimensions below. Describe the observed contitian using a comment number, • "T" if the condition Is observed on the tang or a "C" if the condi-

,ion is observed on the clevis end any other Information needed to describe the observation:

/. ,4 /o._ ._//,.., /,.,__c _/./_ :_-/_,.:.z ,_,_,/_,-,x/_.=s-_,-._Jo,',

/_:c:'(_._/:',I /,',_:_ of tul_;le. _ol_:ed /_ { • e ._c..,,_

:<..so,pp:ox,'.',-,c<_-iT,,o.¢_.o,,.,<4 Io_,_.

..)-:o, ,.'_ _ _r _ " /

)4o'r-E "_ _,- Vou,e //v/@,.z_/Ir-:o,L/(5£E ATF_CH_D F/Gu,_II')

Small thin lines.of the white cotored matertat were found on the capture

feature metal to J-leg interface (aft of the capture feature groove on the

tang J-leg) at 153, 178, 180, 227, 228, and from 230 to 233 degrees. All

of the thin lines of the white colored material ran ctrcumferenttally on

the Jolnt except for the lines of white colored material at 178 degrees.

On the clevis, the white colored material was found on the top of the J-leg

(near the inner clevis leg metal) at 138, 150, 152, 178, 180, and from 162

to 165, 167 to-170, 230 to 234, and 252 to 254 degrees. As on the tang,

all of the thin lines of the white colored material ran ctrcumferenttally

on the joint except for the lines of white colored material at 178 degrees.

c_:/_,'c _<-__._ o-,,,,',,_7

5",..,5/:_'_-/-:o/m/_o_.',.-e

REV. --

ooc No. TWR-17591 Ivo, IV

s_c [ P_(_ A-6
MORTON THIOI(DL INC

Space Operations

Z

C_

"-9

C2_

__J

I,I

L_L_

C2_

<

C_

LL

C_

I

j

/

_J

"9

\

REVISION OOCNO. TWR-17591 J _L IV

sic J _QE A-7
MORTON THIOKOL INC.

Space Operations

Field and Factory Joint - Evaluation Checkoff Worksheet

Inspector(s): _/_UE /?O_J.SG C(- I .,3-C-_'-F" C(J_E',_ _J

Motor No.: _/4//-

Joint:

I Date: I?

[] Forward Dome Factory Joint (531.5)

,_] Forward Field Joint (851.5)

[] Center Field Joint (1171.5)

[] Aft Field Joint (1491.5)

[] Aft Segment Factory Joint (1697.5)

[] Forwqrd Segment Factory Joint (691.5)

[] Forward Center Segment Factory Joint (1011.5)

[] Aft Center Segment Factory Joint (1331.5)

[] Aft Segment Factory Joint (1577.5)

[] Aft Dome Factory Joint (1817.6)

I. Rust on Metal Parts (Corrosion)?

II. Metal Damage?

J no -- yes --

yes

III.

IV.

Clarify below or on an-OCF, if necessary

Metal Slivers from pin holes?

Other?

Describe:

/

_.L--//_yII __ no

yes LLLLLLLLL_ ne

L

=

If yes. record the data below:

Axial Degree

Location (In.) Location

li Applicable (Dog.)

Degree Arc Length Width

If Applicable If Applicable If Applicable

i

Notes I Comments: Pinhole slivers were found--

in the bottom of the lnner clevis leg pinholes in the following holesl

52, 54, 58, 60, 62, 232, 282, 286, 288, 290, and 292. The slivers are case,

material (D6AC) and are typical. ( "_ C=_/C,P i:l :I,;

REVISION

No.ODDTWR-1i591 ......Iv_' IV

i see _ I par-,

A-8
MORTON THIOKOL INC.

Space Operations

De:ailed Case Field Joint O-r,'tg (Post-Removal) - Evaluation Checkoff Worksheet (Wasatch A-2 Bldl_)

Inspector(s): _(_/._K'_ A<_,, ,,._._'H Ecj,p,;,. "__ (_/,.1-_',,¢ ,,/_,/_.so,_v

Motor No.: ("_ 1_i _- ? "

Joint: I._ Forward [] Center

PRIMARY O-RING P.art No.'

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

[] Aft

I;) 7=; J50 -,.q5

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.:

CSVAP

Distance

(Length)

SECONDARY O-RING Part No.: | L.)'7_J J_)-,=_

i

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial NO.: (_10_)_2. t_-]'

yes .o

Yea "_ NO

Yea No

Yes No

CSVAP

Distance

(Length)

CAPTURE FEATURE O-RING Part No.: t L_ 15L)- II

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

b _._° _EP_uz.u_._ - ,c._l

Serial No.: _'_ z_/-_

Yea V ) No _-

Yes _ No

Yes _ No

Yes _ No

CSVAP

Distance

(Length)

Notes I Comments:

REVtSION_

o

DOC

NO.

8EC

TWR-17591 Iv_ IV

IF,.=_A-9
Morton Thiokol Inc.

Space Operations

Date: -IO

Motor NO.: C_I')_ J'_

[] Left (A) [] Right (B) Joint: f::UJC)

O-ring Location: [] Primary [] Secondary

Part Number: }|.17.._ i:_(_)- ! I

Serial Number: _L_('Y'}_ .__ L_

Depth:

Description: _-" _ It_LJ1

O-RING OBSERVATION CLARIFICATION FO_. j.

Inspectorls): _ E_,_ K=LX-X_-.J J_c.L.

• { - _ /

I

C---IE t.D "n_;Ji_ T

[_Capture Feature [] Wiper

Sketch observation below or attach worksheets end list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation.

I, I_.,c' /_'_<" "

L-- 1_,5

REV.

DOC

NO. TWR-17591

SEC

I PAGE

IVOL IV

A-IO
Morton Thiokol Inc. _

Space Operations

Case Field Joint Condition - Evaluation Checkoff Worksheet

MotorNo: gin- -- I Date: ---7-

!Joint: [] Forward (FWD) [_Cemer (CTR) [] Aft (AFT)

Inspector(s): l.-.olp3P._|l I_Isc_1_

Case Fleid Joint Observations:

A, Soot In Proximity to I Past O-ring Groove (SPINS, SICOR

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B, Sooted Grease (HAGRE)?

C, Discolored Grease (DIGRE)?

D, Volume 2 Filler Damage (V2FD)?

E. Leak Check Port Obstructed (LPOBS)?

F. Vent Port Obstructed (VPOBS)?

G, Foreign material In the sealing area during motor operation

(FMIJ)?

H, Rust on sealing surfaces (SSCOR)?

I. Rust on metal parts (PITCO)?

J. Heat affected metal (HTAFF)?

K, Damaged metal sealing surface (SSMET)?

C¢>mment

Z Number Yes No __

Yes J No

Yes _ No

Yes 11/. No __

Yes _ No

Yes No

Yes L/" No --

Yes _// No

Yes No

Yes _ No

Yes'V/No

If any of the above conditions exist, record applicable dimensions below. Describe the observed contitlon using a comment number, a "T" if the condition is observed on the tang or a "C" if the cond|-

don is observed on the clevis and any other information needed to describe the observation:

1. W-,-'V t,_,-k- ÷_._,j t,,,4_ o_c co_ros,_) o_ +_,_.

/ _j

I

I

KEY. ooo NO. TWR-17591 !v_

-- SEC [ PAGE

A-11

IV
MORTON THIOKOL INC.

Space Operations

Field and Factory Joint - Evaluation Checkoff Worklheet

Inspect°r(s):L-o_e_l I (_)e.l s ___3

Motor No.: _,_ - _

Joint:

JDate:;R-7-

[] Forward Dome Factof'y Joint (531.5)

[] Forward Field Joint (851.5)

_ enter Field Joint (1171.5)

[] Aft Field Joint (1491.5)

[] Aft Segment Factory Joint (1897.5)

i

I. Rust on Metal Parts (Corrosion)?

II. Metal Damage?

Clarify below or on an OCF, ff necessary;

III. Metal Slivers from pin holes?

IV. Other?

[] Forwqrd Segment Factory Joint (691.5)

[] Forward Center Segment Factory Joint (1011.5)

[] Aft Center Segment Factory Joint (1331.5)

[] Aft Segment Factory Joint (1577.8)

[] Aft Dome Factory Joint (1817.6)

ii

_/'/ yes no

yes _ no

yoa

Describe:

Iw

3.

If yes, record the data below:

Axial Degree

Location (In.) Location Degree Arc

If Applicable (Deg.) If Applicable

I17_.5 o_Z °

Length

If Applicable

A.cr_.s Ct_u i-_

"_ 0.(o0"

!

!

Width

If Applicable

Notes I Comments:

S_._ T_._l__ B-Ill o_- T_- _(oH73 ,

illus'kr_%_o_- (f_op. UScA_

Vol. 51' For

l

Corros ; o _J.i'!-;;= _,

I ! I

"':" REVISION

,f_"

,°

DO_

NO.

! 8EC

>__ ii_•

TWR-17591 v_.lIV

. . ! man=

A-12
MORTON THIOKOL INC. _ .5"_"-

,.,,.,. _ vl,,v,t,.,_,_, c

Joint: 1"7 Forward [_] Center [] Aft

PRIMARY O-RING Part No.: I L_-'/_._I_ .- Z._%

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: C_C)C_> _,___.,_-

Yes v / No

Yes _._ No

Yea _ No

Yea L_ No

CSVAP

Distance

(Length)

SECONDARY O-RING Part No.: J_.)q _ i_O-r_.=_

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial NO.: (_(_t'_ ___ _

__Yes __+ 'No

__ Yes _ No

__ Yes _ No

__ Yes No

CSVAP

Distance

(Length)

CAPTURE FEATURE O-RING Part No.: I _Y'7__} _t)- I

A. Erosion?

B. Heat Affect?

C. AssomblylDisaasembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

p + .,+e,l

Serial No.: r"V"_'_+J_+ f')_ 1

Yes No

Yea No

Yea _._ No

Yes __ No

CSVAP

Distance

(Length)

13,5 _*

,1.6_,

Notes I Comments.'

REVISION__

DOC

No. TWR-17591

8EC I PAGE

.+

i

I v_ IV

A-13
Morton Thiokol Inc

Space Operations

O-fliNG C BSERVATION CLARIFICATIO[: FORM

"- _

MotorDale:No.: ._-?-_>___ Inspector(s): "_-_';/_(L_: _lcJ-Lr_,,d " ; _%_"

J-!Left (A) r-]R,ght (,R) Joint: E_TP-- FIFLD -_t_T

O-ring Location: [] Primary [] Secondary [_Capture Feature [] Wiper

Part Number: ! t )7.'=; I_(_-( I

Serial Number: (_CC) (_L"35

Depth:

Description: -_P_P _OLL_

Sketch observation below or attach worksheets end list below. Indicate orientation and dimensions,

Show as much detail as necessary to explain the observation.

t

o

H.7 15,7°

I

(

/ : b=

/

:_70_ ,-_#-5,_ 0 °

b=

,Ooi

i,_a,__e_;^&le.

• 160

,e.OI

,OOI

P,EV. _ ,:,oo NO. TWR-17591 [voL

SEC

[ PAaE A- 14

IV
Morton Thiokol Inc.

Space Operations

Case Field Joint Condition - Evaluation Checkoff Worksheet

Motor No.: _/_/--_ I Date: _ -(,,-_"_

Joint: [] Forward (FWD) [] Center (CTR) DAft (AFT)

Inspector(s): /_. {_1 _(:,"

Case Field Joint Observations:

A. Soot In Proximity to I Past O-ring Groove (SPINS, SICOR

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Volume 2 Filler Damage (V2FD)?

E. Leak Check Port Obstructed (LPOBS)?

F. Vent Port Obstructed (VPOBS)?

G. Foreign materiel In the sealing area during motor operation

(FMIJ)?

H. Rust on sealing surfaces (SSCOR)?

I. Rust on metal parts (PITCO)?

J. Heat affected metal (HTAFF)?

K. Damaged metal sealing surface (SSMET)?

Comment

Number

Yes _ No

Yes Pf No

Yes v" No

Yes t,/ No

Yes If No

Yes v" No

Yes V No

Yes _ No

Yes _ No

Yes "-"-'7" No

Yes _ No

If any of the above conditions exist, record applicable dimensions below. Describe the observed confltlon using a comment number, • "T" if the condition is observed on the tang or a "C" if the condition is observed on the clevis and any other Information needed to describe the observation:

/

REV. _ ooc No. TWR-17591 ivoL IV

sEc I P.OE A- 15
|

MORTON THIOKOL INC.

Space Operations

Field and Factory Joint - Evaluation Checkoff Worksheet

_nspector(,): ;_, #_:E_-

Motor No.: _/4I/- _'

Joint:

[] Forward Dome Factory Joint (531.5)

[] Forward Field Joint (851.5)

[] Center Field Joint (1171.5)

Aft Field Joint (1491.5)

[] Aft Segment Factory Joint (1697.5)

[] Forwqrd Segment Factory Joint (891.5)

[] Forward Center Segment Factory Joint (1011.5)

[] Aft Center Segment Factory Joint (1331,5)

[] Aft Segment Factory Joint (1577.5)

[] Aft Dome Factory Joint (1817.8)

I. Rust on Metal Parts (Corrosion)?

II. Metal Damage?

Clarify below or on an OGF, If necessary

II1. Metal Silvers from pin holes?

IV. Other?

peso,be: _,_a,_,., G,-_,_S. ,;I

U

f

-- yea

J

-- yes

C/cv/S ,_o t'--

no m

: no

t

no

no

If yes, record the data below:

Axial Degree

Location (In.) Location

If Applicable (Deg.)

_ /_,

23?-

Degree Arc Length Width

If Applicable If Applicable If Applicable

Notes I Comments:

c/'S_S_ ,' -- (o(jft

• :1 ̧ : "

I i/

REVISION --

J'. i,_i.

DOC :i. I

NO. TWR-17591 ,vo_ IV

i aEc IPA_' A-16
MORTON THIOKOL INC.

Space Operations

Detailed Case Field Joint O-ring (Post-Removal) - Evaluation Checkoff W(i)rksheet (Wasatch A-2 BId_)

Inspector(s): _t_)O_j. _"_t'v_ , _,'_'_" _d._ , '_ - _'_" /_/_c_--'_d'_J

Joint: [] Forward [] Center ,1_] Aft

PRIMARY O-RING Part No.: IL_7._i_0-7__; Serial No.: _Cx_O_

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

m

m

m

m

CSVAP

Yea _ No

Yes No

Yes _ No

Yes _ No

Distance

(Length)

SECONDARY O-RING Part No.: [U'?._LF---___.-Z__

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

i

Serial No.: C>C>C->_>-'_,/

Yea .._j_ No

Yea _ I_o'

-- Yell _ NO

Yea _ No

m

CSVAP

Distance

(Length)

CAPTURE FEATURE O-RING Part No.: //?7_q"XF-,O-// "

A. Erosion?

B. Heat Affect?

C. Anembly/Disanembly Damage?

D. Other? Describe:

If any of the above conditions exJst, record applicable dimensions below:

Condition Degree Mmdmum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: tO :O/_/__r-2 _..,'

, Yea /t/ No -

Yes /J' No '-"

Yes _ No

m m

. Yes _ No

CSVAP

Distance

(Length)

Notes I Comments:

REVISION

i

OOC NO. TWR-17591 I vm. IV

8EC I PAGE

A-17
51orton Thiokol Inc.

Space Operations

Nozzle-to-Case Joint Condition - Evaluation Checkoff Worksheet

Motor No.: /'_/_- _ '1 Date: /O fE_ _?

Joint: Nozzle-to-Case (NOZ)

Inspector(s): "T"_,,,_/.."E /_Q t4/J_ t L

Case Field Joint Observations:

A. Soot in Proximity to / Past O-ring Groove (SPINS, SICOR

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D, Polysulfide Past Wiper O-ring (PSEX)?

E. Leak Check Port Obstructed (LPOBS)?

F. Vent Port Obstructed (VPOBS)?

G. Foreign mate=ial in the sealing area during motor operation

(FMIJ) ?

H. Rust on sealing surfaces (SSCOR)?

I. Rust on metal parts (PITCO)?

J. Heat affected metal (HTAFF)?

K. Damaged metal sealing surface (SSMET)?

7

Yes _"_NNo

Yes _o

Yes _o

Yes No

Yes t_No

Yes Lf'1_No

Yes

Yes

Yes _No

Yes I.--""_N o

Yes _o

Comment

Number

If any of the above conditions exist, record applicable dimensions below. Describe the observed condition using a comment number, an "F" if the condition is observed on the aft dome or an "A" If the

condition is observed on the fixed housing and any other Information needed to completely describe

the observation and its location:

;. ?oL_'CvLFtbE &OT- PMSF- THe _,,_EF_ O-/2/A/O 7hl/Toc_d THE

VC_I_ 5L.o75 _;@O bEAIZEES ,4Bc_/VD 77-/F_ Jo/NT_. (PSe,_'_

REV, _ coo NO. TWR-17591 lVOL IV

sEc IP_aEA- 18
MORTON THIOKOL INC.

Space Operations

sC.

Detailed Nozzle-to-Case Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wasatch A-2 Bldg)

Ins=)ector(s): Scour- E#E_, , WQc /< Y AS//. Z). _r,_r" /J_'Z_:oJ

MotorNo.: QZ 6" " I Date:

Joint: Nozzle-to-Ca=mPRIMARY O-RING - Pert No.: JU7.5"gOI- /_-

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

C- 1.'_1-7 o.¢_o'_ o. oo_,,

Serial No.: ooc_c_P'j

Yes m

Yes

Z Yea

YII

No

No

m

No

m

V" No

CSVAP

Dlltlnce

(Length)

c3. o _c>

SECONDARY O-RING Pert No.: /U7,.C',rQ/-(.,_

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

• D. Other? Describe:

If ;,ny of the above conditlone exilt, record applicable dlmenlione below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serlil No.: _0(3_0 4'/'

Yes _ No

Yea _ No

Yea t,/- No

Yes _ NO

CSVAP

Dietance

(Length)

WIPER O-RING part No.: IU7,,¢'_i'ol -/_/

A. Erosion?

B. H=mt Affect?

C. AssemblylDlaassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record Ippllcable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

C : _rs._" Q.o¢_ o.c_:)3

C zl4 .v" O. oo_. O .oo(

c,, 3_',_" o. ode- O. o :_

Serial No.: _r'_rJ_<_ y

Yes v / No

_ Yes _ No

Yea No

Yes If No

CSVAP

Dietance

(Length)

O.OVO

o. o9o

0.040

REVISION ooc INO. TWR-17591 _ IV

SEC I mAGE

A-19
Morton Thiokol Inc. ,,_'_-C

Space Operations

Date: ,1.-'/s-o°?

Motor No.: (_ ,4t -,_

[] Left (A) [] Rlgh_..._._(. B) Joint: ,_,/OZZ/.d',/CA,,_'_ r"

O-ring Location: L__"Primery [] Secondary [] Capture Feature

Part Number: Jl_/7"3"_01 "/_,_"

Serial Number: O__

Depth;

Description: _'_'_¢'0_" _ 6rJ.,G_(..,')

O-RING OBSERVATION CLARIFICATION FORM /

Inspector(s): ,-_CoT'r" _=4,1; _O_Y __s'J,/. _,_,_,_V" i_J6_._o,,_l

/

[] Wiper

Sketch observation below or attach worksheeta end list below. Indicate orientation end dimensions.

Show as much detail as necessary to explain the observation.

7_ _" /3:z ;7 ° /_o _

/

J

C / R CUMF'ERE:4JI'/_/-

o_ o. 0o3

REV.

DOC

NO. TWR-17591 IV

$EC ] PAGE
Morton Thiokol Inc. ,,_"

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

Date: .l. - 1Y - _?

Motor No.: _ []Left (A) []RI1 B)

O-ring Location: [] Primary

Part Number: / U Y./',R',_ / ,/_t

Serial Number: /__ _//

Depth:

Description:

Inspector(s): ,3"<,oTt- _'_EX.) ;

Joint: /.JO zz.t._" ] cA. CaC"

[] Secondary ['7 Capture Feature

•oocK.,/ A_s/-/..Z),_K',_,r,,_o,.

/

[_Wlper

(sEE _rL.o(_ )

Sketch observation below or attach worksheets and list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation.

27C_ ,3i6,1"/_" 0"

0 e._q

J,.

RA_IAL C_7""

&J _ 0,001

._7o_" 3._'_.3 _ 0 _'

O.ft_

_t,

L _ O,O,_O

V ;z O.o_.._-

H "_ O. 0o.._

REV.

DOC

NO:

8EC

TWR-17591

I PAGE

I VOL

A-21

IV
Morton Thiokol Inc. .._

Space Operations

Nozzle-To-Case Radial Bolt Stat-O-Seals - Evaluation Checkoff Worksheet

Motor No.: (_/J_-8' I Date: _.-,2,_f-S ?

Joint: Nozzle-To-Case Radial Bolt (NOZ, STAT)

P/N, / UT.d'37¢/-O_L Lot Number EC 4. OOO_

Inspector(s): ..R'C077" #",_--_**M¢ ,Lox/ _,/¥E,f_ G4,4 r AJ_'/$O4J'

Bolt Stat-O-Seel Observations:

A. Eroded Star-O-Seals (SORE)? Yes Y/ No

B. Heat Affected Stet-O-Seals (HASOR)? Yes _ No

C. Cuts, Assembly/Disassembly Damage (SCUT, SDMG, SDIS)? v / Yes No

Comment

Number

i

If any of the above conditions exist' describe below:

J

REV. NO. TWR-17591 1vo,. IV

BEC IPAGE

A-22
Morton Thiokol Inc. .5"_-

Space Operations

Motor No. :

Joint:

Ignition System Sealing Surface Condition - Evaluation Checkoff Worksheet

# IDa,e: l lr¢

J_ S&A to Adapter (S&A) [] Adapter to Case (IGN) [] Adapter to Chamber (IGI)

I spectorIs): j 0. po o_ l/

A. Soot in Proximity to ,' Past O-ring Groove (SPINS, SPPOR,

SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Leak Check Port Obstructed (LPOBS)?

E. Foreign material in the sealing area during motor operation

(FMIJ) ?

F. Rust on sealing surfaces (SSCOR)?

G. Rust on metal parts (PITCO)?

H. Heat affected metal (HTAFF)?

I. Damaged metal sealing surface (SSMET)?

J. Damaged metal other than sealing surface (DAMML)?

If any of the above conditions exist, record applicable dimensions below.

Yes

Comment

No Number

Yes .__ No

Yes ___ No

Yes _ No

Yes _ No

Yes _ No

Yes Yes _ No No

Yes _ No

Yes v / No

Describe the observed

condition using a commer, t number, a "FWD" if the condition is observed on the S&A on the S&A

joint or the adapter on the Inner and outer joints or a "AFT'; if the condition is observed on the

adapter on the S&A joint, the chamber on the inner joint or the dome on the outer joint and any other

information needed to describe the observation:

RF.V.__ NO, TWR-17591 Ivo,. IV

SEC I PAGE

A-23
Morton Thiokol Inc.

Space Operations

Corresponding Comment Number __ I Inspector(s): &.l_ai/ D. I_OL,._¢II

270 DEG

O O

LEAK TEST HOLE

180 DEG

FLUOROCARBON

RUBBER SEALS

0 + 0 0 DEG

INDEX HOLE J

O O

90 DEG

Observation Drawing Worksheet - Igniter S&A Gasket (Forward Face)

REV.

DOC NO. TWR-17591 VOL IV

s_c ]P^G_A-24
Morion Thiokol Inc.

Space Operations

_o,orNo.:_- _ IO.'e:,,/e,_e ITime"

Corresponding Comment Number _ [ Inspector(s): _',A_au.)t"

D_o

,,, 2). _o_ell

INDEX HOLE--_

b

90 DEG

© ©

180 DEG ©

FLUOROCARBON

RUBBER SEALS

-5

©

© 0 DEG

LEAK TEST HOLE

270 DEG

Observation Drawing Worksheet - Igniter S&A Gasket (Aft Face)

REV.

DOC

No. TWR-17591

SEC
Morton Thiokol Inc.

Space Operations

Motor No.:

Gasket:

Detailed Igniter Gasket - Evaluation Checkoff Worksheet

i

_- r } Date: _ - _'-t r

[] Inner (IGI) [] Outer (IGN) [_S&A (S&A)

P/N: /us_'.zs--o/ S/N: c¢_x:z__

Inspector(s): __0;_- _-_[W I _oC/Pl _ ll

I. Soot Past Seals (SPINS, SPPOR, SPSOR)?

II. Foreign Material (FMIJ)?

III. Seal Damage (PCUT, PDIS, PDMG, SCUT,

SDIS, SDMG) ?

IV. Heat &ffected Seals or Retainer (PORE, HAPOR

SORE, HASOR, HTAFF)?

V. Rust (SSCOR, PITCO)?

Vl. Metal Damage (SSMET, DAMML)?

If yes, describe below:

yes / no

yes _ no

yes no

yes v/ no

yes @ no

yes no

Comment

Number

REV.

ooc No. TWR-17591

SEC
Morton Thiokol Inc.

Space Operations

Ignition System Sealing Surface Condition - Evaluation Checkoff Worksheet

Motor No.: Qt'/_-- (_ [ Dale: / /_A_ [¢_¢_

Joint: [] S&A to Adaptm (S&A) _Adapter to Case (IGN) [] Adapter to Chamber (IGI)

Inspector(s): AE;& I

/

A. Soot in Proximity to ,' Past O-ring Groove (SPINS, SPPOR, Yes V'

SPSOR)?

B. Sooted Grease (HAGRE)? Yes ___ No

C. Discolored Grease (DIGRE)? Yes v" No

D. Leak Check Port Obstructed (LPOBS)? Yea V / No

E. Foreign material in the sealing area during motor operation Yes -7- No

(FMIJ)?

F. Rust on sealing surfaces (SSCOR)? Yes _ No

G. Rust on metal parts (PITCO)? Yes v '_ No

H. Heat affected metal (HTAFF)? Yes V _" No

I. Damaged metal sealing surface (SSMET)? Yes ---'-'7 No

J. Damaged metal other than sealing surface (DAMML)? Yes v2" No

If any of the above conditions exist, record applicable dimensions below.

Comment

Number

No

m

Describe the observed

condition using a commer, t number, a "FWD" If the condition is observed on the S&A on the S&A

joint or the adapter on the inner and outer Joints or a "AFT" if the condition is observed on the

adapter on the S&A joint, the chamber on the inner joint or the dome on the outer joint and any other

information needed to describe the observation:

hJo ._oo+ _o,..t 4ou,,,aJ o_ e_',_,cr s_clc _# 4-w__ _.c, sk:¢.,+.

REV ooc No. TWR-17591 jvoL IV

sEc JPAG_A-27
_lorton Tliiok()i Inc.

Space Operations

Motor No.: (___i_,]_ ._ j Date:

Corresponding Comment Number [

0 DEG

I

90 DEG

©©

INDEX HOLE

©

FLUOROCARBON

RUBBER SEALS

270 DEG

I

180 DEG

Observation Drawing Worksheet - Igniter Outer Gasket (Aft Face)

REV. NO. t_oc TWR-17591

SEC

I VOt.

I _'_E A-28

IV
3Iorton Thiokoi Inc.

Space Operations

Detailed Igniter Gasket - Evaluation Checkoff Worksheet

Motor NO.: Q._vk- _}' i Date: Z(J _,.,Ov,[ /_'9' '

Gasket: [_ Inner (IGI) _1 Outer (IGN) [] S&A (S&A)

P/N: IL_Iq_--OI S/N: t-L_c,c_._z_-C>P-..

I, Soot Past Seals (SPINS, SPPOR, SPSOR)?

II. Foreign Material (FMIJ)?

III. Seal Damage (PCUT, PDIS, PDMG, SCUT,

SDIS, SDMG) ?

IV. Heat _,ffected Seals or Retainer (PORE, HAPOR

SORE, HASOR, HTAFF)?

V. Rust (SSCOR, PITCO)?

VI. Metal Damage (SSMET, DAMML)?

If yes, describe below:

yes _._ no

yes _ no

yes no

/

yes .._.Y...-- no

yes v// RO

yes no

PRIMARY.

Comment

Number

SECONDARY ._5 q°

/_'-r 5, _.

0 0 0

REV.

Dec

No. TWR-17591

SEC
_[orton Thiokoi Inc.

Space Operations

Ignition System Sealing Surface Condition - Evaluation Checkoff Worksheet

Motor No.: C_vx_-_ ' IDate: _- ,¢__'_

Joint: [] S&A to Adaptel (S&A) [] Adapter to Case (IGN) [_ Adapter to Chamber (IGI)

Inspector(s): ,_'. _o,_._,--

A. Soot in Proximity to ' Pest O-ring Groove (SPINS, SPPOR, Yes v_

SPSOR)?

B. Sooted Grease (HAGRE)? Yes '/

C. Discolored Grease (DIGRE)? Yes ,_

D. Leak Check Port Obstructed (LPOBS)? Yes _-

E. Foreign material in the sealing area during motor operation Yes

(FMIJ)?

F. Rust on sealing surfaces (SSCOR)? Yes ,t"

G. Rust on metal parts (PITCO)? f Yes

H. Heat affected metal (I-ITAFF)? _ Yes v"

I. Damaged metal sealing surface (SSMET)? Yes v"

J. Damaged metal other than sealing surface (DAMML)? Yes J

If any of the above conditions exist, record applicable dimensions below.

Comment

Number

No

No

No

No

No

m

m

m

No

No

No

No

m

No

Describe the observed

condition using a comment number, a "FWD" if the condition is observed on the S&A on the S&A

joint or the adapter on the inner and outer joints or a "AFT" if the condition is observed on the

adapter on the S&A joint, the chamber on the inner joint or the dome on the outer joint and any other

information needed to describe the observation:

REV._ No TWR-17591 jvo, IV

sEc I PAGE A-30
51orton Thiokol Inc.

Space Operations

Motor No.:

Gasket:

Detailed Igniter Gasket - Evaluation Checkoff Worksheet

_lnner (IGI) [] Outer (IGN) [] S&A (S&A)

P/N: _ S/N:

I - I - I d

I. Soot Past Seals (SPINS, SPPOR, SPSOR)?

I1. Foreign Material (FMIJ)?

II1. Seal Damage (PCUT, PDIS, PDMG, SCUT,

SDIS, SDMG)?

IV. Heat P-,ffected Seals or Retainer (PORE, HAPOR

SORE, HASOR, HTAFF)?

V. Rust (SSCOR, PITCO)?

Vl. Metal Damage (SSMET, DAMML)?

If yes, describe below:

yes / no

yes _ no

yes no

yes V_ no

Comment

Number

yes _ no

yes V f no

REV.

DOG No TWR-17591

s_c I pAGE A-31
Morion Thiokol Inc.

Space Operations

Ignition System Stat-O-Seals - Evehmtion Checkoff Worksheet

MotorNo: q,,__ _ I Date:_---J--SF

Joint: Adapter/Chamber (IGI) Case End: STAT

P/N lU"/3";5'7_/-0/ Lot Number _'__<.. ¢_<_/o

Inspector(s): _". _c_ _:c,'-

Bolt Stat-O-Seal Observations:

A. Eroded Stat-O-Seals (SORE)? Yes

B. Heat Affected Stat-O-Seals (HASOR)? Yes

C. Cuts, Assembly/Disassembly Damage (SCUT, SDMG, SDIS)? "_Yes

v I

Comment

Number

No

No

No _.

If any of the above conditions exist, describe below: b

_- I I 5 t_. _--<_ -O'tr,,h

REV.

OOC

No. TWR-17591 JVOL IV

SEC I P^GEA_32
lXlorlon Thiokol Inc.

Space Operations

S'&"

Nozzle Joint Condition - Evaluation Checkoff Worksheet

Inspector(s): _. /._,c_k-¢"/ "_". C,.'(''_" Z.--,/1./¢../T=e-,_

Motor No.: Q t_-_ [ Date: 2.-&,-_'_"

Joint: r-IThroat/Fwd Exit Cone (4)

[] Fixed Housing/Aft End Ring (5)

_.Fwtl Exit Cone/Aft Exit Cone (1)

[] Fwd End Ring/Nose Inlet (2)

[] Nose Inlet/Throat (3)

Case Field Joint Observations:

A. Soot In Proximity to I Past O-ring Groove (SPINS, SICOR

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Leak Check Port Obstructed (LPOBS)?

E. Vent Port Obstructed (VPOBS)?

F. Foreign material in the sealing area during motor operation

(FMIJ)?

G. Rust on sealing surfaces (SSCOR)?

H. Rust on metal parts (PITCO)?

I. Heat affected metal (HTAFF)?

J. Damaged metal sealing surface (SSMET)?

J

Yes No

Yes _ No

Yes _ No

Yes _'_ No

Yes 7 No

Yes _ No

Yes / No

Yes "_ No

7" o

Yes -'_No Yes

Comment

Number

tf any of the above conditions exist, record applicable dimensions below. Describe the observed condition using a comment letter, an "F" If the condition Is observed on the forward end of the joint or

an "A" if the condition Is observed on the aft end of the joint and any other information needed to

completely describe the observation end Its location:

REV. ooc NO. TWR-17591 IVOL IV

sEc [p^oE A-33
MORTON THIOKOL INC. -.SE..

Space Operations

Detailed Nozzle Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wasatch A-2 Bldg)

Inspector(s):

Motor No. :

Joint: _"Fwd Exil Cone/Aft Exit Cone [-'] Fwd End Ring/Nose Inlet

[] Throat/Fwd Exit Cone [] Fixed Housing/AFt End Ring

[] Nose Inlet/Throat

PRIMARY O-RING Pert No.: i L) 7515() "O_ "3

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: CCz:,O_ I ":t

Yea .._ No

Yes _ No

Yes No

Yes No

CSVAP

Distance

(Length)

SECONDARY O-RING Part No.: I U "/51.6L3- _3_ Serial No.:

(If Applicable)

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below: . ..

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width . CSVAP

C:r-c:_r, ,._,_'

Yes _ No

Yes No

Yes No

Yes No

Distance

(Length)

Notes I Comments

REVISIOI_ ooc NO. TWR-17591 I v_ IV

ssc I P^GEA-34
l_lorlon Thiokol Inc.

Space Operalions

Nozzle Joint Condition - Evaluation Checkoff Worksheet

_.spactor(s):_OuJELL N EL-_EUI K _-¢"-

Motor No.: _ I'_- <:_

Joint: [] ThroatlFwd Exit Cone (4)

[] Fixed Housing/Aft End Ring (5)

I--IFwd Exit Cone/Aft Exit Cone (1)

{ Date: "Z /I ,_'-/_ _)

wd End Ring/Nose Inlet (2)

ose Inlet/Throat (3)

Case Field Joint Observations:

11"

A. Soot In Proximity to I Past O-ring Groove (SPINS, SICOR Yes No

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)? f Yes No Q1L

C. Discolored Grease (DIGRE)? Yes v"" No

D. Leak Check Port Obstructed (LPOBS)? Yes _ No

E. Vent Port Obstructed (VPOBS)? Yes "it No

F. Foreign material in time sealing area during motor operation Yes "--7 No

(FMIJ)?

G. Rust on sealing surfaces (SSCOR)? Yes J No

H. Rust on metal parts (PITCO)? v" Yes No 2..

I. Heat affected metal (HTAFF)? _ Yes _ No

J. Damaged metal sealing surface (SSMET)? Yes --7" No

Comment

Number

._=/=_

If any of the above conditions exist, record applicable dimensions below. Describe the observed condition using a comment letter, an "F" if the condition is observed on the forward end of the joint or

nn "A" if the condition is observed on the aft end of the Joint and any other information needed to

completely describe the observation and its location:

,_. ° Vv,._-

&;'_ c _ \o,- c..-¥ ;o _

REV, ooo No, TWR-17591 Ivot IV

s_c I p,.,o_A-35
MORTON THIOKOL INC.

Space Operations

,.,pector(,):

Motor No.: (_1_-_ ' - I i

Joint: r] Fwd Exit Cone/Aft Exit Cone

[] Throet/Fwd Exit Cone

[] Nose Inlet/Throat

PRIMARY O-RING Part No. _. /_75 | _- C>-?

Detailed Nozzle Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wautch A-2 Bldg)

' J Date: Z- /7- _:<;'

_Fw¢l End RlnglNose Inlet

[] Fixed Housing/AFt End Ring

Serial No.: C>_v.._OC>/_J--

A. Erosion?

B. Heat Affect?

C. AssemblylDIsassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Yes No m

Yes Lf NO

m Yes L._ NO

.__ Yes _ No

CSVAP

Distance

(Length)

SECONDARY O-RING Part No.: !t_-')._ 150 -- (_>_

(If Applicable)

A. Erosion?

a. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimension= below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: CD_C> Z.O

/

__ Yee _ No

__ Yes _._ No

Yes No

__ Yes "__.(_ No

CSVAP

Distance

(Length)

Notes I Comments

REVISlOI_ °=NO. TWR-17591 I_ IV

=c i P*(_ A- 36
Morton Thiokol Inc.

Space Operations

Date: ,_- t7-6?

Motor No.:

[] Left (A) []Right (B)

O-ring Location: j_ Primary

Part Number: /L_SI_D7

Serial Number: ('_('2_>/,4--

Depth;

Description: _P_ _ tcx._

O-RiNG OBSERVATION CLARIFICATION FORM /(_,_j ,nspector(,): _-. ,0;_ • P'_V, _, ,'_'G'_

Joint: _-_2_ _ ___;"_r / _3E,

[] Secondary [] Capture Feature [] Wiper

Sketch observation below or attach worksheet$ and list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation.

if

L_ Z._,7

REV.

DOC

NO. TWR-17591

8EC

IV
_i(_rlt_n Thiokoi Inc.

Space Operations

,S'_"

Nozzle Joint Condition - Evaluation Checkoff Worksheet

Inspector(s): L-OUJ_LL AJ_LSE_ ; _llv J_¢.--

Motor No.: Qp,_, - _' u

Joint: [] ThroatlFwd Exit Cone (4)

[]Fixed Housing/Aft End Ring (5)

[] Fwd Exit Cone/Aft Exit Cone (1)

I Date'

[] Fwd End Ring/Nose Inlet (2)

_Nose Inlet/Throat (3)

Case Field Joint Observations:

A. Soot In Proximity to I Past O-ring Groove (SPINS, SICOR

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Leak Check Port Obstructed (LPOBS)?

E. Vent Port Obstructed (VPOBS)?

F. Foreign material in the sealing area during motor operation

(FMIJ) ?

G. Rust on sealing surfaces (SSCOR)?

H. Rust on metal parts (PITCO)?

I. Heal affected metal (HTAFF)?

J. Damaged metal sealing surface (SSMET)?

Yes '11 No

Yes _ No

Yes L..--'_ No

Yes _ No

Yes _ No

Yes _ No

Yes _/ No

Yes _fNo

Yes _'_ No

Yes _" No

Comment

Number

If any of tile above conditions exist, record applicable dimensions below. Describe the observed condition using a comment letter, an "F" if the condition is observed on the forward end of the joint or

an "A" if the condition is observed on the aft end of the Joint and any other Information needed to

completely describe the observation and Its location:

REV. ooc No. TWR-17591 Ivot.

sEc I PAGE A-38

IV
MORTON THIOKOL INC.

Space Operations

Detailed Nozzle Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wesltch A-2 Bldg)

Inspector(I): _P_'JGJ _-,_k : IJ_LV_ _t_'IrfU :_t'nl'_Vl . "--_, (_rt_.Jr _ ,_)_'L_o_J

Motor No.: _(_l(_"_ ' ' _} " I Date: _. -It7 - _>q

Joint: r--i Fwd Exit Cone/Aft Exit Cone

[[_ThroatlFwd Exit Cone Nose Inlet/Throat

PRIMARY O-RING Part Ha.: JL)751¢,O ° i(%

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Deaorlbe:

If any of the above conditions exist, record applicable dimensions below:.

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

[] Fwd End Ring/Nose Inlet

[] Fixed HouslnglAFt End Ring

Serial No.: _|C: I

Yes _ No

Yes _ No

Yes V / No

Z Yes _ No

CSVAP

Distance

(Length)

q.,Y

SECONDARY O-RING Pert No.: 10"/51 ._3-(_c_

(If Applicable)

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Delcrlbe:

If any of the above conditions exist, record applicable dimensions below:.

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

D #/_,7 ° ,e_")l ,_l

Serial No.: _ I _>

Yes .._ No

Yes _ No

Yea _ No

Yes _ No

CSVAP

Distance

(Length)

___,33D._

Notes I Comments

REVlmON_ NO. TWR-17591 _ IV

Itc I P"i A- 39
Morton Thiokol Inc. _-_'_'

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

Date: Motor NO.: o'_-I_-_: ,nspector(,): P._rk.J _.-_. J)._/t_l¢,*_ _._@rrd _ _._ F--_n) _ "_, (_J_.,'_'. A]_'."LJ;O,_ ' <r" -

[] Left (A) [] Right.JB) Joint: IN_,<_j "Tj_w_p_/-'r_lr/vL_-

O-ring Location: L_ Primary [] Secon¢Ja-ry [] Cal_ture Feature [] Wiper

Part Number: | _)'/:_ J_O _ J(_

Serial Number: _lq

Depthi

Description: ,_-P- _ P_mU _J

Sketch observation below or attach worksheete end list below. Indicate orientation and dimenslonl.

Show as much detail as necessary to explain the observation.

0

o o 7_,_ o qoo

\"_\ I

/_-_ _/-,I

_: .COl

,IO0

L,O= ,OOi

•OOt D=

_= _0°

KEV.

DOC

NO.

SEC

TWR-17591

I_A_ A-40

IV
Morton Thiokol Inc.

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

Date: _-'1%_t,y__ Inspector(s): _::_L_ _,_.t.k'_/l,J_t#-_Pr('r Motor No.: _ _. ¢_P_L_ =4J_l.l_A.) ' " _'-i

[-']Left (A) [']Right (B)- Jolql: _r=__ "_-_le_÷ /-l_v'r_o_'_

O-ring Location: [] Primary [_Secondary [] Cept_Jre Feeiure [] Wiper

Part Number: I I)"/_ ! _/") -OcI

Serial Number: _:_)(_(_) |_

Depth;

Description: _ _.O_

Sketch observation below or attach worksheet$ and list below. Indicate orientation and dimensions.

Show el much detail as necessary to explain the observation.

O lq , 7 °

t._= ,C:X3 )

D--- ,001

REV.

DOC

NO. TWR-17591

aEG

IV
_lott.tl 'l'hiol<¢_! Inc.

Space Operations

.S'6"

Nozzle Joint Condition - Evaluation Checkoff Worksheet

Inspector(s): _,F-LLY'. _l_t<.E_-,,_ . LOI_JF_.LL

Motor No.: Q,PtJoint: _/_Throat/Fwd Exit Cone (4)

[] Fixed Housing/Aft End Ring (5)

FiFwd Exit Cone/Aft Exit Cone (t)

Case Field Joint Observations:

_JE c%E

I care: /R

[] Fwd End Ring/Nose inlet (2)

[] Nose Inlet/Throat (3)

A. Soot In Proximity to I Past O-ring Groove (SPINS, SICOR

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Leak Check Port Obstructed (LPOBS)?

E. Vent Port Obstructed (VPOBS)?

F. Foreign material in the sealing area during motor operation

(FMIJ) ?

G. Rust on sealing surfaces (SSCOR)?

H. Rust on metal parts (PITCO)?

I. Heat aflected metal (HTAFF)?

J. Damaged metal sealing surface (SSMET)?

_/' Yes No

Comment

Number

Yes V I No

Yes V / No

Yes ----t7" No

Yes _ No Yes No

Yes V / No

Yes --7 No

Yes L7 No

Yes 7 No

If any of the above conditions exist, record applicable dimensions below. Describe the observed condillon using a comment letter, an "F" if the condition Is observed on the forward end of the joint or

an "A" if the condition is observed on the aft end of the Joint and any other information needed to

completely describe the observation and its location:

De

REV. coo NO. TWR-17591 ]vo,

sEc lPAOEA-42

IV
Morton Thiokol Inc.

Space Operations

i i i

Corresponding Comment Number I I inspector(s): I_ELLV Lo_LC

THROAT ASSEMBLY

CARBON CLOTH

PHENOLIC

GLASS CLOTH PHENOLIC •

I

STEEL

Observation Drawing Worksheet - Throat/Forward Exit Cone Joint

Rev. ooc NO. TWR-17591 ]v_ IV

s_c I PAGE A-43
MORTON THIOKOL INC.

Space Operations

Detailed Nozzle Joint O-rtng (Post-Removal) - Evaluation Checkoff Worksheet, (Wasetch A-2 Bldg)

Inspector(s): SC0][_7" E_,¢,'I W,,'_YWg 5P6_,RY. _, _A..Lv _ /_Jk"_._,_J

Motor No.: (_/_-_ " J Date: 2-/5"-_

Joint: [] Fwd Exit Cone/Aft F.xlt Cone

[]PJ'ThroatlFwd Exit Cone

[] Nose Inlet/Throat

PRIMARY O-RING pert No.: /rJ75/_'0-QI

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

[] Fwd End Ring/Nose Inlet

[] Fixed Houalng/AFt End Ring

Serial No.: O0000_Q

Yea _ No

Yea v / No

Yea No

Yea t,/ No

CSVAP

Distance

(Length)

SECONDARY O-RING Pert No.: / _/"7_'/._'O -02.

(If Applicable)

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If eny of the above conditions exist, record applicable dimensions below:

Condition Degree Mmdmum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: 000¢;_0 _.O

m

u

u

n

Yea No

Yes _ No

Yea _ No

Yea _ No

CSVAP

Distance

(Length)

Notes I Comments

REVISlON_ °=NO. TWR-17591 I _ IV

uc I P^o_A-44
hlorton Thiol¢ol Inc.

Space Operations

Nozzle Joint Condition - Evaluation Checkoff Worksheet

Inspector(s): KEI..-L-y _2_K_I'_ L.C:_JO___L./_ _kJl_" L._/_PJ

Motor No.: (_ _ - '_ I Da,.: / IL/I

Joint: _-1 Throat/Fwd Exit Cone (4) [] Fwd End Ring/Nose Inlet (2)

/_Fixed Housing/Aft End Ring (5) [] Nose Inlet/Throat (3)

Fwd Exit Cone/Aft Exit Cone (1)

Case Field Joint Observations:

A. Soot in P.roximity to I Past O-ring Groove (SPINS, SICOR

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Leak Check Port Obstructed (LPOBS)?

E. Vent Port Obstructed (VPOBS)?

F. Foreign material In the sealing area during motor operation

(FMIJ)?

G. Rust on sealing surfaces (SSCOR)?

H. Rust on metal parts (PITCO)?

I. Heat affected metal (HTAFF)?

J. Damaged metal sealing surface (SSMET)?

Yes V/' No

Yes _ No

Yes No

Yes No

Yes No

Yes --7 No

Yes V / No

Yes _ No

Yes ii/ No

Yes ___ No

Comment

Number

If any of the above conditions exist, record applicable dimensions below. Describe the observed condition using a comment letter, an "F" if the condition is observed on the forward end of the Joint or

an "A" if the condition is observed on the aft end of the Joint and any other information needed to

completely describe the observation and Its location:

IV
MORTON THIOKOL INC.

Space Operations

Detailed Nozzle Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wantch A-2 Bldg)

Inspector(s):

Motor No.:

Jolrf

(.JAYalE SP£,e_y , .3C077- [,_£,,c/.

(_ ,Ab4-'_

[_wd Exit Cone/Aft ExIt Cone

[_ThroatlFwd ExIt Cone

[] Nose Inlet/Throat

I o°t,:

[] Fwd End Ring/Nose Inlet

[_Fixed Housing/AFt End Ring

PRIMARY O-RING Part No.: /U 7..</,5"0 -o ,5"

A. Erosion?

B. Heat Affect?

C. AlsemblylDIsassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:.

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.:. (;:)OC)O C) _"7

Yes v / No

m

Yes 7 No

m Yes No

Yes No

CSVAP

Distance

(Length)

SECONDARY O-RING Part No.: /(J7,5"/,5-o-0_

(If Applicable)

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: ooooo/?

/

Yes _ No

Yes _ No

Yes _ No

Yes _ No

CSVAP

Distance

(Length)

Notes I Comments

REV1SIO_ ODD NO. TWR-17591 I voL IV

m_c I PA_ A-4F,
Fix EC HsuJ_¢/Rt3*" _.,_'0 al/V6 Slat-O-Seals - Evpluation Checkoff Worksheet

Motor No.: GM-8 j Dale: "J,-2Y-_'?

Joint: ,r.,'JcEa #¢_:#_/,.b,"r t#a x,;,_,_ (STAT)

PIN //JT,b'27_-Ol Lot Number _CL oC_/o

Inspector(s):

Bolt Slat-O-Seal Observations:

A. Eroded Slat-O-Seals (SORE)*r Yes

B. He_t Affected Sial-O-Seals (HASOR)? Yes

C. Cuts, Assembly/Disassembly Dr, mage (SCUT, SDMG, SDIS)? ,I Yes

V No

No

No

Comment

Number

If any of the above conditions exist, describe below:

_// 72 S'/_'J" -0- _¢.o,l,f L"a / _x',Lcq$;u ,.

I_EV.

DOC

No. TWR-17591

SEC

VOL

j _^°'_-4 7

IV
Morton Thiokol Inc.

Space Operations

3ase Factory Joint Condition - -valuation Checkoff Worksheet

Joint:

'_ Aft Dome Facto-,/ Joint (1817.8, ADS) F']sliff.-To-Stiff. Factor,/ Joint (1697.5, ASS)

ETA-To-Stiff. Factory Joint (1577.5, FSS)E]Aft Center Segment Factory. Joint (1331.5, ACS)

_'-; Fwd Segment Factory Joint (691.5. FFS) ["_lForward Center Segment Factory Joint (1011.5, FCS)

._Fwd Dome Factory Joint (531.5. FDS)

Case field joint observations:

A. Soot in Proximity to 1 Past O-ring Groove (SFINS. SICOR

SOINT, SPINT, SIPOR. SPPOR SISOR, SPSOR)?

_. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Leak Check Port Obstructed (LPOgS)?

E. Foreign material in the sealing area during motor operation

(FMIJ}?

Rust on sealing surfaces (SSCOR)?

Rust on metal parts (PITCO)?

Heat affected metal (HTAFF)?

Damaged metal sealing surface (SSMET)?

4.

Comment

Numioer

Yes _ No

Yes ._ No

Yes _ No

Yes .,X,.. No

Yes _._ No

Yes _ No .... ;

Yes _" No

Yes ._ No

Yes _ No

tf any of the above conditions exist, record applicaole dimensions below• Describe the observed condition using a comment number, a "T" if the condition is observed on the tang or a "C" if the condition is observed on the clevis and any other information needed to cescribe the ooservation:

,, k •

• L%

°_

_CC

,,o TWR-17591 1,,_,_ Iv

A-48

p
Morton Thiokol Inc.

Space Operations

Factory Joint - Evaluation Checkoff Worksheet

Inspector!s): ,,_,_j_ _f- _/_-_

Joint:

[] Aft Dome Factory Joint (1817.5, ADS) [] Stiff.-to-Stiff. Factory, Joint (1697.5. ASS)

ETA-to-Stiff. Factory Joint (1577.5. FSS)[-'] Aft Center Segment Factory Joint (1331.5, ACS)

[] Fwd Segment Factory Joint (691.5. FFS) [] Forward Canter Segment Factory Joint (1011.5. FCS)

[_ Fwd Dome Factory Joint (531.5, FDS)

I. Corrosion On Metal Parts (PITCO)?

II. Sealing Surface Corrosion (SSCOR)?

IlL Metal Damage (DAMML}?

IV. Sealing Surface Metal Damage (SSMET}?

V, Metal Slivers In Pin Holes (MSIPH)?

Vl. Other?

Describe:

yes _ no

yes _ no

yes _ no

yes /_ no

yes _ no

yes no

If yes. record the data below. Describe the observed condition using the observation code

\

of the corresponding condition from above and the letter "C" if the condition is observed

on the ctevis or "T" if the condition is observed on the tang (i.e. PITCO-T). Field joint

tang and clevis zones are mapped out on the second page of this form.

Comment Description Degree Degree Zone

Number (Use symbols Start Stop (See zone

from above) Location Location description)

(Oeg.) (Deg.)

:,; 4,

Notes / Comments:

[] See attached sheet(s)

RE_,'. _o¢ ,,o. TWR-17591 j,Jet.

_:" =*_" A-49

IV
- MOFIION IHIOKOL INC.

Detailed Case Factory. Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet [Wasatch A-2 Bldg

Motor No.: _-_ ' ' _J

ory Joint:

orward Dome Factory Joint (531.5)

[] Forward Center Segment Factory Joint (1011.5)

[] Aft Segment Factory Joint (1577.5)

[] Aft Dome Factory Joint (1817.6)

[] Forward Segment Factory Joint (691.5)

[] Aft Center Segment Factory Joint (1331.5)

[] Aft Segment Factory Joint (1697.5)

PRIMARY O-RING Serl,,No.: CC 02 o

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

m

m

Yes _ No

Yes _/' No

Yes No

Yes l/' No

CSVAP

Dlstince

(Length)

SECONDARY O-RING Part No.: I_)-75J _O'¢,_,.._

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

0. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width CSVAP

No

No

No

No

Diet|nee

(Length)

Notes / Comments

4

$

RE_StON__ Dec NO.TWR-17591 I v_ IV

i';,,,(_E _ 50

sl:¢
3Iorton Thiokoi Inc.

Space Operations

°.-

4"

t

=ase Factory Joint Condition - -'valuation Checkoff Worksheet

,osoecto ,s,: ,-2

Motor NO.: (,_,-. ,_ I Date: #..2/-J,,_" I Time: .___,___

Joint:

Aft Dome Facto,*/ Joint (1817.6, ADS) []Stiff.-To-Stiff. Factory Joint (1697.5, ASS}

ETA-To-Stiff. Factor,/ Joint (1577.5, FSS)C_]Aft Center Segment Factory Joint (1331.6, ACS)

'_Fwd Segment Factory Joint (691.5, FFS) _-iForward Center Segment Factor/Joint (1011.5, FCS)

Fwd Dome Factor,/ Joint (531.5, FDS)

i ii

B,

C.

D.

E.

Case field joint observations"

A. Soot in Proximity to I Past O-ring Groove (SPINS, SICOR _ Yes

SOINT, SPINT, SIPOR, SPPQR SISOR, SPSOR)?

Sooted Grease (HAGRE)? _ Yes

Discolored Grease (DIGRE) ? Yes

Leak Check Port Obstruct&d (LPOBS)? Yes

Foreign material in the sealing area during motor operation _ Yes

(FMIJ) ?

Rust on sealing surfaces (SSCOR)? Yes

Rust on metal parts (PITCO)? _ Yes

Heat affected metal (HTAFF)? Yes

Damaged metal sealing surface (SSMET)? _ Yes

G.

,4.

•Comment

Number

No

_ No _

1No

No •. ._

NO _ "

.._ No

If any of the above conditions exist, record aDplicaole dimensions below. Describe the observed condition using a comment number, a "T" if the condition is observed on the tang or a "C" if the condition is o0served on the clevis and any other information needed to describe the observation:

"_ :oc .,o TWR-I7591 [,,'nL IV

A-51
_h)rt,)n Thiokol Inc.

Space Operations

Factory Joint - Evaluation Checkoff Worksheet

Inspector(s): /4"/_,__j{'/_

 o,o,.o: I °"": ....... z

Joint:

[] Aft Dome Factory Joint (1817.6, ADS) [] Stiff.-to-Stiff. Factory Joint (1697.5, ASS)

[] ETA-to-Stiff. Factory Joint (1577.5, FSS)J-] Aft Center Segment Factory Joint (1331.5, ACS)

_ Fwd Segment Factory Joint (691.5, FFS) [] Forward Center Segment Factory Joint (1011.5. FCS)

Fwd Dome Factory Joint (531.5, FDS)

I. Corrosion On Metal Parts (PITCO)?

II. Sealing Surfaca Corrosion (SSCOR)?

II1. Metal Damage (DAMML)?

IV. Sealing Surface Metal Damage (SSMET)?

V. Metal Slivers In Pin Holes (MSIPH)?

Vl. Other?

yes _-_ no

yes _ "no

yes ._ no

yes .._ no

yes _

yes

*'.,2 .

NO

no

Describe:

If yes, record the data below. Describe the observed condition using the o[oservation code :_]_.! _:l

of the correspondin,g condition from above and the letter "C" if the condition is observed

on the clevis or "T' if the condition is observed on the tang (i.e. PITCO-T). Field joint

tang and clevis zones are mapped out on the second page of this form. , - _,_ .........

Comment Description Degree Degree Zone

Number (Use symbols Start Stop (See zone

from above) Location Location description)

(Deg.) (Deg.) !ii_.- :t-.;, .,.L_ !.!'-¢:_r,:.

Notes I Comments:

",4,-. 7

;,:'¢' g"

.: 5:

. ,.% _,;];

[] See attached sheet(s)

REV. ooc _ TWR-17591 tve, IV

_c ! o,,OEA_52
MORTON THiOKOL INC.

Cetailed Case Fac.'or_/ Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wasatch A-2 Bldg)

• i

InsDector is):

Motor No.:

Factory Joint:

[] Forward Dome Factory Joint (531.5)

[] Forward Center Segment Factory Joint (1011.5)

[] Aft Segment Factow Joint (1577.5)

[] Aft Dome Factory Joint (1817.6)

i i n •

PRIMARY O-RING Part No.: l(jL?Stc,_-Z__=_

A. Erosion?

B. Heat Affect?

C. AssemblylDisesIembly Damage?

D. Other? Detcribe:

If any of the above conditions exist, record applicable dimension= below:.

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Forward Segment Factory Joint (691.5)

[] Aft Center Segment Factory Joint (1331.5)

[] Aft Segment Factory Joint (1697.5)

Serial No.: C_C_O2-.'d_-7

Yes / No

Yea _ No

Yes _ No

_ Ye, _No

CSVAP

Distance

(Length)

i

SECONDARY O-RING part No.: [L,_75 _._ -2_,

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: C'C_C>c'_Z.I(_

Yeo L// NO

Yes b7 No

-

Yes No

Yes No

CSVAP

Distance

(Length)

i i,

Notes I Comments

I

REVISION

i i, i i

k

0o¢_

NO. TWR-1759] Ivm. IV

BEC I PAGE A-53
._[orton Thit)kol Inc.

Space Operations

_ase Factory Joint Condition - --valuation Checkoff Worksheet

I ' / '

Motor.o C7.,C/-*" !Date: 1,0:

Joint:

_--] Aft Dome Facto'_( Joint (1817.8, ADS) [--]Stiff.-To-Stiff. Factory Joint (1697.5, ASS)

r-] ETA-To-Stiff. Factory Joint (1577.5, FSS)E]Aft Center Segment Factory Joint (1331.5, ACS)

Fwd Segment Factory Joint (591.5, FFS) ,,_Forward Center Segment Factory Joint (1011.5. FCS)

_._J Fwd Dome Factory Joint (531.5, FDS)

Case field joint observations:

A. Soot in Proximity to / Past O-ring Groove (SPINS, S1COR -- Yes __

SOINT, SPINT, SIPOR. SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)? -- Yes

C. Discolored Grease (DIGRE_? -- Yes .._

D. Leak Check Port Obstructed (LPOBS)? -- Yes

E. Foreign material in the sealing area during motor operation Yes ±

(FMIJ)?

_e

F. Rust on sealing surfaces (SSCOR)? -- Yes __

G. Rust on metal parts (PITC3)? -- Yes

H. Heat affec:ed metal (HTAFF)? Yes

.. Damaged metal sealing surface (SSMET)? Yes

• Comment

Number

No

No

No

No

NO -- _

_."---r._.

' - =_'b., o

. ;:'_" '_,_- :

No

No

No

No

If any of the above conditions exist, record applicable dimensions below. Describe the observed condition using a comment numcer, a "T" if the condition is observed on the tang or a "C" if the condition is oi:}served on the clevis and any other information needed to describe the observation:

:oc •,o TWR-17591 l,/eL Iv

A-54
Morton Thiokol Inc.

Space Operations

Factory Joint - Evaluation Checkoff Worksheet

,nspector(s): //_,/_,,¢ _/."[,/) _//_" .__.

Joint:

[] Aft Dome Factory Joint (1817.6, ADS) [] Stiff.-to-Stiff. Factory Joint (1697.5, ASS)

[] ETA-to-Stiff. Factory Joint (1577,5, FSS)["] Aft Center Segment Factory Joint (1331.5, ACS)

[] Fwd Segment Factory Joint (691.5, FFS) _Forward Center Segment Factory Joint (1011.5. FCS)

[] Fwd Dome Factory Joint (531.5, FDS)

f

I, Corrosion On Metal Parts (PITCO)?

II. Sealing Surface Corrosion (SSCOR)?

III, Metal Damage (DAMML)?

IV. Sealing Surface Metal Damage (SSMET)?

V. Metal Slivers In Pin Holes (MSIPH)?

VI. Other?

yes _ no

yes _._ no

yes __ no

yes no

yes ._ no

yes _._ no

Describe:

If yes, record the data below. Describe the observed condition using the observation code -" _:S::

of the corresponding condition from above and the letter "C" if the condition is observed

on the clevis or "T" if the condition is observed on the tang (i.e. PITCO-T). Field joint

tang and clevis :ones are mapped out on the second page of this form.

Comment Description Degree Degree P";' _"t ":_ Zone

Number (Use symbols Start Stop (See zone

from above) Location Location description)

(Dog.) (Dog.) "_ :'_ _

Notes 1 Comments:

- t /

[] See attached sheet(s)

REV. ooc TWR-17591 I _ NO. VCL

sEc ! _*c_ A-55

IV
MORTON l HIOKOL INC.

Space Operations

Detailed Case Factory Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wasatch A-2 Bldg)

Insloectorfs):

Motor No.:

Factory Joint:

orward Dome Factory Joint (531.5) or'ward Center Segment Factory Joint (1011.5)

[] Aft Segment Factory.Joint (1577.5)

[] Aft Dome Factory Joint (1817.6)

PRIMARY O-RING Pert No.i iL',7 51R(.)-_

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Deacribe:

If any of the above conditions exist, record applicable dlmeneions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

[] Forward Segment Factory Joint (691.5)

[] Aft Center Segment Factory Joint (1331.5)

[] Aft Segment Factory Joint (1697.5)

Serial NO.: _C'1,_ _'

/

Yes _ No

Yes _ No

Yes No

__ Yea No

CSVAP

Distince

(Length)

SECONDARY O-RING Part No.: !_)'7515L)-Z5

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensi0ne below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: (_(_)(_ ;?--_'0

__ Yes v / No

Yes _ No

__ Yes No

--...---Yes No

CSVAP

Distance

(Length)

Notes I Comments

$

REVISION__

OOC

NO. TWR-17591

SEC I PAGE

I vc¢ IV

A-56
Blorton Thit)kol Inc.

Space Operations

_ase Factory Joint Condition - -valuation Checkoff Worksheet

MotorNo.: I Date: I T me:,lZ. 

Joint:

Aft Dome Facto"/ Joint (1817.6, ADS) _Sfiff.-To-Stiff. Factor'/ Joint (1897.5, ASS)

ETA-To-Stiff. Factory Joint (1577.5, FSS)_Aft Center Segment Factory Joint (1331.5, ACS)

Fwd Segment Factory Joint (691.5, FFS) [-qForward Canter Segment Factor/ Joint (1011.5. FCS)

r'-'] Fwd Dome Factory Joint (531.5. FDS)

Case field joint observations:

A. Soot in Proximity to / Past O-ring Groove (SPINS, SICOR

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Leak Check Port Obstructed (LPCBS)?

E. _Foreign material in the sealing area during motor operation

(FMIJ}?

F. Rust on sealing surfaces (SSCOR)?

G. Rust on metal parts (PITCO)?

H. Heat affected metal (HTAFF)?

- ,, Damaged metal sealing surface (SSMET)?

Yes .._ No

Comment

Number

__ Yes .__ No --

__ Yes _ No --

__ Yes _ No --

_._ Yes -- No _.L_

-- Yes _ No --

Yes -- No _ .,7,.-

__ Yes _ No --

__ Yes ._ No --

If any of the above conditions exist, record aD_llcar_le dimensions below. Describe the observed condition using a comment number, a "T" if the condition is observed on the tang or a "C" if the condition is observed on the clevis and any other information needed to describe the observation:

!

Rev. DOC

NO.

SEC

TWR-17591 VOL IV

Page A-57
Morton Thiokol inc.

Space Operations

Factory Joint - Evaluation Checkoff Worksheet

.,,,°,.o,o,<,)" U<,,-t,'d:'.

Joint:

[] Aft Dome Factory Joint (1817.6, ADS) [] Stiff.-to-Stiff. Factory Joint (1697.5, ASS)

[] ETA-to-Stiff; Factory Joint (1577.5, FSS)._Aft Canter Segment Factory Joint (1331.5, ACS)

[] F,Nd Segment Factory Joint (691.5, FFS) [] Forward Center Segment Factory Joint (1011.5. FCS)

[] Fwd Dome Factory Joint (531.5, FCS)

1. Corrosion On Metal Parts (PITCO)?

11. Sealing Surface Corrosion (SSCOR)?

III. Metal Damage (DAMML)?

IV. Sealing Surface Metal Damage (SSMET)?

V. Metal Slivers In Pin Holes (MSlPH)?

VI. Other?

Describe:

yes no

yes _ no

yes _ no

)_ no

yes

yes ___ no

yes _ no

I

If yes, record tl_a. data below. Describe the observed condition using the observation code

of the corresponding condition from above and the letter "C" if the condition is observed

on the clevis or "T" if the condition is observed on the tang (i.e. PITCO-T). Field joint

tang and clevis zones are mapped out on the second page of this form.

Comment

Number

Description Degree Degree

(Use symbols Start Stop

from above) Location Location

(Oeg.) (Deg.)

1 --c.. o

1--7 [j

Zone

(See zone

description)

//

d

Notes / Comments:

[] See attached sheet(s)

REV

ooc

NO. TWR-17591 vct.IV

A-58
l_/IUHiUN IHIUKUL llJU.

Space Operations

Detailed Case Factory Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wasatch A-2 Bldg)

Factory Joint:

[] Forward Dome Factory Joint (531.5)

[] Forward Center Segment Factory Joint (1011.5)

[] Aft Segment Factory Joint (1577.5)

[] Aft Dome Factory Joint (1817.6)

PRIMARY O-RING Part No.: 1_)'lSIG_JF_

A. Erosion?

B. Heat Affect?

C. AssemblylDisessembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below.'

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

I"l_,brwerd Segment Factory Joint (691.5)

_Aft Center Segment Factory Joint (1331.5)

[] Aft Segment Factory Joint (1697.5)

Serial NO.: _("l'_ ,_ 5"i_Z-

__ Yes _ No

Yet _ No

__ Yes _ No

__ Yes No

CSVAP

Dlstaince

(Length)

SECONDARY O-RING Part No. = ,.JO_150-_

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimension| below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: ('/'X'".'C__P.I._I

Yes V / No

__ Yes _ No

Yes _ No

Yes t// No

CSVAP

Distance

(Length)

Notes I Comments

4

I

REVISION__ ON_OC. TWR-17 91 I ZV

SEC I PAGE A-59
_Iorton Thiokol Inc.

Space Operations

Case Factory Joint Condition - Evaluation Checkoff Worksheet

_ns,:,.ec,o,',o_: A/_¢.': :-_,"-/-"_- //_ :e /_oa,:_e//

,,.otor No.: (_',://-_ " i O;"e:_/#_w _,,me:/::-0

Joint:

Aft Dome Facto-y Joint (1817.6, ADS) r-!.Stiff.-To-Stiff. Factor,/ Joint (1697.5, ASS)

_,_ETA-To-StiIf. Factor,/ Joint (1577.5, FSS)[]Aft Center Segment Factory Joint (1331.5. ACS)

Fwd Segment Factory Joint (691.5, FFS) ['_Fo_vard Center Segment Factory Joint (1011.5, FCS)

L.J Fwa 2ome Factory Joint (531.5, FDS)

Case field joint observations:

A. Soot in Proximity to / Past C-ring Groove (SPINS. SICQ_

SOINT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C, Discolored Grease (DIGRE}?

D. Leak Check Port Obstructed (LPOBS)?

E. Foreign material in the sealing area during motor operation

(FMIJ)?

F. _ust on sealing surfaces (SSCOR)?

G. Aust on metal parts (PITCQ)?

H. Heat affected metal (HTAFF}?

.. Damaged metal sealing surface (SSMET)?

Yes ._ No

Yes Yes _. No No

Yes Yes ._ No No

I

Yes _ No

.._ Yes No

Yes _._ No

Yes _" No

Comment

Number

If any of the above conditions exist, record aoplicaole dimensions below. Describe the observed condition using a comment number, a "T" if the condition is observed on the tang or a "C" if the condition is observed on the clevis and any other information needed to describe the observation:

z) cor:c i.,, ,n:jeJ,; :4/o/-"io). °

:oo ,,o.TWR-17591 IVOL IV

A-60
_lorton Thiokoi Inc.

Space Operations

Factory Joint - Evaluation Checkotf Worksheet

Joint:

[] Aft Dome Factory Joint (1817.6, ADS) [] Stiff.-to-Stiff. Factory Joint (1697.5, ASS)

,._/=--'T'A-to-Stiff. Factory Joint (1577.5, FSS)I"] Aft Center Segment Factory Joint (1331.5, ACS)

[] Fwd Segment Factory Joint (691,5, FFS) [] Forward Center Segment Factory Joint (1011.5. FCS)

Fwd Dome Factory" Joint (531,5, FCS)

I. Corrosion On Metal Parts (PITCO)?

II. Sealing Surface Corrosion (SSCOR)?

II1. Metal Damage (DAMML)?

IV. Sealing Surface Metal Damage (SSMET)?

V. Metal Slivers In Pin Holes (MSIPH)?

Vl. Other?

Describe:

yes

yes

yes

yes

yes _'

yes .._

no

no

no

nO

no

no

If yes, record the data below. Describe the observed condition using the observation clyde

of the corresponding condition from above and the letter "C'_ if the condition is observedl

on the clevis or "T" if the condition is observed on the tang (i.e. PITCO-T). Field joint

tang and clevis zones are mapped out on the second page of this form.

Comment Description Degree Degree Zone

Number (Use symbols Start Stop (See zone

from above) Location Location description)

(Oeg.) (Oeg.)

7_ Plf_ - _. /ol / o _

/

3 i'Y,e S%,

,cNotes / Comments:

3) _-cJ_J,c_ "

[_] See attached sheet(s)

REV.

OOC

NO. TWR-17591 I VCL IV

s_e t P"_': A-61
_IORTON THIOKOLINC.

Detailed Case Factory Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wasatch A-2 81d c)

Motor No.: ___ ,: l '

Factory Joint:

[] Forward Dome Factory Joint (531.5)

[] Forward Center Segment Factory Joint (1011.5)

[] Aft Segment Factory Joint (1577.5)

[] Aft Dome Factory Joint (1817.6)

"_. 6_,,,.¢ _d_"z._

I Date:

[] For,ffard Segment Factory Joint (691.5)

[] Aft Center Segment Factory Joint (1331.5)

[] Aft Segment Factory Joint (1897.5)

PRIMARY O-RING Part No..' [_L-7_ _5C_ - _-_

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above ¢ondltions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

:Serial No.: C_O ___f-_.C_

Yes _ No

Yes _ No

Yes _ No

Yes _ No

CSVAP

Dlst_ince

(Length)

SECONDARY O-RING part No.: IC_.'-/5L_C>-Z.. C:.

A. Erosion ?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.: ,_---"_.,C_. Z_._

Yes _ No

Yes _ No

Yes /,I/ No

Yes L.// No

CSVAP

Distance

(Length)

Notes I Comments

,I

J

RE'vlSION_ Dec NO.TWR-17591 I rot. IV

SEC I PAGE

A-62
.._[_,,'-ton Thiokol Inc.

... Space Operations

Case Factory Joint Condition - --valuation Checkoff Worksheet

_otor.o.: O//'/--F - I Date:_d_-'_' !T_me: _J6

Joint:

--_ Aft Dome Facto-,/ Joint {1817.50 ADS) ,,_Stiff,-To-Stiff. Factory Joint (1697.5, ASS)

ETA-To-Stiff. Factory Joint (1577.5, FSS)E_Aft Center Segment Factory Joint (133t.5, ACS}

Fwd Segment Factory Joint (691.5. FFS) ['-i Forward Center Segment Factory Joint (1011,50 FCS)

3

Fwd Dome Factory Joint (531.5, FOS)

Case field joint observations:

A. Soot in Proximity to ( Past O-ring Groove (SPINS, SICOR

SO1NT, SPINT, SIPOR, SPPOR SISOR, SPSOR)?

B, Sooted Grease (HAGRE)?

C. Disc=lored Grease (DIGRE)?

D. Leak Check Port Obstructed (LPOBS)?

E. Foreign material in the sealing area during motor operation

(FMIJ)?

F. Rust on sealing surfaces (SSCOR)?

G. Rust on metal parts (PITCO)?

H. Heat affected metal (HTAFF)7

.. Damaged metal sealing surface (SSMET}?

Yes __ No

Yes .._ No

Yes _ No

Yes _ No

Yes _ No

Comment

Number

m

Yes ._ No

___ Ye, No :2_

Yes _ No

Yes _ No

If any of the above conditions exist, record aoplicaole dimensions below. Describe the observed condition using a comment number, a "T" if the condition is observed on the tang or a "'C" if the condition is observed on the cievis and any other information needed to describe the ooservation:

O FM _-C :F,/eco_ _.d _ee_ Ar,_ 9roov_

/_/?-/V

:oc TWR-17591 [_, Iv
Mor*.on Thiokol Inc.

Space Ouerations

Factory Joint - Evaluation Checkoff Worksheet

,nsoector(s): /_/I _'/'_'//_'J-(_7 _"-_- < #_W"T"C///

Joint:

[] Aft Dome Factory, Joint (1817.6, ADS) ._Stiff.-to-Stiff. Factory Joint (1697.5, ASS)

[] ETA-to-Stiff. Factory Joint (1577.5, FSS)[-'] Aft Center Segment Factory Joint (1331.5, ACS)

[] Fwd Segment Factory Joint (691.5, FFS) [] Forward Center Segment Factory Joint (1011.5. FCS)

[-1 F-vd Dome Factory Joint (531.5, FDS)

I. Corrosion On Metal Parts (PITCO)?

II. Sealing Surfaca Corrosion (SSCOR)?

111. Metal Damage (DAMML)?

IV. Sealing Surface Metal Damage (SSMET)?

V. Metal Slivers In Pin Holes {MSIPH)?

VI. Other?

Describe:

yes no

yes _ no

.._ yes no

yes _ no

yes _ no

If yes, record the data below. Describe the observed condition using the observation code

of the corresponding condition from above and the letter "C" if the condition is observed

on the clevis or "T" if the condition is observed on the tang (i.e. PITCO-T). Field joint

tang and clevis -"ones are mapped out on the second page of this form.

Comment Description Degree Degree Zone

Number (Use symbols Start Stop (See zone

from above) Location Location description)

(Deg.) (Deg.)

A:co-c /)-;l.;z . qs .

Notes / Comments: rc,_ : --_

. ,_,/,__(_/_t, " ' "

See attached sheet(s)

REV. ooc NO. TWR-17591
Detailed Case Factor/ Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet.(Wasatch A-2 Bldg}

Mo,orNo.: " ; - or I Data:

Factor3/ Joint:

[] Forward Dome Factory Joint (531.5)

[] Forward Center Segment Factory Joint (1011.5)

[] Aft Segment Factory Joint (1577.5)

[] Aft Dome Factory Joint (1817.6)

[] Forward Segment Factory Joint (691.5)

[] Aft Center Segment Factory Joint (1331.6)

[_Aft Segment Factory Joint (1697.5)

PRIMARY O-RING Part No.." i V "/6 15_- ..;7.__

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

O. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

'Serial No.:

CSVAP

Yes No

Yes I// No

Yes _, No Yes No

Distance

(Length)

SECONDARY O-RING Part No.: | _)_ _ ] 5C't--_._

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Clrcumferentlal

(A, B, C or D) Location Depth Width

Serial No.:

CSVAP

Yes _ No

Yes _ No

Yes No

Yes No

Distance

(Length)

Notes / Comments

J

REVISION__

ooc

NO TWR-17591

SEO I PAGE

I VOL IV

A-65
_Ic_rton Thiokoi Inc.

Space Operations

Case Factory Joint Condition - =valuation Checkoff Worksheet

Motor Q/z,,I'-Z" t Do,e:3 /W ! T me:0"3.J' 

Joint:

_¢:_Aft Dome Facto-,/ Joint (1817.6, ADS) F1Stiff.-To-Stiff. Factor,/ Joint (1697.5, ASS)

r-] ETA-To-Stiff. Factory Joint (1577.5, FSS)r-qAft Center Segment Factory Joint (1331.5. ACS)

Fwd Segment Factory Joint (691.5, FFS) r-_Forward Center Segment Factor,/ Joint (1011.5, FCS)

_J Fwcl Come Factory Joint (531.5, FDS)

Case field joint observations:

A. Soot in Proximity to / Past O-ring Groove (SPINS, SICOR

SOINT, SPINT, SIPOR, SPPOR SlSOR, SPSOR)?

B. Sooted Grease (HAGRE)?

C. Discolored Grease (DIGRE)?

D. Leak Check Port Obstructed (LPOBS)?

E. Foreign material in the sealing area during motor operation

(FMIJ) ?

Rust on sealing surfaces (SSCOR)?

Rust on metal parts (PITCO)?

Heat affected metal (HTAFF)?

,. Damaged metal sealing surface (SSMET)?

Yes .._ No

Yes _ No

Yes _ No

Yes _ No No

Comment

Number

t'_ F Yes __ No

[ G. _ Yes No

• H. Yes _ No

Yes _ No --

If any of the above conditions exist, record applicable dimensions below. Describe the observed condition using a comment number, a "T" if the condition is observed on the tang or a "C" if the condition is observed on the clevis and any other information needed to describe the observation:

I

Rev. DOC

NO. TWR-17591 VOL IV

SEC Page A-66
_h_rton Thiokot Inc.

Space Operations

Factory Joint - Evaluation Checkoff Worksheet

Inspector(s): _/.._ _------_F'-/_/_, /t/'_ _V_a _OH/,.,_"//'

Motor No.: _'_#,.., Z I b;'(': _,/_/_:" .

Joint:

]_I" Aft Dome Factory Joint (1817.5, ADS) [] Stiff.-to-Stiff. Factory Joint (1697.5, ASS) ETA-to-Sliff. Factory Joint (1577.5, FSS)[-] Aft Center Segment Factory Joint (1331.5, ACS)

[] Fwd Segment Factory Joint (691.5, FFS) [] Forward Center Segment Factory Joint (1011.5, FCS)

Fwd Dome Factory Joint (531.5, FDS)

I. Corrosion On Metal Parts (PITCO)?

II. Sealing Surface Corrosion (SSCCR)?

Ill. Metal Damage (DAMML)?

IV. Sealing Surface Metal Damage (SSMET)?

V. Metal Slivers In Pin Holes (MSIPH)?

VI. Other?

Describe:

yes no

yes .__ no

yes no

yes _ no

yes _ no

yes _ no

If yes, record the data below. Describe the observed condition using the observation code

of the corresponding condition from above and the letter "C" if the condition is observed

on the clevis or "T" if the condition is observed on the tang (i.e. PITCO-T). Field joint

tang and clevis -"ones are mapped out on the second page of this form.

Comment Description Degree Degree Zone

Number (Use symbols Start Stop (See zone

from above) Location Location description)

(Deg.) (Deg.)

Notes / Comments:

[] See attached sheet(s)

REV.

OOC

NO. TWR-17591 VCL IV

3EC '=*GE A-67
Detailed Case Fac'.or/ Joint O-ring (Post-Removal) - Evaluation Checkoff Worksheet (Wasatch A-2 Bldg)

Factory Joint:

[] Forward Dome Factory Joint (531.5)

[] Forward Center Segment Factory Joint (1011.5)

[] Aft Segment Factory Joint (1577.5)

[_Aft Dome Factory Joint (1817.6)

[] Forward Segment Factory Joint (691.5)

[] Aft Center Segment Factory Joint (1331.5)

[] Aft Segment Factory Joint (1697,5)

PRIMARY O-RING Part No..' !t_._i ._0-_6

A. Erosion?

B. Heat Affect?

C. Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.:

CSVAP

o .Io7

Yes _ No

Yes _ No

Yes _ No

Yes _ No

Dlstance

(Length)

SECONDARY O-RING Part No.: J_-/5 i_(,>- _L'_

A. Erosion?

B. Heat Affect?

C, Assembly/Disassembly Damage?

D. Other? Describe:

If any of the above conditions exist, record applicable dimensions below:

Condition Degree Maximum Circumferential

(A, B, C or D) Location Depth Width

Serial No.:

CSVAP

Yes _..._"No

Yes _ No

Yes No

Yes No

Distance

(Length)

Notes I Comments

I_EVISION__ ooc No. TWR-17591 j voL IV -

SEC j PAGE

A-68
J_h,rton Thiokoi Inc.

Space Operations

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheat

Motor No.: _ _ - _

Joint: _'S&A to Adapter iS&A)

Plucj: [_ Leak Check(LEAK) Decjree

?

[] Adapter to Case (IGN)

[ Date: "_-13- _"

[] Adapter to Chamber (IGI)

Inspector(s): _CoJc.-_ EA¢- kJ . Roc_v _%k .

PRIMARY O-RING

Part No.: Lot No.:

A. Erosion (PORE)?

B. Heat Affect (HAPOR)?

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

ELS o

Yes No

Yes No

Yes No

Commentl

Number

SECONDARY O-RING (or Shoulder)

Part No.: /O,_'O=_a_--¢_,_" Lot No.: ECLo_bl3

A. Erosion (SORE) ?

B. Heat Affect (HASOR)?

C. Cuts, Assembly/Disassembly Damaga (SCUT, SDMG, SDIS)?

If any of the above conditions exist, record below:

Yes

I. o- ,-:,J3 k. t o.b.

Comment

Number

_L_

CLOSURE SCREW O-RING

Part No.: Lot No.:

A. Erosion (CORE)?

B. Heat Affect (HACOR)?

C. Cuts, Assembly/Disassembly Damage (CCUT, CDMG, CDIS)?

If any of the above conditions exist, record below:

Yes

Yes

Yes

No

No

No

Comment

Number

REV.

DOC

NO. TWR-17591 I VOL

IV

see IPA_E A-69
l_h)rton Thiokol Inc.

Space Operations

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheet

Motor No.: (_(_J_-_

Joint: [_S&A to Adapter (S&A) [] Adapter to Case (IGN)

Plu_'. ,_Leak Check(LEAK ! Degree _0 _:_

,nspector(s): 5Co t÷ E,_kcu:_oda, /XS1⁄4. _Y _F__J_SO_

IDa,e: 3-1_ --_ 5

[] Adapter to Chamber (IGI)

PRIMARY O-RING I '

Part No.: Lot No.:

A. Erosion (PORE) ?

B. Heat Affect (HAPOR)?

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

Yes No

Yes No

Yes No

Comment

Number

SECONDARY O-RING (or Shoulder)

Part No.: I _.J,_'O._'-'-¢_" Lot No.:

A. Erosion (SORE) ?

B. Heat Affect (HASOR)?

C. Cuts, Assembly/Disassembly Damaga (SCUT, SDMG, SDIS)?

If any of the above conditions exist, record below:

I. 5¢c o-r_ _b_¢_,,_o,J _o_-h

Yes

Yes

Yes

V/'No

7 No

No

Comment

Number

m

m

_/__

CLOSURE SCREW O-RING

Part No.: Lot No.:

A. Erosion (CORE)?

B. Heat Affect (HACOR)?

C. Cuts, AssemblylDisassembly Damage (CCUT, CDMG, CDIS)?

If any of the above conditions exist, record below:

Yes No

Yes No

Yes No

Comment

Number

REV.

DOC

NO.

SEC

TWR-17591 IvoL IV

I p^_E A- 70
Morton Thiokoi Inc.

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

Date_-13-._ Insp.otor(,)_co'H Ed,._.

Motor No. Qt'_-_ _L_AP-.¥ M_I__,;_

Joint (Or I_and Degree): _0_°_ "_¢ A

O-Ring Location: [] Prtma%,_.Secondary [] Capture Feature Part Number ! USOr_,_,

Serial or Lot Number:

Description: _P__ _l::>P_. t o LL) m

R_I(,., /ks/_.

!

[] Wiper [] Closure

I

Sketch observation below or attach worksheets and list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation,

I'

Id

t_

l,

I

!

I

,.2

i

o.4. EXT,QUJIoA/ .Z'. _. E X TIt I.),.Cl OX./

REV.

DOC

NO, TWR-17591 vc¢ IV

sEc [PAGE A-71
Morton Thiokol Inc.

Space Operations

Motor No. :

Joint:

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheet

_ - _ I Date:_- 13 - _/

S&A to Adapter (S&A) " I--'] Adapter to Case (IGN) [] Adapter to Chamber (IGI)

Plug: _.Leak Check(LEAK} Degree _)__.._ _-_ _,_"

PRIMARY O-RING ' - l /

Part No.: ( (,,)__c£)p,_.,__ -- (_' Lot No.:

A, Erosion (PORE)?

B, Heat Affect (HAPOR)?

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

hJOTE" T_iS 6bscr_-io _J '_S _"or

pr i_,-,/ s_a[s.

I ?t ° ,a _ ,4 I q .9 °

Comment

Number

Yes L// No

Yes b/' No

Yes b/' No

6o4-h S-__T _u_ts j

SECONDARY O-RING (or Shoulder)

Part No.: I O._"O.c.qc_--_'_ _" Lot No.:

A. Erosion (SORE)?

B. Heat Affect (HASOR)?

C. Cuts, Assembly/Disassembly Demaga (SCUT, SDMG, SDIS)?

If any of the above conditions exist, rec3rd below:

14 oT E : TI_ S _bs< _ w, _-io _J

riu%s , S_oOCt_r' I

Comment

Number

Yes _ No

Yes J No

Yes _ No

_o4 h S'r_T_

CLOSURE SCREW O-RING

Part No.: Lot No.:

A. Erosion (CORE) ?

B. Heat Affect (HACOR)?

C. Cuts, Assembly/Disassembly Damage (CCUT, CDMG, CDIS)?

If any of the above conditions exist, record below:

Yes No

-Yes No

Yes No

Comment

Number

REV.

OOC

NO. TWR-17591 Ivo(. IV

sEc I F,A_EA-7Z
/

0

Morton Thiokol Inc.

Space Operations

Case Joint Plug and Plug Hole - Evaluation Checkoff Worksheet

i |1 i i

Motor No.: (_) _- _/ I Date: Z. --_,- _'_;_

Inspector(l): ,J_, /'_. _C.

• i i i i

Joint:

[] Forward Field Joint (851.6, FWD) [] Center Field Joint (1171.5, CTR)

[] Aft Field Joint (1491.5, AFT) [] Nozzle-to-Case Joint (1875.2, NOZ)

i,

Plug: [] Vent Port (VENT) [] Leak Check (LEAK) [ Degree Location: /

|

c--

I

Plug, plug hole obeervatlonl:

Lot Number: EC'/. _::_ :L

I. Soot Pest Seals(SPINS, SICOR, SOINT,

SPINT, SIPOR, SPPOR SISOR, SPSOR)?

II. Foreign Material (FMIJ)?

Yea

Yes

No

No

IlL Heat Affected Plug (HAPOR0 HASOR, HACOR)?

IV. Rust on sealing surfaces (SSCOR)?

V. Rust on metal parts (PITCO)?

VI. Damaged metal sealing surface (SSMET)?

VII. Damaged metal other than sealing surface (DAMML)?

1111.Plug hole damage, deformed threads (DBHOL)?

If any of the above conditions exist, describe below:

Yes

Yee

Yes

Yea

Yes

Yes

No

,--_No

v/ No

No

No

No

Comment

Number

m

m

REV.

DOC

No. TWR-17591

$EO
Morton Thiokol Inc. SE"

Space Operations

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheet

Motor No.: c/_/t/_:_

Joint: F_ FWD F-1 CTR E1 AFT [] NOZ

Plug: ,_ Vent Port(VENT) [] Leak Check(LEAK)

/ •

r

J Date: _ i-'=-E_., _'_

Inspector(s): J-_Cc_-_ Z--_*'-,--

(

/

PRIMARY O-RING

Part No.: l{2_.2_F_/- /J_ Lot No.:

(

A. Erosion (PORE)?

B. Heat Affect (HAPOR)?

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

Degree , /5_"

m

L11"_es No

Comment

Number

t/f

SECONDARY O-RING (or Shoulder)

Part NO.: I('_<_c, Z2-_- /...5 Lot No.: _CL. CV'2.._..._

A. Erosion (SORE)?

Heat Affect (HASOR)?

Cuts, Assembly/Disassembly Damage (SCUT, SDMG, SDIS)?

If any of the above conditions exist, record below:

J

Yes No

Yes /No

Y • s _I_No-'_

Comment

Number

CLOSURE SCREW O-RING

Part No.: I(J_C 2 "Z.._'- "_-- Lot No.: _'CL C_'._/_., q"

A. Erosion (CORE)?

B, Heat Affect (HACOR)?

C. Cuts, AssemblyDisassembly Damage (CCUT, CDMG, CDIS)?

If any of the above conditions exist, record below:

Yes

m

Yes

m

Yes

m

(I1 No

b j No

No

Comment

Number

REV.

D_

No TWR-17591 i VOL IV

sEc I _,*oE A-74
Morton Thiokol Inc. .3E

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

Motor No. ('-Y/'1 "_' /

Joint (Or Plug and Degree): J._,_" _ t_i)D t_C_

O-Ring Location; L_Primary [] Secondary [] Capture Feature

Part Number: /L_O'_ - _/_"

Serial or o_tt_mber: _C L C_ :Pf/

Description:

[] Wiper [] Closure

Sketch observation below or attach worksheets and list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation.

I i

il

P._ /_4_ y

O. 0. E¢7"au,;_,J ,z'.o. ExT_aJtO_,

REV.

ooc TWR-17591 I

NO. , I VOL

IV

sEc JPAQE A-75
Morton Thlokol Inc.

Space Operations

Case Joint Plug -,nd Plug Hole - Evaluation Checkoff Workaheet

i

Motor No.: (_/W- _ I Date: 2--_.- _"

Inspector(s): /_'. (_,_cf

i

Joint:

[] Forward Field Joint (851.5, FWO)

[] Aft Field Joint (1491.5, AFT)

[_ Center Field Joint (1171.5, CTR)

[] Nozzle-to-Case Joint (1875.2, NOZ)

I

Plug: {_ Vent Port (VENT) [] Leak Check (LEAK) I Degree Location: ('_'-

P/N: /_/( "7_, _?- S'- -0 3 Lot Number: £c_.o_p_/

Plug, plug hole observations:

I. Soot Past Seals(SPINS, SICOR, SOINT,

SPINT, SIPOR, SPPOR SISOR, SPSOR)?

II. Foreign Material (FMIJ)?

III. Heat Affected Plug (HAPOR, HASOR, HACOR)?

IV. Rust on sealing surfaces (SSCOR)?

V. Rust on metal parle (PITCO)?

VI. Damaged metal sealing surface (SSMET)?

VII. Damaged metal other than aeallng surface (DAMML)?

/llh Plug hole damage, deformed threads (DBHOL)?

i

If any of the abova condllions exist, describe below:

Yes

Yes

Yes

Yes

Yes

Yes

Yes

Yes

J" No

No

_/ No

:7" No

J No

No

No

L_ No

Comment

Number

REV.

DOO

No. TWR-17591 IVOL IV

.o IP;,,o,:A-76
lVlorton Thiokol Inc. -YE

Space Operations

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheet

Motor NO.: _t)t,t,_-_ I Date: _;_ FE_ oc'?

Joint: I'-'1 FWD I_ CTR _ AFT ['7 NOZ

Ptug: [_ Vent Port(VENT) [] Leak Check(LEAK) Degree /3 _" _

Inspector(s): ."._Cc{_ _e/'e-,1 ,' Foc_/_?, //_Z', I (To,'y 6,_/S_'_,'1 PRIMARYO-RING 1

ear,No: It S 2Z - q LotNo.:

A. Erosion (PORE)? _ Yes _No

B. Heat Affect (HAPOR)? _ Yes if No

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)? Yes L'-/ No

If any of the above conditions exist, record below:

Comment

Number

f.

SECONDARY O-RING (or Shoulder)

Part No.: [L!__O'L,_ _ I._ Lot No.: EC (__- _9C,_'.._

A. Erosion (SORE)?

Heat Affect (HASOR)?

Cuts, Assembly/Disassembly Damage (SCUT, SDMG, SDIS)?

If any of the above conditions exist, record below:

Yes _ No

Yes No

Yes _ No

Comment

Number

CLOSURE SCREW O-RING

=art No.: IO_;oz z% - LS Lot No.: _--CL ('C'Ot/.._

A, Erosion (CORE)?

B. Heat Affect (HACOR)?

C. Cuts, Assembly/Disassembly Damage (CCUT, CDMG, CDIS)?

If any of the above conditions exist, record below:

Yes '-// No

Yea _ No

Yes _ No

Comment

Number

REV.

DOC NO. TWR-17591 , IVOL IV

sEc J.^oE A-77
Morton Thiokol Inc.

Space Operations

Case Joint Plug end Plug Hole - Evaluation Checkoff Worksheet

Motor No.: _ r_- _" l Date: Z.- _,- rY

Inspector(s): g,. I___-_. _

I

Joint:

[] Forward Field Joint (851.5, FWD) [] Center Field Joint (1171.5, CTR)

[] Aft Field Joint (1491.5, AFT) [] Nozzle-to-Case Joint (1875.2, NOZ)

Plug: [_].Vent Port (VENT) [] Leak Check (LEAK) I Degree Location: /

P/N: I _ _ _'Z,_'-- O 3 Lot Number: £'¢Z.ODO_

Plug, plug hole observations:

L-'_No I. Soot Past Seals(SPiNS, SICOR, SOINT, Yea

SPINT, SIPOR, SPPOR SISOR, SPSOR)?

II. Foreign Material (FMIJ)? Yes No

III. Heat Affected Plug (HAPOR, HASOR, HACOR)? __ Yes vfNo

IV. Rust on sealing surfaces (SSCOR)? Yes _ No

V. Rust on metal parts (PITCO)? Yes _._ No

VI. Damaged metal sealing surface (SSMET)? Yes Y'_No

VII. Damaged metal other than sealing surface (DAMML)? "--'''''_ Yes No

1111.Plug hole damage, deformed threads (DBHOL)? Yes ,-"'f No

Comment

Number

If any of the above conditions exist, describe below:

DOO

Rev. No. TWR-17591

SEO 'i

PAGE

IVOL IV

A-78
Morton Thiokol Inc. .3_

Space Operations

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheet

Motor No.: _/_yl,?,lJoint: [--] FWD _ CTR

Plug:. _] Vent Port(VENT}

Inspector(s): <_c¢,_/ _o/_-<-_

PRIMARY O-RING

Part No.: (C._C2 2 _- L_y

A. Erosion (PORE) ?

B. Heat Affect (HAPOR) ?

I Date: G ,_ 8_

[]_ AFT , [-I NOZ

[_ Leek Check(LEAK) Degree

,, ,, !

Lot No.: C_/,C CCO/_ ,'/

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

See t_7771cd(b .5(/c_ _-

13j-" _"

Yes No

Yes L_No

L.._ f Yes No

Comment

Number

JJ

SECONDARY O-RING (or Shoulder)

Part No.: 1 L')SOZ 2-_" - t5 Lot No.: _.C/..- Cm.O_

A. Erosion (SORE)?

Heat Affect (HASOR)?

Cuts, Assembly/Disassembly Damage (SCUT, SDMG, SDIS)?

If any of the above conditions exist, record below:

J

Yes No

Yes No

Yes _ No

Comment

Number

CLOSURE SCREW O-RING

Part No.: /C_50_7_/- _-..._ Lot No.: _-_L_ C"_/_

A, Erosion (CORE)?

B. Heat Affect (HACOR)?

C. Cuts, AssemblylDisassembly Damage (CCUT, CDMG, CDIS)?

If any of the above conditions exist, record below:

4 t_(,_ (_.,_L / (---" ii

_tO#

Yes _ JNo

Yes

Yes .__ NO

o-FComment

Number

REV.

Dec

NO. TWR-17591 I VOL IV

sec JP,,,,oeA:79
Morton Thiokol Inc. "7e"

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

Date _" / ( _ (_'_ Inspector(s) .,,_'¢c. _ _'_/_,_ , r/_"

Motor No. (,_1__ !

Joint (Or___ and Degree): /_._ _ _ _i6L_

O-Ring Location: l_Primery [-']Secondary [] Capture Feature f--iWiper

Part Number; L//cJ

Serial o_!um_ber: L _T,_

Description:

(u" //{

¢

[] Closure

Sketch observation below or attach worksheets end list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation.

i_,

!

!

i i

• n

- !

L

i !

I

C

G X 1_t5 I'0 ;tl

i i

I

I

I

I

I

I

I

I

REV.

Dec

NO. TWR-17591 I VOL IV

sEc I P^GE A-80
Morton Thiokol Inc. -S'6"

Space Operations

Case Joint Plug and Plug Hole - Evaluation Checkoff Worksheet

Motor No.: ["_/tI_ _)2 I Date: 13 F_./_ _-,_"

Inspector(s): I_-_/_b/ I)j-.,_ FO Lc_ -_'-{_- C.---

Joint:

[] Forward Field Joint (851.5, FWD) [] Center Field Joint (1171.5, CTR)

[] Aft Field Joint (1491.5, AFT) _ Nozzle-to-Case Joint (1875.2, NOZ)

Plug: _'Vent Port (VENT) [] Leak Check (LEAK) Degree Location: /_.,_e

P/N: IU_LI'UG - (.D2j Lot Number: E:(,_Looor

Plug, plug hole observations:

I. Soot Past Seals(SPINS, SICOR, SOINT,

SPINT, SIPOR, SPPOR SISOR, SPSOR)?

II. Foreign Material (FMIJ)?

III. Heat Affected Plug (HAPOR, HASOR, HACOR)?

IV. Rust on sealing surfaces (SSCOR)?

V. Rust on metal parts (PITCO)?

VI. Damaged metal sealing surface (SSMET)?

vii. Damaged melel other then sealing surface (DAMML)?

/111. Plug hole damage, deformed threads (DBHOL)?

Yes

Yes

Yes

Yes

Yes

Yes

Yes

Yes

Comment

Ct N.._oNo Number

,--_N o

_ No

If any of the above conditions exist, describe below:

RE\'.

DOC

NO. TWR-17591

SEC

VOL IV

IPAGE A-81
Morton Thiokol Inc. _d"

Space Operations

Detailecl Port Plug OLring (Post-Removal) - Evaluation Checkoff Worksheet

Motor No.: /'_//,1 - _

Joint: E] FWD [] CTR _ AFT ,_ NOZ

Plug: _] Vent Port(VENT) [] Leak Check(LEAK) Degree

Inspector(s): . Jc_Y'( _cw'_,_ /_°r--e/'-, ," /_'_4 C'_,,

PRIMARY O-RING" / / / )/

Part No.: ((1_C__-?_'_-ct/y Lot No.: _'.C'L (_(')C_-_,

A. Erosion (PORE)?

B. Heat Affect (HAPOR)?

C. Cuts, Assembly/Disassembly Damage (PCUT. PDMG, PDIS)?

if any of the above conditions exist, record below:

_ . -[yP((._(_ O. b _ I. ,D. (YFCu,/_sF(_c_W-r_(-

[ Date: /? _--_'8 _;

Yes L_ No

Yes /-_'_NNo

Yes No

Commenl

Number

//¢

SECONDARY O-RING (or Shoulder) Comment

Part No.: IL)._(D_-?_ /E Lot No.: _C,,(._ 005_ C_N ° Number

A. Erosion (SORE)? Yes _

' Heat Affect (HASOR)? Yes _flNo

Cuts, AssemblyDisassembly Damage (SCUT, SDMG, SDIS)? __ Yes _-----_o

If any of the above conditions exist, record below:

/ f2 ,( Ho - oPt,l/.

_(E ,#rTdC//E!3 CI,q#; F-/c _ I / (_J_/ 5/'/6_,_>"

CLOSURE SCREW O-RING

Part No.:. IL_072_;_.-2_ Lot No.: _"CC_ CO/_-

A. Erosion (CORE)? /

B. Heat Affect (HACOR)?

C. Cuts, Assembly/Disassembly Damage (CCUT, CDMG, CDIS)?

If any of the above conditions exist, record below:

Comment

Yes L_N ° - Number

Yes _/No

Yes _o

REV.

DOC

NO. TWR-17591 I VOL IV

s=c I PAaE A-82
Morton Thiokol Inc.

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

MotorNo. (l?l 

O-Ring Location: [] Primary ,_ Secondary [] Capture Feature

Part Numbe¢: /L'J*O'_? K -/__"

Serial or o_._Number: Z-'Cc C'_O,._

Description:

[]Wiper [] Closure

Sketch observation below or attach worksheets and list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation.

xj@ T'_"."

L _ O. Ioo

i,j _ o. ooZ

O _ O.C_OI

Figure B-3

REV.

Dec

NO. TWR-17591

SEC

, IVOL IV

[P^_E A-83
l_lorton Thiokol Inc.

Space Operations

Nozzle Joint Plug and Plug Hole - Evaluation Checkoff Worksheet

Inspector(s): ,_- LC _ F_/_7/dEt_:'_ r dc'rz_"_z(---

Motor No.: _]11/'- _:_

Jc'zAC-_//

I D,te. .S'?

Joint: [] ThroatlFwd Exit Cone (4)

[] Fixed Housing/Aft End Ring (5)

,J_ Fwd Exit Cone/Aft Exit Cone (1)

Degree Location: _, _ P/N: ] C/SC')) E _'- 02-

[] Fwd End Ring/Nose Inlet (2)

[] Nose Inlet/Throat (3)

=' <V

de-Lcc_ W

O-ring: P/N: / _5o z2_- ZS

Plug, plug hole observations:

I. Soot Past Seals(SPINS, SICOR, SOINT,

SPINT, SIPOR, SPPOR SISOR, SPSOR)?

II. Foreign Material (FMIJ)?

III. Heat Affected Plug (HAPOR, HASOR, HACOR)?

IV. Rust on sealing surfaces (SSCOR)?

V. Rust on metal parts (PITCO)?

VI. Damaged metal sealing surface (SSMET)?

VII. Damaged metal other than sealing surface (DAMML)?

VIII. Plug hole damage, deformed threads (DBHOL)?

Yes t_No

Yes

Yes

Yes c_'_No

Yes

Yes /._NN o

Comment

Number

If any' of the above conditions exist, describe below:

REV.

DOC No. TWR-17591 I VOL IV

IpAGEA-84
Morton Thiokol Inc. .3_

Space Operations

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheet

Motor No.: /#i[- _'

Joint:

I Date: _, xT;_ _y

[] ThroatlFwd Exit Cone (4)

[] Fixed Housing/Aft End Ring (5)

_Fwd Exit Cone/Aft Exit Cone (1)

[] Fwd End Ring/Nose Inlet (2)

[] Nose Inlet/Throat (3)

Plug: ;_] Leak Check(LEAK) Degree _-_Z , .5 n

Inspector(s): '_-ef_---- _dej _ /. _._._/_(

PRIMARY O-RING /

Part No.: Lot No.:

A. Erosion (PORE) ?

B. Heat Affect (HAPOR)?

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

Yes

Yes

Yes

Comment

Number

No

No

No

SECONDARY O-RING (or Shoulder)

Part No.: IIJ_O2Z_-ZS Lot No.: ECL- _@/2--

A. Erosion (SORE) ?

B. Heat Affect (HASOR)?

C. Cuts, Assembly/Disassembly Damage (SCU'T, SDMG, SDIS)?

If any of the above conditions exist, record below:

SeE _4.--r_<(Ye_ C(..4_F'-/ C_ Z-cc'./tJ

i

Yes

_f S/'/( -( e

No

Comment

Number

CLOSURE SCREW O-RING

Part No.: Lot No.:

A. Erosion (CORE) ?

B. Heat Affect (HACOR)?

C. Cuts, Assembly/Disassembly Damage (CCUT, CDMG, CDIS)?

If any of the above conditions exist, record below:

Yes

Yes

Yes

No ,

No

No

Comment

Number

REV.

DOC

NO. TWR-17591

SEC

IVOL IV

[PAar A-85
lVlorton Thiokol Inc.

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

[] Closure

, .,_Jci-(- ;

Sketch observation below or attach worksheets and list below. Indicate orientation and dimensions,

Show as much detail as necessary to explain the observation.

6--- o. z._o--.-q

PE='EFENCE

-T'-{L C.JJT1

L_. OoZYO

REV.

DOe No TWR-17591 l VOL IV

sEc IPAGEA-8E
Morton Thiokol Inc. A"_"

Space Operations

Nozzle Joint Plug and Plug Hole - Evaluation Checkoff Worksheet

,nspector(s):k lly

Motor No.:

Joint: []ThroatlFwd Exit Cone (4)

[] Fixed Housing/Aft End Ring (5)

I-I Fwd Exlt Cone/Aft Exit Cone (I)

[ Date: 2 - /._-'- if7

[_ Fwd End Ring/Nose Inlet (2)

[] Nose Inlet/Throat (3)

Degree Location: _t_ • Z_" P/N: t_spl_ -0 _

O-ring: P/N: { L45Z)27-_ -- _ _

S/N: _CLL;_Q_

L/N: EC/.. coC>_

Plug, plug hole observations:

I. Soot Past Seals(SPINS, SICOR, SOINT,

SPINT, SIPOR, SPPOR SISOR, SPSOR)?

II. Foreign Material (FMIJ)?

III. Heat Affected Plug (HAPOR, HASOR, HACOR)?

IV. Rust on sealing surfaces (SSCOR)?

V. Rust on metal parts (PITCO)?

VI. Damaged metal sealing surface (SSMET)?

VII. Damaged metal other than sealing surface (DAMML)?

VIII. Plug hole damage, deformed threads (DBHOL)?

Yes

Yes

Yes

Yes

Yes

Yes

Yes

Yes

No

No

No

No

No

vf No

No

_'_ No

Comment

Number

If any of the above conditions exist, describe below:

REV.

boo TWR-17591 NO. I VOL IV

sEc I P^OE A-87
Morton Thiokol Inc. ,._

Space Operations

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheet

Motor No.:

Joint: _ [] ThroatlFwd Exit Cone (4)

[] Fixed Housing/Aft End Ring (5)

[] Fwd Exit Cone/Aft Exit Cone (1)

I Date: 17 FE8 _'_

_LFwd End Ring/Nose Inlet (2)

[] Nose Inlet/Throat (3)

Plug: [] Leak Check(LEAK)

Inspector(s): _C _'/:/ _-_e_

PRIMARY O-RING

Part No. :

A. Erosion (PORE) ?

B. Heat Affect (HAPOR)?

Degree Z_'5, ,_ _

Lot No.:

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

z.7

Yes

Yes

Yes

Comment

Number

No

No

No

SECONDARY O-RING (or Shoulder)

Part No.: 1_02_2",._ - ZE3 Lot No.: EC L _(-r@ __

A. Erosion (SORE) ?

B. Heat Affect (HASOR)?

C. Cuts, Assembly/Disassembly Damage (SCU'I', SDMG, SDIS)?

If any of the above conditions exist, record below:

Yes J No

Yes _ No

Yes _o

Comment

Number

5/z A t' G 6 c t'6.

CLOSURE SCREW O-RING

Part No.: =.or No.:

A. Erosion (CORE)?

B. Heat Affect (HACOR)?

C. Cuts, Assembly/Disassembly Damage (CCUT, CDMG, CDIS)?

If any of the above conditions exist, record below:

Comment

Number

Yes No

Yes No

Yes No

REV.

DOC

NO.

SEC

TWR-17591

IP^aEA-88
Morton Thiokol Inc.

Space Operations

_re

Nozzle Joint Plug and Plug Hole - Evaluation Checkoff Worksheet

Inspector(s):

Motor No.:

Joint:

)

[] Throat/Fwd Exit Cone (4)

[] Fixed Housing/Aft End Ring (5)

[] Fwd Exit Cone/Aft Exit Cone (1)

I Date: ?--.-/_--_ff"

[] Fwd End Ring/Nose Inlet (2)

[] Nose Inlet/Throat (3)

Degree Location: 2._ P/N: I_C > I ._'_- t)z. S/N: ]:EL, Oo_:_ "1

O-ring: P/N: //_'bZ.29'_ 25"" L/N: ECt. &_ "r

Plug, plug hole observations:

I. Soot Past Seals(SPINS, SICOR, SOINT,

SPINT, SIPOR, SPPOR SISOR, SPSOR)?

II. Foreign Material (FMIJ)?

III. Heat Affected Plug (HAPOR, HASOR, HACOR)?

IV. Rust on sealing surfaces (SSCOR)?

V. Rust on metal parts (PITCO)?

VI. Damaged metal sealing surface (SSMET)?

VII. Damaged metal other than sealing surface (DAMML)?

VIII. Plug hole damage, deformed threads (DBHOL)?

Yes

Yes

Yes

Yes

Yes

Yes

Yes

Yes

J No

v/

No

No

7 No

v_ No

,1 "_ No

_'f'No

,1"No

Comment

Number

If any of the above conditions exist, describe below:

t_p- 3 I

REV.

DOC

NO. TWR-17591 I VOL IV

see I_A_ A-89
Morton 'lhiokol Inc. .-,g.

Space Operations

Motor No. :

Joint:

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheet

L'_ltl-_, I Date: _7 "/r'-C"a_

_ [] Throat/Fwd Exit Cone (4) [] Fwd End Ring/Nose Inlet (2)

[] Fixed Housing/Aft End Ring (5) _]"Nose Inlet/Throat (3)

[]Fwd Exit Cone/Aft Exit Cone (1) k

Plug: [_] Leak Check{LEAK) Degree _L.-S-o

Inspector(s): ,_mT// /-Jc..._t, /_oc "St //_'_ _'_d,Ay

PRIMARY O-RING _ /

Part No.: Lot No.:

A. Erosion (PORE)?

B. Heat Affect (HAPOR)?

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

Yes

Yes

Yes

Comment

Number

No

No

No

SECONDARY O-RING (or Shoulder)

Part No.: IlJ,_C2:-z_- Z,._ Lot No.: _L _ L 0C3/3

A. Erosion (SORE) ?

B. Heat Affect (HASOR)?

C. Cuts, Assembly/Disassembly Damage (SCU'T, SDMG, SDIS)?

If any of the above conditions exist, record below:

Yes

Yes

Z Yes

Lo t, _. C I_c_ -',_`-_,F_fec,,.fT-/.,ee.__

5c._//-7 c-/-/- L/.,SD/5_

5_c ATT--#C/,'(D _ C_...t,'Z/F,'cAT,,'c,,,_

c'"/No

c..--_No

No

Comment

Number

J#

CLOSURE SCREW O-RING

Part No,: I.ot No.:

A. Erosion (CORE)?

B. Heat Affect (HACOR)?

C. Cuts, Assembly/Disassembly Damage (CCUT, CDM(31 CDIS)?

If any of the above conditions exist, record below:

Yes

Yes

Yes

Comment

Number

No

No

No

REV.

DOC

NO,

SEC

TWR-17591
Morton Thiokol Inc. 3_e

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

Date ( ? ('_ _ ,t_'_ Inspector(s) Set"//-7 L _{,/e-.-, _'cc _ ,//_ / _"_7'

Motor No. _:_{-_._ 'J /

Joint (Or Plug and Degree): _G5 ° ._O/,-t,"

O-Ring Location: [] Primary __ Secondary

Par! Number: ./ Z _._ _ -Z _-_ - 2 _'--

Serial or Lot Number: 7:C/- c'_O/3

Description:

[] Capture Feature []Wiper [] Closure

Sketch observation below or attach worksheeta and list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation.

_E •J','_,4 r'£ $.#

I. _ a. _t,$'o

lu _: 0.002

#.o.Ool

REV.

DOC

No TWR-17591 I vo, IV

sEc I P,aE A-91
Morton Thiokol Inc.

Space Operations

J-c

Nozzle Joint Plug and Plug Hole - Evaluation Checkoff Worksheet

Inspector(s): ,,_. ___,r-, i _. /t,J_\__4v

Motor No.: _ r_/_-

Joint: []Throet/Fwd Exit Cone (4)

[] Fixed Housing/Aft End Ring (5)

[] Fwd Exit Cone/Aft Exit Cone (1)

I Date: Z-/_'-'_" _"

[] Fwd End Ring/Nose Inlet (2)

[] Nose Inlet/Throat (3)

Degree Location: 7_.(,.8.'75- P/N: ..! Lt _'Ot_'_-_ S/N: EeL #G#-z.

O-ring: P/N: t _ _'0_ "z"_ - "t.._ L/N: /_'-CL 0_,/_"

Plug, plug hole observations:

I. Soot Past Seals(SPINS, SICOR, SOINT,

SPINT, SIPOR, SPPOR SISOR, SPSOR)?

II. Foreign Material (FMIJ)?

III. Heat Affected Plug (HAPOR, HASOR, HACOR)?

IV. Rust on sealing surfaces (SSCOR)?

V. Rust on metal parts (PITCO)?

VI. Damaged metal sealing surface (SSMET)?

VII. Damaged metal other than sealing surface (DAMML)?

VIII. Plug hole damage, deformed threads (DBHOL)?

m

m

m

Yes

Yes

Yes

Yes

Yes

Yes

Yes

Yes

No

No

J No

No

t._ No

_----'_No

No

_---"_No

Comment

Number

If any of the above conditions exist, describe below:

REV.

DOC

No. TWR-17591 I VOL IV

sEc J_,_GE_,-92
Morton 'lhiokol Inc.

Space Operations

Detailed Port Plug O-ring (Post-Removal) - Evaluation Checkoff Worksheet

Motor No.: _"_'tl- c, (o I Date: /5 FE._ _>9

Joint: _ ,_Throat/Fwd Exit Cone (4) [] Fwd End Ring/Nose Inlet (2)

[] Fixed Housing/Aft End Ring (5) [] Nose Inlet/Throat (3)

[] Fwd Exit Cone/Aft Exit Cone (1)

Plug: _Leak Check(LEAK I

Inspector(s): _ct. /J _/'c,-7 /

PRIMARY O-RING

Part No. :

A.. Erosion (PORE)?

B. Heat Affect (HAPOR)?

Degree "_L(_/(:_. 2[; _'

Lot No.:

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

Yes

Yes

Yes

Comment

Number

No

No

No

SECONDARY O-RING (or Shoulder)

Part No.: (L?_C_Z?_ _- 2 _ Lot No.: _"_-Cl' CnC"_/?___._

A. Erosion (SORE) ?

B. Heat Affect (HASOR)?

C. Cuts, Assembly/Disassembly Damage (SCU1, SDMG, SDIS)?

If any of the above conditions exist, record below:

Yes _J/No

Yes c"1_N o

Yes

Comment

Number

CLOSURE SCREW O-RING

Part No.: Lot No.:

A. Erosion (CORE) ?

B. Heat Affect (HACOR)?

C. Cuts, Assembly/Disassembly Damage (CCUT, CDMG, CDIS)?

If any, of the above conditions exist, record below:

Yes No

Yes No

Yes No

Comment

Number

REV.

DOC

NO. TWR-17591 IVOL IV

sEc I PAGe A-93
•';'',.,,k.l" _.',.'' ; "-I{IF_IP.-U--'- [|IF_.,.. ...............

Space Operations

Table D-II

Detailed Port Plug O-ring or Small O-ring (A-2) - Evaluation Checkoff Worklheet

Inspector(s): -._co7"7" _"_"_, ,_OCA._y ,_J'A/

Motor No.: Z_.,4_'-,,_ I Dale: ,/V @-_nG "_P

Side: r-]Left (A) [] Right (B).lJolnh F'O,,_cj_.I_ c/o_/¢,¥/ ,re_ _/'_.'_OPy

Plug: [] Vent Port L_-Leak Check O"TrBnsducer O Special Bolt Plug

[] Special Bolt [] Degree O ='

IL)IO02,6 9- 01 ECL 0 0 22.

PRIMARY O-RING N/A: !/'

Part No.: Lot No.:

A. Erosion (PORE)?

B. Heat Affect (HAPOR)?

C. Cuts, Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of Ihe above conditions exist, record below:

Yeg

Yes

Yes

Comment

Number

No

No

No

SECONDARY O-RING (or Shoulder) N/A: Commer

CLOSURE SCREW O-RING N/A:

Part No.: Lot No.:

A. Erosion (SORE) ?

B. Heat Affect (HASOR)?

C. Cuts, AegemblylDi_aeeembly Damage (SCUT, SDMG, SDIS)?

If any of the above conditions exist, record below:

Yes No

Yes No

Yes No

Comment

Number

REV.

DOC

NO. TWR-17591

SEC

IV
lVIorton Thiokol Inc.

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

Date

Motor No. (P_-_

Joint (Or(_and Degree): _)o FUJD

O-Ring Locat!on: [] Primary __Secondary

Part Number: J U_(_,-_,-.,___-I.-_

Serial or Lot Number: _'__J_ OC)_>-_

Description: Scc _'_'JP' | c_ t_ .

Inspector(s) SC_(3J_Jr EdP__k3/ R(:_(._k y

FAC']_ y T_, _JT

[] Capture Feature ['-]Wiper [] Closure

K_ o TE, :

("L; :_-_| _ E a,J qr 0,3 I:>I uq.

-- " " 0 O 1 LI

G.b.

Sketch observation below or attach worksheets and list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation.

_. _ • CIRcU_ F._RE_r/dL

REV.

DOC No. TWR-17591

sec I PAGE A-95
_LVltUil xi_i-OKOtInC. - ..............

Splice Operalions

Table D-II

Detailed Port Plug O-rlng or Small O-rlng (A-2) - Evaluation Checkoff Work0heet

Inspector(g): .,Sco?'-T ,_-_ . AOOCA-"y .,,d,J',,Y'

Motor No.: (_,//,/,_Qo " JDate: /Y ,7"u.,e '8'?

S,d.:OLeft(A_ [] .,ght_S.),lJo,nt:C..._--.,--ro_._d =_//_r/_e_ _=_._.y J

Plug: [] Venl Port L._ Leak Check (--JTraneducer J_ Speclal_"Bolt Plug / J

[] Special Bolt [] Degree 0 u /MIOO2&9-OI _'CL.OO'3.3L.

PRIMARY O-RING N/A: v /

Part No.: Lot No.:

A. Erosion (PORE)?

B. Heat Affect (HAPOR)?

C. Culs. Assembly/Disassembly Damage (PCUT, PDMG, PDIS)?

If any of the above conditions exist, record below:

Yes No

Yes No

Yes No

Commenl

Number

Yes _ No

Yes v/ No

Yea No

Ye0 No

i

Yes No

Yes No

Comment

Number

Comment

Number

REV.

Dec

NO. TWR-17591 IVOL

A-96

IV

SEC I PAOG
Morton Thiokoi Inc.

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

pat. lt-_o-_ inspector(,) SCo4f E¢t¢_:

Motor No. (_. _- _"

Joint (Or(_ and Degree): O ° (-_'[_ AF'T FAC_OP_

O-Ring Location: [] Primary ]_econdary [] Capture Feature

Part Number: I (J._'Oo_o_-'l,'_) -

Serial or Lot Number: _J-C>C)___ 7

Description: __cC _)_ (c_ (J__.

!

TOl _'T

[]Wiper [] Closure

. doou u , - Oct-(: _>_o.. - " U u

Sketch observation below or attach w(_sheets and list below. Indicate orientation and dimensions.

Show as much detail as necessary to explain the observation.

\

_./R Q_ F'cr'.¢_",*.,r/,_

cb,,r

REV. ooo NO. TWR-17591 [vot. IV

SEC [ PAGE A-q7
Morton Thiokol Inc.

Space Operations

O-RING OBSERVATION CLARIFICATION FORM

Motor No. /_ _ Y _,_' IK 1_"IJ" '

Joint (Or I_)and Degree): _-_i--"_- _C_O P,_,¢td + --_C'_-_¢"V j ol _J¢'s

O-Ring Locat!on: [_]Primary" _Secondl(_ [":l Capture Feature/ r"]Wiper [] Closure

Part Number: _e_ be..Scr;_-l-/OK)

Serial or Lot Number: _rc b_-£C_ril_-I-iaO =

Description:

Lol _ ECL oC_q"'}" F_'_6LO t-I I

__T-i-F /A FT _OHE

I o .(d_ ,D.,_8- IS"

FCL Oo.3 I

Sketch obser ,ation below or attach worksheets end list below. Indicate orientation end dimensions.

Show as much detail as .necessary to explain the observation.

a: (.._,_ &¢b_) /t.ll_ I I=_,V" p=,._-;,, I ÷k,_aJ

¢_,=,1 .;,& el, I _ t.d ., .?p,.,.+ j,,_.

REFERENCE_ _

REFERENCE_

@

REFERENCE_

_.0. ¢_ltcu_¢r44ra/n4L _r

REV.

DOC

NO.

SEC

TWR-17591 Iv(x"

I PAGE A-98

IV