# Presentation: 808723

## Section 1

***Overview & Spacecraft Status***

*** ******. . . Mike Cully***
*Swales Aerospace, Inc.*

## Overview Agenda

***Overview Agenda***

***Scope of Review***
***Test Objectives***
***Spacecraft Status***
***Summary of WOA & Problem Reports***
***TV Staffing***

## Scope Of EO-1 Second T/V TRR

***Scope Of EO-1 Second T/V TRR***

***Demonstrate Readiness of all Subsystems to start T/V***
***Status of flight hardware and software***
***Short description of any changes since the last thermal vac test***
***Status of open problem reports***
***Trending plans***
***Work required before pump down***
***Status of critical limits in the ASIST database***
***Review of any critical procedure steps****** ***
***Provide Red Team members an intermediate report card on EO-1 status***
***To obtain review team concurrence to begin EO-1 Second T/V***

## Test Objectives

***Test Objectives***

***Further demonstrate EO-1 Subsystems in Thermal Vacuum  following significant de-integration activities (LVPC Fuse plugs, ACDS, GPS PCU, IRU, WARP, AST) ***
***Verify post T/V Flight Software Changes at operating temperature extremes***
***Increase confidence in hardware/software integration by substantially increasing Power on time for WARP & FSW***
***Perform CPTs at hot and cold plateaus***
***Perform Instrument Turn on Simulation***
***Further characterize ALI Outgassing and validate on-orbit procedure***
***Further develop MOC team capability for normal operations  ***
***Verify modifications to heater circuits at system level (verification performed at panel level)***
***Perform Spectral Registration Comparison for Hyperion & LEISA/AC (secondary objective)***

## Major Configuration Changes for T/V2

***Major Configuration Changes for T/V2***

***Change to smaller chamber (#225) required custom designed base plate and new GSE framing for Cryo panels and Heater panels***
***Static load test performed of new base plate***
***Fit check performed of frame during chamber certification***
***Thermal balance not required. Therefore GSE MLI to separate bays not required ***
***Minimal changes to cabling with exception to extensions for GPS, WARP monitor cable (frequency shift anomaly) and new Hyperion/AC Spectral Registration Comparison cables. Solar Array HOPS GSE cables replaced as result of Fusing changes***
***Use of Hyperion Heater Control GSE to allow better control of test heaters***

## Slide 6

## Spacecraft Status

***Spacecraft Status***

***Completed Post WARP integration CPT on May 26******th***
***CPT went extremely well with minimal issues (AST was simulated)***
***Completed Launch simulation Day 1 and Day 2 on June 6******th***
***Chamber Certification Completed on June 12******th***
***Spacecraft on Table, Wednesday June 14******th ******(dependant on SADA Cable repair)***
***EGSE to be setup around chamber #225 two days in advance of S/C on Table***
***SRC Materials received and in bakeout***
***S/C Roll in projected 6/20/00 (dependant on SADA Cable repair)***
***Start compress following completion of Functional (12 hours) + CPT0 (4 hours)***

## Pre-T/V II Activities

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## WOA Status

***WOA Status***

***Spacecraft I&T WOA Statistics ***
***Total number generated as 3/24/98 through 6/9/00 = 1064***
***Total number from 3/28/00 (RTR) = 112***
***Number Closed out =  1020 (96% closure rate)***
***Open Work Orders = 44 (TBR on 6/09/00)***
*Work In Process**	**	**= 4*
*Open PRs**	**	**= 16 (6/9/00)*
*Future Work**	**	**= 1*
*In Close Out Process **	**= 23*

## Problem Report Status

***Problem Report Status***

***Total number generated from 5/1/98 through 6/9/00 = 1619***
***Total number from 3/28/00 (RTR) = 47 (closed = 32)***
***Number closed out ITD =  1596 (98.6% closure rate)***
***Number open  =  23 (TBR on 6/9/00)***
***Work In Process******	******	******= 10***
***Test verification required ******	******= 2***
***In Closure Process******	******	******= 8***
***Red Book Items ******	******	******= 3***
*WOA 572 One Time Event observed Red Low Limits for bus chassis believed to be associated with SAS cable problem (GSE)*
*WOA 770-20-3 One Time Event Chassis Current during EMC Testing *
*WOA 837-20-1 One Time Event LVPC Current Red Limit*

## Open Problem Reports

## Solar Array Cable Damage

***Solar Array Cable Damage***

***Background***
***During final panel closeout inspections on June 6 a hair line mark (centered around three o'clock) was noticed on the 92 wire bundle that comes out of the SADA.***
***The hair line mark was further inspected and determined to be a cut of the insulation for seven wires.  The geometry of the cut indicated a razor or sharp object.  It must be noted that this cut was very difficult to see.  The location of the cut is approximately 0.75 inches off the face of the SADA interface which is approximately at the start of the bend radius for the cable bundle as it is folded up against the Solar Array Yoke. This obviously high stress area.***
***Under higher magnification it was determined that at least three wires had copper showing.  In addition oxidation has occurred indicating the damage was done some time ago.****** ***

## Solar Array Cable Damage

***Solar Array Cable Damage***

***Background Continued***
***All seven wires were verified as follows:******>Connector Pin # Description - Function******>Cable Wrap J2 7 Inboard S/A panel structural ground******>Cable Wrap J2 37 Circuit 11+ (outboard panel fixed string)******>Cable Wrap J2 19 Circuit 4- (Outboard panel, shuntable)******>Cable Wrap J2 38 Guard (ground wire shield for CSS)******>Cable Wrap J2 14 Guard******>Cable Wrap J2 42 Guard******>Cable Wrap J2 27 Coarse Sun Sensor 2+***
***There is currently 5 spare wires in this cable system***