International Space Station ISS/Shuttle Joint Operations ... · JSC-48503-5A.1 International Space...

JSC-48503-5A.1

International Space Station

ISS/Shuttle Joint Operations

Book

ISS-5A.1

Mission Operations Directorate

Operations Division

Final

November 2, 2000

National Aeronautics andSpace Administration

Lyndon B. Johnson Space CenterHouston, Texas

United StatesSystems Operations Data File JSC-48503-5A.1

INTERNATIONAL SPACE STATION

ISS/SHUTTLE JOINT OPERATIONS BOOK

ISS-5A.1

FINALNovember 2, 2000

APPROVED BY:

___________________________________________Anne M. Vaughan

Book Manager

_____________________________ _____________________________Joseph H. Cavallaro Debbie D. Stapleton

Lead, Cargo Support Operations Chief, Cargo Integration andGroup Operations Branch

___________________________________________Kent H. Adams

5A.1 SODF Coordinator

ACCEPTED BY:

___________________________________________Michael T. HurtSODF Manager

This document is under the configuration control of the Systems Operations DataFile Control Board (SODFCB).

United StatesSystems Operations Data File JSC-48503-5A.1

02 NOV 00 JNT OPSii

Incorporates the following:

CR: MULTI U166 JNT OPS U68

* - Omit from flight book

02 NOV 00 iii JNT OPS

INTERNATIONAL SPACE STATION

JOINT OPERATIONS BOOK - 5A.1

LIST OF EFFECTIVE PAGES

FINAL 02 NOV 00

Sign Off .......................... * 02 NOV 00ii ..................................... * 02 NOV 00iii..................................... * 02 NOV 00iv .................................... * 02 NOV 00v ..................................... * 02 NOV 00vi .................................... * 02 NOV 00

vii.................................... 02 NOV 00viii ................................... 02 NOV 001 ..................................... 02 NOV 002 ..................................... 02 NOV 003 ..................................... 01 NOV 004 ..................................... 01 NOV 005 ..................................... 01 NOV 006 ..................................... 01 NOV 007 ..................................... 01 NOV 008 ..................................... 01 NOV 009 ..................................... 01 NOV 0010 ................................... 01 NOV 0011 ................................... 01 NOV 0012 ................................... 01 NOV 0013 ................................... 31 OCT 0014 ................................... 31 OCT 0015 ................................... 31 OCT 0016 ................................... 31 OCT 0017 ................................... 31 OCT 0018 ................................... 31 OCT 0019 ................................... 31 OCT 0020 ................................... 31 OCT 0021 ................................... 31 OCT 0022 ................................... 31 OCT 0023 ................................... 31 OCT 0024 ................................... 31 OCT 0025 ................................... 01 NOV 0026 ................................... 01 NOV 0027 ................................... 31 OCT 0028 ................................... 31 OCT 0029 ................................... 31 OCT 0030 ................................... 31 OCT 0031 ................................... 31 OCT 0032 ................................... 31 OCT 0033 ................................... 31 OCT 0034 ................................... 31 OCT 0035 ................................... 02 NOV 00

36.................................... 02 NOV 0037.................................... 31 OCT 0038.................................... 02 NOV 0039.................................... 31 OCT 0040.................................... 02 NOV 0041.................................... 31 OCT 0042.................................... 02 NOV 0043.................................... 31 OCT 0044.................................... 31 OCT 0045.................................... 31 OCT 0046.................................... 31 OCT 0047.................................... 10 JUL 0048.................................... 10 JUL 0049.................................... 10 JUL 0050.................................... 10 JUL 0051.................................... 10 JUL 0052.................................... 02 NOV 0053.................................... 31 0CT 0054.................................... 31 0CT 0055.................................... 31 0CT 0056.................................... 31 0CT 0057.................................... 31 0CT 0058.................................... 02 NOV 0059.................................... 31 OCT 0060.................................... 31 OCT 0061.................................... 31 OCT 0062.................................... 02 NOV 0063.................................... 02 NOV 0064.................................... 02 NOV 0065.................................... 31 OCT 0066.................................... 02 NOV 0067.................................... 31 OCT 0068.................................... 02 NOV 0069.................................... 31 OCT 0070.................................... 02 NOV 0071.................................... 31 OCT 0072.................................... 02 NOV 0073.................................... 31 OCT 0074.................................... 02 NOV 0075.................................... 31 OCT 0076.................................... 31 OCT 0077.................................... 31 OCT 0078.................................... 02 NOV 00

02 NOV 00 JNT OPSiv

79 ................................... 31 OCT 0080 ................................... 31 OCT 0081 ................................... 31 OCT 0082 ................................... 02 NOV 0083 ................................... 02 NOV 0084 ................................... 02 NOV 0085 ................................... 31 OCT 0086 ................................... 31 OCT 0087 ................................... 10 JUL 0088 ................................... 10 JUL 0089 ................................... 10 JUL 0090 ................................... 10 JUL 0091 ................................... 10 JUL 0092 ................................... 10 JUL 0093 ................................... 01 NOV 0094 ................................... 02 NOV 0095 ................................... 31 OCT 0096 ................................... 31 OCT 0097 ................................... 31 OCT 0098 ................................... 02 NOV 0099 ................................... 02 NOV 00100 ................................. 02 NOV 00101 ................................. 31 OCT 00102 ................................. 31 OCT 00103 ................................. 31 OCT 00104 ................................. 31 OCT 00105 ................................. 31 OCT 00106 ................................. 02 NOV 00107 ................................. 10 OCT 00108 ................................. 10 OCT 00109 ................................. 10 OCT 00110 ................................. 10 OCT 00111 ................................. 10 OCT 00112 ................................. 10 OCT 00113 ................................. 31 OCT 00114 ................................. 31 OCT 00115 ................................. 02 NOV 00116 ................................. 02 NOV 00117 ................................. 31 OCT 00118 ................................. 02 NOV 00119 ................................. 31 OCT 00120 ................................. 31 OCT 00121 ................................. 31 OCT 00122 ................................. 02 NOV 00123 ................................. 31 OCT 00124 ................................. 02 NOV 00125 ................................. 31 OCT 00126 ................................. 02 NOV 00127 ................................. 31 OCT 00128 ................................. 02 NOV 00129 ................................. 12 SEP 00

130 .................................. 02 NOV 00131 .................................. 12 SEP 00132 .................................. 02 NOV 00133 .................................. 12 SEP 00134 .................................. 12 SEP 00135 .................................. 12 SEP 00136 .................................. 02 NOV 00137 .................................. 12 SEP 00138 .................................. 12 SEP 00139 .................................. 31 OCT 00140 .................................. 31 OCT 00141 .................................. 02 NOV 00142 .................................. 02 NOV 00143 .................................. 01 NOV 00144 .................................. 01 NOV 00145 .................................. 01 NOV 00146 .................................. 02 NOV 00147 .................................. 12 SEP 00148 .................................. 12 SEP 00149 .................................. 19 OCT 00150 .................................. 19 OCT 00151 .................................. 19 OCT 00152 .................................. 02 NOV 00153 .................................. 13 SEP 00154 .................................. 13 SEP 00155 .................................. 13 SEP 00156 .................................. 13 SEP 00157 .................................. 02 NOV 00158 .................................. 02 NOV 00159 .................................. 01 NOV 00160 .................................. 02 NOV 00161 .................................. 01 NOV 00162 .................................. 02 NOV 00163 .................................. 01 NOV 00164 .................................. 02 NOV 00165 .................................. 02 NOV 00166 .................................. 02 NOV 00167 .................................. 01 NOV 00168 .................................. 01 NOV 00169 .................................. 01 NOV 00170 .................................. 01 NOV 00171 .................................. 01 NOV 00172 .................................. 02 NOV 00173 .................................. 02 NOV 00174 .................................. 02 NOV 00175 .................................. 01 NOV 00176 .................................. 02 NOV 00177 .................................. 01 NOV 00178 .................................. 02 NOV 00179 .................................. 01 NOV 00180 .................................. 01 NOV 00

02 NOV 00 JNT OPSv

181 ................................. 02 NOV 00182 ................................. 02 NOV 00183 ................................. 01 NOV 00184 ................................. 01 NOV 00

02 NOV 00 JNT OPSvi

This Page Intentionally Blank

02 NOV 00 JNT OPSvii

CONTENTS

ARRIVAL............................................................................................................... 1P6 FEATHER SOLAR ARRAYS FOR ARRIVAL/DEPARTURE -4A THROUGH 9A.1............................................................................................. 3STATION-ORBITER DOCKING SCRIPT (STAGE 5A.1) ....................................... 13PMA2 PRE-ARRIVAL CONFIGURATION (POST CCS) ........................................ 15PMA2 ARRIVAL (POST CCS) ............................................................................... 19PMA2 POST ARRIVAL CONFIGURATION (POST CCS)...................................... 25ISS POWERDOWN AND RECOVERY FOR SHUTTLE DOCKING - 5A.1 ............ 27TRANSITION TO PROXIMITY OPERATIONS ...................................................... 33

INGRESS STATION.............................................................................................. 35ODS VOLUME PREPARATION FOR DOCKING .................................................. 37ODS VOLUME PREPARATION FOR INGRESS................................................... 39POST DOCKING HATCH LEAK CHECK............................................................... 41HATCH OPENING AND SHUTTLE/ISS DUCT INSTALLATION............................ 431.105 CBM CENTER DISK COVER REMOVAL................................................... 47PMA2 CENTERLINE CAMERA TARGET REMOVAL............................................ 53AUDIO SUBSYSTEM CONFIGURATION FOR DOCKED OPS............................. 55ISS INTERIM INGRESS........................................................................................ 59

MATED OPERATIONS.......................................................................................... 63HANDOVER ATTITUDE CONTROL ORBITER TO CMG TA ................................ 65HANDOVER ATTITUDE CONTROL CMG TA TO ORBITER ................................ 67GENERIC DEPRESS ............................................................................................ 69O2 REPRESS ....................................................................................................... 71GENERIC REPRESS ............................................................................................ 73CAUTION AND WARNING PANEL TEST ............................................................. TBD

VIDEOVDS SHUTTLE AUTO ROUTE - DEROUTE..................................................... 75VDS SHUTTLE MANUAL ROUTE - DEROUTE................................................ 79

EGRESS STATION............................................................................................... 83ISS INTERIM EGRESS ......................................................................................... 851.104 CBM CENTER DISK COVER INSTALLATION ........................................... 87ODS VESTIBULE/PMA2 DEPRESSURIZATION AND HATCH LEAK CHECK...... 93SHUTTLE/ISS DUCT REMOVAL AND HATCH CLOSING.................................... 95

DEPARTURE ........................................................................................................ 99ISS POWERDOWN AND RECOVERY FOR SHUTTLE UNDOCKING - 5A.1 ....... TBDPMA2 PRE-DEPARTURE CONFIGURATION (POST CCS) ................................. 101PMA2 DEPARTURE (POST CCS) ........................................................................ 107PMA2 POST DEPARTURE CONFIGURATION (POST CCS) ............................... 113

COMM/DATA ........................................................................................................ 115COMMUNICATIONS CONFIGURATION .............................................................. 117SHUTTLE VHF SETUP ......................................................................................... 119SHUTTLE VHF ACTIVATION................................................................................ 123HARDLINE AUDIO CONFIG (ISS) ........................................................................ 125

02 NOV 00 JNT OPSviii

HARDLINE AUDIO CONFIG (ISS) BACKOUT ...................................................... 127SHUTTLE PCS SETUP......................................................................................... TBD2.304 PCS LOG FILE SAVE................................................................................. 1292.306 PCS RECONNECT..................................................................................... 1312.307 PCS SCREEN CAPTURE .......................................................................... 1332.309 TRANSFERRING LOG FILES TO FLOPPY DISK ...................................... 1352.303 PCS DEACTIVATION................................................................................. 137AUDIO CONFIGURATION FOR RUSSIAN VOICE COMM CHECKS ................... 139

MALFUNCTION .................................................................................................... 141SHUTTLE/ISS VHF COMM MAL........................................................................... 1432.305 PCS REBOOT ............................................................................................ 1473.602 LOSS OF PCS TELEMETRY (POST CCS) ................................................ 1494.301 PCS RESET BIOS....................................................... REFER TO POC BOOK4.302 PCS RESET CMOS..................................................... REFER TO POC BOOK2.302 ONBOARD FILE TRANSFER..................................................................... 153

CONTINGENCY.................................................................................................... 157HANDOVER ATTITUDE CONTROL ORBITER TO RS THRUSTERS................... 159HANDOVER ATTITUDE CONTROL RS THRUSTERS TO ORBITER................... 161ODS VESTIBULE/PMA2 PRESSURIZATION ....................................................... 163

EMERGENCY RESPONSE................................................................................... 165JOINT EXPEDITED UNDOCKING AND SEPARATION ........................................ 167

CUE CARD............................................................................................................ 173SHUTTLE VHF RADIO.......................................................................................... 175SHUTTLE VHF RADIO CONFIG DIAGRAM.......................................................... 177JOINT EMERGENCY EGRESS ............................................................................ 179

REFERENCE DATA.............................................................................................. 181PROXIMITY OPERATIONS .................................................................................. 183

02 NOV 00

ARRIVAL

ARRIVAL

1

02 NOV 00


ARRIVAL

2

P6 FEATHER SOLAR ARRAYS FOR ARRIVAL/DEPARTURE -

4A THROUGH 9A.1

(JNT OPS/4A - 9A.1/FIN) Page 1 of 10 pages

01 NOV 0010358.doc

1. VERIFYING ISS SYSTEMS HAVE BEEN POWERED DOWN

ÖMCC-H that {2.505 ISS POWERDOWN AND RECOVERY FORSHUTTLE ARRIVAL (DEPARTURE)} has been completed.

NOTEProcedure to be completed for both channels. Total Timeto complete procedure = 1 hour.

2. VERIFYING COMMWITH BGA CONTROLLERPCS P6: EPS: BGA 4B(2B)

BGA 4B(2B)

�ECU 4B(2B)�

Verify Integ Cnt - <incrementing>

3. VERIFYING ECU PWR SUPPLY TEMPS AND VOLTAGE STATUS

Verify SAW PS Temp, °C: -45 --- 54

Verify BGA PS Temp, °C: -45 --- 54Voltage, V: 115 --- 125

4. RECORDING PRESENT BGA STATUS

BGA 4B(2B)

�BGA 4B(2B)�

Record data.

PARAMETER BGA 2B BGA 4B

PV Ch 4B(2B) Mode, Primary PVCU ___________ ___________

BGA Mode, Primary PVCU ___________ ___________

Actual Angle, deg ___________ ___________

Actual Angle Rate, deg/s ___________ ___________

Motor State ___________ ___________

Motor Velocity, deg/s ___________ ___________

Motor Current, A ___________ ___________

Latch 1 Pin Status ___________ ___________

Latch 2 Pin Status ___________ ___________

Copy recorded values for BGA 2B into column titled �INITIAL� instep 13.1.

Copy recorded values for BGA 4B into column titled �INITIAL� instep 13.2.

3


4A THROUGH 9A.1


01 NOV 0010358.doc

5. VERIFYING BGA MODIf the BGA Mode is �Safe/Lock�, �Manual Free�, �Null�, or �Blind� checkwith MCC-H before proceeding. (Safe/Lock to Safe/Lock modetransitions are not possible.)

6. VERIFYING BLIND MODE IMPLEMENTATION TIME AND BGA ANGLE

ÖMCC-H for Blind Mode implementation time and BGA angle.

Record BGA 2B BGA 4BDirected Position, Time After LOC _________sec _________sec(Protect for second Dock/Undock attempt + 15 minutes, 270 minutesmax)

Directed Position, Cmded Angle _________deg _________deg(Optimal power generation position) (0 to 360)

Copy Time After LOC and Cmded Angle values into steps 7 and 8.

7. SETTING BGA BLIND MODE TO DIRECTED POSTION FOR PRIMARYMDMsel Blind Modes

BGA 4B(2B) Blind Modes

�Primary PVCU��Directed Position�

input LOC Timer: 1

BGA 2B BGA 4Binput Time After LOC: _________sec or _________secinput Cmded Angle: _________deg or _________deg

(From step 6) (From step 6)

cmd Armcmd Set

Verify Preselected Blind Mode - Directed PositionVerify Actual LOC Timer - Implement

BGA 2B BGA 4BVerify Preselected Time AfterLOC:

_________sec or _________sec

Verify Preselected Parameter: _________deg or _________deg(From step 6) (From step 6)

4


4A THROUGH 9A.1


01 NOV 0010358.doc

8. SETTING BGA BLIND MODE TO DIRECTED POSTION FOR BACK-UPMDM�Backup PVCU��Directed Position�

input LOC Timer: 1

BGA 2B BGA 4Binput Time After LOC: _________sec or _________secinput Cmded Angle: _________deg or _________deg


cmd Armcmd Set

Verify Preselected Blind Mode - Directed PositionVerify Actual LOC Timer - Implement

BGA 2B BGA 4BVerify Preselected Time AfterLOC:

_________sec or _________sec

Verify Preselected Parameter: _________deg or _________deg(From step 6) (From step 6)

9. SETTING BGA CONTINGENCY CONTROL TO ANGLE HOLD

BGA 4B(2B)

�BGA 4B(2B)�

sel Contingency Control

BGA 4B(2B) Contingency Control

�Angle Hold�

cmd Armcmd Set

NOTESPN 15635 (PR 15635) BGA 2B and BGA 4B ContingencyControl parameter static and indicates �Angle Hold�(Fixed for 5A and subsequent flights).

Verify Contingency Control - Angle Hold

5


4A THROUGH 9A.1


01 NOV 0010358.doc

10. VERIFYING BGA CONTINGENCY MODEConfirm Contingency Control status withMCC-H when timepermits; continue procedure.

NOTERepeat steps 2 ---10 for the opposite BGA beforeproceeding.

11. VERIFYING NEW BGA FEATHER ANGLE AND LATCH SELECTION

ÖMCC-H for BGA feather angle and appropriate anti-rotation latch. IfMCC-H not available use the following table.

Record BGA 2B BGA 4BCmded Angle: (0 to 360) _________deg _________degLatch Select: (1 or 2) _________ _________

Flight Rendezvous Angle,deg (Latch)

Departure Angle,deg (Latch)

BGA 2B BGA 4B BGA 2B BGA 4B

4A N/A N/A 258.75(1) 101.25 (1)

Progress 3 219.375 (1) 140.625 (1) N/A N/A

5A 270 (1) 90 (1) 258.75 (1) 101.25 (1)

Progress 4 219.375 (1) 140.625 (1) N/A N/A

5A.1 149.063 (2) 210.937 (2) 149.063 (2) 210.937(2)

6A 149.063 (2) 210.937 (2) 149.063 (2) 210.937(2)

Soyuz 2 219.375 (1) 140.625 (1) N/A N/A

7A 149.063 (2) 210.937 (2) 149.063 (2) 210.937(2)

4R 219.375 (1) 140.625(1) N/A N/A

7A.1 149.063 (2) 210.937(2) 149.063 (2) 210.937(2)

UF1 149.063 (2) 210.937 (2) 149.063 (2) 210.937 (2)

8A 149.063 (2) 210.937(2) 149.063 (2) 210.937 (2)

UF2 149.063 (2) 210.937 (2) 149.063 (2) 210.937(2)

9A 149.063 (2) 210.937(2) 149.063 (2) 210.937(2)

11A 149.063 (2) 210.937(2) 149.063(2) 210.937(2)

9A.1 149.063(2) 210.937(2) 149.063 (2) 210.937(2)

Copy BGA 2B Cmded Angle and Latch values into step 12, into columntitled �FINAL� in step 13.1 and step 14.

Copy BGA 4B Cmded Angle and Latch values into step 12, into columntitled �FINAL� in step 13.2 and step 14.

6


4A THROUGH 9A.1


01 NOV 0010358.doc

12. CONFIGURING BGA MODE TO DIRECTED POSITION

NOTEIn order to save time, one BGA can be commanded to DirectedPosition Mode while the other is still in transition. Analysis hasshown that perturbations due to additive torque disturbance areminimal.

BGA 4B(2B)

�BGA 4B(2B)�

If PV Ch 4B(2B) Mode, Primary PVCU - Non-Solar Tracking(Fully Commanded) (Contingency/Safe)sel BGA Modes

BGA 4B(2B) Modes

�Directed Position�

BGA 2B BGA 4Binput Cmded Angle: _________deg or _________deg


cmd Armcmd Set

Verify BGA Mode - Directed Position

BGA 4B(2B)

�BGA 4B(2B)�

NOTESPN 17198 (PR 17198) Cmded Angle parameter containsa positive bias and can be as much as 1 deg greater thanthe value issued during commanding. This bias does notaffect the Actual Angle parameter.

BGA 2B BGA 4BVerify Cmded Angle: ______ deg (± 1.0) or ______ deg (± 1.0)


If PV Ch 4B(2B) Mode, Primary PVCU - Autonomous

sel Channel Targeted Modes

BGA 4B(2B) Ch Targeted Modes

7


4A THROUGH 9A.1


01 NOV 0010358.doc

Column: �Non-Solar Tracking�, Row: �Directed Position�

BGA 2B BGA 4Binput Cmded Angle: _________deg or _________deg


cmd Set

Verify Ch 4B(2B) Mode - Non-Solar TrackingVerify BGA Mode - Directed Position

BGA 4B(2B)

�BGA 4B(2B)�


BGA 2B BGA 4BVerify Cmded Angle: ______ deg (± 1.0) or ______ deg (± 1.0)


NOTERepeat steps 11 through 12 for the opposite BGA beforeproceeding.

13. VERIFYING BGA TRANSITION TO DIRECTED POSITION MODE ANDCMDED ANGLE

NOTEIt can take up to 30 minutes if one of the anti-rotation latchesis engaged (15 minutes to unlatch pin and 15 minutes tocomplete the rotation).

13.1 Verify BGA 2B Transition to Directed Position Mode and CmdedAngle.

PCS P6: EPS: BGA 2B

BGA 2B

�BGA 2B�

8


4A THROUGH 9A.1


01 NOV 0010358.doc

Parameter Initial Transition Final

BGA ActualAngle, deg

___________(From step 4)

<ApproachingTarget Angle>

________± 0.5)(From step 11)

BGA Error Angle,deg

N/A <Decreasing> 0.000 (± 1.0)

BGA Actual AngleRate, deg/s

___________(From step 4)

+0.07 --- +0.28or

-0.07 --- -0.28

0.000

DivergenceIndicator

<Blank> <Blank> <Blank>

BGA Motor State ___________(From step 4)

ON ON

BGA MotorVelocity, deg/s

___________(From step 4)

+0.07 --- +0.28or

-0.07 --- -0.28

0.000

BGA MotorCurrent, A

___________(From step 4)

0.10 --- 0.70(± 0.4)

0.10 (± 0.4)

Latch 1 PinStatus

___________(From step 4)

Unlatched Unlatched

Latch 2 PinStatus

___________(From step 4)

Unlatched Unlatched

13.2 Verify BGA 4B Transition to Directed Position Mode and CmdedAngle.

PCS P6: EPS: BGA 4B

BGA 4B

�BGA 4B�

Parameter Initial Transition Final

BGA ActualAngle, deg

___________(From step 4)

<ApproachingTarget Angle>

________± 0.5)(From step 11)

BGA Error Angle,deg

N/A <Decreasing> 0.000 (± 1.0)

BGA Actual AngleRate, deg/s

___________(From step 4)

+0.07 --- +0.28or

-0.07 --- -0.28

0.000

DivergenceIndicator

<Blank> <Blank> <Blank>

BGA Motor State ___________(From step 4)

ON ON

BGA MotorVelocity, deg/s

___________(From step 4)

+0.07 --- +0.28or

-0.07 --- -0.28

0.000

BGA MotorCurrent, A

___________(From step 4)

0.10 --- 0.70(± 0.4)

0.10 (± 0.4)

Latch 1 PinStatus

___________(From step 4)

Unlatched Unlatched

Latch 2 PinStatus

___________(From step 4)

Unlatched Unlatched

9


4A THROUGH 9A.1


01 NOV 0010358.doc

14. CONFIGURING BGA MODE TO SAFE/LOCK (AS NECESSARY)

NOTEIn order to save time, one BGA can be commanded toSafe/Lock Mode while the other is still in transition.Analysis has shown that perturbations due to additivetorque disturbance are minimal.

BGA 4B(2B)

�BGA 4B(2B)�

sel BGA Modes

BGA 4B(2B) Modes

�Safe/Lock�

BGA 2B BGA 4Binput Cmded Angle = _________deg or _________deginput Latch Select = ____________ or ____________


cmd Armcmd Set

Verify BGA Mode - Safe/Lock

BGA 4B(2B)

�BGA 4B(2B)�


BGA 2B BGA 4BVerify Cmded Angle = ______ deg (± 1.0) or ______ deg (± 1.0)


NOTERepeat step 14 for the opposite BGA before proceeding.

10


4A THROUGH 9A.1


01 NOV 0010358.doc

15. VERIFYING BGA LATCH SEQUENCE COMPLETE (AS NECESSARY)

NOTEBGA Latch Sequence Duration takes 8.5 minutes (average)from the point at which the BGA is within 1 deg of thecommanded angle to start of column A in the latchsequence. This time delay allows time to dampen anyremaining motor perturbations before driving the latchmechanism. It takes 11 minutes (average) to completecolumns A through D of the latch sequence. TOTAL TIME= 19.5 minutes at ambient temperature for each BGA.

15.1 Verifying BGA 2B Latch Sequence CompletePCS P6: EPS: BGA 2B

BGA 2B

�BGA 2B�

Verify the appropriate anti-rotation latch is �Latched.�

Parameter Initial(~8.5 min)

Column A:(~4 min)Voltage/CurrentOn

Column B:(~1 min)ActiveActuatorIndication

ColumnC:(~6 min)InactiveActuatorIndication

ColumnD:LatchedIndication

BGALatch 1(2)Pin Status

Unlatched Unlatched Unlatched Unlatched Latched

BGALatch 1(2)Actuator

Inactive Inactive Active Inactive Inactive

BGALatch 1(2)Current, A

Off ScaleLow

~1.25 Off ScaleLow

Off ScaleLow

Off ScaleLow

BGALatch 1(2)Voltage, V

0.0 � 0.1 ~15 0.0 � 0.1 0.0 � 0.1 0.0 � 0.1

BGALatch 1(2)Abort

<blank> <blank> <blank> <blank> <blank>

BGAMotorState

ON ON ON ON OFF*

Initial = BGA within 1 deg of commanded angle* Just after column D in the BGA latch sequence, the motor will turn offindicating the BGA has completed its latch sequence.

** Actual angle may be slightly different than commanded, due to final pin

alignment. (± 0.3 deg).

11


4A THROUGH 9A.1


01 NOV 0010358.doc

***************************************************************************

If Actuator time-out occurs or Latch 1(2) Abort = �X�, ÖMCC-H.

If Latch 1(2) Pin Status = �Unlatched� after 20 minutes, ÖMCC-H.***************************************************************************

15.2 Verifying BGA 4B Latch Sequence CompletePCS P6: EPS: BGA 4B

BGA 4B

�BGA 4B�

Verify the appropriate anti-rotation latch is �Latched.�

Parameter Initial(~8.5 min)

Column A:(~4 min)Voltage/CurrentOn

Column B:(~1 min)ActiveActuatorIndication

ColumnC:(~6 min)InactiveActuatorIndication

ColumnD:LatchedIndication

BGALatch 1(2)Pin Status

Unlatched Unlatched Unlatched Unlatched Latched

BGALatch 1(2)Actuator

Inactive Inactive Active Inactive Inactive

BGALatch 1(2)Current, A

Off ScaleLow

~1.25 Off ScaleLow

Off ScaleLow

Off ScaleLow

BGALatch 1(2)Voltage, V

0.0 � 0.1 ~15 0.0 � 0.1 0.0 � 0.1 0.0 � 0.1

BGALatch 1(2)Abort

<blank> <blank> <blank> <blank> <blank>

BGAMotorState

ON ON ON ON OFF*

Initial = BGA within 1 deg of commanded angle* Just after step D in the BGA latch sequence, the motor will turn offindicating the BGA has completed its latch sequence.

** Actual angle may be slightly different than commanded, due to final pin

alignment. (± 0.3 deg).

***************************************************************************

If Actuator time-out occurs or Latch 1(2) Abort = �X�, ÖMCC-H.

If Latch 1(2) Pin Status = �Unlatched� after 20 minutes, ÖMCC-H.***************************************************************************

12

STATION-ORBITER DOCKING SCRIPT (STAGE 5A.1)(JNT OPS/5A.1/FIN/MULTI) Page 1 of 2 pages

31 OCT 009252.doc

At 170 foot station-keeping, ADCO will prompt Blue/White FCR Flights to this page.At Rendezvous 10 meters (30ft): Blue/White FCR Flights will call All Quiet.All Controllers will monitor Shuttle FD and A/G Loops.

1. CAPTURE PHASE

Controller Expected Call Loop ActionGNC PCT ARMED Shuttle

FDMMACS CONTACT Shuttle

FDShuttle Crew CAPTURE

CONFIRMED2A/G2

ISS Crew - Command ISS to Free Drift

MMACS “MMACS CONFIRMSCAPTURE

CONFIRMED”

ShuttleFD

SSP GC - Start 60 second wall clock inWFCR & BFCR.

RIO - Call MCC-M on ISS OPS andinform of Capture.

ADCO – Confirm Capture Long andArrival Event on ISS FD

GNC SHUTTLE FREE DRIFT ShuttleFD

2. ISS FREE DRIFT – NOMINAL PATH

Controller Expected Call Loop ActionISS Crew ISS FREE DRIFT 2A/G2 ADCO/RIO – Confirm INDICATOR on ISS FDISS FD STATION FLIGHT

CONFIRMS FREEDRIFT

ShuttleFD

CAPCOM – table 5 block 1

3. ISS FREE DRIFT – NO CALL FROM ISS CREW

Controller Expected Call Loop ActionADCO ADCO CONFIRMS

INDICATORISS FD After ADCO confirmation, ISS Flight to

wait for RIO call. At NET “CaptureConfirmed” + 50 seconds Flight toproceed with status call to Shuttle FD.

RIO MOSCOW CONFIRMSINDICATOR

ISS FD

ISS FD STATION FLIGHTCONFIRMS FREE

DRIFT

ShuttleFD


4. ISS ACTIVE CONTROL – NO CHANGE AT CAPTURE CONFIRMED + 50 seconds

Controller Expected Call Loop ActionADCO ADCO CONFIRMS

ACTIVE CONTROLISS FD RIO – Call MCC-M on ISS OPS for

updateISS FD STATION FLIGHT

CONFIRMS ACTIVECONTROL

ShuttleFD


13

STATION-ORBITER DOCKING SCRIPT (STAGE 5A.1)(JNT OPS/5A.1/FIN/MULTI) Page 2 of 2 pages

31 OCT 009252.doc

5. FINAL CALLS TO SHUTTLE CREW – NLT CAPTURE CONFIRMED + 60 sec

Controller Expected Call Loop1 ISS FD “ISS IS FREE DRIFT.” Shuttle

FDCAPCOM STATION FREE DRIFT CONFIRMED A/G

2 ISS FD “ISS IS ACTIVE CONTROL.” ShuttleFD

CAPCOM STATION IN ACTIVE CONTROL, PERFORMFAILED CAPTURE TO UNDOCK

A/G

14

PMA2 PRE-ARRIVAL CONFIGURATION (POST CCS)(JNT OPS/5A.1/FIN) Page 1 of 4 pages

31 OCT 009253.doc

1. GNC COMMAND RESPONSE COUNTERS RESETPCS MCS: GNC Command Response Counters

GNC Command Response Counters

sel Reset

Verify the Since Reset column values are all blank.

Do not close this window until the procedure is complete.

If while executing a command, the Command Accept counter on thatdisplay does not increment

Reselect GNC Command Response Counters to determine if acommand was rejected.

√MCC-H

2. VERIFYING FLIGHT SPECIFIC PADMCC-H If the following information is not recorded elsewhere, record it here.

REQUIRED FOR PRE-ARRIVAL

ADO PRI B/U VERID

COMMENTS

1 MASS PROPERTIES ps012 CCDB SLOT 1 ca00 CMD ATT

QUATRN,SLOT 1:

CCDB SLOT 1 Quatrn 0CCDB SLOT 1 Quatrn 1CCDB SLOT 1 Quatrn 2CCDB SLOT 1 Quatrn 3

3 NON CCDB CA ca08

3. VERIFYING INITIAL CONDITIONSPCS MCS

MCS Summary‘MCS Status’

Verify US Station Mode − Prox OpsVerify RS Station Mode − Prox OpsVerify US GNC Mode − CMG TA(Drift)(UDG)Verify RS GNC Mode − CMG TA(Thrusters)

‘Primary GNC MDM’

Verify Frame Count − <incrementing>

‘Backup GNC MDM’


15


31 OCT 009253.doc

4. LOADING REQUIRED PPLS TO THE PRIMARY GNC MDMFor all PPLs designated in step 2 to load that PPL to the Primary GNCMDM

Perform {1.236 CCS DATA LOAD MANAGEMENT}, all (SODF: GND:C&DH: NOMINAL).

5. LOADING REQUIRED PPLS TO THE BACKUP GNC MDMFor all PPLs designated in step 2 to load that PPL to the Backup GNCMDM

Perform {1.236 CCS DATA LOAD MANAGEMENT}, all (SODF: GND:C&DH: NOMINAL).

6. UPDATING POST ARRIVAL CCDB COMMANDED ATTITUDEMCS: MCS ConfigurationMCS Configuration

‘CCDB Slots’

sel Cmd Att 1

Cmd Att 1

If Cmd Att 0(1)(2)(3) for slot 1 does not match Quat (0,1,2,3) in step 2

If in step 2, Quat (0,1,2,3) is (1,0,0,0)cmd Attitude Quaternion 1,0,0,0

If in Step 2, Quat (0,1,2,3) is not (1,0,0,0)input Quaternion 0 – (from step 2)

1 – (from step 2)2 – (from step 2)3 – (from step 2)

cmd Set

Verify Slot [X] Cmd Att 0 – (as commanded)1 – (as commanded)2 – (as commanded)3 – (as commanded)

7. SETTING MOMENTUM SERVO REFERENCE FRAME

MCS Configuration‘GNC Moding’

sel Drift

Drift

‘Momentum Servo’

16


31 OCT 009253.doc

NOTEThe purpose of this command is to change the MomentumServo Reference Frame to Inertial. Ignore the commandedmomentum vector components.

If Commanded Reference Frame − LVLH(Body)cmd Inertial 0,0,0

Verify Commanded Reference Frame − Inertial

8. VERIFYING ORBITER DOCKED INDICATION

APAS SW Configuration‘Moding Configuration’

Verify Orbiter Docked Indication − NOT Docked

9. VERIFYING STATUS OF ARRIVAL SIGNALS

APAS SW Configuration‘Arrival’

Verify PMA 2 Capture Long LA-1,LA-2 − NoVerify Arrival Flag − No

10. ENABLING ARRIVAL RESPONSE SOFTWARE


sel PMA 2 Arrival Response SW

PMA 2 Arrival Response SW

‘Enable’

cmd Enable

Verify Arrival Response SW − Ena

11. ENABLING APAS LEDS


sel LED Control SW

LED Control SW

cmd Enable

Verify LED Control SW − EnaVerify LED State − On

17


31 OCT 009253.doc

12. PREPARING US GNC FOR AUTOMATIC SW RESPONSE

APAS SW Configuration‘US Inhibits’

sel US GNC Inhibits

US GNC Inhibits

If Mode Transition − Inhcmd Mode Transition − Enable (Verify − Ena)

If Attitude Maneuver − Inhcmd Attitude Maneuver − Enable (Verify − Ena)

If Desat Request − Inhcmd Desat Request − Enable (Verify − Ena)

If Att Cntl Shutdown − Inhcmd Att Cntl Shutdown Enable (Verify − Ena)

18

PMA2 ARRIVAL (POST CCS)(JNT OPS/5A.1/FIN/MULTI) Page 1 of 6 pages

31 OCT 009254.doc

NOTE1. Perform steps 1 --- 4 when orbiter begins approach (range

170 ft, dock - 45 minutes).

2. Perform steps 5 and 6 when orbiter is at 40 ft (dock - 17minutes). These steps should be complete at 30 ft station-keeping.

3. Start step 7 when orbiter starts final approach (from 30 feet).US GNC must be moded to Drift immediately upon call ofCapture.

4. Step 8 shows the APAS signals that indicate Capture.

5. Perform step 9 when orbiter calls Hard Dock complete. Thisstep incorporates post-arrival mass properties and attitudehold control parameters.

6. Step 10 shows the APAS signals that indicate Hard Dock.



sel Reset





√MCC-H

2. VERIFYING FLIGHT-SPECIFIC PADMCC-H If the following information is not recorded elsewhere, record it here.

For step 4: Post Arrival Mass Properties PPL Version ID __________Post-Arrival Non-CCDB CA PPL Version ID __________

For step 5: Desat Target Momentum Components: % __________X __________Y __________Z __________

19


31 OCT 009254.doc

3. VERIFYING INITIAL CONFIGURATIONPCS MCS: APAS SW Configuration

APAS SW Configuration‘Station Configuration’

Verify US Station Mode − Prox OpsVerify RS Station Mode − Prox OpsVerify US GNC Mode − CMG TAVerify RS GNC Mode − CMG TA

‘US Inhibits’

Verify Mode Transition − EnaVerify Attitude Maneuver − EnaVerify Desat Request − EnaVerify Att Cntl Shutdown − Ena

‘Moding Configuration’

Verify Orbiter Docked Indication − Not Docked

‘Arrival’

Verify PMA 2 Arrival Response SW − EnaVerify PMA 2 Capture Long LA-1,LA-2 − NoVerify Arrival Flag − No

‘Related Displays’

sel MCS Configuration

MCS Configuration‘Drift/Indicator Information’

Verify US Drift Available − Yes

4. VERIFYING POST-DEPARTURE PPLs LOADED IN BUFFERPCS MCS: PPL Version IDs

PPL Version IDs‘PPLs Buffer’

Verify Mass Properties Primary MDM Version ID − (As recorded in step 2)Verify Non-CCDB CA PPL Primary MDM Version ID − (As recorded instep 2)

NOTEDo not close the PPL Version IDs page until after step 9.

20


31 OCT 009254.doc

5. PERFORMING MANUAL DESATURATIONOrbiter ⇒ ISS, “Range 40 feet.”

PCS MCS: MCS ConfigurationMCS Configuration

‘Desat Information’

sel Manual CMG Desat

Manual CMG Desat

Verify Thrusters Available − Yes

‘Desaturation Commands’

If Desat Target Momentum Components in step 2 are 100 % and 0,0,0When CMG Desat In Progress − Nocmd Desaturate CMGs 100 % to 0,0,0

If Desat Target Momentum Components in step 2 are not 100 % and 0,0,0input percent %: (as recorded in step 2)

X: (as recorded in step 2)Y: (as recorded in step 2)Z: (as recorded in step 2)

When CMG Desat In Progress − No, cmd Set

‘Desaturation Status’

NOTEThe desaturation will drive the on-line momentumtoward the target momentum. This should happenquickly and may not be visible to the operator.

Monitor for desat complete, as followsVerify CMG Desat In Progress − NoVerify Desat Complete − 100 %

ISS ⇒ orbiter, “Manual desaturation complete.”

6. INHIBITING AUTO ATTITUDE CONTROL HANDOVER TO RSPCS MCS

MCS Summary

sel MCS Safing

MCS Safing‘Station Configuration’

21


31 OCT 009254.doc

If Auto Att Control to RS − Enasel Auto Att Control Handover to RS

Auto Att Control Handover to RS‘Inhibit’

cmd Armcmd Inhibit

Verify Auto Att Control Handover − Inh

ISS ⇒ orbiter, “ISS is ready for docking.”

7. FINAL APPROACH AND CAPTUREISS must be in Free Drift within 60 seconds of Capture.Send the command to mode US GNC to Drift immediately upon orbitercall of Capture.

Orbiter ⇒ ISS, “Initiating final approach.”


sel Drift

Drift‘Moding’

Orbiter ⇒ ISS, “Capture.”

cmd Mode to Drift

Verify US GNC Mode − DriftVerify RS GNC Mode − CMG TA (Indicator)

ISS ⇒ orbiter, “Station in Free Drift.”

22


31 OCT 009254.doc

******************************************************************************

PCSIf at any time orbiter calls Failed Dock and proceeds to separation

MCS: MCS Configuation MCS Configuration‘GNC Moding’

Verify US GNC Mode − DriftVerify RS GNC Mode − IndicationVerify RS Control − Slave

‘MCS ORU Status’

Verify Min ORUs Available − YesVerify CMGs On Line − 4(3)(2)

‘GNC Moding’

sel CMG TA CMG TA

If Thrusters available for CMG Desat − Nocmd RS Prepare Thrusters for CMG Desat

NOTEThe following signal may take up to 4 minutesto occur.

Verify Thrusters Available for CMG Desat − Yes

‘Mode to CMG TA’

sel CMG TA Instances’

CMG TA Instances

cmd Mode to CMG TA using CCDB Slot 1 Execute

Verify Active CCDB Source Slot − 1Verify US GNC Mode − CMG TAVerify RS GNC Mode − CMG TA

ISS ⇒ orbiter, “ISS in CMG TA.”

Exit procedure******************************************************************************

8. VERIFYING APAS INDICATION OF CAPTURE

NOTEThis step shows the APAS signals at Capture andis provided for information only.

23


31 OCT 009254.doc

PCS MCS: APAS SW ConfigurationAPAS_SW_Configuration


Verify Orbiter Docked Indication − Docked

‘Arrival’

Verify PMA2 Capture Long LA-1,LA-2 − Yes

‘Departure’

Verify PMA2 Separation LA-1,LA-2 − No

9. INCORPORATING POST ARRIVAL PPLS

NOTEAfter Capture, orbiter will perform Hard Dock procedure todrive the APAS hooks, which may take up to 17 minutes.

Orbiter ⇒ ISS, “Hard dock complete.”

PCS MCS: PPL Version IDsPPL Version IDs

‘PPLs Buffer’

cmd Mass Properties – Incorporate Executecmd A-Matrix – Incorporate Executecmd Flex Filter – Incorporate Executecmd Steering Law Params – Incorporate Executecmd Momentum Servo Params – Incorporate Execute

10. VERIFYING APAS INDICATION OF HARD DOCK

NOTEThis step shows the APAS signals after HardDock, and is provided for information only.

PCS MCS: APAS SW ConfigurationAPAS_SW_Configuration

‘Arrival’

Verify PMA2 Capture Long LA-1,LA-2 − No

‘Departure’

Verify PMA2 Interface Sealed LA-1,LA-2 − YesVerify PMA2 Separation LA-1, LA-2 − No

24

PMA2 POST ARRIVAL CONFIGURATION (POST CCS)(JNT OPS/5A.1/FIN) Page 1 of 2 pages

01 NOV 009255.doc



sel Reset





√MCC-H

2. VERIFYING CORRECT CONFIGURATIONPCS MCS: APAS SW Configuration


Verify US Station Mode − Prox OpsVerify RS Station Mode − Prox OpsVerify US GNC Mode − CMG TA (Drift)Verify RS GNC Mode − CMG TA (Indicator)


If Orbiter Docked Indication – NOT Dockedsel Orbiter Docked Indication

Orbiter Docked Indication

cmd Docked



Verify PMA2 Arrival Response SW − Ena

‘Departure’

Verify PMA 2 Separation LA-1,LA-2 − No

25

PMA2 POST ARRIVAL CONFIGURATION (POST CCS)(JNT OPS/5A.1/FIN) Page 2 of 2 pages

01 NOV 009255.doc

3. REPLACING US GNC SOFTWARE INHIBITS


sel US GNC Inhibits

US GNC Inhibits

cmd Mode Transition Inhibit (Verify − Inh)cmd Attitude Maneuver Inhibit (Verify − Inh)cmd Att Cntl Shutdown Inhibit (Verify − Inh)cmd Desat Request Inhibit (Verify – Inh)

4. DISABLING ARRIVAL RESPONSE SOFTWARE


sel PMA 2 Arrival Response SW

PMA 2 Arrival Response SW

‘Inhibit'

cmd Arm

Verify State − Arm

cmd Inhibit

Verify Arrival Response SW − InhVerify State − Disarm

5. DISABLING LED CONTROL SOFTWARE


sel LED Control SW

LED Control SW

cmd Inhibit

Verify LED Control SW − InhVerify LED State − Off

26

ISS POWERDOWN AND RECOVERY FOR SHUTTLE DOCKING - 5A.1(JNT OPS/5A.1/FIN/MULTI) Page 1 of 6 pages

31 OCT 009273.doc

1. Once P6 is activated the ISS power generation capability is such that anISS power down will not be required unless the absolute Solar Betaangle ≥ 50°. For absolute Solar Beta angle ≥ 50°, the total ISSpowerdown required is 600 Watts (~200 from the RS and ~400 from theUSOS)

2. Use the POWERUP column in reverse order to back out of thepowerdown.

3. The loads for the major power users are presented below.

Equipment dc Watts

Russian Load Power Down 200 Watts

NODE 1 Lights 196 Watts (7 lights)

PMA3 Shell Heaters 0 W predicted

Node 1 Shell Heaters 0 W predictedTotal for String B 1284 W

PMA1 Shell Heaters 40 W predictedTotal for String B 272 W

SPDA Rail Heaters 120 Watts

Z1 EEATCS Heaters 80 Watts

Z1 DDCU Heaters 200 Watts

Early CommZ14B B

SGTRC 190 Watts

Early CommN1RS1 CPort Antenna Heater (6)Stbd Antenna Heater (13)

70 Watts70 Watts

27


31 OCT 009273.doc

POWERDOWN POWERUP

NOTEDepending on the heater configuration, powerusage may not decrease after every step.

1. POWERDOWN REQUIREMENT VERIFICATIONIf absolute Solar Beta Angle < 50° (no powerdownrequired) >>

2. RS LOAD POWER DOWNTBD (Based on current data, SM and FGB totalpowerdown will be 200 Watts.)

3. POWERDOWN NODE LIGHTSPCS Node 1: EPS

RPCM N13B - B

sel RPC 01cmd RPC Position − Open (Verify − Op)

Node 1: EPSRPCM N13B - A

sel RPC X where [X] = 135

cmd RPC Position − Open (Verify − Op)

Repeat

Node 1: EPSRPCM N14B - B


Node 1: EPSRPCM N14B - C



Repeat

cmd RPC Position −Close (Verify – Cl)




28


31 OCT 009273.doc

POWERDOWN POWERUP

4. INHIBITING PMA3 A AND B SHELL HTRSPCS Task: USOS Powerdown/up Pg 1

3A USOS Powerdown Powerup Display1

sel PMA3 Htrs

PMA3 − Htr Availability

‘Htr [X]A’ where [X] = 1 2 3 4 5

cmd Inhibit

√Htr[X]A Availability − Inh

Repeat

‘Htr [X]B’ where [X] = 1 2 3 4 5

cmd Inhibit

√Htr[X]B Availability − Inh

Repeat

5. INHIBITING NODE 1 A AND B HTRS (1 --- 6)

3A USOS Powerdown Powerup Display 1

sel Node 1 Htrs 1 --- 6

Node1Htr16avail

‘Htr [X]A’ where [X] = 1 2 3 4 5 6

cmd Inhibit


Repeat

cmd Ena Backup

cmd Ena Backup

cmd Ena Backup

29


31 OCT 009273.doc

POWERDOWN POWERUP

‘Htr [X]B’ where [X] = 4321 5 6

cmd Inhibit


Repeat

6. INHIBITING NODE 1 A AND B HTRS (7 --- 9)


sel Node 1 Htrs 7 --- 9

Node1Htr79avail

‘Htr [X]A’ where [X] = 7 8 9

cmd Inhibit


Repeat

‘Htr [X]B’ where [X] = 7 8 9

cmd Inh


Repeat

cmd Ena Backup

cmd Ena Operate

cmd Ena Operate

30


31 OCT 009273.doc

POWERDOWN POWERUP

7. INHIBITING PMA1 A AND B SHELL HTRS


sel PMA1 Htrs

PMA1 HtrAvailability

‘Htr [X]A’ where [X] = 1 3 4 5

cmd Inhibit


Repeat

‘Htr [X]B’ where [X] = 1 2 3 5

cmd Inhibit


Repeat

8. DISABLING Z1 POWER BUS

3A USOS Powerdown Powerup Display 1‘Pwr Bus Rail Htrs- A’

cmd Z13B HtrA Inh (√Availability − Inh)cmd Z14B HtrA Inh (√Availability − Inh)

'Pwr Bus Rail Htrs − B'

cmd Z13B HtrB Inh (√Availability − Inh)cmd Z14B HtrB Inh (√Availability − Inh)

9. DISABLING Z1 EEATCS HEATERS‘EEATCS Loop A Non Op Htr1’‘RPCM Z13B B’

cmd RPC 7 − Op (Verify Pos − Op)

‘EEATCS Loop B Non Op Htr1’‘RPCM Z14B B’

cmd RPC 7 − Op (Verify Pos − Op)

cmd Ena Operate

cmd Ena Backup

cmd Htr A Ena BUcmd Htr A Ena BU

cmd Htr A Ena BUcmd Htr A Ena BU

cmd RPC 7 − Close(Verify Pos − Cl)

cmd RPC 7 − Close(Verify Pos − Cl)

31


31 OCT 009273.doc

POWERDOWN POWERUP

10. DISABLING Z1 DDCU HEATERS‘DDCU Htrs − 1’

‘RPCM Z14B B’

cmd RPC 11 − Op (Verify − Op)

‘RPCM Z13B B’


‘DDCU Htrs − 2’‘RPCM Z14B B’


‘RPCM Z13B B’


11. POWERDOWN C&T HEATERSZ1: EPS:RPCM Z14B BRPCM Z14B B


Node 1: EPS: RPCM N1RS1 C

RPCM N1RS1 C



Repeat

cmd RPC 11 − Close(Verify − Cl)




cmd RPC Position −Close (Verify − Cl)

cmd RPC Position −Close (Verify − Cl)

32

TRANSITION TO PROXIMITY OPERATIONS(JNT OPS/5A.1/FIN/MULTI) Page 1 of 2 pages

31 OCT 009278.doc

1. TRANSITIONING TO PROX OPS MODE: IDENTIFYING CURRENTSTATION MODE AND NAVIGATING TO PROXIMITY OPERATIONSMODE DISPLAY

Primary_CCS_MDM

Primary CCS Station Modes

PCS Verify Current Station Mode – Standard

sel Prox OPS Mode Transition

2. VERIFYING TRANSITION VALIDITY AND NO TRANSITION INPROGRESS

Primary CCS Prox OPS Mode Transitions‘Transition Validity’

PCS cmd Arm Execute

√Checks Inhibits − <Arm>

cmd Inhibit Execute

√Checks Inhibit − <Inh>√Checks State − <Inh>

‘Manual Transition’

Verify IP Mode Coordination in Progress − <blank>Verify Transition in Progress − <blank>Verify Transition Time Remaining: 00:00

3. PERFORMING MODE TRANSITION VALIDITY CHECKPCS cmd Transition to Prox OPS Execute

Verify IP Mode Coordination in Progress − XVerify Validity Checks Passed − ConfirmVerify Validity Checks Failed − BlankVerify Transition Confirmation Invalid − BlankVerify Transition Cancelled − Blank

NOTEOnce initiated, the Mode Transition can becancelled prior to confirmation by:

cmd Cancel Transition Execute

Verify Transition Cancelled − X

Step 4 must be completed within 1 minute of step 3.

33

TRANSITION TO PROXIMITY OPERATIONS(JNT OPS/5A.1/FIN/MULTI) Page 2 of 2 pages

31 OCT 009278.doc

4. COMPLETING TRANSITION TO PROX OPS MODEPCS cmd Confirm Transition Execute

Current Station Mode: Prox OPS

5. VERIFYING TRANSITION IN PROGRESS‘Manual Transition’

Verify IP Mode Coordination in Progress − XVerify Transition in Progress − In ProgVerify Transition Time Remaining is counting down (default value10 minutes)

Verify Transition Status − Incomplete

Wait until Transition Time Remaining = 0

6. VERIFYING TRANSITION COMPLETE‘Manual Transition’

Verify IP Mode Coordination in Progress − <blank>Verify Transition in Progress − <blank>Verify Transition Time Remaining: 00:00Verify Transition Status − <Successful>

NOTEIf the transition was unsuccessful due to the RS nottransitioning to Prox Ops, then the RS will notrespond to the USOS arrival/departure signals.

If Verify Transition Status − <Unsuccessful>‘Transition Details Display’

sel Prox Ops

Prox Ops Transition Details‘Transition Success Criteria’

Verify RS Current Mode – Prox OpsVerify RS Transition Completion Status – Successful

34

02 NOV 00

INGRESS STATION

INGRESS

STATIO

N

35

02 NOV 00


INGRESS

STATIO

N

36

ODS VOLUME PREPARATION FOR DOCKING(JNT OPS/5A.1/FIN) Page 1 of 1 page

31 OCT 009160.doc

EXT A/L 1. √ODS Upper Hatch closedEqual vlv caps (two) → installed

Unstrap centerline camera diffuser flex duct from EXT A/L wall.Attach flex duct to camera bracket to direct air flow to window.If required, tape diffuser open.

AW18A 2. LTG FLOOD 1(3,4) − OFF

A6L 3. √SYS PWR SYS 1,SYS 2 (two) − ON√cb DOCK LT (four) − cl

4. LT TRUSS FWD,AFT (two) − ON

5. LT VEST PORT,STBD (two) − ON

MO13Q 6. AIRLK FAN A(B) − OFF

EXT A/L 7. Disconnect airlock flex duct from booster fan muffler, rotate into middeck,and secure.

MO13Q 8. AIRLK FAN A(B) − ON

9. AIRLK 2 − OFF/ON

10. TNL ADAPT 1 − OFF/ON

11. √Airflow at muffler

Middeck 12. Close Inner Hatch per decal.

13. Equal vlv (two) − OFF, install caps

37

02 NOV 00


38

ODS VOLUME PREPARATION FOR INGRESS(JNT OPS/5A.1/FIN) Page 1 of 1 page

31 OCT 005069.doc

A6L 1. LT VEST PORT, STBD (two) − OFF

2. LT TRUSS FWD, AFT (two) − OFF

Inner 3. Equal vlv caps (two) − remove Hatch

4. Equal vlv (two) − NORM

5. √Hatch ∆P < 0.2 psid

6. Open Hatch per decal.

7. Equal vlv (two) − OFF, reinstall caps

MO13Q 8. TNL ADAPT 1 − ON/OFF

9. AIRLK 2 − ON/OFF

10. AIRLK FAN A(B) − OFF

Middeck 11. Remove diffuser cap from floor fitting.Stow.Mark stowage location (will be reused).

EXT A/L/ 12. Unstrap airlock flex duct. Middeck Connect to middeck floor fitting and to booster fan muffler inlet.


AW18A 14. As required, LTG FLOOD 1(3,4) − ON

15. √Airflow at top of external airlock halo

EXT A/L 16. Unstrap centerline camera diffuser flex duct from camera bracket.Stow duct along stbd top of EXT A/L wall (in straps).

17. Remove, stow Centerline Camera.

39

02 NOV 00


40

POST DOCKING HATCH LEAK CHECK(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

31 OCT 009161.doc

NOTEISS will concurrently perform a leak checkof the PMA3 volume.

1. Notify MCC and ISS, “Beginning initial Hatch leak checks.”

MO10W 2. √14.7 CAB REG INLET SYS 1,SYS 2 (two) − CL

SM 177 EXTERNAL AIRLOCK

3. Record A/L-VEST ∆P: _____ psid.Record EXT A/L PRESS: _____ psia.

SM 210 NODE 1

4. Record NODE 1 CAB PRESS: _____ psia.

5. Wait 20 minutes.

*****************************************************************If A/L-VEST ∆P ≤ previously recorded - 0.16 psid

Notify MCC-H (possible leakage through Hatches).

If EXT A/L Press ≤ previously recorded - 0.16 psiaNotify MCC-H (possible leakage from EXT A/L).

*****************************************************************

6. Notify MCC and ISS: “Initial hatch leak checks complete. Ready forvestibule pressurization.”

41

02 NOV 00


42

HATCH OPENING AND SHUTTLE/ISS DUCT INSTALLATION(JNT OPS/5A.1/FIN/MULTI) Page 1 of 4 pages

31 OCT 005070.doc

SHUTTLE TOOLS AND EQUIPMENT REQUIREDTowel

ISS TOOLS AND EQUIPMENT REQUIREDCSA-CP Rubber Gloves

NOD1 10" Adjustable Wrench D4_G2

PMA Docking Mechanism Accessory KitAPAS Hatch ToolCleaning Pads

APAS Hatch CoverDocking Target Standoff Cross BagDocking Target Base Plate Cover1-1/2" Open End Wrench

EQUALIZE AND INGRESS PMA1. If PMA pressurization is required MCC-H will report expected equalization

time.Lab 2. MPEV → OPEN Fwd LAB: ECLSS Hatch

LAB: ECLSS

3. When dp/dt ~0 or On MCC GO, proceed

4. Open Lab Fwd Hatch per decal.MPEV→ CLOSED

EQUALIZING WITH ODS VESTIBULEPMA 5. APAS EQUAL VLV → OP

LAB: ECLSSLAB: ECLSS

6. When dp/dt ~0 or On MCC GO, proceed.


CRT 7. Record A/L-VEST ∆P: _____ psid.Wait 30 minutes.

************************************************************If A/L-VEST ∆P ≥ previously recorded + 0.16 psid,notify MCC-H (Vestibule/PMA2 Leak).

************************************************************

43


31 OCT 005070.doc

APAS HATCH OPENING8. Open APAS Hatch.

�� APAS Hatch Tool.

Insert tool in hatch socket (ensure fully seated).Rotate tool 3 --- ! � �� "�� # ��$%�� &'�� (��) �� *

***************************************************************If tool prematurely slips or does not engage

If comm available, check MCC-H before proceeding.�� +�,,�� -.��/Position) setting on APAS Hatch Tool.

Reattempt to open Hatch.***************************************************************

Remove tool.Allow Hatch Seals to relax for 3 minutes.

CAUTIONAPAS Hatch Seals require 3 minutesto relax before opening Hatch.

Open Hatch.Tether Hatch Tool to hatch handle.Install APAS Hatch Cover.Secure Hatch in open position to PMA APAS Hatch Standoff.

PMA 9. APAS EQUAL VLV → CL

SHUTTLE EQUALIZATION10. ISS report to shuttle: “PMA Hatch is opened. Go for shuttle equalization

with ISS.”

11. MCC-H report to ISS and shuttle expected equalization time.

ODS 12. Equal vlv (one) → NORM Hatch

REMOVING DOCKING EQUIPMENT

CAUTION1. The Docking Target Base Plate Cover should be put on the

Docking Target Base Plate any time the Docking TargetStandoff Cross Bag is not mounted in order to preventscratches, surface damage.

2. The Docking Target Standoff Cross should be put in its bagto protect the Docking Target Standoff Cross when notmounted to the Docking Target Base Plate. The surface ofthese items are very easily scratched.

44


31 OCT 005070.doc

NOTEDonning of Rubber Gloves required in handling of DockingTarget Standoff Cross and Docking Target Base Plate.

PMA 13. While maintaining a torque on standoff cross threaded hexagonal cap Hatch nut, loosen jam nut on docking target base plate receptacle by applying

a torque (10" Adjustable Wrench and 1-1/2" Open End Wrench).Temporarily stow jam nut by continuing to rotate it onto smaller,non-threaded diameter of receptacle.

Loosen hexagonal cap nut by applying torque.Continue to rotate cap nut until threaded off of receptacle.

14. Remove and insert cross into Docking Target Standoff Cross Bag.Temporarily stow.

15. Install Docking Target Base Plate Cover.

16. Stow 10" Adjustable Wrench in NOD1 D4_G2.Stow 1-1/2" Open End Wrench in PMA.

OPENING ODS HATCH

CRT SPEC 66 ENVIRONMENT

17. When Cabin dP/dT < 0.01, proceed.

ODS 18. √ODS Hatch ∆P ≤ 0.2 psidOpen ODS Hatch per decal.Equal vlv (one) → OFF, cap installed

DOCKING EQUIPMENT REMOVALODS 19. For each Docking Light Vestibule Disconnect cables.

Install caps on outlet.Remove the locking pin.Remove Docking Light.Reinstall locking pin.

20. Mark crosshairs with appropriate identification.

21. Remove crosshairs.Stow lights and crosshairs as required.

WARNINGSurfaces may be below freezing for a short time after initial ODSHatch opening. Avoid direct contact with vestibule surfaces untilSHUTTLE VESTIBULE TEMP 1,2 (two) indicate > 40° F(SM 177 DM STATUS ODS INTERFACE).

45


31 OCT 005070.doc

22. Wipe any condensate from vestibule volume using towel.

IMV CAP/FLANGE SAVER RECONFIGURATION23. PMA2 air duct jumper ←|→ launch restraint bracket

(Use Ratchet and Deep Socket, leave V-Band clamp on flange)Open Velcro straps securing rest of flex duct to Closeout From (twoplaces).

24. Lab Fwd Stbd IMV vlv → (deploy handle) OPENLab Fwd Stbd IMV vlv → CLOSE (stow handle)

25. IMV cap ←|→ Lab Fwd Stbd IMV flange(Use Ratchet and Deep Socket, leave V-Band on flange.)

Using hands and optional FDF/SODF Cover, pry the IMV cap (if required,use screwdriver).

Remove face and bore O-rings from IMV cap.Label both O-rings as “Used O-rings. Return to Houston.”Stow in “Return to Houston” Bag.

26. PMA2 air duct jumper →|← Lab Fwd Stbd IMV flange(Use V-Band clamp, Ratchet, and Deep Socket.)

27. IMV cap →|← PMA2 launch restraint(Use V-Band clamp, Ratchet, and Deep Socket.)

CONFIGURING DUCTINGMO13Q 28. AIRLK FAN A(B) − OFF

Ext A/L 29. Disconnect air inlet flex duct from external A/L duct from halo cross airduct.

PMA 30. Unstow PMA/ODS Interface Duct Segment from PMA.

Ext A/L 31. Connect PMA/ODS Interface Duct Segment to air inlet flex duct withT-handle clamp.

Lab Fwd 32. Lab Fwd Stbd IMV vlv → (deploy handle) OPEN (stow handle)


34. Go to IMV FAN ACTIVATION/DEACTIVATION, Lab Fwd Stbd Fan, steps1 and 2 only, (SODF: ECLSS: A&C: THC).

46

1.105 CBM CENTER DISK COVER REMOVAL(S&M/4A - ALL/FIN) Page 1 of 5 pages

10 JUL 008206.doc

OBJECTIVE:Remove CBM Center Disk Cover to allow crew access to vestibule areas.

LOCATION:Installed: Node 1 Radial PortsStowed: √Maintenance and Assembly Task Supplement (MATS)

DURATION:20 minutes

PARTS:CBM Center Disk Cover (P/N 683-14575-001) Zenith/NadirCBM Center Disk Cover (P/N 683-14575-010) Stbd/Port

MATERIALS:Gray TapeVelcro Strips

TOOLS REQUIRED:Mini Maglite Equivalent Shuttle Tools:Portable Fan FlashlightISS Common IVA Tool Kit: Portable FanKit E: IFM Tool Kit:

Ratchet 1/4" Drive Drawer 1:Kit F: Tool Table Cloth

1/4" Socket, 1/4" Drive General Purpose Tape (1")Lid 2: Drawer 3:

Tablecloth 4" Ratchet1/4" Socket, 1/4" Drive

REFERENCE PROCEDURE(S):None

47


10 JUL 008206.doc

REMOVING TENSION TO CENTER DISK COVER

Pulleys (8)

Standoff Bars (4)

Turnbuckles (2)

ClevisPIP Pins (8)(stowed)

Figure 1.- CBM Center Disk Cover.(IVA side of Zenith/Nadir Cover is shown.)

Figure 2.- Cutaway View of Turnbuckle.

1/4" Socket

Plunger

Pull Ring

Pull Ring

Turnbuckle

48


10 JUL 008206.doc

CAUTIONThis procedure is performed near hatch seals.Care must be taken to avoid seal damage.

1. Pull out Pull Rings (two each Turnbuckle), then turn 90 degrees andrelease so that Pull Rings remain out on top of Plungers.

If Pull Rings do not remain on top of Plungers, restrain Pull Rings on topof Plungers with Gray Tape.

If required, remove Pull Ring Plungers completely from Turnbuckle(two each Turnbuckle) (Ratchet 1/4" Drive, 1/4" Socket).

Temporarily Stow.Refer to Figures 1,2.

Figure 3.- Loosening Turnbuckles.

2. If on IVA side, loosen Turnbuckles (two) by rotating toward center ofCenter Disk Cover (20 --- 25 turns).

If on EVA side, loosen Turnbuckles (two) by rotating away from center ofCenter Disk Cover (20 --- 25 turns).

Refer to Figure 3.

3. If Pull Ring Plungers were removed (refer to step 1), reinstall intoTurnbuckle (two each Turnbuckle) (Ratchet 1/4" Drive, 1/4" Socket).

Refer to Figure 2.

REMOVING CENTER DISK COVER FROM MOUNTING BRACKETS

Figure 4.- Pulley Restrained by Clevis PIP Pin. (View from IVA Side.)

Clevis Bracket

Clevis PIP Pin

LowerRight

UpperLeft

From EVA side

From IVA sideFrom EVA side

From IVA side

Pulley

49


10 JUL 008206.doc

Figure 5.- Pulley Restrained by Clevis PIP Pin. (View from EVA Side.)

Figure 6.- Clevis PIP Pin Stowed in End of Standoff Bar. (View from IVA Side.)

4. Remove PIP Pins from Clevis Brackets (eight).Stow in end of Standoff Bars.Refer to Figures 4 --- 6.

5. Push pulleys (eight) into base of Clevis Brackets to release restraints,then slide out of Clevis (sliding towards IVA side).

Refer to Figures 4 --- 6.

Standoff Bar

Clevis PIP PinStowed in end ofStandoff Bar

Pulley Pulley Restraint

Clevis Bracket

Pulley

Clevis PIP Pin

StowageLocation forClevis PIP Pin(at end ofStandoff Bar)

Turnbuckle CenterDisk Cover

50


10 JUL 008206.doc

Figure 7.- Side View of Standoff Bar.

6. Remove Standoff Bar PIP Pins (two each Standoff Bar) from restraintlocation on Standoff Brackets.

Insert PIP Pins in stowage location on Standoff Brackets.Refer to Figure 7.

7. Rotate Standoff Bar towards center of Cover.Remove Standoff Bar from Standoff Bracket.

CLOSEOUT8. Fold cover diagonally so Turnbuckles meet.

Fold as small as possible for stowage.Secure cover with Velcro Strips.

9. Inform MCC-H of task completion.

10. √MATS for stowage location of Center Disk CoverStow tools, equipment.

IVASide

Clevis PIPPin stowagelocation

StowageLocations forStandoff BarPIP Pin

RestraintLocation forStandoff BarPIP Pin

Standoff Bar

TowardsCenter

of Cover

StandoffBracket

EVASide

51

02 NOV 00


52

PMA2 CENTERLINE CAMERA TARGET REMOVAL(JNT OPS/5A.1/FIN) Page 1 of 2 pages

31 OCT 0010181.doc

WARNINGLexan Cover must be placed on mirror before disassembly.Handle carefully while disassembling beam supports.

1. Retrieve Lexan Cover.

√MCC for stowage location

Install Lexan Cover on target mirror with arrow on label pointing to fifthlens (Velcro straps).

2. Remove Target Assembly from PMA structure, 1/4-turn fasteners (four).

Figure 1.- Assembled Target Beam.Side View

3. Stow 1/4-turn fasteners (four) in respective stowage locations.Refer to Figure 1.

4. Loosen fasteners (eight), remove end beams from center beam(4" Ratchet, 4" Ext, 7/16" Socket).

Refer to Figure 1.

Figure 2.- Target Beam in Stowage Configuration.

5. Stack three pieces of beam structure in stowage configuration.Tape together (Kapton Tape).Refer to Figure 2.

6. Retrieve Target Foam Stowage Box.

√MCC for stowage location

Fastener Locations33 in-lbs, x-pattern

(four each side)

Wing Wing

1/4-turn stowage 1/4-turn stowage

Mirror Target

EndEnd Beam

Center

Mirror Target

End Beam

End Beam

Center

53

PMA2 CENTERLINE CAMERA TARGET REMOVAL(JNT OPS/5A.1/FIN) Page 2 of 2 pages

31 OCT 0010181.doc

Place Target Assembly in Target Foam Stowage Box.

7. Stow tools, equipment.

Report task completion to MCC-H.

8. √MCC for stowage location of Target Beam

54

AUDIO SUBSYSTEM CONFIGURATION FOR DOCKED OPS(JNT OPS/5A.1/FIN) Page 1 of 3 pages

31 OCT 007577.doc

1. CONFIGURING AUDIO SUBSYSTEM FOR DOCKED OPS1.1 Post Docking, clear DAIU1 acting as RAIU1, audio channels.

PCS LAB: C&T: Audio Overview: Audio SubsystemAudio Subsystem

‘ATU’s’

sel RAIU1 (actually DAIU1)

√IAC(X) − On and Active

‘State’

cmd Standby

√State − Standby

1.2 Disconnect RAIU1 audio patch cable from DAIU1.Remove RAIU1 address connector from DAIU1.Connect DAIU1 to its cables and address connector.

1.3 Setting Up DAIU1 Docked Voice Audio Channels

Audio Subsystem‘ATU’s’

sel DAIU1


‘DAIU1 Bus IO’

cmd Enable

√DAIU1 Bus IO − Enable

‘DAIU1 State’

cmd Active

√DAIU1 State − Active

Audio Subsystem‘Audio Displays Menu’

sel IAC(X) Call Select



55


31 OCT 007577.doc

‘Public3’

sel Selectcmd DIA1

‘Public1’

sel Selectcmd DAA1

‘Public4’

sel Selectcmd DAG1

1.4 Verifying Voice Loops Were Established

IACX Loop Select

√GD3 in Public1 T√LB1 in Public1 T√LB1 in Public2√DI1 in Public3 T√DA1 in Public1 T√DG1 in Public4 T

√LB2 in Public1√LB2 in Public2 T√GD4 in Public2 T

2. MAKING CALLS TO ORBITER

NOTEAdjust ATU Volume Level at or above 9 volumeticks out of 12 to ensure that Class 2 tones areaudible throughout the Lab.

AFT ATU 2.1 ATU Lab1 pb → 3 Lab1

√ATU Display − 1G 2G 3T

2.2 ATU Lab1 pb → PAGE

2.3 Ask the orbiter crew to come up on Orbiter ICOMA.

Orbiter: AFD: Docking Ring Audio Center

2.4 ICOM A → On

AFT ATU 2.5 Perform ICOMA voice checks. Lab1

56


31 OCT 007577.doc

2.6 Request orbiter crew select A/G1.


2.7 sel A/G1 → On


2.9 Perform orbiter A/G1 voice checks from station to MCC.

2.10 Return to ICOMA voice channel.ATU Lab1 pb → 3

2.11 Request orbiter crew deselect Docking Ring Audio Center A/G1.


2.12 sel A/G1 → Off


57

02 NOV 00


58

ISS INTERIM INGRESS(JNT OPS/5A.1/FIN) Page 1 of 3 pages

31 OCT 0010179.doc

SHUTTLE TOOLS AND EQUIPMENT REQUIREDTowel

ISS TOOLS AND EQUIPMENT REQUIREDCSA-CP Rubber Gloves


PMA Docking Mechanism Accessory KitAPAS Hatch ToolCleaning Pads


EQUALIZING WITH ODS VESTIBULEPMA 1. APAS EQUAL VLV → OP

LAB: ECLSSLAB: ECLSS

2. When dp/dt ~0 or On MCC GO, proceed.

APAS HATCH OPENING3. Open APAS Hatch.

Select ‘�� ’ (Working Position) torque setting onAPAS Hatch Tool.

Insert tool in hatch socket (ensure fully seated).Rotate tool 3 --- 4 turns in direction of ‘��’ (Open) arrow until it clicks.

***************************************************************If tool prematurely slips or does not engage

If comm available, check MCC-H before proceeding.Select ‘� �� ’ (EmergencyPosition) setting on APAS Hatch Tool.

Reattempt to open Hatch.***************************************************************

Remove tool.Allow Hatch Seals to relax for 3 minutes.

CAUTIONAPAS Hatch Seals require 3 minutesto relax before opening Hatch.

Open Hatch.Tether hatch tool to hatch handle.Install APAS Hatch Cover.

59


31 OCT 0010179.doc

Secure Hatch in open position to PMA APAS Hatch Standoff.

PMA 4. APAS EQUAL VLV → CL

SHUTTLE EQUALIZATION5. ISS report to shuttle: “PMA Hatch is opened. Go for shuttle equalization

with ISS.”

ODS 6. Equal vlv (one) → NORM Hatch

REMOVING DOCKING EQUIPMENT

CAUTION1. The Docking Target Base Plate Cover should be put on the

Docking Target Base Plate any time the Docking TargetStandoff Cross Bag is not mounted in order to preventscratches, surface damage.

2. The Docking Target Standoff Cross should be put in its bagto protect the Docking Target Standoff Cross when notmounted to the Docking Target Base Plate. The surface ofthese items are very easily scratched.

NOTEDonning of rubber gloves required in handling of DockingTarget Standoff Cross and Docking Target Base Plate.

PMA 7. While maintaining a torque on standoff cross threaded hexagonal cap Hatch nut, loosen jam nut on docking target base plate receptacle by applying

a torque (10" Adjustable Wrench and 1-1/2" Open End Wrench).Temporarily stow jam nut by continuing to rotate it onto smaller,non-threaded diameter of receptacle.

Loosen hexagonal cap nut by applying torque.Continue to rotate cap nut until threaded off of receptacle.

8. Remove and insert cross into Docking Target Standoff Cross Bag.Temporarily stow.

9. Install Docking Target Base Plate Cover.

10. Stow 10" Adjustable Wrench in NOD1 D4_G2.Stow 1-1/2" Open End Wrench in PMA.

OPENING ODS HATCHODS 11. √ODS Hatch ∆P ≤ 0.2 psid

Open ODS Hatch per decal.Equal vlv (one) → OFF, cap installed

60


31 OCT 0010179.doc

DOCKING EQUIPMENT REMOVAL

WARNINGSurfaces may be below freezing for a short time after initial ODSHatch opening. Avoid direct contact with vestibule surfaces untilSHUTTLE VESTIBULE TEMP 1,2 (two) indicate > 40 deg F(SM 177 EXTERNAL AIRLOCK).

12. Wipe any condensate from vestibule volume using towel.

CONFIGURING DUCTINGMO13Q 13. AIRLK FAN A(B) − OFF

Ext A/L 14. Disconnect air inlet flex duct from external A/L duct from halo cross airduct.

PMA 15. Unstow PMA/ODS Interface Duct Segment from PMA.

Ext A/L 16. Connect PMA/ODS Interface Duct Segment to air inlet flex duct withT-handle clamp.

Lab Fwd 17. Lab Fwd Stbd IMV vlv → (deploy handle) OPEN (stow handle)


19. Go to IMV FAN ACTIVATION/DEACTIVATION POST CCS, steps 1, 2,Activate Lab Fwd Stbd Fan (SODF: ECLSS: A&C: THC).

61

02 NOV 00


62

02 NOV 00

MATED OPERATIONS

MATED

OPERATIO

NS

63

02 NOV 00


MATED

OPERATIO

NS

64

HANDOVER ATTITUDE CONTROL ORBITER TO CMG TA(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

31 OCT 005687.doc

1. VERIFYING ISS NOT IN CONTROLPCS MCS


Verify ISS Att Cntl Config − Free Drift

2. PREPARING ISS TO TAKE CONTROL

CAUTIONDuring this step, perform only steps 1 --- 5 of {2.405MODING FREE DRIFT TO CMG TA}. Proceedingpast step 5 may result in both the ISS and orbiterattempting to maintain attitude control.

ISS Perform {2.405 MODING FREE DRIFT TO CMG TA}, steps 1 --- 5, Crew (SODF: MCS: NOMINAL: GNC MODING), then:

ISS (MCC-H) ⇒ orbiter, “ISS ready to begin controlling attitude of MatedStack.”

3. COLLAPSING ORBITER DEADBANDSC3(A6) DAP: B/AUTO/VERN(ALT)

Wait 1 minute, then proceed.

4. PLACING ORBITER INTO FREE DRIFTC3(A6) DAP: FREE

Orbiter ⇒ ISS, MCC-H, “Shuttle is in Free Drift.”

5. ASSUMING CONTROL WITH ISSISS Perform {2.405 MODING FREE DRIFT TO CMG TA}, steps 6 --- 10, Crew (SODF: MCS: NOMINAL: GNC MODING), then:

ISS (MCC-H) ⇒ orbiter, “ISS has assumed attitude control.”

6. RETURNING ORBITER TO NOMINAL CONFIGURATIONIf ALT DAP, return to Group B powerdown.

O14, PRI RJD DRIVER, LOGIC (sixteen) − OFF O15, RJDA-1A L2/R2 MANF DRIVER − ON O16:F

65

02 NOV 00


66

HANDOVER ATTITUDE CONTROL CMG TA TO ORBITER(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

31 OCT 005688.doc

1. VERIFYING ORBITER NOT IN CONTROLC3(A6) √DAP: A/FREE/VERN(ALT)

GNC 20 DAP CONFIG

√DAP A___, B____ loaded

Orbiter ⇒ ISS, MCC-H, “Shuttle ready to begin controlling attitude ofMated Stack.”

2. CONFIGURING ISS TO FREE DRIFTISS Perform {2.404 MODING CMG TA TO FREE DRIFT}, all (SODF: MCS: Crew NOMINAL: GNC MODING), then proceed.

ISS (MCC-H) ⇒ orbiter, “ISS is in Free Drift.”

3. ASSUMING CONTROL WITH ORBITERIf ALT DAP required

O14, PRI RJD DRIVER, LOGIC (sixteen) − ON O15, O16:F

If attitude is to be held in LVLHC3(A6) DAP − A/LVLH/VERN(ALT)

If attitude is to be held in Inertial or XPOPDAP − A/INRTL/VERN(ALT)

GNC UNIV PTG

When rates are < 0.1 degrees/second/axisC3(A6) DAP − A/AUTO/VERN(ALT)

Orbiter ⇒ ISS, MCC-H, “Shuttle has established attitude control.”

67

02 NOV 00


68

GENERIC DEPRESS(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

31 OCT 009162.doc

NOTEMCC will provide MET/EVENT and desiredpressure values for use in this procedure.Expect possible dP/dT Klaxon alarm duringdepress.

MO10W 1. √14.7 CABIN REG INLET SYS 1,SYS 2 (two) − CL

AW82B 2. AIRLK DEPRESS vlv cap − Vent, removeAIRLK DEPRESS vlv − 0

SM 66 ENVIRONMENT

CRT 3. If PPO2 < 2.7 at anytime during depressC5 DIRECT O2 vlv − OP

CRT 4. When CABIN PRESS = desired pressureC5 DIRECT O2 vlv − CLAW82B AIRLK DEPRESS vlv − CL

Install AIRLK DEPRESS vlv cap

MET/EVENT DESIREDPRESSURE

69

02 NOV 00


70

O2 REPRESS(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

31 OCT 005089.doc

NOTE1. Purpose is to pressurize stack to 14.96 psia from 14.7 psia

using orbiter O2 while maintaining ISS O2 concentrationbelow US Segment limit of 24.1 %.

2. O2 repress will be repeated as required to allow adequatemixing and to avoid higher than acceptable O2 concentrationin orbiter cabin.

FDA, C/W LIMITS RESET

NOTE1. CABIN PRESS H/W C/W upper limit is not changed because

it is adequate for the target pressures.

2. PPO2 limits are inhibited to avoid nuisance alarms.

3. O2 is limit-sensed by O2 concentration.

1. Contact MCC-H for uplink of B/U C/W and SM ALERT limit resets viaTMBU, if desired.

B/U C&W PARAM ID ENA/INH HI EUCABIN PRESS 0612405 14.96PPO2 A 0612511 INHPPO2 B 0612513 INH

H/W C&W CHANNEL ENA/INHPPO2 A 34 INHPPO2 B 44 INH

2. √MCC-H for repress Cryo configuration

Node 1 3. √PPRV caps installed on port,stbd Hatches

O2 REPRESS INITIATIONOCAC 4. Perform OCAC filter cleaning.

OCAC PWR → OFF

C5 5. DIRECT O2 vlv − OP

6. When ‘S78 O2 CONC’ or ‘S66 CABIN PRESS ’ or ‘S210 NODE 1 CABPRESS’ message, DIRECT O2 vlv − CL

7. MCC-H may ask for another cycle.Wait for O2 to mix and O2 concentration to stabilize.On call from MCC-H, repeat steps 5 --- 7.

OCAC 8. OCAC PWR → ON

9. √MCC-H for post-repress cryo configuration

71

02 NOV 00


72

GENERIC REPRESS(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

31 OCT 005090.doc

NOTEMCC will provide MET/EVENT and desiredpressure values for use in this procedure.

WARNINGTerminate all WCS activity during repress.

L2 1. O2/N2 CNTLR VLV SYS 1 − OP (N2)2 − AUTO

MO10W 2. O2 REG INLET SYS 2 − OP

3. 14.7 CAB REG INLET SYS 1 vlv − OP

4. On MCC call14.7 CABIN REG INLET SYS 2 vlv − OP

SM 66 ENVIRONMENT

CRT 5. When CABIN PRESS = desired pressureMO10W 14.7 CAB REG INLET SYS 1,SYS 2 vlv (two) − CL

MET/EVENT DESIREDPRESSURE

6. If requiredGo to PCS 1(2) CONFIG (FDF: ORB OPS, ECLSS).

If not requiredMO10W O2 REG INLET SYS 2 − CLL2 O2/N2 CNTLR VLV SYS 2 − CL (O2)

73

02 NOV 00


74

VDS SHUTTLE AUTO ROUTE - DEROUTE(JNT OPS/5A.1/FIN) Page 1 of 3 pages

31 OCT 005466.doc

NOTEThis procedure defines the steps needed to AutoRoute/Deroute the Orbiter Video Signal to the station.Each section can be completed separately.

01 - 09 Auto Route10 - 12 Deroute

1. CHECKING VIDEO ROUTING SOFTWAREPCS C&T: Video: Video Overview

‘Video Software’

√Video Software − Enable

NOTEIf the user is not planning to use ShuttleChannel 02, then skip to step 6.

2. CONNECTING SHUTTLE VIDEO LINECM1 LAB: CVIU 3

2.1 Disconnect Cable from VTR 2 to CVIU 3 at VTR 2 end.

2.2 Connect Cable end to Orbiter Video Patch.

NOTEIf the user does not plan to do a Full-Screen Route, then skipto step 4. When the user does the auto route, the user willneed to select VTR 2 to receive the shuttle video signal.

3. AUTO ROUTE VIDEO SIGNALRefer to AUTO ROUTE - DEROUTE (SODF: JNT OPS).

INC 2 BOOK: C&T: NOMINAL

NOTEIf the user does not plan to do a Split-Screen Route, then skipto step 5. When the user does the auto route, the user willneed to select VTR 2 to receive the shuttle video signal.

4. SPLIT SCREEN ROUTE VIDEO SIGNALRefer to SPLIT SCREEN AUTO ROUTE - DEROUTE (SODF: JNT OPS).


5. COORDINATING VIDEO SIGNALCM1 LAB

5.1 Check that Orbiter Team has completed routing the video signal.

5.2 Check that (VTR2) Orbiter Channel 02 has been routed.

75


31 OCT 005466.doc

NOTEIf the user is not planning to use ShuttleChannel 01, then skip to step 10.

6. CONNECTING SHUTTLE VIDEO LINECM1 LAB : CVIU 6


6.2 Connect Cable end to Orbiter Video Patch.

NOTEIf the user does not plan to do a Full-screen Route, then skip tostep 8. When the user does the auto route, the user will needto select VTR 1 to receive the shuttle video signal.

7. AUTO ROUTE VIDEO SIGNALRefer to AUTO ROUTE - DEROUTE (SODF: JNT OPS).


NOTEIf the user does not plan to do a Split-Screen Route, thenskip to step 9. When the user does the auto route, the userwill need to select VTR 1 to receive the shuttle video signal.

8. SPLIT SCREEN ROUTE VIDEO SIGNALRefer to SPLIT SCREEN AUTO ROUTE - DEROUTE (SODF: JNT OPS).


9. COORDINATE VIDEO SIGNALCM1 LAB



10. CHECKING DESTINATIONPCS C&T: Video: Video Overview

‘LAB’

√Destination − not blank

NOTEIf the user did a Split-Screen Route then skip this step. Whenthe user does the deroute, the user will need to select eitherVTR 1 or VTR 2 to remove the shuttle video signal.

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31 OCT 005466.doc

11. DEROUTING VIDEO SIGNALRefer to AUTO ROUTE - DEROUTE (SODF: JNT OPS).


NOTEIf the user did a full screen route then skip this step. Whenthe user does the deroute, the user will need to selecteither VTR 1 or VTR 2 to remove the shuttle video signal.

12. DEROUTING SPLIT SCREEN VIDEO SIGNALRefer to SPLIT SCREEN AUTO ROUTE - DEROUTE (SODF: JNT OPS).


77

02 NOV 00


78

VDS SHUTTLE MANUAL ROUTE - DEROUTE(JNT OPS/5A.1/FIN) Page 1 of 3 pages

31 OCT 005467.doc

NOTE1. This procedure defines the steps needed to manually

route/deroute the Orbiter Video Signal to the station.Each section can be completed separately.

01 - 08 Manual Route09 - 11 Manual Deroute

2. If the user is not planning to use Orbiter Channel 02,then skip to step 5.



1.2 Connect Cable end to the Orbiter Video Patch.

NOTEIf the user does not plan to do a Full-Screen Route, then skipto step 3. When the user does the manual route, the userwill need to select VTR 2 to receive the shuttle video signal.

2. ROUTING VIDEO SIGNALRefer to VDS MANUAL ROUTE - DEROUTE (SODF: JNT OPS).


NOTEIf the user does not plan to do a Split-Screen Route, then skipto step 4. When the user does the manual route, the user willneed to select VTR 2 to receive the shuttle video signal.

3. SPLIT SCREEN ROUTE VIDEO SIGNALRefer to VDS SPLIT SCREEN MANUAL ROUTE - DEROUTE (SODF:JNT OPS).





NOTEIf the user is not planning to use OrbiterChannel 01, then skip to step 9.

79


31 OCT 005467.doc



5.2 Connect Cable end to the Orbiter Video Patch.

NOTEIf the user does not plan to do a Full-Screen Route, then skipto step 7. When the user does the manual route, the userwill need to select VTR 1 to receive the shuttle video signal.

6. ROUTING VIDEO SIGNALRefer to VDS MANUAL ROUTE - DEROUTE (SODF: JNT OPS).


NOTEIf the user does not plan to do a Split-Screen Route, then skipto step 8. When the user does the manual route, the user willneed to select VTR 1 to receive the shuttle video signal.

7. SPLIT SCREEN ROUTE VIDEO SIGNALRefer to VDS SPLIT SCREEN MANUAL ROUTE - DEROUTE (SODF:JNT OPS).





9. CHECKING DESTINATIONPCS C&T: VIDEO: VIDEO OVERVIEW

‘LAB’

√Destination − not blank

NOTEIf the user did a Split-Screen Route then skip this step. Whenthe user does the manual deroute, the user will need to selecteither VTR 1 or VTR 2 to remove the shuttle video signal.

80


31 OCT 005467.doc

10. DEROUTING VIDEO SIGNALRefer to VDS MANUAL ROUTE - DEROUTE (SODF: JNT OPS).


NOTEIf the user did a Full-Screen Route then skip this step. Whenthe user does the manual deroute, the user will need to selecteither VTR 1 or VTR 2 to remove the shuttle video signal.

11. DEROUTING SPLIT SCREEN VIDEO SIGNALRefer to VDS SPLIT SCREEN MANUAL ROUTE - DEROUTE (SODF:JNT OPS).


81

02 NOV 00


82

02 NOV 00

EGRESS STATION

EGRESS

STATIO

N

83

02 NOV 00


EGRESS

STATIO

N

84

ISS INTERIM EGRESS(JNT OPS/5A.1/FIN) Page 1 of 2 pages

31 OCT 0010180.doc

ISS TOOLS AND EQUIPMENT REQUIREDRubber Gloves


PMA2 Docking Mechanism Accessory KitAPAS Hatch ToolCleaning Pads


CONFIGURING DUCTINGPMA2 1. Open grille cover.

2. Perform {IMV FAN ACTIVATION/DEACTIVATION POST CCS} step 3,Deactivate Lab Fwd Stbd Fan (SYSTEMS: ECLSS: A&C: THC), then:

3. Perform {IMV VALVE RECONFIGURATION POST CCS} step 3, CloseLab Fwd Stbd IMV Valve (SYSTEMS: ECLSS: NOM: THC), then:


Ext A/L 5. Disconnect PMA/ODS Interface Duct Segment from halo inlet flex duct.

PMA2 6. Stow free end of PMA/ODS Interface Duct Segment on PMA2 handrail.

Ext A/L 7. Connect external A/L halo inlet flex duct to halo cross duct with T-handleclamp.

MO13Q 8. AIRLK FAN A(B) − ON√Airflow at halo

INSTALLING DOCKING TARGET

CAUTIONDonning of rubber gloves required in handling of DockingTarget Standoff Cross and Docking Target Base Plate.

9. Remove Docking Target Base Plate Cover from Target Base Plate.Stow cover in PMA2.

10. Remove Docking Target Standoff Cross from Standoff Cross Bag.Stow Standoff Cross Bag in PMA2.

NOTEEnsure key on Standoff Cross shaft is aligned with key-wayon mating receptacle, and insert shaft until collar bottoms outon receptacle surface.

85

ISS INTERIM EGRESS(JNT OPS/5A.1/FIN) Page 2 of 2 pages

31 OCT 0010180.doc

11. Insert Docking Target Standoff Cross into keyed receptacle on DockingTarget Base Plate until shaft collar bottoms out.

NOTEWhen all mating parts are correctly assembled, agroove on Docking Target Standoff Cross shaftshould be visible above cap nut (not recessed).

12. Ensure jam nut is positioned onto smaller, non-threaded diameter ofDocking Target Base Plate receptacle.

Rotate cap nut and tighten very firmly onto receptacle.(10" Adjustable Wrench, 80-100 in-lbs design torque)

Thread jam nut onto receptacle, rotating until contact with cap nutoccurs.

While maintaining a torque on cap nut, firmly tighten jam nut againstcap nut (1-1/2" Open End Wrench, 80-100 in-lbs design torque).

13. Stow 10" Adjustable Wrench in NOD1 D4_G2.Stow Docking Mechanism Asessory Kit in PMA.

ODS HATCH CLOSUREODS 14. Close ODS Hatch per decal. Hatch

15. √EQUAL VLV (two) − OFF, capped

APAS HATCH CLOSUREPMA2 16. Disconnect Hatch from PMA APAS Hatch Standoff.

Secure Hatch.Standoff to PMA handrail.Remove APAS Hatch Cover.Stow cover securely in PMA.Inspect Hatch Seals and seal surfaces for debris/damage.Clean APAS Hatch Seals and surface with Cleaning Pads.Close APAS Hatch.

�� Hatch Tool.

Insert tool in hatch socket (ensure fully seated).Rotate tool 3 --- ! � �� "�� # �$%�� &�� '��( �� )

PMA2 17. APAS EQUAL VLV − CL

WARNINGPMA remains unventilated and should notbe considered a habitable module.Restrict activity in PMA to stowage only.

86

1.104 CBM CENTER DISK COVER INSTALLATION(S&M/4A - ALL/FIN) Page 1 of 6 pages

10 JUL 008207.doc

OBJECTIVE:Install CBM Center Disk Cover to restore thermal and meteoroid debrisprotection to the Node 1 Radial Port.

LOCATION:Installed: Node 1 Radial PortsStowed: √Maintenance and Assembly Task Supplement (MATS)

DURATION:20 minutes

PARTS:CBM Center Disk Cover (P/N 683-14575-001) Nadir/ZenithCBM Center Disk Cover (P/N 683-14575-010) Stbd/Port

MATERIALS:Gray Tape

TOOLS REQUIRED:Mini Maglite Equivalent Shuttle Tools:Portable Fan FlashlightISS Common IVA Tool Kit: Portable FanKit E: IFM Tool Kit:

Ratchet 1/4" Drive Drawer 1:Kit F: Tool Table Cloth

1/4" Socket, 1/4" Drive General Purpose Tape (1")Lid 2: Drawer 3:

Tablecloth 4" Ratchet

1/4" Socket, 1/4" Drive

REFERENCE PROCEDURE(S):None

87


10 JUL 008207.doc

INSTALLING CENTER DISK COVER ONTO MOUNTING BRACKETS

Pulleys (8)

Standoff Bars (4)

Turnbuckles (2)

ClevisPIP Pins (8)(stowed)

Figure 1.- CBM Center Disk Cover.

(IVA side of Zenith/Nadir Cover is shown.)

CAUTIONThis procedure is performed near hatch seals.Care must be taken to avoid seal damage.

1. Remove Center Disk Cover from stowage.Slide Cover into vestibule before unfolding for installation.

2. Unfold Cover, Standoff Bars toward Controller Panel Assemblies (CPAs).Refer to Figure 1.

88


10 JUL 008207.doc

Figure 2.- Side View of Standoff Bar Installed in Standoff Bracket.

3. Slide Standoff Bar Hooks (two each Standoff Bar) into Standoff Bracket.Rotate Standoff Bar away from center of Center Disk Cover.Refer to Figure 2.

4. Remove Standoff Bar PIP Pins (two each Standoff Bar) from stowagelocation on Standoff Brackets.

Insert PIP Pins in restraint location on Standoff Brackets.Refer to Figure 2.

Figure 3.- Clevis PIP Pin Stowed in End of Standoff Bar. (View from IVA Side.)

IVASide

Center Disk Cover

Clevis PIPPin stowagelocation

StowageLocations forStandoff BarPIP Pin

RestraintLocation forStandoff BarPIP Pin

Standoff Bar

TowardsCenter

of CoverStandoffBracket

EVASide

Standoff BarHook

Standoff Bar

Clevis PIP PinStowed in end ofStandoff Bar

Pulley Pulley Restraint

89


10 JUL 008207.doc

Figure 4.- Pulley Restrained by Clevis PIP Pin. (View from EVA Side.)

Figure 5.- Pulley Restrained by Clevis PIP Pin. (View from IVA Side.)

5. Slide Pulley Restraints (eight) into Clevis Bracket until pulley snaps intoplace (sliding towards EVA side).

Refer to Figures 3 --- 5.

6. Remove Clevis PIP Pins (eight) from stowage location at end of StandoffBars.

Insert PIP Pins in Clevis Brackets.Refer to Figures 3 --- 5.

Clevis Bracket

Pulley

StowageLocation forClevis PIP Pin(at end ofStandoff Bar)

Turnbuckle CenterDisk Cover

Clevis Bracket

Clevis PIP Pin

Pulley

Clevis PIP Pin

90


10 JUL 008207.doc

RESTORING TENSION TO CENTER DISK COVER

Figure 6.- Cutaway View of Turnbuckle.

7. Pull out Pull Rings (two each Turnbuckle), then turn 90 degrees andrelease so that Pull Rings remain out on top of Plungers.

If Pull Rings do not remain on top of Plungers, restrain Pull Rings on topof Plungers with Gray Tape.

If required, remove Pull Ring Plungers completely from turnbuckle(two each Turnbuckle) (Ratchet 1/4" Drive, 1/4" Socket).

Temporarily stow.Refer to Figure 6.

Figure 7.- Tightening Turnbuckles.

LowerRight

UpperLeft

From EVA side

From IVA sideFrom EVA side

From IVA side

1/4" Socket

Plunger

Pull Ring

Pull Ring

Turnbuckle

91


10 JUL 008207.doc

8. If on IVA side, tighten Turnbuckles (two) by rotating away from center ofCenter Disk Cover (20 --- 25 turns, shaking every 5 turns until cable istaut).

If on EVA side, tighten Turnbuckles (two) by rotating toward center ofCenter Disk Cover (20 --- 25 turns, shaking every 5 turns until cable istaut).

Refer to Figure 7.

9. If required, remove securing tape on Pull Rings.Rotate Pull Rings so Plungers fall back into place.

If Pull Ring Plungers were removed (refer to Step 7), reinstall intoTurnbuckle (two each Turnbuckle) (Ratchet 1/4" Drive, 1/4" Socket).

Refer to Figure 6.

CLOSEOUT10. Inform MCC-H of task completion.

11. Stow tools, equipment.

92

ODS VESTIBULE/PMA2 DEPRESSURIZATION AND HATCH LEAK CHECK(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

01 NOV 009163.doc

1. √ODS Hatch closed

2. √ODS Hatch Equal vlv (two) − OFF, caps installed

A6L 3. √cb ESS 1BC(2CA) SYS PWR CNTL SYS 1(2) − cl

4. √SYS PWR MNA(MNB) − ctr (tb-ON)

5. cb ESS 1BC(2CA) DEP SYS 1(2) VENT ISOL − cl

6. cb MNA(B) DEP SYS 1(2) VENT − cl

7. VEST DEP VLV SYS 1(SYS 2) VENT ISOL − OP (tb−OP)

8. VEST DEP VLV SYS 1(SYS 2) VENT − OP (tb−OP)Wait 15 minutes.

9. VEST DEP VLV SYS 1(SYS 2) VENT − CL (tb−CL)

NOTEMCC-H will perform ODS Hatch and NodeDeck Hatch leak check overnight.

93

02 NOV 00


94

SHUTTLE/ISS DUCT REMOVAL AND HATCH CLOSING(JNT OPS/5A.1/FIN/MULTI) Page 1 of 3 pages

31 OCT 005095.doc

ISS TOOLS AND EQUIPMENT REQUIREDRubber Gloves


PMA2 Docking Mechanism Accessory KitAPAS Hatch ToolCleaning Pads


CONFIGURING DUCTINGPMA2 1. Open grille cover.

2. Perform IMV FAN ACTIVATION/DEACTIVATION, step 3, Deactivate LabFwd Stbd Fan (SODF: ECLSS: A&C: THC), then:

3. Perform IMV VALVE RECONFIGURATION, steps 3, 4, Closing andDeactivating Lab Fwd Stbd IMV Vlv (SODF: ECLSS: A&C: THC), then:


Ext A/L 5. Disconnect PMA/ODS Interface Duct Segment from halo inlet flex duct.

PMA2 6. Stow free-end of PMA/ODS Interface Duct Segment on PMA2 handrail.

Ext A/L 7. Connect external A/L halo inlet flex duct to halo cross duct with T-handleclamp.

MO13Q 8. AIRLK FAN A(B) − ON√Airflow at halo

INSTALLING CROSSHAIRS, DOCKING TARGET AND LIGHTS9. Install crosshairs per markings.

10. For each docking light, remove the locking pin, install docking lightperpendicular to ODS shell, and reinstall the locking pin.

Reconnect cables.

CAUTIONDonning of rubber gloves required in handlingof Docking Target Standoff Cross and DockingTarget Base Plate.

11. Remove Docking Target Base Plate Cover from Target Base Plate.Stow cover in PMA2.

95


31 OCT 005095.doc

12. Remove Docking Target Standoff Cross from Standoff Cross Bag.Stow Standoff Cross Bag in PMA2.

NOTEEnsure key on Standoff Cross shaft is aligned withkey-way on mating receptacle, and insert shaft untilcollar bottoms out on receptacle surface.

13. Insert Docking Target Standoff Cross into keyed receptacle on DockingTarget Base Plate until shaft collar bottoms out.

NOTEWhen all mating parts are correctly assembled, agroove on docking target Standoff Cross shaftshould be visible above cap nut (not recessed).

14. Ensure jam nut is positioned onto smaller, non-threaded diameter ofDocking Target Base Plate receptacle.

Rotate cap nut and tighten very firmly onto receptacle (10" AdjustableWrench, 80-100 in-lbs design torque).

Thread jam nut onto receptacle, rotating until contact with cap nutoccurs.

While maintaining a torque on cap nut, firmly tighten jam nut againstcap nut (1-1/2" Open End Wrench, 80-100 in-lbs design torque).

15. Stow 10" Adjustable Wrench in NOD1 D4_G2.Stow Docking Mechanism Asessory Kit in PMA.

ODS HATCH CLOSUREODS 16. Close ODS Hatch per decal. Hatch

17. √EQUAL VLV (two) − OFF, capped

APAS HATCH CLOSUREPMA2 18. Disconnect Hatch from PMA APAS Hatch Standoff and secure Hatch.

Standoff to PMA handrail.Remove APAS Hatch Cover.Stow cover securely in PMA.Inspect Hatch Seals and seal surfaces for debris/damage.Clean APAS Hatch Seals and surface with Cleaning Pads.Close APAS Hatch.

�� Hatch Tool.

Insert tool in hatch socket (ensure fully seated).Rotate tool 3 --- ! � �� "�� # �$%�� &�� '��( �� )

96


31 OCT 005095.doc

PMA2 19. APAS EQUAL VLV → CL

WARNINGPMA remains unventilated and should not beconsidered a habitable module. Restrict activityin PMA to stowage only.

IMV CAP/FLANGE SAVER RECONFIGURATIONIf PMA Depress is Planned

20. PMA2 air duct jumper ←|→ Lab Fwd Stbd IMV flange (Use Ratchetand Deep Socket, leave V-band clamp on flange.).

21. IMV cap ←|→ PMA2 launch restraint (Use Ratchet and Deep Socket,leave V-band on flange.)

Replace face and bore O-rings on IMV cap.Lubricate O-rings with Braycote.

22. PMA2 air duct jumper →|← PMA2 launch restraint (Use V-bandclamp, Ratchet, and Deep Socket.)

Secure rest of flex duct to Closeout with velcro straps (two places).

23. IMV cap →|← Lab Fwd Stbd IMV flange (Use V-band clamp, Ratchet,and Deep Socket.)

CLOSING LAB FWD HATCHPMA2 24. √All loose equipment removed from PMA2.

Lab 25. Close Lab Fwd Hatch per decal.√MPEV − CLOSED

97

02 NOV 00


98

02 NOV 00

DEPARTURE

DEPARTURE

99

02 NOV 00


DEPARTURE

100

PMA2 PRE-DEPARTURE CONFIGURATION (POST CCS)(JNT OPS/5A.1/FIN) Page 1 of 5 pages

31 OCT 009256.doc



sel Reset

Verify the Since Reset column values are all blank




√MCC-H

2. VERIFYING FLIGHT SPECIFIC PADMCC-H If the following information is not recorded elsewhere, record it here.

Required for Post-Departure ADO Pri B/U Ver ID Comments1 Mass Properties ps012 CCDB SLOT 1 ca00 Cmd Att Quatrn, Slot1:

CCDB SLOT 1 Quatrn 0CCDB SLOT 1 Quatrn 1CCDB SLOT 1 Quatrn 2CCDB SLOT 1 Quatrn 3

3 Non CCDB CA ca08

NOTEIn order to minimize station motion once attitude control isresumed after orbiter separation, the CCDB loaded to Slot 1should have an attitude rate of 0.01 deg/sec.

3. VERIFYING INITIAL CONDITIONSPCS MCS



‘Primary GNC MDM’


‘Backup GNC MDM’


101


31 OCT 009256.doc

4. LOADING REQUIRED PPLS TO THE PRIMARY GNC MDMFor all PPLs designated in step 2 to be loaded to the Primary GNC MDM,to load that PPL to the Primary GNC MDM perform {1.236 CCS DATALOAD MANAGEMENT}, all (SODF: GND: C&DH: NOMINAL), then:

5. LOADING REQUIRED PPLS TO THE BACKUP GNC MDMFor all PPLs designated in step 2 to be loaded to the Backup GNC MDM,to load that PPL to the Backup GNC MDM perform {1.236 CCS DATALOAD MANAGEMENT}, all (SODF: GND: C&DH: NOMINAL), then:

6. UPDATING POST-DEPARTURE CCDB COMMANDED ATTITUDEMCC-H MCS: MCS Configuration

MCS Configuration‘CCDB Slots’

sel Cmd Att 1

Cmd Att 1

If Cmd Att 0(1)(2)(3) DOES NOT MATCH Quat (0,1,2,3) in step 2

If in step 2, Quat (0,1,2,3) is (1,0,0,0)cmd Attitude Quaternion 1,0,0,0

If in step 2, Quat (0,1,2,3) is NOT (1,0,0,0)Input Quaternion 0 – (from step 2)

1 – (from step 2)2 – (from step 2)3 – (from step 2)

cmd Set

Verify Slot [X] Cmd Att 0 – (as commanded)1 – (as commanded)2 – (as commanded)3 – (as commanded)

7. SETTING MOMENTUM SERVO REFERENCE FRAME


sel Drift

Drift‘Momentum Servo’

NOTEThe purpose of this command is to change the MomentumServo Reference Frame to Inertial. Ignore the commandedmomentum vector components.

102


31 OCT 009256.doc

If Commanded Reference Frame − LVLH(Body)cmd Inertial 0,0,0

Verify Commanded Reference Frame − Inertial

8. VERIFYING ORBITER DOCKED INDICATION



******************************************************If Orbiter Docked Indication − NOT Docked

sel Orbiter Docked Indication Orbiter Docked Indication

cmd Docked

Verify Orbiter Docked Indication − Docked******************************************************

9. SETTING BACK OFF TIME

APAS SW Configuration‘Departure Configuration’

sel Pending Back Off Time

Pending Back Off Time

input Time: 250 (sec)

cmd Set

Verify Pending Back Off Time: 250 (sec)Verify Arm State − Arm

cmd Incorporate Pending Back Off Time

Verify Back Off Time: 250 (sec)Verify Arm State − Disarm

10. VERIFYING POST DEPARTURE CONTROL MODE

APAS SW Configuration‘Departure Configuration’

Verify Post Dprtr Cntl Mode − CMG TA

103


31 OCT 009256.doc

***********************************************************If Post Dprtr Cntl Mode − CMG Only(RS Control)

sel Post Dprtr Cntl Mode Post Dprtr Cntl Mode

cmd CMG TA

Verify Post Departure Control Mode − CMG TA***********************************************************

11. PREPARING US GNC INHIBITS FOR AUTOMATIC SOFTWARERESPONSE


sel US GNC Inhibits

US GNC Inhibits

If Mode Transition − Inhcmd Mode Transition Enable (Verify − Ena)

If Attitude Maneuver − Inhcmd Attitude Maneuver Enable (Verify − Ena)

If Desat Request − Inhcmd Desat Request Enable (Verify − Ena)

If Att Cntl Shutdown − Inhcmd Att Cntl Shutdown Enable (Verify − Ena)

12. VERIFYING STATUS OF DEPARTURE SIGNALS

APAS SW Configuration‘Departure’

Verify PMA2 Interface Sealed LA-1,LA-2 − YesVerify PMA2 Separation LA-1,LA-2 − NoVerify Departure Flag − No

13. ENABLING DEPARTURE RESPONSE SOFTWAREsel PMA2 Departure Response SWPMA2 Departure Response SW

‘Enable’

cmd Arm

Verify State − Arm

cmd Enable

Verify Departure Response SW − EnaVerify State − Disarm

104


31 OCT 009256.doc

14. VERIFYING DEPARTURE EVENT SOFTWARE STATUS


Verify Time Since Separation: 0 (sec)

CAUTIONIf the Primary(Secondary) Time Since Separation is observedto be incrementing any time prior to planned departure, ISSmay take attitude control after 250 seconds. Immediate actionis required.

sel PMA2 Departure Response SW

PMA2 Departure Response SW‘Inhibit’

cmd Inhibit

Verify Departure Response SW − Inh

105

02 NOV 00


106

PMA2 DEPARTURE (POST CCS)(JNT OPS/5A.1/FIN) Page 1 of 6 pages

10 OCT 009257.doc

NOTE1. This procedure should be started about 25 minutes prior

to orbiter departure, so that steps 1 --- 6 are complete nolater than about 5 minutes before undocking.

2. Step 7 puts ISS in Free Drift. This should be done within1 minute of separation. If orbiter is controlling the matedstack before undock, this step is not performed.

3. Orbiter separation occurs in step 8.

4. Step 9 should be completed as soon as practical afterseparation.

5. Step 10 is provided for information only.

6. Step 11 should be performed when orbiter reaches arange of 50 feet.



sel Reset





√MCC-H

2. VERIFYING POST-DEPARTURE PADIf the following data is not recorded elsewhere, record it here:

For step 5: Post-Departure Mass Properties PPL Version ID ________Post-Departure Non-CCDB CA PPL Version ID ________



Verify US Station Mode − Prox OpsVerify RS Station Mode − Prox OpsVerify US GNC Mode − CMG TA(Drift)Verify RS GNC Mode − CMG TA(Indicator)

107


10 OCT 009257.doc

‘US Inhibits’

Verify Mode Transition − EnaVerify Attitude Maneuver − EnaVerify Desat Request − EnaVerify Att Cntl Shutdown − Ena



‘Departure Configuration’

Verify Back Off Time: 250 (seconds)Verify Post Dprtr Cntl Mode − CMG TA

‘Departure’

Verify PMA2 Departure Response SW − EnaVerify PMA2 Interface Sealed LA-1,LA-2 − YesVerify PMA2 Separation LA-1,LA-2 − NoVerify Departure Flag − NoVerify Time Since Separation: 0 (seconds)

4. CONFIRMING STATION READY TO RESUME CONTROL AFTERUNDOCK


‘GNC Moding’

sel CMG TA

CMG TA

If Thrusters Available for CMG Desat − Nocmd RS Prepare Thrusters for CMG Desat

NOTEIt could take up to 205 seconds for the RS GNC systemto prepare the thrusters for CMG desaturations.

Verify Thrusters Available for CMG Desat − Yes

5. VERIFYING POST DEPARTURE PPLs LOADED IN BUFFERPCS MCS: PPL Version IDs


Verify Mass Properties Primary MDM Version ID − (as recorded in step 2)

108


10 OCT 009257.doc

Verify Non-CCDB CA PPL Primary MDM Version ID − (as recorded instep 2)

NOTEDo not close the PPL Version IDs page until after step 9.

6. INHIBITING AUTO ATTITUDE CONTROL HANDOVER TO RSPCS MCS: MCS Safing


If Auto Att Control Handover to RS − Enasel Auto Att Control Handover to RS

Auto Att Control Handover to RS‘Inhibit’

cmd Arm (No telemetry available)cmd Inhibit

Verify Auto Att Control Handover to RS − Inh

7. MODING ISS TO FREE DRIFTIf orbiter is controlling the stack, do not perform this step.


‘GNC Moding’

sel Drift

Drift‘Moding’

Verify US Drift Available − Yes

cmd Mode to Drift

Verify US GNC Mode − Drift

8. ORBITER SEPARATIONISS ⇒ orbiter, “Station ready for undocking.”Orbiter ⇒ ISS, “Separation.”

Record the following for reference:

Time of Separation ____/___:___:___

Time of Separation + 04:10 = ____/___:___:___ Time to GO to CMG/TA

109


10 OCT 009257.doc

9. INCORPORATING POST DEPARTURE PPLSThis step must be completed before Time Since Separation reaches250 seconds.


cmd Mass Properties – Incorporate Executecmd A-Matrix – Incorporate Executecmd Flex Filter – Incorporate Executecmd Steering Law Params – Incorporate Executecmd Momentum Servo Params – Incorporate Execute

10. VERIFYING APAS INDICATION OF SEPARATION

NOTEThis step shows the indications from APASand the ACS moding function that confirmseparation.


Verify PMA2 Interface Sealed LA-1,LA-2 − NoVerify PMA2 Separation LA-1,LA-2 − YesVerify Time Since Separation − <incrementing>

******************************************************If Time Since Separation is not incrementing

Go to step 12 (RESUMING ATTITUDECONTROL − MANUAL).

******************************************************

NOTE1. Step 11 monitors the ISS Attitude Control Configuration as the

automatic ACS moding software sends two commands to USGNC: (1) mode to CMG TA with CCDB slot 1 and (2) holdcurrent attitude.

2. If, for whatever reason, the automatic mode transition does nottake place, in step 12 the operator sends those two commands.These commands must be sent with as short a delay betweenthem as possible. The operator may wish to pull up both theCMG TA Instances page and the Attitude Hold page, and havethem side-by-side below the APAS SW Configuration page.

11. RESUMING ATTITUDE CONTROL – AUTOMATICOrbiter ⇒ ISS, “50 feet”


110


10 OCT 009257.doc

If (Back Off Time) – (Time Since Separation) > 60 secondsGo to step 12 (RESUMING ATTITUDE CONTROL – MANUAL).

When Time Since Separation > Back Off Time, proceed.

Verify Time Since Separation > 250 seconds and incrementing.

‘Station Configuration’

Verify US GNC Mode − CMG TAVerify RS GNC Mode − CMG TA

ISS ⇒ orbiter, “Station is in CMG TA, holding current attitude.”

*******************************************************************************If either US GNC Mode or RS GNC Mode is not CMG TA

Go to step 12 (RESUMING ATTITUDE CONTROL − MANUAL).*******************************************************************************

12. RESUMING ATTITUDE CONTROL – MANUALThis step should be performed only if one of the following conditions istrue:

Time Since Separation is not incrementing (step 10 off-nominal block), or

Time Since Separation is incrementing, and is less than Back OffTime by more than 60 seconds (top of step 11), or

Time Since Separation is incrementing, is greater than Back Off Time,and the automatic ACS moding was not successful (step 11 off-nominalblock).

Orbiter ⇒ ISS, “50 feet”

MCS: MCS ConfigurationMCS Configuration

‘GNC Moding’

sel CMG TA

CMG TA‘Mode to CMG TA’

sel CMG TA Instances

CMG TA Instances

cmd Mode to CMG TA using CCDB Slot 1

Verify Active CCDB Source Slot: 1Verify US GNC Mode − CMG TAVerify RS GNC Mode − CMG TA

111


10 OCT 009257.doc

MCS Configuration‘Attitude Information’

sel Attitude Hold

Attitude Hold

cmd Hold Current Attitude

ISS ⇒ orbiter, “Station in CMG TA, holding current attitude.”

112

PMA2 POST DEPARTURE CONFIGURATION (POST CCS)(JNT OPS/5A.1/FIN) Page 1 of 2 pages

31 OCT 009258.doc



sel Reset





√MCC-H





Verify Orbiter Docked Indication − Not Docked

‘Departure’

Verify PMA2 Departure Response SW − EnaVerify PMA2 Interface Sealed LA-1,LA-2 − NoVerify PMA2 Separation LA-1,LA-2 − YesVerify Time Since Separation > 250 and incrementing

3. REPLACING US GNC SOFTWARE INHIBITS

NOTEThe Desat Request remains enabled to allowfor automatic desaturations of the CMGs.


sel US GNC Inhibits

US GNC Inhibits

113

PMA2 POST DEPARTURE CONFIGURATION (POST CCS)(JNT OPS/5A.1/FIN) Page 2 of 2 pages

31 OCT 009258.doc

cmd Mode Transition Inhibit (Verify – Inh)cmd Attitude Maneuver Inhibit (Verify – Inh)cmd Att Cntl Shutdown Inhibit (Verify – Inh)

4. DISABLING DEPARTURE RESPONSE SW


sel PMA2 Departure Response SW

PMA2 Departure Response SW‘Inhibit’

cmd Inhibit

Verify Departure Response SW − Inh

5. ENABLING AUTO ATTITUDE CONTROL HANDOVER TO RSPCS MCS: MCS Safing


sel Auto Att Control Handover to RS

Auto Att Control Handover to RS‘Enable’

cmd Enable

Verify Auto Att Control Handover – Ena

114

02 NOV 00

COMM/DATA

COMM/D

ATA

115

02 NOV 00


COMM/D

ATA

116

COMMUNICATIONS CONFIGURATION(JNT OPS/5A.1/FIN) Page 1 of 1 page

31 OCT 009175.doc

VOSKHOD – SM audio systemCP 2 – SM Comm Panel 2 – slaves config of FGB CH1/USOS RSA1CP 3 – SM Comm Panel 3 – slaves config of FGB CH2/USOS RSA2IMCU – Intermodule Communications UnitFGB Audio – FGB Audio CenterRAIU – Russian Audio Interface UnitDAIU – Docked Audio Interface UnitAUAI – ACS/UCS Audio InterfaceABC – Audio Bus CouplerIAC – Internal Audio ControllerATU 1(2) – Audio Terminal UnitRSA - Russian Space AgencyCC - Capcom

SM FGB

PMA3

PMA1

Z1

P6

NODE1

S-BD LDR (no voice)(optional cmd/tlm)(GCMR + CATO cmd rqd)

VHF 2

➀ ISS voice via STS A/G 1 relay (ISS Sbd is prime).➁ VHF 2 May be used when over Russian ground sites.➂ ISS prime cmd/tlm via S-BD HDR when available – OIU is backup.➃ MCC-M relay enabled as required.➄ Only 4 Orbiter HL loops available – A1R must be ON.

From ISS – reconfigurable; orbiter ATU must be configured➅ ISS Ku prime for OCA/Video/PL Data when activated; ECS dismantled➆ Avionics Rack #3 must be installed for RS to US audio

VHF1&2

VHF 1(A/G 1)

US LAB PMA2

S-BD HDR voice (S/G 1&2)(STS A/G 1 backup) �

Cmd/Tlm�(SHO rqd) ISS

MCC

STSMCC

MCCM

A/G 2 (STS)

A/G 1 (ISS) �

STSRelay

STSCC

ISSCC

MCC-M

Relay

S/G

A/G�

VOSKHOD

IMCU FGBAUDIO

IAC

ATU1

ATU2

CP CPCP 2

CP 3CH1CH2

CP 1CP 4CP 5CP 6

ECS (OCA voice)(B/U to S/G 1& 2)(SHO rqd)

� A1R - Spacelab SwitchesA/G 1, A/A, ICOM A, Page

DAIUABC

AUAI

Ku – PL Data/Video/OCA �

OCA portOCA port

STS

VHF

CDR ATU

ARIU(EVA)

BPSMU

AC

CU

�

RSA VHF �

B/U(voice relay)

117

02 NOV 00


118

SHUTTLE VHF SETUP(JNT OPS/5A.1/FIN) Page 1 of 3 pages

31 OCT 008950.doc

1. STOWAGEUnstow:

VHF RadioARIUVHF ARIU/Radio Cable 4'VHF ISS Antenna Cavity (Window Shade)Antenna Adapter Plate (W6/W1) (Window Shade)BPSMUBPSMU/ODS AdapterAudio/Video I/F Cable 42'

Pre-routed cables:VHF Radio DC Power Cable 12'VHF ARIU/ATU Cable 4' with VHF Radio Comm Extension cable 14'VHF Antenna Cable 20' with AttenuatorAudio/Video I/F Cable 4'

2. ANTENNA INSTALLATIONW6(W1) Remove Window Shade.

Assemble VHF ISS Antenna Cavity to Antenna Adapter Plate.Connect VHF Antenna Cable with Attenuator on ISS Antenna Cavity.Install Antenna Assembly in window.

NOTE1. Place antenna cavity fastener loops over all eight metal

tabs before closing fasteners.

2. Do not touch circuitry inside cavity.

3. Antenna must be flush against window to form groundplane using orbiter.

3. RADIO/ARIU SETUPVHF Radio √Power – Off (vol)

L5 √CDR COMM CCU PWR – OFF

Connect VHF Radio Comm Cable to CCU.

MO52J √DC UTIL PWR – OFF√VHF Radio DC Power Cable to PDB outlet (J2)

Connect VHF Radio DC Power Cable to VHF Radio (J1).Connect VHF ARIU/Radio Cable to both ARIU (J3) and to VHF Radio(AUDIO).

Connect VHF ARIU/ATU Cable to ARIU (J1).Connect BPSMU/ODS Adapter to ARIU (J2).Connect BPSMU Battery.

119


31 OCT 008950.doc

Connect 4' Audio/Video I/F Cable to BPSMU/ODS Adapter.Connect 42' Audio/Video I/F Cable to 4' Audio/Video I/F Cable.Connect BPSMU to 42' Audio/Video I/F Cable.Connect VHF Antenna Cable to VHF Radio (ANT).

4. RADIO AND AUDIO SYSTEM CONFIGURATIONO5 AUD PWR – AUD

A/G1 – T/RAll others – OFFVOL A/G 1 – as required (5 minimum)XMIT/ICOM MODE – PTT/PTT

L5 CDR COMM CCU PWR – ON

ARIU XMIT sw – EVA

MO52J DC UTIL PWR – ON

VHF Radio Power – On (vol)Volume, Squelch − as required

5. CHANNEL SELECTION CHECK

NOTEChannel check is done in reverse order so defaultchannel 1 is selected at the end of the check.

Keypad Press CH 1-5Channel 5 − Contingency VHF-2 Half Duplex

√XMIT: 121.75MHz (Medium power)√RCV: 130.1625 MHz

Channel 4 – Shuttle/Soyuz/Joint EVA (Half Duplex)√XMIT: 143.625 MHz (Medium power)√RCV: 139.2125 MHz

Channel 3 − Shuttle/ISS/Soyuz simplex√RCV/XMIT: 121.75 MHz (Medium power)

Channel 2 − Shuttle/ISS (Docked) Half Duplex√XMIT: 139.2125 MHz (Low power)√RCV: 143.625 MHz

Channel 1 – Shuttle/ISS (RNDZ) Half Duplex√XMIT: 139.2125 MHz (Medium power)√RCV: 143.625 MHz

120


31 OCT 008950.doc

6. VHF RADIO SETTINGS CHECK

NOTEIf radio channels settings not correct, useVHF Cue Card to reprogram settings.

Verify VHF radio settings√AM/FM (Modulation) – FM

√PCV (Encryption) – PT (clear)

√PWR (Power) – MED(LO) as required

WARNINGDo not operate VHF Radio in HI power. Exceedsmaximum allowable radiation levels inside cabinand antenna can be damaged.

121

02 NOV 00


122

SHUTTLE VHF ACTIVATION(JNT OPS/5A.1/FIN) Page 1 of 1 page

31 OCT 008951.doc

VHF TRANSCEIVER POWERUP AND CHECKOUT1. Power radio → On

SQUELCH → Full ccw (for VOL adjust)VOL → as requiredSQUELCH → as required

If speaker is requiredMODE → PressSPKR → Press

√SPKR Annunciator Symbol – “SPKR”

To disable speaker, repeat steps and verify SPKR Annunciator Symbol –blank

2. Panel Illumination adjustLAMP – Press and releaseRepeat for desired back lighting.

NOTEChannel 2 is recommended post docking. If ISS experiencestrouble hearing shuttle, switch to Channel 1 and notify MCC-H.

3. Channel Selection CH – PressSELECT – 1, 2, 3, 4, 5

Channel 1 – Shuttle/ISS (RNDZ) Half DuplexXMIT – 139.2125 MHz (Medium power)RCV – 143.625 MHz

Channel 2 – Shuttle/ISS (Docked) Half DuplexXMIT – 139.2125 MHz (Low power)RCV – 143.625 MHz

Channel 3 – Shuttle/ISS/Soyuz simplexXMIT/RCV – 121.75 MHz (Medium power)

Channel 4 – Shuttle/Soyuz/Joint EVA Half DuplexXMIT – 143.625 MHz (Medium power)RCV – 139.2125 MHz

Channel 5 – Contingency VHF-2 Half DuplexXMIT – 121.75 MHz (Medium power)RCV – 130.1625 MHz

4. ISS crew configures comm system in preparation for communicationswith shuttle.

123

02 NOV 00


124

HARDLINE AUDIO CONFIG (ISS)(JNT OPS/5A.1/FIN) Page 1 of 1 page

31 OCT 0010182.doc

A1R 1. AUD CTR SPACELAB PAGE − ONA/G 1 − ONA/A − ONICOM A − ON

NOTEISS audio config must be complete before next step. Perform a commcheck on one loop at a time. Choose MD or FD ATU as desired.

2. Establish voice contact with ISS, adjusting vol as required.

R10/ MS AUD/MD SPEAKER AUD M042F Verify PAGE ____

ICOM A____A/A____A/G 1_____

3. When comm checks complete, reconfigure ATU

R10/MO42F MS AUD/MD SPEAKER AUD A/G1- T/R, tw - 2A/G2 - RCV, tw - 2A/A - RCV, tw- 2ICOM A - T/R, tw - 2B - RCV, tw - 2

XMIT/ICOM MODE sel - PTT/PTTA13/MO42F MSTR SPKR VOL sel - 8

125

02 NOV 00


126

HARDLINE AUDIO CONFIG (ISS) BACKOUT(JNT OPS/5A.1/FIN) Page 1 of 1 page

31 OCT 0010183.doc

A1R AUD CTR SPACELAB PAGE – OFF AUD CTR SL A/G 1 – OFF AUD CTR SL A/A – OFF

COM A – OFF

127

02 NOV 00


128

2.304 PCS LOG FILE SAVE(POC/4A - ALL/FIN A) Page 1 of 1 page

12 SEP 005330.doc

PCS 1. CDS LOGS DUMPIf PCSCDS Main Control Panel is an icon,double-click the ‘cds_ui’ icon to restore it.

PCSCDS MAIN CONTROL PANEL

sel Filesel Update Log Files

2. SAVE LOGSsel Arrow directly above PCS logosel Save Logs

PCS save logs

Disregard text.Press enter.

NOTE1. The format to use for naming the directory is:

[userinitials] logs [flight day]

2. Use a different directory name each time you save the logs. Ifthe logs need to be saved more than once in a flight day, appendthe directory name with an underscore and a number starting at“1” and increment each time that the logs are saved that day. Anexample directory name would be:

abclogs07_2

Enter directory name.Press enter.

Verify message − Save logs completed

Press enter.

PCS 3. VERIFYING THE LOGS HAVE BEEN SAVEDRight-click anywhere on empty desktop space.

sel Programssel Terminal…

Type ‘cd <directory name>’.Type ‘ls -l’.

Verify Runtime_files/ and logs/ are in the directory.

Close terminal window.

4. Inform MCC-H with the directory name.

129

02 NOV 00


130

2.306 PCS RECONNECT(POC/4A - ALL/FIN A) Page 1 of 1 page

12 SEP 007061.doc

1. CDDF AND CDS SHUTDOWNClose all display windows.Disconnect CDS from MDM.Close CDS window.

2. CONNECTING PCS TO MDM DATAsel Arrow directly above PCS logosel Start/Restart PCS CDS

If popup window appears asking what time source to useOn EPCS

sel RS Time

On PCSsel MDM Time

NOTEA pop-up window may appear saying that the CW Serverfailed to start and it will be retried every 15 seconds.

sel Icon to open PCSCDS Main Control Panel Window

√Status Box is green and ‘Connected ’ is displayed in the PCSCDS MainControl Panel Window

Iconify PCSCDS Main Control Panel Window.

3. PCS FOR DISPLAYS CONFIGURATIONsel Arrow above PCS logosel Start PCS CDDF display

After approximately 1 minute, √‘Increment xA Home Page ’ is displayed.

Displays may now be selected as desired.

131

02 NOV 00


132

2.307 PCS SCREEN CAPTURE(POC/2R - ALL/FIN A) Page 1 of 2 pages

12 SEP 005329.doc

1. OPENING SNAPSHOT WINDOWMove the pointer to an open area on the desktop.Press the right mouse button.

sel Programssel Snapshot…

2. TAKING SNAPSHOT

NOTEYou must have the window that you wishto snapshot open and uncovered.

Snapshot V3.X

sel box next to ‘Hide Window During Capture’sel Snap

NOTEWhen you click on the window, the SnapshotWindow will disappear for 8 --- 16 seconds.

Click on the window you want to take a snapshot of.

3. SAVING SNAPSHOT

NOTEThe image file will be saved in the/export/home/PCSUser directory.

Snapshot V3.X

sel View…

Image Tool V3.X File: Untitled

sel Filesel Save As…

Image Tool: Save As‘File Format’

sel Sun Rastersel GIF

Save As…

Type over ‘Untitled1’ with the name that you wish to call the imagefollowed by ’.gif’.

133

2.307 PCS SCREEN CAPTURE(POC/2R - ALL/FIN A) Page 2 of 2 pages

12 SEP 005329.doc

NOTEThere will be a pop-up window with the message‘Saving to the GIF file format may result in aloss of data. Do you want to continue? ’ Thedifference is negligible and can be ignored.

sel Savesel Yes

Close the display and Snapshot application.

4. RETRIEVING AND VIEWING THE IMAGERight-click on any empty space on the desktop.

sel Programssel Image Viewersel Filesel Open…sel <the desired file>sel OK

Close Image View - Palette window.

134

2.309 TRANSFERRING LOG FILES TO FLOPPY DISK(POC/4A - ALL/FIN A) Page 1 of 1 page

12 SEP 007064.doc

1. PERFORMING PCS LOG FILES SAVEPerform {2.304 PCS LOG FILE SAVE}, all (SODF: POC: NOMINAL:PCS) as needed, then:

2. RUNNING COPY LOGS TO FLOPPY UTILITYsel Arrow directly above PCS logosel Copy PCS logs to floppy

Press Enter.

NOTEIf action fails, the following will be displayed:

If no disk in drive, insert diskette, try again.If no floppy drive attached, shutdown, attach floppy drive, andreboot.

If floppy drive is attached after boot up, shutdown and reboot.If floppy drive not seated properly, shutdown, re-seat, andreboot.

Input directory name from list of available directories listed in theTerminal Window.

sel OK

Verify Copy logs to floppy complete.

Press Enter.

Manually Eject Floppy Disk.

135

02 NOV 00


136

2.303 PCS DEACTIVATION(POC/4A - ALL/FIN A) Page 1 of 2 pages

12 SEP 005743.doc

1. POWERING DOWN EPCS/PCSClose all display windows.Disconnect CDS from MDM.Close CDS window.

At the taskbar on bottom of display,sel EXIT

On Logout Confirmation windowsel OK

When ‘Type any key to continue ’ message appears

If shuttle AFDPCS PCS 1,2 Thinkpad pwr sw → Off

Pwr Sply PCS1 28V DC Pwr Sply sw → Off (Lt Off)PCS2 28V DC Pwr Sply sw → Off (Lt Off)

A15 MNC DC UTIL PWR (J2) → Off

PDIP DC POWER 2 → Off

If in SMPCS PCS Thinkpad pwr sw → OffPwr Sply PCS 28V DC Pwr Sply sw → Off (Lt Off)

If in FGBPCS PCS Thinkpad Pwr sw → OffPwr Sply PCS 28V DC Pwr Sply sw → Off (Lt Off)�� → OFF

2. DISCONNECTING EPCS/PCS POWER AND DATA CABLEIf shuttle AFD

L12/A3 Disconnect both ORB 1553 Data Cables 8' from N1-1 (J103) andN1-2 (J107) and from the1553 PC Card Adapter Cables.

Disconnect both the ORB DC Power Cable 6' and ORB DC PowerCable 10' from the RS/ORB DC power supply (J1) and the ORB DCoutlets.

Disconnect both the ORB Power Supply Adapter Cable 10' from thePCS DC power outlet and the RS/ORB DC power supply (J2).

~

137

2.303 PCS DEACTIVATION(POC/4A - ALL/FIN A) Page 2 of 2 pages

12 SEP 005743.doc

If in SMDisconnect RS DC Power and 1553 Cable 8' to PCR outlet and theRS/ORB DC power supply outlet (J1) and the 1553 PC Card AdapterCable.

Pwr Sply Disconnect the ORB Power Supply Adapter Cable 10' from theRS/ORB DC power supply outlet (J2) and from the PCS.

If in FGBDisconnect RS DC Power and 1553 Cable 8' to PCR outlet and theRS/ORB DC power supply outlet (J1) and the 1553 PC Card AdapterCable.

Pwr Sply Disconnect the ORB Power Supply Adapter Cable 10' from theRS/ORB DC power supply outlet (J2) and from the PCS.

��-10/3 Disconnect the cable, protruding from the GNC 2/RS Bus 8(GNC 1/RS Bus 7) panel (cables are labeled 77KM-2120-1670 and77KM-2120-2190, respectively), from the 10A connector on panel��

3. STOWING EPCS/PCSPCS Thinkpads20V DC Power Cables 10'1553 Card and 22-inch Adapter CardIf shuttle AFD

Stow ORB DC Power Cable 6'ORB DC Power Cable 10'ORB 1553 Data Cables 8'RS/ORB DC Power Supply

If ISS RSStow RS DC Power and 1553 Cable 8' in the FGB.

RS/ORB DC Power Supply

~

138

AUDIO CONFIGURATION FOR RUSSIAN VOICE COMM CHECKS(JNT OPS/5A.1/FIN Page 1 of 2 pages

31 OCT 007575.doc

1. CABLE CONNECTIONSCheck that RAIU1 Address Connector and Audio Cable Connected.

2. POWERING ON RAIU1 FOR FIRST USEPCS LAB: C&T: Audio Overview: Audio Subsystem


sel RAIU1sel RPCM LAD22B A RPC 08cmd Close

√Position − Close

3. SETTING UP PUBLIC RUSSIAN VOICE LOOPSPCS LAB: C&T: Audio Overview: Audio Subsystem


sel RAIU1

√IAC(2) − On and Active

‘RAIU1 Bus IO’

cmd Enable

√RAIU1 Audio Bus IO - Enable

‘RAIU1 State’

cmd Active

√State − Active

Audio Subsystem‘Audio Displays Menu’




‘Public1’

sel Selectcmd RSA1

‘Public4’

139

AUDIO CONFIGURATION FOR RUSSIAN VOICE COMM CHECKS(JNT OPS/5A.1/FIN Page 2 of 2 pages

31 OCT 007575.doc

sel Selectcmd RSA2

4. CREW PERFORMING VOICE CHECKS TO GROUND AND RSAAFT ATU Lab1 ATU Lab1 pb → 1 Lab1 Page RSA1

Perform voice checks on RSA1.

FWD ATU ATU Lab2 pb → 4 Lab2 Page RSA2

Perform voice checks on RSA2.

ATU Lab2 pb → 2

140

02 NOV 00

MALFUNCTION

MALFUNCTIO

N

141

02 NOV 00


MALFUNCTIO

N

142

SHUTTLE/ISS VHF COMM MAL(JNT OPS/5A.1/FIN) Page 1 of 3 pages

01 NOV 008953.doc

1

Radio frequencyinterference maycause a temporaryloss of the VHF link.Reattempt contactfor several minutesprior to declaring afailure.

2

SHUTTLE VHF 1freq set:XMIT = 139.2125RCV = 143.625ISS VHF 1 freq set:XMIT = 143.625RCV = 139.208

3

FocustroubleshootingSHUTTLE VHF firstsince it is notpermanent H/W andrequires significantconfiguration.

Shuttle/ISS VHFComm Mal

Nominal Config:SHUTTLEISS antenna cavityand 20' antennacable withattenuator installed

VHF radio CH 1(2)selected.

ARIU J1 connectedto CDR ATU via 14'pre-routed VHFradio comm cableand 4' ARIUAudio/Pwr cable.

CDR ATU A/G2 T/R,all else OFF.

ARIU J3 connectedto VHF radio audiovia 4' Radio/ARIUcable.

BPSMU, 42'audio/video I/Fcable, and 4'audio/video I/Fcable w/ODSadapter installed atARIU J2 inputconnector.

ISSVHF 1 A/G voiceconfig from any SMcomm panel.

1 Shuttle or ISS

•√MCC to verify other shipconfigured for VHF 1 ops

2 Shuttle or ISS

• Reattempt contact

Contact successful? 3

• Continue nominaloperations.

4 Shuttle or ISS

• Ask MCC if other shipreceiving and to haveother ship attemptcontact.

• Establishes what partialcapability may exist iftime does not permitextensivetroubleshooting.

ISS

Shuttle

5 ISS

•√MCC for next availableVHF 1 ground site passand attempt groundcontact

ISS ground contactsuccessful?

6 Problem isolated toISS H/W.

Yes

No

No

Yes

7 Problem isolated toShuttle H/W.

8 ISS

• Configure alternatecomm panel for VHF 1A/G voice and reattemptcontact.

Contact successful?

9

• Notify MCC of successfulground contact

• Standby while Shuttletroubleshootingcontinues.

10 ISS

• Original ISS comm panelproblem.

• Continue nominal ops onalternate comm panel.

11 Shuttle

•√Error messages on radioLCD

Any messages? 12 Shuttle VHF radioproblem.

13 Shuttle

•√MCC• Swap out radio.

14 Shuttle

•√Antenna adapter plateflush against window

• Reattempt contact withISS.

Contact successful? 15

Continue nominaloperations.

Yes

No

Yes No

1 2

3

27

16

Yes

No

143


01 NOV 008953.doc

16 Shuttle

• Readjust squelch settingto just above noise.

• Reattempt contact.

Contact successful?

14

17

• Continue nominaloperations.

Yes

No

18 Shuttle

•√Stuck key (mutes rcvr!)

TX displayed on radio LCDwhen audio loop not keyed?

19 Problem isolated toSHUTTLE H/W. BPSMU,ATU, ARIU, or VHF radioproblem.

Yes

No

20 Shuttle

•√Radio being keyed andxmtr transmitting on radioLCD

• Go to meter mode onradio [mode (6), pwr (8)]

• Key audio loop andperform test count.

TX (and approx 5 bars forMED pwr) displayed onradio LCD while counting?

21 Problem isolated toSHUTTLE H/W. BPSMU,ATU, ARIU, or VHF radioproblem.

No

Yes

22 Shuttle

Perform following steps astime permits, reattemptingcontact after each step:• Cycle PTT several times.• Check or swap out

BPSMU.• Replace BPSMU with

VLHS/HIU plugged intoARIU.

• ARIU switch to EXCLMIR XMIT.

• ARIU switch to XMITDIS.

• Use radio handset orswap out ARIU.

• Power cycle VHF radio.• Swap out VHF radio.• Swap out each interface

cable.•√MCC

23 Shuttle

•√Internal pwr supply status

While still in meter mode:• Press [R/T] to display

PS1 (~500)• Press [R/T] to display


PS3 (~ -500)• Press [R/T] to display

PS4 (~ -120)• Press [R/T] to display


PS6 (~700)• Press [R/T] to return to

signal strength meter• Exit meter mode [mode

(6), pwr (8)]

All pwr supplies asexpected?

24 Shuttle VHF radioproblem.

No

Yes

25 Shuttle

•√MCC• Swap out radio.

26

144


01 NOV 008953.doc

4

VHF 2 frequency setinterferes withCONUS air trafficcontrol. VHF 2 useover CONUSrestricted toemergencysituations only.

5

SHUTTLE VHF 2freq set:XMIT = 121.75RCV = 130.1625ISS VHF 2 freq set:XMIT = 130.167RCV = 121.75

26 Shuttle

Perform following steps astime permits, reattemptingcontact after each step:• Power cycle VHF radio.• Check or swap out

BPSMU.• Use radio handset or

swap out ARIU.

23

27 Shuttle and ISS

Attempt contact via VHF 2frequency set.• Verify not over CONUS.•√MCC to verify other ship

configuring for VHF 2comm

28

Shuttle• Select CH 5 on VHF

radio.•√MCC

ISS• Configure comm panel

for VHF 2.•√MCC

29 Shuttle or ISS

• Reattempt contact.

Contact successful? 30 VHF 1 freq setproblem.

31 Shuttle and ISS

Return to VHF 1 freq. set. 32

•√MCC

33

Shuttle• Select CH 1(2) on VHF

radio.•√MCC

ISS• Configure comm panel

for VHF 1.•√MCC

Yes

No

54

8

145

02 NOV 00


146

2.305 PCS REBOOT(POC/4A - ALL/FIN A) Page 1 of 2 pages

12 SEP 007062.doc

1. POWERING DOWN EPCS/PCSClose all display windows.

If PCS does not accept inputs from the keyboard or mouse, go to step 2.

Disconnect CDS from MDM.

Close CDS window.

At the taskbar on bottom of displaysel EXIT

On Logout Confirmation windowsel OK

Wait for ‘Type any key to continue ’ message to appear.

2. TURNING OFF POWERPCS Thinkpad pwr sw → Off

Wait 10 seconds.

3. TURNING ON POWERPCS Thinkpad pwr sw → On

4. CONNECTING EPCS/PCS TO MDM DATAPCS2 After bootup, when taskbar appears at bottom of display

sel Arrow directly above PCS logosel Start/Restart PCS CDSsel Icon to open PCSDCS Main Control Panel Window

√Status Box is green and ‘Connected ’ is displayed in the PCSCDSMain Control Panel Window

Iconify PCSCDS Main Control Panel Window.

5. CONFIGURING PCS FOR DISPLAYSsel Arrow above PCS logosel Start PCS CDDF display

After approximately 1 minute, √‘Increment xA Home Page ’ is displayed.


147

2.305 PCS REBOOT(POC/4A - ALL/FIN A) Page 2 of 2 pages

12 SEP 007062.doc

****************************************************************If GMT - <static> or telemetry fields in Caution &Warning toolbar are cyan, go to {2.306 PCSRECONNECT}, all (SODF: POC: NOMINAL: PCS).

****************************************************************


148

C&DH 3.602 LOSS OF PCS TELEMETRY (POST CCS)(C&DH/5A - ALL/FIN 1) Page 1 of 3 pages

19 OCT 005766.doc

1Nominal Config:MDM CC1 − PrimMDM CC2 − BkupMDM CC3 −Stdby/Off

3

1

If in AFD, orbitercrew will need tocontact station crewto determine if PCSis connected.

2

Potential CCSFailure. Connectionshould beperiodicallyattempted duringredundancymanagementoperations to allowfor goodcommunication.Attempt should bemade once every 5minutes for 30minutes. This canbe attempted on anycore PCS.

3

NCS is now incontrol and in a pre-5A configurationNCS does not haveinsight into LABfunctionality.

2

MDM ConnectionFailed MessageBox

Connect Boxstatus − Yellow

User Notification

1 Reconnect to MDM

PCS CDS Main Controlpanel Window• sel Connect to MDM

Is MDM connected statusbox green?

2 Transient loss ofconnection. Commreestablished.

Yes

No

3

• Verify PCS CDS MainControl panel Windowconnection status onother core PCS.


Yes

No

4 PCS Location

Orbiter Aft Flight Deck

ISS

6 Attempt to ReconnectDuring CCS Recoveryby NCS

Attempt to reconnectshould be made once every5 minutes for 30 minutes oruntil good connection isestablished.

PCS CDS Main Controlpanel Window• sel Connect to MDM

Is MDM connected statusbox green on any attempt?

15

• Inform MCC-H andcontinue normaloperations.

16 PCS failure.

5

Any new PCS connectionshould not be attempted inISS until after recovery ofAFD PCS.

7 Check Cables, Power,and 1553 Card onSuspect PCS

•√MDM data cable andpower connection atPDIP/UOP/PCR

•√1553 cable connection atPCMCIA card

Are cables properlyconnected and 1553 cardproperly seated?

Yes

No

8 Swap PCSs

• Reconnect other PCS toPDIP/UOP/PCR

• sel Connect to MDM


Yes No

9

• Reconnect data cable.• When 1553 card is

removed or is unseated,perform {2.305 PCSREBOOT} (SODF: POC:NOMINAL: PCS).


Is MDM connection statusbox green?

Yes

14

•√MCC

Yes No

No

12 PossiblePDIP/UOP/PCR failure.

10 CCS failure.

11 Configure for EPCSOperations

• Perform {2.301 EPCSSETUP-ISS} (SODF:POC: NOMINAL:PCS)

• Perform {1.204 EARLYCOMM POWERUP PRE-CCS}, steps 1 --- 7 only(SODF: C&T:ACTIVATION ANDCHECKOUT: EARLYCOMM)

On MCC-H GO• Perform {3.707 USL

RESTART − CCS} (SODF:C&DH: ACTIVATION ANDCHECKOUT: MODULEACTIVATION)

13 Loose data cable or1553 card unseated.

8

8

16

9

20

17

17

29

149


19 OCT 005766.doc

4

5

4

MCC-H willdetermine if a swapof the Node 1 MDMswill be performed

5

N1-1 Detect RT FailN1-2 malfunctionprocedure shouldenable passthru toNCS.

17 Station Crew CheckC&W Messages

•√Caution & WarningSummary display for anyof the following C&Wmessages:

‘Primary CC DetectedPrimary Node 1 MDMFailure – PMA 1 ’(Warning)

‘Primary INT MDM Fail -Lab ’ (Caution)’will return toNormal

‘Primary INT MDM FailBackup - Lab ’ (Caution)

‘Primary Node 1 MDMDetected RT Fail of OIU –PMA 1’ (Caution) or ‘Node1-2 MDM Detected UserBus Orb N1-2 Fail – PMA 1 ’(Caution)

None of the above C&Wmessages

18 Primary Node 1 MDMfailure.

19

•√MCC

22 Station Crew VerifyPrimary Node 1 MDM

• Wait 10 minutes.Task: CDH SummaryCDH Summary

• sel Primary Node 1 MDMPrimary NCS MDMNode 1

• Verify Frame Counter −<inc>

• Record MDM ID: ______

Is frame counterincrementing?

No

Yes

23 Station Crew VerifyPassthru Enabled

Task: CDH SummaryCDH Summary

• sel Primary CCSPrimary CCS

‘Software Control’• sel Data Path

Primary CCS Data Path‘Tier II Passthru’

•√NCS Passthru – Ena

Is NCS Passthru enabled?No

Yes

24

•√MCC

20 Transient loss of allTier 1 C&C MDMs. Atleast one C&C MDM hasbeen recovered via MightyMouse.

18

7

6

25

22

5

23

17

21

• Perform {4.201 C&CMDMRECONFIGURATION}(SODF: C&DH:CORRECTIVE: MDMRECONFIGURATION),then:

29

150


19 OCT 005766.doc

6

6

NCS Auto Retry iscomplete. Groundwill determine if retrywas successful andperform appropriateprocedure.

7

This step will cyclethe PCS CDS andwill result in the lossof C&W timestampson any messagesreceived; however,cycling the CDS willclear falsemessagesgenerated duringthe MDM transition.

25 Orbiter CrewReconnect PCS

• Station crew reportPrimary Node 1 MDM ID(recorded in block 22) toorbiter crew.

• Orbiter crew connect toappropriate Node 1MDM.



26

•√MCC

27

Comm reestablished withPrimary Node 1 MDM andPCS telemetry regained.

28

• Inform MCC-H.

No

Yes

23

29 Reconnect to MDM

•√Caution & WarningSummary display for anymessages

Was ‘CC MDM Transitionto Primary - LAB ’ cautionmessage received?

Yes

No

30 Restart CDS

• Close all ISS displays.PCS CDS Main Controlpanel Window• sel Terminate Connection• Close CDS Main Control

Panel Window• Restart PCS CDSPCS CDS Main Controlpanel Window• sel Connect to MDM

31

•√MCC-H

2

7

21

151

02 NOV 00


152

2.302 ONBOARD FILE TRANSFER(POC/4A - ALL/FIN A) Page 1 of 4 pages

13 SEP 007063.doc

NOTEThe maximum size for one file transfer is 8 Megabytes (MB).

1. OPENING FILE TRANSFER WINDOW

PCS PCSCDS Main Control Panel

sel Commandssel File Transfer

File and Memory Transfer

NOTEAt this point, decide which file transfer to perform. The optionsinclude1. Get a File Function - initiate a direct file or directory listing

transfer from the C&C MDM or Payload MDM to PCS.

2. Put a File Function - initiate a direct file transfer from PCS tothe C&C MDM or Payload MDM.

3. Indirect File Transfer Function - initiate an indirect file transferbetween the C&C MDM and the Payload or JEM MDMs,between prime and backup C&C MDMs, or between primeand backup Payload MDMs.

4. Indirect Data Load Function - initiate an indirect transfer of afile from the C&C MDM to the memory of the GN&C MDMs,LAB CEU, or Cupola CEU.

To perform the Get a File Function, go to step 2.To perform the Put a File Function, go to step 3.To perform the Indirect File Transfer Function, go to step 4.To perform the Indirect Data Load Function, go to step 5.

2. GETTING A FILE FUNCTION

PCS File and Memory Transfer

sel Commandssel Get a File

Get Remote File

sel Source Node (MDM that PCS is connected to)

‘Abort on MSD Read Error’

sel True

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NOTEOn the Source is Directory radio button, selectTrue when transferring a directory and selectFalse when transferring a file.

‘Source is Directory’

sel True or False as appropriateTrue - for directory listing transferFalse - for file transfer

NOTE1. Direct file transfers to and from the C&C MDM to PCS

are only available if the PCS is connected on a controlbus (i.e., not available in pass-through mode).

2. Due to limitations on the MDM, the source and targetdirectory paths specified during transfers are limited toa total of 96 characters each. In addition, eachdirectory and file name is limited to 32 characters.

Input Source Directory by keyboard or by File Select button (i.e., /fmt).Input Source File by keyboard or by File Select button.

Input Target Directory by keyboard or by File Select button(i.e., /export/home/PCSUser).

Input Target File by keyboard or by File Select button.

sel Apply

Go to step 6.

3. PUT A FILE FUNCTION


sel Commandssel Put a File

Put Remote File

NOTE1. Direct file transfers to and from the C&C MDM to PCS

are only available if PCS is connected on a control bus(i.e., not available in pass-through mode).

2. Due to limitations on the MDM, the source and targetdirectory paths specified during transfers are limited to atotal of 96 characters each. In addition, each directoryand file name is limited to 32 characters.

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13 SEP 007063.doc

Input Source Directory by keyboard or by File Select button(i.e., /export/home/PCSUser).

Input Source File by keyboard or by File Select button.

sel Target Node (MDM that PCS is connected to)

Input Target Directory by keyboard or by File select button (i.e., /fmt).Input Target File by keyboard or by File select button.

sel Apply

Go to step 6.

4. INDIRECT FILE TRANSFER FUNCTION


sel Commandssel Indirect File Transfer

Indirect File Transfer

NOTEOnly certain combinations of source and targetnodes are available for indirect transfers.

sel Source Node (Device to transfer from)sel Target Node (Device to transfer to)

NOTE1. Due to limitations on the MDM, the source and target

directory paths specified during transfers are limited to atotal of 96 characters each. In addition, each directoryand file name is limited to 32 characters.

2. PCS must be connected to the MDM that the user wantsto transfer files to or the MDM that the user wants totransfer files from.

Input Source Directory by keyboard (i.e., /fmt).Input Source File by keyboard.Input Target Directory by keyboard (i.e., /fmt).Input Target File by keyboard.

sel Apply

Go to step 6.

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5. INDIRECT DATA LOAD FUNCTION

NOTEDue to limitations on the MDM, the source and targetdirectory paths specified during transfers are limitedto a total of 96 characters each. In addition, eachdirectory and file name is limited to 32 characters.


sel Commandssel Indirect Data Load

Indirect Data Load

NOTEThis function is not available when PCS is connectedto the Payload MDM.

sel Source Node – C&C Primesel Target Node (Platform to transfer to)

Input the Source Directory (i.e., /cdh).Input the Source File (i.e., gnc3_3.b).Input the Starting Address for the memory location on the Target Nodeto hole the transferred file.

Input the File Length, in decimal, of the file being transferred.

sel Apply

6. MONITORING THE FILE AND MEMORY TRANSFER

PCS File and Memory Transfer‘Active Transfers’

Verify Transfer status – OK

Wait 4 minutes per megabyte of file size to be transferred.

‘Completed Transfers’

Verify Transfer Status – COMPLETED

To perform another file transfer, go to step 1.

sel Commandssel Close

Verify Shutdown

sel Yes

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CONTINGENCY

CONTIN

GENCY

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02 NOV 00


CONTIN

GENCY

158

HANDOVER ATTITUDE CONTROL ORBITER TO RS THRUSTERS(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

01 NOV 007573.doc

1. VERIFYING ISS NOT IN CONTROLPCS SM: MCS

SM: MCS‘RS GNC Status’

Verify RS GNC Mode – Free Drift

If US GNC has been activatedMCSMCS Summary

‘MCS Status’

Verify US GNC Mode − Drift(UDG)(Standby)(Wait)

2. PREPARING ISS TO TAKE CONTROL (VIA MCC-M)If required, MCC-M will prepare the RS for handover by setting thepropellant consumption limit, configuring ��, and preparing thrusters fordesaturation.

MCC-M ⇒ ISS, MCC-H, “Russian Segment ready for handover.”MCC-H ⇒ orbiter, “ISS is ready to begin controlling attitude of the MatedStack.”

3. PLACING ORBITER INTO FREE DRIFTC3(A6) DAP: FREE

Orbiter ⇒ ISS, MCC-H, “Orbiter is in Free Drift.”

4. ASSUMING CONTROL WITH ISS (VIA ISS CREW OR MCC-M)MCC-M will issue the commands to mode the Russian Segment fromIndicator to Thrusters.

MCC-M ⇒ MCC-H, ISS, “Russian Segment has assumed attitude control.”

5. RETURNING ORBITER TO NOMINAL CONFIGURATIONIf ALT DAP, return to Group B powerdown.

O14, PRI RJD DRIVER, LOGIC (sixteen) − OFF O15, RJDA-1A L2/R2 MANF DRIVER − ON O16:F

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HANDOVER ATTITUDE CONTROL RS THRUSTERS TO ORBITER(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

01 NOV 007572.doc

1. VERIFYING ORBITER NOT IN CONTROLPCS SM: MCS

SM:MCS‘RS GNC Status’

Verify RS GNC Mode – Thrusters

C3 √DAP: A/FREE/VERN(ALT)

GNC 20 DAP CONFIG

√DAP ____, ____ loaded

Orbiter ⇒ ISS, MCC-H, “Orbiter ready to begin controlling attitude ofMated Stack.”

2. CONFIGURING ISS TO FREE DRIFT (VIA ISS CREW OR MCC-M)MCC-M will issue command to mode Russian Segment from Thrusters toIndicator

MCC-M ⇒ MCC-H, ISS, “Russian Segment has moded to Indicator.”

ISS (MCC-H) ⇒ orbiter, “ISS is in Free Drift.”

3. ASSUMING CONTROL WITH ORBITERIf ALT DAP required

O14, PRI RJD DRIVER, LOGIC (sixteen) − ON O15, O16:F

If required attitude per Flight Plan is LVLHDAP − A/LVLH/VERN(ALT)

If required attitude per Flight Plan is InertialDAP − A/INRTL/VERN(ALT)

GNC UNIV PTG

When rates are damped < 0.1 deg/sec/axisDAP − A/AUTO/VERN(ALT)

Orbiter ⇒ ISS, MCC-H, “Orbiter has established attitude control.”

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ODS VESTIBULE/PMA2 PRESSURIZATION(JNT OPS/5A.1/FIN/MULTI) Page 1 of 1 page

01 NOV 009164.doc

NOTEExpect possible DP/DT Klaxon, ‘S66 CABIN PRES’and ‘S66 CABIN PPO2’ alarms during pressurization.

ODS 1. ODS Equal vlv (one) → Remove cap Hatch

CAUTIONA total of 10 cycles from OFF to NORM on the equalization valveis required to avoid an excessive negative delta pressure acrossthe APAS Hatch. Opening the equalization valve for more than15 seconds (before cycles are complete) will cause damage tothe Hatch.

NOTEPressurization, including valve cycling, willtake approximately 15 minutes.

2. ODS Equal vlv (one) → NormWait 8 seconds.ODS Equal vlv (one) → OffWait 30 seconds.

Repeat step 2 nine times.

3. ODS Equal vlv (one) → Norm

4. When ODS Hatch ∆P < 0.2 psidODS Equal vlv → Off, install cap

Wait 5 minutes for thermal stabilization.


CRT 5. Record A/L-VEST ∆P: _____ psid.Wait 30 minutes.

***********************************************************If A/L-VEST ∆P ≥ previously recorded + 0.16 psid,

Notify MCC-H (Vestibule/PMA 2 leak).***********************************************************

6. Report results of leak monitoring to MCC-H, “Vestibule final leak checksuccessful.”

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EMERGENCY RESPONSE

EMERGENCY

RESPONSE

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EMERGENCY

RESPONSE

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JOINT EXPEDITED UNDOCKING AND SEPARATION(JNT OPS/5A.1/FIN) Page 1 of 5 pages

01 NOV 005114.doc

NOTE1. This Expedited undocking should be used for the following failures

Non-isolatable prop leak (shuttle)Cabin leak (shuttle)Loss of cooling (two cabin fans, water coolant loops, Freon coolant loops (shuttle))

2. Entrance to this procedure based on Cabin Leak or Loss of Cooling scenario assumes that thisprocedure will be worked concurrently with the associated FDF ORB PKT and ENTRY PKTpowerdown.

3. At least 20 minutes are required to perform mandatory activities through physical separation. Anadditional 45 minutes required for ANY ATTITUDE SEPARATION, or an additional 18 minutesrequired for SHUTTLE EMERGENCY SEPARATION (to OMS TIG).

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ISS CREW SHUTTLE MS SHUTTLE CDR/PLT1a. ISS report to shuttle, “JEUS in progress.”

2a. ISOLATING VEHICLESReturn to home vehicle.

1b. Shuttle report to ISS, “JEUS in progress.”

2b. ISOLATING VEHICLESPerform JOINT EMERGENCY EGRESS

Cue Card (SODF: JNT OPS), then

3b. Perform ISS SAFING as required.

4b. PERFORMING APCU DEACTL12U APCU 1,2 CONV − OFF

√CONV tb − bp√OUTPUT tb − bpOUTPUT − OFF

1c. Shuttle report to ISS, “JEUS in progress.”

2c. ISOLATING VEHICLESAll crew return to home vehicle.

√Only shuttle crew on shuttleGive, “Go for Hatch closure” unless sharing ISS

atmosphere.

3c. PREPARING FOR UNDOCKINGO14, Pri RJD DRIVER, LOGIC (sixteen) − ON O15, O16:FO14, L, AFT DDU cbs (four) − cl O15, O16:E

4c. When sharing ISS atmosphere cplt, give, “Go forHatch closure.”

Hold until “GO for vestibule depress” fromCDR.

After Hatch closure complete, CDR gives “GO todepress vestibule”

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ISS CREW SHUTTLE MS SHUTTLE CDR/PLT

5b. DEPRESSURIZING SHUTTLEVESTIBULE

A6L √cb ESS 1BC SYS PWR CNTL SYS 1 − cl√cb ESS 2CA SYS PWR CNTL SYS 2 − cl

cb ESS 1BC DEP SYS 1 VENT ISOL − clcb ESS 2CA DEP SYS 2 VENT ISOL − clcb ESS MNA DEP SYS 1 VENT − clcb ESS MNB DEP SYS 2 VENT − cl

√SYS PWR SYS 1, SYS2 tb (two) − ONVEST DEP VLV SYS 1(2) VENT ISOL

(two) − OP (tb − OP)VEST DP VLV SYS 1(2) VENT (two) − OP

(tb − OP)

6b. ODS PREPARATION FOR UNDOCKINGIf required, perform PMA-2 HOOKS OPEN

(FDF, RNDZ, APDS), then:Perform DOCKING MECHANISM PWRUP

(FDF, RNDZ, APDS), then:If Airlock Pressure < 8.0 PSIAIf time permits, terminate EVA and repress

airlock.If time not available expect hooks motor

drive to fail during operation.Perform UNDOCKING PREP (FDF: RNDZ,

APDS), then:

Do not perform next steps until ready for undock.

5c. GNC_23_RCSReselect manually deselected jets.

6c. FLT CNTLR PWRUPGNC_25_RM_ORBIT

SW RM INH − ITEM 16 (*)A6U FLT CNTLR PWR − ONCRT SW RM INH − ITEM 16 (*)

7c. CONFIGURING DAPGNC_UNIV_PTG

√Rates < 0.1 °/secA6U DAP: FREE

GNC_20_DAP_CONFIGCONFIG DAP A,B to A7,B7

√DAP A CNTL ACC − ITEM 28 +0 EXEC√DAP B CNTL ACC − ITEM 48 +0 EXEC

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ISS CREW SHUTTLE MS SHUTTLE CDR/PLTHold until given “GO to undock” From CDR. CDR give MS “GO for Command Undocking.”

4a. MODING ISS TO ATTITUDE CONTROLPCS MCS: MCS Configuration

Perform TBS

A7L 7b. COMMAND UNDOCKINGAfter DAP configured, and

On MCC GO (if Comm),

************************************If HOOKS 1(2) OP lt failed ON

APDS PWR ADS − OFF√ADS, failed lts off

************************************APDS CIRC PROT OFF pb − push

(√lt on)

-2:20 8b. UNDOCKING pb − push√HOOKS 1, HOOKS 2 CL lt (two) − off

CRT √HOOKS 1, HOOKS 2 POS < 92 % and decrease

*********************************************CRT If HOOKS 1(2) fail to drive (HOOKS

1(2) DRV CMD − OFF),OPEN HOOKS pb − push

If HOOKS 1(2) appear to stop beforereaching end-of-travel (HOOKS 1(2)POS > 4 % and not decrease), allowfor single motor drive time (~4:40)before performing pnl A7L pwr cycle.

*********************************************-1:30

A7L 9b. √INTERF SEALED lt − off√RDY to HK lt − off (HOOKS 1, HOOKS

2 POS ~30 %)

0:00 10b. √HOOKS 1, HOOKS 2 OP lts (two) − onCRT √HOOKS 1, HOOKS 2 POS: 4 %

√UNDOCK COMPLETE lt − on

*********************************************+2:20 If HOOKS 1(2) fail to open (confirmedby no physical separation)

A7L PWR OFF pb − push√MCC (if time permits)

FIRE PYROS:A6L PYRO PWR MN A, MN C (two) − ONA7L PYROS Ap, Bp, Cp (three) − ON

(√Its on)PYRO CIRC PROT OFF pb − push

(√Its on)ACT HOOKS FIRING pb − push

8c. If OMS TIG < 1 hourGo to SHUTTLE EMERGENCY

SEPARATION (FDF, RENDEZVOUS,CONTINGENCY OPS).

If OMS TIG > 1 hourUnstow HHL.Go to ANY ATTITUDE SEPARATION

(FDF, RENDEZVOUS,CONTINGENCY OPS).

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ISS CREW SHUTTLE MS SHUTTLE CDR/PLTAfter separation:

PYRO CIRC PROT ON pb − push(√OFF lt off)

PYROS Ap, Bp, Cp (three) − OFF(√Its of)

A6L PYROS PWR MN A, MN C (two) −OFF

*********************************************11b. POST UNDOCKING

A7L PWR OFF pb − pushSTATUS lt (eighteen) − off

12b. Perform DOCKING MECHANISMPWRDN (FDF: RNDZ, APDS).

13b. Go to PL SAFING

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172

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CUE CARD

CU

E C

AR

D

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02 NOV 00


CU

E C

AR

D

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TOP

SHUTTLE VHF RADIO(JNT OPS/5A.1/FIN) Page 1 of 1 page

01 NOV 008955.doc

HOOKVELCRO

HOOKVELCRO

JNT OPS-2a/5A.1/A

VHF RADIO SETTINGSAM/FM (Modulation) − FM

PCV (Encryption) − PT (clear)

PWR (Power) − MED

CHANGE AND STORE CHANNEL SETTINGS CH [0-9] − RCV frequency settingsModify PWR as required.Enter first 6 digits of RCV frequency. R/T − XMIT frequency (flashing TX)Enter first 6 digits of XMIT frequency. STO

SPEAKER ACTIVATION MODE SPKRSpeaker muted when radio keyed.

DISPLAY ILLUMINATION LAMPToggles through four light levels.

SIGNAL STRENGTH MODE MODE PWRVertical bars indicate Sig Str(relative scale).

Power-out meter when keyed(1 Watt/bar).

ARIU KEYINGJ1 VOX key to VHF radioJ2 XMIT PTT key to VHF radio

EXCL MIR XMITARIU headset can key VHF radio.ATUs are listen only.

DISABLE MIR XMITARIU is listen only − no key

EVABoth BPSMU/ARIU headset and ATUkey VHF radio.

FREQUENCIES XMIT RCV1 - Shuttle/ISS (RNDZ) Half Duplex 139.2125 (medium power) 143.6252 - Shuttle/ISS (Docked) Half Duplex 139.2125 (low power) 143.6253 - Shuttle/ISS/Soyuz Simplex 121.75 (medium power) 121.754 - Shuttle/Soyuz/Joint EVA Half Duplex 143.825 (medium power) 139.21255 - Contingency VHF-2 Half Duplex 121.75 (medium power) 130.1625

4AM/FM

3SPKR

5PCV

R/T2GRD

1BCN

9LAMP

8PWR

0CH

STO7SCAN

6MODE

FMMED PT

1:139.2125

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TOP BACK OF “VHF RADIO”

SHUTTLE VHF RADIO CONFIG DIAGRAM(JNT OPS/5A.1/FIN) Page 1 of 1 page

01 NOV 009176.doc

HOOKVELCRO

HOOKVELCRO

JNT OPS-2b/5A.1/A

ISS antenna cavityWARNINGDo not operate VHF radio in HI power.Exceeds allowable cabin radiation levelsand can damage antenna

ATU CONFIG - ISSPWR AUDA/G 1 T/R vol 5 +A/G 2 OFFA/A OFFICOM A OFFICOM B OFFMODE PTT/PTT

CCU�

ANT

W6(W1)

ARIUJ2 J1 J3

EXCL MIR

DISABLE

EVA

VHF RADIO

ANT

REMOTE

AUDIO

J1

VOL SQ

PDBMO52J

14' VHF Radio CommCable (pre-routed)

4’ ARIU ATU/Pwr Cable (pre-routed)

4’ Audio/Video I/F

Cable (pre-routed)

20' Antenna Cable(pre-routed)

J2

42’ Audio/Video I/F

Cable

BPSMU/ODS

Adapter(pre-routed)

4’ Radio/ARIU Cable

DC PowerCable (pre-routed)

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TOP

JOINT EMERGENCY EGRESS(JNT OPS/5A.1/FIN) Page 1 of 2 pages

01 NOV 009159.doc

JNT OPS-1a/5A.1/A

This cue card is executed as part of the toxic spill, fire/smoke, cabin leak orloss of cooling powerdown procedures.

EGRESS TO HOME VEHICLE1. If required, all crew return to home vehicle, unstow and don masks.

M013Q 2. √AIRLK FAN A(B) – OFF

HATCH CLOSURE PREP3. Clear Hatch pathway of cables, ducts.

PMA 4. Stow PMA/ODS duct on PMA handrail.Stow ODS air inlet duct in A/L.

5. Disconnect Hatch from Standoff, stow standoff on hand rail.

APAS 6. Remove and securely stow covers for Hatch, Docking Target Baseplate.

7. Install Standoff Cross (by hand if no time available).

HATCH CLOSURES8. On CDR call, “Go for Hatch closure.”

APAS Close Hatch using tool.

√MPEV – CL

ODS 9. Close ODS Hatch per decal.

√EQUAL VLVS (two) − OFF, caps installed

10. Report to ISS, MCC, “ODS and APAS Hatches closed.”

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JOINT EMERGENCY EGRESS(JNT OPS/5A.1/FIN) Page 2 of 2 pages

01 NOV 009159.doc

JNT OPS-1b/5A.1/A

HOOKVELCRO

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REFERENCE DATA

REFERENCE

DATA

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REFERENCE

DATA

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PROXIMITY OPERATIONS(JNT OPS/5A.1/FIN/MULTI) Page 1 of 2 pages

01 NOV 008956.doc

0 30-30-60-90-120-150-180-210-240

DOCK

HARD

DOCK

Orient Arrays for Sun-Tracking (8-10 min)

Ti + 137

Ti + 157Dock + 20

Ti + 157 to 167Dock + 20 to 30

ISS indockingattitude

Begin Pre-heat ofShell Heaters @ Dock - 360(~ 4 hours of pre-heat) ** AnalysisRequired to determine pre-heat time**

Ti + 28Dock - 109

Ti

Dock - 137

ISS beginMNVR todockingattitude(25 min tocomplete)

Ti + 3

ISS config for prox ops:1) Change HTR setup - end pre-heat2) config systems(20 min)

Ti + 20 to 40Dock - 117 to - 97

600 ft

Ti + 90Dock - 47

Feather and lockUS arrays(8-10 min)(See Note 3)

Ti + 69 to 79Dock - 68 to -58

170 ft

Ti +110Dock - 27

Ti + 88 to 98Dock -49 to - 39

Feather and lockRS arrays(8-10 min)(See Note 3)

Flight 5A.1 +Vbar approach** All times are approximate **

Daily Orbit 2

Station Attitude(0,0,0) YPR

End Power downConfig sys for mated ops(20 min)

Ti + 177 to 197Dock + 40 to 60

NOTE 1. Although desirable, docking does not have to occur

over RSA groundsites because onboard crew cancommand RS elements.

2. All times based on nominal atmosphere.3. Solar array feathering angles for the US arrays are 210

deg for 4B, 150 deg for 2B, and 180 deg for FGB andSM arrays.

4. Orbiter burns are in NORMZ outside of 1000 ft, LOWZfrom 1000 ft to 75 ft, and NORMZ inside of 75 ft.

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PROXIMITY OPERATIONS(JNT OPS/5A.1/FIN/MULTI) Page 2 of 2 pages

01 NOV 008956.doc

0 30 60 90 120-30-60-90-120

UNDOCK

Orbiter and ISS inFree drift forunhooking

Undock - 3

Reactivate ISS ACSthrusters (30 secafter undock)

Feather andlock Solar Arrays(8-10 min)(See Note 2)

Undock - 15 to - 5

Undock + 15

400 ft

Solar arraySun Trackinitialization

Time(min)

ISS begin MNVRto undockingattitude (Xvv TEA)

Undock - 90

** Xvv TEA is not necessarily (0,0,0) YPR **

ISS attitudeXvv TEA

+X

+V

+R

Begin Pre-heat of Shell Heaters@ Undock - 360 (~ 4 hours of pre-heat)** Analysis Required to determinepre-heat time**

ISS Config for prox ops:1)Change HTR setup - endpre-heat2)config systems(20 min)

-30

** All Times are approximate**

Undock - 40 to - 20

End Power downConfig sys for nominal ops(20 min)

Undock + 40 to 60

NOTE 1. Orbiter burn in NORMZ during

initial sep until 75 ft, and inLOWZ for the remainder of ProxOps.

2. Solar array feathering angles forthe US arrays are 210 deg for 4B,150 deg for 2B, 320 deg for 2A,70 deg for 4A, 157.5 deg for theFGB arrays, and 180 deg for SMarrays.

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