Apollo 13 transcription

765 Pages·2000·20.45 MB·English

by  Travis Shelton

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'-'-'.'.'-"'.'.'-'-'-' APOLLO 13
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::::::::::::::::::::::: TECHNICAL AIR-TO-GROUND VOICE TRANSCRIPTION
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Prepared by
Test Division
Apollo Spacecraft Program Office
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'_' ::' MANNED SPACECRAFT CENTER
," H0 UST() N,'I'EXA.S
"_ April 1970
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INTRODUCTION
This is the transcription of the technical air-to-ground (TAG)
voice communications of the Apollo 13 mission. The primary communica-
tions net (GOSS net 1) will be in continuous operation for the duration
of the mission. An alternate communications net (GOSS net 2) may be
activated when separate, simultaneous communications links with both
spacecraft are desired.
The transcript is divided into three columns time, speaker, and
text. The time column consists of four two-digit pairs for days, hours,
minutes, and seconds (e.g., 04 22 45 12). The speaker column indicates
the source of a transmission; the text column contains the verbatim
transcript of the communications.
The primary communications r_et (GOSS net 1) comprises the bulk of
the transcript. However, when GOSS net 2 is activated, the communica-
tions on that net will be integrated with the GOSS net 1 communications.
A heavy dark line alongside the time column will indicate GOSS net 2
communications.
A series of three dats (...) is used to designate those portions
of the text that could nct be transcribed because of garbling. A series
of three asterisks (***) is used to designate those portions of the text
that could not be transcribed because of clipping caused by the VOX mode.
One dash (-) is used to _ndicate a speaker's pause or a self-interruption
and subsequent completion of a thought. Two dashes (- -) are used to
indicate an interruption by another speaker or the point at which a
recording was abruptly terminated.
Speakers in the transcript may be identified as follows.
Spacecraft:
CDR Commander James A. (Jim) Lovell, Jr.
CMP Command module pilot John L. Swigert, Jr.
LMP Lunar module pilot Fred W. Haise, Jr.
SC Unidentified crewmember
MS Multiple speakers
\
/
ii
Mission Control Centers:
CC Capsule communicator (CAP COMM)
LCC Launch Control Center
F Flight director
S Surgeon
Remote sites:
AB Airboss (Recovery aircraft)
CT Communications technician (COMM TECH)
IWO USS Iwo Jima
P-l, P-2, etc. Photographic helicopters
R-i, R-2, etc. Recovery helicopters
When the CDR and LMP _re in the undocked lunar module or on the
lunar surface, their speaker designations will be suffixed by either
LM or EVA to indicate their status (e.g., CDR-EVA or LMP-LM). Voice
calls during this mission _ere assigned in accordance with the following
station operating procedures: "For all phases when only the CSM is
manned, the AS-508 call sign will be Apollo 13. When both vehicles are
manned, the call sign will be Odyssey for the CSM and Aquarius for the
LM. The call signs for the CDR and LMP during lunar surface operations
will be the individual crew's first names."
Transcription of these tapes was managed by David M. Goldenbaum,
Test Division, Apollo Spacecraft Program Office, to whom questions re-
garding this document should be referred.
iii
ACRONYM LIST
Because specialized readers of the Apollo 13 transcription, such as
the principal investigators, may not be thoroughly familiar with the
acronyms used during the mission, the decision was made to define those
acronyms that probably will be encountered. For obvious reasons, no
effort was made to include every acronym that conceivably could be used;
only those acronyms that are considered likely to be used are included
here.
AEA Abort electronics assembly
AGS Abort guidance system
ALSCC Apollo lunar surface closeup camera
ALSD Apollo lunar surface drill
ALSEP Apollo lunar surface experiments package
AOS Acquisition of signal
AOT Alinement optical telescope
APS Auxiliary propulsion system (S-IVB)/Ascent propulsion system (LM)
ARS Atmosphere revitalization system
BEF Blunt end forward
CCGE Cold cathode gag.s experiment
CCIG Cold cathode ion gage
CDH Constant delta altitude (height)
CM Command module
CMC Command module computer
COAS Crew optical alinement sight
CP Control point
CPLEE Charged particle lunar environment experiment
CSC Contingency sample collection
CSI Coelliptic sequence initiation
CSM Command and service module
CWEA Caution and warning electronics assembly
DAC Data acquisition camera
DAP Digital autopilot
DEDA Data entry and display assembly
iv
DET Digital event timer
DOI Descent orbit insertion
DPS Descent propulsion system
DSE Data storage equipment
DSEA Data storage equipment assembly
DSKY Display and keyboard
DTO Detailed test objective
ECS Environmental control system
EI Entry interface
EMS Entry monitor system
EMI Extravehicular mobility unit
EPS Electrical power system
ETB Equipment transfer bag
EVA Extravehicular activity
EVT Extravehicular transfer
FDAI Flight director attitude indicator
GDC Gyro display coupler
GET Grotmd elapsed time
GETI Ground elapsed time of ignition
HFE Heat flow experiment
HGA High gain antenna
HTC Handtool carrier
IMU Inertial measurement unit
IP Initial point
ISA Interim stowage assembly
IU Instrument unit
IVT Intravehicular transfer
LAD Lunar atmosphere detector
LCG Liquid cooled garment
LEB Lower equipment bay
LEC Lunar equipment conveyor
LGC Lunar module guidance computer
LM Lunar module
LOI Lunar orbit insertion
LOPC Lunar orbit plane change
LOS Loss of signal/line of sight
LPD Landing point designator
LTC Lunar topographic camera
MCC Mission Control Center/midcourse correction
MESA Modular equipment stowage assembly
MSFN Manned Space Flight Network
i_I'VC Manual thrust vector control
OPS Oxygen purge system
ORDEAL Orbital rate display earth and lunar
PDI Powered descent initiation
PGA Pressure garment assembly
PGNCS Primary guidance, navigation, and control system (CM)
PGNS Primary guidance and navigation system (LM)
PIPA Pulsed integrating pendulous accelerometer
PLSS Portable life support system
PRD Personal radiation dosimeter
PSE Passive seismic experiment
PTC Passive thermal control
RCS Reaction control system
RCU Remote control unit
REFSMMAT Reference to stable member matrix
RLS Radius of landing site
RTG Radioisotope thermoelectric generator
SCE Signal conditioning equipment
SCS Stabilization control system
SECS Sequential events control system
Vi
SEF Sharp end forward
SIDE Suprathermal ion detector experiment
SLA SM/LM adapter
SM Service module
SNAP Systems for nuclear auxiliary power
SPS Service propulsion system
SRC Sample return container
SWC Solar wind composition
$WE Solar wind experiment
TEC Transearth coast
TEI Transearth injection
T. Time of ignition
ig
TLC Tr_islunar coast
TLI Translunar injection
TPF Terminal phase f_nal
TPI Terminal phase ir.itiation
TSB Temporary stowage bag
TVC Thrust vector control
UHT Universal handtool
APOLLO 13 AIR-TO-GROUND VOICE TRANSCRIPTION
Tape 1/1
Page 1
MI_ (REV i)
O ._ Q
00 00 00 02 CDR The clock is running.
00 00 O0 03 CMP Okay. Pll, Jim.
O0 00 00 05 CDR Yaw program.
O0 00 00 12 CMP Clear the tower.
O0 00 O0 14 CDR Yaw complete. Roll program.
00 00 00 16 CC Houston, Roger. Roi1.
00 00 O0 30 CC 13, Houston. GO at 30 seconds.
00 O0 00 34 CDR Roll complete, and we are pitching.
O0 00 00 36 CC Roger that. Stand by for mode I Bravo.
00 00 00 42 CC MARK.
O0 O0 O0 43 CC I Bravo.
O0 00 O0 44 CMP I Bravo.
O0 00 O0 45 CDR RCS COMMAND.
O0 00 O1 03 CC 13, Houston. GO at 1. We show the cabin
relieving.
O0 00 O1 07 CDR 13; Roger.
O0 00 O1 55 CC 13, Houston. Stand by for mode I Charlie.
00 00 O1 58 CC MARK.
O0 00 01 59 CC You're I Charlie.
O0 00 02 00 CDR MARK.
00 00 02 01 CDR I Charlie.
00 O0 02 02 CC And, 13, you are GO for staging.
00 O0 02 04 CDR GO for staging. Roger. We're EDS MANUAL.
Tape 1/2
_ 2
00 00 02 08 CC Copy that.
00 00 02 16 CDR Inboard.
00 00 02 27 CC We confirm inboard out, 13. You're looking
good.
O0 00 02 29 CDR Roger.
00 00 02 48 CDR S-II ignition.
00 00 02 51 CC Roger.
00 00 03 O0 CC 13, Houston. Trajectory is good; thrust is
good.
00 00 03 04 CDR Roger.
00 00 03 15 CDR Skirt SEP ... tower JETT.
00 00 03 21 CC We confirm skirt SEP. Roger. Tower JETT;
mode II, Jim. Looking good.
00 00 03 24 CDR Mode II.
00 00 03 33 CDR Guidance initiate.
00 00 03 43 CC 13, Houston. Guidance is good, and the CMC is
GO.
00 00 03 47 CMP Okay. Thank you.
00 00 03 48 CDR 13; Roger.
00 00 04 16 CC 13, Houston. You are GO at 4 minutes. The
little red lines are right on the little white
lines down here.
00 00 04 22 CDR Sounds good.
00 00 04 55 CC 13, Houston. Coming up 5 minutes. You're
looking perfect. Over.
00 00 04 59 CDR 13; Roger.
00 00 05 32 CDR Inboard.
00 00 05 36 CC Roger. We confirm inboard out.
00 00 05 44 CC 13, Houston. Stand by for S-IVB to COI
capability.
Tape 1/3
Page 3
00 00 05 48 CDR S-IVB to COI. Roger.
O0 O0 05 49 CC Roger. You've got it now, Jim.
O0 00 05 52 CDR We've got S-IVB to COI.
O0 00 06 03 CC You're GO at 6 minutes, 13.
00 00 06 06 CMP GO at 6.
00 00 06 l0 CDR And, Houston, what's the story on engine 5?
00 00 06 14 CC Jim, Houston. We don't have the story on why
the inboard out was early, but the other engines
are GO and you are GO.
00 00 06 21 CDR Roger.
00 00 06 41 CC 13, Houston. Still looking good. Your gimbals
are good; trim is good.
00 00 06 _5 CDR Roger.
00 00 06 53 CC 13, Houston. Level sense arm time 8 plus 38
nominal; S-II cut-off time 9 plus 48. Over.
O0 00 07 02 CDR Roger. Nominal on the level sense arm, 9:48 on
the S-II cut-off.
00 00 07 08 CC That's affirmative, and stand by for S-IVB to
orbit.
00 00 07 ll CC MARK.
00 00 07 12 CC You have S-IVB to orbit, Jim.
00 00 07 14 CDR Roger. We have S-IVB to orbit.
00 00 08 02 CC 13, Houston. Looking good at 8 minutes.
00 00 08 05 CC 13; Roger.
O0 O0 08 45 CC Apollo 13, tlouston. Mark level sense arm.
O0 00 08 48 CDR Mark level sense arm. Roger.
O0 00 08 58 CC Apollo 13, Houston. At 9 minutes, you are GO;
the CMC is GO.