The following day by day timeline summary is outlined for an 11 day mission, as published in the Flight Plan, and a 14 day mission. Flight Plan Design:
* SSRMS Pre-launch checkout at L-48 hours. Mobile Transporter (MT) is at worksite (WS#1) with SSRMS on MBS, PDGF 1.
* ISS SAFER checkouts are completed.
* ISS EMU Checkout is complete.
* MTL & LTL ITCS sample is complete.
* Transfer is not timelined during SSRMS operations due to spatial constraints at therobotics work station (RWS) in the ISS Lab. On EVA 1, 2 & 3, minimal Transfer isscheduled prior to EVA. In the 14 day mission, there are no SSRMS ops during EVA 4,so Transfer is permitted. * Transfer is not scheduled without a loadmaster, except in special cases where the loadmaster has been scheduled lead time at the beginning of a short transfer period.
* No more than 5 crew are allowed to be timelined for Transfer at a given time due to overcrowding.
* Transfer Updates are scheduled every morning beginning on FD03 for 15 minutes (except FD03 - 30 min). Transfer Tagups occur between MS4 and another loadmaster.Transfer Briefings are conducted with crew and MCC, therefore comm must beavailable.
* The SRMS is left powered from FD01 until after EVA 3 on FD08. It is powered up again prior to Late Inspection on Undocking day (FD010 or FD013).
* SSRMS is used from FD03 until completion of EVA 3 on FD08. It is planned to leave the SSRMS at its final MT position (WS#4) during EVA 3 with the wrist reconfigured for undock at the end of its last EVA 3 support task (CETA cart relocation).
* Manipulator Control Interface Unit (MCIU) filter screen checks are scheduled daily, except on days when standard Filter Check is scheduled.
* SSRMS supports S5 install from WS#1, MBS PDGF1.
* SSRMS supports OBSS hand-off for Focused Inspection from WS#4, MBS PDGF1.
* SSRMS supports EVA-2 (CMG R&R) from the Lab PDGF following a walk-off from the MT at WS#4. MT will translate unloaded to WS#7 to be pre-positioned for ESP-3 install. SSRMS walks-off to WS#7, MBS PDGF2 following EVA-2.
* After ESP-3 install completion, MT with SSRMS translates to WS#4 to support EVA 3. This is the final location for the flight as SSRMS support is not required for EVA 4.
* The EECOM water plan is in flux and may vary from what is scheduled in this Flight Plan and documented in this Flight Plan walkthrough. The information provided is the plan at Flight Plan Final publication.
* Ten CWC fills and 7 PWR fills are timelined in the 11 day mission. Two of the timelined PWR fills are for the ISS Oxygen Generating System (OGS), 5 are for EVAs. CWC fills and PWR fills cannot occur at the same time since EECOM would not be able to tell how much water is in each. PWR fills cannot occur during supply nozzle dumps.
* The EECOM water plan for the mission is dependent on the operation of SSPTS. When SSPTS is operating, Orbiter fuel cells produce less water and therefore supply dumping is minimal and the FES can be deactivated for most of the docked timeframe. The Flight Plan assumes water production based on SSPTS not operating and therefore there are several FES dumps and Simo dumps (vs just waste dumps) timelined.
* Water dumps (whether Simo or Waste only) are scheduled on the same flight days for 11 & 14 day missions:
* 11 day: FD03 (pre-dock), FD07 (docked), FD011 (EOM-1).
* 14 day: FD03 (pre-dock), FD07 (docked), FD011 (docked), FD014 (EOM-1).
* All the dump periods, except for FD03, include two Condensate dumps. PWRs are also dumped (emptied out) during the mated dumps for prior to refilling.
* Humidity Separator (Hum Sep) checks are performed in Presleep on FD01 and on any day when a condensate bag is set up to ensure the water is going into the bag and not into the Lower Electronic Box (LEB).
* MERLIN launches powered and returns unpowered. It requires twice daily status checks from FD01 until the facility is shutdown (MERLIN WARM SHUTDOWN) following completion of the 15 hr SPEGIS incubation period. The crew checks the hardware functions and operational temperature. Desired separation of the two status checks each day is between 8 - 12 hours. MERLIN/SPEGIS Setup occurs on FD04. SPEGIS incubation must be initiated by FD07 or there will be loss of science.
* CCM-A is activated on FD01 and deactivated on entry day. It requires twice daily status checks; one as close to Post Sleep as possible and the other as close to Presleep as possible. The crew records rail temperatures and notifies MCC.
* CBTM requires a daily status check at the same time each day +/- 2 hrs. The checks include crew observation logs and AEM hardware status. It is very important the daily checks occur within the same window timeframe to avoid disturbing the experiment light cycle. CBTM requires still photos and three videotape sessions (FD02, 5 or 6).
* PMDIS is an ISS payload and will be setup sometime after hatch opening. Each PMDIS session performed by two Shuttle crewmembers needs to be completed by Launch + 96 hrs (MET 4/00:00). Once the tests are complete, PMDIS equipment will be stowed by the ISS crew.
* SDBIs 1634 (Sleep Short) and 1493 (Latent Virus) are usually scheduled daily for assigned crewmembers, except where impacting specific crew on a critical work day or if SCSC violations would result. SDBI 1490B (PMZ) is only performed if promethazine is taken by a participating crewmember on FD01. SDBI 1503S (Midodrine) is only performed during Shuttle entry.
* 1490B: Actiwatch and sleep log (MS1, MS3).
* 1493: Daily saliva collections and log at crew wake up. (MS1, MS3, MS4).
* 1634: Actiwatch worn throughout mission, daily sleep log. (CDR,PLT, MS1,MS2,MS3).
* 1503S: During entry (MS3).
* DTO 853 Carbon Dioxide Monitor (CDM) is operated over five Sleep periods during the mission, preferably when all Shuttle crew available (that is, no crew in ISS airlock campout). It is activated just prior to sleep and deactivated immediately upon wake-up so that there is least disturbance to the air mixing at the five middeck measurement locations. After each datatake, a battery changeout is performed and the monitoring device is relocated to a different spot in the middeck.
* SDTO 13005-U is desired during docking, S5 installation, reboost and undocking. The Internal Wireless System (IWIS) is only required for docking and reboost. However, there is no reboost planned due to limited prop margins. S5 install and undocking measurements will use other equipment.
* Docked Audio Interface Unit (DAIU): troubleshooting and possible R&R of failed unit occurs while docked to confirm operational. Not currently planned for 11 day mission.FD01 – Launch & Setup
* Lab Window Scratch Pane R&R: performed to improve science imagery and return old pane in the Spacehab. Currently timelined in 11 day mission.
* CEVIS R & R: Replace the current CEVIS which has an anomolous power supply and return. Not currently planned for 11 day mission.
* TVIS Skirt R & R: Performed by ISS crew in the 11 day mission.
* NC1 is designated as a critical burn and G2 Set is left in expansion in the PI checklist. Following the burn the G2 Set contraction will be performed.
* SEE Setup must occur after the GIRA Install.
* MERLIN daily status check.
* CCM-A activation scheduled no later than Launch + 3 hours. Includes pushing a button on the front panel and taking a photo of the front panel. The short photo procedure is P/TV12 Middeck Payloads, which is scheduled in the EZ block.
* CBTM Mufflers are installed on the locker face of each AEM to minimize noise levels in cabin during the mission. This is followed by the first daily status check.
* 1490B, 1634 - Crew participants don Actiwatch activity monitors and wear them throughout the mission. EV (MS2, MS3) crew will remove the watch prior to EVAs. If PMZ required, participating crew (MS1, MS3) will begin following the protocol.FD02 - Surveys, EVA & RNDZ Prep
* 1493 - Latent virus kit is unstowed and placed near sleep area.
* The survey procedures use a smaller amount of time required to perform each scan, scan a larger area, and incorporate the use of IDC while LDRI scans are occurring, thus reducing the likelihood of needing Focused Inspection during the mission (the IDC image is already available if LDRI indicates a suspect area). For this mission, on FD02, the starboard wing is scheduled for 1:45 minutes, the nose cap for 1:00, and the port wing for 2:00. Additionally, the starboard survey incorporates the Flat Field calibration. The two wing surveys cover most of the areas of the crew cabin, so the RMS survey after OBSS berth is no longer required. Those areas of the crew cabin not surveyed will be photographed during the RPM maneuver during rendezvous. As a result of the reduction in time to complete all the FD02 surveys, only three crewmembers are scheduled, vice the four seen on some of the previous missions.
* Scans of the entire starboard wing are not easily performed, or are impossible to perform while docked and so are scheduled first. Three crewmembers are required continuously during the survey with two performing OBSS/RMS ops and one monitoring the LDRI/IDC and situational awareness cameras. Only two crewmembers are required during unberthing and berthing (non-laser ops). The survey is scheduled to continue through the night passes, but the crew may elect to pause if the night time visuals are not sufficient.
* The LDRI survey attitude requires no sun within +/-10 degree field of view (FOV) of the laser bore sight. No sun can be directly behind the instrument, either, within a 20 degree half-cone of the bore sight. And just when you thought things couldn’t be more complicated, it is highly desired to keep the sun at a 90 degree half cone from the bore sight of the LDRI FOV such that it is always behind the instrument, but not directly behind!
* The IDC instrument requires no sun within a 90 degree half cone of the FOV. As a result of the large sun "keep-out zone," the nose cap cannot be completed without changing the Orbiter attitude. This is not desirable. Any infringement of the sun within the 90 degree half cone will result in the IDC instrument being powered off during those times. Informing the crew of when to power off IDC will be taken care of in the PDRS procedures. The IDC line-of-sight is calibrated to align with the LDRI line-of-sight during scans.
* Real-time Ku is desired (not required) during the LDRI 3D calibration in OBSS Unberth. Each surface scan requires as much real-time Ku as possible to downlink DTV. Inertial attitudes are scheduled to maximize Ku and to optimize LDRI lighting. Specifically, the wing attitudes put the sun on the wing in the X-Y plane approximately 60 degrees from the nose and the nose cap attitude puts the sun on the nose pitched down 30 degrees to avoid sun in the crew’s eyes. All maneuvers are scheduled to occur during RMS/OBSS repositioning. If maneuvers are required during the survey, the scanning will be paused. VERN/ALT attitude hold is acceptable for LDRI. DAP A14 is loaded per the Unberth procedure and is used for the survey. Nose jets are disabled during the nose cap survey and ALT/tail only is selected per the procedure.
* Replay of survey data not obtained real-time is scheduled prior to sleep. INCO will provide LOS times in order to help the crew cue the tapes. A dedicated comm maneuver is scheduled to provide sufficient Ku downlink time. Note that TDRS Z does not have the capability for DTV and cannot be used to downlink surveys.
* LCS will be used as a backup to LDRI (sensor package on end of OBSS). LCS has no lighting constraints and requires OCA downlink of data instead of video downlink. LCS requires masking from Ku radiation during surveys due to data degradation. LCS also requires certain S-band antennas be inhibited during data takes but this is handled by the procedure.
* RMS is pre-cradled following survey completion in the OBSS Berth procedure.
* P/TV08 is set up for handheld photo OMS Pod survey, which must occur in daylight.
* MERLIN & CCM-A status checks (twice at both ends of the day).
* CBTM Daily status check and CBTM Photo (to capture location and environment of units for historical documentation.)
* First saliva and log for participating crewmembers (SDBIs).
* CDM (DTO 853) is setup for the first time anytime prior to sleep, but activation must be done just prior to sleep.
FD03 – Docking and S5 Handoff
* A Waste dump is scheduled to start soon after crew wakeup.
* The CWC Condensate bag is installed prior to docking. To verify that the water from the Hum Seps are going into the Cond bag and not into the Lower Electronic Box (LEB), CDR will perform a hum sep check in Presleep.
* CWC Fill #2 is performed.
* The FES may or may not be deactivated soon after SSPTS is activated on FD03. The timeline includes FES-OFF on MCC Go post SSPTS activation.
* Post docking, the PGSC network is reconfigured from the RNDZ configuration to an RMS configuration in preparation for S5 unberth and handoff. The STS PCS is also setup as desired by the crew.
* Prior to docking, the EMUs are removed from the Orbiter airlock to facilitate ISS access after docking.
* Post docking, crewmembers begin preparing for EVA 1. EMU suits, the filled drink EMU bags and EVA tools will be transferred from the Orbiter to the ISS airlock. The REBA will be installed into the EMUs and powered hardware checkout performed. The Equipment Lock is prepared. The procedure takes only 30 minutes since the drink bags were filled FD02. The crew will configure the EVA tools, which may continue while the EV crew is prebreathing on the masks. All crewmembers are timelined an hour for the EVA 1 procedure review.
* The CDR and FE-2 configure the O2 system so that the Orbiter provides the oxygen for EMU prebreathe which conserves ISS resources.
* MS2 and MS3 start EVA campout procedures at the end of the day. The EVA crewmembers cannot initiate repress until at least 8:40 has elapsed at 10.2 psi, which isn’t a problem with the nominal 8 hour sleep period.
* The OIU is activated during RNDZ and will remain on until post undock.
* The hardline audio config is performed post docking. Significant ISS powerdowns are required prior to docking. The DAIU won’t be powered ON until post-docking, so the docked audio setup must wait until that is complete. In the event that the DAIU fails, as it has on previous missions, the STS-118 mission will use UHF comm just like those other flights. DAIU troubleshooting will be performed on FD011 if the mission duration is 14 days.
* The SSV outrate is changed to 2 prior to docking and then changed to 3 post-docking.
* Once docked, the Shuttle will maneuver the stack to the Biased -XLV -ZVV (TEA) attitude. ISS will take over attitude control and maintain it during most of the docked timeframe using Control Moment Gyros (CMGs).
* Most of the attitude changes performed by the CMGs on ISS will require the CDR or PLT to update the attitude in Universal Pointing in the event that the Shuttle must take attitude control quickly.
* The set contraction in Group B Powerdown cannot be scheduled after the Shuttle maneuver to TEA is complete. Previous flight analysis has shown that performing the set contraction in the middle of the post docking maneuver can significantly increase the chance of exceeding the max vern jet cycling limit.
* While the hatches are still closed between the two vehicles post-docking, SRMS S5 operations will begin with grapple and unberth. The unberth cannot begin until ISS is in momentum management (MM) following the handover of attitude control from Shuttle to ISS and the desat request is verified inhibited (step 1 of unberth). This could take up to 30 minutes and therefore approximately 30 min is allotted in the timeline. Once in MM, PRLA release of S5 can be performed and unberth can commence. It is timelined that the unberth will be complete (SRMS in low hover) while the hatches are opened.
* S5 robotics ops will be on hold until after the welcome ceremony, safety brief and camera setups for viewing are complete.
* After the safety briefing, S5 ops will continue. PLT and FE-2 will mnvr the SSRMS to the pre-grapple position. MS1 and MS2 will mnvr the SRMS with S5 truss to the handoff position. SSRMS will grapple S5. Then SRMS will ungrapple S5 and mnvr to the S5 install viewing position for overnight. The SSRMS with S5 is parked at the handoff position overnight.
* MERLIN and CCM-A twice daily status checks.FD04 – S5 Installation and EVA 1
* CBTM daily status check.
* The PMC for the EV crew is conducted via the ISS S/G while in the Crew Lock, during the 40 minutes before the hygiene break per crew request.
* MS2 is EV1, MS3 is EV2, MS1 is IV, PLT is M1, FE-2 is M2.
* Prior to the EVA, SSRMS is located at WS#1 PDGF 1 with the S5 truss in the handoff position. The starboard solar arrays need to be parked during EVA 1 to provide SSRMS S5 access to S4, resulting in lower ISS power generation. MCC-H locks the S3/S4 SARJ at 180 deg, S4 1A BGA at 180 deg and S4 3A BGA at 270 deg. Due to the low power generation, if SSPTS is operational, it must be powered down for EVA 1. PLT powers off OPCUs 1,2 from Panel A15.
* While the EV crew is in the crewlock depress and after MCC-H parks the arrays, the SSRMS maneuvers the S5 to the pre-installation position. After the EV crew egresses the crewlock and sets up, they translate (free float) over to S4 corners 2 and 3 for SSRMS GCA (guided controlled assist) to the S5 launch lock removal position.
* S5 to S4 Launch Lock Removal - SSRMS is moved to the launch lock removal position (about 6 - 12 inches from S4) with EV crew guided assist. Each EV crew ingresses Articulating Portable Foot Restraints (APFRs) and removes launch locks using pistol grip tools (PGTs) from the four S5 corners which will attach to S4.
* S5 Install - SSRMS maneuvers the S5 to a soft capture position with EV crew monitoring structural clearances. Once soft captured, EV crew drive the Rocketdyne Attachment System (RTAS) bolts to an initial torque at each corner. The SSRMS ungrapples S5. The crew then proceed to provide final bolt torque, install ground straps and remove soft capture pins first at corner 1 and 2 and then at corners 3 and 4. S5 installation is complete.
* Photovoltaic Radiator Grapple Fixture (PVRGF) Relocation - The PVRGF provides grapple fixtures for the SRMS and SSRMS to use during the S5 hand-off. After S5 is installed, the PVRGF interferes with S4 3A BGA rotation and therefore the EV crew must relocate it to the keel position on S5. SSRMS provides viewing support.
* S5 Getaheads - Since the crew is already at the S5 truss, if they are ahead of the timeline they can begin performing some Category 4 getaheads (tasks desired prior to mission 15A when the S6 truss is installed). They have until 04:10 PET at which point S5 Cleanup must commence. The getaheads include connecting S5 to S4 electrical connections (1:00), removing S5 to S6 launch locks (00:40), and opening the S5 RTAS capture latch assembly (CLA) (00:15) to allow future S6 capture.
* S5 Cleanup - The crew takes photos, gathers up tools, trash bag with removed launch locks, and translates back to the airlock; on the way relocating the APFRs to CETA Carts 1 and 2 for EVA 3 use.
* P6 FWD PVR Retract and Cinch - The task is performed in preparation for P6 relocation on STS-120/10A. Additionally, it must be performed prior to P6 SASA relocate on EVA 3 due to clearance issues. The crew leaves the airlock location and translates to the P6 forward PVR starboard nadir corners with EV1 forward on P6 and EV2 port. They translate around the PVR to ensure it is in a good config and clear of obstructions for retraction. On EV crew go, MCC-H performs the PVR retraction. After the PVR is retracted, the crew installs cinches and provides torquing.
* EVA Cleanup/Ingress - The crew translates back to the airlock. If time is available they will take photos of MISSEs 3 & 4 to be downlinked via OCA to see if they are in a safe (non-toxic due to leaking) condition for return. IV performs WVS powerdown.
* SSRMS supports the S5 installation and EVA as described above. Once no longer needed for PVRGF viewing support and the EV crew is clear, it is configured to a position to be ready for translation on the MT where it will ride to WS#4 in the evening in support of OBSS hand-off on FD05.
* SRMS is only used for viewing support. After the EVA it is put in precradle for overnight.
* CWC 3 & 4 are filled.
* N2 transfer from Orbiter to replenish the ISS tanks is initiated by STS and ISS crew. 50 lbs are requested. Termination is timelined on FD08. Max rate is 3 lbs / hr, but 1 lb per hour is typically seen.
* One PWR is filled and transferred to the ISS to be used for recharging the Oxygen Generating System (OGS) which occurs on FD06.
* Carbon Dioxide Removal Assembly (CDRA) is activated by ISS crew
* An overnight External Survey is scheduled. Crew turns on PLB illuminators in pre sleep.
* SHAB CC Setup (crew request). Crew sets up a camcorder in the SHAB to drag the video signal over to ISS. The video cable goes to the RWS in the Lab, but won’t interfere with SSRMS ops.
* MERLIN/SPEGIS -FD05 – Focused Inspection (FI) (or Full Day Transfer)
* MERLIN twice daily status checks.
* MERLIN/SPEGIS Setup is scheduled mid-FD04. It cannot occur prior to FD04 in order to allow MELFI temperature to stabilize after docking. SPEGIS canisters are removed from MERLIN and then transferred to the MELFI on ISS. The MERLIN temperature is then ramped up from +4 deg C to +37.5 deg C for later incubation.
* MERLIN Photo (P/TV12 Middeck Payloads) is required once concurrently with MERLIN/SPEGIS Setup. It can also be done during one of the SPEGIS sample insertion / removal activities on another day. View includes crew performing ops.
* MERLIN Video (P/TV Middeck Payloads) is recorded of the payload and front panel for ground verification of on-orbit config. This can be done anytime during docked ops. Crew downlinks at their earliest convenience.
* CBTM - Daily status check.
* PMDIS - FE-2 performs hard drive install and hardware setup. MS5 performs data session.
* CCM-A - twice daily status check.
* Focused Inspection will be performed using the OBSS on the SRMS. A 3 hour placeholder activity is timelined for FI. There is a little more time available if required; however, Transfer and EPO activities would have to be deleted. The crew performing the FI (MS1, MS4, CDR) will begin their day with a DOUG Review. Since the SRMS cannot reach the OBSS in the docking config, the SSRMS must unberth the OBSS and hand it off to the SRMS. SSRMS provides SRMS OBSS viewing support. After the FI is complete, the SSRMS grapples the OBSS from the SRMS and then performs OBSS Berth. The SRMS is put in pre-cradle for overnight. The pre & post FI OBSS handoffs each take about two hours.
* Walk-Off - In the evening, the crew will perform SSRMS walk-off from WS#4 PDGF 1 to the LAB. First, a 30 minute mnvr is performed for the SSRMS to grapple the Lab grapple fixture. MCC-H then performs a base change (approximately 1 hr). The crew returns to the RWS to complete the walk-off by releasing the SSRMS from the MBS PDGF and maneuvering it to the EVA 2 start position.
* MT Translate - MCC-H translates the MT (without SSRMS) to WS#7 from where the SSRMS will support ESP-3 install ops on FD07.
* EPO Educator -
* EPO Drink Bag - MS4 fills drink bags with water to be used to supply water during seed growth on ISS. Must be scheduled prior to EPO KIT-C VIDEO.
* EPO Kit-C Transfer Video requires MS3, MS4, MS5, FE-2. MS4 sets up PD100 camcorder (CC) and records the transfer of seed growth chambers and drink bags from Shuttle to ISS with commentary. After the taping, CC is stowed, tapes are labeled and returned to Shuttle.
* The Kit-C Transfer should occur prior to the first EDU PAO Event on FD07 since Kit-C will probably be discussed. It is highly desired to perform this transfer and video documentation on FD05 since there are few other timeline opportunities due to required crew being involved in EVA 2 as EV crew or SSRMS operator.
* The same camcorder is used for CBTM Video Setup and thus cannot be scheduled at the same time.
* CBTM -
* CBTM Video Setup #1. A 40 minute video session is required for each of the 3 CBTM AEMs on either FD02, 5 or FD06. They should be scheduled around the same time as the CBTM daily status check. The setups use the same PD100 camcorder (CC) as EPO and cannot be scheduled at the same time. The CBTM will be pulled out of the middeck locker to allow for CC attachment. The recording session is unattended by crew; however, after 40 minutes of recording, the crew will remove the CC and mounting equipment, remove the tape and stow the CBTM in the locker.
* PMDIS - MS3’s data session must occur prior to Launch + 96 hrs (or 4/00:00 MET). Upon completion MS3 burns the data to a CD, removes and stows the copied CD and shuts down the PMDIS laptop. FE-2 stows the PMDIS hardware.
* CCM-A - twice daily status checks.
* MERLIN - twice daily status checks (note, first check after SPEGIS act must be 10 min).
* SPEGIS Activation - scheduled prior to Presleep. The 3 SPEGIS canisters are removed (must be at least 2.5 hrs after MERLIN/SPEGIS Setup) from MELFI and transferred to MERLIN where they will be incubated for 15 (+/- 2) hours at a temp of 37.5 deg C. Sband voice is required.
FD06 – CMG-3 R&R
* MS2 is EV1, MS3 is EV2, MS1 is IV, PLT is M1, FE-2 is M2.
* The SSRMS is in the EVA 2 start position following the walk-off to the Lab on FD05.
* Egress/Setup - EV1 translates to the Z1 worksite. EV2 GCAs the SSRMS to the APFR install position near the airlock, installs APFR onto SSRMS (for later), and then free floats to the Z1 worksite where the failed CMG is. The EV crew peels back failed CMG thermal shroud to gain access to CMG-3 and perform WVS survey. MCC-H performs CMG-3 power inhibits.
* Remove Failed CMG - The EV crew removes six bolts and temp stows the old CMG on the Multi-Use Tether (MUT) End Effector (EE) and tethers it to the Z1 handrail.
* Transfer New CMG to ESP-2 - The EV crew returns to the airlock hatch for tether config. EV1 then translates to ESP-3 in the Orbiter cargo bay. EV2 ingresses SSRMS APFR and is maneuvered to the payload bay to the CMG removal location, where he egresses the APFR momentarily to assist EV1 with removing the new CMG multilayer insulation (MLI). MS1 (IV) then deactivates APCUs 1 and 2 to remove heater power that has been provided to the ESP-3 since FD02 keeping the new CMG-3 thermally safe. No other ORU on ESP-3 required heaters. This is done as late as possible just as the EV crew is ready to remove the CMG-3 from ESP-3. Once this power is removed, the new CMG has approximately 24 hours to be transferred to Z1 and installed. EV1 at the ESP-3 connector box location disconnects Shuttle power cables (which provided power to the ESP-3 heaters) from the connector box and mates them to dummy receptacles. The power cables are disconnected at this time in order to allow ESP-3 to be robotically removed from the payload bay the next day (ESP3). EV2 has re-ingressed the SSRMS APFR and attached a retractable tether (RET) to the CMG to assist him with carrying the CMG. EV1 releases the Flight Releasable Attachment Mechanism (FRAM) Flight Support Equipment (FSE) bolt, which attaches the CMG to ESP3. The SSRMS then maneuvers EV2 (with CMG and FSE) to ESP-2 for installation there. Meanwhile, EV1 translates to the ESP-2 location. The purpose of installing the CMG FSE on ESP-2 is to then remove the new CMG from the FSE on ESP-2 so that the old CMG can be attached to that FSE until it is brought back on STS-122/1E. The ESP-2 location was chosen since it is on the airlock making old CMG-3 easily retrievable on 1E. EV1 GCAs SSRMS soft-dock of new CMG to ESP-2 and then drives the FRAM bolt.
* Remove New CMG - EV1 (free float) and EV2 (on SSRMS) remove the six CMG bolts from the FSE and remove the new CMG from ESP-2.
* Install New CMG on Z1 - EV2 carries the new CMG attached to a RET via SSRMS over to the Z1 worksite location. EV1 translates to Z1. After checking for foreign object debris (FOD) in the old CMG cavity, EV1 helps GCA SSRMS to Hand-Off position. EV1 ingresses IAPFR and receives the CMG from EV2. EV2 egresses the SSRMS APFR while EV1 installs CMG into soft dock position on Z1. Both then install the CMG with six bolts using PGTs. Connectors are mated. IV crew then gives MCC-H a Go for Powerup to check new CMG-3 function.
* Install Failed CMG on ESP - Already at the Z1 temp stow location, EV2 retrieves failed CMG and hands it off to EV1 so he can ingress the SSRMS APFR. Once ingressed, EV1 hands-off the CMG back to EV2 who will carry it to the ESP-2 location while riding the SSRMS. Meanwhile, EV1 replaces the Z1 thermal shroud and translates to ESP-2. EV2 inserts the old CMG into the FSE on ESP-2. Both crew then drive the six bolts. Crew installs MLI and the task is complete. Note that driving the shim bolts, which provide shear load support for return, is not planned to be done as they cannot be driven until the failed CMG thermally equalizes with the FSE. This must be done prior to CMG return on 1E.
* Clean Up - SSRMS is maneuvered to the APFR egress position, APFR is removed and stowed. MISSE photos (to inspect for toxic leakage) are taken if time permits and not already done in EVA 1. MS1 powers down WVS.
* SSRMS supports much of the EVA 2 activities as described above. In the evening, the SSRMS will begin a walk-off to WS#7 MBS PDGF2 in support of ESP-3 transfer & installation ops. The SSRMS is left grappled to WS#7 PDGF2 overnight while a base change is performed. The walk-off will be completed FD07 morning.
* SRMS provides viewing support during the EVA. In the evening, it will be put in precradle, which must occur after the SSRMS walk-off activity for clearance reasons.
* CWCs 7 & 8 are filled.
* ISS OGR is recharged using water transferred over in a PWR. This PWR is then transferred back to Shuttle to be filled again later this day. After filling, it will be returned to ISS for future OGR recharging needs.
* Condensate bag swap is performed. CDR performs a hum sep check to make sure condensate is going into the bag. The water from the old bag will be dumped overboard on FD07. The new bag contents will be dumped later after post-undocking (or on FD011 if a 14 day mission).
* CCM-A - twice daily status checks.FD07 – ESP3 Handoff and Install
* SPEGIS - canister termination is performed in the morning approximately 15 hrs (+/- 2 hrs) after incubation began the night before. The three canisters are removed from MERLIN and transferred to MELFI and inserted into a dewar for freezing.
* MERLIN - after the SPEGIS canisters are removed, MERLIN is shutdown (MERLIN Warm Shutdown) and then is configured for descent anytime before landing.
* CBTM - Videotape sessions of CBTM #2 and #3 are performed as described on FD05.
* Prior to beginning any ESP-3 operations, the SSRMS (now attached to MBS PDGF2 at WS#7) must first be released from the Lab and maneuvered to the ESP-3 pre-grapple position. This is done first since it’s highly desired to avoid simultaneous maneuvering of the SRMS and SSRMS. ESP-3 is unberthed via the SRMS and maneuvered to the hand position. A tight clearance exists between ESP-3 and the OBSS during unberth. SSRMS maneuvers to the hand-off position and grapples ESP-3. SRMS ungrapples ESP-3 and maneuvers to a viewing position to support the SSRMS transfer and installation. SSRMS then maneuvers ESP-3 to the install position where it will be mated to the P3 UCCAS1. The SSRMS supports through both stages of capture (performed by CDR & MS4) and then releases ESP-3 and backs off. The SSRMS is then maneuvered into a config position for translate to WS#4. The MT is translated to WS#4 in Presleep to support EVA 3 on FD08. The SRMS remains in the ESP-3 viewing position overnight.
* P/TV10 ESP-3 Unberth, Install - performed prior to SRMS ESP-3 grapple and unberth.EECOM:
* P/TV08 External Survey - Photography of the ISS Structure after the major structure changes (S5 truss, ESP-3 Transfer) are complete. Unlike other missions where the structural changes to ISS are significant and thus the survey is required to be performed as late as possible in the mission, it can be performed any time during STS-118/13A.1. Scheduling requirements include daylight periods and no robotic arm or EVA operations which could cause field of view obstructions.
* Water dump period - includes a simo dump, two PWR dumps (evacuates empty PWRs), and a condensate CWC bag dump. The PWRs can contain 20 lbs of water and appear empty, so the crew will evacuate the bags prior to filling them again. A leaking PWR on a previous mission is thought to be the result of it not being truly empty before the fill began. If SSPTS is operational, a waste dump will be performed instead of a simo dump since less water will be generated by the fuel cells.
PMC: Performed today via OCA videoconferencing to test out the Netmeeting configuration prior to the PFCs on FD09.
* EPO Seed Photo - MS4 unstows the seed packets and photos are taken for documentation purposes with MS3, MS4 and FE-2. The photo session must occur during docked ops at the end of any scheduled PAO event so the crew will already be in appropriate attire for seed photos, saving additional setup time.FD08 – EVA 3
* CCM-A - twice daily status checks.
* CBTM - daily status check.
* Port S-band comm system upgrade tasks include relocating the P6 SASA to P1, since it is not powered at the P6 location after 10A, and installation of the new S-band Transponder (XPDR) and Base Signal Processor (BSP) to be installed at the same time as the P6 SASA task. These tasks are performed while docked for comm redundancy via Orbiter S-band.
* The two Crew and Equipment Transfer Aid (CETA) carts are moved to the starboard side of the MT to allow the MT translation to WS#8 for the SSRMS to support P6 relocation to P5.
* Materials International Space Station Experiment (MISSE) Passive Experiment Container (PEC) - desired after 12 months of exposure (installed on 8/03/06) and to free up room for the CDRA bed to return in the middeck on 10A. If MISSE not returned on 13A.1, they would be returned on 10A in the middeck (since no SHAB) and delay CDRA return.
* MS2 is EV1, FE-2 is EV3, MS1 is IV. PLT and FE-1 are M1 and M2, respectively.
* Egress/Setup - At the time of crew egress, the SSRMS (based at WS#4, PDGF2) is at the APFR install position. EVA 1 installs APFR on SSRMS, ingresses APFR and rides the SSRMS to the P6 truss SASA location. Simultaneously, EV3 translates to CETA cart 2 with the ORU bag containing new BSP and XPDR, ingresses Translational Foot Restraint (TFR) and translates the carts past P1 bay.
* SASA Relocation / P1 BSP & XDPR Install - The work for these is done concurrently by EV1 and EV 3, respectively.
* The SSRMS with EV1 arrives at the SASA remove location on P6 and EV1 egresses the SSRMS APFR. After P6 inhibits are in place (1 hour thermal clock begins) EV1 then demates connectors at P6 and mates to dummy connectors. He re-ingresses the APFR and rides SSRMS while carrying SASA to the P1 location for installation. He egresses APFR and mates SASA connectors. MCC-H applies heater power and the thermal clock stops. Once complete, he holds onto APFR and rides SSRMS to the APFR egress position at CETA 1 location. Note, the P6 fwd PVR must be retracted and cinched for this task due to SSRMS interference. This should have occurred on EVA 1.
* EV3 removes dummy XDPR and BSP boxes and temp stows them. The functional BSP and XDPR boxes are then removed from the ORU bag and 6B covers and then installed on P1 radiator plates using the PGT. Dummy boxes are stowed in ORU bag, dummy XPDR box stowed on 6B cover for 6 retrieval. When complete, MCC-H powers up the new boxes. EV3 then preps CETA carts for relocation by moving them so that CETA2 is in Bay 04. The carts are decoupled at this point and cart couplers are prepped for capture.
* CETA Cart Relocation - Both EV crew are involved with SSRMS support (which begins at the CETA 1 removal position). CETA 1 is moved first, then CETA 2. Each cart is removed from the rails at P1 by one EV crew (EV3) on the SSRMS APFR, who then holds the cart while the arm translates to the install position on the starboard side (S1) of the MT. The other EV crew (EV1) translates to S1. EV3 crew installs the CETA cart on the truss with SSRMS and EV1 assistance. Once installed, the free floating crew (EV1) rotates and locks the wheel bogies (four) into the MT rail and couples CETA 1 to the MT. The sequence is repeated for CETA 2. The task is concluded by EV1 coupling together the CETA carts. EV3 egresses the SSRMS APFR, translates to CETA 2 to grab the ORU bag (with dummy boxes) to take back to the airlock where it is temp stowed. He retrieves the dummy XPDR boxes and 6B cover plate from the bag. The dummy XPDR box will be put in the place of the P6 XPDR, which will be removed in the next task.
* Z1 SASA Gimbal Locks / MISSE Retrieval / P6 Transponder (XPDR) Retrieval - these tasks are performed concurrently by EV1 and EV3, respectively. Robotics support is not required. Mission 12A could not engage the locks due to bolt misalignment; but it still needs to be done in prep for SASA return on 10A. P6 XPDR is removed prior to P6 relocation on 10A since its current location will not receive power post P6 relocation. It will be returned for refurbishment.
* EV1 translates to Z1 and removes the Z1 SASA shroud to access the spare gimbal locks. Using the PGT, he rotates the lock fasteners until properly aligned and seated.
* EV3 retrieves the XPDR 6B cover plate from the ORU bag (temp stowed at the airlock) and translates to P6 for P6 XPDR removal. After removing the P6 XPDR, the dummy XPDR is removed from 6B cover and installed in the P6 XDPR location. P6 XDPR is installed on 6B cover and stowed on body restraint tether (BRT) and brought back to the airlock for return home.
* Time permitting, EV3 will inspect suspect P6 PiP pins along translation paths. This is desired to ensure PiP pins are secure prior to P6 relocation.
* MISSE 3 & 4 retrieval - While the MISSEs have been on-orbit, they may have incurred MMOD strikes that could puncture the tray and cause toxic battery leakage. If the crew had time during EVA 1 or 2, they took photos and downlinked via OCA for analysis. If this has not already been performed, EV1 will visually inspect and perform WVS survey. They will not be retrieved if leaking is seen or the MISSE cannot be closed and latched. EV1 translates to airlock gas tank 2 for MISSE 3, closes it and stows inside A/L. Then he translates to airlock endcone to retrieve MISSE 4. Once the MISSEs are brought inside, MS1 and MS4 disassemble and prep them for return to SHAB as soon as possible.
* SSRMS - supports EVA 3 tasks (P6 SASA, and CETA cart relocations) as described in the EVA section. After the EVA is complete, the SSRMS is no longer needed for the rest of the docked mission and is left in position with only a reconfiguration of the wrist for undocking.
* SRMS - Supports P6 SASA relocation views. After EVA 3 the arm is powered down until needed for Late Inspection.
* CWC Fills 9 & 10, PWR Fills 3 & 4 are performed.
* MS5 performs a two hour LiOH exchange between the SHAB, ISS and Orbiter. 9 STS- 114 cans will be rotated to the Shuttle for use; 3 cans will be transferred to SHAB for return; and 30 STS-118 cans will be transferred to ISS and pre-positioned for use on future missions.
* Shuttle & ISS crew terminate the transfer of N2 from Shuttle to ISS. If the mission is extended, the termination can be delayed until the desired quantity (50 lbs) is obtained.
* CCM-A - twice daily status check.
* CBTM - daily status check.
FD09 - Final Transfers, Off Duty, Hatch Closing (11 day mission)
* A FES Dump is initiated early in the day and terminated as late as possible.
* NOM H2O Config - configures the supply water system from the transfer config (enabled in Post Insertion) to the nominal orbit config when water transfer ops (CWC fills) are complete. This needs to occur before the FES dump is initiated.
* N2 Repress - scheduled at the start of the day and terminated just before hatch close. It is performed to meet the agreed to stack total pressure at hatch closure.
* Shuttle O2 System teardown which was used to support prebreathe.
* PWR Fill #5 is performed. Counting the two OGS PWR Fills, 7 fills have been performed.
* COND SWAP is performed. CDR will perform a hum sep check in presleep to ensure water going into the condensate bag.
* CCM-A - twice daily status check.
* CBTM - daily status check.
* P/TV04 sets up for the farewell and hatch closing.
* BPSMU QD - Drag Thru QD is deactivated.
* SHAB CC Deact - Drag through cables to the Lab and CC used for SHAB viewing are disassembled and stowed.
* SSV Outrate configured to 2.
FD09 - Alternate Version for 14 Day Mission (Crew Conf, Off Duty)
* Secure LAB & NODE MMOD Shields - could not be performed on 13A as planned
* OBSS OSE Installation - install the two OBSS OSE boom stands (assembled on FD07) onto two S1 zenith trunnions. The OBSS itself will be transferred on mission STS-123/ 1J/A. STS-124/1J cannot fly an OBSS requiring the previous mission (1J/A) to leave an OBSS on ISS.
* External Wireless Isolation System (EWIS) Antenna Installation.
* GPS Antenna Assembly (AA) #4 retrieval - return to allow failure analysis and repair.
* P6 AUX BAG MOVE - relocate the bag to Z1 forward to reduce translation time post 10A P6 relocation.
* S3 Wireless Video System (WVS) External Transceiver Assembly (WETA) Antenna Install at Camera Port (CP) 1 on S3 truss - most likely task to be deleted if not enough time in the EVA.
* MS3 is EV2, FE-2 is EV3.
* OBSS OSE Install - crew translates to S1 Zenith outboard (EV2) and inboard (EV3) trunnions and performs the installation.
* EV2 will then head over to S0 nadir-inboard (where the GPS AA #4 is located) and remove the AA. Meanwhile, EV3 translates to P6, retrieves the P6 Auxiliary Bag, then translates to Z1 forward for installation.
* Both crew perform the remaining EVA tasks together, but will not be described here as an EVA C/L with the revised timeline is not yet published.
* Last CWC Fill #10 is performed (in the 11 day no SSPTS plan, this was already accomplished on FD08).FD011 - Entry Prep (EOM-1) (11 day mission)
* NOM H2O Config - configures the supply water system from the transfer config (enabled in Post Insertion) to the nominal orbit config when water transfer ops (CWC fills) are complete.
* L-1 comm checks are scheduled for a prime MLA and prime DFR flyover. No WSSH or MLA, DFR backups are timelined.
* Comm String 2 C/O is performed.
* MADS PWR ON - The MADS instrumentation is activated in preparation for entry.
* SSV Deact.
* Ku Band stow.
* Water Dumps: Simo dump, followed by two condensate CWC dumps.
* FES Dump: initiated following the simo & CWC dumps and terminated as late as possible.
* Entry Cooling Config.
* EPO - MS4 and MS1 provide tours of Shuttle, demonstrations of crew tasks or hardware, and other items of interest. Voice will be recorded. Can be scheduled any time during the mission including post undock.
* CCM-A - twice daily status checks.
* CBTM - status checks.
FD011 - Alternate Version for 14 Day Mission (Transfer, DAIU Troubleshooting)
* Water dump period - includes a waste dump, two PWR dumps (evacuates empty PWRs), and a condensate CWC bag dump.
* O2 Transfer - If required during the mission, early in the day the O2 system is reconfigured (O2 RECONFIG TO XFER) from prebreathe support to a transfer config to ISS gas tanks. The transfer is initiated and will run until just before hatch closing on FD012 (14 day mission).
* CBTM Muffler is removed.
* CCM-A is powered off. FD012 – Alternate Version for 14 Day Mission (Final Transfer, Off Duty, Hatch Closing)