Streak

 2005-037A

---

Minotaur launch of classified STP-R1 satellite from Vandenberg SLC-8. Designated USA-185 and nicknamed Streak because its launch (and SSO) was along the day-night terminator.

STP-R1
Date	Time	Event	Orbit
2005 Sep 23	0224	Launch by Minotaur
		T+1:05? Stage 1 sep, Stage 2 burn
		T+2:15? Stage 2 sep, Stage 3 burn
		T+2:27? Fairing
		T+ 3:30? Stage 3 burnout
		T+10:30? Stage 3 sep
	0234	T+10:40? Stage 4 burn	-3580? x 300 x 96.4
	0235	T+11:50? Stage 4 burnout
	0237?	Stage 4 sep
2005 Sep 30			295 x 320 x 96.3

Intelsat 907

 2003-007A

---

The last Ariane 4 carried another Intelsat 9 to orbit. Mass 4680 kg full, 2838 kg BOL, 1973 kg dry. Size 2.8 x 3.5 x 5.6m with 31 m span. Ariane 4 medium fairing 9.6m and 42 kg adapter ACU1194A.

Intelsat 907
Date	Time	Event	Orbit
2003 Feb 15	0700	Launch by Ariane 44L
		T+2:29 PAL 2,4 sep
		T+2:30 PAL 1,3 sep
		T+3:25 St 1 MECO
		T+3:30 St 1 sep
		T+3:31 St 2 MES
		T+4:18 Fairing sep
		T+5:36 St 2 MECO
		T+5:42 St 2 sep
	0705	T+5:45 St 3 MES
	0718	T+18:47 St 3 MECO
	0720	T+20:55 St 3 sep
		T+22:29 end of V159 mission
2003 Feb 15	1301		653.91 256 x 36899 x 7.0
2003 Feb		LAM-1
2003 Feb		LAM-2
2003 Feb 19		LAM-3
2003 Feb 19	0409		1323.80 31419 x 35697 x 0.4
2003 Feb 21	2100?	LAM-4
2003 Feb 21	2122		1428.53 35564 x 35712 x 0.1 GEO 28W+2E
2003 Feb 25	1014		1436.13 35777 x 35796 x 0.1 GEO 25.8W
2003 May 12			1436.03 35775 x 35795 x 0.0 GEO 27.2W
2006 Aug 8			1436.10 35772 x 35800 x 0.0 GEO 27.5W

Spot 5

 2002-021A

---

SPOT 5 will have a resolution of 2.5m (pan) and 10-20m (color), with a 60 km field of view. Mass will be 3030 kg. SPOT 5 is built by Matra/Toulouse. Orbit will be 832 km sun-synch. Size is 3.1 x 3.1 x 5.7m plus an end-mounted transverse solar panel of about 7m. Total length deployed is probably 10m.

SPOT 5
Date	Time	Event	Orbit
2002 May 4	0131:46	Launch by Ariane 42P V151	CSG ELA2
		T+1:31 PAL sep
		T+3:20 St 1 sep 78.2 km 1.87 km/s
		T+3:23 St 2 burn
		T+3:53 Fairing sep 137 km 2.40 km/s
		T+5:31 St 2 sep 277 km 3.91 km/s
		T+5:36 St 3 burn
		T+9:21 600 km 4.14 km/s
		T+15:44 802 km 6.05 km/s
		T+16:30 806 km 6,42 km/s
	0150:18	T+18:32 St 3 MECO
	0151:01	T+19:15 St 3 sep
		T+25:36 St 3 end of mission
2002 May 13			101.24 816 x 818 x 98.8
2002 May 15		Orbit raise to operational orbit
2002 May 15			101.41 824 x 825 x 98.8
2006 Aug 8			101.41 824 x 825 x 98.7

Payload:

• AOCS 150 kg hydrazine, 15N thrusters

• HRVIR Imaging cameras

  • Pan Cameras, 2.5-m res pan

  • Multispectral cameras 20-m res color, 3 vis and 1 IR band

Seventeen: November 2006

 https://welib.org/md5/f48b6d9077804be37a8ec1ba01e50f21

DBS 1

 1993-078A

---

DirecTV, a subsidiary of Hughes HCI, ordered two Hughes HS-601 satellites for Ku-band DTH domestic US television broadcasting. The first DBS satellite was launched in Dec 1993, by which time DirecTV Inc. was a separate Hughes Electronics company and no longer part of HCI. Half of the satellite capacity was sold to US Satellite Broadcasting (USSB). The DBS 1 satellite had a mass of 1270 kg, with 1590 kg of fuel in GTO and 455 kg of fuel at BOL. The bus was 2.3 x 2.3 x 2.6 m in size with a 26.2 m solar panel span.

DBS 1
Date	Time	Event	Orbit
1993 Dec 18	0127:00	Launch by Ariane
1993 Dec 18	0129	PAL sep (2:21)
	0130	St 1 sep (3:32)
	0131	Fairing sep (4:31)
	0132	St 2 sep (5:44)
	0132	St 3 TIG (5:49)
	0145	St 3 MECO (18:13)
	0148	DBS 1 sep (21:37)
1993 Dec 18			638.17 214 x 36136 x 4.0
1993 Dec 21			1156.47 24104 x 36132 x 0.5
1993 Dec 21	2041?	LAM
1993 Dec 23			1402.10 34134 x 36102 x 0.1
1994 Jan 5			1436.10 35767 x 35806 x 0.0 GEO 101.3W
1994 Jan 25			1436.08 35767 x 35804 x 0.0 GEO 101.2W
1995 Jul 25			1436.09 35777 x 35795 x 0.0 GEO 101.3W
1997 Feb 10			1436.10 35777 x 35795 x 0.0 GEO 101.2W
1998 Jul 4		Primary SCP failed
1999 Oct 15			1436.11 35776 x 35797 x 0.0 GEO 101.2W
1999 Dec 5		mv out
1999 Dec 8			1441.86 35888 x 35910 x 0.01
1999 Dec 21		mv in	1436.09 35774 x 35798 x 0.01 GEO 109.8W
2000 Jun 14			1436.08 35775 x 35797 x 0.05 GEO 109.8W
2003 Jul 19		mv out	110W
2003 Jul 30		mv in	102W
2005 Jul 15			1436.08 35782 x 35790 x 0.0 GEO 101.1W
2005 Jul		mv out to 72W
2005 Aug 21			1435.84 35772 x 35791 x 0.0 GEO 72.6W

Kosmos 2402

 2003-056A

---

11F654M Uragan satellite 794. The first set launched with a Briz-M upper stage, with the Proton third stage suborbital and falling in the Pacific. The first Briz burn lasted 24 minutes, with orbit achieved a full 35 min after liftoff. Briz-M no. 88506 was used.

Kosmos-2402
Date	Time	Event	Orbit
2003 Dec 10	1742:12	Launch by Proton-K/Briz-M	KB LC81
		T+1:58 St 2 start
		T+2:03 St 1 sep
		T+3:03 GO sep
		T+5:28 St 2 MECO
	1747:43	T+5:31 St 2 sep
	1751:45	T+9:33 St 3 MECO	-1200 x 181 x 51.55
	1751:56	T+9:44 St 3 sep
	1753:54	T+11:42 Briz MES1
	1803?	T+21.5m? Positive perigee
	1805?	T+23.0m? Circular orbit?
	1817:24	T+35:12 Briz MECO1	190 x 4347 x 52.4
	2023:19	T+2:41:07 MES-2
	2028	Perigee on equator
	2036:48	T+2:54:36 MECO2
	2038:08	T+2:55:56 DTB sep	291 x 19093 x 53.08
	2313:27	T+5:31:15 MES-3
	2317	DTB Apogee on equator
	2323:29	T+5:41:17 MECO3
	2324:52	T+5:42:40 Briz sep	18929 x 19328 x 65.11
	2325	Deployed

Soyuz TMA-5 (Tian Shan)

 2004-040A

---

11F732 No. 215 was used for the Soyuz TMA-5 flight carrying Expedition 10 to the ISS, mission 9S. Crew was Salizhan Sharipov (Kdr Soyuz, BI ISS-10), Leroy Chiao (BI-1 Soyuz, Cdr ISS) and Yuriy Shargin (BI-2 Soyuz, BI of EP-7 crew).

Callsign Tyan'-Shan' (Tien Shan).

Launch mass 7270 kg. Docking mass 6849 kg, undocking 6862 kg.

Landing position 51 03N 67 18E, very close to the target. 

TMA-5
Date	Time	Event	Orbit
2004 Oct 14	0306:26	Launch by Soyuz-FG No. 0112	PU5
		T+1:53 SAS sep
		T+1:57 Strapons sep
		T+2:37 Fairing sep
	0310	T+4:47 Blok A sep
		T+4:57 KhO interstage sep
	0315:11	T+8:45 Blok I MECO
	0315:14	T+8:48 Blok I sep
	0818:52	DV1 13.8m/s 35s SKD
	0904:19	DV2 4.6m/s 12.6s SKD
	1715		89.26 231 x 243 x 51.6
2004 Oct 15	0353:30	DV3 1.9m/s 6s SKD
2004 Oct 16	0300		91.77 355 x 367 x 51.6
	0355	Begin flyaround
	0400:42	Stationkeeping with Pirs at 243 m
	0404	Resume approach
	0408	At 97 m, halt
	0410	Resume approach
	0415:32	Docked with Pirs
	0714	HO to ISS
2004 Oct 22			91.75 354 x 366 x 51.6
2004 Nov 29	0932	Undock from Pirs
		At 30 m
		Approach
	0953	Dock with Zarya
2005 Apr 24	1545	HC
	1844:40	Undock Zarya
	1847:43	Sep burn 8s
	2116:38	Deorbit 278 kg 4:19 115.4 m/s
	2120:50	DO CO	-35 x 355 x 51.6
	2141:28	Modules sep
	2144:25	Entry interface
	2208:27	Landing at 51 03 24.96N 67 18 02.88E

Inmarsat 303

 1996-070A

---

Lockheed Martin Telecommunications built the third Inmarsat III, this time with the usual apogee motor for Atlas launch from Canaveral. Mass was 2071 kg.

Inmarsat III F3
Date	Time	Event	Orbit
1996 Dec 18	0157	Launch by Atlas IIA AC-129	CC LC36
	0159	Atlas booster sep
	0201	Atlas sep
	0201	Centaur MES-1
	0207?	Centaur MECO-1	200? x 1045? x 28.5?
	0222?	Centaur MES-2
	0223?	Centaur MECO-2
	0229	Centaur sep T+32:02
1996 Dec 19			646.66 1007 x 35778 x 22.7
1996 Dec 20	0250?	AKM
1996 Dec 20			1429.48 35450 x 35863 x 2.7 GEO 154.8E+1.6E
1996 Dec 27			1436.16 35698 x 35877 x 2.7 GEO 158.1E
1997 Jan 15			1436.25 35694 x 35884 x 2.6 GEO 157.4E
1997 Jan		mv out
1997 Feb 1		mv in	1436.07 35768 x 35804 x 2.6 GEO 177.9E
1999 Oct 15			1436.05 35768 x 35802 x 0.6 GEO 178.1E
2006 Aug 2			1436.10 35772 x 35800 x 0.0 GEO 178.1E

Thuraya 1

 2000-066A

---

The Emirates Telecommunications Corp. of Abu Dhabi (Etisalat) contracted for the Al Thuraya comsat system for Middle East mobile telephony services and spun off Thuraya Satellite Telecommunications. Thuraya uses a Boeing Satellite Systems (BSS) Boeing 702/GEM (Hughes HS-GEM, GEO Mobile) model with large 12.25m, 78 kg L-band antenna, based on the HS-702 bus. Power will be 13 kW. Launch 2000 May by Zenit-3SL, with HSC turning over the satellite to Thuraya after 4 months in orbit. Problems with the system meant that Thuraya Satellite Comms finally accepted the overall system in Feb 2002.

Mass is 5108 kg launch. Span is 34.5m. Location 44E.

In 2003, it was planned to lease the satellite to Planetel (California) to provide mobile comms to Asia. It moved to 52E in Aug-Sep 2003 and then to 98E in Jul 2004.

Thuraya 1
Date	Time	Event	Orbit
2000 Oct 21	0552	Launch by Zenit-3SL	Odyssey
		T+2:21 St 1 MECO
		T+2:29 St 2 MES
		T+3:33 Fairing sep
		T+7:20 St 2 MECO
	0600	T+8:35 St 2 sep	-2212 x 182
		T+8:40? Adapter sep	-2212 x 182
		T+8:45 DM-SL MES-1
	0604	T+12:50 DM-SL MECO-1	180 x 200 x 6.3
	0733	T+1:41:00 DM-SL MES-2
		T+1:47:35 DM-SL MECO-2	210 x 35891 x 6.3
	0751	T+1:59:05 DM-SL sep
		T+5:13:19 DM-SL disposal orbit
2000 Oct 21			632.01 222 x 35812 x 6.4
2000 Oct 24		LAM1	637.44 567 x 35745 x 6.5
2000 Oct 25		LAM2	720.15 4693 x 35777 x 5.3
2000 Oct 26		LAM	793.23 8269 x 35744 x 5.9
2000 Oct 28		LAM3	976.16 16681 x 35755 x 5.9
2000 Oct 30?	0600?	LAM4
2000 Oct 31			1399.89 34380 x 35769 x 6.4
2000 Nov 3		LAM5	1497.98 33812 x 40166 x 6.1
2000 Nov 15			1435.97 35738 x 35830 x 6.2 GEO 43.4E
2000 Dec 7			1436.12 35744 x 35829 x 6.2 GEO 44.3E
2003 Aug 27		mv out	GEO 44E
2003 Sep 20		Arrive 52E	1436.09 35766 x 35806 x 4.5 GEO 52.44E
2004 Jun 16			1436.05 35767 x 35804 x 4.1 GEO 52.4E
2004 Aug 4		Arrive at 98E
2004 Aug 25			1436.13 35766 x 35807 x 4.0 GEO 98.4E
2006 Aug 2			1436.15 35765 x 35810 x 3.1 GEO 98.5E
2007 May 10			1436.11 35765 x 35808 x 3.0 GEO 98.6E

Luna 18

  1971-073A

---

After Lunokhod 1, the E-8 program tried to repeat the sample return success of Luna-16 with E-8-5 No. 407 (Luna-18). However, the spacecraft crash-landed on the lunar surface during the second descent burn.

Luna-18
Date	Time	Event	Orbit
1971 Sep 2	1340:40	Launch by Proton-K	KB
	1350	Stage 3 sep
	1354?	MES-1
	1356:28	MECO-1	191 x 243 x 51.57
	1451:19	MES-2
	1459:00	MECO-2
	1503?	Blok D sep
1971 Sep 3	2140:41	TCM 2s
1971 Sep 5	2240:41	TCM 2s
1971 Sep 6	2306:29	LOI burn 241s
	2310:30	Lunar orbit insertion	117.8 73 x 125 x 35.2
1971 Sep 9	0323?	Rev 27 16.8m/s orbit correction	121.4 90 x 184 x 35.7
1971 Sep 10	0736?	Lower perigee 30.7m/s	114.7 15 x 119 x 35.4
1971 Sep 11	0742?	Aux tanks sep
1971 Sep 11	0742:21	Retrofire
	0742:28	Pitchover
	0746:42	Retro off, coast
	0747:10	Retro-2
1971 Sep 11	0747:16	Impact 3 34N 56 30E

Kosmos 2397

 2003-015A

---

Classified Russian Defense Ministry satellite launched in Apr 2003. The Proton used a 49.2 deg transfer orbit. Upper stage was 11S861 No 96L.

According to Kommersant newspaper it was a 71Kh6 US-KMO geostationary early warning satellite with a mass of 2155 kg.

Kosmos-2397
Date	Time	Event	Orbit
2003 Apr 24	0423:13	Launch by Proton/DM2 410-02	KB LC81/24
		T+2:06 St 1 sep
		T+3:03 GO sep
		T+5:30 St 2 sep
		T+9:34 St 3 MECO
	0433	T+9:44 Stage 3 sep
	0536	T+1:13:25 Blok DM-2 MES-1
	0543	T+1:20:28 DM MECO-1	x 49.2
	1057	T+6:33:49? SOZ burn
	1057	T+6:33:49 DM MES-2
	1100	T+6:37:02 DM MECO-2
	1100	T+6:37:17 DM sep
2003 Apr 24			1442.71 35887 x 35944 x 2.4
2003 May 29			1442.30 35886 x 35929 x 2.2 GEO 34.4E+1.5W
2003 Jun 5		brake	1439.35 35774 x 35926 x 2.3 GEO 24.3E+0.8W
2003 Jun 21		mv	1433.16 35558 x 35899 x 2.2 GEO 36.0E+0.7E
2003 Sep 5			1433.00 35544 x 35907 x 2.0 GEO 94.8E+0.8E
2004 Feb 15			1433.22 35548 x 35911 x 1.6 GEO 152W+0.7E
2004 Aug 26			1433.44 35556 x 35912 x 1.1 GEO 8.4W+0.7E

TES/Proba-1

 2001-049A

---

Technology (or Test) Evaluation Satellite.

ISRO imaging satellite to develop Indian reconnaissance capability. The TES project began in 1999 as a response to inadequate intelligence about a Pakistani incursion into Kashmir. 500 km orbit by PSLV. The satellite featured high torque reaction wheels and miniaturized power and control systems, as well as a new camera, a new propellant tank and reaction control systems. The satellite had 1-meter resolution and used a camera with about 70cm aperture.

\imps{2.5}{images/01049A002}

Mass is 1108 kg; launched with 94 kg PROBA and 92 kg BIRD. BIRD and PROBA are mounted on side platforms on the PS4 stage. TES was still operating in 2005 according to the 2005 ISRO report, and the 2015 Rao book implies it was still functioning after 14 years in space.

TES
Date	Time	Event	Orbit
2001 Oct 22	0453:00	Launch by PSLV	SHAR
		T+0:25 PSOM 3-4 burn
		T+1:06 PSOM 1-2 sep 24 km
		T+1:30 PSOM 3-4 sep 43 km
		T+1:52 Stage 1 sep 61 km
		T+1:53 Stage 2 MES 68 km
		T+2:36 Fairing 118 km
		T+4:39 Stage 2 sep 241 km
	0457	T+4:40 Stage 3 burn 242 km
		Stage 3 MECO, coast 445 km
	0501	T+8:20 Stage 3 sep
		T+8:35 Stage 4 burn 456 km
	0508	T+15:12 Stage 4 cutoff 571 km
	0509	T+16:10 Deploy TES	550 x 579 x 97.8
	0509:49	T+16:50 Deploy BIRD
		T+17? Stage 4 RCS burn 8:20
	0520	T+27:38 Deploy Proba

Payload:

• PAN Camera, two-mirror on-axis optics, 1-m resolution

2001-049B

---

ESA smallsat with mass 100 kg, size 0.6 x 0.6 x 0.8m. 1200 km polar orbit by ISRO PSLV Jun 2000. To test satellite autonomy and microprocessor. Contractor is Verheart Design and Development NV of Kruibeke, Belgium using the MiniSIL bus of SI/Newbury-England. Control by SAS/Belgium via Redu.

The satellite was redesignated an ESA Earth Observation 'third party mission' after its techology mission was complete.

Proba
Date	Time	Event	Orbit
2001 Oct 22	0453	Launch
2005 Oct		Still operating

Payload:

• CHRIS Imaging spectrometer 4500A-1.0mu

• SREM Radiation monitor

• DEBIE Orbital Debris evaluation (dust impact detectors)

• HRC High Res Camera, 10m res

• WAC Wide Angle Camera

STS-109 (Columbia)

 2002-010A

---

Servicing Mission 3B was delayed to late 2000 following the addition of 3A and later slipped to 2002. ACS will replace FOC. ACS has three cameras. The WFC, with two 4096 x 2048 CCDs, has a 3.5' FOV and covers the 3700A -1 micron range. HRC, the High Resolution Channel, has a 0.45' FOV and a 1024 x 1024 CCD, covering the 2000 A to 1 micron range. SBC, the Solar Blind Channel, has a 0.5' FOV, a 1024 x 1024 PCA array and covers the 1100 - 1800A range.

EVA 1: install SA and diode box, -V2. (RAC) Install wire harness to diode box. Install thermal covers on WFPC and bays. EVA-2, install SA and diode box, +V2. (RAC) Replace RWA (MULE). EVA 3: Power controller unit replacement (SAC). Telescope completely powered down. Thermal covers installed to protect critical equipment. EVA 4: swap FOC for ACS (SAC); ESM (MULE). Demate FOC and stow on sill; install CASH wire harness for cooling system; install ACS. EVA 5: Install NICMOS cryocooler (SAC); then install NCS radiator (MULE).

Launch mass 116987 kg, landing mass 100562 kg. MECO mass 115817 kg. MECO orbit 56 x 571 x 28.5 deg.

STS-109
Date	Time	Event	Orbit
2002 Jan 16		OV-102 tow to VAB/3
2002 Jan 17		ET mate
2002 Jan 23		Rollout from VAB/3 aborted
2002 Jan 28	1137	Rollout to LC39A
2002 Feb 27		Scrub at T-27h
2002 Mar 1	1122:02	Launch from KSC LC39A
	1124:07	RSRM sep
	1130:26	T+8:24s MECO
	1130:47	ET sep	55 x 574 x 28.5
			90.98 57 x 587 x 28.48
			90.89 62 x 574 x 28.5
		Mass 115243 kg
	1205:59	OMS-2 1:28 40.6m/s	92.30 199 x 574 x 28.46
	1207:27	OMS-2 CO mass 113737 kg
	1207	ET apogee
	1250?	ET reentry near 19N 135W
	1317:12	PLBD open
	1643:49	NC-1B OMS-3R burn 14s 3m/s,
	1644:03	OMS 3 CO
	2200		92.41 211 x 574 x 28.46
2002 Mar 2	0512:52	NC2 burn RCS 1.4m/s
	0710:50	end cabin depress
	1417:34	NC3 burn RCS 1m/s	92.46 216 x 574 x 28.47
2002 Mar 3	0407:37	NH 113549 kg, OMS 207s burn, 99.6m/s
	0509:03	NC4 RCS 20s 1.3m/s
	0600:59	NCC 0.5m/s 5s
	0608	RMS uncradle
	0701:05	TI OMS-5 (L) at 15 km, 10.8s 2.6m/s
	0721:06	MC1 RCS 3s 0.2m/s
	0733:51	OOP Null burn
	0756:29	MC2 1.8s 0.1m/s
	0813:28	MC3 8.1s 0.6m/s
	0823:29	MC4 8.1s 0.6m/s
	0840	At 182 m
	0852	At 90m
	0907	At 45m, 0.03m/s
	0928	RV with HST along -Rbar
	0931:34	RMS grapple HST
	1014	HST 1m from BAPS
	1032	HST berthed on FSS
	1049:41	RMS ungrapple
	1051?	Remote umbilical attached
	1342	Stbd SA retracted
	1445	Port SA retracted	96.16 563 x 583 x 28.5
2002 Mar 4		EVA-1 Grunsfeld, Linnehan
	0616	Begin depress
	0621	Hold at 5psi
	0628	Resume depress
	0630?	Depress
	0631	HO
	0632:02	AL end depress
	0637	Battery power
	0644	Egress EV1 (Grunsfeld)
	0651	Egress EV2 (Linnehan)
	0701:41	Grapple MFR
	0824	SA-2(S) removed
	0837	SA-2(S) in RAC
	0847	SADE Diode box removed
	0847	New diode box in prep
	0930	New diode box installed
	0945	SA-3(S) -V2 removed from RAC
	1025	SA-3(S) connected to HST
	1125	Final clamps for old array in RAC
	1141	SA-3(S) deployed
	1200	HST bay 10 thermal cover installed
	1318	Linnehan prep for ingress
	1322?	Ingress
		TC closed
	1330	Hatch closed
	1337:58	Repress
2002 Mar 5		EVA-2 Newman, Massimino
	0625	Depress begins
	0628	Hold at 5psi
	0631	Resume depress
	0634	Depress complete
	0636	HO
	0636:44	Depress end
	0640	Battery
	0648	Newman egress
	0656	Massimino egress
	0741	Old port SA disconnected
	0803	Old array on RAC
	0820?	New DBA-II diode box off RAC
	0825	Old diode box removed
	0830	New diode box installed
	0840?	Old diode box on RAC
	0910?	Port SA-3 off RAC
	0948	Port +V2 SA-3 attached
	1042	Port SA-3 unfolded
	1120	New RWA-1 off MULE carrier
	1125	Extract old RWA-1
	1140?	Old RWA on MULE
	1145	Install RWA
		Install NOBL blanket on HST bay 6
		Tests on aft shroud bolts
	1343?	Ingress
	1348	TC closed?
	1349	HC
	1356:38	Repress
	1402	Resume repress after 5psi check
2002 Mar 6		EVA-3 Grunsfeld, Linnehan
		Water leak in EMU
		Resize EMU3 for Grunsfeld
	0811	Begin depress
	0825	Depress
	0826:45	AL end depress
	0826	TC open
	0826	HO
	0828	Battery power
	0834	Egress Grunsfeld
	0843	Egress Linnehan
	0900	Disconnect batteries
	0935	HST power down
	1130	Old PCU removed
	1140?	New PCU off SAC, Linnehan
	1143	Linnehan, JG exchange old/new PCUs
	1200	Install PCU in bay 4
	1204	Old PCU on SAC
		Remated batteries in bay 3 and 2
	1430	HST reactivated
	1458	Grunsfeld ingress
	1504	Linnehan ingress
	1507	HC
	1516:10	Repress
2002 Mar 7		EVA-4
	0852	Begin depress
	0856	Depress
	0857	TC open
	0857:29	AL end depress
	0857	HO
	0900	On battery
	0907	Mass. egress
	0918	Newman egress
	1000	FOC unlatched
	1042	FOC removed by Newman
	1100	FOC on sill
	1124	ACS off SAC
	1143	ACS in HST
	1250	FOC in SAC
	1325?	NCS EB unstowed
	1343	NCS EB installed
	1400	Install NCS electronics box complete
	1614	Ingress Massimino
	1622	Ingress Newman
	1624	HC
	1628	Repress (SFN?)
	1630:14	Repress 7:30 (NASA)
2002 Mar 8		EVA-5
	0830	Begin depress
	0833	Halt at 5psi
	0838	Resume
	0841?	Depress
	0842	HO
	0842:39	AL depress end
	0846	Battery
	0854?	Grunsfeld egress
	0901?	Linnehan egress
	1025?	NCS off SAC
	1048	NCS in position in HST
	1100	Cryocooler installed, connected
	1130?	NCS radiator off MULE
	1200	Radiator installed
	1300	Working cables for NCS
	1416	Shroud closed
	1512:49	MFR ungrapple
	1600	Grunsfeld ingress
	1600?	Linnehan ingress
	1602	TC
	1604	HC
	1607:41	Repress 7:20 (NASA)
	1718:04	Reboost
	1849		96.30 578 x 584 x 28.5
2002 Mar 9	0707:55	Grapple HST
	0756	ROEU disconnect
	0834	HST unberth
	0940	HST ap door open
	1004:16	Release HST	96.30 578 x 584 x 28.5
	1005:08	SEP-1 0.4m/s
	1037:16	Sep-2 burn at 300m, 10s 0.8m/s
	1201:02	OMS dual engine adjust 45s 22.8m/s	95.41 498 x 578 x 28.5
	1201:47	OMS 6 CO
2002 Mar 11	1007	RCS 48s 3.5m/s
			95.27 485 x 577 x 28.5
2002 Mar 12	0552:38	PLBD closed
	0822:39	OMS DO 4:04 127.5m/s	95.27 485 x 577 x 28.5
	0826:43	OMS DO CO (KSC 165)	90.73 43 x 577 x 28.5
	0900:52	Entry
	0931:52	MGTD KSC RW33
	0933:09	Wheels stop
	1400?	Tow to OPF