user manual

TABLE 3.3-16 (Continued)
I/4-7 - RCS Propellant (2) (3)
System A Fuel
System A Oxidizer
System B Fuel
System B Oxidizer
Required Ullage Requirement (in _)
Load _ib) 5 M_n4_um _ Max_m,,_ _
107.7'0.9 IIi.0 123.0
208.8'1.9 225.5 237.5
I07.7*0.9 Iii.0 123.0
208.8'1.9 225.5 237.5
FUEL OXIDIZER
Propellant Load 215.4 417.6
Trapped Outside Tanks 10.8 17.6
Tanked 204.6 400.0
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.4 392.0
Amendment 80
418170
*Actual _
Load (lb)
107,7
208.8
107.7
208.8
_Actual "
Ulla&e (In 3)
132.0
205.7
134.0
_lq_o
LM-7 - Helium & Nitrogen
Consumable
Helium - APS tank #1 (6)
- APS tank #2 (6)
- RCS tank #I (6)
- RCS tank #2 (6)
- DPS (SHe)
- DPS (Ambient)(6)
Nitrogen - Ascent
- Descent
Nominal LoadinS Requirement Actual
Pressure Temp Weight Pressure Temp
(PSIA) ('F) _ib) (PSIA) ('F)
3050 70" 6.6 3115 75.0
3050 70" 6.6 3203 76.4
3050 70o 1.05 3126 82.3
3050 70 ° 1.05 3099 81.1
80*2 N/A 48.5 _ _
1600 70 ° I.I 1653 78.3
0.1 N/A N/A
0.6 N/A N/A
Weight
(lb)
LM-7-Water & GOX
Consumable
Ascent Water - tank #i
- tank #2
Descent Water
Ascent COX - tank #I (6)
- tank #2 (6)
Descent GOX (6)
Nominal Loadin_ Requirement Actual
Pressure Weight Pressure Weight
(PSIA) _Zb) (PSIA) (Zb)
N/A 42.5 N/A (99.6%) 42.3
N/A 42.5 N/A (99.2) 42.1
N/A (7) N/A (99.6) 264*
830 2.4 841 (720F) -
830 2.4 838 (72°F) -
2700 48.0 2776 (80°F) -
*As serviced, predicted at lift-off is 254 lb.
NOTES:
Isee Table 3.3-17 for actual propellant load calculation.
2See Section 5.6 for explanation of trapped propellants.
3See Table 3.3-18 for loading uncertainties.
"PV ullage calculation should be 125*50 cubic inches for LM/RCS fuel and
238.5'50 cubic inches for LM/RCS oxidizer per tank.
5LM/RCS required load includes propallant required to fill RCS manifolds
to isolation valves. See Table 3.3-16. See Section 5.6 for trapped
propellants.
6The indicated items should be loaded in accordance with loading windows
contained in the CSM/LM Spacecraft Operational Data Book, Volume II,
Part 2, SNA-8-D-027PT2.
7LM-7 Descent Water load at Earth Launch shall be 250 -0, +i0 pounds.
The initial load will be determined by samplinR reouirements.
3.3-59
SNA-8-D-O27(III)KEV 2