user manual

System A Fuel
System A Oxidizer
System B Fuel
System B Oxidizer
TABLE 3.5-16 (Continued)
LM-10 - RCS PROPELLANT (2) (3)
Required Ullage Requirement (in _)
Load (Ib) 5 Minimum 4 Maximum 4
107.7±0.9 152.5 164.5
208.8±1.9 267.0 279.0
107.7±0.9 152.5 164.5
208.8±1.9 267.0 279.0
Amendment 94
121_0/70
iActual4 i
Ullage (in 3)
FUEL OXIDIZER
Propellant Load 215.4 417.6
Trapped Outside Tanks 10.3 16.2
Tanked 205.1 401.4
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.9 393.4
LM-IO - Helium b Nitrogen
Consumable
Helium - APS tank #i (6)
- APS tank #2 (6)
- RCS tank #I (6)
- RCS tank #2 (6)
- DPS (SHe)
- DPS (Ambient)(6)
Nitrogen - Ascent
- Descent
Nominal Loading Requirement
Pressure ' Temp Weight
_PSIA_ ('F_ (ib)
3050 70 6.6
3050 70 6.6
3050 70 1.05
3050 70 1.05
80±2 N/A 48.5
1600 70 i.i
0.i
0.6
Actual
Pressure Temp Weight
(PSIA_ (°F) (ib)
LM-IO - Water b GOX
Consumable
Ascent Water - tank #I
- tank #2
Descent Water - tank #I
- tank #2
Ascent COX - tank #i (6)
- tank #2 (6)
Descent GOX - tank #i (6)
- tank #2 (6)
Nominal Loading Requirement
Actual
Pressure Weight Pressure
(PSIA) (ib) (PSIA)
N/A 42.5 N/A
N/A 42.5 N/A
N/A (7) N/A
N/A (7) N/A
830 2.4
830 2.4
2700 48.0
2700 48.0
Weight
(lb)
NOTES:
iSee Table 3.5-17 for actual propellant load calculation.
2See Section 5.6 for explanation of trapped propellants.
3See Table 3.5-18 for loading uncertainties.
_PV ullage calculation should be 158.5±50 cubic inches for LM/RCS fuel and
273±50 cubic inches for LM/RCS oxidizer per tank.
5LM/RCS required load includes propellant required to fill RCS manifolds
to isolation valves. See Table 3.5-16. 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-IO Descent Water shall be loaded to provide 365-0.O+10.0 pounds
at Earth Launch. Initial load will be determined by sampling requirements.
3.5-81
SNA-8-1)-027(III)REV 2