user manual

System A Fuel
System A Oxidizer
System B Fuel
System B Oxidizer
TABLE 3.4-16 (Continued)
LH-8 - RCS Propellant (2) (3) .
Required Ullage Requirement (in _)
Load _Ib) 5 Minimum _ Maximum _
107.7±0.9 111.0 123.0
208.8±1.9 225.5 237.5
107.7±0.9 111.0 123.0
208.8±1.9 225.5 237.5
iAciual_
Load (lb)
FUEl. OXIDIZER
Propellant Load 215.4 417.6
Trapped Outside Tanks 10.5 16.9
Tanked 204,9 400.7
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.7 392.7
LM-8 - Helium & Nitrogen
Amendment 88
1015170
IActual"
Ullage (in _)
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 Loadin B Requirement
Pressure Temp Weight
(PSIA) ('F) (lb)
3050 70" 6.6
3050 70" 6.6
3050 70" 1.05
3050 70" 1.05
80¢2 N/A 48.5
1600 70" 1.1
0,1
0.6
Actual
Pressure Temv Weight
{PSIA) ('F) (lb)
LH-8 - Water & COX
Consumable
Ascent Water - tank #I
- tank #2
Descent Water
Ascent GOX - tank #I (6)
- tank #2 (6)
Descent GOX {6)
NOTES:
Nomlnal Loadln R Requirement
Actual
Pressure Weight Pressure
(PSIA) (lb) (PSlA)
N/A 42.5 N/A
N/A 42.5 N/A
N/A (7) N/A
830 2.4
830 2.4
2700 48.0
ISee Table 3.4-17 for actual propellant load calculation.
2See Section 5.6 for explsnstlon of trapped propellants.
3See Table 3.4-18 for loading uncertslntles.
_PV ullage calculation should be 125_50 cubic inches for LM/RCS fuel and
23R,5±50 cubic inches for LH/RCS oxidizer per tank.
5LH/RCS required load includes propellant required to fill RCS mmifolds
to isolation valves. See Table 3.4-16. Sae Section 5.6 for trapped
propellants.
6The Indlceted items should be loaded in accordance with loading windows
contained in the CSM/LM Spacecraft Opcratlonal Data Book, Volume II,
Part 2, SNA-8-D-O27PT2.
7LM-8 Descant Water bhall be loaded to provide 250-0.0+10.0 pounds
at Earth Launch. Inltlal load will be determined by sampling requirements.
3.4-75
SNA_R_D_027 (III) REV 2
!1 !1 U E E U 12 L L: l: L; l: U Ek: L L ,_ L