LUNAR MODULE Subsystem. Assembly

and Installations

Grumman Aircraft Engineering Corporation Manufacturing Engineering

LUNAR MODULE Subsystem Assembly and Installations

Grumman Aircraft Engineering Corporation Manufacturing Engineering

December 1967

FOREWORD

This document provides a general introduction to the tasks and requirements associated with the manufacture of a Lunar Module. Major components of each subsystem are described and illustrated. Flow charts and allied exhibits are also included to show the various phases of subsystem fabrication, installation, and checkout.

CONTENTS

Section Page

GENERAL INFORMATION 5 1 The LM Mission - 6 2 General Description and Characteristics 8

SUBSYSTEMS - 11 1 Ascent Stage Structure 12 2 Descent Stage Structure 12 3 Landing Gear 14 4 Electrical Power 16 5 Environmental Control 20 6 Propulsion 22 7 Reaction Control 24 8 Crew Provisions/Displays 26 9 Guidance, Navigation, and Control 28

10 Instrumentation 30 11 Communications 32 12 Electro-Explosive Devices 34

SUBSYSTEM ASSEMBLY, INSTALLATION AND TEST FLOWS 36

LIST OF ILLUSTRATIONS

Figure Page

1 Lunar Module 9 2 Ascent and Descent Stage Structure 13 3 Landing Gear 15 4 Electrical Power Subsystem 17 5 Electrical Harness and Cable Assemblies 19 6 Environmental Control Subsystem 21 7 Propulsion Subsystem 23 8 Reaction Control Subsystem 25 9 Crew Provisions/Displays Subsystem 27

10 Guidance, Navigation, and Control Subsystem 29 11 Instrumentation Subsystem 31 12 Communications Subsystem 33 13 Electro-Explosive Devices Subsystem 35 14 Lunar Module Integrated Flow 37 15 Lunar Module Assembly, Installation, and Test Flow 39 16 Descent Stage, Group I Equipment 40 17 Ascent Stage, Group II Equipment 41 18 Descent Stage, Group III Equipment 42 19 Ascent and Descent Stages, Group IV Equipment 43 20 Ascent and Descent Stages, Group V Equipment 44 21 Plant 2, Descent Stage Structural Assembly

and Ascent/Descent Final Assembly and Test 45 22 Plant 3, Ascent Stage Structural Assembly 46 23 Plant 5, Ascent/Descent Stages Assembly and Test 47

General Information

1. THE LM MISSION

Grumman is currently building the Lunar Module (LM) which will function as a space ferry to transport two astronauts from a lunar-orbiting Apollo Command Module (CSM) to the moon's surface and back. The LM will be coupled to the CSM via a turn-around docking maneuver, to be performed during the earth-to-moon passage. Shortly after the combined CSM-LM arrives in the vicinity of the moon and achieves a lunar orbit, two of three astronauts riding in the CSM will enter LM through a connecting tunnel. LM will then be separated from the CSM mother ship and, under the control of its crew, will descend and land on the moon at a pre-selected landing site. During their planned stay on the lunar surface,

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the astronauts will carry out such scientific tasks as gathering soil samples, measuring temperature, gravity, and magnetic field strength, and conducting communications experiments. Local explorations in the vicinity of the LM are also planned. Re-embarking, the astronauts will lift off in LM's Ascent Stage. The Descent Stage will act as a launch cradle for the Ascent Stage and will remain on the moon.

The launch profile will bring LM to a rendezvous point with the orbiting CSM. After docking with the CSM, the LM crewmembers will transfer and rejoin the third astronaut in the CSM. The LM Ascent Stage will then be left in a lunar orbit as the CSM starts the trip back to earth.

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2. GENERAL DESCRIPTION AND CHARACTERISTICS

The Ascent Stage of the Lunar Module (LM) is the manned portion of the space vehicle (Figure 1). It contains a crew compartment, hypergolic ascent engine, an aft equipment bay and tank section, and 16 reaction control engines. The crew compartment is used as an operations center by the astronauts during their lunar stay. Lunar descent, lunar landing, lunar launch, and rendezvous and docking with the Command and Service Module (CSM) are also controlled from this compartment.

All or part of the following subsystems are contained in the Ascent Stage:

• Guidance, Navigation & Control

• Crew Provisions/Displays

• Environmental Control

• Electro-Explosive Devices

• Instrumentation

• Electrical Power

• Propulsion

• Reaction Control

• Communications

The unmanned Descent Stage contains equipment essential for landing on the lunar surface and serves as a platform for launching the Ascent Stage after completion of the lunar mission. In addition to the descent engine and its pressurization and propel-lant components, the Descent Stage houses the landing radar, electrical power and pyrotechnics components, and the Apollo Lunar Surface Experiments Package (ALSEP). It also contains outriggers that extend from the ends of the structural beams. These outriggers have provisions for:'

• Attaching the cantilever-type landing gear.

• Locating the Lunar Module within the shroud of the Saturn V aerodynamic shell.

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LUNAR MODULE GENERAL CHARACTERISTICS

DIMENSIONS (Legs Extended)

Overall height: 22 feet, 11 inches Overall width: 14 feet, 1 inch Diameter (diagonally

across landing gear) : 31 feet Ascent stage height: 12 feet, 4 inches Descent stage height: 10 feet, 7 inches

GENERAL DATA

Earth launch weight: 32,000 pounds Pressurized cabin volume: 235 cubic feet Cabin environment: 75°F

100% oxygen at 4.8 ±0.2 psia

Subsystems

1. ASCENT STAGE STRUCTURE

The Ascent Stage structure (Figure 2) consists of the following subassemblies: front face, cabin skin, mid section and aft equipment bay. The front face is mechanically assembled from 10 welded and machined sections. After a sealing and curing operation, the outer flange contour is machined for accurate mating to the cabin skin subassembly. The installation of secondary structure (stringers, shelves, brackets, etc.) completes the front face assembly.

The cabin skin subassembly is fabricated from formed chem-milled skin panels that are welded and mechanically fastened. Sealing of the mechanical joints, trimming of the forward edge to match the front face contour, and the addition of formed longerons and stringers complete the operation for this assembly.

The mid section, the largest of the subassemblies in the Ascent Stage, consists basically of two machined bulkheads, an upper deck tunnel weldment, a lower (engine) deck weldment and chem-milled skins. The mid section is mechanically joined with the front face and cabin skin subassembly and sealed to form the cabin pressure shell of the Ascent Stage.

Cold rails, chem-milled beams, struts, and machined fittings comprise the major structural components in the aft equipment bay. The attachment of this subassembly to the cabin pressure shell completes the Ascent Stage structure.

2. DESCENT STAGE STRUCTURE

The Descent Stage structure (Figure 2) consists primarily of machined parts and chem-milled panel/stiffener assemblies that are mechanically fastened. Fabrication of the Descent Stage begins with the joining of the machined picture frames and the chem-milled panel/stiffener assemblies to form the engine compartment. After the outrigger bulkhead assemblies are attached to the engine compartment with machined cap strips, the eight remaining panel/stiffener assemblies, the upper and lower machined decks, and the machined interstage fittings are added to complete the Descent Stage structure.

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Cabin Skin Assembly

Upper Deck Assembly

Scientific Equipment Bay

Lower Deck Assembly

Mid Section Assembly

Aft Equipment Bay Assembly

Specimen Return Container Assembly

Figure 2 Ascent and Descent Stage Structure

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3. LANDING GEAR

The cantilever-type landing gear (Figure 3) is attached externally to the Descent Stage and folds inward to fit within the shroud of the Saturn V aerodynamic shell. It consists of four sets of legs connected to outriggers that extend from the ends of the Descent Stage structural beams. Each landing gear consists of a primary strut and foot pad, a drive-out mechanism, two secondary struts, two down-lock mechanisms, and a truss. The struts are machined aluminum with machined fittings mechanically attached at the ends. The foot pads consist of inner and outer layers of spun aluminum that are bonded to honeycomb core. The formed aluminum tube probes on the foot pads are each equipped with a sensing device. The side braces are made of swaged tubing.

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Deployment & Down Lock Mechanism

Deployment Truss

Secondary Strut

Uplock Mechanism

Lunar Surface Sensing Probe

, Landing Gear

, Primary Strut

Landing Pad

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Figure 3 Landing Gear

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4. ELECTRICAL POWER (EPS)

The Electrical Power Subsystem (Figure 4) consists of the following major components: four silver-zinc Descent batteries, two Descent electrical control assemblies, two silver-zinc Ascent batteries, two Ascent electrical control assemblies, a relay junction box, a deadface relay, two circuit breaker panels, two inverters, and one lighting control assembly.

The four Descent batteries will supply power to the LM during all but the translunar phase on a normal mission from T-minus 30 minutes up to powered ascent. In the event of a battery failure, an abbreviated mission can be flown with the three remaining Descent batteries.

The Ascent batteries are used during a normal mission from powered ascent to docking, and during an abort requiring separation of the Ascent Stage from the Descent Stage. Prior to separation and during lunar stay, the Ascent batteries will be checked periodically. During powered descent they will be paralleled with the Descent batteries. Failure of an Ascent battery would require an abort.

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DC Buses

CSM/LM Electrical Umbilical Connectors Electrical Control

Umbilical Interstage Connection (2)

(2)

Dead Face Relay

DC/AC Buses

Junction Box

Lighting Control Assy & Cold Plate

Scientific Equipment Power Outlet

Assy (2) Batteries (2)

Figure 4 Electrical Power Subsystem

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Ascent Stage Internal Wiring

Included in the Electrical Power Subsystem are all the electrical harness and cable assemblies on the Lunar Module. The Ascent Stage has approximately 20 major electrical harnesses and 60 electrical cable assemblies. The Descent Stage has approximately 5 major electrical harnesses and 45 electrical cable assemblies. Major harness and cable assemblies contained in the two stages are shown in Figure 5.

Circuit Breaker Panel Disconnects

Panel 1 & 2 Disconnect Bracket

Bulkhead Connectors

Panel 12 Disconnect Bracket

Panel 3 Disconnect Bracket

Panel 8 Disconnect Bracket

Attitude Translational

Abort Sensor Assembly Wiring v

Assembly Wiring

Radar Assembly Wiring

RCS Wiring

Bulkhead Feed Thru Wiring

Interrupt Connector Assembly & Wiring

(R.H. Only)

Ascent Stage External Wiring

Interrupt Connector Assembly (Ascent)

Structure Wiring

Dead Face Connector (Descent)

Propulsion Control Wiring

Descent Stage Internal and External Wiring

Descent Engine Control Assembly Wiring

Stabilization Control Assembly Wiring

Battery Power & Landing Gear Electrical Control Wiring Position Wiring

Battery Power & Landing Radar Wiring Explosive Devices Wiring

Figure 5 Electrical Harness and Cable Assemblies

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5. ENVIRONMENTAL CONTROL (ECS)

The Environmental Control Subsystem (Figure 6) provides a temperature- and pressure-controlled oxygen atmosphere in the LM Cabin and Crew Suits, as well as a resupply of water and oxygen for the portable life support system. It also provides temperature control for on-board electronic equipment, as well as potable water. The subsystem consists of five integrated sections: atmosphere revitalization, oxygen supply and cabin pressure control, heat transport, water management, and cold plate. The major portion of the ECS is in the pressurized equipment compartment in the Ascent Stage. A portion of the glycol loop and two gaseous oxygen tanks are in the Ascent Stage aft equipment bay. A portion of the glycol loop (battery cold plates) is also in the Descent Stage. Two ECS water tanks are in the tankage section of the Ascent Stage; a larger water tank and an oxygen tank and pressure regulator are in the Descent Stage.

and Dump Valve

Coolant Water Evaporator

Steam Vent

Primary Water Evaporator

Coolant Accumulator

Water Tankage (2)

Cold Plates

Oxygen Tanks

Water Fill Ports

Water Bacteria Filters

Filter Secondary Coolant Loop

Coolant Recirculation Assy

Regen. Heat Exchanger

Oxygen Hose Assy

Cabin Temperature Control Valve

Water Hose Control Valve

Water Hose Assy

Cabin Air Recirculation Assy (Fan)

Water Control Module

Suit Temperature Control Valve

Suit Circuit Assembly

Umbilical Hoses (2) — Stowed

Oxygen Control Module

Secondary Water Evaporator

Steam Vent (From Cabin)

Cabin Pressure

Cabin Pressure Relief & Dump Valve

Steam Vent

Water Tank

02 & Glycol (3) Interstage Disconnect

Battery Cold Plates (2)

Figure 6 Environmental Control Subsystem

Gaseous Oxygen Tank High Pressure Oxygen Control Assy

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6. PROPULSION (P/S)

The Ascent Propulsion Subsystem (Figure 7) uses a fixed, constant-thrust rocket engine. The system includes the associated ambient helium pressurization and propellant supply components. The engine develops 3,500 pounds of thrust in vacuum, sufficient to launch the Ascent Stage from the lunar surface and place it in orbit. Two main propellant tanks are used: one for fuel, the other for oxidizer. The tanks are installed on either side of the Ascent Stage structure. The propellant supply sections in this subsystem also provide for fuel and oxidizer interconnect to the Reaction Control Subsystem as a propellant supply for the latter during select mission phases. The fuel is a 50/50 mixture of hydrazine and unsymmetrical dimethyl hydrazine. The oxidizer is nitrogen tetroxide. These propellants constitute a hyper-golic system, that is, engine ignition results when the propellants come in contact with each other.

The Descent Propulsion Subsystem consists of two fuel and two oxidizer tanks with interconnecting gas and liquid balance lines for the like tanks. The pressurization system consists of cryo-genically stored helium and an auxiliary ambient start system. The system is centered about a deep-throttling ablative rocket engine which has restart capabilities. The maximum thrust level is approximately 10,000 lbs. and the engine can be throttled to 1050 lbs. The engine is mounted in the center compartment of the Descent Stage cruciform, suspended at the throat of the combustion chamber on a gimbal ring that is an integral portion of the engine assembly. The engine is gimballed to maintain thrust vector e.g. alignment. The propellants are identical to those used in the Ascent engine and Reaction Control thrusters.

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23 Helium Pressurization Modules ( 2 )

Oxidizer Tank

Helium Tanks (2)

Ascent Engine

Figure 7 Propulsion Subsystem Summon.

Ambient Helium Tank

Supercritical Helium Pressurization

Module

Heat Exchanger

Engine Skirt Contour

Supercritical Helium Storage Tank

Descent Engine

7. REACTION CONTROL (RCS)

The Reaction Control Subsystem (Figure 8) serves to stabilize the LM vehicle during descent and ascent, and to control the vehicle attitude about, and translation along, all axes during landing, rendezvous and docking maneuvers. The RCS consists basically of 16 thrust chambers supplied by two separate helium pressurized propellant supply sections. The 100-lb. thrusters can be fired in a pulsed or continuous mode, and are radiation-cooled. The thrusters and the dual propellant supply sections make up two parallel, independent systems. The propellants are identical to those used in the Descent and Ascent engines. The ascent system propellants can be used to supply the RCS thrusters in certain operational modes.

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Helium Pressurization

Module (2)

Thrust Chamber Assembly

Propellant Quantity Measuring Device

RCS Manifold Crossfeed &APS Interconnect (2)

Figure 8 Reaction Control Subsystem

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8. CREW PROVISIONS/DISPLAYS (CP/DS)

The Crew Provisions/Displays Subsystem on the LM is shown in Figure 9. Support and restraint equipment is provided in the forward part of the main cabin. During flight, the support and restraint equipment provides the astronaut with stability to help him accomplish his tasks, and augments his ability to withstand the lunar landing impact.

Other items included under Crew Provisions are control panels, interior and exterior lighting, food and water containers, pressure and thermal garments, and boots.

The Portable Life Support System (PLSS) is a self-contained rechargeable system that provides limited-time life support for an astronaut exposed to extra-vehicular free space, a decompressed LM, or the lunar surface environment.

Waste management is controlled by means of de

vices which provide for removal and decontamination of urine and feces. These operations are possible under pressurized and unpressurized conditions. Waste water from the PLSS is also collected through waste management devices.

Displays and Controls provide the astronauts with sufficient information and control of the LM subsystems to successfully complete the mission or to return the LM safely to the CSM in an emergency. Located to optimize astronaut safety and mission success, the primary navigation and guidance readouts and data entry panel, propulsion, reaction control, environmental control, flight control and stabilization and control systems panels are either shared or duplicated at both stations. Each astronaut is assigned specific mission responsibilities, and only those parameters are displayed for which there is a potential human response (i.e., control action).

imbal Angle Sequence Transformation Assy

& Cold Plate

S. E. Abort Guidance Panel J

Crewman Optical Alignment Sight /

Support &

Restraint (2) Window'

1 Tracking. Light Electronics Assembly

^ Tracking Light & Cold Plate

Platform & Handrails

Astronauts Equipment

Sequence Camera

Main Panel/Cabin Floodlights (2)

Instrument Panel Glare Shields (2)

S. E. Circuit Breaker Panel

Cmdr's Main Flight Panel

Flight Director Attitude Indicator (2)

S. E. Main Flight Panel

S. E. Center Side Console

Radiation Survey Meter

Portable Life System Support

Flight Data Books

Primary LiOH Stowage Cartridge

Oxygen Purge

S. E. Lower Side Console

Shades (3)

Secondary"] LiOH Cartridge

Stowage (5)

Cmdr's Circuit Breaker Panel

Armrests —Stowed Position (4)

Cmdr's Lower Side Console

Fire Extinguisher Water Dispenser

Engine Stop Button (2)

Cmdr's Lighting Control Panel

Stowage Bag

Cmdr & S. E. Lower Main Flight Panel

Cmdr & S. E. Lower Center Panel

E. V. Visors (Stowed)

Portable Life Support System on Cockpit Floor

Figure 9 Crew Provisions/Displays Subsystem

9. GUIDANCE, NAVIGATION AND CONTROL (GN & C)

The Guidance, Navigation and Control Subsystem (Figure 10) provides for flight path control of the LM throughout the mission. It consists of four major sections: Primary Guidance and Navigation Section, Radar Section, Control Electronics Section and the Abort Guidance Section.

The Primary Guidance and Navigation Section is essentially an aided inertial system whose principal aids are the alignment optical telescope and Radar Section consisting of the landing radar and rendezvous radar. The inertial measurement unit is aligned to an inertial reference by star sightings with the alignment optical telescope. Altitude and velocity information from the landing radar is used to update the inertially derived data. During the coasting descent, lunar stay, and rendezvous phases of the mission, the rendezvous radar coherently tracks its transponder in the CSM to provide range, range rate, and angle measurements (with respect to antenna axes) to the LM guidance computer.

The Control Electronics Section processes the flight data that controls the LM vehicle during all phases of the mission. The Abort Guidance Section provides semi-automatic pre-programmed flight control data to the Control Electronics section when a mission abort maneuver is being executed due to malfunction of the Primary Guidance and Navigation Section.

Alignment Optical Telescope

Rate Gyro Assy & Cold Plate

Abort Sensor Assembly & Cold Plate

Rendezvous Radar Assy

Computer Control & Reticle Dimmer Assy

Data Entry & Display Assy

Fuse Assy #2

Inertial Measuring Unit

Pulse Torque Assy & Cold Plate Abort Electronic Assy

Attitude & Translation Control Assy

Coupling Display Unit & Cold Plate

Power Servo/Signal Conditioner Assy and Cold Plate

Display & Keyboard Assy

Stabilization & Control Assy (2)

Signal Conditioning Assy

Alignment Optical Telescope

ranslation/Thrust Controller Assy (2)

Attitude Controller Assy (2)

Descent Engine Control Assy

Gimbal Drive Actuator

Landing Radar Electronics Assy

Landing Radar Antenna Assy

Figure 10 Guidance, Navigation and Control Subsystem

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10. INSTRUMENTATION (INSTS)

The Instrumentation Subsystem (Figure 11) consists of sensors and the signal conditioning, caution and warning, pulse code modulation and timing, and data storage electronic assemblies. The subsystem monitors the LM subsystems during manned phases of the mission, provides signal inputs to the vehicle displays and caution and warning array, prepares status data for transmission to earth, provides timing frequencies for the subsystems, and stores voice data.

Pulse code modulation telemetry changes data generated by subsystem sensors to digital form for S-band and VHF transmissions to keep ground stations informed of vehicle status.

Included within the subsystem are scientific instruments which will be used by the astronauts during their lunar stay for surface experiments.

Caution & Warning Electronic Assy

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Sensor Power (2)

Sequence Camera Extra Film Stowage

Data Storage Electronic Assy and Cold Plate

Signal Conditioning & Electronic Replaceable Assy No. 1

Specimen Return

Container Assembly

Radioisotope

Thermal Generator

Scientific Equipment Boxes (2)

Figure 11 Instrumentation Subsystem

1 1 . C O M M U N I C A T I O N S ( C S )

The Communications Subsystem (Figure 12) is made up of redundant S-band transceivers and power amplifiers, redundant VHF transceivers, and signal processing equipment with associated antenna systems. These equipments provide the following capabilities: 1) S-band for transmission of PCM telemetry, TV, voice, emergency key and range data between LM and earth; 2) VHF for linking LM and Command Module, and the LM and astronaut on the lunar surface; 3) VHF telemetry capability from LM to Command Module on the far side of the moon; 4) EVA (Extravehicular Astronaut) link to earth via VHF/S-band relay.

12. ELECTRO-EXPLOSIVE DEVICES (EED)

The Electro-Explosive Devices Subsystem (Figure 13) consists of its own redundant power supplies, relay boxes and wiring to accomplish the following:

• Release of the landing gear for deployment

• Enable helium pressurization of the Ascent Propulsion, Descent Propulsion, and Reaction Control Subsystems

• Stage separation

• Venting of Descent Propulsion Subsystem on the lunar surface

Interstage Umbilical Guillotine

Pyro Battery

Explosive Device Relay Box

Subsystem Assembly, Installation and Test Flows

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WEEKS -•

BASIC FLOW

Ascent

FIXTURE

UTILIZATION

Ascent

PLANT

UTILIZATION

Ascent

10

M/S SUB'S & CABIN

FACE ASSY & TRIM

CABIN SKIN FXTS

M/S SUB FXTS

WELDING FXTS

FRONT-FACT FXT

12 13 14 15 16 17 18 19 20 21 22 23 24

ASCENT STRUCTURE

FACE & CABIN BUILD-UP

M/S FIXT

ASC STRUCT MAIN FIXT

FRONT-FACE & CABIN B/ U FIXTURES

25 26 27 28 29 30 31

ASCENlfltoRK STAND

Descent ENG

BU11B4JI*

32 33 34 35 36 37 38 39 40 41 42

FINAL ASSEMBLY INSTALLATIONS

GROUP tt EQUIPMENT

DESCENT STRUCTURE

ASCENT WORKSTAND

Desc

43 44 45

DESCENT : WORkiSfXND

GROUP I EQUIPMENT!

46 47

FINAL ASSY (NSTL'S i

GROUP JH EQUIPMENT!

ASCENT GENERAL TENT

DESC STRUCT MAIN FIXT DESC WORKSTAND:

Descent PLANT 2

DESC GEN TENT

Figure 14 Lunar Module Integrated Flow

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Engine Deck/Skin Subassembly

Front Face Horizontal Front Face Machining Front Face Vertical Build-up & Trimming Build-up

Cabin Skins Drill Up

Cabin Skins Bench Build-up

Docking Tunnel/ Mid Section Build-up Skin Subassembly (Mid Section Assembly Fixture)

Optical Alignment of Navigation Base & Complete Major Structural Installations (Ascent Structure Workstand)

Welding Area

Rotate & Clean Install Electrical Subsystems & Plumbing & Group II Equipment. Conduct Gross Leak Check & RCS Flush, Ditmco and NASA Sell. Prefit Thermal Shielding. (Tent Ascent General Fixture)

Ascent Structure Mating, Sealing & Crew Provision Structural Build-up. (Ascent Structure Main Fixture)

Conduct Proof Pressure Checkout. Install GSE Harness. Cold Flow Tests. (Cold Flow I)

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Install Group IV Equipr ent GFE Fit Check, Electrhjldly Connected Tests, & Opt: Alignment of Equipme Installation & OCPTesU Install Descent Engine Align. (Integrated General Fi> t'

Panels & Bulkheads Descent Structural Build-up (Descent Structure Main Fixture)

Install Group I Equipment (Descent Structure Workstand)

Install Electrical Subsystems & Plumbing, & Group III Equipment. Conduct Gross Leak Check, DITMCO, & NASA Sell. (Tent Descent General)

Conduct Proof Pressure Checkout Install GSE Harness. Cold Flow Tests. (Cold Flow I)

. GFE

ure)

Rotate & Clean

Rotate & Clean

Cold Flow Tests (Cold Flow II)

Ship to Kennedy Space Center

Determine Weight

Install Group V Insulation Pack for ShiPment & Thermal Shielding

Clean Ascent Stage (Ascent General)

Install Group V Insulation & Thermal Shielding (Descent General)

Install Landing Gear & Test Landing Gear Fixture)

Determine Weight Remove Landing Gear & Clean Descent Stage (Landing Gear Fixture)

Pack for Shipment

Figure 15 Lunar Module Assembly, Installation and Test Flow î l̂ummafL

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Main Propulsion Tank

Main Propulsion Tank Main Propulsion Tank

Lower Decks

Figure 16 Descent Stage, Group I Equipment

Electrical Harnesses

Plumbing Lines

Cold Plates

Propulsion Helium Tanks

Propulsion Helium Module

Gox Tanks

Water Boilers

Freon Boiler

Electrical Harnesses

Plumbing Lines

Cold Plates

Water Tanks

Electrical Harnesses

Plumbing Lines

RCS Modules

Main Propulsion Tanks

Clusters

> T ^

Electrical Harnesses

Plumbing Lines

Figure 17 Ascent Stage, Group II Equipment

Electrical Harnesses

Plumbing Lines

Cold Plates

ECS Module

Windows

Engine Cover

42 e^3

Helium Module

0 Water Tank T _

» X (A

Electrical Harnesses

Plumbing Lines

Figure 18 Descent Stage, Group III Equipment

4 Antennas

Ascent Engine

Black Boxes Display and

Control Panels

Batteries

Electronic Explosive Devices

Black Boxes & Scientific

Descent Engine Equipment

Figure 19 Ascent and Descent Stages, Group IV Equipment

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Base Heat Shield

Figure 20 Ascent and Descent Stages, Group V Equipment

Thermal Shield

Shield

Insulation Thermal Shield

Ascent Stage

TDG-1

TAG-2

TAG-1

DS-1

P/B

DS-2

LEGEND

CODE LETTERS FIXTURE AND OPERATIONS PERFORMED

DS-11 DS-2/

Descent Structure Main Fixtures. Descent Structural Assembly Operations

TDG-11 TDG-2J

Tent Descent General Fixtures. Fluid and Electrical Installations. Ditmco

TAG-1 \ TAG-2/

Tent Ascent General Fixtures. Fluid and Electrical Installations. Ditmco

TADG-1 Tent Ascent or Descent General Fixture -Fluid and Electrical Installations. Ditmco.

PB Panel and Bulkhead Subassembly Area-Buildup of Panel and Bulkhead Subassemblies

SEB Scientific Equipment Bay Fixture. Buildup of Scientific Bay

Figure 21 Plant 2, Descent Stage Structural Assembly and Ascent/Descent Final Assembly and Test

Subassembly Area

Sxi. M/S

Subassembly

AMS-2 AFV-1 AMS-2

AFH-1 AMS-1

Cabin Skin Work Bench

WFF

m

ZD

LEGEND

CODE LETTERS FIXTURE AND OPERATIONS PERFORMED

WCS-l) WCS-2/ WMS-H WMS-2J WFF-1) WFF-2 WFF-3 ( WFF-4 J AS-1 AS-2 AS-3 AMS-ll AMS-2/ AFH-1

AFV-1

ASW-1 ASW-T - 2 f

Welding Cabin Skin Fixtures -Weld Cabin Skins Welding Mid Section Fixtures -Weld Mid Section Machined Subassemblies

Welding Front Face Fixtures -Weld Front Face Machined Assemblies

Ascent Structure Main Fixtures - Ascent Structural Mating & Assembly Operations Ascent Mid Section Fixtures - Ascent Mid Section Buildup Ascent Front Face Horizontal Fixture -Front Face Horizontal Buildup Ascent Front Face Vertical Fixture Front Face Vertical Buildup Ascent Structure Workstands - Complete Buildup, Pot, and Alignment of Navigational Base

Figure 22 Plant 3, Ascent Stage Structural Assembly

AG-3 AG-2 AG-1

LEGEND LEGEND

CODE LETTERS

DG-1) DG-2J

IG-1 IG-2 IG-3

FIXTURE AND OPERATIONS PERFORMED

Cold Flow Facility-Cold Flow Operations-Proof Pressure Check

Ascent General-Completion of Final Assembly operations-Installation of Thermal Shield-and Manufacturing update. Descent General-Completion of Final Assembly Operations-Installation of Thermal Shield-and Manufacturing Update. Integrated General-Ascent and Descent Installations-Electronic Subsystems Checkout-Electrically Connected Tests-Alignment-Operational Checkout Procedures.

CODE FIXTURE AND OPERATIONS LETTERS PERFORMED

LG-1 Landing Gear-Installation, Test and Removal of Landing Gear

WCG-1 Weight and CG of Vehicle EM-1 Electromagnetic Test Station-

Electro Magnetic Capabilities Checks

PS-1 Pack for Ship-Packing of Ascent and Descent Stages for Shipment

HS-1 House Spacecraft-House Space-Craft Operations.

HE-1 Handling Equipment-Temporary Storage of Handling Equipment.

VP-1 Vehicle Position-Temporary Holding of Vehicle.

Figure 23 Plant 5, Ascent/Descent Stages Assembly and Test