CHAPTER 7

GMLSs: PRIMARY FUNCTIONS ANDDESCRIPTIONS

The purpose of any delivery unit is to place (launch)a weapon into a desired flight path. That task must bedone safely, efficiently, rapidly, and as frequently as thesituation demands.

We will discuss the major GMLSs maintained byGMs. There are other missile launching systems in use,but they are not manned by GMs. These systemsinclude the NATO Seasparrow and the Harpoon andTomahawk canister launchers.

Before continuing, let’s define the terms mark andmodification, commonly abbreviated Mk and Mod,respectively. Each assembled unit of ordnanceequipment is identified by a name, a mark number, amodification number, and a serial number. Thisinformation is stamped directly on the equipment or onan attached nameplate. A mark number designates amajor change in design. Modification numbers areadded when there has been minor, but significant,design alterations. Units of identical design have thesame name, mark, and mod numbers, but are assigneddifferent serial numbers.

The missile launcher is an integral, but separate,element of the weapons system. The launcher providessupport for the missile before and during launch. Initialmissile flight orientation is provided by aiming the axisof the launcher along the computed line of fire. Thelauncher also provides two major electrical connectionsto the missile. One connection supplies preflightmissile orders that are generated by the missile firecontrol system (MFCS) computer. The otherconnection supplies firing (ignition) voltage to thepropulsion unit of the missile. The firing signal isnormally initiated by the weapons direction system(WDS) and weapons direction equipment (WDE).

Launchers may be rigidly attached to the ship orthey may rotate in train and elevation axes. The Mk 41Vertical Launching System (fig. 7-1) is an example ofa rigid launcher. The Mk 26 and Mk 13 Mods 4 and 7are examples of rotating axes launchers.

As you study chapters 7 and 8, pay particularattention to the terminology associated with eachsystem. For effective communication, we cannotoveremphasize the necessity for using correct technical

Figure 7-1.—Major GMLSs.

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terminology. For example, what is the difference

between a fixed rail and retractable rail? These terms

refer to a common launching system component whose

basic function is to stow or guide a movement of the

missile. The use of correct terminology when talking

about a particular system is absolutely essential. Some

system components do have slang names that are

generally recognized by all GMs and, if appropriate and

within good taste, the manual will mention them. For

more “colorful” definitions, go ask your chief!

Additionally, throughout the chapter, some

component descriptions will include various size

dimensions. They are given only so you will have a

better idea of a physical arrangement.

MK 13 MODS 4 AND 7 GMLS

LEARNING OBJECTIVES: Explain thepurpose/function of the Mk 13 Mods 4 and 7GMLS major components.

We will now study the Standard launching systemby covering a launcher commonly known as the“one-armed bandit.” The Mk 13 Mod 4 GMLS isinstalled aboard FFG-7 Oliver Hazard Perry-class shipsand the Mk 13 Mod 7 is installed aboard CGN-36California- class ships. They provide a varied tacticalarsenal of missiles to engage air and surface targets. Itstows, selects, identifies, loads, aims, and fires StandardSM-1, SM-2, and Harpoon missiles.

Figure 7-2.—Mk 13 Mod 4 GMLS.

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The Mk 13 Mod 7 GMLSs were originally built asMods 0, 1, and 3, but because of the design changes inthe control system giving the launcher Mod 4characteristics, they are now designated as Mod 7s. Thetext will address the Mk 13 Mod 4 configuration. TheMod 7 has the same configuration as the Mod 4.

CAPABILITIES

The Mk 13 Mod 4 (fig. 7-2) GMLS can stow up to40 missiles, one of which will be a guided missiletraining round (GMTR) in the rotating ready servicering (RSR) cells of the magazine. The outer ring stows24 missiles and the inner ring stows 16 missiles. Thesystem is capable of identifying up to seven types ofmissiles, A through G, plus the GMTR.

The main structural units of the magazine are thebase, the outer shell, the inner structure, and the stand.A plenum chamber, attached to the base, vents gases ifa missile accidentally ignites in the magazine. Theinner structure houses, among other components, thetrain and elevation power drives, the RSR/hoist powerdrive, the launcher relay control box, and the missile dcpower supply. In operation, the RSR rotates (betweenthe outer shell and the inner structure) to position theselected missile at the hoist station for loading onto thelauncher.

The missile launcher carriage has unlimited motionin train. The elevation load angle is 90°. The two trainload positions are 0° (inner ring) and 180° (outer ring)(fig. 7-3).

Automatic pointing cutout systems preventpointing a missile at any part of the ship. A firing cutoutmechanism prevents firing missiles in areas hazardousto personnel and at the ship’s structure. Individualship’s structure determines pointing and firing cutoutzones.

A dud-jettison unit is an integral part of the launcherguide. The dud-jettison unit ejects missiles overboardthat fail to fire and are unsafe to return to themagazine.

Modes of Control

The Mk 13 GMLS has two modes of control:automatic control and step control. Automatic controlis the normal mode for loading a missile onto the guidearm and for unloading a missile from the guide arm tothe magazine. The weapons control system (WCS)selects continuous loading or single loading to load andlaunch missiles in automatic control. Continuousloading initiates loading and launching until themagazine is empty or until WCS baits the operation.

Figure 7-3.—Mk 13 Mod 4 GMLS, launcher load positions.

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Single loading initiates the same operations ascontinuous loading, except that after launching onemissile, the launcher trains and elevates to the LOADposition to await further orders. The operation resumeswhen WCS orders another single loading or continuousloading.

Also, if properly set up, the fire control system(FCS) can remotely light off the launching system andauto-load (or auto-unload) a selected type of missile.The launcher can be aimed and a missile fired beforethe GM can return from the mess decks with a fresh cupof coffee.

Step control is the step-by-step sequencing andoperation of the Mk 13 GMLS components by manualswitching at the EP2 panel. The system can be operatedin step control to load and launch missiles in a tacticalsituation if the automatic control circuitry becomesinoperable. Missiles may be loaded onto the guide armin step-load and maybe unloaded into the magazine instep-unload. System components may also be cycledin step-exercise. Interlocks in the system ensure thatselected step control functions are sequentially correct.Indicating lamps on the EP2 panel signal completion ofeach component function.

The launcher train and elevation systems operateunder remote and local control signals. Remote ordersare generated by the FCS computer. Local orders comefrom synchro transmitters within the launching systemcontrol.

Functional Operation

Upon selection of a Standard or Harpoon missile inthe magazine, the weapon is hoisted onto the singleguide arm. Harpoon missiles receive initial warmup onthe guide arm. (Standard missiles do not requirewarmup.)

The launcher trains and elevates in response to

order signals from WCS to aim the missile toward thepredicted target. When the launcher synchronizeswithin 10 either side of the ordered position and themissile is ready internally, WCS may initiate firing.After the missile fires, the launcher automaticallyreturns to the LOAD position to receive the next missile

selected for loading from the magazine.

During continuous launching operations, thesystem is capable, under ideal conditions, of asuccessive firing rate of (1) Standard missiles at10-second intervals and (2) Harpoon missiles at about22-second intervals. This action continues until acease-fire order is given or the missile capacity(excluding the GMTR) of the magazine is ex-hausted.

Personnel Requirements

A launcher control station contains controls andindicators to regulate and monitor launching systemoperations. Under normal operating conditions, theMk 13 GMLS requires the services of a launchercaptain and a safety observer. The launcher captainsupervises the overall operation of the system andperforms all functions at the EP1 and EP2 panels asdirected by WCS. The safety observer watches thelauncher area and warns the launcher captain of unsafeconditions.

LAUNCHER

The Mk 13 GMLS consists of three majorcomponent areas, which are the launcher, the magazine,and the launching system control. We will discuss thelauncher first, then the magazine. Again, watch theterminology.

The launcher (fig. 7-4) is a self-powered majorassembly that supports, aims, and prepares the missilefor firing. Part of the launcher is on top of the stand,while the rest of it sits within the magazine structure.The main components of the launcher are the guide, thecarriage, and the train and elevation power drives.

Launcher Guide

The single arm launcher guide is mounted betweenthe left- and right-hand trunnion supports and consistsof the guide arm structure and a yoke. The guide armholds and prepares the missile for firing. The yoke isan extension of the guide structure, or weldment. Itpivots on trunnions extending from the left- andright-hand trunnion supports. The yoke also providesa weatherproof housing for some guide componentsand serves as a passage for electrical cables and fluidlines.

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Figure 7-4.—Mk 13 Mod 4 GMLS, launcher.

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FIXED GUIDE RAIL.— The fixed rail (fig. 7-5)is slightly less than 30 inches long and is securedto the lower or aft end of the guide arm structure. Inaddition to forward and aft shoe tracks, it contains aninternal track for the hoist chain, the pawl, and therollers. A cam track engages a special pair ofrollers on the chain to compensate for any hoistchain overtravel as it extends up to the launcher. Thisis called the adjustable buckling chain link and is shownin figure 7-12. The cam track directs any excess chaininto an upward curving chamber midway within thefixed rail.

An actuator arm in the forward left section of thefixed rail is a safety device. Through mechanical andhydraulic interlocks, it prevents the aft-motion latchfrom prematurely retracting during an unload cycleuntil the hoist pawl properly engages the aft missileshoe.

LAUNCHER RETRACTABLE RAIL.— Thelauncher retractable rail is an 8-foot-long unit thatpivots between two positions. It remains extendedexcept when the fired missile goes into free flightand during a jettison operation. During missilefiring, it guides the missile for the first 20 inches oftravel and then retracts so the aft shoe and fins donot strike it. For jettisoning a missile, the rail must bein the retracted position to engage the jettisonmechanism.

A pivot unit connects the aft end of theretractable rail to the guide arm structure. The tworetract shafts at the forward end of the retractablerail extend or retract the rail by means of the railoperating piston and control valve block. Latchessecure the rail in the extended or retracted position.A cable within the right-hand shaft contains leadsfor the rocket motor igniters. The left-hand shaftcontains some of the components of the rail retracttrigger.

The rail retract trigger is a pivoting bar thatprotrudes through a slot at the forward end of theretractable rail. When contacted by the forward shoe ofthe fired missile moving forward, the trigger initiatesthe mechanical and hydraulic actions that retract therail.

The arming tool is located between the rocketmotor igniters. It mechanically opens and closesthe circuitry between the missile firing contacts and

the ignition squibs of the rocket motor. The toolis a cylindrical piece that contacts the arming lever ofthe missile. It is actuated by a spring-loaded rod andlinkage mechanism attached to the latch lock of theforward-motion latch. Disengaging the latch lock armsthe rocket motor.

Aft-Motion Latch.— The aft-motion latch (fig.7-5, Detail B) is located near the pivot point of theretractable rail. This device is a stop that preventsa missile from moving backward on the retractablerail. The latch is a hydraulic piston that extendsbehind the aft shoe of the missile. One of itsassociated mechanisms is a rod that mechanicallydetects when a missile is on the guide arm. Thisrod also provides a discharge path for electrostaticcharges on the missile surface. Another plunger ofthe aft-motion latch pivots a piece on the hoist pawlto disengage it (hoist pawl) from the aft shoe of themissile.

Forward-Motion Latch.— The forward-motionlatch (fig. 7-5, Detail B) is a dual-purpose stop.It acts as a positive stop when the hoist raises amissile onto the retractable rail. Until missile firingor jettisoning, the latch also restrains the missilefrom moving forward on the rail and falling onto thedeck.

The latch is a steel piece that pivots into and out ofthe track chamber of the retractable rail, where it makescontact with the aft shoe of the missile. Theforward-motion latch and its operating mechanismprovide a 2,320-pound restraining force that holds themissile on the guide arm. When fired or jettisoned, themissile overcomes this force, pivoting the latch out ofthe track chamber.

The forward-motion latch lock is a movable piecethat bears against the forward-motion latch. The lockprovides the positive stop when the hoist raises a missileonto the retractable rail. During the missile firingsequence, a release piston disengages the latch link.Through linkage, this action causes the arming tool toarm the missile.

The Mk 13 also has a key-operated lock in therelease piston linkage. When closed, the key-operatedlock prevents the forward-motion latch lock fromdisengaging and, in turn, causing the missile to arm.The launcher captain uses the keylock as a safety deviceto prevent accidental arming of the rocket motor duringmissile checkout or inspection.

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Figure 7-5.—Guide arm.

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FIN OPENER AND CONTACTOR AS-SEMBLY.— Functionally, the identification probe(fig. 7-6) is used twice in system operation. During aninitial strikedown on-load of a missile, the fin openerassembly is extended to the missile. The probeconnects the missile-type information to the controlsystem of the launcher. There it is stored in theidentification memory circuits as missile-type andcell-location data. When this action is accomplished,the fin opener assembly is disengaged and the missilemay be unloaded into a cell.

During a load-and-fire operation, the fin openerassembly and probe are engaged again to recheckmissile identification. If the type of missile on the guidematches the type of missile ordered from the RSR,preflight orders/Harpoon warmup are applied to themissile. Otherwise, circuits to the 23-pin contactor willremain open and the incorrect missile cannot belaunched.

ELEVATION POSITIONER.— The elevationpositioner consists of a hydraulic piston and a latch atthe aft end of the guide arm structure (fig. 7-5, DetailA). When the blast door is open and the launcher guideis at 90° elevation, the tapered nose of the piston extendsdown to engage a spud on the door. This locks thelauncher guide to the carriage. The piston, orpositioner, retracts up into a bore within the guide armstructure to allow launcher elevation movements. Thelatch prevents the positioner from springing out due toa loss of hydraulic fluid pressure or because ofvibration.

Carriage

The carriage (fig. 7-7) is mounted on the magazinestand and is the support structure for the launcher guide.The carriage rotates in response to mechanicalmovements of the train power drive and transmits themechanical movements of the elevation power drive tothe launcher guide. In addition, the carriage connects

Figure 7-6.—Right-hand fin opener and contactor assembly.

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Figure 7-7.—Launcher carriage.

the launcher guide with electrical cables, hydraulic TRUNNION SUPPORTS.— The right-handlines, and anti-icing lines. The main components of the trunnion support is a weatherproof, 8-foot-high housingcarriage are a right-hand trunnion support, a left-hand bolted over an opening in the base ring. The structuretrunnion support, and a base ring. contains an opening in its base through which the

elevation chain drive extends.

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The trunnion is a drive shaft keyed to the yoke onone end and splined to the elevation arc on the other.This shaft transmits movements of the elevation arc to

the launcher guide. The trunnion helps support thelauncher guide and rotates on bearings mounted withinan opening of the trunnion support.

The elevation chain drive is a chain and sprocketassembly that transmits the movements of a drive shaftin the base ring to the elevation arc. Four chains connectthe lower sprocket to the upper sprocket. Each sprocketassembly has four wheels. The drive shaft in the basering rotates the lower sprocket. The upper sprocketturns the elevation drive pinion that moves the elevationarc. The chain guide, near the lower sprocket, is afour-channel track that bears outward on the four chainsto dampen their vibrations when operating. The chaintightener, near the upper sprocket, is also a four-wheelsprocket with an adjustment screw for establishing andmaintaining the proper chain tension.

The left-hand trunnion support is physically similarto the right-hand structure. It holds the non-driventrunnion shaft and mainly serves to route cables andhoses up to the fixed rail and rotates with the base ring.

BASE RING.— The base ring is a circular,blastproof structure about 6 1/2 feet across and 17inches high. It is designed to rotate within an off-center

opening of the stand. The base ring also supportsvarious components located inside the stand andtrunnion supports.

Blast Door and Fixed Rail.— The blast door is amovable weldment that pivots up and aside to allow thetransfer of a missile between the magazine and thelauncher guide. With the door latched open, a spanningrail (about 4 1/2 inches long) on one side of theweldment aligns with a fixed rail on the base ring andthe fixed rail on the guide arm. These rails provide thecontinuous tracks for the missile and the hoist. Also,when the door is open, a spud on the door aligns withthe elevation positioner on the guide arm. The blastdoor drive is a hydraulic unit that opens and closes theblast door. One piston raises and lowers the door andanother pivots the door sidewards through a 95-degreearc.

A small section of guide rail is attached to thestructure of the base ring just below the blast dooropening. It is called the fixed rail and rotates with thebase ring. The fixed rail spans the distance between thetop of the inner and outer retractable rails of themagazine and the spanning rail of the blast door.

Launcher Guide Power Unit.— The launcherguide power unit is an accumulator-type power supplythat provides hydraulic fluid pressure to components inthe launcher guide and the blast door. This powersupply uses an electric motor to drive a rotary pumpsubmerged in the main supply tank. A valve blockregulates and filters the hydraulic fluid before chargingthree accumulators. Part of the structure of the base ringforms the supply tank for the launcher guide power unit.

Train and Elevation Mechanical Drives.— Thetrain circle gear is mounted to and around the perimeterof the structure of the base ring. It is an external spurgear that meshes with the train drive pinion. Movementof the pinion rotates the base ring and launcher on thestand bearings.

Elevation drive components transmit the rotarymotion of the elevation B-end motor to the chain drivemechanism in the right-hand trunnion support. Acombination of shafts, couplings, and a planetarydifferential gearbox is in the base ring area.

Electrical Contact Ring.— The electrical contactring (another term for a slip ring) is an electrical transferdevice that allows continuous connections between therotating base ring and the stationary magazine structure.The ring suspends from the bottom of the elevationplanetary differential.

Train and Elevation Power Drives

The text will provide thorough coverage of the Mk13 GMLS power drives in chapter 5. The Mk 13 GMLSpower drives are mounted in the top inner structure ofthe magazine. (See fig. 7-4.)

MAGAZINE

The Mk 13 GMLS magazine (fig. 7-8) stows themissiles, transfers them up to or down from thelauncher, and serves as a mounting pedestal for thelauncher. The magazine may be divided into four mainstructural areas that contain the various majorequipment assemblies.

Stand

The stand (shown in figure 7-8) is a stationary,round structure about 3 feet high. It forms the entire toppart of the magazine structure. Besides the off-centerbase ring opening, the stand has four blowout platesequally spaced around its circumference. Twopersonnel hatches lead to the inner structure and theRSR areas.

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Figure 7.8.—Magazine structure.

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Outer Shell

The armor-plated outer shell is the structurebetween the stand and the base. Service openings arelocated near the bottom and halfway up the shell. Theyprovide access to the warmup contractors and RSRcomponents, respectively. A bearing race for the RSRrollers is attached to the upper section of the shell. Afour-segment missile restraint ring is directly above thebearing race. If a missile accidentally ignites in themagazine, the restraint ring holds it in place.

Inner Structure

The inner structure (fig. 7-9) of the magazine is inthe center of the outer shell. It is made up of threesections: top, middle, and bottom.

The top inner structure is essentially a cylindricalshell with several mounting pads. The magazinehydraulic power supply main tank and the train andelevation hydraulic power drive main tank are integral

parts of the top section. This section also contains amissile restraint ring similar to the one in the outer shell.

The middle inner structure has openings andcomponents for the warmup electrical contact ring. TheRSR radial bearings are in the rims at the top and bottomof this section.

The bottom inner structure, the shortest of the threesections, has five rectangular openings. Three of theopenings have covers that provide access to a ring gear,warmup contractors, and a hoist track. The other twoopenings are for the RSR drive pinion and drivehousing.

Base

The magazine base (shown in fig. 7-8) is at thebottom of the magazine structure. Its main componentsare a base structure, a plenum cap, a flametight hatch,96 blow-in plates, and 96 water injectors. The base addslateral strength to the outer shell, contains all themagazine service connections, and houses the missile

Figure 7-9.—Inner structure.

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water injection system. If a missile ignites in themagazine, the plenum chamber receives the exhaustgases and conducts them to an elbow-shaped duct atthe edge of the chamber. From here, the gases escapeinto the atmosphere.

The plenum cap contains a total of 96 compartmentsunder the RSR cells. Under the 16 inner ring cells,there are 3 compartments for each cell (48). Under the24 outer ring cells, there are 2 compartments for eachcell (another 48). As a result, a compartment is alwaysunderneath each missile for any of the 32 possibleRSR index positions. Each of the 96 compartmentsholds a blow-in plate assembly and a water injectornozzle.

Ready Service Ring (RSR)

The RSR (fig. 7-10) is a separate rotating structureinside the magazine between the inner structure and theouter shell. It indexes the cells clockwise orcounterclockwise to deliver selected missiles to the inner orouter hoist positions. A station-at-hoist interlock switchproduces a lamp indication on the EP2 panel, informingthe operator which cell is at the selected hoist position.

A hydraulic B-end motor inside the inner structuredrives the RSR. A speed reducer, consisting of a series ofgear trains enclosed in a housing, connects the B-end outputshaft to a speed reducer drive pinion. The pinion mesheswith the RSR circle (ring) gear. Two radial

Figure 7-10.—Ready service ring.

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bearings support the RSR laterally on the innerstructure. Twenty-four roller assemblies fastenedto the upper RSR rim between each cell supportthe RSR vertically. These rollers ride on a rollerpath mounted on the outer shell. A positioner (orlatch) under the RSR locks the structure in anyone of 32 index positions. The positioner bladeengages locking clevises along the lowercircumference of the RSR.

A magazine contactor is at the bottom of eachcell. As a missile lowers into a cell, a male-typeconnector plug in the contactor enters a female-typereceptacle in the base of the missile. That establishessystem-to-missile connection. Through this device,missile cell identification circuits are possible.

Each cell has one full-length magazine rail thatguides and supports the missile and hoist chain. A

Figure 7-11.—Magazine hoist.

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missile latch near the bottom of the rail locks the aft

shoe of the missile in the cell. On the opposite wall ofeach cell is a forward-shoe retainer. It engages one ofthe forward shoes to help steady the missile in the cell.Also, at the bottom of each cell is a flame cone. Thecone directs the flame of an ignited missile into the

plenum chamber. Access to each cell is throughindividual doors along the lower inner and outer walls

of the RSR.

Hoist Assembly

The components of the hoist assembly (fig. 7-11)perform all vertical transferring of the missiles. Thehoist chain (fig. 7-12) is an open-end roller andlink-type chain with cam-type projections and detenteson some specific links. They actuate interlock switchesand valves, couple with the shifter half-links on thehoist pawl units, and act as travel limit-stops.

Figure 7-12.—Hoist chain component A. Hoist chain; B. Outer hoist pawl.

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The chain stowage housing, mounted in the innerstructure, stows a majority of the length of the chainwhen it is retracted. A small section of chain remainsexposed on the drive sprocket and in the chain shifter.The hoist B-end hydraulic motor connects to a speedreducer and drive sprocket that drives the chain.

The hoist chain shifter is a hydraulically operateddevice located between the drive mechanism and thecurved tracks. It raises or lowers the hoist chain’sshifter half-link into alignment with either the inner orthe outer hoist pawl unit’s shifter half-link (see fig.7-12). Two curved track assemblies, one for the innerring and one for the outer ring, serve to guide the hoistchain and connected pawl unit. They pivot out andup to the magazine rail of the cell at the selectedhoist position, Additionally, the hoist pawl units arestored in their respective curved track sectionswhen the hoist chain is fully retracted at the magazineposition.

A hoist pawl unit is extended to engage the aftmissile shoe to load a missile. As the hoist pawl reachesthe intermediate position (the point where the aft shoeof the missile rests), a cam follower forces the pawllatch to pivot sufficiently away from the pawl link toclear the aft shoe. At the same time, other surfaces on

the hoist pawl are unlocking and caroming the cell latchopen. The pawl link contacts the bottom of the shoe. Acompression spring returns the pawl latch to its normalposition, closing over the top of the shoe. The missileis then raised to the guide rail of the launcher. There theaft-motion latch mechanism extends and pivots thepawl latch to release it from the aft shoe. The missileis now secured to the launcher rail and the chain retractsto the magazine.

Associated with the hoist assembly are the innerand outer retractable rails of the magazine. (See fig.7-11.) When either rail extends, it forms a continuoustrack between the magazine rail of the station at the hoistposition and the fixed rail mounted on the carriage basering. With both retractable rails retracted, clearance isprovided betweenthe missile heads and the RSR duringRSR rotation. Only one retractable rail may extend ata time.

Magazine Hydraulic PowerSupply

The magazine power supply furnishes hydraulicpressure to operate components of the RSR/hoist powerdrive (refer to fig. 7-2) and other units in the magazine(that is, retractable rails, RSR positioner, and chain

Figure 7-13.—Launcher control station.

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shifter). The power drive consists of an electric motorthat drives a hydraulic A-end pump. The pumpprovides hydraulic fluid pressure to either the RSRB-end or the hoist B-end. A hydraulic control valve

shifts or redirects the output of the A-end to the selectedmotor.

It is not unusual to see this type of arrangement (one

pump or A-end capable of driving two individualmotors or B-ends) in ordnance systems. In the Mk 13

GMLS, the RSR cannot index while the hoist is cycling

(and vice versa). This type of power drive is verypractical in design and results in a smaller, more

compact unit.

Harpoon Warmup

A Harpoon missile does not require warmup in the

magazine, but does require about 10 seconds’ warmup

on the guide arm. Harpoon warmup power is appliedthrough the fin opener arm (23-pin) contactor.

LAUNCHING SYSTEMCONTROL

The launching system control is the control, power

distribution, and test center for the GMLS. The main

components are the EP1, EP2, and EP3 panels locatedwithin the launcher control station (fig. 7-13). Other

components in or near the launcher control station arethe power transfer device (PTD), an inter-communication unit, a strikedown hand control, a

clinometer, a safety observer switch, jacks, andreceptacles. The strikedown and safety switchreceptacle and a telephone jack are mounted outside the

control station.

Power Panel, EP1

The EP1 panel (fig. 7-14) is the power distribution

unit for the launching system. This panel contains115- and 440-VAC power indicators, circuit breaker

on/off switches, fuses, elapsed time indicators, ground

detection indicator, and system safety and power supply

switches. The system safety and power supply switches

Figure 7-14.—Power panel, EP1.

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are a two-position rotary keylock switch that controls solenoid-operated latch locks the door when power is

the system motors. In the SAFE position, the switch available to the panel.opens the start/run circuit of the motor. The key maybe removed (and retained) by system personnel. This

Control Console, EP2

is a safety feature that prevents system operation when The EP2 control console (fig. 7-15) is the control

personnel are working around rotating machinery. A unit for the GMLS. It contains the operating controls

Figure 7-15.—Control console, EP2.

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and indicators on two angular sections on the upper part

of the console. These controls and indicators allow the

operator to select and monitor GMLS operation.

UPPER SECTION.— The upper section contains

missile-related switches. The 40 dud assignment

switches designate which RSR stations contain dud or

normal missiles. Missile code and type assignment

switches are thumbwheel switches that assign a

designated missile numerical code to type A through

type G missiles and T for the GMTR stowed on the RSR

in the magazine. Also, rows of indicating lamps light

up to display the load status of each station (cell) and

identify which station is at the HOIST position.

The Harpoon casualty mode and firing safety

switches are connected in the normal and emergency

firing circuits. The firing safety switch is another rotary

key-type switch. The key is removed in the SAFE

position to inhibit the rocket motor firing circuit.

LOWER SECTION.— The lower section of the

EP2 contains the launching system controls and

indicators. The controls are push-button indicator

switches used to activate and select the mode of

control and type of GMLS operation. For normal

auto/remote control operation, three primary control

switch groups at the center of EP2 start the GMLS

load-and-fire operation. The remote launcher control

or local launcher control push button selects who has

control over loading operations. If remote launcher

control is selected, FCS controls loading and, if

applicable, remote motor starting. In local launcher

control, the EP2 operator has control of the sys-

tem.

The other switches are used with the primary switch

groups for motor activation, step, exercise, and testmodes of system operation. The indicator lamp groups

provide the console operator with information related

to the launching system and missile status.

A timing code and logic status (TCLS) selection

and display module is on the right side of the shelf. This

module is used to troubleshoot and test GMLS

operations. Physically, it is very similar to a pocket

calculator in size and construction.

Push buttons on the TCLS let the operator enter

numerical codes for obtaining information on

equipment electrical status and for timing component

operations. Light-emitting diode (LED) indicators

display timing and circuit status according to the codes

(numbers) punched (entered).

INTERNAL COMPONENTS.— Access to

components inside the EP2 console is through a large

door on the back or two small doors on the front. The

components accessible through the back door are the

printed circuit (PC) cards on the wire-wrap backplane,

fuses, manual handcrank solenoid controls, receptacles

with polarizing key positions, electronic component

circuit cards, terminal boards, and other miscellaneous

components. All components in EP2 are identified by

an electrical designation stamped (or applied) on or near

each component.

Accessible through the two front doors are

rectifiers, low dc voltage power supplies, a rechargeable

nickel-cadmium battery, a battery charger, and a fan for

component cooling.

The rechargeable battery provides dc power to

launching system solenoids under two conditions. If a

power failure occurs in the 115-VAC power distribution

network during an operational cycle (that is, raising the

hoist), the dc battery supply will activate automatically.

The battery will provide a dc output for about 5 seconds

and permit completion of the interrupted cycle. The

second condition is used during maintenance or

troubleshooting procedures in a normal power-off

condition. System personnel activate the manual

handcrank solenoids control and position a selected

toggle switch. This actuates a particular solenoid and

permits handcrank or handpump operation of a

component (that is, extend or retract the launcher

retractable rail).

Electronics Panel, EP3

The EP3 electronics panel contains the electronic

control and test equipment for launcher train and

elevation power drives. The front of the EP3 panel

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Figure 7-16.—Electronics panel, EP3 (sheet 1 of 2).

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(fig. 7-16) contains the train and elevation test moduleand the digital director (DD), the local controlhandwheel module (LCHM), and the electronic servocontrol unit (ESCU).

The LCHM (fig. 7-16, sheet 2 of 2) generates trainand elevation local control position order signals topoint the launcher. Digital readouts on the LCHM showlauncher train and elevation positions. Responsesignals from synchros in the train and elevation powerdrive receiver-regulators operate the digital readouts onthe LCHM. The LCHM is the primary local control unitfor the launcher and comes on-line automatically whenlocal pointing is selected. During a HARPOONcasualty mode, the LCHM is required to point thelauncher.

The test module is used to test train and elevationnonpoint ing zones , nonf i r ing zones , andsynchronization of the power drives. It containsswitches and jacks to select the tests and record traces.

The DD is used to operate the train and elevationpower drives in local control. It is also used with the

test module and the electronic servo control unit(ESCU) to check and test power drive operation. TheDD has rotary and thumbwheel switches to control thepower drives. Digital readouts indicate DD output indegrees and minutes for train and elevation. A diodematrix pinboard, behind a locked cover, generates thestationary position orders for load, strikedown, andjettison operations.

The ESCU is located in the rear of EP3 and is theservo amplifier for the train and elevation power drives.The unit consists of a solid-state amplifier with 13 PCcards on the upper half and amplifier controls and testjacks on the lower half.

MK 26 GMLS AND MODS

LEARNING OBJECTIVES: Explain thepurpose/function of the Mk 26 GMLS majorcomponents with Mod differences.

Figure 7-16.—Electronics panel, EP3 (sheet 2 of 2).

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The Mk 26 Mods 0 through 5 GMLSs (fig. 7-17)have been designed to be an extremely versatile andsophisticated addition to the missile community. Theyare installed aboard the DD-993 Kidd-, CGN-38Virginia-, and CG-47 Tilconderoga- class ships. ThisGMLS possesses one of the quickest reacting andfastest firing rates of any comparable dual-arm system.

Constructed with advanced solid-state electronic,hydraulic, and mechanical features, the Mk 26 GMLS

is compatible with a variety of fire control systems(Standard, ASROC, and AEGIS). The system alsohandles a mixed arsenal of missiles including StandardSM-1, SM-1A, and SM-2 rounds and the ASROC (bothtorpedo and depth charge configurations).

PURPOSE AND CAPABILITIES

As a major subsystem of the ship’s combat system,the Mk 26 GMLS consists of a launcher, a magazine,

Figure 7-17.—Mk 26 GMLS with Mod differences.

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and a launching system control. Depending on the Modconfiguration of the system, 24 to 64 missiles arestowed vertically on the two rotating RSRs of themagazine. In response to remote or local commands,the system auto- or step-loads one or two missiles to thelauncher. A firing rate of two missiles approximatelyevery 9 seconds (with a 1-second salvo time delay) canbe maintained.

The launcher is capable of unlimited train and maybe elevated or depressed through an arc of 100°. Theelevation load position is about 90°, with one train loadposition of 0° or 180° for forward- and aft-mountedlaunchers, respectively. The launcher must be within20 minutes either side of the remote signal position tobe synchronized with an FCS pointing order.

The launcher performs all missile preflightpreparations like other GMLSs except for unfolding themissile fins. That action is accomplished in themagazine. Additionally, an adapter rail for the ASROCmissile is not required on the Mk 26 GMLS.

The RSRs independently index the nearest selectedmissile(s) to the hoist position at one end of themagazine. When the RSR indexes a missile to the otherend of the magazine, it aligns with the strikedown/intertransfer mechanism. System on-load, off-load,and intertransfer (from one RSR to the other) operationsare performed here.

The launching system control (fig. 7-18) is the brainof the launching system. Its electrical/electronic

Figure 7-18.—Launching system control components.

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equipment controls all launching system operations inreponse to ship computer signals. The integratedcontrol station (ICS), located below the launcher infront of the two RSRs, is the major component of thelaunching system control. All the control panels andequipment necessary to activate the system, monitor itsoperations, initiate local orders, and transfer automaticcontrol to weapons control are in this compartment. Inaddition, the ICS houses all the testing and cyclemonitoring equipment needed for maintenanceprocedures.

The ICS operator can communicate directly withother shipboard command stations through a 20-stationship communication network as well as sound-poweredtelephone circuits. Also, the operator can watch thewhole operation of the launching system. Two specialhigh-strength windows in the front of the ICS let theoperator see into the forward parts of the magazine. Aclosed-circuit television system with two remotelylocated cameras allows the ICS operator to monitoron-deck actions and parts of the magazine not visiblethrough the windows during all system operations.

MOD AND SERIAL NUMBERDIFFERENCES

The Mk 26 GMLS is currently divided into sixdifferent Mods that differ mainly in missile-stowagecapacities and “value engineering design changes.”Refer to figure 7-17.

The magazine of the Mod 0, called the basic system,contains two RSRs that can stow 12 missiles each. Byadding one lo-missile module to each RSR, the Mod 0becomes a Mod 1; likewise, by adding two 10-missilemodules to each RSR, the Mod 0 becomes a Mod 2.The Mod 0, then, can stow 24 missiles; the Mod 1, 44missiles; and the Mod 2, 64 missiles. The first eightsystems manufactured were assigned serial numbers 1through 8 and are currently the Mods 0, 1, and 2systems. They are primarily installed on the CGN-38Virginia class.

Mk 26 systems with serial numbers 9 through 18have incorporated valuable engineering design changesinto various components of the launching, loading,strikedown/intertransfer, and control system. Thesedesign changes alter the physical characteristics ofcomponents and systems without affecting theirfunctional characteristics. Generally, these minordesign changes were made to reduce system cost andweight. They also improved system reliability,maintainability, and availability (RMA). These

systems were originally built as Mod 0s and Mod 1s but,because of the number of changes made, are nowdesignated Mod 3s (old Mod 0s) and Mod 4s (oldMod 1s). They are primarily installed on the DDG-993Kidd class.

The Mk 26 Mod 5s are installed on the CG-47Ticonderoga- class ships with the AEGIS weaponssystem. Additional design changes have been made tointerface with the AEGIS equipments. The magazinecapacity is the same as Mod 1 and 4 systems.

The magazine size of the different Mods also affectssome auxiliary equipment. The amount of pipingneeded for the sprinkling and water injection systemsgrows with the magazine stowage capacity. The extrapiping also needs more pressurized seawater. Shipair-conditioning demands differ among the variousMods.

The launcher is the same for all six Mods. Exceptfor internal logic circuitry and some panel displays, theICS for each Mod is the same. The strikedown/intertransfer mechanism is unchanged. However,additional RSR modules do move the mechanismfarther from the launcher.

PERSONNEL REQUIREMENTS

For normal tactical operation, four persons arerequired to run the system. The main control console(MCC) operator activates, readies, and monitors systemfunctioning. A launching system captain is in charge ofthe ICS and supervises total system operation. Twoother personnel are assigned as fin assemblers/foldersand remain at-the-ready in the ICS. They also helpobserve magazine equipment operation through the twoobservation windows and visually verify that correctmissiles are at the hoist positions.

The text will now provide a general physicaldescription of the major component areas of the Mk 26GMLS. We will use the Mod 0 configuration (the basicsystem) as our model, and only the A-side equipmentswill be covered. Be particularly alert to the terminologyassociated with the Mk 26 GMLS.

MAGAZINE

The magazine is a below deck, weathertightcompartment for handling and stowing the missiles inan environmentally controlled condition. Itscomponents perform all operations involved withloading, unloading, strikedown, and intertransfer.

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Ready Service Ring (RSR)

A complete 12-missile RSR (fig. 7-19) is made byjoining three basic support structures: a hoist end, asix-missile section, and a strikedown end (assembled inthat order). The two end sections are structurallysimilar and provide space to mount three hanger railassemblies apiece. The six-missile section is insertedbetween the end sections and is fastened to the

magazine deck. It also supports the launcher platformabove. It has space for three hanger rail assembliesalong each side.

To increase magazine capacity, either one (Mods 1,4, and 5) or two (Mod 2) 10-missile sections are addedto a basic RSR. (See fig. 7-17.) Physically placedbetween a six-missile section and the strikedown end, alo-missile section provides space for five hanger railassemblies along each side.

Figure 7-19.—RSR components, general arrangement.

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Each basic section has three hanger rail chain tracks(upper, intermediate, and lower) that guide the hangerrail chains. A roller track, mounted just above the lowerchain track, guides the hanger rail rollers. The hoist endalso has six proximity switches gang-mounted near itsbottom. As the hanger rails move past these switches,rail-mounted actuators activate them in variouscombinations. This action identifies to the controlsystem individual hanger rails according to the numberassigned them.

Hanger Rail Assemblies

A hanger rail assembly (fig. 7-20) is made up of a13-foot structural rail column. The individual

Figure 7-20.—Hanger rail assembly.

components of the hanger rail support and hold a missileon the RSR. Mounted on the back of each column arethree chain sections with rail links. When joined toother hanger rails, three continuous chains are formedaround the RSR. They secure the rails to the RSR andprovide a means for indexing. A hanger rail rollersupports the assembly vertically in the RSR roller track.

Rail tracks on the front of the column engage andguide the pusher bar, missile shoes, and hoist chain.During loading/unloading operations, the hanger rail atthe HOIST position is locked to the RSR fixed railabove it.

SNUBBER ASSEMBLY.— A snubber assemblyis mounted to the back of each hanger rail. It has paddedarms which close on the missile to stabilize it in theRSR. A hydraulic piston and linkage arrangement atthe hoist station and a similar mechanism at thestrikedown station actuate the snubbers. The arms opento clear the way for all loading and unloadingoperations.

PUSHER BAR.— The hanger rail pusher bar is adevice that rides in the rail tracks and holds the aft shoesof AAW and ASW missiles. There are three differentlatch groups associated with the pusher bar. A pusherbar retainer latch at the bottom of the hanger rail locksthe bar at its fully lowered position. The latch isretracted by the hoist retractable chain track when itextends to align with a hanger rail at the HOISTposition. The retainer latch is spring-loaded to theextended position and reengages the pusher bar whenthe hoist retractable chain track retracts.

An ASW aft shoe restraining latch is near the topof the pusher bar. An AAW aft shoe restraining latch isnear the bottom of the pusher bar. Both latches arespring-loaded devices that close over their applicableaft missile shoe, locking it to the pusher bar.Functionally, during a hoisting operation, the hoist pawlengages the pusher bar and raises it to the launcher.There, guide arm components unlock the (AAW orASW) shoe restraining latches and disengage themissile from the pusher bar. The hoist retracts,returning the empty pusher bar to the magazine.

LOAD SEGMENTS.— The hanger rail containstwo different load segments. They are small, outersections in the guide track. They pivot open to admitmissile shoes to the hanger rail at the strikedown station(only). They close to hold the shoes in the rail at allother times. The upper segment receives the forwardshoe of an AAW and an ASW missile. The lowersegment receives only an ASW aft shoe. (The AAW aft

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shoe enters a loading slot cut in the bottom of the hangerrail near the AAW aft shoe restraining latch.) When ahanger rail is indexed to the strikedown station, the loadsegments align with a hydraulic piston assembly.Through linkage, the load segments are made to openand close as the piston extends and retracts.

HANGER RAIL NUCLEAR LOCK.— Eachhanger rail mounts a hanger rail nuclear lock (referredto as a rail lock). This key-operated device functions inconjunction with a system nuclear lock to permit orprevent the hoisting of a missile from that particular rail.The rail lock is locked (or extended) whenever a nuclearmissile is initially onloaded into that rail. Forconventional missiles, it is normally left unlocked.

ASW DEPTH CHARGE INDICATOR.— TheASW depth charge indicator (fig. 7-21) is a device thatinforms the control system whether an ASROC depthcharge missile is or is not at the hoist station. Mountedto the back of each hanger rail, the device consists oftwo plungers and a proximity switch actuator.

Functionally, when a depth charge missile is loadedinto a hanger rail, one of the fins of the rocket depressesthe spring-loaded fin indicator plunger that extendsthrough the rail. This action moves the switch actuatorplunger and actuator magnet.

The magnet will activate a proximity switch(mounted to the RSR at the hoist station) when thathanger rail is indexed to the HOIST position. Anelectronic signal is relayed to the control systemindicating a depth charge round is at the hoist station.

Also, before any hoist cycle may start (for any typeof missile), the fin plunger must be retracted to allowthe hoist chain to pass. A hydraulic piston on the RSRis made to extend and, through linkage, retracts theplunger from the chain track of the rail.

Figure 7-21.—ASW depth charge indicator.

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Hoist Assembly

The Mk 26 GMLS hoist assembly (fig. 7-22) is anintegral part of the RSR and is very similar to other hoistassemblies. The hoist chain is a link-connected, rollertype about 31 feet long with magnet actuators mountedto various links. They activate proximity switches onthe chain stowage track that indicate the raised,lowered, and intermediate positions of the hoist.

A hoist pawl and latch, an adjustable link, and abuckling link are on the forward end of the hoist chain.The hoist pawl and latch connect the hoist chain to thepusher bar for hoisting operations. The adjustable linkmakes possible the proper positioning and alignment ofmissiles on the launcher guide arm. The buckling linkcompensates for any overtravel of the chain on anextend cycle.

The curved and retractable chain tracks extend fromthe hoist speed reducer and drive sprocket assembly tothe hanger rail. The curved chain track is stationary.The retractable chain track is a pivoting track that alignsthe curved track section with the hanger rail for hoistingoperations. When the retractable chain track extends,it actuates a mechanical linkage that releases the pusherbar retainer latch.

SYSTEM NUCLEAR LOCK.— The systemnuclear lock (also known as the RSR lock) is a devicesimilar to the hanger rail nuclear locks (fig. 7-23). It ismounted to the retractable chain track of the hoist. Bothlocks work together to prevent unauthorized loading ofnuclear warhead missiles.

Both locks must be locked to perform their intendedfunction. Figure 7-23, view A, shows how theretractable chain track is prevented from aligning withthe hanger rail. If the locks are in the conditionsdisplayed in views B, C, and D, hoisting can beaccomplished.

One key fits all the rail locks of one RSR, while adifferent key fits the system nuclear lock. According tonuclear weapon security regulations, the commandingofficer or a designated representative (must be acommissioned officer) maintains custody of these keysat all times. To load a nuclear ASROC round, personnelmust enter the magazine, prepare the missile, and(according to ship’s doctrine) unlock at least one of thelocks.

FIXED RAIL.— The fixed rail section is mountedto the top of the RSR’s hoist end section. (See figs. 7-19and 7-22.) This 4-foot rail bridges the gap between ahanger rail and the span rail assembly. All three rails

Figure 7-22.—Hoist components, general arrangement.

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Figure 7-23.—Hanger rail and system nuclear locks.

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Figure 7-24.—Fin opener assembly.

are locked together by hydraulically operated aligningrods extending into appropriate alignment guides.

Fin Opener Assembly

The Mk 26 GMLS fin opener assembly (fig. 7-24)is mounted to the magazine deck at the hoist station. Itis somewhat physically comparable to other fin openerarm assemblies. During a load cycle, the entireassembly shifts laterally between two positions, AAWor ASW, if required. This action aligns the fin cranksto the fins on the different diameter missiles. Once inproper position, the assembly then raises to engage themissile, unfolds the fins (of AAW and ASW rounds),and then lowers.

During an unload cycle of an ASW missile, the finopener assembly raises, unlocks, and refolds the ASWfins. The fins of AAW missiles cannot be automaticallyrefolded. System personnel must enter the magazineand manually close them.

Associated with the fin opener assembly is an AAWidentification probe (fig. 7-25). It is located within theinlet of the plenum assembly at the hoist station. Theprobe is used to identify AAW missile groups beforethey are hoisted. When the tin opener assembly shiftsto the AAW position, an actuator plate on the left-handopener engages a linkage rod attached to the probe. Asthe assembly raises (or lowers), the probe also raises (or

lowers) to engage (or exit) the aft receptacle of themissile.

Magazine Hydraulic Systems

Within each RSR’s six-missile section and hoist endsection are the components that produce the necessaryhydraulic forces to operate the system during normal

Figure 7-25.—AAW identification probe.

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and emergency conditions. The principal hydraulicsystems are the RSR/hoist main accumulator and powerdrive system and the exercise and emergencyaccumulator system.

RSR/HOIST SYSTEM.— Sharing a commonelectric motor, the RSR/hoist main accumulator systemand the RSR/hoist power drive function during allnormal GMLS operations. The main accumulatorsystem supplies various hydraulic fluid pressures tooperate components of the loading system, thestrikedown system, the jettison devices, and theRSR/hoist power drive.

The RSR/hoist power drive (fig. 7-26) provides thehydraulic power and control needed to index the hangerrails and to raise/lower the hoist chain and pawl. Ahydraulically operated shifter mechanism transfers theoutput of the hydraulic transmission to either the RSRspeed reducer and drive sprocket or to the hoist speedreducer and drive sprocket. The individual drive trainsfor the RSR and hoist are shown in figure 7-26.

EXERCISE AND EMERGENCY AC-CUMULATOR SYSTEM.— Each RSR contains anexercise and emergency accumulator system. It is usedin the event of normal electrical power failure or for

Figure 7-26.—RSR/hoist power drive.

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exercise/maintenance purposes. This system ishydraulically part of the RSR/hoist main accumulatorsystem. However, it uses a smaller electric motor andpump to deliver a reduced hydraulic fluid pressure tothe magazine components and the train power drive.

LAUNCHER

The launcher consists of all the componentsnecessary to receive missiles from the magazine andprepare them for launching. A rectangular plate about18 feet long and 10 feet wide, called the platform,supports the carriage and two dud-jettison devices. Italso provides mounting surfaces for the blast doors,span rails, and some train drive components.

The carriage supports the guide arms and consistsof various components, as shown in figure 7-27. Thestand is secured to the platform and serves as astationary support structure. The base ring fits insidethe stand and rotates on two sets of bearings. Ballbearings near the top of the stand support the weight ofthe rotating launcher. Roller bearings near the bottomof the stand hold the base ring in vertical alignment.

The trunnion support is a boxlike structure mountedto the top of the base ring. It supports the trunnion tubeon ball- and roller-bearing assemblies. It also housesthe elevation drive and other hydraulic components.

The electrical contact ring is located within the base ringarea. It transmits electrical power and anti-icing fluidbetween the stationary and rotating parts of thelauncher.

Blast Door and Span Rail

A blast door is mounted to the platform under eachguide arm. (See fig. 7-17.) In opening, the doorunlatches, raises, and swings aside. This providessufficient clearance for a missile with fins extended topass through. In closing, the sequence is reversed anda seal on the bottom of the door forms a water- andblast-tight closure,

A separate span rail assembly (not part of the blastdoor) is located inside the door opening. (See fig. 7-22.)It is a pivoting rail segment, about 3 feet long, extendedby a hydraulic piston. A bumper pad on the rail contactsthe edge of the blast door opening to provide a positivealigning stop. When fully extended, aligning and latchrods lock the span rail to the freed rail of the guide armand the fixed rail of the magazine.

Guide Arm

The guide arm structure (fig. 7-28) is a steelweldment with three different guide rails, ASW-relatedcomponents, and AAW-related components.

Figure 7-27.—Carriage, general arrangement.

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Figure 7-28.—Guide components, general arrangement.

Depending on the mode (AAW or ASW) in which thesystem is operating, the applicable equipmentsconnect to and prepare the missile for flight.

GUIDE RAILS.— Of the three individual guiderail sections on each guide arm, two are fixed andone is movable. The total length of the aft fixed rail

is about 50 inches. It contains a pair of hinged railtrack segments and an overtravel cam. The pivotingsegments, about 19 inches long, open and close toform the rail track for the aft shoe of an AAW missile.The overtravel cam accommodates a positioning linkon the hoist chain and pawl to allow properpositioning of a missile on the guide rail.

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The forward fixed rail is about 11 1/2 feet long andcontains no fictional components. This rail is usedonly when firing ASW missiles and provides the longeron-rail guidance required by this type of missile.

The retractable rail is mounted between the twofixed rails and is about 6 1/2 feet long. During a loadingoperation, it extends to align with the aft freed rail. Thiscombination forms one continuous rail track for AAWand ASW forward missile shoes. With an AAWmissile, the rail remains extended until the round islaunched. As the missile moves forward, the railretracts to clear the fins of the missile. With an ASWmissile, the rail retracts as soon as the round is loadedonto the guide arm. It remains retracted to form thelonger guidance track with the forward freed rail.

ASW RAIL COMPONENTS.— There are threedifferent components involved with preparing andlaunching ASW missiles on the guide arm. The ASWfire-thru and aft-motion latch piston and controlassembly operates two of these devices.

The ASW fire-thru latch is extended through therail to engage the forward edge of the aft missile shoe.As it extends, it causes the ASW aft shoe restraininglatch (on the pusher bar) to release. During firing, thefire-thru latch holds the ASW missile on the rail untilabout 2,600 pounds of thrust is developed by the rocketmotor and then it trips (releases).

The ASW aft-motion latch is extended by the sameassembly to engage the rear edge of the aft missile shoe.It secures the missile to the rail and allows the pusherbar and hoist chain to retract to the magazine.

The third component is the ASW contactorassembly (fig. 7-29). When it extends, the contactorpins penetrate a pad near the aft shoe of the missile.Electrical power, preflight data, and firing voltages aretransmitted through this connection from UBFCS andWCS to circuits within the missile. At firing, thecontactor retracts into the guide arm.

AAW RAIL COMPONENTS.— The railcomponents required to load, prepare, and launch AAWmissiles involve three separate (and more complicated)assemblies. Located above the aft fixed rail, the AAWfire-thru and aft-motion latch assembly (see fig. 7-28)is functionally similar to its ASW counterpart. TheAAW fire-thru latch trips from 4,000 to 4,600 pounds.The AAW aft-motion latch extends to release the AAWaft-shoe restraining latch (on the pusher bar) to securethe missile to the rail.

Figure 7-29.—ASW contactor assembly.

The two hinged-rail segments (mentioned earlieron the aft fixed rail) operate with the aft-motion latchlinkage. When an AAW missile is loaded to the rail, thesegments are open to accept the missile. As theaft-motion latch extends, mechanical linkages cause thesegments to pivot closed, engaging the aft missile shoe.In this position, the segments prevent any lateralmovement of the missile. They also provide a shorton-rail guidance track. After firing or duringunloading, whenever the aft-motion latch retracts, thesegments pivot open to release the shoes.

A blast shield also operates with the aft-motionlatch linkage. The shield extends with the latch. In thisposition, it can protect the mechanism from launchsequence, rocket firing voltage is applied, and the motorignites.

Launcher Hydraulic Systems

There are three hydraulic systems associated withthe launcher. They provide all the necessary hydraulicforces required to train, elevate, depress, and operate theguide arm components.

The train power drive system is located under thelauncher platform. It drives the launcher through thetraining circle gear mounted to the base ring.

The elevation power drive system is located insidethe carriage. It drives the guide arms through theelevation arc mounted to the trunnion tube. In additionto elevating or depressing the guide arms, the elevation

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power drive system provides the main accumulatorpressure for the guide arm components. Figure 7-27shows the location of the elevation power drive and theguide arm accumulator and control assembly.

The third hydraulic system is the launcher exerciseand emergency accumulator system. (It is very similarto the exercise and emergency accumulator systemsdescribed with the RSR/hoist power drives.) Thissystem is hydraulically connected to the elevationpower drive system. Hydraulic fluid at reducedpressure is supplied to operate the guide armcomponents and the elevation power drive.

LAUNCHING SYSTEM CONTROL

The launching system control components performthree main functions: (1) They distribute electricalpower, (2) they process system orders and responses,and (3) they perform tests to determine systemreadiness. As you study the Mk 26 GMLS controlsystem, you will notice a break with tradition. Panelsare no longer designated EP1, EP2, and so on, but areknown by their full name or first-letter abbreviations.

Most communications and interface betweenweapons control, FCS, and the GMLS are in digitalword format. (There may be some terms presented herewith which you are not yet familiar, but they will beexplained later in the text.) Although not physically

located in the GMLS area, the digital serial transceiver(DST) (shown in fig. 7-18) is a solid-state electronicmodule in the weapons control area. It serves as acommunication Iink between WC and launching systemcontrol. This module receives parallel order data(electrical signals) from a computer in WC. It changesthe order data from parallel to serial form fortransmission to the ICS through cables. One cableconnects to the digital interface module (DIM) and theother to the local control module. The order data signalsdirect launching system operations in remote control.

The DST also provides response data fromlaunching system control to WC. The DST receivesserial response data from the local control module oncables. It changes these data from serial to parallelform. In parallel form, these data are in the correctformat for transmission to the WC computer. Theresponse data show the status of the launching system.

Integrated Control Station (ICS)

The integrated control station (ICS) (fig. 7-30),located at the hoist end of the magazine, is a water- andblast-tight compartment. It houses most of the power,control, monitoring, and test equipments of the system.The major cabinets in the ICS are the power distributioncenter (PDC), the MCC, the right- and left-hand circuitcard housings, and the train and elevation control testcenter.

Figure 7-30.—Integrated control station.

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POWER DISTRIBUTION CENTER (PDC).—PDC houses the electrical components that distributeand regulate all power to the launching system. It iscomparable to other EP1 power panels.

MAIN CONTROL CONSOLE (MCC).— TheMCC (fig. 7-31) is a modular, wraparound type of unit.It contains the operating controls and indicators neededfor programming and monitoring launching systemoperations. The individual modules in the MCC areshown in separate figures for clarity.

The video monitor module (fig. 7-32, view A)consists of electrical components and a TV screen usedfor watching either the launcher area or rear magazineareas.

The local control module (fig. 7-32, view B) is usedby the MCC operator as the local control station for thetrain and elevation power drives. Also provided are afiring safety switch, rail and system nuclear lockindications, and digital readout displays of bothlauncher ordered and actual positions. This moduleacts as a communication link between the DST andother ICS equipments.

The intercom module assembly (fig. 7-32, view C)has a 20-station intercom to other parts of the ship. Asmall compartment can store a set of sound-poweredphones for the MCC operator (plus a deck of cards,

Figure 7-31.—Main control console.

favorite magazines, and the latest copy of the GMtraining manual).

The missile select and launcher display module(fig. 7-33) has a variety of switches and indicators usedby the MCC operator during remote and local controlmodes. When the system is operating in remote control,the operator monitors the indicators that show the statusof power drives, remote WC orders, and load-and-fireoperations. When the launching system is operating inlocal control, the operator selects the type of missile, aload (or unload) operation, and either one or bothlauncher guide arms and RSR/hoist equipment.

The console control shelf assembly is directly infront of the MCC operator’s chair. It provides ahorizontal working space and mounts five separatemodules. They will be described left to right.

The system availability module (fig. 7-34, view A)contains push-button indicating and toggle switches.They are used to tell WC of launching systemavailability status and to select various test modes.

The strikedown step module (fig. 7-34, view B)contains the strikedown hatch, emergency motor, mainmotor, and strikedown step control push-buttonindicating switches.

The system control module (fig. 7-34, view C)contains the all motors start/stop, loading selection,pointing selection, magazine safety, launcher warningbell, and system selection groups of switches.

The launcher step module (fig. 7-34, view D)contains the launcher step control, jettison, andlauncher emergency drive groups of switches. Thismodule provides the controls and indicators forperforming and monitoring load and jettison operationsand for directing the launcher using the emergencymotors.

The telephone selector module (fig. 7-34, view E)has two rotary switches and a telephone jack. The loadand firing indications lamp test switch is a 13-positionrotary switch. The MCC operator uses this switch totest the load-and-fire indicator lamps in the missileselect and launcher display module. The telephoneselector switch is a six-position rotary switch. TheMCC operator positions this switch to select telephonechannels to communicate with either WC or locallaunching system sound-powered phones.

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Figure 7-32.—Main control console modules.

Figure 7-33.—Missile select and launcher display module.

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Figure 7-34.—Console control shelf assembly modules.

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The last component of the MCC is the power supplymodule (fig. 7-35). Electrical receptacles on the bottomof the module connect it to the PDC. The componentsof the module provide regulated dc power to solenoidsand solid-state circuits throughout the system. Many ofthe various rated de-power supplies are identical,interchangeable, and adjustable.

RIGHT- AND LEFT-HAND CIRCUIT CARDHOUSINGS.— The right- and left-hand circuit card

housings (fig. 7-36) are on either side of the MCC.These housings contain the electrical/electroniccomponents used for system control. The two housingsare arranged the same but show different information.The right-hand circuit card housing shows A-side, train,and elevation system status. The left-hand circuit cardhousing shows B-side and strikedown system status.

TRAIN AND ELEVATION CONTROL TESTCENTER.— The train and elevation control test center

Figure 7-35.—Power supply module.

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Figure 7-36.—Circuit card housings, typical.

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(fig. 7-37) is mounted on the right bulkhead of thecontrol compartment. It houses launching system testequipment, a DIM, and an ESCU.

Launching system test equipment is on the uppertwo shelves of the train and elevation control. The testequipment is used for programming and signal tracingof train and elevation components. Operating cycles ofthe launching system may be timed and proximityswitch actuators may be tested and charged. Theelapsed running time of motors, control system, andstrikedown equipment, along with the cumulativenumber of RSR index and raise hoist cycles, aremonitored. The equipment is also used forprogramming and testing integrated circuitcomponents.

The DIM is a solid-state electronic control module.It provides train and elevation analog signals to the trainand elevation control and to the ESCU. Inside the DIMare PC cards that accept either a remote, test, load, orjettison order signal. The signal depends on thepointing mode selected at the MCC. In remote mode,the PC cards accept serial order data from the DSTor-on an alternate path-the same serial order datafrom the local control module (view Bin fig. 7-32).

The PC cards change the serial order data to twoanalog signals: a synchro position order and a velocity

order. The synchro position order causes the train andelevation control to position the launcher. The velocityorder allows the ESCU to compensate the train andelevation control.

The PC cards process test orders the same way asremote orders, except that the order signal generator(OSG) provides the serial order data. For load orjettison mode, a diode pinboard in the DIM generatesfixed position signals. These signals allow the PCcards to generate the desired position.

The ESCU is the servo amplifier for train andelevation control. The PC cards inside the ESCUgenerate command signals that cause the train andelevation power drives to move the launcher to anordered position. The PC cards give command signalsby processing analog synchro pointing orders from theDIM and comparing these orders to the actual positionof the launcher. The actual launcher position isprovided to the ESCU by feedback signals from trainand elevation controls.

Auxiliary Equipments

Located on top of the ICS compartment are othercomponents not directly associated with the controlsystem, but they do bear mentioning.

Figure 7-37.—Train and elevation control test center.

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The personnel access trunk (fig. 7-38) serves as apassageway connecting the ship security station to theICS. It also mounts various weapons system-relatedelectrical and electronic equipments. Interconnectingcabling from WC and ship’s power enter the trunk andare routed to a receptacle assembly. The cables are thenattached to quick-disconnect plugs and routed to theICS.

A filter box assembly has components that filter115-volt ac, 400-Hertz synchro power and the 28-voltdc power for firing circuits. A channel selector (not partof the launching system) contains components used tomatch the frequency of the AAW missile on thelauncher rail to the radar channel frequency of the firecontrol system.

An ASW-missile setting panel (also not part of thelaunching system) contains electrical and electronic

equipment used for programming ASW missiles. Thethermal battery compartment (shown in fig. 7-18) stores15 ASROC missile (depth charge) thermal batteries. Abattery is installed manually in the weapon before it isloaded onto a guide arm. The compartment has twodoors and a combination lock.

Mk 41 VERTICAL LAUNCHINGSYSTEM (VLS)

LEARNING OBJECTIVES: Explain thepurpose/function of the Mk 41 verticallaunching system (VLS). Identify the majorcomponents and Mod differences of the VLS.

Figure 7-38.—Personnel access trunk.

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We will now discuss the physical and functionalcharacteristics of the Mk 41 Mods 0, 1, and 2 VLSs.The Mk 41 Mod 0 VLS is used with the AEGIS,Tomahawk, and underwater weapon systems onboardCG-47 and CG-52 and up class ships. The Mk 41 Mod 1is used with the Tomahawk and underwater weaponsystems onboard DD-963 class ships. The Mk 41 Mod 2is used with the AEGIS, Tomahawk, and underwaterweapon systems onboard DDG-51 class ships.

DESCRIPTION AND CAPABILITIES

The VLS (figs. 7-39, 7-40, and 7-41) is amultipurpose launching system that can load/accept,stow, select, prepare for launch, and launch the Standardmissile Type 2 (SM-2), the Tomahawk cruise missiles,and the vertical launch antisubmarine rocket (ASROCVLA) against air, surface, land, or subsurface targets.

The missiles are contained in separate sealedcanisters that are installed vertically below deck in

Figure 7-39.—Vertica1 Launching System Mk 41 Mod 0.

7-43

Figure 7-40.—Vertica1 Launching System Mk 41 Mod 1.

7-44

Figure 7-41.—Vertical Launching System Mk 41 Mod 2.

7-45

Figure 7-42.—Launcher Control Unit Mk 211 Mod 0.

individual cells of a vertical launcher. The Mk 41Mod 0 VLS on CG-47 and -52 and up class ships hasboth a forward and aft launcher with 61 cells in each.The Mk 41 Mod 1 VLS on DD-963 class ships has asingle, forward 61-cell launcher. The Mk 41 Mod 2VLS on DDG-51 class ships has an aft launcher with 61cells and a forward launcher with 29 cells.

LAUNCHER CONTROL UNITS(LCUs)

Each Mk 41 VLS contains two launcher controlunits (LCU 1 and LCU 2), Mk 211 Mod 0 or Mk 211Mod 1 (figs. 7-42 and 7-43), depending on the class andthe equipment installed. The LCUs interface with theship’s WCSs, manage VLS operations, and interfacewith VLS weapons for hazard monitoring and to select,prepare, and launch missiles. Each LCU is capable ofcontrolling all missiles in either launcher. Theymaintain simultaneous communications with the WCSsand each other.

Status Panel

The status panel Mk 416 Mod 0 or Mk 430 Mod 0monitors hazards and continuous power, controlslauncher power, enables strikedown and anti-icing, andprovides the launcher hazard status to the combatsystems maintenance control or damage control center.The status panel maintains communication with the re-mote launcher enable panel (RLEP) in CIC for remotecontrol of the magazine power and launch enable. Thepanel also includes a relay that is controlled by the safetyobserver’s safety switch during strikedown operations.

Remote Launch Enable Panel (RLEP)

The RLEP, located in CIC, interfaces with the statuspanel to provide control of the remote magazine powerand remote launch enable signals to the launcher. TheMk 428 Mod 0 RLEP is a double panel with one sidefor the forward launcher and an identical side for the aftlauncher. The Mk 441 Mod 0 and 1 RLEP is a singlepanel for controlling one VLS launcher.

Figure 7-43.—Launcher Control Unit Mk 211 Mod 1.

7-46

Figure 7-44.—Vertical Launcher Mk 158 Mod 0.

VERTICAL LAUNCHERS and the Mk 159 Mod 0, which is a 29-cell launcher (figs.

7-44 and 7-45). The launchers are housed in watertight

There are two types of launchers associated with the compartments that extend vertically from the secondVLS—the Mk 158 Mod 0, which is a 61-cell launcher, platform to the 01 level in all three ship classes.

Figure 7-45.—Vertical Launcher Mk 159 Mod 0.

7-47

The module is the primary structure component ofthe VLS launcher (fig. 7-46). It consists of the deckstructure, the intermediate structure, and the basestructure.

On the 8-cell module, the deck structure consists ofeight cell hatches and an uptake hatch. The deckstructure provides ballistic protection and supports theupper ends of the canisters. The deck structure is partof the gas management system that prevents rocketmotor exhaust gases from escaping into the openlauncher area. All hatches (with the exception of thestrikedown hatch) contain heating elements to preventicing. The cell hatches and uptake hatches areautomatically opened by individual drive motors beforemissile launch. After a 10-second delay, to permitventing of the remaining missile exhaust gases in thelauncher cells, the cell hatches automatically close.

The intermediate structure forms the midsection ofthe module and is also a part of the gas managementsystem. It consists of five uptake sections boltedtogether and the outboard structures. The uptakesections form a fluelike structure for venting missile

exhaust gases. The outboard structures are bolted to thesides of the uptake sections that serve as canister guiderails for installation and removal of canisters.

The base structure serves as a base structure for themodule and as a plenum for the gas managementsystem. The intermediate structure mounts directly tothe base structure for support of the module andcanisters. The interior surface of the plenum and uptakeare protected with ablative material to prevent the heatblast from overheating the VLS structure or shipstructure.

The launcher sequencer, mounted to the modulestructure at cell 1, is the interface unit between thecontrolling LCU, other module equipment, and themissiles. The launcher sequencer monitors the status ofthe module and the cells within the module.

5-CELL STRIKEDOWN MODULE

The 5-Cell Strikedown Module Mk 3 Mod 0 (fig.7-47) consists of the deck structure, the intermediatestructure, the base structure, and the strikedown

Figure 7-46.—Module structure.

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Figure 7-47.—5-Ce11 Strikedown Module Mk 3 Mod 0.

equipment. The major subassembliess are common to module—the fifth cell, the elevator, and the cranethe 8-cell module. assembly are on the other side of the module.

The deck structure consists of 5-cell hatches, 1 The base structure is the same as that for the 8-celIuptake hatch, and 1 elevator hatch. The strikedown module, except that the area containing cells 6 throughmodule related equipment is the same as that for the 8 on an 8-cell module are replaced by the elevator and8-cell modules, except the elevator hatch replaces cell crane in the 5-cell strikedown module. There are no cellhatches 6 through 8. openings in the plenum at cells 6 through 8.

The intermediate structure is the same as that of the The strikedown equipment consists of a crane, an8-cell module, except that the elevator extension elevator, an elevator control panel, an elevator powerstructure is part of the outboard structure. The distribution panel, and a junction box (see fig. 7-47).intermediate structure holds four cells on one side of the The crane is a hydraulic expendable boom that is stored

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below deck. The elevator raises and lowers the craneon its platform by means of a three-stage telescopinghydraulic cylinder, controlled by the elevator controlpanel. The elevator power distribution panel andjunction box provides 440 VAC, 60-Hz, three-phasepower to the hydraulic power supply.

of the vent fan. After a missile firing, the blowoutsystem must be operated for a minimum of 20 minutesbefore personnel enter the launcher and for 1 minuteeach hour thereafter that personnel remain in thelauncher.

POWER DISTRIBUTIONLAUNCHER SUPPORT EQUIPMENT

The vertical launcher support equipment consists ofa sill adapter assembly, a canister adapter, and a plenumcell cover that are coated with a heat-absorbing ablativematerial that protects the equipment from heat damage.

The sill adapter assembly is an open, funnel-like,steel weldment assembly that provides the lower matingsurface for the missile canisters. The sill assembly alsodirects missile exhaust away from the sides of themissile cell and into the plenum.

The canister adapter is a combination nozzle andspacer installed under the bottom of the canister toprevent rocket motor exhaust gases from circulatingback into the canister. When used in an empty cell, thecanister adapter holds the plenum cover at latchingheight.

The plenum cell cover is used with the canisteradapter to seal cell openings when a canister is not inplace. The cover also prevents gas from missile firingsin that module from entering the empty cell.

GAS MANAGEMENT SYSTEM

The gas management system includes all thesystems, assemblies, adapters, and covers that werediscussed in the vertical launcher and launcher supportequipment sections. The purpose of the gasmanagement system is to direct exhaust gases from amissile firing to the external atmosphere.

Another part of gas management is the blowoutsystem. It removes toxic fumes from the launcher byopening vent lines and activating the motor controller

The VLS power distribution consists of an ac powerdistribution system THAT applies 60-Hz, three-phase,115 VAC and 440 VAC to the motor control panel(MCP), power distribution panels, system transformerplatform, and module transformer platform. Dc poweris produced within the MCP for equipment use outsideof the MCP, such as prelaunch operations, hatch motors,and the Tomahawk missile prelaunch phase.

FAULT PROCESSING

Fault processing is the detection and reporting offaults within the VLS. This process can beaccomplished by system level fault detection andreporting operations or local level built-in testequipment (BITE) tests.

System level BITE tests are conducted only whenthe VLS is in standby mode and LAUNCH ENABLEis not applied to the launcher. The LCU initiates asystem level BITE test within approximately 30seconds from the time the VLS is placed in the standbymode and every 2 hours thereafter. Other system BITEtests include the LCU, single module, system module,and deluge BITE tests.

SUMMARY

In this chapter we described the major GMLSscurrently in the fleet, focusing on the majorcomponents, function, and operation. In subsequentchapters we will discuss their secondary and auxiliaryequipment, guided missiles, ordnance handingequipment, and other maintenance requirementsassociated with the different types of GMLSs.

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CHAPTER 8

GMLS: SECONDARY AND AUXILIARYFUNCTIONS

You should now have a pretty good understandingof the general physical arrangement and operationalcharacteristics of the major guided-missile launchingsystems (GMLSs). The subject matter of this chapterwill continue along those same lines. We will describethe secondary and auxiliary functions performed by thelaunching systems.

Secondary functions involve the equipmentsassociated with guided-missile jettison and strikedownoperations. Auxiliary functions cover a variety ofequipment areas. We will only address the major typesof fire suppression and environmental control systems.A brief section of general GMLS equipment safetyprecautions is presented at the end of the chapter. Payclose attention to the terminology used to describe eachsystem.

NOTE

Throughout this chapter, as well as in otherareas of this manual, certain equipment orsystem operating procedures will be presented.This is for general training purposes ONLY.The information presented should NOT bemisinterpreted as the absolute step-by-stepsequence of events in any case. ALWAYS referto and use the applicable reference instructions(GMLS publ i cat ions , maintenancerequirement cards, ship doctrines, and so on)when dealing with actual operationalprocedures.

JETTISONING

LEARNING OBJECTIVES: State the purposefor missile jettisoning, and list the majorc o m p o n e n t s a n d o p e r a t i o n o f t h edud-jettisoning assembly for the Mk 13 Mod 4and Mk 26 GMLS.

Jettisoning, also known as dud jettisoning, is the actof clearing an unwanted missile from a launcher guide

rail by ejecting it overboard. Whenever the firing keyis closed, there is never a 100 percent guarantee thatevery missile will properly ignite and launch under itsown power. A dud or misfire condition could exist thatmay lead to a potentially hazardous situation. Shouldthe missile endanger the safety of the ship and itspersonnel or interfere with tactical operations, the orderto jettison the round could be given. In some cases,however, after an appropriate waiting period, themissile may be safely returned to the magazine.

In any event, the final decision rests with thecommanding officer. The orders to prepare to jettisonand to actually jettison are relayed to GMLS personnelby the weapons control system (WCS). The launcherand jettison devices are readied for operation.Generally, a piston slowly extends out to contact themissile. The piston then ejects (or pushes) the missileover the side. The ejecting force is usually supplied bya high-pressure pneumatic source.

MK 13 MOD 4 GMLS JETTISON

The Mk 13 GMLS uses a jettison device (fig. 8-1)that is an integral part of the launcher guide arm.Components of the device are located within theforward part of the guide arm and the yoke. (Also seefig. 7-6.) The jettison device is essentially ahigh-pressure, hydropneumatic ram-type piston.Jettison operations may be performed in the remote,local, or exercise modes as selected by the EP2 paneloperator.

Physical Description

The main jettison components in the guide arm area piston, a beam, a track, two shafts, and a latch. Thepiston, working from hydraulic and nitrogen pressures,is the propelling force. In extending, the piston movesthe beam and the two shafts, pushing the missile fromthe retractable rail. With the retractable rail retracted, acrossbar receiver on the beam engages the crossbar ofthe two shafts. The beam, attached to the forward endof the piston and riding on rollers, is guided onto thebeam track. The shafts are two tubes that slide into

8-1

Figure 8-1.—Mk 13 Mod 4 GMLS jettison device.

bores within the retractable rail. The crossbar receiverengages the shafts and latches them to the beam. Twopawls below the shafts engage the missile forward shoe.The latch is a spring-loaded valve that extends itsplunger into a recess of the beam. The latch locks thebeam and jettison piston in their retracted positions.

Other jettison components are in the yoke sectionof the guide. They include a pressure intensifier pump,a nitrogen tank, and a booster and charging valve block.The pressure intensifier pump is a special pumping unit

for boosting hydraulic pressure when retracting thejettison piston. The increased hydraulic pressureoffsets the high nitrogen pressure used to extend thepiston. Attached to the pressure intensifier pump is ashutoff valve block and solenoid assembly. It opens orcloses the hydraulic fluid pressure line to the launcherguide components. The nitrogen tank is a steel flaskcharged with nitrogen. This pressurized gas extends thejettison piston at the velocity needed to eject a missileoverboard. The booster and the charging valve block

8-2

are part of a hydropneumatic unit. This unit alsocontains a piston and shutoff valves. The valves areused to maintain the nitrogen supply and hydraulicpressure at the proper level for operating the jettisonpiston.

Portable nitrogen supply cylinders (bottles) and anitrogen booster pump supply nitrogen to the tank.Supply cylinders normally are charged to only 1,800psi. This is insufficient pressure to operate the jettisondevice safely. A manually operated nitrogen boosterpump is, therefore, used to increase supply cylinderpressure. The pump increases nitrogen pressure toabout 2,400 psi when the nitrogen tank is filled orrecharged. The Mk 13 Mod 4 GMLS has a permanentlyinstalled unit in the inner magazine structure.

Functional Description

Functionally, the Mk 13 Mod 4 GMLS jettisondevice is a compact, simple, ready-to-use piece ofequipment that is totally independent of the ship’s HPair system.

JETTISON REMOTE.— When jettisoning isordered, the launcher captain activates the REMOTEDUD JETTISON switch on the EP2 panel. Controlsystem circuits automatically cause various guide armcomponents to set up for jettisoning. The fin openerarm assembly retracts. The forward-motion latchunlocks, and the arming device extends. As theretractable rail retracts, the crossbar between thejettison shafts enters the slot in the crossbar receiver.The guide arm is then mechanically prepared for thejettison operation.

The remote circuits also affect the launcher powerdrives. Train control is transferred from the fire controlsystem (FCS) computer to synchros in the launchingcontrol system. Elevation control is switched to aremote FCS gyrocompass. In response, the launcherautomatically moves to a jettison position that aims themissile seaward. Train bearing will be either directlyport or starboard. It is controlled by stationary positionorders from the digital director in the EP3 panel to thelauncher synchros in the train and elevation receiverregulators. Elevation angle will be 36°40' relative tothe horizon. As the ship rolls and pitches, gyrocompasssignals will maintain the 36°40' elevation angle. Thisangle ensures the jettisoned missile will clear the ship.

Extend Jettison.— When the launcher synchron-izes to a jettison position, the EP2 operator reports readyand awaits the final order. Pushing the DUD

JETTISON— JETTISON push button on the EP2initiates the extend and jettison cycles.

The extend dud-jettison solenoid is energized.Hydraulic fluid pressure (1,500-1,600 psi) from thelauncher guide power unit is applied to the front of thejettison latch. However, at this time the latch cannot beretracted. That is because nitrogen pressure (at 2,400psi) is constantly applied to the back of the jettisonpiston. This pressure forces the jettison beam forward(slightly) and places a bind on the latch. Thus normalhydraulic fluid pressure cannot overcome the highernitrogen pressure. The jettison latch remains extendedat this point in the extend sequence.

Hydraulic fluid is, therefore, ported around thelatch. The fluid is directed to a pressure intensifiervalve in the pressure intensifier pump. A pumpingaction takes place as this valve is made to shift rapidlyback and forth. The principle behind this actioninvolves the conversion of an applied pressure withgreat volume by a large area piston into a greaterpressure with less volume by a smaller area piston.Hydraulic fluid pressure is, thus, intensified to morethan 8,000 psi and is ported to the front of the jettisonpiston. Intensified fluid pressure overcomes thenitrogen pressure behind the piston. The jettison pistonand beam retract slightly to release the bind on the latch.Normal hydraulic fluid pressure may then retract thejettison latch.

As the latch retracts, the output of the intensifierpump is isolated and stopped. Nitrogen pressure behindthe jettison piston causes it to creep forward. Its speedis restricted by an orifice. Movement of the piston camsthe two jettison pawls into contact with (behind) theforward missile shoe. The forward-motion latch isdisplaced, and valves are shifted to remove creepcontrol. The piston accelerates and propels the missileseaward.

At the end of piston travel, a buffering action takesplace to slow and stop the piston and beam. Also, aninterlock switch is actuated to provide the launchercaptain with an EXTENDED lamp indication.

Retract Jettison.— After the extended lamp lights,the launcher captain pushes the DUD JETTISONRETRACT push button. A solenoid energizes toactivate the intensifier pump once again. A retract cyclerequires a large volume of hydraulic fluid. A specialisolation valve provides this large supply by closing andisolating hydraulic fluid from the other components ofthe guide arm. This action is necessary to prevent these

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components from reducing the volume of fluidavailable to the intensifier pump.

Intensified hydraulic fluid is then applied to thefront of the extended piston. As the jettison piston andbeam retract, nitrogen is forced back into the nitrogentank. In approximately 15 seconds, the piston reachesits fully retracted position. The latch engages the beamand activates an interlock switch. The control systemindicates RETRACTED.

The isolation valve shifts to make hydraulic fluidavailable to the other guide components. Theforward-motion latch locks, and the arming deviceretracts. The retractable rail reextends; the launcherslews to the load position, ready for future operations.

JETTISON LOCAL.— If the remote elevationorder signal is not available from the FCS gyrocompass,the launcher captain switches to LOCAL DUDJETTISON. Fixed position synchros in the EP2 thensupply the elevation signal. Ship roll compensationconsists of the launcher captain watching a clinometerbubble. The jettison operation is timed to coincide witha down roll. All other operations are the same.

JETTISON EXERCISE.— For maintenancetesting, the EP2 operator shifts the system to theSTEP-EXERCISE mode. Step push buttons must beactivated to extend the arming device and retract theretractable rail.

With the guide arm empty, the rail-loaded indicatorplunger and a hydraulic valve are extended. Theextended valve ports hydraulic fluid to a throttle valve.This valve restricts the flow of hydraulic fluid to thejettison piston and limits the speed of piston travel. Thereduced speed prevents equipment damage that wouldoccur under a no-load condition. Retraction of thejettison piston in the exercise cycle is the same as thatin an actual jettison operation.

MK 26 GMLS JETTISON

The Mk 26 GMLS has two jettison devices. Theyare deck-mounted at an angle to the launcher platformat the A and B dud-jettison positions. The two units arehydromechanically extended and retracted. They usean explosive gas generator to provide the ejecting force.Both the missile and an expendable piston assemblyjettison over the side. Jettison operations start with apreparatory order from the ship’s combat system (SCS).The main control console (MCC) operator in theintegrated control station (ICS) controls all subsequent

actions. The jettison devices of the various Mk 26GMLS mods are identical.

Physical Description

Above the deck, the jettison mounting bracketsupports, encloses, and protects the upper jettisoncomponents (fig. 8-2). Anti-icing fluid is circulatedaround the expendable piston cap to prevent icebuildup. A locking post and screw secure the gasgenerator cover to the bracket.

Below the deck, the 4-foot jettison housing cylindercontains the extender mechanism and the expendablepiston assembly. The upper end of the cylinder isthicker than the lower end. It must be thicker towithstand the explosive force developed by the gasgenerator. A motor housing is bolted to the back of thecylinder. It contains a small bidirectional hydraulicmotor that is controlled by a solenoid valve assembly.

The extender mechanism consists of an extenderscrew, extender nut, and extender sleeve. The extenderscrew is coupled to the output shaft of the hydraulicmotor. The extender nut is threaded onto the screw andbolted to the extender sleeve. The extender screw isrotated counterclockwise (to extend) or clockwise (toretract) by the motor. The extender nut and sleeve (withthe expendable piston assembly) travel out or in on thethreads of the screw.

The extender sleeve serves as the barrel for theexpendable piston assembly. A key and keywayprevent the sleeve from turning as the mechanism isextending or retracting. Gas ports in the aft section ofthe sleeve permit expanding gases from the fired gasgenerator to enter the sleeve. Gas pressure falls thesleeve up to the expendable piston. Only the pistonassembly is propelled overboard.

The expendable piston assembly weighs about 75pounds and fits inside the extender sleeve. A split lockring is bolted to the piston cap. It attaches the cap to thepiston sleeve and the piston assembly to the extendersleeve. A piston plug is inside the piston sleeve. Itserves as a guide for the positioner rod of the safetymechanism. The piston plug is also a header for theexpanding gas pressure.

The gas generator contains an electrically ignitedexplosive charge. When the generator is fired,expanding gases propel the piston assembly and amissile from the guide rail. The generator is a one-shotdevice that must be replaced after each firing.

8-4

Figure 8-2.—Mk 26 GMLS jettison device.

What if a gas generator accidentally fired while the atmosphere. They also prevent the piston and otherjettison device was retracted? A pressure safety relief metal pieces from ejecting outward.mechanism is built into the unit. Components of the When the extender sleeve is retracted, a blow-inmechanism will safely vent the expanding gases to the plug assembly in the wall of the sleeve aligns under the

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gas generator. The assembly is designed to collapseinto the forward chamber of the expendable piston. Gaspressures act only on the front side of the piston plug.That keeps the piston assembly inside the extendersleeve.

Two headless straight pins are staked at right anglesto the center of the positioner rod. They serve as acapture cage for pieces of the blow-in plug assembly.A rupture disc (or plug) is in the center of the piston cap.It breaks (from internal pressure) and allows the gasesto escape. Normally intact, the ruptured disc keepsmoisture out of the jettison device.

Functional Description

When ordered to prepare for jettison operations, theMCC operator presses the RSR/RAIL SELECTION-Aor -B and POINTING SELECTION-JETTISON pushbuttons. Automatically, the launcher slews to thecorrect position and readies itself for jettisoning. Foran antiair warfare (AAW) missile, the AAW armingdevice disarms. The two firing contractors and the AAWcontactor retract. For an antisubmarine warfare (ASW)missile, the ASW contactor retracts. The retractable railextends, and the ASW fire through latch unlocks.

EXTEND JETTISON DEVICE.— As thelauncher synchronizes to the jettison position and theguide arm components are correctly positioned, jettisondevice operations begin. Jettison control circuitsautomatically energize control valve solenoids. Thesolenoids start the hydraulic-mechanical actions toextend the extender sleeve and piston. When the sleeveleaves its retracted position, the train and elevationpower-drive brakes set. They hold the launcher alignedto the jettison position. The extender mechanism drivesthe expendable piston to within one-half inch of the tailcone of the missile and stops (fully extended).

JETTISON FIRING.— With all jettison circuitinterlocks satisfied, a ready-to-jettison indication isgiven on the MCC. When the jettison order is received,the operator depresses the JETTISON FIRE pushbutton. The firing circuits apply 20 VAC to the gasgenerator squibs. The generator ignites and jettisonsthe missile and expendable piston assembly.

RETRACT JETTISON DEVICE.— The MCCoperator starts retract operations by depressing theJETTISON DEVICE-RETRACT push button. Theextender mechanism returns the sleeve to its retractedposition. When the sleeve is fully retracted, controlsystem circuits automatically release the train andelevation power drive brakes. The ASW or AAW aft

shoe latch retracts. The AAW rail segments also retractto clear the guide arm for the next missile. The MCCoperator may return the system to normal operation.

Jettison operations are usually performed in theauto-load mode. For maintenance purposes, thestep-load mode is used. All component operations mustbe initiated manually. The firing circuit to the gasgenerator may be checked but the unit is not ignited.The gas generator is classed as a high-explosive hazard.Handling and stowing procedures are conducted withinstrict adherence to applicable safety regulations.

STRIKEDOWN

LEARNING OBJECTIVES: Identify the majorcomponents of the major GMLS systems, anddescribe the operational procedures forstrikedown of these systems.

Strikedown is a term associated with special GMLSequipments, operational procedures, and modes ofsystem control. They are used during a missile onloador missile offload process. An ondoad operationtransfers missiles from an outside source into themissile magazine. An offload operation is just theopposite.

Strikedown, for our purposes, is strictly an in-houseGMLS operation. How a missile is transferred betweena supplying activity and a receiving activity comesunder the topic of replenishment. As GMs, we aregenerally not responsible for the actual replenishmentactions. However, we must be aware of the basicprocedures. Our main task is to move the missilebetween the ship’s replenishment area and the GMLSstrikedown area safely.

Guided-missile replenishment can be performed invarious ways. Underway replenishment (UNREP) canbe in the form of a connected replenishment (CONREP)or a vertical replenishment (VERTREP). ForCONREP, missiles are moved between ships onappropriate riggings or highlines. For VERTREP, ahelicopter is used to deliver/remove missiles from theship. VERTREP may also be performed while the shipis at anchorage and, in some rare cases, pierside. Acrane is used during dockside or lighter replenishment.(A lighter is an ammunition barge.) The crane is thesimplest of replenishment methods. We will examinereplenishment methods in greater detail later. For now,

8-6

Figure 8-3.—Transfer dolly.

we will stay with the strikedown operations performed handling equipment, which must be installed on theby the GMLSs. launcher. This equipment provides a pneumatically

MK 13 MOD 4 GMLS STRIKEDOWNdriven chain mechanism to transfer the missile between

the guide arm and transfer dolly (fig. 8-3). Figure 8-4

The strikedown onload and offload operations of shows a Mk 13 Mod 4 strikedown operation withthe Mk 13 Mod 4 GMLS require special strikedown strikedown handling equipment installed.

Figure 8-4.—Mk 13 Mod 4 GMLS strikedown operations.

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Figure 8-5.—Typica1 strikedown hand-control unit.

Transfer dolly handling and most launcher andguide arm component movements are initiated andcontrolled by system personnel topside.

Strikedown Gear

The special Mk 13 Mod 4 GMLS strikedown gearconsists of a hand-control unit, a chain-drive fixture,

and air supply components. This gear is stowed nearthe launcher area and must be set up before onloadoperations begin. Strikedown air originates from theship’s HP air system. At the GMLS, HP air is reducedand regulated to the low-pressure requirements (about100 psi) of the equipment. This arrangement providesthe strikedown gear with sufficient operating volumeand pressure. In the following discussion, we will callthis reduced HP air “supply air.”

STRIKEDOWN HAND CONTROL.— Thestrikedown hand-control unit is a hand-held portableswitch box. It is sometimes referred to as the deckcontrol box. The operator of this unit can control trainand elevation launcher movements, the elevationpositioner (latch), and both power-drive brakes.

The box has six toggle switches (five arefunctional) and six indicating lamps. A detachablecable connects the box to the strikedown jack receptacleof the GMLS. The receptacle is mounted on the standor on a bulkhead outside the launcher control room.(Location varies between mark and mod of GMLS.)Figure 8-5 shows a typical hand-control unit. Notewhat functions are controlled and indicated by theswitches and lamps.

CHAIN-DRIVE FIXTURE.— The chain-drive(or strikedown) fixture is shown in figure 8-6. It isinstalled and locked to the front of the guide by two

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quick-release pins. Probes on the fixture actuate astrikedown-fixture-on-launcher interlock switch anddeflect the retractable rail trigger. That prevents anyinterference between the trigger and the strikedownchain.

The link-type chain is guided by the forward shoetracks of the retractable rail. A pair of spring-loadedlatches on the forward end of the chain engage theforward missile shoe. An air motor on the fixture drivesthe chain through a simple gear reduction and sprocketmechanism. As the chain is made to extend or retract,it pulls the missile up to the guide arm or lowers it tothe dolly.

Air motor operation is controlled by apressure-regulating valve and an air-throttle valve.Both components are mounted on the chain-drivefixture. The pressure regulator reduces supply air toabout 20-25 psi for a chain extend cycle. This lowpressure drives the air motor at a slow extend speed. Italso prevents the chain links from buckling when thelatches engage the missile shoe. The air-throttle valveserves two purposes. First, it functions as a directionalvalve controlling the direction of motor rotation.Second, it controls the speed of chain travel near itsextended and retracted limits. The valve throttles orreduces the air pressure available to the drive motor.

MANUAL AIR-CONTROL VALVE.— Themanual air-control valve is a three-position,hand-operated valve (see fig. 8-4). Air line hosesconnect it to a convenient ship supply air source nearthe launcher. Other hoses connect it to the pneumaticcomponents on the chain-drive fixture.

The air-control valve is used to start, stop, and selectthe direction of chain travel. When the valve is in theNEUTRAL position, supply air is isolated from thedrive fixture to stop the chain. When the valve is in theEXTEND or RETRACT position, supply air is portedto shift the air-throttle valve appropriately.

Strikedown Preparations

The EP2 panel must be activated to prepare for anonload operation. The launcher is moved to andsecured at a convenient location to install thestrikedown gear. Additionally, the launcher rail mustbe extended, the arming device retracted (disarmed),and the aft-motion latch retracted.

After the chain-drive fixture and the supply airhoses are attached, the EP2 operator activates thesystem and (carefully) returns the launcher to a LOAD

position. The GMLS is secured once more. Topside,the deck control box is connected to its receptacle. TheEP2 operator activates the GMLS, selects step controland strikedown, and retracts the train positioner. Allsubsequent launcher movements are controlled by thedeck control box operator.

Strikedown Onload Operations

As the loaded transfer dolly arrives on board, thedeck control operator assumes control. The train brakeis released, and the strikedown port (or starboard) traincontrol is selected. Fixed-position synchros drive thelauncher to the predetermined strikedown position.When the launcher arrives at the strikedown position,the operator resets the train brake.

When ready to engage the dolly, the operatorretracts and releases the elevation positioner and brake.The guide slowly depresses from the 90 degree loadposition when the elevation control switch is actuated.The guide mates with and picks up the dolly. The guidecontinues to depress until the elevation strikedownangle is reached. The operator resets the elevationbrake and extends the positioner. Chain-driveoperations can then begin.

EXTEND CHAIN.— The manual air-controlvalve handle is turned to EXTEND. This ports supplyair to shift the air-throttle valve. From the air-throttlevalve and the pressure regulator, 20-25 psi air causesthe air motor to extend the chain slowly. The chaintravels the length of the retractable rail of the launcher.It also extends along a portion of the guide rail of thedolly to reach the forward missile shoe.

Near the end of the chain travel, a cam on one ofthe chain links contacts and shifts linkage connected tothe air-throttle valve. The main air port of the valvecloses. However, through a restricting orifice, supplyair continues to reach the motor. As a result, chain-drivespeed is reduced even further. When the latches of thechain engage the forward missile shoe, chain movementstops. The air-control valve handle is returned to itsNEUTRAL position.

System personnel visually verify that thespring-loaded chain latches have fully engaged behindthe forward shoe of the missile. If the latches are onlypartially engaged, the missile may break loose as thestrikedown chain is retracted. The missile will slidedown the rail, shear off the shoe plate on the dolly, anddrop on deck. Do not even hang around to explain thatone to the chief!

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RETRACT CHAIN.— To move the missile ontothe guide, system personnel must shift the manualair-control valve handle to RETRACT. Full supply airpressure drives the motor at this time, and the missile ispulled onto the guide arm. As the aft shoe of the missilenears the forward-motion latch in the guide, anotherchain cam shifts the air-throttle valve. An orificerestricts air flow to slow motor speed again. Movementstops when the aft shoe of the missile contacts theforward-motion latch. The aft-motion latchautomatically extends behind the aft shoe, and themanual air-control valve handle is turned toNEUTRAL.

After verifying that the aft-motion latch has fullyextended, system personnel release the two chainlatches. That is done by depressing a latch lever. Seefigure 8-6. The manual air-control valve handle isturned to RETRACT again. The chain is returned to itsstowed position in the fixture. The manual air-controlvalve handle is placed in NEUTRAL to concludeair-drive operations.

Return Launcher to Load

The EP2 operator is instructed to select the unloadmode. An empty cell in the ready service ring (RSR) isindexed to the hoist station. The deck control operatorreleases and retracts the elevation brake and positioner.The guide is elevated slowly to the 90 degreeload/unload position, disconnecting from the dolly as ittravels. When the dolly is rolled clear, the deck controloperator releases the train brake. The launcher slews toalign with the blast door.

The EP2 operator takes control and proceeds withnormal unload operations. The identification probe ofthe fin opener arm assembly must be extended toidentify the missile type on the guide arm. Ifstrikedown operations are completed, the deck controlbox is disconnected and replaced by a dummy plug.This device restores full GMLS control to the EP2panel. The launcher is moved to a convenient locationfor removal of the strikedown gear.

Strikedown Offload Operations

Strikedown offload operations are basically thereverse of onload operations. The one differenceconcerns the aft-motion latch of the guide arm. Controlsystem circuits normally prevent the aft-motion latchfrom retracting with a missile on the rail unless the hoistpawl is extended and engaged.

During a strikedown offload operation, theaft-motion latch is retracted with a special tool inserted

into a slot on the fixed rail. The tool is turned manuallyto simulate the presence of the hoist pawl. The EP2operator may then retract the aft-motion latch. Themissile can then be lowered onto the transfer dolly.

MK 26 GMLS STRIKEDOWN/INTERTRANSFER

The Mk 26 GMLS strikedown/intertransfer systemis used for strikedown onloads and offloads. It is alsoused for intertransfer movement of missiles betweenRSRs. The Mk 26 GMLS is adaptable to all standardreplenishment methods.

The strikedown/intertransfer system can be dividedinto two primary equipment areas. The strikedown/intertransfer mechanism is the main component of thesystem. It functions above and below deck.Components on the strikedown end of the RSRs workwith this mechanism in transferring missiles. The otherequipment area involves the portable, on-deck handlingequipments. Different equipments are used for AAWand ASW rounds.

Strikedown/Intertransfer Mechanism

The strikedown/intertransfer mechanism moves themissiles between the deck and magazine and from RSRto RSR. The mechanism consists of six majorassemblies, as shown in figure 8-7.

Figure 8-7.—Mk 26 GMLS strikedown/intertransfermechanism.

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The strikedown support structure mounts theequipment used to raise and lower the carrier assembly.The carrier assembly rides up and down on guide rails,and it is moved by a threaded screw shaft. The shaft isrotated by a small hydraulic motor.

The index drum is a major subassembly of thecarrier. It is mounted on top of the carrier and supportsthe strikedown beam assembly. Hydraulic componentsof the index drum serve to position the strikedownbeam. When the carrier assembly is in the magazine,the index drum can be rotated 60° on either side of thecenterline. This rotation aligns the strikedown be am tothe A-RSR or the B-RSR. When the carrier assembly

is raised to deck level, the index drum can be rotated80° on either side of the centerline. This rotation alignsthe strikedown beam to the A-receiver or B-receiverpositions on deck. At all five positions, the index drumis latched in place.

Components within the index drum also elevate anddepress the strikedown beam. The strikedown beam ishinged to the index drum. The beam is depressed tohorizontal to pickup a missile from or deliver it to theon-deck handling equipment. It is elevated to verticaland latched to ride up and down the support structure.

A strongback assembly (fig. 8-8) hangs from thestrikedown beam. It is used to secure a missile to or

Figure 8-8.—Strikedown beam and strongback assemblies.

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release it from the beam. The strongback is capable ofextending and retracting at both the vertical andhorizontal positions. Four separate openings in thestrongback accept the forward and aft shoes of the AAWand ASW missiles. Shoe latches within these openingssecure the missile to the strongback.

When the strikedown beam is horizontal, theextended strongback is capable of some small verticaland lateral movements. The mobility of the extendedstrongback enables it to align itself to the missile shoes.When the strikedown beam is vertical, the extendedstrongback is only allowed a small lateral movement.When the strongback is fully retracted to the beam, it islatched securely in place.

The strikedown beam also serves to identify themissiles to the control system. The identification takesplace through various proximity switches and an AAWidentification probe. Missile group and typeinformation is sent to the ICS even before the missile islowered to the magazine.

The strikedown marine hatch (refer to fig. 8-7) isthe last major component of the strikedown/intertransfer mechanism. The hatch is hydraulicallyopened and closed by the MCC operator. A strikedowncontrol panel is mounted to the underside of the hatch.When the hatch is opened for strikedown operations,the panel is exposed. This panel permits local controlof the strikedown operations performed on deck. Notethe functions of the switches and lamps of the panel, asshown in figure 8-9.

The strikedown/intertransfer mechanism receivesits hydraulic fluid supply from either the A- orB-RSR/hoist power-drive accumulator system. Amanual transfer valve is positioned to select A-side orB-side supplies. The fluid from one system is notallowed to intermix with the other.

On-Deck Strikedown Equipment

The Mk 26 GMLS uses a variety of special on-deckhandling equipments. They correctly align and position

AAW or ASW missiles to the strongback of thestrikedown beam.

Mounted flush in the strikedown area deck are twopiston assemblies. They are located about 80° on eitherside of the strikedown beam centerline. One is forA-side operations, and one is for B-side operations.These piston assemblies are known as the receiver orpositioner pistons. They also receive hydraulic fluidsupply from the selected RSR/hoist accumulatorsystem. The receiver pistons serve to raise and lowerthe missile between the deck and extended strongback.This operation is controlled by the on-deck strikedowncontrol panel operator.

AAW HANDLING EQUIPMENT.— AAW-typemissiles are shipped to a Mk 26 GMLS in the sametransfer dolly used by other Tartar systems. But hereany similarity ends. To orient an AAW missile to thestrikedown beam properly, the Mk 26 GMLS uses twospecial devices: the AAW dolly deck track and theAAW missile receiver beam. These portableequipments are used to transfer a missile between atransfer dolly and the strikedown mechanism.

AAW Dolly Deck Track.— The AAW dolly decktrack is shown in figure 8-10. It serves to guide andsecure a transfer dolly over the in-deck receiver piston.When the dolly arrives on deck, it is pushed up thewheel ramps and guided along the long deck trackchannel. The dolly is locked in place by forward andaft wheel stops (pins).

Two alignment lever handles are used to shift thetrack and dolly laterally. This action aids in aligning theshoes of the missile to the AAW receiver beam.

AAW Receiver Beam.— The AAW missilereceiver beam is shown in figure 8-11. It is used totransfer the missile between the transfer dolly and thestrikedown beam. The beam is connected and securedto the receiver piston. It is allowed some “floating”movement to aid in missile alignment.

Figure 8-9.—On-deck strikedown control panel; front panel.

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Figure 8-10.—AAW dolly deck track.

Figure 8-11.—AAW missile receiver beam.

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Raising the receiver piston transfers an AAWmissile from a dolly to the receiver beam. (Maximumtravel is about 5 inches.) The bottom shoes of themissile enter the forward- and aft-shoe receptacles inthe beam. The manual lever on the beam is turned tomove a “finger” in the aft-shoe receptacle. This finger,in contact with the aft missile shoe, shifts the missile.As the missile shifts, its upper shoes are disengagedfrom the transfer dolly rail. At the same time, the lowershoes are engaged to the receiver beam. The receiverpiston is then lowered, and the transfer dolly is clearedfrom the area. An offload procedure is just the opposite.

ASW HANDLING EQUIPMENT.— ASW-typemissiles are shipped to a Mk 26 GMLS in Mk 183shipping containers (instead of transfer dollies). Aspecial piece of equipment is used to transfer an ASWmissile between its shipping container and thestrikedown beam. This device is called the ASWcontainer receiver plate (fig. 8-12). The ASW receiverplate is secured to the receiver piston. It also has somedegree of floating movement to aid in missile shoealignment.

When an ASROC missile arrives on board, specialhand trucks are used to position the shipping containerover the receiver plate. After the container is secured

to the receiver plate, the top lid of the container isremoved. The strikedown beam is then depressed tohorizontal. The combined acts of extending thestrongback and raising the receiver piston cause theupper shoes of the missile to engage the ASW shoelatches of the strongback. When the latches areengaged, the strongback is retracted. This action liftsthe missile out of its container, and the receiver pistonis then lowered. An offload operation is just theopposite.

Strikedown Onload Operations

An Mk 26 GMLS strikedown onload may bestudied in three phases: preparations, on-deckoperations, and below-deck operations. Many of theequipment actions do overlap. An entire onloadsequence can be performed rather rapidly either in stepor auto control. In our discussion, we will onload oneAAW missile using the A-side of the GMLS.

SYSTEM PREPARATIONS.— The MCCoperator performs the initial steps to ready the GMLS.After activating the control system, a missile-typedesignation is assigned to an empty hanger rail. TheA-RSR/hoist motor is started, and the manual transfervalve is shifted to provide hydraulic fluid to the

Figure 8-12.—ASW container receiver plate.

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strikedown mechanism. The MCC operator selectseither auto or step strikedown loading control and opensthe marine hatch.

The deck control operator (DCO) establishescommunications with the MCC operator. Thestrikedown control panel is turned ON. Deck personnelremove the protective cover from a receiver pistonassembly (which one depends on the replenishing sideof the ship).

The DCO raises the receiver to set up the AAWdolly deck track and receiver beam. After the handlingequipment is installed, the receiver and beam arelowered. The system is then ready to receive the firstmissile.

ON-DECK OPERATIONS.— The transfer dollyarrives on deck and is pushed onto the AAW dolly decktrack. The missile is aligned and secured over thereceiver beam. The DCO operator raises the carrierfrom the magazine. After the strikedown beam reachesthe strikedown level (raised position), the index drumis rotated 80° from center to the selected receiverposition. The strikedown beam is then depressed to itshorizontal position over the missile. Identification thentakes place. The DCO visually identifies the missile asan AAW or ASW type. A missile identification switchon the panel is placed in the AAW/ASW MISSILEposition. The strongback will extend its full distance inthis case. The other two switch positions (fig. 8-9), theSSM MISSILE and OFF positions, limit strongbackextend-distance to accommodate the larger diameterSSM round. Both positions are inactive at that time.

Ensuring the strongback shoe latches are retracted,the DCO extends the strongback to the missile. Thereceiver piston is raised to place the upper missile shoesin the shoe recesses of the strongback. Jogging theRAISE switch controls the amount of receiver travel.(About 3 1/2 inches of lift is required to seat the missileshoes.) On-deck personnel make final alignmentadjustments using the various lever handles. Themissile is shifted from the dolly to the strongback. TheDCO closes the strongback shoe latches and retracts theloaded strongback to the strikedown beam.

The second phase of missile identification has justtaken place. Proximity switches were activated whenthe forward and aft missile shoe latches engaged. Foran AAW missile, a switch was activated to identify theAAW missile group. The AAW identification probe ofthe strikedown beam (similar to the identification probeat the RSR hoist station) was extended into the round toidentify the AAW missile type. If an ASW missile was

loaded, one switch would identify the round as an ASWtype. Another switch would activate if the missile wasa depth charge configuration. The purpose ofstrikedown beam identification (topside) is to generatecontrol system orders. The RSR may thenautomatically index an empty hanger rail with the samemissile type assignment to the strikedown position.

Back on deck, the DCO raises the loadedstrikedown beam to vertical. The index drum is rotatedto centerline and latched. The carrier is lowered intothe magazine and stops at the intertransfer level. Whilethe carrier is lowering, snubber wedges on the selectedhanger rail unlatch. The snubbers open to receive themissile from the strikedown beam.

BELOW-DECK OPERATIONS.— When thecarrier reaches the intertransfer level, the MCC operatorassumes control. The AAW identification probe isretracted, and the index drum is rotated 60$ to theA-RSR hanger rail. The hanger rail load segments opento receive the missile shoes. The strongback andmissile then extend outward.

When the missile engages the hanger rail, the loadsegments close around the missile shoes. The carrierlowers 6 inches to the carrier stowage level. Loweringthe carrier and missile engages the missile shoerestraining latches. The strongback shoe latches open,and the strongback retracts to the strikedown beam.The index drum rotates the beam back to centerline.The snubbers close and the snubber wedges engage.

One missile onload has just been completed. Ifadditional rounds are to be onloaded, the process startsover again when the DCO raises the carrier. If theonload is finished, personnel topside disconnect andstow the handling equipment. The MCC operatorcloses the marine hatch and returns the GMLS tonormal.

Strikedown Offload and Intertransfer

A strikedown offload is a reverse sequence ofonload operations. Intertransfer operations change thedistribution pattern of the magazine load. Intertransferuses a combination of onload and offload proceduresperformed solely below deck. The marine hatchremains closed, and the MCC operator controls allequipment functions. The operationaccomplished in step or automatic control.

may be

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Figure 8-13.—5-cell strikedown module Mk 3 Mod 0.

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MK 41 VERTICAL LAUNCHING

SYSTEM

The Mk 41 vertical launching system (VLS)

strikedown equipment is housed in the 5-cell

strikedown module Mk 3 Mod 0 (fig. 8-13). This

strikedown equipment occupies cells 6, 7, and 8—the

same cell space used in 8-cell modules Mk 1 Mod 0 andMk 2 Mod 0 for missiles. The VLS strikedown

equipment gives the VLS crew self-contained

equipment that can be used to onload and offload

missile canisters Mk 13 and Mk 15 and training canister

Mk 19 into and out of the module cells. The strikedown

equipment can also be used to remove any empty

canisters and movother strikedown equipment asnecessary.

Strikedown Equipment

The five-cell strikedown module consists of threesubassemblies: the elevator hatch, elevator, and craneassemblies. When not in use, the hatch is closed andthe elevator and crane are stored below deck untilonload or offload operations.

ELEVATOR HATCH ASSEMBLY.— Theelevator hatch assembly (fig. 8-14) is hinged to the deckplatform. This assembly provides weather and ballisticprotection for the strikedown crane, elevator, andlauncher interior. The hatch is driven open or closed bythe elevator hatch cylinder. When closed, the hatch issecured by six hatch dogs. The hatch dogs applypressure to a watertight seal. The dogs are linkedtogether and actuated by two chains, which areconnected to, and operated by, the hatch dog/undogcylinder. Two directional control valves, located below

Figure 8-14.—Elevator hatch in OPEN position.

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Figure 8-15.—Elevator assembly Mk 2 Mod 0.

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the hatch on the walkway side (fig. 8-15), direct the flowof hydraulic fluid to the hatch dog/undog cylinder andthe open/close hatch cylinder. The valves can beactuated manually in an emergency. The hatchoperation is controlled by toggle switches located on thecontrol panel A19.

ELEVATOR ASSEMBLY.— The elevatorassembly Mk 2 Mod 0 shown in figure 8-15 consists ofthe support structure, elevator platform assembly,control panel A19, and power distribution panel A20.These parts work together to raise and lower theelevator assembly.

The support structure forms a shaft on which theelevator platform assembly travels. The shaft has lockbar sockets and guide rails that interface the platformwith sensor switches on the support structure; theseswitches indicates the position of the platform. Analarm bell, mounted on the upper part of the supportstructure, sounds when the hatch or platform is inmotion. An eight-section metal safety screen preventspersonnel from falling into the elevator shaft and themoving platform. If the powered hydraulic pump fails,a manual hydraulic pump (fastened to the lower support

structure) can be used only to dog/undog and open/closethe elevator hatch.

The elevator platform serves as a base for thestrikedown crane. The platform, which is rectangularin shape, is mounted on a three-stage telescopinghydraulic cylinder. The cylinder raises and lowers theplatform. The platform can be moved only when thecrane is stowed. An emergency system, consisting of aspring set and two knurled rollers, stops the downwardmotion of the elevator if hydraulic pressure falls below200 psi.

The control panel A19 (fig. 8-16) is a watertightcabinet mounted on the elevator support structure justbelow the upper walkway, as shown in figure 8-15. TheA19 control panel lever-lock toggle switches controlthe motor hydraulic power start-up, elevator hatch, lockbars, and elevator. These switches, exceptMOTOR-START and MOTOR-STOP, must beactuated and held until the desired ffunction is complete.Except for MOTOR-START and MOTOR-STOP, theoperation can be stopped anytime by the release of thetoggle switch.

Figure 8-16.—Control panel A19.

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Figure 8-17.—Power distribution panel A20.

The power distribution panel (PDP) A20 (fig. 8-17) The crane operator’s console contains theroutes the 440-VAC, 60-Hz, three-phase power througha three-phase power contactor to the 30-hp electricmotor of the hydraulic power supply. The cabinet iswatertight and mounted near the top of the elevatorsupport structure, as shown in figure 8-15. Theoverload relay reset switch and elapsed time meter (thatrecords component in-service time for the elevator) arelocated on the access cover.

CRANE ASSEMBLY.— The Mk 1 Mod 0strikedown crane (fig. 8-18) is a hydraulically powered,knuckled-type crane. The crane mast is bolted to theelevator platform through the drive king post. Thecrane mast contains the crane operator’s console,collapsible operator seat, footrests, and access steps.The elevator assembly supplies the electric power forthe crane indicator night lights and the hydraulic powerthat drives the crane.

The crane has an inner and outer boom connectedin series to the upper end of the mast by pivot points(referred to as knuckles). TWO parallel hydrauliccylinders pivot the inner boom at the mast, and twoothers pivot the outer boom at the inner boom. Aduplex-type hydraulic cylinder attached to the outerboom extends and retracts the two boom extensions.

The crane contains a static hook (on the bottom tip)that is secured with a stowage pin when not in use. Awhip hook, on a pulley block, raises and lowers as thewinch pays out or reels in the winch cable. Thewinch/drive assembly is hydraulically driven.

directional control levers (fig. 8-19) used to train thecrane mast, raise and lower the inner boom, raise andlower the outer boom, extend and retract the boomextensions, and raise and lower the whip hook. Fourvisual indicators are located near the controls. The trainbearing, inner boom elevation angle, and boomextension indicators enable the operator to position theboom over any selected cell. The temperature gaugeallows the operator to monitor hydraulic fluidtemperatures during crane or elevator operations.

Figure 8-19.—Crane operating controls.

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Figure 8-18.—VLS strikedown crane Mk 1 Mod 0 in operating configuration.

Strikedown Operations Before any strikedown operation, the deck

All strikedown operations contribute to the safesupervisor reviews the planned operations with the

loading or offloading of missile canisters from the VLS.crew and delegates specific assignments. During

These operations require a well-trained, competent strikedown operations, it is paramount that the crew

crew that strictly adheres to basic strikedown maintain constant communication. All members of theoperations. strikedown crew, with the exception of the deck crew,

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must be personnel qualification system (PQS) certifiedand have a naval enlisted classification (code) (NEC) of0981.

Strikedown Procedures

Because of the complexity of the procedures forstrikedown operations of the VLS, they cannot becovered here. These procedures are described in detailin NAVSEA Technical Manual SW394-AF-MMO-0501VLS, revision 2, Vertical Launching SystemMk 41 Mods 0/1/2 Strikedown Equipment.

FIRE SUPPRESSION SYSTEMS

LEARNING OBJECTIVES: Explain thepurpose and basic functions of fire suppressionsystems used in GMLSs.

GMLS fire suppression systems are designated asauxiliary equipments within the launching system.They protect the ship and its personnel from hazardousconditions resulting from fires or the high temperaturesof fires. The text discusses three basic classes of firesuppression systems used in the GMLS community:

1. Carbon dioxide (CO2) systems

2. Water injection systems

3. Dry-type sprinkler systems

CO2 systems are used primarily to combat electricalfires. Fixed or installed CO2 systems normally protectthe unmanned GMLS areas, such as magazines andsome launchers. Portable systems (you and a 15-poundCO2 extinguisher) are normally used to protect themanned GMLS areas, such as launcher control rooms.

Water injection systems are designed to direct acontinuous stream of water into the exhaust nozzle of arocket motor. Should the rocket motor accidentallyignite in the magazine, the stream of water will controlthe burning reaction of the propellant. The water willalso cool the missile and the surrounding area. It MAYEVEN extinguish the burning rocket motor, but notnecessarily. Water injection systems are also known asbooster suppression or quenching systems.

Sprinkler systems are designed to spray water ontothe missiles in magazine stowage and handling areas ofa GMLS. Sprinkler systems aid in extinguishing fires.They also cool the missiles below the temperatures thatcould start rocket motor ignition or warhead detonation.

In covering the various GMLS fire suppressionsystems, we will deviate slightly from the sequence wehave followed so far. Atypical or representative systemwill be presented. Any important differences or uniquefeatures of individual GMLSs will be noted. Mainly,component location and numbers are the greatestdifference.

A TYPICAL CARBON DIOXIDE SYSTEM

A typical GMLS carbon dioxide (CO2) system ispermanently installed (fixed) in the missile magazinearea. The system is designed to detect an excessivetemperature buildup and activate automatically. Oncethe system is activated, the entire space is flooded witha large volume of CO2 extinguishing agent. The systemmay also be activated manually from either a local orremote control station.

Physical and Functional Description

The primary pneumatic-mechanical components ofa simple CO2 system include the thermopneumaticcontrol elements and supply cylinders. The supplycylinders are equipped with control and dischargeheads. The system also has other associated valves andalarm switches. Many of these components are locatedjust outside the magazine structure. The control devicesand CO2 discharge nozzles are inside. They arestrategically placed near fire-prone equipments(electric motors, connection boxes, slip rings, and soon).

HEAT-SENSING DEVICES.— Heat-sensingdevices (HSDs) were formerly designatedthermosylphon units. HSDs are the detecting units ofthe system (fig. 8-20). They are designed to develop apneumatic pressure signal when space temperatureincreases to a preset activating point. The rate of risein space temperature maybe rapid or slow.

The HSD consists of a spring-loaded, rubberbellows housed in a mesh-style cage. The bellows isheld in an extended or expanded position against acompressed spring by a fusible element. HSDs aremounted above the area they monitor. They connect tothe control head of the CO2 supply cylinder by apneumatic transmission-line network.

In the event of an actual fire or explosion, a rapidrise in space temperature is experienced. The heatgenerated by the mishap is conducted to the air insidethe HSD bellows. The air inside the bellows quicklyexpands and increases in pressure. This pressure“signal” is transmitted to the control head of the

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Figure 8-20.—Components of a CO2 system, inside magazine structure.

cylinder. The pressure-sensitive head is tripped, and the not quick enough to trip and activate the system. Forsystem is activated. this reason a fusible element is used.

In the event of a smoldering type of fire or a heat HSDs are designed with a fusible link as thebuildup resulting from a fire in an adjacent melting element. The link is made of a low-compartment, a slow rise in space temperature is melting-point metal compound similar to solder. Whenexperienced. In this case, the air inside the HSD a certain temperature is reached, the compound starts tobellows expands (as before). However, its reaction is melt.

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In a GMLS CO2 system, the fusible link is designedto melt at about 160°F (±3°). When the fusible elementmelts, the compressed spring around the bellows isreleased and allowed to expand. This action causes thebellows to collapse. The sudden compression of theHSD bellows creates a pneumatic pressure impulsesignal. The magnitude of this air signal is measured inounces per square inch (osi). The pressure impulse tripsthe control head and activates the system.

Transmission Lines.— Transmission lines connectthe HSDs to the control head. The lines are 1/8-inchOD (outside diameter) by 0.088-inch ID (insidediameter) rockbestos-covered, seamless copper tubing.Quite a few rules pertain to the correct material andinstallation requirements associated with these lines.

Refer to Technical Manual for Magazine SprinklerSystems for guidance when repairing or replacingtransmission lines. (Although this manual is the masterreference for sprinkler systems, much of its informationalso pertains to CO2 system requirements.)

Circle Seal Check Valves.— The circle seal checkvalve (shown in fig. 8-20) is a brass, spring-loadedcheck valve. It closes against a rapid change of airpressure in one direction and opens when air pressureis applied in the other direction. One circle seal checkvalve is installed in each transmission line leading froman HSD. The valve is installed with its directionalarrow (stamped into the body) pointing toward thecontrol head.

Figure 8-21.—Components of a CO2 system; outside magazine structure.

8-24

The check valve prevents the rapid increase of airpressure created by one HSD (such as when its bellowscollapse) from pressurizing the other HSDs. The full air-pressure signal is then ported directly to the controlhead. This action ensures positive system activation.

A vent is installed in the body of the check valve.The vent permits a slow backflow of air to bypass themain check valve element. This venting equalizes airpressure within the system in response to normalchanges in ambient (surrounding) temperature.

SUPPLY CYLINDERS.— GMLS fixed CO2systems usually have at least two supply cylinders. Eachcylinder has a 50-pound CO2 capacity and weighs 165pounds when fully charged. It contains liquid carbondioxide under a pressure of 850 psi at 70°F. Eachcylinder of the system has a discharge head and acylinder valve. At least one of the cylinders will also havea pneumatic control head. The other cylinder(s) will be intandem with the main control cylinder(s). See figure 8-21.

Pneumatic Control Head.— A pneumatic controlhead (shown in fig. 8-21) reacts to HSD pressure signalsor to manual operating levers. The control head istripped to open the discharge head and cylinder valve,which release the liquid CO2 from the cylinder. Thecontrol head consists of an air chamber with adiaphragm. The control head also has two plungers,

safety locking pins, and a manual (local) operatinglever.

The pressure chamber in the control head has anorifice that vents air pressure at a predetermined rate.When pressure in this chamber increases faster than itcan be vented, the diaphragm expands. This movementtrips a lever that releases a trigger mechanism. Thetrigger mechanism shifts the two plungers. Shifting theplungers opens the pilot seat in the cylinder valve.

Cylinder Valve and Discharge Head.— Thecylinder valve and discharge head are shown in figure 8-22. Together, they block the escape of the liquid CO2from the cylinder until the control head is activated.

When the plungers from the “tripped” control headopen the pilot seat, CO2 flows into the chamber abovethe discharge head piston. The piston is shifted (down)against its spring. The ball check valves trap gaspressure in the upper chamber. This keeps the pistonopen (down) and ensures rapid and complete cylinderdischarge. Shifting the piston opens the cylinder valve,allowing CO2 to flow to the exhaust manifold and supplylines. (See fig. 8-21.)

DISCHARGE NOZZLES.— CO2 dischargenozzles are installed so that their discharge blanketscertain key electrical components. The nozzles are alsolocated so that the entire area they serve is flooded withCO2. The nozzle is a bell-shaped device (fig. 8-20)

Figure 8-22.—Cylinder valve and discharge head schematic.

8-25

with an orifice at its discharge point. The orificerestricts the discharge of the CO2 and creates an evenflow from all system nozzles. The gaseous “snow” ofCO2 quickly extinguishes the fire.

MISCELLANEOUS COMPONENTS.— Amanually operated shutoff valve is installed in the CO2

discharge line between the supply cylinders anddischarge nozzles. (See fig. 8-21.) The valve isphysically located outside the magazine near itsentrance. To avoid a CO2 suffocation hazard, unlockthe valve and close it before you enter the magazine. Ifthe system should activate, the supply cylinders willrelease CO2. However, the closed valve will stop theCO2 so that you can keep breathing.

CO2 pressure entering the supply line activates anoperation alarm switch (fig. 8-21). Audible alarms andlights are turned on, signaling that the CO2 system hasactivated. These warning devices are usually located

right outside the magazine area and at the ship’s damagecontrol (DC) central room. The switch must bemanually reset if activated. The alarm circuits maybemaintenance-tested.

A remote control pull box allows personnel torelease the pneumatic control head(s) manually. Thepull box is located outside the magazine. It has atransparent, breakable shield and a pull handle. A wirecable is connected to the control head triggermechanism. Breaking the glass and pulling the handleactivates the system. The CO2 system can also beactivated locally. Manually removing a safety pin andtripping a lever on the pneumatic control head releasesthe CO2.

Actual GMLS CO2 Systems

Every GMLS has some type of CO2 fire-fightingcapability. Some GMLSs have a combination of fixed

Figure 8-23.—Arrangement of inner and outer CO2 systems.

8-26

and portable CO2 protection. Other GMLSs only haveportable extinguishers available. System design andconfiguration sometimes restrict the installation offixed CO2 system hardware.

The Mk 26 GMLSs do not have a fixed CO2 system.Portable extinguishers, readily accessible throughoutkey areas of the GMLSs, provide the protection.

The Mk 13 GMLSs do have fixed CO2 systems inaddition to portable extinguishers. The Mk 13 GMLSshave separate inner and outer magazine CO2 systems(fig. 8-23). The inner system covers the center columnor inner structure. The outer system floods the RSRarea.

A TYPICAL WATER INJECTION SYSTEM

The general purpose of a water injection system hasalready been stated. In a static or ready condition,injection system piping places a charged supply offreshwater under each missile. Should a missileaccidentally ignite, blast pressure will activate thesystem. Instantly, a pressurized stream of freshwaterinjects into the core of the rocket motor. When thelimited supply of freshwater is depleted, salt water

(from the fire main supply) is used to continue theoperation.

Once the injection system is activated, it must besecured manually. Additionally, provisions must bemade to remove and discharge the large quantity ofwater remaining in the magazine. That is normallyaccomplished by a magazine drainage system and anoverboard eductor system.

Why use freshwater? Freshwater is used because itdoes not promote corrosion as quickly as salt water,Salt water can ruin the piping and valves of the system.Normally, an additive to the freshwater slows anycorrosive action and helps seal minor leakage.

System Description

Many of the water injection system components arelocated outside the magazine area. They function tomaintain the system in a ready state and supply thefreshwater and salt water. The components inside themagazine distribute and activate the injection system.Refer to figure 8-24 for a schematic illustration of atypical water injection system.

Figure 8-24.—A typical water injection system; these components are located outside the magazine.

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EXTERNAL MAGAZINE COMPONENTS.—The compression tank of the injection system is usuallylocated in a machinery room below or near themagazine. The tank is an enclosed structure, normallyfilled with freshwater to one half of its 125-gallon(approximate) capacity. The tank is then charged to 200psi from a ship’s HP air supply. The 200-psi freshwaterpressure is transmitted throughout the injection pipingnetwork and remains in a static state under each missile.

A flow switch is installed in the outlet line of thetank. When the system does activate, freshwater flowsthrough the switch. The switch actuates and energizesa variety of equipments. Examples include ship firepumps, alarm circuits, and eductor systems.

A check valve is also installed in the outlet line ofthe tank. When open, it permits freshwater to flow tothe water injector piping. When closed, it prevents saltwater from flowing back into the compression tank.

Another hydraulically operated check valve,designated the main check valve, is shown in figure8-24. It isolates the fire main supply from the injectionsystem until the system activates. In a static state, the200-psi freshwater supply keeps the valve closed

against the ship’s fire main supply. (I&us assume firemain supply pressure is rated at 70 psi. Actual fire mainpressure varies among ships.) However, when thesystem does activate, the 200-psi freshwater pressurewill decrease. As fire main pressure equals or exceedsfreshwater pressure, the main check valve opens. Saltwater flows to the piping network of the system. Amanually operated shutoff valve above the main checkvalve must be closed to secure the system.

INTERNAL MAGAZINE COMPONENTS.—The injection system piping network distributesinjection water around the magazine base area. Atevery position a missile can come to rest, a standpipe isthreaded into the supply lines. Attached to the top ofthe standpipe is a water injection (detector) nozzle. Theunit is just a few inches below the tail cone of the rocketmotor.

The main component parts of a detector nozzle (fig.8-25) include a closure piston and an actuation piston.Three lock balls and a gold-wire spring pin connect thetwo pistons. The lock balls (1/4-inch ball bearings) areforced outward by the actuation piston. They serve tohold the closure piston in place against the 200-psifreshwater supply.

Figure 8-25.—Water injector (detector nozzle).

8-28

The actuation piston is held in place by the

gold-wire spring pin. A force of approximately 16

pounds is required to break (or bend) the pin. Should amissile accidentally ignite, the pressure created by

rocket motor exhaust acts on the top of the actuation

piston. The piston is forced downward and breaks the

pin. The lock balls drop into the throat of the nozzle

and release the closure piston. The 200-psi freshwaterpressure forces the closure piston upward to activate the

injection system.

SYSTEM OPERATION.— Now that the injectionsystem is activated, the other components begin to

function. As the freshwater continues to shoot out thedetector nozzle, the flow switch actuates. Freshwater

pressure decreases and, in a matter of seconds, the main

check valve opens. The system continues to operate,discharging the fire main supply from the (one)activated nozzle. When the emergency is over,

personnel turn off the fire main supply to secure the

system and replace the detector nozzle. The system is

then flushed, refilled, and charged.

A word of caution worth remembering—Use

extreme care when working around a water injectionnozzle. The gold-wire spring pin is sensitive. A

dropped tool or a misplaced foot can result in a

tremendous surprise !

Actual GMLS Water Injection Systems

All GMLSs have a water injection system. Eachsystem operates on the same principle. Only thephysical location and number of components differ.

The Mk 13 GMLSs (fig. 8-26) have a total of 96detector nozzles (48 on the inner ring and 48 on theouter ring). Since the Mk 13 GMLS RSR rotates, theRSR cells (16 inner and 24 outer) can be indexed andstopped at over 96 different positions. The Mk 26GMLS has one detector nozzle at each RSR hanger railposition. The Mk 41 VLS has a deluge system for eachcell canister, which floods the canister during rocketmotor ignition without the missile leaving the canister.

The Mk 13 GMLSs use a special valve in their waterinjection systems. It is called a restart valve. In thetypical water injection system schematic (fig. 8-24), thisvalve would replace the manual shutoff valve above themain check valve. The restart valve may be operatedmanually or by a remote-controlled solenoid. Thesolenoid is actuated by a switch located inside thelauncher control room.

Initially, the injection system must still be activatedautomatically. However, the restart valve may be usedto secure the system. It can also be used to reactivate(restart) the system in an emergency situation (such asa flashback).

A special feature of the Mk 26 GMLS is that asensing line connects the water injection system to the

Figure 8-26.—Mk 13 GMLS magazine base; injection system arrangement inside magazine area.

8-29

sprinkler system (fig. 8-27). Should a rocket motorignite, the detector nozzle activates the injectionsystem. Additionally, the blast pressure pushes theblow-in plate down, causing it to fall into the plenumport of the RSR station. Loss of a blow-in plate releasesthe drop-away plunger of a sprinkler-actuating valveassembly. Water pressure in the sensor line decreasesand starts zone sprinkling. The operation is unique tothe Mk 26 GMLS.

DRY-TYPE SPRINKLER SYSTEMS

A dry-type sprinkler system is one in which thepiping from the outlet side of the main sprinkler controlvalve up to the sprinkler heads contains no water in anormal or ready state. This piping remains “dry” untilthe system is activated.

The sprinkler system may be activatedautomatically or manually. A thermopneumaticsystem, using HSDs, performs the automatic function.Manual control valves, located at separate local andremote control stations, are used to activate the systemmanually.

Once the system is activated, it must be securedmanually. System design permits it to be activated atone station and be secured from another station.

Figure 8-27.—Mk 26 GMLS water injection system.

The Mk 13 GMLS and Mk 41 VLS have dry-typemagazine sprinkler systems. A dry-type sprinklersystem can be divided into four main equipment areas:

1. Automatic control system

2. Hydraulic control system

3. Main sprinkler control valve

4. Sprinkler alarm system

Figure 8-28 is a general schematic arrangement ofthe major sprinkler components. Take a moment tostudy it, as we will refer to it frequently. Locate the fourequipment areas.

Automatic Control System

The automatic or thermopneumatic control systemused on this sprinkler system is similar to that of a CO2

system. The fusible link of the sprinkler HSDs (fig.8-29) melts at 160°F (±3°) and functions the same wayas that in the CO2 system.

Each HSD will also have its own circle seal checkvalve. Groups of HSDs can be connected to a commonmanifold. Each manifold will also have its own ventedcheck valve. Transmission line tubing is the 1/8-inchOD rockbestos style.

Figure 8-29.—Heat-sensing device (HSD).

8-30

Figure 8-28.—Dry-type sprinkler system schematic; in static condition.

8-31

diaphragm is mounted inside an air chamber of thehousing. The back side of the diaphragm chamber (orcase) is connected to the HSD tubing network. Thefront side of the diaphragm is open to the interior of thePRP valve housing.

The compensating vent connects to the backside ofthe diaphragm chamber. Its purpose is to “leak off” anysmall increases or decreases in air pressure around thediaphragm. These variations are caused by normalspace temperature or pressure fluctuations. The slow“leak off” serves to equalize the pressure on both sidesof the diaphragm. In doing so, the compensating ventprevents inadvertent PRP valve actuation. Thecompensating vent is factory calibrated and adjusted, sodo not make any “sailor alterations” to it.

Figure 8-30.—Pneumatica1ly released pilot valve (PRP).

PNEUMATICALLY RELEASED PILOTVALVE.— The pneumatically released pilot (PRP)valve (fig. 8-30) is the main component of the hydrauliccontrol system. It is shock-mounted to the local controlpanel inside the magazine or RSR. The PRP valve, inresponse to the pneumatic pressure signal from one ormore HSDs, starts automatic sprinkler activation.

The outer body of the PRP valve is a circular bronzehousing. Inside the housing is an operating mechanism,a diaphragm, and a compensating vent (fig. 8-31). Theoperating mechanism is a spring-loaded lever deviceconnected to the diaphragm. The slightly flexible

Components outside the PRP valve housing includea hydraulic pilot valve, a Schrader valve, and anair-pressure gauge (see fig. 8-30). The pilot valve isinstalled in a saltwater line of the hydraulic controlsystem. It rotates between a SET (closed) position anda TRIPPED (open) position. The pilot valve must bemanually rotated back to its SET (closed) position witha special wrench (reset key).

The Schrader valve is nothing more than an airvalve stem (like that on a car or bicycle tire). It is onlyused during maintenance testing. Internally, it connectsto the chamber area of the diaphragm. The air-pressuregauge monitors diaphragm chamber pressure rangingfrom O to 36 ounces per square inch (osi).

PRP VALVE OPERATION.— As spacetemperature rises, one or more HSDs activate. They

Figure 8-31.—PRP valve; internal schematic.

8-32

transmit the air-pressure impulse signal to the backside recesses or holes allow the valve to be locked in any ofof the flexible diaphragm of the PRP valve. If the its three positions. Installed between the handle and theincreased pressure is of such magnitude that the lever is a rectangular locking key. The key is securedcompensating vent cannot bleed it off fast enough, the in place by easily broken safety wire (lead-wire seal).diaphragm will bend or move inward (fig. 8-31). The locking key prevents accidental sprinkler

If the diaphragm moves far enough, it releases thelever of the operating mechanism. In turn, the leverrotates and trips the pilot valve. Salt water startsflowing through the hydraulic control system piping.

Hydraulic Control System

The components of the hydraulic control system arelocated on the local and remote control panels. (See fig.8-28.) Various manual shutoff valves and strainers areused in the system. They isolate certain componentsduring maintenance procedures and filter marinegrowth in the saltwater supply. Most of the valves aremanufactured by the Cla-Val Company and are knownby their Cla-Val designation.

L O C A L A N D R E M O T E C O N T R O LVALVES.— The local and remote manual controlvalves (fig. 8-32) are lever-operated rotary valves.Each one has three positions: OPEN, NEUTRAL, andCLOSED.

activation since the handle and lever cannot be squeezedtogether with the key in place. If they cannot besqueezed, the locking pin cannot be retracted and thehandle will not turn.

INLINE CHECK VALVES.— Four inline checkvalves, designated Cla-Val No. 81M, are located on thelocal control board. (See fig. 8-28.) They arespring-loaded check valves that open wide when saltwater flows in the proper direction (with the arrow).They close tight when salt water flows against thearrow. By preventing backflow to other stations, thesecheck valves permit the sprinkler system to be activatedfrom more than one station.

HYDRAULICALLY OPERATED CHECKVALVE.— The hydraulically operated check valve isdesignated Cla-Val No. 81PM-1 (fig. 8-28). It is anormally closed, globe-type check valve that becomesfunctional only during the stop cycle of sprinkleroperation.

The operating handle has a spring-loaded lever When fire main is ported to the upper chamber of

behind it. The lever actuates a locking pin that extends the valve, its diaphragm lifts and opens the bottom

into a recess in the body of the valve. Three separate chamber. Fire main from the top of the main sprinklercontrol valve is then ported out unrestricted to drain line#3. This action permits the main valve to close underspring pressure, which secures sprinkler operation.

DRAINS AND ORIFICES.— The hydrauliccontrol system has three drain lines and two orificerestrictions (fig. 8-28). The drain lines are normallylocated so that they can discharge into a portablecontainer (bucket). The lines should be numbered andtagged so that they can be quickly identified.

Drain lines #1 and #2 contain .098-diameter-orificeplates. The orifices (holes), drilled through flat metalplates, serve two purposes. The primary purpose of theorifices is to prevent a buildup of saltwater backpressure in control system piping. Back pressure isnormally caused by valve leakage. Eventually, thisback pressure could be enough to activate the system.On your daily magazine inspection, you will notice apuddle of water on the deck or in the bucket. Report itso that repairs can be made. The secondary purpose ofthe orifices is to vent operating pressure from thehydraulic control system when it is returned to AUTO

Figure 8-32.—Remote control panel. or NEUTRAL.

8-33

Main Sprinkler Control Valve

The main sprinkler control valve is located insidethe magazine. The valve (fig. 8-33) is a diaphragm-operated, normally (spring) closed, globe-type valve.The upper diaphragm in the bonnet chamber is raisedor lifted by a minimum of 40-psi fire main pressure. Asit lifts, the lower disc is pulled off its seat. Fire main

supply is then free to flow to the sprinkler heads. Theupper end of the valve stem can be seen in a glass sighttube. It provides a visual indication of the condition ofthe stem (stem down, valve closed; stem up, valveopen).

A removable cover is located on the bottom side ofthe body of the valve. Normally, the cover remainsinstalled. During any maintenance testing or repairwork, the cover is unscrewed and replaced with aspecial test casting (fitting).

The test casting is so shaped that it extends up tothe lower seat of the disc. When the disc lifts, the firemain is prevented from flowing to the sprinkler headsby the body of the test casting.

The test casting also has a removable cap. Whenunscrewed, it may be replaced by a standard fire hoseand fitting. After the system activates, the fire mainflows through the hose and is discharged over the side.This process flushes the saltwater piping of thehydraulic control system.

The test casting MUST be installed before any workis performed on the sprinkler system. The test castingMUST be removed after the job is completed. Thesetwo “rules” are extremely important.

Sprinkler Alarm System

Two water-activated switches serve as the alarmportion of the system. Both units are located on the dryor downstream side of the main sprinkler control valve.(See fig. 8-28.)

The leakage alarm switch (fig. 8-34) is the earlywarning unit. The seat of the main control valve canbecome deteriorated through age. A piece of marinegrowth (like a seashell) can get caught on the seat whenthe valve Closes. In either case, saltwater will leak byand enter the switch body. Because water is a goodconductor of electricity, it activates the switch element.

Figure 8-33.—Main sprinkler control valve. Figure 8-34.—Leakage alarm switch.

8-34

An alarm is energized in DC central on the FH (water)circuit.

The operation alarm or flow alarm switch isinstalled farther downstream from the main valve. (Seefig. 8-28.) When the system is activated, fire mainpressure actuates this switch to set off other FH alarmsin DC central.

Sprinkler System Operation

Refer to figure 8-28 as we describe a remote STARTand a remote STOP sprinkler operation. At the remotecontrol station, the lead-wire seal is broken and thelocking key removed. The handle and lever of the valveare squeezed together and turned to the STARTposition. (When the locking pin engages its recess hole,you can let goof the handle.) Fire main control pressureflows through one of the inline check valves on the localboard. (Trace the water flow on the figure.)

The control pressure flows to the top of the mainsprinkler control valve, which lifts to start sprinklingoperations. Control pressure also flows to the bottomchamber of the hydraulically operated check valve. Asmall amount of water flows out drain line #1. Theother two drain lines will be dry at this time. (If youforgot to put the test casting in, your missiles are gettingwet !)

When the system must be secured, the remotecontrol valve handle and lever are squeezed and turnedto CLOSED. Fire main control pressure is reroutedthrough the stop line to another inline check valve.Control pressure enters the upper chamber of thehydraulically operated check valve, causing it to lift.The control pressure in the upper chamber of the mainsprinkler valve is then vented. It flows through thehydraulically y operated check valve and out drain line#3. As the pressure decreases, the main sprinkler valvecloses.

After the main sprinkler control valve has seated,the remote control valve may be returned to OPEN.Fire main control pressure is then isolated from thehydraulic control system. The hydraulically operatedcheck valve will be closed by its spring as waterpressure decreases. Any remaining pressure in the linesis bled through the #1 and #2 orifice drains.

The other operational possibilities will not bedescribed in detail. The major steps for two suchsequences are listed below. Refer to figure 8-28 as yourun the cycles.

Remote station OPEN and local stationCLOSED:

1 Remote—Turned to OPEN

2. Local—Turned to CLOSED

3. Remote—Turned to NEUTRAL

4. Local—Turned to NEUTRAL

Automatic (PRP valve) OPEN and remotestation CLOSED:

1.

2.

3.

4.

PRP valve—Trips

Remote—Turned to CLOSED

PRP valve—Reset manually

Remote-—Tumed to NEUTRAL

Sprinkler System Maintenance

Sprinkler system maintenance is performedperiodically under the Planned Maintenance System.We will describe some of the general procedures usedduring sprinkler testing. ALWAYS refer to theapplicable maintenance instructions BEFOREperforming ANY work.

NOTE

A test casting is treated as a controlled oraccountable item. In other words, thecommanding officer or a designatedrepresentative maintains custody of the testcasting. Before any maintenance is started, twoevents must occur. First, permission must beobtained from proper authority to begin thework. Second, the test casting must be issued.After the work is finished, the test casting mustbe turned in. This issue/turn-in procedureassures command that the test casting is NOTaccidentally left in the system.

The first rule is to install the test casting. (The chiefwill INSIST on that!) Connect the fire hose and fittingto the test casting if the system is to be flushed.

The next phase of the operation tests the automaticcontrol system. Connect a tire (or bicycle) pump to theSchrader valve on the PRP valve. Stroke the pumpslowly to pressurize the pneumatic system. That maytake awhile as the entire pneumatic system is beingfilled. Do NOT exceed 16 osi on the air-pressure gaugeduring the pumping. Excess air pressure can damagethe PRP valve/diaphragm.

8-35

When system air pressure balances or equalizesnear 16 osi, disconnect the pump and wait 5 minutes. Ifthe pressure stabilizes within the 8-16 osi range, thesystem is satisfactorily airtight. A pressure drop below8 osi indicates an air leak, which must be repaired. Usea leak-detector solution to find loose or crackedtransmission line fittings, cracked HSD bellows, and soforth.

If the system is “tight,” CAREFULLY depress thestem of the Schrader valve. SLOWLY bleed the systemto 8 osi. The PRP valve may, after repeated testings, bedamaged if a higher pressure is used during thefollowing step.

The next phase of the operation tests the PRP valve,hydraulic control system, and main sprinkler controlvalve operation. Full y depress the Schrader valve stem.The air from the front side of the diaphragm will bevented quickly to the atmosphere. The 8 osi of air onthe back side of the diaphragm causes it to move. Theoperating mechanism is released, the pilot valve trips,and the system activates.

The system may be secured normally after it flushesfor a few minutes. By the way, we hope you tied theend of the fire hose down. Unsecured, it will whiparound under full fire main pressure.

When testing is completed, ensure ALL the air isbled from the PRP valve. That is done by depressingthe Schrader valve stem. The test casting is removed asthe final step. Take your time during sprinkler systemtests. Be sure you are performing each step correctly.

The necessity to perform sprinkler systemmaintenance correctly cannot be overstressed. Toemphasize this point, we will reprint a portion of anarticle that was published in the Ships Safety Bulletin.The Bulletin is a monthly publication prepared by theNaval Safety Center. The information contained in theBulletin is intended for use by all hands. (The coursenumber given at the end of the article may change, butotherwise the information remains valid.)

MAGAZINE SPRINKLINGSYSTEMS

Inadvertent flooding of shipboardmagazines are on the increase. Causes appearto be the unfamiliarity of personnel in operatingand maintaining sprinkler system components,lack of formal training, improper supervision,and failure to follow prescribed PMSprocedures.

In one incident, a group of three magazineswas inadvertently sprinkled because the pettyofficer in charge failed to ensure that properstep-by-step PMS procedures were followed.In completing PMS, the technician restoredsystem lineup before air test pressure was fullybled off the pneumatically released pilot valve(PRP). Personnel error and haste were at theroot of this mishap.

NAVSEA OP-4, Vol. 2, Fifth Rev.,Change 9, para. 3-22, requires that tests andmaintenance of sprinkling systems beconducted in accordance with NAVSEATechnical Manual S9522-AA-HBK-010 andapplicable PMS instructions. Formal trainingis available in the Sprinkler Systems School atthe Fleet Training Centers in Norfolk and SanDiego. Assistance can also be obtained fromthe Fleet Technical Support Center (FTSC) inyour area.

Actual GMLS Dry-Type Sprinkler Systems

The dry-type, saltwater-operated, magazinesprinkler systems used by the Mk 13 and Mk 26 GMLSsand the Mk 41 VLS are similar. The remote controlstations are located outside the launcher control rooms.The local control panels are located inside the magazinecenter areas. The HSDs and sprinkler heads are equallyspaced around the missile cell/RSR areas.

The Mk 41 VLS has its own uniquely designeddamage control system known as deluge. The delugesystem applies water directly to a missile when arestrained firing or canister overtemperature occurs.Restrained firing is defined as missile motor ignitionand subsequent rupturing of the canister after closure,without missile motion. Overtemperature is defined asan internal canister temperature of 190°F or aboveWITH a missile present. When either of the aboveconditions exists, a sensing device in the canister sendsa deluge request to the deluge control circuits in thelaunch sequencer (LSEQ), which sends a DELUGESYSTEM ON command to the motor control panel(MCP). The MCP determines which cell requiresdeluging and issues a DELUDE ON signal to causedeluging of that particular cell.

A deluge control assembly (fig. 8-35), containing asolenoid control assembly, check valve, pilot valve,deluge control valve, and associated plumbing, isprovided for each cell in the module. All eightassemblies (five for the strikedown module) are

8-36

Figure 8-35.—Deluge water supply and components.

mounted on the inboard side of the modules above theupper walkway.

A 28-gallon freshwater accumulator tank is filledwith 15 gallons of freshwater and pressurized to 225psi. An additional 50 gallons of freshwater is presentin the launcher supply lines between the accumulatortank and the Hy-check deluge control valve. This wateris used first, followed by the water from the accumulatortank. The water level in the accumulator tank ismonitored by a sensing device. The sensing devicesends a signal to both the status panel and central controlstation (CCS), causing an alarm indicating that thewater level has dropped below 13 gallons. When theaccumulator tank pressure drops below 190 psi, a signalis sent to both the status panel and CCS, causing anotheralarm. When the accumulator tank pressure dropsbelow that of the ship’s fire main, the Hy-check delugecontrol valve switches the system from freshwater tosea water to complete the deluge. The deluge flow rateis 40 gpm.

The deluge is secured by an internal reset signaloriginated by the launch sequencer (LSEQ) after 100

seconds (±10 seconds) or by manual operation of theDELUGE RESET switch on the status panel. A thirdmethod of securing the deluge is by operation of thedeluge two-way manual control valve, which securesthe saltwater supply.

When a deluge condition is initiated in a particularcell, any cell in that module which has been delugedbefore that time will be deluged again. This delugeoperation will continue until the deluged canisters havebeen replaced. Also, any empty canisters in the moduleconcerned are deluged.

ENVIRONMENTAL CONTROLSYSTEMS

LEARNING OBJECTIVES: Explain the role ofenvironmental control systems used inguided-missile launching systems. Identify themajor components or systems used in thisprocess.

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All GMLSs contain a variety of auxiliary systemsthat protect the launching equipment and missiles fromexcessive environmental conditions. Environmentalcontrol systems perform the basic functions of heatingand cooling. Ship operations in the tropical climateswill create high internal magazine temperatures andhumidity levels. These conditions affect the reliabilityof missile propellant grains and play havoc with solid-state electronic control circuits. The colder climates alsoaffect missile propellant performance and launchercomponent operation. If ice forms around movableguide-arm components, it could feasibly freeze or lockthose components in place.

In many cases, the GMLS auxiliary systems relyon the ship’s “hotel services” to operate. These servicesare the responsibility of the ship’s engineeringdepartment. Steam from the boilers and chilled waterfrom the cooling plants are two such services suppliedto our equipment. In such cases, a littleinterdepartmental cross-training can be valuable.

ANTI-ICING SYSTEMS

Every GMLS has some type of auxiliary systemthat prevents the accumulation of ice formationsaround critical moving components. One such system isreferred to as an anti-icing or circulating system. It isused to circulate a heated fluid throughout theequipments exposed to the weather. Another type ofsystem uses an electrical coil or strip-type heatingelement to protect the exposed equipment.

Regardless of style, each system has the same endpurpose-to melt the ice. Each GMLS also has its ownversion of an anti-icing system. We will briefly describeatypical system and then point out any uniquedifferences between the GMLSs.

A Typical Anti-Icing System

The typical anti-icing system is an enclosedpressurized fluid system. Its main component is a heatexchanger tank (fig. 8-36). It is normally located in anauxiliary equipment room near the magazine and servesas a reservoir and heater for the anti-icing fluid. Thisfluid is normally a 50:50 mixture of ethylene glycol andwater. The solution is similar to the antifreeze mixture inthe radiator of your car.

Inside the heat exchanger tank is a coiled networkof steam tubes. They are supplied by ship’s auxiliarysteam from the main or auxiliary (donkey) boilers. Thetubes transfer heat to the anti-icing fluid as it (the fluid)flows through the tank. An air bladder (accumulator)

Figure 8-36.—Anti-icing heat exchanger tank.

inside the tank is charged with low-pressure air. Thebladder acts on the fluid to keep a constant pressure inthe system. The bladder also compensates for changesin fluid volume caused by temperature variations andminor leakage.

A steam control valve and a temperature-sensingvalve monitor and regulate the temperature of thefluid. The sensing valve is installed in the return fluidline of the system and connects to the steam controlvalve. The sensing valve is adjusted to open and closethe steam control valve within a selected temperaturerange. This action automatically maintains the anti-icing fluid within the desired heat range. Although thedesign specifications of each GMLS will vary, returnfluid temperature is generally maintained between40°F and 60°F. A thermometer is installed in the returnline to monitor the temperature of the system.

A small electric motor is used to drive acentrifugal-type pump. The pump draws heated fluidfrom the tank and discharges it into the system. Thesupply and return fluid piping networks route the fluidthroughout the critical areas of the GMLS. The pipingsystem includes the normal variety of flow control,relief, and air-bleed valves. Strainers and distributionmanifolds are also used. In many systems, anti-icingfluid is circulated through special internal passagewaysdrilled or machined in a component.

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In addition to circulating heated fluid, anti-icingsystems can also run unheated. This optional featurecirculates a cool fluid mixture used to help dissipate theheat created by a missile blast.

The anti-icing system in the Mk 26 is also used formissile blast cooling. When blast cooling is selectedand a missile is fired, the system starts and runsautomatically to circulate anti-icing fluid in theguided-missile launcher, blast door, jettison devices,blowout plates, and platform. The system runs forapproximately 10 minutes after the last missile is fired.

Actual Anti-Icing Systems

The Mk 13 Mod 4 GMLS uses a heat source otherthan auxiliary steam. Twelve electrically controlledimmersion heating elements are located within the heatexchanger tank of the Mk 13 Mod 4 GMLS. Eachelement is a 1/2-inch copper sheath about 6 feet long.It is bent into a loop that projects about 1 1/2 feet intothe tank. The copper sheaths are heated bysingle-phase, 440-VAC, 60-hertz power. They areenergized through a heater-controller panel located nearthe launcher control room. Tank fluid is heated as itflows across the elements.

The Mk 41 VLS anti-icing system is designed toprevent a buildup of snow or ice that might prevent acell or uptake hatch from opening during launchoperations. The anti-icing system does not provide

coverage of the strikedown hatch. Anti-icing must bemanually enabled for each module individually at thelauncher status panel.

The main items of the anti-icing system are heatersand thermostats built into the uptake and cell hatchassemblies (fig. 8-37). The uptake hatch contains onetubular 14-watt-per-inch heater element and twothermostats that activate the anti-icing system when thetemperature falls within the 33°F to 43°F range. Eachcell hatch has three heater elements; two of the heatersare 175-watt cartridge elements that are built into thehinge brackets on either side of the trunnion. The thirdheater is a 25-watt-per-inch tubular element built intothe cell hatch cover and located around the perimeter ofthe hatch.

AIR-CONDITIONING AND VENTILATIONSYSTEMS

Air-conditioning and ventilation systems are usedin GMLS areas for the general safety of equipment,personnel, and the ship. The purpose of these systemsis to circulate air around vital system components. Thiscirculated air maintains normal temperature andhumidity levels within a space. Air-conditioningsystems use ship-supplied chilled water, a cooling-coilunit, and fan-blower units to circulate cool air.Ventilation systems only use a fan-blower unit tocirculate ambient (surrounding) temperature air.

Figure 8-37.—Module hatch heater elements.

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Launcher control rooms and missile magazines arealways air-conditioned spaces. Some GMLSs use aseparate ventilation system to cool their launchercarriages. Ventilation systems are usuallythermostatically controlled to maintain spacetemperature ranges between (an average) 70°F and100°F. Also, a majority of air systems have cutoffvalves installed somewhere in the supply and exhaustlines. These valves should bear a Circle Williamdamage control classification. Learn where thesevalves are located. They must be closed during nuclear,biological, and chemical (NBC) drills. Additionally,make SURE all air filters are cleaned properly on a strictmaintenance schedule. That will keep these systemsoperating at peak efficiency.

Magazine air-conditioning/ventilating systems canalso serve an important secondary purpose. Consider amissile magazine with an installed or fixed CO2 system.If fire breaks out, the space will be flooded with CO2

extinguishing agent. The air system must be securedquickly to prevent the CO2 from being drawn out of thespace. Normally, the CO2 system has a pressure-operated switch that interconnects to the electricalcircuit of the air system. When the CO2 systemactivates, the switch secures the air system (turns off theblower).

The air system should not be turned on for at least15 minutes after CO2 discharge. This 15-minute timeperiod serves as a cool-down period. The cool-downperiod prevents hydraulic fluids and lubricants fromre-igniting when exposed to a new air supply. After thecool-down period, the space should be ventilated a full15 minutes before anyone enters it. The air systemremoves the CO2 gas and restores air to a life-sustaininglevel.

We wi l l br ie f ly examine the var iousair-conditioning and ventilation systems used in theGMLSs.

Mk 13 Mods 4 and 7 GMLSs

The magazine ventilating systems on the Mk 13GMLSs use air, which is forced into the magazine, fromthe ship’s air-conditioning system. It cools the missilesand inner structure (center column) equipment areas(fig. 8-38). Air enters the magazine through intakeducts under the cells. It flows up around the missilesand enters the inner structure through ventilationscreens at the top of the structure. The exhaust ductsare in the center of the base.

Mk 26 GMLS

The Mk 26 GMLS and Mk 41 VLS use standardship-operated air-conditioning units to cool theirspaces. The Mk 26 has one unit that supplies the ICSand another that supplies the magazine.

GMLS SAFETYSUMMARY

LEARNING 0BJECTIVES: Identify the safetyprecautions personnel use while working onguided missile launching systems.

The object of the last section of this chapter is tointroduce you to the topic of safety. Specifically, wewill emphasize certain safety precautions and warningsthat apply, in general, to shipboard GMLS opera-tions.

The Navy distributes many safety-relatedpublications, periodicals, and special messages. Theircontents are devoted entirely to important safetypractices. Some are general in nature. Others deal withmore specific precautions related to a single equipmentor knowledge area. Certain general ordnance safetypublications are also included in the GM3 throughGMC bibliography list (NAVEDTRA 10052, currentrevision). These are references you should study whenpreparing for an advancement exam.

Each launching system comes with a set of “books”called ordnance publications, or OPs for short. (Theywill be discussed in more detail later in this manual.)Published in a series of volumes, a GMLS OP describesthe system and gives its operating procedures.Information and instructions needed to keep theequipment in proper working order are also included.Volume 1, which gives the description and operation ofthe GMLS, will always contain a section entitled“Safety Summary.” The safety summary is usuallygiven in two parts: (1) general safety precautions and(2) specific safety precautions.

GENERAL SAFETY PRECAUTIONS

General safety precautions, as the name implies,have wide applications in a variety of work-relatedsituations. They pertain to the use of tools and to theexposure to high voltages and pressures. Additionally,they address the general safe handling of explosives andother volatile materials. Study these precautions so that

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Figure 8-38.—Mk 13 GMLS magazine ventilation system.

you will recognize the potential hazards involved. Establish CommunicationsApply these precautions during all phases of operationand maintenance. The following precautions are a Do not activate the launching system untilsmall sampling of warnings that pertain to all the communications have been established between theGMLSs. safety observer and the launcher captain.

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High-Voltage Hazard

Be careful when working in lethal voltage areas.Do not work on live circuits unless absolutelynecessary. Under some conditions, dangerous voltagepotentials may exist in electronic circuits after thepower is shut off. When such potentials are suspected,discharge the appropriate components before touchingthem. Do not perform work in a lethal voltage areaunder any circumstances without the presence of at leastone person able to give first aid in the event of electricshock.

Resuscitation

Do not work with or near high voltages unless youare familiar with the methods of artificial respiration.Obtain resuscitation information from the appropriateauthority.

Hydraulic Pressure Hazard

Always bleed the hydraulic systems of pressurebefore attempting to remove or disassemble anyhydraulic component. Make sure system pressure iszero by observing installed gauges.

Hydraulic Fluid Hazard

If clothing becomes drenched with hydraulic fluid,immediately change into dry clothing. Hydraulic fluidis injurious to health when in prolonged contact withskin. It is also a fire hazard. Immediately wipe upspilled hydraulic fluid.

High-Pressure Water Hazard

Do not perform any maintenance procedures on thewater injection system until all pressure in the lines hasbeen dissipated. Do not work directly over waterinjection nozzles. Do not tamper or drop anything onwater injection nozzles.

High-Pressure Air Hazard

Do not point a jet of high-pressure air at any part ofa human body. The jet may be fatal.

High-Pressure Nitrogen Hazard

Use only approved nitrogen to chargeaccumulators. Never use oxygen or compressed air. Amixture of hydraulic fluid and oxygen is explosive.When charging accumulators, do not disconnect the

charging line until it has been bled. High-pressurenitrogen is present in the charging line.

Carbon Dioxide (CO2) Hazard

Suffocation hazard exists. Before entering themagazine area, unlock and close shutoff valve(s) forCO2 system(s).

Live Missile Hazard

Return any live missile to the magazine beforetroubleshooting components in the launcher area.

Explosion Hazard

Do not take naked lights, matches, or otherflame-producing apparatus into a compartmentcontaining explosives. Smoking is not permitted at anytime within these compartments.

Moving Equipment Hazard

When troubleshooting, shut down the power-drivemotors of equipment not involved in the malfunction orcasualty. After locating a fault, shut down allpower-drive motors; then proceed with correctiveactions.

Launcher Area Hazard

Ensure that the safety observer’s safety switch (ordeadman’s key) is installed before entering the trainingarea/circle of the launcher. Do not leave the switchunattended.

Unauthorized Panel Operation

Do not allow unqualified or unauthorized personnelto operate the control panels. Trainees or other personsundergoing instruction will operate panels under thestrict personal supervision of a qualified andresponsible operator.

Servicing, Adjusting Hazard

Do not reach into any equipment or enter themagazine structure to service or adjust componentsexcept with someone who can give first aid.

SPECIFIC SAFETY PRECAUTIONS

Specific safety precautions and warnings appeartwice in a GMLS OP. They are stated near the

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equipment description or operating procedure to whichthey apply. They are also repeated in the second part ofthe safety summary for emphasis.

We will not attempt to list every specific safetyprecaution. The warnings given in the followingparagraphs, however, can generally be applied to all theGMLSs.

Warning bells or horns will be sounded to alert allpersonnel of impending equipment movement. Thismovement could happen at any time. Do not start thepower-drive motors without clearance from the safetyobserver. Verify all personnel and equipment are clearbefore moving the launcher.

Remove and retain safety switch handles or keys.That prevents the power-drive motors from beingstarted when you are working on or aroundpower-operated equipment. The launching systemmust be deactivated before personnel are permitted tofold missile fins inside the launcher area.

If a missile is on the guide arm, do not retract theaft-motion latch unless the hoist pawl is in ‘fullengagement with the aft missile shoe. Personnel mustnot pass or crawl through an open blast or magazinedoor with the system energized. Observing theclinometer, jettison on the down roll.

SAFETY SUMMARY CONCLUSION

Even though GMLSs are complex machines, theycan be operated and maintained in a relatively safemanner. Safety precautions DO work if the properequipment and procedures are used. All applicablesatiety warnings must be strictly followed. Always useyour common sense and do not skylark.

All equipment operations should be performedcarefully, methodically, and without hurrying. Greaterindividual and team effectiveness will be developed byincreased familiarity with the proper and safe methodsof accomplishing a task. Should a malfunction occuror an incorrect indication appear on a control panel,STOP the operation immediately. Then determinewhether it is safe to proceed. Consider the effect of yourdecision on both equipment and personnel. Do NOT beafraid to ask for help.

Cleanliness and good housekeeping practices in allwork areas are important. They are major factors ineffective accident prevention. Keep tools in goodworking order, and always return them to a properstorage place.

Changes, modifications, or alterations to anyordnance equipments should not be made unlessexplicit authority from NAVSEA or another cognizantauthority is obtained. Safety devices found on GMLSequipment were installed for the protection of personneland equipment. These devices should never beremoved, disabled, or bypassed. Specific authorizationfrom the commanding officer or a designatedrepresentative is required if a safety device must bealtered. Adequate notices should be posted to warn(and remind) personnel of the potential hazard.

This chapter only scratches the surface of safety.You will see more about safety throughout the rest ofthis manual. You will be involved with it everyday ofyour career. Become familiar with ALL the ordnancesafety publications, and set the example in followingthem.

SUMMARY

In this chapter, we discussed the secondary andauxiliary functions of the major GMLSs. Thisdiscussion was primarily directed toward theprocedures used in jettisoning and strikedownoperations. We covered various fire suppressionsystems, including the CO2, water injection, dry-type,and Mk 41 deluge systems. Environmental controlsystems—anti-icing and A/C-were also covered. Theoperational and safety requirements for the differenttypes of sprinkler systems were also discussed.

We concluded the chapter with a safety summaryon the GMLSs and a section on general safetyprecautions. It would probably serve you well to rereadthis section on safety.

In the next chapter, we will discuss the commonelectrical and electronic components and theirschematic symbols, used in the current GMLSs.

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