air-launched guided missiles and guided missile launchers … · chapter 3 air-launched guided...

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CHAPTER 3 AIR-LAUNCHED GUIDED MISSILES AND GUIDED MISSILE LAUNCHERS Guided missiles are self-propelled objects. After launching, they automatically alter their direction of flight in response to signals received from outside sources. They usually carry high-explosive charges and are equipped with a means to explode them at or near a target. The majority of guided missiles used in the Navy are essentially rockets that are maneuvered while in flight. AIR-LAUNCHED GUIDED MISSILES LEARNING OBJECTIVE: Recognize air-launched guided missile classifications. Match missiles with their range and speed. Identify air-launched guided missiles and recognize the methods used to designate them. Identify missile components to include guidance and control, armament, and propulsion systems. Identify the guided missiles used in the Navy today . The purpose of a guided missile is to reach and destroy or damage its target. The type of target involved influences the characteristics of the missile; however, each missile meets the following basic requirements: It must have sufficient speed to intercept or catch its target. It must be maneuverable in flight to correct its flight path as required to intercept the target. It must be capable of inflicting a satisfactory degree of damage to the target on intercept. It must have an acceptable operating envelope (range/altitude) within which it is effective. It must be capable of launching when required and at a satisfactory rate. The missile and its components must be safe to handle, store, and use. In general, a typical guided missile has a long, cylindrical shape, with an oval or a hemispherical shaped nose. It is fitted with a series of stabilizing or maneuvering fins, wings, or canards around its outer surface. MISSILE CLASSIFICATION Guided missiles are classified according to their range, speed, and launch environment, mission, and vehicle type. Range Long-range guided missiles are usually capable of traveling a distance of at least 100 miles. Short-range guided missiles often do not exceed the range capabilities of long-range guns. The Navy has air-launched guided missiles that function within these ranges; they are medium-range or extended-range missiles. Speed The speed capability of guided missiles is expressed in Mach numbers. A Mach number is the ratio of the speed of an object to the speed of sound in the medium through which the object is moving. Under standard atmospheric conditions, sonic speed is about 766 miles per hour (Mach 1.0). Guided missiles are classified according to their speed as shown below: Subsonic—Up to Mach 0.8 Transonic—Mach 0.8 to Mach 1.2 Supersonic—Mach 1.2 to Mach 5.0 Hypersonic—Above Mach 5.0 When considering the speed of an air-launched guided missile, the speed of the launching aircraft is added to the speed of the missile. For example, if a missile's speed is Mach 2.5 and the aircraft's speed, at the time of missile launch, is Mach 2.0, the missile's speed is Mach 4.5. Types of Guided Missiles Guided missiles are divided into two types— service missiles and nonservice missiles. SERVICE MISSILES.—These missiles are generally referred to as tactical missiles. Service 3-1

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Page 1: AIR-LAUNCHED GUIDED MISSILES AND GUIDED MISSILE LAUNCHERS … · CHAPTER 3 AIR-LAUNCHED GUIDED MISSILES AND GUIDED MISSILE LAUNCHERS Guided missiles are self-propelled objects. After

CHAPTER 3

AIR-LAUNCHED GUIDED MISSILES AND GUIDEDMISSILE LAUNCHERS

Guided missiles are self-propelled objects. Afterlaunching, they automatically alter their direction offlight in response to signals received from outsidesources. They usually carry high-explosive charges andare equipped with a means to explode them at or near atarget. The majority of guided missiles used in the Navyare essentially rockets that are maneuvered while inflight.

AIR-LAUNCHED GUIDED MISSILES

LEARNING OBJECTIVE: Recognizeair-launched guided missile classifications.Match missiles with their range and speed.Identify air-launched guided missiles andrecognize the methods used to designate them.Identify missile components to includeguidance and control, armament, andpropulsion systems. Identify the guidedmissiles used in the Navy today.

The purpose of a guided missile is to reach anddestroy or damage its target. The type of target involvedinfluences the characteristics of the missile; however,each missile meets the following basic requirements:

• It must have sufficient speed to intercept or catchits target.

• It must be maneuverable in flight to correct itsflight path as required to intercept the target.

• It must be capable of inflicting a satisfactorydegree of damage to the target on intercept.

• It must have an acceptable operating envelope(range/altitude) within which it is effective.

• It must be capable of launching when requiredand at a satisfactory rate.

• The missile and its components must be safe tohandle, store, and use.

In general, a typical guided missile has a long,cylindrical shape, with an oval or a hemisphericalshaped nose. It is fitted with a series of stabilizing ormaneuvering fins, wings, or canards around its outersurface.

MISSILE CLASSIFICATION

Guided missiles are classified according to theirrange, speed, and launch environment, mission, andvehicle type.

Range

Long-range guided missiles are usually capable oftraveling a distance of at least 100 miles. Short-rangeguided missiles often do not exceed the rangecapabilities of long-range guns. The Navy hasair-launched guided missiles that function within theseranges; they are medium-range or extended-rangemissiles.

Speed

The speed capability of guided missiles isexpressed in Mach numbers. A Mach number is theratio of the speed of an object to the speed of sound inthe medium through which the object is moving. Understandard atmospheric conditions, sonic speed is about766 miles per hour (Mach 1.0). Guided missiles areclassified according to their speed as shown below:

• Subsonic—Up to Mach 0.8

• Transonic—Mach 0.8 to Mach 1.2

• Supersonic—Mach 1.2 to Mach 5.0

• Hypersonic—Above Mach 5.0

When considering the speed of an air-launchedguided missile, the speed of the launching aircraft isadded to the speed of the missile. For example, if amissile's speed is Mach 2.5 and the aircraft's speed, atthe time of missile launch, is Mach 2.0, the missile'sspeed is Mach 4.5.

Types of Guided Missiles

Guided missiles are divided into two types—service missiles and nonservice missiles.

SERVICE MISSILES.—These missiles aregenerally referred to as tactical missiles. Service

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missiles are fully operational and fully explosiveloaded rounds, designed for service use in combat.

NONSERVICE MISSILES.—These include alltypes of missiles other than service or tactical. They aresubdivided as captive air training missiles (CATMs),dummy air training missiles (DATMs), special airtraining missiles (NATMs), and practice guidedweapons (PGWs).

Some practice and training missiles are used foractual launching. They contain live propulsion andguidance systems with inert loaded warheads. They arefitted with pyrotechnic fuze indicator signals and/ortracking flares that give a visual indication ofmissile/target impact. These missiles can also be fittedwith a telemetry-type warhead, which transmitselectronic signals to a monitoring station. Themonitoring station displays the missile's in-flightperformance and missile/target hit. Some types ofexercise missiles contain explosive-destruct charges sothe missiles destroy themselves in flight. Theseexplosive-destruct charges, when installed, are used asa safety measure so the missile does not travel beyondthe established target range.

The CATMs are used for pilot training in aerialtarget acquisition and aircraft controls/displays. Theyhave both tactical and training components.

The DATMs are ground training missiles used totrain ground personnel in missile assembly/disassembly, uploading/downloading, and handlingprocedures.

The NATMs are used for pilot training during fleetweapon training exercises.

The PGWs are used for stowage procedures andtechniques. All components are completely inert.

Service missiles are fired as practice or trainingmissiles when approved by proper authority. Normally,approval is restricted to missiles that are obsolete or tomissiles that have exceeded their normal service life.

Guided missiles used in naval aviation includeair-to-air and air-to-surface missiles. Air-to-air guidedmissiles are fired by one aircraft against anotheraircraft. Air-to-surface guided missiles are fired froman aircraft against a target on the land or water surface.

For further information on the classification ofguided missiles, you should refer to United States NavyAmmunition Historical and Functional Data,NAVSEA SWO10-AB-GTP-010, and Identification ofAmmunition, NAVSEA SW010-AF-ORD-010.

MISSILE DESIGNATION

The Department of Defense established a missileand rocket designation sequence. The basic designation(table 3-1) of every guided missile are letters, which arein sequence. The sequence indicates the following:

1. The environment from which the vehicle islaunched

2. The primary mission of the missile

3. The type of vehicle

Examples of guided missile designators commonto the Aviation Ordnanceman are as follows:

Designator Meaning

AGM Air-launched, surface-attack, guidedmissile

AIM Air-launched, intercept-aerial, guidedmissile

ATM Air-launched, training guided missile

RIM Ship-launched, intercept-aerial, guidedmissile

A design number follows the basic designator. Inturn, the number may be followed by consecutiveletters, which show a modification. For example, thedesignation of AGM-88C means the missile is anair-launched (A), surface-attack (G), missile (M),eighty-eighty missile design (88), third modification(C).

In addition, most guided missiles are given popularnames, such as Sparrow, Sidewinder, and Harpoon.These names are retained regardless of subsequentmodifications to the original missile.

MISSILE IDENTIFICATION

The external surfaces of all Navy guided missiles,except radome and antenna surfaces, are painted white.The color white has no identification color-codingsignificance when used on guided missiles.

There are three significant color codes used onguided missiles and their components—yellow, brown,and blue. These color codes indicate the explosivehazard in the missile component. If components arepainted blue on a practice missile and have a yellow orbrown band painted on them, the component has anexplosive component that doesn't have a comparablepart in a service missile.

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FIRST LETTERDESIGNATINGLAUNCHENVIRONMENT

DESCRIPTION

A Air

B Multiple

C Coffin

F Individual

M Mobile

P Soft Pad

U Underwater

R Ship

Air launched.

Capable of being launched from more than one environment.

Stored horizontally or at less than a 45-degree angle in a protective enclosureand launched from the ground.

Carried and launched by one man.

Launched from a ground vehicle or movable platform.

Partially or non-protected in storage and launched from the ground.

Launched from a submarine or other underwater device.

Launched from a surface vessel, such as a ship or barge.

SECOND LETTERDESIGNATINGMISSION SYMBOL

DESCRIPTION

D Decoy

E Special Electronic

G Surface Attack

I Intercept-Aerial

Q Drone

T Training

U Underwater Attack

W Weather

Vehicles designed or modified to confuse, deceive, or divert enemy defensesby simulating an attack vehicle.

Vehicles designed or modified with electronics equipment orcommunications, countermeasures, and electronic relay missions.

Vehicles designed to destroy enemy land or sea targets.

Vehicles designed to intercept aerial targets in defensive roles.

Vehicles designed for target reconnaissance or surveillance.

Vehicles designed to be modified for training purposes.

Vehicles designed to destroy enemy submarines or other underwater targets orto detonate underwater.

Vehicles designed to observe, record, or relay data pertaining tometeorological phenomena.

THIRD LETTERDESIGNATINGVEHICLE TYPESYMBOL

DESCRIPTION

M Guided Missile

R Rocket

N Probe

An unmanned, self-propelled vehicle with remote or internal trajectoryguidance.

A self-propelled vehicle whose flight trajectory cannot be altered after launch.

A non-orbital instrumented vehicle to monitor and transmit environmentalinformation.

NOTE: The designations listed in the above table cover all the guided missiles and rockets used withinthe Department of Defense. Therefore, the Navy may not use all designations listed.

Table 3-1.—Guided Missile and Rocket Designations

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Each component of the missile, besides being colorcoded, is identifiable by lettering stenciled on theexterior surface of the component. The lettering on acomponent gives information such as the Mark andMod, type and weight of explosive filler, loadingactivity symbol and date of loading, temperature rangerestrictions, and unit serial number.

All missiles used in naval aviation are assignedmissile serial numbers. These numbers are shippedwith the missile's logbook. The missile serial number isnormally the serial number of the leading component ofthe missile, such as the guidance and/or controlcomponents. The serial number is important because itis the number used to track the missile from assembly ata weapons station until it is fired or discontinued fromservice.

For further information concerning identificationof guided missiles, refer to NAVSEA SW010-AF-ORD-010/NAVAIR 11-1-117, Identification ofAmmunition (latest revision).

REVIEW NUMBER 1

Q1. The speed of a guided missile is given in termsof Mach numbers. If a guided missile istraveling at Mach 1, how fast is it going?

Q2. A missile traveling at Mach 3 is traveling at_______ speeds.

Q3. List the two types of guided missiles.

Q4. What two types of guided missiles are used innaval aviation?

Q5. The first letter of a missile designationdescribes the missile's ________.

Q6. Define the missile designation ATM.

Q7. Where would you find the serial number in anassembled missile?

Q8. What do the color codes identify on guidedmissiles?

MISSILE COMPONENTS

Guided missiles are made up of a series ofsubassemblies (figs. 3-1 and 3-2). The varioussubassemblies form a major section of the overallmissile to operate a missile system, such as guidance,control, armament (warhead and fuzing), andpropulsion. The major sections are carefully joined andconnected to each other. They form the completemissile assembly. The arrangement of major sections inthe missile assembly varies, depending on the missiletype.

The guidance section is the brain of the missile. Itdirects its maneuvers and causes the maneuvers to beexecuted by the control section. The armament sectioncarries the explosive charge of the missile, and thefuzing and firing system by which the charge isexploded. The propulsion section provides the forcethat propels the missile.

Guidance and Control Section

The complete missile guidance system includes theelectronic sensing systems that initiate the guidanceorders and the control system that carries them out. Theelements for missile guidance and missile control canbe housed in the same section of the missile, or they canbe in separate sections.

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Figure 3-1.—Typical air-to-air guided missile.

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There are a number of basic guidance systems usedin guided missiles. Homing-type, air-launched, guidedmissiles are currently used. They use radar or infraredhoming systems.

A homing guidance system is one in which themissile seeks out the target, guided by some physicalindication from the target itself. Radar reflections orthermal characteristics of targets are possible physicalinfluences on which homing systems are based.Homing systems are classified as active, semiactive,and passive.

ACTIVE.—In the active homing system, targetillumination is supplied by a component carried in themissile, such as a radar transmitter. The radar signals(fig. 3-3) transmitted from the missile are reflected offthe target back to the receiver in the missile. Thesereflected signals give the missile information such as

the target's distance and speed. This information lets theguidance section compute the correct angle of attack tointercept the target. The control section that receiveselectronic commands from the guidance sectioncontrols the missile’s angle of attack. Mechanicallymanipulated wings, fins, or canard control surfaces aremounted externally on the body of the weapon. Theyare actuated by hydraulic, electric, or gas generatorpower, or combinations of these to alter the missile'scourse.

SEMIACTIVE.—In the semiactive homing sys-tem (fig. 3-4), the missile gets its target illuminationfrom an external source, such as a transmitter carried inthe launching aircraft. The receiver in the missilereceives the signals reflected off the target, computesthe information, and sends electronic commands to thecontrol section. The control section functions in thesame manner as previously discussed.

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Figure 3-2.—Typical air-to-surface guided missile.

Figure 3-3.—Active homing system. Figure 3-4.—Semiactive homing system.

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PASSIVE.—In the passive homing system (fig.3-5), the directing intelligence is received from thetarget. Examples of passive homing include homing ona source of infrared rays (such as the hot exhaust of jetaircraft) or radar signals (such as those transmitted byground radar installations). Like active homing, passivehoming is completely independent of the launchingaircraft. The missile receiver receives signals generatedby the target and then the missile control sectionfunctions in the same manner as previously discussed.

REVIEW NUMBER 1 ANSWERS

A1. If a guided missile is traveling at Mach 1, it istraveling at approximately 766 miles perhour.

A2. A missile traveling at Mach 3 is traveling atsupersonic speeds.

A3. The two types of guided missiles are serviceand nonservice guided missiles.

A4. The two types of guided missiles used in navalaviation are air-to-air and air-to-surfaceguided missiles.

A5. The first letter of a missile designationdescribes the missile's launch environment.

A6. The missile designation ATM stands for anair-launched training guided missile.

A7. The serial number in an assembled missile isusually found on the leading component.

A8. The color codes on guided missiles identifythe explosive hazard in the missile com-ponent.

Armament Section

The armament system contains the payload(explosives), fuzing, safety and arming (S&A) devices,and target-detecting devices (TDDs).

PAYLOAD.—The payload is the element or part ofthe missile that does what a particular missile islaunched to do. The payload is usually considered theexplosive charge, and is carried in the warhead of themissile. High-explosive warheads used in air-to-airguided missiles contain a rather small explosive charge,generally 10 to 18 pounds of H-6, HBX, or PBX highexplosives. The payload contained in high-explosivewarheads used in air-to-surface guided missiles varieswidely, even within specific missile types, dependingon the specific mission. Large payloads, ranging up to450 pounds, are common. Comp B and H-6 are typicalexplosives used in a payload.

Most exercise warheads used with guided missilesare pyrotechnic signaling devices. They signal fuzefunctioning by a brilliant flash, by smoke, or both.Exercise warheads frequently contain high explosives,which vary from live fuzes and boosters to self-destructcharges that can contain as much as 5 pounds of highexplosive.

FUZING.—The fuzing and firing system isnormally located in or next to the missile's warheadsection. It includes those devices and arrangements thatcause the missile's payload to function in properrelation to the target. The system consists of a fuze, asafety and arming (S&A) device, a target-detectingdevice (TDD), or a combination of these devices.

There are two general types of fuzes used in guidedmissiles—proximity fuzes and contact fuzes.Acceleration forces upon missile launching arm bothfuzes. Arming is usually delayed until the fuze issubjected to a given level of accelerating force for aspecified amount of time. In the contact fuze, the forceof impact closes a firing switch within the fuze tocomplete the firing circuit, detonating the warhead.Where proximity fuzing is used, the firing action is verysimilar to the action of proximity fuzes used withbombs and rockets.

SAFETY AND ARMING (S&A) DEVICES.—S&A devices are electromechanical, explosive controldevices. They maintain the explosive train of a fuzingsystem in a safe (unaligned) condition until certainrequirements of acceleration are met after the missile isfired.

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Figure 3-5.—Passive homing system.

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TARGET-DETECTING DEVICES (TDD).—TDDs are electronic detecting devices similar to thedetecting systems in VT fuzes. They detect thepresence of a target and determine the moment offiring. When subjected to the proper target influence,both as to magnitude and change rate, the device sendsan electrical impulse to trigger the firing systems. Thefiring systems then act to fire an associated S&A deviceto initiate detonation of the warhead.

Air-to-air guided missiles are normally fuzed for aproximity burst by using a TDD with an S&A device. Insome cases, a contact fuze may be used as a backup.Air-to-surface guided missile fuzing consists ofinfluence (proximity) and/or contact fuzes. Multifuzingis common in these missiles.

Propulsion Section

Guided missiles use some form of jet power forpropulsion. There are two basic types of jet propulsionpower plants used in missile propulsion systems—theatmospheric (air-breathing) jet and the thermal jetpropulsion systems. The basic difference between thetwo systems is that the atmospheric jet engine dependson the atmosphere to supply the oxygen necessary tostart and sustain burning of the fuel. The thermal jetengine operates independently of the atmosphere bystarting and sustaining combustion with its own supplyof oxygen contained within the missile.

ATMOSPHERIC JET PROPULSION SYS-TEM.—There are three types of atmospheric jetpropulsion systems—the turbojet, pulsejet, and ramjetengines. Of these three systems, only the turbojetengine is currently being used in Navy air-launchedmissiles. A typical turbojet engine includes an airintake, a mechanical compressor driven by a turbine, acombustion chamber, and an exhaust nozzle. Theengine does not require boosting and can beginoperation at zero acceleration.

THERMAL JET PROPULSION SYSTEM.—Thermal jets include solid propellant, liquid propellant,and combined propellant systems. As an AO, you comein contact with all three systems. The solid propellantand combined propellant systems are currently beingused in some air-launched guided missiles.

The majority of air-launched guided missiles usedby the Navy use the solid propellant rocket motor. Theyinclude the double base and multibase smokelesspowder propellants as well as the composite mixtures.Grain configurations vary with the different missiles.Power characteristics and temperature limitations ofthe individual rocket motors also vary.

In some guided missiles, different thrust re-quirements exist during the boost phase as compared tothose of the sustaining phase. The dual thrust rocketmotor (DTRM) is a combined system that contains bothof these elements in one motor. The DTRM contains asingle propellant grain made of two types of solidpropellant—boost and sustaining. The grain isconfigured so the propellant meeting the requirementsfor the boost phase burns at a faster rate than thepropellant for the sustaining phase. After the boostphase propellant burns itself out, the sustainingpropellant sustains the motor in flight over the designedburning time (range of the missile).

REVIEW NUMBER 2

Q1. List the major sections of guided missiles.

Q2. What section is considered the brains of themissile?

Q3. List the three types of homing systems.

Q4. If a missile gets its target illumination fromthe launching aircraft, what type of homingsystem does it have?

Q5. List the components of the armament section.

Q6. Describe the function of safety and arming(S&A) devices.

Q7. What are the two types of propulsion usedwith guided missiles?

Q8. Describe the basic difference between the twotypes of propulsion.

SERVICE GUIDED MISSILES

Missiles have been operational for several years.Still, research on missiles continuously produceschanges in the missile field. The missiles discussed inthis manual are presently operational.

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Sparrow III Guided Missile

The AIM-7F/M missile (fig. 3-6) is a supersonic,air-to-air DTRM, guided missile. It is designed to berail or ejection launched from an interceptor aircraft.The missile's tactical mission is to intercept and destroyenemy aircraft in all-weather environments. It isdesigned to be launched from the F-14 and F/A-18aircraft.

REVIEW NUMBER 2 ANSWERS

A1. Guidance, control, armament, and pro-pulsion are the major sections of guidedmissiles.

A2. The guidance section is considered the brainsof the missile.

A3. The three types of homing systems are active,semiactive, and passive homing.

A4. If a missile gets its target illumination fromthe launching aircraft, it is semiactivehoming.

A5. The armament section consists of thepayload, fuzing, safety and arming (S&A)devices, and target-detecting devices (TDDs).

A6. Safety and arming devices maintain theexplosive train of a fuzing system in a safecondition until the acceleration requirementis met after launch.

A7. The two types of propulsion used with guidedmissiles are atmospheric (air breathing) jetand thermal jet.

A8. The atmosphere jet depends on theatmosphere to supply the oxygen for properfuel burning, and the thermal jet contains itsown supply of oxygen and is independentfrom the atmosphere.

The AIM-7F/M missile is a semiactive missile.Missile guidance depends on RF energy radiated by thelaunching aircraft and reflected by the target.Excluding the radome, the missile body has foursectional tubular shells that house the major functionalcomponents. The four major functional components arethe target seeker, flight control, warhead, and rocketmotor. The overall length of the missile isapproximately 142 inches with a diameter of 8 inches.It weighs approximately 510 pounds. The missile isissued to the fleet as an all-up-round (AUR). The onlyassembly required at fleet level is the installation of thewing and fin assemblies, which are shipped in separateshipping containers.

The radome is ceramic and forms the nosepiece ofthe missile. It does not obstruct RF energy. It covers theRF head assembly of the target seeker and providesprotection against environmental damage.

The target seeker receives and interprets the radarenergy reflected from the target. Then it producessignals that are sent to the flight control section to direct

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Figure 3-6.—AIM-7F/M Sparrow missile.

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the missile to intercept the target or come within lethalrange of it.

The flight control consists of the autopilot and thehydraulic group. These function to provide controlsignals and mechanical energy to move the externalcontrol surfaces that guide the missile toward the pointof intercept, and to stabilize the missile in pitch, yaw,and roll.

The warhead is located between the target seekerand flight control section. The warhead isexplosive-loaded, and it contains the fuze, fuze boostercharge, and the safety and arming (S&A) device. It is acontinuous-rod type of warhead. At detonation, the rodsections expand into a continuous ring. Target kill isaccomplished by collision of the continuous ring withthe target. Detonation is triggered either by a fuze pulsefrom the target seeker at the nearest point of intercept ora fuze pulse from the flight control upon impact withthe target.

The DTRM attaches to the aft end of the missileflight control section. It is equipped with a SAFE/ARMigniter assembly that is manually locked in either theSAFE or ARMED position. This switch can only berepositioned with an arming key. When in the SAFEposition, the arming key cannot be removed. Thisswitch prevents accidental firing of the motor. It shouldnot be moved to the ARMED position untilimmediately before aircraft launch.

The control surfaces consist of four delta-shapedwing and fin assemblies. The wings and fins aredesigned for quick attachment and release without theuse of tools. The wing assemblies attach to the flightcontrol section, which controls their rotary motion toproduce the desired pitch, yaw, and roll. The tail finassemblies attach to fittings on the rear of the rocketmotor and provide stability to the missile.

Another series of the Sparrow III guided missile isthe RIM-7E and RIM-7H. These missiles aresurface-to-air guided missiles. They are used in someships in the ship's Basic Point Defense Surface MissileSystem (BPDSMS) and Improved Point DefenseSurface Missile System (IPDSMS), respectively. As anAviation Ordnanceman, your responsibility for thesemissiles is in the area of handling and stowage only.

For further information concerning the Sparrow III(series) missiles, refer to publication Organizational,Intermediate, and Depot Maintenance InstructionManual with Illustrated Parts Breakdown, NAVAIR01-265GMAD-9-3 (series) and NAVAIR 11-140-6Airborne Weapons Assembly Manual.

Harpoon Guided Missile

The Harpoon surface attack guided missile,AGM-84 series (AGM-84/C/D Tactical) air-launchedmissile (fig. 3-7), is an all-weather antiship attackweapon. The SLAM tactical missile (fig. 3-7),AGM-84E, is a standoff land attack missile. TheHarpoon can be delivered from the F/A-18, P-3, andS-3 aircraft. Both missiles are AURs and require noassembly other than installation of the wing and controlfin assemblies. The missile consists of the guidancesection, warhead section, sustainer section, boattailsection, wings, and control fins. The missile isapproximately 151 inches in length and weighsapproximately 1,144 pounds.

The Harpoon missile has a low-level cruisetrajectory with over-the-horizon range that makes itless susceptible to radar detection. It uses activeguidance and has counter-countermeasure capability.

The guidance section contains the seeker, radaraltimeter, midcourse guidance unit, and power supply.A radome on the front of the guidance section providesthe required aerodynamic shield to protect the internalcomponents of the seeker. During ground handling, aradome protector cap protects the radome.

The warhead section contains a penetration blasttype of explosive, the guided missile fuze, fuze booster,and the pressure probe assembly. It also providesinternal routing of the interconnecting cable from theguidance section to other parts of the missile.

The sustainer section contains the fuel tank and fuelsupply system, missile battery, pyrotechnic relay panel,and the turbojet engine. Three BSU-4/B missile wingsand one BSU-43/B missile wing are attached to thesustainer section by quick-attach, clevis-type fittings.These wings are attached to the missile at theorganizational level. They provide the aerodynamic liftrequired sustaining missile flight. They are made of aframed aluminum honeycomb construction and arenonfolding.

The boattail section contains four control actuators,which control the control fins. Four identicalnonfolding missile control fins (BSU-44/B) providedirectional control of the missile's airframeproportional to the input signal received from theguidance section. The control fins are one-piecealuminum castings, and are attached to the control finactuators by means of an integral torque-limiting,screw-type device.

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For further information concerning theair-launched AGM-84 (series) Harpoon guidedmissiles, refer to the publications Airborne WeaponsAssembly, NAVAIR 11-140-6.2-4, and AirborneWeapons Assembly, AGM-84/E, NAVAIR11-140-6.2-5.

Sidewinder Guided Missile

The Sidewinder guided missiles, AIM-9 series (fig.3-8), are supersonic, air-to-air weapons with passive

infrared target detection, proportional navigationguidance, and torque-balance control systems. They arecapable of being launched from the F-14 and F/A-18aircraft. The AIM-9 series missiles are issued to thefleet as AURs. The components of the ATM-9L-1 areidentical to the AIM-9L/M except that a trainingwarhead is substituted for the tactical warhead in theATM-9L-1. The AIM-9L/M missile is used strictly fortactical purposes. The ATM-9L-1 missile is used forpilot training in target acquisition and missile firing.

3-10

Figure 3-7.—AGM-84 series Harpoon/SLAM guided missile.

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The Sidewinder guided missile is approximately113 inches in length, 5 inches in diameter, weighsapproximately 190 pounds, and consists of five majorcomponents. These components are the guidance and

control section, the target detector section, the S&Adevice, the warhead section, and the rocket motorsection (fig. 3-9).

3-11

Figure 3-8.—AIM-9 series Sidewinder guided missile.

Figure 3-9.—AIM-9 series Sidewinder guided missile (exploded view).

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The guidance and control section consists of thefollowing three major assemblies:

1. An infrared seeker assembly, which is used fordetecting the target.

2. An electronic assembly, which is used forconverting detected target information totracking and guidance command signals.

3. A gas servo assembly (which consists of a gasgenerator, manifold, pistons, rocker arms,electrical solenoids, and thermal battery),where the electrical guidance commands areconverted to mechanical movement of thecontrol fins.

Four BSU-32/B control fins are mounted on theguidance and control section to provide aerodynamiclift and course alterations to the missile during freeflight. They are movable surfaces that are electricallycontrolled and pneumatically operated by the gas servoassembly. The missile's umbilical cable is also attachedto the guidance and control section. A shorting cap/dustcover must be installed on the umbilical connector at alltimes when the missile is not electrically connected tothe LAU-7 launcher. The umbilical cable provides thenecessary path for the exchange of electronic signalsbetween the missile and aircraft before missile launch.It also provides a connection to the launcher-mountedcooling gas supply, which prevents the electroniccomponents of the guidance and control section frombecoming overheated during operation before missilelaunch. The umbilical cable is sheared off at missilelaunch.

The target detector (TD) is a narrow-beam,active-optical, proximity fuze system. The purpose ofthe TD is to detect the presence of an air target withinthe burst range of the missile warhead and generate anelectrical firing signal to the S&A device.

The S&A device attaches to the target detector andis located between the TD section and the warheadsection. The S&A device contains an interrupted firingtrain that is aligned by an acceleration-arming device. Itcontains the necessary high explosives, switches, andcircuits to initiate detonation of the warhead.

The WDU-17/B warhead (used in the AIM-9Lconfiguration) is an annular blast fragmentationwarhead that consists of a case assembly, two boosterplates, an initiator, high explosive, and fragmentationrods. The explosive output from the S&A device istransferred through the initiator to the booster plates.The initiation is then transferred through theexplosive-loaded channels of the booster plates to thebooster pellets at each end of the warhead. Detonationof the booster pellets sets off the high explosive,causing warhead detonation.

The WDU-9A/B warhead (used in the ATM-9L-1configuration) is mechanically interchangeable withthe WDU-17/B tactical warhead. The WDU-9A/Bcontains a smoke-flash mix with CH-6 booster toprovide visual observation of the missile/target hit.

The Mk 36 Mod 7 rocket motor uses a single-grainpropellant. A nonpropulsive head closure located on theforward end of the motor tube, blows out if the motor isaccidentally ignited without the warhead installed,making the motor nonpropulsive (a fire hazard vice amissile hazard). The Mk 36 Mod 8 rocket motor isbasically identical to the Mod 7 motor except that theMod 8 motor is equipped with a safe-arm ignitionassembly. The purpose of this assembly is to preventaccidental or inadvertent rocket motor ignition. Thesafe-arm ignition assembly must be manually rotated tothe armed position before flight. This is accomplishedby the use of a hex-head T-handle.

Four Mk 1 Mod 0 or Mod 1 wings are attached tothe aft end of the motor tube. They provideaerodynamic lift and stability during flight. Each winghas a rolleron assembly that provides pitch, yaw, androll stabilization during free flight. When the missile isfired, the rolleron is uncaged by acceleration and is freeto move through its longitudinal axis during flight. Therolleron wheel is designed so that the passing airstreamcauses it to spin at a very high speed, thus acting as agyroscope, which helps to stabilize the missile andreduce roll during flight.

For further information about the AIM-9L/M andATM-9L-1 Sidewinder guided missile, you shouldrefer to the Sidewinder Guided Missile AIM-9L andTraining Missile, NAVAIR 01-AIM9-2 and AirborneWeapons Assembly Manual NAVAIR 11-140-6.

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Advanced Medium Range Air-to-Air Missile(AMRAAM)

The AMRAAM is an all-weather missile (fig.3-10). Aircraft currently scheduled to carry the missileare the F-14 and F/A-18 aircraft. The AIM-120 is anAUR that consists of a guidance section, armamentsection, propulsion section, and control section.

The guidance section consist of a radome, seekercomponents, electronics unit, inertial reference unit,target detection device, batteries, power converter, andrelated harnesses and hardware.

The armament section includes a WDU-33/Bfragmenting warhead, Mk-44 booster, and a FZU-49/Bsafe and arm fuze (SAF).

The propulsion section consists of a dual-thrust,solid propellant, low-smoke, rocket motor, a blast tubeand exit cone, and an arm/fire device (AFD).

The control section includes four independentlycontrolled electromechanical actuators, four thermalbatteries, a data link assembly, and associatedhardware. Gas pressure-operated mechanical locksduring ground handling and captive carry lock thecontrol surfaces in position. During launch, apyrotechnic gas generator creates enough gas pressureto unlock the control surfaces.

REVIEW NUMBER 3

Q1. Within the radome of the Sparrow III missile,what feature receives and interprets the radarenergy reflected from the target?

Q2. What part of the Sparrow III missile providescontrol signals and mechanical energy tomove external control surfaces that guide themissile?

Q3. To what part of the Sparrow missile is theDRTM attached?

Q4. Name the aircraft from which the Harpoonguided missile is launched.

Q5. The Harpoon missile is less susceptible toradar detection because

Q6. List the sections of the Harpoon missile.

Q7. Sidewinder missiles are equipped with____________ target detection.

Q8. List the five major components of theSidewinder missile.

Q9. By what means is the S&A device aligned?

Q10. What feature of the Sidewinder missile pro-vides aerodynamic lift and stability duringflight?

3-13

Figure 3-10.—AIM-120 AMRAAM guided missile.

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Phoenix Missile

The tactical AIM-54C Phoenix (fig. 3-11) is anair-launched, air-to-air guided missile that employsactive, semiactive, and passive homing capabilities.The AIM-54C is used as a long-range, air-interceptmissile launched from the F-14 aircraft. It is equippedwith the AWG-9 Airborne Missile Control System(AMCS). The missile can be launched in multiplemissile attacks, as required, against hostile forces. Amaximum of six AIM-54C Phoenix missiles can belaunched from a single aircraft, with simultaneousguidance against widely separated targets. In addition,the missile has dogfight, electronic counter-countermeasures (ECCM), and anticruise missilecapabilities.

The physical description of the Phoenix missile isextremely brief because it is classified as Secret. Theoverall length of the missile is 13 feet with a diameter of15 inches. It weighs approximately 1,020 pounds. Themissile consists of the guidance section, the armamentsection, the propulsion section, and the control section.The missile is an AUR. The wings and fins can bemounted or removed to facilitate handling.

Maverick Missile

The tactical AGM-65E Maverick (fig. 3-12) is alaser-guided, rocket-propelled, air-to-ground missile. It

is used against fortified ground installations, armoredvehicles, and surface combatants. Launch aircraft forthe Maverick is the F/A-18

The AGM-65E missile has two major sections—the guidance and control section and the center/aftsection. Four fixed wings are an integral part of thecenter/aft section, and four movable control surfaces(fins) are located at the aft section. These fins areinstalled or removed to aid in handling. The missile isissued to the fleet as an AUR. Installation of the fins isthe only assembly required at the organizationalmaintenance level.

The AGM-65E missile system has all the lasermissile features, including automatic terminal homingon laser energy reflected from the target, which isilluminated by a laser designator. The laser designatorcan be a ground device, either hand-held or tripodmounted. It can also be a stabilized airborne device,mounted either on a separate aircraft or on thelaunching aircraft. Additionally, the warhead provideskinetic penetration into earth-barricaded or concretefortifications and ships. The fuzing system allows aselectable detonation delay to optimize kill capability.

For further information on the AGM-65EMaverick, you should refer to Laser-Guided MissileAGM-65E (Maverick), NAVAIR 11-120-58.

3-14

Figure 3-11.—AIM-54 Phoenix guided missile (typical).

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HARM Missile

The AGM-88A high-speed antiradiation missile(HARM) (fig. 3-13) offers performance improvementsover the existing Standard ARM missile when used fordefense suppression and similar operations.

The HARM missile, in conjunction with thelaunching aircraft's avionics, detects, identifies, andlocates enemy radar, displays threat information, andcomputes target parameters. The HARM missile is 10inches in diameter, 194 inches long, and weighs 780pounds. The missile operates in three basic modes:

3-15

Figure 3-12.—AGM-65E Maverick missile.

Figure 3-13.—AGM-88 HARM missile.

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(1) self-protect (which attacks targets that poseimmediate threat to the aircraft), (2) target ofopportunity (which attacks discrete targets important tothe tactical situation), and (3) prebrief (missileprogrammed to the vicinity of known or expectedtargets, and to attack when lock-on is achieved).Launch aircraft for the HARM are the EA-6B andF/A-18.

Penguin Missile

The AGM-119B (fig. 3-14) is a fire and forget,antisurface ship, all-up-round (AUR) missile. Themissile uses inertial guidance and infrared (IR) homing.The AGM-119B is intended to be launched from theSH-60B LAMPS helicopter. It is the first helicopter-launched, air-surface, antiship missile system in theU.S. Navy inventory.

The missile launch assembly (MLA) contains themissile control system (MCS) and attaches to the wingpylon of the SH-60B LAMPS Mk III helicopter. Itprovides mechanical attachment points for the missilelaunch/release system (BRU-14 rack with twoAERO-1A adapters, which provide a 30-inchsuspension capability). The MLA, with BRU-14attached, carries and launches the Penguin missile oncommand.

REVIEW NUMBER 3 ANSWERS

A1. Within the radome of the Sparrow III missile,the target seeker receives and interprets theradar energy reflected from the target.

A2. The flight control section, which consists ofthe autopilot and hydraulic group, providesthe Sparrow III missile with control signalsand mechanical energy to move externalcontrol surfaces to guide the missile.

A3. The DRTM is attached to the aft end of themissile flight control section of the Sparrowmissile.

A4. The Harpoon guided missile is launched fromF/A-18, S3, and P-3 aircraft.

A5. The Harpoon missile is less susceptible toradar detection because of its low-levelcruise trajectory with over-the-horizonrange.

A6. The sections of the Harpoon missile includethe guidance, warhead, sustainer, and boat-tail sections.

A7. Sidewinder missiles are equipped withpassive infrared target detection.

A8. The five major components of the Sidewindermissile include the guidance and control

3-16

Figure 3-14.—AGM-119B Penguin missile.

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section, target detector section, S&A device,warhead section, and rocket motor section.

A9. An interrupted firing train that is aligned byan acceleration-arming device aligns theS&A device.

A10. Four Mk 1 Mod 0 or Mod 1 wings attached tothe aft end of the motor tube provideaerodynamic lift and stability to theSidewinder missile during flight.

REVIEW NUMBER 4

Q1. List the homing capabilities incorporatedinto the Phoenix missile.

Q2. How many Phoenix missiles can be launchedfrom a single aircraft?

Q3. List the sections of the Phoenix missile.

Q4. List the types of targets the Maverick missileis used against.

Q5. How does the laser guidance system work inthe Maverick missile?

Q6. Name the three basic modes of HARM missileoperation.

Walleye Guided Weapon

The Walleye guided weapon does not contain apropulsion system, as do guided missiles. It is included

in this chapter because it contains a guidance system, acontrol system, externally mounted control surfaces,and is listed in the Air Launched Guided Missiles andComponents section of Navy Ammunition LogisticCode TW010-AA-ORD-010, NAVAIR 11-1-116A.

The Walleye guided weapon system (fig. 3-15) isdesigned to deliver a self-guided, high explosiveweapon from an attack aircraft to a surface target. TheWalleye weapon is issued to the fleet as an AUR. Theonly assembly required at the organizationalmaintenance level is the installation of the wings andfins.

The weapons are grouped into four basicseries—Walleye I (small scale), Walleye I extendedrange data link (ERDL), Walleye II (large scale), andWalleye II ERDL. Note that the Walleye II and WalleyeII ERDL weapons are larger in diameter and length andweigh more than the Walleye I weapon. The Walleye IIERDL weapon also has larger wings. A Walleyeweapon representative of each basic series is discussedin this chapter.

WALLEYE I.—The Mk 21 Walleye I tacticalweapon consists of a guidance section, a warheadsection (including the fuze and fuze booster), a controlsection, four wings, and four fins. The weapon hasprovisions for 14- and 30-inch suspensions, and anejector foot pad that is used to adapt the weapons tovarious types of aircraft bomb racks. The Walleye I(series) weapons are in the 1,000-pound class weaponcategory.

3-17

Figure 3-15.—Walleye guided weapon (typical).

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To form a typical attack situation, the weapon,pilot, and aircraft must perform as a complete weaponssystem. The weapon uses aircraft electrical power (viaan umbilical cable that connects the weapon to theaircraft) from the time electrical power is applied to theaircraft until the aircraft reaches a speed ofapproximately 180 knots. The automatic powerchangeover circuit in the weapon then switches theweapon to ram air turbine (RAT) generator power.

Basically, the guidance section of the weapon andthe aircraft system form a closed-circuit televisionsystem. A television camera mounted in the nose of theguidance section provides a picture of the area forwardof the aircraft and displays this information on atelevision monitor located in the cockpit of the aircraft.Additional circuits provide a cross-hair grid on thepilot's television monitor, which is a pair of vertical anda pair of horizontal lines. This intersection of horizontaland vertical cross hairs (the square in the middle)defines the tracking area. By looking at the video scenedisplayed on the television, the pilot is able to boresightthe weapon and aircraft to acquire the target, initiatelock-on, and confirm weapon tracking.

After boresighting the weapon, selecting the properfuze option, and achieving satisfactory lock-on, thepilot initiates release and escapes the target area. Theweapon continues to track the target until it reaches thepoint of impact.

The Walleye I Mk 27 practice weapon is identicalto the Mk 21 weapon except for the warhead andcontrol sections. The warhead is entirely inert, does notcontain a fuze or fuze booster, and has ballast tomaintain weapon CG (center of gravity) compatibilitywith the Mk 21 weapon. This weapon is used forcaptive-flight pilot training and for aircraft loading andground handling training purposes.

For further information concerning the Walleye Iguided weapon, you should refer to the Walleye IGuided Weapon, NAVAIR 01-15MGA-1.

WALLEYE I ERDL.—The Walleye I extendedrange data link (ERDL) guided weapon consists of thesame basic items as the Walleye I. These weapons aredesigned to be used in conjunction with theAN/AWW-13 data pod. They permit target informationto be transmitted between the weapon and data podbefore and after release of the weapon.

WALLEYE II.—The Mk 5 tactical Walleye IIguided weapon consists of a guidance section, a fairingassembly, a warhead section (including the fuze andfuze booster), a control section, four wings, four fin

adapters, and four fins. The weapon has provisions for30-inch suspension only, and is in the 2,000-poundclass weapon category. The Walleye II (series) weaponsare essentially the same as the Walleye I weaponsexcept they are physically larger in size and haveimproved electronics. Functional operations of theweapon and delivery tactics are basically the same asWalleye I.

For further information concerning the Walleye II(series) weapons, you should refer to the GuidedWeapon (Walleye II), NAVAIR 01-15MGB-2.2.

WALLEYE II ERDL.—The Walleye II extendedrange data link (ERDL) guided weapon Mk 23 Mods 0,1, and 2 (frequency channels A, C, and E) consists ofthe same basic items as the Walleye II Mk 5 weapons.However, these assemblies include added data linkfunctions and extended range capability. The additionof the larger wings enables the weapon to be launchedwith longer slant ranges to a target complex. Theaddition of the data-link pod (Guided WeaponControl-Monitor Set AN/AWW-9/13) and a joystickcontroller (guided weapon control groupOK-293/AWW) on the aircraft allow the pilot toremotely steer the weapon to a specific target within thecomplex with pinpoint accuracy.

The Guided Weapon Control-Monitor SetAN/AWW-9/13, data-link pod (fig. 3-16) is thecommunications link between the pilot and the weapon.The pod is suspended from a standardWalleye-configured bomb rack. It can be jettisoned inan emergency. The pod contains the necessaryelectronics to allow the pilot to receive the transmittedvideo from the weapon and to transmit the commandsignals to the weapon. In addition, the pod contains avideo tape recorder (VTR) that record the videotransmitted by the weapon all the way to impact on thetarget. This allows low-cost weapon performancemonitoring, which can be played back for missionevaluation or for training purposes.

REVIEW NUMBER 4 ANSWERS

A1. The Phoenix missile use active, semiactive,and passive homing.

A2. Six Phoenix missiles can be launched from asingle aircraft.

A3. The Phoenix missile consists of the guidance,armament, propulsion, and control sections.

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A4. The Maverick missile is used against fortifiedground installations, armored vehicles, andsurface combatants.

A5. The Maverick missile has automatic terminalhoming on laser energy reflected from thetarget, which has been illuminated by a laserdesignator.

A6. The three basic modes of HARM missileoperation are self-protect, target ofopportunity, and prebrief.

The weapon system may be used in one- ortwo-aircraft operations. In a single aircraft operation,the aircraft carries both the weapon and the pod, and theaircraft perform both launch and control functions. Inthe two-aircraft operation, one aircraft carries theweapon and a second aircraft carries the pod. In thisoperation, both the launch aircraft and the pod aircraftreceive a video picture of the target area from theweapon. After weapon launch, the pod aircraftmonitors the flight of the weapon and can update theweapon aim point all the way to impact.

Tactically, the two-aircraft operation dominatesbecause of the limited number of available pods. Forexample, a one-pod configured aircraft monitors theweapon control functions for several individual weaponlaunchings during one mission (not simultaneously).The three frequency channels (A, C, and E) are used tocontrol the individual weapons launchings. The threechannels prevent the control section of the weaponfrom responding to override (steering) commands froma pod that is not set to that weapon's specific frequency

channel. Therefore, more than one weapon/podoperation can be conducted in the same area.

The Walleye II ERDL Mk 38 series (frequencychannels A, C, and E) practice guided weapon is usedfor captive flight and data-link training for pilots of datalink configured F/A-18 aircraft. The practice-guidedweapon contains the same data link components as thetactical Walleye II ERDL Mk 23 weapon except that thewarhead in the Mk 38 is filled with inert material.

REVIEW NUMBER 5

Q1. Name the four basic series of Walleye guidedweapon systems.

Q2. List the sections of the Walleye I tacticalweapon.

Q3. When the Walleye I is used, how is a typicalattack situation formed?

Q4. What type of suspension does the Walleye IIhave?

Q5. What is the difference between the Walleye Iand Walleye II weapons?

Q6. Name the functions the Walleye II ERDL havethat the Walleye I and Walleye II don't have.

Q7. The data-link pod provides the_______________.

Q8. What prevents the control section of oneweapon from responding to commands not setto its channel?

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Figure 3-16.—AN/AWW-9/13 advanced data-link pod.

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GUIDED MISSILE LAUNCHERS

LEARNING OBJECTIVE: Describe thepurpose and use of guided missile launchers.Identify the components of the LAU-7/A(series) guided missile launcher.

Guided missile launchers provide the mechanicaland electrical means of suspending and air-launching aguided missile from an aircraft. Because the physical,mechanical, and functional requirements vary for eachparticular missile-to-aircraft configuration (table 3-2),a brief description of each type of missile launcher isdiscussed in the following paragraphs.

LAU-7/A (SERIES) GUIDED MISSILELAUNCHER

The LAU-7/A (series) guided missile launcher (fig.3-17) is a reusable launcher that provides a completelaunching system for use with the AIM-9 Sidewinder(series) missiles. The launcher (fig. 3-17) has fourmajor assemblies—the housing assembly, nitrogenreceiver assembly, mechanism assembly, and powersupply.

Housing Assembly

The housing assembly is the main structuralmember of the launcher. It is an extruded, machined

aluminum member that provides structural rigidity tothe launcher and includes provisions for mounting allother assemblies. It also includes provisions formounting the launcher to the aircraft.

Nitrogen Receiver Assembly

The nitrogen receiver assembly stores thehigh-pressure nitrogen (3,200 psig) used to cool themissile's IR detector in the guidance system. Twonitrogen receiver assemblies are available for use withthe launcher. One is a cylindrical fiber glass containerwith a corrosion-resistant metal liner, and the other is aplain cylindrical steel container. The receiver mounts inthe aft section of the housing assembly and screws intothe aft end of the mechanism assembly. All receiverscontain a charging valve (for refilling), relief valve, anda pressure indicator mounted in the aft end of thecylinder. The pressure indicator is color coded to ensurecorrect readings as follows:

• Red 0 to 2.2 psi

• Yellow 2.2 to 2.8 psi

• Green 2.8 to 3.5 psi

• White 3.5 to 5 psi

All readings listed must be multiplied by 1,000 psi.

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LAU-7/A AIM-9 SIDEWINDER RAIL F-14, F/A-18

LAU-92 AIM-7 SPARROW EJECTOR F-14

LAU-93 AIM-54A/C PHOENIX EJECTOR F-14

LAU-132 AIM-54C PHOENIX EJECTOR F-14D

LAU-115/A AIM-7 SPARROW RAIL F/A-18

LAU-115A/A AIM-120 AMRAAM RAIL F/A-18

LAU-116/A AIM-7 SPARROW EJECTOR F/A-18

LAU-116A/A AIM-120 AMRAAM EJECTOR F/A-18

LAU-117/A(V)2/A AGM-65 MAVERICK RAIL F/A-18

LAU-118/A AGM-88 HARM RAIL EA-6B, F/A-18

LAU-127 AIM-120 AMRAAM

AIM-9 SIDEWINDER

RAIL F/A-18

LAU-138 AIM-9

BOL CHAFF

RAIL F-14D

Table 3-2.—Missile Launcher Application

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REVIEW NUMBER 5 ANSWERS

A1. The four basic series of Walleye guidedweapon systems are the Walleye I, Walleye IEDRL, Walleye II, and Walleye II ERDL.

A2. The sections of the Walleye I tactical weaponinclude the guidance section, warheadsection, control section, four wings, and fourfins.

A3. When the Walleye I is used, a typical attacksituation is formed by the weapon, pilot, andaircraft performing as a complete weaponssystem.

A4. The Walleye II has a 30-inch suspension.

A5. The Walleye I and Walleye II weapons arebasically the same; however, the Walleye II isphysically larger and has improved elec-tronics.

A6. The Walleye II ERDL has added data linkfunctions and extended range capability.

A7. The data-link pod provides the com-munications link between the pilot andweapon.

A8. Three frequency channels (A, C, and E)prevent the control section of one weaponfrom responding to commands not set to itschannel.

3-21

FORWARD FAIRINGASSEMBLY

FORWARDFAIRING DOORS

ATTACHMENT BOLTS ANDTHREAD PROTECTORS

FORWARD PYLONADAPTER ASSEMBLY

SHIPPINGSCREW

AFT PYLONADAPTER ASSEMBLY

UMBILICAL HOOKSUPPORT ASSEMBLY

(HIDDEN)

FIN RETAINERASSEMBLY

(1 PER SIDE)

RETAININGSCREW

SLOTTED DETENTWRENCH/SAFETY PIN

DETENT HOLD-DOWN PIN(WITH LANYARD)

HOUSINGASSEMBLY

AFT FAIRINGASSEMBLY

AFT FAIRINGLATCH ASSEMBLY

AFT SNUBBERMOUNT FITTING

ASSEMBLY (HIDDEN)

BLAST SHIELD

MISSILEEXHAUST SPOILER(LAU-7/A-5 ONLY)

POWER SUPPLY

MECHANISMASSEMBLY

NITROGEN RECEIVERASSEMBLY

AOf0317

Figure 3-17.—LAU-7/A (series) guided missile launcher.

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Mechanism Assembly

The mechanism assembly is an electromechanicaldevice that holds the missile for takeoffs and landingsand releases the missile for launching. It mounts in thecenter of the housing assembly forward of the receiverassembly. The subassemblies of the mechanismassembly are discussed in the following paragraphs.

ELECTRICAL HARNESS ASSEMBLY.—Theelectrical harness assembly consists of the appropriateconnectors and wiring to interconnect between theaircraft power and firing circuits and the launcher. Also,the nitrogen system supply tube is routed through theelectrical wiring harness to the power supply.

DETENT, DETENT LOCK, DETENT-LOCKSOLENOID, AND SNUBBERS.—The detent, detentlock, detent-lock solenoid, and forward snubbers (fig.3-18) make up an electromechanical system thatrestricts longitudinal and lateral motion of the mountedmissile. This system prevents accidental launch orrelease during catapult takeoff or arrested landings. Aslotted detent wrench/safety pin is installed through themechanism assembly to prevent movement of the aftdetent and to safe the launcher firing circuits. It is alsoused to raise the aft detent lug sufficiently to clear themissile hanger during loading. The slotted detent

wrench/safety pin is removed before flight. When thedetent is down (normal), the striker points make contactwith the buttons (contacts) on the forward hanger of themissile. The forward striker point does not have afunction for the missile; the aft striker point makescontact between the missile and the firing safety switch.

NITROGEN CONTROL VALVE.—Thenitrogen control valve is a solenoid-operated shutoffvalve that controls the flow of nitrogen from thereceiver assembly to the missile. The pilot controlsoperation of the control valve from the cockpit.

Power Supply

One power supply is available for use in thelauncher. Power supply PP-2581/A is a single-phasepower supply. It is a self-contained unit with connectorson each end. The aft connector links the power supplyand the mechanism assembly. The forward connectorprovides the connection to the missile's umbilical cable.

Forward Fairing Assembly

The forward fairing assembly is an aluminumcasting that mounts to the forward end of the outerhousing to provide an aerodynamic nose to the front of

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AFT DETENT LUG

AFT STRIKER POINT

STRIKER POINT BUSHINGS

FORWARDSTRIKER POINT

FORWARDDETENT LUG

FORWARDSNUBBERS

DETENT LOCKING BAR

NOTE: 1. MECHANISM ASSEMBLY SHOWN REMOVEDFROM LAUNCHER AND COMPRESSED FOR CLARITY.

AOf0318

Figure 3-18.—Mechanism assembly detent and snubbers.

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the launcher. It has two doors that are spring-loaded toopen. These doors provide access to the umbilical hooksupport assembly.

Umbilical Hook Support Assembly

The umbilical hook support assembly mounts tothe forward housing rails and, during missile loading, isconnected to the missile umbilical shear block. Atmissile launch, the mechanism snaps up, retracting thesheared end of the umbilical cable into the launcher toprevent interference with the missile hangers.

Fin Retainer Assemblies

Two fin retainer assemblies are mounted to theforward end of the housing assembly beneath theforward fairing assembly. The fin retainer is a small,U-shaped bracket that contains two spring retainers thatsnap over the missile fins to prevent movement duringcaptive flight.

Snubber Mount Fitting Assembly, Aft FairingLatch Assembly, and Aft Fairing Assembly

The aft snubber mount fitting assembly, aft snubberassembly, and aft fairing latch (fig. 3-19) are assembledtogether as a group and mounted to the aft end of the

housing assembly. When the aft fairing latch assembly(fig. 3-20) is in the open position, you can access thenitrogen receiver. It also releases the aft snubbers toallow missile loading. When in the closed position, itallows the snubbers to spring over the aft missilehanger, locking it in place.

For further information on the LAU-7/A (series)guided missile launcher, refer to Guided MissileLauncher LAU-7/A, NAVAIR 11-75A-54.

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Figure 3-19.—Aft snubber mount fitting assembly, aft fairing assembly, and aft fairing latch assembly.

Figure 3-20.—Aft fairing latch assembly.

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REVIEW NUMBER 6

Q1. What missile launcher is used to carry andlaunch the Sidewinder missile?

Q2. List the four major assemblies of the LAU-7/Alauncher.

Q3. What is the purpose of the nitrogen receiverassembly?

Q4. What is the purpose of the detent, detent lock,detent-lock solenoid, and snubbersubassemblies of the mechanism assembly?

Q5. What does the LAU-7/A guided missilelauncher provide?

LAU-115 SERIES GUIDED MISSILELAUNCHER

The LAU-115 series guided missile launcher (fig.3-21) is a reusable launcher. It completes the F/A-18aircraft suspension and launching system for theAIM-7 Sparrow missile. The technical characteristicscan be found in (table 3-3). The forward internalgrooves of the rail provide a guide and support for the

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Figure 3-21.—LAU-115A/A, LAU-115B/A, and LAU-115C/A guided missile launchers.

LAU-115/A LAU-115A/A LAU-115B/A LAU-115C/A

Weight: 52 pounds Weight: 59 pounds Weight: 59 pounds Weight: 120 poundsHeight: 7 inches Height: 7 inches Height: 7 inches Height: 10 inchesWidth: 7 inches Width: 7 inches Width: 7 inches Width: 7 inchesLength: 78 inches Length: 82 inches Length: 82 inches Length: 82 inches

Table 3-3.—LAU-115 Technical Characteristics

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forward missile-mounting button. The external railflanges are a guide for the aft missile suspension lugsduring firing. The aft section of the rail consists of aremovable fitting that provides mounting for the aftmissile suspension lugs.

REVIEW NUMBER 6 ANSWERS

A1. The LAU-7/A missile launcher is used tocarry and launch the Sidewinder missile.

A2. The four major assemblies of the LAU-7/Alauncher include the housing, nitrogenreceiver, mechanism, and power supply as-semblies.

A3. The nitrogen receiver assembly is used tostore high-pressure nitrogen (3,200 psig) thatis used to cool missile IR detector guidancesystems.

A4. The detent, detent lock, detent-lock solenoid,and snubber subassemblies of the mechanismassembly are an electromechanical systemthat restricts longitudinal and lateralmovement of mounted missiles. This preventsaccidental launch or release during catapulttakeoffs or arrested landings.

A5. The LAU-7/A guided missile launcherprovides a complete system that lets the pilotmonitor the condition of the missile duringflight, control mode of operation of themissile guidance system, and initiate armingand launch sequence.

The latch mechanism is composed of a detent camand keeper. The detent cam is spring-loaded down and

acts as a stop during missile loading. The cammechanism is constructed so the force created by themissile motor during normal missile firing overcomesthe detent cam spring tension. This action lets themissile button push the detent cam up, actuating themissile-gone switch.

An electrically operated solenoid is used to assurethat the missile is retained during sudden deceleration,such as an arrested landing. The keeper portion of thelatch mechanism is spring-loaded to the down positionand retains the missile during all periods of aircraftacceleration. The keeper mechanism has an indicator.When the keeper is in the down or latched position, theindicator is flush with the launcher skin. If, duringmissile loading, the missile button is not in itsmaximum forward position, the indicator extendsbeyond the upper launcher mold line. This indicatesthat the missile is not properly latched in place. Duringloading, the missile button can slide past the keeper,stopping when contact is made with the detent cam.

During the unloading of a missile, the indicator bellcrank is supported in the launcher structure. Using a3/8-inch square drive tool manually operates it. Thesquare drive end of the bell crank is accessible from theside of the launcher. The launchers are suspended fromBRU-32 bomb racks in the outboard pylons. TwoLAU-7/A launchers can be attached for suspension ofthe AIM-9 missiles. For ground safety, anactuator-operated safety device prevents inadvertentloss of the AIM-7 missile.

LAU-116/A GUIDED MISSILE LAUNCHER

The LAU-116/A guided missile launcher (fig.3-22) is a reusable launcher of the F/A-18 aircraft

3-25Figure 3-22.—LAU-116/A guided missile launcher.

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suspension and launching system for the AIM-7Sparrow missile. The launchers are mounted internallyin the fuselage structure. They are self-contained,gas-operated mechanisms, capable of suspending andejecting the AIM-7 Sparrow missile. Two CCU-45impulse cartridges ignited by an electrical impulseapplied by the missile-firing switch, supply ejectionforce. The rapidly expanding gases actuate the ejectorpistons and release the missile from the launcher.Power is applied to the missile guidance control systemthrough the umbilical plug. An actuator-operated safetydevice prevents inadvertent firing of launchercartridges.

LAU-117/A GUIDED MISSILE LAUNCHER

The LAU-117/A guided missile launcher (fig.3-23) is a reusable launcher that completes the F/A-18aircraft suspension and launching system for theMaverick, AGM-65, air-to-ground missile. Themechanical structure of the launcher is built around abox-section channel or rail, which supports the missile.The missile hooks contact the rail surfaces or tracks,which are hard, anodized metal treated with a drylubricant. Two lug fittings and lugs provide mechanicalinterface with the bomb rack. The two lug fittingsprovide smooth surfaces for the bomb rack swaybraces. The missile restraint device is recessed into therail channel between the lug fittings. A stop on one sideof the rail track engages the missile aft hook to preventdamage to the umbilical connector during loading. Therear of the rail channel provides mounting for the

launcher electronic assembly and the umbilicalengaging assembly. The launcher electronic assemblyhouses all electronic circuitry. Fairings at the front ofthe rail and the rear of the launcher electronic assemblyprovide aerodynamic surfaces. Special brackets andbushings are provided for the Navy's single hoistordnance loading system. The launcher can besuspended from the BRU-32 bomb rack on the inboardand outboard pylons. An electrically operated safetydevice prevents inadvertent loss of the missile.

LAU-118/A GUIDED MISSILE LAUNCHER

The LAU-118/A guided missile launcher (fig.3-24) is a reusable launcher that completes the F/A-18and EA6B aircraft suspension and launching system forthe HARM, AGM-88, air-to-ground guided missile.The launcher consists of the launcher housing, forwardand aft fairing assemblies, forward and aft launchertracks, suspension lugs, insert plugs, and internalelectrical components. The launcher is a structurallymodified Aero 5B-1. The LAU-118/A is suspendedfrom the BRU-32 bomb rack on the inboard andoutboard pylons. An electrically operated retentionmechanism prevents inadvertent loss of the missile.

LAU-92/A GUIDED MISSILE LAUNCHER

The LAU-92/A guided missile launcher (fig. 3-25)carries and launches the AIM-7 (series) Sparrowguided missile on the F-14 aircraft. The launcher isinstalled in semisubmerged fuselage stations 3, 4, 5,

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Figure 3-23.—LAU-117/A guided missile launcher.

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Figure 3-24.—LAU-118 guided missile launcher.

Figure 3-25.—LAU-92/A guided missile launcher.

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and 6. It is retained on the weapons rail by means offour hooks, which are operated by a latch mechanism.The launcher can also be installed on thewing-mounted, multipurpose pylon by using anLAU-92/A adapter. The launcher components areaccessible by means of a door in the adapter.

LAU-93/A GUIDED MISSILE LAUNCHER

The LAU-93/A guided missile launcher (fig. 3-26)carries and launches the AIM-54 Phoenix missile, andis installed on the weapons rail of the F-14 aircraft. Thelauncher provides electrical and coolant connections

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Figure 3-26.—LAU-93/A guided missile launcher.

Figure 3-27.—ADU-299/E missile launcher adapter.

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between the weapons rail and the missile. Themechanical components of the launcher consist of agas-operated, hook-opening linkage and two ejectors, aground safety lock and positive launch pin, coolant, andelectrical umbilical. The launcher can also be installedon the wing-mounted, multipurpose pylon by using anLAU-93/A adapter.

ADU-299/E MISSILE LAUNCHER ADAPTER

The ADU-299/E missile launcher adapter (fig.3-27) is used to adapt the LAU-7 missile launcher,providing Sidewinder missile capabilities. Mechanicalattachment of the adapter to the ejector rack is provided

by two suspension lugs on 30-inch centers. Mechanicalattachment of the adapter to the LAU-7 launcher isprovided by two swivel nuts positioned on 30-inchcenters to mate with the launcher bolts. When thelauncher and adapters are electrically connected andmechanically mated, an adapter harness from the wingpylon to the aft end of the adapter supplies electricalpower.

LAU-127 GUIDED MISSILE LAUNCHER

The LAU-127 guided missile launcher (fig. 3-28) isdesigned to carry and launch the AIM-120 series

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Figure 3-28.—LAU-127 guided missile launcher.

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AMRAAM missile. The LAU-127 will also be capableof launching the AIM-9 series sidewinder missile.

LAU-132 GUIDED MISSILE LAUNCHER

The LAU-132 guided missile launcher is similar inappearance and operation to the LAU-93 launcher. TheLAU-132 was developed for carriage and launch of theAIM-54C Phoenix missile on the F-14D aircraft.

REVIEW NUMBER 7

Q1. What missile launcher is used to carry anAIM-7 Sparrow missile on the outboard pylonof an F/A-18 aircraft/

Q2. What guided missile launcher completes theF/A-18 aircraft suspension and launchingsystem for the Maverick missile?

Q3. What missile is compatible with theLAU-118/A guided missile launcher?

Q4. What missile launcher is used to carry andlaunch the AIM-54 Phoenix missile on theF-14 aircraft?

GUIDED MISSILE HANDLING

LEARNING OBJECTIVE: Identify themethods used in guided missile handling afloatand ashore.

The establishment of the all-up-round (AUR)concept simplified the handling of guided missiles atthe user level. The AUR concept has improved thereliability, availability, and logistics support of currentguided missiles used by fleet activities.

NAD/NWS/NAWMUs

The service life of an AUR missile begins at a navalammunition depot (NAD) or a naval weapons station(NWS). The NAD or NWS receives the individualcomponents of a missile from the manufacturer. TheNAD or NWS assembles the components to make up acomplete round, performing the required operationalchecks and tests. The AUR is then packed into a missilecontainer and is stored as RFI (ready for issue). Themissile logbook is also packed inside the missilecontainer. The missile logbook is compiled from theoperational records that are received with eachcomponent. This logbook remains with the missile untilthe missile is either expended (fired) or disassembled.

Naval Air Weapons Maintenance Unit (NAWMUs)is assigned to areas close to overseas operating forces.Generally, they are located at a naval air station (NAS)or a naval magazine station (NAVMAGSTA). Thepurpose of NAWMUs is to upgrade missiles from anon-RFI (not ready for issue) status to an RFI status.This prevents the time-consuming and costly procedureof shipping non-RFI missiles from overseas operatingareas back to the United States for componentreplacement or scheduled checks and tests. This quickturnaround time increases missile availability todeployed operating units in the fleet.

AFLOAT

Under the AUR concept, missiles are receivedaboard ship in containers completely assembled exceptfor the wings and fins. Depending upon the particularmissile and the type of container involved the wingsand fins may or may not be shipped in the samecontainer as the missile. In most cases, the wings andfins are shipped in separate containers that containeither one complete set of wings and fins (4 wings and 4fins) or two sets of wings and fins (8 wings and 8 fins).

When containerized missiles, wings, and fins arereceived aboard ship, the containers are inspected forany obvious damage. When the inspection reveals adamaged container, it must be sent to the decanningarea to be opened for inspection of the missile or wingsand fins. When a container, missile, or wings and finsdo not meet the inspection criteria listed in theappropriate technical manual, they must be taggednon-RFI and kept separate from RFI material for laterturn-in. Missiles, wings, and fins can be either deepstowed in magazines still in their sealed containers, orthey can be decanned, inspected, and stowed instanchions located in ready-service magazines ormissile magazines. Missiles that are deep stowed intheir sealed containers can be off-loaded as RFI.However, when the seal has been broken and/or themissiles, wings, or fins removed from the container, themissiles, wings, and fins must be tagged non-RFI andoff-loaded to the appropriate NAD, NWS, or NAWMU.

When missiles are decanned for ready service, themissile logbooks are removed from the emptycontainers and turned in to the aviation ordnancecontrol station (AOCS), where they are kept on fileuntil the missile is fired (expended) or off-loaded.When the missile is fired, the missile logbook is mailedto the appropriate NAD or NWS. When the missile is tobe off-loaded, the logbook must be placed in the missilecontainer.

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ASHORE

Guided missile handling functions for naval airstations or shore-based squadrons are the same asshipboard functions except for the obvious differencein working environments. Space limitations are not ascritical ashore and allow for an increase in handlingcapability.

Other details of missile handling, such as MOAT(missile on aircraft test), supply procedures, missilesfiring reports, quality deficiency reports, and loadingprocedures, are discussed in the appropriate chaptersthroughout this manual.

REVIEW NUMBER 8

Q1. What concept simplified the handling ofguided missiles at the user level/

Q2. The responsibility for assembling individualmissile components into complete RFImissiles rests with ____________________.

Q3. What is the purpose of a Naval Air WeaponsMaintenance Unit (NAWMU)?

SAFETY PRECAUTIONS

LEARNING OBJECTIVE: Recognize thesafety precautions to follow when working withguided missiles.

Safety precautions have been established for eachparticular type of missile. All missile handling must becarried out according to the approved local safetyregulations of the ship, depot, or wherever the work isbeing done. All of the safety precautions cannot bediscussed in this chapter. However, some of the generalsafety precautions are as follows:

• Observe detailed precautions. Follow specificinstructions for each type of guided missile. Youwill find the specific instructions in the manualissued for each particular type of aircraft.

• Keep work areas clear of obstructions, loosecables, hoses, and any unneeded equipmentduring missile assembly and testing. Permit onlyassigned personnel engaged in the work in thearea or vicinity of the missile.

• Use only the authorized handling equipmentwith any missile, or any missile section,component, or related parts, including shippingcrates and containers.

• Make sure that all electrical equipment used inmissile handling operations is adequatelyshielded and grounded. Also, avoid injury fromsharp edges often present on nose assemblies,wings, and fins. After assembly, cover all sharpedges with protective covers.

• Use tools specified in the missile manual whenuncrating missile components and forassembling missiles. Do not force any unit. If itdoes not fit or function properly, determine thecause and correct it before proceeding.

• Before connecting igniters in missile motors,check the firing leads for stray or inducedvoltages and for static charges.

• Before handling any piece of ordnance material,inspect the safety device to be sure that it is in aSAFE position. If not, the unit must be madesafe by experienced personnel before furtherwork is performed.

• The wing servo units in many missiles aresupplied with primary power by means of anaccumulator charged from gas bottles (orcylinders) containing compressed air ornitrogen; both of which contain pressure. Useextreme caution when charging accumulatorsand when handling the gas bottles or containersin which the gases are stowed.

• When testing for leaks in a gas container, usesoapy water.

• When cleaning hydraulic units, use only thecleaning solvents or other materials specified inthe particular missile publication.

• Keep your hands and other parts of your bodyclear of exhaust vents when working with testequipment that uses high pneumatic pressure.

• When any hydraulic unit is disassembled forinspection or repair, make sure that theworkbench is thoroughly cleaned of dirt andmetal filings.

• Missile ordnance materials, including rocketmotors, igniters, fuzes, warheads, and in somecases boosters or auxiliary rockets, arepotentially dangerous. Handle each unitaccording to the specific procedures authorizedin the appropriate publication.

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• Load forward-firing ordnance in authorizedloading areas only, with aircraft facinguninhabited areas.

• When leading/handling forward-firing ord-nance, you should avoid working in front orbehind the ordnance.

REVIEW NUMBER 9

Q1. What solution is used to leak test gascontainers/

Q2. When handling forward-firing ordnance,what is the desired place you should work/

REVIEW NUMBER 7 ANSWERS

A1. The LAU-115/A series guided missilelauncher is used to carry an AIM-7 Sparrowmissile on the outboard pylon of an F/A-18aircraft.

A2. The LAU-117/A guided missile launchercompletes the F/A-18 aircraft suspension andlaunching system for the Maverick missile.

A3. The AGM-88 HARM missile is compatiblewith the LAU-118/A guided missile launcher.

A4. The LAU-93/A missile launcher is used tocarry and launch the AIM-54 Phoenix missileon the F-14 aircraft.

REVIEW NUMBER 8 ANSWERS

A1. The handling of guided missiles at the userlevel was simplified by the introduction of theall-up-round (AUR) concept.

A2. The responsibility for assembling individualmissile components into complete RFImissiles rests with naval ammunition depot(NAD) or naval weapons station (NWS).

A3. The purpose of a Naval Air WeaponsMaintenance Unit (NAWMU) is to upgrademissiles from a non-RFI to an RFI status.

REVIEW NUMBER 9 ANSWERS

A1. A soapy water solution is used to leak test gascontainers.

A2. When handling forward-firing ordnance, youshould work on the sides. Work in the front orrear of the ordnance should be kept to aminimum.

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