Manual Tehnic Pt Munitii

T M 4 3 - 0 0 0 1 - 3 0

T E C H N I C A L M A N U A L

A R M Y A M M U N I T I O N D A T A S H E E T S

F O R

R O C K E T S

R O C K E T S Y S T E M S

R O C K E T F U Z E S

R O C K E T M O T O R S

( F e d e r a l S u p p l y C l a s s 1 3 4 0 )

This copy is a reprint which includes current

pages from Changes 1 through 5.

— -—..—.

H E A D Q U A R T E R S , D E P A R T M E N T O F T H E A R M Y

D E C E M B E R 1 9 8 1

TM 43-0001-30C13

CHANGE ))

No. 13 )

HEADQUARTERSDEPARTMENT OF THE ARMY

Washington, DC, 12 October 1993

ARMY AMMUNITION DATA SHEETSFOR

ROCKETS, ROCKET SYSTEMS, ROCKET FUZES, ROCKET MOTORS(FSC 1340)

TM 43-0001-30, 1 December 1981, is changed as follows:

1. Remove old pages and insert new pages as indicated below. New or changed material is indicatedby a vertical bar in the margin of the page.

Remove Insert Pages

A (B blank) A and B3-11 thru 3-13 3-11 thru 3-14

2. File this change sheet in front of the publication for reference purposes,

By Order of the Secretary of the Army:


GORDON R. SULLIVANGeneral, United States Army

Official: Chief of Staff

MILTON H. HAMILTONAdministrative Assistant to the

Secretary of the Army0s467

To be distributed in accordance with DA Form 12-34-E, Block 0851, requirements for TM 43-0001-30.

TM 43-0001-30

L I S T O F E F F E C T I V E P A G E S INSERT LATEST CHANGED PAGES.DESTROY SUPERSEDED PAGES.

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 122CONSISTING OF THE FOLLOWING:

PAGE *CHANGE PAGENO. NO. NO.

Cover o 3-25 thru 3-27A and B 13 3-28 blanki and ii 10 3-29 thru 3-321-1 thru 1-4 0 3-33 and 3-342-1 thru 2-17 0 3-352-18 and 2-19 4 3-362-20 blank 0 3-37 thru 3-402-21 4 3-41 thru 3-442-22 7 3-45 and 3-462-23 and 2-24 0 4-1 thru 4-42-25 1 4-52-26 blank 0 4-6 blank3-1 thru 3-7 0 4-7 thru 4-93-8 thru 3-10 4 4-103-11 thru 3-14 13 4-11 thru 4-163-15 and 3-16 0 5-1 and 5-23-17 5 5-2.1 thru 5-2.63-18 blank 0 5-3 thru 5-143-19 thru 3-21 0 5-15 and 5-163-22 blank 0 A-1 and A-23-23 and 3-24 0 Authentication page

*CHANGENO.

1 000318123110900604401 000

* Zero in this column indicates an original page.

Change 13 A

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THIS PAGE INTENTIONALLY LEFT BLANK

B Change 13

Technical Manual

No. 43-0001-30

TM 43-0001-30

) HEADQUARTERS) DEPARTMENT OF THE ARMY) Washington, DC, 1 December 1981

ARMY AMMUNITION DATA SHEETSFOR ROCKETS, ROCKET SYSTEMS, ROCKET

FUZES, ROCKET MOTORS(Federal Supply Class 1340)

REPORTING OF ERRORS

You can help improve this manual, If you find any mistakes or know of a way toimprove the procedures, please let us know, Mail your DA Form 2028(Recommended Changes to Publications or Blank Forms), or DA Form 2028-2located in the back of this manual direct to Commander, U.S. Army ArmamentResearch, Development and Engineering Center, ATTN: SMCAR-LMB,Picatinny Arsenal, NJ 07806-5000. A reply will be furnished to you.

Paragraph Page

CHAPTER 1. INTRODUCTIONPurpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .... . . . . . . . . . . . . . . . . . . . . 1-1 1-1Scope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . 1-2 1-1Key to Abbreviations and Symbols . . . . . .. . . . .. . . . . . . . . . . . . . 1-3 1-1Metric Conversion Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1-3

CHAPTER 2. GROUND ROCKETSRocket, High-Explosive, 3,5 Inch: AT, M28A2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3Rocket, Practice, 3.5-Inch M29A2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7Rocket, Ground: 3.5-Inch Smoke (WP) M30 . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . 2-11Light Antitank Weapon (LAW) System M72 Series . . . . . . . . . . . . . . . . . . . . . 2-15Rocket, Heat, 66MM, M72, M72A1, M72A2, and

M72A3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . 2-17Rocket, Incendiary 66MM: TPA, M74 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21Rocket, Practice, 35MM, Subcaliber, M73 . . . . . .. . . ... . . . . . . . . . . . . . . . . 2-23

CHAPTER 3. AIRCRAFT ROCKETSComplete Rounds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Typical 2.75-Inch Aircraft Rocket (LSFFAR) . . . . . . . . . . . . . . . . . . . . . . . . .Rocket, Flechette, 2.75-Inch, WDU-4A/A . . . . . . . . . . . . . . . . . .. . . . . . . . . . . .Rocket, High-Explosive, 2.75 -Inch W/M151 Warhead . . . . . . . . . . . . . . . . . . . . . .Rocket, High-Explosive, 2.75-Inch W/M229 Warhead . . . . . . . . . . . . . . . . . .Rocket, Smoke, WP 2.75-Inch W/M156 Warhead . . . . . . . . . . . . . . . . . . . . . .Rocket, Practice, 2.75-Inch W/M230 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . .Rocket, Practice, 2.75-Inch W/Inert Warhead WTU-1/B . . . . . . . . . . . . . .Rocket, Flare, 2.75-Inch W/M257 Illuminating Warhead . . . . . . . . . . . . . . . . .Rocket, 2.75-Inch, Smoke Screening M259 . . . . . . . . . . . . . . . . . . . . . . . . . . .Rocket, Dual Purpose, 2.75-Inch HE W/Warhead, M247. . . . . . . . . . . . . . . . .Rocket, High-Explosive, 2.75-Inch, Multipurpose

Submunition (MPSM) W/M261 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . .

3-13-23-33-73-113-153-193-233-253-293-31

3-33

Change 10 i

TM 43-0001-30

Page

CHAPTER 3.

CHAPTER 4.

CHAPTER 5.

Paragraph

AIRCRAFT ROCKETS - ContinuedRocket, 2.75-Inch, Practice W/M267 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Grenade, General Purpose, HE: M73 Multipurpose

Submunition (MPSM), High-Explosive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Grenade, General Purpose, Practice: M75 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Rocket, Smoke, Signature, Practice, 2.75-Inch Warhead,

M724 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FUZES W/2.75-INCH ROCKETSFuze, Point Detonating, M423 (M407) . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Fuze, Rocket, Electronic Time, M433 . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . .Fuze, Rocket, Proximity M429 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Fuze, Practice, Rocket, M435 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Fuze, Rocket, M439, RC, Variable Time Delay Remotely

Settable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ROCKET MOTORSIntroduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1Rocket Motor Data . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2Rocket Motor MK22, Mod 2 . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . .Rocket Motor MK22, Mod 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . .Rocket Motor MK22, Mod 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Motor, Rocket MK40, Mod 3 . . . . . . . . . . . . . . . . . . . . . . . . . .. . . .. . . . . . . . . . . . . . . . . . . . . . . .Rocket Motor (JATO) M3A2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Rocket Motor (JATO) M8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . .Rocket Motor MK66, Mods 0, 1, 2, or 3 . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . .

3-37

3-413-43

3-45

4-34-74-94-11

4-13

5-15-15-2.15-2.35-2.55-35-75-115-15

APPENDIX A. REFERENCES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-1

i i Change 10

T M 4 3 - 0 0 0 1 - 3 0

CHAPTER 1

INTRODUCTION

1 - 1 . PURPOSE:

a This manual provides general andtechnical information concerning groundand aircraft rockets. It covers generalcharacteristics, specific data, means ofidentification, precautions and general in-formation on packing. General informationpertaining to all types and kinds of conven-tional ammunition and explosives, and colorcoding for earlier manufactured munitionsare contained in Technical Manual (TM)9-1300-200. General information on care,handling, preservation, storing, shippingand destruction of ammunition and explo-sives is contained in TM 9-1300-206, In-formation on training of troops in tacticaluse of 3.5-in. rockets will be found

rockets in FM 23-33.on 66-mm

b The rockets and components de-scibed in chapters 2 and 3 belong toFederal Supply Class 1340. Other itemsused in conjunction with the rockets arecovered in other publications.

1 - 2 . SCOPE:

a For each item of materiel, there areillustrations and descriptions together withcharacteristics and related data. Includedin the related data are weights, dimensions,performance data, packing, shipping andstorage data, type classification, and logis-tics control codes (LCC).

b Information concerning supply, oper-ation, and maintenance of items will befound in the publications referenced forthose items, A complete listing of these

publications is maintained in Departmentof the Army (DA) Pam 310-series indexes,

c . Within this manual, items with thefollowing type-classifications are included:

(1) Standard (LCC-A, LCC-B),OTCM/AMC TC M

(2) Contingency (CON)

(3) Limited Procurement (LP)

(4) Reclassified obsolete (OBS)for regular Army use, but used by Nation-al Guard or Reserve units.

(5) Reclassified OBS for all Armyuse, but used by Marine Corps, Air Forceor Navy.

(6) Reclassified OBS, no users, butUS stocks remain. Items with the followingtype-classification are not included:

Reclassified OBS for all US use. NoUS stocks remain. (Foreign use or stockmay remain.)

d Numerical values, such as weights,dimensions, candlepower, etc., are nomi-nal values, except when specified as maxi-mum or minimum. Actual items may varyslightly from these values. Allowablelimits can be obtained from the drawingsindicated in the data sheets.

1 - 3 . KEY TO ABBREVIATIONS ANDSYMBOLS :

A P - - - - - - - - Armor piercingA P C - - - - - - - - Armor piercing capped

1 - 1

T M 4 3 - 0 0 0 1 - 3 0

APERS - - - - -AR - - - - - - --AT - -- - - - --BD - - - - - - --BE - - - - - ---CP - - - - - - --DA - - - - - - --DS - - - - - - - -FM - -- - - - - -FPS - - - - - - -FT - - - - - - --G's _ _ _ _ _ _ _ _

HE - - - - - - - -H E A T - T - M P - -

HEDP - - - - - -

H E I - - - - - - - -

HEP - - - - - - -HERA - - - - - -

HVAP - - - - - -

HVTP - - - - - -

Illum - - - - - - -JATO - - - - - -LAW - - - - - - -(LP)-T - - - - -LSFFAR - - - - -

Mod - - - - - - -MM - - - - - - --MPS - - - - - --MPSM - - - - - -

MS - - - - - - --

AntipersonnelArmy RegulationAntitankBase detonatingBase ejectionCandlepowerDepartment of the ArmyDiscarding sabotField manualFeet per secondFeetForce of GravityHigh explosiveHigh explosive antitankwith tracer, multi-purposeHigh explosive dualpurposeHigh explosiveincendiaryHigh explosive plasticHigh explosive, rocketassistedHypervelocity, armorpiercingHypervelocity, targetpracticeIlluminatingJet assisted take offLight antitank weaponTest (DODAC)Low-spin folding-finaircraft rocketModifiedMillimeterMeters per secondMultipurpose sub-munitionsMilliseconds

MT - - - - - - - -MTSQ _ _ _ _ _ _

MV - - - - - - --OBS - - - - - --PD - - - - - - - -PDSQ - - - - - - -

P I - - - - - - - - -PIBD - - - - - - -

Prox - - - - - - -PWP - - - - - - -

RAD - - - - - - -RAP - - - - - --

RC - - - - - - --RF - - - - - - - -RPS - - - - - --S&A - - - - - - -

S C - - - - - - - - -S D - - - - - - - - -See _ _ _ _ _ _ _ _

SM - - - - - - --SQ - - - - - - - -

T - - - - - - - - -

- T - - - - - - - -TB - - - - ----TM - - - - ----TP - - - - - - - -TSQ -- - - -- -

V X - - - - - - - - -

WP - - - - - - - -

Mechanical timeMechanical time andsuper-quickMuzzle velocityReclassified obsoletePoint detonatingPoint detonating super-quickPoint initiatingPoint initiating, basedetonatingProximityPlasticized whitephosphorousRam air deceleratorRocket assistedprojectileResistance capacitanceRadio frequencyRevolutions per secondSafety and arming deviceSupply catalogsSelf destroyingSecondsSupply manualSuper-quickTime fuze or fortraining onlyWith tracerTechnical bulletinTechnical manualTarget practiceTime super-quickPersistent toxic (casu-alty) nerve gasWhite phosphorous

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TM 43-0001-30

1-4. METRIC CONVERSION CHART:

For conversions to metric measures:

CONVERSION CHART

Symbol When You Know Multiply by To Find Symbol

LENGTH

in. inches 2.54 centimeters cm

ft feet 30.5 centimeters cm

yd yards 0.914 meters m

mi miles 1.61 kilometers km

AREA

2in square inches 6.45 square centimeters

2cm

ft2 square feet 0.093 square meters m 2

yd2 square yards 0.536 square meters m 2

2mi square miles 2.59 square kilometers k m2

acres 0.405 hectares ha

WEIGHT

OZ ounces 28.3 grams g

lb pounds 0.454 kilograms kg

short tons(20001b) 0.907 tonnes t

VOLUME

fl oz fluid ounces 29.6 milliliters ml

pt pints 0.473 liters 1

qt quarts 0.946 liters 1

gal gallons 3.79 liters 1

ft3cubic feet 0.028 cubic meters 3m

3yd3 cubic yards 0.764 cubic meters m

1-3

TM 43-0001-30


TEMPERATURE (exact)

°F Fahrenheit 5/9 (after sub- Celsius temperature °Ctracting 32)

For conversions from metric measures:


LENGTH

m m millimeters 0.039 inches in

cm centimeters 0.394 inches in

m meters 3.28 feet ft

m meters 1.09 yards yd

km kilometers 0.621 miles mi

AREA

2cm square centimeters 0.155

2

2square inches in

m square meters 1.20 square yards yd2

k m2square kilometers 0.386

2square miles mi

ha hectares (10, 000 m2) 2.47 acres

WEIGHT

g grams 0.035 ounces oz

kg kilograms 2.20 pounds lb

t tonnes (1000 kg) 1.10 short tons

VOLUME

ml milliliters 0.034 fluid ounces fl oz

1 liters 2.11 pints pt

1 liters 1.06 quarts qt

1 liters 0.264 gallons gal

m 3cubic meters 35.3 cubic feet ft3

m 3 cubic meters 1.31 cubic yards yd3

TEMPERATURE (exact)

°C Celsius 9/5 (then add 32) Fahrenheit temperature °Ftemperature

1-4

TM 43-0001-30

CHAPTER 2

GROUND ROCKETS

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TM 43-0001-30

ROCKET, HIGH-EXPLOSIVE, 3.5-INCH: AT, M28A2

Type Classification:

STD (LCC-B) OTCM 36841 Jul 58

Use:

The M28A2 HEAT rocket is usedprimarily against armored targets,tanks and secondary targets, such asgun emplacements, pillboxes and per-sonnel. It is capable of penetratingheavy armor at angles of impact greaterthan 30°. In an antipersonnel role, ithas a fragmentation area 10 yd wide and20 yd deep.

Description:

a. The warhead is cylindrical andtapered. The forward end, called theogive, is thin metal and hollow. Therear end, threaded internally to receivethe fuze which is encircled by a safefyband. The warhead contains a copper

cone whose apex faces aft and acts to shapethe high explosive charge Composition B -

(Comp B).

b . The base detonating (BD) rocketfuze M404A2 consists of a body which con-tains the functioning parts; a safety band,a detonator and a booster pellet. The fuzebody and safety band are olive drab. Thefuze mechanism consists of an activatingplunger, a setback spring, a setbacksleeve, a firing pin assembly, a detent spring, an ejection pin and an ejectionspring. The spring-loaded ejection pinpasses through the fuze body.

c . The motor assembly consists ofa tube which houses the propellant andigniter. The fin assembly is securely at-tached to this tube. The front end of thetube is assembled to the base of the fuze.The rear end forms a nozzle. The cylin-drical motor cavity is divided into four

2 - 3

TM 43-0001-30

sections by two spacer plates which sup-port the grains of propellant powder.

d . Each grain of propellant is5-in. long and approximately 3/8-in. indiameter. Three grains are placed ineach of the four sections formed by thespacer plates. Each lot of propellant isadjusted at the time of manufacture togive standard velocity. The igniter ig-nites the propellant.

e . The igniter consists of a short,cylindrical plastic case containing asmall black powder charge and an elec-trical squib. It is assembled in the for-ward end of the motor on top of the pro-pellant, spacer plates. The leads of theelectrical squib, running parallel to thegrains of propellant, pass from the ig-niter through the nozzle into the expan-sion cone. A green lead (ground) wireis connected to the aluminum supportring of the contact ring assembly. Ared lead (positive) wire is attached to apin which is insulated from the supportring, but is in contact with the coppercontact band. These connections arepositioned 180° apart. Blue lead is usedfor test purpose only.

f . The fin assembly consists of sixaluminum alloy fins and a contact ringassembly. The contact ring assembly,which encircles the fins, consists ofthree rings. The aluminum support ring,which is innermost, is separated fromthe copper contact ring by a plastic in-sulating ring, The fins are spot weldedto the expansion cone, and the expansioncone is press fitted to the rear of themotor tube. The M24 and the M66 off-route mines utilizing M28A2 HEATrockets are described in TM 43-0001-36.

Differences between Models:

The BD rocket fuze M404A1 is similarto BD rocket fuze M404A2. The M404A1differs principally in minor design changesof the functioning parts and the shape of thesafety band.

Functioning:

a . When the safety band is removed,the ejection pin moves outward approxi-mately 3/8 of an inch but still prevents allparts of the fuze mechanism from moving.When the rocket is in the firing chamber,the ejection pin is partially depressed bythe chamber, thereby freeing the setbacksleeve so it can move to the rear when therocket is fired. The fuze is still safe,since the ejection pin prevents movementof the actuating sleeve and firing pin.

b. If it becomes necessary to removethe rocket from the launcher, the ejectionpin will move outward and re-engage thesetback sleeve. This returns the fuze toits original safe condition.

c_. When the rocket is fired, the forceof inertia causes the setback sleeve to moverearward. It is held in its rearward posi-tion by the lockpin. When the rocket leavesthe muzzle of the launcher, the ejection pinis thrown clear of the fuze by the ejectionpin spring. The fuze is then fully armed.

d. During flight, tie firing pin leverand firing pin spring prevent the firing pinfrom striking the detonator, The creepspring retards the forward movement ofthe plunger and actuating sleeve. The ac-tion of the creep spring prevents the fuzefrom firing should the rocket strike lightobjects such as thin brush or undergrowth.

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TM 43-0001-30

e . Upon impact with a more resis-tant object, the plunger and actuatingsleeve move forward until the sleeve hitsthe firing pin lever. This causes thefiring pin to strike and detonate the war-head.

Tabulated Data:

Rocket:Model - - - - - -Type - - - - - - -Diameter - - - -Length (max) - -Weight - - - - -Performance:

Operatingtemperaturelimits - - - - -

Muzzle velocity(at 70°F)(approx) - - - -

Warhead:Type - - - - - - -Body - - - - - - -Color - - - - - -

Diameter - - - -Length - - - - - -Weight - - - - -

M28A2Service3.5 in.23.55 in.9.00 lb

-20° to + 120°F(-28. 6 to +48.4C)

325 ft/sec(99 reps)

HEATSteelOlive drab w/yellowmarkings3, 5 in.10.5 in.4.47 lb

High-explosive train:Detonator - - - -Booster

(tetryl) - - - - -Filler (warhead)

Type - - - - - -weight(approx) - - - -

Fuze:Model - - - - -

Type - - - - - - -Diameter - - - -

M41

0.17 oz (4.81 g)

Comp B

1.88 lb (.854 kg)

M404A1 or M404A2Base detonating2.0 in.

Length:Overall - - - -To shoulder(max) - - - - - -

Weight - - - - - -Armingdistance - - - - -

Motor:Diameter (atfins) - - - - - --L e n g t h - - - - - -Weight - - - - - -Thrust - - - - - -

3.48 in.

2.94 in.1.16 lb

10 ft (3.05 m)

3.5 in.10.413.30 lb6,000-10,000 lb

Propelling initiating train:Igniter:

Model - - - - - M20A1Charge (blackpowder) - - - - 0.13±0.007

( 3 . 5 ± . 2 g )Electricsquab - - - - - - M2

Propelling charge:Propellant:

Model - - - -Type - - - - -

Configuration -

Weight - - - - - -Burning time:

At -20°F - - - -At +120°F - - -

Launchers - - - - -

Packing - - - - - - -

Box:Weight (withcontents) - - - -

M 7SolventMonoperforated,cylindrical, extrudedgrains (12)0.44 lb (198 g)

0.05 sec0.02 sec

M20, M20A1,M20A1B1, M20B1

1 per metal/fiber con-tainer, 3 containersper wooden box

53.0 lb

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TM 43-0001-30

Dimensions:W/metalcontainer - - - 29-9/16 in. x

14-1/16 in. x16-19/32 in.

W/fibercontainer - - - 29-3/16 in. x

13-7/8 in. x16-19/32 in.

Cube:W/metal 3container - - - - 1.6ftW/fiber 3container - - - - 1.5ft

Shipping and storage data:Storage class/SCG - - - - - - - - 1.1EDOT shippingclass - - - - - - - - ADOT designation - ROCKET AMMUNI-

TION WITH EXPLO-SIVE PROJECTILES

Field storage -- Group EDrawings:

Complete assy - -9211744 (82-6-22Loading assy(head) - - - - - - - 82-16-36Loading assy(motor) - - - - - -9225502 (82-16-35)Packing (inner)- -7549038Packing (outer)- -7549040

References:TM 9-1340-222-34

DODAC - - - - - - - 1340-H600

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TM 43-0001-30

ROCKET, PRACTICE, 3. 5-INCH M29A2


STD (LLC-B) AMCTCM 36841 (M29A2)

Use:

For training personnel inhandling of service rockets.

Description:

use, care and

a . The warhead is completely inert.The practice rockets can be fired at buttoned-up, modified target tanks without danger totank crews. The practice rockets have thesame flight characteristics as the HEATrocket.

b. The dummy fuze rocket M405 whichseries as a coupling for the warhead andmotor, is cylindrical. It is threaded exter-nally at the forward end to fit into the

warhead assembly, and internally at therear end to receive the motor assembly.A safety band fits around the seals andfuze. This fuze incorporates a double-locking, bore-riding, round ejection pinassembly simulating that used in basedetonating (BD) fuze M404A2. The body ofthe fuze and the safety band are paintedblue.

c_. The motor assembly consists of atube which houses the propellant and ig-niter, The fin assembly is securelyattached to this tube. The front end of thetube is assembled to the base of the fuze.The rear end forms a nozzle. The cylin-drical motor cavity is divided into foursections by two spacer plates which sup-port the grains of propellant powder.

d. Each grain of propellant is 5-in.long and approximately 3/8-in. in

2 - 7

TM 43-0001-30

diameter. Three grains are placed in eachof the four sections formed by the spacerplates. Each lot of propellant is adjusted atthe time of manufacture to give standardvelocity. The igniter ignites the propellant.

e. The igniter consists of a short, cyl-indrical plastic case containing a smallblack powder charge and an electrical squib.It is assembled in the forward end of themotor on top of the propellant spacer plates.The leads of the electrical squib, runningparallel to the grains of propellant, passfrom the igniter through the nozzle into theexpansion cone. A green lead (ground) wireis connected to the aluminum support ring ofthe contact ring assembly. A red lead(positive) wire is attached to a pin which isinsulated from the support ring, but is incontact with the copper contact band. Theseconnections are positioned 180° apart. Bluelead is used for test purpose only.

f. The fin assembly consists of sixaluminum alloy fins and a contact ringassembly. The contact ring assembly,which encircles the fins, consists of threerings. An aluminum support ring, which isinnermost, is separated from the coppercontact ring by a plastic insulating ring. Thefins are spot welded to the expansion cone;the expansion cone is press-fitted to therear of the motor tube.


a. The M29A1 and M29A2 rockets aresimilar in appearance to the M28A2. TheM29 series differ in that they have a crimp-ing groove at the juncture of the warheadbody and ogive. The rockets of an earlymanufacture are assembled with M28A2rocket warhead metal parts inert loaded withplaster of paris.

b. The M29A1 warhead differs from theM29A2 warhead in the head and trap and

spacer assembly. The ogive is attachedto the head body of four screws staked tothe ogive. Some rockets may have the casttrap and square spacer blades.

The warhead being inert, no functionsoccur when the rocket is fired. The rocketis strictly for training purpose.

Tabulated Data:

Rocket:Model - - - - -

T y p e - - - - - - -Diameter - - - -Length (max) --Weight(approx) - - - - -Performance:

Operatingtemperaturel i m i t s - - - - - -

Muzzle velo-city (at 70°F,approx) - - - - -Range (max,approx) - - - - -

Warhead:T y p e - - - - - - -B o d y - - - - - - -C o l o r - - - - - - -

Diameter - - - -L e n g t h - - - - - -W e i g h t - - - - - -

Fuze:M o d e l - - - - - - -T y p e - - - - - - -Diameter - - - -

Length:Overall - - - - -TO shoulder( m a x ) - - - - - - -

W e i g h t - - - - - - - -

M29A2Practice3.5 in.23.6 in.

9.00 lb

-20° to +120°F(-28. 6 to +48.4°C)

334 fps (101.9 reps)

945 yd (863.7 m)

InertCast ironBlue w/whitemarkings3.5 in.10.5 in.4.47 lb

M405A2Dummy2.0 in.

3.42 in.

2.94 in.1.01 lb

2-8

TM 43-0001-30

Motor:Diameter (atfins) - - - - - - - 3.5 in.Length - - - - - - 10.41 in.Weight - - - - - - 3.30 1bThrust - - - - - - 6,000 to 10,000 lbs

Propellant initiatingtrain:

Igniter:Model - - - - - -Charge (blackpowder) - - - -

Electricalsquib - - - - - -


Model, - - - - - -Type - - - - - -Configuration-

Weight (newtype) - - - - - -Burning time:

At -20°F - - -At +120°F - -

Launchers:M29A2 - - - - - -

M29A1 - - - - - -

Packing - - - - - - -

M20A1

0.125 ± 0.007 OZ+ .2 g)3 . 5 4 ±

M2

M7SolventMonoperforated, cylin-drical extruded grains(12)

0.44 lb (200 g)

0.05 sec0.02 sec

M20, M20A1,M20A1B1, M20B1M20, M20B1

1 per metal/fibercontainer; 3 con-tainers per woodenbox

Box:Weight (withcontents) - - - - 53.0 lbDimensions:

W/metalcontainer - - - 29-9/16 in. x 14-1/16

in. x 6-19/32 in.

W/fibercontainer - - - 29-3/16 in. x 13-7/8

in. x 6-19/32 in.

Cube:W/metalcontainer - - - - 1.6 ft3

W/fiber3container - - - - 1.5 ft

Shipping and storage data:Storage class/S C G - - - - - - - 1.2C (12)DOT shippingclass - - - - - - - BDOTdesignation - - - ROCKET AMMUNI-

TION WITH EMPTYPROJECTILES

Field storage- - Group CDODAC - - - - - - - 1340-H601Drawings:

Complete assy - 82-6-23Loading assy -- 82-6-23Fuze - - - - - - - Dummy 72-5-16Packing (inner)- 7549038Packing (outer)- 7549040

References:TM 9-1340-222-20TM 9-1340-222-34

2 - 9

TM 43-0001-30


2-10

TM 43-0001-30

ROCKET, GROUND: 3.5-INCH SMOKE (WP) M30


(obsolete) was AMCTCM STD (LCC-B)36841 Jul 58

Use:

The 3.5-in. whiteM30 smoke rocket isscreening purposes.

Description:

phosphorous (WP),intended for smoke

a. Smoke rocket, 3.5-in. WP, M30 isfired in the same manner as rocket M28A2.On impact, the rocket bursts to produce aspray of phosphorous particles. Theseignite on contact with air, generating densewhite smoke. The smoke itself is harmless,but the burning particles produce painfulburns. In external contour, the rocket issimilar to the M28A2. Rocket M30 consists

of the WP smoke warhead, base detonating(BD) fuze M404A1 or M404A2, and theservice motor assembly.

b. Rocket fuze BD M404A2 consistsof a body which contains the functioningparts; a safety band, a detonator and abooster pellet. The fuze body and safetyband are olive drab. The fuze mechanismconsists of an activating plunger, a set-back spring, a setback sleeve, a firing pinassembly, a detent spring, an ejection pinand an ejection spring. The spring-loadedejection pin passes th-rough the fuze body.

c. The motor assembly consists of atube which houses the propellant and ig-niter. The fin assembly is securelyattached to this tube. The front end of thetube is assembled to the base of the fuze,The rear end forms a nozzle. The cylin-drical motor cavity is divided into four

2 - 1 1

TM 43-0001-30

sections by two spacer plates which supportthe grains of propellant powder.

d. Each grain of propellant is 5-in. longand approximately 3/8-in. in diameter.Three grains are placed in each of the foursections formed by the spacer plates. Eachlot of propellant is adjusted at the time ofmanufacture to give standard velocity. Theigniter ignites the propellant.

e. The igniter consists of a short, cyl-indrical plastic case containing a smallblack powder charge and an electrical squib.It is assembled in the forward end of themotor on top of the propellant spacer plates.The leads of the electrical squib, runningparallel to the grains of propellant, passfrom the igniter through the nozzle into theexpansion cone. A green lead (ground) wireis connected to the aluminum support ring ofthe contact ring assembly. A red lead (posi-tive) wire is attached to a pin which is insul-ated from the support ring, but is in contactwith the copper contact band. These con-nections are positioned 180° apart. Bluelead is used for test purpose only.

f. The fin assembly consists of sixaluminum alloy fins and a contact ringassembly. The contact ring assembly,which encircles the fins, consists of threerings. An aluminum support ring, which isinnermost, is separated from the coppercontact ring by a plastic insulating ring.The fins are spot welded to the expansioncone, and the expansion cone is press fittedto the rear of the motor tube.


a. This warhead is generally similar tothat of rocket M28A2, except that it has acharge of white phosphorous (WP). At therear, it has a union internally threaded toreceive the fuze. The burster casing (M8)

is press-fitted into the union, and the steelbody is fitted over it. The steel ogive andthe internal steel dome, which closes theforward end of the filler cavity are at-tached to the body.

b. This fuze is similar to BD rocketfuze M404A2. The M404A1 differs princi-pally in minor design changes of the func-tioning parts and the shape of the safetyband.

Functioning:

a. When the safety band is removed,the injection pin moves outward approxi-mately 3/8 of an inch but still prevents allparts of the fuze mechanism from moving.When the rocket is in the firing chamber,the ejection pin is partially depressed bythe chamber, thereby freeing the setbacksleeve so it can move to the rear when therocket is fired.

b . The fuze is still safe, since theejection pin prevents movement of theactuating sleeve and firing pin.

c. If it becomes necessary to removethe rocket from the launcher, the ejectionpin will move outward and re-engage thesetback sleeve. This returns the fuze toits original safe condition.

d. When the rocket is fired, the forceof inertia causes the setback sleeve tomove rearward, It is held in its rearwardposition by the lockpin. When the rocketleaves the muzzle of the launcher, theejection pin is thrown clear of the fuze bythe ejection pin spring. The fuze is thenfully armed.

e . During flight, the firing pin leverand firing pin spring prevent the firing pinfrom striking the detonator. The creep

2 - 1 2

TM 43-0001-30

spring retards the forward movement of theplunger and actuating sleeve. The action ofthe creep spring prevents the fuze fromfiring should the rocket strike light objectssuch as thin brush or undergrowth.

f . Upon impact with a more resistantobject, the plunger and actuating sleevemove forward until the sleeve hits the firingpin lever. This causes the firing pin tostrike and detonate the burster.

Tabulated Data:

Rocket:Model - - - - - - M30DODAC - - - - - 1340-H602Assy drawing- - 82-6-26Type - - - - - - - SmokeDiameter - - - - 3.5 i n .Length (max) - - 23.55 in.Weight (approx)- 9.00 lbPerformance:

Operatingtemperaturelimits - - - - - -20° to +120°F

(-28.6° to +48.4°C)Muzzle velocity(at 70°F,approx) - - - - 317 fps (96.7 mps)Range (max,approx) - - - - 945 yd (863.7 m)

Warhead:Type - - - - - - - ChemicalBody - - - - - - - SteelColor - - - - - - - Gray w/yellow

markingsDiameter - - - - 3.45 in.Length - - - - - - 10.6 in.Weight - - - - - - 4.47 1b

High-explosive train:Detonator - - - - M41Booster

(tetryl) - - - - 0.1702 (4.81 g)Type - - - - - - - W PWeight (approx)- 2.23 lb (1.01 kg)

Fuze:Model - - - M404A1 or M404A2Type - - - - BD

Motor:Diameter(at fins) - - - 3.5 in.Length - - - - 10.41 in.Weight - - - - 3.30 lbThrust - - - - 6,000 to 10,000 lb

Propelling initiating train:Igniter:

Model - - - M20A1Charge(blackpowder) - - 0.125 ± 0.00702

(3.54 ± .2 g)Electricsquib - - - - M2


Model - - -Type - - - -Configura-tion - - - - -

Weight (newtype) - - - -Burning time:

At -20°F -At +120°F -

Launchers - - - -

Packing - - - - -

Box:Weight (withcontents) - - -Dimensions:

W/metalcontainer -

M7Solvent

Monoperforated, cyl-indrical, extrudedgrains (12)

0.44 lb (200 g)

0. 05 see0. 02 secM20, M20A1, M20A1B1,M20B11 per metal/fiber con-tainer; 3 containers perwooden box

53.0 lb

29-9/16 in. x 14-1/16tn. x 6-19/32 in.

2 - 1 3

TM 43-0001-30

W/fibercontainer - - - 29-3/16in. x 13-7/8

in. x 6-19/32 in.

Cube:W/metalcontainer - - - - 1.6 ft3W/fiber

3container - - - - 1.5 ft

Shipping and storage data:Storage Class/SCG - - - - - -- 1.2H (12)DOT shippingclass - - - - - - - AD O T ROCKET AMMUNITIONdesignation - - - W I T H S M O K E

PROJECTILES

Field storage - - Group H

DODAC - - - - - - - 1340-H602

Drawings:Completeassembly - - - - - 82-6-26Loadingassembly - - - - - 82-16-39Fuze (M404A2,type BD) - - - - - - 9209515Packing (inner) -7549038Packing (outer) -7549040

References:TM 9-1340-222-20TM 9-1340-222-34

2–14

TM 43-0001-30

LIGHT ANTITANK WEAPON (LAW) SYSTEM M72 SERIES

2-15

TM 43-0001-30


2-l6

TM 43-000

ROCKET, HEAT, 66 MM, M72, M72A1, M72A2, AND M72A3


M72 & M72A1 OBS-MSR-05806019.M72A2 - STD LCC-B-MSR-09806022.M72A3-STD LCC-A-MSR-09806021.

Use:

Primarily for penetration of armoredtargets. It may be used effectively againstbunkers and other light field of fortifications.

a. Launcher.—

b. Rocket.

Description:

a. The packaged compact portable wea-penis issued as a single shot shoulder-firedlauncher with a HEAT rocket and slingassembly. The rocket launcher is a tubu-lar, telescoping, smooth-bore, open-breech

1-30

type weapon. The outer (front) tube ismade of plastic, impregnated fiberglass;the inner (rear tube) is made of aluminum.The inner tube is oriented with respect tothe outer tube by the channel assembly,which rides in an alinement slot in thetrigger housing assembly. The tubes arelocked in the open position when the detentassembly drops into the rectangular holein the trigger housing assembly.

b . The f in s tab i l i zed rocke t inthis system contains a shaped charge war-head with a point initiating base detonating(PIBD) fuze. The fuze contains a 2-wiresystem from the piezo electric element onthe warhead to the fuze detonator whichprovides electrical fuze initiation when thenose crystal is struck. In addition, thefuze has a mechanical inertial graze ele-ment as a secondary means of functioning.

2 -17

TM 43-0001-30

Differences between Models: Functioning:

The M72A2 rocket is similar to the a. Extending the launcher into theM72A1 with the exception of the warhead extended or firing position automaticallywhich contains a precision shaped charge locks the weapon.liner cone. This provides greater targetpenetration than the M72A1. There isalso a minor change in the wiringbetween the piezo electric element andfuze, otherwise the two systems areidentical. The M72A3 is similar toM72A2.

WARNING

WEAR EAR PLUGS WHEN FIRING THEWEAPON . THE 100 AND 150 METERMARKINGS ON THE FRONT SIGHTARE COATED WITH RADIOACTIVEMATERIAL, THEN LAMINATEDBETWEEN TWO SHEETS OF PLASTIC.IF SIGHT IS BROKEN, REMOVE ANDPLACE IN A PLASTIC SEALED BAG.RETURN BAG TO AMMUNITIONDISPOSAL PERSONNEL.

NOTE

The front sight on theselaunchers, up to and includingthe M72A2 series weapon, isdesigned for use under condi-tions of limited visibility andis coated with a radioactivematerial (Promethium 147)at the 100 and 150 metermarks. On the weapons withthis limited light sight the100 and 150 meter marks arewhite, the remaining markingsare red. On weapons withoutthis feature, all markingson the sight are in red.The M72A3 series weapons donot have this radioactivesight feature.

b. After the trigger safety handleis released, the trigger is depressed.This releases the channel assembly whichdrives the firing pin into the primerof the rocket motor igniter. Thisignites the black powder in the flashtube, which in turn, ignites the integraligniter of the rocket motor. The igniterinitiates the propellant. The burningpropellant propels the rocket from thelauncher.

c. Upon target impact, the fuze traindetonates the charge which collapses thecopper liner into a finger shaped jet.The jet is preceded by extremely hot,high velocity gases which melt a hole inthe target. The copper jet thenpenetrates into the target. Almostsimultaneously the body and ogive areblasted into small fragments by thedetonated octol charge. These fragmentstravel adjacent to, and aft of the lineof fire.

Tabulated Data:

LAW systems (packaged):Models ----- M72A2Weight ----- 4.7 lbLength:

Closedposition - 25.77 in.Extendedposition - 35.16 in.

Launcher --- M72Weight --- 2.50 lb

Rocket ----- M72Warhead -- M18A1Fuze ----- M412A1Motor ---- M54

2-18 Change 4

TM 43-0001-30

Warheads:Weight (loadedand fuzed) ---

Explosive charge:Type ---------Weight -------Body material-

Color --------

Fuzes (integral):Type -- - - - -- --

Weight -------Overall length(max) --------Diameter(max) --------Explosivebooster:

Type -------

Weight ----Armingdistance -----

Motor:weight -------Propellant:

Model -----Type ------Weight ----Configura-tion ------Number ----

Velocity -----Thrust at70°F ---------Burning time -Temperaturelimits -------

Packing ofrocket inlauncher -----

Packing box:Weight

2.3 lb w/contents ---- 117.7 lbDimensions ---- 33-1/2 in. x

60/40 octol0.67 lb (304 g)Steel w/aluminum Cube ----ogiveBlack w/yellow Shipping andmarkings Storage cl

31-1/813-3/4

----- 8.3 ft3

storage data:ass/

----------- 1.1EPoint-initiating, base DOT shipping

in. xin.

detonating class ---------- A0.154 lb DOT

designation --- ROCKET AMMUNITION1.89 in. WITH EXPLOSIVE

PROJECTILE1.28 in. Field storage - Group E

*DODAC -------- 1340-H553, 1340-H554,1340-H555, 1340-H557,

Composition A5(tetryl)

and 1340-H568

0.200z (5.6g) Drawings:Complete

25 - 45 ft (7.6-13.7m) assembly ------ 1OO485O3-M729210276-M72A19244054-M72A2

0.67 lb Loading ------- 9235663Packing (inner)- 9227925

M7 Packing (outer)- 9227926D o u b l e b a s e0.138 lb (62.7g) References:

SC 1340/98-IL TM9-134O-214-1OStick TM 9-1340-222-20 FM 23-3319 TM 9-1340-222-34475 fps (145 reps)

4250 lb7 to 15 milliseconds

*See appropriate supply catalog for-40° to +140°F individual NSN’S pertaining to this(-39.6° to 59.4°C) (these) DODAC(s).

5 per carton; 1 cartonper barrier bag; 3barrier bags per woodenbox

Change 4 2-19

TM 43-0001-30


2-20

T M 1 3 - 0 0 0 1 - 3 0


STD (LCC-A) AMCTCM 9018 March 72

Use:

The M74 incendiary thickenedtriethylaluminum (TPA) is used todefeat or neutralize hard, soft,or jungle targets.Description:

The M74 consists of a rocket warheadcontaining approximately 1.3 pounds ofTPA, a base detonating (BD) fuze

Functioning:

When the projectile is fired, accelera-tion acts upon the fuze sequential leafarming mechanism. The fuze rotorassembly is then free to rotate to thearmed position. When the rotor is inthe armed position, the detonator isalined with the remainder of the explo-sive train. Rocket deceleration, dueto impact, causes the graze elementof the fuze to shift, thereby allowingthe firing pin of the fuze to be driveninto the primer. The primer flashesthrough the flash channel and initiates

and an adapter which adapts the rocket motor the detonator, then the trademark into the warhead. The rockets are issued in the warhead; disseminating the warheadfour round clips. agent.

Change 4 2 - 2 1

TM 43-0001-30

Tabulated Data:

Rocket:Model - - - - - - --Type - - - - - - - - -Length - - - - - - - -Weight (approx) - -

Performance:Operating temper -ature limits - - - -

Range (rnax) - - - -Range (rein) - - - -

Muzzle velocity(approx) - - - - - - -

Burst radius(approx) - - - - - - -

Motor:Model - - - - - - --Length - - - - - - - -Weight - - - - - - - -Thrust - - - - - - - -

Propellant initiatingtrain:

Igniter:Model - - - - - - -Type - - - - - - - -

Propelling charge:Propellant - - - - -Type - - - - - - - - -Configuration - - -

Weight - - - - - - - -Burning time - - -

Launcher - - - - - - - -

M74Incendiary21.0 in.2.95 lb

-40’ to +140°F(-39. 60 to 59. 4°C)825 yd (754 m)22 yd (2o m)(hard targets)

375 ft/sec

65. 5 ft (20 m)

M549.2 in.0.67 lb4250 lb

M56Integral

M 7SolventMonoperforated cyl-indrical extrudedgrains (19)0.138 lb7 to 15 millisecondsM202A1

Packing - - - - - - - --

Warhead:Model - - - - - ---Type - - - - - - - - -Color - - - - - - - - -

Length - - - - - - - -Filler (warhead):

Type - - - - - - --

Weight - - - - - - --

Fuze:M o d e l- - - - - - --Type - - - - - - - - -

DODAC - - - - - ----

Shipping and storagedata:

Storage class/SCG - - - - - - ---DOT shippingclass - - - - - - --DOTdesignation - - - - -

Field storage - - -

References:TM 3-1055-218-12TM 3-1055-456-12

Four per clip

M235IncendiaryRed w/yellow bandand black markings11.60 in.

TriethylaluminumPyroPhoric (TPA)1.3 lb (0.59 kg)

M 4 3 4Base detonating

1340-H110

1.2L (12)

A

ROCKETAMMUNITIONWITH INCENDIARYPROJECTILEGroup D

Information on M196, four tube-CSclips used in the M1202Al launcher.

2 - 2 2 Change 7

*U.S. GOVERNMENT PRINTING OFFICE: 1990-743-049:20203

T M 4 3 - 0 0 0 1 - 3 0

ROCKET, PRACTICE, 35 MM, SUBCALIBER, M73


STD (LCC-A) AMCTCM 7617 April 70

Use:

To train personnel in the operation anduse of the 66-mm antitank rocket, M72series.

Description:

a. The M190 subcaliber launcher withM73 subcaliber rocket can be used againstall solid stationary or moving targets.

Together they can be used in all trainingphases, from fixed firing live to simulatedsituations, such as a “trainfire” typeoperation.

b_ . The M190 subcaliber launcher isa tubular, telescoping, smooth-bore, open-breech weapon.

c_ . The M73 subcaliber rocket consistsof a spotting head, a motor closure, arocket motor and an igniter assembly. Thespotting head contains the same flash com-position used in the M80 explosive simula-

tor (TM 9-1370-203-34&P) to assist in locating

2 - 2 3

TM 43-0001-30

the fired rocket. The forward end of themotor closure provides a cavity that con-tains a base detonating fuze and a primer.The motor case contains tubular grainsor propellant. The rocket is stabilized bysix molded, plastic fins.


The external appearance of the M190subcaliber is almost identical to theM72A1. The M190 differs from the tacti-cal launcher M72A1 by having a subcaliberrocket and a quick release primer housingdoor to simplify reloading. The usedM72A1 launcher is modified by use of aconversion kit to produce the M190 sub-caliber launcher.

Functioning:

Extending the launcher into the extendedor firing position automatically locks theweapon. After the trigger safety handle isreleased, the trigger can be depressed.This releases the channel assembly whichdrives the firing pin into the primer of therocket motor igniter. This ignites theblack powder in the flash tube, which, inturn, ignites the integral igniter of therocket motor. The igniter initiates thepropellant. The burning propellant propelsthe rocket from the launcher. When thespotting head of the rocket strikes a target,an inertia-driven firing pin sets off theprimer. The primer in turn sets off thespotting head which produces a flash, noiseand white smoke.

Tabulated Data:

Rocket:Model - - - - - - - - M73Type - - - - - - - - - PracticeWeight - - - - - - - - 0.321bLength - - - - - - - - 8.87 in.

Diameter - - - - - -Head:

Material - - - - - -Type - - - - - - - -Charge:

Flashcomposition - -Color - - - - - - -

Motor - - - - - - ----Type of propellant:

Model - - - - - - - -Type - - - - - - - - -Weight - - - - - - - -Configuration - - -Number - - - - - - -

Fuze - - - - - - - - - - -

Primer - - - - - - -Velocity at 70°F-Burning time( m a x ) - - - - - - - - -Range - - - - - - --

Temperature limits:Firing - - - - - - - -

Storage - - - - - - -

Launcher - - - - - - - -Packing - - - - - - - - -

Packing box:Weight w/contents-Dimensions - - - - -

Cube - - - - - - - - - - -

Shipping and storagedata:

Storage class/SCG - - - - - - - - --Dot shippingclass - - - - - - - - -

1.37 in.

PlasticSpotting

0.05oz (1 .41g)BlackSteel

M7Double base0.02 lb (9 g)Stick3Integral, basedetonatingStab, M26497 fps

12 milliseconds(55-354 yd)(50-325 m)

-10° to +135°F(-23. 1° to +56. 65°C)-40° to +140°F(-39. 6° to +59. 4°C)M19030 per fiber con-tainer; 3 containersper wooden box

58.8 lb (26, 460 g)32-3/4 in. x 13-1/4in. x 15-7/8 in.

4.0 ft3

1.2E (04)

A

2–24

T M 4 3 - 0 0 0 1 - 3 0

D O T d e s i g n a t i o n - - - - - - - - - R O C K E T A M M U -N I T I O N W I T HEXPLOSIVEPROJECTILE

* D O D A C - - - - - - - - - - - - - - - - - - 1 3 4 0 - H 7 0 8D r a w i n g s :

C o m p l e t e a s s y - - - - - - - - - 1 0 2 4 2 7 2 5L o a d i n g a s s y - - - - - - - - - - 1 0 2 4 2 7 2 5P a c k i n g ( i n n e r ) - - - - - - - 1 0 2 4 2 7 4 3P a c k i n g ( o u t e r ) - - - - - - - 1 0 2 4 2 6 9 7

I n f o r m a t i o n o n S L U F A E m i n e n e u t r a l -i z i n g r o c k e t s , 115MM GB and VXr o c k e t s a n d t h e V I P E R H E A T R o c k e t ,

R e f e r e n c e s :S C 1 3 4 0 / 9 8 - I LT M 9 - 1 3 4 0 - 2 0 3 - 2 0

* S e e a p p r o p r i a t e s u p p l y c a t a l o g f o ri n d i v i d u a l N S N ’ S p e r t a i n i n g t o t h i s( t h e s e ) D O D A C ( S ) .

C h a n g e 1 2 - 2 5

TM 43-0001-30


2-26

TM 43-0001-30

CHAPTER 3

AIRCRAFT ROCKETS2.75-Inch

Complete Rounds: Aircraft Rocket Launchers.

a. Complete rounds can be assem- b. The rockets can be issued unassem-bled in the combinations in table 3-1. bled. This chapter contains informationThey may be fired from the M157, M158, pertaining to the components of the un-M159C, M3 or M200 2.75-Inch assembled rockets.

Table 3-1. 2.75-Inch Complete Round Rocket Combinations

DODAC

1340-H459

1340-H4701340-H4711340-H4891340-H4901340-H1611340-H485

1340-H4881340-H5331340-H5341340-H1601340-H469

1340-H5191340-H4861340-H5931340-H826

1340-H8281340-H1801340-H116

Warhead

Flechette (ANTIPERSONNEL)WDU/4A/A

High Explosive M151

High Explosive M229

Smoke, WP, M156

HE, DP

Practice, WTU-1/BIlluminating M257

Smoke, Screening WP, M259

Motor

Mk40, Mod 3

Mk4, ModsMk40, Mod 3Mk40, Mod 3Mk40, Mod 3Mk40, Mod 3Mk4, Mod 10

Mk40, Mod 3Mk40, Mod 3Mk40, Mod 3Mk40, Mod 3Mk40, Mod 3

Mk40, Mod 3Mk 4, Mod 10Mk40, Mod 13Mk40, Mod 3

Mk40, and ModsMk40Mk40, Mod 3

Fuze

Integral

M427M433M429M423M423M427

M429M427M423M423M433

M423M427M427M438M247NoneM442M446

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TYPICAL 2. 75-INCH AIRCRAFT ROCKET (LSFFAR)

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ROCKET, FLECHETTE, 2.75-INCH, WDU-4A/A


STD (LCC-A) AMCTCM 47560 Nov 69

Use:

The warhead containsused against personnel.

Description:

flechettes and is

a. The complete round consists of awarhead with an integral fuze and rocketmotor,

b . The warhead consists of 3 mainparts: a nose section, a body, and an in-tegral fuze. The nose section, a plasticcone bonded to a metal plate, is attachedto the body by shear pins. The body is a

hollow cylinder loaded with 20 grainflechettes. The most recently manufac-tured WDU-4A/A warheads contain threetracers for the purpose of assisting thepilot/gunner in identifing the beaten zoneof the flechette impact pattern. Twosemicylindrical sleeves retain theflechettes in place. A metal pusher plateis located just aft of the flechettes. Thethreaded end of the body is machined in-ternally to accommodate a base-detonating(BD) fuze.

c. The low-spin folding-fin aircraftrocket (LSFFAR) is an air-to-groundrocket primarily deployed from rotary-wing and other low-speed aircraft. How-ever, it is also used on Air Force andNavy jet aircraftrestricted single

in ripple fire and in afire mode.

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d . The rocket motor is described inChapter 5.


The Mk 40 Mods 1 and 3 have integralbulkhead motor tubes whereas the Mk 40Mod 0 has nonintegral bulkhead tube. Theigniter of the Mod 3 motor differs fromthat of the Mods 0 and 1 motors in that theigniter has been modified to incorporate acarried, frangible case in lieu of the blow-out plug. Also, the squib is located on theperiphery instead of the center of the case.

Functioning:

a. The rocket motor functions whencurrent passes through the launcher firingcontact to the igniter in the rocket motor.This current generates the heat necessaryto initiate the igniter charge which ignitesthe propellant grain. Combustion gasesfrom the burning propellant pressurizes thechamber and exhaust through the nozzle,providing the unequal forces required forrocket thrust.

b. Functioning of the fuze sets off anexpelling charge which forces the pusherplate, flechettes and semicylindricalsleeves forward. This shears the pinsattaching the nose cone to the body and ex-pels the flechettes into the slipstreamahead of the rocket.

Tabulated Data:

Type - - - - - - - - - AntipersonnelWeight (fuzed) - - - 9.3 lbLength - - - - - - - - 17.8 in.Filler:

Type - - - - - - - - 20-grain flechettesNumber - - - - - - 2200Weight - - - - - - - 6.3 1b

Body material - - - Extruded aluminum

Fuze - - - - - ----Type - - - - - - - -Length - - - - - - -Diameter - - - - -Sensitivity - - - -Arming distance-

Setback to arm- -Color - - - - - - - - -


Storage - - - - ---

Drawing number- - - -Packaging for com-plete round - - - - - - -

Packing box:Weight (w/contents - - - - - - -Dimensions - - - - -

IntegralBase detonating3.30 in.2.55 in.15 G's or less(47-100 yd)(43 -92 m)28 G's approxOlive drab w/whitemarkings

-40° to +140°F(-39. 6° to +59. 4°C)-40° to +140°F(-39. 6° to +59. 4°C)D67D9700

1 rocket consistingof warhead, WDLT-4A/A and rocketmotor Mk 40, 3 perfiber container; 4containers perwooden box

162 lb62-13/16 in. x8-11/16 in. x 9-1/2in.

cm)Cube - - - - - - - - - 3.5ft3

Shipping and storage data:Storage class/SCG - - - - - - - - - - 1.2C (12)DOT shippingclass - - - - - - - - - BDOTdesignation - - - - - ROCKET AMMUNI-

TION WITH INERTLOADED PROJEC-TILE

Field storage - - - Group FDODAC for completeround - - - - - - - - - - 1340-H459

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Rocket Motor:Model - - - - - - - - Mk 40, Mod3Length (overall) - - 39.9 in.

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ROCKET, HIGH-EXPLOSIVE, 2. 75-INCH W/M151 WARHEAD


STD (LCC) AMCTCM 3990, 3233 and5178 Ott 65

Use:

This is a general purpose high-explosiverocket that can be presently assembled infive different combinations of motors andfuzes.

Description:

a . This low-spin folding-fin aircraftrocket (LSFFAR) is an air-to-ground rocketprimarily deployed from rotary-wing andother low-speed aircraft. It is also used onAir Force and Navy jet aircraft in ripplefire and in a restricted single fire model.

b . The warhead consists of two mainparts, a nose and a base, brazed together.

The nose section is threaded to receive afuze. The base is made of steel and isthreaded for attachment to rocket motor.

c . Fuzes assembled with 2. 75-in.rockets are classified as point detonating(PD), or proximity, according to themanner in which they are initiated.Except for the Proximity Fuze M429,these fuzes are nondelay and super-quick. The point detonating fuzes andproximity fuzes are threaded into theforward end of the high explosivewarhead.

d. The M151 warhead is availablewith fuzes M423, M427, M429, and M433.These fuzes differ from each otherfunctionally and have the followingcharacteristics:

M423) Oblique impact sensitive, point-M427) detonating, super-quick type fuze.

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M429 Transistorized Doppler typeproximity fuze with a super-quickimpact switch as a backup.

M433 A resistance-capacitance multi-option time delay fuze with selec-table functioning modes for junglecanopy penetration, bunker pene-tration and super-quick for openterrain.

e. The Mk 40 low-spin folding-finaircraft rocket motors are fin stabilizedand have scarfed nozzles. The scarfednozzles give low spin to the rocket andprovide the additional stabilityrequired for deployment from low speedaircraft.

f. The rocket motor is described inChapter 5.


The table below identifies thedifferences between the high-explosiveM151 warhead incorporated within theapproved configurations of motor and fuze.

DODAC

1340-H470

1340-H471

1340-H489

1340-H490

1340-H161

1340-H485

Warhead

High-Explosive M151

Functioning:

a. Fuze Functioning—

(1) A typical PD fuze (M423 andM427) arms under minimum, sustainedacceleration. On impact with the target,the nose of the fuze is crushed and thefiring pin strikes the primer. Primerdetonation sets off, in sequence: thedetonator, the booster lead-in, thebooster, and the explosive in thewarhead.

(2) The M429 proximity fuze isa completely transistorized, continuouswave, doppler device to provide airburstcharacteristics. It was designedprimarily for use with high-explosive(HE) warheads for improved anti-personnellethalities.

(3) The M429 proximity fuze isequipped with a super-quick impactswitch which serves as a backup in theevent of failure of the airburstelectronics. The arming mechanism issimilar to that contained in the M427

Motor Fuze

Mk 40, Mods 1, 3 M427

Mk 40, Mod 3 M433

Mk 40, Mods 1, 3 M429

Mk 40, Mods O, 1, 3 M423

Mk 40, Mod 3 M423

Mk 4, Mod 10 M427

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fuze except that it has been modifiedto include an electric detonator as wellas a battery starter assembly toinitiate an electric battery, Anelectric detonator is assembled in therotor. A plastic (lexan) sleevehouses the thermal battery which islocated directly above the safing andarming (S & A) mechanism.

(4) The M433 fuze is anelectronic multi-option delay timedelay fuze with selectable functioningmodes for forest canopy penetration,bunker structure penetration andsuper-quick (SQ) for open terrain. Thefuze body is steel. A forest canopyswitch extends from the nose of the fuzeto signal to the fuze electronic circuitwhen first contact is made with the treetops . An umbilical assembly ispositioned at the nose of the fuze forelectrical connection to the M132 fuzesafety and timing device located inthe helicopter. Internally, the fuzeconsists of a Resistance Capacitance(RC) electronic time circuit, a safingand arming mechanism with an electricalM84 detonator and a booster assembly.

(5) The M433 fuze has aselectable” time delay range that dependson the height of the forest canopy(40 to 130 feet). After first contactwith the tree tops, a delay timer isactivated which results in warheadfunctioning beneath the canopy, butabove ground level. The bunkerstructure penetration mode is incor-porated into the fuze to defeat themedium hardness targets constructed oflogs, earth, bricks, etc. The fuze canbe set from the cockpit for penetratingup to 10 ft of protection and destroyingthe target from within. The hard targetpenetration RC timer is activated byinertial switch sensing, setback inexcess of 1000 G’s. Also, an SQ point

detonating feature is included toprovide operational flexibility in openterrain, This mode is achieved bysetting delay to zero. First contactwith any surface detonates the round.

(6) The M433 has no internalbattery. Required voltage is suppliedby the aircraft via the M132 safety andtiming device 160 milliseconds prior tothe rocket being fired. During this160 millisecond period, fuze is chargedto give time delay selected by pilots.

(7) The M433 fuze is to beused with M151 warheads.

(8) Testing the M433 fuzeagainst 3 ft thick wood barriersindicates warhead detonations may occur6-in. prior to exit from the barrier toas much as 4.5 ft into the bunker void.

(9) The M433 fuze nose cap isdesigned to provide fuze sensitivityon oblique/graze impacts. With thecap removed and the fuze set in thedelay mode, oblique/graze impactsensitivity is obtained through theinertial action of the firing pin.

(10) Because of the voidsensing characteristics of the M433fuze, complete destruction may beanticipated when a target hit isachieved. It is recommended thatrockets be fired in pairs at minimumranges and steep dive angles to enhancetarget hits,

b. Rocket Functioning. When therocket is launched, with pointdetonating fuze (PD) it becomes armedfrom inertial forces resulting fromsustained acceleration. This freesthe unbalanced rotor to turn and lockthe explosive train in the armedposition. Upon impact with a target,

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the detonator functions and initiatesthe explosive train.

Upon detonation, the warhead shattersinto thousands of small, high-velocityfragments.

Tabulated Data:

Warhead model --- M151Type ------------ High explosiveWeight (fuzed) -- 8.7 lbLength (w/o fuze) 12.9 in.

Filler:Type -------- Comp B4Weight ------ 2.3 lb (1.04 kg)

Body material -- Pearlitic or ferriticmalleable iron

Color ---------- Olive drab, yellowmarkings

Temperature limits:Firing ----- -65° to +150°F

(-53.35° to +64.9°C)Storage ---- -65° to +150oF

(-53.35° to +64.9oC)

Drawing number- 8882186Packing forcomplete round- 1 rocket consisting

of Warhead, HE,M151 with RocketFuze, M423 orM427 with Mk 4motor only andmotor Mk 40, ModsO, 1 or 3 per fibercontainer; 3, 4 or25 containers perwooden box

Packing box:Weiqht w/contents - 127 lbDimensions -------- 62-13/16 in. x

8-11/16 in. x9-1/2 in.

Cube ------------- 3.5 ft3

Shipping and storage data:Storage class/SCG -------------- 1.1E

DOT shippingclass ------------ ADOTdesignation ------ ROCKET

AMMUNITIONWITH EXPLOSIVEPROJECTILES

Field storage ---- Group F

*DODAC -------------- 1340-H470,1340-H471,1340-H489,1340-H490,1340-H161,1340-H485

Drawing numbers ----- 9220807, 9204528,9209570, 9235961,8796521, 9230114,8796522

References:TM 9-1340-222-20TM 9-1340-222-34SC 1340/98-IL

*See appropriate supply catalog forindividual NSN's pertaining to this(these) DODAC(s) .

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ROCKET, HIGH-EXPLOSIVE, 2.75-INCH WITH M229 WARHEAD


STD AMCTCM or OTCM 8685

U s e :

To provide improved aerial artillery capabil-ity for the 2.75-in, rocket.

Description:

This rocket is an air-to-ground rocket primar-ily deployed from rotary-wing and other low-speed awcraft. It is also used on Air Force andNavy jet aircraft in ripple fire mode.

This rocket is used to enhance the lethalityand destructiveness of the 2.75-inch rocket mits aerial artillery role. It uses the M229 war-head which is an elongated version of the M151warhead, and is commonly referred to as the 17-lb warhead.

It consists of three main parts consisting ofthe nose, body, and base. The three main partstire welded together. There is an altermate two-piece design consisting of a one-piece nose bodyplus a base.

Fuzes assembled with 2.75-in. rocketsare classified as point detonating (PD), orproximity, according, to the manner inwhich they are initiated. Except for theProximity Fuze M429, these fuzes are

Change 13 3-11

TM 43-0001-30

nondelay and super-quick. The point detonat-ing fuzes and proximity fuze are threaded intothe forward end of the high explosive warhead.

The M229 warhead is available with fuzesM423, M427, M429 and M433. These fuzes dif-fer from each other functionally and have thefollowing characteristics:

M423) Oblique impact sensitive, point-M427) detonating, super-quick type fuze.

M429 Transistorized doppler type prox-imity fuze with a super-quick impactswitch as a backup.

M433 A resistance-capacitance multi-option time delay fuze with select-able functioning modes for jinglecanopy penetration, bunker penetra-tion and super-quick for openterrain.

The rocket motors are described in Chapter5.

Differences Between Models:

The nose and base of the M229) warhead areessentially identical to the M151 parts, whichare separated by the 10-in, long cylindrical body.

The table below identifies the differencesbetween the high-explosive M229 warhead incor-porated within the approved configurations ofmotor and fuze.

Functioning;

Ignition: Functioning of the 2.75-in. rocketwith an M229 warhead begins when the firingcircuit switch is closed. Current passes through)the launcher firing contact to the igniter in therocket motor. this current generates the heatnecessary to initiate the igniter charge, whichignites the propellant grain. Combustion gasesfrom the burning propellant pressurize thechamber and exhaust through the nozzle, pro-viding the unequal forces required for rocketthrust.

DODAC Warhead Motor Fuze

High Explosive M2291340-H4691340-H4881340-H5331340-H5341340-H1601340-H642

MK40, Mod 3MK40, Mod 1,3MK40, Mod 1,3MK40, Mod 1,3MK40, Mod 3MK66, Mod 2

M433M429M427M423M423M423

Fuze Functioning: The M429 proximity fuzeis a completely transistorized, continuous wave,with doppler device to provide airburst charac-teristics. It is designed primarily for use withHE warheads for improved antipersonnel lethali-ties.

A super-quick impact switch on the M429serves as a backup in the event of failure of theairburst electronics. The arming mechanism issimilar to that contained in the M427 fuzeexcept that it has been modified to include anelectric detonator as well as a battery starterassembly to initiate an electric battery. An elec-tric detonator is assembled in the rotor. A plas-tic (lexan) sleeve houses the thermal batterywhich is located directly above the S&A mecha-nism,

When the rocket is launched, the fuzebecomes armed from inertial forces resulting

from sustained acceleration. this frees theunbalanced rotor to turn and lock the explosivetrain in the armed position. Upon sensing a tar-get, the detonator is fired and initiates the explo -sive train,

Upon detonation, the warhead shatters intothousands of small high-velocity fragments.

Tabulated Data:

Warhead model ---------------- M229Type ------------------------------- High explosiveWeight (fazed) ------------------ 18.1 lbLength (w/o fuze) ------------- 2303 in.Filler:

Type ---------------------------- Comp B4Weight -------------------------- 4.8 lb (2.18 kg)

Color . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Olive drab w/yellowmarkings

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Temperature limits:Firing ---------------------------

storage -------------------------

Packing ---------------------------

r o u n dPackaging for complete

. . . . . . . . . . . . . . . . . . . . . . . . . . .

Packing box:Weight (w/contents) --------Dimensions -------------------

Cube -------------------------------

-65° to + 150oF(-53.35 oto+64.9oC)-65oto + 150oF(-53.35 ot o+64.9oC)1 per fiber con-

tainer 4 containersper wooden box

1 rocket consistingof warhead, HE,M229 w/rocket fuzeand rocket motorper fiber container;3, 4 or 25 contain-ers per wooden box

162 lb72-13/16 in. x 8-11/16 in. x 9-1/2 in.3.5 cu ft

Shipping and Storage Data:

Storage class SAG------------ 1.1EDOT shipping class ----------- ADOT designation -------------- ROCKET

AMMUNITIONWITHEXPLOSIVE

DOT labels

PROJECTILESUN 0181

---------------------- EXPLOSIVE 1.1EField storage -------------------- Group F

*DODAC ------------------------ 1340-H469,1340-H488,1340-H533.1340-H534,1340-H160,1340-H642

Drawings:9220806 ------------------------ W/Motor, Mk40,

Mod 313058371 --------------------- W/Motor, Mk66,

Mod 29218698 ------------------------ Warhead, M2299230116 ------------------------ Packing and

Marking

WARNING

WHEN FIRING ROCKETS WITHTHE M229 WARHEAD FROM THEOH-6A AND UH-60 AIRCRAFT,SAFE SEPARATION DISTANCE IS450 FEET.

References:

TM 9-1340-222-20TM 9-1340-222-34SC 1340/98-IL

*See appropriate supply catalog for individualNSN’s pertaining to this (these) DODAC(s)..

Change 13 3-13

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THIS PAGE INTENTIONALLY LEFT BLANK

3-14 Change 13*U.S. G.P.0.:1993-746-163:80717

PIN: 050170-013

TM 43-0001-30

ROCKET, SMOKE, WP, 2.75 -INCH W/M156 WARHEAD


STD AMCTCM 10756032

Use:

Primarily to provide smoke for targetmarking and incendiary purposes.

.Description:

a . This warhead is a ballistic matchfor high explosive (HE ) Warhead M151. TheM156 consists of a steel body, a base, andan adapter, brazed together. The body isshaped at the forward end to form the ogive.The base is an extruded steel cup threadedfor attachment to the rocket motor. Thesteel adapter, at the forward end of thewarhead, is threaded to receive the fuze.It also serves to retain the burster chargetube.

b. The fuzes assembled in this 2.75-in. rocket are classified as point detonating(PD), or proximity, according to the man-ner in which they are initiated. Except forthe Proximity Fuze M429, these fuzes arenondelay and super-quick. The pointdetonating fuzes and proximity fuze arethreaded into the forward end of the warhead.

c . The WP M156 warhead is availablewith fuzes M423, M427, and M429. Thesefuzes differ from each other functionallyand have the following characteristics:

M423) Oblique impact sensitive,M427) point-detonating, super-quick

type fuze.

M429 Transistorized Doppler typeproximity fuze with a super-quick impact switch as abackup.

3 - 1 5

TM 43-0001-30

d. The LSFFAR 2.75-in. rocket motorsare fin stabilized and have scarfed nozzles.The scarfed nozzles give low spin to therocket and provide the additional stabilityrequired for deployment from low speedaircraft.

e. The rocket motor is described inChapter 5.


The table below describes the differencesbetween the WP smoke M156 warhead incor-porated within the approved configurationsof motor and fuze.

Functioning:

a . I g n i t i o n . Functioning of the 2.75-in.rocket with an M156 warhead begins whenthe firing circuit switch is closed. Currentpasses through the launcher firing contactto the igniter in the rocket motor. Thiscurrent generates the heat necessary toinitiate the igniter charge, which ignitesthe propellant grain. Combustion gasesfrom the burning propellant pressurize thechamber and exhaust through the nozzle,providing the unequal forces required forrocket thrust.

b . Fin Operation. The thrust of thenozzle exhaust blows off the fin retainerand releases the fins. Upon clearing thelauncher, the fins are opened by the force

DODAC Warhead

Smoke WP M1561340-H4721340-H5191340-H4861340-H593

of the fin actuating piston pushing onthe heels of the fins.

c . Fuze Functioning.

(1) A typical point detonating (PD)fuze (M423 and M427) arms under minimum,sustained acceleration. On impact with thetarget, the nose of the fuze is crushed andthe firing pin strikes the primer, initiatingthe explosive train.

(2) The M429 proximity fuze is acompletely transistorized, continuous wave,doppler device to provide airburst charac-teristics. It is designed primarily for usewith HE warheads for improved anti-personnel lethalities. A super-quick impactswitch serves as a backup in the event offailure of the airburst electronics. Thearming mechanism is similar to that con-tained in the M427 fuze except that it hasbeen modified to include an electric detona-tor as well as a battery starter assembly toinitiate an electric battery. An electricdetonator is assembled in the rotor. Aplastic (lexan) sleeve houses the thermalbattery which is located directly above thesafety and arming device (S&A) mechanism.

Tabulated Data:

Warhead model -- M156T y p e - - - - - - - - - S m o k e , W PWeight (fuzed) --- 9.7 lbLength (w/o fuze) - 12.9 in.

Motor Fuze

Mk40, Mod 3 M429Mk40, Mod 0, 3 M423Mk4, Mod 10 M427Mk40, Mod 0, 3 M427

3 - 1 6

Fi l ler :

T y p e - - - - - - - -W e i g h t - - - - - - -

Burster charge:T y p e - - - - - - - - -W e i g h t - - - - - - -

Body mater ia l - - -C o l o r - - - - - - - - -

Temperature limits:F i r i n g - - - - - - - -

S t o r a g e - - - - - - -

P a c k i n g - - - - - - - - -

Drawing number - - -

Packing for completer o u n d - - - - - - - - - - -

White phosphorous2.2 lb (999 g)

Comp B0.12 lb (54.5 g)Steel tubingLight green; redmarking, yellowband

-40° to +165oF(-39.6° to +73.15oC )-40° to +140oF(-39. 6° to +59.4oC )

1 per fiber container;4 or 25 containersper wooden box

D90-1-44

1 rocket consistingof Warhead, Smoke,WP, M156 withrocket fuze andmotor per fiber con-tainer; 4 containersper wooden box

T M 4 3 - 0 0 0 1 - 3 0

Packing box:W e i g h t - - - - - - - - 1 6 2 l bD i m e n s i o n s - - - - - 72-13/16 in. x

8-11/16 in. x 9-1/2i n

Cube - - - - - - - - - 3 . 5 f t3

Shipping and storage data:Storage class/S C G - - - - - - - - - -DOT Shippingc l a s s - - - - - - - - -DOT designation --

F ie ld s torage - - - -* D O D A C - - - - - - - - -

Drawing number ----

References:

1. 2H (12)

AROCKET AMMUNI-TION WITH SMOKEPROJECTILESGroup D1340-H472, 1340-H519, 1340-H486,1340-H5939252330, 9242567

TM 9-1340-222-20&PTM 9-l340-222-34&PSC 1340/98-IL

*See appropriate supply catalog for indi-vidual NSN’s pertaining to this (these)DODAC(s).

Change 5 3-17

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ROCKET, PRACTICE, 2.75-INCH W/M230 WARHEAD


STD AMCTCM or

Use:

OTCM 9153

This warhead is used for training andtesting purposes.

Description:

a . This low-spin folding fin aircraftrocket is an air-to-ground rocket primarilydeployed from rotary-wing and other low-speed aircraft. It is also used on Air Forceand Navy jet aircraft in ripple fire and in arestricted single fire model. The nozzlesare scarfed to produce the low rate of spinrequired for deployment at low speeds.

b. The warhead consists of two mainparts, a nose and a base, brazed together.The nose section is threaded to receive afuze. The base is made of steel, or castiron and is threaded for attachment torocket motor.

c. Fuze M435 is an inert fuze. Itsimulates point detonation fuzes M423and M427 generally in length, weight andconfiguration. It is made entirely ofaluminum.

d. The LSFFAR 2. 75-in, rocketmotors are fin stabilized and have scarfednozzles. The scarfed nozzles impact lowspin to the rocket and provide the addi-tional stability required for deploymentfrom low speed aircraft.

3 - 1 9

T M 4 3 - 0 0 0 1 - 3 0

e. The motors are composed of thefollowing subassemblies and components.

(1) Motor tube and head closureassembly. Integral and non-integral bulk-head tubes are used with the rocket motors.The forward end of the motor tube is inter-nally threaded to accommodate the warhead.The integral bulkhead motor tube has themotor tube and head closure formed in onepiece by impact intrusion. It has no blow-out disk. The non-integral bulkhead motortube is made of aluminum alloy. The motorhead is closed at the aft end by a thin scoreddisk. The disk functions as a blowoutdiaphragm.

(2) Propellant grain and associatedfittings. The propellant grain is internally’burning grain. It is inhibited on both endsand spirally wrapped with inhibiting tapealong the external surface.

(3) Igniter. The igniter Mk 125contains one electrical squib. Currentpassing through the squib bridgewire gen-erates the heat necessary to ignite the squibmix which in turn ignites the powder in theigniter.

(4) Nozzle and fin assembly. Thenozzle and fin assembly consists of a nozzleassembly (one nozzle plate, four inserts,and seals or a burst diaphragm), a fin-actuating mechanism, four fins and a finretainer. It is attached to the aft end ofthe motor tube by a lockwire. Older motorshave stepped-end lockwires; on new produc-tion items, the stepped-end has beeneliminated.


The Mk 40 Mods 1 and 3 have integralbulkhead motor tubes whereas the Mk 40Mod 0 has a non-integral bulkhead tube.

The igniter of the Mod 3 motor differsfrom that of the Mods 0 and 1 motors inthat the igniter has been modified to in-corporate a carried, frangible case inlieu of the blowout plug and the squib islocated on the periphery of the case in-stead of the center of the case. TheM230 has the same configuration, weightand center of gravity as the M151 war-head. Standard M151 metal parts arefilled with an inert filler material havingthe same density as Composition B4 tomanufacture this warhead.

Functioning:

a. Ignition. Functioning of the 2.75-in. rocket with an M230 warhead beginswhen the firing circuit switch is closed.Current passes through the launcherfiring contact to the igniter in the rocketmotor. This current generates the heatnecessary to initiate the igniter charge,which ignites the propellant grain. C o m -bustion gases from the burning propellantpressurizes the chamber and exhaustthrough the nozzle, providing the unequalforces required for rocket thrust,

b. Fin Operation. The thrust of thenozzle exhaust blows off the fin retainerand releases the fins. Upon clearing thelauncher, the fins are opened by theforce of the fin actuating piston pushingon the heels of the fins. The fins areheld by the crosshead of the piston atan angle of 45° with the axis of the mototube.

c. Fuze Functioning. The rocket fuzeM435 is entirely inert.

d . Rocket Functioning. The warheadis entirely inert and is used for practiceonly.

3 - 2 0

T M 4 3 - 0 0 0 1 - 3 0

Tabulated Data:

Warhead model - - - - M230T y p e - - - - - - - - - - - P r a c t i c eWeight ( fuzed) - - - - - 9 .4 lbLength (w/o fuze) - - - - - 12, 9 in.Filler:

T y p e - - - - - - - - - I n e r t m a t e r i a lW e i g h t - - - - - - - - 2 . 3 l b ( 1 0 4 4 g )

Body material - - - - - - - - IronColor - - - - - - - - - - Blue w/white

markingsF u z e - - - - - - - - - - - M 4 3 5

*DODAC ( fuze ) - - - - - 1340-J318

Packing box:Weightw / c o n t e n t s - - - - - 1 2 7 l bDimensions - - - - 6 2 - 1 3 / 1 6 i n , x

8-11/16 in. x9-1/2in.

C u b e - - - - - - - - - 3.5 ft3

Shipping and storage data:Storage class/SCG - - - - - - - - - -

DOT shippingc l a s s - - - - - - - - -DOTd e s i g n a t i o n - - - - -

F ie ld s torage - - -DODAC - - - - - - - - -

Drawing number - - - - -Temperature limits:

F i r i n g - - - - - - - -

Storage - - - - - - -

Packing - - - - - - - - -

1. 2C (12)

B

ROCKET AMMU-NITION WITHINERT LOADEDPROJECTILESGroup B1340-H8289242550

-65° to +150oF(-53 .35°to+64 .9 oC )- 6 50 to +150 oF(-53 .35°to+64 .9oC )1 per fiber container;4 containers perwooden box

Packing box:WeightW/contents ------ 59, 0 lbDimensions - - - - - 20 -13 /16 in . x 8 -1 /4

in. x 9-3/32 in. )

Cube - - - - - - - - - - 0 . 9 f t3

Shipping and storage data:Storage class/S C G - - - - - - - - - - - N / ADOT shippingc lass - - - - - - - - - N / ADOT designation -- NON-EXPLOSIVE

AMMUNITIONFie ld s torage - - - - N/A

*DODAC ‘ - - - - - - - - - 1 3 4 0 - H 8 3 1Drawing number ---- 9221050Packing for completer o u n d - - - - - - - - - - - - 1 rocket consisting

of Warhead, M230 w/Fuze M435 andRocket Motor Mk 40,Mod 1 per fiber con-tainer; 4 containersper wooden box

Motor (Mk 40 Mod 3) - 9220803Packing:

inner (rocket)P A 4 7 - - - - - - - - - - 9 2 3 5 9 6 1Outer (warheadsection w/fuze/motor) - - - - - - - - - 9 2 3 0 1 1 4 , 9 2 3 5 8 4 1

References:SC 1340/98-ILTM 9-1340-222-20TM 9-1340-222-34

*See appropriate supply catalog for indivi-dual NSN’s pertaining to this (these)DODAC(s).

3 - 2 1

TM 43-0001-30


3 - 2 2

TM 43-0001-30

ROCKET, PRACTICE, 2.75-INCH W/INERT WARHEAD WTU-1/B


Std AMCTCM or OTCM 36841 and 9153.

Use .

This warhead is used for training andsupport testing of other rocket components.

Description:

a. The WTU-1/B warhead is an inertslug warhead having the same shape, weightand center of gravity as the standard M151warhead. The warhead does not contain afuze.

b. This warhead simulates flight andtrajectory characteristics of the M151warhead.

Differences between Models: N/A

Functioning:

a. Functioning of the 2. 75-in. rocketbegins when the firing circuit switch isclosed. Current passes through thelauncher firing contact to the igniter in therocket motor. This current generates theheat necessary to initiate the igniter charge,which ignites the propelling grain. Com-bustion gases from the burning propellantpressurize the chamber and exhaust throughthe nozzle, providing the unequal forcesrequired for rocket thrust.

b. The thrust of the nozzle exhaustblows off the fin retainer and releases thefins. Upon clearing the launcher, the finsare opened by the force of the fin actuatingpiston pushing on the heels of the fins.The fins are held by the crosshead of thepiston at an angle of 45° with the axis ofthe motor tube.

3 - 2 3

T M 4 3 - 0 0 0 1 - 3 0

Tabulated Data:

Warhead model --- W T U - 1 / BT y p e - - - - - - - - - - P r a c t i c eW e i g h t - - - - - - - - - 8 . 7 l bL e n g t h - - - - - - - - 1 6 i n .Body material - - - Gray ironColor - - - - - - - - - Blue with white

markings

Packing - - - - - - - - - - 1 per f iber conta iner ;4 containers perwooden box

Packing box:Weightw/contents ----- 59 lb (26550 g)Dimensions - - - - _ 20-13/16 in. x 8-1/4

in. x 9-3/32 in.

C u b e - - - - - - - - - 0.9 ft3

* D O D A C - - - - - - - - - 1 3 4 0 - H 6 6 3

Drawing number ---- 2618015

Drawings:Warhead metalparts assembly --- 656195Packing (inner) --- 9231003Packing (outer) --- 9888110 & 9230114

References:TM 9-1340-222-20TM 9-1340-222-34SC 1340/98-IL

*See appropriate supply catalog for indi-vidual NSN’s pertaining to this (these)DODAC(s).

3 - 2 4

TM 43-0001-30

ROCKET, FLARE, 2.75-INCH W/M257 ILLUMINATING WARHEAD


STD, LCC-A, TT, HQDA, Jan 76

Use:

To provide helicopters with target illuminat-ing capability from a safe standoff distance in ahostile environment.

Description:

This flare rocket is an air-to-ground rocketprimarily deployed from rotary-wing and otherlow-speed aircraft. It is employed with the low-spin folding-fin MK40 motor and with the spinstabilized wrap around fin MK66 motor Mods1,2, and 3.

The M257 illuminating warhead consists ofan ignition system, flare, main parachute,drogue parachute assembly and an integralfuze and delay assembly. The warhead isenclosed in an aluminum case.

The setback-actuated fixed time integralfuze provides a standoff’ distance of approxi-mately 3,000 meters. The arming fuze anddelay assembly is actuated by motor accelera-tion.

The rocket motor is described in Chapter 5.

Differences between Models N/A

Functioning

The rocket with warhead, flare, M257, isfired from helicopter with standard 2.75-in.motor MK40 or MK66 to attain elevation between 2000 and 4000 ft at 3000 m down-range, Upon rocket launch, the M442 fuzearms upon acceleration (17 G’s approximatelyrequired ). After 1.5 seconds (at motorburnout), the fuze functions initiating delaytrain, After nine seconds, delay ignites firstexpulsion charge in fuze assembly. Gas pres-sure forces pusher plate forward, shears pin.

Change 10 3-25

TM 43-0001-30

separates motor and adapter section fromremainder of warhead. Rocket velocity is now800 fps approximately.

The deflector plate, attached by cable tomotor adapter, is extended into airstream,deflects path of motor and adapter. Pusherplate, attached to drogue chute, deploys drogue,Rocket warhead velocity then decreases to 200fps, approximately, during the next two seconds.

Upon deployment of drogue chute, the gasgenerator is activated by pull on lanyardattached to drogue. After two seconds, tile gasgenerator functions the second expulsioncharge located in retainer block of drogue hous-ing. Gas pressure forces pusher plate forward,shearing pins and separating drogue housingfrom main chute insert and candle assembly,

The pusher plate is attached by a threadlineto the pilot chute. The pilot chute is deployed,and, in turn, pulls bag off main chute. Themain chute now deploys the steel cable which isattached to the main chute shroud lines on oneend, and, in turn, pulls a lanyard attached tocandle igniter assembly.

The pull on the lanyard rotates a bellcrank,releasing the firing pin. The firing pin fires arifle primer, which fires boron pellets. Theboron pellets ignite a propellant wafer.Propellant ignites the candle. Ignition gasespressurize nose cap, blowing it free.

The candle, suspended from the main chute,is now burning. During the first 15 seconds,the igniter housing is burned away, The candledescends at 15 fps, burns for 100 seconds with aminimum light output of one million candlepower (CP).

Tabulated Data:

Rocket:Type ----------------------------

Diameter ----------------------Length (Max) -----------------

Weight --------------------------

Performance:Operating temperature

limits -------------------------

Maximum velocity ----------

Warhead:Model ---------------------------Type ----------------------------Body ----------------------------Color ----------------------------

Diameter ----------------------Length -------------------------Weight --------------------------

Candle characteristics:Burn time ---------------------Light output ------------------Parachute descent rate----Composition ------------------

Weight . . . . . . . . . . . . . . . . . . . . . . . . .

Fuze:Model ---------------------------Type ----------------------------

Diameter ----------------------Length:

Overall ----------------------Weight -----------------------Arming time ---------------

MK40, Mod 3MK66 Mod 1, 2.and 32.75-in. nominal68.22 in. (w/MK40Mod 3 motor)70.975 in. (w/MK66series motor)21.8 lb (w/ MK40Mod 3 motor)24.0 lb ( w/MK66series motor)

-25° to + 140°F(-31.35 o to+59.40°C)1600 fps (488 mps)

M257FlareAluminumOlive drab w/whitemarkings2.75-in.31.5-in.10.8 lb

120 sec nominal1 mil cp min15 fps approxMagnesiumSodium Nitrate5.44 lb (2.47 kg)

M442Setback actuated,fixed time1-5-in.

3.1-in.0.6 lb1.1 sec

3-26 Change 10

TM 43-0001-30

Packing ---------------------------

Box:Weight w/contents

(6 fiber containers w/3warheads and 3 motors.unassembled ---------------

Dimensions -------------------

Cubic contents (withfiber container) -----------

Shipping and storage data:Storage class/SCG ----------DOT shipping class --------DOT designation ------------

1 warhead per fibercontainer, 1 motorper fiber container,unassembled

131 lb (58950 g) W/MK40 Mod 3 motor132,5 lb (60101 g)w/MK66 Seriesmotor46-3/16 in. x 11-7/8in. x 9-9/32 in. w/MK40 Mod 3 motor48-1/16 in. x 12-1/4in. x 9-3/8 in. w/MK66 series motor

3 ft3

1.2G (08)AROCKET AMMU-NITION WITHILLUMINATINGPROJECTILE

Field storage ----------------- Group D

DODAC --------------------------- 1340 -H180 w/MK40 Mod 3 motor1340-H181 w/MK66 Mod 1 motor1340-H182 w/MK66 Mod 2 motor1340-H183 w/MK66 Mod 3 motor

Drawings:M257 WHD -------------------9332220

w/MK40 - 3 motor ------- 10399105w/MK66 - 1 motor ------- 13058370-5w/MK66 - 2 motor ------- 13058370-6w/MK66 - 3 motor ------- 13058370-7

Packing:w/MK40 - 3 motor ------- 9294492w/MK66 series motor --- 9357963

References:TM 9-1340-222-20TM 9-1340-222-34

Change 10 3-27 (3-28 blank}

TM 43-0001-30

ROCKET, 2.75-INCH, SMOKE SCREENING WP, M259


STD AMCTCM or OTCM 08786008

Use:

This rocket is used to provide a protec-tive smoke screen. A group of rockets willprovide a smoke screen for approximatelyfive minutes. It is usually deployed fromlow speed rotary-wing aircraft.

Description:

The rocket warhead M259 consists of analuminum casing, an internal canisterassembly and a mechanical fuze with delaycharge. The canister assembly consists of

ten white phosphorous (WP) filled sub-munitions, a central burster, and a pyro-technic delay detonator system. Thecanister is 2-1/2-in. in diameter and 16-in.long with a rear end plate containing acentral burster tube and a forward endplate containing a WP filling port and aclosure plug. The submunitions are per-forated steel sheet formed into two sets offive pie shaped containers packed withfiberglass. The fiberglass serves as amatrix for physically holding the WP andit restricts the flow of WP during func-tioning to produce a greater than five minsmoke source. The central burster isprimacord. The pyrotechnic delay detona-tor system initiates the burster. TheM446 fuze is a mechanical escapement

3 - 2 9

T M 4 3 - 0 0 0 1 - 3 0

type with a 4-1/2 second pyrotechnic delay,arming on acceleration and functioning atdeceleration. The warhead base is exter-nally threaded for attachment to a standardMk 40 Mod 3 motor.

Functioning:

When the rocket motor is actuated thefuze is armed. Six seconds after launchthe fuze actuates the expulsion charge toeject the canister assembly out the nose ofthe warhead, approximately 2500 m downrange. This charge also ignites the centralburster in the canister assembly, whichafter a 0.25 second delay, initiates theburster charge. When the burster chargefunctions, it ruptures the canister and dis-perses the submunitions.

Tabulated Data:

Rocket:Model - - - - - - - -Type - - - - - - - --Weight - - - - - - - -

Length - - - - - - --

Diameter - - - - - -Components:

Fuze - - - - - - ---Weight - - - - - - --Type - - - - - - - --

Warhead:Weight - - - - - - - -Diameter - - - - - -Length - - - - - - - -

Filler:Type - - - - - - - - -Weight - - - - - - - -

M259White phosphorous19.6 lb (motor +whd)62.9 in. (motor +whd)2.75 in.

M446

0.6 lb (272 g)Mechanical-setbackactuated fixed time

8.75 lb2.75 in.25.6 in.

White phosphorous3.51b (1.59 kg)

Temperature limits:Firing - - - - - - - - -40o to +150oF

(-39.6° to +64.9oC )

Packing - - - - - - - - - 4 rockets consistingof Warhead, Smoke,WP, M259 withrocket motor perfiber container; 4containers perwooden box

Packing box:Weight - - - - - - - - 135.0 lbDimensions - - - - - - 72-4/5 in. x 8-3/4

in. x 9-1/2 in.

Cube - - - - - - - - - 3.5 ft3

Shipping and Storage Data:Storage class/SCG - - - - - - - - - 1.2H (12)DOT shippingclass - - - - - - - - - ADOT designation- - ROCKET AMMUNI-

TION W/SMOKEPROJECTILESEXPLOSIVE A ANDFLAMMABLELABELS REQUIRED

Field storage - - - - - Group CDODAC - - - - - - - - - 1340-H116Drawing number - - - - - - D90-1-332

References:TM 9-1055-460-14TM 9-1090-202-12TM 9-1090-203-12TM 9-1300-206TM 9-1340-222-20TM 9-1340-222-34TM 750-244-5-1

3 - 3 0

TM 43-0001-30

ROCKET, DUAL PURPOSE, 2.75-INCH HE W/WARHEAD, M247


LP 9354, LP-U 04736108

Use:

To meet the needs of simultaneouslydefeating enemy armor and personnel.

Description:

A low-spin folding-fin aircraft rocket(LSFFAR), air-to-ground primarily de-ployed from rotary-wing and other low-speed aircraft.

The warhead section configurationmatches the weight and flight characteristicsof the M151 HE warhead. The fragmentatingbody is a take-off from the M229 HE war-head. The shaped charge section is thecopper liner core which was developed fora light antitank weapon (LAW).

The warhead employs the M438 fuze.The armor penetration of this warhead isapproximately the same as the M72 LAWwith antipersonnel performance approxi-mately 70 percent of that of the M151 HEwarhead.

Functioning:

a. Fuze Functioning. The M438 is anintegral point initiating, base detonatingfuze for the M247 dual purpose warhead.The quick-response nature of the M247warhead program dictated that standard,proven components be used for the designof its fuze. Therefore, the M438 fuzesystem consists of the initiating crystalfrom the M72 LAW, and the safety andarming device, thermal battery, and im-pact switch from the M429 proximity fuze.A component board assembly (CBA) is in-corporated to provide fuze intelligenceand safety,

3 - 3 1

T M 4 3 - 0 0 0 1 - 3 0

Ideally, the fuze is initiated by thecrystal upon impact. This provides maxi-mum performance of the warhead. A“spiked” target impact or a graze impact

will function the fuze through the backupimpact switch. However, the shapedcharge effect may be reduced. The CBA,which interprets the impact signal, alsoprovides an impact sensitivity feature whichallows some vegetation penetration prior tofunctioning.

Since the M429 S&A has a rearwardfiring detonator arrangement, the boosteris located at the aft end of the fuze. Thisarrangement, unique in contemporaryordnance practice, is performing success-fully and reliably.

Safety features include:

(1) A pre-armed fuze capable of beingfired only for the duration of the life of thebattery (30 seconds). After this time haselapsed, the fuze cannot be functioned byany mode.

(2) The fuze, upon arming, will sensea shorted impact switch and will fail safeto preclude functioning at arming.

(3) An impact switch which precludesbattlefield contamination with live duds.

d_. Rocket Functioning. When therocket is launched the fuze becomes armedfrom inertial forces resulting from sus-tained acceleration. This frees the unbal-anced rotor to turn and lock the explosivetrain in the armed position. Upon impactwith a target, the piezo electric crystal iscrushed and initiates the explosive train.Upon detonation, the warhead body shattersinto small high-velocity fragments. Thecopper cone is collapsed by the detonationforming a stream of high-velocity particleswhich penetrate armor.

Tabulated Data:

Warhead model - - - -Type - - - - - - - - - --Weight (fuzed) - - - - -Length - - - - - - - - -Filler:

Type - - - - - - - - -Weight - - - - - - - -

C o l o r - - - - - - - --

Temperature limits:Firing - - - - - - - - - -

Storage - - - - - - - - -

Drawing number - - - - - -Packing for completeround - - - - - - - - - - -

Packing box:Weightw/contents - - - - -Dimensions - - - - -

M247HE dual purpose8.8 lb18.68 in.

Comp B42.0 lb (0.91 kg)Black w/yellowmarkings

-65° to +150°F(-53. 35° to +64. 9°C)-65° to +150°F(-53.35° to +64.9oC)9230114, 9235841

1 rocket consistingof warhead HE, dualpurpose with fuzeM438 and motor Mk40, and Mods, 1 perinner pack, 4 perbox

162 lb62-13/16 in. x8-11/16 in. x 9-1/2in.

Cube - - - - - - - - -- 3.5 ft3

Shipping and storage data:Storage class/SCG - - - - - - - - - 1.lEDOT shippingclass - - - - - - - - - ADOT designation- - - - - ROCKET AMMUNI-

TION W/EXPLOSIVEPROJECTILES

Field storage - - - - - - Group FDODAC - - - - - - - 1340-H826

Drawing number - - - - - - 9258191References:

TM 9-1340-222-20 SC 1340/98-ILTM 9-1340-222-34

3 - 3 2

TM 43-0001-30

ROCKET, HIGH - EXPLOSIVE, 2.75 INCH, MULTIPURPOSESUBMUNITION (MPSM) W/M261 WARHEAD)


STD (LCC-A).

Use:

The warhead contains 9 each multipurposesubmunitions for use against personnel, materiel,and light armor.

Description:

The complete round consists of a warheadwith an integral fuze and a rocket motor.

The warhead consists of; (1) a nose cone,assembly, (2) a warhead case, (3) an integral fuze,(4) 9 submunitions, and (5) an expulsion chargeassembly. The nose cone assembly, a plastic conebonded to a metal cup-shaped base, is attached tothe body by shear pins The body is a hollowcylinder loaded with 9 full caliber multipurposesubmunitions (MPSM). Each submunition has aRam Air Decelerator (RAD), folded, which nestsinto the shaped charge cone of the submunitionahead; the 9th (forward) submunition nests intothe forward cup which makes up the base of thenose cone, A metal pusher plate is located just aftof the submunition cargo stack and is forward of

Change 3 3-33

TM 43-0001-30

the expulsion charge assembly. The threaded endof the body is machined internally toaccommodate a base detonating, remote settable,variable range fuze.

The primary warhead fuze, M439 RC, is aresistance-capacitance electronic variable timedelay fuze. The time delay is remotely set for thedesired functioning distance(time) by chargingthe circuit from the fire control center. The fuzebegins timing at the first motion of the rocket andwill function at the prescribed time if the Safetyand Arming device (S&A) is armed. The S&A is amechanical acceleration integrator with anunbalanced rotor holding the M84 electricdetonator and a runaway escapement. Anacceleration greater than 27G is necessary to armthe fuze. The M439 RC fuze is a base mounted,forward firing fuzc. The Fuze connector cableextends from the fuze, through the warhead (in alengthwise channel), and exits the ogive forconnection to the launcher by an umbilical cable.

The HE, MPSM M73 consists of a steel bodywith a fragmenting wall filled with Composition Bexplosive incorporating a shaped charge liner,LX14 booster, explosive lead charge, M230 omni-directional fuze with M55 detonator, wave shaper,and fabric drag device (RAD). The fragmentingbody produces 10 grain fragments with amaximum velocity of approximately 5,000 fps.

The spin stabilized wraparound fin rocket isan air-to-ground rocket primarily deployed fromrotary-wing and other low-speed aircraft. It canalso be used on Air force and Navy jet aircraft, aswell as in the Mobile Ground Launcher System.

Functioning:

The rocket motor functions when currentpasses through the launcher firing contact to theigniter in the rocket motor. The current generatesthe heat necessary to detonate the igniter chargewhich ignites the propellant grain. Combustiongases from the burning propellant pressurize thechamber and exhaust through the nozzle,providing the unequal forces required for rocketthrust.

Upon receipt of the fire signal from the pilot,

the remote fuze setter processes the proper timeconstant (delay) to the M439 RC electronic time fuzeimmediately prior to firing the rocket. The inter-valometer delivers a 160 millisecond pulse interval.The pulse is divided into a 45 millisecond fuzecharging pulse, followed by a 45 millisecond rocketfiring pulse. The remaining 70 milliseconds are usedas dwell interval to maintain spacing between pairs ofrockets fired.

After the rocket is fired and experiences sustainedacceleration, the setback weight of the S&A devicewithin the fuze moves rearward sufficiently to allowthe roller attached to the unbalanced rotor to moveout of the groove provided by the setback weight.Once the roller is free, the unbalanced rotor rotates inresponse to the acceleration forces. The rotation of therotor is delayed by a runaway escapement whichprovides an arming delay (a function of theacceleration) until the rocket is a safe distance fromthe aircraft. When the setback weight experiencesthe necessary magnitude of acceleration, the rotorwill lock into place with the M84 detonator lined upwith the propellant charge and the fuze is armed. Thedetonator is now connected to the firing circuit, theconnection between the electronic module and theumbilical cable is broken, and electronic timing isstarted.

From 1.2 to 25 or more seconds after firing,depending upon the range setting, the detonator isinitiated electrically and ignites the expelling charge.Gases from the expelling charge force the pusher plateand cargo stack forward, shearing the nose cone(ogive) retaining pins and ejecting the submunitionsinto the airstream. The actual ejection range is somedistance from the target as determined by the firecontrol computer along with the aircraft QE based onaircraft elevation, ground speed, and range to target.

The M73 MPSM operation is as follows: Uponrelease of the submunitions into the airstream, theRAD high drag device inflates by Ram air forcedthrough holes in air scoops. The arming stem in theM230 fuze breaks the safety shear wire and retracts,freeing the slider which is then moved across therunaway escapement delay to bring the detonator intoline with the firing pin. The fuze is now fully armed.

3-34 Change 3

If the submunition should be subjectedto an impact force applied in any direc-tion, the sensing mass will move andrelease the lacking ball holding thefiring pin. The firing pin drives for-word and initiates the detonator. Theshaped charge liner penetrates armor orother material in line with its axisand the submunitian body shatters intosmall, high velocity fragments to de-feat soft targets.

Tabulated Data:

Warhead:Type ------------------ 2.75-in.

Rocket, HE,MultipurposeSubmunition(MPSM)

Weight (fuzed) -------- 13.6 lbLength (overall) ------ 26.84 in. (max)Body material ---------

Fuze (integral):Type (electronic) -Length ------------

Diameter ----------

Delay element -----

Delay time --------

Detonator ---------

Setback to arm ---

Extrudedaluminum

M439 RC2.77 in.1.48 in. (max)ElectronicVariableM84 electrical27 g

Arming distance --- 96-126 mExpulsion charge: --------- M10(8O%), black

powder(20%)Propellant weight ----- 5.5 g

Filler (payload):Type ------------------ M73 HE Multi-

purpose Sub-munition (MPSM)

Quantity -------------- 9 eaWeight:

Each -------------- 1.2 lbTotal ------------- 10.8 lb

HE Charge (Comp B):Net HE:

Quantity:Each ---------- 0.2 lbTotal --------- 1,8 lb

Booster LX14:Each ---------- 0.G31 lbTotal --------- 0.279 lb

Detonator M55:Charge ------------ Lead azide -

NOL#130 55 mgLead, PBX-N5 ------ 120 mg

Color --------------------- Olive drab withyellow mark-ings and ayellow band

TM 43-0001-30

Temperature Limits:Firing ------------- - 5 0o to +150°FStorage ------------ -50 to +160°F

Packaging for completeround ---------------- 1 rocket consists

of warhead M261and rocket motorMK66 Mod 1 perfiber container;4 containers perwooden box

Packing box, wooden:Weight with contents(4 warheads in con-tainers) :

With inertmotors -------- 138 lb

With MK66motors -------- 162 lb

Weight unloaded ---- 32 lbDimensions --------- 72-13/16 X 8-11/1

x 9-1/2 in.Cube --------------- 3.5 cu ft

Shipping and Storage Data: (Warhead w/omotor)

Quantity-distanceclass ---------------- 1.1

Storage compatibilitygroup ----------- ----- D

DOT shipping class ----- ADOT designation -------- EXPLOSIVE PRO-

JECTILES -DANGEROUS

Field storage ---------- Group F

Shipping and Storage Data:Complete Round)

Quantity-distanceclass ---------------- 1.1

Storage compatibilitygroup ------ ------ ---- E

DOT shipping class ----- A

DOT label -------------- Explosive ADOT designation -------- ROCKET AMMUNITION

W/EXPLOSIVE PROJECTILES

Field storage ---------- Group FDODAC for complete

round ---------------- 1340-H464

References:

TM 9-1300-200, Chapter 5TM 9-1300-206TM 9-1055-460-14TM 9-1340-201TM 9-1340-222-20

Change 1 3-35

TM 43-0001-30

TM 9-1340-222-34SB 742-1340-92-010SB 742-1340-94-301MIL-STD-1168A (28 Feb 75)

Drawings: AFTERSECONDS

9334097, Warhead, 2.75-Inch HighExplosive M261

9334122, M261, Loaded Case Assembly9334143; Grenade, General Purpose

High Explosive M73233AS400, (Navy), MK66, Mod 1 Motor,

Loaded Assembly

WARNING LESS

● PREMATURE EXPULSION OFSUBMUNITIONS FROM THEM261 WARHEAD AND ITSEFFECT ON FAST MOVINGAIRCRAFT ARE: NORMAL DE-PLOYMENT OF SUBMUNITIONWARHEADS WILL BE FROM AHELICOPTER HOVER POSITION.HOWEVER, IF THE AIRCRAFT ISREQUIRED TO FIRE WHILEMOVING FORWARD AT HIGHSPEED (90 KNOTS AND HIGH-ER), THE AIRCRAFT CAN FLYINTO/UNDER THE SUBMUNI-TIONS IN THE EVENT OFPREMATURE FUNCTIONING OFTHE WARHEAD. THIS IS DUE TOTHE FIRING QUADRANT ELEVA-TION (QE) AT LONG RANGE

TARGET ENGAGEMENT (ABOUT6 KM) AND ASSUMES THEAIRCRAFT WILL CONTINUE TOFLY FORWARD IN A STRAIGHTLINE (SAME AZIMUTH ANDELEVATION) FOR ABOUT 8

FIRING.PROBABILITY OF PREMATUREEXPULSION IS HIGH (1 IN 1000)AND THE RESULTING HAZARDRISK OF FLYING INTO/UNDERTHE SUBMUNITION CLUSTER ISALSO HIGH. DEPENDING UPONTHE NUMBER OF ROUNDSFIRED IN ANY GIVEN MISSION,THE RISK CHANGES FROM 2 IN1000 TO 7.6 IN 100.

● CORRECT USE OF THE M261SUBMUNITION WARHEADS ATRANGES THAN 1000METERS IS AS FOLLOWS:ALTHOUGH THE M261 WARHEADIS DESIGNED FOR MINIMUMENGAGEMENT RANGE OF 1000METERS, THE CURRENTROCKET MANAGEMENT SYS-TEM DOES ALLOW A LOWERMINIMUM RANGE SETTING OF500 METERS. AT 500 METERS,DUE TO THE DECREASE INSEPARATION DISTANCE BE-TWEEN THE AIRCRAFT ANDTHE SUBMUNITIONS, THEHAZARD RISK IS ESTIMATED TOBE FROM 1.57 IN 10 MILLION TO5.97 IN 1 MILLION, DEPENDINGUPON T H E N U M B E R O FROUNDS FIRED. THE ACCEPT-ABLE LEVEL OF RISK IS 1 IN 1MILLION FOR AMMUNITION.

3-36 Change 8

TM 43-0001-30

ROCKET, 2.75-INCH, PRACTICE W/M267 WARHEAD

Type Classification: The warhead consists ofassemblv. (2) a warhead case.

(1) a nose cone(3) and internal

STD (LCC-A).

Use:

The warhead contains three each smoke sig-nature multipurpose submunitions and six simu-lators for use in training and for practice firing.

Description:

The complete round consists of a warheadwith an integral fuze and an Mk66 Mod 1, 2 or3 spin-stabilized, wrap-around fin rocket motor.

fuze, (4}’ nine submunitions, and (5) an expul-sion charge assembly, The nose cone assembly,a plastic cone bonded to a metal cup-shapedbase, is attached to the body by shear pins. Thebody is a hollow cylinder loaded with three fullcaliber practice submunitions and six simula-tors. Each submunition has a Ram AirDecelerator (RAD), folded which nests into theshaped charge cone of the submunition ahead;the ninth forward simulator assembles into thebase of the nose cone, A metal pusher plate islocated just aft of the submunition cargo stackand is forward of the expulsion charge assem-bly. The threaded end of the body is machinedinternally to accommodate a base-detonating,remote settable, variable range fuze.

Change 12 3-37

TM 43-0001-30

The primary warhead fuze, M439 RC, is aresistance-capacitance electronic variable timedelay fuze. The time delay is remotely set forthe desired functioning distance (time) by charg-ing the circuit from the fire control center. Thefuze begins timing at the first motion of therocket and will function at the prescribed timeif the Safety and Arming Device (S&A) isarmed. The S&A is a mechanical accelerationintegrator with an unbalanced rotor holdingthe M84 electric detonator and a runawayescapement, An acceleration greater the 27G isnecessary to arm the fuze. The M439 RC fuzeis a base mounted, forward firing fuze. Thefuze connector cable extends from the fuze,through the warhead (in a lengthwise channel),and exits the ogive for connection to thelauncher by an umbilical cable,

The M75 SM consists of a steel body with asmoke signature flash charge and the identicaloutside configuration as the M73 HE grenade.It has the same weight and center of gravity asthe loaded HE grenade. The M231 omni-directional fuze is used in this practice grenade,

The spin-stabilized, wrap-around fin aircraftrocket is an air-to-ground rocket primarilydeployed from rotary-wing and other low-speedaircraft. It can also be used on Air Force andNavy jet aircraft, as well as in the MobileGround Launcher System.

Functioning:

The rocket motor functions when currentpasses through the launcher firing contact tothe igniter in the rocket motor, The current gen-erates the heat necessary to detonate theigniter charge which ignites the propellantgrain. Combustion gases from the burning pro-pellant pressurize the chamber and exhaustthrough the nozzle, providing the unequalforces required for rocket thrust.

Upon receipt of the fire signal from the pilot,the remote fuze setter processes the propertime constant (delay) to the M439 RC electronictime fuze immediately prior to firing therocket. The intervalometer delivers a 160 milli-second pulse interval. The pulse is divided intoa 45 millisecond fuze charging pulse, followedby a 45 millisecond rocket firing pulse, Theremaining 70 milliseconds are used as a dwellinterval to maintain spacing between pairs ofrockets fired.

After the rocket is fired and experiences sus-tained acceleration, the setback weight of theS&A device within the fuze moves rearward suf-ficiently to allow the roller attached to the unbal-anced rotor to move out of the groove providedby the setback weight. Once the roller is free,the unbalanced rotor rotates in response to theacceleration forces, The rotation of the rotor isdelayed by a runaway escapement which pro-vides an arming delay (a function of the accelera-

tion) until the rocket is a safe distance from theaircraft, When the setback weight experiencesthe necessary magnitude of acceleration, therotor will lock into place with the M84 detona-tor lined up with the propellant charge and thefuze is armed, The detonator is now connectedto the firing circuit, the connection between theelectronic module and the umbilical cable is bro-ken, and electronic timing is started.

From 1.2 to 25 or more seconds after firing,depending upon the range setting, the detona-tor is initiated electrically and ignites the expel-ling charge. Gases from the expelling chargeforce the pusher plate and cargo stack forward,shearing the nose cone (ogive) retaining pinsand ejecting the submunitions into the air-stream, The actual ejection range is some dis-tance from the target at determined by the firecontrol computer along with the aircraft quad-rant elevation (QE) based on aircraft elevation,ground speed, and range to target.

The M75 SM operation is as follows: Uponrelease of the submunitions into the airstream,the RAD high drag device inflates by Ram airforced through holes in air scoops. The armingstem in the M231 fuze breaks the safety shearwire and retracts, freeing the slider which isthen moved across the runaway escapementdelay to bring the detonator into line with thefiring pin. The fuze is now fully armed. If thesubmunition should be subjected to an impactforce applied in any direction, the sensing masswill move and release the locking ball holdingthe firing pin. The firing pin drives forwardand initiates the detonator, The detonatorignites the smoke pyrotechnic charge, resultingin a brilliant flash and a puff of white smoke,

Tabulated Data:

Warhead:Type ----------------------------

Weight (fuzed) ---------------Length (overall) -------------Body material ----------------

Fuze (Integral):Type (electronic) ---------Length -----------------------Diameter --------------------Delay element -------------Delay time ------------------Detonator ------------------Setback to arm------------Arming distance ----------

Expulsion charge --------------

Propellant weight -----------Filler (payload):

Type ----------------------------Quantity -----------------------

2.75-Inch Rocket,Practice, M26713.6 lb26.86 in. (max)Extruded alumi-num (one piece)

M439 RC2.77 in.1.48 in. (max)ElectronicVariableM84 electrical27 g96-126 mM10 (80%), blackpowder (20%)5.5 g

M75 SM3 ea M75 and 6 eainert simulators

3 - 3 8 Change 12

Weight:Each -------------------------- 1.2 lbTotal ------------------------- 10.8 lb

Smoke charge:Aluminum powder ------- 67%Potassium Perchlorate - 33%

Net quantity:-------------------------- 0.04 lb (17 g)

Total ------------------------- 0.12 lb (51 g)Detonator M55:

Charge ----------------------- Lead azide - NOL#130 55 mg

Color ------------------------------ Blue with whitemarkings andbrown band

Temperature limits:Firing ----------------------------50° to + 150oFStorage --------------------------50o to + 160oF

Packing for completeround -------------------------- 1 rocket consists of

warhead M267 androcket motor Mk66Mod 1, Mod 2, orMod 3, per fibercontainer; 4 con-tainers per woodenbox

Packing box, wooden:Weight with contents(4 warheads in containers):

With inert motors -------- 138 lbWith Mk66 motors ------- 162 lb

Weight unloaded ------------32 lbDimensions ------------------- 72-13/16 x 8-11/16

x 9-1/2 in.Cube ---------------------------- 3.5 cu ft

Shipping and Storage Data (warheadonly):

Deleted

Shipping and Storage Data (completeround):

Hazard class/division andstorage compatibility

-- - - - - - - - - - - - - - - - - - DOT shipping class -----------DOT designation --------------

WITH SMOKE

DODAC ---------------------------

Drawings:M267 warhead ---------------

(04) 1.2 GAROCKETAMMUNITION

PROJECTILE1340-H873 (M267warhead)1340-H463 w/Mk66Mod 1 motor1340-H463 w/Mk66Mod 2 motor1340-H974 w/Mk66Mod 3 motor

9334148

TM 43-0001-30

M267 Loaded CaseAssembly -------------------9334123

Grenade, General Purpose,Practice, M75 -------------9334151

M267 warhead w/Mk66Mod 1 motor --------------- 13058370-2



References:

MIL-STD-1168A (28 Feb 75)SB 742-1340-92-010SB 742-1340-94-301TM 9-1055-460-14TM 9-1300-200, chapter 5TM 9-1300-206TM 9-1340-201TM 9-1340-222-20TM 9-1340-222-34

WARNING

PREMATURE EXPULSION OFSUBMUNITIONS FROM THEM267 WARHEAD AND ITSEFFECT ON FAST MOVINGAIRCRAFT ARE: NORMALDEPLOYMENT OF SUBMUNI-TION WARHEADS WILL BEFROM A HELICOPTER HOVERPOSITION. HOWEVER, IF THEAIRCRAFT IS REQUIRED TOFIRE WHILE MOVING FOR-WARD AT HIGH SPEED (90KNOTS AND HIGHER), THEAIRCRAFT CAN FLY INTO/UNDER THE SUBMUNIIIN THE EVENT ‘OF - P R E -MATURE FUNCTIONING OFTHE WARHEAD, THIS IS DUETO THE FIRING QUADRANTELEVATION (QE) AT LONGRANGE TARGET ENGAGE-MENT (ABOUT 6 KM) ANDASSUMES THE AIRCRAFTWILL CONTINUE TO FLYFORWARD IN A STRAIGHTLINE (SAME AZIMUTH ANDELEVATION) FOR ABOUT 8SECONDS AFTER FIRING.PROBABILITY OF PREMA-TURE EXPULSION IS HIGH (1IN 1000) AND THE RESULTINGHAZARD RISK OF FLYINGINTO/UNDER THE SUBMUNI-TION CLUSTER IS ALSO HIGH.DEPENDING UPON THENUMBER OF ROUNDS FIRED

Change 12 3 -39

TM 43-0001-30

IN ANY GIVEN MISSION, THERISK CHANGES FROM 2 IN1000 TO 7.6 IN 100.

CORRECT USE OF THE M267SUBMUNITION WARHEADS ATRANGES LESS THAN 1000METERS IS AS FOLLOWS:ALTHOUGH THE M267WARHEAD IS DESIGNED FORMINIMUM ENGAGEMENTRANGE OF 1000 METERS, THECURRENT ROCKET MANAGE-MENT SYSTEM DOES ALLOW

3-40 Change 12

A LOWER MINIMUM RANGESETTING OF 500 METERS. AT500 METERS, DUE TO THEDECREASE IN SEPARATIONDISTANCE BETWEEN THEAIRCRAFT AND THE SUB-MUNITIONS, THE HAZARDRISK IS ESTIMATED TO BEFROM 1.57 IN 10 MILLION TO5.97 IN 1 MILLION,DEPENDING UPON THENUMBER OF ROUNDS FIRED.THE ACCEPTABLE LEVEL OFRISK IS 1 IN 1 MILLION FORAMMUNITION.

U.S. GOVERNMENT PRINTING OFFICE: 1993 746-163/70425

PIN:050170-012

TM 43-0001-30

GRENADE, GENERAL PURPOSE, HE: M73MULTIPURPOSE SUBMUNITION (MPSM), HIGH EXPLOSIVE

M73 SUBMUNITION (ARMED)


STD (LCC-A)

Use:

The M261 warhead contains 9 eachMPSM’S M73 for use against personnel, materiel,and light armor.

Description:

The submunition grenade consists of a fullcaliber, cylindrical tapered steel casing, prescoredinternally for controlled fragmentation, a RamAir Decelerator (RAD) device for orientation andstabilization, a truncated shaped charge liner.

wave shaper and the M230 omni-directional fuzewith explosive train. The kill mechanism is atruncated subcaliber, 44° included angle, shapedcharge copper liner 33.02mm (1.3 in.) high. Thesubmunition detonation is initiated by the M230fuze which is armed by the action of the Ram AirDecelerator on ejection from the warhead.

Functioning:

When the warhead fuze functions, theexpulsion charge is initiated and, by means of apusher plate, presses the submunitions forwarduntil the nose cone retaining pins are sheared andthe submunitions are expelled into the airstream.The RAD high drag device inflates and turns thesubmunition forward and toward the ground.

Change 3 3-41

3-42

TM 43-0001-30

The shock of inflation by Ram air forced throughholes in the air-scoops in the RAD exerts a strongdrag on the arming stem in the M230 fuze, inexcess of 20 pounds, which breaks the safetyshear wire. The fuze arming stem retractsapproximately 0.110 inch and the arming pin atthe base of the stem is withdrawn from the slider.The slider is then driven across the runawayescapement delay mechanism by its spring tobring the detonator into line with the firing pin.The fuze is now fully armed. If the submunitionshould be subjected to an impact force applied inany direction (as striking the ground or avehicle), the sensing mass will move and releasethe locking ball holding back the spring loadedfiring pin. The firing pin is driven forward andinitiates the M55 stab detonator. The detonatorsets off, in sequence, the explosive lead, thebooster charge, and the high explosive maincharge, The shaped charge lines penetrates lightarmor or other material in line with its axis andthe submunition body shatters into small, highvelocity fragments to defeat soft tragets.

Tabulated Data:

Nomenclature: Grenade, General Purpose: M73

Length, fuzed with folded RAD(approx) ----------------------------

Diameter (max) --------------------Material, steel, thickness -------Weight, loaded ---------------------Explosive charge, Comp B,

net ------------------------------------Detonator, M55, and PBX-N5 lead, charge ------------------

Rooster LX14 ----------------------Cone, material ---------------------D i a m e t e r - - - - - - - - - - - - - -Height (truncated) ---------------

Angle, included --------------------Standoff -------------------------------

Wave shaper material ----------Fragments:

Weight ------------------Shape. platelet -------------

Total number (approx) --Fuze:---------------------------

Weight (approx) ------------Drawing No. -----------------

Grenade Drawing No. -----------

Comparison of HE and Practice Grenades

,

4 in2.55 in0.125 in1 .2 lb

0. 2 lb (90 g)

1.75 mg0.031 lb (14 g)Copper50.8mm (2 in.)33.02mm(1.3 in. )4 4o

19.3mm(.76 in. )Lead

10 gr2.54x6.15x6.15mm195M2300.25 lb

93338259334143

3 - 4 2 Change 3

TM 43-0001-30

GRENADE, GENERAL PURPOSE, PRACTICE: M75

M75 SUBMUNITION (ARMED)


STD (LCC-A)

Use:

The M267 warhead contains 3 each M75practice submunitions and 6 inert simulators foruse in training,.

Description:

The M75 submunition consists of a steelbody with a smoke signature flash charge. Thebody has the identical outside configuration as

the M73 HE grenade However, the wall isthicker and is machined out so that the finishedgrenade with the smoke capsule has the sameweight and center of gravity as the loaded HEgrenade. The smoke/flash charge consists of 17grams of a mixture of potassium perchlorate(33%) and aluminum powder (67%), The chargeis ignited by the M55 detonator in the M23 omni-directional fuze. The M231 fuze is identicalto the M230 fuze (used with the HE grenade)except that there is no explosive lead and nobooster pellet. There is no wave shaper: thesmoke capsule is directly below the fire hole of thefuze,

Change 3 3-43

TM 43-0001-30

Functioning:

The functioning of the M75 grenade issimilar to that of the M73 HE grenade and thesubmunition fuze M231 functions the same as theM230 fuze. When the grenade is armed (theslider now projects approximately 0.25 inch outof the grenade body), and if it is subjected to animpact force applied in any direction (by strikingthe ground or a hard object), the sensing massmoves on its pivot and releases the locking ballholding back the firing pin. The firing pin, drivenby its spring, strikes the M55 stab detonatorwhich, in turn, ignites the smoke pyrotechniccharge, resulting in a brilliant flash and a puff ofwhite smoke.

Tabulated Data:

Nomenclature: Grenade, General Purpose, Practice: M75

Tabulated Data: (continued)

Length, fuzed withfolded RAD (approx) ---------------

Diameter (max) ----------------------Material ---------------------------------

Weight, loaded -----------------------Smoke charge (33% potassiumchlorate/67% aluminumpowder) --------------------------------

Cone material ------------------------Diameter -------------------------------Height (truncated) -----------------

Angle (included) --------------------Fuze: ------------------------------------

Drawing No. -----------------------Grenade Drawing No ----------

4 in.2.55 in.Steel (lowCarbon)1.2 lb

17 g (0.04lb)Copper50.9mm (2 in.)33.02mm (1.31

in )44M23193451689334151

3-44 Change 3

TM 43-0001-30

ROCKET, SMOKE, SIGNATURE, PRACTICE, 2.75-INCH WARHEAD, M274


STD.

Use:

This warhead is used for training and sup-port testing purpose.

Description:

The M274 warhead is a modified version ofthe WTU-1/B Case Iron Inert PracticeWarhead. The modification consists of the addi-tion of a sealed S&A and smoke cartridge, nosecap, firing in, retainer ring, and blow plugs. It

dis employe with the low-spin folding-fin Mk40motor and the spin-stabilized wrap-around finMk66 motor Mods 1, 2 and 3.

The rocket motors are described in chapter 5.

Functioning

Functioning of the 2.75-inch rocket with anM274 warhead begins when the firing circuitswitch is closed, Current passes through thelauncher firing contact to the igniter in therocket motor. This current generates the heatnecessaary to initiate the igniter charge, whichignites the propellant grain. Combustion gasesfrom the burn propellant pressurize the cham-ber and exhaust through the nozzle, providingthe unequal forces required for rocket thrust.

The acceleration of the rocket motor causesthe S&A device to arm. Upon ground impact,the nose cap collapses and drives the firing pininto the primer, resulting in initiation of thesmoke charge, which provides the visible signa-ture.

Change 11 3 - 4 5

TM 43-0001-30

Tabulated Data:

Rocket:Type ---------------------------- Mk40, Mod 3;

Mk66, Mod 1,2,and 3

Diameter ---------------------- 2.75 in. nominalLength ------------------------- 52.7 in. (w/Mk40

Mod 3 motor);55.473 in. (w/Mk66series motor)

Weight -------------------------- 20.7 lb (w/Mk40Mod 3 motor);22.9 lb (w/Mk66series motor)

Temperature Limits:Storage --------------------------65° to 150oF (-54°

to 65.5°C)Operation ----------------------65° to l50°F (-54o

to 65.5oC)

Warhead:Model --------------------------- M274Type ---------------------------- Smoke signature,. -

Body material ----------------Color- - - - - - - - - - - - - - - - - - - -

Length -------------------------Weight --------------------------

Spotting Charge:Type ----------------------------

Weight --------------------------

Explosive:S&A device --------------------Primer --------------------------Detonator ---------------------Lead -----------------------------Booster -------------------------

Packing ---------------------------

practiceIronBlue, white mark-ings w/brown band16.04 in.9.3 lb

PotassiumPerchlorate/Aluminum Powder70.5 gr

EX-100M104M85NANA

1 rocket consistingof warhead M274and motor per fibercontainer, 4 fibercontainers perwood box

Box:Weight w/contents

(4 fiber containersw/4 complete rockets) ---

Dimensions -------------------

Cube ----------------------------

127 lb (w/Mk40Mod 3 motor);142 lb (w/Mk66series motor)62-13/16 X 8-11/16x 9-1/2 in, (w/Mk40Mod 3 motor);66 x 8-1/2 X 9-1/2in. (w/Mk66 seriesmotor)36 (w/Mk40 Mod 3motor);37 (w/Mk66 seriesmotor)

Shipping and Storage Data (completeround:

Storage class/SCG -------------DOT shipping class -----------DOT designation --------------

DODAC ---------------------------

1.3 CJROCKETAMMUNITIONWITH SMOKEPROJECTILES1340-H872 (M274warhead);1340-H971 w/Mk40Mod 3 motor;1340-H972 w/Mk66Mod 1 motor;1340-H973 w/Mk66Mod 2 motor;1340-H975 w/Mk66Mod 3 motor

Drawings:M274 warhead ---------------W/Mk40 Mod 3 motor -----W/Mk66 Mod 1 motor -----

937025113296200-113058371-6

W/Mk66 Mod 2 motor ----- 13058371-7W/Mk66 Mod 3 motor -----13058371-11

References:

TM 9-1340-222-20TM 9-1340-222-34

3-46 Change 11* U.S. GOVERNMENT PRINTING OFFICE: 1993746-1 63/70422

T M 4 3 - 0 0 0 1 - 3 0

CHAPTER 4

FUZES W/2.75-INCH ROCKETS

4 - 1

T M 4 3 - 0 0 0 1 - 3 0


4 - 2

TM 43-0001-30

FUZE, POINT DETONATING, M423 (M427)

Type Classification: Description:

STD AMCTCM 3233 These. fuzes consist of the followingmajor assemblies:

Use:(1) The striker-pin body assembly con-

These fuzes are oblique impact sensitive, sists of an aluminum body with a press-point detonating, super-quick types. Refer fitted steel striker pin. The lower portionto paragraph 3-1, Table 3-1 for the autbor- of the body is secured to the firing pin bodyized warheads which use this fuze. by a circumferential crimp. Upon impact,

4 - 3

T M 4 3 - 0 0 0 1 - 3 0

crush-up initiates the primer and subse-quent explosive train.

(2) The firing pin body assembly con-sists of a firing pin body, plastic hammer,firing pin sleeve, anti-setback washer,firing pin nut, and firing pin. The threadson the lower portion of the body assemblyare used for assembling the fuze to thewarhead.

(3) The safety-and-arming device con-sists of a rotor-housing assembly and un-balanced rotor assembly, an escapementassembly and setback weight. The unbal-anced rotor assembly houses the primerand detonator and is maintained in theunarmed (out-of-line) position.

(4) The booster assembly consists of abooster housing, lead-in cup and appropri-ate explosive charges. The threads on thebooster housing enable the booster assem-bly to be threaded into the lower portion ofthe firing pin body.

Differences between Models;

Externally the M427 fuze is identical tothe M423 fuze. The M427 differs from theM423 in that its internal construction isdesigned to produce the longer arming timeand arming distance required for launchfrom high-speed aircraft. For the author-ized warheads which use these fuzes, referto paragraph 3-2, Table 3-1.

Functioning:

When the rocket motor is fired, sus-tained acceleration permits the set-back(inertial mass) weight to move rearward.This releases the unbalanced rotor which,in rotating, drives the escapement andgear assembly, The rotor arms when it

has traveled the specified arming distancefrom the launcher. It is locked in thearmed position by a spring-loaded pin. Therotor will return to the unarmed position ifthe minimum rocket energy (product ofacceleration and time) is not sustainedthroughout the arming distance. Upon im-pact, the striker-pin body walls are crushedbetween the target and the firing pin body.The firing pin then impacts with the safetyand arming mechanism, firing the primerand detonator, respectively. The detonatorinitiates the explosive train.

Tabulated Data:

Models - - - - - - - - -

T y p e - - - - - - - - - - -

W e i g h t - - - - - - - - - -Length (total) - - - - -I n t r u s i o n - - - - - - - -D i a m e t e r - - - - - - - -

M423, M427Mechanical, point-detonating0.75 lb4.0 in.0. 90 in.1.75 in.

Shipping and storage data:.Storage class/SCG - - - - - - - - - - - - - - -

DOT shippingclass - - - - - - - - - - - - - - - - - - - -DOTd e s i g n a t i o n - - - - -

F ie ld s torage - - -

DODAC :M 4 2 3 - - - - - - - - -M 4 2 7 - - - - - - - - -

M423-1.2 (04)M 4 2 7 - 1 . 1

M423-C & M427-A

DETONATINGFUZES, CLASS A/CEXPLOSIVES -HANDLE CARE-FULLYDO NOT STOREOR LOAD WITHANY HIGHEXPLOSIVESGroup B

1340-J3491340-J346

4 - 4

Drawing numbers:M 4 2 3 . . . . . . . . . . . . .M427. . . . . . . . . . .

Color . . . . . . . . . . . . . . .

Temperature Limits:Firing . . . . . . . . . . . .

Storage . . . . . . . . . . . .

-65o to +165oF (-53.35oto +73 .15 oC )-65o to +165oF (-53.35ot o+ 7 3 . 1 5oC )

Explosive: train:.Primer . . . . . . . . . . . .Detonator . . . . . . . . .Load . . . . . . . . . . . . . .Booster . . . . . . . . . . .

88836838883745

O l i v e d r a b w / b l a c kmarkings

Stab M104Mk 59TetrylTetryl

Explosive weight . . . . .

Arming distance:M 4 2 3 . . . . . . . . . . . .M427 . . . . . . . . . ..

Rocket terminalangle. . . . . . . . . . . . .

Packing . . . . . . .

Packing box:Weight . . . . . . . . . . .Dimensions . . . . . . .

Cube . . . . . . . . . . . . .

TM 43-0001-30

0.32 oz (9g)

4 6 . 9 - 1 0 1 y d ( 4 3 - 9 2 m ) 220-396 yd (200-360 m)

5 o - 90o

12 per metal container;2 containers per wirebound box

39.8 lb (17910 g)14-5/8 in. x 12-13/16 in.x 9-1/8 in.

1.0 ft3

Change 9 4-5 (4-6 blank)

*U.S. G.P.0.:1991-543-050:40210

P IN : 050170 -009

TM 43-0001-30

FUZE, ROCKET, ELECTRONIC TIME, M433


STD MSR

Use:

This fuze is an electronic multi-optiontime delay fuze with selectable functioningmodes for forest canopy penetration,bunker structure penetration and super-quick for open terrain. Refer to paragraph3-2, Table 3-1 for the authorized warheadswhich use this fuze.

Description:

The fuze body is steel. A forest canopyswitch extends from the nose of the fuze tosignal to the fuze electronic circuit whenfirst contact is made with the forest canopyAn umbilical assembly is positioned at thenose of the fuze for electrical connectionto the M433 Fuze Safety and Timing Devicelocated in the helicopter. Internally, thefuze consists of a resistance capacitance(RC) electronic time circuit, a safing andarming mechanism with an electrical M84

4 - 7

T M 4 3 - 0 0 0 1 - 3 0

detonator and a booster assembly. Thefuze has a selectable time delay range thatdepends on the height of the forest canopy(40 to 130 ft). It has no internal battery.Required voltage is supplied by the aircraftvia the safety and timing device 160 milli-seconds prior to the rocket being fired.During this period, the fuze is charged togive the time delay selected by the pilots.

Differences between Models: N /A

Functioning:

After first contact with the forest canopya delay timer is activated which results inwarhead functioning beneath the canopy, butabove ground level. The bunker structurepenetration mode is incorporated into thefuze to defeat the medium hardness targetsconstructed of logs, earth, bricks, etc.The fuze can be set from the cockpit forpenetrating up to 10 feet of protection anddestroying the target from within. Thehard target penetration RC timer is acti-vated by inertial switch sensing setback inexcess of 1000 G’s. Also, an SQ pointdetonating feature is included to provideoperational flexibility in open terrain. Thismode is achieved by setting delay to zero.First contact with any surface detonates theround.

Tabulated Data:

M o d e l - - - - - - - - - - M 4 3 3T y p e - - - - - - - - - - - E l e c t r o n i cW e i g h t - - - - - - - - - - 1 . 8 l bL e n g t h - - - - - - - - - - 5 . 7 5 i n .Intrusion - - - - - - - - 0 . 7 2 i n .Diameter - - - - - - - - 1 . 8 8 i n .Color - - - - - - - - - - O l i v e d r a b w / b l a c k

markings

Temperature limits:F i r i n g - - - - - - - - - 6 5 ° t o + 1 6 5 ° F

(-53.35° to +73.15oC )S t o r a g e - - - - - - - - 6 5 ° t o + 1 6 5 ° F

(-53.35° to +73.15oC )

D e l a y - - - - - - - - - - - 0 . 0 - 0 . 5 s e c

P a c k i n g - - - - - - - - - 8 p e r m e t a l c o n -tainer; 2 containersper wirebound box

Packing box:Weightw / c o n t e n t s - - - - - 5 7 . 8 l bDimensions - - - - 1 4 - 5 / 8 i n . x

12-13/16 in. x9-1/8 in.

C u b e - - - - - - - - - 1.0 ft3

Shipping and storage data:Storage class/SCG - - - - - - - - - 1.1BDOT shippingc l a s s - - - - - - - - - ADOTdes ignat ion - - - - - DETONATING

FUZES, CLASS AEXPLOSIVES -HANDLE CARE-FULLY -DO NOT STOREOR LOAD WITHANY HIGHEXPLOSIVES

Fie ld s torage - - - Group B

DODAC - - - - - - - - - 1 3 4 0 - J 3 5 1

Drawing number --- 9239696

4 - 8

TM 43-0001-30

FUZE, ROCKET, PROXIMITY, M429


AMCTCM or OTCM

Use:

6393

This fuze is an all transistorized, con-tinuous wave, doppler device to provideairburst characteristics. It was designedprimarily for use with HE warheads forimproved anti-personnel effectiveness.Refer to paragraph 3-2, Table 3-1 for theauthorized warheads which use this fuze.

Description:

A super-quick impact switch serves asa backup in the event of failure of the

airburst electronics. The arming mecha-nism is similar to that contained in theM423/M427 Fuze except that it has beenmodified to include an electric detonatoras well as a battery starter assembly toinitiate an electric battery. An electricdetonator is assembled in the rotor. Aplastic (lexan) sleeve houses the thermalbattery which is located directly above thesafety and arming device.


Functioning:

The battery starter assembly is acti-vated when an interlock arm secured tothe rotor releases a spring-activated firing

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TM 43-0001-30

pin after the first 25° of rotor rotation.After 60o of rotation the electrical circuitis completed. Activation of the batteryinitiates a continuous radio frequency (RF)signal and charges the firing capacitor.When the reflected signals reach a specificintensity, the amplifier firing circuit pro-vides a pulse to the firing circuit by dis-charging a firing capacitor through theelectric detonator.

Tabulated Data:

Model - - - - - - - - - -Type - - - - - - - - - - -

Weight - - - - - - - - - -Length (total) - - - - -

Intrusion - - - - - - - -

Diameter - - - - - - - -Color - - - - - - - - - -


Storage - - - - - - -

Explosive train:Detonator - - - - - -Booster - - - - - - -

M429Electrical0.80 lb5.91 in.0.9 in.1.89 in.Olive drab w/blackmarking; white nose

-40 o to +140oF(-39.6° to +59.0oC )-40° to +140oF(-39.6 o to +59.0oC )

Stab, M81Tetryl

WARNING

Total explosivew e i g h t - - - - - - - - - -Arming distance ---

Rocket terminalangle - - - - - - - - - - -Packing - - - - - - - - -

Packing box:Weightw/contents - - - - -

Dimensions - - - -

0.32 oz (9 g)165-363 yd(150 - 330 m)

50-150

10 metal containersper wooden box withfuze wrench

39.8 lb (17910 g)14-5/8 in. x12-13/16 in. x9-1/8 in.

Cube -- - - - - - -- 1.0 ft3

Shipping and storage data:Storage class/SCG -1.2B (04)DOT shipping class - CDOT designation - - - DETONATING

FUZES, CLASS CEXPLOSIVES -HANDLECAREFULLY

Field storage - - - -Group B

DODAC - - - - - - - - - - 1 3 4 0 4 3 5 0Drawing number - - - -11705900

MULTIPLE FIRING OF 2.75-INCH ROCKETS WITH M429 FUZEIS NOT PERMITTED (NO PAIRS, NO SALVOS NOR RIPPLE FIRE),FIRE IN SINGLE ROCKET MODE ONLY. CROSS TALK/RADIOFREQUENCY (RF) INTERFERENCE BETWEEN FUZES (IF TWOROCKETS ARE FIRED AT THE SAME TIME) CAN CAUSE PREMATUREFUNCTIONING .

U . S . GOVERNMENT PRINTING OFFICE, 1989 643.046/00217

4 - 1 0 Change 6

PIN: 050170-006

T M 4 3 - 0 0 0 1 - 3 0

FUZE, PRACTICE, ROCKET, M435

.


Use:

This fuze is used with practice warheadsfor training purposes. Refer to paragraph3-2, Table 3-1 for the authorized warheadsused with this fuze.

Description:

This is an inert fuze. It simulates pointdetonating fuzes M423 and M427 generallyin length, weight and configuration.


Functioning: N / A

Tabulated Data:

Model - - - - - - - - - - M435Type - - - - - - - - - - - PracticeBody material - - - - - AluminumLength (total) - - - - - 4.0in.Intrusion - - - - - - - - 0.9 in.Diameter - - - - - - - - 1.75 in.Co lor - - - - - - - - - - Blue w/white

markings

Packing - - - - - - - - - 81 per carton; 1 car-ton per wooden box

Packing box:Weightw/contents - - - - - 70.0 lb

4 - 1 1

T M 4 3 - 0 0 0 1 - 3 0

Dimensions - - - - 19-5/16 in. x 18 in. Cube - - - - - - - - - 1.1 ft3

x 5-3/8 in.DODAC - - - - - - - - - 1340-J318Drawing number - - - - 9234469

4 - 1 2

T M 4 3 - 0 0 0 1 - 3 0

FUZE, ROCKET, M439, RC, VARLABLE TIME DELAY,REMOTELY SETTABLE


Limited Procurement (LP)-T

Use:

This electronic fuze is designed to bebase mounted in flechette and cargo war-heads. The output is a forward, axiallydirected detonation. It is a resistance-capacitance variable time delay fuze whichallows the pilot to remotely set the fuzefor an air burst at the desired functioningrange fromthe round.

the cockpit just prior to firingThe fuze and Remote Set Fuze

Subsystem are calibrated to provide properstandoff of the warhead when fired at rangesof five hundred (500) to six thousand ninehundred (6900) m. Refer to Table 3-1 for

authorized warhead.

Description:

The fuze consists of a module plastichousing assembly, a safety and armingdevice plastic housing, a mechanical safetyand arming device, and a molded electronicsassembly.

The S&A device consists of an unbalanced

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T M 4 3 - 0 0 0 1 - 3 0

rotor assembly which houses the M84 elec-trical detonator, an escapement and gearassembly (delay mechanism), a single poledouble-throw (SPDT) switch, and a springloaded setback weight. The SPDT switch isin the closed position to connect the fuzeelectronic time circuit to the umbilicalcable assembly for charging.

On initial setback, the switch is trans-ferred to the open position which discon-nects the fuze time circuit from theumbilical assembly, as a safety provision.If the fuze is armed or partially armedprior to rocket launch, it cannot be charged.A rocket launch in this condition will resultin a dud. The detonator is held shorted anddisconnected from the fuze circuit until itreaches an in-line position with the expel-ling charge.

The fuze must be subjected to a sustainedacceleration in order to arm. If accelera-tion is too low, the spring loaded setbackweight will not release the rotor. If accel-eration is sufficient for the setback weightto release the rotor, but time-of-accelera-tion (rocket motor burn) is too short, thesetback weight will return the rotor to theunarmed (safe) condition.

The fuze has a selectable time delayrange which may be set manually by thepilot or automatically by the advanced firecontrol system. It has no internal batteryand the required voltage is supplied by theaircraft via the Remote Set Fuze Subsystem,just prior to firing the round.

If the fuze has been charged and fired,and duds, it will take approximately 45 daysfor the charge to decay so that the fuze issafe. If the fuze is set (charged) and themotor fails to ignite, it may be loaded intoanother tube and fired. The fuze may beset a second time; however, it will function

longer than set time and should not be usedfor accurate measurements: for accuracy,10 days should elapse before resetting.

Functioning:

Upon receipt of the fire signal from thepilot, the remote fuze setter processesthe proper time constant (delay) to the fuzeimmediately prior to firing the rocket.The intervalometer circuit delivers a 60 msor up to 180 ms pulse interval, dependingupon the firing rate selected and the particu-lar fire control subsystem. The pulse isdivided into a 45 ms fuze charging pulse(constant time window regardless of firingrate) and a rocket firing pulse of from10 ms to 45 ms. The remaining ms areused as a dwell interval to maintain spacingbetween pairs of rockets.

After the rocket is fired and experiencessustained acceleration, the setback weightmoves rearward and allows the unbalancedrotor to rotate; the fuze timing is started.Rotation is delayed by a runaway escape-ment to provide an arming delay (0.63 to0.83 seconds, a function of the acceleration)until the rocket is a safe distance from theaircraft. When the rotor has locked intoplace with the M84 detonator lined up withthe propellant charge, the fuze is armed;the detonator is now electrically connectedto the firing circuit, the connection betweenthe electronic module and the umbilicalcable assembly is broken.

From 1.2 to approximately 25 secondsafter firing, depending upon the rangesetting, the detonator is initiated elec-trically and ignites the expelling charge.The energy required to fire the M84detonator, in M439 Fuzes, is 500 ergsat approximately 8 volts. This energyis supplied from the firing capacitorafter time rundown in the fuze. The

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T M 4 3 - 0 0 0 1 - 3 0

resistance of the M84 detonator variesfrom 2.0 to 5.0 ohms.

Tabulated Data:

Model - - - - - - - - - -Type - - - - - - - - - - -

Weight - - - - - - - - -

Length (overall) - - - Diameter (max) - - - -Operationaltemperature - - - - - -

Detonator - - - - - - - -Setback to arm - - - -

Arming distance - - -

Delay - - - - - - - - -- -

Faze, Rocket M439Electronic (resis-tance-capacitancetime delay)0.4 lb2.77 in.1.48 in.

-55° to +160°F(-47.85° to 70.4oC)M84 electrical0.79 + 0.18 oz(22 + 5 g)1 0 5 . 6 - 1 3 8 . 6 y d(96 - 126 m)0 - 2 5 s e c

Packing - - - - - - - - - 25 per wood orfiber box,w/partitions

Packing box:Weightw/contents - - - - - Wood box, 25 fuzes,

22.0 lbDimensions - - - - 8-3/4 in. x 8-3/4

in. x 3-1/2 in.

Cube - - - - - - - - - 0.4 ft3

Shipping and storage data:Storage class/SCG - - - - - - - - - 1.2B (04)DOT shippingclass - - - - -- - - - CDOT designation - - DETONATING

FUZES, CLASS CEXPLOSIVES -HANDLE CARE-FULLY

Field storage - - - Group BDODAC - - - - - - - - - 1340-Drawing numbers

Fuze - - - - - - - - - 9260704Packaging - - - - - 9270749,9270750,

9270751

4 - 1 5

TM 43-0001-30


4 - 1 6

TM 43-0001-30

CHAPTER 5

ROCKET MOTORS

5-1. INTRODUCTION

a. A motor, which propels the rocket,is assembled to the rear of the warheador base-detonating fuze. Generally, themotor consists of the following majorcomponents (fig. 5-2):

(1) Motor body (combustionchamber)

(2) Propelling charge

(3) Igniter assembly

(4) Nozzle(s)

(5) Trap assembly (optional)

(6) Resonance rod assembly(optional)

The base of the motor is constricted toform the throat of one or more nozzles.Flight of the rocket i’s stabilized byfins attached to the rear of the motor,or by spin of the rocket about its axis.This spin is produced by high-velocitygases passing through canted nozzles inthe base of the motor. In some largermotors, an assembly of spin rocketsprovides the initial thrust required torotate the rocket.

b. The motor body, usually a hollowmetal cylinder fitted with a nozzle atthe rear, is either closed at the forwardend or threaded for assembly with thewarhead. The body houses the propellingcharge and the igniter assembly.

c. The propelling charge consists of

e.

one or more grains of sold propellant,

either double-base or composite. Double-base propellant consists principally ofnitrocellulose and nitroglycerin. Com-posite propellant is a mixture of anorganic fuel, an inorganic oxidizingagent and a binding agent. To controlthe burning rate, propellant grainsmay be coated with sheets of a slowerburning inhibitor material. However, ifthe propellant has center-perforatedgrains, resonance rods running throughthese perforations serve the samepurpose by dampening pressure wavescreated by the burning propellant.

d. The igniter assembly consistsof a charge of black powder housed ina cylindrical plastic container, andone or more electric squibs.

The nozzle is convergent-divergent (Venturi-type) in shape toeliminate turbulence and to provide arelatively frictionless flow ofescaping gas. The throat (constrictedportion) of the nozzle may be linedwith a refractory substance, such asgraphite. This prevents heat of thepropellant gases from changing dimen-sions of the throat. A small changein throat area affects functioning ofthe motor by altering flow rate anddirection of the escaping gases. Nozzleson most rocket motors are canted (scarfed).However, motors used with highspeedaircraft rockets have straight nozzles.Nozzle closures or seals preventmoisture from entering the motor. Insome cases, the closure or seals aidignition of the propellant by causingpressure to build up within the chamberwhen the igniter is fired. Specialsafety devices (pressure relief valves,

Change 4 5-1

TM 43-0001-30

etc.) limit pressure and prevent propelling charges are suspended in therupture of the chamber. motor body in a manner which eliminates

the need for a trap.f. A grid-like trap assembly may be

located on the approach side of the 5-2. ROCKET MOTOR DATAnozzle to prevent ejection of unburnedportions of the propellant. Some The following pages contain pertinent

data for rocket motors.

5 - 2 Change 4

TM 43-0001-30

Change 4 5-2.1

TM 43-0001-30


Use:

The Mk22 Mod 2 Rocket Motors are usedto tow the M58A1, M58A1 (Mod), M58A2,M58A3 and M59 Linear Demolition Chargesand the M68, M68A1 and M69 Practice(inert) Linear Demolition Charges.

Tabulated Data:

Type ------------- Mk22 Mod 2Length ----------- 76.5 in.Weight, lbs, asshipped (nominal)- 115 lbsBurn time -------- 2.10-4.48 secImpulse ---------- 6820-8450 lb/seeIgniter:

Resistance, ohms- 0.3 to 0.9Propellant ------- N-4

Type ----------- Extruded doublebase, ethyl-celluloseinhibited,cartridge loaded

Weight --------- 46 lbsConfiguration -- 8-point internal

burning star

Temperature limits:Storage ----------- -40° to +125°FOperation --------- -40° to +125°F

DODAC --------------- 1340-J143

Color Code ---------- Case is blue-gray with abrown band nearthe head, andblack markings

Packing ------------- 1 motor perwooden box

Packing Box:Weight w/contents - 186 lbsDimensions -------- 86-7/8 in.x

12-9/16 in.x10-1/16 in.

Cube -------------- 6.5 cu ft

Shipping and storage data:Quantity-distancehazard class ------ 2Storage compatibilitygroup ------------- JDOT shipping class- BDOT designation --- ROCKET MOTORS,

CLASS BEXPLOSIVES

Field storage ----- Group J

Drawing numbers ----- 10001-2847573 (Navy)

5-2.2 Change 4

TM 43-0001-30

Change 4 5-2.3

TM 43-0001-30


Use:

The Mk22 Mod 3 Rocket Motors are usedto tow the M58A1, M58A1 (Mod), M58A2,M58A3 and M59 Linear Demolition Chargesand the M68, M68A1 and M69 Practice(inert) Linear Demolition Charges.

Tabulated Data:

Type -------------Length -----------Weight, lbs, asshipped (nominal)-Burn time --------Impulse ----------Igniter:

Resistance, ohms-Propellant -------

Type -----------

Weight ---------Configuration --

Mk22 Mod 376.5 in.

115 lbs2.40-3.00 sec7700/8640 lb/see

0.4 to 0.6N-5Extruded doublebase, ethyl-celluloseinhibited,cartridge loaded45 lbs5-point internalburning star

Temperature limits:Storage --------- -40o to +125°FOperation ------- -40° to +125°F

DODAC -------------- 1340-J143

Color Code --------- Case is blue-graywith a brown bandnear the head,and black markings

Packing ----------- 1 motor perwooden box

Packing Box:Weight w/contents 186 lbsDimensions ------ 86-7/8in.x

12-9/16 in.x10-1/16 in.

Cube ------------ 6.5 cu ft

Shipping and storage data:Quantity-distancehazard class ------- 2Storage compatibilitygroup -------------- JDOT shipping class-- BDOT designation ---- ROCKET MOTORS,

CLASS BEXPLOSIVES

Field storage ------ Group J

Drawing numbers ------- 14083-525-174-0050 (Navy)

5-2.4 Change 4

TM 43-0001-30

Change 4 5-2.5

TM 43-0001-30


Use:

The Mk22 Mod 4 Rocket Motors are usedto tow the M58A3 Linear DemolitionCharge and the M68A1 Practice (inert)Linear Demolition Charge. It is partof the US Army’s Mine Clearing LineCharge (MICLIC) System.

Tabulated Data:

Type ------------ Mk22 Mod 4Length ---------- 76.5 in.Weight, lbs, asshipped (nominal)- 115 lbsBurn time ------- 2.40-3.00 secImpulse --------- 7700/8640 lb/seeIgniter:Resistance, ohms- 0.4 to 0.6

Propellant ------ N-5Type ---------- Extruded double

base, ethyl-celluloseinhibited,cartridge loaded

Weight -------- 45 lbsConfiguration - 5-point internal

burning star

Temperature limits:Storage ----------- -40° to +125°FOperation --------- -40° to +125°F

DODAC --------------- TBA

Color Code ---------- Case is blue-graywith a brown bandnear the head,and black markings

Packing ------------- 1 motor perwooden box

Packing box:Weight w/contents-- 186 lbsDimensions -------- 86-7/8 in.x

12-9/16 in.x10-1/16 in.

Cube -------------- 6.5 cu ft

Shipping and storage data:Quantity-distancehazard class ------ 2Storage compatibilitygroup ------------- JDOT shipping class- BDOT designation --- ROCKET MOTORS,

CLASS BEXPLOSIVES

Field storage ----- Group J

Drawing Number ------ TBA

5-2.6 Change 4

TM 43-0001-30

MOTOR, ROCKET MK40 MOD 3


Use:

The motors are used by rotary-wing andother low-speed aircraft. Refer to para-graph 3-2, Table 3-1 for authorized war -

heads using these motors,


Models 1 and 3 have integral bulkheadmotor tubes; Mod 0 has a nonintegral bulk-head tube. The igniter of the Mod 3 motor

differs from that of the Mods 0 and 1 motorsin that the igniter has been modified toincorporate a carried, frangible case inlieu of the blowout plug and the squib islocated on the periphery of the case in lieuof at the center of the case.

NOTE

The nozzle closure on Mods DOD 1was a blow-out plug which has beenchanged to frangible steel burst dia-phragm on the Mod 3. Stocks ofobsolete Mk 40 Mod 0 or 1 motors,if still available, should be disposedof and replaced with Mk40 Mod 3 motors.

5 - 3

T M 4 3 - 0 0 0 1 - 3 0

Functioning:

Current passes through the launcherfiring contact to the igniter in the rocketmotor. This current generates the heatnecessary to initiate the igniter chargewhich ignites the propellant grain. Com-bustion gases from the burning propellantpressurize the chamber and exhaustthrough the nozzle, providing the unequalforces required for rocket thrust.

Tabulated Data:

Model - - - - - - - - --

Weight (nominal) - - -

Length (overall) - - - -Propellant grains:

Model - - - - - - - -Configuration - - -

Propellant - - - - -Type - - - - - - - - -Burn time - - - - -Weight - - - - - - - -

Thrust(over at 77 oF) - - -

Impulse (77°F) - - - - -Igniter:

M o d s 0 , 1 - - - - -M o d 3 - - - - - - - -

Resistance:Mk 125, Mod 4 --

Mk 125, Mod 5 --

Squib - - - - - - - - -Igniter charge:

Black powder - - -Coated magnesiumpowder - - - - - - - -Weight - - - - - - - -Burning time - - - -

Mk 40, Mods 0, 1,and 311 lb39.3 in.

Mk 43, Mod 18-point star per-forated cylindersN5 (Mk 43)Double base1.55 - 1.69 sec5.9 lb

720 lb1150 lb/see

Mk 125, Mod 4Mk 125, Mod 5

0.70 ohms to1.50 ohms0. 70 ohms to2.00 ohmsMk 1, Mod 0

80 percent

20 percent0.3602 (10 g)0. 2 sec


Storage- - - - - - - -

Motor Burnout:Range - - - - - - -Velocity - - - - - -

Launch spin rate(at launch) - - - - - -

Launcher exit velocity(64.5 in. tube) - - -

Acceleration:Initial - - - - - - --Final - - - - - - - - -

Range - - - - - - - - - -

Color code: - - - - - -

Packing - - - - - - - - -

Packing box:Weightw/contents - - - -Dimensions - - - -

Cube - - - - - - - -

Shipping and storageStorage class/S C G - - - - - - - -DOT shipping

-65° to +150oF(-53.35° to 64.9oC)-65° to +150oF(-53.35° to 64.9oC )

1460 ft (445 m)1965 fps (599 reps)

1 rps

112 fps

35-4040-45Max at 43° QEwith MPSM warhead8,080 mWhite w/brown bandnear head and blackmarkings1 motor w/propellantgrain, coated sta-bilizing rod ignitionand fin assy in fibercontainer; 6 con-tainers per woodenbox

131 lb46-3/16 in. x 11-7/8in. x 9-9/32 in.

2.8 ft3

data:

- 1 . 3 C

class - - - - - - - - Group BDOTdesignation - - - - ROCKET MOTORS

5 - 4

T M 4 3 - 0 0 0 1 - 3 0

DODAC - - - - - - - - - 1340-J106, Mk 4Mod 101340-J107, Mk 40Mod 0

1340-J108, Mk40Mod 13

Drawing numbers - - - 13736589220803

5 - 5

TM 43-0001-30


5 - 6

T M 4 3 - 0 0 0 1 - 3 0

ROCKET, MOTOR (JATO)M3A2


STD AMCTC 1106

Use:

The rocket motor is a solid-propellantthrust unit used primarily for launchingtarget planes from a catapult, although itmay be used for other applications re-quiring a unit of the same characteristics.

Description:

The JATO M3A2 rocket motor consistsof the following:

Body assembly. The body assembly is acylindrical steel tube closed at the forwardend by the head and threaded externally atthe open rear end to receive the nozzle.

Nozzle. The nozzle, which is of steel,

5 - 7

T M 4 3 - 0 0 0 1 - 3 0

is of the convergent-divergent type com-prising a conical rear portion and cylindri-cal forward portion. The cylindrical for-ward end of the nozzle is threaded internallyto engage the rear of the body assembly.

Igniter plug assembly. The igniterassembly consists of a “shorted” igniterplug and a nozzle closure which are con-nected by two lengths of igniter cable. Thenozzle closure is a plastic, cup-shapeddisk into which two copper terminal insertsare molded. The closure is cemented per-manently into the expansion cone. Theigniter plug is a standard, two-pronged,rubber-bodied electric plug which is short-circuited by a copper wire tied across itsprongs. The two cables from the plug arecrimped into the terminal inserts in thenozzle closure.

Igniter assembly. The igniter assemblyis designated “Igniter, JATO, M21.” Itconsists of a plastic igniter case containinga 463-grain charge of black powder, twosquibs, each of 1.0 ohm resistance, andtwo 24-in. long external lead wires whichare connected to the squibs. Electric ter-minals for the squibs and lead wires areriveted to the plastic wall of the ignitercase. The lead wires pass through thecenter of the JATO and are crimped intothe copper terminal inserts in the nozzleclosure.

Propelling charge. The propellingcharge consists of seven monoperforatecylindrical extruded grains of double-basepropellant M16 (T6). The grains arearranged in the JATO lengthwise with onegrain in the center and six grains sur-rounding it.

Rear trap assembly. The rear trapassembly is a star-shaped steel castingwith six equally spaced radial arms and

a hexagonal center hole.trap rods, one each from

Six cylindricaleach radial arm,

extend axially toward the forward end ofthe JATO to form a cagelike support whichreceives six of the seven propellant grains.

Front trap assembly. The front trapassembly is a wheel-shaped steel castingcomprising an outer ring, center hub, andthree radial spokes. A cylindrical trap rodextends from the center of the hub axiallytoward the rear of the JATO. This rodreceives the seventh (center) grain of thepropelling charge.

Functioning:

The JATO is designed to function safelyand reliably when connected to any electri-cal source which will deliver 2 amperesat a minimum of 1-1/2 volts, althoughhigher voltages may be used if desired.Satisfactory results have been obtiained byignition from ordinary 110-volt house cur-rent. Applying current through the ignitercable activates the 463-grain charge ofblack powder, which ignites the propellingcharge. Burning creates a rapid expandinggas which can only escape through thenozzle assembly. The nozzle assembly isdesigned for a venture effect which furthercompresses the gas and increases the thrustrequired to launch the rocket or aircraft.

Tabulated Data:

Complete Rocket, Motor:Type - - - - - - - - - - JATO M3A2Weight, loaded - - - 27.1 lbWeight,after fired - - - - - - 17.6 lbLength (includingnozzle) - - - - - - - -21.51 in.Diameter Outside(nozzle) - - - - - - - - 5.38 in.Diameter Body - - - - 5.12 in.

5 - 8

T M 4 3 - 0 0 0 1 - 3 0

Diameter (insidebody) - - - - - - - - -Diameter, Nozzlethroat - - - - - - - -

Catapult usedwith - - - - - - - - -

Components:Propelling charge:

Type - - - - - - - -

Weight - - - - - - -Igniter:

Type - - - - - - - -Weight - - - - - - -Weight (plugassembly) - - - - -

Performance:Burning time - - -Thrust - - - - - - - -


Storage - - - - - - -

4.75 in.

L 28 in.

A - 7

M21 extruded solidtabular9.2 lb

M18A1E10.14 lb

0.12 lb

CONFCONF

-40° to +160oF(+4° to +70°C)-60° to +70oF(+15o to +21oC )(cool dry area)

Packing - - - - - - - - - Two per wooden boxPacking box:

Weightw/contents - - - - - 71. 7 lbDimensions - - - - - 26-7/8 x 12-1/2 x

7-1/2 in.

Volume - - - - - - - - 1.44 ft3

Shipping and storage data:Storage class/SAG - - - - - - - - - - JDOT shippingclass - - - - - - - - - ADOTdesignation - - - - - ROCKET MOTOR

FOR ASSIST INLAUNCH OF TAR-GET PLANES

DODAC - - - - - - - - - 1340-H305Drawing number - - - 8799792

5 - 9

TM 43-0001-30


5 - 1 0

TM 43-0001-30

ROCKET MOTOR (JATO) M8

5 - 1 1

T M 4 3 - 0 0 0 1 - 3 0

Type Classification: Tabulated Data:

STD OTCM/AMCTC 36841

Use:

The JATO M8 is a solid-propellantthrust unit used primarily for applyingthrust to assist aircraft on take-off. Itcan be used for other applications requiringunits of the same characteristics.

Description:

The JATO M8 rocket motor consists ofthe following:

Body assembly — a deep-drawn steelcase with a thicker ring welded to the rear(aft) end, which provides the chamber forloading the propelling charge.

Closure assembly – which seals therear (aft) end of the JATO and provides amount for the nozzle and blowout assem-blies.

Igniter assembly – consists of a plasticigniter case which contains the ignitercharge.

Complete Rocket Motor:Type - - - - - - - - - JATO M8Weight, loaded - - 158.5 lbLength (max) - - - - 34.32 in.Diameter (max) - - 10.0 in.Used with - - - - - - Assist aircraft on

take-offComnponents:

Propelling charge:Type - - - - - - - - M301, Cast OGKWeight - - - - - - - 70.0 lb

Igniter assembly:Type - - - - - - - - M31A1Igniter charge - - 87 grains of igniter

compositionElectric squibs - 2 (Mk 1 Mod 0)Length - - - - - - - 3.68 in.

Performance:Burning time - - - - 14.0 secThrust - - - - - - - - 1000 lb

Temperature limits:Firing - - - - - - - - -60° to +140°F

( -51oto +59oC )Restricted to tem-perature rangesmarked on JATO)

Storage - - - - - - - 60° to 70oF(15° to 21oC) (cooldry area)

Functioning:Packing - - - - - - - - - One per wooden box

The igniter assembly is ignited by twoelectric squibs, Mk 1 Mod 0, connected inparallel. In turn, the propellant is ignited.The pressure created by the expanding pro-pellant gases can only be vented throughthe nozzle assembly. The nozzle assemblyis designed for a venture effect which com-presses the gases generated and increasesthe thrust required to assist launch of thedesired item.

Packing box WoodenWeight - - - - - - - - 224.9 1bDimensions - - - - - 39-3/4 in. x

16-7/32 in. x 12-1/8in.

Volume - - - - - - - 4.5 ft3

5 - 1 2

T M 4 3 - 0 0 0 1 - 3 0

Shipping and storage data:Storage class/SCG - - - - - - - - - - - -DOT shippingclass - - - - - - - - - -DOT designation - --ROCKET MOTOR

TO ASSIST IN AIR-CRAFT TAKE-OFF

DODAC - - - - - - - - - 1340-

Drawing number - - - 82-6-25

5 - 1 3

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5 - 1 4

TM 43-0001-30

ROCKET MOTOR MK66, MODS 0, 1,2, OR 3

Type Classification

STD AMCTCM 955

Use:

The motors are used by rotary wing andother low speed aircraft; they may also be usedwith high performance aircraft.

Differences between Models

The MK66 motors utilize a longer motortube (than the MK40) of a different aluminumalloy, and a new nozzle and fin assembly. Thefins are of a spring loaded, wrap-around design

and are attached around the circumference ofthe single nozzle. The propellant grain islonger and of a different formation than thestandard grain; however, the stabilizing rod andigniter are essentially the same as used on theMK40 motor, The MK66 motors have a substan-tially higher thrust, 1300 lbs. and a longerrange. The MK66 Mod 0 was developed by theNavy but never fielded.

The MK66 Mod 1 motor is a nozzle modifica-tion of the Mod 0 to increase the spin rate f’rom4 - 5.5 RPS to 9 - 10 RPS (at launch) forincreased accuracy and provide interface withexisting and improved launchers, A detentgroove has been added forward of the wraparound fins.

Change 10 5 - 1 5

TM 43-0001-30

The MK66 Mod 2 motor is the same as theMod 1 motor except that it contains a Hazordsof Electromagnetic Radiation to Ordnance(HERO) filter which allows it to be handled andstored in electromagnetic radiation environ-ments.

The MK66 Mod 3 motor is physically andfunctionally the same as the Mod 1 motorexcept that it has a radio frequency (RF) filterin the firing circuit. The filter is physicallylocated on the igniter can. It also has a metallicbrass shield over the fin and nozzle assembly toshunt any arc formed during loading/unloadingrockets into or from the launcher. The RF fil-ter resists inadvertent firing by stray RF cur-rents.

Tabulated Data

Type ---------------------------- MK66 Mod 1Length ------------------------- 41.7 in.Weight, shipped

(nominal) ------------------- 13.6 lbBurn time (77oF) ------------ 1.05-1.10 secAverage thrust (77oF) -----1300-1370 lbImpulse (77oF) --------------- 1500 lb/seeMotor burnout:

Range ------------------------ 1300 ft (397 m)Velocity ---------------------- 2425 fps

Launch spin rate ------------ 10 rpsLauncher ext (64.5

in. tube):Velocity ---------------------- 148 fps

Acceleration, GInitial ------------------------ 60-70Final --------------------------- 95-100

Range - max atQE 43o:

w/MPSM warhead ------- 11407 yd(10,426 m)

IgniterResistance, ohms --------- Mod 1 0.64 -2.5

Mod 2 2.2 -3.5Mod 3 0.64 -2.5

Propellant --------------------- NOSIH AA-2

Type --------------------------

Weight -----------------------Configuration -------------

Temperature limits:Storage -------------------------

Operation ---------------------

DODAC ---------------------------

Color code -----------------------

Packing ---------------------------

Packing box:Weight w/contents ----------Dimensions -------------------

Cube ----------------------------

Shipping and storage data:Storage class/SCG ----------DOT shipping class --------DOT designation ------------

Field Storage -----------------Drawings: ------------------------

Extruded doublebase, ethylcelluloseinhibited, cartridgeloaded7 lb8-point internalburning star

-65° to + 165°F(-53.35 o to+73.15oC)-500 to + 150oF(-45° to + 64.9°C)

MK66 Mod 11340-J146MK66 Mod 21340-J147MK66 Mod 31340-H309Case: whitew/brown band nearhead, black mark-ings1 motor w/propel-lant grain, coatedstabilizer rod,igniter and fin assyin fiber container;6 containers perwooden box (whenpacked Separatelyfrom warheads)

146 lb48-5/8 in. x 11-7/8in. x 9-9/32 in.2.9 ft3

1.3CBROCKETMOTORSGroup FZ33AS100 (Navy)

5 - 1 6 Change 10 U.S. GOVERNMENT PRINTING OFFICE: 1992 643-048/70006

TM 43-0001-30

APPENDIX A

R E F E R E N C E S

A-1. Administrative Publications

a Army RegulationsDictionary of United States Army Terms. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AR310-25Authorized Abbreviations and Brevity Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AR310-50

b PamphletsIndex of Administrative Publications. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DA Pam 310-l

(Microfiche only)Index of Blank Forms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DA Pam 310-2

(Microfiche only)Index of Doctrinal Training and Organizational Publications. . . . . . . . . . . . . . . . . . . DA Pam 310-3

(Microfiche only)Index of Technical Publications (Includes: Equipment

Identification Lists, Lubrication Order, ModificationWork Orders, Supply Bulletins, Supply Catalogs, SupplyManuals, Technical Bulletins, Technical Manuals andTechnical Publications Rescinded for Active Army UseBut valid For USAR, ARNG, or FMS/IL Programs. . . . . . . . . . . . . . . . . DA Pam 310-4

(Microfiche only)

A-3. Doctrinal Training and Organizational Publications

Rotary Wing Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FM 1-5166-Millimeter High Explosive Antitank Rocket M72A1, M72A2

and M72. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FM 23-33

A-4. Equipment Publications

a Technical ManualsOperator’s and Organizational Maintenance Manual:

Launcher, Rocket: 66MM, 4-Tube, M202. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 3-1055-218-12Operator’s and Organizational Maintenance Manual (Including

Repair Parts and Special Tools List): Launcher, Rocket:66MM, 4-Tube, M202A1 (NSN 1055-00-021-3909) . . . . . . . . . . . . . . . . . . . . . . . . TM 3-

Operator, Organizational, Direct Support and General SupportMaintenance Manual (Including Repair Parts and SpecialTools List With Depot Maintenance Allowance): 2.75-InchAircraft-Rocket Launchers M158A1, M200 and M200A1 (Used

0 5 5 - 4 5 6 - 1 2

W/Rotary-Wing Aircraft Armament Subsystems). . . . . . . . . . . . . . . . . . . . . . . . . . TM 9-1055-460-13&P

A-1

TM 43-0001-30

Organizational Maintenance Manual: Rocket Launcher M190W/Subcaliber 35-MM Practice Rocket M73 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 9-1340-203-20

Operator’s Manual for 66MM Light Antitank Weapon (LAW) SystemM72A1 and M72A2 with Coupler and Practice Rocket Launcherwith M73 Practice Rocket... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 9-1340-214-10

Organizational Maintenance Manual (Including Repair Partsand Special Tools List): 2.75-Inch Low Spin, Folding FinAircraft Rockets: 66MM, TOW Light Anti-tank Weapon Systems;3.5-Inch Rockets and M3A2E1 Rocket Motor (JATO) . . . . . . . . . . . . . . . . . . . . . . TM 9-1340-222-20

Direct Support and General Support Maintenance Manual(Including Repair Parts and Special Tools List) For2.75-Inch Low Spin, Folding Pin Aircraft Rockets; 66MMLight Antitank Weapon Systems, 3.5-Inch Rockets and M3A2E1Rocket Motor (JATO) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 9-1340-222-34

Direct Support and General Support Maintenance Manual(including Repair Parts and Special Tools List):Military Pyrotechnics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 9-l370-203-34&P

Destruction of Conventional Ammunition and ImprovedConventional Munitions to Prevent Enemy Use. . . . . . . . . . . . . . . . . . . . . . . . . . . . TM 750-244-5-1b. Technical Bulletins

Munitions Suspended or Restricted . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TB 9-1300-385-1

A-5. Supply Catalogs

Ammunition and Explosives: Classes 1305 through 1330 . . . . . . . . . . . . . . . . . . . . . . SC 1305/30-ILAmmunition and Explosives: Classes 1340 through 1398 . . . . . . . . . . . . . . . . . . . . . . SC 1340/98-IL

A-2

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Official:

E. C. MEYERGeneral, United States Army

Chief of Staff

ROBERT M. JOYCEBrigadier General, United States Army

The Adjutant General

Distribution:

To be distributed in accordance with DA Form 12.40, OrganizationalMaintenance requirements for Small Rockets; Jatos; and 66MM LAW SystemM72; Plus, Direct and General Support Maintenance requirements for SmallRockets, and Jatos.

PIN: 050170-009

Documents

Manual Tehnic Pt Munitii