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MI1-STD-1226A
1,
29 Octobu 1965
SUPERSEDING MIL+TD-1226 3 Octoba 1961
MILITARY STANDARD
II
ENGINE, GASOLINE: AIR-COOLED, 1-1/2 BHP, 4-CYCLE MILITARY DESIGN, MODEL IA(M ‘INSTALLATION PROCEDURES
)
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MIL-STD--1226A 29 October 196S
!
DEPARTMENT
OF DEFEUSE
WASHINGTON, D. C.
20301
I i !
[
Engie, Gasoiine, Procedures.
i
MiI.-.STl-2262A.A
{
t I I
.4ir-Cooled,
1. This Military Standard of the Department ~of Defense.
l-1,~ EHP,
Milita~
is ~.andatory
Model IAQ8, Installation
for u.?: by ,1!1Departments
ar.ci Agencies
.;, hwmmmded wrrecticn:, a.dc!it;ons,,jr de IAcos sb... u!(; !)? ati,di’eswl 10 the -. D!rectw, U. S. Army Mobility Equipment Center, Reswr.h, De~ell.ymlm!, and Efigineev img Directorate, .%T”TN: ONE FR-P. DE-KM, Fort Relvoir, ‘i a., >2060.
i
I
) i
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I
ii I 1
Design,
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MIL-STD-1226A 290c10&?l%s
1.1 1.2 2. 2.1 2.2 3. 3.1 4. 4.1 4.2 4.3 5. )
5.1 5,?
TABLES
●
1. 11. 111.
Opemtional Temperatwt
L]mits
. ...
. .
Engine Specifications Fuel Consumption
.
? .
.
.
. .. .
,11
. . ..
8 10
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MIL-STD=l 226A 29 Odeber 196S
FIGURES e,.,
I
1.
Engine
mounting
bracket
...........................
9 -.
Welded engine mounting bracket
3.
Slamped engine monnting
4,
Cast engine mounting bracket
bracket
..... . ..................... 11
. .
.
.
,,
.
.
5.. Beam mounting instrdlation
.
.
.
.
.
Final spring force (per spring)
7.
Factor E as a function of L rmd D for beam mounting
8.
Permissible
9.
Total deflection and natural deflection . ..
.
.
.
N .
14
~~~~ . ---- =-.:--
lG ..
for beam mounting
17
..........................V . ...........
18
frequency as a function of static . . . . . . . .. ................................................. 19
10.
Rigid quill-type coupling
11.
Alignment
12.
Flexible coupling installation
13.
Critical speeds for directly attached end itsm . .
14.
Vibratory torque at critical speeds for directly attached end item
.
method
12
. .. ... ....... .. . .... ............ .. ..... 15
6,
spring force (per spring)
..
.
.
.
...... . .
.
. .
. 20
.. ........................21 . .... . .
... 22
... ..
23
.
. . ..
.
24
15. Average torque magnifier for riirsctly attached end item .. . ............... . .... .. .......... .............. 25 16.
Permissible
maximum stiffness of flexible coupling
~~, Maximum limits for fuel tank locations 18.
Cooling air outlet and engine Military Design Engine
mounting .
.
. . . ... .... .
26
.
.
pads
Model lAOS-111
?7 Z*
.
19.
Model 1A08-111, l+ HP Engine Perfornmncc Characteristics and .> -9 dimensions . ... ........ ........ ........ ............. .. ..................... . . ........................ ...........................
20.
Model IAOS-HI Military Desigu Engine Power Takeoff End
21.
Model 1AM-III Nilitary
Design Engine Rope Starter
.
iv
End
.
.. . . .
.
30 . 31
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.,
“:... .
‘“ ‘tiiG’3=&72%L&*’’” :’ -%
-.
,W
~M
.,+,
,,. . .
i.
,.~coFE
“Mstio’ti
‘i. Be&+,‘V”;‘E~ne
iIiS51066
— Belts, V; E@ine Accessory Drive (0.500 Inch Noniinal Width).
~lS51067
— Belts, V; Engine Accessory Drive (11/16 Inch Nominal Width).
MS51068
— Belts, V; Engine Accessory Drive (3/4 Inch Neminal Width).
MS51069
— Belts, V; Engiue Ac. cessory Drive (7/S Inch Nominal Width).
Ms51070
— 13elta, V; Engine Accessory Drive 1 Inch Nominal Width).
11S51086
Filter, Fluid, Pres. sure and Strainer, Sediment; A u toemotive, Fuel (10 GPH, Coarse Fil-
Ac. $:, c’e9,ao.ry Drive ; “(0.380 @ch NOrnI‘%1 Width).
I.1 ‘COve’Rig6.‘tiis Stiriijaiij COVi& ‘Me iwornrnetidid indalkitioii plio&du”i& for the tide, iAm, iv2-Kp, ~itititi ,detib engine. M 0bj6div& ‘he objtitive of k stand~ is tb insu”i% cornikibility of the engine aiiil tlie end item ‘of @qui~oMnt. 2. REFERENCED
DOCUMENTS
2.1 Governmental. The issues of the folkming decuments in effect on the date of invitation for bids form a Dart of this standard to the extmt specified herein. SK?ECIFICATIONS MILV-1’73
MILT.wzI
JiiL-V–l
— Varnish, iKoistureand-Fungus-Resistant (for the Treatment of Communications, Electronic, and Associated Electrical Equipment), — Treatment Paintkg rial.
137
_
and of hlat,e.
Vsrni~h, El~tricalInsulati~g.,(fOr Electro - Mo tive Equipment).
MIL-B–I104O
— Eelt, V; Engine Accessory Drive.
MIIiE-55301
— Electro rnagndtic Compatibility.
STANDARDS MS%I064
-
Phllej,
Groote:
E-ii:
tration). (@i6S of specifimtions and standards requiti by suppliers in connection with s~mific maamernent f tiitions should be obtained f mm the pkuring aciivity or as dh+cted by the contracting oificer.) 2.2 NOiGoiirniiientaI. The isi,iv% of the following documents in effect oli date of ifivitatiori for’ b.ds form a jafi of this standa’td to the extent specifi++dhetiii,.
S.OCIET~ ,O”F Ai!T03’iOTIVE ENGINEERS
gine” Acc65soF+ c..
.
,)
Drive Btilt4.
~ ““:”’S~E Haiitibooii .. ’.,
:.. 1
.
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,, ~li&STD+1226A ;;::9 Qyby “>p5
~~~.
(Applicht.ionfor copies should. be addressed to the Society of Automotive Engineers, 485 Lexin& ten ‘Avenue,New York, N.Y. 10017.) ,..., ,, 3. DEFINITIONS “3.1” Definitions. For “the p&’pose of this standard,. the. following definitions shall 3fJply. 3.L1 Tlte Military Design engine” Model 1.A08. A single-cylinder air-coeled, overhe a d-valve, 8-cubic-inch-displacement en@e ha%ing ‘a rating of 1’1/2net continuous hor.aepow,er rating at 3,600 rpm. ~3.1.2 Maximum net corrected brake komepoww. The maximum net correckd brake ?mrsepower rating with all accessories (including fan, muffler, and air cleaner) at any engine speed withh the’ opa-sting range is the maximum observed horsepower available from the engiue at wide-open throttle cm’rect.sd to standard atmospheric candit. ions. %1.3 [mter-mif tent ~~@brake honre.j]owe+. Tile intermittent net brake horsepower rating is 90 percent of the maximum n{?t corrected brake horsepower. 3.1,4 Conti?tiuows net b~ake how.qmzow. continuous net brake horsepoii-er rating is 1.5 observed horsepower at 3,600 rpm.
Tne
L GENERAL
REQUIREMENTS
“ 43 Design simplicif.y. The desigwef:the end item shall be such that completi removal. of the engine frem the driven corn. pouen!. or, the driven component from the engine can be accomplished with minimum dkwssembly and withoui: the use of special tools. ~. DETAIL
REQ(JIREMENTs
5.1 Power requirements. ‘llne maximum horsepower required to drive the end item, including power transmission system under the environmental cxtremss s~,ecjfied for the end item, shall not exceed the )jet con. iinuous horsepower rating r,f the engiue unless int.ermittenl operation is indi~ted in the end-item specification, at which time the intermittent power requirement shall not be exceeded. 5:2 Operatimla] requirements. The end item design and Jocation of hoods and other external components slmll not cause the engine to exceed the operational limits specified in table I tinder a.fl opersting con. ditions of load aud environmental extremes specified i:l the end-item specifications. T.,,,,.,, J. ()~.,a(i.,,dCC,,,,,<,.(,,,, 1;.<;,.,
.,
4.1 safety. \%’!Ien installed in the ~11~ item, rotating or reciprocating parts and parts subject to high temperatures that ur> so located as to become a hazard te operat. ics personnel and equipment shall be in. sdated, fuilj: enciosed, or guarded, Exhaust. piping shall he located to mi, (fkrs and minimize hazard to ouerating personn?l. !.2 Llse ccmditions~ The installation” shall withstand shock loads as specitk.d in the end item specification. Tbe installation .,, . ... . shall be 2
such that the eugine will notbe required tmoperate in a tilted position of more thau ,15 degrees from the horizontal in any plane at, itiy, time.
] –------—---( ~
..lmbient air
I Cylinde~: head ......./ Lubric.ti”g _.
oil
CooGr.g .;L ,Cwburetm air
~ ~ 1
Mei
I I
!—-–
in t],,! vicinity of the. er,zinc ( T_lndm SW+A plug
~
in tk,e oii sump . .. ... I 1 .&t ..oli.~ air outlet! I Air .l*.W:V inlet .. .....8
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MIL-STD-1226A 29 October i%5 5.3 Maintainability. The engine inatallation shall permit maximum accessibility for replacemen~ adj ustmenti and repair to al I parLs of the engine with minimum disturbancc to adjacent parts of the end item without the use of special took.
/
5.3.1 CooE~g awl sturti.mg szWen2. Clearmlce shall be provided for: (a) Winding the starter rope on the starter pulley with a gloved (arctic type) hand withoui interference.
/
!
(b) Removal of tbe flywheel housing and flywheel without removing other components of the end item,
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5.3.2 F?(.c L ..lpfem. Clearance shal! be provirled for:
* ,,
(a)
Carburetor
1
5.3.3 Induction sMsf.em C!earancc shall be provided for: (a) servicing ‘(ne air
cleaner.
(b) Operating the winterization air ccmtrol on dsy. type air cleaners. S,:1.4 Luh?-icdzng
5.3.6 Ignitioti s@em. Clearance shall he provided for removing, replacing, and adjusting spark plugs, high tension cables, breaker pointa, and capacitors. 5.3,7 Vu$ves. Clearance shall ha provided for removing rocker-am covers and adjusting valve tappet clearance. 5.4 E n g i n e mounting requirements. Mounting brackets shall be in accordance witii figurea 1, 2, 3, or 4 unlese other means of mounting is approved by the cmttsnctfng officer. The mounting braeketa shall be furnished by the end-item manufacturer and shall be installed in euch a manner as tn permit assembly without deflection or cleiormation of brackets or engine mounting Dads.
acljustmcil~s,
,,
(b) Remora! of the fuel filter. 1,
5.3.5 Governor system. Clearance shall be provided for governor speed and linkage adjustments.
system. Clearance shall
be provided for: (a) Removal and insertion of the oilgage rod and zddition of oil with or without a removable spout or funnel. (b) Removal an(i replacement of the oi! drain plug and for draining the oil. The cil sha!i drai:) completely and shall not flow over auy pall nf the end item. An extensicm to the crsnkcaw drain s~~tem i.s permissible.
.i..t.1 Vibration isolators. StiitabIe viLwation isolators which stress an elastomer in shear or compression or both shear and compression shall be used on all insh~ations when shock mounting is specified in the end-item specification. The method of calcidation for determining the maximum allowable spring force of four vibratinn isoiators equally spaced about the cen@r of gravity of the end item for beam mounting (see figure 5) shall be as specified in .5.4.2.1. When vibration isolators are not equally spaced about the center of gravity o complete analysis shall he conducted ta determine the maximum permissible spring t’orce for each ieolator. 5.4.2 f?ee-igu require nwts for direct n~owttimfIo~ end item. The maximum resultant moment that the equipment mounting pads can absorb without deformation i: 650 lb-ft. This limiting moment shall not be exceeded. Cantilever mounting of end items to the engine is prohibited unless specifically detailed on . Military design 3
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MIL-STD-1226A z90chber196s
) which is a function of L = distance of CG of equipment from engine equipment mounting pa&, and D = distance of equipment support from engine equipment mounting pads,
drawings. Cantilever mounting of the engine to the end item is permissible provided the applicable end-item specification does not require free fall test. 5.4.2.1 Method for calcsslatitl~ mazimam allowobfe spring fwx. The final spring force shall not apply to the weight of the end item a G-magnification factor that w7ill cause a moment exceeding 650 lb-f t, when calculated as shown in figures G through 9. 5.4.2.2 Procedure. The following procedure shall be foflowed in selecting four vibration mounts equally spaced about the center of gravity of the end item to withstand freefall, shock-load requirements. (a) Determine weight of equipment; e.g., WNI = 80 lb. (b) Select a vibration isolator, and compute spring rate; e.g., k = 3,000 lb/inch (obtain spring force from manufacturer).
Example, L = 8 inches D = 14 inches Therefore, factor e = 2.5
(f) Determine maximum permissible force (see figure 8), For e = 2.6 W* = 80 lb Therefore, Maximum permissible spring force = 5,100 lb w Ve$JS is i%gh~ than ‘&e find spr:big force and the four shock mounts are suit-
.Sof..
able if the natural frequency and total deflection of the mounts am within the design specification.
(c) Calculate the static deflection by the following formulfi:
1)
(g) Determine natural frequency and total deflection (see figure 9).
Whsre, 80 = static deflection (inches) k = spiring rate in ibiilmh = 3,000 lb/inch
Static deflection
Se = 0.0089 inch
Natural frequency
F = 2,000 CPM
Total deflection F
shall not be
Gf ibe engine
W, = weight of engine = 27 lb -.
.“
86 lb (d) from design chart (see figure 6) determine final spring force F, = 1,700 lb. \ e) Determine factor e (see figure 7) 4
t = greater
g,owrned
0.57 inch than
70 percent
speed.
5,5 Power transmission requirements. The drive unit shall be connected to the engine drive shaft by one of the following methods. Torsional vibration deterrnina. tions shall be made as specified in 5,5.5,
5.5.1 Ri.gid-guill cuup~in~. When a rigitiquill coupling is used on the driven equipment ehaf t the coupling shall be in accorclsncc with figure 10.
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MIL-ST&1226A 29 G16ber 196s
) S.5.2 Flezibie coupkng. When a flexible coupling is used between the engine and end item, the coupling shall p~ovide the cor:ect torsional flexibility and a sufficient tiegree of dampening to insure that the maximum vibration torque doee not exceed 4i O lb-in (see 5.5.5.2). 5.5.2.1 Sh@t r?~ieaiin.eme?d.The misalinement of the engine shaft and driven equipment shaft shall not exceed the limits shown in figure 11 vihen a flexible coupling is used bet wwn the engine and end item. 5.5.2.2 COt@ig iutulkztian, The coupling ::hall be installed on the engine shaft by a taper connection in accordance with tigurc 12.
5.5.3.1 P2dlev abe-ment. The’allnenrent of pulleys shall insure optimum belt life and power transmission. 5.5.4 Gear drive. when an independent reduction gear drive is used,” it{ shall be coupled to the engine through a suitable flexible coupling (see 5,5.2) or V-belt drke (see 5.5.3). 5.5.4,1 Dir e c bmounted gear-reduotiou drive. When a direct-mounted gear-reduction drive is used, it shall be coupled to the engine power-takeoff shaft ae specified in 5.5.5.1.
5.5.3 6’e~t drive. V.helte used shall conform to MIL-B-1104O. The belt sise and pulley dimension shall conform to MS51064 Ih rougir MS51070, a8 applicable.
5.5.5 Method jor cakufatin~: ters-iona( eibvatiors stres8ea. The maximum Allowable vibration torque ehall not exceed 410 lb-h. for the ehaft between the reciprocating masses of the engine and the attachment point of tbe driven equipment.
%5.5.1 P~oceduw for directl:~ cmmected end item. The following procedure for torsional vibration ca!culatim shall be t’ollmwrl: (a) Conditions.
The characterktics
of the directly-cnnnected
end item ,are:
End item inertia
Jx = 0,15 lb-in-see? or ~~ = 57.8 lb-in’
Engine speed range 3,500 to 3,760 rpm. (b) Evaluate the critiesl speeds occuring 3,760 rpm from figure 13.
in the engine speed range, of 3,500 to
For Jl, = 0.15 lb-iwsec” the nearest critical speed occurs at ~. Nc = 3,.t40 rpm for n = S% .s,,,, ‘l’he (:;tgine sIuJI rml be cqwratetl co!rtinwowly at aIIy critical speed which will result in a ii,ra?ory t,nrq:lc in ~;;ctss of .110Ib.in, (c)
Dercrnlin.
the
.:ibratory
torque in the shafting from figure Id,
For Jx = 0.15 lb-in-sect nnd n = 31,$. ‘The’vibratory torque T. = 50S lbiu. Sinw the critical 8peed N. = 3,440 rpm is ix?low the mlninrum speed m-nge, t.h~ actual vibratory torque at N -3,500 rpm shrill be determined. J 5
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MIL-STD-1226A 290d0bw196s
)
(d) Calculate speed ratio N NC
-.3500 =
~440-
=
1.017
(e) Determine averaiw torque magnifier from figure 15. For speed ratio = 1.017, the average torque mamrifier’ T;TC
= 0.670,
thus thevibrhrytorque T This \-aIue is within
= 0.670 x 508 = 341 lb-in. the vibratory
Pr-ocedrwe {or flexible couplim~ load. The following information shall be determined if a flexible coupling is used : 5.5.52
connected
(a) The inertia of the driven machine (see appendix 10.10) (b) The stiffness of the coupling (fu~nished by the coupling manufacturer) shall notexceedthk maximum permissible stiffness (see figure 16). 3.6 Wkcellrmeorrs
design requirements.
S.6.1 A?terotimz. The errgk shall not be altered in any manner by tire end-item Custodima: Amy - MO(ERDL) Navy - YD Air Force - e9 itcview arti}ities: Amy — MO CL Navy — YD BYc Air Fore. -69 DSA — Cs
User mtivitiea: Army — EL
Navy - Nene Air
6
Force — Nom
at 3,500 rpm
torque
limits for the crmkdmft.
manufacturer purposes.
for assembly or inetallati ori
5,~:~ ~l{e(. ~.ot’~,‘The eupacity of the fuel Lank for the end item may be determined from table 111. The location of the fuel tank and maximum allowable length of fue! supp]Y line shall lIOL exeeed tke limits specified ill figure 17. 3.6.3
[email protected] outlet. Clear&oce shall be !movided for’ the outlet of coaling air as shown on figure 18. 5.6.4 ,Voi.w induct;o)i In applications where :xkiiticnal noise rwiuction is rwqllired, a secmwlm-y muffler shall be directly cow nectcd to the muffler outlet; however the =ecm)dary muff],.? sbail be self supporting, Prqnaring activity: .Army — MO(EKDL; Pmiwt No. 2805.0115
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I + M&Ll12:&A
) 10. APPENDIX I
j
10.1 General Description of Engine. The model IA08 Military design tmgine is a single-vertical-cylinder, overhead-valve, aircooled, spark-i 6mition, 4-cycle, gasoline engine, The net continuous brake horsepower rating is 1\j hp at 3,600 rpm. The eugine will develop 85 percent of the maximum brake horsepower specified in the performance charts. The engine is treated and painted ill accordance with MIL-T-704. ~~ce~s~ries. The ~,~gin~ ~S supplied will be equipped with all accessories as uutlined in the installation dra~ving (see figure 19) and shall be ready for immediate operation after the engine is CW. rectly serviced and cleprocessecl. Tbe engine has. the following featnres. lo.~
i \
Engine
,te,. Thr cugim ail iO.2.l Ill {j-wit, C{CCI cleaner is of the dry Ircplacenhlc c!ement) typt? with :! rest?icl ion indicator (see figure 20). Cleani]}g and servicing instructions are embossed in the air cleaner bo{ly. 10.2.2 F’/!cl ;iltw. The fuel Iilter consists of a strainer and the sediment bo~vi. It is provided fm. use betu’een the iue} supply dud the fuel pump. The filter body is ~al)lleci for 1,,~.illch \TpT fue]-]ine fittillF~. 10.2.3 F[{ei P?<,IJP. The t’uci pumII is a single.:tc.ting, diaphva.grn-type pump rate(! for s static pressure range bet wcen 1.5 psi minimum to 5.00 psi maximum, measured tit a poin; 16 inches above fur! pmnp out. !$t II-it:, ,,un,~, cmrl acticm 8! 1,Sq~ rpnl. The flew pressuw hmd is bc,tween 1.73 ]Jsi and ?.00 psi with a normol heccl pre..sure of !? psi. Thz rated capacity of the pum:~ :It 1,S00 i?roke,c per minute is 5 ga]](.!:.: per hour.
manifold wiich is completely housed withh the engine shrouding. An external muffler is uot required for normal installation to limit the engine noise since the mufflermanifold is w.pable of attenuating the overall engine noise level to S3 db when meaeured at a distance of 50 feat The muffler outlet is a standard ME twwhole flange (see figure 19) positioned at an angle of 45 degrees to enable the exhaust gasee to escape into the atmosphere away from the engine. 10.2.5 Coo/ing .$ustent. A single
cooling-
besting system is provided to insure operation over the specified temperature range from minus 25° F. to 120” F. Cooling air is provided by a centrifugal fan integral with the diecast aluminum flywheel. The cooling air is forced over the to? portion of the cylinder barrel and is d]schsrged ::cro.ss the bottom of the engine oil pan. Tbe system is designed to maintain safe engine temperatures m,er the eutire” load range. At ~ated $p?ed, the airtlow is S2 cub:c feet ~minute. 10.3 Engine
ill ustration
and installation.
Figure 21 is a photograph of the model 1A08 Militm-y design engine illustrating the major components viewed from the rope starter end. Figure 20 is a similar ilh.mtration of the engine viewed from ,the engjne power takeoff shaft. The installation drawings are presented in figore 19 and illustrat: the overall dimensions of the engine, the location of the major components and the detailed d:rnensinns of the engine mount. i];r !~ads, w!uipmeni mounting pads, and the power takeo.T shaft. The dimensio,?s indicated .shal] 1?? used to assist in the d,... .si~mrd the in.sra!lation,
10.1 Engine
specification<.
The engine
specitic:.tions arc as listed in tnble II: 7
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h#L-$&~12222A II.
T.,.. Military
dwip
engi.t,
mode!
Enpiw
wrf@ti.##*
1A 08:
A. Engine:
B. Fuel
pump -
Fuel
filter
. . ..-. -....— ....... . ....... ... . ..........
.. . .. . . ... . . ......... .. . ..... ... . .. . . . . ... .. . . . ... .. .dhpbragm
. ...... ...
................ ....................... ........ . ....................~MlO86
Fuel consumptionat rafxd load and ?.Peed,IbAhp-hr .................................... ...............l.lO
,) C. Lubricationsystem: Lubricationsystem ......... ..... .................. ..... .. .. ............. .... . ... . 0,1 sump capacity, pints
..
. ......
.,ll;,sh..v”llor . .......,
.
.. ..................... ............... . .. .... . .... .....................l.00
011 consumption, maximum at rated load and speed, IWbhp-hr .-..-.._ .....- .......0.o25
D. Ignition:
... ..-.--. ......-.-...-mw~
Ignition systen> ............ ........ ........ ........ .... .. ... .. . . .............. .. ..
spark plug .. ............... ........ ............................... .... ................................................... . ..............J&m Electromagnetic
.................... .. ............ . .................................................... .............lfIkEAWO1
compatibility
E. Governorcharacteristics: Speed remhtion, percent
.
Ratxd load and speed, rpm
.. . ....... .... ...
No-load speed, mm (maximum)
Engine speed
.. . . ..
..
.
.
. . ..
. .
A
. .. ............ .. . ... . .. ........... - . ......................3.600 .
s-wbilitv (at cons!mlt value of load). Pement .
. .....3.708 .
. . ...PIus or minus 1/3 of 1
Maximum speed surging Aaractmi+:im: P.ated load to no load, seconds .... .............................................................................................4
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I *
1’
Mll#’lD-12Z6A 29 Octab.r 194S
)
,c.mw 1[,
)?n,q;nt Speci@tio,w-(Cnnt’d
No load tQrated km!, seconds Maximumspesd change during
. .....................
. .. .. .
.... . . ... ........................ .....4
4-second surging yeriod, percent . .........-....-.6
Ratsd load to no load, rpm .............................. .............. No load to rated load, mm ...... . .. ... . . F. Engine and
I
Air
. .......... . .... .
..dl6
.... .. ..... . .................... .. ..... ..?ll.
acmssories:
cleaner
. ..
Cranking system Main bearings _ oranksbaft
Dry
)
.
. .... .. .............. ...........
. . . . . .. .
. .
Life between
.. ...... ..
....-
-dry
type
....................._.... .. .......... ..............- ......... ......nW
. .. . . ..... ........ ... . ...... ... ........... . ....... ......... ..... ... ... .... ...tapared roller
rotation, viewed frrm, drive end
weight, pounds __
.. . ... .
.——.—..—
..-_—
cmntsrcloclnvise
....-...---...-” . . ...”_-_._....._——-..-.49.5
major overhaul or rebuild, hours .._.– ....................._........_- . ..._-—l
$66
G. Overall dimensions:
o
10,5 Fuel consumption. The piwl-tlnmttle fuel consumption characteristics (at 3,600 rpm ) of the 11~~bnp Military drsigu engine am pre:entwi iu the follmving table.
There is a 10 percent increase in the fuel consumption at 3,800 rpm and a 10 per. cent decrease at 3,400 rpm, The effect of altitude
is
insignificant.
9
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,
i
MIL–STD-1226A October 1965
29
) ,1.,,,., 11;,r,,d .<,, $.,,> >,,,!(0,,
i
F,xelconsumption. cal
,,,.(!?. a>, fi,tghv.., k.!. CX423
)
11
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MIL-STD-1226A 290c40k 1%5
)
;R
I
\\ =
MIN)
---~
R TYPICAL
& ,//
,
‘!
1
I
“ ,1+. L
NOTES:
3/!6
i. MATERIAL: 2 FIcTIoNAL 3. NUMEER 4. ’v”
STEEL
PLATE
TOi_CRANCE~I/3Z REGw QED:
SURFACES
I/u ST
2/ BE
ENGiNE FLAT
ANO
SOUARE
WI THIN 2,007
T.I. R
CX-425
● )
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MIL-SID-1226A 29 Octdm?1%5
“’)
3
●
r’
)
7 J_
I
\ +3LANKOUT REOUiRED
CORNER(S)AS F@R CLEARANCE
~;
DRILL
L----
I
z
--d
2 HOLES
NOTES: I.
MATERIALT
2,
FRACTWNAL
3, NUMBER 4.
o )
*“sTEEL
PLATE
TOLERANCFS:~
REQuIRED:
(MIN) j$”
2#NGlNE
“V” SURFACES TO SE FLAT AND SQUARE TO EACH OTNERWl~lN ?.OOS*T. I,R,
CX-M4
13
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t
MIL-STD-1226A ~90ctab0r 196S
(
~-
5“6 -i-l
—-.—2?E?&._ 3.247
~-l
‘+6 4
.. _‘
~W OR!LL \2~lA SmTFACE 6 HOLES
I/ 4+IMINI
~
m.
-s
t
Ii
1
.-
I 13/,6
i
’16 R > TYP
!
..-
‘\ \%
/.
—___
h
.1
f
I+J
/
I
i.-. 2
L25 /&4 DRILL n/;”
___._/
DIA SPOTFACE
2 HOLES NDTES’ i. 2,
MA? ERIAL: SAE ORAFT ANGLES
3,
BLEND
4.
ALL
RADII
FRACTIONAL
5.
FILLETS
6.
HOLES
309 ALUMINUM ,0-#
AND MAY
TO A SMOOTH
CONTOUR
TOL. ~ 1/32. ROUNC 9E
3/,6
R !INLESS
OTHERWISE
SPECIFIEo
cofi ED
7
“v “ SURFACES
Tc
R
PJo. REOUIREG
2 /FNG}NE
eE
fLAT
AND.
SQUARE
TO E,2ch
OTHER
WITHIN
t ,oo5TI.
R
!
i 1
CX-432
)
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* ,.,
) ,,
—END
ITEM
SECURED TO
ENGINE
MOUNTING
‘,
L
t-
\l
PADS
-,/:::: / 1
:; lNSTAUATm
C. G.
-4EWIFMEm SUPPORT
)
//
+—--
‘VIBRATION
L6 —-+-. ISOLATORS
L~ ____.~~
WHICH
STRESS RUBBER IN SHEAR OR COMPRESSION , NO. REQUI RED: 4
/ENGINE F,.,-.%~. Bc8,,,4f><,,!< Pot method.
CX427
)
21
Downloaded from http://www.everyspec.com
MIL-STD-1226A 29 OdObw 1965
TAPER LOCK TYPE BUSHING
ENGINE FLEXIBLE
COUPLING
CX.-.429
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?
MIL-S~1226A 290e10bw 1965 ‘)
I
o
.05
.10
.!5
.20
END ITEM INERTIA F1.rnx
1:1. L.rilio.l
..IIzcJ.. f~,r
‘?hctly
.25
.30
JM , LB-lN-SECz
mttwl,.d
,mi
ilem.
CX442
2$
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MIL-STD-1226A !WOdober 1965
600
I
I
~.:,
“
i“”’!
‘
;, ---’ .-l-;-~:
--.,j
--
.+-n
--J
—...-
I
=3’--’“~’’--”’i’ .-+-’-T-& ;: ,; ~: +....:... .{..-+. :. .I
.— - J
~ : _ ~ /
1. -.3 ?!!..:. !_.:L=:..:, .-h”: ....... ;“l’;i:.~ ! >~~;. ~~
300 I
z T
m
-1
;. b+:
..-._!.
1,
...... j:..
_—. -
,..
I 300
,...J
.x
,~.’.. ..J... ..
L-4--442 .! L... ..- ... o
.0s
.10 END ITEM
.!..
:. ..... . -------
: ----J---L--I
..M....!.... .J .......i-–
200
~.
-i.. --: .15
.....!.
,-...:...-.-...:....:.
.20
.25
J J 3CI
INERTIA. J ~ , L9-lN-SEC2
Cx- 443
24
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‘)
1.0
u
.0
CX444
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MJL-J~lD-l,326A
_... ,. _
—-—+--—
,..
o 0 m
0 0 (lvki/Ni-El
26
‘w>
sS3NdjllS
gNlldf?f)~
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o M&STD=l 226A *’ odder 1965
/-- FUF.L TANK MOUNTED ABOVE PUMP LEVEL (M Axt MuM LENGTH OF FUEL SUPPLY LINE /
20 FEET)
/
.4L.~
CARBURETOR=
Y ... —.-..
-- —-
‘)
FUEL PUMP LEVEL
“$
—. ,,,
L
.
.)
~’~+
i ENGINE :
/’% /:
r —--—.-__L .-_—-w_,
~~
.- J\
-7
3FTMAX”
/’
~--
-“
FILTER
1
FUEL PUMP
\ \
)
(
-FUEL TANK MOUNTED BELGW PUMP LEVEL (MAXIMUM LENGTH OF FIJEL SUPPLY LINE 10 FEET )
Downloaded from http://www.everyspec.com
MIL-STD-1226A 290d&ww6s
MOWTIMG
PA()
R0Lm6
28
}
18
i
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)
) r ~.. l..
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s
(’
MIL–STD-1226A ?? ckmbe?1966
l)@
F, f,!.”,. 3:. .V<.d,l 1.4(1 s-1/1 .u;w,r!,
30
4,.;7,,
,.3$!,;”< ,d,<:,,r !<.: ,., f .,,, /.
II
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MIL–STD–1226A
‘)
29 October 1965
1. 2.
3. 4. -).
:arbqretor S+.mk
PIUS
Tens inn Cabl& High E2hav>stOutlet
7. 6.’
9. 10. !“;.
F!cm=?I. >1,~.+vl 1.1,,...!)/.vim<,,~,+
)
31
