weight ‘and balance data reporting forms for aircraft

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MILITARY. . . . .“

MIL-STD-1374A

30 September 1977

SUPERSEDINGMIL-STD-137431 March 1972

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sT.AN~’~RD’”’‘

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WEIGHT ‘AND BALANCE

DATA REPORTING FORMS

FOR AIRCRAFT

(INCLUDING ROTORCRAFT)

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MIL-STD>1374A .,,:,,,

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DEPARTMENT’OF DEFENSE

Washington, D.C. 20301..-

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Weight and Balance Data Reporting Forms for Aircraft,,.

MIL-STR-1374A :-

1, : This Military Standards mandatory for use by all Departments?

and Agencies of the Department’ of Defense.,. -.

Recommended corrections, additions; or deletions shopldbe.%

2.addressed to the Commander, Naval Air Systems Command, Evaluation Division

(Code: AIR-506), Department of the Navy,

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94

D(C. 20360.

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MIL-STD-1374A

FOREWORD

This standard is based on the coordinated efforts of the Military Services

and Weight Engineers of the Aerospace Industry./

This standard supersedes both MIL-STD-254 Weight and Balance Data ReportingForms ’for Aircraft and MIL-STD-451 ‘Weight and Balance Reporting Formsfor Rotorcraft by combining the common features of both standards inaddition to providing for the.features ‘unique”to each.

The format is adaptable to either manual or machine method preparation.

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“ Paragraph 1..

1.11.’2,1.:3-

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4.”461 ~4,,.2

4:.2.14.2.2-

5.. -“5.1‘5.1.1

5.1.1.15.1.1.25.1.1.3

5.1.1.45.1.2

5.,1.2..1

5.1;2.2. 5.1.2.3 ‘

5.1.2.4~5.1;2,5’5.1.2.6.. ...5.1.2.75.1.2.85.1.2.95.1.2.105.1.2.115.1.2.125;1.2,135.1.2.14..5.1.2.155.1.2,16”:5.1”.2.,17

- 5.1.2.185.:1.2.195.1.2.205..1.3

5.1.3.15.1.3.2

Scope.. “ ;,1Concepts “;

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Principles,.,.,. 1’.-...,...

REFERENCED DOCU~NTS ~~ ‘-’:,“.’,, ‘:”2~Issues of documents’ ,,. 2““DEFINITIONS

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Weight defin”it-ion “ ,~< : : - - ‘“3,.,‘3‘GENERAL REQUIREMENTS ‘ = “.”: :“= _~,,. 3

General instruct~ons, ., ‘. -.: j~,:- .:.’:“5: “.,Design drawings. ~ ,.,: :, . .; . - ~,.’,..

Basic drawings ‘“St-ructuredrawi”ngs’ ‘ ~~~-“,., ~ ~.5’DETAIL REQUIREMENTS 6,-;Detail ins~ructions and glossary of terms 6.Group Wei’ght”Statement; Part I . 6Weight empty

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Useful “load..,,. .. . 7“

Dimensionaland structural data. “..

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Description of.dimensional and s,tructur~l.data.’ ,7Detail.Weight Statement, Part II. ‘ “.. - ?Items serving a ‘structuralas well..asan . ‘.“

equipment function 7.Items common to the several stru.ctur’a”lgroups, , ‘ 9. “wing,,Rotor.”and-~ail‘Groups;-: .. .,~ -. -.-”1-0,’Body G~.OUp ‘. :~ ... ..-7.. -. 11Alighting’Gear Groups ‘ ... - ~ , -’ ,1.2-;

Engine,sect~on of Nac,elle;Group” “ .“ :.”. ’12 ‘:

Air Induction Group :: ~3..

Propulsion Group ,13 ~

Flight Control Group 14Auxiliary Power Plant Group

..15.

Instrument Group.. 1.5“:”’

Hydraulic and Pneumatic Group”” ‘- ‘ .“”. ‘- -.’15Electrical Group ‘- ’16. . .Avionics Group .. :16 -..::-.AfiatientGroup

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‘Fur~ighing.and Equ~Qmeri’t.Group, , .: - 16A5r-Condit50n2n$;and Anti-Icing:,Equipment Group .16Photographic Group . 17Load and Handling Group.

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Special Equipment..,.

.17Appendix I, Detail Wei~ht Statement, Part II,

Structural IncrementsPurposeStructural increments

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9/27

for Design Features 17 ‘.’17”

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Paragraph 5.1.3.35.1.3.45.1.3.5

5.1.3.6

5.1.3.7

5.1.4

I 2. 5.1.4.1

5.1.4.2

5.1.5

6.

6.16.2

Figure 1.2.3.

Part I

Part II

MIL-STD-1374A

CONTENTS (Continued)

Page

Discussion of incrementsMethods of determining incrementsAccuracy of incrementsNonpermanent jointPermanent jointAppendix II, Detail Weight Statement, Part II,

Design Criteria Data for Weight Estimationand Analysis

PurposeDesign CriteriaWeight and Balance Status-Aircraft, Part 111NOTESAbbreviationsChanges from previous “issue

WingWing

Wing

FIGURES

structural increments for design featuresplanformbasic structure weight vs. semi-span

WEIGHT.STATEMENTS

Group Weight StatementDetailed Weight Statement

‘part III Weight and Balance Status

1818181919

19191919212121

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1. SCOPE

MIL-STD-1374A

1.1 ‘ =“ This document covers standard weight statementsand forms Parts I, II, and III hereof, for procurement of weight andbalance data for aircraft (including rotorcraft), states the principlesfollowe~ in the formulation of these standards, furnishes instructionswhere necessary for uniform compilation o’fthe required weight and

. descriptive data, and provides a glossary of terms for which definitionsmay not be self-evident on the weight statements and forms.

Sufficient detail is included to cover the majority of componentsfor most fixed wing, rotary wing, or V/STOL type aircraft. Blank spacesare provided for “write-ins)’ to detail weights” for advanced design

vehicles, hypersonic structures, projected propulsion systems, etc. Care

should be taken before adding a l%rite-inll to ascertain that reasonably

appropriate terms are not already available for usage.

1.2 ~. The detail and group weight statement have.been predicated on the following basic concepts:

a. The primary purposes of the weight data are

to provide information in the most advantageous form for developmentand improvement of aircraft weight estimating methods, and for weight

controls during design and construction of aircraft. Such data and methods

can serve the significant functions of bringing avoidable adverse trendsto light at an early stage, pointing out areas in which design weight

control can be most fruitful, establishing realistic weight goals, andevaluating on a rational basis the weight costs of design features duringthe evolution of new configurations.

b. The secondary purpose of the weight data is toprovide reasonably detailed information for engineering checking and

reference purpose~. -

1.3 Principles. The followifig principles have been followedto implement the above basic concepts:

a. Structural weight has been broken down into

functional and identifiable components which will permit and encourage

the analysis of structural weight variations and stimulate development

of lighter and.rnore efficient structure.

b.’ Insofar as “practicable, all tangible and readily

identifiable components and provisions for a specific function or instal-

lation have been allocated to the functional group, regardless of geo-graphic location and physical method of attachment. Where compromiseof this principle was necessary because of multipurpose function (e.g. , doors

and panels which serve as closure for structural surface as well a,saparticular installation function), items have been allocated geographically”

with as complete function isolation and identification as -possible.

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MIL-STD-1374A

c. The importance of consistent allocation of @weights by all contractors in completing the detail statement has beenrecognized. The amplifying instructions in this document are furnishedto insure consistency in allocation to the greatest extent practicable.

/d. Provision has been made for tabulating in an

appendix of the detail statement the total net weight increments forspecial functions, installations, or features, including the semitangibleweights which are buried in the structural group weights but which can .

be determined approximately by appropriate observation and analysis.during the design and development phases of a new aircraft;

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* 2. REFERENCED DOCUMENTS

2.1 Issues of documents.issue in effect on date of invitation forform a part of the standard to the extent

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The following documents of the

bids or request for proposalspecified her-ein:

I SPECIFICATIONS

MILITARY

MIL-S-8698 Structural Design Requirements-Helicopters

MIL-W-25140 Weight and Balance Control System (For

I Aircraft and Rotorcraft)I

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INAVAL AIR SYSTEMS COMMAND

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SD-24 General Specification for Design Constructionof Aircraft Weapons for the United States Navy

STANDARDS ~

MILITARY

MIL-STD-12 Abbreviations for Use on Drawings and in Technical ~Type Publications

PUBLICATIONS

AIR RESEARCH AND DEVELOPMENT COMMAND .,“

ARDC Manual 80-1 Handbook of Instructions for Aircraft Designs

‘ARMY AVIATION

AMCP 706-201,

SYSTEMS COMMAND

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MIL-STD-1374A

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* 3. DEFINITIONS

3.1 Weight definitions. Weight definitions shall be as

specified in MIL-W-25140. Airframe unit weight is defined and derived onpage 8 of Part I.

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4. GENERAL REQUIREMENTS

4.1 General instructions.

4.1.1 Weight control systems shall provide for determinationof breakdown weight data required by the statements for consistency ofallocations in accordance with the item allocations of the Detail WeightStatement, Part II and the concepts and principles outlined in 1.2 and1.3. If it becomes necessary to deviate from the listed allocations,adequate cross reference and brief reason shall be indicated by footnote. ‘

Further structural and equipment breakdowns, and generous use of footnotes,are encouraged when such practices will further understanding the tabulateddata and aid in the intended purposes.

4.1.2 The Detail Weight Statement, Part II lists entriesto take care of foreseeable cases. Write-in spaces have been providedfor new installations and expansion of the listed entries. Insofar.aspracticable, nomenclature for write-ins shall identify the function ofthe items, and allocation shall be made consistent with the principles“outlined in 1.3. Use of the words “provision” and “installation” shallbe avoided, unless further breakdown is given to indicate what is includedin the item. Supplementary sheets may be inserted when insufficient spaceis available for new installations or expanded breakdowns.

4.1.3 All bolts, nuts,. rivets, etc., and loose’items ofattachment shall be allocated to the same group as the item being attached.

4.1.4 Equipment and system support shall be allocated to

the same group as the item being supported. Multipurpose supportsshall be allocated to “the primary function. Where a primary allocationcannot be determined by observation, such as may occur for fairleads,supports for wire harnesses, and brackets, an arbitrary allocation may be

made.

4.1.5 Where more than one weight category is provided inthe statements for a given installation, allocation shall be made to theWeight Empty, Useful Load, or Special Equipment categories in accordance

with the category allocation assigned in the design detail specificationfor the model aircraft concerned, or in the general design specificationsof the procuring activity. If a conflict in category allocation of anyitem occurs between weight statement and model detail specification, thelatter shall govern in all cases.

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MIL-STD-1374A

4.1.6 All items of power distribution systems (electrical,hydraulic, and pneumatic including fluid in the respective tubing forhydraulic systems, from main distribution points to actuating’units) shall ,’be allocated with the items operated. All’components from source of powerto main distribution points shall be considered to comprise the main system.The distribution system for a given item shall be assumed to include allcomponents which would be unnecessary and could be removed if power actuationof the item were to be eliminated. Where several successive branches froma distribution system are involved, and a clear-cut main distribution pointis not readily apparent, it shall be assumed that power is supplied to a

given geographic location primarily for the function requiring the largestpower, and to other functions in the sequence of descending power requirements.For hydraulic power transmission to the various operating mechanisms (e.g.,

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pages 3, 6, 8, 17 of the Detail Weight Statement, Part II) hydraulic “Fluid”shall be listed separately as a write-in term.

4.1.7 Where a number of identical items and weight for thetotal number of these items are provided for in the statements, the “No.”of identical items shall be entered in the appropriate spaces to avoidambiguity. Design data, such as “size”, “type”, “model”, and “capacity”

shall be completed where specifically provided for, and shall be written infor other items when considered necessary. When abbreviations are necessaryfor write-ins owing to space limitations, the abbreviations as required bySection 6 shall be used.

* 4.1”.8 When business machine methods are utilized and reportsare produced automatically by machines, all pages as shown on the GroupWeight Statement and Detail Weight Statement (Parts I, and II, respectively) .0must be identically reproduced. Where write-in items are necessary, or”wheie an existing item is altered in any manner, an appropriate flag entryshall be made in the righthand margin directly ,opposite the line, Machines”shall be programmed to include all indicated totals including those designatedby parenthesis, i.e., ( ).

I * 4.1.9 Page size. The “normalfull size copies of these formsI are 8-1/2 by 11 inches for Parts I and II, and 11 by 30 inches (foldable to “e

8-1/2 by 11 inches) for Part III. These may be obtained from the procuringactivity, or as directed by the contracting officer. Requests shouldspecify: “Full size forms Part I, II, or III or all, as applicable, ofMIL-STD-1374.” Parts I, II, and III herein are photographic reductions of.

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pages prepared in accordance with the above page size standards and thereforerepresent standards of content and arrangement only.

4.1.10 All pages not used for the presentation,of data may beomitted from the reports.

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MIL-STD-1374A.

4.2 Design drawings. Drawings supplied with the DetailWeight Statement shall be as specified in 4.2.1, 4.2.2, 4.2.3, and 4.2.4.The drawings shall be reductions of current design group drawings.

4.2.1 Basic drawings. Basic drawings shall contain a threeview drawing which shall include the overall dimensions and an inboard ‘profile drawing.

4.2.2 Structure drawings. Structure drawings shall containdirect and cross-sectional views (not isometric) accurately scaled, whichshall include or be attached to the drawing , with details and dimensionsthat show the following:

a. Wing. Structural box including box chord andthickness along the span, typical! cross sections showing flaps, slats,etc., engine location and centroid, fuel tank locations and centroids,store locations and centroids, dimensions and areas for flaps, slats,ailerons, spoilers, leading edge, trailing edge, major cutouts, etc., foldand production joints, materials used, critical temperature areas with ‘design temperatures. Areas shall be shown in square feet and identified by

cross hatching or other suitable means. .

b. Tail. Drawings and information compatible withwing requirement where applicable.

c* Rotor. Hub and hinge, including method of rotorattachment, typical cross section including any balance weight, structuralbox, rotor chord and thickness along the span. Blade area in square feetidentified by cross hatching or suitable means.

d. Fuselage, Hull, and Booms. Primary antisecondary

structure including bulkheads, frames, longerons and stringers, majorcutouts, flooring, major fittings and splices, pressurized area includingvolume, materials, critical temperature areas with design temperaturesindicated. Fuel tank.areas shall be cross hatched and capacities indicated(where not shown on a separate fuel system drawing). Major cutouts, weaponsbays, store provisions, engine, engine compartment and access doors, landinggear support and cutout shall be identified.

e. Nacelle. Primary and secondary structure withdetails compatible with wing and fuselage requirements when applicable.

f. Air Induction System. Details may be included on

a separate drawing or included on the fuselage or nacelle drawings. Inlet

design including spike, ramp, mechanisms, etc., shall be shown.


MIL-STD-1374A

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g“ Alighting Gear. Main, nose, or tail, and auxiliarygear drawings detailing the gear structure, rolling stock, retractingmechanism: attachment fittings, catapult and arrest structure. Sizes anddimensions are to be included for the rolling stock, oleo, travel, wheeltravel (where different from oleo travel), struct length from axle tocenterline trunnion.

4.2.3 Propulsion system drawings. Propuls<cn system drawingsshall show the following: ..

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L a. Engine. Location and shape, mounts,intake attachment station, etc. (unlessshown on the fuselagestructuraldrawings). Bleed or bypass ducts not shown on theinduction drawing.

b. Fuel System. Tank locations,shapes.

2.

access provisions,or nacellebasic air

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and cap-acities as well as location of the major distribution-system components.

* c. Transmission System. Gear Loxes and supports,drive shafts, and supports, from engine to final output drive points.Horsepower, torque, rpm, and gear ratios shall be shown for each stage.Also for each gear box shown, the overall gear box input/output maximumcontinuous hp and rpm.

4.2.4 Equipment drawings. Equipment drawings shall be scaleddrawi~.gsto show maj~r component locations and schematics to show thefunctional layout of the flight control,hydraulic, pneumatic,electrical,air conditioning, and anti-icing groups. Isometric drawings may be substituted.

5. DETAIL REQUIREMENTS Q

5.1 Detail instructions and glossary of items. Specificitems referred to in the Military Standards, specifications,—and in theweight statement are identified by page-line numbers of the weight statementconcerned.

5.1.1

5.1.1.1

@2?.S.Pwe%h~ statemen~j part I.

Weight empty.

Item 2-37, Landing Gear “Type”: Insert “Tricycle”, “Tail Wheel”,“Bicycle”, “Quadricycle”, or similar general descriptive nomenclature.

* Item 3-111 Manufacturing Variation: This wej.ghtis the variation ofweight empty between successively weighed aircraft because of unaccountable

tolerances on sheet and material gages, salvages, pai~t thickness, etc. Itis also intended as an overall factor for differences between weight bookkeepi-ng records and actual weights after the contractor has applied his bestefforts to account for variations in tangible items (e.g., fuel cells,purchased parts, and equipment items) to reconcile any initial, or consistent-

ly repeated, variation from the weight bookkeeping records.

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MIL-STD-1374A

5.1.1.2 Useful load.

Item 4-128: Oil for transmission or gear box which has a self-contained independent sys”tem is included in the”weight empty as Item 20-28 Drive System, Propulsion Group.

‘.Item 4-129, Trapped Oil: ‘were “unusab~e” rather than J’Trapped” :oil has been established for the model delete “Trapped“ “andinsert”

“Unusable”. ,..-, ..

5.1.1.3 Dimensional and structural data. Items 5-lthrough

5-41’require dimensional entries which apply to the weights listed in“Basi,cStructure”. Items such as radomes, canopies, pylons, etc;,.shouldnot normally be included in the.dimensions unless they are ‘apart of“Basic Structure”. ‘It&ms 5-4”2through 6-57 represent structural data . “’sufficient for preliminary ‘design weight estimating. Items’“under 6-20”should be predicated on the critical design condition.or conditions whichdesign- the structure.” Paragraph 5.1.1.4 provides instructions fordescribing the data submi.tted for Part I, Page 5. ,“

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5.1’.1.4 Description of dimensional and”structural data.Specific definitions for dimensional and structural data are usuallyimpractical due to variations in design configuration: and.requirements.Page 7 provides” space for descriptions which apply to the data,includedon Pages 5 ,and 6. Drawings and/or sketches-may be.used as they’are effectivemeans to clearly show where listed dimensions a“ndareas”apply. (Required

‘The-structural design conditionswith the Detailed Weight Statement.)”and speeds should be briefly described and”related to the affected “structure. Rotor systems should be described as to type (articulating,”flapping, rigid, etc.) with rotor tip speed as “designed in MIL-S-8698and design factors “clarified”with regard to power on> Power offj auto:rotation, etc., that may design the rotor. Any dimensions or structuraldata on Pages 5 and 6 which requires “clarification should be describedon Page” 7.

5.1.2 Detail Weight Statement; Part II. “---

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5.1:2.1.. -“ “items serving”.a structtirai aswell as.an equipment

function. (Items serving-”such multipurpose functions ~resent difficultyin coding and in applicatio-n to weight estimating’methods. Therefore,

all--parts of.s“uchinstalla.ti&s which are m“ultiptirposeand.~~rinotbe “isolate:d”as serving a single function and which are integral with thestructure o’f.:the“rotor, wing, tail body, “or nacelle shall be allocated

to these structural :groups.by”write-in’.entries~ ‘using functional identifyingnomenclature. Structural increment’s’sh,allbe”shown in .Appendix I to theDetail Weight Statement, Par,t.iIIto-i%olat”e:”the”structural weight “portion “of such installations. ‘eTjp&a~’”installations in this’category are:

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MIL-STD-1374A

a. Air supply, bleed air, and exhaust ductingsystems in which skin or webs serve as part of duct contour (duct wallsand stiffeners which can be isolated primarily as duct system areallocated to “Engine Section or Nacelle Group, Air Induction System”or “Propulsion Group, Exhaust System”).

b. Double skin and baffle construction for “heatanti-icing ducts and rotor pressure ducts (ducting allocated to “Anti-Icing” and rotor pressure ducts, similar to paragraph (a) above).

c* Integral tanks in which skin, webs, and load-carrying seal fittings are utilized to fo~ the cavity, or bag-typeinstallations in which skin, webs,” and backing board provide tanksupport (backing board, separate tank supports, sealant material, nonload-carrying fittings are allocated to “Fuel System”).

d. Skin or webs serving as deflector plate orradiation protection, or fabricated of special materials to act as heator fire barriers,. or acting under elevated temperature conditions (non-structural shrouding and fire shielding are allocated to “PropulsionGroup”).

e. Load-carrying armor-plate.

f. Engine section structure, engine supports andremoval tracks, etc. , for.engines buried in the body (mounts and vibrationisolators are allocated to the “Engine Section”).

g“ Catapult, arresting, and barrier-crash installa-tions. (Catapult’,arresting, and barrier crash fittings are allocated

to “Alighting Gear”).

h“. Load handling gear installations. (Inflighttowing and external cargo sling, rescue hoist fittings are allocated

“Load and Handling”).

i. Flooring and supports. (Provisicn has beenfor allocation to “Basic Structure” and “Secondary Structure” in theGroup”, as well as allocation to nonstructural flooring in the “Furn:

to

made“Bodysliings

and Equipment Group”. Refer to discussion of “Flooring” under 5.1.2.4.)

j+ Randomes which do not form normal contour ofwing, tail, or body are allocated to the “Avionics Group”.

k. Removable structural panels or.structural doorsfor special functions are included in the basic structural groups.

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5.1.2.2

MIL-STD-1374A

Items common to the several structural groups.

* Pages 2, 5, 7, 10, 11 include a line item titled “Joints, splices and”fasteners”. These items include all doublers, fillers, spacers, gussets,angles, clips, fittings for joints, rivets, bolts, nuts, screws, etc. Theitems shall, insofar as practicable, be allocated by structural functionserved. For example, Items 2-7 and 2-13 shall include all joint, splice,and fastener material in the interspar skin and spanwise stiffeners, thkspar caps, and interspar skin attachment to spar caps; Item 2-17 shallinclude all joint, splice, and fastener material in webs, web stiffeners,and web attachment to spar caps; Item 2-24 and 11-25 shall include alljoint, splice, and fastener material for fastening ribs or bulkheads to

skins and spars; Items 2-34 and 2-39 shall include’leading and trailingedge attachment to spars.

Items 2-21, 2-22, 2-23, 5-12, 5-13, 7-21, 7-22, 7-23, 11-4, 11-24, 16-14, Bulkheads, Ribs, Frames, Chordwise Stiffeners, &ridMinor Frames:

Bulkheads are the main structural members which assist in carrying loadsaround major cutouts, or which distribute major concentrated loads (externalor within the structure). Bulkhead~ include a reinforced or speciallystiffened shear web or truss over the partial or complete cross section andmay also act as partitions to separate an area into physical compartments,or as closures to an area. Body bulkheads, Item 11-4, should be listed

individually and identified by location and by nomenclature which indicatesfunction e.g., “Front Spar Bulkhead Sta. 150”, “Equipment Section”, “Bulkhead65,” and “Fuel Tank Sta. 140”. A supplementary page (11A) may be appendedif necessary (“Nonstructural partitions”, such as movable separators, arecoded to Item 35-52). For large aircraft, it is also desirable to append asimilar breakdown of minor frames, Item 11-24. Ribs and frames are similarbut usually of relatively lighter .construction and serve the functionprimarily of stiffening the skin surface to maintain contour under air loador internal structure .crushing loads. They are not specially reinforced todistribute major,load concentrations. Minor frames and chordwise stiffenersusually have very limited shear web depth, may be partial rather thancomplete contours, and are used primarily for additional local reinforcement,skin stiffening, or to distribute minor local loads.

* Items 3-8, 8-13; 13-5, 16-34, Doors and Frames”: These items includethe framing around the door opening, hinges, and all other items,of the ‘door installation. Columrs are provided for the door “Structure”, aridfora breakdown of the “Operating Mechanism” for power-operated doors. Operating

mechanism shall be allocated to the group to which the door is allocated.

Item 11-39, LongitudinalPartitions: These are longitudinalstructuralbulkheads in the body contributingto body strength, similar to transversebulkheads. (“Nonstructuralpartitions”,such as movable cabin “Separators”,are coded to “Furnishingsand Equipment Group”, Item 35-52.)

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MIL-S7D-1374A.

* Items 3-52,

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53, Exterior Finish: These.items include “camouflage;paint~-”protection” .from elements, filler for-aerodynamic smoothness, e~c”. ;’

*’” Basic protective interior finish is.coded to the item which, it

covers. Items 3-53, 8-51, 13-53, 1-7-53, Interior Finish”:,. Include any

finish added over basic protective coating and.sealants necessary for”“ ,:

press”ur,izationor flotation.

5.1.2.3 Wing,.Rotor, and .TailGroups. Surface Folding:orpivoting actuation systems are to be included.on pages 3, 6,,8;~:and.1O:. “when prov’idedfor ground operation (i.e., wing.fold) and -to Fligh”t~~ ,~:-Controls,.pages .23 and 26, when used dtitiingflight.- ~

Item 5-56 “Blade”.Ass”embly”includes.that structural.portion of therotor between the tip and the.first.hinge .p’oint,inboar”d,ofthe tip, andincludes the root end attachment. “ ..

,.* Items 2-6,”2-12, 5-11, 7-6”,7-12,“.9-7,10-9, Cover:” when-sandwich.

or”filler construction is used, include weight of “I&@”i Skin”, “outerSkin” and “Filler” in cover weight.. Code full’depth’core to”Items 2-28,.5-13, 7-28, 9-14 and 10-11. Use footnotes to call ‘attentionto typeo’fconstruction.

Tip burner hous%ng integral with rotor blade,”write in as Itern”5-42; where removable with burner’,write in as,Item”18-13. ‘:’ -,

Items 2-32, 5-20, and 7-32, Leading Edge Covering:”’ Refer.to 5.1.2.1. ..

regarding double skin construction used as ducting.

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Items” 2-40 and 2-’41, Trailing Edge Core and Bonding Adhesive: To:

be used for full depth core trailing edge construction similar to treatment

of 2-28 and 2-29 for the structural box,.

Items 2-43 ‘and 2-44, Variable’Sweep Pivot Structure: Include ~~write-ink where “Bushings” and “Pins” does not adequately descrifie thetype of pivot structure. Sweep mechanism should be detailed’on page.23

under “wing positioning’! column”with note d,e”s”cribin’gvariable sweep.

‘Items2-47, 2-48, and 7-47, Attachments Wing to Fuselage Wing toNacelles; Tail to Fuselage: Include .identifiable fittingsand hardwarefor attachment of wings.

*, It.em.3-4, Wing Fold: Include..identifiab-le structure necessary for,fold actuationund”er “structure’’colurnn, structural bo~-hinge”an~

,carry-.thru structure to be included on page 2. Fold penalty-in Append5x. ,.I should include both structural penalty buried in pag”e ?-and secondarv

structure including mechanism on naee 3-., —=. - .

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I *

Item 5-41, Internal Duct Structure: This item to be used only whereinternal ducting also serves a structural function in the rotor blades.Allocate non-structuralducting for pressure jet or anti-icing to “PropulsionSystem, Drive”, Item 20-34 or “Anti-icing”,Item 38-15. Refer to 5.1.2.1,“Duct Systems”.

Items 5-45, 5-46, Balance Weights: These are supplementalnon-lcad-carrying weights added to the

Pages 3, 6, and 8, Powerhyc?raulic “Fluid”.

Items 6-5, 6-6, and 6-7,

. .structure for blade balancing or ‘inertia.

Transmission: Refer to 4.1.6 for listing of

Gimbal Ring, Yoke, and Universal Joints:These ~re normally the structural attach~ent of the rotor hub to theaircraft. Write-in lines are provided for other types of such attachments,

for which appropriate descriptive nomenclature should be inserted.

Items 4-21 and 9-21, Tabs: If tab balance weights are used, Write in

on line 22, as applicable.

5.1-.2.4 Body Group. If tubular welded basic structure is used,sicgle write-ins may be used for the entire structure, or sections of thestructure, as appropriate.

Items 11-44, 12-28, Flooring and Supports: Flooring is considered as

follows:

a. “Basic Structure”partially carries flight and landing loads“Fuel Decks” and “Control Decks” and theirunder Item 11-44.

and coded to Item 11-44 if itthrough the aircraft structure.supports should be written in

b. “Secondary Structure” and coded to Item 12-28 ifit is fixed in place, but if removed does not impair flight and landingstrength of the flyable aircraft (that is, flooring is present only as awalkway or for support of equipment, cargo, etc.).

c. “Auxiliaryr’and coded to “Furnishings, and EquipmentGroup”, Item 35-24, if it is removable for various missions, or hinged for

stowage to provide extra deck space, or if it is ovirlay to increase localfloor-load capacity.

Item 11-51: Rotor support included for the structural membel-swhoseprimary function is to provide a structural connection between the rotor”and the body. The pylon fairing is listed as Item 11-52 if structural, or

under Item 13-46 if nonstructural.

11 ‘


I

*

*

*

k

*

MIL-STD-1374A

\

Item 11-45, Firewall: Refer to discussion under 5.1.2.6, Item 16-24.

Items 12-5, 12-11, Canopy: Includes glass and plexiglass. Bullet-

resistant glass shall be allocated to “Armament Group”, Item 32-29.

Page 13, Power Transmission: Refer to 4.1.6 for listing of hydraulic s“Fluid”.

5.1.2.5 Alighting Gear Groups.

Item 14-1, Landing Gear “Type”: Insert “Trailing Arm”, “Conventional”,

“Articulating”, “Quadricycle”, or similar general descriptive nomenclature.

Item 14-3, Location: Insert column headings descriptive of the

location, such as: Fuselage, Wing, Nace~le, etc.

Where landing gear drive mechanisms for taxiing are provided, writedescriptive breakdown of page 15 with weights tabulated in last column.

5.1.2.6 Engine Section or Nacelle Group. Rings and annularsections solely for generating lift are to be coded under wing, page 2.

in

.

Rings and annular sections which may generate lift but are basically fox

propulsion efficiency are to be coded under Items 16-13 and 16-32 usingwrite-ins for adequate description of the structure.

Item 16-9, Gear Box Support Structure and Item 18-8, Reduction GearBox: Allocate to these items only the gear boxes and mounts used exclusivelyfor driving the propeller/fan or a load compressor in pressure jets.Otherwise, allocate gear boxes and mounts to “Drive System”, page 20.

Item 16-22, Pylons: Where pylons are built-up structure of spars,frames, skin, skin stiffeners, etc., insert breakdown tY written items”

Item 16-24, Firewall: Nonstructural firewalls, or firewalls whichserve a structural function in the nacelle, are coded to this item. Fire-walls which serve a structural function in the body are coded to “BodyGroup”, Item 11-45. Firewalls in a wing (rather than a wing nacelle),which serve a structural function for the wing, shall be coded to “WingGroup”, Item 2-54.

Item 16-32, Cowling: If cowl is sectionalized for maintenance orfunctional purposes, write in breakdown of sections, usi~g descriptive

nomenclature.

Page 20, Power Transmission: Refer to 4.1.6 for listing of hydraulic“Fluid”.

12 “


I

I

5.1.2.7 Air Induction Group.

Item 17-3,0Engine Dome: If the engineengine, it is listed under.18-4? Otherwise

MIL-STD-1374A

,domeis supplied with th’eit shall be included here.

5.1.2.8 ‘“ Propulsion Group. Separate cola”ns areincluded toallow for dissimilar engines, Auxiliary’Power Plant Group, page 27; isprovided for power plants used only to supply power for starting orequipment.

‘.Item”18-4,Engine (as installed): List engine weighti includingall residual,s”asspecified in SD-24, afidall engineaccessories’ whichare a part”of the specified’engine weight. For unusual cases in which -items commonly included in other.groups are included inengine weight

‘ -(e.g.,starter generators), appropriate cross-reference is desirable..Where.rotor tip burners are used, write in using line 18-7.

Fuel”lines from distribution point to burners, write.in as Item 19-38.

..Item 18-12, Accessory Gear Boxes and Drives: This’item includes.allm”ulti-purposegear boxes’and drives which are notintegral withdrive system gear boxes (Items 20-4 and” 21-5) nor ~n the specifiedengine weight.

Item 18-21, Exhaust System Shroud, and Item 18-28, Engine.Cooling:Refer-to discussion under 5.1.2.1’for duct systems where structuralsurfaces form part of duct contour.

Item18-40, Starting System: Power supplies such as gas generatorsshall be coded,here as .a write-in solely for”starting and to the power .’plant group yhen..u~edfor other power requirements in addition to starting.When air turbine starters are used”,air supply ducts shall be “listed-as;a’write-in’item. For casesin which skin or webs serve as part of theduct, refer to 5.1.2.1;

.. . .Items 18-41 and ~8-42? Starter Type:” Descrfbe byAN and MIL standard

number, and nomenclature.such as “Pneumatic”, and.’’CartGidg,’’,.and “Air- ;. fuel Combustion”.’ ~ “ ~~‘,.. ..

~Item 18-50,”Propeller Controls: Includes governors, synchronizers,boostersp pumps, relays; switches, lights, timers, circuit<breakers, ~etc. Under”’’Type”,list “Electrical’’,”’’Hydraulic”, “Manual”, etc.

Items 18-51, 18-52, Propeller Oil and”Tank: These items providefor entries when a separate oil supply system for hydraulic propellersis u“sed. When engine oil is used for hydraulic propeller supply, propelleroil is included under “Trapped” or “Unusable” oil in the useful.load.

.13

—..-.. -


I

MIL-STD-1374A

Item 20-2,” Identify gear boxes in column headings in sequence fromengine output to rotor(s), fans or props.

Item 20-22: Include’all components for independent gear box.lubrica-tion system. Include drive system lubrication in Item 21-20..

item 19-4, Tanks: List each cell or tank individually, even thoughtanks may be interconnected. Wetted are’asof tanks shall,also belisted as a write-initem, integral tanks excepted. Under “Type” list“s.s.”, “Bladder”, “Aluminum”, etc.

Item 19-18, Integral Tank Seals and Sealants: This item includes allsealant compound, corner seal fittings, and other non-load-carryingtank seal fittings. Also refer”to discussion under 5.1.2.1 for itemsserving a structural and equipment function.

Item 19-39, Pumps: Include all pumps, including those buried intanks.

* Items 19-45 to 19-54, Lubricating and Fuel Plumbing Systems: Includesall piping, fittings, drains, valves, supports, etc., except for itemsspecifically provided for on page 19 and major or novel items for whick,a write-in item may be warranted.

“Fuel Gaging Equipment “ is allocated to “Instruments”, page 28.

* 5.1.2.9 Flight Controls Group. Insert data for fixed wingsystems controls on pages 23 and 24, rotating’rotorffan systems controlson page 25 (v/stol transition systems controls to page 26).

For “Wing Positioning” or “Rotor/Fan Attitude” controls, write inon page 22 any controls which are in the cockpit and allocate the remainderof the system to “Wing Positioning” or “Rotor/Fan Attitude” columns.Use similar treatment for any other special flight feature controls,inserting a descriptive colu~ heading on pages-23 or 26, as

Rotating Controls, page 25, columns 5 and 6, defined as

control items which rotate with the rotor.

Rotor/Fan Attitude Controls,,page 26, column 2; definedcontrols which tilt the rotor axis.

appropriate.

those rotorcraft

as those

●

✜✎

e

-,i

For aircraft with powered flight control systems, follow the generalguidance of paragraph 4.1.6 by-coding the power distribution components(from the main distribution.point) to the “Flight Control Group” andthe power supply components to the appropriate power generation groups(“Hydraulic”, “Pneumatic”, “Electrical”).

,.

.

I/,.


III

Items 23-5, 24-5, 25-6, 26-5,

manual or boost systems: Includes

Controls” to the devices actuated.

MIL-STD-1374A

/Mechanical Operating Mechanism: Forall mechanical controls from the “CockpitFor powex-operated systems: Includes

all mechanical (pilot actuated) controls between the “Cockpit Controls” andthe “Power Operating Mechanism”.

2 * Items 23-10, 23-17, 23-26, 23-41; 24-10, 24-17, 24-26, 24-41, 25-19,25-25, 25-42, 26-10, 26-17, 26–26, and 26-41, Power Operating Mechanisms:For boc,stsystems: Includes all boost system components (wiring, plumbing,

G actuators, etc.) from power distribution point to, and including, the boostunit. For power systems: Includes all power system components (wiring,plumbing, actuators, etc.) from power distribution point to the surfacesactuated; mechanical components from power units to surfaces actuated”shallbe allocated to “Mechanism”, Items 23-14, 23-22, 23-31, 24-14, 24-22, 24-31, 25-23, 25-32, 26-14, 26-22, and 26-31.

I Items 23-34, 24-34, 25-38, and 26-34, Artificial Feel: -If specialfeel “Systemsr’are provided, insert breakdown by write-in items. Write-in“q” springs and speed sensing devices.

Items 23-48, 24-48, 25-48, 26-48, Supports, Guides, etc.: Includesseals and covers for pulleys and cables.

● * 5.1.2.10 Auxiliary Power Plant Group.

Page 27: Includes complete auxiliary power plant installation. Forunusual cases, in which items commonly included in other groups (e.g.,generators and alternators) are included in the auxiliary power unit (apu)wej.ght,appropriate cross-reference is desirable.

\* 5.1.2.11 Instrument Group. The “Installation”—. column is provided

~ for allocation of all wiring, circuit breakers, plugs, relays, switches,tubicg, valves, brackets, etc., for instruments.

“Fuel Gaging Equipment” (inlcuding probes, amplifiers, indicators,:-. wiring, etc.) is to be allocated to “Instruments”.

Item 28-53, Instrument Power System: Alternators,’ inverters, vacuum

pumps, etc., useti exclusively for instrument power should be written in asspecific entries under this item. Multipurpose power supply or powerconversion items are listed under “Electrical Group”, Items 30–3 and 30-22.

* 5,1.2.12 Hydraulic and Pneumatic Group. Refer to 4.1.6 fordiscussion of main system and determination of distribution points.

e 15


- MIL-STD-1374A,

* 5.1.2.13 Electrical”Group. Refer to 4.1.6 for discussion ’of.0main system and determination of distribution points.

Items 30-3, 30-14, Power Supply and Conversion Equipment:“Allmultipurpose power supply and conversion equipment are allocated to

these items. Single purpose power supply and conversion items are codedto the group service (e.g.,

instrument inverters are coded to !lInstrumentlrItem 28-53). 3

Item 30-31, Wiring: Where extensive use has been made of aluminumwiring, nylon-jacketed wiring,

etc. , add appropriate’ footnote.

Item 30-34, Lights and Signal Devices:Includes all necessary

wiring, switches, relays, etc.

* 5.1.2.14 Avionics Group. All avionics equipment shall beallocated to this group. When for special reasons, it is necessary todeviate from this practice, cross-reference to other groups to whichavionics equipment has been allocated shall be made.

The “Installation!t., column is provided for allocation of contractor-furnished brackets,

tables, shelves, wiring, cabling, plugs, etc. Government-furnishedinstallation items shall be listed separately in the installation column.

*’ 5.1.2.15 Armament Group.

Item 32-28, Passive Protection:Refer to discussion under 5.1.2.1

for armor and deflector plate serving a structural and equipment function.

* 5.1.2.16 Furnishing and Equipment Group.

Item 35-24, Auxiliary Flooring: Refer to discussion of flooringunder 5.1.2.4, Items 11-44 and 12-28.

Item 35-52, Partitions (Nonstructural):Refer to discussion of“Longitudinal Partitions” under 5.1.2.2,1tem 11-39.

Item 35-53, Vibration Absorbers:Separately identifiable devices

(not incl. engine or equipment type isolators) which generally functionto improve the.vibration environment for crew and passengers. In thisrespect they serve a function similar to acoustical and thermal insulationand are considered furnishing.

* 5.1.2.17 Air Conditioning and Anti-Icing Equipment Group.

Items 37-43 and 38–42, Hydraulic Controls:Refer to 4.1.6 forlisting of hydraulic “Fluid’!.

.-.

,,.,

“,,’,,,

-2,.

I16 ‘

b,”

: ,,).,

,.,.,

a;“.,, ..,.

,,.3:,,:

,:1 ,,Ij y

,!,, I


MIL-STD-1374A

I

II

‘*

.,_

Item 38-15, Ducting:..Refer to discussion under 5.1.2.1 for ductsystems where structural surfaces form part of duct contour.

Where’-equipmentor installation serves both air-conditioning andanti-icing functions, code to primary function and cross-reference underthe other; where a distinct primary allocation is not apparent, anarbitrary allocation may be made with appropriate cross-reference ofdual function.

5.1.2.18” Photographic Group. Gun camera mounts, wiring,etc., are allocated to this group.

* 5.1.2.19 Load and Handling Group. See 5.1.2.1 for discussionof items serving structural and equipment ftinction.

Item 40-29, Ramps: Allocate ramps to this item which are not-partof the cargo doors or which do not serve as a closure for a structural

I surface. ~efer to 1.3b. Other ramps should be allocated or writteninto the appropriate structural group.

5.1.2.20 Special Equipment.

Item 41-38, “Type” Tanks: List “S.S.”, “Bladder”, “Aluminum”, etc.

5.1.3 ,Appendix I, Detail Weight Statement, Part II.Structural Increments for Design Features (pages 42-44).

5.1.3.1 Purpose. Pages 42 and 43 provide for determinationand listing of net structural weight increments for special functions,installation, and other”design features. Such information is consideredessential for a full understanding of structural weight variations amongvarious configurations, and for ,formulationand improvement of weightestimating methods.

5.1.3.2 Structural increments. These net structural weight

increments are a“lreadyincluded in the structural weights tabulated inthe Detail Weight Statement, Part 11,.but are of such nature that,they

:..may not be directly apparent quantitatively during the normal processesof calculating weights from drawings and coding to items in a weightstatement. Insofar as practicable, tangible portions of these netincrements are isolated as items in the structural groups under “SecondaryStructure”. Semitangible portions of these net increments which do notlend themselves to automatic coding as items on the weight statement,are buried or masked in the “Basic Structure”, and must therefore bequantitatively evaluated by some rational analytic procedure. In the

I

latter cate~orv are the weight penalties caused by major cutouts andjoints,landing

rem&able structural panels, portions of the wing designed byrather than flight loads, blas~ protection, gun reactions, heavy

I

17


I

..- . .

skin,.servingprimarily as”deflector plate, use of’special materials inhigh temperature regions; etc. In general, the intangible weight .fncrementis in the form’of increases in skin and web gages,’special ribs.andauxiliary sparij doublers, built-up sections around cutouts and otherlocal increases. ~A total net increment represents the weight penaltiesof a.feature for the existing 15asicconfiguration, and does.not-entail :evaluation of the relative merits of weight of .,o”t”herconfigurations ortypes of construction which might’be.possible without the.-feature.Therefore, areas,basic geometry,.type of.construction, design conditions,and design philosophy which led.to selection of the existing .configur”ationare assumed to be unchanged.

.,

5.,1.3’.3 Discussion of increments. Since mere.listing of netstructural increments may, in’some cases-,warrant discussion co avoid”ambiguity, page 44 provides for.amplifying and clarifying remarks.Brief discussion should be utilize’dto indicate: The source.’ofthe netincrement.,.interms of its basic and-secondary structure components; the

effects of overlapping penalties’,one of whic”hmasks or includes thepotential ,effectof ‘another,and for which, therefore, a distributed orinclusive increment has.been listed, etc. Schematic diagrams of typestructure are desirable and should be included”where considered necessaryfor clarity. Tabular ~reakdown of the derivation of the’net incrementin the form”shown in Fig”tire1 may be used to advantage in the discussion’.

.

5.1.3.4 Methods of determining increments. Any rationalprocedure for determining the increments maybe used. Discussion ofproposed procedures with the procuring activity is encouraged. .TWO ‘ ~possible approaches”are suggested in the following paragraphs. A corn-bination of approaches may-be found to be advantageous. “L

5.1.3.4.1 The.normal structural design processes and review of’structural drawings-may be utilized to determine qualitatively, as:thedesign progresses,the area in which the structural compromises havebeen made for design features. A review and analysis of the criticaldesign loads and conditions may produce information concerning “themagnitude of the compromises, from which the weight increment may be cdeduced. ,’

5;1.3.4.2 Graphical plots of weight distribution of the’st’ructuralelements (covering, webs, spar caps,.etc), superimposed on a planform {ofthe structural envelope may.yield information from which total local .“weight increments may be deduced. A study of the irregularities in theweight distribution, their location on the envelope, and a review and ‘“analysis of the critical structural loads and design conditions mayproduce qualitative allocation of these irregularities to particulardesign features. An example of this type of approach for a wing isshown in Figure 2 and Figure 3.

5.1.3.5 Accuracy of increments. It is ,recognizedthat somedegree of approximation will be inherent,in determining the intangibleportion of the structural increments.

..

.-

,,18,

..

.,.

.$

./,”

0“”


I

*

*

*

MIL-STD-1374A

5.1.3.6 Nonpermanent joint. This type of joint is one which

can be readily disconnected in the field “for folding, stowage, &intenance

disassembly, etc., purposes. The structure may be in the form of concen-trated tension or shear connections and doubler plates,.”ora ringof removable ,connections.

,.5.1.’3.:7; Permanent joint. This type.of joint is incorporated”

for manufacturing reasons and cannot be readily disconnected in’ the field.

The structure is continuous but addition=l”and’mating members, fittings,, --doublers; splices, etc., may have been added for”manufact,uringassembly ~purposes. .

5.1.4 ‘ Appendix II, Detail-Weight Statement, Part II,’

Supplementary Data for Weight Estimation and’Analysis. To”be completed. “-

when data are agreed upon..-.

.,5.1.4.1 Purpose. Page 45 provides:for detailed datato.supplement

that included on pages 5, 6 and 7. Part I compatible with and necessaryfor analytical weight estimating methods used with the Part ,11 level ofweight”breakdown.

5.1.4.2 Design Criteria;’ These “data supplementing infotiation

provided in Part I, pages 5“and 6, should be consistent with the aircraftdesign stage at. time of submittal. Line items’ for’which,data are not yetavailable shal,l be so indicated. “Pertinent design criteria not listed on

page 45 which materially affects the aircraft weight should” be added.

5.1..5,..

.Weight and Balance Status - Aircraft, Part III. The

compilation of data for, and use of, the status report form is considered

to be self-explanatory for the most part. The following instructions are

intended to aid in the preparation of the status report.

a. All entries in Column 8“,page 1 shall be detailed ‘ “

on the combined GOV’T/CONTRACTOR pages. Delete the words “CONTRACTOR” and

add appropriate’ page numbers as required, i.e. 2, 2a, 3, 3a, etc. Use aseparate column for each change and additional sh,eets if:necessary.Changesare to be identified ‘in’”tabularsummary called forin Instruction b.

b.; Attach a tabular sunuiar$ ,of Govit responsibility

changes l“isted’on Column 3, page 1 listing the following information, asapplicable’, for each change.

(2). Contract Change Order number.

(3) “Letter’designationof correspondence refer-ence for pending change not yet assigned an ECP number.

.-..

.19


MIL-STD-1”374A

(4) Brief subject/title, together with changes toweight empty and horizontal moment, -useful ’load, and horizontal moment, andgross weight center of gravity, for GOV’T .responsibility chan&es incorporated

~ince las~”status report (ColUmn 8, page 1). List the column number on :

added pages in which the change”is,detailed.

(5) Authorized ’changes (Column 3, page 1) shz.11be listed’as a separate group and may reference and carry forward the ,total .?

of weights, moments and center of gravity for the “authorized” changessummarized in the last status report.

c. All entries on page 1, Column 9 shall be detailedon the combined GOV’T/CONTRACTOR pages. Delete the words “GOV’T” and addappropriate page numbers as required, i.e. 2, 2a, 3, 3a, etc. Use a separatecolumn for each change and additional sheets if necessary. Minor changesin group weights due to revised estimated, calculated, or actual weightsneed not.be listed in detail and may be combined into one or more columnsusing appropriate headings such as Calc vs Est, etc. Include brief discussionof reasons for all important or major weight changes, variation, or C.G.

investigated or applied.brief titles to identify

shifts, including horizontal moment changes and any remedial measures beingUse column numbers from the appropriate page andeach change; c’

o

d.basis for current weightcurrent group weights ofActual Weight Status.

On page 1, for each item of weight empty, under

data, Columns 10’thru 12, list percentages ofColu~ 6 which are in an Estimated, Calculated, or

If Main and Auxiliary Engines are used, attache.breakdown of main and auxiliary Propulsion Groups:

1f. Enter airframe weight on page la as updated from

page 8, Part I of the Estimated Weight Report. c.

g. (1) Page la - Lines 175 & 176. Delete the. .

1

inapplicable wheel position. Most Fwd & Most Aft should show extremes(paragraph 3.8.3 of MIL-W-25140).

1’

(2) Recommended C.G. Limits. Indicate wh~therwheels up or down. If limits vary with gross weight, include C.G. envelopeplot. State conditions which determine the C.G. limits and source of datain initial issue and whenever limits are revised.

II


‘“MIL-STD-1374A

6. NOTES

6.1 Abbreviations. When abbreviations are necessary forwrite-ins or in machine tabulation methods, the abbreviations of MIL-STD-12shall be used wherever space permits. The following list summarizesacceptable abbreviations commonly used for weight data or used in theSummary Weight Statement, Detail Weight Statement, and Weight and BalanceStatus, Parts I, II, and III, respectively, of this standard. Where morethan one abbreviation is shown, the first given is preferred.

alighting - alightbarometric - bartcboost - bst-bungee.- buncollision - coincompartmentation - comptncontingency - cntcyco-pilot - c-pitcovering - covrgcyclic - Cycduct - dufairlead - frldfingerplate - frplfire warning - fwngflasher - flshrgusset - gusheadset microphone - hdstmkhook - hk

incidence - incidinertia - iner

king - kg

liner - lnroxidizer - oxidiz

pedal - pdlpitot – pitpylon - pynrainshield - rnsd

shelf - shlfshelves - shlves

shimmy - shiny

stabilizing - stabgstick - stcksupercharger - s-chg

thermoswitch - thswtransponder - xpdr

walkway-wkwy

* 6.2 Changes from previous issue. The margins of thisspecification are marked with an asterisk to indicate where changes(additions, codifications, corrections, deletions) from the previousissue were made. This was done as a convenience only and the’Governmentassumes no liability whatsoever for any inaccuracies in the”senotations.Bidders and contractors are cautioned to evaluate the requirements ofthis document based on the entire content irrespective of the marginalnotations and relationship to the last previous issue.

CUSTODIANS: PREPARING ACTIVITYNAVY - AS NAVY - ASAIR FORCE - 11 PROJECT NO. 1500-0092

21


.,

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.

J..C

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~

FUSEL~GE

L’

ATTAC~NT

‘,~ ,?“,1

,,

sWING

SWEEP

&PIVOT,

CHORDWISE

WELDS

22

BARRICADE

ENGAGEMENT

WING,

FUEL

PYLON

SUPPORT

STRUCTURAL

ELEMENT

Upper

IntersparCover&Stiffeners

‘

LowerIntersparCover&

Stiffeners

292

318

‘

-14

-55

8 10

24,..

53

58

,

18

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SparWebs&

Stiffeners

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Pins

&Bushings

10”

194

,, 20

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SweepActuatorAttachment

‘,

45

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’164

’40

2899

TOTAL

BASIC

STRUCTURE

INCREMENT

‘.

755

TOTAL

SECONDARY

STRUCTURE

INCREMENT

.,

,ToTAL

STRUCTURAL-INCREMENT

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9

755

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28

40

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99

173

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increments

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design

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AtixlLiARY

FLAP=

SWEEP

ACTUATOR

PICK-UP

WING

PIVOT

CENTER

SECTION

-L.

E.FAIRING

II

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II

II

II

II

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PART I

GROUP WEIGHT STATEMENT

&

I

MIL-STD-1374A

.

I


I

MIL-STD-1374PART I - TAB PAGENAm MODELDATE REPORT

II

G~OUP WEIGHC STATEMEiT

AIRCbFT

(.+NCLUDING XOTORCRAPI)

ESTIMArED - cALduuvm - hcTuAL

(CROSs OUT THOSE NOT APPLZCABLE)

AIRCRAFT, GOVERMENT NO.

AIRCR4FT, CONTRACTORNO.

MANUFACTUREDBY

MAIN AUX

ENGINEMANUFACTURED-BY

ENGINE NO.ENGINE TYPEPROPELLERMANUFACTUREDBYPROPELLER MODELPROPELLER hWER

PAGES REMOVED PAGE KO.

cm

1


MIL-sTI?-1374PART I - TM .’““ GRoup ~IGHT sTAT~NT. PAGE ., “NM . WEIGHT EMPTY . MODEL

DATE -REPORT ‘ ●

--

=

0

ig

* CHANGE TO FLOATS AND STRUTS FOR WATER TYPE GEAR.**LANDING GEAR ‘f’TYPE”:INSERT “TRICYCLE”,“TAIL wEEL”, “BImcLE”, ‘:QUADRICyCLE”> OR SIMILAR

DESCRIPTIVENOMENCLATURE.“.

2


I

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●

MIL-Sl%1374 PART I - TAB GROUP WEIGHT STATl?ME~ PAGENAMF. WEIGHT EMPTY MODELDATE REPORT

58 PROPULSION GROUP x AUXILIARY XX MAIN x59 IATION I6061

~ ~63 UST SYSTEN64 ~G65 WATER INJECTION

.66 ENGINE CONTROL67 STARTING SYSTEM68 PROPELLER INSTALLATION69 SMOKE ABATEMENT70 LUBRICATING SYSTEM71 FUEL SYSTEM72 TANKS - PROTECTED73 - UNPROTECTED74 PLU?fBING.ETC.7576 DRIVE SYSTEM77 GEAR BOXES, LUB SY h ROTOR BRK78 TRANSMISSIONDRIVE79 ROTOR SHAFTS8081 FLIGHT CONTROLS GROUP82 coc~~ O LT83 SYSTEMS CONTROLS848586 AUKILIARY POWER PLANT GROUP87 INSTRUMENTSGROUP88 HYDRAULIC & PNEUMATIC GROUP8990 ELECTRICAL GROUP9192 AVIONICS GROUP93 ~94 INSTALLATION9596 tiwr GROUP (INcL.PA8sIvE p:OT. LBs,)97 FURNISHINGS & EQUIPMENT GROUP98 ACCOMMODATIONFOR PERSONNEL

- 99 MISCELLANEOUSEQUIPMENT,100 FURNISHINGS,101 EMERGENCY EQUIPMENT,102.103 AIR CONDITIONINGGROUPa4 ANTI-ICING GROUP

106 PHOTOGMPHIC.GROUP107 LOAD & HANDLING GROUP108 AIRCRAFT HANDLING109 LOADING HANDLING110 BALLAST111 MANUFACTURINGVARIATION

-112 TOTAL CONTRACTOR CONTROLLED i I113 TOTAL GFAE

HT EMPTY - PG 2-3

3

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-.

\.””..

.’

HIL-STD-1374‘PAR-TI - TABNAMEDATE

,.. .

‘.-.,.

GROUP WEIGHT STATEMENT PAGEUSEFUL LOAD AND GROss WEIGHT MODEL ...

REPORT

115 LOAD CONDITION116117 CREW (NO. )118 PASSENGERS (NO. )119 FUEL LOCATION TYPE GALS.120 UNUSAELE121 INTERNAL122123124125 FXTERNAL126127128 OIL129 TRAPPED130 ENGINE131132 roEL TANXS (LOCATION )133 WATER INJECTIONFLUID “ ( GALS,)134135 BAGGAGE136 CARGO137138 GUN INSTALLATIONS ,139 GUNS LOCAT.FIX.ORFLEX.QUANT::TYCALIBER . .

.140 .“

.141142 AMMo.143144145 SUPP Tv S*

146 WEAPONS INSTALL. ** .

147148Iibq150151152,153154155 .,

156157158159’,160.161.162 SURVIVALKITS163 LIFE RAFTS164 OXYGEN .. .

.165 MISC. .. .,,

166 . .,i67,168169 TO AL USEFUL LOAD ,. +

170 WEtGHT EMPTY1/1 GROSS WEIGHT

* IF REMOVABLEAND SPECIFIEDAS USEFUL LOAD.**LIsT sTo~s, MIssILEs, soNoBuoys,ETC. lW1.CIWED BY RAC’K$,LAUNCHERS,.CHUT”ES,ETC. THAT ARE NOT

PART OF WEIGHT EMPTY. LIST IDENTIFICATION,LOCATION, AND QUAiiTITYFOR ALL.ITEMS SHOWNINCLUDING INSTALIiATION,

.. ...’

4

I

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,,

MIL.{:TD-137hPART I - TAB GROUP WEIGHT STATEMENT PAGEN~,! DIMENS1ONALAND STRUCTURALDATA MODEL

DATE~ REPORT

I

II

I

5


MXL-ST.D-1374- TAE GROUP WSIGHT STAT~~ ‘.

NAM’ DIMENSIONALAND STRUCT~ DATA “

DATE (CONTINUED)

, ..

PAGEMODELREPORT

‘0

:.I

“o,\

1“ 6

“m


MIL-STD-1374PART I - TAE GROUP WEIGHT STATEMRNT PAGENAME DESCRIPTIONOF DIMENSIONAL MODEL

,+

DATE AND STRUCTURALDATA REPORT

1 I1

2 REFERTO PAMGRAPH 5.1.1.4 O*34 DETAILED REQUIFSMENTSFOR INSTRUCTIONSFOR USE567891011 I12

131415161718 .,19202122 I

.

23 I2425 I2627 I28 ]293031 I32?33

- 323637383940 I414943444546 I’474849 I505152535455 I56

..

7


1 I I I ITHE AIRFRAME UNIT WEIGHT ~0 BE ENTE$ED ON LI~E.-56OF P~GE 6 OF T@

IE GROUP !@IGHT

STATEMRNT SHOULD BE DERIVED’BE~OW IN DET/iILSHOWING THOSE I@MS DEDUC@ED FROM !@EMPTY.

IGHTTHE ITRMS BELOW FOLLOW rHE DEFIN~TIONOF 4/IRFRAMEI@IT WEIGH~ CARRIED IN THE

DOCUMENT “CONTlbiCTORCOST DATA REPORTING[SYSTET4°@iTED 5 NO@MBER 197!3. AIRF@ E UNIT .WEIGHT IS THE SAMS AS PREVIOUSIY.CALLED /UIFRAND IiCPRAND I$NOT TO R$SCONFUSEtiWITHWORK BREAKDOWN STRUCTURE (WBS) AIRFRAME kOST DEFI~TION.

1 I 1f I I I

WEIGHT RMJ’TY1 1 I

I I I

I “iDEDUCT THE FOLLOWING ITEMS IjESCRIBEDiNP&T 11!I I I

I 1 1 I

L 1 I1 [WHEELSBRARES, TIRES & TUBES ..

.

2 IENGINES- MAIN AND AUXILIARYi 1 i !

I I i I3 RUBBER OR”NYLON FUJILC LLSE

4 STARTERS - MAIN ~ Ii1 1 1 ! I 1

ld~sP 1:

F ‘9 AVIONICS I 1’

10 TLTTS & POWER OPERATED MOUNT~ . II

I I I11 AIR CONDITIONING,ANTI-ICING Al@ PRESSURIZATIONUN!TS & FLUiDS

12 CAMERAS & OPTICAL”VIEWFINDERS I - II I

! I 1 I

IAIPXMME UNIT WEIGHT I I 1L

lNOTESFOR PAGE 5: I I* INSERT INCHES FROM CENTER LINE OF THk ROTOR TO THE ELASTiICAXIS Ok THE BLAIk

Attachment FOR THE ROTORS.** PAMLLEL TOTHE CENTER LINtiOF THE VltHICLEFOR WING AND!TAIL. I I

~ posED FORIN ~uous IN~ ~DN CONTY w

,

:,

,=

ALL OTHERS.****NosE To AFT TIp ,oFFusE

8

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I,

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PART II

DETAIL WEIGHT STATEMENT

,.. .

MIL-STD-1374A

/

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MIL-STD-1374 PART II-TABNAMEDATE

PAGEMODELREPORT

I I I \

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I

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. ,.,,.

MIL-STD-1374PART II-Tin” WING-GROUP PAGENANE BASIC STRUCTURE MODELDATE REPORT

1 I CENTER INTERN OUTER GLOVE2 I-SECTION* PANEL* PANEL* *** ,. 1“3 . .4 UPPER I .5- -SPAR CAPS 6 SPAN. STIFF..6 ‘-COVERINCL.INTGRL.STIFF.‘7 -JOINTS, SPLICES & FAST:8 -DOORS& PANELS (STRUCT)910 LOWER11 -SPAR CAPS & SPAN.STIFF.12 -COVRR INCL.INTGRAL.S’TIFF.13 -JOINTS. SPLICES & FAST.14 -DOORS & PANBLS (STRUCT)15 . ,., -

.’r6 SPAR WEBS & SHEAR PANELS

.17 -JOINTS. SPLICES & FAST. I18 -DOORS & PANELS (STRUCT)192021 INTERSPAR - RIBS’22 -BULRHEADS23 -CHORDWISE STIFFENERS24 -JOINTS, SPLICES 6 FAST.2526

,.-,

●

✎✎✎

✎✌✌* IDENTIFY LOCATION BY’BUTTLINESOR SPANWISE STATION.,** INCLUDE FULL DEp~ C(JM o~y+ coDE sANDWIcHPANELS TO THE COVER.***INcLuDEBAsIc FLIGHT oR LANDING LoAI)CARRYING STRUCTUREONLY.

.,2

L


—

II

~

-.

MIL-STD-1374PART II-TAB WING GROUP PAGENAME SECONDARY STRUCTURE MODELDATE DOORS, PANELS AND MISCELLANEOUS REPORT.

1 xx2 &34 WING FOLD5

8 DOORS & FRAMES9 -IANDING1011 -STORES1213 -MISSILE1415 -GUN1617 -AFn40.18 .

19 -FUEL202122 -ACCESS2324

.2526.2728 PANELS-NON STRUCTUUL

3132

35

3138394041424344 zLOVE4546 aALKWAYS, STEPS. & GRIPS 1

4748 FAIRING 6 FILLET (IDENTIFY).49

. .

50 I51 bTATIC DISCHARGERS52 ~TERIoR FINISH,53 kNTERIOR (INCL. LB.SEAL.)541..5556 kOTAL-5EC~E

~ DESCRIBE THE TYPE OF POWER USED FOR ACTUATION: HYDRAULIC - H, ELECTRICAL - E, PNEUMATIC - P.k*DEscRIBE~JoR DooRsMD P~Ls BY sy~oLS I.E.LocAT_foN- c.s.,op., I.P.,ETC.

3

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,.

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. .,

MIL-STD-1374PART II-TABNAM)?,DATE ,’

II lx AILERONS XX iP01LER5 x

;1 INBOARDI OUTBOAIUl[INBOARD 10UTBOARi)l I

4

s,,

-.

,2


I

I

I

IMIL-STD-1374PART II-TAB WING GROUP PAGENAME CONTROL SURFACES MODELDATE CONTD. REPORT

1 x xx T.E. FLAPS2 L.E.FLAF 3R SLAT INBO@D OUT~OARD3 SURFACE SUPPORTS SURFACE SUPPORTSI SURFACE SUPPORTS,45 SPARS67 COVER INCL. STIFFENERS89 RIBS10 -FLAP TRACK / HINGE SUPT11 -AIL. HINGE SUPPORT12 -OTHER1314 CORE * -(HONEYCOMBTYPE)15 -BONDING ADHESIVE1617 T.E.STRIPS1819 FABRIC & DOPE .

. 2021 TABS222J JOINT. SPLICES. FASTENERS -24?5 92627?829 BALANCE WSIGHTS & SDPPORTS3031 AERO.SEAL323334 CONTROL HORNS353637 ACCESS DOORS 1 i3839 HINGES & PINS

, 40 EXTERIOR FINISH4142434445 SUPPORTS - HINGES46 - BRACKETS47 - TRACKS

.48 - CARRIAGES49 - ROLLERS505525354 COLOMN TOTALS55 TOTALS OF SURFS AND SUPTS56 TOTAL-CONTROLSURFACES PAGES57 TOTAL-WINGGROUP - PG 2-4A

*INCLUDE FULL DEPTH TYPE CORE OhLY. CODE SANDWICH PANELS TO THE COVERS.


●

-.

-.

I

MIL-STD-1374PART II-TAB ROTOR GROUP PAGENAME BLADE ASSEMBLY MODELDATE REPORT

1234 SPAR - FRONT5 -INTERMEDIATE6 -REAR7 -JOINTS, SPLICES & FAST.891011 INTERSPAR - COVER & STIFF.

~ ~ ..13 -CORE14 -JOINTS. SPLICES & FAST.151617

~ LEADING EDGE “,19 -MEMBER

& - VER &~ ‘21 -RIBS22 -CORE23 J~~T.2425?627 TEATTTNC EDGF ,.

?R2930 -STIFFENERS31 -RIBS32 -CORE33 -JOINTS, SPLICES & FAST.3435363738 . . .

3940 TIPS - IF NOT INTEGRAL41 INTERNAL DUCT STRUCTURE4243 FAILURE DETECTION44 I

45 BAIANCE NEIGHTS - TIP I46 - LEADING EDGE47 I

,484950 ROOT END ATTACHMENT51 -FITTINGS . . .52 -FASTENERS53 EXTERIOR FINISH

. 5455 COLUMN TOTALS56 TOTAL - BLADE ASSEMBLY

I &

5


.,. .

MIL-STD-1374PART 11-TAl”NANEDATE

.

... .

,. ...

,.

ROTOR GROUP ..HUB.AND HINGE

..’,

.,, ..0PAGE “ ‘MODELREPORT

1 ‘1 1.XHUB XX”. HINGE & BLADE RETENTION x2 I IFLAPPINGILEiD-LAGl PITCH IBLD-FOLDI3 I, ! 1 14 HOUSING ,.5 GIMBAL RING !-6 YOKE I ,.7 UNIVRRSAL JOINTS .)8910 .

11 ‘1213 BEARINGS14 SEALS. SPACERS & RETAINERS . . .

15 BLADE GRIPS’16 BAU.NCE WEIGHTS 1.

17 STOPS18 LUB SYSTEM INCL. LBS.OIL

-19 FAIRI??GS& DUST COVERS.,

-20 GREASE2122

-23,.

24& ~.26 PINS .. . .27 LINKS28 DAMPERS OR RESTRAINERS29 DRAG BRACE’30 lTENsIONsmw AsssI.G3Ly3199 I I

--

...

;;34 SHAFTS

-35 PITCH ARMS36.37”38 BLADE FOLD NECH.39 .,

40 .-.41424344 -SUPPORTS’4546 VIBRATION ABSORBERS47 ,..484950 FAS_.51 ,.;52

.,,

54.55” COLUMN TOTALS I56 TOTAL - HUB & HINGE

b TOTAL-ROTORGROUP - PG 5($6 1*MAIN DISTRIBUTIONPOINT TO ACTUATING UNIT.

6

J%4


I

MIL-STD-1374PART II-TABNAMR

DATE

TAIL GROUPBAkIC STRUCTURE

.,

PAGEMODELREPORT

I1’1 IX HOR.STABILIZ. XX FINS x2 ICTR.SECT ]OUTR.PNL] VERTICALI DORSAL Ivlmwl 134 UPPER5 -SPAR CAPS & SPAN.STIFF.6 -COVER INCL.INTGRAL.STIFF.7 -JOINTS, SPLICES & FAST.8 -DooRs”& PAtiEL5(STRUCT) 4

1 19 I I I I I I I I

*INCLUDE FULL DEPTR TYPE COW. oNLy. CODE SANDWICH PANELS TO THE COVERS.

7


,.

.,

. .MIL-STD-1374’PARTII-TAB TAIL GROUP

.,

@

PAGENAME SECONDARY STRUCTURE MODELDATE DOORS, PANELS AND MISCELLANEOUS REPORT

1 X HOR.STABILIZ. XX2

FINS xCTR.SECT OUTR.PNL VERTICAL DORSAL VENTRAL

34 ** * AREA5 ,. LOC P SQ FT6 FOLD-STRUCTURE

7 -MECH. & CTLS.:

8 -POWER TRANS.9 -ACTUATOR & LOCK .10 -EF53RGENCY1112

..

13 DOORS & DOOR FRAMES14151617 -ACCESS18192021222324 ,2526 PANELS-NON STRUCTURAL?7 I 1\ 1 I

2829 I

30 I ●31

32 .,33-, , t34

35. 36

37 WALKWAYS. STEPS. & ~PS. 38 139 ~

b 40&l424344.45

,.

46 I47 STATIC DISCHARGERS48 I

, 49 EXTERIOR FINISH5051 INTERIOR (INCL. LB.SEAI,)5253 I54 I I I I I55 COLUMN TOTALS56 TOTALS HORIZ. STAR, FIN & DORSAL

TOTAL-SECONDARYSTRUCTURE

* DESCRIBE THE TYPE OF POWER USED FOR ACTUATION: HYDRAULIC - H, ELECTRICAL- E.**DEsc~IBE MAJOR DOORS AND PANELS BY SYMBOLS, I.E., LOCATION - C.S., O.P., I.P.;

8

PNEUFL4TIC- P.ETC.

‘e


●

I

=

..

.

MIL-STD-1374PART II-TAB TAIL GROUl”NAME

PAGECONTROL‘SURFACES MODEL

DATE REPORT

1 lx xx R-ELEV$TORS CE@’ER OUT40ARD

K

3 SURFACE SUPPORT~ SURFACE SUPPORTS SURFACE SUPPORTS,45 SPARS6I COVER INcI.,.STIFFENERS8910 RIBS11121314 CORE *-15 -BONDING ADHESIVE1617 T.E. STRIPS ..

1819 FABRIC & DOPE2021 TABS22.232425 TORQUE TUBES26-272829 BALANCE WEIQSM

.& SUPlQ13TS

,3031 AERO.SEAL3233.34 CONTROL HORNS353637 A~3839 A PTNS

40 EXTERIOR FINISH41 JOINTS, SPLICES, FASTENERS42434445 sUPPORTS - HINGES

.,

46 - BRACRETS47 ,.

48.4950

..,.

.51 . . .

52535455 cOLOMN TOTALS56 hOTAL FOR EAC

kINCLUDEFULL DEPTH CORE ONLY. CODE SANDWICH PhTELS TO TRE COVERS.

f“- .,.9

. .

-’P’

I

I


MIL-STD-1374PART XI-TAiNAME

TAIL GROUPROTOR GROUP

PAGEMODEL

10

●


.

,“. ..’,“, ). ,, ,.

,, ,,

,“ ,“,,.,, ,

MIL+iTD-1374’PART II-TAB BODY GROUPlJA14E BASIC STkUCTUiEDATE

.$., ,.

PAGE -MODELREPORT

$1 .’ x FUSELAGE OR HULL XX BOOMS2 SECTION

.3 . STATION4 BULKREADS & FRAMES * ,- ,c2 1 I6 .,78 ,,,

9,,!. ,...-f10

111? .

131415161718 ,1920212223 ‘24 MINOR FRAMES25 JOINTS, SPLICES & FAST. “

...

76 1;; COVER-UPPERBETWEEN LONGN. ‘28 -SIDE BETWEEN LONGERONS . r.

29 -LOWER BETWEEN LONGERONS-3031 ‘cOVER LONGL.STIFF.-UFPER32 “ -SIDE BETWEEN LONGERONS33 -LOWER BETWEEN LONGERONS3435 LONGERONS - UPPER36 -SIDE37 -LOWER38 .

39 LONGITUDINAL PARTITIONS **40 F s **41 KEEL **42 DOORS & PANELS (STRUCT)**4344 FLOORING-& SUPPORT **45 FIREWALL **46 PALLET RAILS & SUPPORT ** ~~ I47LR Iii50 ,.

51 ROTOR SUPPORT52 PYLON.5354 STEP ASSEMBLY

TOTALSS4 FOR FUSE OR HULL57 TOTAL - BASIC 4TRUCTURELIST ALL MAIN ANU WATERTIGHT BULKHEADS AND FR4NES’INDIVIDUALLY. MINOR FRAMES MAY BE CONBINED.IDENTIPY TAIL CARRY THRU.

**INCLUDE BASIC’FLIGHT OR LANDING Loffl CARRYING SjTRuc~R~ ()~y.

!“.!

11 \

‘v? ,“

I


MIL-STD-1374PART 11-TAE BODY.GROUP PAGENAME SECONDARY STRUCTURE MODELDATE REPORT

*IDENTIFY POUNDS OF BULLET OR BIRD PROTECTION INCLUDED.

,

12 ‘


●✎“

1..

I

1.

MIL-STD-1374PART II-TAB BODY GROUP PAGENAME SECONDARY STRUCTURE (CON’T) MODELDATE (DOORS,RAMYS, PANELS 6 MISC.) REPORT

1 I ** * x xx OPERATINGMRCHANISM x2“ LO P AREA STRUCT MECR 6 POWER ACTUATOR EMERG.3 SO FT CONTROLS TRANS. LOCKMECH45 DOORS & DOOR FRAMES6 -ALIGHT.GEAR789 -STORES1011 so~s1?13 -MISSILES,14 -GUNS15 -AMMo16 -FUEL.17.1819 I -ESCAPE20,2122 -COMPARTMENT

.24 -ENTRANCE25267778

29 E

31 -LIFE RAFT32 -CAMFJU33 , -ACCESS343536 RAl@s3738-39 FAlw&(&Qh -- TRU~) **4041 LADDERS (RETRACTABLE)4.2 I,43 WALXWAYS. STEPS, GRIPS44 PYLON I BOOM FOLD,4546 FAIRINGS474849505152 EXTERIOR FINISH,53 INTERIOR (INCL. LB.SEAL) I I 154 I I I I I55 COLUMN TOTALS56 TOTAL SEC. STRUCT. PG 12-13

●57 ,TOTAL-BODY GROUP - PG 11-13* DESCRIBE THE TYPE OF ‘POWERUSED FOR ACTUATION: HYDRAULIC - H, PNEUMATIC - P, ELECTRICAL- E, ETc.**DEscRIBEMAJOR DOORS AND PANELS BY ABBREVIATIONSOF THEIR LOCATIONS: FWD, AFT, B-BOOMS.

‘o 13


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.,.

,,,.,’

. . . ,-

MIL-$TD-1374PART II-TAB ALIGHTING GEAR GRoupNAM”

PAGE(INCLUDINGLAUNCH AND RECOVERY.GEAR) MODEL

DATE REPORT

/. I 1 1 I I I

& ~TOTALS FOR UN AND NOSE

5;5

PAGE TOTAL I*“’’fiPE”REFERS TO hWETHER THE GEAR IS TR.AILINGAM, conventional,ART1c~TzNG, ETC,**INPUT.”FT/LBSPER.BkiRE TIMES 1o-6.

IN ‘fHECASE OF AN AIRCRAFT WITH OUTRIGGERS,’ADD ANOTHER PAGE (14A).

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14

%


..

MIL-STD-1374PART ‘II-TAB ALIGHTING GEAR GROUP PAGENAME CONTROLS MODEL

DATE REPORT

I

I.53 .-. .,


I

MIL-STD-1374PART II-TAR ENGINE SECTION OR NACELLE GROUP PAGE”’” m

NAME . MODELDATE : RSPORT

16

,’

,,


MIL-STD-1374PART II-TAB AIR INDUCTION SYSTEM GROUP PAGENAME MODELDATE REPORT

.

.-.

.

I

I

1 STRUCTURE2

OPERATINGMECHANISM TOTALmm POWER ACTUATOR4

3EMERG

4CONTROLS TR4NS, LOCK.MECH~

5 INLET LIPS67 FIXED DUCT STRUCTURE8 FRAMEs9 COVERS

.11 ATTACHING ANGLES ETC.121314 RAMP STRUCTURE15 FIXED16 VARIARLE1718 BELLMOUTH19 -CONTROLS20.21 PLUG~ ~23 PLUG C~S24752627 SPIKE CONTROLS2829.30 ENGINE DOMES3132 NASTER CONTROLS3334 DOORS

37 G3839&o414243444546 MISC.47 WATER INJECTION48 HEAT PROTECTION49 SCREENS50 PARTIAL SEPARATORS5152 EXTERIOR FINISH,53 INTERIOR FINISH54.55.56 I57 TOTAL-AIR INDUCTION SYSI TEM GROUP,

17

“55 ,.


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.-,, “,, ,’ ,- ., . ..-. . ...’

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MIL-STD-1374 PAitTII-TAR PROPULSION GROUP . .,

NAMEPAGEMODEL

~ ,~’

DATE REPORT

‘e

,..

I 1 I*“ISOLATENA.JORCONTRACTORFURNISHED AREAS OF INSTALI.ATIONE.G. NOZZLES, THRUST REVERSERS,

J

INFRA-RED,NOISE SUPPRESSORS,ETC.**propellerG~R Box MD ~TENSION s~T oNLy.

18.,

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.,

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,.MIL-ST*1374 PART 11-TAE

.,,.PROPULSION GROUP PAGE’

.NAME , LUBRICATING & FUEL SYSTEM MODEL

57.1 Ik INDICATE TYPE AS TO SELF SEAL, BLADDER, ALUMINUM, ETC. WITH TOTALS SHOWN FOR PROTECTEDAND

J

UNPROTECTEDTANKS.**lDE~IFy As p~ssIfRE (p) OR Gravity’. ..

. . .

19


MIL-STD-1374PART II-T* ‘ PROPULSION GROUP PAGE

w, DRIVE SYSTEM - ,PONERTRANSMISSION MODEL :

DATE TO ROTORS, FANS,‘ORPROPS RJ3PORT

-rIL [ u.

7 SE.-., ...-8 I GEARS - DRa - np.

.,

“18t

19?021.

-?’+ Pms2’475 s26 =BLOWER SYSTEM27 -PLUMBING‘28 -OIL2930313233 ROTOR BRAXE34.3536.37 FREE NHEELING DEVICE38 DEPRASING UNIT39.40.’4142434445 SUPPORTS46 -GEAR BOXES47 LUBRICATING SYSTRM48 ROTOR BRAKE&q505152 DRIP PAN53 EXTERIOR FINISH5455 COLUMN TOTALS56 PAGE TOTAL - DRIVE SYSTEM. IC7 i

1 J, 1 I J

*INSERT A G~R Box IDE~TIFIcATIoN IN THE c(jJ.,mHEADINGS, ‘ANDDO LIKEWISE ON,A SUPPLEMENTALPAGE 20A IF IT IS REQUIRED FOR AN Auxiliary DRIVE SYSTEM.

.

20


O,,

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,,

MIL-STD-1374PART II-TAB PROPULSION GROUP

NAUS ,. DRIVE SYSTEM - POI@TRAIiSMISSION

DATE TO ROTORS, FANS OR PROPSm,..,”.

.PAGE

I

MODEL I

REPORTLuril ,

1 x TIL4.NSMISSIONDRIVE7 *t~oM; ,

X ROTOR JET,- ENGINE BOX BOX BOX I3 *TO “.

SHAFT DRIVEBOX I BOX I BOX BOX

L , 1

4243

~46h7u

$n51525354 COLUMNTOTALS55 TOTALFORTl+ANSMI~ I56

klNSERTA GEARBOXIDENTIFICATIONINTHECOLUMNHEADINGS,ANDDO LIKEWISEONA SUPPLEMENTALPAGE 21A IF IT IS REQUIRED FOR AN AUXILIARY DRIVE SYSTEN.

21

3? ,,,.’


.,. .,.,

MIL-STD-1374PART II-TAR ‘ ~IGHT coNT~6Ls GRQG’”NAM21

~AGE. ,

COCHPIT & AUTO FLIGHT CONTROLSDATE

MODEL . .,.’,.- REPORT..

,’4,

. -.,-

*FROM MAIN DISTRIBUTIONPOINTS TO ACTUATING UNITS.

.’z~.,

I

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MIL-iTD-1374P+lT II-TAB FLIGHT CONTROLS GROUP PAGENAME ,, SYSTEM CONTROEDATE

MODELFIXED WING SYSTEMS REPORT

%1 x LATERAL * X LONGI- DIREC- WING2 TUDINAL*ITIONAL* POSI-3 TYPE* TIONING4 .,5 MECHANICALOPER.MECH.6 CONTROLS7 TENSIONREGULATORS8 ACTUATORS910 ELECTRICALOPER.MECH.11’ CONTROLS12 CIRCUITRY.**13 OPEWTING MOTORS14 MECHANISM151617 HYDRAULICOPER.MRCH.18 CONTROLS,19 PLUMBING**20 ACCUMULATORS I21 ACTUATORS22 MECHANISM23 **,242526 H.27 c~?8 PLUMBINGOR DUCTING**29 BOTTLES(AIR).30 ACTUATORSOR NOZZLES.31 MECHANISM323334 lARTIFrc1fiFEEL35 BOB WEIGHT.36.37 DAMPING3839 I404142 MECHANICALOPER.MKH.43 ELECTRICALOPER.MECH. ...!$4 HYDRAULICOPER.MSCH.45 ., I46 TRIM CONTROLSUPPORTS I

I,47 1. I48 SUPPORTS: GUIDESJL2C.49 ILING

.

50 -1

51 BODY

535455 COLUFOlTOTALS 1 i56 TOTAL - SYSTEMS CONTROL PAGE -

, )* IDENTIFY THE TYPE OF CONTROL SURFACE - AILERON, FLAIIERON,.ETC. AND TYPE OF POWER - POWERED (P)OR BOOST (B).

**FROM MAIN DISTRIBUTIONPOINTS TO ACTUATING UiITS.,.

J.

23

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.. . .

,,. .:.

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MIL-STD-1374PART II-TAB..

FLIGHT CONTROLS GROUFNAME SYSTEM CONTROLSDATE FIXED WING SYSTEMS- CONT.

i“

,’.

* IDENTIFY THE TYPE OF CONTROL SURFACE - SLOTTED, FOWLER, KRUEGER, ETC..

** FRoM.THE ~lN DistributionpoINTs To THE AcTuATING uNITs:., ..... .-.

***lNcLIJDEBOUNDARY LAYER OF REACTION CONTROLS UNDER.THIS HE@ING. ,’ ,-““<

,,24

,,

( L&L ‘“

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,,,.


e

I

MIL-STD-1374PART II-TAB FLIGHT kONTROLs GROUPNA??

PAGESYSTEMS CONTROLS MODEL

DATE ROTARY WING SYSTEMS REPORT,.

45 HYDRAULIC OPER. MECH. I I I 1 I46 TRIM CONTROL SUPWS I

.47 I48 SUPPORTS. GUIDES. ETC.49 WING50 L51 .- ODY52535455 COLUMN TOTALS56 TOTAL - SYSTEMS CONTROL PAGE

* INDICATE TYPE OF POWER - (P) FOR PoWERED OR (B) FOR BOOST.”**FROM THE MAIN DISTRIBUTIONPOINTS TO THE ACTUATING UNITS.

.,

25

b23


.,. -.,

I

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I

!

MIL-STD-1374PART I - TAB FLIGHT CONTROL GROUP PAGENAME SYSTEMS CONTROLS TRANSITION MODELDATE V/STOL SYSTEM RBPORT

‘o’

1 ROTORIFAN NACELLE2 MIXING lATTITUDEIA~E 1 I I3 ~E* I 1“L 1. 1 I

4 5 MECHANICAL OPER. MECH.!

6 CONTROLS7 TENSION REGULATORS8 ACTUATORS910 ELECTRICAL OPER. MRCH.11 CONTROLS ... .

12 CIRCUITRY **13 OPERATING.140TORS14 MECHANISM151617 HYDRAULIC OPER. MECH.18 CONTROLS19 PLUMBING **20 ACCUMULATORS21 ACTUATORS .

22 MECHANISM23 ID **

H26 PNEUMATICS OPER. MECH.27 CONTROLS28 PLUMBING OR DUCTING **- -- . . .29. BOTTLES (AIR) ‘30 ACTUATORS OR NOZZLE-. , ,.

31 MXCHANISM323334 ARTIFICIAL FEEL35 BOB WEIGHT363738 DAMPING?94041 TRIM CONTROLS ,,42 MECHANICAL OPER. MECH:43 ELECTRICALOPER. MECH.44 HYDRAULIC OPER. MECH.4546 TRIM CONTROL SUPPORTS ,“

4748 SUPPORTS. GUIDES. ETC.49 NG ,.

50 -TAIL I51 -BODY52 . I53 “, I5455 COLiMN TOTALS

I I I I I ,,56 TOTAL - SYSTEMS CONTROLS TRANSITION

TOTAL - FLIGHT CONTROLS GROUP - PG 22-26* .l~IcATE TypE oF pQ~R . (p) FOR pQ~RIJD OR (B) FOR BQosT,**FRoM ~E WIN DistributionpQINTs To ~E Ac~ATING UNITSc

26

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I

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MIL-STD-1374PART II - TAE AUXILIARY POWER PLANT GROUP PAGENAME MODELDATE REPORT

1234 ENGINE OR POWER UNIT MODEL5 ENGINE6 ENGINE SUPPORTS

8 AIR INDUCTION SYSTEM910 EXHAUST SYSTEM

r 1112 HYDRAULIC SYSTEM-PLUMBING13 -FLUID14.1516 COOLING SYSTEM17181920 LUBRICATING SYSTEM2122 PLUMBING23 OIL242526 FUEL SYSTEM27 TANKS (VOL. GALS.28293031 CONTROLS32333435 STARTING SYSTEM36373839

4142 FIRE BARRIER4344 FIRE EXTINGUISHINGSYSTEM45 ,.

46 INSTRUMENTS4748 ELECTRICAL SYSTEM49505152535455 COLUMh1 TOTALS

57

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I

MIL-STD-1374PART II - TAR INSTRUMENT GROUP PAGE

NAME MODEL

DATE REPORT

1 FUNCTIONAL GROUP, ITEMS X INDICATOR X TRANSMIT & AMPL X INSTALL9

2 ANO QUANTITT X GFE CFE x GFE x3

CFE

4‘5678 -,

910

.11,121314151617

.1819 I20212223

-24256

:728

,2930313233

-343536.

~ .,

.38?940

-41424344

,45.4647484950 \

5152

/ 5354 I I I I55 COLUMN TOTALS ,. I56 TOTAL - PAGE

, 57 TOTAL - ~P*LIST ITEMS BY FUNCTIONALGRoUPS (FLIGHT,ENGINE, AND MISC.) LIST SUB-GROUPSBY CREW STATIONS.ADD SUPPLEYIENTARYPAGES 28A IF THEY ARE NECESSARY. CODE NAVIGATIONALEQUIPMENT TO FURNISHINGSPAGE 35.

“o

.

0“

-.

28

(4!(.(


MIL-STD-1374PART II - TAB HYDRAULIC AND PNEUMATIC GROUPNAMsDATE

PAGEMODELREPORT

9

1 x HYDRAULIC * xx2

PNEUMATIC * XPLT. CON I IUTILITY !EMERG, UTILITY IMERG.

3 SYSTEM PRESSURE (PSI) I I1 I I45 PUMPS & COMPSRS. OTT. MODEL6

, 7 , t -1

9101112 RR40TE PUMP DRIVES13 QTY. CAP. EA.14 RESERVOIRS.. I 1

T

I

FOR EACH MODULE AND IDENTIPY IT.

29


MIL-STD-1374PART’11 - TAB ELECTRICAL GROUP *NAMEDATE

PAGEMODELRXPORT

1 AC(HZ )(VOLTS ) DC(AMP) (VOLTS )23 POWER SUPPLY KVA AMP QTY4 GENERATOR-MAIN5 -AUK.6 -EMERG.7 coNsTAwT SPEED DRIVE

...

89 REMOTE GENERATOR DRIVES

’10 COOLING-~N. & GEN. DRIVE(AN )(NO. )(An )

12 BATTERY CONTAINER & SUPT,:S

1314 PWR CONVERSIONKVA AMP QTY15 INVERT. (DC-AC)16 cowvRT. (Ac-Dc)17 TRANSFORMER18 TRANS. RECTIFR.19 FREQNC. CONVRT.202122 PWR. DISTRIBUTION& CNTLS.23 GENERATOR CONTROL BOXES24 CUTOUTS & VOLT. REGULATORS25 AMMETERS k VOLTMETERS26 SWITCHRS. RHEO.. SW. PANELS27 CIRCUIT B~ & FUSES

;98

RRCEPT. & CONNECTORPLUGS30 RELAYS31 WIRING32 CONDUIT3334 LIGHTS & SIGNAL DEVICES35 LIGHTS - INTERIOR36 - EXTERIOR37 - LDG.-TAXI (INCL.MECR.)38

SIGNAL DEVICES - LIGHTS

4243 EOUIPMENT SUPPORTS44 - WING45 - TAIL46 - BODY47 - NACELLE4849 FURNISHES POWER FOR-(ITEMS)5051 -525354

.56 ;$;() - PAGE7 - ELECTRICALGROUP

*INCLUDES THE SYSTEM FROM THE SOURCES OF POWER TO THE MAIN DISTRIBUTIONPOINTS.

30


e MIL-STD-1374PART 11 - TAE AVIONICS GROUP PAGE

‘?

.Z

I

NAM3 MODELDATE REPORT

1 “EQUIPMENTCOMPONENTSAND X EQUIPMENT XK INSTALLATION X2 PART NOS. OR IDENTIFICATION GFE CFR GFE CFE3 LIST BY FUNCTIONAL GROUP *

“4567 ,’

“89101112 -1314151617181920212273

;226272829303132333435363738394041.42434445

k 4647bR TABLES

.,

49 RACKS. SHELVES, & SUPTS.50 LOCKERS51 PODS (IF NOT U.L.)52 CRASH DATA RECORDER535455 COLUNN TOTALS I..

II 561 TOTAL - PAGE i571 TOTAL - AVIONICS GROUP PG 31- 1

*LIST THE CONTINENTS (INCLUDING~TENNAE, SWITCHES, RELAYS, FILTERS, ETC.) FROM THE MAIN DISTRI-BUTION POINTS TO THE UNIT OPERATED BY A FUNCTIONALGROUP (E.G. COMMUNICATIONS,VHF SRARCH, NAV-IGATION. INTERCOMMUNICATIONS,ETC.). DO NoT INCLUDE NOsE ~o~s. ADD supplementarypAGEs 31AIF IT Ii NECESSARY;

.-.

L(2

31


I

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MIL-STD-1374PART II - TAB,,

ARMAMENT GROUP PAGE “NAME (GUNS, TURRETS, ARMOR, MODELDATE & SUBMARINE DETRCT.) REPORT ,,

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e

.

* DESCRIPTIVELOCATION E.G. 20NM GUNS (2) NOSE, TURRET-NOSE,SONOBUOYS (SSQ-15),AFT FUSELAGE,S.U.S. (MK-50),ETC.

** LIsT componentsBY pAc~GED GRoups (TURRETsTRuCTuRE,Accessories,cIRcuITRY, ETc”.). ADD

SUPPLEMENTARYPAGES 32A IF IT IS NECESSARY.***oTHER THAN IT~ ~2-16.

32,.

yo,


● MIL-STD-1374PART 11 - ‘TAE ARMAMENT GROUPNAME (EXPENDABLEwEApON provisions)DATE

PAGEMODELREPORT

a,.

1 I2 LOCATION *3&56 EXPENDABLEWEAPONS7 CONTROLS & PROVISIONS8 -CONTROLS (SELECT)910 -RELEASE OR LAUNCH111213 -JETTISON SYSTEN1415 -FUSING1617 -HEATING18192021222324 IINSTALLATION**25 ] -RACKS (TYPE NO. )2627

29331 I32 -PYLONS3334 -1.AUNCHERS353637 I

~ 38394041 ORTS424344 -RAILS OR TRACKS4546 -PYLONS.-

* pRovIDE A DescriptiveLocATIoN - E.G. BOMBS - FUSELAGE INTERNAL (MAX. SIX FIR-83),MISslLEs -FUSELAGE EXTERNAL (MAX. FG’JRAIM-54A), MISSILES - WING EXTERNAL (MAX. TWO AIM-54A).

o**IF NOT SPECIFIEII As usEF~ LOAD. ADD A SUFFLEMENTARYPAGE 33A IF IT IS NECESSARY.

33


,.

,-

1 >

,MIL-STD-1374’PART II - TAB FURNISHINGSAND EQUIPMENT GROUiNAME ACCOMMODATIONSFOR PERSONNELDATE

PAGEMODELREPORT

1 x“ .SRATS2

xx xx xPILOT COPILOT * * MISC. OXYGEN

3 ACCOM. SYSTEN4 SEATS (MODEL )5 SEAT STRUCTURR6 HEADREST7 CUSHIONS ***8

.,,,.

9 BELT ,,

10 HARNEss.11 INERTIA RREL1213 CATAPULT14 ROCXET15 DROGUE SYSTRN16 STABILIZATIONSYSTEM I.. 1 1 f

,. a

:.

* IF THERE ARE MORE THAN 5 CREWMEMBERS,AND ADDITIONAL SPACE IS REQUIRED, ADD ADDITIONALPAGE 34A.** IF THEY ARE NoT spEcIFIEDAs usEFIJ’LLO#J)oR spEcIAL EQuIpM~T.***IF THEy ARE LocATED IN TRE sEAT AND ARE.NOT sPECIFIEDAS USEFUL LOAD..

34

m.,,,,


0/’

I

MIL-STD-1374PART II - TAB FURNISHINGSAND EQUIPMENT GROUP PAGENAlm MISC. EQUIPMENT,AND FURNISHINGS MODELDATE REPORT

12

Misc. FURNI-EQUIP.

3SHINGS

4 MISCELLANEOUSEQUIPMENT5 PORTABLE PLATFORM/LADDER671 DATA CASES & HOLDERS9 I iu 1

9 MANUALS *10 BALANCE COMPUTER & SUPT.11 WRIGHING DEVICE-BUILT-IN12 TOOL LOCKBRS1314 RAIN REMOVAL - WIPERS15 - FORCED AIR16 - CHEMICAL17 WINDSHIELD WASHEFLS1819 RELEASE MECH.-TARGETTOW2021 BILGE SYSTEM2223 Rs

~ AUXI I~2526 COCKPIT DISPLAY-CONSOLES?7 -INSTRUMENTPANELS7!7 -OVERHEAD PANELS29 -SIDE CONSOLES30 -CENTER CONTROL STAND3132 NAVIGATION - LOCKERS33 -TABLES34 -SHELVES35 -STOWAGE3637 -CHARTS 6 MAPS I3839ho4142L344 FURNISHINGS45 -FLOOR COVERING46 -ACCOUSTIC INS~ ION4748 -TRIM49 -CURTAINS & SCRRENS50 -CRASH PADDING5152 -partitions (NON-STRUCT)53 -VIBRATION ABSORBERS5455 COLUMN TOTALS I56 TOTAL PAGE - MISC. EQUIP. & FURNISHINGS57

*IF THN ARE NOT SPECIFIEDAS SPECIAL EQUIPMENT, INCLUDE THEM UNDER THIS ITEM.

a 35

’73


I

I

l!lL-STD-1374PART II - TAENAMEDATE

541 I I i I I

55 I COLUMNTOTALS56! TOTAL PAGE - RMERGENCY EQUIPMENT

,

‘i-~ - FURNISHINGS 6 EOUIPMENT GROUP

*IF IT IS NOT SPECIFIEDAS USEFUL LOAD OR SPECIAL EQUIPMENT, INCLUDE IT UNDER TRIS HEADING.

36


t

● NIL-STD-1374”PART II - TAB AIR CONDITIONINGGROUP PAGENAMX MODELDATE REPORT

‘o

/:

1 COCXPIT CABIN2

ELECTRN. WEAPON COMNON~ SYSTEM SYSTEM BAY SYS. YSTEM

. I>4 FUNCTIONS PERFORMED *5 HEATERS(BTU )(NO. )**

67 COMPRESSORS (NO. )8 HEAT EXCHANGERS (NO. )**

I I f16I. TURBINES (NO. ))

11 FANS (NO. ) I I1? I MOTOR~ (N(l )

t --, -------.- 1

El=1$

14 VAPOR15 COMI16 CONI17 VITAt

ICYCLE SYSTEM‘RXSSORS (NO. ))ENSERS (NO.

., .v.-u’ORATORS (NO. )1819 PLUMBING20

IPLUID(TYPE )(oTY )

m.

?61 w~ I I27 PRESSURE REGULATORS I I I I,0 I I !

29 I30 SCOOPS31 DUCTING(INCL.INSULATION) I2? I

331 I I I I I I3435 I I I I i I

t:; klG.DJG I I I I I I I I

IN I40 CONTROLS41 MANUAL42 ELECTRICAL43 HYDRAULIC (FLUID LBS)44 PNEUMATICL5 I I

I L . . r I46 / I47 DEFOG SYSTEM48 SUPPORTS & BRACXETS49 WING50 TAIL51 BODY52 NACELLE5354 PRESSURIZATIONSEALING55 ~ COL TOTAL .

AETOTAL ~%R cONDITTONINGGROUP

* INDICATE FUNCTION PERFORMID: VENTILATION- V, HEATING - H, COOLING - C, PRESSURIZATION- P.**IF THEy Am NoT spEcIFIEDAs spEcIAL EQIJIPmNT, INCLUDE THEN UNDER THIS HEADING.

37


MIL-STD-1374PART 11 - T~- ANTI-ICING GROUP PAGE “e,NAME MODEL

DATE REPORT

1.1’ t WING TAIL AIR ROTOR’OR CANOPY& FUEL2 I IINDUCTN.IPROPELL. .’. I [ I I I I

54 I I I I I/ 55 COLUMN TOTALI 56 TOTAL PAGE, 57I TOTAL - ANTI-ICING GROUP

* IF NOT SPECIFIEDAS SPECIAL EQUIPMENT, INCLUDE THEM UNDER THE GIVEN HEADING.**FRoM THE MAIN D1sTRIBUTIONPOINTS TO THE ACTUA’L’ING.UNIT.

.

/,,

38

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*

a

MIL-STD-1374PART 11 - TAE PHOTOGRAPHICGROUP PAGENAME MODEL

DATE REPORT

-11 PHOTO INSTALLATION?.345 EQUIPNENT ITEM * MODEL67 CAMERAS8

OPTICAL VIEWFINDERS

11121314151617-1819202122 MOUNTS 6 ADAPTERS

2425262728 INSXALL4TIONPROVIS1ONS?9

-+1 , 1

*IF NOT SPECIFIEDAS USEFUL LOAD OR SPECIAL EQUIPMENT, INCLUDE IT UNDER THE GIVEN HEADINGS.

39


I

MIL-STD-1374PART II - TAB LOAD AND HANDLING GROUP * PAGE

NAME MODEL

DATE REPORT ‘,

*

1 ,. AIRCRAFT LOAD23

BALJAST HANDLING HANDLING

456 HOISTING SLING78 FITTINGS9 TIE DOWN10 JACKING1112 TOWING13 LEVELING ,,

14 HOISTING1516 ANCHORAGE171819 BLADE STOWAGE RACKS20 TAIL POST JACK2122

23 TIE DOWN FITTINGS242526 PALLET RAILS & SUPPORTS

28 . .

29 RAMPs - CARGO LOAOING3031 DROP LINE INSTALLATION3233 AERIAL DELIVERY SYSTEM

,“.

a:34 I35 BOOM ASSY. (HOIST)

..

. 36 .

37 HOIST. 3839

T i,414243 BALLAST PROVISIONS444546

s.

47484950 GEAR STOWAGE PROVISION5152535455 COW TOTAL56 TOT~E .,.57 TOTAL - LOAD & HANDLING GROUP

DO NOT INcL~E ITEMS SPECIFIEDAS SPECIAL EQUIPMENT OR USEFUL.LOAD:-

40

.


,..

●✎✎

MIL-STD-1374PART II - TABNAMEDATE

SPECIAL EQUIPMENT *NOT INCLUDED IN WEIGHT EMPTT

~AGEMODELREPORT

1234 TARGET TOWING EQUIPMENT5 HOIST NOT BUILT IN - CARGO6 - ENGINE7 - WEAPONS89 SPECIAL LOADING PLATFORMS10 ENGINE MAINT. PLAT. (IF NOT BU::LT IN)1112 H~G1314 LIFE RAFTS-TYPE OTT1516 COVERS COCKPIT17 AIR INDUCTION1819,20 TOOL KITS,212223 ANTI-ICING BOOTS - WING24 TAIL252627 ANTI-ICING FLUID282930 FIR? EXTINGUISHERBOTTLE 6 VALTm31 ENGINE (SIZE OTT )~3233 PORTABLE (SIZE OTT )34353637 FUEL TANKS38 TYPE OTY. LOC. CAP.394041,424344 ASSIST TAKE OFF INSTAL.45 BOTTLES - SIZE QTY464748 TROOP SEATS49 PO TABLR E LITTERS-50515 PORTABLE LAUDERS5:54,555657

*INCLUDE oN THIS PAGE ONLY THOSE ITEMS WUICH ARE AIRBORNE EQUIPMENTNOT SPECIFIED AS UEIGHTEMPTY OR NORMAL USEFUL LOAD.

41


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NIL-STD-1374 APPENDIX S TO PART 11NAME STRUCTURAL INCREMENTSFORDATE DESIGN FEATURES *

PAGEMODELREPORT

1 WING ROTOR TAIL FUSELAGE NACELLE ALIGH.GR2 JOINTS - FOLDING3 - VARIABLE SWEE4 - C.S. TO FUSELAGE5 - C.S. TO O.P.6 - PYLON7

“8 (STA.- ) FuSELAGE BREAK9

TS-ALIGHT GR. - MAIN

1?13 -WEAPONS BAY14 -SONOBUOY BAY15 -HOIST16 -CARGO DOORS17 -RAm1819 REMOVAELE PANELS - STR. **2021 TRANSPORTABILITY2223 VARIABLE INCIDENCE2425 FUSELAGE CARRY THRU FOR26 DISCONTINUOUSWING97 I I

,.

*.

L,

28 HORIZ. TAIL cARRY THRU FOR29 DISCONTINUOUSTAIL3031 FLAPS“- L.E.32 - T.E.33 SPOILERS34 SLATS35363738 ~AR - MAIN?Q404142 PROPULSION - MAIN

-43 - LIFT444546 LIFT ENGINE ~ LOUVERS

4869 F~L50 - ~REMOVABLE51 -DROPPABLE52 -PRESSURIZATION53545556 I57 I 1

* THE WEIGHTS FOR THE INCREMENTSARE ALREADY INCLUDEDWITHIN THE STRUCTURALGROUPS.ADD SUPPLEMENTARYPAGES 42A IF IT IS NECESSARY.

**IDENTIFyTHE pANELs.

I 42

IL


I

NIL-STD-1374PART II - TAB APPENDIX I TO PART II PAGE

NAME STRUCTURALINCREMENTSFOR MODEL

DATE DESIGN FEATURES * REPORT/~FF P~ NOTES)

1 WING ROTOR TAIL FUSELAGE NACELLE ALIGH. GR2 CATAPULTING- STRUCTURE3 - FITTINGS45 ARRESTING - STRUCTURE6 - FITTINGS78 BARRIER CRASH9 SEAT EJECTIONS10

~ ARMAlm3~12 s13 - STRUCT. ARMOR14 - FIXED GUNS15 - TURRETS1617 SONOBUOYS1819 ANTI-ICING - BOOT20 - THERMAL2122 DITCHING23 FLOTATION2425 ATO26

& CARGO - TIEDOWN _ . . . —28~ - HOIS DR SL NGI29 t RAMT I30 - DOOR31 SIDE WILS I

*THE mIGHTS FOR THE INCUNTS ARE ALMADY INCLUDED WI~xN THE STRUcTuitALcmozms.ADD SUPPLEMENTARYPAGES 42A IF IT IS NECESSARY.

43


II

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MIL-STD-1374PART II - TAB APPENIYIx

NAME STRUCTURALDATE

I ‘TOPART IIINCREMENTSFOR

DESIGN FEATURES

PAGEMODELREPORT

(CONTINUED)—

;

.

eJ* I ( I I

35363738~~

.40414243444546 I474849 !

50.5i

53 ,’54 ,.

55 I5657

44

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I

MIL-STD-1374PART II - ‘ME APPENMX 11 TO PART II PAGENAME DESIGN CRITERIA DATA MODELDATE FOR WEIGHT ESTIUhTIONAND ANALYSIS REPORT

45


,*:I

I

PART III

,1

●1’

MIL-STD-1374A

WEIGHT AND BALANCE STATUS


NEIGHT AND BALANCE STATUS

IMODELENGINECOWTR4CTNUMBER

D.7E

I ISSUE

1 ‘WING GROUP

? BASIC STRUCT - CENTER SECTION3 - 1NTM3 PAXEL4 - OUTER PANEL5 - GLOVE6 SECOND STRUCT (INCL FoLD)7 AILERONS INCL BAL wc8 FLAPS - TRAILING EWE9 - LEADING EDGE10 SLATS

m ~POILERS

.,4 ROTOR GROUP

h ~ LADE ASSEMBLY

& ~cL FOLD>,..

8 I19 I TAIL GROUP,“ ...~c & s~m~D s’r~”~T-ST*.. , .“. .

21 I22 VENTRAL

-w% ELEVATOR - lNLL . BAL24 RUDDERS - lNCL BAL UT

26 - HUB & HINGE..

36 \

13. !~T ‘TIN7 G G GEAR GROUF

k DRIVE

—

,LhTION

m

:TEDTED

—

m& FLIGHT CONTROLS GROUP82 COCSPIT CTLS (INcL AFcs)83 SYSTEMS CONTROLS

MIL-sTD-1374 PART 111 AIRCRAFT PACE ~

REVISEDGUAR

OR

U S4FPROPOSED

SPECSIJM

cy&M;s

I I TOTC.LClggtt; L4ST CHbNGC BETWEENcON -

0.S1S FORST4TUS

TRACTOIILAST a CURRENTSTATIJSREPORU CUQRENTOC.TA

RE$PUN-SIBILITy SLIM

CHANGES COLUMNS T ala!-

a VbRIAL 4@5 04T ED ,g~ti - ~oN-% % %TOT4L

TlONS ~N ~ ESIBILITYTR&~ToR ~

cA ;15SllE CHdNGES REspON- ~

COLUMN 6 SLIM,~m;; ~ c:~u}:s ;Pj:j: “’’’’”

L T

CH4NGcS c

2 3 4 5 6 7 B 9 10 II 12

I

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Lz.2 ~ — I I .173 GROSS WEIGHT - ~ ,..Dow174 GROSS WSIGHT - WHEELS UP I I I175 MOST FIQ - WLS UP - DOW

a MOST AFT - U31EELSUP - DOW

... .

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wEIGHT AND BbLANCE STATUS MIL-STD-1374 PART 111 AIRCRAPT PACE 2—

[ ------


WEIGHT AND BALANCE STATUS MIL-STD-1374 PART 111 AIRCRAFT PAGE &

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●✍✎

STANDARDIZATION DOCUMENT IMPROVEMENT PROPOSAL I OMB ApprovalNo. 22-R255

INSTRUCTIONS: The purpose of this form ia to solicit beneficial comments which will heIp achieve procure-ment of sui~able products at reasonable cost and minimum delay, or will otherwise enhance use of the documen!DoD contractors, government activities, or manufacturers/vendors who are prospective suppliers of the productare invited to submit comments to the government. Fold on lines on reverse side, stapIe in comer, and send topreparing activity. Comments submitted on this form do not constitute or imply authorrzaticn to waive anyportion of the referenced document(s) or to amend contractual requirements. Attach any pertinent data whichmay be of use in improving this document. If there are additional pipers, attach to form and place both in anenvelope addressed to preparing activity.

}OCUMENT IDENTIFIER AND TITLE MIL-STD-1S7GA WEIGHT AND BALANCE DATA REPORTING

~omfsFOR AIRCRAFT (INcLuDING ROTORCRAFT)lAMEOF oRGANIZATION AND ADDRESS CONTRACT NUMBER

Mb.TERIAL PROCURED UNOER A., .-

~qOIREcT GOVERNMENT CONTSACT ~sLIBcow:r!Ac

HAS ANY PART OF TtiE DOCUMENT CREATED PROBLEMSOR REQUIRED INTERPRETATIONIN PROCUREMENT.—

uSE?

A. GIVE PARAGRApH NtiMeER AND WORDING.

S. RECOMMENDATIONS FOR CORRECT’!NG +HE DEFICIENCIES

.,.

COMMENTSON ANY DOCUMENT Requirement CONSIDERED TOO RIGIO

,.,.

IS THE DOCUMENT RESTRICTIVE?

~ YES O NO (//’$ yes,’, hiwh.mw.sy?)

REMARKS

JBMITTED BY (Printed or typed name and addrees - Optional) TELEPHONE NO.

DATE

------ ..---

DD ,:~;,l 426 S/N 0102 -o14-IB02REPLACES EDITION OF I JAN 66 WHICH MAY BE USEO

*U.S. GOVERNMENT PRINTING OFFICE: 1977–703-122/6435

~. J.. I


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