Downloaded from http://www.everyspec.com
MIL-STD-1374A
30
1977
September
SUPERSEDING
MIL-STD-1374
31 March 1972
,.
,.
.“
.
,...
MILITARY
;
,/
.. .
.
.
,-
sT.AN~’~RD’”’
‘
.,
.“
...”.
..
-.
.,,
.;
.
WEIGHT
DATA
,.
‘AND BALANCE
REPORTING
FORMS
FOR AIRCRAFT
(INCLUDING
ROTORCRAFT)
-.1
I
I
. ,,
,.-,, ~
I
.-
*
I
.
I
FSC 1500
I
Downloaded from http://www.everyspec.com
—
,,
,:,,,MIL-STD>1374A
.,
., ..
DEPARTMENT’OF DEFENSE
Washington, D.C.
..-
20301
,.
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.
,.
?
-.
.%
2.
Recommended corrections, additions; or deletions shopldbe
addressed to the Commander, Naval Air Systems Command, Evaluation Division
D(C. 20360.
(Code:
AIR-506),
Department
of the Navy,
“, *.
,.
,,.
*
.-
.,
. .
x
94
,.
,.
...-
Downloaded from http://www.everyspec.com
MIL-STD-1374A
FOREWORD
This standard
and Weight
is based on the coordinated
efforts
Engineers of the Aerospace
Industry.
of the Military
/
Services
This standard supersedes both MIL-STD-254 Weight and Balance Data Reporting
Forms ’for Aircraft and MIL-STD-451 ‘Weight and Balance Reporting Forms
for Rotorcraft by combining the common features of both standards in
addition to providing for the.features ‘unique”to each.
The format is adaptable to either manual or machine method preparation.
~
..
.
.. .
,..
. . . . ........
.,’-,
‘e
b
I
I
. .
I
iii
I
Downloaded from http://www.everyspec.com
,,’
,,
“
Paragraph
1..
1.1
1.’2
,1.:3.2.
Scope.. “
., ;,1
----- .. . ,--. ,.,
Concepts
“;
.1
Principles
1’
.-...,... .,.
.,”
‘:”2
~
REFERENCED DOCU~NTS
~~
‘-’:,
“.’,,
,,.
2“
Issues of documents’
“
,. 2.i
.,.
.
DEFINITIONS
“3
‘
..~...3.
“’”.3.
I’
Weight defin”it-ion “
,~<
:
: - - ‘“3,.,
4.”
‘GENERAL REQUIREMENTS
‘
= “.”: :“= _~,,. ‘3
3
General instruct~ons, .,
‘.
-.: j~,:- .:.’:
461
~
4,,.2
Design drawings. ~
,.,:
:, . .; ..’,..
~, “.,
“5:
4:.2.1
Basic drawings
‘“
4.2.2~.5’
St-ructuredrawi”ngs’
‘
~~~-“,., ~
DETAIL REQUIREMENTS
6,-;
5.. -“
5.1
Detail ins~ructions and glossary of terms
6.
‘5.1.1
Group Wei’ght”
Statement; Part I
.
6
,,
6..
5.1.1.1
Weight empty
..,,
.
..
.
5. 1.1.2
7“
Useful “load
..
. . ,7
5.1.1.3
Dimensionaland structural data.
i“
5.1.1.4
Description of.dimensional and s,tructur~l.data.’ ,7
5.1.2
Detail.Weight Statement, Part II. ‘ “.. ?
5.,1.2..1 Items serving a ‘structural as well..asan
. ‘.“
7.
equipment function
5.1;2.2
Items common to the several stru.ctur’a”l
groups, ,
‘ 9. “
.
5.1.2.3 ‘ wing,,Rotor.”and-~ail‘Groups;-: ..
.,~
-. -.-”1-0,’
...
..- 11
Body G~.OUp
‘. :~
5.1.2.4
7.. -.
,1.2;
~5.1;2,5’
Alighting’Gear Groups ‘ ...
~ , -’
’12
‘:
5.1.2.6.
“
.“ :.”.
Engine,sect~on of Nac,elle;Group”
. ...
:: ~3..
Air Induction Group
5.1.2.7
Propulsion Group
5.1.2.8
,13 ~
5.1.2.9
Flight Control Group
14
.
.15.
5.1.2.10 Auxiliary Power Plant Group
..
5.1.2.11 Instrument Group
1.5“:”’
5.1.2.12 Hydraulic and Pneumatic Group”” ‘‘ .“”. ‘- -.’15
’16
‘5;1.2,13 Electrical Group
.. .
..
5.1.2.14 Avionics Group
:16
..
..::
,.
,16’ :
5.1.2.15 -.Afiatient
Group
16
.Group , , .:
5.1.2,16” ‘Fur~ighing.and Equ~Qmeri’t
:5.1”.2.,17A5r-Condit50n2n$;and Anti-Icing:,
Equipment Group
.16
. .:..
17
- 5.1.2.18 Photographic Group
’17”
5.:1.2.19 Load and Handling Group.
,!.. ,.
..,.
5.1.2.20 Special Equipment
.17
5..1.3
Appendix I, Detail Wei~ht Statement, Part II,
Structural Increments for Design Features
17
‘.’
17”
Purpose
5.1.3.1
5.1.3.2
17
“
Structural increments
. .
,’
iv
,“
.
9/27
.
.
I
I
Downloaded from http://www.everyspec.com
MIL-STD-1374A
CONTENTS (Continued)
Page
Paragraph
,..
5.1.3.3
5.1.3.4
5.1.3.5
5.1.3.6
5.1.3.7
5.1.4
5.1.4.1
5.1.4.2
5.1.5
6.
6.1
6.2
2.
Discussion of increments
Methods of determining increments
Accuracy of increments
Nonpermanent joint
Permanent joint
Appendix II, Detail Weight Statement, Part II,
Design Criteria Data for Weight Estimation
and Analysis
Purpose
Design Criteria
Weight and Balance Status-Aircraft, Part 111
NOTES
Abbreviations
Changes from previous “issue
18
18
18
19
19
19
19
19
19
21
21
21
FIGURES
Figure
1.
2.
3.
Wing structural increments for design features
Wing planform
Wing basic structure weight vs. semi-span
22
23
24
WEIGHT.STATEMENTS
Part I
Part II
‘part III
Group Weight Statement
Detailed Weight Statement
Weight
and Balance
Status
v
/
,-
Downloaded from http://www.everyspec.com
MIL-STD-1374A
1.
SCOPE
1.1
This document covers standard weight statements
‘ =“
and forms Parts I, II, and III hereof, for procurement of weight and
balance data for aircraft (including rotorcraft), states the principles
followe~ in the formulation of these standards, furnishes instructions
where necessary for uniform compilation o’f the required weight and
descriptive data, and provides a glossary of terms for which definitions
may not be self-evident on the weight statements and forms.
.
Sufficient detail is included to cover the majority of components
Blank spaces
for most fixed wing, rotary wing, or V/STOL type aircraft.
are provided for “write-ins)’ to detail weights” for advanced design
Care
vehicles, hypersonic structures, projected propulsion systems, etc.
should be taken before adding a l%rite-inll to ascertain that reasonably
appropriate terms are not already available for usage.
.
1.2
been predicated
~.
The detail and group weight
on the following basic concepts:
statement
have
a.
The primary purposes of the weight data are
to provide information in the most advantageous form for development
and 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 trends
to light at an early stage, pointing out areas in which design weight
control can be most fruitful, establishing realistic weight goals, and
evaluating on a rational basis the weight costs of design features during
the evolution of new configurations.
b.
The secondary purpose of the weight data is to
provide reasonably detailed information for engineering checking and
reference purpose~. 1.3
to implement
Principles.
The followifig principles
the above basic concepts:
have been followed
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.
Insofar as “practicable, all tangible and readily
b.’
identifiable components and provisions for a specific function or installation have been allocated to the functional group, regardless of geographic location and physical method of attachment.
Where compromise
of this principle was necessary because of multipurpose function (e.g. , doors
and panels which serve as closure for structural surface as well a,s a
particular installation function), items have been allocated geographically”
with as complete function isolation and identification as -possible.
‘9
1
I
Downloaded from http://www.everyspec.com
MIL-STD-1374A
@
c.
The importance of consistent allocation of
weights by all contractors in completing the detail statement has been
recognized. The amplifying instructions in this document are furnished
to insure consistency in allocation to the greatest extent practicable.
/
Provision has been made for tabulating in an
d.
appendix of the detail statement the total net weight increments for
special functions, installations, or features, including the semitangible
weights 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;
---
*
2.
.
.-t
REFERENCED DOCUMENTS
2.1
The following documents of the
Issues of documents.
issue in effect on date of invitation for bids or request for proposal
form a part of the standard to the extent specified her-ein:
SPECIFICATIONS
MILITARY
MIL-S-8698
Structural Design Requirements-Helicopters
MIL-W-25140
Weight and Balance Control System (For
Aircraft and Rotorcraft)
I
a
I
I
NAVAL AIR SYSTEMS COMMAND
I
SD-24
General Specification for Design Construction
of Aircraft Weapons for the United States Navy
STANDARDS
~
MILITARY
MIL-STD-12
Abbreviations for Use
Type Publications
on Drawings and in Technical
PUBLICATIONS
.,
“
AIR RESEARCH AND DEVELOPMENT COMMAND
ARDC Manual
80-1
Handbook
of Instructions
for Aircraft
Designs
‘ARMY AVIATION SYSTEMS COMMAND
AMCP 706-201, -202, -203
Army
Engineering
,’
/
2
Design
Handbooks
~
Downloaded from http://www.everyspec.com
MIL-STD-1374A
●
*
3.
DEFINITIONS
Weight definitions. Weight definitions shall be as
3.1
specified in MIL-W-25140.
Airframe unit weight is defined and derived on
page 8 of Part I.
—
4.
GENERAL REQUIREMENTS
✌
✎✍✎
4.1
General instructions.
Weight control systems shall provide for determination
4.1.1
of breakdown weight data required by the statements for consistency of
allocations in accordance with the item allocations of the Detail Weight
Statement, Part II and the concepts and principles outlined in 1.2 and
1.3. 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 tabulated
data and aid in the intended purposes.
The Detail Weight Statement, Part II lists entries
4.1.2
to take care of foreseeable cases. Write-in spaces have been provided
for new installations and expansion of the listed entries. Insofar.as
practicable, nomenclature for write-ins shall identify the function of
the items, and allocation shall be made consistent with the principles
“outlined in 1.3. Use of the words “provision” and “installation” shall
be avoided, unless further breakdown is given to indicate what is included
in the item. Supplementary sheets may be inserted when insufficient space
is available for new installations or expanded breakdowns.
All bolts, nuts,. rivets, etc., and loose’ items of
4.1.3
attachment shall be allocated to the same group as the item being attached.
Equipment and system support shall be allocated to
4.1.4
the same group as the item being supported. Multipurpose supports
shall be allocated to “the primary function. Where a primary allocation
cannot be determined by observation, such as may occur for fairleads,
supports for wire harnesses, and brackets, an arbitrary allocation may be
made.
Where more than one weight category is provided in
4.1.5
the statements for a given installation, allocation shall be made to the
Weight Empty, Useful Load, or Special Equipment categories in accordance
with the category allocation assigned in the design detail specification
for the model aircraft concerned, or in the general design specifications
of the procuring activity. If a conflict in category allocation of any
item occurs between weight statement and model detail specification, the
latter shall govern in all cases.
.
3
I
I
Downloaded from http://www.everyspec.com
MIL-STD-1374A
4.1.6
All items of power distribution systems (electrical,
hydraulic, and pneumatic including fluid in the respective tubing for
hydraulic systems, from main distribution points to actuating’ units) shall
,’
be allocated with the items operated. All’ components from source of power
to main distribution points shall be considered to comprise the main system.
The distribution system for a given item shall be assumed to include all
components which would be unnecessary and could be removed if power actuation
of the item were to be eliminated. Where several successive branches from
a distribution system are involved, and a clear-cut main distribution point
is not readily apparent, it shall be assumed that power is supplied to a
given geographic location primarily for the function requiring the largest
power, and to other functions in the sequence of descending power requirements.
For hydraulic power transmission to the various operating mechanisms (e.g.,
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 the
total number of these items are provided for in the statements, the “No.”
of identical items shall be entered in the appropriate spaces to avoid
ambiguity. Design data, such as “size”, “type”, “model”, and “capacity”
shall be completed where specifically provided for, and shall be written in
for other items when considered necessary. When abbreviations are necessary
for write-ins owing to space limitations, the abbreviations as required by
Section 6 shall be used.
*
*
4.1”.8
When business machine methods are utilized and reports
are produced automatically by machines, all pages as shown on the Group
Weight Statement and Detail Weight Statement (Parts I, and II, respectively)
.0
must be identically reproduced. Where write-in items are necessary, or”
wheie an existing item is altered in any manner, an appropriate flag entry
shall be made in the righthand margin directly ,opposite the line, Machines”
shall be programmed to include all indicated totals including those designated
by parenthesis, i.e., ( ).
4.1.9
Page size. The “normalfull size copies of these forms
are 8-1/2 by 11 inches for Parts I and II, and 11 by 30 inches (foldable to
8-1/2 by 11 inches) for Part III. These may be obtained from the procuring
activity, or as directed by the contracting officer. Requests should
specify: “Full size forms Part I, II, or III or all, as applicable, of
MIL-STD-1374.” Parts I, II, and III herein are photographic reductions of.
pages prepared in accordance with the above page size standards and therefore
represent standards of content and arrangement only.
4.1.10
All pages not used for the presentation,of data may be
omitted from the reports.
4
“e
.:
*
I
Downloaded from http://www.everyspec.com
m
I
I
.
.*
MIL-STD-1374A
.
Design drawings. Drawings supplied with the Detail
4.2
Weight 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.
Basic drawings shall contain a three
Basic drawings.
4.2.1
view drawing which shall include the overall dimensions and an inboard
profile drawing.
4.2.2
Structure drawings. Structure drawings shall contain
direct and cross-sectional views (not isometric) accurately scaled, which
shall include or be attached to the drawing , with details and dimensions
that show the following:
Wing. Structural box including box chord and
a.
thickness 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., fold
‘
and 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. .
9
Tail. Drawings and information compatible with
b.
wing requirement where applicable.
Rotor. Hub and hinge, including method of rotor
c*
attachment, typical cross section including any balance weight, structural
box, rotor chord and thickness along the span. Blade area in square feet
identified by cross hatching or suitable means.
Fuselage, Hull, and Booms. Primary antisecondary
d.
structure including bulkheads, frames, longerons and stringers, major
cutouts, flooring, major fittings and splices, pressurized area including
volume, materials, critical temperature areas with design temperatures
indicated. Fuel tank.areas shall be cross hatched and capacities indicated
(where not shown on a separate fuel system drawing). Major cutouts, weapons
bays, store provisions, engine, engine compartment and access doors, landing
gear support and cutout shall be identified.
Nacelle. Primary and secondary structure with
e.
details compatible with wing and fuselage requirements when applicable.
Air Induction System. Details may be included on
f.
a separate drawing or included on the fuselage or nacelle drawings. Inlet
design including spike, ramp, mechanisms, etc., shall be shown.
‘
Downloaded from http://www.everyspec.com
MIL-STD-1374A
Alighting Gear. Main, nose, or tail, and auxiliary
g“
gear drawings detailing the gear structure, rolling stock, retracting
mechanism: attachment fittings, catapult and arrest structure. Sizes and
dimensions are to be included for the rolling stock, oleo, travel, wheel
travel (where different from oleo travel), struct length from axle to
centerline trunnion.
Propuls<cn system drawings
Propulsion system drawings.
4.2.3
—.
shall show the following: ..
2.
L
Engine. Location and shape, mounts, access provisions,
a.
intake attachment station, etc. (unless shown on the fuselage or nacelle
structural drawings). Bleed or bypass ducts not shown on the basic air
induction drawing.
.-:
Fuel System. Tank locations, shapes. and capb.
acities as well as location of the major distribution-system components.
*
Transmission System. Gear Loxes and supports,
c.
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 maximum
continuous hp and rpm.
4.2.4
Equipment drawings. Equipment drawings shall be scaled
drawi~.gsto show maj~r component locations and schematics to show the
functional layout of the flight control, hydraulic, pneumatic, electrical,
air conditioning, and anti-icing groups.
5.
I
Isometric drawings may be substituted.
DETAIL REQUIREMENTS
Q
5.1
Detail instructions and glossary of items. Specific
items referred to in the Military Standards, specifications,—and in the
weight statement are identified by page-line numbers of the weight statement
concerned.
I
I
I
5.1.1
@2?.S.P
we%h~ statemen~j
5.1.1.1
Weight empty.
part
I.
I
Item 2-37, Landing Gear “Type”: Insert “Tricycle”, “Tail Wheel”,
“Bicycle”, “Quadricycle”, or similar general descriptive nomenclature.
*
Item 3-111 Manufacturing Variation: This wej.ght is the variation of
weight empty between successively weighed aircraft because of unaccountable
tolerances on sheet and material gages, salvages, pai~t thickness, etc. It
is also intended as an overall factor for differences between weight bookkeeping records and actual weights after the contractor has applied his best
efforts to account for variations in tangible items (e.g., fuel cells,
purchased parts, and equipment items) to reconcile any initial, or consistently repeated, variation from the weight bookkeeping records.
6
,
●“
‘Q
Downloaded from http://www.everyspec.com
MIL-STD-1374A
5.1.1.2
Useful load.
Item 4-128: Oil for transmission or gear box which has a selfcontained independent sys”tem is included in the”weight empty as Item 2028 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 “ “and insert”
,..
“Unusable”.
-,
..
Dimensional and structural data. Items 5-lthrough
5.1.1.3
5-41’require dimensional entries which apply to the weights listed in
Items such as radomes, canopies, pylons, etc;,. should
“Basi,c Structure”.
not normally be included in the.dimensions unless they are ‘apart of
“Basic Structure”. ‘It&ms 5-4”2 through 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 which
design- the structure.” Paragraph 5.1.1.4 provides instructions for
describing the data submi.tted for Part I, Page .
5.
,“
- :.
5.1’.1.4
Description of dimensional and”structural data.
Specific definitions for dimensional and structural data are usually
impractical due to variations in design configuration: and.requirements.
Page 7 provides” space for descriptions which apply to the data, included
on Pages 5 ,and 6. Drawings and/or sketches-may be.used as they’are effective
(Required
means to clearly show where listed dimensions a“ndareas” apply.
with the Detailed Weight Statement.)” ‘The-structural design conditions
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-8698
and design factors “clarified”with regard to power on> Power offj auto:
rotation, etc., that may design the rotor. Any dimensions or structural
data on Pages 5 and 6 which requires “clarification should be described
on Page” 7.
5.1.2
Detail Weight Statement; Part II.
“---
..,”’
5.1:2.1.. -“ “items serving”.a structtirai aswell as.an equipment
function. (Items serving-”such multipurpose functions ~resent difficulty
Therefore,
in coding and in applicatio-n to weight estimating’ methods.
all--parts of.s“uch installa.ti&s which are m“ultiptirposeand. ~~rinotbe “
isolate:d”as serving a single function and which are integral with the
structure o’f.:the
“rotor, wing, tail body, “or nacelle shall be allocated
to these structural :groups.by”write-in’.entries~ ‘using functional identifying
nomenclature.
Structural increment’s’sh,allbe” shown in .Appendix I to the
Detail Weight Statement, Par,t.iIIto-i%olat”e:”the”
structural weight “portion
of such installations. ‘eTjp&a~’”installations in this’category are:
..” -
~’
.
.
.“
:
‘
“
I
I
Downloaded from http://www.everyspec.com
MIL-STD-1374A
Air supply, bleed air, and exhaust ducting
a.
systems in which skin or webs serve as part of duct contour (duct walls
and stiffeners which can be isolated primarily as duct system are
allocated to “Engine Section or Nacelle Group, Air Induction System”
or “Propulsion Group, Exhaust System”).
Double skin and baffle construction for “heat
b.
anti-icing ducts and rotor pressure ducts (ducting allocated to “AntiIcing” and rotor pressure ducts, similar to paragraph (a) above).
Integral tanks in which skin, webs, and loadc*
carrying seal fittings are utilized to fo~ the cavity, or bag-type
installations in which skin, webs,” and backing board provide tank
support (backing board, separate tank supports, sealant material, nonloadcarrying fittings are allocated to “Fuel System”).
Skin or webs serving as deflector plate or
d.
radiation protection, or fabricated of special materials to act as heat
or fire barriers,. or acting under elevated temperature conditions (nonstructural shrouding and fire shielding are allocated to “Propulsion
Group”).
e.
Load-carrying armor-plate.
f.
Engine section structure, engine supports and
removal tracks, etc. , for.engines buried in the body (mounts and vibration
isolators are allocated to the “Engine Section”).
Catapult, arresting, and barrier-crash installag“
tions. (Catapult’, arresting, and barrier crash fittings are allocated
to “Alighting Gear”).
h“. Load handling gear installations.
(Inflight
towing and external cargo sling, rescue hoist fittings are allocated to
“Load and Handling”).
Flooring and supports.
i.
(Provisicn has been mad e
for allocation to “Basic Structure” and “Secondary Structure” in the “Body
Group”, as well as allocation to nonstructural flooring in the “Furn: sliings
and Equipment Group”. Refer to discussion of “Flooring” under 5.1.2.4.)
Randomes which do not form normal contour of
j+
wing, tail, or body are allocated to the “Avionics Group”.
k.
Removable structural panels or.structural doors
for special functions are included in the basic structural groups.
8
I
Downloaded from http://www.everyspec.com
MIL-STD-1374A
5. 1.2.2
*
.:
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. The
items shall, insofar as practicable, be allocated by structural function
served. For example, Items 2-7 and 2-13 shall include all joint, splice,
and fastener material in the interspar skin and spanwise stiffeners, thk
spar caps, and interspar skin attachment to spar caps; Item 2-17 shall
include all joint, splice, and fastener material in webs, web stiffeners,
and web attachment to spar caps; Item 2-24 and 11-25 shall include all
joint, splice, and fastener material for fastening ribs or bulkheads to
skins and spars; Items 2-34 and 2-39 shall include’ leading and trailing
edge attachment to spars.
7.
Items 2-21, 2-22, 2-23, 5-12, 5-13, 7-21, 7-22, 7-23, 11-4, 11-24, 1614, Bulkheads, Ribs, Frames, Chordwise Stiffeners, &ridMinor Frames:
Bulkheads are the main structural members which assist in carrying loads
around major cutouts, or which distribute major concentrated loads (external
or within the structure). Bulkhead~ include a reinforced or specially
stiffened shear web or truss over the partial or complete cross section and
may 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 indicates
function e.g., “Front Spar Bulkhead Sta. 150”, “Equipment Section”, “Bulkhead
65,” and “Fuel Tank Sta. 140”. A supplementary page (11A) may be appended
if necessary (“Nonstructural partitions”, such as movable separators, are
coded to Item 35-52). For large aircraft, it is also desirable to append a
similar breakdown of minor frames, Item 11-24. Ribs and frames are similar
but usually of relatively lighter .construction and serve the function
primarily of stiffening the skin surface to maintain contour under air load
or internal structure .crushing loads. They are not specially reinforced to
distribute major, load concentrations. Minor frames and chordwise stiffeners
usually have very limited shear web depth, may be partial rather than
complete 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
the framing around the door opening, hinges,
door installation. Columrs are provided for
a breakdown of the “Operating Mechanism” for
mechanism shall be allocated to the group to
Frames”: These items include
and all other items,of the ‘
the door “Structure”, aridfor
power-operated doors. Operating
which the door is allocated.
Item 11-39, LongitudinalPartitions: These are longitudinal structural
bulkheads in the body contributing to body strength, similar to transverse
bulkheads. (“Nonstructuralpartitions”, such as movable cabin “Separators”,
are coded to “Furnishingsand Equipment Group”, Item 35-52.)
9
,..
..
Downloaded from http://www.everyspec.com
. .
MIL-S7D-1374A.
*
Items 3-52,
53, Exterior Finish:
from elements,
*’”
,.
0“
These.items include “camouflage;paint~-”protection” .
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,ization or flotation.
,:
5.1.2.3
Wing,.Rotor, and .Tail Groups. Surface Folding:or
pivoting actuation systems are to be included.on pages 3, 6,,8;~:and.1O:. “
when prov’idedfor ground operation (i.e., wing.f
old) and -to Fligh”t~~ ,~:Controls,. pages .23 and 26, when used dtitiing
flight. ~
*
,>
Item 5-56 “Blade”.Ass”embly”
includes.that structural .portion of the
rotor between the tip and the.first.hinge .p’oint,inboar”d
,ofthe tip, and
..
includes 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”, “outer
Skin” 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 ‘attention to typeo’f
construction.
Tip burner hous%ng integral with rotor blade,”write in as Itern”542; where removable with burner’,write in as,Item”18-13. ‘:’
-,
Items 2-32, 5-20, and 7-32, Leading Edge Covering:”’ Refer.to
regarding double skin construction used as ducting.
Q
. ..
5.1.2.1
To:
Items” 2-40 and 2-’41, Trailing Edge Core and Bonding Adhesive:
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 the
type of pivot structure.
Sweep mechanism should be detailed’on page.23
under “wing positioning’! column”with note d,e”s”cribin’g
variable sweep.
,~,”
‘Items2-47, 2-48, and 7-47, Attachments Wing to Fuselage Wing to
Nacelles; Tail to Fuselage: Include .identifiable fittingsand hardware
for attachment of wings.
*,
. ,.
It.em.3-4, Wing Fold:
Include..identifiab-le structure necessary for
,fold actuationund”er “structure’’co
lurnn,
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-.
- .
.
:,
..
1“
L
,.
,0 ‘
Downloaded from http://www.everyspec.com
I
MIL-STD-1374A
Item 5-41, Internal Duct Structure: This item to be used only where
internal ducting also serves a structural function in the rotor blades.
Allocate non-structuralducting for pressure jet or anti-icing to “Propulsion
System, 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 structure for blade balancing or ‘inertia.
Pages 3, 6, and 8, Power Transmission:
hyc?raulic “Fluid”.
Refer to 4.1.6 for listing of
Items 6-5, 6-6, and 6-7, Gimbal Ring, Yoke, and Universal Joints:
These ~re normally the structural attach~ent of the rotor hub to the
aircraft. 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:
on line 22, as applicable.
If tab balance weights are used, Write in
Body Group. If tubular welded basic structure is used,
5. 1-.2.4
sicgle write-ins may be used for the entire structure, or sections of the
structure, as appropriate.
Items 11-44, 12-28, Flooring and Supports:
Flooring is considered as
follows:
a.
“Basic Structure” and coded to Item 11-44 if it
partially carries flight and landing loads through the aircraft structure.
“Fuel Decks” and “Control Decks” and their supports should be written in
under Item 11-44.
b.
“Secondary Structure” and coded to Item 12-28 if
it is fixed in place, but if removed does not impair flight and landing
strength of the flyable aircraft (that is, flooring is present only as a
walkway or for support of equipment, cargo, etc.).
“Auxiliaryr’ and coded to “Furnishings, and Equipment
c.
Group”, 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 local
floor-load capacity.
I
*
Item 11-51: Rotor support included for the structural membel-s whose
primary 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
‘
Downloaded from http://www.everyspec.com
MIL-STD-1374A
\
Item 11-45,
Firewall:
Refer to discussion under 5.1.2.6, Item 16-24.
BulletItems 12-5, 12-11, Canopy:
Includes glass and plexiglass.
resistant glass shall be allocated to “Armament Group”, Item 32-29.
Page 13, Power Transmission:
“Fluid”.
5.1.2.5
Alighting
Refer to 4.1.6 for listing of hydraulic
Gear Groups.
*
Item 14-1, Landing Gear “Type”:
Insert “Trailing Arm”, “Conventional”,
“Articulating”, “Quadricycle”, or similar general descriptive nomenclature.
*
Insert column headings descriptive
Item 14-3, Location:
location, such as: Fuselage, Wing, Nace~le, etc.
of the
Where landing gear drive mechanisms for taxiing are provided, write in
descriptive breakdown of page 15 with weights tabulated in last column.
Engine Section or Nacelle Group. Rings and annular
5.1.2.6
sections solely for generating lift are to be coded under wing, page 2.
.
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 using
write-ins for adequate description of the structure.
*
Item 16-9,
Gear Box Support Structure and Item 18-8, Reduction Gear
Box: Allocate to these items only the gear boxes and mounts used exclusively
for 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”
k
Item 16-24, Firewall: Nonstructural firewalls, or firewalls which
serve a structural function in the nacelle, are coded to this item. Firewalls which serve a structural function in the body are coded to “Body
Group”, Item 11-45. Firewalls in a wing (rather than a wing nacelle),
which serve a structural function for the wing, shall be coded to “Wing
Group”, Item 2-54.
Item 16-32, Cowling:
functional purposes, write
nomenclature.
*
If cowl is sectionalized for maintenance or
in breakdown of sections, usi~g descriptive
Page 20, Power Transmission:
Refer to 4.1.6 for listing of hydraulic
“Fluid”.
I
12
“
s
Downloaded from http://www.everyspec.com
I
MIL-STD-1374A
5.1.2.7
Air Induction Group.
Item 17-3,0Engine Dome: If the engine ,dome is supplied with th’e
engine, it is listed under.18-4? Otherwise it shall be included here.
Propulsion Group. Separate cola”ns areincluded to
5.1.2.8
‘“
allow for dissimilar engines, Auxiliary’Power Plant Group, page 27; is
provided for power plants used only to supply power for starting or
equipment.
‘.Item”18-4,Engine (as installed): List engine weighti including
all residual,s”asspecified in SD-24, afidall engineaccessories’ which
are 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 1938.
..Item 18-12, Accessory Gear Boxes and Drives: This’item includes
.allm”ulti-purposegear boxes’and drives which are not integral with
drive system gear boxes (Items 20-4 and” 21-5) nor ~n the specified
engine 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 structural
surfaces form part of duct contour.
Item18-40, Starting System: Power supplies such as gas generators
shall 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 the
duct, 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,
~
’Hydraulic”, “Manual”, etc.
etc. Under”’’Type”,list “Electrical’’,”’
Items 18-51,
18-52,
Propeller Oil and”Tank: These items provide
for entries when a separate oil supply system for hydraulic propellers
is u“sed. When engine oil is used for hydraulic propeller supply, propeller
oil
is included under “Trapped” or “Unusable” oil in the useful.load.
I
.
—..-..
-
13
I
Downloaded from http://www.everyspec.com
●
MIL-STD-1374A
Item 20-2,” Identify gear boxes in column headings in sequence from
engine output to rotor(s), fans or props.
Item 20-22: Include’all components for independent gear box.lubrication system. Include drive system lubrication in Item 21-20..
item 19-4, Tanks: List each cell or tank individually, even though
tanks may be interconnected. Wetted are’asof tanks shall,also be
listed 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 all
sealant compound, corner seal fittings, and other non-load-carrying
tank seal fittings. Also refer”to discussion under 5.1.2.1 for items
serving a structural and equipment function.
Item 19-39, Pumps:
✜✎
Include all pumps, including those buried in
tanks.
*
Items 19-45 to 19-54, Lubricating and Fuel Plumbing Systems: Includes
all piping, fittings, drains, valves, supports, etc., except for items
specifically 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.
*
Flight Controls Group. Insert data for fixed wing
5.1.2.9
systems controls on pages 23 and 24 , rotating’rotorffan systems controls
on page 25 (v/stol transition systems controls to page 26).
For “Wing Positioning” or “Rotor/Fan Attitude” controls, write in
on page 22 any controls which are in the cockpit and allocate the remainder
of 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 appropriate.
Rotating Controls, page 25, columns 5 and 6, defined as those rotorcraft
control items which rotate with the rotor.
Rotor/Fan Attitude Controls,,page 26, column 2; defined as those
controls which tilt the rotor axis.
For aircraft with powered flight control systems, follow the general
guidance of paragraph 4.1.6 by-coding the power distribution components
(from the main distribution.point) to the “Flight Control Group” and
the power supply components to the appropriate power generation groups
(“Hydraulic”, “Pneumatic”, “Electrical”).
,.
.
I/,.
e
,i
Downloaded from http://www.everyspec.com
I
II
MIL-STD-1374A
/
Items 23-5, 24-5, 25-6, 26-5, Mechanical Operating Mechanism: For
manual or boost systems:
Includes all mechanical controls from the “Cockpit
For powex-operated systems: Includes
Controls” to the devices actuated.
all mechanical (pilot actuated) controls between the “Cockpit Controls” and
the “Power Operating Mechanism”.
2
*
G
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,
actuators, etc.) from power distribution point to, and including, the boost
unit. For power systems: Includes all power system components (wiring,
plumbing, actuators, etc.) from power distribution point to the surfaces
actuated; mechanical components from power units to surfaces actuated”shall
be allocated to “Mechanism”, Items 23-14, 23-22, 23-31, 24-14, 24-22, 2431, 25-23, 25-32, 26-14, 26-22, and 26-31.
Items 23-34, 24-34, 25-38, and 26-34, Artificial Feel: - If special
feel “Systemsr’are provided, insert breakdown by write-in items. Write-in
“q” springs and speed sensing devices.
I
Items 23-48, 24-48, 25-48, 26-48, Supports, Guides, etc.:
seals and covers for pulleys and cables.
●
*
*
~
5.1.2.10
Includes
Auxiliary Power Plant Group.
Page 27: Includes complete auxiliary power plant installation. For
unusual 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.
\
Instrument
Group. The “Installation” column is provided
5.1.2.11
—.
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 as
specific entries under this item.
Multipurpose power supply or power
conversion items are listed under “Electrical Group”, Items 30–3 and 30-22.
*
e
Hydraulic and Pneumatic Group. Refer to 4.1.6 for
discussion of main system and determination of distribution points.
5,1.2.12
15
Downloaded from http://www.everyspec.com
- MIL-STD-1374A,
*
5.1.2.13
Electrical”Group. Refer to 4.1.6 for discussion ’of
main system and determination of distribution
points.
.0
Items
30-3,
30-14,
Power Supply and Conversion Equipment:
multipurpose power supply and conversion equipment are allocated“All
to
these items. Single purpose power supply and conversion items are coded
to the group service (e.g.,
instrument inverters are coded to !lInstrumentlr
Item 28-53).
3
Item 30-31, Wiring:
Where
wiring, nylon-jacketed wiring,
extensive use has been made of aluminum
etc. , add appropriate’ footnote.
Item 30-34, Lights and Signal Devices:
wiring, switches, relays, etc.
*
all necessary
.-.
5.1.2.14
Avionics Group. All avionics equipment shall be
When for special reasons, it is necessary to
deviate from this practice, cross-reference to other groups to which
avionics equipment has been allocated shall be made.
The brackets,
“Installation!t
column is provided for allocation of contractor-furnished
allocated
.,
Includes
to this group.
tables, shelves, wiring, cabling, plugs, etc.
Government-furnished
installation 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 flooring
under 5.1.2.4, Items 11-44 and 12-28.
,,.
Item 35-52, Partitions (Nonstructural):
“Longitudinal Partitions” under 5.1.2.2,1tem Refer
11-39.to discussion of
“,
,,,,’
-2
,.
Item 35-53, Vibration Absorbers:
Separately identifiable devices
(not incl. engine or equipment type isolators) which generally function
to improve the.vibration environment for crew and passengers. In this
respect they serve a function similar to acoustical and thermal insulation
and are considered furnishing.
*
5.1.2.17
Air Conditioning and Anti-Icing Equipment Group.
Items 37-43 and 38–42, Hydraulic Controls:
listing of hydraulic “Fluid’!.
Refer to 4.1.6 for
b,”
;
a
:,
I
,).,
,.,
,.
16
‘
,“...,
,.
,,.
3:
,,:
,:1 ,,
Ij y
,!
,,
I
Downloaded from http://www.everyspec.com
MIL-STD-1374A
Item 38-15, Ducting:..Refer to discussion under 5.1.2.1 for duct
systems where structural surfaces form part of duct contour.
Where’-equipmentor installation serves both air-conditioning and
anti-icing functions, code to primary function and cross-reference under
the other; where a distinct primary allocation is not apparent, an
arbitrary allocation may be made with appropriate cross-reference of
dual function.
I
I
*
5.1.2.19
Load and Handling Group. See 5.1.2.1 for discussion
of items serving structural and equipment ftinction.
Gun camera mounts, wiring,
Item 40-29, Ramps: Allocate ramps to this item which are not-part
of the cargo doors or which do not serve as a closure for a structural
surface. ~efer to 1.3b. Other ramps should be allocated or written
into the appropriate structural group.
5.1.2.20
Item 41-38,
Special Equipment.
“Type” Tanks:
List “S.S.”,
“Bladder”,
“Aluminum”,
etc.
,Appendix I, Detail Weight Statement, Part II.
5.1.3
Structural Increments for Design Features (pages 42-44).
5.1.3.1
Purpose. Pages 42 and 43 provide for determination
and listing of net structural weight increments for special functions,
installation, and other”design features. Such information is considered
essential for a full understanding of structural weight variations among
various configurations, and for ,formulation and improvement of weight
estimating methods.
I
I
Photographic Group.
5.1.2.18”
etc., are allocated to this group.
.,_
I
I
‘*
:..
Structural increments. These net structural weight
5.1.3.2
increments are a“lreadyincluded in the structural weights tabulated in
the Detail Weight Statement, Part 11,.but are of such nature that,they
may not be directly apparent quantitatively during the normal processes
of calculating weights from drawings and coding to items in a weight
statement. Insofar as practicable, tangible portions of these net
increments are isolated as items in the structural groups under “Secondary
Structure”. Semitangible portions of these net increments which do not
lend themselves to automatic coding as items on the weight statement,
are buried or masked in the “Basic Structure”, and must therefore be
quantitatively evaluated by some rational analytic procedure. In the
latter cate~orv are the weight penalties caused by major cutouts and
joints, rem&able structural panels, portions of the wing designed by
landing rather than flight loads, blas~ protection, gun reactions, heavy
17
I
Downloaded from http://www.everyspec.com
..-
. .
skin,.servingprimarily as”deflector plate, use of’special materials in
high temperature regions; etc. In general, the intangible weight .fncrement
is in the form’of increases in skin and web gages,’special ribs.and
auxiliary sparij doublers, built-up sections around cutouts and other
local increases. ~A total net increment represents the weight penalties
of a.feature for the existing 15asicconfiguration, and does.not-entail :
evaluation of the relative merits of weight of .,o”t”her
configurations or
types 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”ation
.,
are assumed to be unchanged.
5.,1.3’.3
Discussion of increments. Since mere.listing of net
structural 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 net
increment.,.in
terms of its basic and-secondary structure components; the
effects of overlapping penalties’,one of whic”hmasks or includes the
potential ,effectof ‘another,and for which, therefore, a distributed or
inclusive increment has.been listed, etc. Schematic diagrams of type
structure are desirable and should be included”where considered necessary
for clarity. Tabular ~reakdown of the derivation of the’net increment
in the form”shown in Fig”tire
1 may be used to advantage in the discussion’.
.
5.1.3.4
Methods of determining increments. Any rational
procedure for determining the increments maybe used. Discussion of
proposed procedures with the procuring activity is encouraged. .TWO ‘
possible approaches”are suggested in the following paragraphs. A corn“L
bination of approaches may-be found to be advantageous.
..
~
The.normal structural design processes and review of’
5.1.3.4.1
structural drawings-may be utilized to determine qualitatively, as:the
design progresses,the area in which the structural compromises have
been made for design features. A review and analysis of the critical
design loads and conditions may produce information concerning “the
magnitude of the compromises, from which the weight increment may be c
,’
deduced.
5;1.3.4.2
Graphical plots of weight distribution of the’st’ructural
elements (covering, webs, spar caps, .etc), superimposed on a planform {of
the structural envelope may.yield information from which total local
.“
weight increments may be deduced. A study of the irregularities in the
‘“
weight distribution, their location on the envelope, and a review and
analysis of the critical structural loads and design conditions may
produce qualitative allocation of these irregularities to particular
design features. An example of this type of approach for a wing is
shown in Figure 2 and Figure 3.
Accuracy of increments. It is ,recognized that some
5.1.3.5
degree of approximation will be inherent,in determining the intangible
portion of the structural increments.
.18,
,,
.,.
.$
./,”
..
0“”
I
Downloaded from http://www.everyspec.com
MIL-STD-1374A
5.1.3.6
can be readily
This type of joint is one which
Nonpermanent joint.
disconnected in the field “for folding, stowage, &intenance
disassembly, etc. , purposes. The structure may be in the form of concentrated tension or shear connections and doubler plates,.”ora ringof removable
connections.
5.1.’3.:7;
for manufacturing
,
,.
Permanent joint.
This type.of joint is incorporated”
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. .
Appendix II, Detail-Weight Statement, Part II,’
5.1.4
‘
To”be completed.
Supplementary Data for Weight Estimation and’Analysis.
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 necessary
for analytical weight estimating methods used with the Part ,11 level of
weight”breakdown.
*
Design Criteria;’ These “data supplementing infotiation
5.1.4.2
provided in Part I, pages 5“and 6, should be consistent with the aircraft
Line items’ for’which,data are not yet
design stage at. time of submittal.
available shal,l be so indicated.
“Pertinent design criteria not listed on
page 45 which materially affects the aircraft weight should” be added.
*
,..
.Weight and Balance Status - Aircraft, Part III.
The
5.1..5
compilation of data for, and use of, the status report form is considered
The following instructions are
to be self-explanatory
for the most part.
intended to aid in the preparation of the status report.
‘
All entries in Column 8“,page 1 shall be detailed
a.
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 a
separate 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, as
applicable’, for each change.
(2). Contract Change Order number.
(3) “Letter’designationof correspondence reference for pending change not yet assigned an ECP number.
.-..
.19
“
1
1
1’
I
I
Downloaded from http://www.everyspec.com
MIL-STD-1”374A
(4) Brief subject/title, together with changes to
weight empty and horizontal moment, useful
’load, and horizontal moment, and
gross weight center of gravity, for GOV’T .responsibility chan&es incorporated
~ince
las~”status report (ColUmn 8, page 1).
added pages in which the change”is,detailed.
:
List the column number on
(5) Authorized ’changes (Column 3, page 1) shz.11
be listed’as a separate group and may reference and carry forward the ,total
of weights, moments and center of gravity for the “authorized” changes
summarized in the last status report.
.?
All entries on page 1, Column 9 shall be detailed
c.
on the combined GOV’T/CONTRACTOR pages. Delete the words “GOV’T” and add
appropriate page numbers as required, i.e. 2, 2a, 3, 3a, etc. Use a separate
column for each change and additional sheets if necessary. Minor changes
in group weights due to revised estimated, calculated, or actual weights
need not.be listed in detail and may be combined into one or more columns
using appropriate headings such as Calc vs Est, etc. Include brief discussion
of reasons for all important or major weight changes, variation, or C.G.
shifts, including horizontal moment changes and any remedial measures being
investigated or applied. Use column numbers from the appropriate page and
c’
brief titles to identify each change;
o
On page 1, for each item of weight empty, under
d.
basis for current weight data, Columns 10’thru 12, list percentages of
current group weights of Colu~ 6 which are in an Estimated, Calculated, or
Actual Weight Status.
e.
If Main and Auxiliary
Engines
are used,
attach
breakdown of main and auxiliary Propulsion Groups:
f.
Enter airframe weight
page 8, Part I of the Estimated Weight Report.
on page
la as updated
from
(1) Page la - Lines 175 & 176. Delete the
g.
inapplicable wheel position.
Most Fwd & Most Aft should show extremes
(paragraph 3.8.3 of MIL-W-25140).
(2)
wheels up or down. If limits
plot. State conditions which
in initial issue and whenever
Recommended C.G. Limits. Indicate wh~ther
vary with gross weight, include C.G. envelope
determine the C.G. limits and source of data
limits are revised.
c.
.
.
Downloaded from http://www.everyspec.com
‘“MIL-STD-1374A
6.
NOTES
6.1
write-ins
Abbreviations.
or in machine tabulation
When abbreviations are necessary for
methods, the abbreviations of MIL-STD-12
shall be used wherever space permits. The following list summarizes
acceptable abbreviations commonly used for weight data or used in the
Summary Weight Statement, Detail Weight Statement, and Weight and Balance
Status, Parts I, II, and III, respectively, of this standard. Where more
than one abbreviation is shown, the first given is preferred.
alighting - alight
barometric - bartc
boost - bst
-bungee.- bun
collision - coin
compartmentation - comptn
contingency - cntcy
co-pilot - c-pit
covering - covrg
cyclic - Cyc
duct - du
fairlead - frld
fingerplate - frpl
fire warning - fwng
flasher - flshr
gusset - gus
headset microphone - hdstmk
hook - hk
*
incidence - incid
inertia - iner
king - kg
liner - lnr
oxidizer - oxidiz
pedal - pdl
pitot – pit
pylon - pyn
rainshield - rnsd
shelf - shlf
shelves - shlves
shimmy - shiny
stabilizing - stabg
stick - stck
supercharger - s-chg
thermoswitch - thsw
transponder - xpdr
walkway-wkwy
6.2
The margins of this
Changes from previous issue.
specification are marked with an asterisk to indicate where changes
(additions, codifications, corrections, deletions) from the previous
issue were made. This was done as a convenience only and the’Government
assumes no liability whatsoever for any inaccuracies in the”senotations.
Bidders and contractors are cautioned to evaluate the requirements of
this document based on the entire content irrespective of the marginal
notations and relationship to the last previous issue.
PREPARING ACTIVITY
NAVY - AS
PROJECT NO. 1500-0092
CUSTODIANS:
NAVY - AS
AIR FORCE - 11
21
Is
ELEMENT
STRUCTURE
.
.
‘,
,’
,
‘.
.,
~
c.
‘
m
INCREMENT
INCREMENT
,ToTAL STRUCTURAL-INCREMENT
TOTAL SECONDARY
TOTAL BASIC STRUCTURE
Sweep Actuator Attachment
Pins & Bushings
Fuselage & Nacelle Attachment
..
,,
Pylon Attachment
,,
755
755
20
194
,,
-55
Interspar Ribs & Bulkheads
~
-14
Spar Webs & Stiffeners
292
318
‘
‘
sWING
SWEEP
& PIVOT,
Lower Interspar Cover & Stiffeners
Upper Interspar Cover & Stiffeners
STRUCTURAL
:.”,
40,’
,,
‘“:,
,:
,,
,.,
28
28
10”
10
8
PYLON
SUPPORT
,..’
,..
.,
,.
‘,?,
99
99
45
.,.
24
,..
3
,.
24
(\
-.
BARRICADE
ENGAGEMENT
.,
increments for design features
:,-
,’,
’40
,,
18
22
CHORDWISE
WELDS
,.
,.
173
9
’164
18
58 ,
53
WING,
FUEL
.,
.,.’
,“
~
,!
.,
.,,
. .
:,
.
,,;!
.,
,.
,“.
,’
‘,,
‘; “:
.,’.
,,, ,
,,,
.,,
‘.
,,
./.
,’,
,
a
.’”
,.,
.,,.
,.
.,
,..
.,,
.,.
,,:.
154”
,..
.,,
,“’
,,
:154
,,
.,..,
,.
.,
,.,
,.
,’”.
.,
,,,,,
.,,’.
. . ..
‘,
.140, ,
,.
,, !
,,
14:
‘,.,
.t
L’
‘,
~
,? “,1
,,
I
J..
FUSEL~GE
ATTAC~NT
,.
u
A
,{
. :“ .:.?’
Cc’”
. .
~
.,.,
,,.
Downloaded from http://www.everyspec.com
I
I
CENTER
WING
I
SECTION
PIVOT
SWEEP ACTUATOR
PICK-UP
AtixlLiARY
I
I00
I
FLAP=
l.f!
I
-L.
I
,.1
I
200
I
2.
Wing
SEMI-SPAN,
FIGURE
I
E. FAIRING
I
1
I
1
I
I
I
1
I
I
y
~
Downloaded from http://www.everyspec.com
m
a
3
w
,-z
“0
10
El 5 ——-
0
in
1-
3
w
—
‘x
u-i
m 15
-1
+-
\
20
—
d
r—
-
FIGURE
I00
!“ti:
___
‘
A
.;,
3.
/
I
I
=%..
1
I
200
I
,. I
I
I
300
‘.!,
structure weight vs. semi-span
I
~.--_
STIFFNESS
I
.
—
1
BASIC STR. LESS STR. INCREMENTS-FOR
DESIGN
FEATURES
5 LESS NON-OPTIMUM
FACTORS
STRUCTURE
SE MI- SPA N, IN CHE,S
‘
BASIC
Wing basic
1
=4..
/
/
,
.’
,.
,
,,
‘.
,.,
Downloaded from http://www.everyspec.com
Downloaded from http://www.everyspec.com
I
MIL-STD-1374A
:
I
I
I
-=
PART I
GROUP WEIGHT STATEMENT
I
,-...
.
.<,
&
I
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART I - TAB
NAm
DATE
PAGE
MODEL
REPORT
I
I
G~OUP WEIGHC STATEMEiT
AIRCbFT
(.
+NCLUDING XOTORCRAPI)
ESTIMArED - cALduuvm
- hcTuAL
(CROS
s OUT THOSE NOT APPLZCABLE)
AIRCRAFT, GOVERMENT NO.
AIRCR4FT, CONTRACTOR NO.
MANUFACTURED BY
AUX
MAIN
ENGINE MANUFACTURED-BY
ENGINE NO.
ENGINE TYPE
PROPELLER MANUFACTURED BY
PROPELLER MODEL
PROPELLER hWER
PAGE KO.
PAGES REMOVED
1
cm
Downloaded from http://www.everyspec.com
MIL-sTI?-1374PART I - TM
NM
.
.’““ GRoup ~IGHT sTAT~NT.
WEIGHT EMPTY
.
DATE
PAGE .,
MODEL
-REPORT
“
‘
●
=
--
0
i
g
* CHANGE TO FLOATS AND STRUTS FOR WATER TYPE GEAR.
**LANDING GEAR ‘f’TYPE”:INSERT “TRICYCLE”, “TAIL wEEL”,
DESCRIPTIVE NOMENCLATURE.“.
2
“BImcLE”, ‘:QUADRICyCLE”> OR SIMILAR
Downloaded from http://www.everyspec.com
I
58
59
60
61
~
I
.:
●
63
64
65
. 66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
90
91
92
93
94
95
96
97
98
- 99
,100
,101
PAGE
MODEL
REPORT
GROUP WEIGHT STATl?ME~
WEIGHT EMPTY
MIL-Sl%1374 PART I - TAB
NAMF.
DATE
x
PROPULSION GROUP
IATION
AUXILIARY
XX
MAIN
~
UST SYSTEN
~G
WATER INJECTION
ENGINE CONTROL
STARTING SYSTEM
PROPELLER INSTALLATION
SMOKE ABATEMENT
LUBRICATING SYSTEM
FUEL SYSTEM
TANKS - PROTECTED
- UNPROTECTED
PLU?fBING.ETC.
DRIVE SYSTEM
GEAR BOXES, LUB SY h ROTOR BRK
TRANSMISSIONDRIVE
ROTOR SHAFTS
FLIGHT CONTROLS GROUP
coc~~
O LT
SYSTEMS CONTROLS
AUKILIARY POWER PLANT GROUP
INSTRUMENTS GROUP
HYDRAULIC & PNEUMATIC GROUP
ELECTRICAL GROUP
AVIONICS GROUP
~
INSTALLATION
LBs,)
tiwr
GROUP (INcL.PA8sIvE p:OT.
FURNISHINGS & EQUIPMENT GROUP
ACCOMMODATION FOR PERSONNEL
MISCELLANEOUS EQUIPMENT
FURNISHINGS
EMERGENCY EQUIPMENT
,102
.103 AIR CONDITIONINGGROUP
ANTI-ICING GROUP
a4
106
107
108
109
110
111
-112
113
PHOTOGMPHIC. GROUP
LOAD & HANDLING GROUP
AIRCRAFT HANDLING
LOADING HANDLING
BALLAST
MANUFACTURINGVARIATION
TOTAL CONTRACTOR CONTROLLED
TOTAL GFAE
HT EMPTY - PG 2-3
i
3
s?!?
I
x
I
Downloaded from http://www.everyspec.com
-.
,.. .
\.””
.’
..
‘.-.
,.
GROUP WEIGHT STATEMENT
PAGE
HIL-STD-1374‘PAR-T
I - TAB
USEFUL LOAD AND GROss WEIGHT
MODEL ..
.
NAME
REPORT
DATE
LOAD CONDITION
115
116
117 CREW (NO.
)
118 PASSENGERS (NO.
)
GALS.
LOCATION
TYPE
119 FUEL
120
UNUSAELE
INTERNAL
121
122
123
124
125
FXTERNAL
126
127
128 OIL
129
TRAPPED
ENGINE
130
131
132 roEL TANXS (LOCATION
)
GALS,)
133 WATER INJECTION FLUID “ (
134
135 BAGGAGE
136 CARGO
137
,
138 GUN INSTALLATIONS
. .
:TY CALIBER
GUNS LOCAT.FIX.ORFLEX.QUANT:
139
.“
.140
.141
AMMo.
142
143
144
SUPPvTS*
145
.
146
WEAPONS INSTALL. **
147
148
Iibq
150
151
152
,153
154
.,
155
156
157
158
159’
,160
.161
.162 SURVIVAL KITS
163 LIFE RAFTS
.. .
164 OXYGEN
.,,
..
.165 MISC.
.
166 .
,i67
,168
,.
+
169 TO AL USEFUL LOAD
170 WEtGHT EMPTY
1/1 GROSS WEIGHT
* IF REMOVABLE AND SPECIFIED AS USEFUL LOAD.
**LIsT sTo~s, MIssILEs, soNoBuoys, ETC. lW1.CIWED BY RAC’K$,LAUNCHERS,.CHUT”ES,ETC. THAT ARE NOT
PART OF WEIGHT EMPTY. LIST IDENTIFICATION,LOCATION, AND QUAiiTITYFOR ALL.ITEMS SHOWN
..
...’
INCLUDING INSTALIiATION,
4
I
●
I
Downloaded from http://www.everyspec.com
,,
MIL.{:TD-137hPART I - TAB
N~,!
DATE~
GROUP WEIGHT STATEMENT
DIMENS1ONAL AND STRUCTURALDATA
PAGE
MODEL
REPORT
I
II
5
1“
Downloaded from http://www.everyspec.com
, ..
MXL-ST.D-1374- TAE
NAM’
DATE
GROUP WSIGHT STAT~~
DIMENSIONAL AND STRUCT~
(CONTINUED)
‘.
DATA
“
PAGE
MODEL
REPORT
‘0
:.
“o,
\
6
“m
I
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART I - TAE
NAME
DATE
1
2
3
4
5
6
7
8
9
10
11
PAGE
MODEL
REPORT
GROUP WEIGHT STATEMRNT
DESCRIPTION OF DIMENSIONAL
AND STRUCTURAL DATA
1
I
REFERTO PAMGRAPH 5.1.1.4 O*
DETAILED REQUIFSMENTSFOR INSTRUCTIONSFOR USE
I
12
,+
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27 I
28 ]
29
30
31
32
?3
3
- 32
36
37
38
39
40
41
49
43
44
45
46
’47
48
49 I
50
51
52
53
54
55
56
.,
I
.
I
I
I
I
I
I
..
7
Downloaded from http://www.everyspec.com
1
I
I
I
I
I
THE AIRFRAME UNIT WEIGHT ~0 BE ENTE$ED ON LI~E.-56OF P~GE 6 OF T@E GROUP !@IGHT
STATEMRNT SHOULD BE DERIVED’BE~OW IN DET/iILSHOWING THOSE I@MS DEDUC@ED FROM !@IGHT
EMPTY. THE ITRMS BELOW FOLLOW rHE DEFIN~TION OF 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$NOT TO R$SCONFUSEtiWITH
WORK BREAKDOWN STRUCTURE (WBS) AIRFRAME kOST DEFI~TION.
1
I
1
f
I
I
I
WEIGHT RMJ’TY
I “i
1
I
I
1
L
I
DEDUCT THE FOLLOWING ITEMS IjESCRIBEDiNP&T
1
I
I
I
I
I
1
1
11!
I
..
1 [WHEELS BRARES, TIRES & TUBES
2 IENGINES - MAIN AND AUXILIARY
I
3
RUBBER OR”NYLON FUJILCELLS
4
STARTERS - MAIN ~
P
ld~s
F
.
i
I
1
1
1
i
i
1
!
i
I
I
1
I
!
1:
‘9 AVIONICS
10 TLTTS
,
I
1’
I
& POWER OPERATED MOUNT~
.
I
I
I
I
I
:,
11 AIR CONDITIONING,ANTI-ICING Al@ PRESSURIZATIONUN!TS & FLUiDS
12 CAMERAS & OPTICAL”VIEWFINDERS I
-
I
!
I
1
I
I
IAIPXMME UNIT WEIGHT
I
I
1
I
L
~
lNOTES FOR 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 N CONTY~uous w IN~ ~D
ALL OTHERS.
****NosE To AFT TIp ,oFFusE
8
3’+
,=
I
I
I
Downloaded from http://www.everyspec.com
,
MIL-STD-1374A
i
:
.
PART
II
DETAIL WEIGHT STATEMENT
.-.
,
/
,.
..
Downloaded from http://www.everyspec.com
.
.
\
W#
Downloaded from http://www.everyspec.com
I
PAGE
MODEL
REPORT
MIL-STD-1374 PART II-TAB
NAME
DATE
I
,.
I
I
I
\
I
“o
:
I
-.
1’
L
Downloaded from http://www.everyspec.com
,.,
.
,.
WING-GROUP
BASIC STRUCTURE
MIL-STD-1374 PART II-Tin”
NANE
PAGE
MODEL
REPORT
DATE
1
2
3
4
5.6
‘7
8
9
10
11
12
13
14
15
.’r6
.17
18
19
20
21
’22
23
24
25
26
OUTER
PANEL*
I CENTER INTERN
I-SECTION* PANEL*
UPPER
-SPAR CAPS 6 SPAN. STIFF.
‘-COVERINCL.INTGRL.STIFF.
-JOINTS, SPLICES & FAST:
-DOORS& PANELS (STRUCT)
GLOVE
***
,.
1“
. .
.
I
LOWER
-SPAR CAPS & SPAN.STIFF.
-COVRR INCL.INTGRAL.S’TIFF.
-JOINTS. SPLICES & FAST.
-DOORS & PANBLS (STRUCT)
.
SPAR WEBS & SHEAR PANELS
-JOINTS. SPLICES & FAST.
-DOORS & PANELS (STRUCT)
,.-,
,.,
I
INTERSPAR - RIBS
-BULRHEADS
-CHORDWISE STIFFENERS
-JOINTS, SPLICES 6 FAST.
●
✎✎
✎
✎✌✌
*
IDENTIFY LOCATION BY’BUTTLINESOR SPANWISE STATION.
coDE sANDWIcH PANELS TO THE COVER.
FULL
DEp~
C(JM o~y+
***INcLuDE BAsIc FLIGHT oR LANDING LoAI)CARRYING STRUCTURE ONLY.
,**
INCLUDE
.,
2
Downloaded from http://www.everyspec.com
—
MIL-STD-1374 PART II-TAB
NAME
DATE
WING GROUP
SECONDARY STRUCTURE
DOORS, PANELS AND MISCELLANEOUS.
1
2
3
4 WING FOLD
5
xx
&
8 DOORS & FRAMES
9
-IANDING
10
11
-STORES
12
13
-MISSILE
14
15
-GUN
16
17
-AFn40
.
18
19
-FUEL
20
21
22
-ACCESS
23
24
.25
26
.27
28 PANELS-NON STRUCTUUL
I
I
PAGE
MODEL
REPORT
.
31
32
35
~
-.
31
38
39
40
41
42
43
44 zLOVE
45
46 aALKWAYS, STEPS. & GRIPS
47
48 FAIRING 6 FILLET (IDENTIFY)
.49
50 I
51 bTATIC DISCHARGERS
52 ~TERIoR FINISH
,53 kNTERIOR (INCL.
LB.SEAL.)
541..
55
56 kOTAL-5EC~E
1
.
.
~ DESCRIBE THE TYPE OF POWER USED FOR ACTUATION: HYDRAULIC - H, ELECTRICAL - E, PNEUMATIC - P.
- c.s.,op., I.P., ETC.
k*DEscRIBE~JoR DooRsMD P~Ls BY sy~oLS I.E. LocAT_foN
3
-3$
Downloaded from http://www.everyspec.com
s,,
,..
..$,
. .,
,.
MIL-STD-1374 PART II-TAB
NAM)?,
,’
DATE
I
I
;1
lx
AILERONS
XX
iP01LER5
x
INBOARDI OUTBOAIUl[
INBOARD 10UTBOARi)l
I
-.
,2
i
4
I
I
I
Downloaded from http://www.everyspec.com
I
MIL-STD-1374 PART II-TAB
NAME
DATE
1
2
3
4
5 SPARS
6
7 COVER INCL. STIFFENERS
8
9 RIBS
10
-FLAP TRACK / HINGE SUPT
11
-AIL. HINGE SUPPORT
12
-OTHER
13
14 CORE * -(HONEYCOMB TYPE)
15
-BONDING ADHESIVE
16
17 T.E.STRIPS
18
.
19 FABRIC & DOPE
. 20
21 TABS
22
J2
JOINT. SPLICES. FASTENERS
24
?5
9
26
27
?8
29 BALANCE WSIGHTS & SDPPORTS
30
31 AERO.SEAL
32
33
34 CONTROL HORNS
35
36
37 ACCESS DOORS
38
39 HINGES & PINS
, 40 EXTERIOR FINISH
41
42
43
44
45 SUPPORTS - HINGES
46
- BRACKETS
47
- TRACKS
.48
- CARRIAGES
49
- ROLLERS
50
5
52
53
54 COLOMN TOTALS
55 TOTALS OF SURFS AND SUPTS
56 TOTAL-CONTROLSURFACES PAGES
57 TOTAL-WING GROUP - PG 2-4A
*INCLUDE FULL DEPTH TYPE CORE OhLY.
WING GROUP
CONTROL SURFACES
CONTD.
PAGE
MODEL
REPORT
x
xx
T.E. FLAPS
L.E.FLAF 3R SLAT
INBO@D
OUT~OARD
SURFACE SUPPORTS SURFACE SUPPORTSI SURFACE SUPPORTS,
-
1
CODE SANDWICH PANELS TO THE COVERS.
i
I
Downloaded from http://www.everyspec.com
●
-.
-.
MIL-STD-1374 PART II-TAB
NAME
DATE
ROTOR GROUP
BLADE ASSEMBLY
1
2
3
4 SPAR - FRONT
5
-INTERMEDIATE
6
-REAR
7
-JOINTS, SPLICES & FAST.
8
9
10
11 INTERSPAR - COVER & STIFF.
..
~
~
13
-CORE
14
-JOINTS. SPLICES & FAST.
15
16
17
~
LEADING EDGE
19
-MEMBER
&
~ - VER &
21
-RIBS
22
-CORE
23
J~~T.
24
25
?6
27 TEATTTNC EDGF
?R
29
30
-STIFFENERS
31
-RIBS
32
-CORE
33
-JOINTS, SPLICES & FAST.
34
35
36
37
38
39
40 TIPS - IF NOT INTEGRAL
41 INTERNAL DUCT STRUCTURE
42
43 FAILURE DETECTION
44
45 BAIANCE NEIGHTS - TIP
46
- LEADING EDGE
47
, 48
49
50 ROOT END ATTACHMENT
51
-FITTINGS
52
-FASTENERS
53 EXTERIOR FINISH
. 54
55
COLUMN TOTALS
56 TOTAL - BLADE ASSEMBLY
PAGE
MODEL
REPORT
“,
‘
,.
.
..
I
I
I
.
. .
I
5
&
.
...
Downloaded from http://www.everyspec.com
.
,. ...
.,
.
.
,.
..’,
.,,
MIL-STD-1374PART 11-TAl”
NANE
DATE
ROTOR GROUP ..
HUB.AND HINGE
1 ‘1
1.XHUB
2 I
I
3 ,
,.
4 HOUSING
5 GIMBAL RING
6 YOKE
7 UNIVRRSAL JOINTS
8
9
10
‘
11
12
13 BEARINGS
14 SEALS. SPACERS & RETAINERS
15 BLADE GRIPS’
16 BAU.NCE WEIGHTS
17 STOPS
18 LUB SYSTEM INCL.
LBS.OIL
-19 FAIRI??GS& DUST COVERS
-20 GREASE
21
22
-23
24
~
&
..
.26 PINS
27 LINKS
28 DAMPERS OR RESTRAINERS
29 DRAG BRACE’
30 lTENsIONsmw
AsssI.G3Ly
31
I
99
PAGE “ ‘
MODEL
REPORT
XX”.
HINGE & BLADE RETENTION
IFLAPPINGI LEiD-LAGl PITCH I BLD-FOLDI
!
..0
x
1
1
!I ,.
.)
-.
...
. . .
1.
.,
,.
. .
I
;;
34
-35
36
.37”
38
39
40
41
42
43
44
’45
46
47
48
SHAFTS
PITCH ARMS
BLADE FOLD NECH.
.,
.-.
-SUPPORTS
VIBRATION ABSORBERS
,..
49
50 FAS_
.51
;52
,.
.,,
54
.55” COLUMN TOTALS
I
56 TOTAL - HUB & HINGE
TOTAL-ROTOR GROUP - PG 5($6
b
*MAIN DISTRIBUTIONPOINT TO ACTUATING UNIT.
1
6
J%4
Downloaded from http://www.everyspec.com
TAIL GROUP
BAkIC STRUCTURE
.,
MIL-STD-1374 PART II-TAB
NAMR
DATE
1’1
I 2
3
4
5
6
7
8
1 19
PAGE
MODEL
REPORT
IX HOR.STABILIZ. XX
FINS
ICTR.SECT ]OUTR.PNL] VERTICALI DORSAL
x
Ivlmwl
1
UPPER
-SPAR CAPS & SPAN.STIFF.
-COVER INCL.INTGRAL.STIFF.
-JOINTS, SPLICES & FAST.
-DooRs”& PAtiEL5(STRUCT)
I
4
I
I
I
I
I
*INCLUDE FULL DEPTR TYPE COW. oNLy. CODE SANDWICH PANELS TO THE COVERS.
7
I
I
I
Downloaded from http://www.everyspec.com
,.
.,
.,
. .
@
MIL-STD-1374’PARTII-TAB
NAME
DATE
1
2
3
4
5
6
7
8
9
TAIL GROUP
SECONDARY STRUCTURE
DOORS, PANELS AND MISCELLANEOUS
X HOR.STABILIZ. XX
CTR.SECT OUTR.PNL VERTICAL
..
,
1
●
I
1
I
I
.,
t
,
34
35
. 36
37
x
VENTRAL
:
I
?7
28
29
30
31
32
33
-,
FINS
DORSAL
** *
AREA
,.
LOC P SQ FT
FOLD-STRUCTURE
-MECH. & CTLS.
-POWER TRANS.
-ACTUATOR & LOCK
.
-EF53RGENCY
10
11
12
13 DOORS & DOOR FRAMES
14
15
16
17
-ACCESS
18
19
20
21
22
23
24
25
26 PANELS-NON STRUCTURAL
\
PAGE
MODEL
REPORT
WALKWAYS. STEPS. & ~PS
. 38
39
b 40
1
~
&l
42
43
44
.45
46
47 STATIC DISCHARGERS
48
, 49 EXTERIOR FINISH
50
51 INTERIOR (INCL.
52
53
54
55
,.
I
I
LB.SEAI,)
I
I
I
I
I
I
COLUMN TOTALS
56 TOTALS HORIZ. STAR, FIN & DORSAL
TOTAL-SECONDARYSTRUCTURE
* DESCRIBE THE TYPE OF POWER USED FOR ACTUATION: HYDRAULIC - H, ELECTRICAL - E. PNEUFL4TIC- P.
**DEsc~IBE MAJOR DOORS AND PANELS BY SYMBOLS, I.E., LOCATION - C.S., O.P., I.P.; ETC.
8
‘e
Downloaded from http://www.everyspec.com
●
MIL-STD-1374 PART II-TAB
NAME
DATE
1
I
=
..
.
TAIL GROUl”
CONTROL ‘SURFACES
PAGE
MODEL
REPORT
lx
3
4
5 SPARS
6
I COVER INcI.,.
STIFFENERS
8
9
10 RIBS
11
12
13
14 CORE *15
-BONDING ADHESIVE
16
17 T.E. STRIPS
18
19 FABRIC & DOPE
20
21 TABS
22.
23
24
25 TORQUE TUBES
2627
28
29 BALANCE WEIQSM & SUPlQ13TS
,30
31 AERO.SEAL
32
33
.34 CONTROL HORNS
35
36
37 A~
38
39
A PTNS
EXTERIOR FINISH
40
41 JOINTS, SPLICES, FASTENERS
42
43
44
45 sUPPORTS - HINGES
46
- BRACRETS
47
48
.49
50
.51
52
53
54
55 cOLOMN TOTALS
56 hOTAL FOR EAC
Rxx
K
ELEV$TORS
CE@’ER
OUT40ARD
SURFACE SUPPORT~ SURFACE SUPPORTS SURFACE SUPPORTS,
.
.
I
I
.,
,.
..,.
. .
.
kINCLUDEFULL DEPTH CORE ONLY. CODE SANDWICH PhTELS TO TRE COVERS.
f“-
.,.
9
..
-’P’
Downloaded from http://www.everyspec.com
MIL-STD-1374PART XI-TAi
NAME
TAIL GROUP
ROTOR GROUP
10
PAGE
MODEL
●
I
Downloaded from http://www.everyspec.com
,“.
..’
,“,
,,
,,
,“
.,,
,,
,
1
.’
x
2
SECTION
.
STATION
.3
4
BULKREADS & FRAMES *
c
2
1
6
7
,,,
8
,,
,.
!.
9
.-f
10
11
1?
13
14
15
16
17
18
,
19
20
21
22
23 ‘
24
MINOR FRAMES
25
JOINTS, SPLICES & FAST. “
76 1
;;
COVER-UPPERBETWEEN LONGN.
‘
28
-SIDE BETWEEN LONGERONS
29
-LOWER BETWEEN LONGERONS
-30
31 ‘cOVER LONGL.STIFF.-UFPER
32
“ -SIDE BETWEEN LONGERONS
33
-LOWER BETWEEN LONGERONS
34
35
LONGERONS - UPPER
36
-SIDE
37
-LOWER
.
38
39
LONGITUDINAL PARTITIONS **
40
F
s **
41
KEEL **
42
DOORS & PANELS (STRUCT) **
43
44
FLOORING-& SUPPORT **
45
FIREWALL **
46
PALLET RAILS & SUPPORT **
~~
47
LR
50
51
52
.53
54
,.
.,
BODY GROUP
BASIC STkUCTUiE
$
ii
.$
,“
MIL+iTD-1374’PART II-TAB
lJA14E
DATE
.
,.
,,
).
PAGE
MODEL
REPORT
FUSELAGE OR HULL
-
XX BOOMS
,-
,
I
.,
.
...
r.
.
I
I
,.
ROTOR SUPPORT
PYLON
STEP ASSEMBLY
TOTALS
FOR FUSE OR HULL
S4
57
TOTAL - BASIC 4TRUCTURE
LIST 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?
,“
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART 11-TAE
NAME
DATE
BODY.GROUP
SECONDARY STRUCTURE
*IDENTIFY POUNDS OF BULLET OR BIRD PROTECTION INCLUDED.
,
12
‘
PAGE
MODEL
REPORT
Downloaded from http://www.everyspec.com
● ✎“
MIL-STD-1374 PART II-TAB
NAME
DATE
1
.
** *
x
OPERATING MRCHANISM
xx
1 I
2“
LO P AREA STRUCT
POWER ACTUATOR
MECR 6
SO FT
3
CONTROLS TRANS. LOCKMECH
4
5
DOORS & DOOR FRAMES
6
-ALIGHT.GEAR
7
8
-STORES
9
10
11
so~s
1?
13
-MISSILES
,14
-GUNS
15
-AMMo
16
-FUEL
.17
.18
19 I -ESCAPE
20
,21
22
-COMPARTMENT
.24
25
26
77
78
29
31
32
33 ,
I
1.
‘o
BODY GROUP
SECONDARY STRUCTURE (CON’T)
(DOORS, RAMYS, PANELS 6 MISC.)
PAGE
MODEL
REPORT
x
EMERG.
-ENTRANCE
E
-LIFE RAFT
-CAMFJU
-ACCESS
34
35
36
RAl@s
37
38
**
-39 FAlw&(&Qh -- TRU~)
40
41
LADDERS (RETRACTABLE)
I
4.2
WALXWAYS. STEPS, GRIPS
,43
44
PYLON I BOOM FOLD
,45
46
FAIRINGS
47
48
49
50
51
52
EXTERIOR FINISH
LB.SEAL)
INTERIOR (INCL.
I
,53
I
1
I
I
I
54
I
I
55
COLUMN TOTALS
56
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.
13
Downloaded from http://www.everyspec.com
,.,,,,
.,, ,
.
.
,, ,..
.
,’
.
,,
,.
,.,’
.
MIL-$TD-1374 PART II-TAB
NAM”
DATE
.
,-
.
ALIGHTING GEAR GRoup
(INCLUDINGLAUNCH AND RECOVERY.GEAR)
PAGE
MODEL
REPORT
“e.
,’
.,
.
,,
/.
&
1
I
1
I
I
I
~
5
TOTALS FOR UN
AND NOSE
PAGE TOTAL
5;
*“’’fiPE”REFERS TO hWETHER THE GEAR IS TR.AILINGAM, conventional,ART1c~TzNG,
**INPUT.”FT/LBSPER.BkiRE TIMES 1o-6.
IN ‘fHECASE OF AN AIRCRAFT WITH OUTRIGGERS,’
ADD ANOTHER PAGE (14A).
14
%
I
ETC,
I
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART ‘II-TAB
NAME
DATE
ALIGHTING GEAR GROUP
CONTROLS
PAGE
MODEL
REPORT
.
I
.53
.-. .,
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART II-TAR
NAME
.
DATE :
ENGINE SECTION OR NACELLE GROUP
PAGE”’”
MODEL
RSPORT
,’
16
I
,,
m
I
I
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART II-TAB
NAME
DATE
.
1
2
3
4
5
6
7
8
9
AIR INDUCTION SYSTEM GROUP
PAGE
MODEL
REPORT
STRUCTURE
OPERATING MECHANISM
mm
POWER ACTUATOR4 EMERG
CONTROLS TR4NS, LOCK.MECH~
INLET LIPS
FIXED DUCT STRUCTURE
FRAMEs
COVERS
.11
ATTACHING ANGLES ETC.
12
13
14
RAMP STRUCTURE
15
FIXED
VARIARLE
16
17
18
BELLMOUTH
19
-CONTROLS
20
.21
PLUG
~
~
23
PLUG C~S
24
75
26
27
SPIKE CONTROLS
28
29
.30
ENGINE DOMES
31
NASTER CONTROLS
32
33
34
DOORS
.-.
.
37
G
38
39
&o
41
42
43
44
45
46
MISC.
47
WATER INJECTION
48
HEAT PROTECTION
49
SCREENS
PARTIAL SEPARATORS
50
51
52
EXTERIOR FINISH
,53
INTERIOR FINISH
54
.55
.56 I
,57 I TOTAL-AIR INDUCTION SYSTEM GROUP
17
“55
,.
TOTAL
I
.
Downloaded from http://www.everyspec.com
,.
,,
.“,,
. ..-.
.,
,-
,’
.
,,
...’
,.
,,
MIL-STD-1374 PAitTII-TAR
NAME
DATE
PROPULSION GROUP .
.,
PAGE
MODEL
REPORT
~ ,~’
I
I
I
‘e
1
,..
1.
1
I
*“ISOLATE NA.JORCONTRACTOR FURNISHED AREAS OF INSTALI.ATION
E.G. NOZZLES, THRUST REVERSERS,
INFRA-RED, NOISE SUPPRESSORS,ETC.
I
**propeller
G~R Box MD ~TENSION s~T
J
oNLy.
I
1’
18.,
o
Downloaded from http://www.everyspec.com
,,
.’
,:
,.
.’.
,,
,.
.,
,.,
,.
MIL-ST*1374 PART 11-TAE
.NAME
PROPULSION GROUP
, LUBRICATING & FUEL SYSTEM
.,,.
PAGE’
MODEL
I
,.
.
I
57.1
J
k INDICATE TYPE AS TO SELF SEAL, BLADDER, ALUMINUM, ETC. WITH TOTALS SHOWN FOR PROTECTED AND
UNPROTECTED TANKS.
..
**lDE~IFy As p~ssIfRE (p) OR Gravity’.
. ..
19
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART II-T*
w,
DATE
‘
PAGE
MODEL
:
RJ3PORT
PROPULSION GROUP
DRIVE SYSTEM - ,PONERTRANSMISSION
TO ROTORS, FANS, ‘ORPROPS
r
IL
[
u.
I
SE.-., ...GEARS - DR
- np
7
8
a
.
.,
t
“18
19
?0
21.
?’+
Pms
2’4
s
75
26
=BLOWER SYSTEM
-PLUMBING
27
-OIL
‘28
29
30
31
32
ROTOR BRAXE
33
34
.35
36
.37 FREE NHEELING DEVICE
38
DEPRASING UNIT
39
.40
.’41
42
43
44
45
SUPPORTS
-GEAR BOXES
46
47
LUBRICATING SYSTRM
48
ROTOR BRAKE
&q
50
51
52
DRIP PAN
EXTERIOR FINISH
53
54
55
COLUMN TOTALS
PAGE TOTAL - DRIVE SYSTEM.
56
1
C7
J,
.
I
i
1
I
A G~R
Box
IDE~TIFIcATIoN
IN THE c(jJ.,mHEADINGS, ‘ANDDO LIKEWISE ON,A SUPPLEMENTAL
PAGE 20A IF IT IS REQUIRED FOR AN Auxiliary DRIVE SYSTEM.
*INSERT
20
J
Downloaded from http://www.everyspec.com
,’.
,,
O
.
,,
.,
,,
MIL-STD-1374 PART II-TAB
NAUS ,.
DATE
1
7
,3
.
PROPULSION GROUP
DRIVE SYSTEM - POI@TRAIiSMISSION
TO ROTORS, FANS OR PROPS
m,..,”.
Luril
,
x
ENGINE
BOX
*t~oM; ,
*TO
“.
L
TIL4.NSMISSION
DRIVE
BOX
BOX
I
BOX
I
BOX
I
PAGE
MODEL
REPORT
X
ROTOR
SHAFT
BOX
,
BOX
I
JET
I DRIVE
1
.
42
43
~
46
h7
u
$n
51
52
53
54
55
56
COLUMNTOTALS
TOTALFORTl+ANSMI~
I
klNSERT
A GEARBOX IDENTIFICATION
IN THECOLUMNHEADINGS,
ANDDO LIKEWISE
ON A SUPPLEMENTAL
PAGE 21A IF IT IS REQUIRED FOR AN AUXILIARY DRIVE SYSTEN.
21
3? ,,,
.’
1-
Downloaded from http://www.everyspec.com
.,.
.
,.,
MIL-STD-1374 PART II-TAR
NAM21
DATE
‘
~IGHT coNT~6Ls GRQG’”
COCHPIT & AUTO FLIGHT CONTROLS
,..
~AGE.
,
MODEL . .,.’
REPORT
I
I
,’
4,
I
,.
. -.
,-
*FROM MAIN DISTRIBUTIONPOINTS TO ACTUATING UNITS.
.’
z~.,
I
Downloaded from http://www.everyspec.com
MIL-iTD-1374 P+lT II-TAB
NAME
DATE
%
,,
1
FLIGHT CONTROLS GROUP
SYSTEM CONTROE
FIXED WING SYSTEMS
x
2
3
TYPE*
.,
4
5 MECHANICALOPER.MECH.
6
CONTROLS
7
TENSIONREGULATORS
8
ACTUATORS
9
10 ELECTRICALOPER.MECH.
11’
CONTROLS
12
CIRCUITRY.**
13
OPEWTING MOTORS
14
MECHANISM
15
16
17 HYDRAULICOPER.MRCH.
18
CONTROLS
PLUMBING**
,19
20
ACCUMULATORS
21
ACTUATORS
22
MECHANISM
**
23
,24
25
H.
26
c~
27
PLUMBINGOR DUCTING**
?8
29
BOTTLES(AIR)
ACTUATORSOR NOZZLES
.30
MECHANISM
.31
32
33
34 lARTIFrc1fiFEEL
BOB WEIGHT
35
.36
.37 DAMPING
38
39
40
41
42
MECHANICALOPER.MKH.
43
ELECTRICALOPER.MECH.
.!$4 HYDRAULICOPER.MSCH.
.,
45
46
TRIM CONTROLSUPPORTS
,47
48
49
50
51
53
54
55
56
LATERAL *
X LONGI-
DIRECTUDINAL*ITIONAL*
WING
POSITIONING
I
I
..
I
I
1.
SUPPORTS: GUIDESJL2C.
ILING
PAGE
MODEL
REPORT
I
I
.
-1
BODY
COLUFOlTOTALS
TOTAL - SYSTEMS CONTROL PAGE
1
i
-
)
,
ETC. AND TYPE OF POWER - POWERED (P)
* IDENTIFY THE TYPE OF CONTROL SURFACE - AILERON, FLAIIERON,.
OR BOOST (B).
**FROM MAIN DISTRIBUTIONPOINTS TO ACTUATING
UiITS.
,.
J.
23
,.
J,,.
.. .
,,.
.
.
Downloaded from http://www.everyspec.com
:.
,.’
.,
..
,,
,“
..
FLIGHT CONTROLS GROUF
SYSTEM CONTROLS
MIL-STD-1374 PART II-TAB
NAME
FIXED WING SYSTEMS- CONT.
DATE
,.
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
‘“
.
.,
,-““<
... . .-.
I
Downloaded from http://www.everyspec.com
e
MIL-STD-1374 PART II-TAB
NA??
DATE
45
46
.47
48
49
50
51
52
53
54
55
56
HYDRAULIC OPER. MECH.
TRIM CONTROL SUPWS
FLIGHT kONTROLs GROUP
SYSTEMS CONTROLS
ROTARY WING SYSTEMS
,.
I
I
PAGE
MODEL
REPORT
I
1
I
SUPPORTS. GUIDES. ETC.
WING
L
.- ODY
COLUMN TOTALS
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
I
.,.
.,
-
Downloaded from http://www.everyspec.com
‘o’
MIL-STD-1374PART I - TAB
NAME
DATE
4
1
2
3
L
5
MIXING
~E*
ROTORIFAN NACELLE
lATTITUDEIA~E
1
I
1“
1.
I
1“
I
27
28
29.
30
31
32
33
34
35
36
37
38
?9
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
I
1
I
!
... .
.
PNEUMATICS OPER. MECH.
CONTROLS
PLUMBING OR DUCTING **BOTTLES (AIR)
‘
ACTUATORS OR NOZZLE-.
MXCHANISM
-- . .
.
,
,.
ARTIFICIAL FEEL
BOB WEIGHT
DAMPING
.
,,
TRIM CONTROLS
MECHANICAL OPER. MECH:
ELECTRICAL OPER. MECH.
HYDRAULIC OPER. MECH.
,“
TRIM CONTROL SUPPORTS
SUPPORTS. GUIDES. ETC.
NG
-TAIL
-BODY
.
,.
I
I
“,
I
I
I
COLiMN TOTALS
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
!
I
MECHANICAL OPER. MECH.
CONTROLS
TENSION REGULATORS
ACTUATORS
6
7
8
9
10 ELECTRICAL OPER. MRCH.
CONTROLS
11
CIRCUITRY **
12
OPERATING.140TORS
13
MECHANISM
14
15
16
17 HYDRAULIC OPER. MECH.
CONTROLS
18
PLUMBING **
19
ACCUMULATORS
20
ACTUATORS
21
MECHANISM
22
ID **
23
H
26
PAGE
MODEL
RBPORT
FLIGHT CONTROL GROUP
SYSTEMS CONTROLS TRANSITION
V/STOL SYSTEM
I
I
I
,,
I
Downloaded from http://www.everyspec.com
MIL-STD-1374PART II - TAE
NAME
DATE
1
2
3
4
5
6
8
9
10
r 11
12
13
14.
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
AUXILIARY POWER PLANT GROUP
ENGINE OR POWER UNIT MODEL
ENGINE
ENGINE SUPPORTS
AIR INDUCTION SYSTEM
EXHAUST SYSTEM
HYDRAULIC SYSTEM-PLUMBING
-FLUID
COOLING SYSTEM
LUBRICATING SYSTEM
PLUMBING
OIL
FUEL SYSTEM
TANKS (VOL.
GALS.
CONTROLS
STARTING SYSTEM
41
42 FIRE BARRIER
43
44 FIRE EXTINGUISHINGSYSTEM
,.
45
46 INSTRUMENTS
47
48 ELECTRICAL SYSTEM
49
50
51
52
53
54
1 TOTALS
55 COLUMh
57
I
27
PAGE
MODEL
REPORT
I
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART II - TAR
NAME
DATE
1 FUNCTIONAL GROUP, ITEMS
2 ANO QUANTITT
3
4
‘5
6
7
8
9
10
.11
, 12
13
14
15
16
17
. 18
19 I
20
21
22
23
- 24
25
6
:7
28
, 29
30
31
32
33
- 34
35
36.
X INDICATOR
X
X GFE
CFE x
“o
PAGE
MODEL
REPORT
INSTRUMENT GROUP
TRANSMIT & AMPL
GFE
CFE
X INSTALL
x
9
-,
.
0“
.,
~
. 38
?9
40
- 41
42
43
44
, 45
.46
47
48
49
\
50
51
52
/ 53
I
I
I
I
54
,.
55 COLUMN TOTALS
I
56 TOTAL - PAGE
, 57 TOTAL - ~P
*LIST ITEMS BY FUNCTIONAL GRoUPS (FLIGHT, ENGINE, AND MISC.) LIST SUB-GROUPS BY CREW STATIONS.
ADD SUPPLEYIENTARY
PAGES 28A IF THEY ARE NECESSARY. CODE NAVIGATIONALEQUIPMENT TO FURNISHINGS
PAGE 35.
28
(4!(.(
-.
I
Downloaded from http://www.everyspec.com
MIL-STD-1374PART II - TAB
NAMs
DATE
,
1
2
3
4
5
6
7
PAGE
MODEL
REPORT
HYDRAULIC AND PNEUMATIC GROUP
x
PLT. CON I
SYSTEM PRESSURE (PSI)
1
xx
HYDRAULIC *
PNEUMATIC * X
IUTILITY !EMERG, UTILITY IMERG.
I
I
I
I
PUMPS & COMPSRS. OTT. MODEL
,
-1
t
9
10
11
12
RR40TE PUMP DRIVES
QTY. CAP. EA.
13
14 RESERVOIRS
..
1
I
9
T
FOR EACH MODULE AND IDENTIPY IT.
29
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART’11 - TAB
NAME
DATE
ELECTRICAL GROUP *
1
2
3 POWER SUPPLY KVA AMP QTY
4
GENERATOR-MAIN
5
-AUK.
6
-EMERG.
7
coNsTAwT SPEED DRIVE
8
REMOTE GENERATOR DRIVES
9
’10 COOLING-~N. & GEN. DRIVE
(AN
)(NO. )(An )
12
BATTERY CONTAINER & SUPT,
13
14 PWR CONVERSION KVA AMP QTY
15
INVERT. (DC-AC)
16
cowvRT. (Ac-Dc)
17
TRANSFORMER
18
TRANS. RECTIFR.
19
FREQNC. CONVRT.
20
21
22 PWR. DISTRIBUTION & CNTLS.
23
GENERATOR CONTROL BOXES
24
CUTOUTS & VOLT. REGULATORS
25
AMMETERS k VOLTMETERS
26
SWITCHRS. RHEO.. SW. PANELS
27
CIRCUIT B~
& FUSES
8
;9
RRCEPT. & CONNECTOR PLUGS
30
RELAYS
WIRING
31
32
CONDUIT
33
34 LIGHTS & SIGNAL DEVICES
35
LIGHTS - INTERIOR
36
- EXTERIOR
37
- LDG.-TAXI (INCL. MECR.)
38
SIGNAL DEVICES - LIGHTS
42
43
44
45
46
47
48
49
50
51
52
53
54
PAGE
MODEL
RXPORT
AC(HZ
)(VOLTS
) DC(AMP)
(VOLTS )
..
:S
EOUIPMENT SUPPORTS
- WING
- TAIL
- BODY
- NACELLE
FURNISHES POWER FOR-(ITEMS)
-
.
56 ;$;() - PAGE
- ELECTRICAL GROUP
7
*INCLUDES THE SYSTEM FROM THE SOURCES OF POWER TO THE MAIN DISTRIBUTIONPOINTS.
30
I
Downloaded from http://www.everyspec.com
e
MIL-STD-1374PART 11 - TAE
NAM3
DATE
AVIONICS GROUP
1 “EQUIPMENTCOMPONENTS AND
2 PART NOS. OR IDENTIFICATION
3 LIST BY FUNCTIONAL GROUP
*
“4
5
6
,’
7
“8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
73
‘?
.Z
X
EQUIPMENT
GFE
CFR
PAGE
MODEL
REPORT
XK INSTALLATION
GFE
CFE
X
;2
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
.42
43
44
45
k 46
47
.,
TABLES
bR
49
RACKS. SHELVES, & SUPTS.
50
LOCKERS
51
PODS (IF NOT U.L.)
52
CRASH DATA RECORDER
53
54
I
55
.. COLUNN TOTALS
i
561 TOTAL - PAGE
571 TOTAL - AVIONICS GROUP PG 311
*LIST THE CONTINENTS (INCLUDING~TENNAE, SWITCHES, RELAYS, FILTERS, ETC.) FROM THE MAIN DISTRIBUTION POINTS TO THE UNIT OPERATED BY A FUNCTIONAL GROUP (E.G. COMMUNICATIONS,VHF SRARCH, NAVIGATION. INTERCOMMUNICATIONS,ETC.). DO NoT INCLUDE NOsE ~o~s.
ADD supplementarypAGEs 31A
IF IT Ii NECESSARY;
II
31
.-.
L(2
Downloaded from http://www.everyspec.com
.,
,,
MIL-STD-1374PART II - TAB
NAME
DATE
ARMAMENT GROUP
(GUNS, TURRETS, ARMOR,
& SUBMARINE DETRCT.)
PAGE “
MODEL
REPORT
,,
.:<
a
e
.
I
*
DESCRIPTIVE LOCATION E.G. 20NM GUNS (2) NOSE, TURRET-NOSE,SONOBUOYS (SSQ-15),AFT FUSELAGE,
S.U.S. (MK-50),ETC.
** LIsT components BY pAc~GED GRoups (TURRET sTRuCTuRE,Accessories, cIRcuITRY, ETc”.). ADD
SUPPLEMENTARYPAGES 32A IF IT IS NECESSARY.
***oTHER THAN IT~ ~2-16.
32
yo,
,.
Downloaded from http://www.everyspec.com
●
MIL-STD-1374PART 11 - ‘TAE
NAME
DATE
1 I
2
LOCATION *
3
&
5
6 EXPENDABLEWEAPONS
7
CONTROLS & PROVISIONS
8
-CONTROLS (SELECT)
9
10
-RELEASE OR LAUNCH
11
12
13
-JETTISON SYSTEN
14
15
-FUSING
16
17
-HEATING
18
19
20
21
22
23
24 IINSTALLATION**
25 ]
-RACKS (TYPE
NO.
26
27
a,.
29
3
31
32
33
34
35
36
37
~ 38
39
40
41
42
43
44
45
46
.-
PAGE
MODEL
REPORT
ARMAMENT GROUP
(EXPENDABLEwEApON provisions)
)
I
-PYLONS
-1.AUNCHERS
I
ORTS
-RAILS OR TRACKS
-PYLONS
* pRovIDE A Descriptive LocATIoN - E.G. BOMBS - FUSELAGE INTERNAL (MAX. SIX FIR-83),MISslLEs FUSELAGE EXTERNAL (MAX. FG’JRAIM-54A), MISSILES - WING EXTERNAL (MAX. TWO AIM-54A).
**IF NOT SPECIFIEII
As usEF~
LOAD.
ADD A SUFFLEMENTARYPAGE 33A IF IT IS NECESSARY.
o
33
Downloaded from http://www.everyspec.com
,.
,-
,MIL-STD-1374’
PART II - TAB
NAME
DATE
FURNISHINGS AND EQUIPMENT GROUi
ACCOMMODATIONSFOR PERSONNEL
1
2
3
4
5
6
7
8
9
10
.11
12
13
14
15
16
..
x“
PILOT
SEATS (MODEL
SEAT STRUCTURR
HEADREST
CUSHIONS ***
PAGE
MODEL
REPORT
.SRATS
COPILOT
*
*
xx
xx
x
MISC.
OXYGEN
ACCOM.
SYSTEN
)
,.
CATAPULT
ROCXET
DROGUE SYSTRN
STABILIZATIONSYSTEM
.,,
,,
BELT
HARNEss
INERTIA RREL
1
I
1
f
,.
1
a
:
.
>* IF THERE ARE MORE THAN 5 CREWMEMBERS,AND ADDITIONAL SPACE IS REQUIRED, ADD ADDITIONAL PAGE 34A.
** IF THEY ARE NoT spEcIFIED As usEFIJ’L
LO#J)oR spEcIAL EQuIpM~T.
***IF THEy ARE LocATED IN TRE sEAT AND ARE.NOT sPECIFIED AS USEFUL LOAD..
34
m.
,,,,
Downloaded from http://www.everyspec.com
MIL-STD-1374PART II - TAB
NAlm
DATE
0
/’
I
FURNISHINGSAND EQUIPMENT GROUP
MISC. EQUIPMENT,AND FURNISHINGS
PAGE
MODEL
REPORT
1
Misc.
2
EQUIP.
3
4 MISCELLANEOUS EQUIPMENT
5
PORTABLE PLATFORM/LADDER
6
71
DATA CASES & HOLDERS
I
9 1
u
MANUALS *
9
10
BALANCE COMPUTER & SUPT.
11
WRIGHING DEVICE-BUILT-IN
12
TOOL LOCKBRS
13
14
RAIN REMOVAL - WIPERS
15
- FORCED AIR
16
- CHEMICAL
17
WINDSHIELD WASHEFLS
18
19
RELEASE MECH.-TARGET TOW
20
21
BILGE SYSTEM
22
23
Rs
~
~ AUXI I
25
26
COCKPIT DISPLAY-CONSOLES
?7
-INSTRUMENTPANELS
7!7
-OVERHEAD PANELS
29
-SIDE CONSOLES
30
-CENTER CONTROL STAND
31
32
NAVIGATION - LOCKERS
33
-TABLES
34
-SHELVES
35
-STOWAGE
36
37
-CHARTS 6 MAPS
I
38
39
ho
41
42
L3
44 FURNISHINGS
45
-FLOOR COVERING
46
-ACCOUSTIC INS~
ION
47
48
-TRIM
49
-CURTAINS & SCRRENS
50
-CRASH PADDING
51
52
-partitions (NON-STRUCT)
53
-VIBRATION ABSORBERS
54
55 COLUMN TOTALS
I
56 TOTAL PAGE - MISC. EQUIP. & FURNISHINGS
57
*IF THN ARE NOT SPECIFIED AS SPECIAL EQUIPMENT, INCLUDE THEM UNDER THIS ITEM.
a
35
’73
FURNISHINGS
i
Downloaded from http://www.everyspec.com
l!lL-STD-1374
PART II - TAE
NAME
DATE
I
I
I
541
55 I COLUMNTOTALS
56! TOTAL PAGE - RMERGENCY EQUIPMENT
‘i-~
-
FURNISHINGS
6
I
i
I
I
,
EOUIPMENT GROUP
*IF IT IS NOT SPECIFIED AS USEFUL LOAD OR SPECIAL EQUIPMENT, INCLUDE IT UNDER TRIS HEADING.
36
t
Downloaded from http://www.everyspec.com
●
‘o
1
~ 2
/: >
.
I
4
5
6
7
8
FUNCTIONS PERFORMED *
HEATERS(BTU
)(NO.
)**
COMPRESSORS
HEAT EXCHANGERS
)
)**
(NO.
(NO.
COCXPIT CABIN
SYSTEM
I
16 I.
TURBINES
FANS
11
MOTOR~
1?
--, I -------
t 1$
.-
(NO.
(NO.
)
(N(l
)
I
f
I
I
)
I
VAPOR CYCLE SYSTEM
(NO.
COMI‘RXSSORS
(NO.
CONI)ENSERS
VITA t
(NO.
.v.-u’ORATORS
PLUMBING
PLUID(TYPE
)
)
)(oTY
)
?61 w~
I
PRESSURE REGULATORS
27
,0 I
29
30
SCOOPS
31
DUCTING(INCL.INSULATION)
2?
331
34
35 I
klG.DJG
IN
40
41
42
43
44
L5
. .
COMNON
YSTEM
)
El=
I L
ELECTRN. WEAPON
SYSTEM BAY SYS.
1
14
15
16
17
.,
18
19
20
I m.
t:;
PAGE
MODEL
REPORT
AIR CONDITIONINGGROUP
NIL-STD-1374”
PART II - TAB
NAMX
DATE
CONTROLS
MANUAL
ELECTRICAL
HYDRAULIC (FLUID
PNEUMATIC
I
I
I
I
I
!
I
I
I
I
I
I
I
I
i
I
I
I
I
I
I
I
I
I
I
I
I
I
I
LBS)
I
r
46
47
48
49
50
51
52
53
54
55 ~
I
/
I
DEFOG SYSTEM
SUPPORTS & BRACXETS
WING
TAIL
BODY
NACELLE
PRESSURIZATIONSEALING
.
COL
TOTAL
AE
TOTAL ~%R
cONDITTONINGGROUP
* INDICATE FUNCTION PERFORMID: VENTILATION - V, HEATING - H, COOLING - C, PRESSURIZATION- P.
INCLUDE THEN UNDER THIS HEADING.
**IF THEy Am NoT spEcIFIED As spEcIAL EQIJIPmNT,
37
I
I
I
Downloaded from http://www.everyspec.com
1.1’
2
. I
54
55
PAGE
MODEL
REPORT
ANTI-ICING GROUP
MIL-STD-1374PART 11 - T~NAME
DATE
t WING
[
TAIL
I
I
I
“e,
FUEL
ROTOR’OR CANOPY&
AIR
.’
IINDUCTN.IPROPELL.
I
I
I
I
I
I
I
COLUMN TOTAL
TOTAL PAGE
I 56
, 57I TOTAL - ANTI-ICING GROUP
* IF NOT SPECIFIED AS SPECIAL EQUIPMENT, INCLUDE THEM UNDER THE GIVEN HEADING.
**FRoM THE MAIN D1sTRIBUTIONPOINTS TO THE ACTUA’L’ING.UNIT.
.
/
/
,,
38
q
7(U
Downloaded from http://www.everyspec.com
-1
*
1
?.
3
4
5 EQUIPNENT ITEM *
6
7 CAMERAS
8
OPTICAL VIEWFINDERS
PAGE
MODEL
REPORT
PHOTOGRAPHICGROUP
MIL-STD-1374PART 11 - TAE
NAME
DATE
PHOTO
INSTALLATION
MODEL
11
12
13
14
15
16
1718
19
20
21
22 MOUNTS 6 ADAPTERS
24
25
26
27
28
?9
INSXALL4TIONPROVIS1ONS
-+1
,
1
*IF NOT SPECIFIED AS USEFUL LOAD OR SPECIAL EQUIPMENT, INCLUDE IT UNDER THE GIVEN HEADINGS.
a
39
Downloaded from http://www.everyspec.com
,.
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
28
29
30
31
32
33
34
35
. 36
37
. 38
39
I
PAGE
MODEL
REPORT
LOAD AND HANDLING GROUP *
MIL-STD-1374PART II - TAB
NAME
DATE
BALJAST
‘,
AIRCRAFT LOAD
HANDLING HANDLING
HOISTING SLING
,
“.
FITTINGS
TIE DOWN
JACKING
TOWING
LEVELING
HOISTING
,,
ANCHORAGE
BLADE STOWAGE RACKS
TAIL POST JACK
TIE DOWN FITTINGS
PALLET RAILS & SUPPORTS
a:
.
.
RAMPs - CARGO LOAOING
DROP LINE INSTALLATION
AERIAL DELIVERY SYSTEM
I
..
BOOM ASSY. (HOIST)
.
HOIST
T
41
42
43 BALLAST PROVISIONS
44
45
46
47
48
49
50 GEAR STOWAGE PROVISION
51
52
53
54
55 COW
TOTAL
.,.
56 TOT~E
57 TOTAL - LOAD & HANDLING GROUP
*DO NOT INcL~E ITEMS SPECIFIED AS SPECIAL EQUIPMENT OR USEFUL .LOAD:-
i,
s.
40
.
Downloaded from http://www.everyspec.com
MIL-STD-1374PART II - TAB
NAME
DATE
,..
●✎
SPECIAL EQUIPMENT *
NOT INCLUDED IN WEIGHT EMPTT
~AGE
MODEL
REPORT
1
2
3
4
TARGET TOWING EQUIPMENT
5
HOIST NOT BUILT IN - CARGO
6
- ENGINE
7
- WEAPONS
8
SPECIAL LOADING PLATFORMS
9
10
ENGINE MAINT. PLAT. (IF NOT BU::LT IN)
11
12
H~G
13
14
LIFE RAFTS-TYPE
OTT
15
16
COVERS COCKPIT
17
AIR INDUCTION
18
19
TOOL KITS
,20
,21
22
23
ANTI-ICING BOOTS - WING
24
TAIL
25
26
ANTI-ICING FLUID
27
28
29
FIR? EXTINGUISHER BOTTLE 6 VALTm
30
ENGINE (SIZE
31
OTT
)
~32
PORTABLE (SIZE
33
OTT
)
34
35
36
FUEL TANKS
37
TYPE OTY. LOC. CAP.
38
39
40
41
,42
43
ASSIST TAKE OFF INSTAL.
44
BOTTLES - SIZE
45
QTY
46
47
48
TROOP SEATS
49
PORTABLE LITTERS
-50
51
5
PORTABLE LAUDERS
5:
54
,55
56
57
*INCLUDE oN THIS PAGE ONLY THOSE ITEMS WUICH ARE AIRBORNE EQUIPMENT NOT SPECIFIED AS UEIGHT
EMPTY OR NORMAL USEFUL LOAD.
41
Downloaded from http://www.everyspec.com
APPENDIX S TO PART 11
STRUCTURAL INCREMENTS FOR
DESIGN FEATURES *
NIL-STD-1374
NAME
DATE
1
2
3
4
5
6
7
“8
9
WING
JOINTS -
FOLDING
VARIABLE SWEE
C.S. TO FUSELAGE
C.S. TO O.P.
PYLON
(STA.-
) FuSELAGE BREAK
ROTOR
TAIL
PAGE
MODEL
REPORT
FUSELAGE NACELLE
ALIGH.GR
,.
TS-ALIGHT GR. - MAIN
1?
13
-WEAPONS BAY
14
-SONOBUOY BAY
15
-HOIST
16
-CARGO DOORS
17
-RAm
18
19 REMOVAELE PANELS - STR.
20
21 TRANSPORTABILITY
22
23 VARIABLE INCIDENCE
24
25 FUSELAGE CARRY THRU FOR
26
DISCONTINUOUSWING
97
L,
28
29
30
31
32
33
34
35
36
37
38
?Q
40
41
42
-43
44
45
46
I
I
I
I
L
*.
**
I
I
HORIZ. TAIL cARRY THRU FOR
DISCONTINUOUSTAIL
FLAPS“- L.E.
- T.E.
SPOILERS
SLATS
~AR
- MAIN
PROPULSION - MAIN
- LIFT
LIFT ENGINE ~
48
69 F~L
50
51
52
53
54
55
56
57 I
LOUVERS
~REMOVABLE
-DROPPABLE
-PRESSURIZATION
I
1
* THE WEIGHTS FOR THE INCREMENTS ARE ALREADY INCLUDED WITHIN THE STRUCTURAL GROUPS.
ADD SUPPLEMENTARYPAGES 42A IF IT IS NECESSARY.
**IDENTIFy THE pANELs.
42
Downloaded from http://www.everyspec.com
/~FF
1
2
3
4
5
6
7
8
9
10
~
P~
WING
ROTOR
NOTES)
TAIL
FUSELAGE NACELLE ALIGH. GR
CATAPULTING - STRUCTURE
- FITTINGS
ARRESTING - STRUCTURE
- FITTINGS
BARRIER CRASH
SEAT EJECTIONS
~ ARMAlm3
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
I
PAGE
MODEL
REPORT
APPENDIX I TO PART II
STRUCTURAL INCREMENTS FOR
DESIGN FEATURES *
NIL-STD-1374PART II - TAB
NAME
DATE
s
- STRUCT. ARMOR
- FIXED GUNS
- TURRETS
SONOBUOYS
ANTI-ICING - BOOT
- THERMAL
DITCHING
FLOTATION
ATO
&
CARGO - TIEDOWN
~ 28
- HOIS DR SLING
29 t
RAMT
30
- DOOR
SIDE WILS
31
_
.
.
.
I
I
cmozms.
*THE mIGHTS FOR THE INCUNTS
ARE ALMADY INCLUDED WI~xN THE STRUcTuitAL
ADD SUPPLEMENTARYPAGES 42A IF IT IS NECESSARY.
43
—
Downloaded from http://www.everyspec.com
MIL-STD-1374 PART II - TAB
NAME
DATE
PAGE
MODEL
REPORT
APPENIYIx I ‘TO PART II
STRUCTURAL INCREMENTS FOR
DESIGN FEATURES
—
(CONTINUED)
;
.
J*
I
I
I
1
I
53
54
55
56
57
I
(
35
36
37
38
~~
.40
41
42
43
44
45
46
47
48
49
50
. 5i
I
e
I
!
,’
,.
I
I
I
I
44
a
L
Downloaded from http://www.everyspec.com
I
MIL-STD-1374PART II - ‘ME
NAME
DATE
APPENMX 11 TO PART II
DESIGN CRITERIA DATA
FOR WEIGHT ESTIUhTION AND ANALYSIS
45
PAGE
MODEL
REPORT
I
Downloaded from http://www.everyspec.com
MIL-STD-1374A
,*:
I
1’
PART III
WEIGHT AND BALANCE STATUS
,1
●
Downloaded from http://www.everyspec.com
I
MODEL
ENGINE
I
I
TOTC.L
Clggtt;
REVISED
GUAR
cON -
TRACTOII
RE$PUNSIBILITy
CHANGES
OR
COWTR4CT
NUMBER
a
U S4F
ISSUE
2
1
?
3
4
5
6
7
8
9
10
m
3
4
L4ST
ST4TUS
BETWEEN
LAST a CURRENT
STATIJSREPORU
ED
15SllE
SLIM
c:~u}:s
6
,g~ti
TOT4L
~oN-
-
SIBILITYTR&~ToR
CHdNGES REspON-
7
B
9
.,
8 I
19 I TAIL GROUP
,“
...~c & s~m~D
.. ,
21
22
%
24
26
..
.“.
.
FOLD >
s’r~”~T-ST*
I
VENTRAL
-w
ELEVATOR - lNLL . BAL
RUDDERS - lNCL BAL UT
- HUB & HINGE
36 \
7
G
G GEAR GROUF
13. !~T ‘TIN
k DRIVE
—
I
,LhTION
m
:TED
TED
—
m
&
82
83
FLIGHT CONTROLS GROUP
COCSPIT CTLS (INcL AFcs)
SYSTEMS CONTROLS
[
[
V-7’
FOR
CUQRENTOC.TA
%
%
%
E
c
A
L
c
;
T
~
~
“’’’’”
CH4NGcS
;Pj:j:
‘WING GROUP
BASIC STRUCT - CENTER SECTION
- 1NTM3 PAXEL
- OUTER PANEL
- GLOVE
SECOND STRUCT (INCL FoLD)
AILERONS INCL BAL wc
FLAPS - TRAILING EWE
- LEADING EDGE
SLATS
~POILERS
4 ROTOR GROUP
h
~
LADE ASSEMBLY
&
,.. ~cL
0.S1S
T ala!04T
~N ~
5
CHbNGC
SLIM
COLUMNS
4@5
VbRIAL
PROPOSED TlONS
SPEC
SIJM
COLUMN 6
cy&M;s
,~m;; ~
D.7E
I
PACE ~
AIRCRAFT
MIL-sTD-1374 PART 111
NEIGHT AND BALANCE STATUS
10
II
12
Downloaded from http://www.everyspec.com
.
e
I
I
I
Lz.2 ~
173 GROSS WEIGHT - ~
Dow
174 GROSS WSIGHT - WHEELS UP
175 MOST FIQ - WLS
UP - DOW
MOST AFT - U31EELSUP - DOW
a
—
I
I
I
I
.
,..
I
..
.
.
Downloaded from http://www.everyspec.com
e
I
[ ------
a
.
.
wEIGHT AND BbLANCE STATUS
MIL-STD-1374 PART 111
AIRCRAPT
PACE —2
Downloaded from http://www.everyspec.com
WEIGHT AND BALANCE STATUS
MIL-STD-1374 PART 111
AIRCRAFT
PAGE &
,,.
I
9
%
Downloaded from http://www.everyspec.com
,.
●
—
STANDARDIZATION DOCUMENT IMPROVEMENT PROPOSAL
I
OMB Approval
No. 22-R255
INSTRUCTIONS: The purpose of this form ia to solicit beneficial comments which will heIp achieve procurement 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 product
are invited to submit comments to the government.
Fold on lines on reverse side, stapIe in comer, and send to
preparing activity.
Comments submitted on this form do not constitute or imply authorrzaticn
to waive any
portion of the referenced document(s) or to amend contractual requirements.
Attach any pertinent data which
If there are additional pipers,
attach to form and place both in an
may be of use in improving this document.
envelope 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
.,
%>b
~qOIREcT
‘3
UNOER
GOVERNMENT
.-
A
CONTSACT
~sLIBcow:r!Ac
.—
HAS
ANY
PART
OF
TtiE
DOCUMENT
CREATED
PROBLEMSOR
REQUIRED
INTERPRETATIONIN
PROCUREMENT
uSE?
A.
GIVE
PARAGRApH
S.
RECOMMENDATIONS
NtiMeER
FOR
AND
WORDING.
CORRECT’!NG
+HE
DEFICIENCIES
.,.
COMMENTSON
ANY
DOCUMENT
Requirement
CONSIDERED
TOO
RIGIO
,.,.
,:<”,.,
IS THE
~
DOCUMENT
RESTRICTIVE?
YES
NO
O
(//’$
yes,’,
hiwh.mw.sy?)
REMARKS
JBMITTED
BY
(Printed
or
typed
name
and
addrees
TELEPHONE
- Optional)
NO.
DATE
------
..--S/N
DD ,:~;,l 426
●✍✎
REPLACES
*U.S.
EDITION
GOVERNMENT
PRINTING
~.
..
J
OF
I JAN
OFFICE:
66
WHICH
MAY
BE
0102 -o14-IB02
USEO
1977–703-122/6435
I