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MIL-STD-1333B9 January 1987SUPERSEDINGMIL-STD-1333A30 June 1976

MILITARY STANDARD

AIRCREW STATION GEOMETRY

FOR

M’ILITARY AIRCRAFT

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MIL-STD-1333B

DEPARTMENT OF DEFENSEWashington, O.C. 20301

Aircrew Station Geometry for Military Aircraft

1. This military standard is approved for use by all Departments and Agenciesof the Department of Defense.

2. Certain provisions of this standard are the subject of internationalstandardization agreements.

3. Beneficial comnents (recommendations, additions, deletions) and anypertinent data which may be of use in improving this document should beaddressed to: Naval Air En ineerin Center, Systems Engineering andStandardization Department ?Code 93?9 Lakehurst, NJ 08733-5100 by using theself-addressed Standardization Document Improvement Proposal (DD Form 1426)appearing at the end of this document or by letter.

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MIL-STD-1333B

CONTENTS

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REFERENCED DOCUMENTS . . ● . .Government documents . . . .Specifications and standards

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publications . .Order of precedence

DEFINITIONS . . . . .Design eye positionDesign eye line . .

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Horizontal vision line .Back tangent line . . . .Bottom tanqent line . . .

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Neutral seat reference point (NSRP)Buttock reference point . . . . . .Thigh tangent line . . . . . . . .Control grip reference point . . .

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Efficient, safe, and comfortable aircrew4operation . . . . .

GENERAL REQUIREMENTS .Selection of geometryBasic geometry guideSeating geometry . .External vision . . .Internal vision . . .

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44.14.1.14.1.24.24.34.44*54.5.14.5.1.14.5.1.24.64.74.7.14.7.2

Ejection clearance dimensions5555667 “7

Anthropometric considerationsBody dimensions . . . . . . .Functional body data . . . .Reach zones . . . . . . . . .Effects of personal and survival equipmentAccessibility of controls . . . . .Selection of controls . . . . . . .Location and actuation of controls

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CONTROL AND DISPLAY REQUIREMENTS 7777777778

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Stick type . . . . .Control wheel type .Propulsion controls .Single throttle . . .Multiple throttle . .Collective lever . .Brake and yaw control

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MIL-STD-1333B

CONTENTS (continued)

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5.25.2.15.2.25.2.35.2.3.15.2.3.25.3

66:16.1.16.1.26.26.2.16.2.2

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Control panels and consoles . . . . . . . . . .Lower surface consoles . . . . . . . . . . . .Overhead consoles . . ...” ● COOOOOO

Instrument panel . . . . . . . . . . . . . . .Instrument panel clearance . . . . . . . . . .Instrument panel viewing angle . . . . . . . .Seats. . . . . . . . . . ● ● ● ● “”””” ● ●

MULTI-CREW STATION REQUIREMENTS . . . . . . ● . .

Tandem arrangement . . . . . . . . . . . . . .Dual control . . . . . . . . . . ● ● *OQ ● ●

Single control . . . . . . . . . . . . . . . .Side-by-side arrangement . . . ● . . . . . . .Dual control . . . . . . . ● . ● sos c ● ● ●

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International interest . . . . . . . . . . . .Subject term (keyword) listing . . . . . . . .Changes from previous issue . . . . . . . . . .

TABLE

Personal and survival equipment . . . . . . . .

FIGURES

Basic geometry guide.... . . . . . . . . . .Seating geometry .e . . . . . . . . . . . . . .Cockpit clearance dimensions . . . . . . . . . .Reach zones - minimum link percentile . . . . .propulsion control geometry . . . . . ● . . . .

Collective control geometry . . . . . . . . . .Yaw control pedals . . . . . ...e”””~oo

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MIL-STD-1333B

MILITARY STANDARD

AIRCREH STATION GEOMETRYFOR

MILITARYAIRCRAFT

1. SCOPE

1.1 SwE The requirements defined herein appaircraft acquired by the Mllltary Services.

1.2 PurDose. This standard establishes the des

y to all piloted

gn requirement foraircrew sta=ometry in military afrcraft. The goal Is to obtain des~gnthat is efficient, safe and comfortable for operation by aircrew personnel forthe ranges of body stzes specified by the acquiring actlvlty.

2. REFERENCED DOCUMENTS

2.1 Government documents.

2.1.1 Specifications and standards. Unless otherwise” specified, thefollowing specifications and standards of the issue l~sted In that \ssue ofthe Department of Defense Index of Speclflcations and Standards (DoDISS)specified In the solicitation form a part of this standard to the extentspecified herein.

SPECIFICATIONS

MILITARY

MIL-B-8584

MIL-S-18471

MIL-A-23121

MIL-H-46855

MIL-S-58095

MIL-S-8

MIL-A-8

771

815

Brake Systems, Hheel, Aircraft, Design of

System, Aircrew Automated Escape, Ejection SeatType, General Specification for

Aircrew Environmental Escape and CockpitCapsule System, General Specification for

Human Engineering Requirements for MilitarySystems, Equipment and Facilities

Seat System, Crashworthy, Non-Ejection, Aircrew,General Speclffcations for

Seat, Aircrew, Adjustable, Atrcraft, GeneralSpeclflcatlon for

Aircrew, Automated Escape Systems, GeneralSpecification for


MIL-STD-1333B

STANDARDS

MILITARY

MIL-STD-203 - Aircrew Station Controls and Displays forFixed Wing Aircraft

MIL-STD-250 - Aircrew Station Controls and Displays forRotary Wing Aircraft

MIL-STD-850 - Aircrew Station Vision Requirements forMilitary Aircraft

MIL-STD-1472 - Human Engineering Design Crlterta for ,Military Systems, Equipment and Facilities

2.1.2 Other Government documents, drawinqs, and publications. Thefollowing other Government documents, drawings, and publications form a partof this standard to the extent specified herein.

PUBLICATIONSb

ARMY

USANL TR 72-52-CE - Anthropometry of U.S. Army Aviators 1970

USANL TR 77-024 - Anthropometry of Noreenof the U.S. Army 1977

NAW

NAVAIR 13-1-6 Series - Aviation-Crew Systems Manual

(Copies of specifications, standards, drawings, and publications required bythe contractors h connection with specific procurement functions should beobtained from the acquiring activity or as directed by the contractingofficer.)

2.2 Order of precedence. In the event of a conflict between the text ofthis standard and the references cited herein, the text of th!s standard shalltake precedence.

3. DEFINITIONS

3.1 ~. The design eye position is the midpoint ofthe design eye line from which all crewstation dimensions are related and ref-erenced.

3.2 Deslqn eye I;;e. The design eye’line fs a segment of the over thenose vtsion l~ne connecting two points which represents the predicted eye pos-Itlons of the extremes of the aircrew population specified by the acqutringactivity. /

3.3 Horizontal vision lhe. The horizontal vision line is a referenceline passing through the design eye position (3.1) and parallel to thefuselage reference line as specified by the acquiring activity.

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MIL-STD-1333B

3.4 Back tanqent line. The back tangent line is established by avertically inclined plan tangent to the back of a seated crewmember at thethoracic region and buttocks.

3.5 Bottom tangent llne. Shown on a typical Inboard profile drawing ofan aircrew station as a line depictfng a lateral plane on the seat back whichis tangent to the compressed seat at the points where the posterior aspects ofthe buttocks and thorax, w!th appropriate clothing, contact the cushton. Theamount of compress~on should be that which would occur with an aircrew memberhaving a mean welghtof the population specified by the acqulrlng activityunder l-g fltght conditions.

3.6 Seat reference point (SRP). The seat reference point Is theIntersectionof the back tangent line and the bottom tangent l~ne.

3.7 Neutral seat reference point (NSRP). The neutral seat referencepoint is the seat reference point with the seat h the nominal midposftion ofthe seat adjustment range.

3.8 Buttock reference point. The buttock reference point is the mostforward Ilmlt of the bottom tangent llne and represents the body pressurepoints located 5.75 Inches forward of the seat reference point. Thisrepresents the area of the lowest seat cushion compression under a staticvertical load of l-g.

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3.9 Thigh tangent line. The thigh tangent llne Is the average l~ne ofthe a~rcraft seat when occupied by a crewmember with the maximum weight asspecified by the acquiring actlv!~y. The thigh tangent line originates at thebuttock reference point and extends upward and forward from that point to theforward edge of the seat.

3.10 Control grip reference point. The control grip reference point Isthe point at which the crewmember’s second finger (middle digit) \s in contactwith the forward or downward face of any grip-type control such as controlstick, control wheel, collective stick, or throttle.

3.11 Efficient, safe, and comfortable aircrew operation. Efficient,safe, and comfortable aircrew operation Is defined by the dimensions, size,and adjustments of an aircrew station that will allo; the aircrew to: reachand actuate all controls, have external vision in accordance with MIL-STD-850,have unobstructed internal view of all cr~tical controls and displays, be ableto function effectively without undue fatigue or discomfort, and escapewithout injury.

4. GENERAL REQUIREMENTS

4.1 Selection of geometry. Aircrew station geometry shall take Intoconsiderationall aspects of control and display requirements associated withsafe flight, execution of the mission, and safe emergency egress and shallconform to the requirements specified herein. Proposed geometry andaccommodation limitations, If any, shall be approved by the acquiring activity.

4.1.1 Bas!c qeometry guide. A basic geometry guide for this document ispresented as Figure 1 for a particular flight staion and population member.Figure 1 also Indexes definitions of this standard.

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MIL-STD-1333B

4.1.2 Seatinqgeometry. The seating geometry shall conform to therequirements of Figure 2 for the specified population and seat back angles asshown. Other requirements for ejection seat design and seat components shallbe in accordance with MIL-S-18471.

4.2 External vlslon. The external vision for aircrew stations shallconform to the requirements of MIL-STD-850 from all pointson the design eyeline. The effects of body positioning such as head rest bracing on a catapultlaunchand normal head level positioningunder l-g flight conditionsshall beconsidered.

4.3 Internal vision. The internal vision of all controls and displaysshall be accessible from all points on the design eye line. The effects ofbody posltbning such as head rest bracing on a catapult launch and normalhead levelpos~tionlngunder l-g conditions shall be considered.

4.4 Ejectionclearancedimensions. The ejection clearance dimensionsfor flight stations shall allow unobstructed egress by any member of thepopulation specified by the acqutring activity. Figure 3 provides guidance fora particularflight stat~onand populationmember.

4.5 Anthropometric considerations. The aircrew station geometry shallbe basedon the anthropometrfc range specified by the acquiring activity andemploy~ng the factors outllned In MIL-STD-1472 and obtained from studiesconducted In accordance with the requirements of MIL-H-46855.

4.5.1 Body dimensions. The requirements for body dimensions shall conformto the following documents for U.S. Army acqulsitlons, as applicable. Otherservices shall specify body dimensions of the population to be accommodated.

ArmyUSANL TR 72-52-CEUSANL TR 77-O-24

4.5.1.1 Functional body data. Functional body data crltlcal combinationsas provided by the acquiring activity shall be used ~n the design for afrcrewsafety, accommodationand comfort for the specified population. Figures 4, 5,6, 8, and 9 present arm and leg link values derived from cockpit workspacestud~es and are provtded for guidance.

4.5.1.2 Reach zones. Applicable data of reach and grasp capability forthe population defined by the acquiring activity shall be considered for reachzones Illustrated in Figure 4 and defined as follows. Control locationswithin these zones shall be In accordance with MIL-STD-203 and MIL-STD–250 asapplicable.

ZONE 1 Restraint Harness Locked - Functional Reach

This zone Includes the area that can be functionally reached and actuatedby any crewmember of the population defined by the acquir!ng activity whenlocated at the appropriate design eye pos!t~on fully restrained and equippedwithout stretch of arm or shoulder muscles. Controls placed In this zoneshall include those frequently used during operation of the aircraft in fllghtphases which require full restraint. This would include such flight phases astakeoff, landing, low altitude-hi-speed flight, weapons dellvery, and escape.This zone defines the maximum limit allowed for the placement of emergency(escape system) controls and establishes the forwardmost operation limit ofprimary flight and propulsion controls.

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MIL-STD-1333B

ZONE 2 Restraint Harness Locked - Maximum Functional Reach

This zone includes the area that can be functionally reached and actuatedby any crewmember of the population defined by the acqulrlng actlvlty whenlocated at the appropriate design eye posltlon fully restrained and equippedwith maximum stretch of shoulder and arm muscles. This zone defines themaximum llmlt allowed for the placement of helicopter primary flight andpropulsion controls and the placement of emergency controls other than escapecontrols.

ZONE 3 Re$traint Harness Unlocked - Maximum Functional Reach

This zone includes the area that can be functionally reached andactuated by any crewmember of the population defined by the acquiring activitywhen located at the appropriate design eye position with the shoulderrestraint fully extended and the arms stretched full length.

4.6 Effects of personal and survival equipment. All geometryrequirements specified herein are based upon nude body dlmensioos and do not’include any tolerance for clothing or equipment, except flight boots and basicheadgear. Many Items”of personal and survival equipment significantly alterthe crewmember’s posWon in the aircrew station. All such equ~pmentspecified by the acqulrlng activity shall be considered at the earliest pointin design. Adjustments shall be made to the geometry to accommodate requiredequipment for the anthropometricrange specifiedby the acquiringactivity. Acheck list of most frequently used items is contained In NAVAIR 13-1-6Ser~esManualsand as otherwise specffied by the acquiring activity. The llst inTable I Is representative of most frequently used items for specific missionenvironment and aircraft requirements and shall be considered.

TABLE I. Personal and survival equipment.

Common Equipment

Fllght SuitFl\ght BootsFlight GlovesHelmetSurvival Vestand Equipment

Specific to Aircraft I Specific to Mission IType Needs and Environment

Anti-G Garment Helmet~Mounted Systems‘Pressure Suit (tncludlng, but notTorso Harness ~limited to):Oxygen Delivery Night Vision Systems

System Integrated Helmet andDfsplay Systems

Flash-BlandnessProt.Laser ProtectionChemical/Biological/Radiolog~calProt.Systems

‘Ball~stic$:-ProtectionFlota’tlon5ystems$old+e~her Prot. ..‘- Systems

.

‘Individual@olingSvstems

4.7 Accessibilityof controls. Crewstation controls shall beaccessible and usable by the entire anthropometric range specified by the

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MIL-STD-1333B

4.7.1 Selection of controls. Selection of controls for the respectivecrewmembers shall be based upon the analyses and data derived from the studiesrequfred by MIL-H-46855 or by other techniques specified by the acquiringact!vity.

4.7.2 Locat~on and actuation of controls. The location and actuation ofcontrols shall conform to paragraphs 4.5 and 4.6 of this document and shall beIn accordance with the requirements of MIL-STD-203 or MIL-STD-250, asapplicable. Specific control locations and arrangements shall be establishedwithin the specified reach zones in accordance with the designated aircraftmission requirements and shall conform to requirements specified in 4.5 and4.6.

5. CONTROL AND DISPLAY REQUIREMENTS

5.1 Controls.

5.1.1 Pitch and roll controls.

5.1.1.1 Stick type. The.vertical location of the control grip referencepoint shall be operable within Zone 1 for the specified population. Themaximum envelope of st~ck throw shall be based on Zone 1 reach as defined in4.5.1.2. Amtn\mum clearance of 1.5 inches shall be maintained between thestick and all-structures when the st~ck is In any extreme position. Specialconsideration shall be given to the effectof personal and survival equipment,examples of which are shown in Table I, when establishing stick envelope.

5.1.1.2 Control wheel type. A minimum clearance of 1:5 inches between thewheel and structure shall be maintained in addition to a minimum clearance of0.5 inch between the crewmembers hand and body and a minimum clearance of 1.5inches between the bottom surface of the wheel and the aircrew member’s legwhen operated throughout the critical anthropometric range as specified by theacquiring activity. The maximum wheel throw envelope shall be based on Zone 1reach as defined in 4.5.1.2 while the above minimum clearances are maintained.

5.1.2 Propulsion controls.

5.1.2.1 Single throttle. The location of the forwardmost position of thethrottle shall be based on Zone 1 reach as defined in 4.5.1.2. All controlson the throttle shall be operable throughout the entire range of movement andprovide 1.5 inches minimum structural clearance of the maximum specified arm.Figure 5 Is provided as guidance with dimensions which are for a particularflight station and population member.

‘5.1.2.2 Multiple throttle. Locate the same as for single throttle, exceptthe geometry of all throttles shall be based upon the forwardmost position ofthe throttle furthest from the crewmember laterally.

5.1.3 Collective lever. The collective control shall be locatgd as shownin Figure 6.

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MIL-STD-1333B

5.1.4 Brake and yaw control pedals. The yaw control requirements hereindo not apply to aircraft which have the yaw control Integrated Into a multiaxis flight controller.The yaw control shall consist of two pedals of theconfiguration conforming to MIL-B-8584. Differential braking deftned byMIL-B-8584 shall be provided by these pedals. The most forward adjustmentposltionof the yaw controls shall be based upon the specified leg lengthseated with the seat full aft and full down, and yaw controls on, full forwardthrow, with the brake fully depressed, as shown In F\gure 8. The most aftadjustment position of~~e yaw controls shall be based on the minimumspecified l,eglength seated w~th seat full forward and full up and fullforward-yaw control throw, with the brake fully depressed as shown In F~gure9. Yaw control pedals forward and aft range requ~rements shall be based onfunctional leg throw data provided by the acquiring actlvlty. AmWmumclearance as shown In Figure 7 of 1.5 Inches above and 0.75 Inches on eitherside of the pedal shall be ma!ntalned over the maximum speclf~ed foot in aflight boot, throughout the full pedal travel Including brake application wtththe mldheel at the fulcrum position of the pedal. Hlth normal brakingprocedures, a 1.5 Inch clearance between maximum s~ze footwear and alladjacent Instruments and structure shall be maintained for any flight stationseating geometry and po ulation member.

!Throughout the range of yaw control

adjustment and travel, he distance from the brake fulcrum to the nearestpoint on the crewstatlon floor shall be a minimumof 4.75 inches. Pedallength shall be the minimum required to satisfy braking requirements.

5.2 Control panels and consoles.

5.2.1 Lower surface consoles.

(a) Locate sfde consoles to provide physical and visual access bycrewmemberof minimum functional reach as defined in 4.5.1.2.

(b) Locate center console to provide physical and visual access bycrewmember of minimum functional reach as defined in 4.5.1.2.

5.2.2 Overhead consoles. Locate to provide unrestricted view of theconsole elements with the same access as for lower surface console(s).

5.2.3 Instrument panel.

5.2.3.1 Instrument panel clearance. The instrument panel shall be locatedso as to provide a 1.5 inch clearance with the crewmember’s legs through thefull range of leg movement as shown in Figure 7. On aircraft equipped withejection seats, clearance shall be provided as shown in Figure 3.

5.2.3.2 Instrument panel viewing anqle. The panel shall provide the mostnormal viewing angle as practicable ‘fromthe design eye position.

5.3 Seats. Aircrew seats conforming to the requirement of MIL-S-18471,NIL-A-23121,MIL-S-58095, MIL-S-81771, and MIL-A-81815 shall provide the bodypositioning capability in accordance with the requirements specified herein.

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MIL-STD-1333B

6. MULTI-CREW STATION REQUIREMENTS...’

6.1

6.1.1

duplicatedactivity.

Tandem arrangement.

Dual control.

(a) The single crew station geometry specified herein shall befor both crew stations unless otherwise specified by the acquiring

(b) Minimum fore and aft spacing between the crew stations shallbe based on the minimum space required to accommodatethe largest specifiedcrewmember in each station while maintaining full control movements in bothstations.

(c) The external vision for the forward and aft crew stationsshall conform to MIL-STD-850.

6.1.2 Slnqle control.

(a) The flight control station geometry shall conform to therequirements herein while the other crew station geometry shall be configuredfor the specific aircraft mission.

(b) Minimum spacing between forward and aft crew stations shall bebased on the minimum space required to accommodate safely the largestcrewmember as specified by the acquiring activities crlti,calcombinations Ineach station while performing the assigned mission function.

(c) External vision for the aft crew member shall be as specifiedby the acquir~ng activity and shall depend on the aircraft type and mission.

6.2

6.2.1

Side-bY-side arrangement

Dual control

(a) This configuration shall consist of two crew stationsside-by-side, slmllar in seating, clearances, and flight controls. Propulsioncontrol -locations-shall be based-on the requirements for equally adequateaccess and operation by either crewmember under all flight conditions.

(b) Both crew positions shall be on the same level,unlessotherwise sDecified. The lateral centerline spacing between crewmembers shallbe amhimurnof 26 inches and a maxlmumof 42”for”conflguratlonswith displays and controlsrotary wing aircraft, the d~menslons shall bemaximum of 50 inches.

(c) Minimum lateral spacing shall

Inches centerline to centerlinecommon for both crewmembers. Ina minimum of 26 fnches and a

be based won mlnlmumxlearancesbetween seat and sttucture or controls; and provldlng for no Interferencebetween crewmembers h performance of their flight tasks. The absolute mlnlmumclearance between seats shall be 3 Inches for non-ejection seats and 6 hchesfor ejection seats.

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MIL-STD-1333B

6.2.2 Single control. The flight control station geometry shall conformto the requirements herein and the other crew station geometry shall beconfigured for the specific aircraft mission.

7. NOTES

7.1 International interest. Certain provisions of this standard arethe subject of international standardization agreements (ASCC 10/55 and STANAG3639). Hhen revision or cancellation of this standard is proposed, which willaffect or violate the international agreement concerned, the preparingactivity shall take appropriate reconciliation action through internationalstandardizationoffices, If required.

7.2 Subject term (key word) Iistlnq.o

geometry, aircrew stationdesign eye positionfunctional body datareach zonescontroldisplay ~anthropometry, aviatorvision, Internalvision, external

---- 1.3 Changes from prevfous issue. Asterisks or vertical lines are notused In this revision to identify changes w~th respect to the previous Issuedue to the extensiveness of the changes.

Custodians: Preparing activity:Army - AV Navy - ASNavy - AS (Project No. 15GP-0058)Air Force - 11

Reviewer activity:Army - MI

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MIL-STD-1333B

EXTERNAL V1S1ONMIL-STD-1350

NOR. VLSION LINE

PARA. 3.3

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t~,.. -~,iTcll A~Jj ROLL co~T’R(jL

PARA.5.1.1

PROPULSION CONTROLSPARA. 5.~,2/FIG.5

\

RACK TANGENT LINEPARA. 3.4/FIC. 2

tiESIGN )zW P061moN

PARA. 3.1/FJG. 2

/

y~

NEUTRAL SEATREFERENCE

PAIUw3.7 MD 3.8/FIO. 2k’AW CONTJIC)L PEDALS -FIG. 7, 8 AND 9

BUITOCK REF POINT

PARA.3.8/Flc. 2

COCK PIT FLOOR

(REF. ) PARA. S.1.4

‘flllGI1 TANGENT LJNEPA1{A. 3.9/FIG.2

‘] \coLLE::TT:N’LE

lJOTTOhl TANGENT LINE

PARA. 3.5/FIG.2 PARA 5.1.3/FIG.6

FIGURE 1. Basic geometry guide.

10

POINT


—

IIIL-STD-1333B

DISIANCE FllOkI DESIGN EYE IWSl”IlON TO VE1l”rlCAL PLANE bPNEUTRAL SEAT REFERENCE POINT FOR VARIOUS SEAT

LUCK ANGLES

-e’-

... .

SEAT BACK ANGLE

I DEGllEES)

10

104

11

‘ox” { INCIIES)

7.7

7.4

7.1

6.9

6.6

6.3

6,1

s.@

S.s

5.3

5.0

t-34

-i ‘“st-

+lJrI .5

NSW --wT8MIN

+–+-i

2-WAY SEAT ALkIUSTkW~ 4-WAY SEAT AWUSTMENT

.

J HORIZONTAL IVIS1ON LINE

/

1

---1SEAT IIACK

n

“DOWN VISION

PER hllL-STH50

/-GLARE Sill ELD

INSTRUMENT IMNEL

BRAKE FULCRUM POINT(IN NEUTRAL ADJUS2MNT)

90”

TIIIGII TANGENT ANGLE

TIIIGII TANGENT LiNE o1.2~ hllN

BUTTOCK REF POINT 6.25 I’IAX

cuxEs:

.

31.0

(SEE NOTE 3)

I)AC K “TANGENTLIFE

1 lIORIZONTAL PLANE

1. TWQiTANGE2WAtCLEU=AHl NIMW 5“AN) ANAXI1’lRIOF~”o PORNEuamRts, ‘m tmuml a 10°SHAILAPPLY.

2. TIEDItE261LRGStKMiAPPLYTO A PAR’TIWLARFLICWTSTATIWANDPOPUMTI~mm.

3. DINENSI(MSSASH)ON 13*SEATBACKAKLE. RX FIXEDWC AIRCRAFT,LESSTNAN13°SEATBACKMUX IS-lMBLE.

FIGURE 2. Seating geometry.


MIL-STD-1333B

7’

.

I

●

.


MIL-STD-1333B

CENTER LINE

OF CREW STATION

\+./

l\‘!

II

I

I

\

I

L ‘01=4 ‘ND5-,\

.

IMCK TANGENT LINEJ

\

ZONE3

\

&_.p>+KnF5:

2-WAY SEAT

1. FOR ZONE DEFINITIONSEE PARAGRAPH 4.5.1.2.

2. DIMENSIONS IN INCHES.

3. DItlENSIONS SHOWN APPLY TO A PARTICULAR FLIGHT STATIONAND POPULATION ?IEHBER.

4. FUNCTIONALREACH AS SPECIFIEDBY IHE ACQUIRItWACTIVITY.GRASP AS SPECIFIEDBY THE ACQUIRINGACTIVITY.

5. CONSIDERATIONSHALL DE GIVEN TO DIFFEREttCESBETWEENLINKHODELDATA (e.g. SHOULDERPIVOT POINT AS SHOWN ABOVE)ANDCLASSICALANT14ROPOtlETR1CDATA (e.g. FUNCTIONALARII REACH)SPECIFIEDBY THE ACQUIRINC ACTIVITY.

4-WAY SEAT

/

FIGURE 4. Reach zones - minimum link percentile.


MIL-STD-1333B

cENTER LINE OF CREWSTATION

n-’

-

FIG. 4 zla!l (ml. mcn?rxu ARHIJM)

1 (

7.25

I f /~/~CUMANCE WITHALLSnUKmRE WITHNAxP~~lE ARH LINX

I ‘-’”12 HAx6 MI!

rum: NSRP

1. FOR ZONE DEFINITION SEE PARAGRAPH4.5.1.2.

“2. DItlENSIONS 1114INCHES.

3. DIHCNSIONS SHOWNAPPLY TO A PARTICULAR FLIGHT STATIONAND POPULATION HEHBER.

4, FUNCTIONAL REACH AS SPECIFIED BY THE ACQUIRING ACTIVITY.GRASP AS SPECIFIED BY THE ACQUIRING ACTIVITY.

3. CONSIDERATION SHALL BE GIVEN TO DIFFERENCES BETWEEN LINKtlODEL DATA (e.g. SHOULDER PIVOT POINT AS SHOWNABOVE) ANOCLASSICAL ANTIIROPOHETRICDATA (e.g. FUNCTIONAL ARM REACH)SPECIFIED BY THE ACQUIRING ACTIVITY.

1.5 MIN CIMRAf=WITMAU SIWCIWRE

-1 P

@

I/ ,

I

/

.-

FIGURE 50 Propulsion control ~eometry.


MIL-STD-1333B‘

-+-nc’m’n’’”’o’cn’’vs’’”o”I

I

MINIMUM PERCENTILE ARM LINK (FiO. 4)

*# 4

~

1.ZS

.k

13 klAX

t>

I

F

.~/” *

/“

1.

4 0, Ctxuxmv, PtTmCO~OL ORIP

I

.S99h

A

1. FOR ZONE DEFINITION SEE PARAGRAPH 4. S.1.2.

2. DII!ENSIONSIN INCHES.

3. DIMENSIONS SHOWNAPPLY TO A PARTICULAR FLICNT 6TATIONAND POPULATION HEtlBER.

4. FUNCTIONAL REACH AS SPECIFIED BY THE ACQUIRING ACTIVITY.GRASP AS SPECIFIED BY THE ACQUIRING ACTIVITY.

5. CONSIDERATIONSHALLBE GIVEN TO DIFFERENCES BETWEEN LINKliODEL DATA (e.g. SIIOULDER PIVOT POINT AS SHOWNABOVE) ANDCLASSICAL ANTHROPOHETRICDATA (e.g. FUNCTIONAL ARH REACH)SPECIFIED BY THE ACQUIRING ACTfVITY.

1.5 MN

ANCEDETWEENAL1.S’IWCTURE ANIIMAX%IMWLIWN -E1.lN~\V

LENOTIIATAL1, SEATPOSITIONS

I.SR DESRFDRK(;ION OFUXIISOFCOLLFCI IVF.

3.0 1- PITCIICONTRO1. GRIPVIYtTUAL PIVOT lWNN”r

FIGURE 6. Collective control geometry.

\s


MIL-STD-1333B

TRAVEL

1-CLEARAREA -i e

. 14 3 -

(PARL 5.L4)

I FWD AFT !ADJUST ADJUST I

II

I

\\ t’-. 30 Af/~

II

/ >

—INSTRUMENT PANEL

1’

NO B~AKE 1(SJEmoTE 3)

L 1.50‘~

1 !=150

75 .75t

@ ‘~ ‘

If}

. .— .._i____=--. .

I tI I / “17--

II w’ 8 NSRP1, ‘\ ‘

3.5 ‘ It

11-1$I ---1- .~I * \

r~‘+++’

II MIL-B-8584JPEDAL WITH /

t-i

1

7,5MIN10.5MAX MAX BRAKE /FwD ADJuST

FWD THROW

An ADJUST~AFT THROW

% %PILOT PEDAL ‘:

1. fJXIJSWPIDALTIWELNEED~BEA SIRAIQ~LINE.

2, CLEARANCEmm BAsrmm HAxPERcEi?nLEm w-m LARGESTSIZEFcunnuR. -slum M EWARDH3SrIwsTwm PasITLo?JUm mu FURUARDmm AtmsT,rwu}YRWARD- ‘IMRW,AM)EIJLlBRAKETIUW...

3. aumu SHAu BE NAItWAINHl wml h! m TWtOumm FulL YAM amuOLTRAvn..

4. DI~ICRtS IN lNO+ES..

5. DIttDKICX?SSiU%RJAPPLY‘TOA PARTI(XLAR FLXXI =ATION AM MIATKX4 t4DEWlt. ‘

FIGURE 7. ~aw control pedals.


MIL-STD-1333B

-.

..

fis’

L FUDAILIUSIWDnmu

4-UAYSEAT

THAx PmmnLEKNEEPIvur IFSEATBACX

Awls(SEEFIG.

#

U7rEs:

1. BAsm ON HAXIt’llRlPERcmrxls m FUUY Dm2mm INMPGESTSIZEFWIWEAR.

2. DIPEZ6KXtS IN INQES .

3. A AK)B TO BESPDWIRI BYTIEAQUIRItGACIIVITY.

4. D-IW SKM APPLYTO A PARTKXMRFLIM ~ATICR4ANDFOPUIA’TION=.

5. -XDDUTNM SHALLBEGXV~ lU DIFFEXMXSINLINKtCX.WLDATAStKW A&)VE AtKICIJSSICAL AI?IWIKRE1’RIC DATASPECIFIEDBYTIIEAQUUUNG KXIVITY.

,,

FIGURE 8. Yaw control pedals - forward range.

[7

2)

------- ------ --- —--———--— —-l–– –-–-, –--– r— –--— .— —-—.- .—


MIL-STD-1333B

. .

AFT

FWD

FULLFWWUPPOSITION

4-WAY SEAT

MIN PERCENTILE q ,KNEE PIVOT

TIIIGII TANGENT ANGLE

45.

AOJUSTTHROW

KYIts:

1. BAsm ON NI?II?UMmwrrnJ! m lwLLYImIE?mml.?!WA1.usTSIZE~.

2. DItC3JGIONSIN IKXES.

3. A AN)B TO BES?WXF~ BYTHEQIRIti ACXIVX’lY.

4. DIlE2WClSSUM APPLYTO A PMMIMR FIJtln5TATIDNMD K)PUIATIONHD!B=.

5. -ILXXATI(M SHALLBE GIVm ‘K) DIFmltkFs BEIWIZNLIFX HXEL DATASIUXRiAIXIVEAIRl CIXSICAL ~IC DATASPlXIFIE2) BY ‘IHEA~IRItW ACTIVITY.

FIGURE 9. Yaw control pedals - aft range.

~~

.-


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AOORE$S(Wmd, CUy, St-k ZW Cods)

k

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5. REMARKS

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AIRCREW STATION GEOMETRY FOR M’ILITARY AIRCRAFTeveryspec.com/MIL-STD/MIL-STD-1300-1399/download.php?spec=MIL_STD_1333B.525.pdfmil-std-1333b 9 january 1987 superseding mil-std-1333a