United States Army Aotation Planning ^Manual

7-3 rene# FM 101-20-1

FIELD MANUAL

UNITED STATES ARMY AOTATION PLANNING ^MANUAL

HEADQUARTERS, DEPARTMENT Of THE ARMY SEPTEMBER 1971

ÏHE ARMY ÜBRARV1 WASHINGTON, D. C.

FOR-OFFICIAL USE ONLY

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FOREWORD

This manual is published in accordance with the be revised annually to ensure current and accurate provisions of AR 95-70 and contains official U.S. data, as well as provide additional factors of interest. Army aviation factors data in a single-source document AMC is responsible for coordinating pertinent planning to be used as a planning guide ONLY. The factors, factors with the appropriate Army staff agency. when used with other Army program documents (e.g., Army Materiel Plan and Materiel Annex Part II to 5 Year Force Structure and U.S. Army Aircraft Standard Users of this manual are encouraged to submit Avionics/Surveillance Configuration, 5 Year Plan recommended changes or comments to improve the Requirement), will assist commanders, planners, and manual. Comments should be keyed to the specific programmers in establishing a basis for operational, page, paragraph, and line of the text. Reasons should logistical, materiel, personnel, estimates, and the cost be provided for each comment to ensure understanding requirements for combat readiness of all types and and full evaluation. Comments should be forwarded models of Army aircraft. In the event such Army direct to Headquarters, U.S. Army Materiel Command, program documents, as mentioned above, indicate later Research, Development and Engineering Directorate, revision, such revisions will take precedence. The data Attn: AMCRD-F, Washington, D.C., 20315. may be used in the preparation of estimates by major commands (theatre, field army, or equivalent) but will Distribution of this Department of the Army not be used as a basis of reporting cost or other data. publication to Active Army, National Guard, and United States Army Reserve units is by formula These planning factors were developed from distribution and pinpoint distribution methods. Other diversified operational and logistical statistical data and DOD agencies should request copies required from the were obtained from various Department of the Army Adjutant General, Washington, D.C. Under provisions staff offices and other Army agencies having primary of Army Regulation 310-1, Military Publications, responsibilities for the specific mission activities or normal publications supply channels should be related functions. followed.

This manual is published in looseleaf form to Requests from agencies outside of DOD will be facilitate insertion of revisions, changes, * and/or forwarded to The Adjutant General, Washington, D.C. additions. Each set of published planning factors will 20315.

NOTE

This publication is printed in two parts. FM 101-20-1 (PART I) is classified FOR OFFICIAL USE ONLY. FM 101-20-2 (PART II) is classified CONFIDENTIAL. Pages 2-57, 2-58, 2-63, 2-64, 2-83/ 2-84; Chapter 3, and Chapter 5 are contained in FM 101-20-2.

FOR OmeiAL USE ONir i/(ii blank) i FM 101-20-1

FIELD MANUAL 1 HEADQUARTERS 1 DEPARTMENT OF THE ARMY No. 101-20-1 J Washington, D. C., 28 September 1971

UNITED STATES ARMY

AVIATION PLANNING MANUAL

PART I

Page Foreword i

Chapter 1. OPERATIONS

Section I. Aircraft authorizations 1-1 II. (FOUO) Flying hour program (U) 1-17 HI. Attrition 1-19 IV. Standard aircraft characteristics 1-20

Chapter 2. LOGISTICS AND MATERIEL

Section I. Maximum allowable operating time (MAOT) (major components) 2-1 II. Aircraft equipment (Also See Part II) 2-11 III. Ferrying and shipping 2-98 IV. Tools 2-106 V. Inspections 2-118 VI. Fuel and oil 2-121 VII. Maintenance man-hours 2-123 VIII. Maintenance Categories 2-125

Chapter 4. COSTS

Section I. Army aircraft maintenance and operating costs per flying hour 4-1 II. Aircraft unit flyaway costs 4-3 III. Avionics costs 4-5 IV. Armament Costs 4-14

APPENDIX A REFERENCES A-I

INDEX Index 1

*This manual, together with FM 101-20-2, 28 September 1971, supersedes FM 101-20, 14 August 1970.

TOR OFFICIAL USE ONLY HI FM 101-20-1

CLASSES OF ARMY AIRCRAFT

LONG- COMBAT TRAINING PRE POPULAR NAME RANGE ACCEPT ACCEPT FERREO FOLLOW-ON AND TYPE SUBST SUBST AFTER FY 73 COBRA

AH-1G UH-1B UH-1C

ATTACK HELICOPTER

CHINOOK

LIGHT TACTICAL CH-47 TRANSPORT SYSTEM CARGO TRANSPORT HELICOPTER (MEDIUM LIFT)

TARHE

CH-54A HEAVY LIFT HELICOPTER CARGO TRANSPORT HELICOPTER

CAYUSE

■iv

KIOWA' AARS OH-6A OR OH-13 OH-13 (AERIAL ARMORED OH-58A OH-23 OH-23 RECONNAISSANCE SYSTEM)

LIGHT OBSERVATION HELICOPTER

IROQUOIS UTILITY TACTICAL UH-1D/H UH-1B TRANSPORT CH-34C AIRCRAFT UTILITY (UTILITY/TACTICAL) SYSTEM TRANSPORT HELICOPTER

SIOUX

TH-13T OFF-THE- SHELF BASIC INSTRUMENT TRAINER HELICOPTER

OSAGE

TH-55A OH-23 OFF-THE SHELF PRIMARY TRAINER HELICOPTER

AV 010094

IV FOR orriciAL WE-ONL* FM 101-20-1

CLASSES OF ARMY AIRCRAFT

LONG- COMBAT TRAINING POPULAR NAME RANGE PRE- ACCEPT ACCEPT FERRED AND TYPE FOLLOW-ON SUBST SUBST AFTER FY 73

SEMINOLE

U-8D U-1A U-8F U-6A

UTILITY AIRPLANE

COURIER

U-10A

UTILITY STOL AIRPLANE (SPECIAL FORCES AIRCRAFT)

UTE

U-21 U-8D

UTILITY AIRPLANE

MOHAWK

MANNED AERIAL VEHICLE/ SURVEILLANCE OBSERVATION STOL AIRPLANE

MESCALERO

T-41B 0-1 OFF-THE-SHELF

FLIGHT TRAINER AIRPLANE

COCHISE

U-6A OFF-THE-SHELF T-42A 0-1D

INSTRUMENT TRAINER AIRPLANE

AV 010095

EOR OPfKIAl U«¡r ONI Y v/(vi blank) 1 FM 101-20-1

CHAPTER 1

OPERATIONS

Section I AIRCRAFT AUTHORIZATIONS

Aircraft authorizations are listed by TOE unit authorizations. The current Major Item Analysis (Data Sheets) contains details concerning authorizations for specific areas or commands.

-EOR-OFFICIAL USE ONLY

101-20-1 FM

*3»!O ]cn 1VI3IJJO MOT io Infantry Division(Active) Infantry Division(Reserve) Mechanized Division. Armored Division.... 1-1. BasisofIssue-AircraftAuthorizationperUnit. *HHC, InfBde(3) *HHB, DivArty *HHC, InfBde(3).... *HHB, DivArty *HHB, DivArty... *HHB, DivArty.... Armd CavSqdn Avn Bn,InfDiv Maint Bn Air CavSqdn Avn Bn,InfDiv Avn Co,MechDiv Maint Bn HHC, MechBde(3) Armd CavSqdn Maint Bn Armd CavSqdn... Avn Co,ArmdDiv. HHC, ArmdBde(3) *Avn GSCo *Aslt HelCo *Acft MaintCo.... *Air CavTrp(3)... *HHT, AirCavSqdn *Avn GSCo *Aslt HelCo *Acft MaintCo. *Air CavTrp... *Acft MaintCo.. *Air CavTrp.... UNIT RECAP RECAP-!/ RECAP RECAP RECAP RECAP RECAP RECAP RECAP RECAP RECAP RECAP RECAP 29-15 55-89 37-87 3742 29-25 55424 37 29-35 17-105 55424 17-208 17-206 17-205 17-108 17-105 17-108 17-105 17-87 1742 17 TOE 7-78 7-77 7- 7 5 742 6- 302 7 7- 7 5 742 7-78 7-77 6- 3 02 7 6-302 6-302 TOTAL ACFT 102 160 (13) (29) (18) (14) (81) (13) (29) (18) (14) (10) (12) (27) (14) (10) (12) (27) (14) 42 42 27 85 27 64 27 64 (1) (4) (1) 0) 1 1 1 (14) (30) (12) (12) (14) (12) (10) (14) (10) (12) (14) LOH 42 42 30 62 42 10 10 (6) (6) (6) 10 (6) 6 6 (27) AH-1G 27 33 15 (6) (6) (9) (9) 6 6 9 9 (23) (24) (23) UH-1H 45 30 28 30 65 (7) 13 (6) (1) (4) (7) (6) 13 (4) (1) (8) (1) (8) 8 4 8 8 1 1 1 CH47 CH-54 OV-1B OV-1C U-21 U-10 FFICIAL USE ONLY U-10 U-21 OV-1C OV-1B CH-54 CH-47 1 1 (7) (6) (1) (4) 30 0) (8) 28 65 (23) (24) UH-1H 6 (6) (9) 33 27 (27) AH-1G 6 (6) 30 62 (12) (30) (14) (10) LOH 1 1 (1) (4) (1) 42 85 (29) (13) (18) (81) (14) (27) 160 AC FT TOTAL 6-201 57-58 57-55 57-57 TOE 17-275 17-276 17-278 5742 55-99 29-55 17-108 57- 55-89 29-15 UNIT *Aslt Hel Co *Avn GS Co *Acft Maint Co *Air Cav Trp (3) *HHT, Air Cav Sqdn *Acft Maint Co *Air Cav Trp Avn Bn, Abn Div RECAP RECAP Maint Bn RECAP Air Cav Sqdn RECAP Maint Bn *HHC, Abn Div Bde (3) *HHB, Div Arty RECAP Airborne Division Unit (CONT). Authorization per of Issue — Aircraft 1-1. Basis CO

FM 101-20-1

101-20-1 FM AINf) isn. WiaUJO-TOJ Airmobile Division 1-1. BasisofIssue-AircraftAuthorizationperUnit(CONT). ♦HHC, AmblDivBde(3) TC Bn,AcftMaint Air CavSqdn Med Bn Avn Gp Div Arty *HHT, AirCavSqdn *Avn Co(GS) *Avn Btry(DivArty) Acft MaintCo(2) HHC, TCM&SBn Air CavTrp(3) HHC, MedBn Aslt HelBn(2) Aslt SptHelBn FA BnAerialArty Aslt HelCo(6) Atk HelCo(2) HHC, AsltHelBn(2).. Arty Btry,Aer(3) *HHC, AsltSptHelBn H&S Btry,AerialArty. Aslt SptHelCo(3). UNIT RECAP RECAP RECAP RECAP RECAP RECAP RECAP RECAP RECAP 67-42 55-406 55-407 55-405 17-98 17-96 17-95 67 TOE 8-26 8- 2 5 7- 2 58 7-256 7-257 7-255 7-202 7- 2 00 6- 7 27 6-726 6-702 1-167 6-725 6-700 1-166 1-165 (120) ACFT TOTAL 422 226 (36) 150 (81) (12) (24) (26) (48) (36) (19) 85 12 50 39 (4) 58 O) (4) (6) (2) (3) 5 (24) (30) (10) (16) LOH 30 88 (2) 16 (6) 16 2 6 (27) (24) (36) AH-1G 27 24 24 87 36 36 (120) UH-1H (12) 120 132 (24) (12) (10) 193 28 12 (2) 0) (4) (2) (3) (3) 3 2 3 6 i (48) CH47 48 48 48 CH-54 OV-1B OV-1C U-21 UH-1M STANO (6) U-10 RO R ornetAL use U-10 U-21 OV-1C OV-1B O CH-54 16 16 (16) CH-47 3 3 3 2 2 2 8 (5) (4) (2) (7) (9) (4) (8) (1) (2) 16 28 74 (24) (69) 135 UH-1H 9 (9) 18 27 45 99 (27) (45) (18) AH-1G 9 6 (8) (6) (9) (9) (8) 10 30 80 (30) (10) LOH 8 6 8 6 2 (2) (4) 11 8 11 8 (8) 85 71 26 11 8 (81) (13) (17) (54) (87) (10) (26) (17) (11) 114 330 ACFT TOTAL 7-102 1-258 6 7 7- 7-357 02 3 6- 17-102 TOE 17-185 17-187 17-175 17-196 17-198 37-102 57-102 77-102 17-105 17-108 17-186 17-87 55424 6742 1742 17-145 29-35 RECAP RECAP RECAP RECAP RECAP RECAP UNIT Acft Maint Co HHT, Air Cav Sqdn Air Cav Trp HHT, Air Cav Atk Sqdn .... Atk Hel Co (3) Aslt Spt Hel Co Aslt Hel Co (37 Avn Co (GS) Air Cav Trp HHC, Avn Bn *HHC, Mech Bde (Sep) *HHC, Abn Bde (Sep) *HHC, Light Inf Bde . *HHC, Inf Bde (Sep) . *HHC, Armd Bde (Sep) HHC, Ambl Bde Maint Bn Air Cav Sqdn Air Cav Atk Sqdn Armd Cav Sqdn HHC, Armd Bde (2) Avn Bn HHB, Div Arty Separate Brigades Unit (CONT). Authorization per Issue — Aircraft 1-1 Basis of TRICAP Division I wi

FM 101-20-1 "“POR OmChfrtr-PSC ONLX U-10 1 2 5 U-21 OV-1C OV-1B CH-54 1 16 CH47 1 1 5 1 4 2 2 (8) (6) (8) (4) (1) 22 28 UH-1H (24) (9) 27 AH-1G (27) 1 1 2 3 3 4 2 (2) (6) 18 (1) 30 32 LOH (10) (30) 8 5 5 2 2 9 (4) (2) 13 JO 85 17 32 49 ACFT TOTAL (10) (12) (27) (81) 1-66 1-207 1-127 1-137 1-177 1-252 1-256 1-258 1-500 5-35 5-36 5-52 TOE 17-51 17-56 17-58 17-195 17-52 17-196 17-198 RECAP RECAP RECAP * UNIT .. HHT, Armd Cav Regt ... *HHT, Cav Sqdn ... HHT, Cav Sqdn (3) Air Cav Trp (3) HHC, Engr Cbt Bn .... *Air Cav Trp Armored Cavalry Regiment *Air Traffic Control . *Avn Co, Corps *Avn Co, Army Recon Hel Co . Air Cav Sqdn (Separate) Avn Bde, HHC *Engr Cbt Gp, HHC Avn Co, Aslt Spt Hel *Engr Cbt Bn, Army/Corps Avn Gp, HHC Avn Bn, HHC Avn Operating Teams per Unit (CONT). Authorization Basis of Issue - Aircraft ¿> 1-1.

FM 101-20-1

101-20-1 FM

3Sn 1VIDIJJO \io-i Corps SignalBn Med Det,HelAmbulance(RA) Med Det,HelAmbulance(RC) Med Co,AirAmbulance Avn Co,AsltHel—Separate... Engr ConstBde,HHC. HHB, FABde(Pershing) HHB, AbnCorpsArty HHB, CorpsArty HHB, FieldArtyGp... Engr ConstGp,HHC.. Engr CbtBde,HHC... Field ArtyBn(Pershing) *Engr BaseSurveyCo. *Engr TOPOCo,Corps *Engr Comd,HHC.... 1-1. BasisofIssue—AircraftAuthorizationperUnit(CONT). HHC, CorpsSigBn HHB, FABn(Pershing) UNIT RECAP RECAP 11-16 11-15 TOE 5-101 7- 357 6-616 6- 615 6-604 6-502 6-501 6- 4 01 5- 3 48 5-327 5-201 5-112 5-111 8-660 8-660 8- 137 TOTAL AC FT 25 29 (4) (6) 4 4 3 2 2 6 5 5 3 2 6 6 6 1 LOH (1) 4 2 2 2 2 6 2 2 6 1 AH-1G UH-1H 25 23 (4) (5) 4 6 2 5 CH-47 CH-54 OV-1B OV-1C U-21 U-10 FM 101-20-1 1-1. Basis of Issue — Aircraft Authorization per Unit (CONT).

TOTAL UNIT TOE ACFT LOH AH-1G UH-1H CH47 CH-54 OV-1B OV-1C U-21 U-10

Signal Const Bn RECAP 11-25 4 4 *HHC, Sig Const Bn 11-26 (4) (4)

Signal Cable Const Bn RECAP 11-45 3 3 *HHC, Sig Cable Const Bn .... 1146 (3) (3)

Army Comd Sig Rdo/Cable Bn RECAP 11-75 3 '2 1 *HHC, Army Comd Sig Rdo/Cab Bn 11-76 (3) (2) (1)

Army Area Sig Bn RECAP 11-85 1 1 *HHC Sig Army Area Bn 11-86 0) (1) r i Army Comd Sig Op Bn RECAP 11-95 9 2 5 2 *HHC, Army Cömd Sig Op Bn 11-96 (9) (2) (5) (2)

*HHC Sig Bde, Army 11-102 3 2 1

HMD, Sig Bn 11-116 1 1

*HHD, Sig Gpi Army 11-122 4 2 1

Abn Corps, Sig Bn RECAP 11-225 6 1 5 HHC, Sig Bn, Abn Corps 11-226 (6) 0) (5)

HHC, USA Strategic Command 11-302 1

*Sig Co, Msgr 11-358 7 2

Sig Radio Relay Co 11-377 1 1

*Avn Co, Atk Hel 17-111 23 21 2 FOR OFFICIAL USE ONLY 2 (2) (2) U-10 9 1 5 15*1 (5) U-21 18 OV-1D 12 OV-1C OV-1B CH-47 32/ UH-1H AH-1G 4 (4) (4) LOH 3 9 4 3 6 5 5 2 2 (6) (6) 15 12 (5) 18 18 ACFT TOTAL 39-52 32-97 44-2 TOE 32-59 2 5 32- 32-57 31-125 26 1 31- 28 1 30- 01 1 31- 72 2 19- 30-79 19-262 30-5 30-6 00 5 20- RECAP RECAP RECAP r; UNIT HHC, Spec Forces Spt Bn .. Recon Spt Spec Forces Spt Bn HHC, MI Bn, Air (MIBARS) ♦ADA Bde, HHB ... ♦ASA Avn Co (ELIS) . *ASA Co Div Spt ASA Avn Co (EW) ... Msl Comd (Air Trans) *ASA Gp Field Army Abn Spec Forces Gp Avn Co, Survl Airplane . ♦Scout Organization MI Co, Aerial Survl *MP Gp, HHD Unit (CONT). Authorization per of Issue - Aircraft 1-1. Basis Spt MI Bn, Air Recon *MP Bde, HHD (O

FM 101-20-1 rent-ornciAL use ONLY. U-10 U-21 OV-1C 0V-1B CH-54 CH-47 1 2 2 2 (2) UH-1H AH-1G 1 1 1 1 1 2 1 1 1 2 LOH 2 2 1 2 3 1 1 2 1 1 2 2 3 2 (2) 10 TOTAL ACFT TOE 44-12 54-12 2 2 54- 44-102 44-112 6 55- 55-11 55-62 55-111 55-112 55-202 55-259 55-457 55-465 55-458 55-466 RECAP UNIT Maint (Seaborne) ... HHC, Trans Acft Depot ADA Gp, HHB *ADA Bde, HHB *ADA Gp, HHB ♦FASCOM, HHC *Spt Bde, HHC ♦Trans Motor Trans Bde, HHC HHD . ♦Trans Mvmt Con Center, ♦Trans Tml Gp, HHC ♦Trans Bde, HHC (COSCOM) .. ♦Trans Tml Bde, HHC ♦Trans Rwy Gp, HHC Avn Co, Hvy Hel TC Co, Acft DS TC Co, Acft GS TC Bn, Acft Depot Maint per Unit (CONT). Authorization Basis of Issue — Aircraft o 1-1.

FM 101-20-1 LOR orriciAL use ONLY 12 y U-10 U-21 OV-1C OV-1B CH-54 11 11 CH-47 UH-1H AH-1G LOH 7 2 7 4 13 5/ 12 12 15 ACFT TOTAL WGZM WAY3 WG40 WA46 WHVC WGU WAX4 WAYL WG8H WGZL WE2E WG7G UIC WDHW WHMX WDHY UNIT

12th Avn Co, GS ... 236th Avn Co, ASHC 90th Avn Co, ASHC .

19th Avn Bn, HHC .... 352d Avn Det 2d Avn Det 44th Avn Det 367th Avn Det 23d Avn Det 358th Avn Det 70th Avn Det 5 2d Avn Det 3d Avn Det .. 6th Avn Hat . 4th Avn Det . USARSO USMA ARADCOM USARAL USARHAW USARV V Nonstandard BOI-Addendum Detachment and of Issue - Aviation 1-1. Basis USARRYUKYUI USAJAPAN USARSUPTHAI USAEIGHT

FM 101-20-1 JJ

101-20-1 FM

iMNO 3Cn IVIJIJjO MOT ¿J 1-1.BasisofIssue-AviationDetachmentandNonstandardBOI--Addendum2/(CONT). y InASOPandJSOPhassameBOIasActiveInfantryDivision(160aircraft). Source: OACSFOR y OneU-21authorizedtounitsubordinateARADCOMbyMTOEincludedhere. V Thisaddendumisprovidedtoaccountforthoseaircraftauthorizationswhich,inadditionthe 2/ RU-Typeaircraft. NOTE. OrganicDSmaintenancecapabilityistobeprovidedinthoseunitswhichareunderlined. * AircraftBOIchangesfrom“T”,“G”or“H”seriesTOE. SETAE USAREUR 6th AvnDet 357th AvnDet..(BELGIUM) 356th AvnDet 22d AvnDetAWSCOM 56th AvnDet IstAvnDet preceeding BOI,areusedtocomputecommandrequirements. UNIT C WDHX 4 WG1H WG1G WAY1 WFKA WAYZ UIC ACFT TOTAL 2 7 8 5 1 LOH AH-1G UH-1H 2 3 3 a CH-47 CH-54 OV-1B OV-1C U-21 U-10 FM 101-20-1

1-2. Test and Test Support Aircraft. 1-3. Authorized Aircraft Designations.

Requirements for test and test support aircraft are a. All Department of Army Aircraft have been established as follows: assigned designations in accordance with provisions of AR 700-26. Explanation of terms are as follows: a. All plans of test or development programs which require the use of aircraft for any phase will (1) Status prefix symbol. The status symbol identify the specific type of aircraft required and the (letter), will indicate an aircraft being used for purpose (e.g., competitive evaluation of navigation aids experimentation and special or service test and will be in utility helicopter, air transportability of missile in placed at the immediate left of the modified mission cargo helicopter). symbol, or the mission/type symbol if no modified mission symbol is applicable. b. The agency providing test service to customers normally requires one aircraft to support two plans of (2) Modified mission symbol. A letter used to test, with the following exceptions: indicate the current capabUity of an aircraft when it is so modified that its original intended capability is no (1) An aircraft which is on bailment for an longer applicable, or when it has an added or restricted extended period cannot be considered as an available capability. The modified mission symbol will consist of asset to fill additional requirements. a prefix letter placed at the immediate left of the basic mission or type symbol. Only one modified mission (2) An aircraft which has been modified to a symbol will be used in any one designation. special configuration (flying lab, ski installation) in support of a particular specialized long range R & D (3) Basic mission symbol. A letter used to program may not be considered as a suitable available indicate the basic intended function or capability of asset to apply against normal test and test support the aircraft, such as observation, utility, etc. aircraft requirements during a given fiscal year. (How- ever, this aircraft may become available for use in (4) Type symbol. An additional letter which other programs in subsequent years.) Nonstandard air- designates helicopter and V/STOL aircraft. An aircraft craft assets shall not be considered as suitable sub- identified by a type symbol, such as “H” for heli- stitutes for Army aircraft when computing test and test copter, will be further identified by only one mission support aircraft requirements. Requirements should be symbol whether it be basic mission or a modified based on use of Army-type aircraft to support Army mission symbol. (A basic mission or type symbol, once programs. Use of nonstandard aircraft (C-47, T-28) for officially assigned, will not be changed without the Army test programs will be authorized only if an Army- approval of the Assistant Secretary of Defense type aircraft cannot be made available or is not suitable (Installation and Logistics)). for the intended purpose. (5) Design number. The sequence number of each new design of the same basic mission or type aircraft. A number will be assigned consecutively for each basic mission or type. New design numbers will Example: A USAF jet aircraft may be necés- be assigned when an existing aircraft is redesigned to sary for missile chase at firing sites. an extent that it no longer reflects the original configuration or capability. c. In addition to those aircraft required to support research, development, test, and evaluation, a require- (6) Series letter. A letter used to denote ment is established for allocation of additional aircraft. differences affecting the relation of the vehicle to its Three models of each new type aircraft will be pro- ground environment, and major modifications to the cured by Department of the Army. The three aircraft aircraft which result in significant changes to its will be assigned to USA Test activities and will be logistic support. A letter will be assigned to each series utilized during the service life of that particular type change of a specific basic design. In designing new aircraft for service and logistical testing. aircraft, the series letter will be in consecutive order TOR OrFfCIAL U5C-ONLY- 1-13 FM 101-20-1 starting with the letter “A.” To avoid confusion, the (7) Complete designation. The complete letters “I” and “O” will not be used as series symbols. designation shall consist of items (1) through (6) as (Examples of series symbol change would be instal- applicable, in the order shown. A dash (—) will be lation of different engines, propellers, extra fuel tank, inserted between the basic mission/type symbol and etc.) the design number.

EXAMPLE: Y U H - 1 A

Status Prefix Symbol (Prototype)-< 1 Basic Mission Symbol (Utility Mission)-* Type Symbol (Helicopter Type) -* Design Number (No. Type Helicopter)-* Series Letter (1st Series)-*

b. Status prefix symbols (classification letters) are as follows:

LETTER TITLE DESCRIPTION

G Permanently An aircraft permanently grounded, Grounded used for ground instruction and training.

J Special Test, Aircraft on special test programs Temporary by authorized organizations or on bailment contract having a special test configuration or whose installed property has been temporarily removed to accommodate the test. At completion of the test, the vehicle will be returned either to its original configuration or to standard operational configuration.

N Special Test, Aircraft on special test programs Permanent by authorized activities or on bailment contract, whose configuration is so drastically changed that return of aircraft to its original configuration or conversion to standard operational configuration is beyond practicable or economical limits.

X Experimental Aircraft in a developmental, experimental stage where basic mission and design number have been designated but no established as a standard vehicle for service use.

1-14 FOR OFFICIAL USE ONLY FM 101-20-1

LETTER TITLE DESCRIPTION

Y Prototype Aircraft procured in limited quantities to develop the potentialities of the design.

Z Planning Designations used for identification purpose during the planning or pre- development stage.

c. Modified missions symbols (prefix letters) are as follows:

LETTER TITLE DESCRIPTION

A Attack Aircraft modified to search out, attack, and destroy enemy land or sea targets, using conventional or special weapons. Also used for interdiction and close air support mission.

C Cargo/ Aircraft modified for canying cargo Transport and/or passengers.

R Reconnaissance Aircraft modified and permanently equipped for photographic and/or electronic reconnaissance missions.

T Trainer Aircraft modified and equipped for training purposes.

U Utility Aircraft having small payload, modified to perform miscellaneous missions such as carrying cargo or passengers, and towing targets.

V Staff Aircraft modified to provide accommodations such as chairs, tables, lounge, and berths for the transportation of staff personnel.

d. Basic mission and type symbols are as follows:

LETTER TITLE DESCRIPTION

A Attack Aircraft designed to search out, attack, and destroy enemy land or sea targets, using conventional or special weapons. Also used for interdiction and close air support missions.

cnp nccin A I IICC nim-v 1-15 FM 101-20-1

LETTER TITLE DESCRIPTION

C Cargo/ Aircraft designed for carrying cargo Transport and/or passengers.

H Helicopter A rotary-wing aircraft designed with the capability of flight in any plan; e.g., horizontal, vertical, or diagonal.

O Observation Aircraft designed to observe (through visual or other means) and report tactical information concerning composition and disposition of enemy forces, troops, and supplies in an active combat area.

R Reconnaissance Aircraft designed to perform reconnaissance missions.

T Trainer Aircraft designed for training personnel in the operation of aircraft and/or related equipment, and having provisions for instructor personnel.

U Utility Aircraft used for miscellaneous missions such as carrying cargo and/or passengers, towing targets, etc. These aircraft include those having a small payload.

V VTOL and Aircraft designed for vertical STOL takeoff or landing with no takeoff or landing roll, or aircraft capable of takeoff and landing in a minimum prescribed distance.

X Research Aircraft designed for testing configurations of radical nature. These aircraft are not normally intended for use as tactical aircraft.

e. Application for a special aircraft designation or cancellation of a previously authorized designation may be accomplished by addressing the request to C.G. U.S. Army Materiel Command, Attn: AMCRD-F, Washington, D.C. 20315.

1-16 FM 101-20-1

Section II. (FOUO) FLYING HOUR PROGRAM

The flying hour program can be calculated by development of command flying hour programs in- taking the average inventory for the command and clude: the projected aircraft inventory, mission require- multiplying it by the annual flying hour program for ments of the command, aviator availability, budgetary the particular aircraft. limitations, logistical considerations and other variables \ which may affect aircraft utilization within the Example: commands. The DA Flying Hour Program is not USCONARC expressed in flying hour rates. OV-1 — Fiscal year 1972 Average number of aircraft 13 c. The basic flying hour planning factors con- Annual flying hour rate 240 tained below are suitable for use in intermediate and 13 X 240 = 3120 hours long range planning at any level of command. Two points of rationale used in the development of these Source: OACSFOR factors should be considered in planning applications; these are:

(1) Aircraft assigned to TOE units are in- 1-4. (FOUO) Basic Annual Flying Hour Planning Fac- tended to meet combat requirements. In a peacetime tors i/- situation or non-combat environment, utilization of these aircraft should be restricted to only that flying a. A Worldwide Flying Hour Program is developed time necessary to provide adequate training for avia- annually by the Department of the Army for use in tion units and other units which are supported by budget preparation and in planning for logistical sup- aviation units. port of aircraft. It is used as a basis for management of the entire aircraft inventory and is not applicable to (2) Indirect support aircraft are assigned to the operation of a single aircraft or to the aircraft of meet specific administrative and training requirements. any specific aviation unit or activity. Utilization of indirect support aircraft, except training and training support aircraft assigned to the aviation ' b. The flying hour program for each major training base, must meet or exceed the planning factors command is published annually in Annex V, Volume II shown, to justify their retention in the aircraft inven- of the Department of the Army Program and Budget tory at every level of command. Utilization of training Guidance Document. This document lists flying hour base aircraft is determined by the student training rate guidance in bulk flying hours for each type of aircraft approved or programmed for the year under considera- assigned to the major commands. Factors considered in tion.

FOR OfFICIAL USD-QNl* 1-17 FM 101-20-1

1-5. (FOUO) Basic Annual Flying Hour Planning Factors 1/.

TYPE TOE TOE INDIRECT AIRCRAFT PEACETIME OR ACTIVE SUPPORT NON-COMBAT COMBAT AIRCRAFT (WORLDWIDE) ENVIRONMENT ENVIRONMENT ALL ENVIRONMENT-2/ (WORLDWIDE)

0-1 960 U-6 300 600 600 U-8/10 384 900 600 U-21 384 900 600 OV-1 240 840 600 T-42 600 T-41 600 U-1A 360 720 600 OH-6 240 840 420 OH-13 240 660 420 OH-23 240 660 420 OH-58 240 840 420 UH-1 (Armed) 240 720 420 UH-1B/C 324 720 420 UH-1D/H 324 960 420 AH-1G 240 840 CH-34 172 600 420 CH-47 240 720 420 CH-54 180 600

I/All factors include associated float aircraft. 2/Does not include training and training support aircraft assigned to the training base.

Source: OACSFOR

1-18 EOP OFFICIAL USE-ONLY* FM 101-20-1

Section III. ATTRITION

1-6. Attrition Factors, Worldwide Monthly Rates.

WORLD WIDE AIRCRAFT SYSTEMS PEACETIME

Airplane Observation: 0-1 .0018 Airplane Combat Surveillance: OV-1 .0010 Airplane Utility: U-6 .0012 Airplane Utility: U-10 .0025 Airplane Fixed Wing Trainer: T-41 .0011 Airplane Instrument Trainer: T-42 .0009 Airplane Utility: U-8 .0016 Airplane Utility: U-21 .0016 Airplane Utility: U-l .0021

Helicopter Instrument Trainer: TH-13 .0012 Helicopter Primary Trainer: TH-55 .0015 Helicopter Cargo Transport: CH-47 .0009 Helicopter Cargo Transport: CH-54 af .0009 Helicopter Observation: OH-6 .0048 Helicopter Observation: OH-13 .0021 Helicopter Observation: OH-23 .0011 Helicopter Observation: OH-58 y .0048 Helicopter Utility: UH-1 .0025 Helicopter Cargo Transport: CH-34 .0022 Helicopter Attack: AH-1G .0031

World-Wide Peacetime Factors With Insufficient Or Unrealistic Experience Data: i/U-10. Factor of .0050 considered unrealistic. Losses during preceding 12 month period totaled 2 while only 1 loss occurred during prior 24 month period. The factor shown is based on the prior 24 month period. 2/ U-21. No peacetime loss experience. The factor shown is based on U-8. l/U-l. Factor of .0031 considered excessive due to high loss experience during preceding 12 month period. The factor shown is based on the prior 24 month period. V CH-54. No peacetime loss experience. The factor shown is based on CH-47. l/ OH-58. No peacetime loss experience. The factor shown is based on OH-6. Source: AMSAV-D-ZRA

FOR OFFICIAL USE ONLY 1-19 FM 101-20-1

1-7. Formula For Calculating Monthly Attrition Maintenance Trainers, (c) Depot inventory, and (d) Factors. aircraft in-transit.

Example: 3. Attrition during time frame = 29. Peacetime Attrition Factor. 0-1 Aircraft. 4. Calculation: 1. Time Frame = 36 months. 29 attrition -s- 455 density -5- 36 2. Density (average) = 455. Nóte: To arrive at an months = .0018. (Monthly peacetime attrition factor) average in use density the following category of aircraft were deleted, (a) USARV inventory, (b) Source: AMSAV-D-ZRA

Section IV. STANDARD AIRCRAFT CHARACTERISTICS

Standard aircraft characteristic data contained deletions of aircraft components or equipment are herein will change as modifications or additions and made.

1-20 Egn orrieiAi use OMIT- FM 101-20-1

AV 000002

Figure 1-1. AH-1G (Hueycobra)

1-21 FM 101-20-1

•3 FT 6 IN. i?

10 FT 3 IN. /°\ p-3 FTH *.7 FT 4 IN.

t *4 FT

52 FT 11.65 IN. 14 FT 4 IN. 8 FT 6 IN.

0^3 ¿23 13 FT SVi IN.-

2 FT 4-1/4 IN.

—44 FT 5.2 IN.

AV 000003

Figure 1-2. Principal dimensions, AH-1G (HueycobraJ

1-22 ■COR omcmt use om-^ -ron ornciAL une ONLY 2.4 3.3 3.7 2.8 2.9 3.5 L.F. 8148 (C) 9500 7937 (C) 7020 (C) 9500 6231 (C) 6600 5425 (C) LB. 5479*(C) AVIONICS WEIGHTS ARMAMENT FUEL AND OIL Location Fuselage Qty 3.4 gal Spec MIL-L-7808 No. tanks 1 Location Fuselage Qty 247 gal Spec MIL-T-5624 No. tanks 2 Grade JP-4/5 - Heavy Scout Hog Light Scout Clean Refer to chapter 2. Refer to chapter 2. * For Basic Mission OU: Fuel: (C) Calculated Max. Takeoff Max. Landing Design Combat LOADING Basic Empty 4' m PERSONNEL Pilot Copilot.. . Pilot 1 Gunner 1 Ferry Mission Hog Mission Light Scout, Heavy Scout or DEVELOPMENT Mfr’s Model: Bell 209 DESCRIPTION MISSION AND FEATURES lizer bar and provides a stable gun platform. external stores on wings. System (SAS) eliminates stabi- critical components. Hardpoints for rockets, and Stability Control Augmentation Armor protection for crew and Advanced flexible gun turret. 18 September 1966 First acft delivered 4 April 1966 Date of contract 7 September 1965 First flight (Similar aircraft) combat proven. of weapons to capability of quickly changing a wide combination maintainability are match the desired mission. Reliability and parts which have been ensured through the use of many UH-1 stations and an integral maneuverability and speed. Four wing stores versatility with the chin turret provide a high degree of armament level plus increased rotor system gives a low vibration all normal and emèrgency situations. the 540 “Door Hinge” A mission designed fuselage coupled with to give both pilot and gunner nearly featuring tandem seating of functions under control systems permitting flexibility in division crew stations have flight control and fire unlimited visibility. Both or night flying, and to navigate by dead unprepared areas, day from +125 F to below freezing conditions. temperatures, including target acquisition, reconnaissance by fire, speed flight, search and or performing these missions from prepared aircraft is capable of of operation within a wide range reckoning or instrument “HueyCobra” is of compact design The gas turbine powered support, and troop helicopter support. The multiple weapons fire delivering weapons fire, low altitude high helicopter capable of of this aircraft are that of an armed tactical The primary missions (LBS) DIMENSIONS POWERPLANT ENGINE RATINGS ance (static) 7 ft, 10 in. lateral) 10 ft, 4 in. operating 53 ft. Rotor gnd clear- Height 11 ft, 7 in. Tread 7 ft, 4 in. Rotors static 53 ft. Span (max Rotors Fuselage 44 ft, 5-1/4 in. SEA NET STD ESHP SHP THRUST RPM MIN to the TH-1G. »TH-1G. Addition of Instructor Flight Controls and Instrument Panel converts the AH-1G Length: Rotor dia 44 ft Normal 1296 1250 115 6040 Cont. Military 1450 1400 126 6300 30 LEVEL JET 0.3115 Reduction Gear Ratio None Augmentation Fixed Area Tail Pipe Lycoming Mfi Characteristics. (Hueycobra) 1-8. AH-1G/TH-1G* 104.33 Engine Spec. No Free Power Turbine Type (1)T53-L-13 No. and Model IS) W

FM 101-20-1 -EOR-OmCIAL l> 6.97 5.05 0 0 2.7 5.6 2.7 65 60 192 192 141 371.1 1600 7671 1210 1860 18200 10650 10000 10000 IV MISSION FERRY (CLEAN) 8.64 6.25 4.0 9.2 1.4 65 65 70.1 953 604 127 344 125 9500 2668 HOG 1230 11420 10000 5600/7200 III MISSION ft ft 8.64 6.25 4.0 9.2 1.8 65 65 95.3 127 344 125 1205 1384 9500 2416 1230 11420 10000 5350/7250 II MISSION HEAVY SCOUT 8.34 6.04 3.7 8.3 2.4 65 64 105 267 141.1 133 1500 1792 1384 9171 1330 12450 10000 I MISSION 6350/9800 LIGHT SCOUT (4) O)" (1)* (1)* (1)* (2)* (2) (2) (2) O) (3) (3) * CONDITIONS (Grade JP4) (lb) Fuel at 6.5 Ibs/gal (lb) Payload (Outbound) (lb) Payload (inbound) (lb SHP) Takeoff Power Loading (lb sq ft) Disk Loading (Min. R/D) (kn) Autorotation Speed at SL (ft) Takeoff Ground Run ft (ft) Takeoff to Clear 50 at SL (fpm) Vertical Rate of Climb (kn) Speed for Max R/C at SL (fpm) Maximum Rate of Climb at SL (min) Time: SL to 5000 ft (min) Time: SL to 10,000 ft (ft) Service Ceiling (100 fpm) (ft) Absolute Hovering Ceiling (kn) Average Cruise Speed (ft) Cruising Altitude (Initial) (ft) Cruising Altitude (Final) (hr) Total Mission Time (kn) Average Cruise Speed .(ft) Cruising Altitude (Outboard) (Min/Max) (ft) Cruising Altitude (Inboard) (hr) Total Mission Time (Hueycobra). AH-1G Typical Mission - Performance Loading and 1-9. lb) ( WEIGHT TAKEOFF (mi) COMBAT RANGE (nmi) COMBAT RADIUS n

FM 101-20-1 ■EOR orriciAL use ONLY 125 0 0 0 0 54 149 154 155 6231 2490 6231 2170 17700 10000 24550 23800 IV MISSION FERRY (CLEAN) 0 0 0 0 58 132 135 132 6578 2140 2140 7020 HOG 13750 20200 21000 Sea Level III MISSION 0 0 61 137 139 137 1745 1745 7383 9450 7937 17100 16250 Sea Level II MISSION HEAVY SCOUT 0 0 0 0 62 140 142 140 1665 1665 7413 8500 8148 15350 16300 Sea Level I MISSION LIGHT SCOUT (2)* (2)* (1) (1)* (1)* (2)* (2)* (2) (2) (2) (2) r CONDITIONS , are presented on paragraph 1-10 shaft horsepower * Based on transmission limit of 1100 (c) All data are for 6600 rpm. Phase B Flight Test Results of the AH-1G Bell Helicopter (HueyCobra)”. (a) Power required is based on “Engineering based on Lycoming Model Spec. 104.33. (b) Power available and fuel flow are pounds (4) Includes crew of two (2) at 400 included. (5) Smoke grenades and full ammo load (2) Normal rated power range missions (3) Detailed description of radius and (1) Military rated power PERFORMANCE BASIS NOTES (ft) Total from 50 ft (kn) Basic Speed at 5000 ft -(ft) Ground Roll at SL (kn) Speed for Max R/C at SL Ceiling (ft) Absolute Hovering (kn) Max Speed at SL ft/min) (ft) Combat Ceiling (500 ft/min) (ft) Service Ceiling (100 ft (ft) Takeoff to Clear 50 (fpm) Maximum Rate of Climb at SL (fpm) Combat Climb at SL (ft) Takeoff Ground Run (ft) Combat Altitude (kn) Combat Speed (CONT). AH-1G (Hueycobra) — Typical Mission and Performance 1-9. Loading (lb) LANDING WEIGHT (lb) COMBAT WEIGHT

FM 101-20-1 FM 101-20-1

1-10. Performance Notes, AH-1G (Hueycobra). and fire rockets during a period of ten (10) minutes combat at normal power. Climb on course to 10,000 LIGHT SCOUT MISSION - Armed Tactical feet at normal power and return to home base at Helicopter — Radius cruise speed. Range free allowances are two (2) Start engine; warm-up, takeoff, and climb on course at minutes of normal power for warm-up and takeoff, ten normal power to 6350 feet initial cruise altitude. (10) minutes of combat time at normal power, plus Maintain 55-feet-per-minute rate of climb at cruise ten percent of initial fuel for landing and reserve. speed to an altitude of 9800 feet. Descend to sea level and fire rockets during a period of ten (10) minutes FERRY MISSION — Clean (Without Auxihary combat at normal power. Climb on course to 10,000 Tanks) — Range feet at normal power and return to home base at Start engine, warm-up, takeoff, and climb on course at cruise speed. Range free allowances are two (2) normal power to 10,000 feet initial cruise altitude. Fly minutes of normal power for warm-up and takeoff, ten out at cruise speeds until ninety percent of initial fuel (10) minutes of combat time at normal power, plus is consumed and land at remote base. Range free ten percent of initial fuel for landing and reserve. allowance include two (2) minutes at normal rated power for warm-up and takeoff, and ten percent of HEAVY SCOUT MISSION - Armed Tactical initial fuel for landing and reserve. Helicopter — Radius Start engine, warm-up, takeoff, and climb on course at GENERAL NOTES: normal power to 5350 feet initial cruise altitude. a. Cruise speed as used above denotes airspeed Maintain 41.6-feet-per-minute rate of climb at cruise for long-range operation and is the greater of speed to an altitude of 7250 feet. Descend to sea level the two speeds at which ninety-nine percent and fire rockets during a period of ten (10) minutes of the maximum miles per pound of fuel are combat at normal power. Climb on course to 10,000 attainable at the momentary weight and feet at normal power and return to home base at altitude. cruise speed. Range free allowances are two (2) minutes of normal power for warm-up and takeoff, ten b. Data do not include ground effect. (10) minutes of combat time at normal power, plus ten percent of initial fuel for landing and reserve. PERFORMANCE BASIS: a. Power required is based upon “Engineering HOG MISSION — Armed Tactical Helicopter — Radius Phase B Flight-Test Data”. Start engine, warm-up, takeoff, and climb on course at normal power to 5600 feet initial cruise altitude. b. Power available and fuel flow are based on Maintain 50-feet-per-minute rate of climb at cruise Lycoming Model Specification No. 104.33, speed to an altitude of 7200 feet. Descend to sea level and includes particle separators and filters.

1-26 FOR OrriCHfcfc-USC ONL* FM 101-20-1

s ►* UK ;-’î lil S*; ’3H ItL - 4-e m mm t

wm «m -

s ■ ARMY

AV 000010

Figure 1-3. CH-34C (Choctaw)

fOR orriciAL use ONLY

446-903 0 - 71 - 3 FM 101-20-1

-56 FT-

n n □G

12 FT

46 FT 9 IN. ¿zz }- X

37 FT

65 FT 10 IN

ion \

AV 000011

Figure 14. Principal dimensions, CH-34C (Choctaw)

1-28 ■TOR ornciAL use ONLY- rriciAL use ONLY 2.44 2.63 2.44 2.63 L.F. 1100 115/145 10-1/2 gal 262 gal 2 Fuselage, fwd MIL-L-6082 LB MIL-G-5572 (1) 100 gal (1)70 gal (1)92 gal AVIONICS WEIGHTS ARMAMENT FUEL AND OIL Fuselage, aft . Fuselage, fwd. Fuselage, cen . Total qty .... Spec No. tanks: Spec No. tanks Location QtV Grade Grade (overload) .... +13,300 ,068 (normal) +12 (calculated) ... 7,660 note a paragraph 1-13.) Fuel: Refer to chapter 2. *For basic mission. Oil: ^Limited by max takeoff weight. None. Empty Basic 7,800 12,068 Design Max takeoff Max landing 413,300 (See +Limited by performance. Combat *8,930 Max takeoff 2 18 or PERSONNEL Litters 8 Troops Crew (normal) DEVELOPMENT S-58 Mfr’s Model: Sikorsky AND DESCRIPTION MISSION CAPACITIES procured for use by the Modified version of the Navy model XHSS-1 lifting hehcopter using a single main The CH-34C is a single-engine of the CH-34C helicopter is the transportation The principal mission Length 13 ft, 5 in. Width 5 ft Height above gnd .. 2 ft, 20 in. Width 4 ft, 5 in. Height 4 ft Floor area 67-3/4 sq ft to 37 feet. folding tail pylon reduces the stowage length March 1954 First flight (XHSS-1) December 1954 First flight March 1955 First acceptance Distance”, figure 1^. the CH-34C Cabin volume 405 cu ft Max cargo: See “Payload- Cargo compartment: and rotor flight controls incorporate two parallel 5000 pounds. Main by the tail servo systems. Torque compensation independent hydraulic a head- coordinated by engine torque to maintain rotor is automatically rotor head life, a hydraulic clutch ing. For ease of starting and to lengthen engine speed, at which point is used to accelerate the transmission to heating are provided for the positive clutching occurs. Ventilation and for winterization. The landing cockpit and cabin and provisions are made gear and a tail wheel. The gear consists of a main two-wheel alighting as a prototype model of Department of Army. The XHSS-1 served (including aeromedical evacuation). of cargo and personnel are tail rotor. The main and tail rotors rotor and a single antitorque mounted in of all-metal construction. The engine is four-bladed and are Access to inclined 35 degrees from horizontal. the nose facing aft and nose doors. is provided through clam-shell type the engine compartment up to is available for externally transporting and cargo. A cargo sling January 1959 Production completed patients, rapid loading of passengers, litter A large cabin door facihtates Cargo door: . Height 5 ft, 10 in. 9 DIMENSIONS POWERPLANT MIN BHP RPM ALT ENGINE RATINGS folded) 37 ft operating 65 ft, 10 in. Fuselage 46 ft, 9 in. Fuselage (pylon Rotors Rotors static .... 58 ft, 3-1/2 in. Idling 11 ft, 4-3/4 in. Static 9 ft, 2 in. clearance 6 ft, 6 in. lateral) 40 ft (Choctaw) Characteristics. 1-11. CH-34C Red. gear ratio .. D.D. Rotor dia 56 ft ... (1) R-1820-84C No. & model Engine spec No . N895D Span (max Length: 3500 Cont. Normal 1275 2500 except takeoff) METO power (max right Mfr W stg, 1 spd Superch 1 Height 15 ft, 11 in. Tread 12 ft Main rotor gnd clearance: 700 5 Takeoff 1525 2800 2400 30 Military 1425 2700 Tail rotor gnd

FM 101-20-1

101-20-1 FM o-ran 1VI3UJO x&i öd COMBAT WEIGHT^(lb) COMBAT RADIUS&(nmi) FIRST LANDINGWEIGHT-^(ib) COMBAT RANGE&(nmi) TAKEOFF WEIGHT&(lb) 1-T2. LoadingandPerformance•TypicalMission,CH-34C(Choctaw). Basic speedat5000ft2/ (ft) Max speedatSL-2/ (kn) Speed formaxrateofclimbat SL2/(kn) Max rateofclimbatSL-2/ (fpm) Takeoff groundrunatSL/clear50ft(ft) Absolute hoveringceiling-2/(ft) Service ceiling(100fpm)-2/(ft) Combat ceiling(500fpm)2/(ft) Combat climb^(fpm) Combat speed-2/(k) Combat altitude(ft) Ground rollatSL/clear50ft(ft) Total missiontime(hr) Cruising altitude(ft) Average cruisingspeed(kn) Total missiontime(hr) Cruising altitude(ft) Average cruisingspeed(kn) Absolute hoveringceiling5/.(ft) Service ceiling(100fpm)-^(ft) Time: SLto10,000ft3/(min) Time: SLto5000ft-^(min) n Max rateofclimbatSL-^(fpm) Speed formaxrateofclimbatSL(kn) Vertical rateofclimbatSL2/(fpm) Takeoff groundrunatSL/clear50ft-1/(ft) Autorotation speed(minR/D)(kn) Disk loading(Ib/sqft) Takeoff powerloading(lb/bhp) Payload (inbound)(lb) Payload (outbound)(lb) Fuel at6.0Ib/gal(grade100/130)(lb) CONDITIONS MISSION 20.500 BASIC 13,700 19.500 12,141 10,400 13,300 2540 8930 2330 5000 5000 5000 2100 None 3211 1120 1572 5.29 9.12 14.1 136 133 136 238 0/0 131 0/0 100 2.7 2.6 0/0 4.7 65 98 94 65 58 NORMAL 20.350 13,600 19.350 11,269 12,500 2279 12,068 2520 2300 5000 8990 5000 3.4 5000 4800 None 1370 1572 4.91 8.47 136 132 290 0/0 148 570 136 0/0 3.3 0/0 9.7 3.8 65 91 85 65 58 20.700 DESIGN 14,000 19.700 11,360 12,500 12,068 2580 2580 8854 4800 None 2506 1370 1356 4.91 8.47 136 133 133 251 9.7 0/0 116 570 0/0 2.5 0/0 2.8 3.8 SL SL 65 SL 93 90 65 58 à COMBAT 15,200 14,400 10.989 11.989 10,850 i 12,789 7800 5000 5000 1860 5000 1600 3000 2000 1200 3000 1572 5.20 8.98 12.7 126 128 126 245 0/0 123 210 0/0 2.7 2.6 0/0 4.4 65 92 95 65 58 EVACU- 14,700 14,100 11,123 11,200 18,200 ATION 7400 5000 9123 5000 1820 1560 2060 None 1830 3000 9789 1572 3.98 6.87 125 127 125 0/0 154 0/0 2.7 0/0 5.6 2.5 65 93 65 58 22,000 20,900 15,500 11,200 18,200 RANGE FERRY 8375 2790 2550 5000 5000 None None 2060 1830 9789 1572 3.98 6.87 137 371 134 137 0/0 0/0 3.4 3.8 0/0 5.6 2.5 65 98 65 58 FOR Of FICI AI USE 0/0 8375 RANGE FERRY 0/0 ATION 10,375 EVACU- 0/0 10,375 COMBAT 0/0 8342 DESIGN 0/0 8375 NORMAL 0/0 BASIC 8375 MISSION CONDITIONS a. Data source: Phase IV flight tests. b. Performance is based on powers shown. for takeoff and landing. c. Data do not include ground effect except 50 ft (ft) Ground roll at SL/clear ^ (lb) LANDING WEIGHT (CONT). CH-34C (Choctaw) - Typical Mission, and Performance 1-12, Loading Performance Basis: ■^/Military power. -l^Max power. are given in paragraph 1-13. of RADIUS and RANGE missions -^/Detailed descriptions 2 at 400 lb. -^/includes crew of takeoff). -2/METO (max except 0.8 at =90°. -2/Limited by Mach if (radius is shown. -2/ For RADIUS mission

FM 101-20-1 FM 101-20-1

1-13. Performance Notes, CH-34C (Choctaw). GENERAL DATA

FORMULA: RADIUS MISSIONS I & II a. Maximum overload takeoff weight is limited by the requirement that vertical climb at sea level on a Warm up, take off, climb on course to 5000 feet standard day with military power shall not be less than at METO power, cruise out at long range speeds to an 100 fpm. Maximum normal takeoff weight is limited advanced area, land, and unload cargo. Without refuel- by the requirement that vertical climb at sea level on a ing, warm up, take off, climb on course to 5000 feet hot day with military power shall not be less than 300 at METO power, and return at long range speeds. fpm. Range-free allowances are 10 minutes of METO power for warmups and takeoffs, plus 10 percent of initial b. Engine ratings shown are engine manufacturer’s fuel for reserve. guaranteed ratings. Power values used in performance calculations for the R-1820-84C engine are as follows: FORMULA: RADIUS MISSION HI

Same as Radius Missions I & II, except at sea CRITICAL level. BHP RPM ALTITUDE

FORMULA: RADIUS MISSION IV Max 1425 2800 2450

Same as Radius Missions I & II, except eight litter Military 1400 2700 2550 patients are carried on inbound leg. METO 1275 2500 3100 FORMULA: RADIUS MISSION V

Same as Radius Missions I & II, except payload is carried inbound instead of outbound.

FORMULA: RANGE MISSIONS I, II, IV & VI PERFORMANCE REFERENCE

Warm up, take off, climb on course to 5000 feet Sikorsky Aircraft Report No. 58123, Substantiat- at METO power, and cruise out at long range speeds ing Data for Standard Aircraft Characteristics and untfl only reserve fuel remains. Range-free allowances Performances Charts for H-34A Helicopter. are 5 minutes of METO power for warmup and takeoff, plus 10 percent of initial fuel for reserve. DATA SOURCE

FORMULA: RANGE MISSION III Sikorsky Aircraft Report No. SER 3236. Detail Specification. Same as Range Missions I, II, IV & VI, except at sea level. Wright Aero Div. Engine Spec. No. N-895D.

1-32 TOR OmetAL use ONL* Figure 1-5. CH47A, B, and C (Chinook), typical (minor differences apparent between A, B, and C models)

FOR orneiAL use ONL* 1-33 FM 101-20-1

— 12 FT 5 IN. —

<0. r

—4 11 FT. 11 IN. 1- 51 FT 2 IN. 2-J E

98 FT 3-1/4 IN.

18 FT 6-1/2 IN •17 FT 11 IN STATIC 10 FT 11 IN. G3 Q Q Q 7 FT 4-1/2 IN. STATIC 2 DEG 18 IN. MIN GND 51 FT CLEARANCE

• CONTROLS NEUTRAL AV 000017

Figure 1-6. Principal dimensions, CH47A (Chinook)

1-34 FOR orriciAL use ONL* -f

1-14. CH-47A (Chinook) Characteristics.

POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model . . (2) T55-L-7 Mfr’s Model: Vertol LB L.F. Empty (SPFG) . 18,084 Mfr . Lycoming The principal mission of the CH-47A helicopter is the transport of Design gross wt. 28,550 2.67 Engine spec No cargo, troops, and equipment within the combat area. In addition, Max alt gross wt 33.000 3.00 T55-L-5 . . . 124.18C this helicopter is suitable for special support functions. It is suitable Max takeoff . . 33.000 3.00 T55-L-7/7B . 124.20-A for operations during day, night, visual, and instrument conditions. Max landing . . 33.000 3.00 T55-L-7C 124.31 The CH-47A helicopter is a twin-turbine-engine, tandem rotary-wing aircraft. It is powered by two Lycoming T55-L-7 shaft turbine engines FUEL AND OIL ENGINE RATINGS mounted on the aft fuselage. The engines simultaneously drive two Fuel: SHP RPM ALT MIN tandem three-bladed rotary wings through a combining transmission, Grade . . . JP-4 T55-L-7 drive shafting, and reduction transmission. The forward transmis- Spec .... MIL-T-5624 MUitary 2650 15,150 SL 30 sion is mounted in the pylon above the cockpit. The aft transmis- No. tanks: Normal 2200 15,000 SL Cont. sion, the combining transmission, and drive shafting are located in the aft pylon section. A gas-turbined auxiliary power unit, used Nacelle . (2) 621 gal (50 T55-L-7B for starting the engines, is mounted in the aft pylon section. Pods percent self- Military 2650 15,800 SL 30 on the sides of the fuselage contain fuel tanks. The helicopter is sealing) Normal 2200 15,000 SL Cont. equipped with nonretractable quadricycle landing gear. The aft 630 gal (non- self-sealing) wheels are full-swivel type. The entrance door is located at the T55-L-7C Oil: Max 2850 16,000 SL 10 forward right side of the cabin fuselage section. At the rear of the cabin fuselage section is a hydraulically powered loading ramp. Spec Military 2650 15,750 SL 30 Temps above Normal 2500 15,350 SL Cont. A 16,000 pound cargo hook assembly is provided for transporting external loads. -25*F MIL-L-23699 Temps below DIMENSIONS -25*F MIL-L-7808 DEVELOPMENT No. tanks.... 2 Rotor dia .... 59 ft, 1-1/4 in. Location .... Integral with Length: Date of contract . 27 June 1960 engine Rotors First flight . . . . 6 September 1961 Qty 7 gal operating . . 98 ft, 3-1/4 in. Production status Completed May 1967 Rotors folded . 51 ft AVIONICS Fuselage .... 51 ft CAPACITIES PERSONNEL Height 18 ft, 6-1/2 in. Refer to chapter 2. Tread 11 ft, 6 in. Cargo compartment: Crew (normal) 4 Main rotor gnd clearance: Floor 226-1/4 Troops 33 ARMAMENT Idling (fwd) . . 10 ft, 11 in. Length 30 ft, 2 in. Litters 24 (aft) ... 18 ft, 6-1/2 in. Width 7 ft, 6 in. Refer to chapter 2. Static (fwd) . . 7 ft, 8 in. Height 6 ft, 6 in. (aft)... 17 ft, 11 in. Volume 1487 cu ft Forward door: FM 101-20-1 Height 5 ft, 6 in. Width 3 ft Cargo ramp door: Length 6 ft, 6 in. M tfl Width 7 ft, 6 in. FM 101-20-1

1-15. Loading and Performance - Typical Mission, CH-47A (Chinook).

MISSION MISSION MISSION CONDITIONS I II III

Gross weight (lb) . 28,262 33,000 33,000 Weight empty (lb) , 17,932 18,112 17,552 Payload (lb) , 6000 13,400 Radius of action (nmi) . 100 20 Ferry range ,(nmi) . 866 Cruise altitude (ft) , SL SL 6000 Cruise speed (kn) , 130 110 110 ^Max @ SL military power (kn) 130 110 110 ^Max @ SL normal power (kn) 130 110 110 ^Max @ 5000 ft, normal power 1 (kn) . 114 94 94 Hover ceiling OGE 95°F, military power, std atmosphere (ft) 6000 7900 7900 Hover ceiling IGE military power, std atmosphere . . (ft) 11.900 9200 9200 Service ceiling Normal power (ft) 11.900 9200 9200 Military power 1 eng out (ft) 6000 1400 1400 R/C Max — military power — SL (ft/min) 2750 2160 2166

NOTES: 1. All performance based on NASA standard atmosphere unless otherwise noted. 2. ^Max reflects airspeed limitations specified in TM55-1520-209-10. 3. CH-47A model specifications'114-X-601.

1-16. Performance Notes, CH-47A (Chinook). plate of external cargo = 26 sq ft. Cruise at sea level. Return with fuel reserve for 10-minute cruise at return FORMULA: MISSION I gross weight.

Deliver 6000-pound internal payload to any point 100 nautical miles and return with 3000-pound internal payload. Cruise at sea level. Land with 10 percent of initial fuel reserve. FORMULA: MISSION III

FORMULA: MISSION II Ferry Range of 866 nautical miles. Land with 10 percent of initial fuel reserve. Climb to 6000 feet, 256 Deliver 13,400-pound external payload to any nautical miles. Cruise 6000 feet for 610 nautical miles. point 20 nautical miles and return. Equivalent flat Total ferry time: 7 hours, 50 minutes.

1-36 •FOR OFFICIAL USE OHL* FM 101-20*1

12 FT 5 IN

-| 10 FT 6 IN. —

v: E

99 FT

18 FT 7-13/16 IN.

10 FT 11-1/16 IN. CO Q Ü Û Q

2° 9

51 FT

18 IN. MIN GND AV 000019 CLEARANCE

Figure 1-7. Principal dimensions, Ch47B and C (Chinook)

-fOR-ernciAL USE ONIY 1-37 EOR OrriCIAL USE-ONLY- LB L.F. AVIONICS WEIGHTS ARMAMENT FUEL AND OIL 25°F MIL-L-23699 25°F MIL-L-7808 Fuselage (2) 621 gal Temps above Temps below *For basic mission. Qty 7 gal Grade JP4 Spec MIL-T-5624 No. tanks: Engine contained oil supply Spec 2.54 gross weight ... 40,000 Fuel: *19,153 Empty Oil: 19,194 Basic * 33,000 3.00 Design Max alternate 33,000 3.00 Normal takeoff .. 40,000 2.54 Alternate takeoff. Refer to chapter 2. Refer to chapter 2. 21,734 3.00 Combat * 40,000 2.54 Max landing 4 24 or PERSONNEL Crew . Litters Troops ,.... 33 Completed February 1968 June 1966 October 1966 DEVELOPMENT Vertol Mfr’s Model: AND DESCRIPTION MISSION CAPACITIES (£door ... 3 ft, 6 in. tandem rotor helicopter with built-in The CH-47B is a large air of the CH47B helicopter is to provide The principal mission Floor 226-1/2 sq ft Height 6 ft, 6 in. Length 30 ft, 2-1/2 in. Length 6 ft, 6 in. Height 5 ft, 2-1/2 in. Height above ground Width ...... 7 ft, 6 in. Width 7 ft, 6 in. Width 2 ft, 10-3/4 in. for rescue of personnel. troops and litter patients and 2 attendants or 33 accomodations for 24 helicopter is equipped with an unobstructed troop commander. The First flight utilized and cargo. The aircraft can also be transportation for troops and has a with straight-in rear loading 30-foot long cargo compartment external cubic feet. Other features include an capacity of over 2450 operations; capacity which may be used for towing cargo hook of 10-ton system, thus which powers the utility hydraulic an auxihary power unit stability for external ground power sources; eliminating the requirement Vertol SAS; and provisions for utilizing system provided through capacity by 2000 gallons. collapsible fuel tanks to increase the fuel ranging from -25° F. to +125°F. Entrance door: Date of contract . Production status. Cargo compartment: operations in temperatures The complete helicopter is designed for Cargo ramp door: 4 DIMENSIONS MIN SHP RPM ALT POWERPLANT ENGINE RATINGS operating ... 98 ft, 11 in. 65.93:1 ratio 124.20-A T55-L-7B 124.31 T55-L-7C Rotors Fuselage 51 ft Idling fwd .... 10 ft, 11 in. Rotors folded . 51 ft Static fwd 7 ft, 2-1/2 in. Engine spec No. (Chinook) Characteristics. 1-17. CH-47B Lycoming Mfr Engine/rotor gear (2) T55-L-7C No. & model Rotor ground clearance : Rotor dia 60 ft Length: SL 10 Maximum 2850 16000 Height (overall) . 18 ft, 7-3/4 in. SL 30 Military 2650 15750 SL Cont Normal 2500 15350 Tread 10 ft, 6 in. co co

FM 101-20-1 ■EOR OFFICIAL USE ONLY 60 145-2/ 142 134 114 700-2/ V 1,075 1,520 1,090 9,550 7,400 40,000 FERRY MAXIMUM Id' MISSION 60 20 IV 138-1/.2/ 132-1/ 100-3/ 100 0 700-2/ 1,440 8,950 7,400 18,800 40,000 PAYLOAD MISSION^ EXTERNAL 60 95 145-â' 114 142 134 700-2/ m 1,520-2/ 7,935 9,550 7,400 15,900 40,000 PRIMARY MISSION-^/ 165-2/ 150 163 144 134 100 II 9,000 4,500 2,200-2/ 3,650 BASIC 33,000 10,650 14,200 MISSION^ GW) (DESIGN 168-2/ 166 138 145 100 100 I 6,000 3.000 7.000 3,500 2,440-2/ 2,300 2/ 1,800-2/ 6,000 6,050 BASIC 30,900 18,000 16,200 12,850 16,300 á/ MISSION (lb) (lb) (lb) (lb) (lb) (kn) (kn). (kn). (kn). (kn). • (ft). . (ft). • (ft). (nmi). (nmi). (nmi). - (ft)- ... (ft). (ft/min). (ft/min), 4 Guaranteed Estimated ! Estimated Estimated Guaranteed normal power, power power maximum power maximum power, 10 ft wheel height . maximum power at I Guaranteed Estimated gross weight (outbound) Payload guaranteed power Vmax SL/STD, military SL/STD, Max cruise speed at (inbound) Payload guaranteed Payload estimated (outbound) V-Cruise (best range) at SL/STD V-Cruise (best range) at 5000 F Payload estimated (inbound) Ferry range Service ceiling, single engine at military Max rate-of-climb at SL/STD military Vertical rate-of-climb at SL/STD, Service ceiling at normal power Radius of action Hover ceiling, OGE at STD temperature Hover ceiling, IGE at STD temperature CONDITIONS CH-47B (Chinook) - Typical Mission, and Performance 1-18. Loading

FM 101-20-1 1-40 —TOR Orr-KIAL USE "ONLY 4 (CONT). CH-47B (Chinook) Mission, and Pertormance-Typical 1-18. Loading NOTES: area. to 26 ft. 2/drag payload equivalent •lAVith external at the gross weight required for the 6000 ft. for ten minutes at 95° F, OGE shall be capable of hovering at For Mission I the helicopter lb., and of 6000 lb., return payload of 3000 gross weight includes an outbound payload Mission 1 (guaranteed). The Mission 1 accomplishment of 100 nmi. fuel for a radius of all pertinent factors, see TM 55-1520-209-10. approved operational limits which consider performance capability only. For The above table reflects weight of maximum power and at a gross out-of-ground effect at sea level standard, helicopter shall be capable of hovering During Mission III the 39,500 pounds (guaranteed). ■transmission limit. ■^Mission cruise speed.

FM 101-20-1 FM 101-20-1

1-19. Performance Notes, CH-47B (Chinook). FORMULA: RANGE MISSION III

FORMULA: RADIUS MISSIONS I & II Warm up, take off, cruise out at long range speeds at sea level until 90 percent of initial fuel is consumed, Warm up, take off, climb on course to 5000 feet land, and unload cargo. Range-free allowances are 2 at normal power, cruise out at long range speeds to minutes of normal power for warmup and takeoff, plus remote base, land, and unload cargo. Without refueling, 10 percent of initial fuel for reserve. warm up, take off, climb on course to 5000 feet at normal power, and return at long range speeds. Range- free allowances are 2 minutes of normal power for FORMULA: RANGE MISSION IV each warmup and takeoff, plus 10 percent of initial fuel for reserve. Warm up, take off, cruise out at 100 knots at sea level with external cargo until 10 minutes of cruise FORMULA: RADIUS MISSION III fuel remains, detach cargo, and land. Range-free Warm up, take off, cruise out at long range speeds allowances are 2 minutes of normal power for warmup at sea level to remote base, land, and unload outbound and takeoff, plus 10 minutes of cruise fuel for reserve. cargo, load inbound cargo. Without refueling, warm up, take off, return at long range speeds at sea level, land, and ' unload cargo. Range-free allowances are 2 minutes FORMULA: RANGE MISSION V of normal power for each warmup and takeoff, plus 10 percent of initial fuel for reserve. Warm up, take off, climb on course to optimum cruise altitude at cruise speed, cruise out at long range FORMULA: RADIUS MISSION IV speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal power Warm up, take off, cruise out at 100 knots at sea for warmup and takeoff, plus 10 percent of initial fuel level with external cargo to remote base, detach cargo, for reserve. and land. Without refueling, warm up, take off, and return at long range speeds at sea level. Range-free allowances are 2 minutes of normal power for each warmup and takeoff, plus 10 minutes of cruise fuel for PERFORMANCE REFERENCES reserve. Vertol Report 114-P-J-602. Detail Specifications FORMULA: RANGE MISSIONS I & II for The Model CH-47B Helicopter.

Warm up, take off, climb on course to 5000 feet Boeing-Vertol Report 114-AD-6Ó1. Estimated at normal power, cruise out at long range speeds until Performance Capability of CH-47B and CH-47C Heli- 90 percent of initial fuel is consumed, land, and copters. unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent Lycoming Model Specification 124.31, T55-L-7C of iriitial fuel for reserve. Shaft Turbine Engine.

FOR ornciAL use ONLY 1-41 «2 -TOR ornciAL y L.F. LB WEIGHTS AVIONICS ARMAMENT 25° F MIL-L-23699 25° F MIL-L-7808 Fuselage main.. (2) 621 gal Fuselage aux... (4) 520 gal Temps above Temps below For basic mission. gross wt 46,000 takeoff 33,000 takeoff 46,000 Qty . 1141 gal Engine contained oil supply Grade JP4 Spec MIL-T-5624 No. tanks: Spec Qty 7 gal M 9,723 Empty 9,772 Basic M 3.00 Design 33,000 3.00 Combat -523,886 Max alternate Normal Alternate Fuel: 6,000 Max landing 4 Oil: Refer to chapter 2. Refer to chapter 2. FUEL AND OIL June 1966 January 1969 or PERSONNEL Crew 4 Litters 24 Troops 33 DEVELOPMENT Vertol Mfr’s Model: AND DESCRIPTION MISSION CLEARANCES at door 3 ft, 6 in. (floor) 30 ft, 2-1/2 in. air transportation is to provide mission of the CH47C The principal tandem rotor helicopter with built-in The CH47C is a large Floor 226-1/2 sq ft Height 5 ft, 2-1/2 in. Height above ground Width 7 ft, 6 in. Height 6 ft, 6 in. Length Length 6 ft, 6 in. Width 2 ft, 10-3/4 in. Width 7 ft, 6 in. of The aircraft can also be utilized for rescue for troops and cargo. personnel. 33 troops 24 litter patients and 2 attendants or accommodations for unobstructed The helicopter is equipped with an and troop commander. operations; capacity which may be used for towing cargó hook of 10-ton and has a with straight-in rear loading 30-foot long cargo compartment external cubic feet. Other features include an capacity of over 1450 stability for external ground power sources; eliminating the requirements Vertol SAS; and provisions for utilizing system provided through gallons. The to increase the fuel capacity by 2000 collapsible fuel tanks from -25°F to +125°F. system, thus which powers the utility hydraulic an auxiliary power unit in temperatures ranging complete helicopter is designed for operations Date of contract Cargo Ramp Door: Entrance Door: Aircraft in production Cargo Compartment: DIMENSIONS POWERPLANT MIN SHP RPM ALT ENGINE RATINGS operating ... 99 ft ratio 64.05:1 Rotors Rotors folded . 51 ft Fuselage 51 ft Static fwd .... 7 ft, 2-1/2 in. Idling fwd .... 10 ft, 11 in. .... (2)T55-L-11 No. & model Lycoming Mfr 124.27A Engine spec No .. Engine/Rotor gear SL 10 Max ... 3750 16000 SL 30 Mil.... 3400 16000 SL Cont. Nor ... 3000 15400 Rotor dia 60 ft Length: Height (overall) . 18 ft, 7-3/4 in. Rotor ground clearance Tread 10 ft, 6 in. (Chinook) Characteristics. 1-20. CH-47C < ■»

FM 101-20-1 fOR OFFICIAL USE ONLY 123*/ 123*/ 111*/ 123*/ V 1,226 1,3802/ 7,600 8,000*/ 46,000 FERRY MISSION MAXIMUM 20 1002/ 1002/ 1002/ 1002/ 0 1,2602/ 7,600 IV*/ 8,000*/ 23,300 46,000 MISSION PAYLOAD EXTERNAL 100 123*/ 111*/ 123^/ 123*/ III 1,3802/ 7,600 8,000*/ 9,875 19,750 46,000 MISSION PRIMARY 100 138 155 1642/ 140 1642/ II 2,8802/ 7,350 3,675 9,5502/ 2,5852' 14,750 15,000 15,0005/ BASIC 33,000 MISSION (DESIGN GW) 100 100 136 156*/ 141 156^ I 1,2202/ 9,600 2,045^ 6,650 6,000 4,000 4,5003' V 12,750 10,200^ 13,300 12,000 BASIC 39,200?/ MISSION 4 CONDITIONS (nmi) Estimated (nmi) Guaranteed (ft) Estimated (ft) Guaranteed (kn) Estimated . (kn) Guaranteed maximum power, 10 ft. wheel height (ft) max power at military power (ft/min) power (ft/min) power at (nmi) Ferry range Hover ceiling IGE at STD temperature, Radius of action, Hover ceiling, OGE at STD temperature, Service ceiling, STD temp, single engine (ft) Service ceiling at normal power Rate-of-climb at SL/STD military Vertical rate-of-climb at SL/STD maximum (kn) V-Cruise (best range) at 5000 ft/STD (kn) V-Cruise (best range) at SL/STD (inbound) (lb) Payload guaranteed (lb) Payload estimated (outbound) (lb) Payload estimated (inbound) power (kn) Vax SL/STD, military SL/STD normal power Max cruise speed at (lb) Gross weight (outbound) (lb) Payload guaranteed CH-47C (Chinook). — Typical Mission, and'Performance 1-21. Loading m M

FM 101-20-1 FOR orneiAL UAE 4 1 2 (CONT). CH-47C (Chinook) - Typical Mission, and Performance 1-21. Loading 100 nmi. NOTES: y Transmission Limit of at gross weight required for accomplishment 6000 ft for 10 minutes at 95°F, OGE shall be capable of hovering at For Mission I the helicopter y Structural Envelope y At 230 RPM lb., and fuel for a radius of weight includes an outbound payload of 12,000 lb., return payload of 6000 Mission I (guaranteed). The Mission I gross (Troop Seats Incl.) Equivalent to 26 FT Drag Area U With External Payload at 6000 ft/95°F at 245 RPM. y Hover Gross Weight a gross weight of 43,000 pounds be capable of hovering out-of-ground effect at SL/STD, maximum power, and During Mission HI the helicopter, shall (guaranteed). Payload y With 12000 LB (Outbound) y Mission Cruise Speed System limit y Current Hydraulic

FM 101-20-1 FM 101-20-1

1-22. Performance Notes, CH-47C (Chinook). unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent FORMULA: RADIUS MISSIONS I & II of initial fuel for reserve.

Warm up, take off, climb on course to 5000 feet FORMULA: RANGE MISSION III at normal power, cruise out at long range speeds to remote base, land, and unload cargo. Without refueling, Warm up, take off, cruise out at long range speeds warm up, take off, climb on course to 5000 feet at at sea level until 90 percent of initial fuel is consumed, normal power, and return at long range speeds. Range- land, and unload cargo. Range-free allowances are 2 free allowances are 2 minutes of normal power for minutes of normal power for warmup and takeoff, plus each warmup and takeoff, plus 10 percent of initial 10 percent of initial fuel for reserve. fuel for reserve. FORMULA: RANGE MISSION IV

FORMULA: RADIUS MISSION HI Warm up, take off, cruise out at 100 knots at sea level with- external cargo until 10 minutes of cruise Warm up, take off, cruise out at long range speeds fuel remains, detach cargo, and land. Range-free at sea level to remote base, land, and unload outbound allowances are 2 minutes of normal power for warmup cargo, load inbound cargo. Without refueling, warm up, and takeoff, plus 10 minutes of cruise fuel for reserve. take off, return at long range speeds at sea level, land and unload cargo. Range-free allowances are 2 minutes FORMULA: RANGE MISSION V of normal power for each warmup and takeoff, plus 10 percent of initial fuel for reserve. Warm up, take off, climb on course to optimum cruise altitude at cruise speed, and cruise out at long FORMULA: RADIUS MISSION IV range speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal Warm up, take off, cruise out at 100 knots at sea power for warmup and takeoff, plus 10 percent of level with external cargo to remote base, detach cargo, initial fuel for reserve. and land. Without refueling, warm up, take off, and return at long range speeds at sea level. Range-free PERFORMANCE REFERENCES allowances are 2 minutes of normal power for each warmup and takeoff, plus 10 minutes of cruise fuel for Vertol Report 114-PJ-7003, Detail Specification reserve. for The CH-47C Helicopter. Lycoming Report 124.27, T55-L-11 Engine Speci- FORMULA: RANGE MISSIONS I & II fication.

Warm up, take off, climb on course to 5000 feet Boeing-Vertol Report 114-AD-601, Estimated at normal power, cruise out at long range speeds until Performance Capabilities of CH-47B and CH-47C Heli- 90 percent of initial fuel is consumed, land, and copters.

roR oprrciAi use OMUT 1-45 FM 101-20-1

AV 000024

Figure 1-8. CH-54A and B (Tarhe), typical (minor differences apparent between A and B models)

1-46 ron ornciAL use ONLY FM 101-20-1

TUI hhñr4□

19 FT 9 N

3 FT 1014 IN

88 FT 6 IN

72 FT

16 FT 8 IN 16 FT (IDLING) O 9 FT .4 IN. 1

70 FT 3 IN. AV 000025

Figure 1-9. Principal dimensions, CH-54A and B (Tarhe)

FOR orneiAL use OMLY. 1-47

101-20-1 FM jen 1VI3UJÖ aoj an Gnd clearance: Tread 19ft,9in. Width (cockpit)7ft,1in. Height (static)25ft,in. Length (fuselage)70ft,3in. Length (rotors Main rotordia72ft Normal Military ...4500900030 T73-P-1 Normal Military ...4050900030 JFTD12A-1 Type Axial Weight 925lb Spec 2424 Mfr Pratt&Whitney No. &model....(2)JFTD12A-1 Tail rotor9ft,4in. Main rotor(idling)..16ft,8in. 1-23. CH-54A(Tarhe)Characteristics. operating) 88ft,5in. rated ....40009000Cont. rated 32009000Cont. or (2)T73-P-1 ENGINE RATINGS DIMENSIONS POWERPLANT SHP RPMMIN SHP RPMMIN Four-blade, anti-torquetail A four-point20,000lb Rear facingseatforaft Six-blade mainrotor. hoist. Spaceandstructuralprovisionsarealsomadeforacargosling or towingassembly. pitch stick.Cargohandlingprovisionsincludeahydraulicpowered cyclic anddirectionaltrimcontrolsaconventionalcollective stabilization equipmentisalsoprovided.Theaftfacingpilotseathas controls areprovidedforforwardfacingpilotseats.Automatic pilot, copilot,andanaftfacingpilot.Conventionalhelicopterflight forming thenoseofhelicoptercarriesbasicaccommodationsfor gear assembliesandafixednoseassembly.Theenclosedcockpit anti-torque tailrotor.Thetwogasturbineenginesarelocatedabove the fuselage.Thewheel-typealightinggearconsistsoftwofixedmain main components. serves asaworkplatformforservicingengines,rotorsystems,and capability intoareasunsuitableforlanding.Flattoppedfuselage rotor. the helicopterhoversoverhead,therebyextendingoperational externally byahoist,thegroundcrewmayloadorunloadcargowhile include, movementofheavyoutsizedloads,towingsurfacevehicles a 15,000lbcapacityhoist. tion ofpersonnel,vehicles,andequipment.Sincecargoiscarried recovery ofdownedaircraft,andbyusedetachablepods,transporta- suspension systemand capacity cargohoist pilot/hoist operator. r This helicopterisoftheall-metal,singlemainrotortypewithone Missions thatmaybeaccomplishedwiththeCH-54Ahelicopter Production statusoutofproduction First productionacftdeliveredNov66 FEATURES MISSION ANDDESCRIPTION Mfr’s Model:Sikorsky DEVELOPMENT Passengers (withPodAttached) Crew (normal) Attendants 3 Litters 2 4 Troops 45 Aft pilot... Pilot Copilot .... and or PERSONNEL c None. Refer tochapter2. Oil: Fuel: **Combat 22,024 Qty 1.9gal Spec MIL-L-23699 Qty 1338gal Spec MIL-T-5624 Grade JP-l,-4,or-5 **Basic mission. Alternate Gross Basic 20,650 Empty 19,234 •Limited byperformance. (design) 38,0002.50 takeoff gross..*42,0002.26 FUEL ANDOIL ARMAMENT AVIONICS WEIGHTS LB L.F. EOR orntiAL use ONLY 95 SL SL 2.9 130Í/ 274 IV 6.50 4.91 None None 1,750 4,150 3,050 8,700 18.648 18.648 25.600 24,400 24.600 13,600 18,400 FERRY RANGE 19,900 130/SL-S^ 26,478 95 25 95 SL 42 SL III 400 400 0.53 0.57 6.37 1)950 None 10.32 1,320 5/ 2,300 6,000 6,000 CARGO 20,000-» 42,000 ALTERNATE * 90 85 85 SL SL SL 2.4 100 259 3.05 II 6.60 4.98 J/ 1.340 1.340 None 1.700 6,600 8,900 4.000 3.000 8.700 90/SL 19,048 18,100 19,600 13,300 39,421 16,000-6/ 26,878 RADIUS 100 MILE Data do not include ground effect. Data Source: Detail Spec for Army CH-54A. Performance is based on powers shown in paragraph 1-25. Performance Basis: sq ft). •6/Carried by external sling (load drag-129 -2/ Transfer of cargo while hovering. •8/Limited by attitude. 95 95 SL SL SL 2.6 2.5 130-S/ 124 234 773 I 7.04 9.33 None 3.800 3.800 1,400 1,714 6,800 8,700 18,648 23,200 12,100 22,100 21,900 33,688 22,024 11,522-^ 130/SL-iV BASIC 38,000 MISSION CONDITIONS m (ft) Service ceiling-1/ , (fpm) Max rate of climb at SL-1/ (kn) Max speed/aItitude-2^ (ft) Absolute hovering ceiling-1/ (kn) Combat speed-2/ (fpm) Combat climb-1/ (ft) Combat ceiling-1/ (ft) Combat altitude (kn) Average cruising speed (ft) Cruising altitude (hrs) Total mission time engine out)-!/ (ft) Service ceiling (one (kn) Average cruising speed (ft) Cruising altitude (hrs) Total mission timé fpm)V ... (ft) Service ceiling (100 (ft) Absolute hovering ceiling-1/ (lb) Fuel at SL-1/ (fpm) Vertical rate of climb SL-1/ (fp) Max rate of climb at engine out)J/ (fpm) Max rate of climb (one (lb/sq ft) Disk loading (lb/bhp) Takeoff power loading (lb) Payload (outbound) (lb) Payload (inbound) (lb) LANDING WEIGHT (lb) FIRST LANDING WEIGHT (lb) COMBAT WEIGHT (nmi) COMBAT RADIUS-^ (nmi) COMBAT RANGED CH-54A (Tarhe). - Typical Mission, and Performance 1-24- Loading -4/Includes crew of 2 at 200 lb. each. (lb) TAKEOFF WEIGHT-^/ RANGE Missions are given in paragraph 1-25. -3/ Detailed description of RADIUS and -2/Carried by single-point or 4-point hoist system. -2/Normal power. J/Takeoff power. to

FM 101-20-1 hM 101-20-1

1-25. Performance Notes, CH-54A (Tarfie). off power for warmup and takeoff and 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION I GENERAL DATA: Warm up, take off, cruise out at sea level at recommended cruise speeds to remote base, and land. a. Dual engine operation is limited to 6600 SHP Deposit cargo and without refueling, warm up, and by transmission time-power criteria; for single-engine take off. At sea level, return to home base at recom- operation, manufacturer’s guaranteed ratings in para- mended cruise speeds. Range-free allowances are 4 graph 1-23 are applicable. minutes at takeoff power for warmups and takeoffs and 10 percent of initial fuel for reserve. b. Powers used in performance calculations are as follows: FORMULA: RADIUS MISSION II ENGINE: (2) T73-P-1 Warm up, take off, and cruise out at sea level to remote area 100 nautical miles distant at recommended SHP RPM CRITICAL ALTITUDE cruise speeds. Hover out of ground effect for 5 minutes to pick up cargo. At sea level, return to home Takeoff: 6600 9000 14,000 base at recommended cruise speeds. Hover out of Normal: 5400 9000 16,300- ground effect for 5 minutes, to deposit cargo, and land. Range-free allowances are 2 minutes at takeoff power for warmup and takeoff, 10 minutes for hovering, and 10 percent of initial fuel for reserve. c. Maximum overbad takeoff weight is limited by the requirement that vertical climb at sea level of a FORMULA: RADIUS MISSION III standard day with takeoff power shall not bé less than 100 fpm. Warm up, take off, cruise out at 2000 feet at recommended cruise speeds to remote base and deposit d. Maximum alternate takeoff gross weight is cargo. Without refueling, return to home base at 42,000 pounds, at 6600 SHP (2 engines) for hover and recommended cruise speeds. Range-free allowances are takeoff to 20 knots. Above 20 knots, reduce to 6000 2 minutes at takeoff power for warmups and takeoffs SHP. and 5 percent of initial fuel for reserve. e. All takeoffs requiring more than 5400 SHP FORMULA: RANGE MISSIONS IV total power shall be logged as a 6600 SHP takeoff. Never exceed speed of 95 knots CAS from SL to 2000 Warm up, take off, and cruise out at sea level at feet density altitude at weights above 38,000 pounds. recommended cruise speeds until only reserve fuel Above 2000 feet reduce airspeed 6 knots per 1000 feet remains. Range-free allowances are 2 minutes at take- to a maximum altitude of 6000 feet.

1-50 FOR OFFICIAL USE OHIV 1-51 (8743 lb. JP-4) LB L.F. AVIONICS ARMAMENT WEIGHTS FUEL AND OIL (USABLE) Spec MIL-L-23699 Qty 1.9 gal Qty 1345 gal. Spec MIL-T-5624 Grade JP-4/5 None. Refer to chapter 2. OU: Fuel: 4,060 Combat 2 ,765 Empty 19 2,960 Basic 2 2.0 Gross (Design) ..47,000 PERSONNEL Litters 24 Attendants 3 Troops 45 Co-pUot Pilot Aft-pilot Observers Passengers (with pod attached) Crew (normal) DEVELOPMENT Sikorsky S-64F Mfr’s Model: AND DESCRIPTION MISSION FEATURES point hoist. single, main rotor type helicopter The CH-548 is an all-metal load suspension system. include accomplished with the CH-54B helicopter Missions that may be Four-blade anti-torque taU rotor. 25.000 lb. capacity single 20.000 lb. capacity four point Six-blade main rotor. Aft-facing pUot/hoist operator. June 1969 First flight 6 September 1968 Contract date kit. are also made for installation of a towing system (AFCS) is also pitch control. An automatic flight control of a removable single provided. Cargo handling capabilities consist suspension system. Provisions point hydraulic powered four point load a conventional collective cyclic and directional trim controls and co-pilot, aft-facing pilot and craft has basic accommodations for a pilot, flight controls are provided for two observers. Conventional helicopter has electrically operated the pilot and co-pilot. The aft-facing pilot forming the nose of the air- a crane configuration. The inclosed cockpit nose gear and a single fixed, fully swiveling fixed main gear assemblies are constructed and assembled in assembly. The fuselage and landing gear engines tail rotor. It is powered by two gas turbine with one anti-torque of two The wheel type landing gear consists located above the fuselage. rotor and servicing of the engines, work platform for maintenance of the power train system. systems and other components as a landing. The flat top of the fuselage serves areas unsuitable for into thereby extending operational capability copter hovers overhead, the heli- crew may load or unload cargo while by a hoist, the ground of by use of detachable pads, transportation downed aircraft, and equipment. Since cargo is carried externally personnel, vehicles and recovery of outside loads, towing of surface vehicles, movement of heavy •i SHP RPM MIN DIMENSIONS POWERPLANT ENGINE RATINGS (idling) 15 ft, 8 in. operating 88 ft, 6 in. Tail rotor 9 ft, 4 in. Main rotor Fuselage 70 ft, 3 in. Rotors rated 4430 9000 Cont. Width (cockpit) 7 ft, 1 in. Gnd clearance: Height (static) 25 ft, 4 in. Tread 19 ft, 9 in. Length: Main rotor dia 72 ft, 3 in. Normal Military 4800 9000 30 935 lbs Weight 2454 Spec Pratt & Whitney Mfr Axial Type (2)T73-P-700 No. & model (Tarhe) Characteristics. 1-26. CH-54B

FM 101-20-1 FM 101-20-1

1-27. Loading and Performance Data — Typical Mission, CH-54B (Tarhe)

FERRY CONDITIONS MISSION II

TAKEOFF WEIGHT 2/ (lb) 32,323 Fuel (lb) 8,743 Payload (outbound) 3/ (lb) Payload (inbound) ^ (lb) Takeoff Power Loading (lb/bhp) 4.08 Disk Loading (lb/sq ft) 7.95 Vertical Rate of Climb at SL d/ (fpm) Max Rate of Climb at SL 2/ (fpm) 2,718 Max Rate of Climb (one engine out) 1/ (fpm) 1,704 Service Ceiling (100 fpm) (ft) Service Ceiling (one engine out) d/ (ft) 13,000 Absolute Hovering Ceiling d/ (ft) COMBAT RANGE (nmi) 232 Average Cruising Speed (kn) 95 Cruising Altitude (ft) SL Total Mission Time (hrs) 2.5 COMBAT RADIUS (nmi) Average Cruising Speed (kn) Cruising Altitude (ft) Total Mission Time (hrs) FIRST LANDING WEIGHT (lb) COMBAT WEIGHT (lb) Combat Altitude (ft) Combat Speed (kn) Combat Climb d/ (fpm) Combat Ceiling 2/ (ft) Service Ceiling d/ (ft) Absolute Hovering Ceiling d/ (ft) Max Rate of Climb at SL (fpm) Max Speed/Altitude 2/ (kn) LANDING WEIGHT (lb) 24,283 d-/ Takeoff Power. Normal Power. ^ Includes crew of 3 at 200 lb each. y Carried by single-point or 4-point hoist system.

FORMULA: Basic Mission I Warm up, take off, cruise out. at sea level at recommended cruise speeds to remote base, and land. Deposit cargo and without refueling, warm up, and take off. At sea level, return to home base at recommended cruise speeds. Range-free allowances are 4 minutes at takeoff power for warmups and takeoffs and 10 percent of initial fuel for reserve. FORMULA: Ferry Mission II Warm up, take off, and cruise out at sea level at recommended cruise speeds until only reserve fuel remains. Range-free allowances are 2 minutes at takeoff power for warmup and takeoff and 10 percent of initial fuel for reserve. 1-52 roR-ornciAi use ONLY FM 101-20-1

r F- fs»

^^*—11 «i;>iuii1

AV 000027

¿ Figure 1-10. OH-6A (Cayuse)

roji orneiAL use OHL*. 1-53 FM 101-20-1

7 m %

S FTM/2IN 8 FT 6 IN

4 FT 6-3/4 IN. —1

6 FT 9-1/4 IN.

26 FT4 IN.

CE 3 g {-F- 4 FT 3 IN. Tl (DISK DIAMETER)

30 FT 3-3/4 IN.

AV 000028

Figure 1-11. Principal dimensions, 0H-6A (Cayuse)

1-54 •Fou orriciAi use owtY 1-28. 0H-6A (Cayuse) Characteristics.

POWERPLANT MISSION AND DESCRIPTION WEIGHTS Empty .1158 No. & model .. . (1) T63-A-5A Mfr’s Model: Hughes 500 Useful load .1242 Mfr Allison Div of Pilot . 200 GMC The principal missions of the OH-6A light observation helicopter are Observers (2), Engine spec No.. 580F, Amend- visual observation and target acquisition, reconnaissance, and command Copilot (1) . 600 ment 1, dtd control. This helicopter is employed in support of combat companies, Cargo 42 18 Aug 1965 and will operate for extended periods of time with only such support as provided by one mechanic with handtools. Normal operation is Fuel 400 ENGINE RATINGS limited to day or night visual flight conditions. Gross (FAA certified) .2400 The light observation helicopter is a single-lifting, 4-blade rotor, Max structure .2700 Output 4-place helicopter with a normal gross weight of 2400 lb or less. It is FUEL AND OIL Ratings SHP powered by a T63-A-5A free turbine engine with 317 SHP, derated to Takeoff & mil *317 252.5 SHP. It incorporates dual flight controls with the secondary cyclic Fuel: Normal **270 control element easily removable. The flight instruments are limited to Spec, and Output speed those required for day and night marginal visual conditions. The cargo Grade. MIL-T-5624(JP4/5) SEC lb/ area contains troop-type seats which are easily stowable when not in use. ASTM-1655,Type A SHP- or A1 rpm HR DEVELOPMENT MIL-F-46005A, Type 1 Takeoff & mil .... 6000 0.697 (C.I.T.E.) r i Normal 6000 0.706 Qty ... 61.5 gal Design competition initiated October 1960 Above ratings developed on Oil: standard sea level static Fhght evaluation completed June 1964 Spec .. . MIL-L-7808/23699 conditions. Production contract May 1965 No. *Derated to 252.5 for 5 min First production acft deliveries September 1966 tanks . 1 **Derated to 214.5 Location. Engine section Qty ... 3 qt Main Transmission: DIMENSIONS Spec ... MIL-L-7808/23699 Rotor dia 26 ft, 4 in. Qty 8.0 pt Length: Tail Rotor Transmission: Rotor Spec MIL-L-7808/23699 FEATURES PERSONNEL operating .... 30 ft, 3-3/4 in. Qty 0.5 pt Rotor folded ... 23 ft Dual controls. Crew (normal) 1 AVIONICS Height 8 ft, 6 in. Stowable troop seats. Observer 2 Tread 6 ft, 9-1/4 in. Copilot 1 Refer to chapter 2. ARMAMENT

FM 101-20-1 Refer to chapter 2.

cnat

101-20-1 FM

*1N0 3Sn IVPUJO MOTI 1-29. LoadingandPerformance-TypicalMission,OH-6A(Cayuse). -^faormal power. 3/For RADIUSmission: includes copilotat200lbs. A/pakeoff powerUpto5minutes, TAKEOFF WEIGHT(lb) COMBAT ALTITUDE(ft). COMBAT WEIGHT3(lb). COMBAT RANGE(nmi). COMBAT RADIUS(nmi). Time: Sealevelto10,000ft-1/(minutes) Time: Sealevelto5000ftA/(minutes) Max rateofclimbatsealevelA/(fpm) Payload (notincludingpilot)(lb) LIMIT FLIGHTLOADFACTORS Absolute hoverceilingA/(ft). Service ceiling(100fpm)-2^(ft). Speed formaxR/C,sealevel(knots) Speed forMin.R/D(knots) Takeoff powerloading(lb/bhp) Disk loading(lb/sqft) Fuel (lb) Maneuver Positive(g). Combat speed-2/(knots). Mission time(hr). Maneuver Negative (g). Max rateofclimb@sealevelA/(fpm). Cruising altitude(ft). Basic speedat5000ft-2/(knots). Maximum speed-A/(knots). Speed formaxR/C,sealevel(knots). Absolute hoverceilingA/(ft). Service ceiling-2/.(ft). Combat climb^(fpm). Average cruisingspeed(knots). Cruising altitude(ft). Average cruisingspeed(knots). Total missiontime(hr). MISSION 20,950 11,200 12,200 12,200 12,200 18.400 14.400 BASIC 2250 2159 1961 1860 1925 0.50 2.82 8.55 56.0 54.0 3.96 400 400 370 128 130 104 116 185 104 I 3.6 3.6 2.5 5.3 55 ALTERNATE 1A (CLEAN) 10,500 17.850 15.850 6,500 9600 2207 9600 9600 2400 117 1680 1860 1560 0.50 2.54 4.41 9.50 56.0 54.0 II 400 637 4/ 330 102 128 112 102 165 3.3 3.3 7.0 3.3 56 ALTERNATE 1A (ARMED) 10, 500 17.850 15.850 6,500 III 9500 9500 2400-6/ 2208 9500 1860 1680 1560 0.50 2.54 4.41 9.50 58.0 54.0 400 400 56 316 117 128 112 100 158 100 3.2 3.2 3.3 7.0 i RANGE FERRY IV SEA LEVELMISSION HIGH SPEED 20,750 11,200 18,400 14,100 2220 2220 2159 1977 1925 V 56.0 8.55 0.50 2.82 54.0 3.96 294 400 400 130 129 147 129 130 128 2.5 2.3 2.3 5.3 SL SL SL 55 row ornciAt-usc-ONuy « r atmospheric conditions. is out of ground effect and for standard b. All performance YOH-6A extrapolated. a. Army flight test (CONT). OH-6A (Cayuse) - Typical Mission, and Performance 1-29. Loading Performance Basis: Armament Kit XM-27 or XM-27E-1 -é/lncludes lb/tank, trapped fuel of 19.5 weight including tanks with an empty 4 Mark XII torso -^/includes -2/ Limited by V ne

FM 101-20-1 FM 101-20-1

1-30. Performance Notes, OH-6A (Cayuse). FORMULA: RADIUS MISSION V

FORMULA: RADIUS MISSION I, II, & III Warm up, take off, and accelerate to maximum speed. Cruise at sea level at maximum speed, as limited Warm up, take off, climb on course at military by normal power or Vne to remote base. Do not land. power to altitude for best range at average cruise Return to home base. Range-free allowances are 2 weight. Cruise to remote base at speed for best range. minutes of normal power for warmup and 10 percent Do not land. Return to home base. Range-free allow- of initial fuel for reserve. ances are 2 minutes of normal power for warmup and 10 percent of initial fuel for reserves. FORMULA: RANGE MISSION V

FORMULA: RANGE MISSION I, II, & III Warm up, take off, and accelerate, to maximum speed. Cruise at sea level at maximum speed, as limited Warm up, take off, and climb on course at mili- by normal rated power Vne to remote base. Range-free tary power to altitude for best range at average cruise allowances are 2 minutes of normal power for warmup weight. Cruise to remote base at speed for best range. and 10 percent of initial fuel for reserve. Range-free allowances are 2 minutes of normal power for warmup and 10 percent of initial fuel for reserve. GENERAL DATA

FORMULA: FERRY RANGE MISSION IV For detailed planning refer to applicable technical manual. Warm up, take off, and climb on course at military power to 5,000 feet. At steady cruise, climb to PERFORMANCE REFERENCE stay at optimum altitude as weight decreases. Range- free allowance is 2 minutes of normal power for Hughes Tool Company-Standard Aircraft Char- warmup. No reserve fuel allowance. acteristics (OH-6 A).

1-68 JJQR ornciAL use O-NLY» FM 101-20-1

AV 000030

Figure 1-12. OH-13H, and S (Sioux) typical (minor differences apparent between H and S models)

F-OR OFFICIAL USE QMLX 1-59

446-903 0-71-5 -41 FT 4-3/4 IN.

30 FT 5 IN.

□ X

35 fl

9 FT 7 IN

”ON OH-13H SERIAL NO. 58-1497 AND SUBSEQUENT

5 FT 8-1/4 IN. •5 FT 10-1/4 IN.

1/2 1/2 6 FT 8-1/2 IN. 9 FT 3-1/2 IN. \AJ

AV 000035 Figure 1-13. Principal dimensions, 0H-13H (Sioux)

1-60 FOR ornciAL usc-oNb* *fOR OFFTCfAL USE-ONIX LB L.F. section WEIGHTS AVIONICS FUEL AND OIL ARMAMENT Qty 3 gal Location Engine uselage Location F 1-1/2 gal Qty 4 Spec MIL-L-22851 No. tanks 1 IL-G-5572 Spec M 0/87 Grade 8 No. tanks 2 Refer to chapter 2. Refer to chapter 2. Fuel: Oil: 1850 Empty (actual) 2450 2.5 Design 2750 Overload * PERSONNEL or controls are installed. Litters (ext) 2 Crew (normal) 1 Passengers/observers.... *2 ♦Limited to 1 when dual DEVELOPMENT Bell47G-2 Mfr’s Model: AND DESCRIPTION MISSION FEATURES lieu of except for the 0-435-23C engine in Similar to the OH-13G tail a 2-blade main rotor and a 2-blade The OH-13H incorporates of the OH-13H are observation, training, The principal missions (prov). Float landing gear (prov). Extended range torso tank Dual controls (prov). Night flying equipment. M2 armament subsystem. January 1956 First flight June 1956 First acceptance Winterization kit (prov). The metal main rotor the 0-335-5D engine and metal rotor blades. responsiveness to collective control movements. January 1956 Date of contract June 1960 Production completed a float-type have been included for installation of attached. Provisions twist which increases blades are of constant chord with an increased fuselage boosted cyclic control system. The rotor with a hydraulically with a bubble-type canopy enclosure. is an open-tube configuration landing gear. general utility. reconnaissance, and wheels the skid-type, with ground handling The landing gear is of » BHP RPM ALT MIN DIMENSIONS POWERPLANT ENGINE RATINGS operating .... 41 ft, 4-3/4 in. (static) 8 ft, 8-1/2 in. (idling) 8 ft, 8-1/2 in. Fuselage 31 ft, 4-3/4 in. lateral) 8 ft, 6-3/4 in. Rotors static .. 41 ft, 4-3/4 in. Rotors Rotor gnd clearance Tread 7 ft, 6 in. Span (max Height 9 ft, 5-1/2 in. Length: 5 ft, 1-1/2 in. Rotor dia 3 SL 5 Takeoff 260 3400 SL Cont. Normal 250 3200 . 222IB Engine spec No . . . D.D. Red. gear ratio . . Lycoming Mfr (1) 0-435-23C No. & model (Sioux) Characteristics. 1-31. 0H-13H

FM 101-20-1 FM 101-20-1

8 FT 6-3/4 IN.

8 FT 2-1/4 IN.

7 FT6 N.

9 FT 7 N

U± r 3

31 FT 7 IN.

43 FT 2-1/2 IN.

31 FT 4 IN.

1/4

9 FT 5-1/2 IN.

22 FT 6-1/2 IN AV 000037

Figure 1-14. Principal dimensions, 0H-13S (Sioux)

162 r-OR OFFICIAL USE ONLY «fOR orricTAL U LB L.F. 1 100/130 3-1/2 gal 57 gal Engine section 2 Fuselage MIL-L-22851 MIL-G-5572 WEIGHTS AVIONICS ARMAMENT FUEL AND OIL Location Qty... • Location Qty ... Spec . . . No. tanks Spec . . . Grade . . No. tanks Refer to chapter 2. Fuel: Oil: Refer to chapter 2. 1980 Empty (actual) .... 2850 2.5 Design 1 *2 PERSONNEL controls are installed. Crew (normal) ...... Passengers/observers. . . *Limited to 1 when dual DEVELOPMENT Bell 47G3-B Mfr’s Model: AND DESCRIPTION MISSION FEATURES a 2-blade main rotor and a 2-blade The OH-13S incorporates of the OH-13S are observation, recon- The principal missions except for the 0-435-25A turbocharged Similar to the OH-13H (prov). Extended range torso tank city increased to 57 gal. Dual controls (prov). Night flying equipment. M2 armament subsystem. increased 2 feet. Increased main rotor rotor diameter has been altitude performance, disk matches rotor with engine for higher to 2850 lb and fuel capa- weight of the OH-13S has been increased cockpit configuration with a bubble-type fuselage is an open-tube hand- gear is of the skid-type, with ground enclosure. The landing Main naturally aspirated 0-435-23C engine. engine in lieu of the utility. naissance, and general The boosted cyclic control system. tail rotor with a hydraulically ling wheels attached. to turbulence. Gross .more maneuverability, and less susceptibility BHP RPM ALT MIN DIMENSIONS POWERPLANT ENGINE RATINGS operating . . 43 ft, 2-1/2 in. (static) 8 ft, 8-1/2 inc (idling) 8 ft, 8-1/2 in. Rotors static . 43 ft, 2-1/2 in. Fuselage .... 31 ft, 8-1/2 in. Rotors lateral) 8 ft, 6-3/4 in. Rotor gnd clearance Height 9 ft, 5-1/2 in. Span (max Tread 7 ft, 6 in. Engine spec No . 2309A Red. gear ratio . D.D. SL 5 Takeoff 270 3200 SL Cont. Normal 220 3200 37 ft, 1-1/2 in. Rotor dia Length: . . (1) 0-435-25A No. & model ycoming Mfr L (Sioux) Characteristics. 1-32. OH-13S è

FM 101-20-1 FM 101-20-1 1-33. Loading and Performance - Typical Mission, OH-13 (Sioux).

MODEL H

Mission weight (lb) 2500 2500 275.0 2850 2950 Empty weight (lb) 1630 1630 1850 1980 2060 Useful load (lb) 870 870 900 870 890 Fuel load (lb) 174 246 246 342 342 Oil load (lb) 15 15 18 22 22 Payload (lb) 681 610 640 510 533 Max endurance at sea level (hr) 2.6 3.8 3.0 3.7 3.5 Max range at 5000 ft (miles) . 172 246 224 203 192 Max R/C (ft/min) 801 801 720 975 900 HOGE ceiling (ft) 500 500 300 10,800 8400

HIGE ceiling (ft) 3800 3800 3400 12,000+ 12,000+

Service ceiling (ft) 10,300 10,300 8900 12,000+ 12,000+ Takeoff power (hp) 210 210 240 270 270 Military power (hp) 210 210 220 220 220 Cont power (hp) 210 210 220 220 220 Turbocharged no no no yes yes

Speed-Vne(kn) 85 87 87 91 91 Main rotor Disk area (sq ft) 968.5 968.5 968.5 1085 1085 Blade area (sq ft) 35.4 35.4 32.2 34.27 34.27 Disk load (psf) 2.57 2.57 2.84 2.63 2.72 Blade load (psf) 70.4 70.4 85.1 83.2 86.1 Solidity 0.0370 0.0370 0.0332 0.0314 0.0314 Tip speed (fps) (3200 rpm) 654 654 654 695 695 Tail rotor Disk area (sq ft) 26.8 26.8 26.8 26.8 26.8 Blade area (sq ft) 2.4 2.4 2.4 2.4 2.4 Solidity 0.0895 0.0895 0.0895 0.0895 0.0895 Tip speed (fps) 587 587 587 587 587

■POR OTHCIAL USD-ONLY FM 101-20-1

AV 000042

Figure 1-15. OH-23D, and G (Raven), typical (minor differences apparent between D and G models)

WE ONLY 1-65 FM 101-20-1

10 FT

9 FT 3-1/2 IN

6 FT 1-1/2 IN.

-6 FT 6 IN.-

7 FT 9-1/2 IN

10-1/2 IN. I FT 1-3/4 IN. *3 'N (=0)

3 FT 1-3/4 IN.

40 FT 8-1/2 IN.

a 6 IN -

10 FT 1-1/2 IN n

3-1/2 IN 6 FT 3-1/2 IN.

7 DEG 25 MIN I FT 3/4 IN.

27 FT 9-1/4 IN. AV 000045

Figure 1-16. Principal dimensions, OH-:23D (Raven)

1-66 roR ornciAL use ONLY* •fOR ofPteiAL use OHL-Y LB L.F. AVIONICS ARMAMENT WEIGHTS FUEL AND OIL Location Engine sump Qty 3-1/3 gal Spec MIL-L-6082 Qty 46 gal Grade 1100 No. tanks 1 Location Fuselage Spec MIL-G-5572 No. tanks 1 Grade 115/145 2700 3.0 (normal) + 2700 3.0 (overload) + Refer to chapter 2. Refer to chapter 2. Oil: Fuel: * For basic mission. + Limited by structure. Max takeoff +2700 4.0 Max landing Max takeoff 1772 Empty (actual) ... 1781 Basic (actual *2350 Combat 2700 3.0 Design 1 á « PERSONNEL or or or Attendant . Litters (ext) Crew Litters (ext) Crew Student pilot Crew Crew ... Passenger DEVELOPMENT UH-12D Mfr’s Model: Hiller AND DESCRIPTION MISSION FEATURES t for the V0435-23C The OH-23D is similar to the OH-23C except single side-by-side helicopter with a The OH-23D is a three-place, of the OH-23D is pilot training. Alternate The principal mission tail rotor blades. C-133 aircraft. Interchangeable main rotor and Dual controls (prov). Rotormatic control. Ground handling wheels. Transportable in C-124 and External litters. January 1958 First service use December 1957 First acceptance October 1956 First flight drive system. gross weight, and a new transmission and September 1956 Date of contract rotor blades, increase of design engine, redesigned all-metal main and tail control- trim system is incorporated with the cyclic from the left seat. A and lateral trim. The fuselage is of all-metal, stick for longitudinal semimonocoque construction set operated seat, with provisions for a second operated from the center of controls control system consists of a single set external litters. The and two tail rotor, skid-type landing gear main rotor, an antitorque and medical evacuation. missions are observation DIMENSIONS POWERPLANT MIN BHP RPM ALT ENGINE RATINGS operating ... 40 ft, 8-1/2 in. Idling 9 ft, 3-1/2 in. Static 6 ft, 4 in. Rotors static .. 40 ft, 8-1/2 in. Fuselage 27 ft, 9-1/2 in. lateral) 10 ft Rotors takeoff) gearratio ■■■■8.66:1 Rotor gnd clearance: Height 10 ft, 1-1/2 in. Span (max Tread 7 ft, 6 in. Rotor dia 35 ft, 5 in. Length: * METO power (max except SL Cont *Normal 245 3200 SL Cont Takeoff 255 3400 Eng/maih rotor Engine spec No . 2221 Red. gear ratio .. D.D. 0-435-23C No. & model ... (1) ycoming Mfr L (Raven) Characteristics. 1-34. OH-23D >i

FM 101-20-1 FOR OrriCIAL u 0 43 70 43 70 9.3 3.8 2.7 280 130 III 184 980 2.31 2278-5/ 1450 None None 6500 5000 1330 2026 1750 5000 9700 17,800 16350 21,650 FERRY RANGE 0 0 43 42 73 II 60 56 9.6 4.2 2.5 280 180 460 850 2.39 630 305 2356-5/ 1320 None 5550 5000 2233 1510 2693 5000 1000 7050 0/335 0/443 16,700 12,430 EVACUATION t 0 0 43 I 41 70 82 70 70 5.0 2.6 2.4 280 210 177 630 2.52 10.1 155 955 2478 4/ 1250 None None 4000 5000 5000 2350 2350 5000 1380 5600 0/368 0/474 16,100 12,100 17,600 BASIC MISSION ... (ft) ... .. (kn) ... .. (nmi) ...... (kn) ... 1 ... (ft) ...... (hr) ...... (lb) ...... (ft) ...... (ft) ...... (lb) ...... (ft) ...... (kn) . (fpm) ...... (ft) ...... (ft) ...... (ft) ...... (ft) ...... (ft) ... . (fpm) ... (lb/sqft) ...... (lb) .... (lb) ...... (lb) ...... (lb) ... .(lb/bhp) ...... (kn) ...... (ft) ...... (ft) ...... (fpm) ... .. (fpm) ...... (kn) ... .. (min) ...... (ft) ... . . (nmi) ...... (ft) ... • • • (hr) ... ♦ CONDITIONS 115/145) Fuel at 6.0 Ib/gal (grade Payload (outbound) Payload (inbound) Takeoff power loading Disk loading (min R/D) Autorotation speed at SL-1/ Takeoff ground run at SL-^. Vertical rate of climb ft-t/ Takeoff to clear 50 of climb at SIÀ-/ .... Speed for max rate SL-^ Max rate of climb at Service ceiling (100 fpm)-L/ Absolute hovering ceiling-1/ Average cruising speed Time: SL to 5000 ft-1/ Average cruising speed Cruising altitude Total mission time Cruising altitude Total mission time Ground roll at SL (power on/autorotation) Total from 50 ft (power on/autorotation) Combat altitude Combat speed-1/ Combat climb-1/ Combat ceiling (500 fpm)-l/ Service ceiling (100 fpm)-!/. Absolute hovering ceiling-1/ Takeoff ground run at SL-l/ Takeoff to clear 50 ft-1/ Max rate of climb at SL-i/ WEIGHT TAKEOFF ” COMBAT RANGE-«/ FIRST LANDING WEIGHT-2/. ] ‘ ] COMBAT RADIUS-2/ COMBAT WEIGHT-2/ (Raven). OH-23D Mission, - Typical Performance and 1-35. Loading 00

FM 101-20-1 •fOR OrriCIAL UÍHi'OMlY- 77 á/ 83 41 HI 2026 0/464 0/359 FERRY RANGE 606/ 66 & 38 II 2564 0/453 0/388 EVACUATION 83 41 I 2226 0/470 0/361 BASIC MISSION CONDITIONS for takeoff and landing. c. Data do not include ground effect except on UH-12D flight tests. a. Data source: Calculated data based b. Performance is based on powers shown. ft) on/autorotation) ( Ground roll at SL (power ft) oiVautorotation) ( Total from 50 ft (power (kn) of climb at SL -1/. Speed for max rate (kn) Max speed at SL ft (kn) ft ^ Basic speed at 5000 Performance Basis: ■2/For RADIUS mission if radius is shown. •^Includes crew of 2 at 400 lb. 2/Includes crew of 1 at 200 lb. RANGE missions are given in paragraph 1-36. •2/Detailed descriptions of RADIUS and ■£/Limited by stall. (lb) LANDING WEIGHT-1/ -1/METO power. (CONT). OH-23D (Raven) - Typical Mission, and Performance 1-35. Loading

FM 101-20-1 FM 101-20-1

1-36. Performance Notes, OH-23D (Raven). until 90 percent of initial fuel is consumed. Range-free allowances are 5 minutes of METO power at sea level FORMULA: RADIUS MISSION I for warmup and takeoff plus 10 percent of initial fuel for reserve. Warm up, take off, climb on course to 5000 feet at METO power, cruise out at long range speed to remote base, and land. Without refueling and with no GENERAL NOTES change in payload, warm up, take off, climb on course to 5000 feet at METO power, and return at long range Engine ratings shown are manufacturer’s guaran- speed. Range-free allowances are 10 minutes of METO teed ratings. METO values used in performance cal- power at sea level for warmups and takeoffs plus 10 culations are as follows: percent of initial fuel for reserve. BHP FOR FORMULA: RADIUS MISSION II BHPFOR FORWARD ALT RPM HOVER FLIGHT Warm up, take off, climb on course to 5000 feet at METO power, cruise out at long range speed to SL 3200 246.0 248.0 remote base, land, and load two litter patients. With- out refueling, warm up, take off, climb on course to 5000 ft ... 3200 207.5 209.5 5000 feet at METO power, and return at long range speed. Range-free allowances are 10 minutes for warm- 10,000 ft . 3200 174.0 176.0 ups and takeoffs plus 10 percent of initial fuel for reserve.

FORMULA: RANGE MISSIONS I & III PERFORMANCE REFERENCES

Warm up, take off, climb on course to 5000 feet Hiller Report No. 58-61. Characteristics Perfor- ât METO power, and cruise out at long range speed manee.

1-70 FOR OFHCIAL U3C ONLY Figure 1-17. OH-23F (Raven)

fUK UhhlUAL USt UNLI FM 101-20-1

-10 FT-

10 FT 1/2 IN.

6 FT 10-1/2 IN.

^ -4.

h 6 FT 6 IN. -j

•7 R 9-1/2 IN.

F=t0

3/4 1 6 R 2-1/2 IN

10-1/2 IN. r Ai ^3 •N H la

28 FT 11-1/4 IN.

40 FT 8-1/2 IN.

6 IN.—

10 FT 10-1/2 IN.

n -k 'LJ 3-1/2 IN. DEG 7 FT 1/2 IN. MIN L 1 R 10 IN.

AV 000048 -31 FT 8-1/4 IN.-

Figure 1-18. Principal dimensions, OH-23F (Raven)

1-72 FOR OFFICIAL USE ONLY FOR OFHCIAL USE ONI Y. 3.0 3.0 4.0 3.0 L.F. LB AVIONICS ARMAMENT WEIGHTS FUEL AND OIL Qty 3-1/3 gal Location Fuselage Spec MIL-L-6082 No. tanks 1 Location Fuselage Qty 46 gal Grade 1100 No. tanks 1 Spec MIL-G-5572 Grade 115/145 2800 (normal) + 2800 (overload) + Refer to chapter 2. Refer to chapter 2. Oil: Fuel: •For basic mission. +2800 Max landing +Limited by structure. Max takeoff 1903 Basic (actual) Max takeoff 2800 Design *2530 Combat 1903 Empty (actual) ... PERSONNEL Crew (normal) Passenger .... DEVELOPMENT E4 Mfr’s Model: Hiller AND DESCRIPTION MISSION FEATURES A capacity to the OH-23D except for a passenger The OH-23F is similar of the OH-23F is geodetic survey. The principal mission an helicopter with a single main rotor, The OH-23F is a four-place and C-133 aircraft. and tail rotor blades. Interchangeable main rotor Rotormatic control. Gnd handling wheels. Transportable in C-124 January 1960 First flight January 1960 First acceptance increases performance. and the 0-540-9 engine. The 0-540-9 engine October 1959 Date of contract Completed Production status construction fuselage is of all-metal, semimonocoque and lateral trim. The side-by-side. with the cyclic control stick for longitudinal system is incorporated aft, is with the pilot forward and three passengers Seating arrangement system and skid-type landing gear. The control antitorque tail rotor, seat. A trim of controls operated from the forward consists of a single set SL Cont. SL Cont. ALT MIN 3200 3200 RPM DIMENSIONS POWERPLANT BHP ENGINE RATINGS operating .... 40 ft, 8-1/2 in. Idling 9 ft, 3-1/2 in. Static 6 ft, 4 in. Fuselage 31 ft, 8-1/4 in. lateral) 10 ft Rotors Rotors static ... 40 ft, 8-1/2 in. .66:1 gearratio 8 Rotor gnd clearance: Span (max Height 10 ft, 10-1/2 in. Tread 7 ft, 6 in. Rotor dia 35 ft, 5 in. Length: •METO power. Takeoff 305 2304 Engine spec No ... D.D. Red. gear ratio ... Engine/main rotor (1)0-540-9 No. & Model Lycoming Mfr (Raven) Characteristics. 1-37. OH-23F •Normal 305 co

FM 101-20-1 FM 101-20-1

1-38. Loading and Performance - Typical Mission, OH-23F (Raven). BASIC AND DESIGN CONDITIONS MISSION

TAKEOFF WEIGHT .... (lb). 2800 Fuel at 6.0 lb/gal (grade 115/145 .... (lb). 516 Payload (outbound) .... (lb). 200 Payload (inbound) .... (lb). 200 Takeoff power loading . (lb/bhp). 9.2 Disk loading (Ib/sq ft). 282 Autorotation speed (min R/D) (kn). 45 Takeoff ground run at SL-f/ .... (ft). 0 Takeoff to clear 50 ft-" .... (ft). 0 Vertical rate of climb at SL . . . (fpm). 750 Max rate of climb at SL . . . (fpm). 1380 Speed for max rate of climb at SL (kn). 46 Time: SL to 5000 ft : .. . (min). 36 Service ceiling (100 fpm) .... (ft). 17,600 Absolute hovering ceiling .... (ft). 7200 COMBAT RANGE-2/ ... (nmi). 282 Average cruising speed (kn). 78 Cruising altitude .... (ft). 5000 Total mission time . ... (hr). 3.7 COMBAT RADIUS-2/ . .. (nmi). 141 Average cruising speed (kn). 78 Cruising altitude .... (ft). 5000 Total mission time . . .. (hr). 3.5 FIRST LANDING WEIGHT-2/ .... (lb). 2530 Ground roll at SL (power on/autorotation) .... (ft). 0/275 Total from 50 ft (power on/autorotation) .... (ft). 0/400 COMBAT WEIGHT-2/ .... (lb). 2530 Combat altitude .... (ft). 5000 Combat speed-l-/ (kn). 78 Combat climb-!-/ 0. ... (fpm). 1510 Combat ceiling (500 fpm)-" .... (ft). 16,100 Service ceiling (100 fpm)-L/ .... (ft). 20,000 Absolute hovering ceiling-A-/. .... (ft). 10,000 Takeoff ground run at SL-!-/ .... (ft). 0 Takeoff to clear 50 ft-^/ .... (ft). 0 Max rate of climb at SL-1/ . . . (fpm). 1620 Speed for max rate of climb at SL-" (kn). 46 Max speed at SL ft -L/ (kn). 83 Basic speed at 5000 ft-^/ (kn). 78 4/ LANDING WEIGHT-2/ .. . . (lb). 2310 Ground roll at SL (power on/autorotation) .... (ft). 0/275 Total from 50 ft (power on/autorotation) . .... (ft). 0/400

i/METO power. ^/Detailed descriptions of RADIUS and RANGE missions are given in paragraph 1-39. -^/por Radius Mission if radius is shown. ! ^/Limited by stall.

1-74 EOR OFFICIAt-USC ONLY- FM 101-20-1

1-39. Performance Notes, OH-23F (Raven). GENERAL NOTES

FORMULA: RADIUS MISSION II Engine ratings listed in paragraph 1-37 are manufacturer’s guaranteed ratings. METO power values Warm up, take off, climb on course to 5000 feet used in performance calculations are as follows: at METO power, cruise out at long range speed to remote base, and land. Without refueling and with no BHP FOR change in payload, warm up, take off, climb on course BHP FOR FORWARD to 5000 feet at METO power, and return at long range ALT RPM HOVER FLIGHT speed. Range-free allowances are 10 minutes of METO power at sea level for warmups and takeoffs plus 10 SL 3200 305 305 percent of initial fuel for reserve. 5000 ft .. . 3200 282 282 FORMULA: RANGE MISSION I 10,000 ft . 3200 238 238 Warm up, take off, cUmb on course to 5000 feet at METO power, and cruise out at long range speed until 90 percent of initial fuel is consumed. Range-free allowances are 5 minutes of METO power at sea level PERFORMANCE REFERENCE for warmup and takeoff plus 10 percent of initial fuel for reserve. Commercial and military technical manuals.

POU OFFICIAL USE ONLY

446-903 0-71 - 6 FM 101-20-1

10 FT

9 FT 3-1/2 IN.

6 FT 1-1/2 IN

7 FT 9-1/2 IN.

qn)

■10-1/2 IN I FT 1-3/4 IN. 3SFr IN [2) 3 FT 1-3/4 IN.

40 FT 8-1/2 IN.

6 IN.

5 FT 6 IN.— / 10 FT 1-1/2 IN. a 6 FT 3-1/2 IN. 3-1/2 IN

7 DEG 25 MIN 1 FT 3/4 IN.

27 FT 9-1/4 IN. AV 000050

Figure 1-19. Principal dimensions, OH-23G (Raven)

1-76 FOR OFFICIAL UM-ONLY K?R OPf+CIAL UCt OMI Y 177 LB L.F. WEIGHTS ARMAMENT Location Fuselage Qty 3-1/3 gal Spec MIL-L-6082 No. tanks 1 Location Fuselage Qty 46 gal Grade 1100 Spec MIL-G-5572 No. tanks 1 Grade 115/145 2800 3.0 (normal) + 2800 3.0 (overload) + Refer to chapter 2. Refer to chapter 2. OU: Fuel: •For basic mission. AVIONICS +2800 4.0 Max landing +Limited by structure. Max takeoff Max takeoff 1903 Empty (actual).... 1903 Basic (actual) .... 2800 3.0 Design *2650 Combat FUEL AND OIL t f July 1963 August 1963 October 1962 Completed PERSONNEL or or or Litters (ext) 1 Litters (ext) 2 Attendant 1 Student pilot 1 Crew 1 Crew 1 Passenger 2 Crew 1 Crew (normal) 1 Hiller UH-12E Mfr’s Model: AND DESCRIPTION MISSION and C-133 aircraft. and tail rotor blades. for the 0-540-9 engine. The OH-23G is similar to the OH-23D except single side-by-side helicopter with a The OH-23G is a three-place, Alternate of the OH-23G is armed reconnaissance. The principal mission Interchangeable main rotor Rotormatic control. External litters. Dual controls (prov). Transportable in C-124 First flight First acceptance. Gnd handling wheels. Date of contract Production status construc- fuselage is of all-metal, semimonocoque dinal lateral trim. The tion. The 0-540-9 engine increases performance. the left seat. for a second set operated from center seat with provisions for longitu- with the cyclic control stick A trim system is incorporated FEATURES from the of a single set of controls operated control system consists and medical evacuation. missions are training gear. The tail rotor, and skid-type landing main rotor, an antitorque DEVELOPMENT « DIMENSIONS POWERPLANT MIN BHP RPM ALT ENGINE RATINGS operating .... 40 ft, 8-1/2 in. Idling 9 ft, 3-1/2 in. Static 6 ft, 4 in. Fuselage 27 ft, 9-1/2 in. lateral) 10 ft Rotors static ... 40 ft, 8-1/2 in. Rotors .66:1 gearratio 8 Rotor gnd clearance: Span (max Height 10 ft, 1-1/2 in. Tread 7 ft, 6 in. (Raven) Characteristics. 1-40. OH-23G Rotor dia 35 ft, 5 in. •METO power. Length: SL Cont. Takeoff 305 3200 2304 Engine spec No .... D.D. Red. gear ratio .... Eng/main rotor (1) 0-540-9 No. & model Lycoming Mfr SL Cont. •Normal 305 3200 /

FM 101-20-1 FM 101-20-1

1-41. Loading and Performance - Typical Mission, OH-23G (Raven). BASIC AND DESIGN CONDITIONS MISSION EVACUATION TRAINING I II HI TAKEOFF WEIGHT (lb) 2800 4/ 2400 3^ 2600 Fuel at 6.0 Ib/gal (grade 115/145) (lb) 276 230 276 Payload (outbound) (lb) 214 55 None Payload (inbound) (lb) 140 400 None Takeoff power loading (lb/bhp) 9.2 9.2 8.5 Disk loading (lb/sq ft) 2.82 2.82 2.62 Autorotation speed (min R/D) (kn) 45 45 45 Takeoff ground run at SL1/ (ft) 0 0 0 Takeoff to clear 50 ft i/ (ft) 0 0 0 Vertical rate of climb at SL i/ (fpm) 750 750 1090 Max rate of climb at SL 1/ (fpn>) 1380 1380 1510 Speed for max rate of climb at SL i/ (kn) 46 46 46 Time: SL to 5000 ft-1/ (min) 3.6 3.6 3.2 Service ceiling (100 fpm) J/ (ft) 17,600 17,600 18,100 Absolute hovering ceiling 1/ (ft) 7200 7200 10,000 COMBAT RANGE 1/ (nmi) 152 155 Average cruising speed (kn) 78 78 Cruising altitude (ft) 5000 5000 Total mission time (hr) 2.1 1.9 COMBAT RADIUS 2/ (nmi) 70 65 73 Average cruising speed (kn) 78 65 78 Cruising altitude (ft) 5000 5000 5000 Total mission time (hr) 1.9 2.0 1.8 FIRST LANDING WEIGHT 3/. (lb) 2650 2275 2475 Ground roll at SL (power on/autorotation) . .. (ft) 0/275 0/275 0/275 Total from 50 ft (power on/autorotation) .... (ft) 0/400 0/400 0/400 COMBAT WEIGHT (lb) 2650 2675 2475 Combat altitude (ft) 5000 5000 5000 Combat speed U (kn) 78 65 78 Combat climb !/ (fpm) 1420 1350 1560 Combat ceiling (500 fpm) i/ (ft) 14,400 14,400 15,500 Service ceiling (100 fpm) i/ (ft) 19,200 18,800 20,000 Absolute hovering ceiling J/ (ft) 9200 9000 10,000 Takeoff ground run at SL i/ (ft) 0 0 0 Takeoff to clear 50 ft J/ (ft) 0 0 0 Max rate of climb at SL i/ (fpm) 1515 1500 1660 Speed for max rate of climb at SL 1/ (kn) 46 46 46 Max speed at SL ft J/ (kn) 83 65 6/ 83 Basic speed at 5000 ft J/ (kn) 78 & 65 & 78 LANDING WEIGHT 3/ (lb) 2475 2550 2350 Ground roll at SL (power on/autorotation) . .. (ft) 0121S 0/275 0/275 Total from 50 ft (power on/autorotation) .... (ft) 0/400 0/400 0/400

-1/METO power. 2/Detailed descriptions of RADIUS and RANGE missions are given in paragraph 1-42. 2/For RADIUS mission if radius is shown. 4/lncludes crew of 2 at 400 lb. ^Includes crew of 1 at 200 lb. ^/Limited by stall.

1-78 roR-erriciAi use onb-Y FM 101-20-1

1-42. Performance Notes, OH-23G (Raven). until 90 percent of initial fuel is consumed. Range-free allowances are 5 minutes of METO power at sea level FORMULA: RADIUS MISSIONS I & III for warmup and takeoff plus 10 percent of initial fuel for reserve. Warm up, take off, climb on course to 5000 feet at METO power, cruise out at long range speed to GENERAL NOTES. remote base, and land. Without refueling and with no change in payload, warm up, take off, climb on course Engine ratings listéd in paragraph 140 are man- to 5000 feet at METO, power, and return at long range ufacturer’s guaranteed ratings. METO power values speed. Range-free allowances are 10 minutes of METO used in performance calculations are as follows: power at sea level for warmups and takeoffs plus 10 percent of initial fuel for reserve. BHP FOR BHP FOR FORWARD FORMULA: RADIUS MISSION II ALT RPM HOVER FLIGHT Warm up, take off, climb on course to 500 feet at SL 3200 305 305 METO power, cruise out at long range speed to remote base, land, and load two litter patients. Without refueling, warm up, take off, cUmb on course to 5000 feet 5000 ft ... 3200 282 282 at METO power, and return at long range speed. Range-free allowances are 10 minutes for warmups and 10,000 ft 3200 238 238 takeoffs plus 10 percent of initial fuel for reserve.

FORMULA: RANGE MISSIONS I & III PERFORMANCE REFERENCES: Warm up, take off, climb on course to 5000 feet at METO power, and cruise out at long range speed Commercial and military technical manuals.

hUK UhHUAL U¿E UHL-* 1-79 Figure 1-20. OH-58 A, Light observation helicopter (Kiowa)

1-80 K)R OMICIAL USE ONLY 6' 5.4"

STA 107.1 20 y- 20' 0.5" BLADE TURNING DROOP 2' 3.3" 9' 7.0" 5' 4.7 r STATIC t □00 1 8.0 1.5" TURNING 6' 5.7" UNITED STATES ARMY T 0.8" rip-ti] C ST A 107.5 STATIC 5' 2.0" 6'8.0" ♦

8' 1.3" 32' 1.9"

40' 11.8"

12'7.1"

1' 1.0" «éT P

6' 5.20" 35 4.0

AV 000185

Figure 1-21. Principal dimensions, OH-58 A (Kiowa)

roR-orriciAL USE ONLY ^ 1-81 POR OFFICIAL U3C ONLY 1 10-W-30 1 Fuselage 73 gal Fuselage MIL-L-2104 MIL-L-7808 MIL-L-23699 MIL-L-7808 JP- 4 MlL-T-5624 MIL-F-46005 (Type I) MIL-G-5572 AVIONICS ARMAMENT FUEL AND OIL LB LF. LOADING 2.71 mission .... 2766.6 Location.. Alternate . Spec No. Tanks. Emergency Spec Engine Spec Unarmed 2.52 Armed mission . 2973.6 Spec Alternate .. Grade .... 586 Empty 1 1807.6 Empty (with armor) M/R Hub ... 1766.2 3.50 Basic 3000 2.50 Design Combat Location .. . Qty Oil: Transmission 3000 2.50 Max structural . . Fuel: No. Tanks .. WEIGHTS Refer to chapter 2. Refer to chapter 2. 4 1 1 2 PERSONNEL Crew (normal) Copilot Observer .... DEVELOPMENT BeU 206A Mfg’s Model: AND DESCRIPTION MISSION FEATURES t main rotor type. The This helicopter is the single engine, single be employed Helicopter shall for which the OH-58A The missions rotor system Rear seat paUetized Cargo platform Dual controls Two bladed seesaw of hour endurance at a takeoff gross weight 260 mile range or 3.0 or company level without use of special kits tasks at the combat to utility helicopter shall be readily adaptable command control. The brigade, The helicopter shall be organic to division, special attachments. conditions. marginal visual flight with a range at 230 weapon system and 2000 rounds of ammunition, as well as the pylon which provides the cabin and fuel cell enclosure May 1969 First production article and target acquisition, reconnaissance, are: visual observation, pounds. miles at a takeoff gross weight of 2967 the forward section fuselage is divided into three main sections, the engine provides the support, the intermediate section supports and the tail boom which equipment and electronics compartments, stabUizer and the tail rotor. supports the horizontal stabilizer, the vertical is the shock-absorbing skid on top of the fuselage. The landing gear of the main rotor horizontally The free turbine engine is mounted aft type. daily opera- level, and be capable of continuous .battalion, or equivalent tactical com- area, with maximum availability to the tion in the forward visual and shall be limited to day and night ¡ mander. Normal operations with a perform an unarmed observation mission I The OH-58A can armed with the XM-27E-1 ' 2760 pounds. It can perform a scout mission, ment 1 compressor, free turbine 18 in. 135 lbs. 17.44:1 15.5 in. 803-F Amend- Axial-centrifugal (1) T63-A-700 Allison Corp. 41 in. SHP RPM DUR DIMENSIONS POWERPLANT ENGINE RATINGS operating .... 40 ft, 11.8 in. removed 32 ft, 1.9 in. rotor fairing .. 9 ft, 7.0 in. Rotors Disk area 979.8 sq. ft. Blade area 38.26 sq. ft. Disk area 20.97 sq. ft. Blade area .... 2.26 sq. ft. Blades To top of gear ratio .... ’•‘Derated for Transmission Length: Normal 270 6180 Cont.* Height: Standard Sea Level Static Conditions Takeoff 317 6180 5 min. Length Helicopter rotor Mfr Engine spec. no. Main rotor: Rotor dia 35 ft, 4 in. Height .. No. & model Tail rotor: Width Weight Type Tread of skids .... 6 ft, 5.4 in. (Kiowa) Characteristics. 1-43. OH-58A

FM 101-20-1 FM 101-20-1

1-44. Loading and Performance - Typical Mission, OH-58A (Kiowa).

I II CONDITIONS BASIC MISSION ALTERNATE (Unarmed Observation) (Armed Scout)

TAKEOFF WEIGHT 2760 29671/ Fuel 455 428 Payload 170 298 Takeoff Power Loading 9.15 9.84 Disk Loading 2.82 3.03 Speed for Min. R/D 49 49 Vertical Rate of Climb @ Sea Level Í/ Max Rate of climb @ Sea Level 1/.. .. 1780 1600 Speed for Max R/C @ Sea Level .... 48 50 Time Sea Level to 5000 ft. -Î/ 3.5 4.0 Time Sea Level to 10,000 ft. -1/ 7.5 8.5 Service Ceiling (100 fpm) 2/ 19.000 17.200 Absolute Hover Ceiling J/ 8,000 5,400 COMBAT RANGE 260 230 Average speed 102 120 Cruising Altitude 14.000 10,000 Total Mission Time 2.98 2.47 COMBAT RADIUS 147 121 Average Speed 102 102

Cruising Altitude ; 14.000 12.200 Total Mission Time 2.98 2.47 COMBAT WEIGHT 3/ 2550 2770 Combat Altitude 14.000 10,000 Combat Speed 87 99 Combat Climb -1/ 1090 1120 Service Ceiling-^ 21.000 19,500 Absolute Hover Ceiling 10,600 8000 Max R/C @ Sea Level ^ 1750 1600 Speed for Max R/C 48 50 Max Speed @ Sea Level 120 120 Basic Speed @ 5000 ft 114 114

J/ Takeoff power up to 5 minutes. -2/Normal Power. -2/For Radius Mission. ^/includes XM-27E-1 Armament Kit. Performance Basis: Bell flight test 206A MOD. All performance is out of ground effect and for standard atmospheric conditions.

1-45. Performance Notes, OH-58A (Kiowa). Warmup — Two minutes at normal power at sea level Takeoff and Climb — On course at military power to RADIUS MISSION - III altitude for best range at average cruise weight Cruise — At speed for best range RANGE MISSION - I II Reserve - 10% takeoff fuel

TOR ornaAL use ONLY 1-83 FM 101-20-1

1 * î. ,t . È* .**■ -

AV 000055

Figure 1-22. UH-1B (Iroquois)

1-84 rmjg-ÖEI FM 101-20-1

|-*— 9 FT 3- 1/2 IN

8 FT 4-3/4 IN.—►j

i Œ=

<4 fr

52 FT 10-3/4 IN.

13 FT 2-1/2 IN.

A1 14 FT 9 IN.

38 FT 5 IN

42 FT 8-1/2 IN AV 000056 Figure 1-23. Principal dimensions, UH-1B (Iroquois)

rOR OFPt€IAL UCC ONLY 1-85 186 PfHMtfFlÇIALi U» ONLY or LB L.F. MIL-L-23699 WEIGHTS AVIONICS ARMAMENT FUEL AND OIL Fuselage (2) 165 gal Ferry (1) 350 gal 4557 (calculated).... P-4/5 Grade J IL-T-5624 Spec M No. tanks: Total qty 515 gal Spec MIL-L-7808 No. tanks 1 Location Fuselage Qty 3-1/4 gal Empty 4825 Basic 6600 3.0 Design *For basic mission. 6596 3.0 Combat * 8500 2.3 Max takeoff 8500 Max landing Fuel: Oil: Refer to chapter 2. Refer to chapter 2. 1 2- 1 3 4 7 December 1960 March 1960 December 1961 Ferry T rainer Alternate PERSONNEL Basic mission Transport mission attendant) student) Crew (pilot and medical Litters Crew Passengers Crew Passengers Crew (instructor & Crew DEVELOPMENT Bell 204 Mfr’s Model: AND DESCRIPTION MISSION (overall) Usable cubage CAPACITIES Inside clearance Main cargo door Limit floor loads of personnel, UH-1B are the transport missions of the The principal a low UH-1B is of compact design having The gas-turbine-powered may be allow straight-through loading. Litters Sliding cabin doors Length (overall). ... 4 ft Width (floor level).. 6 ft, 8-1/2 in, Height (max) 4 ft Length (overall) ... 4 ft, 7 in. Height (max) 4 ft Width (floor level).. 2 ft, 7 in. to serve as an aerial supplies, and or crews, equipment, special teams serve to the aircraft to pylons are attachable Universal weapons platform. be used for or external fuel tanks. It may also as mounts for weapons may be and as an instrument trainer. These missions medical evacuation areas, under or unprepared takeoff and landing performed from prepared flight. including light icing, and day or night instrument operations tail rotor are main rotor and the two-bladed silhouette. The two-bladed construction The fuselage is of semimonocoque of all-metal construction. cargo floor is or both sides simultaneously. The loaded from either side have removed, additional cargo area. Some UH-lB’s, the copilot’s seat is thus loading. The copilot’s controls are removable, knee-high to facilitate or, when for a passenger in the copilot’s seat providing accomodations power-driven hoist supported complete provisions for a variable speed, or cargo while hovering. by a swing boom, capable of lifting personnel First flight First delivery ... Date of contract Cargo area: Copilot area: Height (max) 4 ft Width (max 4 ft Cargo area 300 Ib/sq ft Copilot area 75 Ib/sq ft Cargo area 140 cu ft Copilot area 20 cu ft RPM RPM -9/-11 turbine SFC Output 0.694 6607 0.702 6607 0.715 6607 SFC Output 0.682 6610 0.690 6610 0.702 6610 SHP 960 900 825 POWERPLANT DIMENSIONS ENGINE RATINGS operating .... 53 ft (takeoff) (takeoff) 1100 Rotors Rotors static ... 53 ft Fuselage 42 ft, 8-1/2 in. lateral) 9 ft, 3-1/2 in. (static) 7 ft, 4-3/4 in. ... (1) T53-L-5/ No. & model Lycoming Mfr Free power Type Red. gear ratio .. 0.3119 ixed area Tailpipe F Augmentation .. None Characteristics. UH-1B (Iroquois) 1-46. T53-L-5 Rating/SL Max Rating/SL SHP Mil NRP T53-L-9/11 Max Mil 1000 NRP 900 Rotor dia 44 ft Length: Span (max Height 14 ft, 8-1/2 in. Rotor gnd clearance: Tread 8 ft, 4-3/4 in.

FM 101-20-1 1-47. Loading and Performance - Typical Missions, UH-1B (Iroquois). TRANSPORT INSTRUMENT CONDITIONS (CARGO OR ARMED 12/ TRAINER FERRY PASSENGER) TAKEOFF WEIGHT .... (lb) 6762 6605 6088 ^/ 8390 é/ Fuel at 6.5 Ib/gal (grade JP-4) ...... (lb) 1073 1073 1073 5/ 3348-2/ Payload (outbound) .... (lb) 800 0 0 0 Payload (inbound) .... (lb) 0 90 0 0 Takeoff power loading^. . (lb/bhp) 7.04 6.86 6.34 8.74 Disk loading /.... (Ib/sq ft) 4.45 4.35 4.00 5.52 Autorotation speed (min R/D) ...... (kn) 57.0 56.5 55.6 60.1 Takeoff ground run at SL1/ .... (ft) 0 0 0 0 Takeoff to clear 50 ft í/ .... (ft) 0 0 0 0 Vertical rate of climb at SL ¿/ .. . (fpm) 1610 1780 2330 Maximum rate of climb at SL 2/...... (fpm) 1910 2010 2300 1250 Speed for max R/C at SL . .. (kn) 57.0 56.5 55.6 60.1 Time: SL to 5000 ft 2/ . .. (min) 2.7 2.5 2.3 4.6 Time: SL to 10,000 ft2/ ... (min) 6.0 5.4 4.9 ....11/ Service ceiling (100 fpm)-2/ .... (ft) 18,000 17.000 20,200 8800 Absolute hovering ceiling -1/. .... (ft) 11,500 12.400 14,900 COMBAT RANGE ... (nmi) 230 210 218 695 Average cruise speed ... (kn) 106 90 106 103.4 Initial cruising altitude .... (ft) 10,000 10.000 10,000 5000 Final cruising altitude .... (ft) 10,000 10,000 10,000 10,000 Total mission time .... (hr) 2.25 2.45 2.12 6.88 COMBAT RADIUS .. (nmi) 112.7 94.5 98.8 Average cruise speed ... (kn) 106 90 106 Cruising altitude (outbound) .... (ft) 10,000 10,000 10,000 Cruising altitude (inbound) .... (ft) 10,000 10,000 10,000 Total mission time .... (hr) 2.22 2.4 1.95 FIRST LANDING WEIGHT 2/ .... (lb) 6253 6145 5631 Ground roll at SL .... (ft) 0 0 0 Total from 50 ft .... (ft) 0 0 0

FM 101-20-1 COMBAT WEIGHT 2/ .... (lb) 5453 7241 5631 5377 Combat altitude .... (ft) 10,000 5000 10,000 10,000 Combat speed .... (kn) 106 100 106 106 Combat climb 2/ ... (fpm) 2190 1590 2050 2220 oo Combat ceiling (500 ft/min) 2/, 12/ .... (ft) 22,400 15.400 21,400 22,600 vj 1-88 0 0 0 0 120 54.1 2810 5377 117.5 18,500 FERRY 23,250 0 0 0 0 120 54.6 2620 5188 117.5 TRAINER 16,800 22,200 INSTRUMENT 0 0 0 0 105 100 58.0 1740 9000 5639 16,000 / ARMED 12 0 0 0 0 120 54.2 2740 4996 117.5 18,200 23,100 OR (CARGO TRANSPORT PASSENGER) ■ (ft) • (ft) • (ft) • (ft) (fpm) • (kn) • (kn) • (kn) • (ft) • (ft) • (lb) CONDITIONS missions are given in paragraph M8. Detailed descriptions of RADIUS and RANGE ft/min)-2/ 12/ Service ceiling (100 12/ . Absolute hovering ceiling-L/ at SL Speed for max R/C at SL-l/ Takeoff ground run ft-!/ Takeoff to clear 50 ft-1/ Basic speed at 5000 at SL-2/.. Maximum rate of climb Max speed at SL-á/ Ground roll at SL “YUH-1B Category II Performance Tests.” a. Power required based on FTC-TDR-62-21, on Lycoming Model Specification No. 104. 16-B. b. Power available and fuel flow are based c. All data are at 6600 engine rpm. include ground effect. d. Except for Ferry Mission, data do not Total from 50 ft Includes crew of 1 at 200 lb. Includes crew of 2 at 400 lb. horsepower available. Based on engine specification takeoff shaft (CONT). UH-1B (Iroquois) - Typical Missions, and Performance 1-47. Loading LANDING WEIGHTJ/ 12/ Armed W/M-16 subsystem. 11/ Above service ceiling. ^V limit. i/Takeoff power. Performance Basis: ■2/ Includes 1 x 350 gallon tank. 2/For RADIUS mission if radius is shown. ■2/Normal rated power. & Three 250-lb litter patients. ne

FM 101-20-1 FM 101-20-1

1-48. Performance Notes, UH-1B (Iroquois). FORMULA: RANGE MISSION II

FORMULA: RADIUS MISSION I Warm up, take off, climb on course to 10,000 feet at normal power, and proceed at cruise speeds until 90 Warm up, take off, climb on course to 10,000 feet percent of initial fuel is consumed. Range-free allow- at normal power, proceed at cruise speeds to remote ances are 2 minutes of normal power for warmup and base, and land. Without refueling, warm up, take off, takeoff plus 10 percent of initial fuel for reserve. climb on course to 5000 feet at normal power, and return at cruise speeds. Range-free allowances are 4 FORMULA: RANGE MISSION III minutes of normal power for warmups and takeoffs plus 10 percent of initial fuel for reserve. Warm up, take off, climb on course to 5000 feet initial altitude at normal power, proceed at cruise speeds to remote base, and land. Range-free allowances FORMULA: RADIUS MISSION II are 5 minutes of normal power for warmup and takeoff, plus 20 minutes at speeds for maximum Warm up, take off, climb on course to 10,000 feet endurance at sea level, plus 5 percent of initial fuel for at normal power, proceed at cruise speeds to remote reserve. base, and land. Without refueling, warm up, take off, climb on course to 10,000 feet at normal power, and FORMULA: RANGE MISSION IV return at cruise speeds. Range-free allowances are 4 minutes of normal power for warmups and takeoffs Warm up, take off, climb on course to 5000 feet plus 10 percent of initial fuel for reserve. initial altitude at normal power, maintain 30 feet per minute rate of climb to final altitude of 10,000 feet, and proceed at cruise speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal power for warmup and takeoff plus 10 FORMULA: RADIUS MISSION III percent of initial fuel for reserve.

Warm up, take off, climb on course to 10,000 feet GENERAL NOTES at normal power, proceed at cruise speeds to remote base, and land. Without refueling, warm up, take off, a. Cruise speed as used above denotes airspeed for climb on course to 10,000 feet at normal power, and long-operation or maximum permissible speed, which- return at cruise speed. Range-free allowances are 10 ever is lower. minutes of normal power for warmups and takeoffs plus 20 minutes at speeds for maximum endurance at b. Except for ferry mission takeoff, data do not sea level, plus 5 percent of initial fuel for reserve. include ground effect.

f-Q-R OFFICIAL USE ONLY 1-89 FM 101-20-1

AV 000058

Figure 1-24. UH-1C and M (Iroquois)

1-90 HUK UH-IUAL U St UNtY FM 101-20-1

r 9 FT 13/32 IN.

7 FT 1 3/4 IN.

— 8 FT IN.—I

44 FT

52 FT 10% IN.

c=-- cs-' %

12 FT 8 IN FT 9 IN

AV 000059

Figure 1-25. Principal dimensions, UH-1C and M (Iroquois)

rFOR OFFICIAL U3C Q}4ÇT 1-91

446-903 0-71-7 i« -POR orne L.F. or LB 9500 4830 MIL-L-23699 WEIGHTS AVIONICS FEATURES ARMAMENT FUEL AND OIL boxes 2.8 gal and gear skid-type landing gear. P-4/5 Grade J IL-T-5624 Spec M 242 gal Qty IL-L-7808 Spec M Qty-Engine .... 4 gal Qty-Transmission Empty Refer to chapter 2. Refer to chapter 2. Gross Fuel: AU metal, semi-rigid rotor, OU: Ferry Trainer Alternate Basic mission PERSONNEL Transport mission student) 2 attendant) 2 Litters 3 Crew (instructor & Crew 1 Crew (pUot and medical Crew 1 Passengers 4 Crew 1 Passengers 7 BeU Mfr’s Model: DEVELOPMENT 8-1/2 in. 6 ft. 4 ft AND DESCRIPTION MISSION CAPACITIES Usable cubage Main cargo door Limit floor loads (overall) level) level) 2 ft, 7 in. transporting UH-1C helicopter are missions of the The principal main between the UH-1C and UH-1B is the The main difference Length (overaU) Length (overall) .. 4 ft, 7 in. Height (max) ... 4 ft Height (max) .... 4 ft Width (floor Width (floor supplies; medical equipment and special teams or crews, personnel, and by attachment of appropriate weapons; target and area fire prepared These missions may be performed from instrument trainer. operations and landing areas, under instrument or unprepared takeoff be by and day or night flight. Navigation may including light icing, point service; reconnaissance and security; evacuation; ambulance use of radio aids. dead reckoning or by has a flexure has the 540 rotor system which rotor system. The UH-1C gross stable gun platform, higher maximum system provides a more rotor hub and a wider cord blade. The 540 plate, hinge-half type speed. Some UH-lC’s have complete weight, and higher forward by a speed, power driven hoist supported provisions for a variable or cargo while hovering. swing boom, capable of lifting personnel Cargo area: Height (max) 4 ft CopUot area: Weight (max) 4 ft Cargo area 300 Ib/sq ft CopUot area 75 Ib/sq ft Cargo area 140 cu ft CopUot area 20 cu ft AVSCOM Contracting agency une 1965 thru November 1967 Delivery schedule J Output SFC RPM IB -9A/-11/-1 turbine 0.682 6610 0.702 6610 0.690 6610 14 ft, 9 in. 53 ft 53 ft 9 ft, 1/2 in. 8 ft, 4-1/2 in. 7 ft, 4-1/2 in. 44 ft 42 ft, 8 in. 900 1000 1100 SHP DIMENSIONS POWERPLANT ENGINE RATINGS operating .... Fuselage Rotors static . . . Rotors lateral) (static) (Iroquois) Characteristics. 1-49. UH-1C/M* (l)T53-L-9/ No. & model Lycoming Mfr 104.22-B&.28 Engine spec No ... Rating/SL Free power Type 0.3119 Red. gear ratio .... Rotor gnd clearance: NRP Rotor dia Length: T53-L-9/11 Span (max Height MU None Augmentation .... Max (takeoff) Fixed area Tailpipe Tread *UH-1M incorporates the T53-L-13 engineT

FM 101-20-1 FM 101-20-1

î-50. Performance - Typical Mission, UH-1C (Iroquois).

Takeoff distance (ft) 0 Rate of climb (fpm) 2,420 Service ceiling (ft) 21,100 Cruise speed-ï/ (kn) 92-110 Max, speed (kn) 140 Range (nmi) 300 Landing distance (ft) 0

-¿/Normal rated power (6600 rpm) at sea level.

F£L&-OI FILIAL U!>b UNLl 1-93 FM 101-20-1

AV 000061

Figure 1-26. UH-1D and H (Iroquois)

1-94 FOR ornciAL USC OML^ FM 101-20-1

p— 9 FT 13/32 IN.—

7 FT 8-7/16 IN.

- 8 FT 6-39/64 IN. -

9 FT 4 IN.

2 FT 6-1/2 IN.

44 FT 10-3/32 IN.

II FT 8-21/32 IN.

11 FT 9-3/4 IN. D 14 FT 5-1/2 IN. □ □ □ 1 FT 3 IN S: GROUND LINE DESIGN GROSS WEIGHT 40 FT 7-3/32 IN.

41 FT 11-5/32 IN. AV 000062

Figure 1-27. Principal dimensions, UH-1D and H (Iroquois)

ron ornciAL DCE DULY 1-95 196 ron OFFICIAL USE or LB L.F. MIL-L-23699 WEIGHTS AVIONICS ARMAMENT FUEL AND OIL Ferry (1)300 gal Fuselage (2) 209 gal 5098 lated) Grade JP-4/5 Spec MIL-T-5624 No. tanks: Spec MIL-L-7808 No. tanks 1 Location Fuselage Qty 4-1/2 gal Total qty 509 gal Empty (calcu- 6600 3.0 Design 9500 2.2 Combat 9500 2.2 Max takeoff 9500 Max landing Fuel: OU: Refer to chapter 2. Refer to chapter 2. Cargo Alternate Basic mission Ferry mission Litter evacuation attendant) 2 Crew 1 Passengers 4 Crew 1 Litters ....'. 6 Passengers 12 Crew (pUot & medical Crew 1 Crew (pUot & copUot) 2 Bell 205 Mfr’s Model: AND DESCRIPTION MISSION ~~ CAPACITIES PERSONNEL Usable cubage Inside clearance Main cargo door Limit floor loads t of personnel, transportation of the UH-1D include The missions The design having a low sUhouette. The UH-1D is of compact each side of the cabin allow simplified The sliding doors along level) 8 ft Length (overall) . . 7 ft, 8 in. Width (floor Height (max) ... .4 ft, 1 in. Length (overaU) .. 3 ft, 7 in. Height (max) .... 4 ft Width 2 ft, 7 in. ground 2 ft Cargo area 220 cu ft CopUot area 20 cu ft medical evacuation, delivery of protective equipment and supplies, train- appropriate weapons, and instrument fire by attachment of areas, under instrument operations pared takeoff and landing and day or night flight. including light icing, the is of all-metal construction as are semimonocoque fuselage the two main rotor blades. taU rotor blades and from either side or both sides simulta- straight-through loading may be performed from prepared or unpre- ing. These missions or un- is especially useful whUe loading neously. This capabüity speed, power-driven hoist have complete provisions for a variable to The knee-high cargo floor also contributes loading litter patients. seat is also removed, an passenger can be carried. If the copUot’s Some UH-lD’s extra 8.75 square feet of cargo area is gained. extra the copUot’s controls are removable, an loading ease. Since Cargo area: lifting personnel or cargo supported by a swing boom, capable of fuel system with closed while hovering. Retrofit of a crashworthy on the UH-1D aircraft. circuit refueling capabUity is being accomplished CopUot area: Height 4 ft Width (max) 6 ft, 2-1/2 in Height above Cargo area 300 Ib/sq ft CopUot area 75 Ib/sq ft Capacity Output IB -9A/-11/-1 turbine 104.28 & .22-B Lycoming Free power (1) T53-L-9/ Fixed area 0.312 None POWERPLANT DIMENSIONS ENGINE RATINGS operating .... 57 ft, 1 in. Rotors Rotors static . . 57 ft, 1 in. Fuselage 41 ft, 11-1/4 in. lateral) 9 ft, 4 in. stops) 6 ft, 6 in. (static, against (Iroquois) Characteristics. 1-51. UH-1D ... No. & model Mfr Engine spec No.. Red. gear ratio .. Type Rating SHP SFC RPM Tailpipe Augmentation .. T53-L-9/11 Rotor dia 48 ft Max (takeoff) 1100 0.682 6610 MU 1000 0.690 6610 NRP 900 0.702 6610 Length: Span (max Tread 8 ft, 6-1/2 in. Height 14 ft, 5-1/2 in. Gnd clearance

FM 101-20-1 FOB ornciAL use ONL-Y 197 0 4 0 0 0 0 9.3 110 103 580 6.87 55.1 55.1 7.99 4.86 5753 2070 1260 8700 3000 8795-5/ 3309 2/ 705.0 FERRY 10,000 18,100 10,000 25,400 27,200 15,200 0 0 0 0 0 0 5.6 2.6 118 2.34 50.9 50.9 1520 3.83 6.30 7600 7800 5000 6320 5000 1960 1880 1359 1500-2/ 143.3 103.5 6930-5/ 18,900 16,200 10,000 12,200 22,400 LITTER EVACUATION P 0 0 0 0 0 0 99 2.7 9.8 4.1 110 134 259 420 2.62 55.5 55.5 8.14 4.95 5800 2040 8220 1220 1359 2300 7800 2420 8954-^/ 103.5 17,800 10,000 10,000 25,200 27,000 10,000 14,900 TROOP) OR (CARGO 8100/10,000 TRANSPORT 0 0 0 0 0 0 2.9 6.2 110 149 102 800 2.92 2.99 51.7 51.7 6.66 4.05 5855 2020 1620 6655 1359 1730 BASIC 7334-é/ 105.4 305.4 17,600 10,000 10,000 25,000 26.900 10,100 10,000 10,000 20.900 CARRIER) (PERSONNEL 10,000/10,000 CONDITIONS Service ceiling (100 ft/min)-2/ (ft) Absolute hovering ceiling (6600 rpm)-!/ (ft) (ft) Combat ceiling (500 ft/min)-2/ Takeoff ground run at SL (6600 rpm)-!/ (ft) (fpm) Combat climb-2/ (ft) Combat altitude (kn) Combat speed-â/ (kn) Average cruise speed (hr) Total mission time (ft) Ground roll at SL (6600 rpm) (ft) Total from 50 ft (6600 rpm) (ft) Cruising altitude (outbound) (min/max) (ft) Cruising altitude (inbound) (hr) Total mission time (kn) Average cruise speed (ft) Cruising altitude (initial) (ftl Cruising altitude (final) (kn) Speed for max R/C at SL (ft) Service ceiling (100 fpm)-2/ (ft) Absolute hovering ceiling (6600 rpm)-i/ (lb/sq ft) Disk loading (min R/D) (kn) Autorotation speed at SL-2/ (fpm) Maximum rate of climb JP-4) (lb) Fuel at 6.5 Ib/gal (grade (min) Time: SL to 5000 ft-2/. (min) Time: SL to 10,000 ft-2/ at SL (6600 rpm)-i/ (ft) Takeoff ground run at SL (6600 rpm)-¿/.... (fpm) Vertical rate of climb (Ib/SHP) . Takeoff power loading-^/ ft (6600 rpm)J~/ (ft) Takeoff to clear 50 (lb) Payload (outbound) (lb) Payload (inbound) (lb) FIRST LANDING WEIGHT-2/ (lb) COMBAT WEIGHT-2/ (nmi) COMBAT RADIUS 10/ (nmi) COMBAT RANGE 10/ (lb) TAKEOFF WEIGHT UH-1D (Iroquois). - Typical Missions, and Performance 1-52. Loading

FM 101-20-1 FOR orriciAL use ONUT 0 0 0 120 119 48.6 2420 5753 FERRY 0 0 0 118 52.8 1560 7143 117.5 LITTER EVACUATION » 0 0 0 120 119 48.7 2400 5247 TROOP) OR (CARGO TRANSPORT 0 0 0 120 119 48.8 2360 5247 BASIC CARRIER) (PERSONNEL CONDITIONS missions are given in paragraph 1-53. Detailed descriptions of RADIUS and RANGE ft (6600 rpm) 1/ (ft) Takeoff to clear 50 at SL (fpm) Maximum rate of climb at SL (kn) Speed for max R/C ft 4/ (kn) Basic speed at 5000 (kn) Max speed at SL 4/ rpm) (ft) Ground roll at SL (6600 rpm) (ft) Total from 50 ft (6600 204B FAA Flight Test. a. Power required based on Bell Model on Lycoming Model Specification No. 104.28. b. Power available and fuel flow based noted. c. All data are at 6400 rpm unless otherwise V limit. ne (CONT). UH-1D (Iroquois) - Typical Missions, and Performance 1r52. Loading (lb) LANDING WEIGHT^ 2/ Normal rated power. J/ Takeoff po wer. & For RADIUS mission if radius is shown. & Includes crew of 2 at 400 lb. shaft horsepower. â/ Based on engine specification takeoff Performance Basis: è/Includes crew of 1 at 200 lb. ^ Includes two 150-gallon ferry tanks. S' Six 250-pound litter patients.

FM 101-20-1 FM 101-20-1

1-53. Performance Notes, UH-1D (Iroquois). on course to 5000 feet at normal rated power, and return at long range cruise speed. Range-free allow- FORMULA: RADIUS MISSION I ances are 4 minutes at normal rated power for warmups and takeoffs plus 10 percent of initial fuel for Warm up, take off, climb on course to 10,000 feet reserve. initial altitude at normal rated power, proceed at long range cruise speed to remote base, land, and unload FORMULA: RANGE MISSION I passengers. Without refueling, warm up, take off, climb on course to 10,000 feet at normal rated power, and Warm up, take off, and climb on course to 10,000 return at long range cruise speed. Range-free allow- feet initial altitude at normal rated power. Proceed at ances are 4 minutes at normal rated power for warm- long range cruise speed to remote base and land. ups and takeoffs plus 10 percent of initial fuel for Range-free allowances are 2 minutes at normal rated reserve. power for warmup and takeoff plus 10 percent ol initial fuel for reserve. FORMULA: RADIUS MISSION II FORMULA: RANGE MISSION II

Warm up, take off, and climb on course to 8100 Warm up, take off, and climb on course to 7800 feet at normal rated power. Cruise climb on course at feet at normal rated power. Cruise climb on course at long range cruise speed to final altitude of 10,000 feet. long range cruise speed to final altitude of 10,000 feet. Proceed at long range speed to remote base, land, and Proceed at long range cruise speed to remote base and unload cargo or troops. Without refueling, warm up, land. Range-free allowances are 2 minutes at normal take off, climb on course to 10,000 feet at normal rated power for warmup and takeoff plus 10 percent rated power, and return at long range cruise speed. of initial fuel for reserve. Range-free allowances are 4 minutes at normal rated power for warmups and takeoffs plus 10 percent of FORMULA: RANGE MISSION IV initial fuel for reserve. Warm up, take off, and climb on course to 8700 FORMULA. RADIUS MISSION III feet at normal power. Cruise climb on course at long range cruise speed to final altitude of 10,000 feet. Warm up, take off, and climb on course to 10,000 Proceed at long range cruise speed to remote base and feet at normal rated power. Proceed at long range land. Range-free allowances are 2 minutes at normal cruise speed to remote base, land, and pick up litter rated power for warmup and takeoff plus 10 percent patients. Without refueling, warm up, take off, climb of initial fuel for reserve.

-FOR OFFICIAlrUSE ONLY- 1-99 1100 ~F-QR OrriCIAL USE ONLY LB L.F. or 5132 9500 2.2 6600 3.0 9500 9500 2.2 MIL-L-7808 WEIGHTS AVIONICS ARMAMENT FUEL AND OIL Ferry (1) 300 gal Fuselage (2) 209 gal Spec MIL-T-5624 Grade JP-4/5 No. tanks: Total qty 509 gal Spec MIL-L-23699 Location Fuselage Qty 4-1/2 gal No. tanks 1 Empty Design .... Combat ... Max landing Max takeoff Fuel: Oil: Refer to chapter 2. Refer to chapter 2. 1 1 12 1 2 2 4 6 Cargo Alternate Basic mission Ferry mission PERSONNEL Litter evacuation attendant) Crew Litters Passengers Crew Passengers Crew (pilot & medical Crew Crew (pilot & copilot) Bell 205 Mfr’s Model: AND DESCRIPTION MISSION CAPACITIES Usable cubage Inside clearance Main cargo door Limit floor loads UH-1D with the T53-L-13 turbine The UH-1H is a modified level) 8 ft Length (overall) .. 7 ft, 8 in. Length (overall) .. 3 ft, 7 in. Width (floor Height (max) .... 4 ft, 1 in. Height (max) .... 4 ft Width 2 ft, 7 in. ground 2 ft Cargo area 220 cu ft Copilot area .... 20 cu ft Some the UH-1D will be the UH-1H model. future production of both and mission are the same for engine. The basic description All and overall mission capabilities. of climb, range, endurance, provisions for a variable speed, power- UH-lH’s have complete by a swing boom, capable of Ufting driven hoist supported rate over the UH-1D are takeoff distance, aircraft. The advantages of hovering. Production and retrofit personnel or cargo while on the UH-1D/H aircraft. ability is being accomplished with closed circuit refueling cap- a crashworthy fuel system Cargo area: Height (max) 4 ft Height above Copilot area: Width (max) 6 ft, 2-1/2 in. Cargo area 300 Ib/sq ft Copilot area 75 Ib/sq ft Capacity: Output 104.33 Lycoming (1) T53-L-13 Fixed area 0.312 None 14 ft, 5-1/2 in. 57 ft, 1 in. 57 ft, 1 in. 9 ft, 4 in. 8 ft, 6-1/2 in. 6 ft, 6 in. 41ft, 11-1/4 in. 48 ft DIMENSIONS POWERPLANT ENGINE RATINGS operating .... Rotors Rotors static .. Fuselage stops) (static, against lateral) (Iroquois) Characteristics. 1-54. UH-1H . No. & model Mfr Red. gear ratio Type Tailpipe SFC RPM Rating/SL SIff Augmentation * 1400 SHP flat rated to 1100 SHP. T53-L-13 Mil ' 1400* 0.580 6300 NRP 1250* 0.598 6040 Rotor dia Length: Span (max Height Tread Gnd clearance

FM 101-20-1 JX)R ornciAL ose ONLY 0 0 0 0 65 65 4.1 110 676 580 10.2 6.13 5.14 8.45 1112 8700 3600 33202/ 9305 i/ 10,000 13,640 FERRY 0 0 0 60 60 2.9 5.9 133 121 6.74 4.10 1691 1960 ISOOi/ 1370 7414Í/ 16,000 19,140 LITTER EVACUATION P 0 0 0 65 65 9.9 4.6 124 107 105 250 420 2.37 5.11 8.42 1126 7800 1370 4000 T 2420 9264i/ 10,000 13,960 TROOP) OR (CARGO TRANSPORT 0 0 0 61 61 6.2 3.1 111 141 111 275 800 2.46 6.94 4.22 1620 1653 1370 7644 6/ 10,000 10,000 14,800 18,340 BASIC CARRIER) (PERSONNEL CONDITIONS Average cruise speed (kn) (hr) Total mission time (ft) Cruising altitude (final) (ft) Absolute hovering ceiling (6600 rpm)]/. (kn) Average cruise speed (ft) Cruising altitude (initial) (kn) Speed for max R/C at SL (ft) Service ceiling (100 fpm)2/ (min) Time: SL to 5000 ft 2/. (min) Time: SL to 10,000 ft 2 (fpm) Maximum rate of climb at SL!/ (kn) Autorotation speed (min R/D) (ft) Takeoff to clear 50 ft (6600 rpm)!/. (fpm) Vertical rate of climb at SL (6600 rpm)L/ lb) JP4) ( Fuel at 6.5 Ib/gal (grade ft) (Ib/sq Disk loading (ft) Takeoff ground run at SL (6600 rpm)!-/ (Ib/SHP) Takeoff power loading^/ (lb) Payload (outbound) lb) ( Payload (inbound) COMBAT RADIUSlW (nmi) (nmi) COMBAT RANGE 10/ UH-1H (Iroquois). - Typical Missions, and Performance 1-55. Loading (lb) TAKEOFF WEIGHT

FM 101-20-1 1-102 0 0 0 0 116 120 120 56.1 6316 2200 2178 6316 10,000 23,150 23,680 20,700 FERRY 0 0 0 0 0 0 120 120 120 2.38 62.0 5000 1370 1399 6789 5000 8289 6789 LITTER 10,000 15,960 16,842 11,600 EVACUATION 0 0 0 0 0 0 116 120 120 2.54 55.8 8584 6164 2276 2251 8584 10,000 10,000 23,694 24,210 21,400 TROOP) 8100/10,000 TRANSPORT (CARGO OR 0 0 0 0 0 0 116 120 120 2.73 55.9 6997 6197 2256 2232 6977 10,000 10,000 23,550 24,070 21,300 BASIC CARRIER) 10,000/10,000 (PERSONNEL CONDITIONS ft) ( Cruising altitude (inbound) ft) (min/max) ( Cruising altitude (outbound) hr) ( Total mission time ft) rpm) ( Ground roll at SL (6600 (ft) Total from 50 ft (6600 rpm) (ft) Service ceiling (100 ft/min)2/ (ft) Absolute hovering ceiling (6600 rpm)!/ (ft) Combat altitude (kn) Combat speed!/ (fpm) Combat climb2V (ft) Combat ceiling (500 ft/min)2/ (fpm) Maximum rate of climb at SlS/ (kn) Sper i for max R/C at SL ! (kn) Basic speed at 5000 ft!/. (ft) Takeoff ground run at SL (6600 rpm)!/ (ft) Takeoff to clear 50 ft (6600 rpm)!/ (kn) Max speed at SL!/ Ground roll at SL (6600 rpm) ' (ft) Total from 50 ft (6600 rpm) (ft) (CONT). UH-1H (Iroquois) - Typical Missions, and Performance 1-55. Loading (lb) FIRST LANDING WEIGHTS/. (lb) COMBAT WEIGHTS/ (lb) LANDING WEIGHTS/

FM 101-20-1 FOR OFFICIAL USE ONI Y 1103 Model UH-1D H Helicopter TM 55-1520-210-10. a. Reference operator’s Manual Army noted. b. All data are at 6600 rpm unless otherwise Six 250-pound litter patients. RANGE missions are given in paragraph 1-52. 19/ Detailed descriptions of RADIUS and Performance Basis: (CONT). UH-1H (Iroquois) - Typical Missions, and Performance 1-55. Loading 1 at 200 lb. 9/ Includes crew of 2 at 400 lb. ly Includes crew of ÛJ V limit. specification takeoff shaft horsepower. 2/ Based on engine power. 1/ Takeoff 2J Normal rated power. if radius is shown. 2/ For RADIUS mission ferry tanks. ■1/ Includes two 150-gallon ne

FM 101-20-1 FM 101-20-1

AV 000070

Figure 1-28. TH-13T (Sioux)

1-104 POR orriciAL use ONLY FM 101-20-1

8 FT 6-3/4 IN

8 FT 2-1/4 IN.

- 7 FT 6 IN.- 9 FT 5-1/2 IN

u £

32 FT 4 N.

-43 FT 2-1/2 IN.-

5 FT 10-1/4 IN.

1/2

6 FT 7-3/4 IN.

9 FT 4 N. 22 FT 6-1/2 IN AV 000071

Figure 1-29. Principal dimensions, TH-13T (Sioux)

EQR OFFICIAL UCC ONt’Y 1-105 1106 TOK OFFICIAL*U¿E ONK LB L.F. WEIGHTS AVIONICS ARMAMENT FUEL AND OIL 100/130 Grade MIL-G-5572 Spec 2 No. tanks Fuselage Location 57 gal Qty MIL-L-22851 Spec 1 No. tanks Location Engine section Qty 3-1/2 gal Fuel: ... 2060 Empty (actual) 2950 2.5 Design Refer to chapter 2. OU: None. PERSONNEL Crew (normal) ... Passenger/student. DEVELOPMENT BeU47G3-Bl Mfr’s Model: AND DESCRIPTION MISSION FEATURES June 1964 Contract awarded December 1964 First acft delivered December 1968 Last production acft training. is primary instrument mission of the TH-13T The principal tail rotor a 2-blade main rotor and a 2-blade The TH-13T incorporates cockpit configuration with a bubble-type fuselage is an open-tube handling gear is of the skid-type, with ground enclosure. The landing The boosted cyclic and collective control system. with a hydraulically controls are installed. wheels attached. Dual Dual controls. DIMENSIONS POWERPLANT MIN BHP RPM ALT ENGINE RATINGS operating .... 43 ft, 2-1/2 in. Rotors static ... 43 ft, 2-1/2 in. Rotors Fuselage 32 ft, 4 in. lateral) 8 ft, 6-3/4 in. (idling) 8 ft, 8-1/2 in. (static) 8 ft, 8-1/2 in. Engine spec No . 2309A Red. gear ratio . D.D. ... (1) 0435-25A No. & model Lycoming Mfr SL Cont. Normal 220 3200 7 ft, 1-1/2 in. Rotor dia 3 SL 5 Takeoff 270 3200 Length: Span (max Height 9 ft, 3-1/2 in. Rotor gnd clearance Tread 7 ft, 6 in. (Sioux) Characteristics. 1-56. TH-13T

FM 101-20-1 AV 000073

Figure 1-30. TH-55A (Osage)

rnp nmfifli "cc nM1 v

446-903 0 - 71 - 8 1-108 FM 101-20-1 AV 000074

7 FT 5-1/2 IN. 4 FT3IN. 7 FT2IN. [73^ 10 IN Figure 1-31.Principaldimensions,TH-55A(Osage) 6 FT6-1/2IN.MAX FULLY COMPRESSED LANDING GEAR 27 FT9-1/2IN. 28 FT3IN. F” 22 FT4IN. 12 FT6IN 8 FT2-1/2IN a 6 FT7-1/2IN. 3 FT4IN FOR OfriCIAL USE ONH.Y 1109 LB 1065 below 40° F 1 1100 above 40° F, 2 gal 1 MIL-L-22851 115/145 Left rear of cabin 25 gal MIL-G-5572 AVIONICS WEIGHTS ARMAMENT FUEL AND OIL tanks. . Qty Spec . . . No. tanks Location. Qty Grade. . . Spec . . . , No. of Grade. . . . 1600 Design (gross) .... 1008.1 Empty 591.9 Useful load NA Combat 1600 Max takeoff None. Refer to chapter 2. Oil: Fuel: 1 1 2 i PERSONNEL Student pilot . . Instructor pilot. Crew (normal). . . DEVELOPMENT AND DESCRIPTION MISSION is designed to accommodate an instructor The two-place cabin is manufactured by the Hughes Tool The TH-55A helicopter April 1969 Last production acft November 1964 First acft delivered June 1964 Contract awarded each have a complete set of flight controls. structor and student in- seating arrangement side by side. The and student with the of a helicopter. Training will be accom- tion and performance training and from an established aviation plished only in CONUS base. opera- training of military pilots in the basic of the TH-55A is the mission Division, Culver City, California. The Company, Aircraft 22 ft, 4 in. 28 ft, 3 in. 8-deg washout NACA 0015 DIMENSIONS BHP RPM MIN POWERPLANT ENGINE RATINGS section .... NACA 0015 centerline) . . 2 ft, 5 in. blades 2 operating. . ratio 6:1 Span (from boom Airfoil Rotor dia.... 3 ft, 4 in. Delta 3 angle . 30 deg Number of Static 7 ft, 5-1/2 in. clearance .... 3 ft, 2-1/2 in. Operating. ... 8 ft, 3-1/2 in. Rotors static. Fuselage 21 ft, 10-3/4 in. Rotors blades max power rotor rear Airfoil section. . NACA 0015 Horizontal stabilizer: Tail rotor: Tail rotor gnd Height 8 ft, 2-1/2 in. Tread (static) . . 6 ft, 3 in.(approx^ Main rotor gnd clearance: Length: Blade twist. . . Airfoil section. Number of Main rotor dia. . 27 ft, 5 in. (Osage) Characteristics. 1-57. TH-55A Cont. Normal 160 2700-2900 5 Takeoff 180 2900 FAA type cert. . 1E10 Engine to main No. & model. . . (l)H10-360-B!A ycoming Mfr L

FM. 101-20-1 FM 101-20-1

1-58. Loading and Performance - Typical Mission, TH-55A (Osage).

CONDITIONS BASIC MISSION Fuel at 6.0 Ib/gal (grade 91/96) (lb) 150 Payload (lb) 591.9 Cruise speed at SL (kn) 75 Rate of climb at SL (ft/min) 1400 Endurance (2700 rpm) 2-1/2 hrs at 65 knots cruise speed (min) Hover ceiling, out of ground effect, 110°F (ft) 1000 (min) Normal autorotation speed (kn) 45 Normal autorotation rotor speed (rpm) 480 Autorotation rate of descent at 1000 ft, 100 F, 480 rpm and 45 knots (ft/min) 1900 (max) Altitude necessary to regain normal autorotation rotor speed from lower red line (ft) 200 (max) Range (normal) (nmi) 200 Service ceiling • (ft) 11,000

1-110 FOR "OFFICIAL USE ONLtt FM 101-20-1

AV 000076

Figure 1-32. 0-1D, E, and G (Bird Dog), typical (minor differences apparent between D, E, and G models)

TOR ornciAL use ONL-Y im FM 101-20-1

36 FT

7 FT 6 IN. B 7

[-7 FT 6-1/2 IN. STATIC-1 (DESIGN GROSS WEIGHT)

10 FT 6-1 /2 IN. ill

9 FT 6 FT 10-1/2 IN.

0000 5 FT 4 IN. crVIl^r 2 DEG 35 MIN SWEEPBACK

24 FT 9 IN.

9 FT 2 IN

9 IN 7 FT 6 IN. STATIC (DESIGN GROSS WEIGHT) 12 DEG 29 MIN

AV 000077 25 FT 1 IN.

Figure 1-33. Principal dimensions, 0-1E, and G (Bird Dog)

1-112 FOITOI-HriM 1.15t OI ill I K 7 R 6-1/2 IN. STATIC H (DESIGN GROSS WEIGHT)

10 FT 6-1/2 IN.

9 R 6 R 10-1/2 IN. 1

cr 2 DEG 35 MIN SWEEPBACK "*0

24 R 9 IN.

9 R 2 IN

7 FT 6 IN. STATIC (DESIGN GROSS WEIGHT) ] 2 DEG 42 MIN o

25 FT 9-1/2 IN. AV 000079

Figure 1-34. Principal dimensions, O-ID (Bird Dog)

‘ ron orneiAL use ONL*- 1-113 1-114 . -TOR Of 4.4 L.F. +4.0 2/4.O &4/J.5 &^3.5 LB +2400 1065 below 0.0°C 1100 above 0.0°C, 80/87 or 115/145 2 1 MIL-G-5572 42 gal MIL-L-6082 2-1/2 gal engine sump .Wings, inbd WEIGHTS AVIONICS ARMAMENT FUEL AND OIL 1724 (calculated) Grade .. Spec ... No. tanks Location Qty .... Grade . . Spec .... No. tanks. Location . Qty Empty 1729 Basic (calculated).. 2400 Design J/2394 Combat 2/2400 Max takeoff Max landing ^Wing flaps extended. Fuel: -^For basic mission. 2/Limited by strength. —^Wing flaps retracted. Oil: Refer to chapter 2. None. May 1965 May 1965 June 1965 November 1966 FEATURES Dual flight controls. Tandem landing gear kit (prov). Skis and floats (prov). Self-sealing fuel tanks. Single-slotted flaps. DEVELOPMENT 3 ft, 11 in. AND DESCRIPTION MISSION 305B (Modified) Mfr’s Model: Cessna CAPACITIES (rear seat removed) Cargo compartment Baggage compartment observation. of the O-lD are reconnaissance and The principal missions gear for tandem landing gear and skis or flotation Provisions are made Litter patient or The normal crew consists of pilot and observer. wing flaps High-lift, slotted, electrically operated coque construction. of semimono- all-metal, high-wing aircraft The O-ID is a dual-controlled, leaves. Tail- gear consists of two spring steel are provided. The landing to the possible by spring-loaded cables attached wheel steering is made rudder control system. instal- more cargo and is provided with a socket is removable to accept to face fore can be changed to allow the observer lation so the seat back are made by removing the rear or aft. Ambulance or cargo conversions stretcher or cargo as desired. seat back and installing the Gran portable seat fore-and-aft on tracks. The observer’s The pilot’s seat is adjustable observer. passenger may be carried in lieu of the Design initiated First flight (basic prototype) First acceptance Production completed .... Length 1ft, 11 in. Height 2 ft, 5 in. Width 2 ft Length 4 ft, 11 in. Height 2 ft, 5 in. to Width 2 ft, 2 in. speed 2 7 ft, 6 in. D.D. McCauley 90M-O Constant . 1,0470-15 . Continental , 1435 DIMENSIONS POWERPLANT BHP RPM ALT MIN Incidence (root) 1 deg, 30 min Incidence (tip). .. 1 deg, 30 min Span 36 ft. Dihedral 2 deg,' 8 min Sweepback (LE) 2 deg, 25 min clearance 9 in. No. & model ... Mfr Engine spec No . Red. gear ratio .. Blade design No . Prop mfr Prop type Nj). blades Prop dia .. Takeoff 213 2600 SL 5 Normal 190 2300 SL Cont Wing: Length 25 ft,9-1/2 in. Height 9 ft,2 in. Tread 7 ft, 6-1/2 in. Prop gnd (Bird Dog) Characteristics. 1-59. 0-1D ENGINE RATINGS

FM 101-20-1 FM 101-20-1

1-60. Loading and Performance-Typical Mission, Q-1D (Bird Dog). CONDITIONS BASIC MISSION FERRY RANGE TAKEOFF WEIGHT (lb) . 2400 i'' 2200 6/ Fuel at 6.0 Ib/gal (grade 80/87 or 115/145).. (lb) . 237 237 Payload (lb) . None None Wing loading (lb/sq ft) . 13.8 12.6 Stall speed (power off) (kn) . 48 46 Takeoff ground run at SL J/ (ft) . 370 300 Takeoff to clear 50 ft 1/ (ft) . 750 620 Rate of climb at SL 2/ (fpnt) . 1140 1310 Time: SL to 10,000 ft 2/ (min) . 12.2 10.3 Time: SL to 20,000 ft 2/ (min) . 47.5 34.5 Service ceiling (100 fpm) 2/ (ft) . 20.300 22,200 COMBAT RANGE V (nmi) . 461 473 Average cruising speed (kn) . 105 104 Cruising altitude (ft) . 10,000 10,000 Total mission time (hr) . 4.4 4.6 COMBAT RADIUS V (nmi) . 206 Average cruising speed (kn) . 105 Cruising altitude (ft) . 10,000 Total mission time (hr) . 4.0 FIRST LANDING WEIGHT 4/ (lb) . 2294 Ground roll at SL (ft) . 285 Total from 50 ft (ft) . 645 COMBAT WEIGHT Û/ (lb) . 2294 1989 Combat altitude 2/ (ft) . 10,000 10,000 Combat speed 2/ (kn) . 125 127 Combat climb 2/ (fpm) • 695 930 Combat ceiling (500 fpm) 2/ (ft) . 13,800 17.300 Service ceiling (100 fpm) 2/ (ft) . 21.300 24.300 Takeoff ground run at SL J/ (ft) . 330 Takeoff to clear 50 ft 1/ (ft) . 675 Rate of climb at SL 2/ (fpm) • 1225 1505 Max speed at SL 2/ (kn) . 133 134 Basic speed at 5000 ft 2/ (kn) . 130 132 LANDING WEIGHT 4/ (lb) . 2189 1989 Ground roll at SL (ft) . 270 250 Total from 50 ft (ft) . 620 585

J/Takeoff power. 2/Normal power. •2/Detailed descriptions of RADIUS and RANGE missions are given in paragraph 1-61. â/For RADIUS mission if radius is shown. 2/lncludes crew of 2 at 400 lb. 6/Includes crew of 1 at 200 lb. Performance Basis: a. Data source: Contractor flight tests. b. Performance is based on powers shown.

ron oFPtctAL use ONLY 1-115 FM 101-20-1

1-61. Performance Notes, 0-1D (Bird Dog). FORMULA: RANGE MISSIONS I, II, III, & IV

FORMULA: RADIUS MISSIONS I & II Warm up, take off, climb on course to 5000 feet at normal power, and cruise out at long range speeds Warm up, take off, climb on course to 5000 feet until all but reserve fuel is consumed. Range-free at normal power, cruise out at long range speeds to allowances are 5 minutes of normal power for warmup remote base, and land. Without refueling, warm up, and takeoff, plus fuel for 20 minutes at sea level, and take off, climb on course to 5000 feet at normal 5 percent of initial fuel for reserve. power, and return at long range speeds. Range-free allowances are 10 minutes of normal power for warm- PERFORMANCE REFERENCE ups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel Cessna Report No. 305B-6506-014, Substantiating for reserve. Data for Standard Aircraft Characteristics Charts.

1-116 FOR Off ICIAL IISF ONI Y

101-20-1 FM

"XINO 3Sn 1VI3IJJO MOT Prop typeFixedpitch Prop modelNo..1A200FM9047 Prop mfrMcCauley Mfr Continental No. &model....(1)0-470-11 Prop dia7ft,6in. Engine specNo..1276b No. blades2 Red. gearratio..D.D. Takeoff 2132600SL5 Normal 1902300SLCont. Wing: 1-62. 0-1E(BirdDog)Characteristics. Prop gnd Tread Height Length Incidence (tip).. Incidence (root). Dihedral Span Sweepback (LE). clearance ENGINE RATINGS BHP RPMALTMIN POWERPLANT DIMENSIONS -1 deg, 36 ft 9 ft,2in. 2 deg,8min 9 in. 7 ft, 25 ft, 2 deg,35min 1 deg,30min 30 min 6-1/2 in. 9-1/2 in. MISSIONANDDESCRIPTION observation. TheO-IEisadual-controlled,all-metal,high-wing cables attachedtotheruddercontrolsystem. spring steelleaves.Tailwheelsteeringismadepossiblebyspring-loaded operated wingflapsareprovided.Thelandinggearconsistsoftwo aircraft ofsemimonocoqueconstruction.High-lift,slotted,electrically gear. Thepilot’sseatisadjustablefore-and-aftontracks. made byremovingtherearseatbackandinstallingGranportable observer tofaceforeoraft.Ambulancecargoconversionsare a socketinstallationsotheseatbackcanbechangedtoallow observer’s seatisremovabletoacceptmorecargoandprovidedwith passenger maybecarriedinlieuoftheobserver. stretcher orcargoasdesired. Production completed.... Design initiated First flight(basicprototype) First acceptance Width 2ft Height 2ft,5in. Length 1ft,11in. Height 2ft,5in. Length 4ft,11in. Width 2ft, in. •Includes baggagecompartment. Provisions aremadefortandemlandinggearandskisorflotation The principalmissionsoftheO-lEarereconnaissanceand The normalcrewconsistsofpilotandobserver.Litterpatientor * Baggage compartment *Cargo compartment (rear seatremoved) CAPACITIES Mfr’s Model:Cessna305C to 3ft, 11 in. DEVELOPMENT FEATURES Tandem landinggearkit Skis andfloats(prov). Single-slotted flaps. Dual controls. 1December1955 December1956 1January1956 October1957 (prov). FUELANDOIL Max takeoff(alt)....+2400±4.0 Combat *2180 Design 24004.4 Empty (calculated)..1614 Max landing+2400±4.0 Max inflight+24004.4 Basic (calculated)...1618 +Limited bystrength. ±Wing flapsretracted. Fuel: *For basicmission. *Wing flapsextended. OU: None. Refer tochapter2. Grade 80/87 No. tanks..2 Grade 10above0.0°C, Qty 41gal Location ...Wings,inbd Spec MIL-G-5572 No. tanks..1 Qty 2-1/2gal Location ...Enginesump Spec MIL-L-6082 ARMAMENT WEIGHTS AVIONICS 0.0°C 1065 below LB L.F. & *3.5 & *3.5 FOR OFFICIAL USE OHL¥ 45 86 246 5.3 285 525 12.0 454 10.3 101 35.5 101 2089 2/ 1295 None 5000 1868 1245 5000 1535 21,300 16,600 23,400 FERRY RANGE 48 86 100 5.3 246 390 675 13.8 449 14.2 101 945 101 44.0 2/ 2400-2/ 1035 5000 2179 5000 1210 18,600 13,000 20,400 ALTERNATE t RANGE WEIGHT <9 46 86 83 86 123 2.3 2.0 310 560 196 12.4 11.0 101 280 560 101 39.7 290 535 2165-2/ 1225 None 5000 5000 2113 1000 2113 5000 1270 20,600 13,700 21,000 DESIGN MISSION 47 86 86 5.3 246 4.9 350 620 13.2 455 209 12.4 101 290 570 101 945 44.0 2/ 310 565 2291 i/ 1115 5000 None 5000 2180 2180 5000 1210 19,500 13,000 20,400 BASIC MISSION (ft) • (ft) . (ft) ■ (ft) • (ft) .(kn) (fpm) (fpm) . .(kn) (Ib/sq ft) . .... (ft). .. (fpm). .. (min) . .. (min). .... (ft) . .. (nmi) . .... (kn) . .... (ft)...... (hr).. .. (nmi) ...... (kn) ...... (ft)...... (hr) ...... (lb) ...... (ft)...... (ft) ...... (lb) .. (kn). (ft). • Ob) Ob). Ob). CONDITIONS 80/87) Fuel at 6.0 Ib/gal (grade Payload Wing loading Stall speed (power off) at SL ¿/.. Takeoff ground run Rate of climb at SL-2/ ft 1/ Takeoff to clear 50 ft 2/ ... . Time: SLto 10,000 .... Time: SLto 20,000ft2/ fpm) 2/ Service ceiling (100 Average cruising speed Cruising altitude Total mission time Average cruising speed Cruising altitude Total mission time Ground roll at SL Total from 50 ft Combat altitude Combat speed 2/ Combat climb 2/ Service ceiling (100 fpm) 2/ ... Combat ceiling (500 fpm) 2/ .. Takeoff ground run at SL-1/ . .. Rate of climb at SL 2/ Takeoff to clear 50 ft i/ Max speed at SL 2/ Dog) (Bird 0-1E Typical Mission, - and Performance Loading 1-63. WEIGHT TAKEOFF / COMBAT RANGE 2 COMBAT RADIUS ¿/ FIRST LANDING WEIGHT 4/ ... COMBAT WEIGHT 1/

101-20-1 PPtCIAL USE ONLY 101 250 530 1868 FERRY RANGE 101 290 570 2179 4 ALTERNATE WEIGHT RANGE 101 275 555 2061 DESIGN MISSION 101 555 275 2070 BASIC MISSION Time to service ceiling. test of O-lE. a. Data source: Flight b. Performance is based on powers shown. 1 at 200 lb. & Includes crew of Performance Basis: t CONDITIONS ft 2/ (kn) ... Basic speed at 5000 (ft) ... Ground roll at SL (ft) ... Total from 50 ft paragraph 1 -64. missions are given in For RADIUS mission if radius is shown. (CONT). 0-1E (Bird Dog) - Typical Mission, and Performance 1-63. Loading ... 4/ (Jb) LANDING WEIGHT i/Takeoff power. 2/NormaI power. of RADIUS and RANGE 2/Detailed descriptions ^ Includes crew of 2 at 400 lb.

FM 101-20-1 FM 101-20-1

1-64. Performance Notes, 0-1E (Bird Dog). FORMULA: RANGE MISSIONS I, II, III, & IV

FORMULA: RADIUS MISSIONS I & II Warm up, take off, climb on course to 5000 feet at normal power, and cruise out at long range speeds Warm up, take off, climb on course to 5000 feet until all but reserve fuel is consumed. Range-free at normal power, cruise out at long range speeds to allowances are 5 minutes of normal power for warmup remote base, and land. Without refueling,' warm up, and takeoff, plus fuel for 20 minutes at sea level, and take off, climb -on course to 5000 feet at normal 5 percent of initial fuel for reserve. power, and return at long range speeds. Range-free allowances are 10 minutes of normal power for warm- PERFORMANCE REFERENCE ups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel Cessna Report No. 991, Substantiating Data for for reserve. Standard Aircraft Characteristics Charts.

1, FH trat USE ONLY 1121 & 3.5 $ &3.5 LB L.F. 1065 below 0.0°C AVIONICS WEIGHTS ARMAMENT FUEL AND OIL Qty 2-1/2 gal Spec MIL-L-6082 No. tanks... 1 Location . . . Engine sump Location ... Wings, inbd Qty 41 gal Grade 1100 above 0.0°C, Spec MIL-G-5572 No. tanks... 2 Grade 80/87 or 115/145 None. Refer to chapter 2. Oil: Fuel: *For basic mission. ®Wing flaps extended. tWing flaps retracted. +Limited by strength. +2400 4.4 Max inflight +2400 +4.0 Max landing 1614 Empty (calculated). 1618 Basic (calculated) . 2400 4.4 Design +2400 +4.0 Max takeoff (alt) .. *2180 Combat February 1966 February 1966 March 1966 November 1970 FEATURES axle assy. (prov). Dual controls. Self-sealing fuel tanks. Castoring landing gear Single-slotted flaps. Skis and floats (prov). Tandem landing gear kit DEVELOPMENT AND DESCRIPTION MISSION Cessna 305A (Modified) Mfr’s Model: CAPACITIES (rear seat removed) *Cargo compartment Baggage compartment Litter patient The normal crew consists of pilot and observer. for tandem landing gear and skis or flotation Provisions are made ob- of the O-IG are reconnaissance and The principal missions fore-or-aft. Ambulance or cargo conversions the observer to face observer. or passenger may be carried in lieu of the rudder control system. cables attached to the to accept more cargo and is provided observer’s seat is removable allow so the seat back can be changed to with a socket installation Gran the rear seat back and installing the are made, by removing cargo as desired. portable stretcher or electrically construction. High-lift, slotted, aircraft of semimonocoque of two are provided. The landing gear consists operated wing flaps steering is made possible by spring-loaded spring steel leaves. Tailwheel is adjustable fore-and-aft on racks. The gear. The pilot’s seat is a dual-controlled, all-metal, high-wing servation. The O-IG *Includes baggage compartment. Height 2 ft, 5 in. Width 2 ft, 2 in. Length 4 ft, 11 in. Height 2 ft, 5 in. Length 1 ft, 11 in. Width 2 ft First flight (basic prototype) First acceptance ...... Design initiated Production completed . . . . or-HB DIMENSIONS MIN BHP RPM ALT POWERPLANT ENGINE RATINGS

clearance 9 in. Incidence (tip) .. 1 deg, 30 min Dihedral .2 deg, 8 min Sweepback (LE) . 2 deg, 35 min Incidence (root) . 1 deg, 30 min Span 36 ft Length 25 ft, 9-1/2 in Height 9 ft, 2 in. Tread 7 ft, 6-1/2 in. Prop gnd Normal 100 2300 SL Cont. Wing: Takeoff 213 2600 SL 5 No. blades 2 ft. 6 in. Prop dia 7 1276b Engine spec No . D.D. Red. gear ratio .. ixed pitch Prop type F ... (1) 0-470-11A No. & model ontinental Mfr C cCauley Prop mfr M 1A200FM9047 Prop model No . (Bird Dog) Characteristics. 1-65. 0-1G

FM 101-20-1

x prieiAL use mjJY. 45 86 5.3 285 525 246 454 12.0 101 10.3 35.5 2089 1295 None 5000 1868 1245 5000 1535 21,300 16,600 23,400 FERRY RANGE 48 86 246 5.3 100 390 675 449 13.8 101 14.2 945 44.0 2/ 2400 Í/ 1035 5000 2179 5000 1210 18,600 13,000 20,400 ALTERNATE RANGE WEIGHT 46 86 83 86 2.3 123 2.0 310 560 196 12.4 280 101 11.0 560 290 39.7 535 2165 2/ 1225 None 5000 5000 2113 1000 2113 5000 1270 20,600 13,700 21,000 DESIGN MISSION 47 86 86 5.3 246 4.9 350 630 455 13.2 209 290 101 12.4 570 945 310 565 44.0-2/ 2291 5/ 1115 None 5000 5000 2180 2180 1210 5000 19,500 13,000 20,400 BASIC MISSION CONDITIONS 80/87 or 115/145) ... (lb)... Fuel at 6.0 Ib/gal (grade (lb/q ft) ... Wing loading (lb)... Payload (kn) Stall speed (power off) at SL ^ (ft) Takeoff ground run 2/ (fpm) Rate of climb at SL ft i/. (ft) Takeoff to clear 50 S ft 2/ (min) Time: SL to 10,000 ft 2/. (min)... Time: SL to 20,000 (ft) • • • Service ceiling (100 fpm)-2/ (kn) Average cruising speed (ft) Cruising altitude (hr) . Total mission time (kn)... Average cruising speed (ft) Cruising altitude (hr) . Total mission time (ft) . Ground roll at SL (ft)... Combat altitude (ft) Total from 50 ft (k) Combat speed 2/ (fpm) Combat climb 2/ (ft) ... Combat ceiling (500 fpm) 2/ (ft) ... Service ceiling (100 fpm) 2/ (fpm) Rate of climb at SL 2/ (ft) Takeoff ground run at SL 2/ (ft)... Takeoff to clear 50 ft -1^ n (Bird Dog). - Typical, Q-1G and Performance 1-66. Loading (lb) ... TAKEOFF WEIGHT (nmi) ... COMBAT RANGE 2/ (nmi) . !. COMBAT RADIUS V (i) | ^ ^ FIRST LANDING WEIGHT 4/ (lb) !.. COMBAT WEIGHT 4/ b IS} ro

FM 101-20-1 FOR officiAL use ONLY 101 101 530 250 1868 FERRY RANGE 101 101 290 570 2179 t ALTERNATE RANGE WEIGHT 101 101 555 275 2061 DESIGN MISSION 101 101 555 275 2070 BASIC MISSION CONDITIONS ft 2/ (kn) . Basic speed at 5000 Normal power. (kn) . Max speed at SL 2/ (ft) . Ground roll at SL (ft) . Total from 50 ft b. Performance is based on powers shown. a. Data source: Flight test of O-IE. Performance Basis: 1/ (lb). LANDING WEIGHT if radius is shown. 4/ For RADIUS mission JY Includes crew of 1 at 200 lb. 1/ Time to service ceiling. are given in paragraph 1-67. of RADIUS and RANGE missions ^ Detailed descriptions -S' Includes crew of 2 at 400 lb. -1/ Takeoff power. (Bird Dog) (CONT). 0-1G and Performance-Typical, 1-66. Loading

FM 101-20-1 FM 101-20-1

1-67. Performance Notes, 0-1G (Bird Dog). FORMULA: RANGE MISSIONS I, II, & IV FORMULA: RADIUS MISSION I Warm up, take off, climb on course to 5000 feet at normal power, and cruise out at long range speeds Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds to until all but reserve fuel is consumed. Range-free remote base, and land. Without refueling, warm up, allowances are 5 minutes of normal power for warmup take off, climb on course to 5000 feet at normal and takeoff, plus fuel for 20 minutes at sea level, and power, and return at long range speeds. Range-free 5 percent of initial fuel for reserve. allowances are 10 minutes of normal power for warmups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve. FORMULA: RADIUS MISSION III

FORMULA: RADIUS MISSION II Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds to Warm up, take off, climb on course to 5000 feet remote area, and lay wire. Climb on course to 5000 at normal power, cruise out to remote base at long feet at normal power and return at long range speeds. range speeds, and return at long range speeds. Range- Range-free allowances are 5 minutes of normal power free allowances are 5 minutes of normal power for for warmup and takeoff, plus 10 minutes of normal warmup and takeoff, plus fuel for 20 minutes at power for wire laying, fuel for 20 minutes at speeds speeds for long range at sea level, and 5 percent of for long range at sea level, and 5 percent of initial fuel initail fuel for reserve. for reserve.

1-124 FOR OFFICIAL USg-e-WJT FM 101-20-1

AV 000083

Figure 1-35. U-1A (Otter)

FOR OFFICIAL U3C ONLY 1-125 FM 101-20-1

II FT

DIHEDRAL 2 DEG—

-11 FT 2 IN.

-21 FT 2 IN.- (E

-58 FT-

□ □

u o DEG

1/2 IN. 41 FT 10 IN. AV 000084

Figure 1-36. Principal dimensions, U-1A (Otter)

1-126 OFFicret use ONLY POR OI DUAL Uit UNI* LB L.F. WEIGHTS AVIONICS ARMAMENT FUEL AND OIL Location Fuselage Qty 216 gal Spec MIL-L-6082 mission) 7615 Grade 91/96 Spec MIL-F-5572 No. tanks 3 Grade 1100 No. tanks 1 Location Fuselage Qty 10-3/4 gal ♦Limited by strength. Empty 4828 Basic 4900 Fuel: Refer to chapter 2. 3.5 Design 8000 Combat (basic 3.5 Max takeoff .. .*8000 3.5 Max landing .. .*8000 Oil: None. or Fiscal year 1959 plus plus PERSONNEL *Provisions for copilot. **Includes copilot. . Crew (pilots) *1 Litter patients 4 Passengers **10 Ambulatory patients ... 3 Attendant 1 DEVELOPMENT AND DESCRIPTION MISSION DHC-3 Mfr’s Model: DeHaviland CAPACITIES Inside clearance Main cargo door Limit floor loads of the U-l A aircraft is utility transport, The principal mission level) 4 ft, 4 in. compartment. 75 Ib/sq ft with high-wing, single-engine monoplane The U-l A is an all-metal, to with a tailwheel power steering system The aircraft is equipped ground 3 ft, 10-1/2 in. Width 4 ft, 3-1/2 in. Height 3 ft, 9 in. Length (overall). 12 ft, 8 in. Height (max) .. 4 ft, 10-3/4 in. Length 3 ft, 8 in. Width (floor Height 4 ft, 8-1/2 in. Width 3 ft, 8-1/2 in. Height above Baggage Cabin 100 Ib/sq ft carry a and passenger service. It is designed to light cargo hauling, duties, and aerial surveys. communications, liaison snow or ice. Alternate one of whom may act as copilot. pilot and ten passengers, evacuation, supply dropping, reconnaissance, missions include casualty floats for which may be interchanged with twin a fixed landing gear from or combination wheel-skis for operation operation from water permit holding a straight facilitate taxiing in strong winds and to wheel-skis. course in a cross-wind when on combination Army completed Production quantities deUvered to U.S. Baggage compartment: Cabin: 59/61 tubes augmenter DIMENSIONS POWERPLANT BHP RPM ALT MIN ENGINE RATINGS No 7035A9 Incidence (tip) .. 2 deg, 30 min Span 58 ft Incidence (root) . 2 deg, 30 min Dihedral 2 deg Sweepback 0.0 deg (Otter) Characteristics. 1-68. U-1A R-1340- No. & model ... (1) Red. gear ratio .. 0.667 Balde design 1053 Engine spec No .. stg, 1 spd Superch 1 St d Prop mfr Ham ratt & Whitney Mfr P ydromatic Prop type H No. blades 3 0 ft. 9 in. Prop dia 1 Augmentation .. Exhaust thrust Takeoff 600 2250 SL S Normal 550 2200 SL Cont. Length 41 ft, 10 in. Wing: Height 12 ft, 7 in. Tread 11 ft, 2 in.

FM 101-20-1 FM 101-20-1

1-69. Loading and Performance - Typical Mission, U-1A (Otter). BASIC FERRY CONDITIONS MISSION EVACUATION RANGE

TAKEOFF WEIGHT (lb) . 8000-5/ 6662-é/ 6462-5/ Fuel at 6.0 Ib/gal (grade 91/96) (lb) . 1020 1281 1281 Payload (outbound) (lb) . 1800 None None Payload (inbound) (lb) . 1800 1950 Wing loading (Ib/sq ft) . 21.3 18.3 16.9 Stall speed (power off) (kn) . 58 58 44 Takeoff ground run at SL1/ (ft) . 1050 660 420 Takeoff to clear 50 ft 1/ (ft). 1600 1050 830 Rate of climb at SL 2/ (fpm) . 735 940 1070 Time: SL to 10,000 ft 2/ (min) . 17-, 11 10 Time: SL to 20,000 ft 2/ (min) . 43-2/ 36 33 Service ceiling (100 fpm) 2/ (ft) . 18,800 22,400 23,000 COMBAT RANGE/ (nmi) . 680 800 Average cruising speed 1 (kn) . 104 108 Initial cruising altitude (ft) . 5000 5000 Total mission time (hr) . 6.6 7.2 COMBAT RADIUS-2/ (nmi) . 325 350 Average cruising speed (kn) . 104 106 Cruising altitude (ft) . 5000 5000 Total mission time (hr) . 6.6 6.7 FIRST LANDING WEIGHT 4/ (lb) . ’ 7750 5900 Ground roll at SL (ft) . 580 440 Total from 50 ft (ft) . 1160 880 COMBAT WEIGHT 4/ (lb) . 7750 8000 5862 Combat altitude (ft) . 5000 5000 5000 Combat speed 2/ (kn) . 136 136 137 Combat climb 2/ (fpm) • 720 690 1190 Combat ceiling (500 fpm).2/ (ft) . 11,700 11,200 20,300 Service ceiling (100 fpm) 2/ (ft) . 19,800 18,800 27,200 Takeoff ground run at SL 1/- (ft) . 800 950 Takeoff to clear 50 ft 1/ (ft) . 1430 1630 Max rate of climb at SL 2/ (fpm) • 810 735 1400 Max speed at 5000 ft 2/ (kn) . 137 136 138 Basic speed at 5000 ft-2/ (kn) . 137 136 138 LANDING WEIGHT-4/ (lb) . 7750 7446 5149 Ground roll at SL (ft) . 540 560 390 Total from 50 ft (ft) . 1190 1150 780

i/Max power. 2/METO power (max except takeoff). 2/Detailed descriptions of RADIUS and RANGE missions are given in paragraph 1 -70. 4/For RADIUS mission if radius is shown. ■5/Includes crew of 1 at 200 lb. £/Includes crew of 2 at 400 lb. •2/ Time to service ceiling. Performance Basis: a. Data source: Flight test. b. Performance is based on powers shown.

1-128 FOR-erriCIAL USE—ONIX FM 101-20-1

1-70. Performance Notes, U-1A (Otter). and takeoff, plus fuel for 20 minutes at sea level, and 5 percent of initial fuel for reserve. FORMULA: RADIUS MISSION I GENERAL DATA Warm up, take off, climb on course to 5000 feet at METO power, cruise out at long range speeds to Engine ratings shown are engine manufacturer’s remote base, and land. Without refueling, warm up, guaranteed ratings. Power values used in performance take off, climb on course to 5000 feet at METO calculations for the R-1340-59 and -61 engines are as power, and return at long range speeds. Range-free follows: allowances are 10 minutes of METO power for warmups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel CRITICAL for reserve. BHP RPM ALTITUDE

FORMULA: RADIUS MISSION II Max 600 2250 6000 METO . . 550 2200 8000 Same as Radius Mission I except the payload is loaded at remote area.

FORMULA: RANGE MISSIONS I & III USABLE CUBAGE Warm up, take off, climb on course to 5000 feet at METO power, and cruise out at long range speeds Cabin (seats removed) 293 cu ft until all but reserve fuel is consumed. Range-free allowances are 5 minutes of METO power for warmup Baggage compartment 70 cu ft

FOR OFn-et 1-129 FM 101-20-1

Vi r

AV 000086

Figure 1-37. U-6A (Beaver), typical

1-130 11 ni i H rn ifti urr nuiT FM 101-20-1

48 FT

8 FT ó IN. n

DIHEDRAL 2 DEG

15 FT 9-3/4 IN ■Bl

□ m a D

ösO 10 FT 5 IN. 12 FT 8-1/4 IN. Ir □

I FT U

30 FT 6 IN. AV 000087

Figure 1-38. Principal dimensions, U-6A (Beaver)

■EQR CFPN-ML UfC ONLY 1-131

101-20-1 FM

ïl^-1 Z£l~l Prop gnd Tread 10ft,2-1/2in. Height 10ft,5in. Wing: Length 30ft,5in. Takeoff 450‘2300SL5 Normal 4002200SLCont. Prop dia No. blades.... Prop type.. Prop mfr Blade design Superch Engine specNo. Mfr Red. gearratio. No. &model 1-71. U-€A(Beaver)Characteristics. clearance 1ft Sweepback (LE).0.0deg Dihedral 2deg Incidence (tip).0.0deg Incidence (root).0.0deg Span 48ft No ENGINE RATINGS BHP RPMALTMIN POWERPLANT DIMENSIONS Pratt &Whitney (1) R-985-AN- 8 ft,6in. Constant speed 6101A-18 Ham std D.D. 2 2035 1 stg,spd -3 9A 14B, -39,or First acceptance Production completed Provisions fortwobombracks Dual controls. Filtered carburetorair capable ofcarryingone250-poundbomborachemicaltank. operation fromwaterand/orwithskisforsnoworice. light photographicduties. include supplydropping,reconnaissance,instrumenttraining,and cargo hauling,andpassengerservice.Itisdesignedtocarryapilot a fixedlandinggearwhichmaybeinterchangedwithtwinfloatsfor five passengers,oneofwhommayactascopilot.Alternatemissions induction system. (500 lboneachwing). under eachwingcapableof carrying 250lboneachrack The U-6Aisanall-metal,high-wing,single-enginemonoplanewith The principalmissionoftheU-6Aaircraftisutilitytransport,light There areprovisionsfortworacksundereachwing,rack FEATURES Mfr’s Model:DeHavillandDHC-2 MISSION ANDDESCRIPTION DEVELOPMENT Passengers Attendant 1 Ambulatory patients2 Passengers (max)5 Crew 1 Litters 2 Baggage 222lband PERSONNEL and and plus or or October 1951 full fuel ( Oil: None. Max landing**51003.3 Max inflight**51003.3 Max takeoff Combat (basic Design Refer tochapter2. *Some acfthaveexternalfuselage Fuel: Max takeoff **Limited bymaxtakeoff, Basic Empty Qty 6-1/4gal Location Fuselage No. tanks1 Spec MIL-L-6082 Grade 1100 tank inlieuofwingtiptanks. Qty 138gal No. tanks Grade 91/96 (normal) **51003.3 (overload) *51003.3 *(wing tip)....2 Spec :MIL-G-5572 mission) 4559 *Limited byspace. (fuselage) ....3 weight. FUEL ANDOIL ARMAMENT AVIONICS WEIGHTS 3310 3300 5100 3.3 LB L.F. 1-72. Loading and Performance - Typical Mission, U-6A (Beaver).

BASIC EVACUATION WIRE LAY FERRY CONDITIONS MISSION RADIUS RADIUS RANGE TAKEOFF WEIGHT (lb) 5100 44996/ 4246 ^ 4299 i/ Fuel at 6.0 Ib/gal (grade 91/96) (lb) 570 828 570 828 Payload (outbound) (lb) 1080 None None None Payload (inbound) (lb) 1080 900 216 Wing loading (lb/sq ft) 19.3 18.0 17.0 17.2 Stall speed (power off) (kn) 45 44 43 43 Takeoff ground run at SL (ft) 680 740 560 695 Takeoff to clear 50 ft 1/ (ft) 960 920 770 860 Rate of climb at SL 2/ (fpm) 985 1050 1220 1145 Time: SL to 10,000 ft 2/ (min) 11.5 10.5 9.0 9.5 Time: SL to 20,000 ft ^ (min) 31.2 35 27.2 30.3 ^ Service ceiling (100 fpm) 2/ (ft) 19,900 20,450 22,400 21,400 COMBAT RANGE ^ (nmi) 531 824 Average cruising speed (kn) 97 91 Cruising altitude (ft) 5000 5000 Total mission time (hr) 5.5 9.1 COMBAT RADIUS % (nmi) 246 340 260 Average crusiing speed (kn) 97 95 92 Cruising altitude (ft) 5000 5000 5000 Total mission time (hr) 5.1 7.2 5.7 FIRST LANDING WEIGHT 4/ (lb) 4559 4140 Ground roll at SL (ft) 650 525 Total from 50 ft fft) 1240 1070 COMBAT WEIGHT ^ (lb) 4559 5040 3742 3540 Combat altitude (ft) 5000 5000 5000 5000 Combat speed 4/ (kn) 141 132 141 132 Combat climb 4/ (fpm) 1110 865 1510 1590 Combat ceiling (500 fpm) J/ (ft) 15,200 11,450 19,700 20,150 Service ceiling (100 fpm) 2/ (ft) 21,000 17,900 24,600 24,950 Takeoff ground run at SL J/ (ft) 620 875 475 Takeoff to clear 50 ft 4/ (ft) 865 1130 650 Max rate of climb at SL i/ (fpm) 1280 1040 1730 1830

FM 101-20 Max speed at 2800 ft 4/ (kn) 142 132 142 132 Basic speed at 5000 ft J/.., (kn) 141 132 - 141 132 ron ornriAi vnr ONI Y 455 965 3540 FERRY RANGE 495 1020 3517 RADIUS WIRE LAY 610 1190 4644 RADIUS EVACUATION 605 4309 1180 BASIC MISSION i CONDITIONS . (ft).. at SL Ground roll (ft)... Total from 50 ft 200 lb. Includes crew of 1 at a. Data source: Flight test. b. Performance is based on powers shown. U-6A (Beaver) (CONT). - Typical Mission, and Performance 1-72. Loading (lb)... WEIGHT 4/ LANDING Performance Basis: -1/Max power. -2/Normal power. 2 at 400 lb. ■è/ Includes crew of if radius is shown. -4/ For RADIUS mission are given in paragraph 1-73. of RADIUS and RANGE missions -^Detailed descriptions J/ Time to service ceiling.

FM 101-20-1 FM 101-20-1

1-73. Performance Notes, U-6A (Beaver). for warmup and takeoff, plus 10 minutes of normal power for wire laying, fuel for 20 minutes at speeds FORMULA: RADIUS MISSION I for long range at sea level, and 5 percent of initial fuel for reserve. Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds to FORMULA: RANGE MISSIONS I, II, & V remote base, and land. Without refueling, warm up, take off, climb on course to 5000 feet at normal Warm up, take off, climb on course to 5000 feet power, and return at long range speeds. Range-free at normal power, and cruise out at long range speeds allowances are 10 minutes of normal power for warm- until all but reserve fuel is consumed. Range-free ups and takeoffs, plus fuel for 20 minutes at speeds allowances are 5 minutes of normal power for warmup for long range at sea level, and 5 percent of initial fuel and takeoff, plus fuel for 20 minutes at sea level, and for reserve. 5 percent of initial fuel for reserve.

FORMULA: RADIUS MISSION II GENERAL DATA

Same as Radius Mission I except that cargo is Engine ratings shown are engine manufacturer’s unloaded at remote base. guaranteed ratings. Power values used in performance calculations for the R-985-AN-14B, -39, and -39A FORMULA: RADIUS MISSION III engines are as follows:

Same as Radius Mission I except two litter and two ambulatory patients are loaded at the remote base. LEVEL CLIMB FLIGHT FORMULA: CRITICAL CRITICAL Warm up, take off, climb on course to 5000 feet BHP RPM ALTITUDE ALTITUDE at normal power, cruise out at long range speeds to remote area, and lay wire. Climb on course to 5000 Max 450 2300 2600 2800 feet at normal power and return at long range speeds. Range-free allowances are 5 minutes of normal power Normal ... 400 2200 4400 4600

P€>tt-ofnci 1-135 AV 000089

Figure 1-39. U-8D and G (Seminole), typical, (minor differences apparent between D and G models)

1-136 FOR ornchft-b-us* ONLY FM 101-20-1

45 FT 3-1/2 IN

7 FT 9 IN

12 FT 9 IN.

16 FT 4 IN.

31 FT 6-1/2 IN.

I \ I I [

□□□

^ y ^7

10 IN.

CD Cb 11 FT 6-1/2 IN

? 10 FT 9 IN. AV 000090

Figure 1-40. Principal dimensions, U-8D (Seminole)

POR OFFICIAL USE ONL* 1-137 FOR orriciAL u L.F. -1.76 +4.4 LB WEIGHTS AVIONICS ARMAMENT FUEL AND OIL (lOr to 60°F).Type III 60° F) Type II (below 10°F). .3050 5953 mission) (overload) .*7300 (normal) .*7300 Spec MIL-G-5572 Grade .115/145 No. tanks 8 Location Wing Qty 230 gal Grade (above Spec MIL-L-22851 *Limited by strength. „ , MIL-L-15016 Qty 8 gal No. tanks 2 weight. 4978 Basic (calculated)... 7000 Design 4944 Empty (calculated).. Combat (basic Max takeoff **Limited by max takeoff Max takeoff **7000 Max landing . Fuel: Oil: Refer to chapter 2. None. t 4 October 1955 November 1956 October 1958 PERSONNEL Forward 2621b Aft 300 lb Crew 1 Baggage compartment: Passengers 5 DEVELOPMENT Beech E-50 Mfr’s Model: AND DESCRIPTION MISSION FEATURES personnel of the U-8D is the transportation of The principal mission be Cantilever, low-wing monoplane and can The U-8D is a clean three allows the front seat to accommodate The cabin arrangement is accomplished by jettisoning the cabin Emergency evacuation are spar, and rear section of the wings The leading edge, main of windshields. Warm air system is utilized for anti-icing except it has three- The U-8D is similar to the U-8A and B, soundproofing. light. First flight First acceptance Formerly designated L-23D Production completed .... Cabin heating, ventilation, and Full-feathering props. Nonicing carburetors. Steerable nose wheel. Deicing equipment. Throw-over control column. Anticollision rotating beacon Oxygen system. cabin seat a cargo carrier by removing the rear quickly converted into seat. and the right-hand front in the pilot on the left, assist pilot or passenger persons abreast, the ón the right, while the rear seat accommodates center, and a passenger three additional passengers. the rear cabin windows. door and by opening metal propellers plus blade metal propellers in lieu of two-blade have been modified to U-8D aircraft. All U-8A and B aircraft increased horsepower and gross weight. hinge loops and stainless steel rods. joined by piano-type CC, FF POWERPLANT ENGINE RATINGS DIMENSIONS Span 45 ft, 3-1/2 in. Dihedral 7 deg Sweepback .... 0.0 deg Incidence (root). 5 deg, 48 min Incidence (tip).. 1 deg clearance 1 ft, 3 in. (2) 0-480-1 No. & model Lycoming Mfr 2202 Engine spec No ... 0.642 Red. gear ratio .... 10151-B8 Blade design No ... Hartzell Prop mfr (Seminole) Characteristics. 1-74. U-8D/G* Hydramatic, Prop type 3 No. blades 1 stg, centrif Superch 7 ft, 9 in. Prop dia Take BHP RPM ALT MIN Takeoff 340 3400 SL 5 Normal 320 3200 SL Cont. Wing: Height 11 ft, 6-1/2 in. Length 31 ft, 6-1/2 in. Tread 12 ft, 9 in. Prop gnd cabin. *U-8G incorporates a different seating arrangement, Airstairdoor, and extended w 00

FM 101-20-1 pen OPFieiAf-UiE Ot*4Y 1139 6.5 139 200 285 17.2 8.55 5347 1765 2250 23.9 71.5 1185 1095 1900 1780 1380 6618 4/ None 11,600 10,000 31,700 10,000 26,500 10.000 27.000 FERRY RANGE 7.8 199 830 171 172 155 430-5/ 912 682 5.10 5.45 1485 21.6 1550 1240 2010 26.4 75.0 2018 5948 6630 1430 1480 1380 9500 2385 7300 4/ None - 10,900 10,000 10,000 29,700 10,000 24,100 25,500 MISSION NORMAL < 7.8 199 750 140 140 882 155 387 5.67 1350 6.43 21.6 75.0 26.4 1620 2090 1266 5768 2063 1430 1480 6768 1062 1000 9500 2385 7300 4/ None 11,100 10,000 30.500 10,000 25,000 10,000 25.500 DESIGN MISSION 7.8 199 830 140 140 155 528 682 7.62 8.08 1485 21.6 1550 26.4 75.0 2010 1240 5948 1121 2018 6630 1430 1480 1380 9500 2385 7300 4/ None 10,900 10,000 10,000 24,100 29,700 10,000 25,500 BASIC MISSION t CONDITIONS Rate of climb at SL 2^ (fpm) (ft) Service ceiling (100 fpm) 2^ (ft) Service ceiling (one engine out) 2/ (ft) Takeoff ground run at SL -1/ (ft) Takeoff to clear 50 ft 1/ (kn) Combat speed 2/ (fpm) Combat climb 2/ (ft) Combat ceiling (500 fpm) 2/ (ft) Combat altitude (ft) Ground roll at SL (ft) Total from 50 ft (kn) Average cruising speed (ft) Cruising altitude (hr) Total mission time (ft) Service ceiling (one engine out) 2/ (kn) Average cruising speed (ft) Cruising altitude (hr) Total mission time (ft) Service ceiling (100 fpm) 2/ 2/ (fpm) Rate of climb at SL (one engine out) 2/ ... (fpm) Rate of climb at SL (land config) (kn) Stall speed (power off) ft 2/ (min) Time: SL to 10,000 (min) Time: SL to 20,000 ft 2/ 115/145) (lb) Fuel at 6.0 Ib/gal (grade at SL (ft) Takeoff ground run ft -1/ (ft) Takeoff to clear 50 (psf) Wing loading (lb) Payload (outbound) (lb) Payload (inbound) U-8D (Seminole) - Typical Mission, and Performance 1-75. Loading (lb) COMBAT WEIGHT 2/ (lb) FIRST LANDING WEIGHT & (nmi) COMBAT RADIUS 2/ (nmi) COMBAT RANGE (Ib) TAKEOFF WEIGHT

FM 101-20-1 1140 EOE'OmCIAL U3C ONLY 193 200 1000 1630 5347 FERRY RANGE 192 200 1000 1630 5342 MISSION NORMAL 192 200 1015 1640 5445 DESIGN MISSION 192 200 1000 1630 5342 BASIC MISSION r CONDITIONS . (kn) at 9000 ft 2/ Max speed . (kn) at 5000 ft 2/ Basic speed (ft) . Ground roll at SL (ft). Total from 50 ft (CONT). (Seminole) U-8D Mission, and Performance-Typical Loading 1-75. Phase IV flight test. (lb). WEIGHT LANDING Performance Basis: 1 at 200 lb. 4/Includes crew of -1/Max power. -2/METO power. if radius is shown. -2/For RADIUS mission power used for cruise. ^ 65-percent METO

FM 101-20-1 FM 101-20-1

1-76. Performance Notes, U-8D (Seminole). FORMULA: RANGE MISSION III

FORMULA: RADIUS MISSIONS I & II Warm up, take off, climb on course to 10,000 feet at METO power, and cruise out at 65 percent power Warm up, take off, climb on course to 10,000 feet until only reserve fuel remains. Range-free allowances at METO power, cruise out at long range speeds to are 5 minutes of METO power for warmup and remote base, land, and discharge passengers and bag- takeoff, plus fuel for 20 minutes at speeds for long gage. Without refueling, warm up, take off, climb on range at sea level, and 5 percent of initial fuel for course to 10,000 feet at METO power, and return at reserve. long range speeds. Range-free allowances are 10 minutes of METO power for warmups and takeoffs, plus GENERAL DATA fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve. Engine ratings shown are engine manufacturer’s guaranteed ratings. Power values used in performance FORMULA: RADIUS MISSION HI calculations for the 0-480-1 engine are as follows:

Warm up, take off, climb on course to 10,000 feet at METO power, cruise out at 65 percent power to BHP RPM ALT MIN remote base, land, and discharge passengers and baggage. Without refueling, warm up, take off, climb on ¡ Max 340 3400 SL 5 course to 10,000 feet at METO power, and return at 65 percent power. Range-free allowances are 10 min- METO 320 3200 SL Cont. utes of METO power for warmups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve. PERFORMANCE REFERENCE FORMULA: RANGE MISSIONS I, II, & IV Beech Aerodynamic Report 691, Performance Warm up, take off, climb on course to 10,000 feet Data for the USAF Standard Aircraft Characteristics at METO power, and cruise out at long range speeds Charts from Phase IV Flight Test of the L-23D Air- until only reserve fuel remains. Range-free allowances plane. are 5 minutes of METO power for warmup and takeoff, plus fuel for 20 minutes at speeds for long Beech Aerodynamic Report 725, U.S. Army Flight range at sea level, and 5 percent of initial fuel for Manual Substantiating Data from USAF Phase IV reserve. Flight Tests (U-8D).

hOR OmefÄL U3C ONLY 1-141 FM 101-20-1

51 U

AV 000093

Figure 1-41. U-8F (Seminole)

1-142 FOR OFFICIAL U5C OMLÍ FM 101-20-1

45 FT 10-1/2 IN.

7 FT 9 IN

12 FT 9 IN.

I7_FT 2-3/4 IN

33 FT 4 IN

/ V

Ci □□□ 14 FT 2 IN

8 FT 9 IN

Figure 142. Principal dimensions, U-8F (Seminole)

FOR orneiAL use ONLY 1-143 1-144 L.F. -2.64 +6.6 -2.64 +6.6 LB MIL-L-15016 WEIGHTS AVIONICS ARMAMENT FUEL AND OIL 6276 mission) 7700 (overload) * 7700 (normal) . * Spec MIL-G-5572 Location Wing Grade 115/145 No. tanks 8 Qty 230 gal Grade S-1065,W-3050 Spec MIL-L-6082 No. tanks 2 Qty 8 gal *Limited by strength. 5246 Empty (calculated) . 5282 Basic (calculated) . 7700 Design Combat (basic) Max takeoff: **Limited by gear strength. **7350 Max landing Fuel: Oil: Refer to chapter 2. None. August 1958 February 1959 December 1962 PERSONNEL Floor 1501b Shelf 1501b Baggage compartment: Crew 1 Passengers 5 DEVELOPMENT Beech Mfg. Model: FEATURES of personnel. is the transportation mission of the U-8F The principal converted low-wing monoplane easily The U-8F is a semimonocoque, is arranged to the U-8D except the larger fuselage The U-8F is similar cabin heat. each station. manually operated. and is It is equipped with dual flight controls right of a center aisle. seats. by removing the passenger compartment into a cargo carrier compartment and passenger compartments. The crew with separate crew seat on the pilot’s seat on the left and the copilot’s is arranged with the The passenger compartment with sliding doors. separated from the on the left is arranged with two passenger seats passenger compartment aisle. The seats on the right of the center and two or three passenger facilitate removal or installation and permit track-mounted seats passenger compartment with access from the the rear of the passenger located at The baggage compartment is versatile seating arrangements. the left side of the fuselage, compartment. The cabin access door on steps and may be opened or aft of the wing, incorporates stair-type electrically actuated feature fuel injection and manually selected, or outside. A jettisonable closed and locked from either the inside access door. Powerplants escape hatch is located opposite the cabin inlet air source selection. First flight First delivery Fresh air and oxygen outlets at Electrically actuated flaps. Production completed Thermostatically controlled Full feathering props. Conventional flight controls, Steerable nose wheel. Hydraulically controlled brakes. AND DESCRIPTION MISSION Crossfeed fuel system. Windshield wipers. Deicing and anti-ice equipment. y 10-1/2 in. type) (3-piston BMP RPM ALT MIN 340 3400 11,000 5 320 3200 11,000 Cont. ENGINE RATINGS 100 percent percent chord. 0.0 deg chord 0.0 deg Outer panel 25 Center section Span 45 ft, Incidence (root). .4 deg, 48 min. Incidence (tip) .. 0.0 deg Dihedral 7 deg Sweepback: clearance 10-1/2 in. Engine spec No .. 2228A Lycoming Mfr 77:120 Red. gear ratio ...... (2) 0480-3 No. & model stg, centrif Superch 1 artzell Prop mfr H 10151-B8 Blade design No . . No. blades 3 yd, FF, CS Prop type H ft, 9 in. Prop dia 7 Fuel injection Augmentation ... Takeoff 320 3400 SL 5 Normal 320 3200 SL Cont. Wing: (Seminole) Characteristics. 1-77. U-8F Length 33 ft, 4 in. Height 14 ft, 2 in. POWERPLANT Prop gnd Tread 12 ft, 9 in. DIMENSIONS

FM 101-20-1 FÖR UhhlUAL 'OSt UNLÎ 68 6.8 194 127 208 204 600 310 15.7 9.61 24.7 1065 1935 1060 1665 1220 5643 1000 1720 1550 5650 2100 1380 69222/ None 17,500 10,000 13,500 10.000 29,800 34,600 30.000 FERRY RANGE 72 8.1 193 172 207 171 760 184 203 778 883Í/ 415 5/ 19.1 5.23 4.97 27.5 1665 1360 1820 1065 1285 1670 5643 1304 1380 1320 7044 2030 6266 7800 2200 77002/ None 15,450 10,000 10,000 10,000 27.100 32,400 27.100 MISSION NORMAL 72 8.1 193 207 184 130 720 135 203 898 434 19.1 27.5 6.83 6.67 1060 1660 1300 1870 1735 5632 1310 1320 1304 1158 1000 2075 7119 6138 2200 7800 7700 2/ None 15.900 10,000 10,000 10,000 32.900 27,700 27,100 DESIGN MISSION 72 8.1 193 184 134 130 760 207 203 539 778 19.1 27.5 8.35 8.38 1665 1355 1825 1065 1685 1320 1304 1280 5643 1104 1380 7054 2025 6276 2200 7800 7700 2/ None 15,550 10,000 10,000 10.000 27,200 32,500 27.000 BASIC MISSION CONDITIONS 2/ (fpnr). Rate of climb at SL (one engine out) (fpm) • Rate of climb at SL 100/130) (lb). Fuel at 6.0 Ib/gal (grade Basic speed at 5000 ft 2/ (kn) . Total from 50 ft (ft) . (ft) . Service ceiling (100 fpm) 2/ (fpm) • Max rate of climb at SL2/ Max speed at 12,000 ft 2/ (kn). Ground roll at SL (ft) . (ft) . Service ceiling (one engine out) 2/ (ft) . Takeoff ground run at SL 27 (ft) . Takeoff to clear 50 ft 2/ (ft) . Service ceiling (one engine out) 2/ at SLÍ/ (ft). Takeoff ground run ft 1/ (ft) . Takeoff to clear 50 fpm) 2/ (ft) . Service ceiling (100 (lb) . Payload (outbound) (lb/sq ft). Wing loading (kn). Stall speed (power off) (kn) . Combat speed .2/ (fpm) . Combat climb 2/ (ft) . Combat ceiling (500 fpm) 27 (hr) . Total mission time (ft) . Ground roll at SL (ft) . Total from 50 ft (ft) . Combat altitude ;. (kn) . Average cruising speed (hr). Total mission time (kn) . Average cruising speed ft 2/ (min) . Time: SL to 10,000 ft 2/ (min) . Time: SL to 20,000 (lb). Payload (inbound) (ft) . Cruising altitude (ft) . Cruising altitude U-8F (Seminole). - Typical Mission. and Performance 1-78. Loading i/Maximum power — 3400 rpm. 2/Normal power — 3200 rpm. (lb) . FIRST LANDING WEIGHT 2/ (lb). WEIGHT TAKEOFF LANDING WEIGHT (lb) . (lb). COMBAT WEIGHT 2/ (nmi) . COMBAT RANGE (nmi). COMBAT RADIUS 3/

FM 101-20-1 ”4« POR OFFICIAL U3C 0HL4 • • flight test. a. Data source: Contractor’s on powers shown. b. Performance is based Performance Basis: (Seminole) (COISIT). Typical Mission, U-8F Performance - 1-78. Loading 1 at 200 lb. -includes crew of is shown. mission if radius -2/por RADIUS power used for cruise. -^65-percent normal

FM 101-20-1 FM 101-20-1

1-79. Performance Notes, U-8F (Seminole). long range at sea level, and 5 percent of initial fuel for reserve. FORMULA: RADIUS MISSIONS I & II FORMULA: RANGE MISSION III Warm up, take off, climb on course to 10,000 feet at normal power, cruise out at long range speeds to Warm up, take off, climb on course to 10,000 feet remote base, land, and discharge passengers and bag- at normal power, and cruise out at 65-percent power gage. Without refueling, warm up, take off, cUmb on until all but reserve fuel is consumed. Range-free course to 10,000 feet at normal power, and return at allowances are 5 minutes of normal power for warmup long range speeds. Range-free allowances are 10 min- and takeoff, plus fuel for 20 minutes at speeds for utes of normal power for warmups and takeoffs, plus long range at sea level, and 5 percent of initial fuel for fuel for 20 minutes at speeds for long range at sea reserve. level, and 5 pevcent of initial fuel for reserve. PERFORMANCE REFERENCE FORMULA: RADIUS MISSION III Beech Aerodynamic Report 677, Jackson, P.A., Warm up, take off, climb on course to 10,000 feet Type Inspection Report No. 50-20, Model 65 (L-23F), at normal power, cruise out at 65-percent power to Gross Weight 7368 lb. remote base, land, and discharge passengers and baggage. Without refueling, warm up, take off, climb on Beech Aerodynamic Report 678 and Appendixes course to 10,000 feet at normal power, and return at A, B, C, and D, Hughes, A.C., Preliminary Flight-Test 65-percent power. Range-free allowances are 10 min- Evaluation L-23F Prototype. utes of normal power for warmups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea Beech Aerodynamic Report 679, Jackson, P.A., level, and 5 percent of initial fuel for reserve. FUght-Test Performance, Model 65 (L-23F), 7368 lb.

FORMULA: RANGE MISSIONS I, II, & IV Beech Aerodynamic Report 695, Jackson, PA., Type Inspection Report 65-2, Model 65 (L-23F), 7700 Warm up, take off, climb on course to 10,000 feet lb. at normal power, and cruise out at long range speeds until all but reserve fuel is consumed. Range-free Beech Aerodynamic Report 732, Ross, H.C., U.S. allowances are 5 minutes of normal power for warmup Army Flight Manual Substantiating Data from Beech and takeoff, plus fuel for 20 minutes at speeds for Flight Tests (L-23F).

ROB OFFICIAI USE ONU* 1-147 Figure M3. U-lOA (Helio-Courier)

FOR OFFICIAL USE ONLY 30 FT 3-1/2 IN. I FT8-1/2IN. Figure 1-44.Principaldimensions, U-10A(Helio-Courier) hOlt OFICAL USEQMLY. o o 0^ o 39 FT 9 FT 5 FT 23 □ «TO"" 8 FT FT 10IN 14 FT8IN FM 101-20-1 1-149 FOB- ornciAL use LB 2249 3000 3920 WEIGHTS AVIONICS ARMAMENT FUEL AND OIL gal Wing, left (1)30 30 gal Wing, right (1) IL-G-5572 Spec M 00/130 Grade 1 No. tanks: 0 gal Qty 6 Grade 1065,1080 Spec MIL-L-6082 No. tanks 1 Location Engine sump Qty .. 2-1/2 gal Empty . Max takeoff (normal) Max takeoff (overload) Fuel: OU: Refer to chapter 2. None. 2 2 PERSONNEL copilot) Crew (normal) (pilot, Passengers Helio-Courier Mfr’s Model: courier, the U-10A aircraft include assignments of Basic mission air vehicle in the STOL category The U-10A is a versatile four- high-wing, conventional-geared, The U-10A is an all-metal, engine splined to a three- The U-10A is powered by a six-cylinder radio parachute delivery and small groups, observation, cargo carrying, transport. of time, evacuation, and utility relay for extended periods fields to utilize small, rough, and unprepared specifically designed Adaptability of protection for pilot and crew. and offering a maximum and snow. the airplane to operate on water to floats and skis enables edge type slotted flaps, and full-span leading as long-span, high-lift items characteristics feature such place aircraft. The aerodynamic balanced is obtained by short-span, Frise-type, slots. Lateral control spoilers. in conjunction with leading edge ailerons which are operated The for lateral control at higher speed. Ailerons alone are used stabilizer with airplane has an all-movable, slab-type, horizontal and rudder. antibalance tab and a large vertical stabilizer control and spinner to aid bladed propeller with a constant-speed engine cooling. AND DESCRIPTION MISSION G1D6 10151C-5 constant speed BHP RPM 1 ft, 8-1/2 in. 8 ft, 10 in. 0.0 deg 30 ft, 3-1/2 in. 9 ft POWERPLANT DIMENSIONS ENGINE RATINGS 100 percent outer panel 25 chord center section clearance ... percent chord. 0.0 deg Span 39 ft Incidence .... 3 deg Sweepback (LE) Dihedral 1 deg Sweepback (LE) Length Height Tread Prop gnd P-907-10 No (1) GO-480- No. & model No 2227B Engine spec NA Superch 0.641 (77:120) Red. gear ratio .B3Z20-1/ Blade design No ... Hartzell Prop mfr 3 No. blades Hydraulic, Prop type Prop type certificate 8 ft Prop dia Characteristics. Courier) U-10A (Helio 1-80. Takeoff 295 3400 Normal 280 2750 Wing: en o

FM 101-20-1 FM 101-20-1

1-81. Loading and Performance - Typical Mission, U-10A (Helio Courier).

CONDITIONS BASIC MISSION Max speed at SL (kn). 145

Max speed, 5000 ft (kn), 142 Min speed, power off, 40-deg flaps (kn) 42 Performance cruise at 6000 ft, 74-percent power, 2750 rpm (kn) 139 Range at 139 kn (nmi) . 436 (no reserve) Extended range cruise at 10,000 ft, 49-percent power, 2200 rpm (kn) 121 Range at 121 kn (nmi) . 700 (no reserve) Max endurance at 5000 ft, 29-percent power, 75 in TAS (hr) 9.14 (no leserve) Service ceiling (100 fpm R/C) (ft). 22,000 Takeoff data at SL, 0 wing, 25-deg flaps, paved runway: Takeoff weight (lb), 3000 Ground roll (ft) 290 Total distance over 50-ft obstacle (ft). 500 Landing data at SL, 0 wind, 40-deg flaps, paved runway: Ground roll (ft), 180 Total distance over 50-ft obstacle (ft). 495

LOR orneiAi USE umi'y 1-151 FM 101-20-1

AV 000106

Figure M5. U-21A and RU-21A(Ute)

1-152 roR orrmALTCE ONLY FM 101-20-1

45 FT 10-1/2 IN

7 FT 9 IN

to»

12 FT 9 IN.

17 FT 2-23/32 IN-.

r\ f\ « 17

35 FT 6 IN

Cs 14 FT 2-9/16 IN 2 DEG □ DO

1 FT idï——^ I- 12 FT 3-15/32 IN. ^ AV 000107

Figure 1-46. Principal dimensions, U-21A and RU-21A (Ute)

F-OR OFFICIAL USE ONLY 1-153 K>R OrPICIÆT LB tank 10 114 gal 2 2.3 gal each 256 gal MIL-L-7808 MIL-L-23699 NaceUe JP4/5 MIL-T-5624 40° F (25°) 40° F (25°C) (8) wing (2) NaceUe WEIGHTS AVIONICS ARMAMENT FUEL AND OIL Below . Above . Location . Spec .... Location Qty .... No. tanks Qty .... Grade ... No. tanks Location Qty .... Spec 5401 Empty Fuel: Refer to chapter 2. None. 9650 Gross takeoff 9168 Gross landing 3000 Cargo capacity Oil: or plus plus 30 September 1966 AVSCOM 3 2 April 1967 23 May 1967 March 1967 July 1967 23 June 1967 PERSONNEL Litter patients 3 Attendant 1 Pilot 1 Ambulatory patients 3 2/troops 1 10 i/Passengers 6 2/Combat - equipped -1/ Normal seats DEVELOPMENT AND DESCRIPTION MISSION Corporation 65-A90-1 Beech Aircraft Mfr’s Model: FEATURES utility aircraft. The first production The U-21A is an off-the-shelf low wing, all metal construction The U-21 A is an unpressurized, system. feathering, and reversible props. t design with an all-weather capability. The aircraft of versatile USATECOM for confirmation. aircraft was tested by in the the U-21 A is to perform utility services primary mission of and commanders and their staff in command combat zone, support The liaison and aero-medical evacuation. control, adminstration, aircraft is configured for troop transport; basic version of the or air cargo transport. ambulance, staff transport, Date of contract Contracting agency No. of test aircraft First flight (scheduled) air are available for service as however, alternate configurations Completion of test and evaluation Contract delivery schedule Rotating beacon light. Deicing and anti-icing system. Steerable nose wheel. Cabin heating and Ventilating Controllable pitch, full ALT SL (PT6A-20) 10-1/2 in. 45 ft. PT 6A-20 Modified for instaUation of special mission EW equipment. DIMENSIONS POWERPLANT ENGINE RATINGS (root) 4.8° (tip) 0.0° (TE) NVAL Span Incidence Sweepback (LE) . 0.0° Sweepforward Dihedral 7° clearance 1 ft. .... (2) T74-CP-700 No. & model NVAL Mfr Turboprop Type Hartzell Prop mfr 3 No. blades Hyd, CS, FF Prop type 7 ft. 9 in. Prop dia RU-21A Note: Wing Takeoff SHP 550 Length 35 ft. 6 in. Height 14 ft. 2-1/2 in. Tread 12 ft. 9 in. Prop gnd (UTE) Characteristics. U-21A and RU-21A S 1-82.

FM 101-20-1 FM 101-20-1

1-83. Performance - Typical Mission, U-21A (UTE).

Payload (lb) . . 2000 i/

Range (nmi) . . 1249 Cruise speed 2/ (kn) . . 180 Max speed (kn) . . 230 Min takeoff distance (ft) . . 1000 Min landing distance (ft) . . 800

Rate of climb (1 engine) (fpm) . . 350 Service ceiling (2 engines) .... (ft) . . 25,000 Service ceiling (1 engine) .... (ft) . . 10,000

y 3000 lb with fuel trade off.

^ True airspeed at normal rated power.

COP OPFirifll »»cc ^KII v 1-155

446-903 0-71 - 11 FM 101-20-1

¿mm*. um-

jJr

AV 000109

Figure 1-47. OV-1A and C (Mohawk), typical, (minor differences apparent between A and C models)

-«a

1-156 AV 000110

12 FT 9-3/4 IN. Figure 148.Principaldimensions, 0V-1AandC(Mohawk) 0 . EOR-OFICA L USEONLY nVr"! Ü 0 FT II FT8-1/4IN 42 FT [— 9FT 41 FT1-3/8IN. 15 FT10IN.— T 2IN.STATIC / n/r! n l

12 FT 8 IN. FM 101-20-1 1-157 1-158 5.0 L.F. gal or L-23699 592-1/2 gal JP-4 (1) 292-1/2 (2) 150 gal LB AVIONICS WEIGHTS ARMAMENT FUEL AND OIL Fuselage... External... Spec MIL-L-23699 Qty 5 gal Total qty.... Spec MIL-T-5624 No. tanks: Grade mission) .... 11,252 Refer to chapter 2. Refer to chapter 2. OU: Fuel: 9,400 Empty Basic 9,781 Max takeoff ... 15,020 Max landing ... 15,020 715 Design 11, Combat (basic Normal takeoff. 12,012 4 DEVELOPMENT AND DESCRIPTION MISSION tanks are incorporated to carry 150-gallon fuel External provisions day-and-night KA-30 camera installation A remotely operated, seated side-by-side within a bubbled enclosure The crew of two are of operating twin-turboprop aircraft capable The OV-1 A is a two-place and are visual reconnaissance missions of the OV-1A The primary April 1960 First flight (prototype) September 1960 Estimated first service use and emergency resupply containers. flight path. photo coverage along the aircraft provides horizon-to-horizon provided. panoramic camera is also A nose-mounted KA-60,70-mm end of the fuselage. at the extreme forward include a unimproved runways. Design features from small fields and with wide span flaps. construction equipped radilogical monitoring. resupply, liaison, and three-tail configuration of semimonocoque dual-controlled, midwing, is capable of performing reconnaissance. It and photographic observation, emergency artillery gunfire spotting, air control, missions of observation, i RPM Output .670 1700 .679 1700 .692 1700 -C&21C SFC turbine 10 ft 12.46 104.11 Ham std 7103-6 3 Free power (2) T-53-L-7 Lycoming DIMENSIONS POWERPLANT ENGINE RATINGS Area 330 sq ft Span 42 ft MAC 98 in. Length 41 ft, 1-1/2 in. Height 12 ft, 8 in. Tread 9 ft, 2 in. Wing: NRP 900 Rating/SL SHP Max(takeoff) 1100 Mil 1000 Red. gear ratio Blade design No Engine spec No No. blades .... Prop dia Prop mfr Mfr Type No. & model. (Mohawk) Characteristics. 1-84. 0V-1A

FM 101-20-1 irrAL use ONLY- V V y 76 205 430 18.5 5.63 5.93 35.0 43Í5 1450 1935 1195 1005 7 8 14,371 23,800 20,000 150-GAL 244/8000 1901/1950 EXT TANKS FERRY, TWO 190 355-2/ 390 200 251 825-2/ 16.0 1.92 1.96 28.0 41.4 1901 1500 1255-2^ 1141 1300 2/ 2100 5000 2645 5 65/57 6 12,887 13,647 11,936 24,200 Military 245/9000 255/5000 256/8000 2253/5000 RESUPPLY, EMERGENCY CONTAINERS CONTAINERS TWO RESUPPLY TWO RESUPPLY ft) 69 190 264 172 & 320 2/ 200 261 878 â/ 424 12.0 18.4 37.2 2.09 2.13 1901 1080 6/ 1141 2560 5000 3185 3 61/54 12,273 10,562 11,513 Military TWO A6 TWO A6 266/5000 EJECTORS EJECTORS 2752/5000 257/10,000 267/10,000 NIGHT PHOTO (Service ceiling above 25,000 (Combat ceiling above 25,000 ft) 68 190 660 6/ 270 “/ 200 858 2/ 433 264 11.0 36.4 2.14 2.17 1901 10100/ 1141 2675 5000 1 3310 60/53 12,012 11,252 10,301 Military 269/5000 2860/5000 260/10,000 NO STORES NO STORES 270/10,000 OBSERVATION, min, • (ft) • (ft) • (hr) • (hr) (min) (nmi) ..(kn) (Ib/sq ft) ::::83 . .. . (lb) ....(kn) ... . (ft) . .. . (ft) . .. . (ft) .. (kn/ft) 9 COMBAT LOADING CONDITION LOADING CONDITION TAKEOFF Average cruising speed Cruising altitude(s) Fuel 4/ Stall speed (power-off) Payload Wing loading Service ceiling (100 fpm) -i/ ... calm Takeoff run at SL — 25-kn wind Takeoff run at SL — -1/ Rate of climb at SL ft — calm . . Takeoff to clear 50 i/ Max speed/altitude ft i/ Time: SL to 20,000 Time: SL to 25,000 ft !/ Combat range Cruise time (fpm) Rate of climb at SL Engine power (lb) Fuel (fpm/ft) Rate of climb/combat altitude Mission time (lb) Fuel 2/ (kn) Stall speed-power-off 4/approach power (ft) Combat ceiling (1500 fpm) (kn) Max speed at SL - calm . . (ft) Landing distance to clear 50-ft obstacle (kn/ft) Combat speed/combat altitude (kn/ft) Max speed/altitude (Mohawk). OV-1A Typical Mission, - and Performance Loading 1-85. TAKEOFF WEIGHT fuel) (lb) LANDING WEIGHT (10 percent internal fuel) (lb) COMBAT WEIGHT (60 percent internal -i/Normal rated power. -2/Military rated power. to

FM 101-20-1 1-160 rate of climb as per detail spec 532-1.. control and positive (CONT). OV-1A (Mohawk) - Typical Mission, and Performance 1-85. Loading control at max rpm. -4/Flt idle power, propeller second. is based on a rate of sink of 8 ft per ^Landing distance on mission specifications. ^See notes off, propeller control at max rpm. at 120 percent of stall speed-power -i/Power for level flight of sink of 14 ft per second. ^Landing distance is based on a rate singe-engine speeds satisfying minimum speeds for are based upon takeoff and obstacle -^Takeoff distances speeds satisfying single-engine control. are based upon takeoff and obstacle -^Takeoff distances

FM 101-20-1 FM 101-20-1

1-86. Loading and Performance - Typical Mission, FERRY MISSION (Column 7, paragraph 1-86) OV-1A (Mohawk). Warm up, taxi, take off, and cUmb on course to TACTICAL AIR OBSERVATION MISSION AND altitude for maximum range at normal rated power, NIGHT PHOTOGRAPHY (Columns 1, 3, and 5, para- cruise at altitude and velocity for maximum range until graph 1-86). all but reserve fuel is consumed, and drop external fuel tanks when empty. Range-free allowances are 5 min- Warm up, taxi, take off, climb on course to 5000 utes at normal rated power for warmup, taxi, and feet at normal rated power, and cruise at 200 knots at takeoff, plus 10 percent of initial internal fuel for 5000 feet until all but reserve fuel is, consumed. reserve. Range-free allowances are 5 minutes at normal rated power for warmup, taxi, and takeoff, plus 10 percent of initial internal fuel for reserve.

F.e«-OPPICIAL USE ONLY 1-161 FM 101-20-1

USAFíMY ARMY

AV 000112

Figure 1-49. OV-1B (Mohawk)

1-162 FOR OmCHttrUSrOhttas. AV 000113

12 FT 9-3/4 IN. 0 Figure 1-50.Principaldimensions, 0V-1B(Mohawk) n ■ TOROmeiA L OTE-ONY 0 FT 48 FT II FT8-1/4IN.A —=3 43 FT11-3/8IN 15FT10IN.— r" 9FT2IN.STATIC 50QQ (¿2 y ! ir!

12 FT 8 IN. FM 101-20-1 1-163

101-20-1 FM

fmio asn TVI3UJ0 UOJ 2 Tread Height Length Wing: Prop dia.... NRP Mil Max (takeoff) No. ofblades Prop mfr.... Blade designNo Red. gearratio. Type Rating/SL Engine specNo Mfr No. &model. 1-87. 0V-1B(Mohawk)Characteristics. MAC Span Area ENGINE RATINGS POWERPLANT DIMENSIONS 1000 1100 900 SHP 9 ft.2in. 43 ft.11-1/2in. 94.8 in. 48 ft 360 sqft 12 ft.8in. (2) T53-L-7 3 Ham std 7125-6 Lycoming 10 ft Free power 12.4 104.21B &.11C turbine 0.692 1700 0.679 1700 0.670 1700 SFC RPM Output Estimated firstserviceuseJanuary 1963 First flight(prototype)November1961 # path. provides horizon-to-horizonphotocoveragealongtheaircraftflight standard equipment. at theextremeforwardendoffuselage. construction equippedwithwidespanflaps. include amidwing,three-tailconfigurationofsemimonocoque operating fromsmallfieldsandunimprovedrunways.Designfeatures performing missionsofphotographicreconnaissance,visualreconnais- radiological monitoring. sance andobservation,artillerygunfirespotting,aircontrol, tanks ortworesupplycontainers. the sidelookingairborneradar(SEAR).Inaddition,itiscapableof External provisionsareincorporatedtocarrytwo150-gallonfuel The OV-1BcarriesanAPS-94sidelookingairborneradarantennaas A remotelyoperatedday-and-nightKA-30camerainstallation The crewoftwoareseatedside-by-sidewithinabubbledenclosure The OV-1Bisatwo-place,twin-turbopropaircraftcapableof The primarymissionoftheOV-1Biselectronicsurveillanceusing MISSION ANDDESCRIPTION Mfr’s Model:Grumman DEVELOPMENT 4 AVIONICS Refer tochapter2. Refer tochapter2. Oil: No. tanks: Fuel: Max landing...16,643 Max takeoff...16,643 Normal takeoff.13,654 Combat (basic Design 13,1004.0 Basic 1.217 Empty E10,983 Total Qty...597gal Spec MIL-L-23699 Qty 5gal External (2)150gal Fuselage ....(1)297gal Spec MIL-T-5624 Grade JP-4 mission) 12,882 FUEL ANDOIL ARMAMENT WEIGHTS LB L.F. POR ornciAt USE ONLY 15 79 203 5.30 4.98 26.5 44.6 1053 1410 7 2185 2160 20,000 15,918 24,900 150-GAL 226/8000 1930/1950 EXT TANKS FERRY, TWO 13 23 77 193 334 200 1.64 1.69 1330 1158 42.1 2530 1270 5000 1930 1500 2000 2320 235.9 5 6 13,431 14,396 23,800 15,168 26,500 71.5/58 Military 238/5000 2175/5000 RESUPPLY, EMERGENCY CONTAINERS CONTAINERS 239.5/10,000 226.8/10,000 TWO RESUPPLY TWO RESUPPLY 10 16 193 890 358 200 264 1.77 1.80 38.7 73.8 1158 2940 1690 1930 1040 5000 2700 244.9 3 12,178 4 13,143 26,900 13,915 28,750 Military 68.2/55.2 248/5000 TWO A6 TWO A6 2560/5000 EJECTORS EJECTORS 238/12,000 249.5/11,500 NIGHT PHOTO, 38 73 193 9.5 870 365 200 995 1.84 1.80 15.5 1158 3050 1625 1930 5000 2800 247.2 11,917 12,882 27,700 13,654 29,500 2 1 Military 67.5/54.6 250/5000 2660/5000 252/11,500 NO STORES 240.5/12,500 NO STORES OBSERVATION, COMBAT LOADING CONDITION CONDITION TAKEOFF LOADING (kn) Average cruising speed (ft) Cruising altitude (s) Stall speed-power-off/approach power ^ .. (kn) (lb) Fuel Landing distance clear 50-ft obstacle ... (ft) (fpm) Rate of climb at SL 2s. (kn/ft) Max speed/altitude 2/ (lb) Fuel (fpm/ft) Rate of climb/combat altitude 2S ... . (ft) Combat ceiling (500 fpm) 2/. (kn) Max speed at SL 2/ Engine power (kn/ft) Combat speed/combat altitude 2/.. .. (ft) Service ceiling (100 fpm) 2/ (hr) Cruise time (hr) Mission time 2/ (fpm) Rate of climb at SL (lb) Fuel internal/external (min) Time: SL to 25,000 ft 2/ (nmi) Combat range 2/ 4/ (kn) Stall speed (power-off) 1/ (kn/ft) Max speed/altitude (min) Time: SL to 20,000 ft 2/ (lb) Payload (lb/sq ft) Wing loading calm (ft) Takeoff run at SL — ft - calm (ft) Takeoff to clear 50 fuel) (lb) LANDING WEIGHT (10 percent internal fuel) . (lb) COMBAT WEIGHT (60 percent internal (lb) TAKEOFF WEIGHT OV-1B (Mohawk). - Typical Mission, and Performance 1-88. Loading

FM 101-20-1 UAL 'USfc ÖRTY- propeller control at max rpm. ^Flight idle power, .2/Military rated power. off, propeller control at max rpm. at 120 percent of stall speed, power -£/Power for level flight rated power. J/ Normal specifications. -2/ See notes on mission (CONT). Mission, OV-1B (Mohawk) - Typical Loading and Performance g 1-88.

FM 101-20-1 FM 101-20-1

1-89. Performance Notes, OV-1B (Mohawk). FERRY MISSION (Column 7, paragraph 1-89).

TACTICAL AIR OBSERVATION MISSION AND Warm up, taxi, take off, climb on course to NIGHT PHOTOGRAPHY (Columns 1, 3, and 5, para- altitude for maximum range at normal rated power, graph 1-89). cruise at altitude and velocity for maximum range until all but reserve fuel is consumed, and drop external fuel Warm up, taxi, take off, climb on course to 5000 tanks when empty. Range-free allowances are 5 min- feet at normal rated power, and cruise at 200 knots at utes at normal rated power for warmup, taxi, and take 5000 feet until all but reserve fuel is consumed. off, plus 10 percent of initial fuel for reserve. Range-free allowances are 5 minutes at norma] rated power for warmup, taxi, and take off, plus 10 percent of initial internal fuel for reserve.

FOR orrrciAL U3E ONLY- 1-167 1168 FOR 'OFFICIAL USE ONUY LB L.F. WEIGHTS AVIONICS DIMENSIONS FUEL AND OIL Fuselage (1) 297 gal External .... (2) 150 gal mission) 12,296 Spec MIL-L-23699 Spec MIL-T-5624 No. tanks: Qty 5 gal Grade JP-4 Total qty 597 gal Span 42 ft/48 ft Area 330 sq ft MAC 98 in. 10,011 Empty ,379 Basic 10 4.9/4.0 Design 11,924 Combat (basic Fuel: Refer to chapter 2. Normal takeoff . 12,682 Max takeoff ...15,302 Max landing ...15,302 Oil: Length 41 ft, 1-1/2 in. Wing: Height 12 ft, 8 in. Tread 9 ft, 2 in. DEVELOPMENT Grumman Mfr’s Model: AND DESCRIPTION MISSION of twin-turboprop aircraft capable The OV-1C is a two-place, seated side-by side within a bubbled The crew of two are day-and night KA-30 or KA-76 camera A remotely operated carry two 150-gallon External provisions are incorporated to detection equipment. The OV-1C carries AN/UAS4 infrared Infrared (IR) is to perform mission of the OV-1C The primary * three-taü configuration of semi- include a midwing, March 1961 First flight (prototype) July 1961 First service use gunfire spotting, air control, and and observation, artillery radiological monitoring. features fields and unimproved runways. Design operating from small equipped with wide span flaps. monocoque construction forward end of the fuselage. enclosure at the extreme 70-mm panoramic aircraft flight path. A nose-mounted KA-60, camera is also provided. portion of the electro- distinguishable in the visual and infrared it is using the Infrared sensor. In addition reconnaissance missions photographic missions, visual reconnaissance capable of performing the horizon-to-horizon photo coverage along installation provides it possible to detect The infrared surveillance system makes magnetic spectrum. fuel tanks or two resupply containers. that are military terrestrial targets by inherent characteristics * t ‘T RPM 1700 1700 1700 1700 1600 RPM Output Output turbine and .35 SHP SEC 1160* 0.620 1000* 0.650 ARMAMENT POWERPLANT ENGINE RATINGS (Mohawk) Characteristics. 1-90. OV-1C Lycoming Mfr Power free Type 104.11C, .21-B Engine spec No ... 12.46 Red. gear ratio .... (2) T53-L-7/15 No. & model ♦Mechanical limited. 3 No. blades Blade design No ...7125-6 Ham std Prop mfr 10 ft Prop dia NRP Refer to chapter 2. Rating/SL SHP SEC Rating/SL MU Max (takeoff) 1100 0.670 Mil 1000 0.679 NRP 900 0.692 T52-L-15 T53-L-7

FM 101-20-1 FfieiAl use ONLY 80 215 930 5.17 4.72 45.3 1081 1630 1440 2230 3880 27/22 64/47 20,000 14,961 230/SL 7 150-GAL EXT TANKS 20,200/21,300 FERRY, TWO 78 193 239 200 362 802 1.78 1.83 1335 8/ 1158 43.0 2320 1800 5000 1270 1930 1500 2000 72/58 22/17 47/35 12,460 13,425 20,400 14,197 Military 5 6 240/5000, 240/5000 229/5000 1620/5000 RESUPPLY 21,600/23,200 CONTAINERS EMERGENCY CONTAINERS TWO RESUPPLY TWO RESUPPLY 74 193 8702/ 252 200 397 640 264 1.96 2.00 39.2 1158 2780 1680 1040 5000 1930 2175 69/55 15/13 27/22 11,206 12,171 24,300 12,943 Military 4 3 252/5000 2000/5000 253/10,000 243/10,000 TWO A6 TWO A6 EJECTORS EJECTORS 25,700/26,500 NIGHT PHOTO, 74 193 850^ 255 200 408 613 990 2.01 2.05 38.4 1158 2880 1640 5000 1930 2270 68/54 14/12 24/20 10,945 11,910 25,200 12,682 1 Military 256/5000 ' 2 2100/5000 256/10,000 246/10,000 NO STORES NO STORES 26,200/27,450 OBSERVATION COMBAT LOADING CONDITION CONDITION TAKEOFF LOADING (kn) . Average cruising speed (ft) . Cruising altitude(s) Fuel (lb) .. . Stall speed-power off 4/ /approach power. (kn)... Landing distance to clear 50-ft obstacle (ft) . . . (fpm) . ■. Rate of climb at SL 2/ (kn/ft) .. . Max speed/altitude 2/ (fpm/ft)... Rate of climb/combat altitude 2/ (kn)... Max speed at SL 2/ (lb) .. . Fuel (ft) ... Combat ceiling (500 fpm) 2/. Engine power (kn/ft)... Combat speed/combat altitude 2/ (hr). Cruise time (hr) . Mission time (ft). Service ceiling (100 fpm) (nmi) . Combat ranged (fpm) . Rate of climb at SL ^..._ (min). Time: SL to 20,000 ft Í/’2/ (min). Time: SL to 25,000 ft ¿<2/ 4/ (kn). Stall speed (power-off) -1/ (kn/ft). Max speed/altitude (lb). Fuel (lb/sq ft) . Wing loading calm-^ (ft) . Takeoff run at SL — 25-kn wind & (ft). Takeoff run at SL - ft - calm-^ (ft). Takeoff to clear 50 (lb). Payload LANDING WEIGHT (10 percent internal fuel) .. (lb) ... fuel).. (lb) COMBAT WEIGHT (60 percent internal (lb).. TAKEOFF WEIGHT OV-1C (Mohawk). - Typical Mission. and Performance 1-91. Loading

FM 101-20-1 FQR OmCIAt-ö-St with rate of sink equal to 8 fps. sink equal to 14 fps. speed in takeoff configuration. -^lilitary rated power. specifications. ■2/See notes on mission propeller control at max rpm. 4/Flight idle power, rated power. -formal speed equal to 110 percent of landing stall speed with rate of ^Landing distance is based on approach off, propeller control at max rpm. at 120 percent of stall speed, power i/Power for level flight stall equal to 120 percent of power-off are based on takeoff and obstacle speed ^Takeoff distances speed equal to 110 percent of landing stall speed, power off, ■^Landing distance is based on approach (CONT). OV-1C (Mohawk) - Typical Mission, and Performance 1-91. Loading

FM 101-20-1 FM 101-20-1

1-92. Performance Notes, OV-1C (Mohawk). FERRY MISSION (Column 7, paragraph 1-92).

TACTICAL AIR OBSERVATION MISSION AND Warm up, taxi, take off, climb on course to NIGHT PHOTOGRAPHY (Columns 1, 3, and 5, para- altitude for maximum range at normal rated power, graph 1-92. cruise at altitude and velocity for maximum range, and drop external fuel tanks when empty. Range-free Warm up, taxi, take off, climb on course to 5000 allowances are 5 minutes for warmup, taxi, and take- feet at normal rated power, and cruise at 200 knots at off, plus 10 percent of initial internal fuel for reserve. 5000 feet until all but reserve fuel is consumed. Range-free allowances are 5 minutes for warmup taxi and takeoff, plus 10 percent of initial internal fuel for reserve.

1-171

446-903 0-71-12 1-172 L.F 4.0/2.0 150 gal 297 gal ¿97 gal 12 ft 8 in 360 sq ft 48 ft 98 in 41 ft 3.65 in 9 ft 2 in LB JP-4/5 MIL-F-5624 5 gallon WEIGHTS 0) (2) MIL-L-23699 AVIONICS FUEL & OIL 11,896 12,104 15.421 15,497 15,647 15.421 18,337 14,315 DIMENSIONS Refer to Chapter 2 # Empty Spec Fuselage Basic Grade Design Externa] Combat Total Qty Spec Qty (IR) (SLAR) Normal Take-Off Max Area Take- Off Span Max MAC Landing Fuel No. Tanks Oil: Wing: Length Height Tread DEVELOPMENT AND DESCRIPTION MISSION of the OV-1D is to perform either The primary mission missions. The SLAR and airborne radar (SLAR) In addition it is capable IR are interchangeable. or side looking infrared (IR) reconnaissance missions, visual of performing photographic observation, artillery gun fire reconnaissance and and radiological monitoring. spotting, air control, place, twin turboprop aircraft The OV-1D is a two from small fields and unim- capable of operating a midwing, proved runways. Design features include con- three-tail configuration of semimonocoque struction equipped with wide span flaps. within a The crew of two are seated side-by-side fuselage. LS 59A 150 gallon fuel tanks, two ECM pods or end of the bubbled enclosure at the extreme forward The OV-1D is equipped with three independent automatic photographic systems, all of which have by either exposure controls and can be operated the pilot or observer. carry two External provisions are incorporated to photo flasher. Sept 68 First flight (prototype) First service use j]y 70 u « 12.38 Lycoming 104.39 Free Power Turbine Ham Std 10 ft. 5157C-6 3 (2) T53-L-701 POWERPLANT 1400 .590 1650 1250 .610 1590 ENGINE RATINGS MIL NRP No. & Model Mfr. Type Engine Spec Nr Red. Gear Ratio Prop Mfg Blade Design Nr No. of Blades Prop Dia. Rating/SL SHP SFC RPM T53L-701 Output (Mohawk) Characteristics. 1-93. 0V-1D

FM 101-20-1 iiSiRí1'

AV 000118

Figure 1-51. T41B (Mescalero)

FOR OFFICIAL USrONL¥ 1-173 FM 101-20-1

8 FT n IN ]r^>u

DEG 25 FT 6 IN

11 FT 4 IN.

8 FT 4 IN

36 FT 2 IN

I l^l

6 FT 4 IN.

AV 000119 7 FT 2 IN.

Figure 1-52. Principal dimensions, T-41B (Mescalero)

1-174 ftOR ornciAL use ONL*

101-20-1 FM

MU rruici ain WUIJJ Prop dia6ft,4in. Prop typeCS,VP Mfr Continental No. &model(1)IO-360D 1-94. T-41B(Mescalero)Characteristics. Wingspan 36ft,2in. Height 8ft,11in. Tread 7ft,2in. ENGINE RATING To bepublished. POWERPLANT DIMENSIONS will beusedintwoconfigurationsasfollows: pending availabilityofthe0H-6A.Missionsincludeprimaryand advanced contacttrainerandinstallationsupportroles.TheT-41B weight, includingelectronics,crewoftwo(instructorandstudent),at weight, includingelectronics,crewofone,twopassengers,at200 200 poundseach,andfuelforendurance4.5hoursat110knots. pounds each,andfuelforendurance4.5hoursat110knots. High wing. All metal. Dual side-by-sidecontrols. Fixed tricyclelandinggear. The T-41Bisaninteriminventoryfilltoreplace0-1drawdown Normal mission-FAAnormalcategorytoincludeaircraftempty Utility mission-FAAnormalcategorytoincludeaircraftempty Date ofcontract8August1966 First ProductionacftOctober1966 FEATURES MISSION ANDDESCRIPTION Mfr’s Model:Cessna172 DEVELOPMENT Crew Passengers Crew Instructor pilot Student pilot.. PERSONNEL or 2 2 1 1 1 m Utility 2200 Normal 2500 Empty 1545 Fuel: Refer tochapter2. None Qty FUEL ANDOIL ARMAMENT WEIGHTS AVIONICS 42 gal LB FM 101-20-1

1-95. Performance - Typical Mission, T-41B (Mescalero). Range (4.5 hours) (mi)... 595

Cruise speed J/ (mph)... 130 Max speed (mph)... 138 Takeoff distance (ft)... 865 Landing distance (ft)... 520 Rate of climb (fpm)... 645

Service ceiling (ft)... 13,100

1/75-percent power at 7000 feet.

1-176 utr ruin Y FM 101-20-1

AV 000121

Figure 1-53. T-42A (Cochise)

..con orneiAi USE oMwr 1.177 FM 101-20-

AV 000122

1-178

101-20-1 FM

MU AINU SSCI 1 1-96. T-42A(Cochise)Characteristics. No. &model....(2)IO-470-L Mfr Continental Prop mfrMcCauley Prop typeHyd,CS,FF Engine specNo..1634-B Prop dia6ft,in. Blade designNo..78FF-0 No. blades2 Takeoff 2602625SLCont. Normal 2602625SLCont. Wing: Height 9ft,7in. Length 27ft,3in. Tread 9ft,7in. Prop and Incidence (root). Span •37ft,10in. Dihedral 6deg Sweepback ....0.0deg clearance 10-1/2in. (tip) ENGINE RATINGS BHP RPMALTMIN POWERPLANT DIMENSIONS 4 deg -i deg instrument flying,inbothdayandnightInstrumentFlightRuleopera- tions. .^... training ofsingleengineratedpilots.„,. une noplane, withretractablelandinggear.,„ two additionalstudentssitimmediatelybehind.Theinstructorand student pilots.Theinstructorandprimarysitsidebyside;the primary studenteachhaveacompletesetofflightcontrolsandin- students fromtheforwardprimaryseattorearseats. struments. Theseatingarrangementpermitsinflightmovementsof windows onbothsidesofthewindshield. fogging ofwindshield. Date ofcontract Production completed^ First flightJidy1965 First acceptance^ Cabin airconditioning,heating, Cabin soundproofing. Oxygen system. Dual controlsandinstruments. Steerable nosewheel. Propeller anti-icingandwing Fuel injection. Three-axis trim. Rotating beacon. and ventilation. The primarymissionoftheT-42Aistrainingmilitarypilotsin and stabilizerdeicing. The secondarymissionoftheT-42Aistwin-enginetransition The T-42Aisanallmetaltwin-engine,fourplacelowwingmo- The cabinisdesignedtoaccommodateaninstructorpilotandthree Emergency evacuationisaccomplishedbyquickreleasejettisono The warmairsystemisutilizedforanti-icing,defrostingandde- » FEATURES MISSION ANDDESCRIPTION Mfr’s Model:Beech95-B55B DEVELOPMENT Crew Crew Passengers Instructor pilot Student pilot.. or PERSONNEL 1 Basic .. Empty Max takeoff Max Design Fuel: Oil: None Qty 6gal Refer tochapter2. Grade 115/145 No. tanks4 Spec MIL-G-5572 Location Wing Qty 142gal Grade &Spec..TypeIIHI, Location Engines ARMAMENT FUEL ANDOIL AVIONICS WEIGHTS 3423 3480 MIL-L-22851 5610 do 5100 Grade 3050, 5100 do MIL-L-15016 LB or L.F. +4.4, -3.0 FM 101-20-1

1-97. Loading and Performance - Typical Mission, T-42A (Cochise).

TAKEOFF LOADING CONDITIONS BASIC MISSION

Takeoff Weight (LB) 5,100 Fuel (LB) 852 Payload (LB) Wing Loading (Lbs/Sq Ft) . . . 25.5 Stall Speed 1/. (Kn) 66 Stall Speed U. (Kn) 73.5 Takeoff Run at SL (Ft) 910 Takeoff Run to Clear 50 ft (Ft) 1,255 Max Speed SL (Kn) 205 Rate Climb SL (FPM) 1,670 Time SL to 10,000 ft . . . (Min) 8 Service Ceiling (100 FPM) (Ft) 1,970

LANDING WEIGHT

(10% Fuel) 4,333

Fuei (Lb) 85 Ground Roll At SL (Ft) 997 Landing Distance to Clear 50 Ft. Obstacle (Ft) 1,534

i/ Zero Thrust, Flaps 28°, and Gear Down 2/ Power OFF, Flaps Up, and Gear Up

1-180 FOR OmeiAL-Q-SE OIILY FM 101-20-1

CHAPTER 2

LOGISTICS AND MATERIEL

Section I. MAXIMUM ALLOWABLE OPERATING TIME (MAOT) (MAJOR COMPONENTS)

2-1. Major Components.

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

AH-1G Engine (T53-L-13) 6001/ Indefinite

Engine (T53-L-13A) 1200 Indefinite

Engine (T53-L-13B) 1200 Indefinite

Main Rotor Blade Assembly 1100 1100

Main Rotor Hub Assembly 1100 Indefinite

Yoke 3300 3300

Extension Assembly 3300 3300

Retention Straps 2200 2200

Pin 2200 2200

Fitting 2200 2200

Nut 2200 2200

Transmission Assembly 1100 Indefinite

Main Input Quill Assembly 1100 Indefinite

Mast Assembly 1100 Indefinite

Mast Bearing 1100 1100

Blade Assembly, Tail Rotor 1100 1100

Tail Rotor Hub Assembly 1100 1100

Grip 1100 1100

Yoke 1100 1100

TOB OPEICIAL UEII ONLY- 2-1 FM 101-20-1

2-1. Major Components (CONT).

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

AH-lG(Cont) . .. Forty-two degree gearbox 1500 Indefinite

Ninety degree gearbox 1100 Indefinite

Swashplate and Support 1100 Indefinite

Assembly

Outer Ring 3300 3300

Inner Ring 3300 3300

Scissors and Sleeve Assembly 1100 1100

Scissors Assembly 3300 3300

Drive Link:

P/N 209-010408-1 400 400

P/N 209-010408-5 25 25

Engine Mount Trunnion: 300 300

P/N 206-060-113-1

Servo Cylinder Assembly 3300 Indefinite

Cylinder 3300 3300

Bearing Housing 3300 3300

CH-34C Engine (R-1820-84C) 1000 Indefinite

Main rotor head 1100 Indefinite

Main transmission 1100 Indefinite

Intermediate gearbox 1300 Indefinite

Tail rotor gearbox 1300 Indefinite

Hydro-mechanical clutch 800 Indefinite

Main rotor blade 2500 2500

2-2 EQR OrnCTTU UHL UHL I FM 101-20-1

2-1. Major Components (CONT).

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

CH-47A Engine (T55-L-7) 1800 Indefinite

Forward rotor head 2400 Indefinite

Aft rotor head 2400 Indefinite

Forward transmission 1200 J/ Indefinite

Aft transmission 1200 \J Indefinite Combining transmission 1200 y Indefinite

Engine transmission 1200 2/ Indefinite

Rotor blades, forward 3600 3600

Rotor blades, aft 2400 2400

CH-47B Engine (T55-L-7C) 1800 Indefinite

Forward rotor head 1200 Indefinite

Aft rotor head 1200 Indefinite

Forward transmission 1200 J/ Indefinite

Aft transmission 1200 i/ Indefinite

Combining transmission 1200 y Indefinite

Engine transmission 12001/ Indefinite

Rotor blades, forward 6000 2/ 6000 2/

Rotor blades, aft 4000 y 4000 2/

CH-47C Engine (T55-L-11) 300 Indefinite

Forward rotor head 1200 Indefinite

Aft rotor head 1200 Indefinite

Forward transmission 1200 y Indefinite

Aft transmission 1200 y Indefinite

Combining transmission 1200 y Indefinite

.ron ornciAt use PMLM. 2-3 FM 101-20-1

2-1. Major Components (CONT).

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

CH-47C (Cont) Engine transmission 900 J/ Indefinite Rotor blades, forward 6000 U 6000 2/ Rotor blades, aft 4000 2/ 4000 2/

CH-54A Engine (T73-P-1) 1000 Indefinite

Main rotor head 500 Indefinite

Tail rotor head 800 Indefinite

Main gearbox 1000 Indefinite

Intermediate gearbox On cond Indefinite

Main rotor servo and control 1000 Indefinite arm assembly

AFCS servo 1000 Indefinite

APP clutch On cond Indefinite

Main blades 5000 5000

Tail rotor gearbox and servo assembly 1200 Indefinite

Fuel control (T73-P-1) 1000 Indefinite

Auxiliary power unit On cond Indefinite

CH-54B Engine (T73-P-700) 800 Indefinite

Main rotor head 800 Indefinite

Main rotor servo 1200 Indefinite

AFCS servo 1200 Indefinite

Tail rotor assembly 800 Indefinite

Tail rotor gearbox and servo assembly 1200 Indefinite

Intermediate gearbox 1200 Indefinite

Main gearbox 1000 Indefinite

Main rotor dampers 7200 7200

2-4 FOR emciAL ucc ONLY FM 101-20-1

2-1. Major Components (CONT).

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

CH-54B (Cont) . Main rotor blade 2500 2500

Tail rotor blade 1600 1600

Main cargo hoist 240 Indefinite

OH-6A Engine (T63-A-5A) 750 Indefinite

Fuel control 750 Indefinite

N2 governor 750 Indefinite

Main transmission 750 Indefinite

Main rotor swashplate bearing 1200 Indefinite

Main rotor hub 1200 5714

Tail rotor transmission 750 Indefinite

Tail rotor assembly 600 Indefinite

Overrunning clutch 1200 Indefinite

Main rotor blades NA 1655

Main rotor drive shaft NA 1990

OH-13H Engine (0435-23C) 1500 Indefinite

OH-I3S/T Engine (0-435-25A) 1200 Indefinite

OH-13 (aU) ... Main transmission On cond Indefinite

Tail rotor gearbox On cond Indefinite

OH-23D Engine (0-435-23C) 1500 Indefinite

Main transmission 1500 Indefinite

Cooling fan gearbox:

P/N 74180 1000 Indefinite

P/N 74155 550 Indefinite

Tail rotor gearbox 2000 Indefinite

2-5 FM 101-20-1

2-1. Major Components (CONT).

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

OH-23D (Cont). . Main rotor head 2500 2500

Main rotor blades 1500 5000

Tail rotor blades 5400 5400

OH-23 F/G Engine (0-540-9A) 900 Indefinite

Main transmission 1500 Indefinite

Cooling fan gearbox 1000 Indefinite

Tail rotor gearbox 2000 Indefinite

Main rotor head 2500 2500

Main rotor blades assembly 1500 5000

Tail rotor blades assembly 5400 5400

OH-58 A Engine (T63-A-700) 750 Indefinite

Main transmission 1200 Indefinite

Swashplate and support assembly 1200 Indefinite

Main rotor swashplate bearing NA 1200

Main rotor hub 1200 Indefinite

Grip NA 4800

Strap assembly NA 1200

Pin, strap retaining NA 1200

Fitting assembly NA 1200

Main rotor blades NA 1200

Mast assembly 1200 Indefinite

Mast NA 1200

Tail rotor transmission 1200 Indefinite

2-6 ¿JQR OFFICIAL-USE ONLY FM 101-20-1

2-1. Major Components (CONT).

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

OH-58A (Cont). Tail rotor hub 1200 Indefinite

, Blade assembly NA 1200'

Trunnion assembly NA 2400

Freewheeling assembly 1200 Indefinite

Drive shaft assembly, main 1200 Indefinite

Pylon isolation mount NA 1200

Tail rotor drive shaft installation 1200 Indefinite

TH-55A Tail rotor retention straps 2800 2800

Main rotor blades 1366 1366

Horiz stabilizer assembly 3070 3070

Tail rotor drive shaft 3000 3000

Tail rotor drive shaft driven spline 3000 3000

Tail rotor gearbox input shaft 3000 3000

Main rotor gearbox pinion assembly 3000 3000

Lower pulley coupling shaft 1500 1500

Tail boom assembly 17,370 17,370

Engine 1600 Indefinite

Tail rotor gearbox 1800 Indefinite

UH-1B Engine (T53-L-5/9/9A/11/11A,B) 1200 Indefinite

, Engine (T53-L-11CJD) 1800 Indefinite

Main rotor hub 1100 Indefinite

/ Main transmission 1100 Indefinite

Ninety-degree gearbox 1100 Indefinite

TOR ornciAL üSE OHL* 2-7

446-903 0 - 71 - 13 FM 101-20-1

2-1. Major Components (CONT).

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

UH-1B (Cont) .. . Forty-two degree gearbox 1500 Indefinite

Main rotor blades 1000 1000

Main rotor mast 1100 Indefinite

Tail rotor blades and hub 1100 1100

UH-1C Engine (T53-L5/9/9A/11/11A,B) 1200 Indefinite

Engine (T53-L-11C,D) 1800 Indefinite

Main rotor hub 1100 Indefinite

Main transmission 1100 Indefinite

Main rotor mast 1100 Indefinite

Main rotor blades 1100 Indefinite

Forty-two degree gearbox 1500 Indefinite

Ninety-degree gearbox 1100 Indefinite

Swashplate and support 1100 Indefinite

\ Scissors and sleeve assembly 1100 Indefinite

Stabilizer bar 2200 2200

UH-1D Engine (T53-L-9/9A/11 only) 1200 Indefinite

Engine (T53-L-5/11 A3) 1200 Indefinite

Engine (T53-L-11C,D) 1800 Indefinite

UH-1H Engine (T53-L-13 only) 600 Indefinite

Engine (T53-L-13A3) 1200 Indefinite

Main rotor hub 1100 Indefinite

Main transmission 1100 Indefinite

Main rotor mast 1100 Indefinite

Forty-two degree gearbox 1500 Indefinite

2-8 FM 101-20-1

2-1. Major Components (CONT).

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

UH-1H (Cont) .. Ninety degree gearbox 1100 Indefinite

Main rotor blades: 48 foot 2500 2500

Tail rotor blades and hub 1100 1100

O-l/E/G Engine (0470-1 IB) 1800 Indefinite

O-ID Engine (0470-15) 1800 Indefinite

Propeller:

P/N 2A36CIUS90MO 1800 Indefinite

OV-1A/B/C/D Engine (T53-L-7) 1200 Indefinite

(T53-L-7A) 1800 Indefinite

(T53-L-15) 1200 Indefinite

(T53-L-701) 1200 Indefinite

Propeller 1200 Indefinite

Propeller control 1200 Indefinite

U-l A Engine (R-l 340-59/61) 1300 Indefinite

Propeller 1700 Indefinite

Governor 1100 Indefinite

U-6A Engine 1400 Indefinite

(R-985-AN-14B/39/39A)

Propeller:

Modified 1400 Indefinite

Unmodified 825 Indefinite

Governor 1400 Indefinite

Wing strut 6000 6000

ron ornciAi uao ONLY 2-9 FM 101-20-1

2-1. Major Components (CONT).

TYPE OF AIRCRAFT MAJOR COMPONENT MAOT LIFE EXPECTANCY

U-8D/G Engine (0480-1B) 2000 Indefinite

Propeller 2000 Indefinite

U-8F Engine (0480-3A) 2000 Indefinite

Propeller 2000 Indefinite

U-21A Engine (T47-CP-700) 2100 3/ Indefinite

Propeller:

P/N HCB3TN3BT10173E8 1500 Indefinite

2-10 FOR’OfriCIAL LKPE ONLY- FM 101-20-1

2-1. Major Components (CONT).

NOTE: MAOT (Maximum allowable operating time) is the maximum operating time, interval or usage increment limit at which it is mandatory that a component will be removed from a service aircraft. (When used in reference to overhaul components, MAOT is the same as the term “time between overhaul” (TBO) previously used.)

NOTE: MTR (meantime to removal) is the average serviceable life of an item. The MTR is substantially less than the MAOT and varies under different operating conditions (i.e., erosion of engine turbine blades due to ingestion of dust in RVN). Refer to AVSCOM, ATTN: AMSAV-R-E for MTR data.

NOTE: This manual is a general guide. Check should be made with the most current publication for the specific MAOT.

2/Component MAOT varies according to part numbers. MAOT shown is for part with the highest value. All old part numbers will be modified to the high time configurations.

^/Component MAOT and/or life expectancy varies with different part numbers. Life shown is for the part with the highest value.

2/TB 55-1510-209-20/2 goal is 2400 hours.

Section M. AIRCRAFT EQUIPMENT

2-2. Avionics and Surveillance Equipment Configura- presently in active Army use with configurations other tions.* than those presented are being scheduled for retrofit as applicable. Further details on Army aircraft configurations and the associated ground avionics systems and The aircraft configurations listed depict the maintenance support equipments are available in the approved installation requirements for avionics and US Army Standard Avionics and Performance surveillance equipments in Army aircraft. The aircraft Configurations Five-Year Requirement Plan.

*Source: SELAE-E ron ornciAL pan ONLY FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (COIMT)

AH-1G

O I X TYPE NUMBER FUNCTION/NOUN <

AM-3209( )/ASN Servo Amplifier AN/APX-72 IFF Transponder AN/ARC-51BX UHF-AM Radio Set

AN/ARC-54 or VHF-FM Radio Set Vl AN/ARC-131 VHF-FM Radio Set Vl AN/ARC-134 VHF-AM Radio Set

AN/ARN-83 ADF Receiver

AN/ASN-43 Gyro Compass AN/ASW-( ) (BHC#570A) SAS

AS-2285( )/ARC VHF-FM Comm Ant AT-884( )/APX IFF Antenna AT-1108( )/ARC UHF-VHF Comm Ant BB-649( )/A Battery C-161K )/AIC Intercom Set

C-8157( )/ARC Control-Ind Ass’y CN-1314( )/A Gyroscope

ID-48( )/ARN Course Indicator ID-250( )/ARN Course Indicator ID-998( )/ASN RMI Indicator

KIT-1 A/TSEC IFF Computer CPO MC-1 Rate Switch Gyro MD-736( )/A Signal Discriminator MT-3802( )/ARC Mount (KY-28)

PP-6508( )/U Static Inverter

PU-543( )/A Inverter CPO (Complete Provisions Only) Racks, mounting, flanges, wiring, etc. 2-12 FOR ornciAftm ONLX 2-2. Avionics and Surveillance Equipment Configurations (CONT).

AH-1G

Ü H S3 TYPE NUMBER FUNCTION/NOUN <

TS-1843( )/APX IFF Test Set 2/CPO

TSEC/KY-28 Comm Security Set CPO

'^Either the AN/ARC-54 or AN/ARC-131 may be installed but not both.

2/Will be installed upon availability of equipment.

WIl OFFICIAL USE IM¥ FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

CH-34C

u Tt a TYPE NUMBER FUNCTION/NOUN CJ

AN/APX-44 IFF Transponder Set ^CPO

AN/ARA-31 FM Antenna Group

AN/ARC-44 VHF-FM Radio Set

AN/ARC-55 UHF-AM Radio Set

AN/ARC-73 VHF-AM Radio Set ‘/CPO

AN/ARC-102 HF-AM Radio Set Vcvo

AN/ARN-6 or 59 ADF Receiver

AN/ARN-12 or 32 Market Beacon Receiver

AN/ARN-30( ) VOR Receiver

AN/ASN-23 Auto Pilot

AN-3150-2 Battery

AN-3533 Inverter 500VA

AT-450/ARC UHF Comm Antenna

AT-640/ARN Marker Beacon Antenna

2 CU-1658/A HF Antenna Coupler /CPO

J-2 Gyro Compass

MT-3772/A Mount 2/CPO

MX-1646/AIC Headset Adapter

^Installed in selected area when installed, VHF/AM is removed

^Installed when required to accomplish mission

2-14 FOU UhULIAL U3L UHL l. FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

os OJ so O CN TfOs OO O ' so so C** obob oI SO so VO so CH-47 6b 5 6bóó os Os so Os O o OO 0\ »—I Os so so P- vo ( >- SO s¿ r- oo obobov >- SO SO VO so Sv' WWW fc < < < m u u o r- i— r- r- T T ^r 'T t T X 33 x X s X s TYPE NUMBER FUNCTION/NOUN U o u u u u 5

AM-3209( )/ASN Servo Amplifier

AN/APX-44 IFF Transponder

AN/APX-72 IFF Transponder ycpo ^CPO 6/CPO %PO

AN/ARA-31 FM Antenna GP

AN/ARC-44 VHF-FM Radio Set

AN/ARC-51BX UHF-AM Radio Set

AN/ARC-54 VHF-FM Radio Set

AN/ARC-55 UHF- AM Radio Set

AN/ARC-73 VHF-AM Radio Set CPO CPO CPO CPO CPO CPO CPO CPO

AN/ARC-102 HF-AM Radio Set CPO CPO CPO CPO CPO CPO CPO CPO CPO CPO

AN/ARC-131 VHF-FM Radio Set

AN/ARC-134 VHF-AM Radio Set

AN/ARN-30E VOR Receiver

AN/ARN-59 ADF Receiver #1

AN/ARN-59 ADF Receiver #2 CPO

AN/ARN-82 VOR Receiver

AN/ARN-83 ADF Receiver

AN/ASN-43 Gyro Compass

AN/ASN-72 Decca Nav Sys CPO CPO CPO CPO CPO CPO CPO MCPO

AS-580( )/ARN-30 VOR Antenna

AS-1703( )/AR FM Comm Antenna

AS-1869( )/ARN ADF Sense Antenna

AS-1870( )/ARN ADF Sense Antenna

AS-1922( )/ARC FM'Homing Antenna

AT-450( )/ARC UHF Comm Antenna

TOR OPriCIAL USE PWLY- 2-15 FM 101-20.1

2-2. Avionics and Surveillance Equipment Configurations (CONT). ov rJ vo CTv vo rJ cN ■v* oo o —v vo *o VO t—■ oo oó oó Ov 9 vo vo 9 99 CH-47 ■Vt OOÓÓ >OOvO CO OV -H VO vo »o VO V£> 9 >- >< 5« b b < < u o U r- r- r- T T T T T T 9 9 3C s X 33 K X SB as X- TYPE NUMBER FUNCTION/NOUN 5 (J u u O U V u u u

AT-640( )/ARN Marker Beacon Ant

AT-884( )/APX IFF Antenna

AT-1108( )/ARC UHF-VHF Comm Ant

BB-432( )/A Battery

C-161K )/AIC Intercom Set

C-4209( )/ARC Control (T-366( )/ARC)

C-8157( )/ARC Control Ind. Ass’y

CN-81K )/ASN(SBU-6A) Displacement Gyro

CU-942( )/ARC FM Antenna Coupler

CU-99K )/AR HF Antenna Coupler CPO CPO CPO CPO CPO CPO CPO 2/CP0

CU-1658( )/A HF Antenna Coupler VCPO CPO CPO

CV- 1275( )/ARN RMI Converter

DMN 4-4.1 VOR Antenna

DY-86( )/ARN-30 or Dynamotor

PP-2792( )/ARN-30D Power Supply

F-726( )/AR Filter

ID-250( )/ARN Course Indicator

ID-453( )/ARN-30 Course Indicator

ID- 998( )/ASN RMI Indicator

IN-14 Course Indicator

J-2 Gyro Compass

Kit-1 A/TSEC IFF Computer CPO CPO CPO CPO CPO CPO CPO CPO

M-40A Mount (CV-1275( )/ARN)

MD-736( )/A Signal Discriminator

MT-1142( )/ARC Mount (T-366( )/ARC)

MT-1719( )/AR Mount (CU-991( )/AR) CPO CPO CPO CPO CPO CPO Yc?o

2-16 ron ornciAL uae ONU FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

ON 04 kO SO 04 < >- >* VO >- u. tu tu VO fe u o u t— t— c- f T T T 'T ví- vt- T as as as X X x as SC S X TYPE NUMBER FUNCTION/NOUN u o u o u u o

MT-2292( )/ARN Mount (R-l041 ( )/ARN) CPO

3 MT-2641( )/ARC-94 Mount (AN/ARC-102) /i

MT-3772( )/A Mount (CU-1658A/A) 5fcpo CPO CPO

MT-3802( )/ARC Mount (KY-28)

R-1041( )/ARN Marker Beacon Receiver CPO CPO CPO CPO CPO CPO CPO CPO CPO CPO

SI-07F Filter

T-366( )/ARC VHF-AM Transmitter

TSEC/KY-28 Comm Security Set CPO CPO CPO CPO CPO CPO CPO CPO CPO

TS-1843( )APX IFF Test Set CPO CPO CPO CPO CPO CPO CPO CPO CPO

114E 2186-16 or Speed Trim Amplifier n Yi

114E 2186-19 Speed Trim Amplifier % 4/l %

114E 2186-23 or Speed Trim Amplifier

114E 2186-26 Speed Trim Amplifier

114E 2186-30 Speed Trim Amplifier

114E 3030-40 or SAS Amplifier % 5/2

y2 114E 3030-42 or SAS Amplifier V2 Ÿ2

114E 303043 SAS Amplifier 5/ÍJ % s/2 S/2

114E 303047 SAS Amplifier

114E 303049 SAS Amplifier

1560-CH47-209-13 Control

'/installation of complete provisions was discontinued after S/N 68-15814.

2/Provisions for CU-1658A/A and MT- 3772A/A were installed in production starting with S/N 68-15835. Prior aircraft have provisions for CU-991( )/AR and MT-1719( )/AR.

3/lnstalled in production, S/N 68-15860 and subsequent.

4/Vertol P/N 114E2186-16 or 114E 2186-19 may be used; however, the former is the preferred item.

^Vertol P/N 114E 303040 is only authorized when small landing gear is installed. Vwill be installed when available. When AN/APX-72 is installed the AN/APX44 is removed.

E-OR ornciAi use ONLY 2-17 r FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

vo CO ’i- Tf Tí-vo ooTí- 00 oo oo v¿ dv d\ 00 s 00^ 3:00 V¿ r- 0¿> Ch VC VO VO VO VC O 'w' V». ' ‘ < < < < ■»vt VO VO VO vo X X X sc TYPE NUMBER FUNCTION/NOUN S u u u

AM-3209( )/ASN Servo Amplifier *AM-6279( )/ASW AFCS Amplifier *AM-6280( )/ASW AFCS Amplifier

AN/APX-44 IFF Transponder ■4

AN/APX-72 IFF Transponder VCPO

AN/ARC-51BX UHF-AM Radio Set AN/ARC-54 VHF-FM Radio Set 24 M

AN/ARC-73 VHF-AM Radio Set CPO AN/ARC-102 HF- AM Radio Set CPO CPO CPO CPO CPO AN/ARC-131 VHF-FM Radio Set 24' AN/ARC-134 VHF-AM Radio Set AN/ARN-82 VOR Receiver AN/ARN-83 ADF Receiver

AN/ASH-19 Voice Warning Set AN/ASH-23 Voice Warning-Recorder AN/ASN-43 Gyro Compass AN/ASW-29 Flight Control System AS-1304( )/ARN VOR Antenna AS-1703( )/AR FM Comm Antenna

AS-1922( )/ARC FM Homing Antenna AT-884( )/APX IFF Antenna AT-1108( )/ARC UHF/VHF Antenna

BB-434( )/A Battery

C-1611( )/AIC Intercom Set C-4209( )/ARC Control (T-366( )/ARC)

2-18 FOR OPPrCIAL OTE OHUX FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (COIMT).

CO Tj" vo vo 00 s 00 3 3 T-H v¿ cb ov Ov dv vo VO vo vo VO CH-54 oè Tf O VO rt i C\ d> dv VO VO 'w' vo vo < < < ea < T uo X X X X s TYPE NUMBER FUNCTION/NOUN a u V U o

*C- 7266( )/ASW-29 Control (AFCS)

*C-7269( )/ASW Control (AN/ASW-29)

C-8157( )/ARC Control-lnd. Ass’y

*C-8476( )/ASW Control (AFCS)

*C-8477( )/ASW Control-Monitor (AFCS)

*C-8478( )/ASW Controller (AFCS)

CN-1179( )/ASW Displacement Gyro

CN-1314( )/A Gyroscope

*CN-1325( )/ASW Gyroscope

CU-942( )/ARC FM Antenna Coupler

CU-99K )/AR HF Antenna Coupler CPO

CU-1658( )/A HF Antenna Coupler CPO CPO CPO CPO

F- 726( )/AR Filter

ID-250( )/ARN Course Indicator

lD-998( )/ASN RMI Indicator

ID-1720( )/ASW Indicator (AFCS)

KIT-1 A/TSEC IFF Computer CPO CPO CPO CPO CPO

MD-736( )/A Signal Discriminator

MT-1142( )/ARC Mount (T-366( )/ARC)

MT-1719( )/AR Mount (CU-99K )/AR) CPO

MT-3772A/A Mount (CU-1658( )/A) CPO CPO CPO CPO

MT-3802( )/ARC Mount (KY-28)

*MX-8611( )/ASW Accelerometer (AFCS)

PP-2792( )/ARN-30D Power Supply

PU-543( )/A Inverter

FOfr OFFICIAL USE ONI Y 2-19 FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (COIMT). cn if vo vo oo oo 00 oo I vo OO Ov Ov Ov CH-54 VO vo VO VO V^p vo oil TJ- Tt TJ- 00 00 00 oo v¿ ok 0\ Ov VO VO VO V—'vo vo' < < < PQ Tí- -a- IT) lo VJ •o lOI X X X X 3 TYPE NUMBER FUNCTION/NOUN u U U u

SN-410( )/ASW-29 Synchro (AFCS) SN-441( )/ASW Synchro (AFCS) *SN-442( )/ASW Synchronizer (AFCS) T-366( )/ARC VHF-FM Transmitter

TS-1843( )/APX IFF Test Set ^CPO ^CPO %:PO %:PO YCPO TSEC/KY-28 Comm Security Set CPO CPO CPO CPO CPO

TW-333/ASH-19 Message Tape Signal Adapter

'/Either the AN/APX-44 or AN/APX-72 may be installed but not botlu 2/Either the AN/ARC-54 or AN/ARC-131 may be installed but not both. ^/installed upon availability of equipment.

* Electronic components comprising the CH-54B AFCS system. The Flight Control System (AN/ASW-29) for CH-54A is shown as a complete system.

2-20 roK-ornciAL use-ONU^ FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

OH-6A ov vo I »o 00 > > fe < < VO VO S S TYPE NUMBER FUNCTION/NOUN o O

AM-12049 Filter (Static Inv)

AN/APX-72 IFF Transponder

AN/ARC-51BX UHF-AM Radio Set K AN/ARC-54 or VHF-FM Radio Set

AN/ARC-131 VHF-FM Radio Set

AN/ARC-73 VHF-AM Radio Set Vcvo

AN/ARC-111 VHF-AM Radio Set YCPO

AN/ARC-114 VHF-FM Radio Set #1

*AN/ARC-114 VHF-FM Radio Set #2 CPO

AN/ARC-115 VHF-AM Radio Set

AN/ARC-116 UHF-AM Radio Set VCPO

AN/ARN-59 ADF Receiver Yi

AN/ARN-83 ADF Receiver

AN/ARN-89 ADF Receiver

AN/ASN-43 Gyro Compass 4 AS-1703( )/AR FM Comm Antenna A

AT-884( )/APX IFF Antenna

BB-641( )/A Battery

BB-678( )/A Battery

C-1611( )/AIC Intercom Set

C-6533C )/AlC Intercom Set

C-8157( )/ARC Control-Ind Ass’y 1 1

CU-1794( )/ARC FM Coupler

CU-1796( )/ARC FM Coupler

CU-1893( )/ARC FM Coupler

CU-1894( )/ARC FM Coupler “H

^OR OrPIClAL-USF OigLY- 2-21 FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

OH-6A

<3\ oo S’ >-

< < s>s TYPE NUMBER FUNCTION/N OUN o o*

ID-1351( )/A Course Indicator KIT-1 A/TSEC IFF Computer CPO PP-( ) Static Inverter PP-( ) Static Inverter

TS-1843( )/APX IFF Test Set 6/6PO

TSEC/KY-28 Comm Security Set CPO Hughes #369A 4385 Homing Damp Network Yi Hughes #369A 4420 Hdset/Mic Filter Assy Hughes #369A 4508 FM Homing Ant Balum Hughes #369A 4536 FM Antenna Coupler Hughes #369A 4583-3 FM Antenna Coupler Hughes #369A 4575 UHF/VHF Ant Diplexer Hughes #369A 4587 Pilot/Cô-Pilot Mic Filter Hughes #369A 4605 FM Hi Pass Filter Hughes #369A 4606 VHF Band Pass Filter Hughes #369A 4612 UHF Hi Pass FUter

Hughes #369A 4675 UHF/VHF Ant Diplexer UHF/VHF Antenna

(P/O Eng Air Inlet Frg) FM Comm Antenna

(P/O Canopy Frame) FM Homing Antenna

(Tape on Canopy)

ADF Sense Antenna

2-22 POU OFPieiAL U3E OHt¥ FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

’/[Tie AN/ARC-51BX was installed in lieu of the AN/ARC-116 during production. Replacement of AN/ARC-51BX is predicated on availability of AN/ARC-116.

Vlnstalled in S/N 65-12916 and 65-12917 only.

^Installed in S/N 65-12918 and subsequent aircraft.

Vlnstalled in S/N 68-17353 and subsequent aircraft.

Vlnstalled in S/N 68-17306 and subsequent aircraft.

Vlnstalled when equipment becomes available.

* FY-68-69 aircraft contain wiring provisions for 2 ea AN/ARC-114, 1 ea AN/ARC-115 and 1 ea AN/ARC-116; however, the maximum number of sets that can be installed at any given time is 3. i.e. 1 ea AN/ARC-114, 1 ea AN/ARC-115, 1 ea AN/ARC-116 or 2 ea AN/ARC-114 and 1 ea AN/ARC-115 or 2 ea ÀN/ARC-114 and 1 ea AN/ARC-116.

TOR ornciAi ust UNL I

446-903 0-71-14 FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

OH-13

TYPE NUMBER FUNCTION/NOUN O oSC

AN/ARA-31 FM Antenna Group AN/ARA-56 FM Antenna Group AN/ARC-44 VHF-FM Radio Set n AN/ARC-45 UHF-AM Radio Set AN/ARC-54 VHF-FM Radio Set Yl AN/ARC-60 UHF-AM Radio Set AN/ARC-7 3 VHF-AM Radio Set CPO AN/ARC-111 VHF-AM Radio Set ft AN/3151-2 Battery AS-1703( )/ARC VHF-FM Antenna n AT-1108( )/ARC UHF-VHF Antenna C-16U( )/AIC Intercom Set % CU-942( )/ARC Coupler

ID-48( )/ARN Course Indicator MX-1646/AIC Headset Adapter ft

‘/OH-ISH aircraft were produced in 1955 through 1959 with factory installation of AN/ARC-60, AN/ARC-44, and the AN/ARA-31. OH-13H models scheduled for Europe will have the ARC Type 12 system installed. The ARC Type 12 will be replaced by the AN/ARC-111 in Europe. Complete provisions for the AN/ARC-60 will be retained.

2/lnstalled in FY64 models only on production. Installed on FY63 aircraft under Project ZYR. 3/lnstalled in FY63 models only on production. Remove under Project ZYR.

TOR OfflCIAL USE OMLX FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

OH-23

» ae s TYPE NUMBER FUNCTION/NOUN o o o

AN/ARA-31 FM Antenna Group Vl

AN/ARA-56 FM Antenna Group

AN/ARC-44 VHF-FM Radio Set y\

AN/ARC-45 UHF.-AM Radio Set

AN/ARC-54 VHF-FM Radio Set

AN/ARC-60 UHF-AM Radio Set 24

AN/ARC-73 VHF-AM Radio Set VCPO

AN/ARN-59 ADF Receiver

AN-3151-2 Battery

AS-1703/ARC VHF-FM Antenna %

3 AT-1108/ARC UHF-VHF /l

C-1611 ( )/AlC Intercom Set 4/2

CU-942/ARN Antenna Coupler 4/l

ID-48( )/ARN Course Indicator 4/l

MX-1646/AIC Headset Adapter %

BB-434/A Battery

*T-22RA/M(AN/ARC-95) HF AM Radio Set

AT-454/AR Antenna

î/lnstalled in FY62 and FY63 aircraft only.

^Installed in FY62 aircraft only.

^Installed in FY63 and FY64 aircraft only.

Vlnstalled in FY64 aircraft only on production.

* Commercial Item

f-QR"OFFICIAL U3rOWLY 2-25 FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

OH-5 8 A

< CO •o X TYPE NUMBER FUNCTION/NOUN O-

AN/APX-72 IFF Transponder

AN/ARC-51BX UHF-AM Radio Set AN/ARC-114 VHF-FM Radio Set #1

AN/ARC-114 VHF-FM Radio Set #2 CPO AN/ARC-115 VHF-AM Radio Set AN/ARC-116 UHF-AM Radio Set CPO AN/ARN-89 ADF Receiver AN/ASN-43 Gyro Compass AT-884( )/APX IFF Antenna BB-676( )/A Battery C-6533/ARC Intercom Set ID-1351( )/A Course Indicator KIT-1 A/TSEC IFF Computer CPO

PP-( ) Static Inverter TS-1843( )/APX IFF Test Set ?tPO TSEC/KY-28 Comm Security Set CPO

BeU #206-032-310 ADF Sense Antenna

BeU #206-075-380 FM Low Pass Filter BeU #206-075-381 UHF Hi Pass FUter BeU #206-075-382 VHF Band Pass FUter

BeU #206-075-518 FM Antenna Coupler BeU #206-075-523-1 FM Homing Antenna BeU #206-075-543 VHF Comm Antenna BeU #206-075-551 UHF Comm Antenna

1/The AN/ARC-51BX was instaUed in Ueu of the AN/ARC-116 during initial production. Replacement of the AN/ARC-51BX is predicated on availability of AN/ARC-116. VinstaUed upon availabiUty of equipment.

2-26 FOB OFFICIAL UGC OMLY FM 101-20-1

2-2. Avionics and Surveillance Equipment Configurations (CONT).

£ o« ■ç* «3$ «y ^v oo c r*» c 00 UH-1 «a 3 r- •“ Sä 3 \0 3 VO 3 .£ VO r? VO 3 VO ® • CO w CO w CO 'v' CO w CO w CO w CO x K ac ac oa U U Q Û S’ X TYPE NUMBER FUNCTION/NOUN X

AM-3209( )/ASN Servo Amplifier

AN/AAS-29 IR Night Vision Sys

AN/APX-44 or IFF Transponder

AN/APX-72 IFF Transponder

AN/ARC-51BX UHF-AM Radio Set

AN/ARC-54 or VHF-FM Radio Set

AN/ARC-131 VHF-FM Radio Set

AN/ARC-7 3 VHF-AM Radio Set CPO CPO CPO CPO yCpo

AN/ARC-102 HF-AM Radio Set 7CPÖ CPO CPO CPO VCPO CPO CPO CPO CPO CPO