FIELD MANUAL UNITED STATES ARMY AVIATION PLANNING MANUAL

RECAP 17 6-302 1742 17-87 17-105 17-108 29-35 55424 64 (14) (12) (10) 27 (27) 1 0) 42 (14) (12) (6) 10 (10) 9 (9) 13 4 8 (8) 1 (1) Mechanized Division . *HHB, Div Arty ... Armd Cav Sqdn *Air Cav Trp ... Maint Bn *Acft Maint Co . HHC, Mech Bde (3) Avn Co, Mech Div RECAP RECAP RECAP 37 6-302 17-105 17-108 29-25 55424 3742 37-87 64 (14) 27 (27) 1 (1) (12) (10) 42 (14) 10 (10) (12) (6) 9 (9) 13 8 (8) 1 (1) (4) Infantry Division (Active) *HHB, Div Arty *HHC, Inf Bde (3) .... Avn Bn, Inf Div *Aslt Hel Co *Avn GS Co Air Cav Sqdn *HHT, Air Cav Sqdn *Air Cav Trp (3) ... Maint Bn *Acft Maint Co .... RECAP RECAP RECAP RECAP 7 6- 3 742 7- 7 7-77 7-78 17-205 17-206 17-208 29-15 55-89 160 (14) (18) 42 (29) (13) 85 (4) (81) 1 (1) 62 (14) (12) 6 (6) 30 (30) 33 6 (6) 27 (27) 65 (6) 30 (23) (7) 28 (4) (24) 1 (1) Infantry Division (Reserve) *HHB, Div Arty *HHC, Inf Bde (3) Avn Bn, Inf Div *Aslt Hel Co *Avn GS Co Armd Cav Sqdn RECAP-!/ RECAP RECAP 7 6- 3 742 7- 7 7-77 7-78 17-105 102 (14) (18) 42 (29) (13) 27 42 (14) (12) 6 (6) 10 15 6 (6) 45 (6) 30 (23) (7) 8 FM 101-20-1 FFICIAL USE ONLY 1-1. Basis of Issue — Aircraft Authorization per Unit (CONT). UNIT *Air Cav Trp Maint Bn RECAP *Acft Maint Co TOE 17-108 29-15 55-89 TOTAL AC FT (27) 1 (1) LOH (10) AH-1G (9) UH-1H (8) 1 0) CH-47 CH-54 OV-1B OV-1C U-21 U-10 Airborne Division RECAP *HHB, Div Arty Air Cav Sqdn RECAP *HHT, Air Cav Sqdn *Air Cav Trp (3) Maint Bn RECAP *Acft Maint Co *HHC, Abn Div Bde (3) Avn Bn, Abn Div RECAP *Aslt Hel Co *Avn GS Co 57- 6-201 17-275 17-276 17-278 29-55 55-99 5742 57-55 57-57 57-58 160 (14) 85 (4) (81) 1 (1) (18) 42 (29) (13) 62 (14) 30 (30) (12) 6 (6) 33 27 (27) 6 (6) 65 28 (4) (24) 1 (1) (6) 30 (23) (7) CO FM 101-20-1 AINf) isn. WiaUJO-TOJ 1-1. Basis of Issue - Aircraft Authorization per Unit (CONT). UNIT TOE TOTAL ACFT LOH AH-1G UH-1H i CH47 CH-54 OV-1B OV-1C U-21 STANO UH-1M U-10 Airmobile Division Div Arty *Avn Btry (Div Arty) FA Bn Aerial Arty H&S Btry, Aerial Arty . Arty Btry, Aer Arty (3) Avn Gp Aslt Spt Hel Bn *HHC, Aslt Spt Hel Bn Aslt Spt Hel Co (3) . . *Avn Co (GS) Aslt Hel Bn (2) HHC, Aslt Hel Bn (2) .. Atk Hel Co (2) Aslt Hel Co (6) Med Bn HHC, Med Bn Air Cav Sqdn *HHT, Air Cav Sqdn Air Cav Trp (3) TC Bn, Acft Maint HHC, TC M&S Bn Acft Maint Co (2) ♦HHC, Ambl Div Bde (3) RECAP RECAP RECAP RECAP RECAP RECAP RECAP RECAP RECAP 67 6-700 6-702 6-725 6-726 6- 7 7- 2 1-165 1-166 1-167 7-202 7-255 7-256 7-257 7- 2 8- 2 8-26 17-95 17-96 17-98 55-405 55-406 55-407 67-42 422 58 (19) 39 (3) (36) 226 50 (2) (48) (26) 150 (6) (24) (120) 12 (12) 85 (4) (81) 5 O) (4) (36) 88 16 (16) 16 (10) 6 (6) 30 (30) 2 (2) (24) 87 36 36 (36) 24 24 (24) 27 (27) 193 6 (3) 3 (3) 132 2 (2) (10) 120 (120) 12 (12) 28 (4) (24) 3 0) (2) (12) 48 48 48 (48) (6) FM 101-20-1 RO R ornetAL use O 1-1 Basis of Issue — Aircraft Authorization per Unit (CONT). UNIT TRICAP Division HHB, Div Arty HHC, Armd Bde (2) Avn Bn HHC, Avn Bn Aslt Spt Hel Co Aslt Hel Co (37 Avn Co (GS) Armd Cav Sqdn Air Cav Trp Air Cav Atk Sqdn HHT, Air Cav Atk Sqdn .... Atk Hel Co (3) Air Cav Sqdn HHT, Air Cav Sqdn Air Cav Trp Maint Bn Acft Maint Co HHC, Ambl Bde Separate Brigades *HHC, Inf Bde (Sep) . *HHC, Armd Bde (Sep) *HHC, Mech Bde (Sep) *HHC, Abn Bde (Sep) *HHC, Light Inf Bde . TOE TOTAL ACFT LOH AH-1G UH-1H CH-47 CH-54 OV-1B OV-1C U-21 U-10 RECAP RECAP RECAP RECAP RECAP RECAP 6- 3 1742 17-145 7- 7 1-258 7-357 17-87 17-105 17-108 17-185 17-186 17-187 17-175 17-196 17-198 29-35 55424 6742 330 (11) (8) 114 (17) (87) (10) 26 (26) 71 (17) (54) 85 (4) (81) 2 (2) (13) 80 (9) (8) 6 (6) 9 (9) 10 (10) 30 (30) (8) 99 18 (18) 9 (9) 45 (45) 27 (27) 135 (2) 16 74 16 (1) (69) (4) 8 (8) 16 (7) (9) 28 (4) (24) 2 (2) (5) (16) 7-102 17-102 37-102 57-102 77-102 11 8 8 6 8 6 11 8 11 8 3 2 2 3 3 I wi FM 101-20-1 "“POR OmChfrtr-PSC ONLX ¿> 1-1. Basis of Issue - Aircraft Authorization per Unit (CONT). UNIT TOE TOTAL ACFT LOH AH-1G UH-1H CH47 CH-54 OV-1B OV-1C U-21 U-10 Armored Cavalry Regiment HHT, Armd Cav Regt .. HHT, Cav Sqdn (3) ... *Air Cav Trp RECAP 17-51 17-52 17-56 17-58 49 (10) (12) (27) 18 (2) (6) (10) (9) 22 (8) (6) (8) Air Cav Sqdn (Separate) *HHT, Cav Sqdn ... Air Cav Trp (3) RECAP 17-195 17-196 17-198 85 (4) (81) 30 (30) 27 (27) 28 (4) (24) Avn Bde, HHC *Avn Co, Corps *Avn Co, Army Recon Hel Co . *Air Traffic Control . Avn Gp, HHC Avn Bn, HHC Avn Co, Aslt Spt Hel Avn Operating Teams *Engr Cbt Bn, Army/Corps HHC, Engr Cbt Bn .... *Engr Cbt Gp, HHC RECAP 1-66 1-127 1-137 1-177 1-207 1-252 1-256 1-258 1-500 5-35 5-36 5-52 8 JO 13 32 5 5 2 17 9 2 (2) 2 4 3 32 2 3 4 5 1 1 (1) 2 2 1 1 1 (1) 16 1 2 1 5 * FM 101-20-1 3Sn 1VIDIJJO \io-i 1-1. Basis of Issue — Aircraft Authorization per Unit (CONT). UNIT TOE TOTAL AC FT LOH AH-1G UH-1H CH-47 CH-54 OV-1B OV-1C U-21 U-10 Engr Cbt Bde, HHC ... Engr Const Bde, HHC . Engr Const Gp, HHC .. *Engr Comd, HHC .... *Engr TOPO Co, Corps *Engr Base Survey Co . HHB, Field Arty Gp ... HHB, Corps Arty HHB, Abn Corps Arty HHB, FA Bde (Pershing) Field Arty Bn (Pershing) HHB, FA Bn (Pershing) Avn Co, Aslt Hel — Separate ... Med Co, Air Ambulance RECAP Med Det, Hel Ambulance (RC) Med Det, Hel Ambulance (RA) Corps Signal Bn HHC, Corps Sig Bn RECAP 5-101 5-111 5-112 5-201 5-327 5- 3 6- 4 6-501 6-502 6-604 6- 6 6-616 7- 3 8- 1 8-660 8-660 11-15 11-16 3 3 5 5 1 4 6 2 2 6 4 (4) 29 25 2 6 6 (6) 2 2 4 2 2 6 2 2 6 1 (1) 4 (4) 23 25 2 6 5 (5) FM 101-20-1 1-1. Basis of Issue — Aircraft Authorization per Unit (CONT). UNIT Signal Const Bn *HHC, Sig Const Bn Signal Cable Const Bn *HHC, Sig Cable Const Bn .... Army Comd Sig Rdo/Cable Bn *HHC, Army Comd Sig Rdo/Cab Bn Army Area Sig Bn *HHC Sig Army Area Bn r i Army Comd Sig Op Bn *HHC, Army Cömd Sig Op Bn *HHC Sig Bde, Army HMD, Sig Bn *HHD, Sig Gpi Army Abn Corps, Sig Bn HHC, Sig Bn, Abn Corps RECAP RECAP RECAP RECAP RECAP TOE RECAP HHC, USA Strategic Command *Sig Co, Msgr Sig Radio Relay Co *Avn Co, Atk Hel 11-25 11-26 11-45 1146 11-75 11-76 11-85 11-86 11-95 11-96 11-102 11-116 11-122 11-225 11-226 11-302 11-358 11-377 17-111 TOTAL ACFT 4 (4) 3 (3) 3 (3) 1 0) 9 (9) 3 1 4 6 (6) 1 7 1 23 LOH AH-1G UH-1H CH47 CH-54 OV-1B OV-1C U-21 U-10 4 (4) 3 (3) '2 (2) 1 (1) 2 (2) 1 2 1 0) 1 (1) 21 5 (5) 2 1 5 (5) 2 1 2 2 (2) 1 FM 101-20-1 FOR OFFICIAL USE ONLY r; 1-1. Basis of Issue - Aircraft Authorization per Unit (CONT). UNIT *MP Bde, HHD *MP Gp, HHD ♦Scout Organization . MI Bn, Air Recon Spt (MIBARS) HHC, MI Bn, Air Recon Spt MI Co, Aerial Survl Avn Co, Survl Airplane RECAP Abn Spec Forces Gp Spec Forces Spt Bn HHC, Spec Forces Spt Bn .. *ASA Gp Field Army *ASA Co Div Spt ♦ASA Avn Co (ELIS) . ASA Avn Co (EW) ... Msl Comd (Air Trans) ♦ADA Bde, HHB ... RECAP RECAP TOE 19-262 19- 2 20- 5 30-5 30-6 30-79 30- 1 31- 1 31-125 31- 1 32- 5 32-57 32-59 32-97 39-52 44-2 TOTAL ACFT 2 5 2 5 (5) 18 18 6 (6) (6) 12 3 15 9 4 3 LOH 4 (4) (4) AH-1G UH-1H CH-47 OV-1B OV-1C OV-1D U-21 U-10 32/ 12 18 1 5 (5) 2 (2) (2) 15*1 9 (O FM 101-20-1 rent-ornciAL use ONLY. o 1-1. Basis of Issue — Aircraft Authorization per Unit (CONT). UNIT ADA Gp, HHB *ADA Bde, HHB *ADA Gp, HHB ♦FASCOM, HHC *Spt Bde, HHC ♦Trans Mvmt Con Center, HHD . ♦Trans Motor Trans Bde, HHC ♦Trans Bde, HHC (COSCOM) .. ♦Trans Tml Bde, HHC ♦Trans Tml Gp, HHC ♦Trans Rwy Gp, HHC Avn Co, Hvy Hel TC Co, Acft DS TC Co, Acft GS TC Bn, Acft Depot Maint HHC, Trans Acft Depot Maint (Seaborne) ... RECAP TOE 44-12 44-102 44-112 54-12 54- 2 55- 6 55-11 55-62 55-111 55-112 55-202 55-259 55-457 55-458 55-465 55-466 TOTAL ACFT 2 2 2 3 2 1 1 2 1 1 1 10 2 3 2 (2) LOH AH-1G UH-1H CH-47 CH-54 0V-1B OV-1C U-21 U-10 1 1 1 2 1 1 2 1 1 1 1 2 2 2 (2) FM 101-20-1 LOR orriciAL use ONLY JJ 1-1. Basis of Issue - Aviation Detachment and Nonstandard BOI-Addendum V UNIT UIC TOTAL ACFT LOH AH-1G UH-1H CH-47 CH-54 OV-1B OV-1C U-21 U-10 USAEIGHT 3d Avn Det .. 6th Avn Hat . 5 2d Avn Det USAJAPAN 4th Avn Det . USARSUPTHAI 70th Avn Det USARRYUKYUI 23d Avn Det USARV 358th Avn Det USARHAW 367th Avn Det USARAL 19th Avn Bn, HHC .... 90th Avn Co, ASHC . 236th Avn Co, ASHC 12th Avn Co, GS ... USMA 2d Avn Det ARADCOM 44th Avn Det USARSO 352d Avn Det WDHW WHMX WDHY WG7G WGZL WE2E WGU WG8H WAX4 WA46 WHVC WAYL WAY3 WG40 WGZM 7 4 2 7 12 12 15 13 5/ 11 11 12 y FM 101-20-1 iMNO 3Cn IVIJIJjO MOT ¿J 1-1. Basis of Issue - Aviation Detachment and Nonstandard BOI--Addendum2/(CONT). UNIT UIC TOTAL ACFT LOH AH-1G UH-1H CH-47 CH-54 OV-1B OV-1C U-21 U-10 USAREUR IstAvnDet 22d Avn Det AWSCOM 56th Avn Det 356th Avn Det 357th Avn Det .. (BELGIUM) SETAE 6th Avn Det WAYZ WFKA WAY1 WG1G WG1H 5 8 7 1 2 3 3 2 WDHX 4 * Aircraft BOI changes from “T”, “G” or “H” series TOE. NOTE. Organic DS maintenance capability is to be provided in those units which are underlined. y In ASOP and JSOP has same BOI as Active Infantry Division (160 aircraft). 2/ RU-Type aircraft. V This addendum is provided to account for those aircraft authorizations which, in addition to the preceeding BOI, are used to compute command requirements. y One U-21 authorized to unit subordinate to ARADCOM by MTOE included here. Source: OACSFOR C a FM 101-20-1 FM 101-20-1 1-2. Test and Test Support Aircraft. Requirements for test and test support aircraft are established as follows: a. All plans of test or development programs which require the use of aircraft for any phase will identify the specific type of aircraft required and the purpose (e.g., competitive evaluation of navigation aids in utility helicopter, air transportability of missile in cargo helicopter). b. The agency providing test service to customers normally requires one aircraft to support two plans of test, with the following exceptions: (1) An aircraft which is on bailment for an extended period cannot be considered as an available asset to fill additional requirements. (2) An aircraft which has been modified to a special configuration (flying lab, ski installation) in support of a particular specialized long range R & D program may not be considered as a suitable available asset to apply against normal test and test support aircraft requirements during a given fiscal year. (How- ever, this aircraft may become available for use in other programs in subsequent years.) Nonstandard air- craft assets shall not be considered as suitable sub- stitutes for Army aircraft when computing test and test support aircraft requirements. Requirements should be based on use of Army-type aircraft to support Army programs. Use of nonstandard aircraft (C-47, T-28) for Army test programs will be authorized only if an Army- type aircraft cannot be made available or is not suitable for the intended purpose. Example: A USAF jet aircraft may be necés- sary for missile chase at firing sites. c. In addition to those aircraft required to support research, development, test, and evaluation, a require- ment is established for allocation of additional aircraft. Three models of each new type aircraft will be pro- cured by Department of the Army. The three aircraft will be assigned to USA Test activities and will be utilized during the service life of that particular type aircraft for service and logistical testing. 1-3. Authorized Aircraft Designations. a. All Department of Army Aircraft have been assigned designations in accordance with provisions of AR 700-26. Explanation of terms are as follows: (1) Status prefix symbol. The status symbol (letter), will indicate an aircraft being used for experimentation and special or service test and will be placed at the immediate left of the modified mission symbol, or the mission/type symbol if no modified mission symbol is applicable. (2) Modified mission symbol. A letter used to indicate the current capabUity of an aircraft when it is so modified that its original intended capability is no longer applicable, or when it has an added or restricted capability. The modified mission symbol will consist of a prefix letter placed at the immediate left of the basic mission or type symbol. Only one modified mission symbol will be used in any one designation. (3) Basic mission symbol. A letter used to indicate the basic intended function or capability of the aircraft, such as observation, utility, etc. (4) Type symbol. An additional letter which designates helicopter and V/STOL aircraft. An aircraft identified by a type symbol, such as “H” for heli- copter, will be further identified by only one mission symbol whether it be basic mission or a modified mission symbol. (A basic mission or type symbol, once officially assigned, will not be changed without the approval of the Assistant Secretary of Defense (Installation and Logistics)). (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 be assigned when an existing aircraft is redesigned to an extent that it no longer reflects the original configuration or capability. (6) Series letter. A letter used to denote differences affecting the relation of the vehicle to its ground environment, and major modifications to the aircraft which result in significant changes to its logistic support. A letter will be assigned to each series change of a specific basic design. In designing new 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 letters “I” and “O” will not be used as series symbols. (Examples of series symbol change would be instal- lation of different engines, propellers, extra fuel tank, etc.) (7) Complete designation. The complete designation shall consist of items (1) through (6) as applicable, in the order shown. A dash (—) will be inserted between the basic mission/type symbol and 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 J N X Permanently An aircraft permanently grounded, Grounded used for ground instruction and training. Special Test, Temporary Special Test, Permanent Experimental Aircraft on special test programs 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. Aircraft on special test programs by authorized activities or on bail- ment 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. 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 Z Planning Aircraft procured in limited quantities to develop the potentialities of the design. Designations used for identification purpose during the planning or pre- development stage. c. Modified missions symbols (prefix letters) are as follows: LETTER A C R T U V TITLE Attack Cargo/ Transport Reconnaissance Trainer Utility Staff DESCRIPTION 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. Aircraft modified for canying cargo and/or passengers. Aircraft modified and permanently equipped for photographic and/or electronic reconnaissance missions. Aircraft modified and equipped for training purposes. Aircraft having small payload, modified to perform miscellaneous missions such as carrying cargo or passengers, and towing targets. Aircraft modified to provide accommo- dations such as chairs, tables, lounge, and berths for the transportation of staff personnel. d. Basic mission and type symbols are as follows: LETTER TITLE A Attack DESCRIPTION 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 C H O R T U V X TITLE Cargo/ Transport Helicopter Observation Reconnaissance Trainer Utility VTOL and STOL Research DESCRIPTION Aircraft designed for carrying cargo and/or passengers. A rotary-wing aircraft designed with the capability of flight in any plan; e.g., horizontal, vertical, or diagonal. 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. Aircraft designed to perform reconnaissance missions. Aircraft designed for training personnel in the operation of aircraft and/or related equipment, and having provisions for instructor personnel. Aircraft used for miscellaneous missions such as carrying cargo and/or passengers, towing targets, etc. These aircraft include those having a small payload. Aircraft designed for vertical takeoff or landing with no takeoff or landing roll, or aircraft capable of takeoff and landing in a minimum prescribed distance. Aircraft designed for testing config- urations 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 taking the average inventory for the command and multiplying it by the annual flying hour program for the particular aircraft. \ Example: USCONARC OV-1 — Fiscal year 1972 Average number of aircraft 13 Annual flying hour rate 240 13 X 240 = 3120 hours Source: OACSFOR 1-4. (FOUO) Basic Annual Flying Hour Planning Fac- tors i/- a. A Worldwide Flying Hour Program is developed annually by the Department of the Army for use in budget preparation and in planning for logistical sup- port of aircraft. It is used as a basis for management of the entire aircraft inventory and is not applicable to the operation of a single aircraft or to the aircraft of any specific aviation unit or activity. ' b. The flying hour program for each major command is published annually in Annex V, Volume II of the Department of the Army Program and Budget Guidance Document. This document lists flying hour guidance in bulk flying hours for each type of aircraft assigned to the major commands. Factors considered in development of command flying hour programs in- clude: the projected aircraft inventory, mission require- ments of the command, aviator availability, budgetary limitations, logistical considerations and other variables which may affect aircraft utilization within the commands. The DA Flying Hour Program is not expressed in flying hour rates. c. The basic flying hour planning factors con- tained below are suitable for use in intermediate and long range planning at any level of command. Two points of rationale used in the development of these factors should be considered in planning applications; these are: (1) Aircraft assigned to TOE units are in- tended to meet combat requirements. In a peacetime situation or non-combat environment, utilization of these aircraft should be restricted to only that flying time necessary to provide adequate training for avia- tion units and other units which are supported by aviation units. (2) Indirect support aircraft are assigned to meet specific administrative and training requirements. Utilization of indirect support aircraft, except training and training support aircraft assigned to the aviation training base, must meet or exceed the planning factors shown, to justify their retention in the aircraft inven- tory at every level of command. Utilization of training base aircraft is determined by the student training rate approved or programmed for the year under considera- tion. FOR OfFICIAL USD-QNl* 1-17 FM 101-20-1 1-5. (FOUO) Basic Annual Flying Hour Planning Factors 1/. TYPE AIRCRAFT 0-1 U-6 U-8/10 U-21 OV-1 T-42 T-41 U-1A OH-6 OH-13 OH-23 OH-58 UH-1 (Armed) UH-1B/C UH-1D/H AH-1G CH-34 CH-47 CH-54 TOE PEACETIME OR NON-COMBAT ENVIRONMENT (WORLDWIDE) 300 384 384 240 360 240 240 240 240 240 324 324 240 172 240 180 TOE ACTIVE COMBAT ENVIRONMENT 960 600 900 900 840 720 840 660 660 840 720 720 960 840 600 720 600 INDIRECT SUPPORT AIRCRAFT (WORLDWIDE) ALL ENVIRONMENT-2/ 600 600 600 600 600 600 600 420 420 420 420 420 420 420 420 420 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. AIRCRAFT SYSTEMS WORLD WIDE PEACETIME Airplane Observation: 0-1 Airplane Combat Surveillance: OV-1 Airplane Utility: U-6 Airplane Utility: U-10 Airplane Fixed Wing Trainer: T-41 Airplane Instrument Trainer: T-42 Airplane Utility: U-8 Airplane Utility: U-21 Airplane Utility: U-l Helicopter Instrument Trainer: TH-13 Helicopter Primary Trainer: TH-55 Helicopter Cargo Transport: CH-47 Helicopter Cargo Transport: CH-54 Helicopter Observation: OH-6 Helicopter Observation: OH-13 Helicopter Observation: OH-23 Helicopter Observation: OH-58 Helicopter Utility: UH-1 Helicopter Cargo Transport: CH-34 Helicopter Attack: AH-1G af y .0018 .0010 .0012 .0025 .0011 .0009 .0016 .0016 .0021 .0012 .0015 .0009 .0009 .0048 .0021 .0011 .0048 .0025 .0022 .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 Factors. Example: Peacetime Attrition Factor. 0-1 Aircraft. 1. Time Frame = 36 months. 2. Density (average) = 455. Nóte: To arrive at an average in use density the following category of aircraft were deleted, (a) USARV inventory, (b) Maintenance Trainers, (c) Depot inventory, and (d) aircraft in-transit. 3. Attrition during time frame = 29. 4. Calculation: 29 attrition -s- 455 density -5- 36 months = .0018. (Monthly peacetime attrition factor) Source: AMSAV-D-ZRA Section IV. STANDARD AIRCRAFT CHARACTERISTICS Standard aircraft characteristic data contained herein will change as modifications or additions and deletions of aircraft components or equipment are made. 1-20 Egn orrieiAi use OMIT- FM 101-20-1 Y 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. 8 FT 6 IN. 14 FT 4 IN. 0^3 ¿23 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-^ 13 FT SVi IN.- -ron ornciAL une ONLY m 4' 1-8. AH-1G/TH-1G* (Hueycobra) Characteristics. POWERPLANT No. and Model (1)T53-L-13 Mfi Lycoming Engine Spec. No 104.33 Type Free Power Turbine Reduction Gear Ratio 0.3115 Tail Pipe Fixed Area Augmentation None ENGINE RATINGS SEA NET LEVEL JET STD ESHP SHP THRUST RPM MIN (LBS) Military 1450 1400 126 6300 30 Normal 1296 1250 115 6040 Cont. DIMENSIONS Rotor dia 44 ft Length: Rotors operating 53 ft. Rotors static 53 ft. Fuselage 44 ft, 5-1/4 in. Span (max lateral) 10 ft, 4 in. Height 11 ft, 7 in. Tread 7 ft, 4 in. Rotor gnd clear- ance (static) 7 ft, 10 in. MISSION AND DESCRIPTION Mfr’s Model: Bell 209 The primary missions of this aircraft are that of an armed tactical helicopter capable of delivering weapons fire, low altitude high speed flight, search and target acquisition, reconnaissance by fire, multiple weapons fire support, and troop helicopter support. The aircraft is capable of performing these missions from prepared or unprepared areas, day or night flying, and to navigate by dead reckoning or instrument operation within a wide range of temperatures, including from +125 F to below freezing conditions. The gas turbine powered “HueyCobra” is of compact design featuring tandem seating to give both pilot and gunner nearly unlimited visibility. Both crew stations have flight control and fire control systems permitting flexibility in division of functions under all normal and emèrgency situations. A mission designed fuselage coupled with the 540 “Door Hinge” rotor system gives a low vibration level plus increased maneuverability and speed. Four wing stores stations and an integral chin turret provide a high degree of armament versatility with the capability of quickly changing a wide combination of weapons to match the desired mission. Reliability and maintainability are ensured through the use of many UH-1 parts which have been combat proven. DEVELOPMENT Date of contract 4 April 1966 First flight (Similar aircraft) 7 September 1965 First acft delivered 18 September 1966 FEATURES Advanced flexible gun turret. Armor protection for crew and critical components. Hardpoints for rockets, and external stores on wings. Stability Control Augmentation System (SAS) eliminates stabi- lizer bar and provides a stable gun platform. PERSONNEL Light Scout, Heavy Scout or Hog Mission Pilot 1 Gunner 1 Ferry Mission Pilot Copilot.. . WEIGHTS LOADING Empty Basic Design Combat Clean Light Scout Heavy Scout Hog Max. Takeoff Max. Landing LB. 5425 (C) 5479*(C) 6600 6231 (C) 8148 (C) 7937 (C) 7020 (C) 9500 9500 L.F. 3.5 3.7 2.8 2.9 3.3 2.4 (C) Calculated * For Basic Mission FUEL AND OIL Fuel: Grade JP-4/5 - Spec MIL-T-5624 No. tanks 2 Location Fuselage Qty 247 gal OU: Spec MIL-L-7808 No. tanks 1 Location Fuselage Qty 3.4 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. IS) W »TH-1G. Addition of Instructor Flight Controls and Instrument Panel converts the AH-1G to the TH-1G. FM 101-20-1 -EOR-OmCIAL l> 1-9. Loading and Performance - Typical Mission AH-1G (Hueycobra). CONDITIONS TAKEOFF WEIGHT (lb) Fuel at 6.5 Ibs/gal (Grade JP4) (lb) Payload (Outbound) (lb) Payload (inbound) (lb) Takeoff Power Loading (lb SHP) Disk Loading (lb sq ft) Autorotation Speed (Min. R/D) (kn) Takeoff Ground Run at SL (ft) Takeoff to Clear 50 ft (ft) Vertical Rate of Climb at SL (fpm) Maximum Rate of Climb at SL (fpm) Speed for Max R/C at SL (kn) Time: SL to 5000 ft (min) Time: SL to 10,000 ft (min) Service Ceiling (100 fpm) (ft) Absolute Hovering Ceiling (ft) COMBAT RANGE (nmi) Average Cruise Speed (kn) Cruising Altitude (Initial) (ft) Cruising Altitude (Final) (ft) Total Mission Time (hr) COMBAT RADIUS (nmi) Average Cruise Speed (kn) Cruising Altitude (Outboard) (Min/Max) .(ft) Cruising Altitude (Inboard) (ft) Total Mission Time (hr) (4) O)" (1)* (1)* (1)* (2)* (2) (2) (2) O) (3) (3) MISSION I LIGHT SCOUT 9171 1500 1792 1384 8.34 6.04 65 105 267 1330 64 3.7 8.3 12450 141.1 133 6350/9800 10000 2.4 MISSION II HEAVY SCOUT 9500 1205 2416 1384 8.64 6.25 65 127 344 1230 65 4.0 9.2 11420 95.3 125 5350/7250 10000 1.8 MISSION III HOG 9500 953 2668 604 8.64 6.25 65 127 344 1230 65 4.0 9.2 11420 70.1 125 5600/7200 10000 1.4 MISSION IV FERRY (CLEAN) 7671 1600 192 192 6.97 5.05 65 0 0 1210 1860 60 2.7 5.6 18200 10650 371.1 141 10000 10000 2.7 * ft ft FM 101-20-1 ■EOR orriciAL use ONLY 125 r 1-9. Loading and Performance — Typical Mission AH-1G (Hueycobra) (CONT). CONDITIONS MISSION I LIGHT SCOUT MISSION II HEAVY SCOUT MISSION III HOG MISSION IV FERRY (CLEAN) COMBAT WEIGHT (lb) Combat Altitude (ft) Combat Speed (kn) Combat Climb (fpm) Combat Ceiling (500 ft/min) (ft) Service Ceiling (100 ft/min) (ft) Absolute Hovering Ceiling (ft) Takeoff Ground Run at SL (ft) Takeoff to Clear 50 ft (ft) Maximum Rate of Climb at SL (fpm) Speed for Max R/C at SL (kn) Max Speed at SL (kn) Basic Speed at 5000 ft (kn) LANDING WEIGHT (lb) Ground Roll at SL -(ft) Total from 50 ft (ft) NOTES (2) (2) (2) (2) (1) (1)* (1)* (2)* (2)* (2)* (2)* 8148 Sea Level 140 1665 15350 16300 8500 0 0 1665 62 140 142 7413 0 0 7937 Sea Level 137 1745 16250 17100 9450 0 0 1745 61 137 139 7383 7020 Sea Level 132 2140 20200 21000 13750 0 0 2140 58 132 135 6578 0 0 6231 10000 155 2170 23800 24550 17700 0 0 2490 54 149 154 6231 0 0 (1) Military rated power (2) Normal rated power (3) Detailed description of radius and range missions , are presented on paragraph 1-10 (4) Includes crew of two (2) at 400 pounds (5) Smoke grenades and full ammo load included. * Based on transmission limit of 1100 shaft horsepower PERFORMANCE BASIS (a) Power required is based on “Engineering Phase B Flight Test Results of the AH-1G Bell Helicopter (HueyCobra)”. (b) Power available and fuel flow are based on Lycoming Model Spec. 104.33. (c) All data are for 6600 rpm. FM 101-20-1 FM 101-20-1 1-10. Performance Notes, AH-1G (Hueycobra). LIGHT SCOUT MISSION - Armed Tactical Helicopter — Radius Start engine; warm-up, takeoff, and climb on course at normal power to 6350 feet initial cruise altitude. Maintain 55-feet-per-minute rate of climb at cruise speed to an altitude of 9800 feet. Descend to sea level and fire rockets during a period of ten (10) minutes combat at normal power. Climb on course to 10,000 feet at normal power and return to home base at cruise speed. Range free allowances are two (2) minutes of normal power for warm-up and takeoff, ten (10) minutes of combat time at normal power, plus ten percent of initial fuel for landing and reserve. HEAVY SCOUT MISSION - Armed Tactical Helicopter — Radius Start engine, warm-up, takeoff, and climb on course at normal power to 5350 feet initial cruise altitude. Maintain 41.6-feet-per-minute rate of climb at cruise speed to an altitude of 7250 feet. Descend to sea level and fire rockets during a period of ten (10) minutes combat at normal power. Climb on course to 10,000 feet at normal power and return to home base at cruise speed. Range free allowances are two (2) minutes of normal power for warm-up and takeoff, ten (10) minutes of combat time at normal power, plus ten percent of initial fuel for landing and reserve. HOG MISSION — Armed Tactical Helicopter — Radius Start engine, warm-up, takeoff, and climb on course at normal power to 5600 feet initial cruise altitude. Maintain 50-feet-per-minute rate of climb at cruise speed to an altitude of 7200 feet. Descend to sea level and fire rockets during a period of ten (10) minutes combat at normal power. Climb on course to 10,000 feet at normal power and return to home base at cruise speed. Range free allowances are two (2) minutes of normal power for warm-up and takeoff, ten (10) minutes of combat time at normal power, plus ten percent of initial fuel for landing and reserve. FERRY MISSION — Clean (Without Auxihary Tanks) — Range Start engine, warm-up, takeoff, and climb on course at normal power to 10,000 feet initial cruise altitude. Fly out at cruise speeds until ninety percent of initial fuel is consumed and land at remote base. Range free allowance include two (2) minutes at normal rated power for warm-up and takeoff, and ten percent of initial fuel for landing and reserve. GENERAL NOTES: a. Cruise speed as used above denotes airspeed for long-range operation and is the greater of the two speeds at which ninety-nine percent of the maximum miles per pound of fuel are attainable at the momentary weight and altitude. b. Data do not include ground effect. PERFORMANCE BASIS: a. Power required is based upon “Engineering Phase B Flight-Test Data”. b. Power available and fuel flow are based on Lycoming Model Specification No. 104.33, 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 O AV 000011 Figure 14. Principal dimensions, CH-34C (Choctaw) 1-28 ■TOR ornciAL use ONLY- rriciAL use ONLY 9 1-11. CH-34C (Choctaw) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model ... (1) R-1820-84C Mfr Wright Engine spec No . N895D Superch 1 stg, 1 spd Red. gear ratio .. D.D. ENGINE RATINGS BHP RPM ALT MIN Takeoff 1525 2800 700 5 Military 1425 2700 2400 30 Normal 1275 2500 3500 Cont. METO power (max except takeoff) DIMENSIONS Rotor dia 56 ft Length: Rotors operating 65 ft, 10 in. Rotors static .... 58 ft, 3-1/2 in. Fuselage 46 ft, 9 in. Fuselage (pylon folded) 37 ft Span (max lateral) 40 ft Height 15 ft, 11 in. Tread 12 ft Main rotor gnd clearance: Idling 11 ft, 4-3/4 in. Static 9 ft, 2 in. Tail rotor gnd clearance 6 ft, 6 in. Mfr’s Model: Sikorsky S-58 The principal mission of the CH-34C helicopter is the transportation of cargo and personnel (including aeromedical evacuation). The CH-34C is a single-engine hehcopter using a single main lifting rotor and a single antitorque tail rotor. The main and tail rotors are four-bladed and are of all-metal construction. The engine is mounted in the nose facing aft and inclined 35 degrees from horizontal. Access to the engine compartment is provided through clam-shell type nose doors. A large cabin door facihtates rapid loading of passengers, litter patients, and cargo. A cargo sling is available for externally transporting up to 5000 pounds. Main rotor flight controls incorporate two parallel and independent hydraulic servo systems. Torque compensation by the tail rotor is automatically coordinated by engine torque to maintain a head- ing. For ease of starting and to lengthen rotor head life, a hydraulic clutch is used to accelerate the transmission to engine speed, at which point positive clutching occurs. Ventilation and heating are provided for the cockpit and cabin and provisions are made for winterization. The landing gear consists of a main two-wheel alighting gear and a tail wheel. The folding tail pylon reduces the stowage length to 37 feet. DEVELOPMENT Modified version of the Navy model XHSS-1 procured for use by the Department of Army. The XHSS-1 served as a prototype model of the CH-34C First flight (XHSS-1) March 1954 First flight December 1954 First acceptance March 1955 Production completed January 1959 CAPACITIES Max cargo: See “Payload- Distance”, figure 1^. Cargo compartment: Length 13 ft, 5 in. Width 5 ft . Height 5 ft, 10 in. Cargo door: Height 4 ft Width 4 ft, 5 in. Height above gnd .. 2 ft, 20 in. Floor area 67-3/4 sq ft Cabin volume 405 cu ft PERSONNEL Crew (normal) Troops 2 18 or Litters 8 LB L.F. Empty (calculated) ... 7,660 Basic 7,800 Design 12,068 Combat *8,930 Max takeoff (overload) .... +13,300 Max takeoff (normal) +12,068 Max landing 413,300 *For basic mission. +Limited by performance. (See note a paragraph 1-13.) ^Limited by max takeoff weight. 2.63 2.44 2.63 2.44 FUEL AND OIL Fuel: Grade Spec No. tanks: Fuselage, fwd. Fuselage, cen . Fuselage, aft . Total qty .... Oil: Grade Spec No. tanks Location QtV 115/145 MIL-G-5572 (1) 100 gal (1)70 gal (1)92 gal 262 gal 1100 MIL-L-6082 2 Fuselage, fwd 10-1/2 gal AVIONICS Refer to chapter 2. ARMAMENT None. FM 101-20-1 o-ran 1VI3UJO x&i öd 1-T2. Loading and Performance • Typical Mission, CH-34C (Choctaw). CONDITIONS BASIC MISSION NORMAL DESIGN COMBAT EVACU- ATION FERRY RANGE TAKEOFF WEIGHT & (lb) Fuel at 6.0 Ib/gal (grade 100/130) (lb) Payload (outbound) (lb) Payload (inbound) (lb) Takeoff power loading (lb/bhp) Disk loading (Ib/sq ft) Autorotation speed (min R/D) (kn) Takeoff ground run at SL/clear 50 ft -1/ (ft) Vertical rate of climb at SL 2/ (fpm) Max rate of climb at SL-^ (fpm) Speed for max rate of climb at SL (kn) Time: SL to 5000 ft-^ (min) Time: SL to 10,000 ft 3/ (min) Service ceiling (100 fpm)-^ (ft) Absolute hovering ceiling 5/. (ft) COMBAT RANGE & (nmi) Average cruising speed (kn) Cruising altitude (ft) Total mission time (hr) COMBAT RADIUS & (nmi) Average cruising speed (kn) Cruising altitude (ft) Total mission time (hr) FIRST LANDING WEIGHT-^ (ib) Ground roll at SL/clear 50 ft (ft) COMBAT WEIGHT^ (lb) Combat altitude (ft) Combat speed-2/ (kn) Combat climb ^ (fpm) Combat ceiling (500 fpm) 2/ (ft) Service ceiling (100 fpm)-2/ (ft) Absolute hovering ceiling-2/ (ft) Takeoff ground run at SL/clear 50 ft (ft) Max rate of climb at SL-2/ (fpm) Speed for max rate of climb at SL 2/ (kn) Max speed at SL-2/ (kn) Basic speed at 5000 ft 2/ (ft) 13,300 1572 3211 None 9.12 5.29 58 0/0 100 1120 65 4.7 14.1 10,400 2100 238 94 5000 2.6 131 98 5000 2.7 12,141 0/0 8930 5000 136 2330 19.500 20.500 13,700 0/0 2540 65 133 136 12,068 1572 2279 None 8.47 4.91 58 0/0 570 1370 65 3.8 9.7 12,500 4800 290 85 5000 3.4 148 91 5000 3.3 11,269 0/0 8990 5000 136 2300 19.350 20.350 13,600 0/0 2520 65 132 136 12,068 1356 2506 None 8.47 4.91 58 0/0 570 1370 65 3.8 9.7 12,500 4800 251 90 SL 2.8 116 93 SL 2.5 11,360 0/0 8854 SL 133 2580 19.700 20.700 14,000 0/0 2580 65 133 136 12,789 1572 3000 2000 8.98 5.20 58 0/0 210 1200 65 4.4 12.7 10,850 3000 245 95 5000 2.6 123 92 5000 2.7 11.989 0/0 10.989 5000 126 1600 14,400 15,200 7800 0/0 1860 65 128 126 9789 1572 3000 None 6.87 3.98 58 0/0 1830 2060 65 2.5 5.6 18,200 11,200 154 93 5000 2.7 9123 0/0 11,123 5000 125 1560 14,100 14,700 7400 0/0 1820 65 127 125 9789 1572 None None 6.87 3.98 58 0/0 1830 2060 65 2.5 5.6 18,200 11,200 371 98 5000 3.8 3.4 0/0 8375 5000 137 2550 20,900 22,000 15,500 0/0 2790 65 134 137 à i FM 101-20-1 FOR Of FICI AI USE 1-12, Loading and Performance - Typical Mission, CH-34C (Choctaw) (CONT). CONDITIONS BASIC MISSION NORMAL DESIGN COMBAT EVACU- ATION FERRY RANGE LANDING WEIGHT ^ (lb) Ground roll at SL/clear 50 ft (ft) 8375 0/0 8375 0/0 8342 0/0 10,375 0/0 10,375 0/0 8375 0/0 -l^Max power. ■^/Military power. -2/METO (max except takeoff). -^/Detailed descriptions of RADIUS and RANGE missions are given in paragraph 1-13. -2/ For RADIUS mission if (radius is shown. -^/includes crew of 2 at 400 lb. -2/Limited by Mach 0.8 at =90°. Performance Basis: a. Data source: Phase IV flight tests. b. Performance is based on powers shown. c. Data do not include ground effect except for takeoff and landing. FM 101-20-1 FM 101-20-1 1-13. Performance Notes, CH-34C (Choctaw). FORMULA: RADIUS MISSIONS I & II Warm up, take off, climb on course to 5000 feet at METO power, cruise out at long range speeds to an advanced area, land, and unload cargo. Without refuel- ing, warm up, take off, climb on course to 5000 feet at METO power, and return at long range speeds. Range-free allowances are 10 minutes of METO power for warmups and takeoffs, plus 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION HI Same as Radius Missions I & II, except at sea level. FORMULA: RADIUS MISSION IV Same as Radius Missions I & II, except eight litter patients are carried on inbound leg. 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 Warm up, take off, climb on course to 5000 feet at METO power, and cruise out at long range speeds untfl only reserve fuel remains. Range-free allowances are 5 minutes of METO power for warmup and takeoff, plus 10 percent of initial fuel for reserve. FORMULA: RANGE MISSION III Same as Range Missions I, II, IV & VI, except at sea level. GENERAL DATA a. Maximum overload takeoff weight is limited by the requirement that vertical climb at sea level on a standard day with military power shall not be less than 100 fpm. Maximum normal takeoff weight is limited by the requirement that vertical climb at sea level on a hot day with military power shall not be less than 300 fpm. b. Engine ratings shown are engine manufacturer’s guaranteed ratings. Power values used in performance calculations for the R-1820-84C engine are as follows: CRITICAL BHP RPM ALTITUDE Max 1425 2800 2450 Military 1400 2700 2550 METO 1275 2500 3100 PERFORMANCE REFERENCE Sikorsky Aircraft Report No. 58123, Substantiat- ing Data for Standard Aircraft Characteristics and Performances Charts for H-34A Helicopter. DATA SOURCE Sikorsky Aircraft Report No. SER 3236. Detail Specification. 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- 2-J E 98 FT 3-1/4 IN. 18 FT 6-1/2 IN •17 FT 11 IN STATIC G3 Q Q Q 10 FT 11 IN. 7 FT 4-1/2 IN. STATIC 2 DEG 51 FT AV 000017 1-34 Figure 1-6. Principal dimensions, CH47A (Chinook) FOR orriciAL use ONL* 18 IN. MIN GND CLEARANCE • CONTROLS NEUTRAL 51 FT 2 IN. -f 1-14. CH-47A (Chinook) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model . Mfr Engine spec No T55-L-5 . . . T55-L-7/7B . . (2) T55-L-7 . Lycoming 124.18C 124.20-A T55-L-7C 124.31 ENGINE RATINGS SHP RPM ALT MIN T55-L-7 MUitary 2650 15,150 SL 30 Normal 2200 15,000 SL Cont. T55-L-7B Military 2650 15,800 SL 30 Normal 2200 15,000 SL Cont. T55-L-7C Max 2850 16,000 SL 10 Military 2650 15,750 SL 30 Normal 2500 15,350 SL Cont. DIMENSIONS Rotor dia .... 59 ft, 1-1/4 in. Length: Rotors operating . . 98 ft, 3-1/4 in. Rotors folded . 51 ft Fuselage .... 51 ft Height 18 ft, 6-1/2 in. Tread 11 ft, 6 in. Main rotor gnd clearance: Idling (fwd) . . 10 ft, 11 in. (aft) ... 18 ft, 6-1/2 in. Static (fwd) . . 7 ft, 8 in. (aft)... 17 ft, 11 in. Mfr’s Model: Vertol The principal mission of the CH-47A helicopter is the transport of cargo, troops, and equipment within the combat area. In addition, this helicopter is suitable for special support functions. It is suitable for operations during day, night, visual, and instrument conditions. 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 mounted on the aft fuselage. The engines simultaneously drive two tandem three-bladed rotary wings through a combining transmission, drive shafting, and reduction transmission. The forward transmis- sion is mounted in the pylon above the cockpit. The aft transmis- sion, the combining transmission, and drive shafting are located in the aft pylon section. A gas-turbined auxiliary power unit, used for starting the engines, is mounted in the aft pylon section. Pods on the sides of the fuselage contain fuel tanks. The helicopter is equipped with nonretractable quadricycle landing gear. The aft wheels are full-swivel type. The entrance door is located at the forward right side of the cabin fuselage section. At the rear of the cabin fuselage section is a hydraulically powered loading ramp. A 16,000 pound cargo hook assembly is provided for transporting external loads. DEVELOPMENT Date of contract . First flight . . . . Production status 27 June 1960 6 September 1961 Completed May 1967 CAPACITIES M tfl Cargo compartment: Floor 226-1/4 Length 30 ft, 2 in. Width 7 ft, 6 in. Height 6 ft, 6 in. Volume 1487 cu ft Forward door: Height 5 ft, 6 in. Width 3 ft Cargo ramp door: Length 6 ft, 6 in. Width 7 ft, 6 in. PERSONNEL Crew (normal) 4 Troops 33 Litters 24 Empty (SPFG) . Design gross wt. Max alt gross wt Max takeoff . . Max landing . . LB 18,084 28,550 33.000 33.000 33.000 L.F. 2.67 3.00 3.00 3.00 FUEL AND OIL Fuel: Grade . . . Spec .... No. tanks: Nacelle . Oil: Spec Temps above -25*F Temps below -25*F No. tanks.... Location .... Qty JP-4 MIL-T-5624 (2) 621 gal (50 percent self- sealing) 630 gal (non- self-sealing) MIL-L-23699 MIL-L-7808 2 Integral with engine 7 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. FM 101-20-1 FM 101-20-1 1-15. Loading and Performance - Typical Mission, CH-47A (Chinook). CONDITIONS MISSION MISSION MISSION I II III Gross weight (lb) . Weight empty (lb) , Payload (lb) , Radius of action (nmi) . Ferry range ,(nmi) . Cruise altitude (ft) , Cruise speed (kn) , ^Max @ SL military power (kn) ^Max @ SL normal power (kn) ^Max @ 5000 ft, normal power 1 (kn) . Hover ceiling OGE 95°F, military power, std atmosphere (ft) Hover ceiling IGE military power, std atmosphere . . (ft) Service ceiling Normal power (ft) Military power 1 eng out (ft) R/C Max — military power — SL (ft/min) 28,262 17,932 6000 100 SL 130 130 130 114 6000 11.900 11.900 6000 2750 33,000 18,112 13,400 20 SL 110 110 110 94 7900 9200 9200 1400 2160 33,000 17,552 866 6000 110 110 110 94 7900 9200 9200 1400 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). FORMULA: MISSION I Deliver 6000-pound internal payload to any point 100 nautical miles and return with 3000-pound inter- nal payload. Cruise at sea level. Land with 10 percent of initial fuel reserve. FORMULA: MISSION II Deliver 13,400-pound external payload to any point 20 nautical miles and return. Equivalent flat 1-36 plate of external cargo = 26 sq ft. Cruise at sea level. Return with fuel reserve for 10-minute cruise at return gross weight. FORMULA: MISSION III Ferry Range of 866 nautical miles. Land with 10 percent of initial fuel reserve. Climb to 6000 feet, 256 nautical miles. Cruise 6000 feet for 610 nautical miles. Total ferry time: 7 hours, 50 minutes. •FOR OFFICIAL USE OHL* FM 101-20*1 12 FT 5 IN sa i -| 10 FT 6 IN. — Ev: 99 FT AV 000019 18 FT 7-13/16 IN. CO Q Ü Û Q 10 FT 11-1/16 IN. 2° 9 51 FT 18 IN. MIN GND CLEARANCE Figure 1-7. Principal dimensions, Ch47B and C (Chinook) -fOR-ernciAL USE ONIY 1-37 EOR OrriCIAL USE-ONLY- co co 1-17. CH-47B (Chinook) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model (2) T55-L-7C Mfr Lycoming Engine spec No. T55-L-7B 124.20-A T55-L-7C 124.31 Engine/rotor gear ratio 65.93:1 ENGINE RATINGS SHP RPM ALT MIN Maximum 2850 16000 SL 10 Military 2650 15750 SL 30 Normal 2500 15350 SL Cont DIMENSIONS Rotor dia 60 ft Length: Rotors operating ... 98 ft, 11 in. Rotors folded . 51 ft Fuselage 51 ft Height (overall) . 18 ft, 7-3/4 in. Tread 10 ft, 6 in. Rotor ground clearance : Static fwd 7 ft, 2-1/2 in. Idling fwd .... 10 ft, 11 in. Mfr’s Model: Vertol The principal mission of the CH47B helicopter is to provide air transportation for troops and cargo. The aircraft can also be utilized for rescue of personnel. The CH-47B is a large tandem rotor helicopter with built-in accomodations for 24 litter patients and 2 attendants or 33 troops and troop commander. The helicopter is equipped with an unobstructed 30-foot long cargo compartment with straight-in rear loading and has a capacity of over 2450 cubic feet. Other features include an external cargo hook of 10-ton capacity which may be used for towing operations; an auxihary power unit which powers the utility hydraulic system, thus eliminating the requirement for external ground power sources; stability system provided through Vertol SAS; and provisions for utilizing collapsible fuel tanks to increase the fuel capacity by 2000 gallons. The complete helicopter is designed for operations in temperatures ranging from -25° F. to +125°F. DEVELOPMENT Date of contract . First flight Production status. June 1966 October 1966 Completed February 1968 CAPACITIES PERSONNEL Cargo compartment: Floor 226-1/2 sq ft Width ...... 7 ft, 6 in. Height 6 ft, 6 in. Length 30 ft, 2-1/2 in. Cargo ramp door: Length 6 ft, 6 in. Width 7 ft, 6 in. Entrance door: Height 5 ft, 2-1/2 in. Width 2 ft, 10-3/4 in. Height above ground (£door ... 3 ft, 6 in. Crew . Litters 4 24 or Troops ,.... 33 LB L.F. Empty *19,153 Basic *19,194 Design 33,000 3.00 Combat *21,734 3.00 Max alternate gross weight ... 40,000 2.54 Normal takeoff .. 33,000 3.00 Alternate takeoff. 40,000 2.54 Max landing 40,000 2.54 *For basic mission. FUEL AND OIL Fuel: Grade JP4 Spec MIL-T-5624 No. tanks: Fuselage (2) 621 gal Oil: Engine contained oil supply Spec Temps above 25°F MIL-L-23699 Temps below 25°F MIL-L-7808 Qty 7 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. 4 FM 101-20-1 ■EOR OFFICIAL USE ONLY 4 1-18. Loading and Performance - Typical Mission, CH-47B (Chinook) CONDITIONS Estimated gross weight Payload guaranteed (outbound) Payload guaranteed (inbound) Payload estimated (outbound) Payload estimated (inbound) Vmax at SL/STD, military power Max cruise speed at SL/STD, normal power, Guaranteed Estimated ! V-Cruise (best range) at SL/STD V-Cruise (best range) at 5000 F Max rate-of-climb at SL/STD military power Vertical rate-of-climb at SL/STD, maximum power Service ceiling at normal power Service ceiling, single engine at military power I Guaranteed Estimated Hover ceiling, OGE at STD temperature maximum power Hover ceiling, IGE at STD temperature maximum power, 10 ft wheel height . Radius of action Guaranteed Estimated Ferry range (lb) (lb) (lb) (lb) (lb) (kn) BASIC MISSION á/ I BASIC MISSION^ (DESIGN GW) II PRIMARY MISSION-^/ m EXTERNAL PAYLOAD MISSION^ IV MAXIMUM FERRY MISSION Id' V 30,900 33,000 40,000 40,000 40,000 6,000 3.000 7.000 3,500 168-2/ 9,000 4,500 165-2/ 15,900 7,935 145-â' 18,800 0 138-1/.2/ 1,075 145-2/ (kn). (kn). (kn). (kn). 166 145 138 150 163 144 134 142 134 114 132-1/ 100-3/ 100 142 134 114 (ft/min). 2,440-2/ 2,200-2/ 1,520-2/ 1,440 (ft/min), ... (ft). 2,300 2/ 1,800-2/ 18,000 16,200 60 9,550 60 8,950 1,520 60 9,550 • (ft). - (ft)- • (ft). . (ft). (nmi). (nmi). (nmi). 6,000 6,050 12,850 16,300 100 100 3,650 10,650 14,200 100 700-2/ 7,400 95 700-2/ 7,400 20 700-2/ 7,400 1,090 FM 101-20-1 1-40 —TOR Orr-KIAL USE "ONLY 1-18. Loading and Pertormance-Typical Mission, CH-47B (Chinook) (CONT). NOTES: •lAVith external payload equivalent to 26 ft. 2/drag area. ■transmission limit. ■^Mission cruise speed. The above table reflects performance capability only. For approved operational limits which consider all pertinent factors, see TM 55-1520-209-10. For Mission I the helicopter shall be capable of hovering at 6000 ft. for ten minutes at 95° F, OGE at the gross weight required for the accomplishment of Mission 1 (guaranteed). The Mission 1 gross weight includes an outbound payload of 6000 lb., return payload of 3000 lb., and fuel for a radius of 100 nmi. During Mission III the helicopter shall be capable of hovering out-of-ground effect at sea level standard, maximum power and at a gross weight of 39,500 pounds (guaranteed). 4 FM 101-20-1 FM 101-20-1 1-19. Performance Notes, CH-47B (Chinook). FORMULA: RADIUS MISSIONS I & II Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds to remote base, land, and unload cargo. Without refueling, 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 each warmup and takeoff, plus 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION III Warm up, take off, cruise out at long range speeds at sea level to remote base, land, and unload outbound 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 of normal power for each warmup and takeoff, plus 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION IV Warm up, take off, cruise out at 100 knots at sea level with external cargo to remote base, detach cargo, 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 reserve. FORMULA: RANGE MISSIONS I & II Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds until 90 percent of initial fuel is consumed, land, and unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of iriitial fuel for reserve. FORMULA: RANGE MISSION III Warm up, take off, cruise out at long range speeds at sea level until 90 percent of initial fuel is consumed, land, and unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of initial fuel for reserve. FORMULA: RANGE MISSION IV Warm up, take off, cruise out at 100 knots at sea level with external cargo until 10 minutes of cruise fuel remains, detach cargo, and land. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 minutes of cruise fuel for reserve. FORMULA: RANGE MISSION V Warm up, take off, climb on course to optimum cruise altitude at cruise speed, cruise out at long range speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of initial fuel for reserve. PERFORMANCE REFERENCES Vertol Report 114-P-J-602. Detail Specifications for The Model CH-47B Helicopter. Boeing-Vertol Report 114-AD-6Ó1. Estimated Performance Capability of CH-47B and CH-47C Heli- copters. Lycoming Model Specification 124.31, T55-L-7C Shaft Turbine Engine. FOR ornciAL use ONLY 1-41 «2 -TOR ornciAL y 1-20. CH-47C (Chinook) Characteristics. < ■» POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model .... (2)T55-L-11 Mfr Lycoming Engine spec No .. 124.27A Engine/Rotor gear ratio 64.05:1 ENGINE RATINGS SHP RPM ALT MIN Max ... 3750 16000 SL 10 Mil.... 3400 16000 SL 30 Nor ... 3000 15400 SL Cont. DIMENSIONS Rotor dia 60 ft Length: Rotors operating ... 99 ft Rotors folded . 51 ft Fuselage 51 ft Height (overall) . 18 ft, 7-3/4 in. Tread 10 ft, 6 in. Rotor ground clearance Static fwd .... 7 ft, 2-1/2 in. Idling fwd .... 10 ft, 11 in. Mfr’s Model: Vertol The principal mission of the CH47C is to provide air transportation for troops and cargo. The aircraft can also be utilized for rescue of personnel. The CH47C is a large tandem rotor helicopter with built-in accommodations for 24 litter patients and 2 attendants or 33 troops and troop commander. The helicopter is equipped with an unobstructed 30-foot long cargo compartment with straight-in rear loading and has a capacity of over 1450 cubic feet. Other features include an external cargó hook of 10-ton capacity which may be used for towing operations; an auxiliary power unit which powers the utility hydraulic system, thus eliminating the requirements for external ground power sources; stability system provided through Vertol SAS; and provisions for utilizing collapsible fuel tanks to increase the fuel capacity by 2000 gallons. The complete helicopter is designed for operations in temperatures ranging from -25°F to +125°F. DEVELOPMENT Date of contract Aircraft in production CLEARANCES Cargo Compartment: Floor 226-1/2 sq ft Width 7 ft, 6 in. Height 6 ft, 6 in. Length (floor) 30 ft, 2-1/2 in. Cargo Ramp Door: Length 6 ft, 6 in. Width 7 ft, 6 in. Entrance Door: Height 5 ft, 2-1/2 in. Width 2 ft, 10-3/4 in. Height above ground at door 3 ft, 6 in. June 1966 January 1969 PERSONNEL Crew 4 Troops 33 or Litters 24 LB L.F. Empty M 9,723 Basic M9,772 Design 33,000 3.00 Combat -523,886 3.00 Max alternate gross wt 46,000 Normal takeoff 33,000 Alternate takeoff 46,000 Max landing 46,000 For basic mission. FUEL AND OIL Fuel: Grade JP4 Spec MIL-T-5624 No. tanks: Fuselage main.. (2) 621 gal Fuselage aux... (4) 520 gal Qty . 1141 gal Oil: Engine contained oil supply Spec Temps above 25° F MIL-L-23699 Temps below 25° F MIL-L-7808 Qty 7 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. FM 101-20-1 fOR OFFICIAL USE ONLY 4 1-21. Loading and'Performance — Typical Mission, CH-47C (Chinook). CONDITIONS Gross weight (lb) Payload guaranteed (outbound) (lb) Payload guaranteed (inbound) (lb) Payload estimated (outbound) (lb) Payload estimated (inbound) (lb) Vmax at SL/STD, military power (kn) Max cruise speed at SL/STD normal power Guaranteed . (kn) Estimated (kn) V-Cruise (best range) at SL/STD (kn) V-Cruise (best range) at 5000 ft/STD (kn) Rate-of-climb at SL/STD military power (ft/min) Vertical rate-of-climb at SL/STD maximum power (ft/min) Service ceiling at normal power (ft) Service ceiling, STD temp, single engine at military power Guaranteed (ft) Estimated (ft) Hover ceiling, OGE at STD temperature, max power (ft) Hover ceiling IGE at STD temperature, maximum power, 10 ft. wheel height Radius of action, Guaranteed (nmi) Estimated (nmi) Ferry range (nmi) BASIC MISSION I 39,200?/ 12,000 6,000 13,300 6,650 156^ 156*/ 141 136 2,045^ 1,2202/ 10,200^ 4,000 4,5003' V 9,600 12,750 100 100 BASIC MISSION (DESIGN GW) II 33,000 7,350 3,675 1642/ 155 1642/ 140 138 2,8802/ 2,5852' 15,0005/ 9,5502/ 14,750 15,000 100 PRIMARY MISSION III 46,000 19,750 9,875 123^/ 123*/ 123*/ 111*/ 1,3802/ 8,000*/ 7,600 100 EXTERNAL PAYLOAD MISSION IV*/ 46,000 23,300 0 1002/ 1002/ 1002/ 1002/ 1,2602/ 8,000*/ 7,600 20 MAXIMUM FERRY MISSION V 46,000 123*/ 123*/ 123*/ 111*/ 1,3802/ 8,000*/ 7,600 1,226 M FM 101-20-1 FOR orneiAL UAE 1-21. Loading and Performance - Typical Mission, CH-47C (Chinook) (CONT). NOTES: U With External Payload Equivalent to 26 FT2 Drag Area (Troop Seats Incl.) y Hover Gross Weight at 6000 ft/95°F at 245 RPM. y Transmission Limit y Structural Envelope y Mission Cruise Speed (Outbound) y Current Hydraulic System limit y At 230 RPM y With 12000 LB Payload For Mission I the helicopter shall be capable of hovering at 6000 ft for 10 minutes at 95°F, OGE at gross weight required for accomplishment of Mission I (guaranteed). The Mission I gross weight includes an outbound payload of 12,000 lb., return payload of 6000 lb., and fuel for a radius of 100 nmi. During Mission HI the helicopter, shall be capable of hovering out-of-ground effect at SL/STD, maximum power, and a gross weight of 43,000 pounds (guaranteed). 1 4 FM 101-20-1 FM 101-20-1 1-22. Performance Notes, CH-47C (Chinook). FORMULA: RADIUS MISSIONS I & II Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds to remote base, land, and unload cargo. Without refueling, 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 each warmup and takeoff, plus 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION HI Warm up, take off, cruise out at long range speeds at sea level to remote base, land, and unload outbound 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 of normal power for each warmup and takeoff, plus 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION IV Warm up, take off, cruise out at 100 knots at sea level with external cargo to remote base, detach cargo, 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 reserve. FORMULA: RANGE MISSIONS I & II Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds until 90 percent of initial fuel is consumed, land, and unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of initial fuel for reserve. FORMULA: RANGE MISSION III Warm up, take off, cruise out at long range speeds at sea level until 90 percent of initial fuel is consumed, land, and unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of initial fuel for reserve. FORMULA: RANGE MISSION IV Warm up, take off, cruise out at 100 knots at sea level with- external cargo until 10 minutes of cruise fuel remains, detach cargo, and land. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 minutes of cruise fuel for reserve. FORMULA: RANGE MISSION V Warm up, take off, climb on course to optimum cruise altitude at cruise speed, and cruise out at long range speeds until 90 percent of initial fuel is con- sumed. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of initial fuel for reserve. PERFORMANCE REFERENCES Vertol Report 114-PJ-7003, Detail Specification for The CH-47C Helicopter. Lycoming Report 124.27, T55-L-11 Engine Speci- fication. Boeing-Vertol Report 114-AD-601, Estimated Performance Capabilities of CH-47B and CH-47C Heli- 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 25 FT 5 IN. © © TUI □hhñr4 19 FT 9 N 3 FT 1014 IN o 88 FT 6 IN 72 FT 16 FT 8 IN (IDLING) O 9 FT .4 IN. 1 70 FT 3 IN. 16 FT AV 000025 Figure 1-9. Principal dimensions, CH-54A and B (Tarhe) FOR orneiAL use OMLY. 1-47 jen 1VI3UJÖ aoj an 1-23. CH-54A (Tarhe) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model .... (2) JFTD12A-1 or (2) T73-P-1 Mfr Pratt & Whitney Spec 2424 Type Axial Weight 925 lb ENGINE RATINGS JFTD12A-1 SHP RPM MIN Military ... 4050 9000 30 Normal rated 3200 9000 Cont. T73-P-1 SHP RPM MIN Military ... 4500 9000 30 Normal rated .... 4000 9000 Cont. DIMENSIONS Main rotor dia 72 ft Length (rotors operating) 88 ft, 5 in. Length (fuselage) 70 ft, 3 in. Height (static) 25 ft, 5 in. Width (cockpit) 7 ft, 1 in. Tread 19 ft, 9 in. Gnd clearance: Main rotor (idling) .. 16 ft, 8 in. Tail rotor 9 ft, 4 in. Mfr’s Model: Sikorsky Missions that may be accomplished with the CH-54A helicopter include, movement of heavy outsized loads, towing of surface vehicles recovery of downed aircraft, and by use of detachable pods, transporta- tion of personnel, vehicles, and equipment. Since cargo is carried externally by a hoist, the ground crew may load or unload cargo while the helicopter hovers overhead, thereby extending the operational capability into areas unsuitable for landing. Flattopped fuselage serves as a work platform for servicing engines, rotor systems, and main components. This helicopter is of the all-metal, single main rotor type with one anti-torque tail rotor. The two gas turbine engines are located above the fuselage. The wheel-type alighting gear consists of two fixed main gear assemblies and a fixed nose gear assembly. The enclosed cockpit forming the nose of the helicopter carries basic accommodations for pilot, copilot, and an aft facing pilot. Conventional helicopter flight controls are provided for forward facing pilot seats. Automatic stabilization equipment is also provided. The aft facing pilot seat has cyclic and directional trim controls and a conventional collective pitch stick. Cargo handling provisions include a hydraulic powered hoist. Space and structural provisions are also made for a cargo sling or towing assembly. LB L.F. Empty 19,234 Basic 20,650 Gross (design) 38,000 2.50 Alternate takeoff gross .. *42,000 2.26 **Combat 22,024 •Limited by performance. **Basic mission. FUEL AND OIL Fuel: Grade JP-l,-4,or-5 Spec MIL-T-5624 Qty 1338 gal Oil: Spec MIL-L-23699 Qty 1.9 gal AVIONICS DEVELOPMENT Refer to chapter 2. First production acft delivered Nov 66 Production status out of production ARMAMENT FEATURES Six-blade main rotor. Rear facing seat for aft pilot/hoist operator. A four-point 20,000 lb capacity cargo hoist suspension system and a 15,000 lb capacity hoist. Four-blade, anti-torque tail rotor. PERSONNEL None. Crew (normal) Pilot Copilot .... Aft pilot . .. Passengers (with Pod Attached) Troops 45 or Litters 24 and Attendants 3 r c FM 101-20-1 EOR orntiAL use ONLY * 1-24- Loading and Performance - Typical Mission, CH-54A (Tarhe). CONDITIONS BASIC MISSION I 100 MILE RADIUS II ALTERNATE CARGO III FERRY RANGE IV TAKEOFF WEIGHT-^/ (lb) Fuel (lb) Payload (outbound) (lb) Payload (inbound) (lb) Takeoff power loading (lb/bhp) Disk loading (lb/sq ft) Vertical rate of climb at SL-1/ (fpm) Max rate of climb at SL-1/ (fpm) Max rate of climb (one engine out)J/ (fpm) Service ceiling (100 fpm)V ... (ft) Service ceiling (one engine out)-!/ (ft) Absolute hovering ceiling-1/ (ft) COMBAT RANGED (nmi) Average cruising speed (kn) Cruising altitude (ft) Total mission timé (hrs) 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-2/ (kn) Combat climb-1/ (fpm) Combat ceiling-1/ (ft) Service ceiling-1/ , (ft) Absolute hovering ceiling-1/ (ft) Max rate of climb at SL-1/ (fpm) Max speed/aItitude-2^ (kn) LANDING WEIGHT (lb) 38,000 8,700 11,522-^ None 7.04 9.33 1,400 1,714 773 12,100 6,800 234 95 SL 2.5 124 95 SL 2.6 33,688 22,024 SL 130-S/ 3.800 22,100 23,200 21,900 3.800 130/SL-iV 18,648 26,878 8.700 None 16,000-6/ 4.98 6.60 3.000 1.700 19,600 13,300 18,100 259 85 SL 3.05 100 85 SL 2.4 J/ 39,421 SL 90 1.340 6,600 8,900 4.000 1.340 90/SL 19,048 42,000 1)950 5/ 20,000-» None 6.37 10.32 400 1,320 400 6,000 2,300 6,000 42 95 SL 0.57 25 95 SL 0.53 26,478 8,700 None None 4.91 6.50 3,050 1,750 19,900 13,600 18,400 274 95 SL 2.9 18.648 SL 130Í/ 4,150 24.600 25.600 24,400 130/SL-S^ 18.648 to J/Takeoff power. -2/Normal power. -3/ Detailed description of RADIUS and RANGE Missions are given in paragraph 1-25. -4/Includes crew of 2 at 200 lb. each. -2/Carried by single-point or 4-point hoist system. •6/Carried by external sling (load drag-129 sq ft). -2/ Transfer of cargo while hovering. •8/Limited by attitude. Performance Basis: Data Source: Detail Spec for Army CH-54A. Performance is based on powers shown in paragraph 1-25. Data do not include ground effect. FM 101-20-1 hM 101-20-1 1-25. Performance Notes, CH-54A (Tarfie). FORMULA: RADIUS 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 recom- mended cruise speeds. Range-free allowances are 4 minutes at takeoff power for warmups and takeoffs and 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION II Warm up, take off, and cruise out at sea level to remote area 100 nautical miles distant at recommended cruise speeds. Hover out of ground effect for 5 min- utes to pick up cargo. At sea level, return to home base at recommended cruise speeds. Hover out of 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 hover- ing, and 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION III Warm up, take off, cruise out at 2000 feet at recommended cruise speeds to remote base and deposit cargo. Without refueling, return to home base at recommended cruise speeds. Range-free allowances are 2 minutes at takeoff power for warmups and takeoffs and 5 percent of initial fuel for reserve. FORMULA: RANGE MISSIONS IV 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 take- off power for warmup and takeoff and 10 percent of initial fuel for reserve. GENERAL DATA: a. Dual engine operation is limited to 6600 SHP by transmission time-power criteria; for single-engine operation, manufacturer’s guaranteed ratings in para- graph 1-23 are applicable. b. Powers used in performance calculations are as follows: ENGINE: (2) T73-P-1 SHP RPM CRITICAL ALTITUDE Takeoff: 6600 9000 14,000 Normal: 5400 9000 16,300- c. Maximum overbad takeoff weight is limited by the requirement that vertical climb at sea level of a standard day with takeoff power shall not bé less than 100 fpm. d. Maximum alternate takeoff gross weight is 42,000 pounds, at 6600 SHP (2 engines) for hover and takeoff to 20 knots. Above 20 knots, reduce to 6000 SHP. e. All takeoffs requiring more than 5400 SHP total power shall be logged as a 6600 SHP takeoff. Never exceed speed of 95 knots CAS from SL to 2000 feet density altitude at weights above 38,000 pounds. Above 2000 feet reduce airspeed 6 knots per 1000 feet to a maximum altitude of 6000 feet. 1-50 FOR OFFICIAL USE OHIV 1-51 •i 1-26. CH-54B (Tarhe) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model (2)T73-P-700 Mfr Pratt & Whitney Spec 2454 Type Axial Weight 935 lbs ENGINE RATINGS SHP RPM MIN Military 4800 9000 30 Normal rated 4430 9000 Cont. DIMENSIONS Main rotor dia 72 ft, 3 in. Length: Rotors operating 88 ft, 6 in. Fuselage 70 ft, 3 in. Height (static) 25 ft, 4 in. Width (cockpit) 7 ft, 1 in. Tread 19 ft, 9 in. Gnd clearance: Main rotor (idling) 15 ft, 8 in. Tail rotor 9 ft, 4 in. Mfr’s Model: Sikorsky S-64F Missions that may be accomplished with the CH-54B helicopter include movement of heavy outside loads, towing of surface vehicles, recovery of downed aircraft, and by use of detachable pads, transportation of personnel, vehicles and equipment. Since cargo is carried externally by a hoist, the ground crew may load or unload cargo while the heli- copter hovers overhead, thereby extending operational capability into areas unsuitable for landing. The flat top of the fuselage serves as a work platform for maintenance and servicing of the engines, rotor systems and other components of the power train system. The CH-548 is an all-metal single, main rotor type helicopter with one anti-torque tail rotor. It is powered by two gas turbine engines located above the fuselage. The wheel type landing gear consists of two fixed main gear assemblies and a single fixed, fully swiveling nose gear assembly. The fuselage and landing gear are constructed and assembled in a crane configuration. The inclosed cockpit forming the nose of the air- craft has basic accommodations for a pilot, co-pilot, aft-facing pilot and two observers. Conventional helicopter flight controls are provided for the pilot and co-pilot. The aft-facing pilot has electrically operated cyclic and directional trim controls and a conventional collective pitch control. An automatic flight control system (AFCS) is also provided. Cargo handling capabilities consist of a removable single point hydraulic powered four point load suspension system. Provisions are also made for installation of a towing kit. LB L.F. Empty 19,765 Basic 22,960 Gross (Design) ..47,000 2.0 Combat 24,060 FUEL AND OIL (USABLE) Fuel: Grade JP-4/5 Spec MIL-T-5624 Qty 1345 gal. (8743 lb. JP-4) OU: Spec MIL-L-23699 Qty 1.9 gal DEVELOPMENT Contract date 6 September 1968 First flight June 1969 AVIONICS FEATURES PERSONNEL Six-blade main rotor. Aft-facing pUot/hoist operator. 20.000 lb. capacity four point load suspension system. 25.000 lb. capacity single point hoist. Four-blade anti-torque taU rotor. Crew (normal) Pilot Co-pUot Aft-pilot Observers Passengers (with pod attached) Troops 45 Litters 24 Attendants 3 Refer to chapter 2. ARMAMENT None. FM 101-20-1 FM 101-20-1 1-27. Loading and Performance Data — Typical Mission, CH-54B (Tarhe) CONDITIONS FERRY MISSION II TAKEOFF WEIGHT 2/ (lb) Fuel (lb) Payload (outbound) 3/ (lb) Payload (inbound) ^ (lb) Takeoff Power Loading (lb/bhp) Disk Loading (lb/sq ft) Vertical Rate of Climb at SL d/ (fpm) Max Rate of Climb at SL 2/ (fpm) Max Rate of Climb (one engine out) 1/ (fpm) Service Ceiling (100 fpm) (ft) Service Ceiling (one engine out) d/ (ft) Absolute Hovering Ceiling d/ (ft) COMBAT RANGE (nmi) Average Cruising Speed (kn) Cruising Altitude (ft) Total Mission Time (hrs) 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) 32,323 8,743 4.08 7.95 2,718 1,704 13,000 232 95 SL 2.5 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 rF- fs» ^^*—11 «i;>iuii1 AV 000027 ¿ Figure 1-10. OH-6A (Cayuse) roji orneiAL use OHL*. 1-53 FM 101-20-1 m7 % S FTM/2IN 8 FT 6 IN O 4 FT 6-3/4 IN. —1 6 FT 9-1/4 IN. 26 FT4 IN. CE 3 g {-F- Tl 4 FT 3 IN. (DISK DIAMETER) AV 000028 30 FT 3-3/4 IN. O 1-54 Figure 1-11. Principal dimensions, 0H-6A (Cayuse) •Fou orriciAi use owtY 1-28. 0H-6A (Cayuse) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS r i No. & model .. . (1) T63-A-5A Mfr Allison Div of GMC Engine spec No.. 580F, Amend- ment 1, dtd 18 Aug 1965 ENGINE RATINGS Output Ratings SHP Takeoff & mil *317 Normal **270 Output speed SEC lb/ SHP- rpm HR Takeoff & mil .... 6000 0.697 Normal 6000 0.706 Above ratings developed on standard sea level static conditions. *Derated to 252.5 for 5 min **Derated to 214.5 DIMENSIONS Rotor dia 26 ft, 4 in. Length: Rotor operating .... 30 ft, 3-3/4 in. Rotor folded ... 23 ft Height 8 ft, 6 in. Tread 6 ft, 9-1/4 in. Mfr’s Model: Hughes 500 The principal missions of the OH-6A light observation helicopter are visual observation and target acquisition, reconnaissance, and command control. This helicopter is employed in support of combat companies, and will operate for extended periods of time with only such support as provided by one mechanic with handtools. Normal operation is limited to day or night visual flight conditions. The light observation helicopter is a single-lifting, 4-blade rotor, 4-place helicopter with a normal gross weight of 2400 lb or less. It is powered by a T63-A-5A free turbine engine with 317 SHP, derated to 252.5 SHP. It incorporates dual flight controls with the secondary cyclic control element easily removable. The flight instruments are limited to those required for day and night marginal visual conditions. The cargo area contains troop-type seats which are easily stowable when not in use. DEVELOPMENT Design competition initiated October 1960 Fhght evaluation completed June 1964 Production contract May 1965 First production acft deliveries September 1966 FEATURES Dual controls. Stowable troop seats. PERSONNEL Crew (normal) 1 Observer 2 Copilot 1 Empty Useful load Pilot Observers (2), Copilot (1) Cargo Fuel Gross (FAA certified) Max structure .1158 .1242 . 200 . 600 42 400 .2400 .2700 FUEL AND OIL Fuel: Spec, and Grade. MIL-T-5624(JP4/5) ASTM-1655,Type A or A1 MIL-F-46005A, Type 1 (C.I.T.E.) 61.5 gal Qty ... Oil: Spec .. No. tanks . MIL-L-7808/23699 . 1 Location. Engine section Qty ... 3 qt Main Transmission: Spec ... MIL-L-7808/23699 Qty 8.0 pt Tail Rotor Transmission: Spec MIL-L-7808/23699 Qty 0.5 pt AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. at cn FM 101-20-1 *1N0 3Sn IVPUJO MOTI 1-29. Loading and Performance - Typical Mission, OH-6A (Cayuse). BASIC MISSION I ALTERNATE 1A (CLEAN) II ALTERNATE 1A (ARMED) III FERRY RANGE IV HIGH SPEED SEA LEVEL MISSION V TAKEOFF WEIGHT (lb) Fuel (lb) Payload (not including pilot) (lb) Takeoff power loading (lb/bhp) Disk loading (lb/sq ft) Speed for Min. R/D (knots) Max rate of climb at sea level A/ (fpm) Speed for max R/C, sea level (knots) Time: Sea level to 5000 ft A/ (minutes) Time: Sea level to 10,000 ft-1/ (minutes) Service ceiling (100 fpm)-2^ (ft). Absolute hover ceiling A/ (ft) . COMBAT RANGE (nmi) . Average cruising speed (knots) . Cruising altitude (ft) . Total mission time (hr). COMBAT RADIUS (nmi). Average cruising speed (knots) . Cruising altitude (ft) . Mission time (hr) . COMBAT WEIGHT 3 (lb) . COMBAT ALTITUDE (ft) . Combat speed-2/ (knots). Combat climb ^ (fpm) . Service ceiling-2/. (ft). Absolute hover ceiling A/ (ft). Max rate of climb @ sea level A/ (fpm) . Speed for max R/C, sea level (knots) . Maximum speed-A/ (knots). Basic speed at 5000 ft -2/ (knots) . LIMIT FLIGHT LOAD FACTORS Maneuver Positive (g). Maneuver Negative (g). 2159 400 400 8.55 3.96 54.0 1925 56.0 2.5 5.3 18.400 11,200 370 104 12,200 3.6 185 104 12,200 3.6 1961 12,200 116 1860 20,950 14.400 2250 55 130 128 2.82 0.50 2400 400 637 4/ 9.50 4.41 54.0 1560 56.0 3.3 7.0 15.850 6,500 330 102 9600 3.3 165 102 9600 3.3 2207 9600 112 1680 17.850 10,500 1860 56 128 117 2.54 0.50 2400-6/ 400 400 9.50 4.41 54.0 1560 58.0 3.3 7.0 15.850 6,500 316 100 9500 3.2 158 100 9500 3.2 2208 9500 112 1680 17.850 10, 500 1860 56 128 117 2.54 0.50 2159 400 400 8.55 3.96 54.0 1925 56.0 2.5 5.3 18,400 11,200 294 129 SL 2.3 147 129 SL 2.3 1977 SL 130 2220 20,750 14,100 2220 55 130 128 2.82 0.50 A/pakeoff power Up to 5 minutes, -^faormal power. 3/For RADIUS mission: includes copilot at 200 lbs. i FM 101-20-1 row ornciAt-usc-ONuy r « 1-29. Loading and Performance - Typical Mission, OH-6A (Cayuse) (CONT). -^/includes 4 Mark XII torso tanks with an empty weight including trapped fuel of 19.5 lb/tank, -é/lncludes XM-27 or XM-27E-1 Armament Kit -2/ Limited by Vne Performance Basis: a. Army flight test YOH-6A extrapolated. b. All performance is out of ground effect and for standard atmospheric conditions. FM 101-20-1 FM 101-20-1 1-30. Performance Notes, OH-6A (Cayuse). FORMULA: RADIUS MISSION I, II, & III Warm up, take off, climb on course at military power to altitude for best range at average cruise weight. Cruise to remote base at speed for best range. Do not land. Return to home base. Range-free allow- ances are 2 minutes of normal power for warmup and 10 percent of initial fuel for reserves. FORMULA: RANGE MISSION I, II, & III Warm up, take off, and climb on course at mili- tary power to altitude for best range at average cruise weight. Cruise to remote base at speed for best range. Range-free allowances are 2 minutes of normal power for warmup and 10 percent of initial fuel for reserve. FORMULA: FERRY RANGE MISSION IV Warm up, take off, and climb on course at mili- tary power to 5,000 feet. At steady cruise, climb to stay at optimum altitude as weight decreases. Range- free allowance is 2 minutes of normal power for warmup. No reserve fuel allowance. FORMULA: RADIUS MISSION V Warm up, take off, and accelerate to maximum speed. Cruise at sea level at maximum speed, as limited by normal power or Vne to remote base. Do not land. Return to home base. Range-free allowances are 2 minutes of normal power for warmup and 10 percent of initial fuel for reserve. FORMULA: RANGE MISSION V Warm up, take off, and accelerate, to maximum speed. Cruise at sea level at maximum speed, as limited by normal rated power Vne to remote base. Range-free allowances are 2 minutes of normal power for warmup and 10 percent of initial fuel for reserve. GENERAL DATA For detailed planning refer to applicable technical manual. PERFORMANCE REFERENCE Hughes Tool Company-Standard Aircraft Char- acteristics (OH-6 A). 1-68 JJQR ornciAL use O-NLY» FM 101-20-1 mm 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 \AJ 6 FT 8-1/2 IN. 9 FT 3-1/2 IN. AV 000035 Figure 1-13. Principal dimensions, 0H-13H (Sioux) 1-60 FOR ornciAL usc-oNb* *fOR OFFTCfAL USE-ONIX » * 1-31. 0H-13H (Sioux) Characteristics. POWERPLANT MISSION AND DESCRIPTION No. & model (1) 0-435-23C Mfr Lycoming Engine spec No . . . 222IB Red. gear ratio . . . D.D. ENGINE RATINGS BHP RPM ALT MIN Takeoff 260 3400 SL 5 Normal 250 3200 SL Cont. Mfr’s Model: Bell47G-2 The principal missions of the OH-13H are observation, training, reconnaissance, and general utility. The OH-13H incorporates a 2-blade main rotor and a 2-blade tail rotor with a hydraulically boosted cyclic control system. The fuselage is an open-tube configuration with a bubble-type canopy enclosure. The landing gear is of the skid-type, with ground handling wheels attached. Provisions have been included for installation of a float-type landing gear. DIMENSIONS DEVELOPMENT Similar to the OH-13G except for the 0-435-23C engine in lieu of the 0-335-5D engine and metal rotor blades. The metal main rotor blades are of constant chord with an increased twist which increases responsiveness to collective control movements. Date of contract January 1956 First flight January 1956 First acceptance June 1956 Production completed June 1960 FEATURES PERSONNEL Rotor dia 35 ft, 1-1/2 in. Length: Rotors operating .... 41 ft, 4-3/4 in. Rotors static .. 41 ft, 4-3/4 in. Fuselage 31 ft, 4-3/4 in. Span (max lateral) 8 ft, 6-3/4 in. Height 9 ft, 5-1/2 in. Tread 7 ft, 6 in. Rotor gnd clearance (static) 8 ft, 8-1/2 in. (idling) 8 ft, 8-1/2 in. Float landing gear (prov). Winterization kit (prov). Dual controls (prov). Night flying equipment. M2 armament subsystem. Extended range torso tank (prov). Crew (normal) 1 Passengers/observers.... *2 or Litters (ext) 2 ♦Limited to 1 when dual controls are installed. WEIGHTS LB L.F. Empty (actual) 1850 Design 2450 2.5 Overload 2750 FUEL AND OIL Fuel: Grade 80/87 Spec MIL-G-5572 No. tanks 2 Location Fuselage Qty 41-1/2 gal Oil: Spec MIL-L-22851 No. tanks 1 Location Engine section Qty 3 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. FM 101-20-1 FM 101-20-1 8 FT 6-3/4 IN. 7 FT6 N. 8 FT 2-1/4 IN. 9 FT 7 N iS U± r 3 31 FT 7 IN. 43 FT 2-1/2 IN. AV 000037 31 FT 4 IN. 1/4 9 FT 5-1/2 IN. © 22 FT 6-1/2 IN Figure 1-14. Principal dimensions, 0H-13S (Sioux) 162 r-OR OFFICIAL USE ONLY «fOR orricTAL U 1-32. OH-13S (Sioux) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model . . (1) 0-435-25A Mfr Lycoming Engine spec No . 2309A Red. gear ratio . D.D. ENGINE RATINGS BHP RPM ALT MIN Takeoff 270 3200 SL 5 Normal 220 3200 SL Cont. DIMENSIONS Rotor dia 37 ft, 1-1/2 in. Length: Rotors operating . . 43 ft, 2-1/2 in. Rotors static . 43 ft, 2-1/2 in. Fuselage .... 31 ft, 8-1/2 in. Span (max lateral) 8 ft, 6-3/4 in. Height 9 ft, 5-1/2 in. Tread 7 ft, 6 in. Rotor gnd clearance (static) 8 ft, 8-1/2 inc (idling) 8 ft, 8-1/2 in. Mfr’s Model: Bell 47G3-B The principal missions of the OH-13S are observation, recon- naissance, and general utility. The OH-13S incorporates a 2-blade main rotor and a 2-blade tail rotor with a hydraulically boosted cyclic control system. The fuselage is an open-tube configuration with a bubble-type cockpit enclosure. The landing gear is of the skid-type, with ground hand- ling wheels attached. DEVELOPMENT Similar to the OH-13H except for the 0-435-25A turbocharged engine in lieu of the naturally aspirated 0-435-23C engine. Main rotor diameter has been increased 2 feet. Increased main rotor disk matches rotor with engine for higher altitude performance, .more maneuverability, and less susceptibility to turbulence. Gross weight of the OH-13S has been increased to 2850 lb and fuel capa- city increased to 57 gal. FEATURES Dual controls (prov). Night flying equipment. M2 armament subsystem. Extended range torso tank (prov). PERSONNEL Crew (normal) ...... Passengers/observers. . . *Limited to 1 when dual controls are installed. 1 *2 LB L.F. Empty (actual) .... 1980 Design 2850 2.5 FUEL AND OIL Fuel: Grade . . Spec . . . No. tanks Location Qty ... Oil: Spec . . . No. tanks Location Qty... • 100/130 MIL-G-5572 2 Fuselage 57 gal MIL-L-22851 1 Engine section 3-1/2 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. è FM 101-20-1 FM 101-20-1 1-33. Loading and Performance - Typical Mission, OH-13 (Sioux). MODEL H Mission weight (lb) Empty weight (lb) Useful load (lb) Fuel load (lb) Oil load (lb) Payload (lb) Max endurance at sea level (hr) Max range at 5000 ft (miles) . Max R/C (ft/min) HOGE ceiling (ft) HIGE ceiling (ft) Service ceiling (ft) Takeoff power (hp) Military power (hp) Cont power (hp) Turbocharged Speed-Vne(kn) Main rotor Disk area (sq ft) Blade area (sq ft) Disk load (psf) Blade load (psf) Solidity Tip speed (fps) (3200 rpm) Tail rotor Disk area (sq ft) Blade area (sq ft) Solidity Tip speed (fps) 2500 1630 870 174 15 681 2.6 172 801 500 3800 10,300 210 210 210 no 85 968.5 35.4 2.57 70.4 0.0370 654 26.8 2.4 0.0895 587 2500 1630 870 246 15 610 3.8 246 801 500 3800 10,300 210 210 210 no 87 968.5 35.4 2.57 70.4 0.0370 654 26.8 2.4 0.0895 587 275.0 1850 900 246 18 640 3.0 224 720 300 3400 8900 240 220 220 no 87 968.5 32.2 2.84 85.1 0.0332 654 26.8 2.4 0.0895 587 2850 1980 870 342 22 510 3.7 203 975 10,800 12,000+ 12,000+ 270 220 220 yes 91 1085 34.27 2.63 83.2 0.0314 695 26.8 2.4 0.0895 587 2950 2060 890 342 22 533 3.5 192 900 8400 12,000+ 12,000+ 270 220 220 yes 91 1085 34.27 2.72 86.1 0.0314 695 26.8 2.4 0.0895 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 9 FT 3-1/2 IN 10 FT 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. AV 000045 40 FT 8-1/2 IN. a 6 IN - 10 FT 1-1/2 IN n 3-1/2 IN 7 DEG 25 MIN I FT 3/4 IN. 27 FT 9-1/4 IN. 1-66 Figure 1-16. Principal dimensions, OH-:23D (Raven) roR ornciAL use ONLY* 6 FT 3-1/2 IN. •fOR ofPteiAL use OHL-Y t « á 1-34. OH-23D (Raven) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model ... (1) 0-435-23C Mfr Lycoming Engine spec No . 2221 Red. gear ratio .. D.D. Eng/maih rotor gearratio ■■■■8.66:1 ENGINE RATINGS BHP RPM ALT MIN Takeoff 255 3400 SL Cont *Normal 245 3200 SL Cont * METO power (max except takeoff) DIMENSIONS Rotor dia 35 ft, 5 in. Length: Rotors operating ... 40 ft, 8-1/2 in. Rotors static .. 40 ft, 8-1/2 in. Fuselage 27 ft, 9-1/2 in. Span (max lateral) 10 ft Height 10 ft, 1-1/2 in. Tread 7 ft, 6 in. Rotor gnd clearance: Static 6 ft, 4 in. Idling 9 ft, 3-1/2 in. Mfr’s Model: Hiller UH-12D The principal mission of the OH-23D is pilot training. Alternate missions are observation and medical evacuation. The OH-23D is a three-place, side-by-side helicopter with a single main rotor, an antitorque tail rotor, skid-type landing gear and two external litters. The control system consists of a single set of controls operated from the center seat, with provisions for a second set operated from the left seat. A trim system is incorporated with the cyclic control- stick for longitudinal and lateral trim. The fuselage is of all-metal, semimonocoque construction DEVELOPMENT LB L.F. Empty (actual) ... 1772 Basic (actual 1781 Design 2700 3.0 Combat *2350 Max takeoff (overload) +2700 3.0 Max takeoff (normal) +2700 3.0 Max landing +2700 4.0 * For basic mission. + Limited by structure. The OH-23D is similar to the OH-23C except for the V0435-23C engine, redesigned all-metal main and tail rotor blades, increase of design gross weight, and a new transmission and drive system. Date of contract September 1956 First flight October 1956 First acceptance December 1957 First service use January 1958 FUEL AND OIL FEATURES External litters. Rotormatic control. Ground handling wheels. Dual controls (prov). Transportable in C-124 and C-133 aircraft. Interchangeable main rotor and tail rotor blades. PERSONNEL Crew ... Passenger or Crew Student pilot or Crew Litters (ext) or Crew Litters (ext) Attendant . Fuel: Grade 115/145 Spec MIL-G-5572 No. tanks 1 Location Fuselage Qty 46 gal Oil: Grade 1100 Spec MIL-L-6082 No. tanks 1 Location Engine sump Qty 3-1/3 gal AVIONICS Refer to chapter 2. ARMAMENT 1Refer to chapter 2. >i FM 101-20-1 FOR OrriCIAL u 00 1-35. Loading and Performance - Typical Mission, OH-23D (Raven). CONDITIONS TAKEOFF WEIGHT Fuel at 6.0 Ib/gal (grade 115/145) Payload (outbound) Payload (inbound) Takeoff power loading Disk loading Autorotation speed (min R/D) Takeoff ground run at SL-1/ Takeoff to clear 50 ft-t/ Vertical rate of climb at SL-^. Max rate of climb at SL-^ Speed for max rate of climb at SIÀ-/ .... Time: SL to 5000 ft-1/ Service ceiling (100 fpm)-L/ Absolute hovering ceiling-1/ COMBAT RANGE-«/ ” Average cruising speed Cruising altitude Total mission time COMBAT RADIUS-2/ ] ‘ ] Average cruising speed Cruising altitude Total mission time FIRST LANDING WEIGHT-2/. Ground roll at SL (power on/autorotation) Total from 50 ft (power on/autorotation) COMBAT WEIGHT-2/ 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/ .... (lb) ... .... (lb) ... .... (lb) ... .... (lb) ... .(lb/bhp) ... (lb/sqft) ... . ...(kn) ... .... (ft) ... .... (ft) ... ...(fpm) ... .. (fpm) ... ... (kn) ... .. (min) ... .... (ft) ... ... (ft) ... . . (nmi) . . . .. (kn) ... .... (ft) ... 1 • • • (hr) ... .. (nmi) ... ...(kn) ... ... (ft) ... ... (hr) ... ... (lb) ... ... (ft) ... ... (ft) ... ... (lb) ... ... (ft) ... ...(kn) . (fpm) ... ... (ft) .. . ... (ft) . .. ... (ft) ... ... (ft) ... ... (ft) ... . (fpm) ... ♦ BASIC MISSION I 2478 4/ 280 None None 10.1 2.52 43 0 210 630 1250 41 5.0 16,100 4000 177 70 5000 2.6 82 70 5000 2.4 2350 0/368 0/474 2350 5000 70 955 12,100 17,600 5600 0 155 1380 EVACUATION II 2356-5/ 280 None 460 9.6 2.39 43 0 180 850 1320 42 4.2 16,700 5550 73 60 5000 2.5 2233 0/335 0/443 2693 5000 56 630 7050 12,430 1510 0 305 1000 FERRY RANGE III 2278-5/ 280 None None 9.3 2.31 43 0 130 980 1450 43 3.8 17,800 6500 184 70 5000 2.7 2026 5000 70 1330 16350 21,650 9700 1750 t FM 101-20-1 •fOR OrriCIAL UÍHi'OMlY- 1-35. Loading and Performance - Typical Mission, OH-23D (Raven) (CONT). CONDITIONS BASIC MISSION I EVACUATION II FERRY RANGE HI Speed for max rate of climb at SL -1/. (kn) Max speed at SL ft (kn) Basic speed at 5000 ft ^ (kn) LANDING WEIGHT-1/ (lb) Ground roll at SL (power on/autorotation) (ft) Total from 50 ft (power oiVautorotation) (ft) 41 83 2226 0/361 0/470 38 66 & 606/ 2564 0/388 0/453 41 83 77 á/ 2026 0/359 0/464 -1/METO power. •2/Detailed descriptions of RADIUS and RANGE missions are given in paragraph 1-36. ■2/For RADIUS mission if radius is shown. •^Includes crew of 2 at 400 lb. 2/Includes crew of 1 at 200 lb. ■£/Limited by stall. Performance Basis: a. Data source: Calculated data based on UH-12D flight tests. b. Performance is based on powers shown. c. Data do not include ground effect except for takeoff and landing. <o FM 101-20-1 FM 101-20-1 1-36. Performance Notes, OH-23D (Raven). FORMULA: RADIUS MISSION I 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 change in payload, warm up, take off, climb on course to 5000 feet at METO power, and return at long range speed. Range-free allowances are 10 minutes of METO power at sea level for warmups and takeoffs plus 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION II Warm up, take off, climb on course to 5000 feet at METO power, cruise out at long range speed to remote base, land, and load two litter patients. With- out refueling, warm up, take off, climb on course to 5000 feet at METO power, and return at long range speed. Range-free allowances are 10 minutes for warm- ups and takeoffs plus 10 percent of initial fuel for reserve. until 90 percent of initial fuel is consumed. Range-free allowances are 5 minutes of METO power at sea level for warmup and takeoff plus 10 percent of initial fuel for reserve. GENERAL NOTES Engine ratings shown are manufacturer’s guaran- teed ratings. METO values used in performance cal- culations are as follows: BHP FOR BHPFOR FORWARD ALT RPM HOVER FLIGHT SL 3200 246.0 248.0 5000 ft ... 3200 207.5 209.5 10,000 ft . 3200 174.0 176.0 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