FM 101-20 FIELD MANUAL

C&T- CONTINGENCY AND TRAINING SOURCE: AVSCOM (AMSAV-ERT) VI .A k. Army Aircraft Type Classification/Reclassification (TC/R) Schedule (ROTARY WING) TYPE, MODEL SERIES (TMS) CURRENT TYPE CLASS (CTC) PROPOSED TC/R PHASE IN (FY-QTR) PHASE OUT (FY-QTR) REPLACEMENT SYSTEM DA TARGET DATE AH-1G (TH-lG)j CH-47A CH-47B CH-47C CH-54A CH-54B OH-6A OH-13S OH-5 8 A UH-1B UH-1C UH-1D UH-1H UH-1M TH-13T TH-55A STD-A STD-A STD-B LP-U STD-A LP-U STD-A STD-B STD-A STD-B STD-B STD-B STD-A STD-B STD-A STD-A STD-B STD-A C & T C & T C & T OB OB C & T 73-2 72-4 73-2 73- 77-4 74- 74-3 73-3 CH-47C OH-58A UH-1M UH-1H SEPT 74 MAR 75 LP-U - LIMITED PRODUCTION-URGENT C & T - CONTINGENCY AND TRAINING OB - OBSOLETE SOURCE: AVSCOM (AMSAV-ERT) vii/(viii blank) r i f FM 101-20 CHAPTER 1 OPERATIONS Section I AIRCRAFT AUTHORIZATIONS Aircraft authorizations are listed by TOE unit authorizations. The current Major Item Analysis (Data Sheets) contains details concerning authorizations for specific areas or commands. « k A / ISJ 1-1. Basis of Issue - Aircraft Authorization per Unit. UNIT Armored Division HHB, Div Arty HHC, Armd Bde (3) Avn Co, Armd Div . Armd Cav Sqdn ... Air Cav Trp .... Maint Bn Acft Maint Co .. RECAP RECAP 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 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 Infantry Division (Reserve) HHB, Div Arty .' HHC, Inf Bde (3) Avn Bn, Inf Div Aslt Hel Co Avn GS Co Armd Cav Sqdn RECAPS RECAP TOE 17 6-302 1742 17-87 17-105 17-108 29-35 55424 37 6-302 17-105 17-108 29-25 55 424 3742 37-87 7 6- 3 742 7- 7 7-77 7-78 17-205 17-206 17-208 29-15 55-89 RECAP 7 6- 3 742 7- 7 7-77 7-78 17-105 TOTAL ACFT 64 (14) (12) (10) 27 (27) 1 0) 64 (14) 27 (27) 1 0) (12) (10) 160 (14) (18) 42 (29) (13) 85 (4) (81) 1 0) 102 (14) (18) 42 (29) (13) 27 LOH 42 (14) (12) (6) 10 (10) 42 (14) 10 (10) (12) (6) 62 (14) (12) 6 (6) 30 (30) 42 (14) (12) 6 (6) 10 AH-1G 9 (9) 9 (9) UH-1H 4 8 (8) 1 0) 33 6 (6) 27 (27) 15 6 (6) 13 8 (8) 1 (1) (4) 65 (6) 30 (23) (7) 28 (4) (24) 1 (1) CH47 45 (6) 30 (23) (7) 8 CH-54 OV-1B OV-1C U-21 U-10 FM 101-20 i 1-1. Basis of Issue — Aircraft Authorization per Unit (CONT). UNIT TOE TOTAL AC FT LOH AH-1G UH-1H CH47 CH-54 OV-1B OV-1C U-21 U-10 Air Cav Trp . Maint Bn ' Acft Maint Co RECAP 17-108 29-15 55-89 (27) 1 0) (10) (9) (8) 1 0) Airborne Division HHB, DivArty Air Cav Sqdn HHT, Air Cav Sqdn Air Cav Trp (3) .... Maint Bn Acft Maint Co .... HHC, Abn Div Bde (3) Avn Bn, Abn Div .... Aslt Hel Co RECAP RECAP RECAP RECAP Avn GS Co 57- 6-201 17-275 17-276 17-278 29-55 55-99 57-42 57-55 57-57 57-58 160 (14) 85 (4) (81) 1 0) (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) » w FM 101-20 1-1. Basis of Issue - Aircraft Authorization per Unit (CONT). UNIT 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 TOE 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 TOTAL ACFT 422 58 (19) 39 (3) (36) 226 50 (2) (48) (26) 150 (6) (24) (120) 12 (12) 85 (4) (81) 5 0) (4) (36) LOH 88 16 (16) 16 (10) 6 (6) 30 (30) 2 (2) (24) AH-1G UH-1H 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 (1) (2) (12) CH-47 48 CH 48 48 (48) 1-5 1-1 Basis of Issue - Aircraft Authorization per Unit (CONT). UNIT TOE TOTAL AC FT LOH AH-1G UH-1H CH47 CH-54 OV-1B OV-1C U-21 U-10 TRICAP Division .. .. HHB, Div Arty ... . HHC, Armd Bde (2) Avn Bn HHC, Avn Bn . .. Aslt Spt Hel Co Aslt Hel Co (3) . RECAP RECAP 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 RECAP RECAP RECAP RECAP 6- 3 17-42, 17-145 7- 7 1-258 7-357 17-87 17-135 17-108 17-285 17-286 17-287 17-175 17-196 17-198 29-315 55-424 67-62 347 (11) (8) 114 (17) (87) (10) 27 (27) 88 (7) (81) 85 (4) (81) (1) (1) (13) 98 (9) (8) 6 (6) 10 (10) 27 (27) 30 (30) (8) 99 18 (18) 9 (9) 45 (45) 27 (27) Separate Brigades HHC, Inf Bde (Sep) . HHC, Armd Bde (Sep) HHC, Mech Bde (Sep) HHC, Abn Bde (Sep) HHC, Light Inf Bde . 7-102 17-102 37-102 57-102 77-102 11 8 8 11 11 8 6 6 8 8 134 (2) 74 (1) (69) (4) 8 (8) 16 (7) (9) 28 (4) (24) (1) (1) (5) 3 2 2 3 3 16 16 (16) FM 101-20 à 1-1. Basis of Issue - Aircraft Authorization per Unit (CONT). UNIT TOE TOTAL ACFT LOH AH-1G UH-IH CH-47 CH-54 0V-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 10 13 32 4 5 2 17 9 2 (2) ■ 2 4 3 32 1 1 (1) 5 5 3 2 2 1 1 1 0) 16 1 2 1 5 FM 101-20 ( 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-2J 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 ... Med Det, Hel Ambulance (RC) Med Det, Hel Ambulance (RA) Corps Signal Bn HHC, Corps Sig Bn RECAP RECAP 5-101 5-111 5-112 5-201 5- 3 . 5-348 6401 .6-501 6- 5 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 0) 1 1 1 2 1 2 4 (4) 23 25 2 6 5 (5) FM 101-20 “ 1-1- Basis of Issue - Aircraft Authorization per Unit (COIMT). UNIT Signal Const Bn HHC, Sig Const Bn Army Area Sig Bn HHC Sig Army Area Bn Army Comd Sig Op Bn . HHC, Army Comd Sig Op Bn HHC Sig Bde, Army HHD, Sig Bn HHD, Sig Gp, Army Abn Corps, Sig Bn HHC, Sig Bn, Abn Corps HHC, USA Strategic Command Sig Co, Msgr Sig Radio Relay Co Avn Co, Atk Hel RECAP Signal Cable Const Bn HHC, Sig Cable Const Bn Army Comd Sig Rdo/Cable Bn .. HHC, Army Comd Sig Rdo/Cab Bn RECAP RECAP RECAP RECAP RECAP TOE 11-25 11-26 11-45 11-46 11-75 11-76 11-85 11-86 11-95 11-96 1-102 1-116 1-122 1-225 1-226 1-302 1-358 1-377 17-111 TOTA ACFT 4 (4) 3 (3) 3 (3) 1 0) 9 (9) 3 1 4 6 (6) 1 7 1 23 LOH 4 (4) 3 (3) 2 (2) 1 0) 2 (2) 1 2 1 (1) AH-1G UH-1H 21 1 0) 5 (5) 2 1 5 (5) 2 1 2 CH-47 CH-54 OV-1B OV-1C U-21 U-10 2 (2) 1 ( FM 101-20 < 1-1. Basis of Issue - Aircraft Authorization per Unit (CONT). UNIT TOE TOTAL AC FT LOH AH-lG UH-1H CH47 OV-1B OV-1C OV-1D U-21 U-10 MPBde.HHD MP Gp, HMD Scout Organization . MI Bn, Air Recon Spt (MIBARS) HHC, MI Bn, Air Recon Spt MI Co, Aerial Survl Avn Co, Survl Airplane ASA Gp Field Army ASA Co Div Spt ASA Avn Co (ELIS) . ASA Avn Co (EW) .. Msl Comd (Air Trans) ADA Bde, HHB ... RECAP Abn Spec Forces Gp Spec Forces Spt Bn HHC, Spec Forces Spt Bn RECAP RECAP 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 2 5 2 5 (5) 18 18 6 (6) (6) 12 3 15 9 4 3 4 (4) (4) 32/ 12 18 1 5 (5) 2 (2) (2) 15 9 (0 FM 101 20 1-10 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 0V-1C U-21 U-10 ADA Gp, HHB ADA Bde, HHB ADA Gp, HHB FASCOM, HHC SptBde, 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) .... HHC Div (Training) RECAP 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 97-4 2 2 2 3 2 1 1 2 1 1 1 10 2 3 2 (2) 3 2 2 2 (2) 2 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. Source: OACSFOR c FM 101-20 r FM 101-20 i 1-2. Test.and Test Support Aircraft. Requirements for test and test support aircraft are established as follows: a. All plans of test or research/development pro- grams 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, armament test bed) 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 neces- sary for missile chase at firing sites. c. In addition to aircraft originally assigned to support research, development, test, and evaluation, additional aircraft may be allocated, if required, in accordance with revised development/test programs. 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 capability 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 (Instal- lation 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 con- figuration or capability. (6) Series letter. A letter used to denote dif- ferences 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 1-11 l 1 FM 101-20 starting with the letter “A.” To avoid confusion, the letters “I” and “O” will not be usèd as series symbols. (Examples of series, symbol change would be installa- tion 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. Y U H - 1 A EXAMPLE: Status Prefix Symbol (Prototype)-^ Basic Mission Symbol (Utility Mission)-* Type Symbol (Helicopter Type) *■ Design Number (No. Type Helicopter)-*- Series Letter (1st Series)-* b. Status prefix symbols (classificátion letters) are as follows: LETTER TITLE DESCRIPTION G Permanently Grounded J Special Test, Temporary o N Special Test, Permanent . - f no' ■ X Experimental An aircraft permanently grounded, used for ground instruction and training. 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 not established as a standard vehicle for service use. i 1-12 / FM 101-20 LETTER TITLE DESCRIPTION Prototype 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 TITLE DESCRIPTION Attack R Cargo/ Transport Drone Reconnaissance 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 carrying cargo and/or passengers. Aircraft modified to be controlled from a point outside the aircraft. Aircraft modified and permanently equipped for photographic and/or electronic reconnaissance missions. U Trainer Utility Staff 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 DESCRIPTION Attack Aircraft designed to search out, attack, and destroy enemy land or sea targets, using conventional or special weapons. Also used for interdiction and close air support missions. 1-13 FM 101-20 LETTER TITLE H O R U 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. f- A complete listing of model designations assigned to military aircraft is contained in Army Pamphlet 700-6. 1-14 FM 101-20 Section II. 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 1973 Average number of aircraft 13 Annual flying hour rate 240 13 X 240 = 3120 hours Source: OACSFOR 1-4. Basic Annual Flying Hour Planning Factors 2/. 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 com- mand is published annually in Chapter V, Section 4 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 include: the projected aircraft inventory, mission requirements 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. 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 intended to meet combat requirements. In a peacetime situation or noncombat environment, utilization of these aircraft should be restricted to only that flying time necessary to provide adequate training for aviation units and other units which are supported by aviation units. (2) Indirect support aircraft are assigned to TDA units and must meet specific administrative, training, or RDTE requirements. Utilization of indirect support aircraft, except training and training support aircraft assigned to the aviation training base and RDTE aircraft, must meet or exceed the planning factors shown, to justify retention in the aircraft inventory at every level of command. Utilization of training base aircraft is determined by the student training rate approved or programmed for the year under consideration. Utilization of RDTE aircraft is basically determined by the requirements of the RDTE programs supported. 1-15 FM 101-20 1-5. Basic Annual Flying Hour Planning Factors-^ TYPE AIRCRAFT TOE PEACETIME OR NON-COMBAT ENVIRONMENT (WORLDWIDE) TOE ACTIVE COMBAT ENVIRONMENT INDIRECT SUPPORT AIRCRAFT ALL "RAFT (WORLDWIDE! ENVIRONMENT U-8/10 U-21 OV-1 T41 T-42 OH-6 OH-13 OH-58 UH-1 (Armed) UH-1B/C/M UH-1D/H AH-1G CH-47 CH-54 384 384 240 240 240 240 240 324 324 240 240 180 900 900 840 840 660 840 720 720 960 840 720 600 600 600 600 600 600 420 420 420 420 420 420 420 ■^All factors include operational readiness float aircraft. -V Does not include training and training support aircraft assigned to the training base -f Does not include RDTE (test and test support) aircraft. Source: OACSFOR 1-16 FM 101-20 Section III. ATTRITION 1-6. Attrition Factors, World-Wide Monthly Rates. AIRCRAFT SYSTEMS WORLD WIDE PEACETIME Airplane Helicopter Observation: 0-1 Combat Surveillance: OV-1 Utility: U-10 Fixed Wing Trainer: T-41 Instrument Trainer: T-42 Utility: U-8/RU-8 Utility: U-21/RU-21 Utility: U-9/RU-9 Instrument Trainer: TH-13 Primary Trainer: TH-55 Cargo Transport: CH-47 Cargo Transport: CH-54 Observation: OH-6 Observation: OH-13 Observation: OH-58 Utility: UH-1 Attack: AH-1G .0018 .0010 .0049* .0007* .0020* .0016 .0016 .0019* .0004* .0013* .0009 .0009 .0048 .0021 .0021 .0025 .0031 •Indicates attrition factors formulated as outlined in paragraph 1-7, Section III, Chapter 1 of this manual. Other attrition factors are DA directed. Source: AVSCOM (AMSAV-QMA) 1-17 FM 101-20 1-7. Formula for Calculating Monthly Attrition Factors. Example: Peacetime Attrition Factor. T-41 Aircraft. 1. Time Frame = 24 months. 2. Density (average) = 229. Note: To arrive at an average in use density the following category of aircraft were not considered. a. USARV inventory and losses. b. Maintenance trainers. c. stocks. d. 3. Attrition (losses) during time frame = 4. 4. Factor calculation: 4 attrition -f- 24 months = .1667 -f- 229 density = .0007 (monthly peacetime attrition factors). 5. Comments: Variations between prior and present factors are attributed mainly to the number of accident losses and to inventory increases or decreases during FY 71 thru 72. Depot inventory/war reserves/claimant Source: AVSCOM (AMSAV-QMA) 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. 1-18 FM 101-20 ‘AV 012001 Figure 1-1. AH-1G (Hueycobra) 1-19 FM 101-20 3FT 61N 10 FT 2 IN 4 FT 5IN 3FT F— 7 FT > 271N TL U. 44 FT 6FT 2IN -47 O/. 70 °* 10FT4IN 3.75 IN MAXIMUM LENGTH 13 FT 9 IN - 52 FT 11 IN ROTORS TURNING 14FT4IN 8FT6IN 10FT4IN 7 11FT7IN 2FT 4.25IN 9 FT 2 IN 45FT 2.21 N 7FT 10IN AV 012002 1FT 1.25IN Figure 1-2. Principal dimensions, AH-1G (Hueycobra) 1-20 1-21 ( 1-8. AH-1G/TH-1G* (Hueycobra) Characteristics. POWERPLANT No. and Model (1) T53-L-13B Mfr Lycoming Engine Spec. No 104.33 Type ; Free Power Turbine Reduction Gear Ratio 0.3115 TailPipe Fixed Area Augmentation None ENGINE RATINGS SEA LEVEL STD ESHP SHP NET JET THRUST RPM (LBS) MIN' Military 1450 1400 126 Normal 1296 1250 115 6300 30 6040 Cont. DIMENSIONS'. ‘ 10 Rotor dia :! 44 ft ; -I j ; * v * k Length: j Rotors ; > J, operating 053 ft. Rotors static : 53 ft. Fuselage . 45 ft, 2-1/4 in. Span (max lateral) 10. ft, 4.in. y Height í*l-ft, 7;in. ' Tread 7.ft\ ? Rotor gnd clear- k¿. . - anee (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, under day and0night VFI^ or IMC conditions within a temperature range of~25 F to +125 F. 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 emergency 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. Official operations and maintenance publications pertaining to the AH-1G are listed under TM 55-1520-221 series manuals. Other features include a crashworthy fuel system with closed circuit refueling capability, and a traetpr tailrotor system. DEVELOPMENT Date of contract ;i 4 April 1966 First flight (Similar aircraft) 7 September 1965 First aeft 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 .. : 258 gal Oil: Spec M1L-L-7808/ MIL-L-23699 No. tanks 1 Location Fuselage Qty 3.4 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. *TH-1G. Addition of Instructor Flight Controls and Instrument Panel converts the AH-1G to the TH-1G. FM 101-20 1-22 1-9. Loading and Performance - Typical Mission AH-1G (Hueycobra). CONDITIONS TAKEOFF WEIGHT (ib) Fuel at 6.5 Ibs/gal (Grade JP-4) (lb) Payload (Outbound) (jb) Payload (inbound) (]b) 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 (mjn) Time: SL to 10,000 ft (min) Service Ceiling (100 fpm) (ft) Absolute Hovering Ceiling (ft) MISSION I LIGHT SCOUT (4) (1)* (1)* (1)* O)* (2)* (2) (2) (2) (1) 9171 1572 1792 1384 8.34 6.04 65 105 267 1330 64 3.7 8.3 12450 COMBAT RANGE (nmi) (3) 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 (fo) (3) 141.1 133 6350/9800 10000 2.4 o MISSION II HEAVY SCOUT MISSION III HOG MISSION IV FERRY (CLEAN) 9500 1277 2416 1384 8.64 6.25 65 127 344 1230 65 4.0 9.2 11420 9500 1025 2668 604 8.64 6.25 65 127 344 1230 65 4.0 9.2 11420 7671 1672 192 192 6.97 5.05 65 0 0 1210 1860 60 2.7 5.6 18200 10650 M O 371.1 141 10000 10000 2.7 95.3 125 5350/7250 10000 1.8 70.1 125 5600/7200 10000 1.4 1-23 1-9. Loadingand 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) (2) Combat Climb (fpm) (2) Combat Ceiling (500 ft/min) (ft) (2) Service Ceiling (100 ft/min) (ft) (2) Absolute Hovering Ceiling (ft) (1) Takeoff Ground Run at SL (ft) (1) Takeoff to Clear 50 ft (ft) (1) Maximum Rate of Climb at SL (fpm) (2) Speed for Max R/C at SL (kn) (2) Max Speed at SL (kn) (2) Basic Speed at 5000 ft (kn) (2) LANDING WEIGHT . (lb) Ground Roll at SL (ft) Total from 50 ft ... (ft) 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 0 0 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 in 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 FM 101-20 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, warmup, 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 Auxiliary 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. 1-24 FM 101-20 AV 000016 Figure 1-3. CH47A, B, and C (Chinook), typical (minor differences apparent between A, B, and C models) 1-25 FM 101-20 — 12 FT 5 IN.-* mc -J 11 FT. 11 IN. 98 FT 3-1/4 IN. 18 FT- 6-1/2 IN 17 FT n IN STATIC G3 P 10 FT Q OOP II IN _L 7 FT 4-1/2 IN STATIC 2 DEG 5 FT 18 IN. MIN GND CLEARANCE AV 000017 * CONTROLS NEUTRAL Figure 1-4. Principal dimensions, CH47A (Chinook) 1-26 1-27 1-11. CH-47A (Chinook) Characteristics. POWERPLANT No. & model .... (2) T55-L-7 Mfr Lycoming Engine spec No . . T55-L-7/7B 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 MUitary 2650 15,750 SL 30 Normal 2400 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 lift, 11 in. •Main rotor gnd clearance: Idling (fwd) . . 10 ft, 11 in. (aft). . Static (fwd) . . (aft). . . 18 ft, 6-1/2 in. 7 ft, 8 in. 17 ft, 11 in. MISSION AND DESCRIPTION WEIGHTS 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 27 June 1960 First flight . . 6 September 1961 Production status Completed May 1967 CAPACITIES Cargo compartment: Floor Length Width Height Volume Forward door: Height Width 226-1/4 sq 30 ft, 2 in. 7 ft, 6 in. 6 ft, 6 in. 1487 cu ft 5 ft, 6 in. 3 ft PERSONNEL ft Crew (normal) Troops Litters 4 33 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 2.00 2.00 2.00 FUEL AND OIL Fuel: Grade JP-4 Spec M1L-T-5624 No. tanks: Nacelle .... (2) 621 gal (50 percent self- sealing) 630 gal (non- self-sealing) Oil: Spec Temps above -25* F Temps below -25* F No. tanks.... Location .... Qty MIL-L-23699 MIL-L-7808 2 Integral with engine 7 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. Cargo ramp door: Length 6 ft, 6 in. Width 7 ft, 6 in. FM 101-20 FM 101-20 1-12. 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 (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 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. 1-13. Performance Notes, CH-47A (Chinook). FORMULA: MISSION I r r 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 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. 1-28 FM 101-20 — 12 FT 5 IN. — H 10 FT 6 IN. c 2 E 99 FT 18 FT 7-13/16 IN. \ i . i IP. o -O Q Q 10 FT 11-1/16 IN. 2° 9 51 FT AV 000019 18 IN. MIN GND CLEARANCE Figure 1-5. Principal dimensions, CH-47B and C (Chinook) 1-29 52 FT oc-1 r 1-14. CH-47B (Chinook) Characteristics. POWERPLANT No. & Model .... (2) T55-L-7C Mfr Lycoming Engine spec No. 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 2400 15350 SL Cont DIMENSIONS Rotor dia 60 ft Length: Rotors operating... 98ft, 11 in. Rotors folded . 51ft Fuselage 51 ft Height (overall) . 18 ft, 7-3/4 in. Tread lift, 11 in. Rotor ground clearance: Static fwd .... 7 ft, 2-1/2 in. Idling fwd 10 ft, 11 in. MISSION AND DESCRIPTION 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 auxiliary 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 Cargo compartment: Floor 226-1/4 sq ft 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 . Litters 4 24 or Troops 33 WEIGHTS LB L.F. Empty *19,153 Basic *19,194 Design 33,000 3.00 Combat *21,734 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 JP-4 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 M1L-L-7808 Qty 7 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. 4 L FM 101-20 1-31 1-15. 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 *{'' ■ 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 : i1.. Ferry range ... (lb).. (lb). . (lb).. (lb).. (lb).. (kn).. . . (kn)... .. (kn)... .. (kn)... .. (kn). .. (ft/min)... (ft/min)... ... (ft). .. . (ft). . . . (ft)... . (ft)... . (ft)... (nmi)... (nmi)... (nmi)... BASIC MISSION 4/ I 30,900 6,000 3.000 7.000 3,500 168-2/ 166 145 138 2,440 2,3002/ 18,000 6,000 6,050 12,850 16,300 100 100 BASIC MISSION^ (DESIGN GW) II 33,000 9,000 4,500 165^ 150 163 144 134 2,2002/ 1,800-2/ 16,200 3,650 10,650 14,200 100 PRIMARY MISSION^/ HI 40,000 15,900 7,935 145 2/ 142 134 114 1,520-2/ 60 9,550 7002/ 7,400 95 EXTERNAL PAYLOAD MISSION-S' IV 132-1/ 1002/ 100 1,440 60 8,950 7002/ 7,400 20 MAXIMUM FERRY MISSION 19'' V 40,000 1,075 145-2/ 142 134 .114 1,520 60 ' 9,550 700-2' 7,400 1,090 40,000 18,800 0 138 2/>2/ k. FM 101-20 1-32 1-15. Loading and Performance - Typical Mission, CH-47B (Chinook) (CONT). NOTES: JAVith 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 I (guaranteed). The Mission I 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). j FM 101-20 FM 101-20 1-16. 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 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, 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-60I. Estimated Performance Capability of CH-47B and CH-47C Heli- copters. Lycoming Model Specification 124.31, T55-L-7C Shaft Turbine Engine. 1-33 1-34 1-17. CH-47C (Chinook) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model .... (2)T55-L-11A Mfr Lycoming Engine spec No .. 124.38 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 11 ft, 11 inr 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 tor 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 3U-toot long cargo compartment with straight-in rear loading and has a capacity of over 1450 cubic feet. Other features include an external cargo hook of 10-ton capacity which may be used for towing operations- an auxiliary power unit which powers the utility hydraulic system thus ’ e iminating 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 from ^^to+^^S01^681811601 f°r °perations in temperatures ranging DEVELOPMENT Date of contract... June 1966 Aircraft in production January 1969 CAPACITIES Cargo compartment: Floor 226-1/4 sq ft 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 . Troops 4 33 or Litters 24 i-iD Empty M 9,723 Basic M 9,772 Design 33,000 Combat 323,886 Max alternate gross wt 46,000 Normal takeoff 33,000 Alternate takeoff 46,000 Max landing 46,000 ■^For basic mission. 3.00 2.15 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 OU: 6 Engine contained oU SUDDIV 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 1-35 1-18. Loading and Performance — Typical Mission, CH-47C (Chinook). CONDITIONS BASIC MISSION I BASIC MISSION (DESIGN GW) II PRIMARY MISSION III EXTERNAL PAYLOAD MISSION IW MAXIMUM FERRY MISSION V 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) 39,200V 12,000 6,000 13,300 6,650 156^ 156*/ 141 136 2,045^ 1,2202/ 10,2004/ 4,000 4,500^ 5/ 9,600 12,750 100 100 33,000 7,350 3,675 1642/ 155 164?/ 140 138 2,8802/ 2,5852' 15,000$/ 9,5502/ 14,750 15,000 100 46,000 19,750 9,875 1234/ 1234/ 1234/ 1114/ 1,3802/ 8,0004/ 7,600 100 46,000 23,300 0 100$/ IOO5/ 100$/ loo57 1,2602/ 8,0004/ 7,600 20 46,000 1234/ 1234/ 1234/ 1114/ 1,3802/ 8,0004/ 7,600 1,226 FM 101-20 1-36 1-18. Loading and Performance - Typical Mission, CH-47C (Chinook) (COIMT). NOTES: U With External Payload Equivalent to 26 FT2 Drag Area (Troop Seats Incl.) ' ^ Hover Gross Weight at 6000 ft/95°F at 245 RPM. 2/ Transmission Limit. U Structural Envelope. y Mission Cruise Speed (Outbound). y Current Hydraulic System limit. V At 230 RPM. 5/ With 12000 LB Payload. For Mission I the helicopter shall be capable of hovering at 6000 ft for 10 minutes at 950F, 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 III 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). j FM 101-20 FM 101-20 1-19. 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 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 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-47-B-and CH-47C Heli- copters. - 1-37 FM 101-20 IS Av 000024 Figure 1-6. CK-54A and B (Tarhe), typical (minor differences apparent between A and B models) 1-38 A FM 101-20 25 FT 5 IN. ® © □LD HDC □ ft 19 FT 9 IN 3 FT IO'/J IN. o tan# 88 FT 6 IN. 72 FT =3E 6 FT 16 FT 8 IN. (IDLING) o 9 FT 4 IN. V 1 70 FT 3 IN. AV 000025 Figure 1-7. Principal dimensions, CH-54A and B (Tarhe) 1-39 Ê * Olrl 1-20. CH-54A (Tarhe) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model.... (2) T73-P-1 Mfr Pratt & Whitney Spec 2453 Type Axial Weight 9251b ENGINE RATINGS T73TM SHP RPM MIN MUitary ...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 S-64E 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. DEVELOPMENT LB L.F. Empty 19,219 Basic 21,479 Gross (design) 38,000 2.50 Alternate takeoff gross .. 42,000 2.26 Combat 22,764 FUEL AND OIL Fuel: Grade JP-4 or -5 Spec MIL-T-5624 Qty 1357 (8817 lb. JP-4) Oil: Spec MIL-L-23699 Qty 1.9 gal AVIONICS First production acft delivered Nov 66 Production status out of production FEATURES PERSONNEL Refer to chapter 2. ARMAMENT Six-blade main rotor. Rear facing seat for aft pilot/hoist operator A four-point 20,000 lb capacity load suspension system and a 20,000 lb capacity single point cargo hoist. Four-blade, anti-torque tail rotor. Crew (normal) 3 Pilot 1 Copilot 1 Aft pilot 1 Observers 2 None. Passengers (with Pod Attached) Troops 45 or Litters 24 and Attendants 3 FM 101-20 FM 101-20 1-21. Loading and Performance — Typical Mission, CH-54A (Tarhe). CONDITIONS SEA LEVEL STANDARD DAY MISSION I 4000 FOOT 95°F MISSION II FERRY MISSION III TAKEOFF WEIGHT J/ (lb) Fuel (lb) Payload (outbound)^ (lb) Payload (inbound)^ (lb) Takeoff power loading (lb/bhp) Disk loading (Ib/sq ft) Max rate of climb at SLjJ .. . (fpm) Max rate of climb (one engine out)JJ .. . (fpm) Service ceiling (100 fpm) (ft) Service ceiling (one engine out) (ft) RANGE (nmi) Average cruising speed (kn) Cruising altitude (ft) Mission time (hrs) RADIUS 4/ (nmi) Average cruising speed (kn) Cruising altitude (ft) Mission time (hrs) LANDING WEIGHT (lb) 42,000 2,705 17,818 18,803 6.36 10.31 1,350 450 8,000 2,000 20 80 2,000 0.5 21,725 42,000 2,695 17,828 19,055 6.36 10.31 1,350 450 8,000 2,000 20 80 4,000 0.6 21,715 30,300 8,817 4.59 7.44 2,625 1,525 12,000 241 100 SL 2.5 22,360 _I/Mihtary power. , ¿/Normal power. ¿/Carried by single-point hoist or four-point load suspension system. ¿/Detailed descriptions of RANGE and RADIUS missions are given in paragraph 1-22. _5/ Includes crew of 3 at 200 lb. each. Does not include any baggage, Engine Air Particle Separators (EAPS) at 300 lbs., or Passive Defense (Armor) Protection at 1285 lbs. Performance Basis: Data Source: Army CH-54A Model Spec. No. SER64509-2. TM 55-1520-217-10/1 Operator’s Manual (CH-54A). Performance is based on powers shown in paragraph 1-20. FORMULA: MISSION I (Sea Level, Standard Day) Warm up for 1 minute, take off at sea level, standard day conditions and climb at BROC. Cruise out 20 nautical miles at 2000 feet pressure altitude, standard day conditions, to a sea level standard day remote site. Hover for 5 minutes in ground effect while delivering and picking up cargo. Climb at BROC and cruise back at 2000 feet pressure altitude, standard day conditions, to a sea level standard day home base. Hover for 1 minute in ground effect and deposit cargo. Land with 10% initial fuel reserve. FORMULA: MISSION II (4000 foot, 95°F) Warm up for 1 minute, take off at sea level, standard day conditions and climb at BROC. Cruise out 20 nautical miles to a 4000 foot pressure altitude, 95°F day conditions remote site. Hover for 5 minutes in ground effect while delivering and picking up cargo. Cruise back to a sea level standard day home base. Hover for 1 minute in ground effect and deposit cargo. Land with 10% initial fuel reserve. FORMULA: MISSION III (Ferry) Warm up for 1 minute, take off at sea level standard day conditions and cruise out at best range speed until only reserve fuel remains. Land with 10% initial fuel reserve. 1-41 1 • *1, 1-42 1-22. CH-54B (Tarhe) Characteristics. WEIGHTS Mfr’s Model: Sikorsky S-64F No. & model (2)T73-P-700 Mfr Pratt & Whitney Spec 2456 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. MISSION AND DESCRIPTION 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 pods, trans- portation 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 operational capa- bility 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-54B is an all-metal single, main rotor type helicopter with one antitorque 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 enclosed cockpit forming the nose of the aircraft 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 tor installation of a towing kit. DEVELOPMENT First flight First production aircraft delivered Production status June 1969 .Dec 1969 Out of production FEATURES PERSONNEL Six-blade main rotor. Aft-facing pilot/hoist operator. 25.000 lb. capacity four point load suspension system. 25.000 lb. capacity single point hoist. Four-blade anti-torque tail rotor. Crew (normal) . . Pilot Co-pilot Aft-pilot Observers Passengers (with pod attached) Troops Litters 24 Attendants 3 3 1 1 1 2 45 LB L.F. Empty 19,864 Basic .'...22,124 Gross (Design) .. 47,000 2.0 Combat 23,409 FUEL AND OIL (USABLE) Fuel: Grade Jp.4/5 Spec MIL-T-5624 Qty 1357 gal. (8817 lb. JP4) Oil: Spec MIL-L-23699 Qfy 1.9 gal AVIONICS Refer to chapter 2. ARMAMENT None. FM 101-20 FM 101-20 1-23. Loading and Performance Data — Typical Mission, CH-54B (Tarhe) CONDITIONS SEA LEVEL STANDARD DAY MISSION I 4000 FOOT 95°F MISSION II FERRY MISSION HI TAKEOFF WEIGHTßJ (Ib) Fuel (lb) Payload (outbound) ^ (lb) Payload (inbound)^ (lb) Takeoff Power Loading (lb/bhp) Disk Loading (Ib/sq ft) Max Rate of Climb at SL jj (fpm) Max Rate of Climb (one engine out) J/ .. (fpm) Service Ceiling ( 100 fpm) 2/ (ft) Service Ceiling (one engine out) JJ (ft) RANGE (nmi) Average Cruising Speed (kn) . Cruising Altitude (ft) Mission Time (hrs) RADIUS (nmi) Average Cruising Speed (kn) Cruising Altitude (ft) Mission Time (hrs) LANDING WEIGHT (lb) 47.000 3,055 21,822 23.000 5.95 11.50 1,350 490 10.000 2,000 20 85 2,000 0.3 21,225 47.000 2,590 22,286 23,477 5.95 11.50 1,350 490 10.000 2,000 20 85 2,000 0.5 19,360 29,950 8,817 3.79 7.36 2,915 1,890 12,000 228 100 SL 2.3 22,005 ^Military power. 2/ Normal power. 3J Carried by single-point hoist or four-point load suspension system. 4j Detailed descriptions of RANGE and RADIUS Missions is given below. ßj Includes crew of 3 at 200 lbs. each. Does not include any baggage, Engine Air Particle Separators (EAPS) at 300 lbs., or Passive Defense (Armor) Protection at 1285 lbs. Data Source: Army CH-54B Model Spec No. SER 64279. TM 55-1520-217-10/2 Operator’s Manual (CH-54B). NOTE Performance is based on powers shown in paragraph 1-22. FORMULA: MISSION I (Sea Level, Standard Day) Warm up for 1 minute, take off at sea level, standard day conditions and climb at BROC. Cruise out 20 nautical miles at 2000 feet pressure altitude, standard day conditions, to a sea level standard day remote site. Hover for 5 minutes in ground effect while delivering and picking up cargo. Climb at BROC and cruise back at 2000 feet pressure altitude standard day conditions to a sea level standard day home base. Hover for 1 minute in ground effect and deposit cargo. Land with 10% initial fuel reserve. 1-43 FM 101-20 FORMULA: MISSION II (4000 foot, 95°F) Warm up for 1 minute, take off at sea level, standard day conditions and climb at BROC. Cruise out 20 nautical miles to a 4000 foot pressure altitude, 95°F day conditions remote site. Hover for 5 minutes in ground effect while delivering and picking up cargo. Cruise back to a sea level standard day home base. Hover for 1 minute in ground effect and deposit cargo. Land with 10% initial fuel reserve. FORMULA: MISSION III (Ferry) Warm up for 1 minute, take off at sea level standard day conditions and cruise out at best range speed until only reserve fuel remains. Land with 10% initial fuel reserve. FM 101-20 KWH V tOSS 'VW ‘ :f J ~ o o ‘ s. r~ -'- - ■ " ■ -.•*.« "-t',-*'.1 AV 057000 Figure 1-8. OH-6A (Cayuse) 1-45 FM 101-20 13— z_ L ¿i I 4 R3 IN. I DIAMETER 26 n 4 IN. DIAMETER 8 FT 4-5/16 IN O' f*4FT6-13/16 IN.— 6 FT 9-1/4 IN. 30 FT 3-3/4 IN ss a AV 057252 11-082C Figure 1-9. Principal dimensions, OH-6A (Cayuse) 1-46 1-47 1-24. OH-6 A (Cay use) Characteristics. POWERPLANT No. & model .. (1)T63-A-5A Mfr Detroit Diesel Allison Div of CMC Engine spec No. 580J, dtd 30 Sept. 1970 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 MISSION AND DESCRIPTION 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 Flight evaluation completed June 1964 Production contract May 1965 First production acft deliveries September 1966 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. FEATURES PERSONNEL Dual controls. Stowable troop seats. Crew (normal) Observer Copilot 1 2 1 WEIGHTS Empty 1158 Useful load 1242 Pilot 200 Observers (2), Copilot (1) Cargo Fuel Gross (FAA certified) Max structure FUEL AND OIL Fuel: Grade JP-4 Spec MIL-T-5624 Alternate ... JP-5, MIL-T-5624 Qty 61.5 gal Oil: Spec ...... MIL-L-23699 Alternate ... M1L-L-7808 No. tanks .. 1 Location ... Engine section Qty 3 qt Main Transmission: Spec MIL-L-23699 ■ Alternate ... MIL-L-7808 1 Qty 8.0 pt Tail Rotor Transmission: Spec MIL-L-23699 Alternate ... MIL-L-7808 Qty 0.5 pt AVIONICS Refer to chapter 2. ARMAMENT 600 42 400 2400 2700 Refer to chapter 2. FM 101-20 1-48 1-25. Loading and Performance - Typical Mission, OH-6 A (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). TaJceoff power loading (lb/bhp) . Disk loading (lb/sq ft) . Speed for Min. R/D (knots) . Max rate of climb at sea level i/ (fpm). Speed for max R/C, sea level J-f (knots). Time: Sea level to 5000 ftM (minutes) Time: Sea level to 10,000 ft J/ (minutes) Service ceiling (100 fpm)-2^ (ft) Absolute hover ceiling -V (ft) COMBAT RANGE (nmi) Average cruising speed Jl ^ (knots) Cruising altitude (ft) Total mission time (hr) COMBAT RADIUS (nmi) Average cruising speedJZ/8/ (knots) Cruising altitude . * (ft) Mission time (hr) COMBAT WEIGHT 3 (lb) COMBAT ALTITUDE (ft) Combat speed 3/ (knots) Combat climb-1/ (fpm) Service ceiling-2/ (ft) Absolute hover ceiling -f/ (ft) Max rate of climb @ sea level -1/ (fpm) Speed for max R¿C, sea level (knots) Maximum speed (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 55 104 117 2.82 0.50 2400 400 637 4/ 9.50 4.41 54.0 1560 58.0 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 56 102 113 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 56 100 110 2.54 0.50 2159 400 400 8.55 3.96 54.0 1925 56.0 2.5 5.3 18,400 11,200 294 130 SL 2.3 147 130 SL 2.3 1977 SL 130 2220 20,750 14,100 2220 55 130 2.82 0.50 JAakeoff power up to 5 minutes, -formal power. -^For RADIUS mission, includes copilot at 200 lbs. FM 101-20 1-49 5 i 1-25. Loading and Performance — Typical Mission, 0H-6A (Cayuse) (CONT). ^/includes 4 Mark XII torso tanks with an empty weight including trapped fuel of 19.5 Ib/tank. ^/includes XM-27 or XM-27E-1 Armament Kit. U Limited by Vne. Jl/At combat altitude and combat weight. Performance Basis: a. Army flight test YOH-6A extrapolated. b. All performance is out of ground effect and for standard atmospheric conditions. Speeds given are true airspeed. FM 101-20 FM 101-20 1-26. 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 (0H-6A). 1-50 FM 101-20 *423 mm AV 0000301 Figure 1-10. OH-13S (Sioux) Typical 1-51 , FM 101-20 B FT 6-3/4 IN. 7 FT 6 IN. 8 FT 2-1/4 IN. 9 FT 7 IN. sr _D 'Æi x □ 31 FT7 IN. -43 FT 2-1/2 IN. AV 000037 31 FT 4 IN 1/4 a 9 FT 5-1/2 IN © 22 FT 6-1/2 IN Figure 1-11. Principal dimensions, OH-13S (Sioux) 1-52 1-53 1-27. 0H-13S (Sioux) Characteristics. POWERPLANT No. & model . . (1) 0-435-25A Mfr Lycoming Engine spec No . 2354 L 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, 7 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. MISSION AND DESCRIPTION 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 ¿-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 WEIGHTS LB L.F. Empty (actual) .... 1980 Design 2850 2.5 FUEL AND OIL Fuel: Grade Spec No. tanks .... Location .... Qty Oil: Spec Temps above +30°F Type II Temp below +30°F Type III No. tanks .... Location .... Qty 115/145 MIL-G-5572 2 Fuselage 57 gal MIL-L-22851 MIL-L-22851 1 Engine section 3-1/2 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. FM 101-20 FM 101-20 1-28. Loading and Performance — Typical Mission, OH-13S (Sioux). Mission weight (lb) 2850 Empty weight (lb) 1980 Useful load (lb) 870 Fuel load (lb) 342 Oil load (lb) 22 Payload (lb) 510 Max endurance at sea level (hr) 3.7 Max range at 5000 ft (miles) 203 Max R/C (ft/min) 975 HOGE ceiling (ft) 10,800 HIGE ceiling (ft) 12,000+ Service ceiling (ft) 12,000+ Takeoff power (hp) 270 Military power (hp) 220 Cont power (hp) 220 Turbocharged yes Speed-Vne(kn) 91 Main rotor Disk area (sq ft) 1085 Blade area (sq ft) 34.27 Disk load (psf) • 2.63 Blade load (psf) 83.2 Solidity 0.0314 Tip speed (fps) (3200 rpm) 695 Tail rotor Disk area (sq ft) 26.8 Blade area (sq ft) 2.4 Solidity 0.0895 Tip speed (fps) 587 1-54 FM 101-20 .«ir* AV 000184 Figure 1-12. OH-58A, Light observation helicopter (Kiowa) 1-55 FM 101-20 6 FT 5.4 IN—■ 5 FT 10 IN BLADE DROOP STA 107.1 2° 7 20 FT 0.5 IN 9 FT 7.0 IN 5 FT 4.7 IN STATIC 1 FT 8.0 IN □00 = CG -®/? UNITED STATES ARMY STA 107.5 STATIC 6 FT 8.0 IN * 5 FT 2.0 IN 8 FT 1.3 IN 32 FT 1.9 IN TURNING 2 FT 3.3 IN ~T~- 8 FT 1.5 IN 6 FT 5.7 IN TURNING 7 FT 0.8 IN 40 FT 11.8 IN 12 FT 7.1 IN 1 FT 3 1.0 IN 1T3. AN 0 IN 6 FT 5.20 IN 35 FT 4 AV 000185 Figure 1-13. Principal dimensions, OH-58A (Kiowa) 1-56 1-57 * 1-29. OH-58A (Kiowa) Characteristics. POWERPLANT (1) T63-A-700 Allison Corp. 803-F Amend- ment 1 Axial-centrifugal compressor, free turbine 41 in. 15.5 in. 18 in. 135 lbs. 17.44:1 ENGINE RATINGS Standard Sea Level Static Conditions SHP RPM DUR Takeoff 317 6000 5 min. Normal 270 6000 Cont.* ♦Derated for Transmission DIMENSIONS No. & model .. Mfr Engine spec. no. Type Length Width Height Weight Helicopter rotor gear ratio .... Rotor dia 35 ft, 4 in. Length: Rotors operating .... 40 ft, 11.8 in. Blades removed 32 ft, 1.9 in. Height: To top of rotor fairing .. 9 ft, 7.0 in. Tread of skids .... 6 ft, 5.4 in. Main rotor: Disk area 979.8 sq. ft. Blade area 38.26 sq. ft. Tail rotor: DiSÍfareá 20.97"sq. ft. Blade area .... 2.26 sq. ft. MISSION AND DESCRIPTION Mfg’s Model: Bell 206A The missions for which the OH-58 A Helicopter are employed are: visual observation, target acquisition, reconnaissance, and command control. The helicopter is readily adaptable to utility tasks at the combat company level without use of special kits or special attach- ments. The helicopter is organic to division, brigade, battalion, or equivalent level, and capable of continuous daily operation in the forward area, with maximum availability to the tactical commander. Normal operation is limited to day and night visual and marginal visual flight conditions. The OH-58A can perform an unarmed observation mission with a 260-mile range or 3.0-hour endurance at a takeoff gross weight of 2760 pounds. It can perform a scout mission, armed with the XM-27E-1 weapon system and 2000 rounds of ammunition, with a range at 230 miles at a takeoff gross weight of 2967 pounds. •This helicopter is the single engine, single main rotor type. The fuselage is divided into three main sections; the forward section which provides the cabin and fuel cell enclosures as well as the pylon support, the intermediate section which supports the engine provides the equip- ment and electronics compartments, and the tail boom which supports the horizontal stabilizer, the vertical stabilizer, and the tail rotor. The free turbine engine is mounted aft of the main rotor horizontally on top of the fuselage. The landing gear is the shock-absorbing skid type. DEVELOPMENT First production article May 1969 FEATURES PERSONNEL Dual controls Rear seat palletized Gárgo "platform Crew (normal) Observer .... Two bladed seesaw rotor system Copilot 1 2 1 WEIGHTS LOADING LB L.F. Empty 1586 Empty (with armor) 1807.6 Basic 1766.2 3.50 Design 3000 2.50 Combat Unarmed mission .... 2842.7 2.64 Armed mission . 3000 2.50 Max structural . . 3000 2.50 FUEL AND OIL Fuel: Grade JP-4 Spec MIL-T-5624 Alternate ... JP-5, MIL-T-5624 Emergency .. MIL-G-5572 w/o TCP No. Tanks ... 1 Location .... Fuselage Qty 73 gal OU: Engine Spec MIL-L-23699 Alternate .. .MIL-L-7808 No. Tanks .. 1 Location ... Fuselage Transmission: Spec MIL-L-23699 Alternate ... MIL-L-7808 M/R Hub . . . 10-W-30 Spec MIL-L-2104 AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. f FM 101-20 FM 101-20 1-30. Loading and Performance — Typical Mission, OH-58A (Kiowa). CONDITIONS I BASIC MISSION (Unarmed Observation) II ALTERNATE (Armed Scout) TAKEOFF WEIGHT Fuel Payload Takeoff Power Loading Disk Loading Speed for Min. R/D Vertical Rate of Climb @ Sea Level 1/ Max Rate of climb @ Sea Level ^. Speed for Max R/C @ Sea Level . . . . Time Sea Level to 5000 ft. i/ Time Sea Level to 10,000 ft. -1/ Service Ceiling (100 fpm) 2/ Absolute Hover Ceiling -i/ COMBAT RANGE Average speed Cruising Altitude Total Mission Time COMBAT RADIUS Average Speed Cruising Altitude .... Total Mission Time .. . COMBAT WEIGHT 2/ .. . Combat Altitude .... Combat Speed Combat Climb -i/ Service Ceiling ^ .... Absolute Hover Ceiling Max R/C @ Sea Level -1/. . Speed for Max R/C .... Max Speed @ Sea Level . . Basic Speed @ 5000 ft. 2760 455 170 9.15 2.82 49 1780 48 3.5 7.5 19.000 8,000 260 102 14.000 2.98 147 102 14.000 2.98 2550 14.000 87 1090 21.000 10,600 1750 48 120 114 2967 4/ 428 298 9.84 3.03 49 1600 50 4.0 ■ 8.5 17.200 5,400 230 120 10,000 2.47 121 102 f 12.200 2.47 2770 10,000 99 1120 19,500 8000 1600 50 120 114 J/ Takeoff power up to 5 minutes. -2/Normal Power. ■2/ For Radius Mission. 4/lncludes XM-27E-1 Armament Kit. Performance Basis: Bell flight test 206A MOD. All performance is out of ground effect and for standard atmospheric conditions. 1-31. Performance Notes, OH-58A (Kiowa). RADIUS MISSION - I & II RANGE MISSION - I & II Warmup — Two minutes at normal power at sea level Takeoff and Climb — On course at military power to altitude for best range at average cruise weight Cruise — At speed for best range Reserve — 10% takeoff fuel 1-58 FM 101-20 f Wk ?mmc> Cf >9 moan ■as O AV;000055 Figure 1-14. UH-1B (Iroquois) 1-59 L_>> 52 FT 10-3/4 IN. 13 FT 2-1/2 IN. A 38 FT 5 IN. 42 R 8-1/2 IN. AV 000056 1-60 Figure 1-15. Principal dimensions, UH-1B (Iroquois) 14 FT 9 IN. 1-61 H-1B (Iroquois) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & Model .. (1) T-53-L-9A/-11/ -11B/-11C/-11D Mfr Lycoming Type Free power turbine Red. gear ratio . 0.3119 Tailpipe Fixed area Augmentation . None ENGINE RATINGS ' T53-L-9/11 Rating/SL SHP SFC Output RPM Max (takeoff) Mil NRP 960 900 825 0.694 6607 0.702 2207 0.715 6607 DIMENSIONS Rotor dia 44 ft Length: Rotors operating .... 53 ft , Rotors static ... 53 ft ' Fuselage 42 ft, 8-1/2 in. Span (max lateral) 9 ft, 3-1/2 in. Height 14 ft, 8-1/2 in. Tread 8 ft, 4-3/4 in. Rotor gnd clearance: (static) 7 ft, 4-3/4 in>, / Mfr’s Model: Bell 204 The principal missions of the UH-1B are the transport of personnel, special teams or crews, equipment, supplies, and to serve as an aerial weapons platform. Universal pylons are attachable to the aircraft to serve as mounts for weapons or external fuel tanks. It may also be used for medical evacuation and as an instrument trainer. These missions may be performed from prepared or unprepared takeoff and landing areas, under instrument operations including light icing, and day or night flight. The gas-turbine-powered UH-1B is of compact design having a low silhouette. The two-bladed main rotor and the two-bladed tail rotor are of all-metal construction. The fuselage is of semimonocoque construction, Sliding cabin doors allow straight-through loading. Litters may be loaded from either side or both sides simultaneously. The cargo floor is knee-high to facilitate loading. The copilot’s controls are removable, thus providing accomodations for a passenger in the copilot’s seat or, when the copilot’s seat is removed, additional cargo area. Some UH-lB’s, have complete provisions for a variable speed, power-driven hoist supported by a swing boom, capable of lifting personnel or up to 600 pounds of cargo. DEVELOPMENT Date of contract First flight First delivery . .. December 1960 March 1960 December 1961 CAPACITIES Inside clearance Cargo area: Length (overall).... 4 ft 1 Width (floor level).. 6 ft, 8-1/2 in. Height (max) 4 ft Copilot area: Length (overall) ... 4 ft, 7 in. Width (floor level).. 2 ft, 7 in. Height (max) 4 ft Main cargo door Height (max) 4 ft Width (max 4 ft Limit floor loads (overall) Cargo area 300 Ib/sq ft Copilot area 75 Ib/sq ft Usable cubage Cargo area 140 cu ft Copilot area 20 cu ft PERSONNEL Basic mission Crew (pilot and medical attendant) Litters Transport mission Crew Passengers Alternate Crew Passengers Trainer Crew (instructor & student) Ferry Crew 2 3 1 4 1 7 2 1 LB L.F. Empty (calculated).... 4557 Basic 4825 Design 6600 3.0 Combat *6596 3.0 Max takeoff 8500 2.3 Max landing 8500 *For basic mission. FUEL AND OIL Fuel: Grade JP-4/5 Spec MIL-T-5624 No. tanks: Fuselage (2) 165 gal Ferry (1) 350 gal Total qty 515 gal Oil: Spec M1L-L-7808 or MIL-L-23699 No. tanks 1 Location Fuselage Qty 3-1/4 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. FM 101-20 1-62 1-33. Loading and Performance - Typical Missions, UH-1B (Iroquois). CONDmONS TAKEOFF WEIGHT Fuel at 6.5 Ib/gal (grade JP-4) ... Payload (outbound) Payload (inbound) Takeoff power loading^. Disk loading Autorotation speed (min R/D) ... Takeoff ground run at SL i/ Takeoff to clear 50 ft 1/ Vertical rate of climb at SL ¿A ... Maximum rate of climb at SL 2/.. Speed for max R/C at SL Time: SL to 5000 ft 2/ Time: SL to 10,000 ft Service ceiling (100 fpm) 2/. Absolute hovering ceiling -Î/. COMBAT RANGE lû' Average cruise speed Initial cruising altitude Final cruising altitude Total mission time COMBAT RADIUS Average cruise speed Cruising altitude (outbound) Cruising altitude (inbound) Total mission time FIRST LANDING WEIGHT 2/ Ground roll at SL Total from 50 ft COMBAT WEIGHT 2/ Combat altitude Combat speed Combat climb 2/ Combat ceiling (500 ft/min) 2/, 12/ TRANSPORT .... (lb) .. ... (lb) • • ... (lb) .. ... (lb) .. (lb/bhp) .. (lb/sqft) .. .. (kn) .. ... (ft) .. ... (ft) .. . . (fpm) .. ... (fpm) .. .. (kn) .. .. (min) .. .. (min) .. ... (ft) .. . .. (ft) .. . .. (nmi) ... .. (kn) ... ... (ft) ... ... (ft) ... ... (hr) ... . (nmi) ... .. (kn) ... ... (ft) ... ... (ft) ... ... (hr) ... ... (lb) ... ... (ft) ... ... (ft) ... .. (lb) ... .. (ft) ... .. (kn) ... . (fpm) .. . .. (ft) .. . (CARGO OR PASSENGER) 6762 1073 800 0 7.04 4.45 57.0 0 0 1610 1910 57.0 2.7 6.0 18,000 11,500 230 106 2000-4000 2000-4000 2.25 112.7 106 2000-4000 2000-4000 2.22 6253 0 0 5453 2000-4000 106 2190 22,400 INSTRUMENT TRAINER ARMED 12/ 7500 1073 0 0 6.86 4.35 56.5 0 0 1780 2010 56.5 2.5 5.4 17,000 12.400 210 90 2000-4000 2000-4000 2.45 94.5 90 2000-4000 2000-4000 2.4 6145 0 0 7241 2000-4000 100 1590 15.400 60885/ 10733' 0 0 6.34 4.00 55.6 0 0 2330 2300 55.6 2.3 4.9 20,200 14,900 218 106 2000-4000 2000-4000 2.12 98.8 106 2000-4000 2000-4000 1.95 5631 0 0 5631 2000-4000 106 2050 21,400 FERRY 8390 5/ 3348^/ 0 0 8.74 5.52 60.1 0 0 1250 60.1 * 4.6 ....n/ 8800 695 103.4 2000-4000 2000-4000 6.88 5377 2000-4000 106 2220 22,600 « FM 101-20 1-63 I r 1-33. Loading and Performance — Typical Missions, UH-1B (Iroquois) (COIMT). CONDITIONS TRANSPORT (CARGO OR PASSENGER) ARMED 12/ INSTRUMENT TRAINER FERRY Service ceiling (100 ft/min)-2/ 12/ Absolute hovering ceiling2/’ 12/ . Takeoff ground run at SL-1/ Takeoff to clear 50 ft-!/ Maximum rate of-climb at SL-2/. . Speed for max R/G at SL Max speed at SL-â/ Basic speed at 5000 ft^/ LANDING WEIGHT-2/ Ground roll at SL ■ Total from 50 ft • (ft) ■ (ft) ■ (ft) ■ (ft) (fpm) • (kit) ■ (kn) • (kn) • (lb) . (ft) • (ft) 23,100 18,200 0 0 2740 54.2 120 117.5 4996 0 0 16,000 9000 0 0 1740 58.0 105 100 5639 0 0 22,200 16,800 0 0 2620 54.6 120 117.5 5188 0 0 23,250 18,500 0 0 2810 54.1 120 117.5 5377 0 0 i/Takeoff power. 2/Normal rated power. 2/For RADIUS mission if radius is shown. 2/ Vne limit. 2/ Includes crew of 2 at 400 lb. ^/Includes crew of 1 at 20Ö lb. 2/ Includes 1 x 350 gallon tanlç.i <• &/ Based on engine specificationjtakeoff shaft horsepower available. % Three 250-lb litter patients. 12/ Detailed descriptions of RADIUS and RANGE missions are given in paragraph 148. !i/ Above service ceiling. 12/ Armed W/M-21 subsystem. Performance Basis: a. Power required based on FTC-TDR-62-21, “YUH-1B Category II Performance Tests.” b. Power available and fuel flow are based on Lycoming Model Specification No. 104. 16-B. c. All data are at 6600 engine rpm. d. Except for Ferry Mission, data do not include ground effect. FM 101-20 FM 101-20 1-34. Performance Notes, UH-1B (Iroquois). FORMULA: RADIUS MISSION I Warm up, take off, climb on course to 2000-4000 feet at normal power, proceed at cruise speeds to remote base, and land. Without refueling, warm up, take off, climb on course to 2000-4000 feet at normal power, and return at cruise speeds. Range-free allowances are 4 minutes of normal power for warmups and takeoffs plus 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION II Warm up, take off, climb on course to 2000-4000 feet at normal power, proceed at cruise speeds to remote base, and land. Without refueling, warm up, take off, climb on course to 2000-4000 feet at normal power, and return at cruise speeds. Range-free allowances are 4 minutes of normal power for warmups and takeoffs plus 10 percent of initial fuel for reserve. FORMULA: RADIUS MISSION III Warm up, takeoff, climb on course to 2000-4000 feet at normal power, proceed at cruise speeds to remote base, and land. Without refueling, warm up, take off, climb on course to 2000-4000 feet at normal power, and return at cruise speed. Range-free allowances are 10 minutes of normal power for warmups and takeoffs plus 20 minutes at speeds for maximum endurance at sea level, plus 5 percent of initial fuel for reserve. FORMULA: RANGE MISSION II Warm up, take off, climb on course to 2000-4000 feet at normal power, and proceed at cruise speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal power for warmup and takeoff plus 10 percent of initial fuel for reserve. FORMULA: RANGE MISSION III Warm up, take off, climb on course to 2000-4000 feet initial altitude at normal power, proceed at cruise speeds to remote base, and land. Range-free allowances are 5 minutes of normal power for warmup and takeoff, plus 20 minutes at speeds for maximum endurance at sea level, plus 5 percent of initial fuel for reserve. FORMULA: RANGE MISSION IV Warm up, take off, climb on course to 2000-4000 feet initial altitude at normal power, maintain 30 feet per minute rate of climb to final altitude of 2000-4000 feet, and proceed at cruise speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal power for warmup and takeoff plus 10 percent of initial fuel for reserve. GENERAL NOTES a. Cruise speed as used above denotes airspeed for long-operation or maximum permissible speed, whichever is lower. b. Except for ferry mission takeoff, data do not include ground effect. FM 101-20 X* I AV 000058 Figure 1-16. UH-1C and M (Iroquois) 1-65 FM 101-20 r 9 FT 13/32 IN. ö A8 FT 4'/2 IN 7 FT 1 3/4 IN. í-=¡* 44 FT 52 FT 10% IN C=" 12 FT 8 IN FT 9 IN ftr AV 000059 Figure 1-17. Principal dimensions, UH-IC and M (Iroquois) i 1-67 « 1-35. UH-1C/M* (Iroquois) Characteristics. POWERPLANT MISSION AND DESCRIPTION WEIGHTS No. & model (1) T53-L-9A/ -11/-11B/-11C/ -1 ID Mfr Lycoming Engine spec No ... 104.22-B & .28 Type Free power turbine Red. gear ratio ... 0.3119 Tailpipe Fixed area Augmentation .... None ENGINE RATINGS T53-L-9/11 Rating/SL SHP Max (takeoff) 1100 Mil 1000 NRP ' 900 Output SFC RPM 0.682 6610 0.690 6610 0.702 6610 DIMENSIONS Rotor dia 44 ft Length: Rotors operating 53 ft Rotors static .... 53 ft Fuselage 42 ft, 8 in. Span (max lateral) 9 ft, 1/2 in. Height 14 ft, 9 in. Tread 8 ft, 4-1/2 in. Rotor gnd clearance: (static) 7 ft, 4-1/2 in. Mfr’s Model: Bell The principal missions of the UH-1C helicopter are transporting personnel, special teams or crews, equipment and supplies; medical evacuation; ambulance service; reconnaissance and security; point target and area fire by attachment of appropriate weapons; and instrument trainer. These missions may be performed from prepared or unprepared takeoff and landing areas, under instrument operations including light icing, and day or night flight. Navigation may be by dead reckoning or by use of radio aids. The main difference between the UH-1C and UH-1B is the main rotor system. The UH-1C has the 540 rotor system which has a flexure plate, hinge-half type hub and a wider cord blade. The 540 rotor system provides a more stable gun platform, higher maximum gross weight, and higher forward speed. Some UH-lC’s have complete provisions for a variable speed, power driven hoist supported by a swing boom, capable of lifting personnel or up to 600 pounds of cargo. DEVELOPMENT Contracting agency AVSCOM Delivery schedule ... ■. June 1965 thru November 1967 CAPACITIES *UH-1M incorporates the T53-L-13 engine. Cargo area: Length (overall) .. 4 ft Width (floor level) 6 ft. 8-1/2 in. Height (max) ... 4 ft Copilot area: Length (overall) .. 4 ft, 7 in. Width (floor level) 2 ft, 7 in. Height (max) .... 4 ft Main cargo door Height (max) 4 ft Weight (max) 4 ft Limit floor loads (overaU) Cargo area 300 Ib/sq ft Copilot area 75 Ib/sq ft Usable cubage Cargo area 140 cu ft Copilot area 20 cu ft PERSONNEL Basic mission Crew (pilot and medical attendant) 2 Litters 3 Transport mission Crew 1 Passengers 4 Alternate Crew 1 Passengers : - • • 7 Trainer Crew (instructor & student) 2 Ferry Crew 1 Empty Gross LB L.F. 4830 9500 FUEL AND OIL Fuel: Grade JP-4/5 Spec MIL-T-5624 Qty 242 gal OU: Spec MIL-L-7808 or MIL-L-23699 Qty-Engine .... 4 gal Qty-T ransmission and gear boxes 2.8 gal AVIONICS Refer to chapter 2. ARMAMENT Refer to chapter 2. FEATURES All metal, semi-rigid rotor, skid-type landing gear. FM 101-20 FM 101-20 ¡ 1-36. Performance — Typical Mission, UH-1C (Iroquois). Takeoff distance (ft) Rate of climb (fpm) Service ceiling (ft) Cruise speeds/ (kn) Max speed (kn) Range (nmi) Landing distance (ft) 0 2,420 21,100 92-110 140 300 0 -lAlormal rated power (6600 rpm) at sea level. 1-68 4 FM 101-20 1 S Av boooëv •&■■■:■{*,. «• '• ■ •*£,•*•-.•»' J- ■ "''*'***^F Figure 1-18. UH-1D and H (Iroquois) 1-69 k FM 101-20 7 FT8-7/16 IN. k—9 FT 13/32 IN.— - 8 FT 6-39/64 IN. - 9 FT 4 IN. 2 FT 6-1/2 IN. — _ 44 FT 10-3/32 IN 11 FT 8-21/32 IN 1 8 FT 6 IN 5$ □SE3 11 FT 9-3/4 IN □ □ □ CU 1 FT 3 IN. GROUND LINE DESIGN GROSS WEIGHT 40 FT 7-3/32 IN. 41 FT 11-5/32 IN. AV 000062 Figure 1-19. Principal dimensions, UH-1D and H (Iroquois) 1-70 4i 14 FT 5-1/2 IN. 1-71 C « 1-37. UH-1D (Iroquois) Characteristics. POWERPLANT No. & model .. (1)T53-L-9A/ -11/-11B/-11C/ -11D Mfr Lycoming Engine spec No 104.28 & .22-B Type Free power turbine Red. gear ratio . 0.312- Tailpipe Fixed area Augmentation . None ENGINE RATINGS T53-L-9/11 Output Rating SHP SFC RPM Max (takeoff) 1100 0.682 6610 Mil 1000 0.690 6610 NRP 900 0.702 '6610 DIMENSIONS, Rotor dia 48 ft Length: . J,, Rotors operating .... 57 ft, 1 in. t._ Rotors static .. 57 ft, 1 in., Fuselage 41 ft, 11-1/4 in. Span (max lateral) 9 ft, 4 in. Height 14 ft, 5-1/2 in. Tread 8 ft, 6-1/2 in. Gnd clearance r (static, against stops) 6 ft, 6 in. MISSION AND DESCRIPTION Mfr’s Model: BeU 205 The missions of the UH-1D include transportation of personnel, equipment and supplies, medical evacuation, delivery of protective fire by attachment of appropriate weapons, and instrument train- ing. These missions may be performed from prepared or unpre- pared takeoff and landing areas, under instrument operations including light icing, and day or night flight. - The UH-1D is of compact design having a low silhouette. The semimonocoque fuselage is of all-metal construction as are the tail rotor blades and the two main rotor blades. The sliding doors along each side of the cabin allow simplified straight-through loading from either side or both sides simulta- neously. This capability is especially useful while loading or un- loading litter patients. The knee-high cargo floor also contributes to loading ease. Since the copilot’s controls are removable, an extra passenger can be carried. If the copilot’s seat is also removed, an extra 8.75 square feet of cargo area is gained. Some UH-lD’s have complete provisions for a variable speed, power-driven hoist sup- ported by a swing boom, capable of lifting personnel or 600 pounds of ..cargo while hovering. Retrofit of a crashworthy fuel system with closed ■ circuit refueling capability is being accomplished on the UH-1D aircraft. CAPACITIES Inside clearance Cargo area: Length (overall) .. 7 ft, 8 in. Width (floor level) 8 ft Height (max) .... 4 ft, 1 in. Copilot area: Length (overall) .. 3 ft, 7 in. • Width 2 ft, 7 in. Height (max) .... 4 ft Main cargo door Height 4 ft Width (max) ... . .6 ft, 2-1/2 in Height above ground 2 ft Limit floor loads Cargo area 300 Ib/sq ft Copilot area 75 Ib/sq ft Usable cubage Capacity Cargo area 220 cu ft Copilot area 20 cu ft PERSONNEL Basic mission Crew 1 Passengers 4 Alternate Crew 1 Passengers 12 Litter evacuation Crew (pilot & medical attendant) 2 Litters 6 Cargo Crew 1 Ferry mission Crew (pilot & copilot) 2 WEIGHTS LB L.F