206 L4 Manufacturers Data

MANUFACTURER ’S DATA

BHT-206L4-MD-1

Section 1 SYSTEM DESCRIPTIO DESCRIPTION N

1 TABLE OF CONTENTS Paragraph Number

Subject Introduction....... Introduc tion........... ......... ......... ......... ......... ......... ......... ......... ......... ........ ......... ......... ......... ......... ......... ......... ......... ......... ........ ...... Helico Hel icopt pter er De Desc scrip ripti tion on — Ge Gene neral ral... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... .. Princip Prin cipal al Dim Dimensi ensions ons ..... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... ...... .. Location Loca tion Ref Referen erences.. ces...... ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ......... ......... ........ ........ ......... ......... .... Fusel Fus elage age St Stat ation ions s ... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Waterli Wat erlines..... nes.......... ......... ........ ......... ......... ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... .... Buttoc But tock k Lin Lines es ... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ..... Fusela Fus elage ge — Ge Gener neral al Ar Arran rangem gement... ent...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ... Fusel Fus elage age — For Forwa ward rd Se Sect ction. ion.... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Fusel Fus elage age — Int Interm ermedi ediat ate e Se Sect ction ion ... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... .. Fusel Fus elage age — Ta Tailb ilboom oom Sec Secti tion.... on....... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Cabin Cabi n Har Hard d Poin Points..... ts.......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ....... Cowlings...... Cowl ings.......... ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ....... ... Landing Land ing Gea Gear....... r........... ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ....... ... Ground Grou nd Hand Handling. ling..... ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ....... ... Crew and Pas Passeng senger er Sea Seating ting.... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ........ .... Seat Se at Re Rest strai raint nt Ass Assem embli blies... es...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... .. Instru Ins trume ment nt Pa Pane nell an and d Con Consol soles es ... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Pitot/St Pito t/Static atic Sys System tem .... ........ ........ ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ........ ...... .. Instrume Inst rument nt Sys System. tem..... ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ...... Flight Flig ht Inst Instrume ruments... nts....... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ...... .. Airspe Air speed ed Ind Indica icato torr ... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Altimet Alti meter er ..... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ......... ......... ........ ........ .... Turn Tur n an and d Sl Slip ip Ind Indic icat ator..... or........ ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... .. Verti Ve rtica call Sp Speed eed Ind Indica icato torr ... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Attit At titude ude Ind Indica icato torr ... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ..... Inclinom Incl inomete eter...... r.......... ......... ......... ........ ......... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ...... .. Direct Dir ection ional al Gy Gyro ro ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Navi Na vigat gation ion Ins Instru trume ment nts s .. ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ... Magne Ma gneti tic c Com Compas pass s ... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ... Propu Pr opulsi lsion on Ins Instru trume ments. nts.... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... ).... .... .... .... .... .... .... .... .... .... .... .... .... .... .... .... .... .... .. Dual Tachometer Turbine/Rotor (N2 /NR).. Gas Producer Indicator (N1)... )...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Torque Tor queme meter ter Ind Indica icator.... tor....... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Turbin Tur bine e Ou Outl tlet et Tem Temper perat ature ure Ind Indica icato tor.. r..... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ... Engine Eng ine Oil Pre Press ssure ure/T /Temp emper erat ature ure Ind Indica icato torr ... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ... Transm Tra nsmis issio sion n Oi Oill Pre Press ssure ure/T /Temp emper erat atur ure e Ind Indica icato tor.. r..... ..... ..... ...... ...... ..... ..... ...

1-1........... 1-1........... 1-2 12 ... ...... ...... ..... .. 1-3........... 1-3....... .... 1-4........... 1-4....... .... 1-414-A A ... ...... ..... 1-4-B 1-4 -B .... ....... ... 1-414-C C ... ...... ..... 1-5 15 ... ...... ...... ..... .. 1-5-A 15-A ... ...... ..... 1-515-B B ... ...... ..... 1-515-C C ... ...... ..... 1-6........... 1-6....... .... 1-7........... 1-7....... .... 1-8........... 1-8....... .... 1-9........... 1-9....... .... 1-10 1-1 0 .... ........ ...... 1-10 110-A -A ... ..... .. 1-11.... 111....... ..... .. 1-12 1-1 2 ..... ......... .... 1-13 1-1 3 .... ........ ...... 1-13-A 1-1 3-A .... ...... 1-13 113-A-A-1 1 .. 1-13-A 1-1 3-A-2 -2 .. 1-13 113-A-A-3 3 .. 1-13 113-A-A-4 4 .. 1-13 113-A -A-5.. -5.. 1-13-A 1-1 3-A-6 -6 .. 1-13113-AA-7 7 .. 1-13 113-B -B ... ..... .. 1-13 113-B-B-1 1 .. 1-13 113-C -C ... ..... .. 1-13 113-C -C--1.. 1-13 113-C-C-2 2 .. 1-13 113-C-C-3 3 .. 1-13 113-C-C-4 4 .. 1-13 113-C-C-5 5 .. 1-13 113-C-C-6 6 ..

Pa g e Number 1-7 1-7 17 1-10 1-1 0 1-10 1-1 0 1-10 110 1-10 1-1 0 1-10 110 1-10 110 1-10 110 1-15 115 1-16 116 1-16 1-1 6 1-16 1-1 6 1-17 1-1 7 1-17 1-1 7 1-17 1-1 7 1-17 117 1-18 118 1-18 1-1 8 1-18 1-1 8 1-18 1-1 8 1-18 118 1-23 1-2 3 1-23 123 1-23 123 1-23 123 1-24 1-2 4 1-24 124 1-24 124 1-24 124 1-24 124 1-25 125 1-25 125 1-26 126 1-26 126 1-26 126 1-27 127

23 OCT 2008— 2008—Rev. 1——— 1———1-1 1-1

The world's largest digital library

Try Scribd FREE for 30 days to access over 125 million titles without ads or interruptions! Start Free Trial Cancel Anytime.























BHT-206L4-MD-1


TABLE OF CONTENTS (CONT) Subject Fuel Pre Fuel Pressu ssure re/DC /DC Loa Loadme dmeter ter .. ..... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Fuell Qua Fue Quant ntit ity y Ind Indic icat ator... or...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... FUEL QTY switch (206L4 and 206L3+ IGW Upgrade Helicopters S/N S/ N 512 51244 44 and Sub Subse seque quent nt)... )...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... Miscel Mis cellan laneou eous s In Instr strum umen ents. ts.... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Outs Ou tside ide Air Te Temp mper eratu ature re Ga Gauge uge ... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Eight Ei ght Day Clo Clock ck or Dig Digita itall Chr Chrono onome mete terr ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... .... .. Hourmet Hour meter..... er......... ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ...... .. Cauti Ca ution on an and d War Warnin ning g Sy Syst stem... em...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Engine Engi ne Out.. Out...... ......... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ....... ... Rotor Rot or Low RP RPM M ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Warni Wa rning ng Aud Audio io Mut Mute e Sy Syste stem m ... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... .. Battery Bat tery Hot .... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ...... .. Battery Bat tery Rel Relay....... ay........... ......... ......... ........ ......... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ....... ... Generato Gene ratorr Fail Failure..... ure......... ........ ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ......... ......... ........ ....... ... Transm Tra nsmiss issio ion n Oi Oill Pre Press ssur ure e ... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Trans Tra nsmis missi sion on Oi Oill Tem Temper perat ature.. ure..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Engine Eng ine Chi Chip p De Detec tecto torr ... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Transm Tra nsmiss ission ion Chi Chip p Det Detec ecto tor..... r........ ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ... Taill Rot Tai Rotor or Ge Gear arbox box Chi Chip p De Detec tecto tor..... r........ ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ... Fuel Low .... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ......... ......... ...... Fuell Boo Fue Boost st Pum Pumps ps ... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Fuel Filt Filter... er....... ........ ........ ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ...... Baggag Bag gage e Doo Doorr ... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Litter Litt er Door .... ........ ......... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ...... Spare Spar e Caut Caution ion Ligh Light..... t......... ......... ......... ........ ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ........ ........ ...... .. Fuel Valv Valve e Swi Switch tch .... ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ...... .. Misce Mis cella llaneo neous us Con Contro troll Pa Panel.. nel..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Parti Par ticle cle Sep Separ arato atorr Pur Purge ge Sw Switc itch h ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... .... .. Cautio Cau tion n and War Warnin ning g Pa Pane nell Bri Bright ght/Di /Dim m Sw Switc itch h ... ...... ...... ...... ...... ..... ..... ...... ...... ..... .... .. Engine Eng ine Ant Antii-ic icing ing Sw Switc itch... h...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Hydra Hyd rauli ulic c Sy Syste stem m Sw Switc itch h ... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... .. Overhe Ove rhead ad Cons Console........ ole............ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ...... .. Gener Ge nerato atorr Sw Swit itch ch .. ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... .. Battery Bat tery Swi Switch..... tch......... ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ .... Defog Def og Bl Blow ower er Swi Switc tch h ... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... .. Pitott Hea Pito Heatt Swi Switch tch .... ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ..... Positi Pos ition on Lig Light ht Sw Swit itch ch ... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Anti-co Anti -collis llision ion Ligh Lightt Swit Switch.... ch........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ...... Instru Ins trume ment nt Lig Light ht Rhe Rheos ostat.... tat....... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... ..

Paragraph Number

Page Number

1-13-C1-13 -C-7.. 7.. 1-13 113-C-C-8.. 8..

1-27 1-27 1-28 128

1-13-C1-13 -C-9.. 9.. 1-13 113-D..... -D..... 1-13 113-D-D-1.. 1.. 1-13113-DD-2.. 2.. 1-13-D1-1 3-D-3.. 3.. 1-14.. 114..... ...... ..... 1-14-A..... 1-1 4-A..... 1-14 114-B..... -B..... 1-14 114-C..... -C..... 1-14-D..... 1-1 4-D..... 1-14-E 1-1 4-E .... ...... 1-14-F 1-1 4-F ..... 1-14 114-G... -G..... .. 1-14114-H H ... ..... .. 1-14 114-I. -I.... ...... ... 1-14 114-J. -J.... ..... .. 1-14 114-K..... -K..... 1-14-L 1-1 4-L .... ...... 1-14 114-M. -M.... ..... 1-14-N..... 1-1 4-N..... 1-14 114-O... -O..... .. 1-14-P 1-1 4-P .... ...... 1-14-Q.... 1-1 4-Q...... 1-15...... 1-1 5......... ... 1-16.. 116..... ...... ..... 1-16 116-A..... -A..... 1-16 116-B..... -B..... 1-16 116-C..... -C..... 1-16 116-D..... -D..... 1-17...... 1-1 7......... ... 1-17117-A A ... ..... .. 1-17-B..... 1-1 7-B..... 1-17 117-C.... -C...... 1-17-D..... 1-1 7-D..... 1-17 117-E -E ... ..... .. 1-17-F 1-1 7-F .... ...... 1-17 117-G.. -G..... ...

1-28 1-28 1-28 128 1-28 128 1-28 128 1-29 1-2 9 1-29 129 1-29 1-2 9 1-29 129 1-29 129 1-30 1-3 0 1-30 1-3 0 1-30 1-3 0 1-30 130 1-30 130 1-30 130 1-30 130 1-30 130 1-31 1-3 1 1-31 131 1-31 1-3 1 1-31 131 1-31 1-3 1 1-31 1-3 1 1-32 1-3 2 1-32 132 1-32 132 1-32 132 1-32 132 1-32 132 1-32 1-3 2 1-32 132 1-33 1-3 3 1-33 133 1-33 1-3 3 1-33 133 1-33 1-3 3 1-33 133
























BHT-206L4-MD-1

TABLE OF CONTENTS (CONT) Subject Governor Gover nor RP RPM M Inc Incre reas ase/ e/Dec Decrea rease se Swi Switc tch... h...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ..... Landi La nding ng Lig Light ht Sw Swit itch.. ch..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... .. Start Sta rt Swi Switch tch ..... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ......... ......... ........ ........ .... Rotorr Brak Roto Brake e .... ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ .... Ventilat Vent ilation ion Sys System.... tem........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ...... .. Defog Def og Sys System........ tem............ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ....... Porta Por table ble Fir Fire e Ex Exti tingu nguis isher her ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Elec El ectri trica call Sy Syste stem m — Ge Gene neral ral ... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ... Batter Bat tery y Sys System..... tem......... ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ...... .. Exte Ex terna rnall Po Powe werr Sy Syst stem em .. ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ... Batter Bat tery y Char Charging..... ging.......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ .... Gene Ge nera rator tor Sy Syst stem em ... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ..... Starter Sta rter/Ign /Ignite iterr Sys System.. tem...... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ........ .... Circu Ci rcuit it Bre Break akers ers an and d Sw Swit itche ches s ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Battery Bat tery Swi Switch tch .... ........ ......... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ .... Gener Ge nerat ator or Sw Swit itch ch ... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... .. Gener Ge nerat ator or Fi Field eld and Res Reset et Ci Circu rcuit it Bre Breake akers rs... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ... Start Sta rt Swit Switch ch .... ........ ........ ......... ......... ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ .... Elec El ectr trica icall Sy Syst stem em Ind Indic icato ators rs ... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ... Elec El ectr trica icall Sy Syst stem em Em Emer ergen gencie cies s an and d Mal Malfun functi ctions ons ... ...... ...... ..... ..... ...... ...... ...... ..... .. Batter Bat tery y Ho Hott Wa Warni rning ng Lig Light ht... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Batter Bat tery y Re Rela lay y Cau Cautio tion n Lig Light.... ht....... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Gener Ge nerat ator or Fa Fail il Ca Caut ution ion Lig Light ht ... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ..... Elec El ectr trica icall Sy Syst stem em — Com Comple plete te Ele Elect ctric rical al Fa Fail ilure ure .. ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Fuel Sys System tem — Gen General... eral....... ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ...... .. Fuell Sy Fue Syste stem m Cir Circu cula latio tion n ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ... Fuell Bur Fue Burn n Se Seque quenc nce e ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ..... Fuel Cell Cells s ..... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ....... ... Fuell Boo Fue Boost st Pu Pumps mps ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... .. Fuel Mani Manifold..... fold......... ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ....... Fuel Pres Pressure sure Tran Transduc sducer.... er........ ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ....... ... Fuel Valv Valve e .... ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ........ .... Airfr Ai rfram ame e Fue Fuell Fil Filte terr ... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ... In-Li In -Line ne Fue Fuell Fil Filte ters rs an and d InIn-Lin Line e Che Check ck Va Valve lves... s...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Fuel Flow Swit Switche ches s ..... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ........ .... Duall El Dua Elem emen entt Eje Eject ctor or Pu Pump mp ... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Fuel Low Leve Levell Det Detect ector.... or........ ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ......... ......... ........ ...... .. Fuell Sum Fue Sump p Dra Drain in Va Valv lves..... es........ ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Fuell Qua Fue Quanti ntity ty Tra Trans nsmi mitt tter er ... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ... Fuell Sy Fue Syste stem m — Em Emerg ergen ency cy Op Oper erati ation.... on....... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...

Paragraph Number 1-20-A 1-20 -A ... ..... .. 1-20 120-B -B ... ..... .. 1-20-C 1-2 0-C ..... 1-21 1-2 1 ..... ......... .... 1-22 1-2 2 ..... ......... .... 1-23 1-2 3 .... ........ ...... 1-24.... 124....... ..... .. 1-25.... 125....... ..... .. 1-25-A 1-2 5-A ..... 1-25 125-B -B ... ..... .. 1-25-C 1-2 5-C .... ...... 1-25 125-D -D ... ..... .. 1-25-E 1-2 5-E .... ...... 1-25 125-F. -F.... ..... .. 1-25-F1-2 5-F-1 1 .. 1-25 125-F-F-2 2 .. 1-25 125-F-F-3 3 .. 1-25-F1-2 5-F-4 4 .. 1-25 125-G.... -G...... 1-25 125-H -H ... ..... .. 1-25 125-H-H-1 1 .. 1-25 125-H-H-2 2 .. 1-25 125-H -H-3.. -3.. 1-25 125-I... -I...... ..... 1-26 1-2 6 .... ........ ...... 1-26 126-A -A ... ..... .. 1-26 126-B -B ... ..... .. 1-26-C 1-2 6-C .... ...... 1-26 126-D -D ... ..... .. 1-26-E 1-2 6-E .... ...... 1-26-F.. 1-2 6-F...... .... 1-26-G..... 1-2 6-G..... 1-26126-H H ... ..... .. 1-26 126-I.. -I..... ..... .. 1-26-J.... 1-2 6-J...... .. 1-26 126-K -K ... ..... .. 1-26-L.. 1-2 6-L...... .... 1-26 126-M... -M..... .. 1-26 126-N -N ... ..... .. 1-26126-O O ... ..... ..

Pa g e Number 1-36 1-36 1-36 136 1-36 1-3 6 1-36 1-3 6 1-36 1-3 6 1-36 1-3 6 1-36 136 1-37 137 1-37 1-3 7 1-37 137 1-37 1-3 7 1-39 139 1-39 1-3 9 1-39 139 1-40 1-4 0 1-40 140 1-40 140 1-40 1-4 0 1-42 142 1-42 142 1-42 142 1-42 142 1-42 142 1-42 142 1-43 1-4 3 1-45 145 1-45 145 1-49 1-4 9 1-49 149 1-49 1-4 9 1-49 1-4 9 1-49 1-4 9 1-50 150 1-50 150 1-50 1-5 0 1-50 150 1-50 1-5 0 1-50 150 1-51 151 1-51 151























BHT-206L4-MD-1


TABLE OF CONTENTS (CONT) Subject Combusti Combus tion on Se Sect ction... ion...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Turbine Turb ine Sec Section. tion..... ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ...... Turbin Tur bine e Out Outle lett Te Temp mpera eratu ture re (T (TOT)... OT)...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ... Power Pow er and Acc Acces essor sory y Ge Gear arbox.. box..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... .... .. Engin En gine e Tor Torque queme mete terr ... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... .. Engine Eng ine Ac Acces cessor sories. ies.... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Engin En gine e Oil Sy Syst stem em ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Engin En gine e Fue Fuell and Con Contr trol ol Sy Syste stem m ... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Droop op Com Compe pensa nsator tor Sy Syst stem em ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... .... .. N2 Dro Retir Re tireme ement nt Ind Index ex Nu Numb mber er (RI (RIN) N) ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ... Drivetra Driv etrain in Sys System tem ..... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ...... Freew Fre ewhee heell As Assem sembly bly ... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Main Mai n Dri Drive vesha shaft..... ft........ ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ... Transmi Tran smissio ssion n .... ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ...... .. Transm Tra nsmiss ission ion Oi Oill Sy Syst stem.... em....... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ... Transm Tra nsmiss issio ion n Mou Mount nts.. s..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ... Transmi Tran smissi ssion on Res Restrai traint...... nt........... ......... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ...... Main Roto Rotorr Mast.... Mast......... ......... ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ...... Main Mai n Rot Rotor or Sys System tem .... ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ...... Main Mai n Rot Rotor or Bla Blade des s ... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... .... .. Tail Rot Rotor or Driv Drive e .... ........ ........ ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ....... ... Taill Rot Tai Rotor or Dr Drive ivesh shaft aft Ha Hange ngerr Bea Bearin rings.. gs..... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... .... .. Taill Rot Tai Rotor or Ge Gear arbox box ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Taill Rot Tai Rotor or Hu Hub b And Bla Blade de As Assem sembly bly ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... .... .. Main Mai n Rot Rotor or Flig Flight ht Cont Controls rols .... ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ........ ... Cyclic Cyc lic Fli Flight ght Con Contr trols. ols.... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Collec Col lecti tive ve Fli Fligh ghtt Con Contro trols ls ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Eleva Ele vato torr Fli Flight ght Con Contr trols.... ols....... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Taill Rot Tai Rotor or Dir Direc ecti tiona onall Co Contr ntrols. ols.... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Verti Ve rtica call Con Contr trol ol Col Column. umn.... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Swashp Swa shpla late te and Col Collec lecti tive ve Lev Lever er ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... .. Duall Co Dua Contr ntrols ols ... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Hydrauli Hydr aulic c Sys System. tem..... ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ...... .. Hydra Hyd rauli ulic c Sy Syst stem em Com Compon ponent ents... s...... ...... ...... ...... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... .... .. Hydra Hy drauli ulic c Pu Pump mp ... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Hydra Hy drauli ulic c So Solen lenoid oid Va Valv lve..... e....... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ..... Hydrauli Hydr aulic c Filt Filters.... ers........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ......... ......... ........ ........ ...... .. Pres Pr essur sure e Re Relie lieff Va Valv lve e .. ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...

Paragraph Number 1-28-B..... 1-28 -B..... 1-28-C..... 1-2 8-C..... 1-28 128-C-C-1.. 1.. 1-28 128-D..... -D..... 1-28 128-D-D-1.. 1.. 1-28 128-D-D-2.. 2.. 1-28 128-D-D-3.. 3.. 1-28 128-D-D-4.. 4.. 1-28 128-D-D-5.. 5.. 1-29.. 129..... ...... ..... 1-30...... 1-3 0......... ... 1-30 130-A.... -A...... 1-30 130-B.... -B...... 1-30-C..... 1-3 0-C..... 1-30 130-D..... -D..... 1-30 130-E -E ... ..... .. 1-30-F 1-3 0-F .... ...... 1-30-G.... 1-3 0-G...... 1-31...... 1-3 1......... ... 1-31 131-A..... -A..... 1-32...... 1-3 2......... ... 1-32 132-A.... -A...... 1-32 132-B..... -B..... 1-33.. 133..... ...... ..... 1-34...... 1-3 4......... ... 1-34 134-A..... -A..... 1-34 134-B..... -B..... 1-34 134-C..... -C..... 1-34 134-D..... -D..... 1-34 134-E -E ... ..... .. 1-34 134-F -F ... ..... .. 1-34 134-G... -G..... .. 1-35...... 1-3 5......... ... 1-35 135-A..... -A..... 1-35 135-A-A-1.. 1.. 1-35 135-A-A-2.. 2.. 1-35-A1-3 5-A-3.. 3.. 1-35 135-A-A-4.. 4..

Page Number 1-58 1-58 1-58 1-5 8 1-58 158 1-58 158 1-59 159 1-59 159 1-60 160 1-60 160 1-62 162 1-63 163 1-63 1-6 3 1-63 163 1-66 166 1-66 1-6 6 1-66 166 1-69 169 1-69 1-6 9 1-70 1-7 0 1-70 1-7 0 1-70 170 1-71 1-7 1 1-71 171 1-71 171 1-72 172 1-72 1-7 2 1-73 173 1-73 173 1-73 173 1-77 177 1-77 177 1-77 177 1-80 180 1-80 1-8 0 1-80 180 1-80 180 1-82 182 1-82 1-8 2 1-82 182
























BHT-206L4-MD-1

FIGURES Subject

Figure Number

General Gener al Hel Helico icopt pter er and Mai Main n Com Compon ponent ents s ... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Princip Prin cipal al Dim Dimensi ensions ons ..... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ......... ......... ...... .. Cabin Cab in an and d Bag Baggag gage e Com Compa part rtmen mentt ... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Instrume Inst rument nt Pan Panel...... el........... ......... ........ ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ....... Pitot-s Pito t-stat tatic ic Sys System. tem..... ........ ......... ......... ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ .... Cyclic Cyc lic and Col Colle lect ctive ive Con Contr trol ol Sw Swit itche ches.. s..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... DC Powe Powerr Sys System tem .... ........ ......... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ...... .. Leftt Fue Lef Fuell Boo Boost st Pum Pump p Alt Alter ernat nate e Ci Circu rcuit it Sc Schem hemati atic.... c....... ...... ...... ...... ...... ...... ...... ...... ... Fuel Sys System... tem........ ......... ........ ......... ......... ........ ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ........ .... Fuell Bur Fue Burn n Se Seque quence nce ... ...... ...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ..... Parti Pa rticle cle Se Separ parato atorr and Vo Vort rtex ex Gen Gener erat ator or ... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ...... ...... ..... ..... ... Powerr Pla Powe Plant nt .... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ......... ......... ........ .... Engine Engi ne Oil Sys System tem .... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ....... ... Drivetr Driv etrain ain Sys System tem .... ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ....... ... Freewhee Free wheell Sha Shaft ft Asse Assembly mbly .... ........ ........ ........ ........ ......... ......... ........ ........ ........ ......... ......... ........ ........ ........ ........ ...... Transmis Tran smission sion Oil Sys System....... tem........... ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ .... Cyclic Cycl ic Cont Controls. rols...... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ...... .. Collect Coll ective ive Cont Controls rols .... ........ ......... ......... ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ ........ .... Elevato Elev atorr Cont Controls...... rols........... ......... ........ ......... ......... ........ ........ ........ ......... ......... ........ ......... ......... ........ ......... ......... ......... ........ ... Tail Roto Rotorr Cont Controls rols .... ......... ......... ........ ......... ......... ........ ........ ......... ......... ........ ......... ......... ........ ........ ........ ........ ........ ........ .... Swashpl Swa shplate ate and Supp Support ort .... ........ ........ ........ ........ ........ ........ ........ ........ ........ ........ ........ ........ ........ ........ ........ ........ ....... ... Hydrauli Hydr aulic c Sys System.... tem........ ........ ........ ........ ........ ......... ......... ........ ........ ......... ......... ........ ........ ........ ........ ........ ......... ......... ........ .... Hydra Hyd rauli ulic c Sy Syste stem m Sc Sche hemat matic... ic...... ..... ..... ...... ...... ...... ...... ...... ..... ..... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...

1-1 ... 1-1 ...... ...... ..... .. 1-2........... 1-2....... .... 1-3 13 ... ...... ...... ..... .. 1-4........... 1-4....... .... 1-5........... 1-5....... .... 1-6 16 ... ...... ...... ..... .. 1-7........... 1-7....... .... 1-8 18 ... ...... ...... ..... .. 1-9........... 1-9....... .... 1-10.... 110....... ..... .. 1-11.... 111....... ..... .. 1-12 1-1 2 .... ........ ...... 1-13 1-1 3 ..... ......... .... 1-14 1-1 4 .... ........ ...... 1-15 1-1 5 .... ........ ...... 1-16 1-1 6 .... ......... ..... 1-17 1-1 7 ..... ......... .... 1-18 1-1 8 ..... ......... .... 1-19 1-1 9 .... ........ ...... 1-20 1-2 0 ..... ......... .... 1-21 1-2 1 .... ........ ...... 1-22 1-2 2 .... ......... ..... 1-23.... 123....... ..... ..

Page Number 1-8 1-8 1-11 1-1 1 1-14 114 1-19 1-1 9 1-22 1-2 2 1-35 135 1-38 1-3 8 1-41 141 1-44 1-4 4 1-46 146 1-53 153 1-55 1-5 5 1-61 1-6 1 1-64 1-6 4 1-65 1-6 5 1-67 1-6 7 1-74 1-7 4 1-75 1-7 5 1-76 1-7 6 1-78 1-7 8 1-79 1-7 9 1-81 1-8 1 1-83 183
















































BHT-206L4-MD-1

Section 1 SYSTEM DESCRIPTIO DESCRIPTION N

1 1-1. 1-1. INTRODUCTION The 206L4 LongRanger helicopter, its primary and auxiliary systems, as well as emergency equipment are described in this section. The main helicopter and its components are shown in Fig Figure ure 1-1 1-1.. The information in this Manufacturer’s Data is also applicable to 206L1+ and 206L3+ helicopters (Increased Gross Weight Upgrade kit 206-706-530 installed per B H T - 2 0 6 - S I - 2 0 5 2) 2) . I n f o r m a t i o n t h a t i s specifically applicable to 206L1+ and 206L3+ helicopters will be identified as “206L1+ and 206L3+ IGW Upgrade”.

1-2. 1-2. HELI HELICO COPT PTER ER DESCR ESCRIP IPTI TION ON — GENERAL The LongRanger (F (F i gu gu r e 1 -1 - 1 ) is a single engine, seven place helicopter designed to takeoff and land on any reasonably level terrain. Standard configuration provides for one pilot and six passengers.

The basic 206L4 as well as the 206L3+ IGW Upgrade helicopters have a fuel capacity of 112.0 U.S. gallons (110.7 gallons usable) [99.4 U.S. gallons (98.4 gallons usable) for the 206L1+ IGW Upgrade] distributed into three cells. The helicopters are designed to operate on standard aviation jet fuels. The helicopter is powered by a Rolls-Royce turboshaft engine, model 250-C30P, 250-C30P, that provides 490 Shaft Horsepower (SHP) for takeoff and 370 SHP for maximum continuous operation. The drivetrain system provides a means of transmitting power from the engine to the main and tail rotor assemblies. The main rotor is a semi-rigid, seesaw, two blade design that employs a preconed and underslung feathering axis to ensure smooth operation. The tail rotor is a semi-rigid, delta hinged, two blade design. The flight controls are mechanical linkages that are actuated by conventional controls and are used to control flight attitude and direction. Both the cyclic and the collective























BHT-206L4-MD-1


3 4

2 5 1 6 7 8 9

INTERMEDIATE SECTION

10

12

36

11

FORWARD SECTION

35

13 14 34 15 33

16 32

TAILBOOM SECTION
























BHT-206L4-MD-1

1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31.

Hydraulic servo actuators and reservoir Main rotor hub and blades Tail rotor gearbox and servicing door Tail rotor hub and blades Tail Tail rotor driveshaft and cover Horizontal stabilizer and end plates Engine and transmission oil cooler blower Engine and access door Baggage compartment door Main input driveshaft Litter door Cabin ventilation inlet Aft fairing Engine cowling Air inlet induction cowling Transmission cowling Forward cowling Pitot tube External power receptacle Battery Static port Crew door Passenger door Landing gear Fuel cell filler cap Fuel sump drain button Fuel shutoff valve panel Main transmission Intake cowling access door Tailboom Tailboom attachment access panel Engine oil tank and access panel























BHT-206L4-MD-1

1-3. 1-3. PRIN PRINCI CIP PAL DIME DIMENS NSIO IONS NS Principle exterior dimensions are shown in Figur Fig ure e 11-2 2. All height dimensions must be considered approximate due to variations in loading and landing gear deflection. Principle interior dimensions of the cabin and baggage compartment are shown in Fi Figur gure e 11-3 3.

1-4. 1-4. LOCA LOCATI TION ON REFE REFERE RENC NCES ES Locations on and within the helicopter can be determined in relation to fuselage stations, waterlines and buttock lines, measured from known reference points. Refer to the BHT-206L4-MM,, Chapter 6 (BHT-206L1-MM / BHT-206L4-MM BHT-206L3-MM for 206L1+ and 206L3+ IGW Upgrade) for a lines drawing of the helicopter.

1-4 1-4-A. -A.

FUSE FUSELA LAGE GE STATIO ATIONS NS

Fuselage stations (FS or STA) are vertical planes perpendicular to, and measured along the longitudinal axis of the helicopter. Station zero is the reference datum plane and is located 55.16 inches (1401 mm) forward of the forward jack point centerline.

1-4-B.

WATERLINES

Waterlines (WL) are horizontal planes perpendicular to, and measured along the vertical axis of the helicopter. Waterline zero is a plane 20 inches (508 mm) below the

MANUFACTURER ’S DATA Intermediate Section, and the Tailboom Section.

1-5-A.

FUSELAGE — FORWARD SECTION

The forward section (F ( F ig i g ur u r e 1 -1 -1 ) utilizes aluminum honeycomb structure and provides the major load carrying elements of the forward cabin. It provides for pilot and passenger seating, fuel cell enclosure, and pylon support. The cabin area accommodates up to seven persons or 80 cubic feet (2.2 m3) of cargo. The pilot's station is situated on the right side of the crew compartment. The left side can accommodate a passenger, or a copilot if the dual controls are installed. Floor loading in the cabin area is limited to 75 pounds per square foot (3.7 kg/100 cm2). The crew and passenger doors contain a three-component wedge shaped window of blue tinted plastic with the lower forward section being used as a sliding window for ventilation. This sliding window is adjustable and the window handle functions not only as a handle to open, but also as a retainer to keep the window from sliding out of the track. The windshields are fabricated of tinted acrylic plastic and are supported by formed aluminum alloy sections. Two blue-tinted transparent lower windows (chin bubbles)
























BHT-206L4-MD-1

6 FT. 10.7 IN. (2.10 m)

206L4 (206L1+ AND 206L3+ IGW UPGRADE) STANDARD LOW GEAR

4 FT. 4.0 IN. (1.32 m)

6 FT. 4.2 IN. (1.93 m)

TURNING RADIUS 23 FT. 10.0 IN. (7.26 m)

NO LOAD ON GEAR 7 FT. 5.0 IN. (2.30 m)

AT GROSS WT .OF 4000 LBS. 7 FT. 8.1 IN. (2.34 m) PIVOT POINT 4 FT. 4.0 IN. 1 FT. 1.0 IN. (1.32 m) (0.33 m)

5.5°

3 FT. 2.9 IN. (0.988 m) 37 FT. 0.0 IN. (11.28 m)

5° 9 FT. 6.1 IN. (2.90 m)

23 FT. 6.2 IN. (7.17 m)

6 FT. 5.7 IN. (1.97 m)

C PITCH CHANGE AXIS 2°15' PRECONE

10 FT. 0.4 IN. (3.05 m)

8° 30' FLAPPING (UP + DOWN) 5° CLEARANCE 1 FT. 11.3 IN. (0.59 m)

5.25 IN. (0.13 m)

























BHT-206L4-MD-1


6 FT. 10.7 IN. (2.10 m)

206L4 (206L1+ AND 206L3+ IGW UPGRADE) HIGH SKID GEAR

1 FT. 6.0 IN. (0.46 m)

4 FT. 4.0 IN. (1.32 m)

6 FT. 4.2 IN. (1.93 m)



AT GROSS WT .OF 4000 LBS. 7 FT. 9.6 IN. (2.38 m) PIVOT POINT 4 FT. 4.0 IN. 1 FT. 1.0 IN. (1.32 m) (0.33 m)

5.5°

3 FT. 2.9 IN. (0.988 m) 37 FT. 0.0 IN. (11.28 m)

5° 10 FT. 0.0 IN. (3.05 m)

10 FT. 10.8 IN. (3.32 m)
























BHT-206L4-MD-1

206L4 (206L1+ AND 206L3+ IGW UPGRADE) EMERGENCY FLOAT KIT

6 FT. 10.7 IN. (2.10 m)

1 FT. 7.2 IN. (0.49 m) 4 FT. 4.0 IN. (1.32 m)

1 FT. 6.0 IN. (0.46 m)

AT GROSS WT .OF 4000 LBS. 8 FT. 1.2 IN. (2.47 m)

6 FT. 4.2 IN. (1.93 m)



PIVOT POINT 4 FT. 4.0 IN. 1 FT. 1.0 IN. (1.32 m) (0.33 m)

5.5°

3 FT. 2.9 IN. (0.988 m) 37 FT. 0.0 IN. (11.28 m)

5° 10 FT. 0.0 IN. (3.05 m)

10 FT. 10.8 IN. (3.32 m)























BHT-206L4-MD-1


1.3 FT (0.4 m)

3.6 FT (1.1 m)

4.2 FT (1.3 m)

3.7 FT (1.1 m)

1.8 FT (0.5 m)

5.0 FT (1.5 m) 4.2 FT (1.3 m)

3.1 FT (0.9 m)























MANUFACTURER ’S DATA A crew door is installed on each side of the forward fuselage to provide access to the cockpit area. Each door is equipped with a latch assembly, which may be operated from either side of the door, and a lock, installed in the exterior door handle. Each door i n c o r p o r a te te s a s l i d i n g w i n d o w a n d a stationary window. A passenger door is installed on each side of the fuselage to provide access to the cabin area. Each door is equipped with a latch assembly, which may be operated from either side of the door, and a lock installed in the exterior door handle. The left passenger door is hinged on the litter door so that the two may be opened together to aid in loading the helicopter. The litter door, located between the crew and passenger doors on the left side of the helicopter, is hinged forward and is opened in conjunction with the left passenger door to provide increased access for loading the

BHT-206L4-MD-1 Doors and panels are also provided at various locations in the cowling and fairings for servicing and inspection. The engine oil reservoir access door and the oil cooler access door are located on the aft fairing. The engine cowling has side panels which are hinged for easy access, and the air induction cowling has doors on both sides for inspection of the transmission area. Most miscellaneous access doors open on piano hinges and are secured with flush latches and winghead stud fasteners.

1-5-B -5-B..

FUSELA SELAG GE — INTERMED MEDIATE ATE SECTION

The intermediate section (Fig (Figure ure 1-1 1-1)) utilizes an aluminum semi-monocoque construction and provides a deck for engine installation, a baggage compartment, and a compartment under the engine deck for heater and electrical equipment. A titanium engine pan, located below the engine, acts as both a drip pan and firewall. It























BHT-206L4-MD-1


heater or environmental control unit and provides a convenient location near the source of bleed air.

A one-piece cowling is used to cover the tail rotor driveshafts and is secured with quick release fasteners.

1-5-C.

The tail rotor gearbox fairing encloses the tail rotor gearbox and is attached attached to the tailboom and vertical fin. It incorporates a white position light and three screens. The screens provide cooling airflow for the tail rotor gearbox. The oil level in the gearbox is visible through one of the screened openings.

FUSELAGE — TAILBOOM SECTION

The tailboom (Fig (Figur ure e 11-1 1) is attached to the aft fuselage by means of four bolts. It consists of an aluminum alloy monocoque tailboom which supports the tail rotor drivetrain as well as a horizontal stabilizer with end plates, vertical fin, and fairings. Modifications of the tailboom, including installation of antenna, lights or equipment that change the mass or mass distribution of the helicopter, are not permitted without appropriate Bell Helicopter approval. The horizontal stabilizer is constructed of aluminum honeycomb. The stabilizer is an inverted airfoil that provides a downward resultant lift on the tailboom to maintain the cabin in a nearly level attitude throughout the

1-6. 1-6. CABI CABIN N HARD HARD POIN POINT TS Two airframe hard points are located on the belly of the helicopter forward of the front crosstube and one hard point is located on the belly aft of the baggage compartment. These hard points are used for jacking and mooring. Clevises may be attached to these hard points for securing helicopter tie-downs. The hard points are not to be used for towing. Refer to Section 2 for additional information.

























MANUFACTURER ’S DATA The air inlet induction cowling encloses the aft portion of the main transmission. Inlet ducts are provided on each side of the air induction cowling to direct the airflow into the induction screen or particle separator. Two Two doors are also provided for maintenance and inspection of the induction area and main transmission. The induction screen is located inside and attached to the air induction cowl and the forward side of the forward engine firewall. The engine cowling, which includes the engine upper cowling and engine side cowling doors, is constructed of aluminum

BHT-206L4-MD-1 installed, the front mounting hardware must be modified to include a spacer bar, springs, and two lower supports per side. This additional attachment hardware will prevent medium frequency vibrations from being transmitted from the landing gear to the airframe. It is recommended that no components be attached to the landing gear assembly except as designated by the manufacturer. Unauthorized attachments may lead to failure of the crosstubes.

1-9 1-9. GROU GROUN ND HA HANDLI NDLIN NG























BHT-206L4-MD-1

1-1 1-11. INST INSTRU RUME MENT NT PANE PANEL L AND AND CONSOLES The instrument panel (Fi (Figu gure re 11-4 4) is mounted on a center pedestal forward of the two crew seats and the top is tilted forward at a 5° angle for maximum visibility. Flight instruments are located on the right side of the panel and system instruments are in two vertical rows to the left of the flight instruments. Caution and Warning panel lights are mounted just below the glare shield across the top of the instrument panel.

MANUFACTURER ’S DATA mounted in the upper left corner of the pilot's windshield. The magnetic compass is mounted to the right side of the cabin structure slightly forward of the instrument panel. The hourmeter is mounted in the battery compartment.

1-13-A 1-13-A.. FLIGHT FLIGHT INSTRU INSTRUMEN MENTS TS The flight instruments include the airspeed indicator, altimeter, turn and slip indicator (optional), vertical speed indicator (optional), attitude indicator (optional) or inclinometer and directional gyro (optional).
























FUEL LOW

SPARE SPARE

LITTER DOOR OPEN

SPARE

SPARE SP

SPARE

GEN FAIL BAGGAGE DOOR

SPARE

SPARE SP

SPARE

2

R/FUEL PUMP L/FUEL PUMP

FUEL FILTER

ENG CHIP

T/R CHIP

TRANS CHIP

4

3

BATTERY HOT BATTERY RLY

BHT-206L4-MD-1

TRANS ENG OUT OIL PRESS TRANS ROTOR OIL TEMP LOW RPM

WRN HORN MUTE

CAUTION 7

LT TEST 6

5

8

1 ENG 15 OIL 15

60 70 50 80 40 TORQUE 90

10

10 SI P P SI

30

100 20 PERCENT 11 110 0 10 120 0

°C T

5

5 X 10

0

150

120

22

100

TOT

0

20

17 4 AIRSPEED 14 MPH 6 12 X 10 8 10

40

60 KNOTS

80

23

XMSN 15 OIL 15

LT TEST

4 5

10

10 SI P P SI

3 TURB 6

10

7 TEMP °CX100 8

X 10

0

9

50 40

20

TOTAL FUEL QTY

MINIMUM COCKPIT WEIGHT 170 LBS. SELECTIVE PASSENGER LOADING

3 2 1 0

4

5

FUEL QTY LBS x100

6 7 8

ROTOR 80 T

POWER TURBINE

R

30 50 40 30

60 70 80 GAS PRODUCER

% RPM

4

20 10

5

20 17 90

7 0

100

PERCENT 11 110 0 RPM

10

120

0 11

6 8

1

90

100

3 2 9

9

70

60

FWD

THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED HELICOPTER FLIGHT MANUAL.

14

16

OUT

5

5

21

2 1

°C T

PULL FOR QUICK ERECT

AVOID CONT OPS 71.8% TO 91.5% N2























BHT-206L4-MD-1


29
























BHT-206L4-MD-1

1. 2. 3. 4. 5. 6. 7.

Engine oil temperature/pressure gauge Torquemeter indicator Airspeed indicator RPM warning horn mute button Attitude indicator (optional)/inclinometer (not shown) Caution and warning panel Caution and warning panel light test button

























BHT-206L4-MD-1
























MANUFACTURER ’S DATA 1-13-A-2 A-2.

ALTI ALTIM METE ETER

BHT-206L4-MD-1 straight and level flight, i.e. "in trim". If the helicopter is in a slip or skid, the ball will move off center. 1-131-13-AA-4. 4.

VERTIC ERTICAL AL SPEE SPEED D INDICA INDICATOR TOR























BHT-206L4-MD-1 The manual caging knob should be pulled out to erect the gyro when power is applied. The pitch trim knob is used to adjust the helicopter symbol vertically.

MANUFACTURER ’S DATA flux valve and therefore, must be set prior to takeoff and periodically during flight to correct for magnetic variation and gyroscopic precession. A fail flag will be visible when power to the indicator is lost, warning























MANUFACTURER ’S DATA 1-13 1-13-C-C-1. 1.

DUAL DUAL TAC TACHOM HOMET ETER ER ROTOR (N2 /NR)

BHT-206L4-MD-1 TURBINE URBINE//

1-13 1-13-C -C-2 -2..

GAS GAS PROD PRODUC UCER ER IND INDIC ICAT ATOR OR (N (N1)























BHT-206L4-MD-1

1-13 1-13-C -C-3 -3..

TORQU ORQUEM EMET ETER ER INDIC INDICAT ATOR OR


NOTE Alternate indicators to that shown may be installed on 206L1+ and 206L3+ IGW Upgrade helicopters.









































































































































































































































































































































































































































































































































































































































































































BHT-206L4-MD-1


19

39 1 36

37

2 35

40

3 18

24 23 22

32

34

38

8 4

5

6

21

7 20

32 33

9 28 14 13

12

30

10

11

27 31 29

16

26 25

17

15

. 14. 15. 16. 17. 18. 19. 20.

on re res s ra n Up stop Stop mount Link attachment Hydraulic pump and NR tachometer generator Lower chip detector Upper chip detector Nodal beam assemblies and mounts Drag pin Link attachment Main input driveshaft Rotor brake assembly (optional) Spacer

21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40.

Freewheel chip detector Forward freewheel housing and shaft assembly Freewheel assembly Aft freewheel housing and output adapter Forward shaft assembly Oil cooler blower shaft hanger Oil cooler blower shaft Oil cooler blower Thomas couplings Aft short shaft Tail rotor driveshaft hanger bearings Tail rotor segmented driveshafts (qty 5) Tail rotor driveshaft hangers Tail rotor gearbox input pinion Tail rotor gearbox Oil filler cap Tail rotor gearbox chip detector Tail rotor gearbox output shaft Tail rotor hub and blade assembly Tail rotor pitch change mechanism 206L4_MD_01_0038

Figure 1-14. Drivetrain System

1-64

Rev. 1

23 OCT 2008
















BHT-206L4-MD-1

1 MATES WITH MAIN INPUT K-FLEX DRIVESHAFT MATES WITH TAIL ROTOR DRIVESHAFT ADAPTER

2

MATES WITH ENGINE PTO SHAFT

MATES WITH ADAPTER (ITEM 1)

4

3

1. 2. 3. 4.

Adapter Inner shaft Sprag clutch Outer shaft























BHT-206L4-MD-1

1-30-B 1-30-B.. MAIN MAIN DRI DRIVE VESH SHAF AFT T The main driveshaft (Fig (Figure ure 1-1 1-14 4) is designed to transfer power from the engine to the transmission during normal operations and to transfer drive from the transmission to the tail rotor system during autorotation. The main driveshaft rotates at 6016 RPM at 100% N2. The helicopter uses the Kaflex driveshaft, which provides a flexible drive coupling between the freewheeling unit and transmission. This flexing allows for the smooth transfer of torque when the transmission and freewheeling unit are not aligned. The driveshaft is made up of three rectangular plate sets in each coupling. Each coupling can be considered a truss work in which torque loads are carried as axial loads through the straight members of each plate. Preflight inspection consists of checking the flex frames for cracks and for condition and security.

1-301-30-C. C. TRANS RANSMI MISS SSIO ION N The transmission (Fig (Figure ure 11-14 14), ), located on the cabin roof, incorporates a nodal beam suspension and restraint. It is mounted on two nodes, and a flexure assembly absorbs normal vibrations and vertical movement. Elastomeric bearings are used to minimize vibrations being transferred into the airframe. The transmission reduces engine RPM, changes the angle of drive from the engine to the rotor, and serves as the structural member that links the mast to the airframe. It provides a two-stage reduction of 15.23 to 1.0 (6016 to 395 RPM). The first stage is a bevel gear arrangement with a 3.26 to 1.0 reduction; the second stage reduction is obtained through a planetary gear train that provides a

MANUFACTURER ’S DATA arrangement, planetary gear train, and accessory gear drive. Components attached attached to the transmission assembly are the main driveshaft, transmission oil pump, transmission oil filter housing, hydraulic pump, rotor RPM tachometer generator, and two magnetic chip detectors. The transmission system is equipped with a temperature switch, temperature bulb, pressure switch, and wet line pressure gauge to provide system information.

1-30-D 1-30-D.. TRANSMI RANSMISSIO SSION N OIL OIL SYSTE SYSTEM M The transmission oil system (Fig (Figure ure 11-16 16)) includes a pump, a pressure regulating valve, an oil cooler, a filter element, and two spray jets. The pump is a constant volume type driven by the accessory gear, which delivers pressurized oil externally to the filter and housing assembly, cooler, and then returns it to the main transmission where spray jets lubricate the internal parts. A sight glass is located on the right side of the main transmission lower case where the oil level can be easily checked. A non-vented filter cap is located on the transmission top case. The oil system also provides lubrication for the freewheeling assembly mounted in the engine accessory gearcase. Pressurized oil is delivered from the transmission into a T-fitting on the cabin roof. Oil flowing out of the left side of the fitting is reduced in pressure and is utilized to lubricate the freewheeling unit. Oil flowing out of the right side of the fitting delivers regulated pressure into the transmission oil pressure gauge and into the oil pressure switch for the TRANS OIL PRESS caution light.


























BHT-206L4-MD-1

ENGINE SECTION TRANSMISSION SECTION

1

PRESSURE OIL FROM PUMP TO COOLER PRESSURE OIL FROM COOLER INTO TRANSMISSION AND FREEWHEEL LUBRICATING OIL THERMOBULB CLOG FILTER INDICATOR HIGH TEMP WARNING SW

FILTER BYPASS VALVE

MAST ASSEMBLY

OIL COOLER THERMO BYPASS VALVE

2 3

OIL COOLER

4 MAST BEARING MAGNETIC CHIP DETECTOR

OIL RETURN FROM FREEWHEEL ASSEMBLY

CHIP COLLECTOR PAN

5

OIL JET NO. 2 BLOWER ASSEMBLY FILTER ELEMENT

PLANETARY ASSEMBLY

1 OIL PRESSURE TO FREEWHEEL ASSEMBLY

8

1. 2. 3. 4. 5. 6. 7. 8.

7

FILTER FREEWHEEL UNIT OIL JET NO. 1

OIL PRESSURE FROM FILTER TO PRESSURE SWITCH AND INDICATOR

Oil cooler Return oil nose Outlet oil nose Oil filter housing Drain valves (baggage compartment) Restrictor Pressure regulating valve Oil pump

PRESSURE REG VALVE OIL PUMP 4.5 TO 5 GPM (17 TO 19 IPM)

6

RESTRICTORS IN FITTING

DRAIN PLUG AND MAGNETIC CHIP DETECTOR

OVERBOARD DRAIN LINES

ENGINE

INTERNAL JETS TO SUN GEAR AND PLANETARY DRAIN PLUG AND MAGNETIC CHIP DETECTOR

NOTE 1

To pilot oil pressure gauge and low pressure warning switch.

206L4_MD_01_0035

Figure 1-16. Transmission Oil System

23 OCT 2008

Rev. 1

1-67







































MANUFACTURER ’S DATA The oil cooler blower is mounted aft of the engine firewall on the helicopter structure and supplies air to the engine and transmission oil cooler. The cooler blower shaft is mounted on two sealed bearings and is connected to the forward and the aft short shafts. It passes through the blower assembly housing, and the blower impeller is bolted to the shaft. This shaft is part of the tail rotor driveshaft system and is used to power the blower. During normal operation, oil flows from the transmission to the cooler and back to the transmission. Two transmission oil cooler drain valves (pressure line/return line) are located inside the baggage compartment to allow for the draining of the transmission oil cooler when transmission oil is changed.

1-30-E. 1-30-E. TRANSMIS RANSMISSIO SION N MOUNT MOUNTS S The transmission, mast, main rotor hub, and the blade assembly are supported by and isolated from the fuselage by means of the transmission mounts (nodal beam) and transmission restraint (Fig (Figure ure 11-14 14). ). This is accomplished through the use of four link attachments and two stop mounts bolted to the transmission. Attached to these are four link assemblies, which are secured to the four supports and the flexure assemblies. The support assemblies are bolted to the cabin roof shell and cabin roof beam. The support assemblies contain elastomeric bearing and bushing members to isolate and balance

BHT-206L4-MD-1 The up stops mounted on the drag pins restrict the vertical movement of the transmission and all oscillatory movement. Tuning weights, which are bolted to the arm and flexure assemblies, provide for the fine-tuning and balance of the transmission mounting system. The arm and flexure assembly is the primary nodal beam component that isolates main rotor and transmission vibrations from the fuselage. The nodal beam installation develops a standing wave form to reduce fuselage vibrations throughout the helicopter's speed range. The arm assemblies are manufactured from aluminum alloy and are bushing-mounted to the fore and aft support assemblies. The flexure assembly, which is contained between the two arm assemblies, consists of a laminated elastomer flexure, shims, and shear pads bonded into metal brackets. Tellurium lead tuning weights, which are located on the end of the arm assemblies adjacent to the flexure, provide a method for tuning the nodal beam installation. The forward and aft support assemblies, which are manufactured from aluminum alloy, contain bonded elastomeric bearing and bushing members to isolate the arm and flexure assemblies from the fuselage.

1-30-F 1-30-F.. TRANSMI RANSMISSI SSION ON RESTRA RESTRAINT INT The transmission restraint (Fig (Figure ure 11-14 14)) is an























BHT-206L4-MD-1 cabin roof beam. It provides a fixed structural support for the transmission restraint. The two steel stop mounts, which are attached to the lower aft portion of the transmission case, limit vertical and oscillatory movement of the transmission. The two steel drag pins limit the oscillatory movement of the transmission through the stop mounts. Vertical restraint is limited by the up stops, which consist of a bonded upper and lower disc in contact with the stop mounts.

1-30-G 1-30-G.. MAIN MAIN ROT ROTOR OR MAS MAST T The main rotor mast (Figu (Figure re 1-1 1-14 4) is attached to the transmission by means of a mast locking plate and studs in the top of the transmission case. The mast is a hollow, steel shaft that transmits rotational energy from the transmission to the rotor system. It has three sets of splines and two threaded areas incorporated into its design. The upper spline is master splined to correctly position the main rotor trunnion. The swashplate drive splines, located in the mid portion of the mast, are machined to receive a collar set to which the swashplate drive link is attached. The lower splines are the drive splines where the rotational energy from the transmission is transmitted to the mast from the planetary gearing. The upper portion of the mast is threaded to receive the mast retaining nut.

MANUFACTURER ’S DATA to the yoke by means of the tension-torsion (T-T) strap assemblies which transfer centrifugal loading from the blades to the yoke and also assist to counteract aerodynamic forces. The pitch change bearings are housed in the grips and are grease lubricated. The change in blade pitch angle is accomplished by rotating the grips on the yoke with an input at the pitch horns. The blades are attached to the grips with bolts which have hollow shanks that are used to install weight for static and dynamic balance of the hub and blad e assembly. Blade alignment is accomplished by adjustment of the blade latches which engage the root end of the blade. The trunnion mates the rotor system to the mast, transmits drive to the yoke assembly, and serves as a pivot point for the rotor flapping axis. The yoke supports the main rotor system. It has two hollow and preconed journals to relieve stresses. Each journal has the hollow bore especially machined at the outboard end to fit a seal assembly, and the inboard end is machined to fit the tension-torsion (T-T) strap end fitting. The T-T strap, which consists of stainless steel wire wrapped around two steel ends, provides a connection between the grips and yoke. During rotor feathering, the flexibility of the strap allows the grip bearings to rotate on























MANUFACTURER ’S DATA -11° -11° twist and an airfoil characterized by a significant positive camber to the first 1/3 of the chord length and by the flat symmetrical surfaces of the aft 2/3. Through the use of a droop-snoot airfoil section, rotor blade efficiency is significantly improved compared to symmetrical blade shapes. A wide thrust margin for maneuverability and high efficiency in a hover are, in part, the result of this airfoil design. It is an all metal bonded assembly consisting of three structural members: an aluminum spar, spar closure, and a trailing edge strip. Skins, stabilized by honeycomb core, are bonded to the major section by adhesive applied under heat and pressure. Reinforcing doublers, grip plates, and drag plates are bonded to the blade butt end. The basic portion of the blade has a 13.026 inch (33.09 cm) chord.

BHT-206L4-MD-1 means of a splined adapter and the first tail rotor driveshaft segment. The segmented tail rotor driveshaft consists of five segments that extend along the top of the tailboom. Each segment of the drive system is identical and interchangeable with the others.

1-32 1-32-A -A.. TAIL AIL ROTO ROTOR R DRIV DRIVES ESHA HAF FT HANGER BEARINGS Seven hanger bearing assemblies ( Fig Figure ure 1-1 1-14 4) support the driveshafts driveshafts and flexible, steel, disc couplings. Thomas couplings are used to both connect the shaft sections and allow continued alignment with the tailboom.

1-32-B. 1-32-B. TAIL ROTOR ROTOR GEARBO GEARBOX X The flap restraint is installed on the main rotor hub trunnion and incorporates counterweights counterweights and springs which serve to limit flapping freedom during starting and shutdown, but permit normal flapping at operating RPM.

1-32. TAIL ROTOR ROTOR DRIVE The tail rotor driveshaft (Fig (Figure ure 11-14 14)) is made up of the forward short shaft, the oil cooler blower shaft, the aft short shaft, and the tail

The tail rotor gearbox (Fig (Figur ure e 11-14 14), ), located on the aft end of the tailboom, drives the left side mounted tail rotor. It contains two spiral bevel gears positioned at 90° angles to the other. The direction of drive is changed 90° and there is a speed reduction of 2.35 to 1.0 at the gearbox to achieve an output shaft speed of 2550 RPM. The magnesium housing is attached to the tailboom by means of four bolts and two alignment pins. The assembly includes a breather type filler cap, oil level sight gauge,

























BHT-206L4-MD-1


1-33. TAIL ROTOR ROTOR HUB AND BLADE BLADE ASSEMBLY

1-34 1-34.. MAIN MAIN ROTO ROTOR R FLIG FLIGHT HT CONTROLS

The tail rotor assembly (Fig (Figure ure 11-14 14)) is a delta hinge type that consists of a hub and two interchangeable blades. The yoke of the hub is made with a 4° twist for each blade.

The flight controls (F (F i gu gu r e 1 - 17 17 through Figure Fig ure 11-20 20)) are mechanical linkages that are actuated by conventional controls and used to control flight attitude and direction. Both the cyclic (longitudinal and lateral) and the collective controls incorporate hydraulic servo actuators. A synchronized elevator is linked into the fore and aft controls at the cyclic torque tube.

The aluminum alloy forged yoke is attached to the tail rotor gearbox shaft by means of a splined trunnion inside the yoke to provide a flapping axis for the assembly. At the time of assembly, spanwise balance is accomplished by using washers on the blade bolts at the yoke, and chordwise balance is accomplished by using weights and washers on the trunnion bearing housing restraining bolts. The tail rotor blades are all metal assemblies consisting of a stainless steel shell reinforced by a honeycomb filler and stainless steel leading edge abrasive strip. Ballast stations, located at the inboard trailing edge and the tip

The flight controls are routed beneath the forward seats, aft to the vertical control column, then up to the cabin roof. The vertical control column also serves as a primary cabin structure. Access doors on the aft side of the control column and seat panels are provided for inspection of control components and maintenance accessibility. Dual controls are installed as an option to provide dual flight control capability either for operations requiring a pilot and a copilot or
























1-34-A. 1-34-A. CYCLIC CYCLIC FLIGHT FLIGHT CONTRO CONTROLS LS

BHT-206L4-MD-1 servo actuator to the swashplate collective lever. Collective pitch control is transmitted to the main rotor controls by vertical movement of the swashplate. The servo actuator is mounted on a support, which is located on the cabin roof directly forward of the transmission, along with two servo actuators for the cyclic system.

The cyclic flight controls (Fig (Figure ure 11-17 17)) consist of a control stick, torque tube, yoke, hydraulic servo actuators, control tubes, and bellcranks. Movement of the control stick is transmitted through linkage and hydraulic servo actuators to the swashplate, which actuates the rotating controls to the main rotor. Servo actuators are incorporated to minimize the effort required to move the controls and to reduce main rotor feedback forces. The cyclic stick extends upward and forward from the front of the pilot seat. The torque tube connects to the cyclic stick support and provides a mounting point for the elevator controls. The cyclic system yoke extends aft from the cyclic stick support and jackshaft. Movement of the cyclic stick is transmitted to the mixing lever by means of the yoke.

The collective stick is installed to the left of the pilot seat, and it extends upward and f o r w a r d t h r o u g h a f l e x i b l e c o v e r. r. T h e collective jackshaft provides a mounting point for the collective stick. An adjustable friction bearing mounted on the jackshaft allows the pilot to adjust the friction to his own requirements. requirements. A minimum friction adjustment clamp located at the left end of the jackshaft ensures that the collective stick will always have a preset minimum friction to eliminate collective bounce.

This mixing lever transmits cyclic movement to the swashplate through mechanical linkage and servo actuators.

The collective trunnion and lever is installed between the collective jackshaft and control tube. It ties the collective controls to the























BHT-206L4-MD-1


18 17

15 16 12

14 13 9

10 7 8

11
























BHT-206L4-MD-1

16

15 14 MIXING LEVER

13 12 9

11

8

10

CYCLIC CONTROLS (REF) 7























BHT-206L4-MD-1


























MANUFACTURER ’S DATA The horizontal stabilizer/elevator is mounted on the tailboom. The horizontal stabilizer section is stationary while the elevator, which is attached to the aft side of the stabilizer, is synchronized to fore and aft cyclic application. The elevator horn is connected to the cyclic torque tube through the elevator control linkage. The elevator control linkage consists of control tubes, bellcranks, and walking beams. The forward control tube, which contains a shear pin, is attached to an eyebolt mounted in the cyclic torque tube. The aft control tube is attached to the elevator horn.

BHT-206L4-MD-1 means of control tubes and a bellcrank. The copilot pedals can be positioned, as desired, by means of the pedal adjuster. Alternate pedals may also be installed which allow the copilot to manually adjust the position of the pedal foot rests. Connecting linkage consists of push-pull tubes, bellcranks, levers, and supports that connect the pilot tail rotor control pedals to the tail rotor pitch change mechanism. Tail rotor pitch control is accomplished by means of bellcrank, rod, and lever assembly mounted on the tail rotor gearbox which actuates a control tube through the hollow























BHT-206L4-MD-1


11 10 9 12 8 ALTERNATE PEDALS 7 1
























BHT-206L4-MD-1

1 2

3 4

18

17 5 6 7























BHT-206L4-MD-1


The collective lever and link assembly is mounted to the swashplate support assembly and transfers collective inputs to the lower swashplate. Movement of the collective pitch lever actuates the collective sleeve assembly that in turn raises or lowers the swashplate and transmits collective input to the main rotor.

pressurized hydraulic fluid flows to the three servo actuators (F ( F i gu gu r e 1 -2 -2 3). 3). When it is energized (switch OFF), the pressurized hydraulic fluid is directed back to the reservoir and bypasses the three servo actuators. In case of a total electrical failure, the system is fail-safe ON (no electrical power = hydraulics ON).

The swashplate drive assembly consists of a collar set, idler drive link, and idler lever. The collar set is attached to the mast and the idler drive link is attached to the outer ring of the swashplate. This connects the upper

The cyclic and collective servo actuator support is installed on the cabin roof forward of the transmission. It serves as a mount for the three servo actuators and associated bellcranks. The collective servo actuator is
























BHT-206L4-MD-1

10

9 5

























BHT-206L4-MD-1 1-35 1-35-A -A-2 -2..

HYDRA HYDRAUL ULIC IC SOLEN SOLENOI OID D VALVE ALVE

The hydraulic solenoid valve (Fig (Figure ure 11-22 22)) is mounted on the cabin roof forward of the hydraulic pump and reservoir. The valve is electrically closed and is controlled by the

MANUFACTURER ’S DATA differential pressure across the filter is 70 ±10 PSI, the red button will rise. To prevent inaccurate indications of clogging, the indicator will not work when the hydraulic fluid temperature is less than 2°C (35°F). The return line filter incorporates a bypass valve.
























SYSTEM CAPACITY 65 CUBIC INCHES RESERVOIR CAPACITY 40.0 CUBIC INCHES RESERVE CAPACITY 24.3 CUBIC INCHES OPERATING PRESSURE 1000 PSI OPERATING TEMPERATURE -65 TO 160°F (-54 TO 71°C) HYDRAULIC FLUID MIL-H-5606

BHT-206L4-MD-1

SEE DETAIL B SEE

1

DETAIL B

16

2 3

SEE DETAIL B

4 15 5

6

15























206 L4 Manufacturers Data

Recommend Documents