Beechcraft Bonanza 36 and A36 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual

v i s u a l or usual nondestruct~vetesting techniques. This may render t h e part, component or structural assernbiy, even though originally manufactured by BEECHCRAFT, unsuit- able and unsafe for airplane use. BEECHCRAFT expressly disclaims a n y responsibility for m a l f u n c t i o n s , failures, damage or i n j u r y caused by use of non-BEECHCRAFT approved parts. TABLE OF CONTENTS SECTION 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . General SECTION !I . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Limitations SECTION III . . . . . . . . . . . . . . . . . . . . Emergency Procedures SECTION 1V . . . . . . . . . . . . . . . . . . . . . . .Normal Procedures SECTION V . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Performance SECTION VI . . . . . . . Weight and 8 a l a n c e / E q u i p m e n t List SECTION Vll . . . . . . . . . . . . . . . . . . . . . Systems Descriptiofi SECTION V l l l . . . . . Handling, Servicing and Maintenance SECTION 1X . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Supplements . . . . . . . . . . . . . . . . . . . . . . . . SECTION X Safety Information b Revised: March 1983 8,2(a) - EQUiPMENT LIST This list details the items Included in the empty weight shown In Section 6.2 Aeroplane Type:............... BEECH A36 ...... Registration Marking:. VW-FIWI SerialNa: E-434 I ISSUE: .... FOUR 12.8.98 1 - DATE:,, ,.. ENGINESPROPELLERS INSTRUMENTS .............. .... ConMnental 10-520 ........... 1 Altimeters.. .. 1 Harkell PHGC3YF.......... I Ammeters,. ...................... 1 ............................ Clocks.. 1 COMPASSES Magnetic...........................f GAUGES ......... Remote Indicating............ 0 Engine Oil Pressure +I Fuel Conten& ,,.,, , .. ,,.,,,,, , , 2 .......... THERMOMETERS Manifold Pressure,, 1 .............. Engine Temp(Cyl.Hd.).. . . . . 1 Suction Pressure I Oil Temp ..........................1 Outside Air Temp ............. 5 LIGHTS 'b <- : ,r<v,.i / . ................... Anti-coliision.. t :%.J INDiCATORS -:..-.I ............... inst. Full Panel.. t I ;>:,, ............. Airspeed............ . . . . . ... I Inst. FloodlSpot.. 7 > --. . , . . , Directional Gyro...............I Landing............... . . . ..... I :,:- --* . ..;, . .,,> -,> ,-di . . . .................. Exhaust Gas Temp .......... I Map Reading.. 2 *.J.71 ::2 ,/': - Flight Hour.......................-I Navigation........................ 3 ........ Fuel Flow.........................1 White Strobes (Tips) 0 ,-,A.,,.,*- Gyro Horizon.................... I Cockpit............................t -. , ....... Stall Warning ...................I Passenger Overhead 4 ," J ..,. :,: .,-.. -..- T a c h ~Recording .............. I Taxi. ................................. 1 <,.,.<I .,:::: JX ;;: . . . . Trim Indicator...................1 , . RESTRAINT EQUIPMENT C < i Turn Co-ordinator.............1 .shy, . . Gear Postn. Lights.. 4 ,9 ; ., . Inertia Reels.. 2 ..J . , . . . . . . . . . ................... .-. KC"' ................. Vertical Speed.. ................I Full harnesses 2 '* --1 Flap Position....................1 Lap Belts...................... 4 Assigned Attitude .............1 MISCELLANEOUS EQUIPMENT RADIO EQUIPMENT (TYPE) Dual Controls ...................1 ADF.. ........... KING KR85 Fire Ext,(PortabIa)..... . . .. 1 NP-FIE)....... STEC-50 Land,Gear Warn.Harn ...... 7 Speakers. . . . . I Cabin Heater,...................I ............... GlsIope........ KING KN75 Vacuum Pumps I Headsets..... f Heated Pitots................,.. 4 HF Corn. ...... CODAN HF2000 Alternate Static.. ...............1 NavlCorn ...... KING KX175B Cargo Door ...................... ? G PSICorn.. . . GARMtN GNC3OO La rnbswaol Seat Covers... 6 AudiojMkr.. . . KING KMA24 Txponder..... KING K V 6 A DISPOSABLE LOAD LIST ..... Encoder.. ACK A-30 First Aid Kit ......................0 .................... Stormscope. STRIKEFINDER SF2000 Torch.,. ..... 1 ........... .... l t r SIGTRONICS SPA400 V,S. BeaconJE.L.T.. ELT- 10 SECTION 7 - RADIO SYSTEMS Tk'PE BEECII A36 OPEII..I'I'IONAI, I,IhfIT4TIC>NS $ A434 VI I-mv 7.f 'I'his aircraft must be operated in accordance with the Visual Flight Rules unless the flight Manual includes a Night VFR or IPH Supplement. When inshllcd, calibrated and maintained in accordance with Civil Aviatiorl Ordcrs, the radio communication and radio navigation systcms in thc aircraft are approved for the types of operation and maximum operating altitud ts shown in the table below. (Hcfcr to Departmcnt of Aviation Publication 50). 7 . 2 Civil Aviation Ordcrs Parts 20.8 and 20,11 specify the radio systcms req uirctf for certain operations. 7,3 t~nserviccabtcradio systems are required to be entered o n the !b.iaintcnar~ce Release. 7.3 Ren~ovalof items of the radio systetn's may require weight and balaoce assessment and securing of remaining items o f equipmeilt to maintain airwortt~incssof the aircrafl. NOTE: THE: CARRIAGE OF FIEADPHONES IS M I A T O R Y R M S Y S O P I iSYSTEM i EQULPXIENT ! I T Y P E OF OPERAT kyD ALTITUDE ION APPRQVED LIMITATION 1t I'HFCOM 1 I K W G KX-175B (I3TI1OliSAVDS , OF FEET) I r n i VFR 20 1 WIF COM 2 ! CARMI74 CNC 300 I : F ,IZ9 i P 4 V l i F N A V 1 I PART OF K M C 1 ; KT-175B/KI-204 , TSO'Q GPS i CARMIN cNC 300 CI,IDESLOPE KING m 7 5 IMARKER KING IiMA-24 ATC SSH K M G KT-76A I1F COhI I CODnN H F 2000 ADF I KING KR 85 STORMSCOPE , SF200 INSIGHT ENCODEH I ACK A-SO INTERCOM SPA 400 SIGTRONICS II I j TSO C129 I i P4 : 30 , 50 3 0 3 U 25 TSO'D C l lOA I Pd 30 ! PJ 1's0 C50 U P4 W - F I M Beech A36 June 1997 SECTION 8 APPROVED SUPPLEMENTS GENERAL Flight Manual Suppiements covering the special, operations for which this aeropiane i s approved are listed below. The operations listed shall be conducted in accordance with the limitations m d instructions contained in the appropriate Supplements included in this Manual. SUPPLEMENT TITLE I . Night V.M.C. Operations ' 2. 1.F.R-operations. 3. GARMN GNC Operation (Particula amendment No 4) 4. Operations with DOOR REMOVED CIVIL hVL\TION SAFE'FY AUTIIORITY Irnnvk!.l. ITIOI'EI.I.OL, i ~ c . 350 w n a l ~ ~ ~ ~ o i i AW, PIOUA, olrm F h l nFmOm A3IPlArr;: FI.TCHT :3111,rlL FOR BtCat t'bnEE 35-C33?, E33t, F33n, F33C, 36 ~ 3 6U?aFUtIES \!rill HhRWELL F$OPEtlmS PW S'IC 5~783CE SW. NO. mrs w w m WT B E a m TN m e A ~ P L M Z AT ALL TI^ t . ~ ~ ~ t i IURTLELL P R O X L L E ~ S ARC fltSTnLLm Fm S T C rh'10ssc. moarn.rIob! ccnzcn:m \!arEflr svrrr.i?.mrS CR StTFIISam CORRRPOlm WG DFORt442iP;I X:i PIACkWS, h=C;;GT SPECIFIMTTOEi, OR WSIC AmPmE FLfCHT filWhl. ( I F APPLZCAJLE), A . F R I I P E t W l S : 1. Hark~cllconrisnt-qpccd, thrcc.bladc~l propcllav (75 Ib:. @ S h t i o n +1; >ladcls 36 and A ~ GC? C t a t l a h -9) llubs; I I l C * C 3 Y Y - 1 ) 1 at* nlC-CjlT-IRF 8lndac: 6cGB-6n, 8h68-63, 07 ~$1604-6.7 Spinncr: n - R 9 5 - 1 (9 l b s . @ Scatio? *!; t!zJc1z 3G and ~ 3 6Q SLaticn :3) Govcrnar: C1201r52 o r ~2lab ? i t c h S C t t i n c s a t 30 lnch 3ta:ion: I.72 ~2.9' - Hlch 32.0' Mi". D i a m t o r : H o t ovcr 80 inch@', n e t w d c r 78 inchcs Ew!nc: C o n s i n c n u l 1 0 - 5 2 0 4 , XO-52O-al, nnd :3-520.83 2 . Hartzcll constlnc-:peed, WQ-bladcd prspcllcr (51 Iba. C Stntion -1; Kodclt 36 and h36 e S t a t i o n - 9 ) Hub:: MC-C2Yk'-LB Or atC-C2W-Lbi 81adoz: 8kGEm or rBLBW Splhhcr: A-2295 ( 5 pbs7d5 S t a ? i m ~ i ; Iiotcl: 36 on4 n36 @ Sration -9) Covtrnsr: c 1 7 C f ~ 5 2o r D2L05& Pilch ZdLLinl:', nt ;n inch :Lltion: 1.2:: 13.0° - l\i,-h ?9.O0 l l i n . \ ) i s ~ l c t c v : t40: ovcv 0'1 i n c l ~ c z , rto!. r~n:!..r I b ? inctlc-s EnCLnc; Contancntal IO-520-iil an-I 10->PC-3U BEECHCRAn DebonairlBortanza 35-833, 35-C33, €33, f33, and G33 (Serials CD-388 thru CD-t 3OU); 35-C33A, E33A, and F33A (Serials CE-1 thru CE-1013); Bonanza E33C and F33C (Serials CJ-1 thru CJ-155); P35, S35, V35, V35TC, V35A, V35A+TC, V356, and V358-TC (Serials D-6874 thru D-10403); 36 and A36 (Serlals E-1 thru E-2061); and A36TC {Serials EA-1 thru EA-272 except EA-242) LANDPLANES PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT far the FUEL SELECTOR VALVE STOP INSTALLATION (BEECHCRAFT SfRVlCE I N S f RUCTIONS NO. 1248) GENERAL This document is to be attached to the Pilot's 0peratir.g Handbook and FAA Approved Airplane Flight Manual when the airplane is equipped with the Fuel Selector Va\ve Stop Installation which has been installed in accordance with BEECHCRAFT Service Instructions No. 1248. This document supersedes or adds to the Pilot's Operating Handbook and F A A Approved Airp!ane Flight Manual only where covered in the items contained herein. F A A A p p r o v d Issued: March, 1983 PIN 36-590002-39 NOTE This installation is not applicable to airplanes equipped with the Brittain wing tip fuel system. LIMITATIONS PLACARDS On Fuel Selector Panel: L E F T , RIGHT A N D OFF-NOT IN S A M E POSITIONS Q N ALL BONANZAS and; 1GEPRESS STOP TURN HANDLE L TO OFF _J EMERGENCY PROCEDURES No Change FAA Approved Issued: March, 1983 PIN 36-5913042-39 NORMAL PROCEDURES No Change PERFQRMANCE No Change WEIGHT AND BALANCE No Change SYSTEMS DESCRIPTION FUEL SYSTEM FUEL TANK SEL ECT/QN The fuel selector valve handje is located forward and to the left of the pilot's seat. Takeoffs and landings should be made using the tank that is more nearly futt. On airplanes equipped with the fLel selector valve stop installation [BEECHCRAFT Service instructions No. 1248), the pilot is cautioned to observe that the short, pointed end of the handle aligns with the fuel tank position being selected. The tank positions are tacated on the ah side of the valve. The OFF position js forward and to the left. An OFF position lock*out feature has been added to prevent FAA Approved Issued: March, 1983 PtN 36-590002-39 inadvertant selection of the OFF position. To select OFF. depress the lock-out stop and rotate the handle to the full clockwise position. Depression of the iock-out stop is not required when moving the handle countsrclockwise from O F F to LEFT MAIN or RIGHT MAIN. When selecting the LEFT MAtN or RIGHT MAIN fuel tanks, position handle by sight and by feeling for detent. I f the engine stops because o f insufficier~tfuel, refer fo the EMERGENCY PROCEDURES Sectior! for the Air Start procedures. Approved: -fOJ W. H. Schultz Beech Aircraft Corporation FAA Approved Issued: March, 1983 PIN 36-590002-39 Arcraft Flight Manual Supplsrnent for k h c r a R A36 equip@ with Garmin GNC 300 CASA AiRCRAFT FLIGHT MANUAL SUPPLEMENT FOR BEECHCRAFT A36 with GARMIN GNC 300 Reg No. VH-FLM Serial No. €434 1 . This supplement must be attached to the CASA approved Beechcraft A36 Aircraft Flight Manual when the Garrnin GNC 300 GPS COM system h a s been installed in accordance with Aiworthiness Instruction f 0-12 Issue 3. 2. The information contained herein supplements or supersedes t h e basic Aircraft Flight Manual onJy in those areas listed. For limitations, prccedures, and performance information not contained in this supplement, consult the basic Aircraft Flight Manual. 3. This and the following pages are to be attached to the front af the CASA approved supplement before insedion into the Aircraft Flight Manual. Approved by: 0 Delegate of CASA 20-Aug-96 Page 1 of 1 f Aircrafl Flight Manual Supplemsnl lor 8eechcraft A3q quipped wiih Garrnin GNC 300 GPS - #f installed) 1. GPS is not approved as a sole means of navigation. 2. users are cautioned that satellite avaiiability and accuracy are subject to change. 3. The pilot must monitor approved NAVAlDS and compare the information with GPS position information. This page is ta be inserted in the Flight Manual Supplement for the Garmin GNC 300 Navigation System. . I', Approved by' Delegate o l CASA Date: 20-Aug-96 Page 2 of 11 Aircraft Flight Manual Supplement for SeechcnR A36 equipped with Gamin GNC 300 LOG OF REVISIONS Approved by: Delegate of CASA Date: 20-Aug-96 Page 3 of 11 Page Revision N o Subject Date I Approval Aircrafl Flight Manual Supplement for BeechcraH A36 equip@ with Garrnin GNC 300 SECTION - G E N E R A L A. INTRODUCTION 1. EQUIPMENT DESCRIPTION The Garrnin GNC 300 system is a fully integrated panel mounted instrument, which contains a 760 channel (1 18.000 to 136.975 Mhz, in 25 Khz steps) VHF communications transceiver and a global positioning system (GPS) navigation computer. The GPS system is designed to provide the pilot with navigation and pasition information from received satellite signals. Flight plans are entered into the receiverldisplay unit as a number of waypoints to be flown. A CDI Is displayed in the GPS ROU and is repeated to a dedicated panel-mounted GDI when selected. Steering information is also coupled to the autopilot in the NAV mode. Automatic barometric aiding is provided from an A C K A-30 altitude serialirer. Pressure altitude data in this system is automatically provided from an approved source. The unit also allows communications in the aviation voice band from Therefore, this system may be used .-s a primary means of IFR navigation for GPS or DME Arrivals. The navigation database is an electronic memory containing information on airports. navaids, intersections, SiD's, STAR'S. instrument approaches, special use a~rspace,and other items of value to the piict Every 28 days, new navigattcn database information is available from Jeppesen Sanderson for any specified data base region This information is made available to the Garrnin GNC 300 receiver via a pilot accessible data base card. 5. GENERAL 1. Provided the Garrnin GNG 300 navigation recejver is receiving adequate satellite signals, the system will provide position accuracy commensurate with selective availability. The Garrnin GNC 300 h a s been demonstrated capable of and has bzen shown to meet the accuracy specifications of 1 . VFRIIFA oceanicldornestic eo route an terminal operation within the U.S . National Airspace System using WGS-84 {WAD 83) chart references in accordance with the criteria of class A2, TSO C-129, Airborne Supplemental Navigation Equipment using the Global Positionjng System (GPS). 2. VFRIIFR oceanic, domestic en route and terminal operation approval of class A 2 Global Positioning System equipment in accordance with the criteria of CASA AAC6-26 Issue 2, "Ainuarthiness Approval of Global Positioning System Navigation Equipment for use as a VFR and IFR Supplemental Navigation System". 20-Aug -96 Page 4 of II Aircralt Flight Manual Supplement fo? Beechcrafl A 3 6 equipped with Garmin GNC 300 SECTION 2 - OPERATiNG LIMITATI0N.S A The Garmin GNC 300 Pilot's Guide, Pb-4 JW-WM7-00 (or later applicable revision) or subsequent FAA approved revision, must k immediately available to the flight crew or pilots have undertaken an approved ground course. 8 . The Garrnin GNC 300 must have software version 2.02 (1995 Garrnin Corp) or subsequent F A A approved revisions installed. C . When using the Garrnin GNC 300, additional navigation equipment required for the specific type of VFUIIFR operation must be installed and operable. D. IFW navigation is prohibited unless the p i l ~ tverifies each seiected waypoint and navaid for accuracy by reference to current approved data. The pilot must verify Ithe currency of the navigation data base prjor 10 Use. E. The Garmin GNC 300 position must be checked for accuracy prior to use as a means of navigation and under the following conditions: 1 . Prior to each carnpuls~ryrepoding point dilring IFR operation when not under radar surveillance or control. 2. At or prior to arrival at each en route waypoint during RE\IAV opefation along approved RNAV routes 3. Prior lo requesting off-airway routing. and at hourly ~ntemalsIhereafter during R N A V operation off approved R N A V routes I=. When GPS integrity (Receiver Autonomous Integrity Monitor (RAIM) ) capability is lost, IFR operation using GPS data is nct authorised. G. GPS is not approved as a sole means of navigation H. Users are cautioned that satelliie avaiiabjlity and accuracy are subject to change. I. The ? : o t must monitcr approved NAVAIDS and compare the information with GPS posit:cci information. 20-Aug-96 Page 5 of 1 1 Aircraft Flight Manual Suppiemen1 lor Beechcraft A36 equipped with Garmin GNC 300 SECTION 3 - EMERGENCY I ABNORMAL PROCEDURES A. EMERGENCY PROCEDURES NO CHANGE B. ABNORMAL PROCEDURES 1. When GPS integrity (RA1M) capability is lost, the MSG annunciator located on the instrument panet will illuminate and flash along with the MSG key on the RDU. When this occurs, press the MSG key to view the new message(s).is pressed. Any messages relating to RAIM failure or degradation are described in Appendix 0 of Garmin GNC 300 Pilot's Guide 2. Certain messages will remain on the Message Page after they are viewed. If this occurs, both the RDU MSG annunciator and the MSG annunciator located on the instrument pane! will remain on continuously. 3. If the Gatmin GNC 300 navigation information displayed on the dedicated CDI is f\agged or the Garmin GNC 300 CDU displays system messages indicating a degradation or loss of navigation capability, utilise the remaining operational navigation receiver equipment as required. 4. For Garrnin GNC 300 Dead Reckoning (DR) operational procedures, refer to the Garmin GNC 300 Pilot's Guide. 20-Aug-96 Page 6 of11 Aircrafi Flight Manual Supplement for BeechcraR A36 equipped with Garmin GNC 300 SECTION 4 - NORMAL. OPERATING PROCEDURES A. OPERATION WARNlhrG . . .. ... FAMILMR~WWITH T H E EN-ROUTE OPERArrbn UF T H € . . ..' Garmin GNC 300 DOES NOT CONSTITUTE PROFiClEfiCY IN , APPROACH UPERAUONS. D o N O T ATTEMPT APPROACH: OPERA TiONS IN IMC PHOR TO ATTAINING PROFICiENCY IN THE U S E OF THE Garmin GNC 300, Norma! operating procedures are outlined in the Garrnin GNC 300 Pilot's Guide, PN 190- 00067-00 (or later applicable revision). B. SYSTEM SWITCHES AND ANNUNCIATORS 1. An Integrated Navigation Source Selector and Display Unit (INSSDU) is located on the instrument panel. This unit is used to switch navigation data from either the No. 1 VHF navigation receiver or the Garmin GNC 300 to the dedicated panel mounted CD1 and au!opilot. The unrt also annunc~atesGPS status. 2. Three switches are located on the INSSDU panel as foiloi~s' a . SOURCE SELECT switch - NAV 1 (up p o s i t ~ ~ n ) GPS (cenIre position) APPR ARM (momentary down posiiion) b. GPS SEQ switch - HOLD (up position) AUTO SEQ (down position) C . LAMP switch - BRIGHT (up position) DIM (centre position) LAMP TEST (momentary down position) 3. T h e firnctions of the s~vitchesare briefly descr~bedbelow: a. SOURCE S E L E C T 1. N14V I Data from No. 1 VHF navigation receiver will be supplied into the NAV 1 COf and autopilot. The green NAV I annunciator on the INSSOU unit will be iilurninaled. 1 1 . GPS Data from the Garrnin GNC 300 will be supplied into the dedicated GPS CDI and autopilot. The blue GPS annunciator on the INSSOU wit will be illuminated. Page 7 of 7 1 AircraR Flighi Manual Supplemen! lor Beechcrafl A36 equipped with Garmin GNC 300 NOTE: - When a LOC or ILS frecluency Is selected on VHF N A V i , nna&ation information present& to the auto-pilot wiji default to L O m L S irrespective of the position of ihe NAVIGPS switch on the Instrument panel. iii. APPR A R M NOT APPROVED FOR OPERATIONS G P S SEQ i. WOLO Wiil cause the GPS receiver to stop the automatic waypolfit sequencing. ii. AUTO SEQ The GPS receiver will automatically sequence through waypoints of the active flight plan. C. LAMP 4. 3 navigation source selectors/annunciators are incorporated in the INSSOU panel. These annunciators (including coloring) are as follows: a. NA V 7 (green) VHF NAV I selected as navigation source. b. GPS (blue) Garrn~nGNC 300 selected as navigation source. C. ARM (white) NOT APPROVED FOR OPERATIONS 5. 6 GPS status annunciators are also incorporated in the INSSDU panel. These annunciators (including coloring) are as follows: a. WPT (amber) Waypoint arrival alert, When approaching the active waypoint, the WPT annunciator will illuminate with the lead time as default set. For flight plan intermediate waypoints, the WPT annunciator will extinguish upon waypoint arrival and sequencing to the next waypoint. For an autonomous active waypoint or the last waypoint for a flight plan, the WPT annunciator will extinguish approximately 1 minute after waypoint passage. b. MSG (amber} The MSG annunciator alerts the pilot that a message is waiting in the message queue. The message may be a routine advisory message or an indications of system problems, such as loss of position. The MSG annunciator will flash until the MSG key on the RDU is pressed until all new messages are read. Messages remaining in the queue after being read will be indicated by a steady MSG annunciator illuminated. Details of the various messages are listed in Appndix E to the Garrnin GNC 300 Pilot's Guide. ' 2Q-Aug-96 Page 8 o f 51 Arcrafl Flight Manual Supplement lor Beechcrafi A36 equip@ with Garmin GNC 3W c. WOLD (amber) The HOLD annunciator alerts the pilot that the active flight Pian or approach profiie is currently in hold (pfan suspended at the current active waypoint). HOLD mode (or Suspend mode) may be manually selected by the User or automatically set by the Garrnin GNC 300 at predefined Hold Wypoints in the database (such as the Missed Approach Point (MAP) in any approach), HOLD allows the pilot to execute holding or a procedure turn when required (in the case of the MAP, the waypoint is placed in hold automatically since sequencing to the missed approach waypointls) is inhibited unless intentionally selected by the pilot (as per TSO G I 29). d. AUTO (green) Automatic waypoint sequencir!g as per active flight plan. e. WARN (red) System warning. Refer to Appendix 0 of Garrnin GNC 300 Pilot's Guide for list of warningsimessages. f . A C W (green) Approach coupled D. G P S COURSE INDICATIONS ON DEDICATEI.. PANEL MOUNTED CDI Left or right cross-track deviation, TOiFROM and navigation VALID flag data from the Garrnin GNC 300 is displayed at all times when the NAV/GPS switch is in G P S position and No. 1 VHF navigation receiver is not selected to a LOC/ILS frequency. NOTE: Manual s ~ t e c t j o n of t h e Course Selector is required for correct tracking and/or deviation information to be displayed on the hrAV f CD1. E. AUTOPILOT 1 . The autopilot when ~n NAVlLOC mode will couple from IeR or right cross-track deviation data supplied from either the VHF navigation receiver or the Garmin GNC 300 depending on t h e position of the NAVlGPS switch located on the INSSOU panel, or upon selection of a LOCliLS frequency on the No. I VHF navigation receiver. NO TE: Wtren a 10C or ILS frequency is selected on VHF NAV 1 irrespective of the position of MA V G P S switch, navigation information supplied to both the NAY .I CDI and at~fopilotwill default to VHF NAV I . 2 Left or right cross-track deviation from the Garmin GNC 300 GPS is coupled to the autopilot whenever the NAVlGPS switch i s in the GPS position and NAVlLOC is selected and engaged on the autopilot. 20-Aug-96 Page 9 of 11 ~ i r c r a f lFlighl Manual Supplement for Beechcraft A36 equip* with Garrnin GNC 300 3. An initial angle of intercept to the desired course musf be established with a manually steered heading or autopilot HDG mode. With autopilot HOG mode engaged and NAVJLOC mode armed (with the NAV/GPS switch selected to GPS), the autopilot will capture the desired track as computed from the GPS. {See Note - GPS Course Indications on dedicated panel mounted CDI). F. POWER 1. A three (3) ampere circuit breaker located in the avionics section of the circuit breaker panel powers the Garmin GNC 300 navigation system and iNSSDU unit. 20-Aug-96 Page f 0 of 11 BEECHCRAFT SERIES 33,35,36,55,58 PILOT'S OPERATING HANDBOOK AND F A A APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR INSIDE CABIN DOOR HANDLE WITH OPEN/ CLOSED PLACARD THIS SUPPLEMENT IS APPLICABLE TO PILOT'S OPERATING HANDBOOKS AND FAA APPROVED AIRPLANE FLIGHT MANUALS: (SEE NEXT PAGE FOR APPLICABILITY) Airplane Serial Number: Airplane Registration Number: W:%. Schultz Beech Aircraft Corporatior, DOA CE-2 COPYRIGHT BEECH 1990 F A A Approved P I N 58-590000-49 Issued: December, 1490 This supplement applies to the following Pilot's Operating H a ndbouks and FAA Approved Airplane Flight Manuals: F A A Approved P/N 58-590000.49 Issued: December, 1990 35-633 35-C33, E33, F33 35-C3JA, E33A, E33C F33A, F33C F33A, F33C G33 F35 G35 W 35 N35, P3S S35-TC 535 V35-TC V35A-TC V35B-TC V35E3 V35, V35A, V358 A36 36, A 3 6 A36 A36-TC " 33-590000-173 33-59OO02-9B 33-590003-7 8 33-590009-7 3 33-590009-15 33-590027-3 35-59007 1-1 3 35-590072-9 35490073-1 5 35-590094-7 -35-590110-3 35-5901 10-13 3 35-5901 13-3 .35-590116-3 35-590118-23 35-5901 18-29 35-5901I 8-31 B 36-590002-17 36-590002-19C 36-590002-37 i 36-590003-3 At1 All All CE-674 & after, CJ-129 & after CE-290 tfiru CE- 673, CJ-26 thru CJ-128 All All Aft All AjI All All All All 13-9069thru D- 9947 0-9948 & after 0-7977thru D- 9947 E-927 t h r u E-2110 except E-1946 &. E-2104 €-I t h r u E-926 E- 1 946, E-2104, E- 21 l l & after EA-1 thru EAd272 except EA-242 1 F A A Approved P I N 58-590000-49 Issued: December, 1990 MODEL 536-TC 036-TC 95-B55B 95-55,95-A55 58, 58A PART NUMBER 36-590006-3 36-590006-f 9 55-590000-49 55-590000-650 58-590000-21 *111 A/C SERIALS EA-242, EA-273 thru EA-388 except EA-326 EA-326, EA-389 &. after AIt TC-7 thru TC-501 except TC-350 & TC-37 1 TH-773 thru TH- 1395 except TH- 7389 58, 58A 58,58A 58, 58A €55, ESSA 58-590000-310 58-590000-35 TH-I thru TH-772 TH-1389,TH-1396 thru TH-1471,TH- 1476, TH-1487,TH- TC-350, TE-1 t hru TE-942, except TE-938 TE-938, TE-943 thru TE-1083 TE-I197 on!y TC-2003 & after TC-1608 thru TC- 2002 TC-371, TC-502 thru TC-3 607 TK-I thru TK-84 TK-85 thru TK-1 SO, except 7°K-7 47 95-C55,85-C55A, 58-590000-39 96-590010-17 96-590010-298 1489, TH-1498 TH-1472& after, except TH-1476, Tt-1-1487, TH-1489, TH-1498 TE-1084 & after 055, D55A, E55, E55A E55, E55A E55, E55A 95-B55. 95-BS5A 95-B55, 95-B55A 95-B55, 95-855A 58TC 58TC, 58TCA - - 96-59001 0-31 96-590010-37 96-59001 1-'I 7 96-59001 1-23 96-59001 1-25 106-590000-5 106-590000-19 L 1 MODEL PART NUMBER A / C SERIALS 58TC. 58TCA 106-590000-21 : TK-147, TK-151 &' after F A A Approved P/N 58-59000Q.49 Issued: December, 19W CONTENTS GENERAL . . . . . . . . . . . . - . . . . . . . . . . . ..Page 5 LIMiTATiONS . . . . . . . . . . . . . . . . . . . . . . . .Page 5 EMERGENCY PROCEDURES . . . . . . . . . . . . .Page 6 NORMAL PROCEDURES . . . . . . . . . . . . . . . .Page 6 PERFORMANCE . . .... . . . . . . . . . . . . . . . .Page 6 WEIGHT & BALANCE . . . . . . . . . . . . . . . . . .Page 6 SYSTEMS DESCRIPTION . . . . . . . . . . . . . . .Page 6 . . HANDLING. SERVICING 8, MAINTENANCE .Page 7 GENERAL The information in this supplement is FAA-appraved ma- terial and must be attached to the Pilot's Opefating Hand- book and FAA Approved Airplane Flight Manual when the airplane has been modified by installation of the Inside Cabin Door Handle With Open/Ctosed Placard in accor- dance with Beech Kit 351-5050, The information in this supplement wpersedes or adds to the basic Pilot's Operating Handbook and FAA Approved Airplane flight Manual only as set forth below. Users of the manual are advised to always refer to the supplement for possibly superseding information and placarding ap- plicabte to operation of the airplane. PLACARDS On inside of Cabin Door Adjacent to Door Handle: F A A Approved P / N 58-590000-49 Issued: Decernber, f 990 EMERGENCY PROCEDURES No change. NORMAL PROCEDURES BEFORE TAKEOFF All procedures specified in t h e Pilot's Operating Hand- book and F A A Approved Airplane Flight Manual for the particular airplane shall be completed. In addition, accom- plish the following: - Doors and Windows - SECURE (Check cabin door lock indicator - CLOSED) PERFORMANCE Na change. WEIGHT AND BALANCE No change. SYSTEMS DESCRlPTtON DOORS, WINDOWS AND EXITS CABIN DOUR The airplane has a conventional cabin door on the for- ward right side of the fuselage and when closed, the out- side cabin door handle is spring loaded to fit into a re- cess in the door to create a fiat aerodyndmicaily clean surface. The door may be locked with a key. To open the door from the outside, Iift the handle from its recess and pull until the door opens. F A A Approved P \ N 58-590000-49 Issued: December, 1990 To close t h e cabin door from the inside, observe that the door handle is in the open position. In this position, the latch hand0 is free to move approximately one inch in ei- ther direction before engagement of the locking mecha- nism. Then grasp the door and firmly pull the door closed, Rotate the door handle fully counterclockwise into the locked position. Observe that the door handle indica- tor is in the CLOSED position. When the door is properly locked, the door latch handle is free to move approxi- mately one inch in either direction. NOTE When checking the door latch bandle, do not move it far enough to engage t h e door latch release mechanism. Press firmly outward at t h e top rear corner of'the door. If any movement of the door is detected, completely open the door and close again following the above instructions. Ta open the door from t h e inside, depress the lock button and rotate the handle clockwise. HANDLING, SERVlCtNG, AND MAINTENANCE No change.' F A A Approved P / N 5 8-590000-49 Issued: December, 1990 FLIGHT MANUAL SUPPLEMENT NIGHT V. M, C. OPERATI GNS This aeroplane i s e l i g i b l e f o r Night V, M. C. o p e r a t i o n s pro- vided t h a t t h e radio communication a n d r a d i o n a v i g a tion s y s t e m s i n s tat led in t h e aeroplane a r e approved f o r t h i s t y p e of u p e r a t i o n - see F l i g h t Manual Section 7 - Radio S y s t e m s and Operational bimi ta t ions. Note: Reported u n s e r v l c e a b i l i t y of i n ~ t r u r r ~ e n t s , radiosystemsandequip- - merit w i l I b e i n d i c a t e d on theMaintenar,ce Release. A i r Navigation O r d e r s P a r t 2 0 r e q u i r e the placarding o r removal of unserviceable instruments, r a d i o systems and equipment. AUSTRALIA DEPARTMENT OF TRANSPORT CERTIFICATE OF AIRWORTHINESS - A I R C R m 5. This Certificate of Aitworthiness i s issued pursuant to the Convention on International Civil Aviation dated 7th December, 1944, and the Air Navipa- tion Regulations of Australia, in respect of the above rne~ltiorlcdaircraft rvhtch is consiclered to be airworthy when maintained and operated in accordance with the Air Navigation Regulations and the lirnita tions specified in the flight manual approved or issued for the aircraft under the Air Navigation Regula- tions. ; G. Subject to suspe~lsionor cancellation under the Air Navigation ReguIations, the period during which this certificate shall remain in farce shall, be from i t s date of issuc%l. . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . ....... .. ..... . .a until the aircraft ceases to be registered in the Register of Australian Aircraft. I Date of Issue 3. Aircraft Serial No. E434 Place and Year of 1 . Nationality and Registration Marks VH- m q No entries or endorsements may be made on this certificate except in the manner and by a person authorised by the Secretary to the Department of Transport. 2, Manufacturer ~eechcraf t Corpora.tion Signature &2L2-. . . . ..... - A ., , .a . . ... ALL CERTIFICATES OF AIRWORTHINESS PREVIOUSLY ISSUED IN RESPECT OF; THIS AIRCRAFT ARE HEREBY SUPERSEDED AND CANCELLED blnnl~facturer'sDesignation of Aircraft : Construction Appointment Secretary to the Department of Transport Department Delegate of the of Transport Secretary to t h e Authorised Person appointed under O the Air Navigation Regulations. 0.o.T. 14A { R e v 4 / 7 7 ) Beech ~ 3 6 U . S , A , 1973 1 4. Categories NomaZ i S.L. r&E -OFF WEIGHT 1 - L B 1 A 2 2 0 0 i 1 i \ 'q\ L 0 ~ l T ' f HfICWT - FEET j uA 5 0 1 0 a r~ultll~'i. WIHD C O W N E N T * K*TS f HOT E : 1 FLA S . TEC CORPORATION R T . 3, BLOG. 946 wOCTERS INDUSTRIAL COMPLEX M I N E R A L WELLS, T E X A S 76067 FAA APPROVES SUPPLEMtNT T0 PILOT'S O P E R k T i l i G HAX3jgQ1: A?iZ/QP. FAA APPROVE0 A1 R?LANE FC I GET MANUAL FOR 8 E E C t i M O D E L S F33A, S/?i CE-316 & UP, 36 AND A36 S - T E C S'tSTE!! S O THO A X I S A U T O P A T I C F l I G E T G U I D A N C E SYSTEK ( 11: V2i.T S Y S T E K ) R E G . N 2 , S E R , !:,'. F ? P T h i s s u p ? I e m e n t m;jt be a t t a c h e d t o t h i a 2 p i i c ? S l ~;h5 A ~ p r o v e dR i r p l a n ~ F l is?: Manual, P i l o t ' s O p e r a t i n g FLandSsok, o r F i l o t ' s O p e r a t j n g Eandbook and FA;. A';:- roved A i r p l a n e F l i g h t F l z ~ u a l modified by t h ? i ~ s C 2 i l d t i c n cf S - T E C Syscer;.- 53 A u t o p i l o t Model ST- 189-50 i n s t ; l ' r e r ; ir, a t . c ~ ? - d z n c av i t h S T C SA5240S'rl-0. !r,c ir,f:?** mation c o n t a i n e d h ? r e i n sup?jern?nts t h ~ir,forr.?Cigr, o f t h e b a s i c PO? a n l l c y - A ' ? : ; for Lini t a t i o n s , P r c c e d ~ r e sand P ? r f o r , ~ c c c ei n = o r ~ ? i i o nn o t c o n t a i n e d i n ; h i s S u p p l e m e n t , c o n s ~ lt "Lhe b a s i c PO:+ a n d / o r 4;;;. S E C T I O N I This m a n u a l i s t o a c q u a i n t t h e p i l o t w i t h t h e f e a t g r e s a n d f u n c t i o n s s f the S y s t e m 50 Two AXES A u t o p i l o t and t o p r o v l d e o p e r a t i n g i n s t r u c t i o n s for t h e system when instal l e d i n t h e above a i r c r a f t model (5). The a i r c r a f t must be o p e r a t e d w i t h i n t h e 1 i n t i t a t i o n s herein p r o v i d e d when t h e a u t o p i l o t i s i n u s e . S E C T I O N I I O P E R A T I N G LIMITATICmh'S 1. A u t o p i l o t o p 2 r a t i o n p r o h i b i t e d a b o v e 178 KIAS (205 b l P l i , I A S ) , ( A u t o p i l o t Vmo). 2. A u t o p i l o t m9st be OFF d u r i ~ g t a k e - o f f and l a n d i n g , 3 . U s e o f f l a p s p r o h i b i t e d d u r i n g o p e r a t i o n s i n a l t i t u d e h o l d mode. Page 1 c f 7 S -TECCORPORATION MINERAL WELLS, T E X A S 76067 EMERGENCY O P E R A T I N G P R O C E D U R E S In t h e e v e n t o f a n a u t o p i l o t m a l f u n c t i o n , o r any t i m e t h e autopilot i s not p e r f o r m i n g a s e x p e c t e d o r c o m n d e d , do not a t t e m p t t o i d e n t i f y t h e system p r o b l e m . I r m e d i a t e l y r e g a i n control o f t h e a i r c r a f t by overpowering t h e a u t o p i l ~ t a s n e c e s s a r y and t h e n d i s c o n n e c t t h e a u t o p i l o t ; Do not reengage the autopilot u n t i l the p r o b l e m h a s been i d e n t i f i e d and corrected. 2 . Autopilot my be d i s c o n n e c t e d b y : a + Oepressirrg t h e " A P Oisconnect" S w i t c h on the l e f t horn o f t h e p i l o t ' s control wheel ( i f i n s t a l l e d ) . b. D e p r e s s i n g the tlON-OFF" S w i t c h on t h e a u t o p i b t p r o g r a m m e r uni t , c. having autopilot r n ~ s t e rs w i t c h t o "OFF" p o s i t i o n . d . P u l l i n g t h e a u t o p i l o t circuit breaker. 2. A l t i t u d e l o s s d u r i n g a m a l f u n c t i o n a n d r e c o v e r y . a . The f o l l o ~ i n g a 1 t i t u d e l o s s e s a n d b a n k a n g l e s w e r e recorded 2 f t ~ ra r . a l f u n c t i o n w i t h a 3 second recov- e r y d e l a y : Conf i q u r a t i o n - B ? n t Anql e / A 1 t i t u d e Loss C l i m b 55' / - 6 0 ' C r u i s e 60' / - 2 2 0 ' D e s c e n t 51" -320' b . The following a l t f t u d e l o s s e s a n d b 2 n k a n g l e s w s r e recorded ~ f t e r2 K 2 1 f u n c t i o n w i t h 2 1 second recov- e r y d e l a y : Conf i g u r d t i o n Bank Angle/A: t i t u d e l o s s Mdneuvering 20' / - 4 0 ' Approach (coup1 96 o r uncoupled) 2 0 9 - 4 0 ' The a b ~ ~ e v a l u e s zr? t h e w o r s t c a s e f o r a l l t h e mcdels covered by t h i s d o c u ~ ~ z n t . S E C T I O N IV I . NORMAL O P E R A T I t i G PROCEDURES 4 - 1 S Y S T E M DESCRIPTION The S y s t e m 50 is a pure r a t e a u t o p i l o t w h i c h u s e s an i n c l i n e d r a t e gyro i n t h e Turn C o o r d i n a t o r i n s t r u m e n t a s t h e prirrary r o l l and t u r n r a t e sensor a n d an accelePpIw4.er and an a b s o l u t e p r e s s u r e t r a n s d u c e r a s p i t c h rate s e n s o r s . The ? " + , I ~ 0 ~ r d i n d t o r i n c l u d e s a n a u t o p i l o t p i c k - o f f , a gyro R?#'.i d e t e c t o r a n d an i n s t r u m e n t power monitor. Cow e l e c t r i c a l power w i l l c a u s e t h e i n s t r u m e n t " f l a 4 " t o a p p e a r w h i l e l o w R P M w i l l c ? u s e t h e a u t o p i l o t t o disconnect. The autopilot i n c l u d e s an automa t i c p r e - f l i g h t t e s t f e a t u r e t h a t allows a v i s u a l check o f a l l t k a a n n u z ~ i a t o rI a 3 p ~an6 checks c r i t i c a l e l e m e n t s o f the a c c e l e r o m e t e r s y s t e m . The t e s t f e a t u r e w i l l n o t enable a u t o p i l o t f u n c t i o n u n l e s s t h e a u t o m a t i c t e s t seqyence i s s a t i s f a c t o r l y completed. FAA/OAS APPROY E D f'/N 89335 D A T E : 1 1 - I $ - 5 3 Pz;e 2 o f 7 S . T E C C O F ~ ~ Q R A T I O ~ J M I N E R A L WELLS, TEXAS 76067 When the p r e - f l i g h t t ? s t i s s? t i s f d c t o r i l y c o m p l e t e d and when t h e r a t e gyr: 8PM i s c o r r e c t , t h e green "RW"l i g h t w i l l illuninate i n d i c a t i ~ g the a u t o - p i l o t i s ready f o r t h e f u n c t i o n d l check a n d o p e r a t i o n . The a u t o p i l o t c a n m t be engdged u n l e s s t h e " R D Y " l i g 9 t i s i l l u m i c d t e d . When t h e systee i s e q s i p e e d r r i t i ; t h e o n t i o c a l 3" A i r O r i v e f i C i r e c t i a n 2 l Gyro ( D . G . ) O r 2 COK;?ES 5ys:e-, dir?::l-,n?.: i n f o r m a t i o n j s c r d v i d e t T S ?;s a ~ t o p i l o tby a h e a 2 i n : k g i n t h ~ i n s ; r d r : e n t . PitcPI a x i s c o n t r o l i s p r o v i d e d f o r t h e a1 t i t u d c h o l d f u n c t i o n b y use o f t h e a c c e l e r ~ m e t ~ r &r?d the p r e s s u r ? t r a n s d x e r . When t h e a1 t i t u d e h o l d mode i s engag$< a n e l e v z t o r trim s e n s o r i n the p i t c h s e r v o w i l l d e t e c t t h e e l e v a t c r trir;; c o n d i t i o n . Ghen e l e v a t o r trim i s necessary l o re-establ i s h 2 trir.:! c o r , b i t i o n , trirr, i n d i c z t o r ? i9nt.s on th.? p r o ; - - ? x : ? r u n j t v i l 'I i l l g - i n z t ~ :z i n d i c a t e t h e d i r e c t i o n t~ t r i r ttr, rss"r3re E t r j G ~ 1 7 i e d c ~ n a i t j ~ r , . 1. ! ! G < E . 2 ~ . ~ , ; r ~ i ; ~ j r - 2nc An>ljr;: i d : ~ v Lr,; ", P~.r?*.i'-5 , .cde s v ; i t c h ~ s27.: ?or,,?. c i a t i o n f c r t h e s y s t e m . FM /R?,5 A??ROVEC; p/:t 89335 DATE: 11-18-83 Page 3 o f 7 S - T E C CORPORAT:!,: MINERAL W E L L S , TEXA', 75267 3 . 8p:dy L i g h t (R3Y) - Green R D ' i l a m p i l l u f i i n a t e s when z ~ t c p i l o t i s r e 2 d y f o r engagemefi t . 4 . O h - O . F i S t a S i 1 i z ~ r Kode Swi t c h - Monentzry actuatior, eng2ges roll s y s t e r i r ; s t 2 3 i l i z e r ( S T S ! god. and 2 1 1 0 % ~use o f t h ~ . ; , J r r k r ; ~ b ( I t e - :. t 3 corr!-r~znd t u r r ; r a t e des i r e d . W?,zp tne sy~rer;; i ~ ; . g ~ z t j n g a momentzry a c t u a t i o n w i j 1 d i s e n g a g e t h e s y s t e c and c ? n < e ] a 1 1 a ~ n u n c i a t i o n s , 5. A1 t i t u d e P ~ d dS w i t c h ( A L T ) - Momentary a c t t l a t i o n w i l l engage E I t i t u d e h o l d mcde O r d i s e n g z g ~a 1 t i t u d e rode i i p r e v i 0 1 i 5 l y p ~ ~ i 3 e d .T h i s f u n - c t i o n i s a1 so a v a i l a b l e by u s e o f a n option21 control w h e e l rraunted a l t i t u d e e n ~ z g e j d i s e n g a g e s w i t c h , f o r a d d e d c o n v e n i e n c e . 6. h v i g a t i o n r o d e S w i t c h - Moflantary z ~ t i v ? t i ~ r h f l l engzg? t h E VQ3 T r z c k i n ~Mode. ? h i s mcde prcZti;(?s 13% s;~s:~: c ? i ~ ,f f ~ r C O r f o r t ' ~ > I e cress : ~ v ? : ~ y t r ~ z k i n ; . 0. U? T r i m L i g h t ( U P ) - T h i s 1 i g h t i l l u ~ i n z t ? s t3 i s d i c z t e t h e nee3 f o r nose t r i , ~ : . 1. Turr; KsoS a c d F ~ a d i ~ S w i t c h - Th? t u r c knob a ; l o x ; t E i 2 s a l e c c i o r ; o ? -t v r n r a t e 5 u.2 t o s t z r ; d a r d r a t e ' 3 3 / 5 e c . ) e i t h ? r + r i , s k t C r - I e f i . I u r c - i n g t h e knob t o t h e r i g h t o r l e f t w i l l c d ~ s e2 t u r n t h d t 1 s p t - o p o r t i o n 2 l t o t h e disp1acezer;t o f t h e knob f r o z c e n t e r . For l e v e l f7 i g h t t h e el e c t r o r L i c s p r o v i d e a s m a l 'l d e a d zone o f a p p r o x i r r z t e l y lo0 a t t h e c e n t e r i n d i c e . To a c t u a t e h e a d i n g mode, momentdrily de?t-ess t h e t u r n knot.. T O r e t u r n t o S T 6 b d e f r o m HOG, d e p r e s s t h e t u r n k n o b . W h ~ nt h e s y s t e q i s o a ? - a t i n g i n a n y r a d i s mob? a n d t h e s y s t e n i s e : a i p x i w i t h a D . G . , d s ~ e s s i n c t u r n knn5 w i l l r e t u r n the s y s t e " t s F 2 5 P c d e d i t ~ c t l y . P a g e 4 o f 7 :-, 7 7 r- r l ] . t l :- 'Ll <? " I: 0 0 1 *U r t l L 1 1. ( I > an L *- -17 L nr or r - ~ r .c -1 0 1.n LJ. 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S e l e c t A P E Rode - t h e ~ o r . t r ~ 1 wheel s h o u l d d g ~ i n f c l l e v : r a . d i ~c e e 3 l e rr!>veyent a n d w i t h r 3 r e a u t h o r i t y t h 3 s produces by Nk\i Mode. 7 . Move c o n t r o l w h e e l t o l e v e l f l i g h t p ~ s f t i ~ r ; - Engage ALT M o d e . M v e c o n t r o l w h e e l f c r e 2 n d a f t t o o v e r p o n d e r p i t c h servo c 1 1 ~ t c b . O v e r p o w e r s c t i o n s h c ~ l b be s - 9 9 t h w f L h fit n ~ i s ec r j e r k y f e e l . ] f U~.JS::? sclinds o r e x c e s s i v e p l ? y i s d E t e c t e d , + 2 v e t h e s e r v o i f i s t a 7 1 a t i o n i n s s e r t c - c p r i o r t o fli g h t . -t . ; r i ~ C i y : ; l - Fl.iar,sal1 y 2 2 2 7 b:r,;c ~ T ~ s s ; ; T ~ t: ~ i . j ~ * : r ~ l w h 3 f . 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M a n e u v e r z i r c r a f t t o s e l e c t e d r a d i a l ( o r 1 0 ~ d l j ~ ? r )w i t k i n - ! nee::<- w i d t h and w i t h i n 10' o f t h e c o u r s e heading. 3 . E n g a g e N A V M d e f o r V04? t r a c k i n g . 1. Engage A P R Rode f o r V O ? o r L O C a p p r o a c h I o t r z c k t h e l o c a l i z e r f r o n t c o u r s e o u t b o u n d t g : k e p r o c e d ~ r et u r n a r e ? , nar,euvEr t; t h e l K d ? i z a r :er,t?r w h e c Gn ; h c c;t?~;r.< h?"ic;, S E ; ~ C ~ ? E V ~Yode. To t r a c k t h ? I c c a l i z e r back c o u r s e i c > c ; . r , d , 1;;2n?r;~?r t a t h e .ocaliz e r b z z k cs:;rs? c e n t s r a n d , when Cn t ' n ~ir,':;;r,r', k~?:",~r;;, $51 ec t Rf': 406 e . lEQU I RED O ? E R 4 T I R G E Q U I P?!E?iT ' e x t o f t h i s Sec:ion n o t ? ? f e z t e d b1; i r t s t a l l a t i ~ r ~ c f t h i s e;l;ipael:t. ' e x t o f t h i s S e c t i o n n o t a f f e c t e d by i n s t d l l a t i o r , o f t h i s equl\Frnrnt. s - T E C C O W O R A T I O ~ ~ J ' DAS 5 SL P/fi 8 9 3 3 5 -D A T E : 11-18-83 Page 7 o f 7 CASA APPROVED BEECH A36 VH-FIM SUPPLEMENT S-TEC AbTOPILOT SYSTEM AUTO A V I h DESIGN FLIGHT MANUAL SUPPLEMENT 9614591FMS AUSTRALIAN APPROVED FLIGHT MANUAL SUPPLEMENT S-TEC AUTOPILOT SYSTEM (310DEIJ ST-189-50) This manual consists of this Cover Page and die CASA approved Log of Pages and the S - E C Corporation F M approved f;li@~t Mama1 Supplement PM 89335, dated 1 I - 18-83 (7 Pages) 'I'his supplement must be incorporated itlto the approved Beech Flight Manuat when the S-TEC auropitot system (Modzl ST-189-50) i s installed in accordar~cewith Auto Avia Design Engineering Instruct ion 96/45 9 E I 1. ?Itinfomatioa c orltained Iierein supplemexrts the infw-mation in the basic aircraft Flight Manual. For limitations, proccd~rres, aud performance data not contained it1 h i s docutuent, consult the aircraft Flight Manual. REVISION: 0 PAGE 1 OF 2 CASA APPROVED BEECH A36 VH-FIM SUPPLEMENT S-TEC AUTOPILOT SYSTEM LOG OF P A G E S ORICMAL. ISSUE: 17th September, 1336 ISSUE 0 0 DATE 1 7th Sep ternher, 1 996 t 7th Scpternbcr, 1996 S-TEC Corporation FAA approved Flight Manual Supplement PIN 89335, dated 1 1-18-83: PAGE 1 2 3 4 5 6 7 DATE 13th November, 1983 18th November, 1983 18th November, 1983 tQth November, 1983 18th November, 1983 18th November, 1983 18th November, 1983 Approved: Dated: .2. .6. .S E P . . . . .1996 . . . . . for the Authority REVISION: O PAGE 2 OF 2 BEECHCRAFT Bonanza 36.A 3 6 E - l t h ~ E-926 SECTION I GENERAL TABLE OF CONTENTS SUBJECT Imponant Notice ................................1-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . Use of the Handbook 1-4 Revising the Handbook .....................I.... 1-7 Airplane Flight Manual Supplements Aevlsion Record ................... .......... 1-8 Vendor-Issued STC Supplements ................. 1-8 Airplans Three Mew ............................ 1-9 Ground Turning Clearance ...................... 1-10 Descriptive Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-11 Ensine .....................................1-11 Pr0~0l18r .I.............llIl...........l...l 1-11 FlId .....*................................. 1-11 Ofl Cepacity ........................I....... 1-12 Wei~hW............................I....... 1-12 Cabin And Entry Dimensions ................ 1.12 Baggage Space and Entry Dimensions ....... 1 -1 2 Spacfic Loadings ......................I.1..1-12 General Airspeed Terminology and Symbols ..... 3-13 Meteorological Terminology ................... ,. 1-16 Power Terminology ..................am....,.... 1-16 Engine Controls and lnstrumenfs ................ 1-16 Airplane hrforrnance and Flight . Planning T e dnology ........................ 1 17 ................ Weight and Balance Terminology 1-18 August 1982 Section I General BEECt-ICRAFT Bonanza 36, A 3 6 E-1 thru E-926 INTENTIONALLY LEFT BLANK August 1982 BEECHCRAFT Bonanza 36,A 3 6 Section l E-1 thru E-926 General THANK YOU . . . for displaying confidence in us by selecting a BEECHCRAFT airplane. Our design engineers, assemblers and inspectors have utilized their skills and years of experience to ensure that the BEECHCRAFT Bonanza meets the high standards of quality and performance for which BEECHCRAFT airplanes have become famous t h ~ o u g h o u tthe world. IMPORTANT NOTICE This handbook must be read carefully by the owner a n d operator in order to become famitiar with the operation of the BEECHCRAFT Bonanza, The handbook presents suggestions and recommendations to help obtain safe and maximum performance without sacrificing economy. The BEECHCRAFT Bonanza must be operated according to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual, anwor placards located in the airplane. As a further reminder, the owner and operator of this airplane should also be familiar with the applicable Federal A v i a t i o n Regulations concerning operation and maintenance of the airplane and FAR Part 91 General Operating and Flight Rules. Likewise this airplane must be operated a n d maintained jn accordance with FAA Airworthiness Directives which may be issued against it. The Federal Aviation Regulations place the responsibility for t h e maintenance of this airplane on the owner and the operator who must ensure that aII maintenance is done by quafified mechanics in conformity with at! airworthiness requirements established for this airplane. All limits, procedures, safety practices, time limits, servicing, and maintenance requirements contained in this handbook are considered mandatory for the continued airworthiness of this airplane, in a condition equal to that of its original manufacture. August 1982 Section I BEECHCRAFT Bonanza 36,A36 General E - 1 thru E - 9 2 6 Authorized BEECHCRAm Aero or Aviation Centers or International Distributors or Dealers can provide recommended modification, service, a n d aperating procedures issued by both F A 4 and Beech Aircraft Corporation, designed to get maximum utility and safety from this airplane. USE OF THE HANDBOOK The Pilot's Operating Handbook is designed to facilitate maintaining documents necessary for the safe and efficient operation of the BEECHCRAFT Bonanza, The handbook h a s been prepared in loose leaf form for ease in maintenance and in a convenient size for storage. The handbook has been arranged with quick reference labs im- printed with the title of each section and contains ten basic divisions: Section 1 General Section 2 Limitations Section 3 Emergency Procedures Section 4 Norma! Procedures Section 5 Performance Section 6 Weight and BalanceEquipment LisC Section 7 S y s t e m s Description Section 8 Handling, Servicing and Maintenance Section 9 Supplements Section 10 Safety Information August 1982 BEECHCRAFT Bonanza 36,A 3 6 E-3 thru E - 9 2 6 Section l General NOTE Except as noted, all airspeeds quoted in this handbook are Indicated Airspeeds (IAS}a n d as- s u m e zero instrument error, tn a n effort to provide as complete coverage as possible, appf icable to a n y configuration of the airplane, some optionai equipment has been included in the scope of the handbook. How- ever, due to the variety of airplane appoint- ments and arrangements available, optional equipment described and depicted herein may not be designated as such in every case. The following information may be provided t o the holder of this manual automatically: 3 . Original issues and revisions of Class I and Class 11 Service instructions 2. Original issues and revisions of FAA Ap- proved Airplane Flight Manual Supple- ments 3. Reissues and revisions of FAA Approved Airplane Flight Manuals, Flight Hand- books, Owner's Manuals, Pilot's Op- erating Manuals. and Pilot's Operating Handbooks This service is free and will be provided only to holders of this handbook who are listed on t h e FAA Aircraft Registration Branch List or t h e BEECHCRAFT International Owners Notifi- cation Service List, and then only if you are listed by airplane serial number for the mode{ August 1982 1-5 Section I B E E C H C R A F T B O ~ I ~ ~ Z ~ 36.A 3 6 General E-f thru E-926 far which this handbook is applicable. For detailed information on how to obtain "Revision Service" appiicable to this hand- book or other BEECHCRAFT Service Publj- cations consult a BEECHCRAFT Aero or Aviation Center or International Distributor or Dealer, or refer to the latest revision of BEECH- CRAFT Service Instructions No. 0250-010. BEECH AIRCRAFT CORPORATION EX- PRESSLY RESERVES THE RIGHT "C SUPER- SEDE, CANCEL, AND/OR DECLARE QB- SOtETE, WTHOUT PRIOR NOTICE, ANY PART, PART NUMBER, KIT OR PUBLICATION REF- ERENCED IN THE HANDBOOK. The uwnerjoperator should always refer t o all supplements, whether STC Supplements or Beech SuppIements, for possible placards, limitations. normal, ernergenc y and other op- erational procedures for proper operation of t h e airplane with optional equipment installed. August 1982 BEECHCRAFT Bonanza 36, A 3 6 E- t t h r u E-926 Section 1 General REVISING f HE HANDBOOK Immediately fallowing the title page is t h e "Log of Revisions" page(s). f h e tog of Revisions pages are used for maintaining a listing of a \ l effective pages in the hand- book (except the SUPPLEMENTS section), and as a record of revisions to these pages. In the lower right corner of the outlined portion of the Log of Revisions i s a box containing a capital letter which denotes the issue or reissue of t h e handbook. This letter may be suffixed by a number which indicates the numerical revision, When a revision t o any information in the handbook is made, a new bg of Ae- visions will be issued. All Logs of Revisions must be re- tained in the handbook to provide a c u r r e n t record of m a - terial status until a reissue is made, WARNING When this handbook is used for airplane operational purposes it is the pilot's respon- sibility to maintain it in current status. August 1982 Section I BEECHCRAFT Bonanza 36,A36 General €-I thru E-926 AIRPLANE FLIGHT MANUAL SU PPLEM.ENTS REVISION R E C O R D Section IX contains the FAA Approved Airplane Flight Manual Supplements headed by a Log of Supplements page. On the "Log'' page is a listing of t h e FAA Approved Swppiemental Equipment available for installation on the airplane. When new supplements are received or existing supplements are revised, a new "Log" page will repiace the previous one, since it contains a listing of a l l previous approvals, plus the new approval. The supplemental material will be added to the grouping in accordance with the descriptive listing. Upon receipt of a new or revised supplement, compare the " t o g " page just received with the existing "Log" page in t h e manual. Retain the "Log" page with the latest date on the bottom of t h e page and discard the other log. VENDOR-ISSUED STC SUPPLEMENTS When a new airplane is delivered from the factory, the handbook delivered with it contains either an STC ISuppjemental Type Certificate) Supplement or a Beech Flight Manual Supplement for every installed item requiring a supplement, If a new handbook for operation of the airplane is obtained at a later date, it i s the responsi- bility of t h e owner/operator to ensure that ail required STC Supplements ( a s well as weight and balance and other pertinent data) are transferred into the new handbook 1 - 8 August 1982 BEECHCRAFf Bonanza 38,A36 E-1 thm E-926 WING AREA '177.6 sq. ft +'I81 .O sq. f t *36 prior to E-185 **A38, E-t 85 t h r ~E-926 AtRPlANE THREE-VIEW August 1982 Section I BEECHCRAFT Bonanza 36,A36 General E-1 thru E-926 G R O U N D TURNING CLEARANCE Radius for Wing Tip . . . . . . . . . . . . . . . . . . 27 ft. 7 in. Radius for Nose Wheel . . . . . . . . . . . . . . . I3 ft. 8 in. Radius for Inside Gear . . . . . . . . . . . . . . . . 6 f t . 3 in+ Radius far Outside Gear . . . . . . . . . . . . . 15 f t . 10 in, TURNING RADII ARE CALCULATED USING FULL STEER- ING, ONE 8RAKE AND PARTIAL POWER. 1- 10 August 1982 BEECHCRAFT Bonanza 3 6 . A 3 6 E-1 thru E-926 Section I General DESCRIPTIVE DATA ENGINE One Telsdyne Continental Motors Corporation engine model 10-520-0, 10-520-BA or 10.520-80. It is a fuel- injected, direct-drive, air-coaled, horizontally-opposed, 6 . cylinder. 520-cubic inch-displacement, 285-horsepower- rated engine. McCauley constant speed, two blade, 84 inch diameter propeller using a McCauley 2A36C23 hub with 848-0 blades. O f McCauley constant speed, three blade, 80 inch diameter propeller using a McCauiey 3A32C76 hub with 82NB-2 blades. NOTE Other p r o p e / / e r s may be approved but not installed as original equipment. These are listed in the FAAAircraft Specification 3A7 5 or approved by Supplemental Type Certificate. FUEL Aviation Gasoline 100LL (blue) or f 00 (green) minimum grade. S TANDARD $ YS TEM Total Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 gat. Total Usable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 gal. OPTIONAL SYSTEM Total Capacity . . . . . . . . . . . . . . . . . . . .... . . . . , 80 gal. Total Usable . . . . . . . . . . . . . . . . . , . . . . . . . . . . . A74 gal. August 1982 1-7 I Section 1 General 8EECHCRAFT Bonanza 36,A36 E-l thru E-926 OIL CAPACITY The oil capacity is 12 q u a r t s . WEIGHTS Maximum Ramp Weight . . . . . . . . . . . . . . . . . . . . 361 2 Ibs Maximum Take-Off Weight . . . . . . . . . . . . . . . . . 3600 lbs . . . . . . . . . . . . . . . . . . Maximum landing Weight 3600 ibs Maximum Zero Fuej Weight . . . . . . No Structural Limit Maximum Weight in Baggage Compartment . . . . . . . . . . . . . . . . . . . 400 Ibs. CABIN AND ENTRY DIMENSIONS Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 f t I f in. Height . . . . . . . . . . . . . . . . . . . . . . . . . ... . . . . . . . . 4 f t 2 in. Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 ft 6 in. Cabin Door . . . . . . . . . . . . . . . . 37 in. wide by 36 in. high BAGGAGE SPACE AND ENTRY OtMENSlONS Compartment Volume . . . . . . . , . . . . . . . . . . . . . . . 40 cu ft Hat Shelf Volume . . . . . . . . . . . . . . . . . . . . . . . , . . 7.7 cu f t Door Width (Minimum) . . . . . . . . . . . . . . . . . . . ..... 45 in. Door Height (Minimum) . . . . . . . . . . . . . . . . . . . . .- .. 35 in. SPECIFIC LOAD1NGS (Maximum Take-Off Weight} Wing Loading 136) . . . . . . . . . . . . . . . . . . . . .. 20.3 Ib&q ft Wing Loading (A36) . . . . . . . . . . . . . . . . . . . . 7 9.9 Ibq'sq ft Power loading . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.6 lbqhp 1-12 August 7982 BEECHCRAFT B o n a n z a 36.A36 E-? thru E-926 GENERAL AIRSPEED TERMINOLOGY A N D SYMBOLS C A S Calibrated Airspeed is the indicated speed of an airplane, corrected for position and instrument error. Calibrated airspeed is q u a i to true airspeed in standard atmosphere a t sea level. GS Ground Speed is t h e speed of a n airplane relative to the ground. IAS Indicated Airspeed is the speed of an airplane as shown on the airspeed indicator when corrected for instrument error. IAS values published i n this handbook assume zero instrument error. KCAS Calibrated Airspeed expressed in "knots". KlAS Indicated Airspeed expressed in "knots". TAS True Airsceed is the airspeed of a n airplane relative to undisturbed air which is the GAS corrected for altitude, temperature, and compressibility. V~ Maneuvering Speed is t h e maximum speed at which application of full available aero- dynamic control will not overstress the airplane. V~~ Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a pre- scribed extended position. August 1982 1-13 Section I General BEECHCRAFT Bonanza 36,A36 E- 'I thru E-926 V~~ Maximum Landing Gear Extended Speed is the maximum speed at which a n airplane can be safefy flown with t h e landing gear extended. V~~ . Maximum Landing Gear Operating Speed is the maximum speed a t which the landing gear can be safely extended or retracted. 'NE Never Exceed Speed is the speed limit that may not be exceeded ar any time. V~~ Maximum Srructuraf Cruising Speed is the vC speed that should not be exceeded except in smooth air and then only with caution. V~ Slalling Speed or the minimum steady flight speed at which the airplane is controllable. V~~ Stalling Speed or the minimum s~eadyflight speed at which the airplane is controtlable in t h e landing configuration, 'X Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in t h e shortest possible horizonral distance. Vy Best Rate-of-Climb Speed is t h e airspeed which delivers the greatest gain in altitude in the shortest possible time. August 7982 BEECHCRAFT Bonanza 36,A36 Section l E - 1 thru E-926 General METEOROLOGiCAt TERMINOLOGY OAT International Standard Atmosphere in which (1 ) T h e air is a dry perfect gas; (2) The temperature a t sea level is I5 O Celsius (5g0 Fahrenheit); ( 3 ) The pressure at sea level is 29.92 in Hg. (1013,2millibars); (4) The temperature gradient from sea level to the altitude at which the temperature is -56.s0C (-69.7O F) is -0.00198°C (-0.003566OF) per foot and zero above that altitude. Outside Air Temperature is the free air static temperature, obtained either from inflight temperature indica- tions adjusted for instrument error and compressibility effects, or ground meteorological sources. Indicated The number actually read from an Pressure a lttrneter when the barometric sub- Altitude scale has been set to 29.92 in Hg. (107 3,2millibars). Pressure Altitude measured from standard Aititude sea-level pressure (29.92 in, Hg) by a pressure or barometric a ltimetar. It is the indicated pressure altitude corrected for position and instrument error, In this Handbook, altimeter instrument errors a r e assumed to be zero. Position errors may be obtained from the Altimeter Correction Graph, August 1982 Section l General Station Pressure Wind BEECHCRAFT Bonanza 36,A 3 5 E - f thru E-926 Actual atmospheric pressure at field elevation. The wind velocities recorded a s variables on the charts of this hand- book are to be understood a s the head- wind or tailwind components of the reported winds, POWER TERMINOLOGY Take off and Highest power rating Maximum not limited by time. Continuous Cruise Power recommended for Climb cruise climb. ENGINE CONTROLS A N D iNSTRUMENfS Throttle Used to control power by intro- Control ducing fuel-air mixture into the intake passages of the engine. Settings are reflected by readings on the manifold pressure gage. Propeller Control Mixture Control This control requests the propeller governor to maintain engine] propeller rpm at a selected value by controlling propeller blade angle, This control is used ta set fuel flow in all modes of operation and cuts off f u e l completely for engine s h u t down. August 1982 BEECHCRAFT Bonanza 36,A 3 6 E-1 t h ~ ~ E-926 Section 1 General EGT This indicator is used to identify (Exhaust Gas the lean and best p w e r fuel Temperature flow for various power Indicator) settings. Tachometer Propel!er Governor fndicates the rpm of the snginql propel lor. Regulates the rpm of the engine/ propeller by Increasing or decreasing the propeller pitch through a pitch change mechenism in the propeller hub. AIRPLANE PERFORMANCE AND FUQHT PUNNING TERMINOLOGY Climb Gradient The ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. Demonstrated The maximum BUO crosswind corn- Crosswind pansnt for which adequate control of Velocity the airplane during takeoff and land- ing was actually demonstrated during certification tests* Route Segment Minimum enroute IFR' altitude. A part of a route. Each end of that part is identified by: (1) a geograph- ical location; or (2) a point at which a definite radio fix can be established. August 1982 Section I General GPH PPH BEECHCRAFT Bonanza 3 6 , A 3 6 E-? thru E-926 U.S. Gallons per hour, Pounds per hour. WEIGHT AND BALANCE TERMINOLOGY Refere nce An imaginary vertical plane from Datum which all horizontal distances are measured for balance purposes. Station A location along the airplane fuselage uslral1y given in rerrns of distance from the reference datum. Arm The horizontal distance from the ref- erence datum ro the center of gravity (C.G.) of an item, Moment The product of the weight of an item mu1tiplied by irs arm. (Moment divided by a constant is used to simplify bal- ance calculations by reducing the number of digits.) Airplane The point at which an airplane would Center of balance if suspended. Its distance Gravity from the reference datum is found (C.G.) by dividing the total moment by the tota! weight of the airplane. C.G. Arm The arm obtained by adding the air- plane's individual moments and dividing the sum b y the totat weight. August 1982 BEECH CRAFT Bonanza 36,A36 €4 thru E-926 C.G. Limits Usable Fusl Unusable Fusl Standard EmpW W~ight Basic E W ~ Y Weight Payload Useful Laad Maximum Ramp Weight Maximum Take-off Weight Maximum hnding Weight Section l Qeneral The extreme center of gravlry !ma- tions within whleh tbe airplane must be operated at a given weight. Fuel available for flight planning. Fuel rlsmsining after a runout test has been completed in accodance with governmental regulations. Weight of a standard airplane including unusable fuel, full operating fluids and fult oil. Standard empty weight plus optional equipment. Weight of occupants, cargo end baggage. Difference between take-off weight, or ramp weight if applicable, end besic empty weight. Maximum weight approved fur ground maneuvsring. [It Includes weight of start taxi, and run-up fuel). Maximum weight approved for the start of the take-off run, Maximum weight approvd for th8 landing touchdown. August 1982 Section 1 General Zero Fuel Weight T a r e Leveling Poi nts Jack Points BEECHCRAFT Bonanza 36,A 3 6 E - I thru E-926 Weighr exclusive of usable fuel. The weight of chocks, blocks, stands, etc., used on the scales when weighing an airplane. Those points which are used during the weighing process to level the airplane. Points on the airplane identified by the manufacrurer as suitable for supporting the airpiane for weighing or other purposes. August 7 982 BEECHCRAm Bonanza 36.A38 E-1 thnt E-926 SECTION II LIMITATIONS TABLE OF CONTENTS PAGE Airspeed Limitations ............................ 2-3 Airspeed Indicator Markings ..................... 2-4 Power Plant Limftations ........................... 2-5 Engine .................... ,. ...........**... 2-5 Operating timltatlons .................... 2-6 Fuel Grades .............................I... 2-5 Oil Specifications ..................~.........2-6 Propeller Specifications ................... ,.. 2-6 Power Plant Instrument Markings (Round Type) ...................................2-7 Miscellaneous Instrument Markings [Roundfype) ..................................2-8 Power Plant Instrument Markings ............ (Vertical Electrically Operated Type] 2-8 Miscellaneous instrument Markings (Vertical Electrically Operated Type) ............ 2-9 Weight tim Its ................................... 2-9 ........... Center of Gravity Limits (Gear Down) 2-10 Maneuver Limits ............................... 2-10 Approved Maneuvers ............................ 2-10 .... ..................... Flight Load Factors .,,. 2-11 .......................... Minimum Flight Crew 2-71 Kinds of Operation Lirnits ....................... 2-11 ....................... Fuel I . . . ~ . . . . . . . . . ~ C I . . .2-12 ................. ..................... Seating ,l 2-12 August '1982 Section 11 BEECHCRAFT Bonanza 36,A 3 6 Limitations E - l thtu E.926 TABLE OF CONTENTS (E=ontinued) SUBJECT PAGE Placards . . . . . . . . . . . . . . . . . . . . .. , . . . . . . , , . . . . . . . . 2-13 Required Equipment for Various Conditions of Flight . . . . . . . . . . . . . . . . . , . . . . . . . . 2-24 August 7982 BEECHCRAFT Bonanza 36,A36 Section 1 1 E - l thru E-926 Limitations The limitations included in this section have been approved by the Federal Aviarion Administration. The following limitations must be observed in the operation of this airplane, AIRSPEED LIMITATIONS August 1982 . SPEED Never Exceed v~E Maximum Structural Cruising v~~ Or v~ .. CAS 203 234 204 235 Do not exceed this speed in any operation 765 - 190 140 ' ' ' ' ' 160 -"' Maneuvering v~ 1 139 except in smooth air and then oniy with caution 166 1 Maximum Flap Extended v~E Maximum Flap Extensia n E-1 thru thru E-105 E-706 thru E-926 Maximum Landing Gear Operating/ Extended V~~ and 'LE Do not make full or abrupt control movements above this speed 123 I17 123 1 5 2 191 122 I f 3 I22 ! : 175 Do not exceed this speed 142 1 140 130 140 Do nut operate with flaps ex- tended above this speed 153 135 142 176 I . Do not extend flaps above this speed Do not extend, retract or operate with landing gear extended above this speed except in emergency t "AIRSPEED INDICATOR MARKINGS 'The Airspeed Indicator is marked in CAS values (0 **Effective E-106 and Afier 4 a Cg m td MARKING White Arc - - -- - -. Green Arc Yellow Arc CAS 1AS , Red Line \ 203 I 234 2041 b 235 SIGNIFICANCE full Flap Operating Range Maximum speed for ALL operations KNOTS I MPH 56-1 13 KNOTS 1 MPH 64-1 30 56-1 17 56-123 65-165 165-203 63-1 35 63-142 71 - 192 191-235 * '56-1 22 . Normal Operating Range Operate with caution only in smooth air 75-1 90 --.--. 64-140 62-166 190-234 166-204 BEECHCRAFT Bonanza 36,A36 E-7 thru E-926 Section II Limitations POWER PLANT tlM!TATIONS ENGINE One Teledyne Continental Motors Corporation model 10-520-8, 10-520-BA or 10-520-86 engine Engine Speed , . . . . . . , . . . , . . . . . . . . .. . . . . . . 2700 rpm Cylinder Head Temperature . . . . . . . . . . . . . 460bF/2380C Oil temperature . . . . . . . . . . . . . . . . . . . . . . . . 240aF/1 1 Oil Pressure Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 psi Maximum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100 psi Fuel Pressure Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.5 psi Maximum . . , . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17.5 psi Mixture - Set per leaning instructions on performance charts. FUEL GRADES Aviation Gasoline 1 0 0 L L (blue) or 100 (green) minimum grade. Ashless dispersant oils m u s t meet Teledyne Continental Motors Corporation Specification MHS-248. Refer to APPROVED ENGINE OILS in t h e Handling, Servicing, and Maintenance section August 1982 2-5 Section il BEECHCRAFTBonanza 36,A 3 6 Limitations E-1 thru E-926 PROPELLER SPECIFICATIONS McCauley constant speed, two blade propeller Hub: 2A36C23 Blades; 848-0 Diameter: Maximum 84 in., Minimum 82 in, Pitch settings at 30 in* sta.: LOW 13.3' High - nor under 29.2O McCauley constant speed, three bladed propeller Hub: 3A32C76 Blades: 82NB-2 Diameter: Maximum 8Q in., Minimum 78.5 in. Pitch sectings at 30 in. sra.: Low - 1 3 . 3 O rt: 0.2O High - not under 29#0°f 0.5° NOTE Other propellers may be approved but not installed as origina I equipment. These are listed in the FAAAircraft Specification 3A15 or approved by Supplemental Type Certificate. August 1982 BEECHCRAFT Bonanza 36,A36 Section ll E-1 t h f u E-926 ~irnitatians POWER PLANT INSTRUMENT MARKINGS {ROUND TYPE) OIL, TEMPERATURE .............. Caution (Yellow Radial) 4 00°Ff180C Operating R a n g e (Green Arc) ........ 1003 to 240aFIJ80t o 1 16 O C Maximum {Red Radiai) . . . . . . . . . . . . . . 24Q°F/1 16OC OIL PRESSURE Minimum Pressure (Red Radial) ............ 30 psi Operating Range (Green Arc) . . . , , . . . . 30 t o 60 psi Maximum Pressure (Red Radial) . . . . . . . . . . 3 00 psi FUEL FLOW . . . . . . . . . . . . . . . . . . . . Minimum {Red Radial) 1.5 psi ...... Operating Range (Green Arc) 6.9to 24.3 gph . . . . . . . . . . . . . . . . . . . . . . . . . or 41,4 to 146.8 pph . . . . . . . . . . . . . . . . . . . Maximum (Red Radial) 17.5 psi TACHOMETER . . . Operating Range (Green Arc) 1800 to 2700 rpm . . . . . . . . . . . . Maximum RPM (Red Radial} 2700 rpm CYLINDER HEAD TEMPERATURE Operating Range . . . . . . . . (Green Arc) 200° to 460°Ffi30 to 238OC Maximum Temperature . . . . . . . . . . . . . . . . . . . {Red Radial) .... 4fj0°Ff1380C MANIFOLD P R E S S U R E Operating Range . . . . . . . . . . . . . . . . . . . (Green Arc) 15 to 29.6 in. Hg . . . . . . . . . . . . . . . . Maximum (Red Radial) 29.6 in. Hg August f 982 2-7 Section 11 BEECHCRAm Bonanza 36,A36 Limitations E - 1 thru E-926 MISCELLANEOUS INSTRUMENT MARKINGS (ROUND TYPE) INSTRUMENT PRESSUflE . . . . . . . . . . . . . . . . . Minimum (Red Radial) 3.5 in: Hg . . . . . Operating Range (Green Arc) 3.5 to 5.5 in. tig . . . . . . . . . . . . . . . . . Maximum (Red Radial) 5.5 in. Hg or . . . . . Operating Range (Green Arc) 4 , 3 to 5.9 in. Hg FUEL QUANTITY . . . . . . Yellow Band (44-gallon system) E to 112 full . . . . . . Yellow Band (74-gallon system) E t o 318 full POWER PLANT INSTRUMENT MARKINGS (VERTICAL ELECTRICALLY OPERATED TYPE) 01L TEMPERATURE Caution (Yellow tine) . . . , . . . . . . . . . . . . 1003F/380C Operating Range (Green Band) . . . . . . . 10QQto 240°F,/380 to 116°C . . . . . . . . . . . . . . . . Maxi m u m (Red Li ne) 240°F/1 16OC OIL PRESSURE . . . . . . . . . . . . . . Minimum Pressure {Red Line) 30 psi . . . . . . . Operaring Range {Green Band) 30 ro 60 psi . . . . . . . . . . . . Maximum Pressure (Red Line) 100 psi FUEL FLOW . . . . . . . . . . . . . . . . . . . . . . Minimum {Red Line) 1.5 psi Operating Range (Green Band) . 41.4 to 145.8 pph . . . . . . . . . . . . . . . . . . . . . Maxi mum (Red Line) 1 7 . 5 psi TACHOMETER Operating Range (Green B a n d ) , 1800 to 2700 rpm . . . . . . . . . . . . . Maximum RPM (Red Line) 2700 rpm August 1982 BEECHCRAFT Bonanza 36. A 3 6 Section I I E-I thru E-926 limitatitins CYLINDER HEAD TEMPERATURE Operating Range (Green Band) . . . . . . . 200° to 460°F/93a to 238OC Maximum Temperature . . . . . . . . . . . . . . . . . . . . . . . . . (Red t i n e ) 460dF/2380C MANIFOLD PRESSURE Operati ng Range . . . . . . . . . . . . . . . . . . IGreen Band) 15 to 29.6 in. Hg . . . . . . . . . . . . . . . . . . Maximum {Red tine) 29.6 in. Hg MISCELLANEOUS INSTRUMENT MARKINGS (VERTICAL ELECTRICALLY OPERATED TYPE) INSTRUMENT PRESSURE . . . . . . . . . . . . . . . . . Minimum (Red Radial) 3.5 in. M g Operating Range (Green Arc) . . . . . 3.5 to 5 5 in. Wg . . . . . . . . . . . . . . . . . Maximum (Red Radial) 5.5 in* M g or . . . . Operating Range (Green Arc) 4.3 to 5.9 in. Hg FUEL QCIANTln . . . . . . Yellow Band (22-gal Main Tank) O to 80 lbs. . . . . . . Yellow Band (37-gal Main Tank) 0 to 80 Ibs. WEIGHT LIMITS . . . . . . . . . . . . . . . . . . . . Maximum Ramp Weight 3612 lbs Maxi mum Take-off . . . . . . . . . . . . . . . . . . . . . . . and Landing Weight 3600 lbs . . . . . . . . . . . . . Zero Fuel Weight No Structural limitation . . . . . . . Maximum Baggage Compartment Load 400 lbs August 7 982 2-9 Section \ I BEECHCRAFT Bonanza 36,A 3 6 Limitations E-7 thru E-926 CENTER OF GRAVlTY LIMlTS (Gear Down) Forward: 74.0 inches aft of datum to 3100 ibs with straight line variation to 81.0inches at 3600 lbs. Aft: 87.7 inches aft of datum at all weights. R E F E R E N C E DATUM Datum is 83.7 i,~ches f o r w a r d of center line through forward jack paints. M A C leading edge is 66.7 inches aft of datum. MAC lengrh is 65.3 inches. MANEUVER LIMITS This is a utirity category airplane. Spins are prohibited. No acrobatic maneuvers are approved except those listed below. Maximum slip duration is 30 seconds for airplanes with baffled main fuel cells in both wings and ZQ seconds for airplanes with unbaffled main fuel cells in either wing. APPROVED MANEUVERS (3800POUNDS) MANEUVER ENTRY SPEED (CAS) . Chandelle . . . . . . . . . . . . . . . . . . ... 132 kts/l52 mph Steep T u r n . . . . . . . . . . . . . . . . . . . . . 132 kts1152 mph Lazy Eight . . . . . . . . . . . . . . . . , . . . . . 132 kts1162 mph . . . . . . . . . Stall {Except Whip) Use slow deceleration Minimum fuel tor above maneuvers - 10 gallons each main tank. Spins, are prohibited. August I 982 BEECHCRAFT Bonanza 36,A 3 6 Section II E-l thru E-926 Limitations FClGHT LOAD FACTORS (3600 POUNDS) Positive Maneuvering Load Factors Flaps Up . . . . . . . . . . . . . . . . . . . . . . . . . . . ..,.. 4.4G Flaps Down . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 .OG MINIMUM FLIGHT CREW One ( I ) Pilot KINDS OF OPERATION LIMITS This airplane is approved for the following type operations when the required equipment is installed and operational as defined herein: 1 . VFR day and night 2. I f R day a n d night 3,FAR 91 operations when all pertinent limitations and performance considerations a r e comptied with. WARNING FLIGHT tN ICING CONDITIONS IS PROH!BITED. NOTE Refer t o "REQUIRED EQUIPMENT F O R VARIOUS CONDITIONS OF FLlGHT" at the end ~f this Section. August t 982 Section ll Limitations BEECHCRAFT Bonanza 36,A 3 6 E - 1 t h t ~ E-926 FUEL STANDARD SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . Total Capacity 50 gal. Total Usable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 gal. OPT10NAL SYSTEM Total Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80 gal. Total Usable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74 gal. FUEL MANAGEMENT Take off on main tank that is more neariy full. When operating fuei selector, feel for detent position. Do not take off when Fuel Quantity Gages indicate in Yellow Band or wirh less than 13 gallons in each main tank. Maximum slip d ~ r a t i ~ n : 30 seconds for airplanes with baffled main fuel cells in both'wings. 20 seconds far airplanes with unbaffled main fuel cells in ei~herwing. SEATING All seats m u s t be in the upright p s i t i o n for take-off and landi ng. August t 982 PmyIimunAircraft Temporar Change to Yhe Pilot's Operatlng Handbook and FAA Approved Alrplane Fllght Manual Publlcdlan 38, A38 Pllot'a Operating Handbook Aftected and FA4 Approved Airplane Flight Man- ual (PIN 38-580002-19C, Releaued Auguet, 1982 or Subsequent) Airplane %t€al E-1thru E428 Numbsn Ameted De8crlptlon ot The addltlan of a placard to the fuel Change eekctor to warn of the no-flow condklon that exlste between the fuel selector detenfa. Flllng lnatrucllbna lnaart thla tsmporarj change Into the 38, A38 Pllot'a Operatlng Handbook and FAA Approved Alrplane FllgFrt Man- ual Imrnedlataly fol/owlng page 2-12 (Sactlon ! I , UMITATIONS) and retaln untlt rseclnded or rapiacad, Bonanza 38,A38 Locat~dOn The F ~ c eOf ;The Fuel Selecfor V&%, Fot Those A/@mw In Cump//afice With S.B. 2870: WARNING POSlTfON SELECTOR IN DETENTS ONLY - NO FUEL FLOW TO ENGINE BEWEEN bETf NTS Approved: 0 1 C * A, C,Jackson Raythean Aircraft Company DOA CE-2 BEECHCRAFT Bonanza 36,A 3 6 E-f thru E-926 Section ll Limitations On Fuel Selector Valve: Standard 44 Gallon /Usable) System: OFF 0 -I- R M TANK 22 GAL 0 22 GAL Optional 74 Gallon (Usable) System: OFF t RH TANK 37 GAL 0 37 GAL On Fuel Selecfof Panel: r 00 NOT TAKE OFF I F FUEL QUANTITY GAGES> $- INOICATE IN YELLOW BAND O R WITH LESS @- I THAN 13 GALLONS IN EACH MAIN TANK I August 1982 2-1 3 0 UTILITY CATEGORY AIRPLANE THIS AIRPLANE MUST BE OPERATED IN COMPLIANCE WITH THE 0 OPERATING LfMlTATtONS STATED IN THE FORM OF PLACARDS, MARKINGS A N D MANUALS. MAXIMUM WEIGHT 3600 LB. REFER TO WEfGHT A N D BALANCE DATA FOR LOADING INSTRUCT1OMS. OCCUPIED SEATS MUST BE IN UPRIGHT POSITiON DURING TAKEOFF AND L A N D I N d . ALTITUDE LOST 1N STALL RECOVERY 300 FEET. FLIGHT MANEUVER LOAD FACTOR: FLAPS UP 4.4 G; FLAPS DOWN 3.0 G N O ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW: 1 MANEUVER MAXIMUM ENTRY SPEED CHANDELLES ................................... 160 MPH 1139 KNOTS) LAZY EIGHTS ................................... 160 MPH (139 KNOTS) STEEP TURNS .................................. 160 MPH (139 KNOTS) STALLS (EXCEPT WHIP STALLS) ................ SLOW DECELERATION NOTE: INTENTIONAL SPINS PROHiBiTED AfRSPEED LIMITATION M A X I M U M LANDING GEAR EXTENDED SPEED. 175 MPH 1152 KNOTS) ........ 0 MAXIMUM DESIGN MANEUVER SPEED 160 MPH (139 KNOTS) @ BEECHCRAFT Bonanza 36, A36 Section !I €-I thru E-926 Limitations On Left Side Panel [Airspeed Values are CAS): (E-357, 358, 367 and E-364 rhtu E-926) @ AIR SPEED LIMITATION @ MAXIMUM SPEED WITH WNOING GEAR I!-ENBEO {MORMnL) 175 MPH (152 KTS} MAXIMUM OESEON MANEUVERING SPEED 160 MPH. (139 KTSl UTILITY CATEGORY AIRPLANE OPERATE Itd ACCOROANC6 WITH F A A APPROVED AIRPLANE FLIGHT MANUAL. INTENTIONAL S P I N S PROHIBITED NO ACROBATfC MANPUVERS APPROVED EXCEPT THOSE USTED 1N T h e AIRP-ME FLIGHT MkNUAt. In Full View of Pilot: (E-7 thru E- 784) unless baffled main fuel c e h are installed in both wings, w.... , -* TURNING TYPE TAKEOFFS, AND TAKEOFF IMMEDIATELY FOLLOWING FAST TAXI TURN PROHIBITED, AVOID PROLONGED SLIPS (20 SECONDS OR MORE} WITH FUEL TANKS LESS THAN HALF FULL. On Left Side Panel Below Instrument Subpanel When Emergency Static Air System is Instafled: r o WARNING oE M E R G E N C Y AIRSPEED STATIC S O U R C E O N EMERGENCY S E E PILOTS CHECK LIST OR FLIGHT MANUAL =P ; E M E R G E N C Y P R O C E D U R E S FOR AIRSPEED €4 ALTIMETER CALIBRATION E R R OR 0 OFF N O R M A L 0 August 1982 2-15 Section I1 BEECHCRAFT Bonanra36, A36 limitations E-7 thru E-926 PLACARDS ICont'dl On Left Side Pane/ Near Firewall Air Controls: (361 -... VENT SHUTOFF 0 PULL TO CLOSE CONTROL TO CLOSE On Left-Hand Side of Nose Whee! We// Bdkhead Below Generator Circuit Breaker (E-7 thru E-476 except E-397) I GENERATOR CIRCUIT 8REAKER PUSH TO RESET Under Left Subpanel.- {E-397 and E-477 thru E- 762 except E-710) A LT CtRCUlT BREAKER August 1982 BEECHCRAFT Bonanza 3 6 , A 3 8 E - 1 thru E-926 Section !I Limitations On Con fro/ C:onso/e: P \ THROTTLE 0 FF PROPELLER PUSH OPEN PUSH HI R P M AUX FUEL PUMP OPERATION TAKE-OFF AND LANO WITH AUX FUEL PUMP OFF EXCEPT IN CASE QF LQSS Qf FUEL PRESS FUEL MIX. ALTERNATE AIR PUSH R I C H PULL AND RELEASE On Oxygen Consaki W A R N I N G DO NOT SMOKE WHILE OXYGEN IS IN USE HOSE PLUG M U S T BE PULLED OUT TO STOP FLOW OF OXYGEN Around Each Oxygen O u t k i : August 7982 Section El Limitations BEECHCRAFT Bonanxa 36,A36 E - I thru E-926 PLACARDS (Cont'd) On Top of Front Spar Carry- Thru Structure Between Front Seats: EMERGENCY LANDING GEAR INSTRUCTIONS e TO EXTEND $ ENGAGE HANDLE IN AEAFl OF FRONT SEAT AND TURN COUhlTERCLOCKWfSE AS F A R A S POSSIBLE I SO TURNS) On Emergency Crank Access Cover: (E-477 and after) LANDING GEAR EMERGENCY CRANK PULL OUT LIFT U P Below Controls on Control Console: r NOTICE REMOVE WINTER BAFFLES WHEN OAT EXCEEDS 70" F L J 2-t 8 August 7982 BEECHCRAFT Bonanza 36, A36 Section Ii E-1 thru E-926 Limitations On Left Side Window When Shoulder Hamass is /nsra/led: [Prior to E-825) On Windows Adjacent to Pilot's and Copifat's Seats: (Em825 and after) I WHf N SHOULDER HARNESS IS IN USE, SNUG U P BELT WITH BUCKLE CENTERED IN FRONT OF OCCUPANT WITH SEAT BACK UPRIGHT r ' SHOULDER HARNESS M U S T BE WORN A T ALL TIMES WHILE AT I PILOT POSITIONS -.... : On Windows Adjacent to 3rd 4th, 5rh B 6th Seats: (E-825 and after) SHOULDER HARNESS MUST BE WQRN DURING TAKE-OFF AND LANDING WITH SEAT BACK UPRIGHT - Qn Windows Adjacent to 3 r d & 4th Aft Facing Club Seats: {E -825 and after) August 1982 SHOULDER H A R N E S S MUST BE WQRN DURING I TAKE-OFF A N D LANDlNG WITH SEAT BACK UPRIGHT / A N D AFT FAClNG SEATS MUST HAVE HEADREST FULLY EXTENDED : Section.ll BEECHCRAFT Eananza36, A36 ~irnitaiians E - 1 thru E-926 PLACARDS (Cont'd) On Left Cabin Sidewall (Prior to E-825); On Storm Window (36 only) (CAS): ALL AFT FACING SEATS MUST HAVE BACK UPRIGHT AND HEADREST FULLY RAISED DURiNG TAKEOFF AND LANDING . CAUTION . DO NOT OPEN ABOVE 145 MPH (126 KNOTS) Below Left and Right Openable Windows After Compliance with BEECHCRAFT Service Instructions 7 24 7: ( EMERGENCY EXIT \ LIFT LATCH - PULL PIN PUSH WINDOW OUT L. D O NOT OPEN IN FLIGHT LATCH WINDOW BEFORE TAKE-OFF 2-20 Revised: March 1983 BEECHCRAFT Bonanza 36,A36 E - 1 thru E.926 Section II Limitations On Inboafd Side of Seat Back for 3rd & 4th Seats: (6-825and after) __II I 0 T U R N : RED HANDLE UNLOCK I SEAT BACK 1 0 On fnsrrurnenr Panel when Anti-coilision Lights are not hstal/ed.' THIS AIRCRAFT NOT FULLY EQUIPPED FOR NIGHT FLIGHT On /nstrumsnt Panel: - .. ... .. .. August 1982 1 WHEN UTILITY DOORS ARE REMOVED - A18 SPEED IS NOT TO EXCEED 190 MPH (165 KNOTS) CAS Section II BEECHCRAFT Bonanza 36,A36 imitations €4 thru E-926 PLACARDS (Cont'd) On Baggage Straps Aft Side of Front Seat Backs: fIMAXIMUM LOADING 50 LBS On Left Cabin Sidewali: T BAGGAQE AND CARGO COMPARTMENT LOAD IN ACCORDANCE WITH WEIGHT AND B A U N C E DATA Q MAXIMUM STRUCTURAL CAPACITY-400 POUNDS @ 1 WHEN UTILITY DOORS ARE FIEMOVED THE FOLLOWING RESTRICTIONS APPLY TO CABlN AREA: 1. N O SMOKING 2. ALL LOOSE OBJECTS M U S T BE SECURED 3. PERSONNEL N O T S E C U R E D IN SEATS BY SAFETY BELTS MUST WEAR PARACHUTES f h In Lieu of LH Cabin Sidewa// Placard [if required by CAR 3.74, due ro optional equipment configwation): BAGGAGE AND CARGO COMPARTMENT LOAD IN ACCORDANCE WITH WEIGHT AND BAlANCE DATA MAX1MUM STflUCTURAL CAPACtTY-400 POUNDS @MAXIMUM 5 M AND ~ T H " S E A TCAFACIW POUNDS@ WHEN UTlLllT DOQRS ARE REMOVEDTHE FOLLOWING RESTRICTIONS APPLY TO CABIN AfiEA; 1 . NO SMOKING 2. ALL LOOSE OBJECTS MUST B E SECURED 3. PERSONNEL NQTSECURED IN SEATS BY SAFETY BELTS MUST WEAR PARACHUTES 'A 2-22 August 1982 BEECHCRAFT Bonanza 36,A38 E-3 thru E-926 Section I1 ~ i m i t e t i o k -" HAT SHELF N O HEAVY OBJECTS Above Inside Dour Handle: (E- I thru E-476) ROTATE @ HANDLE TO / FULL LOCKED\ (E-477and after) w ROTATE HANDLE TO FULL LOCKED POSITION . e August f 982 2-23 Section Ii BEECHCRAFT Bonanza 36,A36 Limitations E-'l thru E-926 REQUIRED EQUIPMENT FOR VARlOUS CQNDlfiQNS OF FLIGHT Part 91 of the Federal Aviation Regulations specifies t h e minimum numbers and types of airplane instruments and equipment which must be instatled and operable fat various kinds d flight conditions. This includes VFR day, VFR night, IFR day, and 1FR night. Regulations also require that all airplanes be certificated by the manufacturer for operations under various flight conditions, At certification, all required equipment must be in operating condition and should be maintained to assure continued airworthiness. If deviations froi the installed equipment were not permitted, or if the operating rules did not provide for various flight conditions, the airplane could not be flown unless ail equipment was operable. With appropriate limitations, the operation of every system or component installed in t h e airplane is not necessary, when the remaining operative instruments and equipment provide for continued safe operation. Operation in a c c o r d a ~ c e with limitations established t o maintain ai worthiness, can permit continued or uninterrupted aperation of the alrplane temporarily. For the cake of brevity, t h e Required Equipment Listing does not include obviously required items such as wings, rudders, flaps, engine, landing gear, etc. Also t h e list does not include items which do not affect the airworthiness o f the airplane such as entena inrnent systems. passenger convenience items, etc. However, it is important to note that ALL REMS WHICH ARE RELATED TO THE AIA- WORTHINESS OF THE A I R P M N E AND NOT INCLUDED O N THE U S T ARE AUTOMATICALLY REQUIRED TO BE O PERATlVE. 2-24 August '1982 BEECHCRAFT 8onanxa 36,A36 Section I1 E - l thru E-926 Limitations To enablethe pilot to rapidly determine t h e FAA equipment requirements necessary for a flight into specific conditions, the foliowing equipment requirements and exceptions are presented. It is the final responsibility of the pilot to determine whether t h e lack of, or inoperative status of a piece of equipment on his airplane, will limit the conditions under which h e may operate the airplane. LEGEND Numbers refer to quantities required to be operative for a specified condition. - ) Indicates that the item may be inoperative for the , specified condition. ) Refer t o the REMARKS AND/OR EXCEPTIONS column for explicit information or reference. August 1982 2-25 - SYSTEM and/or COMPONENT GENERAL Overwater flight ATA 100 CHAPTER 23 COMMUNICATIONS VHF communicarions syslern ATA f 00 CHAPTER 24 ELECTRICAL POWER Battery DC alterna~or DC allernator out indicator light Standby generator VFR Day c VFR Night s * IFR Day Z * * 1 1 1 . I -+Per FAR 91 IFR Night 7 t t I - -'Optional 1 1 Rernarks and/or Exceptions -*Per FAA 91 1 1 9 1 1 1 ATA 100 CHAPTER 25 EQUIPMENT AND FURNISHING Seat belts Shoulder harness Emergency locator transrn~tler ATA 100 CHAPTER 26 FIRE PROTECTION Portable fire extinguisher ATA 100 CHAPTER 27 FLIGHT CONTROLS Elevator trim tab