BEECHCRAFT Sundowner 180 C23 (M-1285 and After)

datum at 2030 Ibs. Aft: 114.0 inches aft of datum at all weights. REFERENCE DATUM Datum is 103 inches forward of wing leading edqe, MAC length is 52.7 inches. MANEUVER LIMITS This airplane is approved for 4 place in the Normal Category and for 2 place in the Utility and Acrobatic Category. Maximum slip duration is 30 seconds. NORMAL CATEGORY (2450 POUNDS) No acrobatic maneuvers approved. UTILITY CATEGORY (2030 POUNDS) No acrobatic maneuvers are approved except those listed below. MANEUVER ENTRY SPEED (CAS) Chandelle 116 kts/133 mph Steep Turn 116 kts/133 mph Lazy Eight. . . . . . . . . . . . . . . . . . . . .. 116 kts/133 mph Stall (Except Whip) Use slow deceleration Intentional Spins M-1494 and after (only if certificated as Acrobatic) or prior airplanes modified by Kit No. 23-4007-1 S per 5.1. No. 0619-090 Use slow deceleration I A CROBA T IC CATEGORY (2030 POUNDS) For additional approved acrobatic maneuvers, see FAA Approved Airplane Flight Manual Supplement. 2-8 Revised: October 1979 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) FLIGHT LOAD FACTORS Section II Limitations NORMAL CATEGORY (2450 POUNDS) Flight maneuvering load factor Flaps Up +3.8, -1.9 Flaps Down +1.9 UTILITY CATEGORY (2030 POUNDS) Flight maneuvering load factor Flaps Up +4.4, -2.2 Flaps Down +2.2 ACROBATIC CATEGORY (2030 POUNDS) Flight maneuvering load factor Flaps Up +6.0, -3.0 Flaps Down +2.0 MINIMUM FLIGHT CREW One (1) Pilot KINDS OF OPERATION LIMITS 1. VFR day and night 2. IFR day and night REQUIRED EQUIPMENT FOR VARIOUS CONDITIONS OF FLIGHT Federal Aviation Regulations (91.3(a), 91.24, 91.25, 91.32, 91.33,91.52,91.90,91.97, 91.170) specify the minimum numbers and types of airplane instruments and equipment which must be installed and operable for various kinds of flight conditions. This includes VFR day, VFR night, IFR day, and IFR night. February 1979 2-9 Section II Limitations BEECHCRAFT Sundowner 180 C23 (M-1285 and After) 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 from 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 all equipment was operable. With appropriate limitations, the operation of every system or component installed in the airplane is not necessary, when the remaining operative instruments and equipment provide for continued safe operation. Operation in accordance with limitations established to maintain airworthiness, can permit continued or uninterrupted operation of the airplane temporarily. For the sake of brevity, the Required Equipment Listing does not include obviously required items such as wings, rudders, flaps, engine, landing gear, etc. Also the list does not include items which do not affect the airworthiness of the airplane such as entertainment systems, passenger convenience items, etc. However, it is important to note that ALL ITEMS WHICH ARE RELATED TO THE AIR- WORTHINESS OF THE AIRPLANE AND NOT INCLUDED ON THE LIST ARE AUTOMATICALLY REQUIRED TO BE OPERATIVE. To enabJe the pilot to rapidly determine the FAA equipment requirements necessary for a flight into specific conditions, the following equipment requirements and exceptions are presented. It is the final responsibility of the pilot to determine whether the lack of, or inoperative status of a piece of equipment on his airplane, will limit the conditions under which he may operate the airplane. 2-10 February 1 979 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) Section II Limitations WARNING FLIGHT IN ICING CONDITIONS PROHIBITED. I 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 to the REMARKS AND/OR EXCEPTIONS column for explicit information or reference. December, 1991 2-11 I\) .~ I\) J:- c CD cfI) i I VFR Dav SYSTEM VFR Niaht and/or IFR Dav COMPONENT IFR Niaht Remarks and/or Exceptions GENERAL Overwater flight * * * * - *Per FAR 91.33 COMMUNICATIONS VHF communications system * * * * - *Per FAR 91.33 ELECTRICAL POWER Battery 1 1 1 1 DC alternator 1 1 1 1 Starter Engaged 1 1 1 1 - May be inoperative Warning Light provided ammeter is (M-2278 and after) operative and monitored It/) _. CD 3 n_. ,...,... _.D) 0 ~. :::s o - :::s - en m m m o :::E: 00 N::XJ CIJ» -." S ... ~cn NC co:::S CJ1g- D) ~ :::s :::s Q. CD » ...~~ ""co !o ." CD r:r..eQ) ..< ~ CD ~ CO ~ ~ w EQUIPMENT AND FURNISHING Seat belts and Shoulder harness Emergency locator trans- mitter FIRE PROTECTION Portable fire extinguisher * * * * - Per Person or Per FAR 91.33 - Per FAR 91.52 -*Optional om Nm wm -0 3::J: ~O N:O co» 01'" Q) -t ~ en e.c: »~ -he. r+o ~ ~ -~ CD ..~ co o r- 3· en_. CD r+(,) Q) r+ 0'. o·o ~ ~ -UJ - ~ ~ ~ "T1 (1) c-..e C» ..< ~ CD " CD VFR Day SYSTEM VFR Night and/or IFR Day COMPONENT IFR Night Remarks and/ or Exceptions FLIGHT CONTROLS Stabilator trim tab indicator 1 1 1 1 - May be inoperative for ferry fl ight provided tabs are visually checked in the neutral position prior to take-off and checked for fu II ra nge of operation. Flap position indicator 1 1 1 1 - May be inoperative provided flap (On electric flap system) travel is vi sua Ily inspected prior to take-off. Stall warning 1 1 1 1 .... cn_. (1) 3 n_......... _.C» 0 =. ~ o - ~ -en tXJ m m o o:::t NO w::D _:I> S"T1 ,-4 ~cn NS:::: 0)::1 0'10. D) 0 ::1 ~ o.~ :I>~ ;t'~ (1) 0) ~o " om (1) Nm C'" .. wm e FUEL EQUIPMENT -0 Q) S::I: ..< 10 • .::D CD Fuel boost pump 1 1 1 1 ~» -..J Engine driven fuel pump 1 1 1 1 U'I" CD Q) -t Fuel quantity indicator 2 2 2 2 - One may be inoperative pro- ::s tn Cloc vided other side is operational »::S ~Q. and amount of fuel on board can "'0 be established to be adequate ~ ~ -:s for the intended flight. CD .. Fuel pressure indicator 1 1 1 1 •(X) 0 ICE AND RAIN PROTECTION Emergency static * * * * -*Optional r- air source 3· tn Pitot heater * * 1 1 -*Optional _. (1) ... (') Q) ... ~ I ... _._. 0 o :s ..... ::s _ U'I --------- en - ~ ..C» ." CD C'" ...r::D) -<..CD --J CD SYSTEM VFR Day VFR Night and/or IFR Day COMPONENT IFR Night Remarks and/ or Exceptions LIGHTS Cockpit and instrument - * - * -*Lights must be operative. lights Taxi light - - - - Landing light - * - * -*Per FAR 91.33 Rotating beacon * 1 * 1 -*Optional Position light - 3 - 3 r-en _. CD 3 (')_. r+ r+ _. Q) 0 :!'. =' o - =' - en m m m o oJ: NO w::D _l> 3:'" .-t .. en Nr:: co::S (J1Q. Q) 0 =' ~ Q.=' »~ ;: ..CD co .:!..o ." 00' CD Nm C"' ... NAVIGATION wm e -0 m INSTRUMENTS SJ: -< '0 -' -':IJ CD Altimeter 1 1 1 1 ~» -...J Ai rspeed indicator 1 1 1 1 (J1-r1 CD m -I Vertical speed - - - - ::s en e.c: Magnetic compass 1 1 1 1 »::S .... e. Attitude indicator - - 1 1 r+o ~ ~ Turn coordinator - - 1 1 -::s Directional gyro 1 1 CD - - .....II Clock - - 1 1 CX) Transponder * * * * -*Per FAR 91.24, 91.90, 91.97 0 Navigation equipment - - * * -*Per FAR 91.33 VACUUM Vacuum system for 1 1 r- - - 3' en instrument air -·CD r+(') IVacuum gage 1 1 m r+ ~ - - r+ _. _. 0 -' o ::s --.J ::s _ (I) - ~ ~ co ." CD C'" ...t: m...< ~ (D '-J CD VFR Day SYSTEM VFR Night and/or IFR Day COMPONENT IFR Night Remarks and/ or Exceptions ENGINE INDICATING INSTRUMENTS Engine tachometer indicator 1 1 1 1 Exhaust gas temperature * * * * -*Optional indicator ENGINE OIL INSTRUMENTS Oil pressure indicator 1 1 1 1 Oil temperature indicator 1 1 1 1 r-(J) _. CD 3 (")_. ,....... _.m 0 =. ::s o - ::s - fA D:J m m o :I: nn N::D w» -." S-I ~C/) Nt: co::S U1g- m ~ ::s ::s Q. CD » ...-h~ S'co .::!..O BEECHCRAFT Sundowner 180 C23 (M-1285 and After) Section II Limitations FUEL TOTAL FUEL with left and right wing fuel systems full: M-1285 thru M-1516: Two *29.9-gallon tanks in wings with a total of *58 gallons usable. M-1517 thru M-1879 except M-1875 and prior airplanes after compliance with Service Instructions No. 0624-281: Two *29.9-gallon tanks in wings with a total of *52 gallons usable. M-1875, M-1880 and after: Two *29.9-gallon tanks in wings with a total of *57.2 gallons usable. *Value given is nominal. Tank capacity will vary with temperature and manufacturing tolerances. FUEL MANAGEMENT On M-1517 thru M-1879 except M-1875, and prior air- planes if service Instruction No. 0624-281 is ac- complished: Do not take off when the Fuel Quantity Gages indicate in the Yellow Band or with less than 11 gallons in each main tank. Maximum slip duration: 30 seconds On M-1875, M-1880 and after: Do not take off when Fuel Quantity Gages indicate in Yellow Band on either gage. Maximum slip duration: 30 seconds February 1979 2-19 Section II Limitations BEECHCRAFT Sundowner 180 C23 (M-1285 and After) PLACARDS On Left Cabin Door or Left Side Panel: (M-1285 thru M-1979 except M-1971) (CAS) 2030 LBS 2450 LBS FLAPS UP +3 .8 -1 9 DOWN +1.9 136 MPH FLAPS UP +44 -2.2 DOWN +22 NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW: MANEUVER MAXIMUM ENTRY SPEED CHANDELLES 133 MPH LAZY EIGHTS 133 MPH STEEP TURNS 133 MPH STALLS (EXCEPT WHIP STALLS) SLOW DECELERATION NOTE: MAXIMUM ALTITUDE LOSS DURING STALL 300 FT MAXIMUM MANEUVERING SPEED NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED UTILITY CATEGORY MAXIMUM DESIGN WEIGHT REFER TO WEIGHT AND BALANCE DATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR ~ . ~ THIS AIRPLANE MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NORMAL CATEGORY MAXIMUM DESIGN WEIGHT REFER TO WEIGHT AND BALANCE DATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR ~---------------------+ 2-20 February 1979 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) Section II Limitations On Instrument Panel in Full View of Pilot (M-1285 through M-1493, unless modified by Kit No. 23-4007-1 S and Service Instructions No. 0619-090): IIITHIS AIRPLANE MUST BE OPERATED AS Al NORMAL OR UTILITY CATEGORY AIRPLANE. I NTENTIONAL SPINS ARE PROHIBITED. NO ACROBATIC MANEUVERS APPROVED EXCEPT: CHANDELLES, LAZY EIGHTS, STEEP TURNS, ~ND STALLS (EXCEPT WHIP STALLS)." --1 On Left Cabin Door or Left Side Panel (M-1971, M-1980 and after) (CAS) 2030 LBS 2450 LBS FLAPS UP +4.4 -2.2 DOWN +2.2 NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW: MANEUVER MAXIMUM ENTRY SPEED CHANDELLES 116 KTS/133 MPH LAZY EIGHTS 116 KTS/133 MPH STEEP TURNS 116 KTS/133 MPH STAllS (EXCEPT WHIP STALLS) SLOW DECELERATION NOTE: MAXIMUM ALTITUDE lOSS DURING STALL 300 FT FLAPS UP +3.8 -1.9 DOWN +1.9 MAXIMUM MANEUVERING SPEED 118 KTS/136 MPH NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED UTILITY CATEGORY MAXIMUM DESIGN WEIGHT REFER TO WEIGHT AND BALANCE DATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD fACTOR I;THIS AIRPLANE MUST BE OPERATED IN COMPLIANCE~WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NORMAL CATEGORY MAXIMUM DESIGN WEIGHT REFER TO WEIGHT AND BALANCE DATA fOR LOADING INSTRUCTIONS fLIGHT MANEUVERING LOAD FACTOR ~------------~ February 1979 2-21 Section II Limitations BEECHCRAFT Sundowner 180 C23 (M-1285 and After) PLACARDS On Left Cabin Door or Left Side Panel (Acrobatic): (M-1285 thru M-1979 except M-1971) (CAS) 2030 L8S 2450 lBS flAPS UP +3 8 - 1 9 DOWN +19 136 MPH FLAPS UP +60 -30 DOWN +20 NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW: MANEUVER MAXIMUM ENTRY SPEED CHANDELLES 133 MPH LAZY EIGHTS 133 MPH STEEP TURNS 133 MPH STALLS (EXCEPT WHIP STAlLSI SLOW DECELERA nON NOTE: MAXIMUM ALTITUDE LOSS DURING STALL 300 FT SPINS (FOR OPERATIONAL LIMIT ATlONS SEE PLACARD ON SUN VISOR) MAXIMUM MANEUVERING SPEED NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED UTILITY & ACROBATIC CATEGORY MAXIMUM DESIGN WEIGHT REFER TO WEIGHT AND BALANCE OATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR I~HIS AIRPLANE MUST BE OPERATED IN COMPLlANC~WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NORMAL CATEGORY MAXIMUM DESIGN WEIGHT REFER TO WEIGHT AND BALANCE DATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR BARRel ROll AILERON ROLL SNAP ROLL SPLIT S ll::IMMElMANN lOOP + RECOMMENDED ENTRY SPEED 130 MPH 130 MPH 100 MPH 90 MPH 150 MPH 140 MP~ On Right and Left Cabin Doors (Acrobatic): REMOVE DOOR -$-HOLD - OPEN ROD PRIOR-$- TO OPERATION IN ACROBATIC CATEGORY 2-22 February 1979 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) Section II Limitations 2030 LIS 2450 LIS FLAPS UP +60 -30 DOWN +20 NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW: MANEUVER MAXIMUM INTRY S'IID CHANDELLES 116 KTS/133 M'H LAZY EIGHTS 116 KTS/133 M'H STEEP TURNS 116 KTS/133 MP'H STALLS IEXCEPT WHIP STALLS) SLOW DECELERATION NOTE: MAXIMUM ALTITUDE LOSS DURING STAll 300 fT SPINS IFOR OPERATIONAL LIMITATIONS SEE PLACARD ON SUN VISOR) FLAPS UP + 3 8 - 1 9 DOWN +19 MAXIMUM MANEUVERING SPEED 118 KTS/136 MPH NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED UTILITY & ACROBATIC CATEGORY MAXIMUM DESIGN WEIGHT REFER TO WEIGHT AND BALANCE OATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR On Left Door or Left Side Panel (Acrobatic): (M-1971, M- 1980 and after) (CAS) ~HIS AIRPLANE MUST BE OPERATED IN COMPLlANC~WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NORMAL CATEGORY MAXIMUM DESIGN WEIGHT REFER TO WEIGHT AND BALANCE DATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR BARRel ROll AILERON ROll SNAP ROLL SPLIT S ~ I M M El M A N N LOOP + RECOMMENDED ENTRY SPEED 113 KTS/130 MPH 113 KTS/130 MPH 87 KTS/100 MPH 79 KTS/90 MPH 130 KTS/150 MPH 122 KTS/140 MP~ On Right Side of Instrument Panel (Acrobatic): w-----~ CAUTION CONTINUOUS INVERTED FLIGHT WILL CAUSE LOSS OF OIL AND OIL PRESSURE. REAR CG LIMITED AND CARRYING OF BAGGAGE OR REAR SEAT PASSENGERS AND USE OF FLAPS PROHIBITED DURING ACROBATIC MANEUVERS. ~-----~ February 1979 2-23 Section II Limitations BEECHCRAFT Sundowner 180 C23 (M-1285 and After) L L PLACARDS On Upper Right Instrument Panel: fRAISE FLAP51 TO INCREASE BRAKE ~FFECTIVENES~ On Flap Extension Handle: (M-1285 thru M-1979 except M-1971) (CAS) r--;LAPS PULL TO EXTEND, MAX SPEED 110 MP~ RETRACTED . . . . . .. 0° FIRST NOTCH 15° SECOND NOTCH . . . . 25° THIRD NOTCH ..... 35° On Flap Extension Handle: (M-1971, M-1980 and after) (CAS) I FLAPS PULL TO EXTEND, MAX SPEED 96 KTS/110 MPHI RETRACTED. . . . • .• 0 0 FIRST NOTCH . . . . . . 150 SECOND NOTCH . . . . 250 THIRD NOTCH ..... 350 2-24 February 1 979 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) Section II Limitations On Sunvisor Above Pilot's Seat (Acrobatic): r-;: .. OPERATlONAl LIMITATIONS SPINS: The airplane will not 'pln If orthodo. enlry IS u,ecl, but will enter a ,poral d i_e . Speed bu ild, up rapidly In a ,poral dive . requiring high pullout loads; therefore. if a Sopuol is Inadvertently cn.crcdrccovcryfromthc\plJolis-tobelOitiatcdwithintwolu,ns ENTRY: Slalilhe aorplane wilh the conlrol column hard back, thrcttte In idle po,it ion, flaps up. carburetor beet as rcquucd and with Ihe nose about 15 above Ihehomon . AI the.tall. apply lull rudder in the direction ecqvncd 10 'pIn A slight rudder applicction Immediately before the stall will assure the direclion of ,p.n . The aorplane nose will drop and rolate towards the applied rudder. When Ihe wings are 90 tothehomon. apply full aileron agc,"st lie aga,"sl the ,nlended di'ectlon of spin) The oJrpJone will go slightly Inverfed and enter a norma l span If aileron agolnst is not applicd OJ applied too lotc, the:- oltplanc will enter Q rapid spiral dive and recovery mu~1 b e In lli· ated by tho second turn If the full baCK stiCK 1$ not applied and held , the ouplonc moy iplfO' Agoln recovery must be Initiated nol late r than fht> sccond'urn If aileron 's oppl;~d too carty . the olrplont!' will not rolale and mer~ly r['moln In a \ trolg h. ,tolled cond ition RECOVERY : IMMEDIATelY MOVE THE CONTROL COLUMN FUll FORWARD AND SIMULIANEOUSLY APPLY FUll RUDDER OPPOSITE TO THE DIRECTION OF THE SPIN; CONTINUE TO HOLD THIS CONTROL POSITION UNTIl ROIAtlON STOPS AND THEN NEUTRALIZE All CONTROLS AND EXECUTE ASM001H PUllOUT AILERONS SHOULD BE NEUTRAL AND THROTTLE IN IDLE POSITION AT ALL TIMES DURING RECOVERY ~----------------~ The above placard reads as follows: "OPERATIONAL LIMITATIONS SPINS: The airplane will not spin if orthodox entry is used, but will enter a spiral dive. Speed builds up rapidly in a spiral dive, requiring high pullout loads; therefore, if a spiral is inadvertently entered recovery from the spiral is to be ini- itiated within two turns. ENTRY: Stall the airplane with the control column hard back, throttle in idle position, flaps up, carburetor heat as required and with the nose about 15° above the horizon. At the stall, apply full rudder in the direction required to spin. A slight rudder application immediately before the stall will assure the dir~~tion of spin. The airplane nose will drop and rotate towards applieBrlJ(;Jder. When the wings are 90° to the horizon, apply full aileron ~g~jr1St -O.e. against the intended direction of spin). The airplane will go.slightly inv~rted and enter a normal spin. If aileron agai!'st is not ap.p,!ied or applied too lateLthe airplane will enter a spiral dive, and recovery must be initiatea by the second turn. If the full back stick is not applied and held, the airplane may spiral. Again recovery must be initiated not later than the second turn. If the aileron is applied too early, the airplane will not rotate and merely remain in a straight stalled condition. RECOVERY: Immediately move the control col- umn full forward and simultaneously apply full rudder opposite to the direction of the spin; continue to hold this control position until rota- tion stops and then neutralize all controls and execute a smooth pullout. Ailerons should be neutral and throttle in idle position at all times during recovery." February 1979 2-25 Section II Limitations PLACARDS BEECHCRAFT Sundowner 180 C23 (M-1285 and After) On Fuel Selector Panel (M-1285 through M-1516): L TANK 29 GAL , RTANK 29 GAL » On Fuel Selector Panel (M-1517 through M-1879 except M-1875 or prior airplanes after compliance with Service Instructions No. 0624-281): L 2-26 February 1979 ___ellll Aircraft Sundowner C23 Temporary Change to the Pilot'. Operating Handbook and FAA Approved Airplane Flight Manual PIN 189-590008-23TC1 Publication C23 Pllot-s Operating Handbook and Affected . FAA Approved Airplane Flight Manual (PIN 169-590008-23_ Issued February_ 1979 or Subsequent) Airplane serial M-1285 and After Number. Affected Description at The addition of a placard to the fuel Change selector to warn of the no-flow condition that exists between the fuel selector detents. Filing Instructions fnsert this temporary change Into the C23 Pllot-s Operating Handbook and FAA Approved Airplane Flight Manual Immediately following page 2-28 (Sec- tion "_ UMITATIONS) and retain until rescinded or replaced. PIN 189-590008-23TC1 August 28, 1887 1012 IIIIJIII--Aircraft LIMITATIONS PLACARDS Sundown., C23 Located On The Face Of The Fuel Selector Valve, For Those Airplanes In Compliance With S.8. 2670: WARNING - POSlnON SELECTOR IN DETENTS ONLY - NO FUEL FLOWTO ENGINE BETWEEN DETENTS Approved: 20'2 A.C. Jackson Raytheon Aircraft Company DOA CE-2 PIN 189-590008-23TC1 August 28, 1997 BEECHCRAFT Sundowner 180 C23 (M-1285andAfter) Section II Limitations On Fuel Selector Panel (M-1875, M-1880 thru M-2224): • OR On Fuel Selector Panel (Serials M-2225 and after, or earlier airplane serials which have complied with BEECHCRAFT Service Instructions No. 1095): Adjacent to Engine Instrument Cluster (M-1517 through M- 1879 except M-1875 or prior airplanes after compliance with Service Instructions No. 0624-281): r DO NOT TAKE OFF WHEN FUel QUANTITY GAUGE INDICATES IN YEllOW OR WITH IL LESS THAN 11 GALLONS IN EACH MAIN TANK MAXIMUM SLIP DURATION IS 30 SECONOS..J Adjacent to Engine InstrumentCluster (M-1875, M-1880 and after): [ DO NOT TAKE OFF WHEN FUel QUANTITY GAUGE INDICATES IN YelLOW ONI EITHER GAUGE MAXIMUM SLIP DURATION 30 SEC ~ August, 1980 2·27 Section II Limitations PLACARDS BEECHCRAFT Sundowner 180 C23 (M-1285 and After) Above Right and Left Cabin Doors (M-1285 thru M-1412 and M-1415, M-1419, M-1423, M-1439 and M-1447): ~ OPEN On Left Cabin Door (Acrobatic): ~ OPEN rEMERGENCY EXIT e~ TURN HANDLE CLOCKWISE & PULL LATCH ABOVE ARM REST, THEN KICK-OUT TO JETTISON DOOR On Right Cabin Door (Acrobatic): ~MERGENCY EXIT' TURN HANDLE COUNTER- CLOCKWISE & PULL LATCH ABOVE ARM REST, THEN KICK-OUT TO JETTISON DOOR 2-28 December, 1991 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) On Baggage Compartment Door: Section II Limitations I TO LEVEL AIRCRAFT - LEVEL l l!.AGGAGE COMPARTMENT FLOO.!J On Pedestal Between Front Seats: r; --I ~ r---l N 0 I I N I I o I I S I I E I I u I I P I I I I L L ~ On Second W'indow Frame Right Side (M-1658 and after as required by weight and balance data): I BAGGAGE, CARGO OR FAMILY SEATS I LOAD IN ACCORDANCE -$- WITH WEIGHT & BALANCE -DATA -$- L MAXIMUM SEAT CAPACITY POUNDS -.-J February 1979 2-29 Section II Limitations BEECHCRAFT Sundowner 180 C23 (M-1285 and After) PLACARDS On Lower Sidewall Adjacent to Pilot (when installed): WARNING EMERGENCY AIRSPEED STATIC SOURCE SEE FLIGHT MANUAL NORMAL EMERGENCY PROCEDURES OFF FOR AIRSPEED ALTIMETER /0 CALIBRATION ERROR , ON~:: + _-~ " EMERGENCY ID L ~ or; o WARNING 0 EMERGENCY AIRSPEED STATIC SOURCE ON EMERGENCY SEE PILOTS CHECK LIST ~ OR FLIGHT MANUAL (-- - • EMERGENCY PROCEDURES -- FOR AIRSPEED & ALTIMETER CALIBRATION ERROR o NO~~AL 0 or; Ie±> WARNING ffil EMERGENCY AIRSPEED srAllC SOURCE EMERGENCY ,", ON SEE PILOTS CHECK LIST {I OR FLIGHT MANUAL '. : OFF EMERGENCY PROCEDURES, ~ FORC~~::i~~N& ~~~~ETERA NORMAL L<±) <±)--l On Aft Cabin Bulkhead: L 2-30 HAT SHELF NO HEAVY OBJECTS February 1979 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) On Baggage Compartment Door: Section II Limitations IBAGGAGE COMPARTMENTl 270 POUNDS L MAXIMUM CAPACITY ~ On Upper Aft Corner of Each Cabin Door (when installed): f'iNSTRUCTIONS - SHOULDER STRAPl 1. OCCUPANT SHORTER THAN 4FT 71N DO NOT USE SHOULDER STRAP 2. NEVER USE SHOULDER STRAP L WITH OUT LAP BELTS .-J or; ~NSTRUCTION-SHOULDER STRA~ 1. OCCUPANTS SHORTER THAN 4 FT. 7 IN. DO NOT USE SHOULDER STRAP. 2. PLACE SEAT BACK IN THE UPRIGHT POSITION DURING L TAKEOFF AND LANDING. ~ February 1979 2-31 Section II Limitations 2-32 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) INTENTIONALLY LEFT BLANK February 1979