Al LANE FLIGHT MANUAL SUPPLEMENT NO. 185.14.

gross weight is limited to that which is authorized by each particular STC. The pilot is advised to determine this gross limit from each appropriate STC. 5. Center of Gravity Limits -Center of gravity range, inches aft of datum Forward Lim.it Aft Limit Weig·ht, lbs. 43.3 46.5 3600 34.5 46.5 2100 34.5 46.5 1700 Straight line variation between points. 6. Fuel Limitations A. Wing Tip Fuel Tank Capacities (U.S. Gallonsj_ In addition to standard tanks and long range tanks (if installed). Wing Tip Fuel Tank Total capacity 185-Al85E Total Capacity Each Tank Total Usable Total Usable Each Tank FAA APPROVED DATE: = = = = --~---·_I________ 28.0 14.0 27.6 13.8 A185F 30.0 15.0 29.6 14.6 Page STC SA8036NM FLINT AERO, INC. 4 Report Number 185.14 Origination Date Originated By SUPPLEMENTAL AFM, P.O.H. AND AFM SUPPLEMENT TO CESSNA MODELS 185 8 185A, lSSB, l85C, 1850 l85E 8 Al85E, Al85F SEC'J~ION 2 LIMITATIONS Revision Revisioo Date Revised By B. Wing Tip Fuel Tank Transfer. Limits FAA -When feeding from either or both main tanks, do not fer wing tip tank fuel a main fuel tank until at least 14.0 gallons below full (15.0 U.S. gallons for the Al85F). -When feeding from either main tank, begin tip tank transfer .into that tank before its level drops below five gallons remaining. When feeding from both main tanks, begin t tank transfer before either main tank drops below five gallons remaining. -Do not transfer wing t unless level flight. -Do not trans wing tip fuel during take 0ff 1 landing 1 refueling, and when empty. Note: Main fuel tank quantity below the full level can be determined by reference to fuel quantity gauges and by calculating fuel used by: l) Estimating engine fuel flow rates versus time. 2) If installed, using engine fuel flow rate indicator versus time. DATE: Page STC SABO FLIN'l~ AERO, INC. 5 Report Number Revision 185.14 Origination Dai@ SUPPLEMENTAL AFM, P.O.H. AND AFM SUPPLEMENT TO CESSNA MODELS 185, 185A, 185B, 185C, 1850 185E, A185E, Al85F Revision Dal" Originated By S:r:C'rION 2 LIMITATIONS Revised Ely Placards The lowing information is displayed in the form of composite or individual placards. 1. In full view of pilot: 2. For 185, 185A, 185B, 185C, 185D, 185E, A185E: TO':rAL WING TIP FUEL 2 8 U.S. GALLONS ( 2 7 6 GALLONS USABLE) • TRANSFER FUEL DURING LEVEL FLIGHT. TRANSFER FUEL WHEN MAIN TANK CONTAINS NO'l' LESS THAN 5. 0 GALLONS AND IS AT LEAST 14.0 GALLONS BELOW FULL. WING TIP FUEL SWI'rCH MUST BE OFF DURING TAKEOFF, LANDING, REFUELING, AND WHEN EMPTY. MONITOR MAIN FUEL TANK GAUGE WHL..iE TRANSFERRING WING TIP FUEL TO PREVENT OVER FILLING. For Al85F: TOTAL WING TIP FU.EL 30 U.S. GALLONS (29.6 GALLONS USABLE). 'I'RANSFER FUEL DURING LEVEL FLIGHT. TRANSFER FUEL WHEN MAIN TANK CONTAINS NOT LESS THAN 5.0 GALLONS AND IS AT LEAST 15.0 GALLONS BELOW FULL. WING TIP FUEL SWITCH MUS'I' BE OFF DURING TAKEOFF, LANDING, REFUELING, AND WHEN EMPTY. MONITOR MAIN FUEL TANK GAUGE WHILE TRANSFERRING WING TIP FUEL TO PREVENT OVER FILLING. F'orward each tip tank filler: For 185, 185A, 185B, 185C, 1850, 1B5E, Al85E: 14.0 U.S. GALLONS (13.8 GALLONS USABLE) l00LL OR 100/130 MIN. GRADE AVIATION GASOLINE For Al85F: 1.5.0 U.S. GALLONS (14.8 GALLONS USABLE) lOOLL OR 100/130 MIN. GRADE AVIATION GASOLINE FAA APPROVED DATE: STC SA80 Report Number 185.14 Origina!ion Oalt1 Onginaied By FLINT AERO, INC. SUPPLEMENTAL AFM, P.O.H. AND AFM SUPPLEMENT TO CESSNA MODELS 185 1 185A, l85B 1 l85C, 185D l85E, AlBSE, A185F SECTION 2 LIMITA'rIONS 3 • Adjacent to wing fuel tank pump switches Page 6 Revision Revisoo By WING 'I'IP FUEL TANK PUMPS MUST BE OFF DURING 'rAKEOFF, Ll\.NDING, REFUELING AND WHEN EMPTY. MONITOR MAIN FUEL TANK GAUGE WHILE TRANSFERRING WING TIP FUEL TO PREVENT OVER JnLLING. 4. 5. FAA At wing tip fuel tank pump For 185, 185A, 185B, 185C, 185D, 185E, Al85E: LEFT WING TIP FUEL 14.0 GALLONS 13.8 GALLONS USABLE ON OFF For Al85F: LEF'r WING TIP FUEL 15.0 GALLONS 14.8 GALLONS USABLE ON OFF RIGHT WING TIP FUEL 14.0 GALLONS 13.8 GALLONS USABLE ON OFF RIGHT WING TIP FUEL 15.0 GALLONS 14.8 GALLONS USABLE ON OFF near wing tip fuel gauge: For 185, 185A, 185B, 185C, 1850, 185E, AlBSE: LEFT WING TIP FUEL 13.8 U.S. GALLONS USABLE For Al85F: LEFT WING TIP FUEL 14.8 U.S. GALLONS USi-\.BLE DATE: RIGHT WING TIP FUEL 13.8 U.S. GALLONS USABLE RIGHT WING TIP FUEL 14.8 U.S. GALLONS USABLE STC SA Report Number 185.14 Origination Dale Originated By FLINT AERO, INC. SUPPLEMENTAL AFM, P.O.H. AND AFM SUPPLEMENT TO CESSNA MODELS 185, 185A, 185B, l85C, 185D 18SE, Al85E 8 Al85F SEC'I'ION 2 LIMITATIONS Paga 7 Revision Revision Date Revised By 6. Installed acent to each wing fuel tank leak detection drain (3 per side): FUEL OR VAPOR FROM DRAIN REQUIRES IMMEDIATE REPAIRS 7. Installed adjacent to appropriate wing tip tank pump circuit breakers or fuses: TIP TANK L PUMP TIP TANK R PUMP r'AA APPROVED DATE: Report Number 185.14 Origination Dale Originated By FLINT AERO, INC. SUPPLEMENTAL AFM, P.O.H® AND AFM SUPPLEMENT TO CESSNA MODELS 185 1 185A 1 185B, 185C, 185D 185E, Al85E, Al85F SEC'rION 3 EMERGENCY PROCEDURES Pago 8 Revision Revision Date Revised By All references in the Cessna Pilot 1 s Operating Handbook to the auxiliary fuel pump are to the electric fuel pump supplying fuel to the engine. With Flint Aero, Inc. Wing Tip Fuel Tanks installed, fuel transfer to the standard main wing tanks provided by the wing tip fuel transfer tank pumps controlled by the wing tip fuel tank transfer pump switches. EMERGENCY LANDING WITH OR WITHOUT ENGINE POWER (adgj_ Wing Tip Fuel Tan le transfer pump switches ..•.. OFF. WING FIR1'~ (add) Wing Tip Fuel Tank transfer pump switches ..... OFF. FAA APPROVED DATE: Page FLINT AERO, INC. 9 Report Number Ravisioo 185.14 01iginalion Dal® SUPPLEMENTAL AFM, P.O.H. AND .AFM SUPPLEMENT TO CESSNA MODELS 185, 185A, 185B, l85C, 185D lSSE, A185E, A185F Revision Data Originated By SECTION 4 NORMAL PROCEDURES Revised By PREFLIGHT INSPECTION - WING TIP FUEL TRANSFER TANKS 1. Visually inspect external areas of wing around wing tip fuel tanks for any signs of fuel leakage. 2. Check each wing tip tank lines for obstructions. for quantity. cap security and vent Visually check wing tip fuel tanks 3. From each wing tip fuel tank, drain a sample quantity of fuel. Check for contamination. If any water is visible, additional amounts of fuel until all water is expelled from the tank. 4. switch on. Check wing tip fuel tank gauges for fuel quantity. 5. With master switch on, check each wing tip fuel tank pump for operation by operating each pump separately with wing tip fuel tank transfer switches. Listen for pump If no noise or vibration, assume pump is not Check for serviceability. Before Takeoff (addl. a. the following to the before takeoff procedure: Wing tip fuel tank pump switches ...•........ OFF Fru~ APPROVED DATE: STC SA803 R0port Numoor 185.14 Origination Dale Originated By FLINT AERO, INC. SUPPLEMENTAL AFM, P.O.H. AND AFM SUPPLEMENT TO CESSNA MODELS 185, 185A, 185B, lSSC, 185D l85E, A185E, Al85F SECTION 5 PERFORMANCE Revision Revision Dal® Revised By The performance tables in this supplement address the operation of an airplane incorporating STC SA8036NM at gross weights greater than previously certificated. For any weight greater than the previously certificated gross weight, use the performance tables in this supplement. However, interpolation of performance data may be used between that appropriate to the highest previous Cessna weights and the 3600 pound maximum gross weight of these performance tables. For weights equal to or less than tb.e previously certificated gross weight, use the standard pecformance tables applicable to the basic unmodified airplane. The Fl Tip Fuel Tanks may be used in con-junction with other approved modifications provided it is determined that no interference exists. In this instance, the performance procedure in the paragraph above applies and in addition performance decrements must be applied as previously defined for that other installation. FAA APPROVED DATE: Paga S'rC SA8036NM FLINT AERO, INC. 11 Report Number Ravi>.ion 185.14 SUPPLEMENTAL AFM, P.O.H. AND Origination Date Ali"'M SUPPLEMENT TO CESSNA MODELS Revision Date 1135, 185.A, l.8SB., l85C, 185D Originated By 18.SE., A1S5E 1 Al85F Revised By SECTION 5 STALL SPEEDS CONDITIONS: Power Off NOTES: 1. Altitude loss during a stall recovery may be as much as 200 fl. STAU. SPEED, CAS Anole of Bank 0 Dea 30D= 45 [1':!cl 60 De<! Condition MPH KCAS MPH KCAS MPH KCAS MPH KCAS MQ..cJ.!tl 185, 185A, Flaps Up 69 60 75 65 83 72 98 85 1858, 185C, 185D, 185E Flaps20 Deg 67 58 72 62 79 69 94 82 3600100 Gross Flaps40 Deg 66 57 71 61 78 68 93 81 Weiaht STALL SPEED, CAS ft.ncile of Bank 0 De<! 30 Dea 45 De;::i 60 Dea Condition MPH KCAS MPH KCAS MPH KCAS MPH KCAS Mog~J A185E Flaps Up 66 58 7'1 62 79 69 94 82 Flap(, 20 Deg 65 56 70 60 77 ol 91 80 360011,s Gross Flaps40 Deg 63 55 68 59 75 65 89 77 Weiciht STALL SPEED, CAS Anole of Bank ODea 30 ilPn 45 Dea 60 Dea Goridition MPH KCAS MPH KCAS MPH KCAS MPH KCAS Model A185F Flaps Up 65 57 70 61 78 68 92 80 Flaps 20 Deg 61 53 65 57 72 63 86 75 36001bs Gross Flaps40 Deg 60 52 64 56 71 62 84 73 Weiaht FAA APPROVED DA'l'E: ~ Paga FLINT AERO, INC. 12 Report Number R1111ision 185.14 SUPPLEMENTAL AFM, P00.H. AND Origination Dale AFM SUPPLEMENT TO CESSNA MODELS Revision Date 185, 185A, 185B, 18SC, 1850 Originatocl By 185E, AlSSE., Al85F Revisoo By SECTION 5 PERFORMANCE-TAKEOFF DISTANCE CONDITIONS: NOTES: Flaps 20 1. Short field technique as specified in Section 4. 2850 RPM, Full Throttle, 2. Where distance value has been deleted, climb pe1ionnanc:e after and Mixture Set at Placard lift-off is less than 150 fpm at takeoff speed. Fuel Flow Prior to Brake 3. Decrease distances ·10% for each 10 knots headwind. For operation Release with tailwinds up to 10 l<nots, increase distances by 10% for each 2.5 l<nots. Cowl Flaps Open 4. For operation on a dry, grass runway, incre.150 distances by 15% of the "ground Paved, Level, Ory Runway rolr figure Zero Wind •jf a 3--bladed orooeller is installed increase KlAS values bv 3 CESSNA 185 ·· 185E TAKEOFF DISTANCE, FE!IT TAKEOFF ODEGC 100EG C 200EG C 30 DEG C 40 DEG C GROSS SPEED PRESS TOTAL TOTAL TOTAL TOTAL TOTAL WEIGHT, IAS ALT GNO fOCLR ONO TOClR GND TOCLR GND TOCLR ClNO TOC~ POUNDS LIFT AT UNiTS FT ROLL 50FOOT ROLL 50FOOT ROLL 50FOOT ROLL 50FOOT ROLL 50 FOOT OFF 50 FT OBSTCL OBSTCt OBSTCL OBSTCL OBSTCL 3600 61 73 MPH S. L, 1086 1788 1171 1850 1239 1901 1319 200l 1415 2131 58 64 KTS 1000 1177 1850 1247 1911 1331 2019 1425 2144 1517 2270 2000 1244 1908, 1327 2013 1435 2158 1549 2315 1688 250!! 3000 1335 2024 1445 2171 1571 2345 1700 2525 1838 2722 4000 1450 2178 1571 23•5 1712 2543 1858 2750 2014 2974 5000 1583 2361 1724 2560 1871 2769 2021 2984 2156 3180 6000 1724 2560 1878 2778 2027 2994 2171 3202 2358 3476 7000 1884 2788 2042 3014 2200 3245 2373 3499 2530 3730 8000 2056 3035 2215 3266 2381 3510 2546 3754 CESSNA A185E, F TAKEOFF DISTANCE. FEET TAKEOFF ODEGC 10DEG C 20DEG C JODEGC 40DEG C GROSS SPEED PRESS TOTAL TOTAL TOTAi. TOTAL TOTAL WEIGHT. IAS ALT GNO TOCLR GND TOCI.R GND TOCLR GND TOCLR GNO TOC~ POUNDS LIFT AT UNITS FT ROLL 50FOOT ROLL 50 FO<lT ROLL 50FOOT ROLL 50FOOT ROLL OOFOOT OFF 50FT OBSTCL OllSTCt OBSTCL OBSTCL OBSTCL 3600 64 71 MPH S.L. 771 1548 862 1610 924 1661 1004 1763 1100 1891 111851: 5ll 62 Kl'S 1000 862 1610 932 1671 1016 1779 1110 1904 1202 21l30 2000 929 1668 1012 1773 1120 1918 1234 2075 1373 2268 3600 60 00 MPH 3000 1020 1784 113(l 1931 1256 2105 1385 2285 1523 2482 11185F 52 58 KTS 4000 1135 1938 1256 2105 1397 2303 1543 2510 1699 2734 5000 1268 2121 1409 2320 1556 25:>9 1706 2744 1841 2940 6000 1409 2320 1563 2538 1712 2754 1856 2962 2043 3236 7000 1569 2548 1727 2774 1885 3005 2058 3259 2215 3490 8000 1741 2795 1900 3026 2066 3270 2231 3514 2393 3755 F'AA APPROVED DATE: Page FLINT AERO, INC. 13 Report Number Revision 185.14 SUPPLEMENTAL AFM,, P.O.H. AND Origina!ion Data AFM SUPPLEMENT TO CESSNA MODELS Revision Date 185, l85A., 185B,, 185C, 18.50 Originated By l85E, Al85E., 1U85F Revisad By SEC'1 rION 5 PERFORMANCE MAXIMUM RATE OF CLIMB MIXTURE SETTING PRESS GPH COND!TIONS: ALT Flaps UP SL 23 2700 RPM 4000 21 Full Throttle 8000 19 Mixture Set at Placard Fuel Flow 12,000 17 Cowl Flaps Open CESSNA 185 185A, 1858, 185C, 185D, 185E PRESS CLIMB SPEED RATE OF CLIMB, FPM WElGHT ALTITUDE, IAS TEMPERATURE, DEG C LBS FEET MPH KTS -20 0 20 40 3600 0 87 76 1237 1066 909 754 2000 87 76 1069 902 741 587 4000 87 76 909 731 574 419 6000 87 76 734 567 413 262 8000 87 76 563 399 252 115 10000 87 76 396 232 84 12000 87 76 232 78 CESSNA Ai 85E, A 185F PRESS CUMB SPEED RA TE OF CUMS, FPM WEIGHT ALTITUDE, IAS TEMPERATURE, DEG C LBS FEET MPH KTS ~20 0 20 40 3600 0 92 80 1370 1199 1042 887 2000 92 80 1202 1035 874 720 4000 92 80 '1042 864 707 552 6000 92 80 867 700 546 395 8000 92 80 696 532 385 248 10000 92 80 529 365 217 771 12000 92 80 365 211 60 FAA APPROVED DA'rE: I S'I'C Page SA8036NM FLINT AERO, INC. 14 Report Number Revision 185.14 SUPPLEMENTAL AFM, P.O.H. AND Origination Datei AFM SUPPLEMENT TO CESSNA MODELS Revision Date 185, 185A, 185B, l85C, 185D Originated By 185E., Al85E 1 Al85F Revised 811 gQ.Il9fil:PERFQRMA~ RANG~ PROf:.!.U,;_ With wing tip fuel tanks 28.0 U.S. Gallons (27.6 usable). 30.0 U.S. Gallons (29.6 usable) for A185F. Manufacturers maximum usable fuel charts for range and endurance calculations are valid fOf usable fuel quantity as slated in the basic manual. Full use of wing tip tank fuel for extended range and endur<111ce was not deteimined. J.M!QliiQJ;!ISTANCE - §HQRT FIELD CONDITIONS NOTES: Flaps 40 degrees 1. Short field technique as specifled in Section 4. Power Off 2. Decrease distances 10% for each 10 knots headwind. For operation Maximum Braking with tailwinds up to 1O knots, increase distances by 10%. Paved, Leve!, Dry Runway 3. For operation on a dry, grass runway, increase distances by 40% of !he Z:eroWind ·ground roll" figure. CESSNA i85 - 185E STOPPING AND LANDING DISTAl,JCE, FEET 0 DEG C 10 DEG C 20 DEG C 30 DEG C 40 DEG C INOICATEO GROSS AIIISl'EED PRESS TOTAL TO TOTAi. TO TOTAL TO TOTAL TO rQTAI. TO WEIGHT AT ALT STOPPING CLEA/I STOPPING CLEA/I STOPPING CLEAi! STOPPING CLEAR STOPPING CUiAR POUNDS SOFT DIST !lllFOOT 01ST 5>01'00T DIST !>OfOOT D1$T OOfOOT DIST 50FOOT MPH I<",$ FT OBSTACLE OBSTACLE OBSTIICL~ OBSTACLE OSll'TAClE 3600 77 61 S. L. 494 1252 506 1293 511 132'9 531 1371 545 1411 1000 506 1293 519 1334 533 1376 546 1415 558 1446 2000 518 1332 532 1375 547 1418 561 1459 577 1504 3000 534 1378 549 1422 564 1467 578 1508 593 1550 4000 549 1424 564 1467 580 1512 595 1556 611 1600 5000 565 1470 581 1516 597 1559 611 Hl02 624 16311 6000 581 1516 597 1561 612 Hl04 626 1642 643 1691 7000 598 1563 613 160'1 629 1650 644 1695 658 1734 8000 615 1611 630 1654 645 1697 660 1116 674 1m CESSNA A185E, AH.l5F STOPPING AND LANDING DISTANCE, FEET INOICATEO 0 DEGC 10DEG C 200£:GC 30DEG C 40DEGC GROSS AIRSPIEE!l PRESS TOTA!. TO TOTAi. TO TCIT/1.1. TO TOTAi. TO TOfAI. TO WEIGHT AT ALT STOPP ..G CLEAi! STOPPING Ci.EA~ STOPPING C:!.EAR STOPPIIIIG C:UiAR STOPl'!l>IG Cl.EAR POUNDS 50 ~"T 01ST SOfOOT DIST 511FOOT lllST OIIIFOOT DlftlT OOFOOT DIST SO FOOT MPH KT$ FT OBSTACLE OBSTACLE OBSYACtE OBSTACLE 06STACl.l: 71 67 S. L. 494 1375 506 1415 5"17 1452 531 1494 544 1534 1000 506 1416 5-JB 1457 533 1499 546 1538 557 1571 2000 5°18 1455 532 1498 547 1541 561 1582 577 1627 3000 533 1501 548 1545 564 159() 578 1631 593 1673 4000 549 1547 564 1590 579 1635 595 Hl79 610 1723 5000 565 1593 581 1639 596 1683 611 1725 624 1762 6000 581 1639 597 1684 612 1727 625 1765 643 1814 7000 597 1686 613 1731 628 1173 644 1818 658 1857 8000 614 1734 629 1777 645 1820 659 1861 673 1900 FAA APPROVED DATE: Pag@ C FLIN'r AERO, INC. 15 Report Number Revi&ioo 185.14 SUPPLEMENTAL AFM, P®O.H0 AND AFM SUPPLEMENT TO CESSNA MODELS 185, l85A, 185B, l85C, 1850 l8SE, A185E, Al85F Origination Dal@ Originai<Ml By SECTION 6 WEIGHT AND BALANCE/EQUIPMENT LIS~I ITEM EQUIPMENT LIST DESCRIPTION REF WEIGHT ARM NO DRAWING lbs. inches C. ELECTRICAL SYSTEMS C-1-F Fuel Pump - l.H. Wing Tip Tank FA185-IN 1.5 34.3 C-2-F Fuel Pump - R.H. Wing lip Tank FAHl5-lN 1.5 34.3 D. INSTRUMENTS D-1-F Gauges - L.H. & R.H. Wing Tip Fuel Tank Quantity Indicator FA185--IN 2.5 37.8 F-1-F Placards: Various - see this supplement section 2 limitiltions FA185--IN nag'I neg'I J. SPECIAL PACKAGES J-1-F Wing tips & fuel tillnks including positic:in lights (net change) 1 - Remove Cessna lllling tips and install Flint Aero Wing Tip Fuel Tanks FAl85-!N 31.Cl 52.6 2 - Unusabh;i fl.lEII in Flint Aero Wing Tip Tmnks (0.4 U.S. Gal. at 6 lbs./U.S.gat) FA185-IN 2.4 46.4 TOTAL INSTALLATION NET CHANGE 38.9 49.9 Revision Date Ravisoo Ely MOMENT lb.-~n. 51.5 51.5 95 neg'! 163"1 111 1940 NOTE FOR In Cllllculating I/I/flight and balance fur full lllli11g tip fuel tank: 27.6 U.S. gal. usabla x 8 lbs.JU.S. 185-A-i85E gat x 46.4 in. arm= 7684 lbs. - in. or 7.684 lbs. - in/1000 C.G. = total moment divided by tot.ii weight_ NOTE FOR In calculating \1\18ight and balance fur full wing tip fuel tank: 29.6 U.S. gal. usable x 6 lbs./U.S. A185F: gal. x 46.4 in. arm= 8241 lbs. - in. or 8.241 lbs. - in/1000 C.G. = total moment divided by total FAA APPROVED DATE: __________,__Mllll!.ll&i!.!,!l ________imr_i___w ________________________.,,,_,_,......,.j STCReport Nurnb<K 185 14 Origination Dale Originaled By 0.000 3700 3600 3500 -- ~ 3400 - § 3300 [ 3200 ._: 3100 :r: JOO() Cl ~290() -$ 2800 !i~ 2400 Cl 2300 - UJ 2:200 Q 2100 g 2000 - 1000 1800 1700 - 50 1.000 60 FLINT AERO, INC. SUPPLEMENTAL AFM, P®O.H® AND AFM SUPPLEMENT TO CESSNA MODELS 185, 185A, 185B, 185C, 185D 185E 1 A185E, A185F 2000 3.000 4.000 5.000 6.000 1.000 LOAD MOMENT/ iOOO, pound -inch'i!ili 70 80 00 100 no 120 -130 140 8.000 150 LOADED AIRPLANE MOMENT/ 1000, pound -inches FAA APPROVED DATE: Page 16 Revision Revisio11 Date Revisocl By 9.000 10.000 160 170 100 I Report Number 185.14 Origination Date Originated By FLIN'I' AERO, INC. SUPPLEMENTAL AFM, P.O.H. AND AFM SUPPLEMENT TO CESSNA MODELS 185 1 l85A 1 185B, 185C 1 185D 185E, A185E, Al85F SECTION 7 AIRPLANE & SYSTEMS DESCRIPTIONS 1. Wina Tio fuel Tank- Can~cities (U.S.G~ a. In addition to standard tanks: Wing Ti:t2 Fuel Tank 185-A185E Total Capacity = 28.0 Total Capacity Each Tank = 14.0 •rotal Usable = 27.6 Total Usable Each Tank = 13.8 2. pperation of Wing 'I'ip Fuel Tanks (transferl Page 17 R011ision Revision Date Revised By Al85F 30.0 15.0 29.6 14.6 a. •ro transfer, turn applicable "wing tip fuel tank transfer switchu• on. When wing tip tanks indicate empty, turn applicable transfer switch off. As a general procedure, do not transfer wing tip tank fuel until burning approximately one hour of fuel from each main tank. NOTE: Should the transfer pump fail, it is not possible to transfer fuel from the affected tank in flight. See diagram on page 18 FAA APPROVED DATE: R ..po,t Num!>M 185.14 Ongmalion Date On1,1111.1too By WING TIP TANK FUEL TRANSFER r----; PUMP SWITCH 1NON-VENTED FILLER CAP LH WING TIP FUEL QUANTITY INDICATOR FAA VENT (WITH CHECK VALVE) FLINT AERO, INC. SUPPLEMENTAL AFM, PwO.H. AND AFM SUPPLEMENT TO CESSNA MODELS 185, 185A, 185B, 185C, 185D 185E, Al85E, Al85F SEC'I'ION 7 AIRPLANE & SYSTEMS DESCRIPTIONS TIP TANK LEFT PUMP \ (2) 5 AMP THERMAL CIRCUIT BREAKERS OPTIONAL (2) 5 AMP FUSES WING TIP TANK FUEL TRANSFER PUMP SWITCHES TRANSFER PUMPS I Paga 18 Rovi;;ion Dale B WING TIP TANK FUEL TRANSFER PUMP SWITCH VENT (WITH CHECK VALVE) NON-VENTED FILLER CAP AIRCRAFT M.AIN BUSS BAR CHECK FLIGHT MJ\NUAL FOR LOCATION RHWlNG TIP FUEL QUANTITY INDICATOR ~TC SA8036NM FLINT AERO, INC. Report Number 185.14 SUPPLEMENTAL AFM, P.O.H. AND Origination Date AFM SUPPLEMENT TO CESSNA MODELS 185 1 185A, 185B, 18SC, 1850 OriginatooBy 185E, Al85E, Al!35F AIRFRAME SECTION 7 AIRPLANE & SYSTEMS DESCRIPTIONS WITH WING TIP FUEL TANKS (TRANSFER) Paga 19 Revision Revision Data Revisoo By Left and right wing tip fuel transfer tank quantity gauges and pump switches are located on subpanels in left and right wing roots. Fuses or circuit breakers are connected to the aircraft electrical system main buss bar and are accessible with visible placarding. FUEL QUANTITY DATE (U.S. GALLONS) Add 27.6 U.S. gallons ( 29.6 U.S. gallons for A185F) additional usable fuel to the total fuel available in the Cessna tanks. In addition to the Cessna main fuel tanks, two wing tip fuel transfer tanks are installed as wing tip extensions. The capacity is 14.0 U.S. gallons each tank (13.8 usable U.S. gallons)[15.0 U.S. gallons (14.8 usable) for Al85F]. These tanks transfer to their respective main wing tank by transfer pumps controlled by switches in the cockpit. Each wing tip tank has a water drain and is vented through an overboard vent line. Each tank has an individual quantity gauge. NO'I'ES The wing tip fuel (transfer) tank quantity gauges are similar in operation to the main fuel tank gauges and visual inspection of the tanks during preflight is the best assurance of fuel quantities. No provision is provided to visually determine reduced tank quantity. FAA APPROVED DATE: Report Numoo, 185.14 Origination Dala Originaioo By FLINT AERO, INC. SUPPLEMENTAL AFM 11 P.O.H. AND AFM SUPPLEMENT TO CESSNA MODELS 185 1 185A, 185B, 185C, 185D 185E 11 A185E, A185F Page 20 Revision Revision Date Revised By The fuel in the wing tip fuel transfer tanks is available to the engine only through the aircraft main fuel tanks. The main fuel tank gauges are the sole reference gauges for immediately available engine fuel. Should a wing tip fuel (transfer) tank pump fail, it is not possible to transfer fuel from the affected tank during the flight in progress and the pilot must immediately adjust his range and endurance calculations on the basis of the available fuel through the standard fuel system. FAA APPROVED DATE: Report Numoor 185.14 Origination Dat<> Origimatoo Sy FLINT AERO, INC. SUPPLEMENTAL AFM, P00.H. AND AFM SUPPLEMENT TO CESSNA MODELS 185, 185A, lBSB, 185C, lBSD 185B, A18SE, A185F SECTION 8 AIRPLANE HANDLING, SERVICE AND MAINTENANCE WITH WING TIP FUEL ('rRANSFER) NO"rE Before flight, check the filler neck fuel quantity. No is made for capacity in the auxiliary tanks. FAA APPROVED DATE: Page 21 Ravislori Revision Dale Ravi~ By reduced ---------,-=-r:r:err-~-..---~--·------------------------------