TCDS TC 689

Page No. 1 2 3 4 5 Rev. No. 3 1 1 1 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 689 Revision 3 Textron Aviation F17D SF17D October 12, 2016 TYPE CERTIFICATION DATA SHEET NO. 689 Type Certificate Holder Textron Aviation Inc. One Cessna Boulevard Wichita, Kansas 67215 Type Certificate Holder Record Beech Aircraft Corporation transferred to Raytheon Aircraft Company on April 15, 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12, 2013 Beechcraft Corporation transferred to Textron Aviation Inc. on October 12, 2016 689 2 Rev. 3 MODELS: Beechcraft F17D (UC-43C) and SP17D, 5 PCL-SB I.C. NUMBER: 689 (Approved 8/26/38 and 6/10/41 respectively) (Same as E17B, I.C. 641, except engine installation) Engine Jacobs 1-6, L-6M or I-6MB Fuel 80 min. octane aviation gasoline Engine limits Maximum, except take-off (sea level) 24.5 in. Hg.. 2100 pm (300 hp) (Straight line manifold pressure variation with altitude to 3700 ft.) 23.5 in. Hg.. 2100 rpm (one minute) 26.0 in. Hg.. 2200 rpm Airspeed limits Landplane: Level flight or climb - 189 mph True Ind. Glide or dive - 222 mph True Ind. Flaps extended - 117 mph True Ind. Level flight or climb - 140 mph True Ind. Glide or dive - 169 mph True Ind. Flaps extended - 117 mph True Ind. Propeller limits Maximum permissible diameter 107 in. C.G. range Landplane (+17.4) (8.4 percent MAC) to (*27.4) (26 percent MAC) Seaplane (*16.5) (6.8 percent MAC) to (*23.5) (19.1 percent MAC) Datum Leading edge of lower wing MAC 57.2 in. L.B. MAC (+12.6) Leveling means Airplane level when stagger (horizontal distance between wing trailing edges near fuselage) is Maximum weight Landplane - 3590 1bs. Seaplane - 3940 1bs. No. seats 5 (2 at (+18), 3 at (+62)) (See item 301) Baggage 125 1bs. maximum (+88) (See item 216) Fuel capacity 77 gallons (three tanks - two 24 gallon tanks in lower wings (+24) and one 29 gallon tank in fuselage (+32)) (See item 314) Oil capacity 5 gallons (-16) Control surface 38 degrees up 25 degrees down movements Flevator tabs 21 degrees ap 25 degrees down 32 degrees up 24 degrees down 28 degrees right 28 degrees left Rev. 3 3 689 Serial Nos. eligible Required equipment Landplane: 211 and up, except 219"102, 103, 104, 105, 106. Items 101'111, 43 degrees down and all AAF numbers 107, 108, 109, 110, 113 and 114 105, 108, 109, 110, 111, 113, 114, 151, 152, and 153 Specifications Pertinent to All Models Type Certificate No. 689 (CAR 4a) None (See NOTE A) Export eligibility Eligible for export as follows, subject to (a)rovisions of MOP 2-4: Landplane and seaplane eligible Skiplane - not eligible. However, structure complies with Canadian requirements for ski gear when Item 310 is installed. pedestal height 17 in. Tread is same as (b) All other countries except New Zealand. EQUIPMENT: A plus (+) or minus (-) sign preceding the weight of an optional item indicates the net weight change between that item and the equivalent required item. Propeller and Propeller Accessories Propeller - fixed pitch metal 56 lbs. (-59) 218. Constant speed governor - Hamilton Standard A4 (minimum low pitch setting 11 degrees at 42 in. station) 5 1bs. (-22) Propeller - Hamilton Standard hub 2B20, blades 6135A-12 to 6135A-16. 6' 1/8" maximum, 7' 8-7/8" minimum 104 lbs. (-59) Engines and Engine Accessories - Fuel and Oil Systems Engine ring cowl (NACA type) (-44) Carburetor heater (muff (-44) Starter (Eclipse E60) (-26) 109. Oil radiator (Drawing E179850 or Harrison 3074410) (-34) 110- Wobble pump (type D-2) (+12) Engine driven fuel pump series or Romec RD-3080) (-28) 0il tanks (6-1/2 or 8 gallon) 1bs. (-16 one 23 or 24 gallon tank, upper 20 1bs. (+47) One 23 or 24 gallon tank, upper 20 lbs. (+47) replace lower wing tanks) Ignition shielding Breeze or Titeflex 15 1bs- (-45) 10 1bs- (-45 219. Special oil drain and oil radiator by-pass valve 3 1bs. (-29) 220. Exhaust gas analyzer (Breeze or Cambridge) 5 lbs. (-8) 223- Auxiliary engine drive units (a) Jacobs No. 669 (c) (3 drives) 7 1bs. (-26) Jacobs No. 768 or 776 (2 drives) 4 1bs. (-26) 314- One 23 gallon fuel tank in each lower wing (replacing 24 gallon tanks) No change in weight Landing Gear and Floats 106- 7.50-10 wheels (Goodyear 10HBM) with 6-ply tires (wheels must be placarded for these tires) 75 1bs. (+5) 107- 10x3 tail wheel with 4-ply H.D. tire (wheels must be placarded for this tire) 5 lbs. (+205) 151. Edo 39-4000 floats with water rudders 305. Dual brakes +2 lbs. (=} 306. Hand operated parking brake 2 1bs. 307. Emergency wood landing skids (Drawing E170140) 16 1bs. 1+22 308- Puncture proof tubes +8 1bs. 310- Skiplane landing gear (Drawings E17820 and E17840) +3 1bs. (+20) 311. 10 in. smooth contour tail wheel assembly with 6-ply tire +1 1b. (+205) 689 4 Rev. 3 Electrical Equipment Generator (Eclipse G) 15 amp 15 1bs. (-28) Battery (Exide 6TS-13-1) 36 1bs. (-21) or (+92) Landing gear motor (Dumore D5, fuse required) 9 1bs. (+7) Flap motor (Dumore KL, 30 amp fuse required) 8 lbs. (+45) 25 amp (Eclipse D) 20 1bs. (-28) (b) 50 amp (Eclipse E) 25 1bs. (-28) 217. Landing lights (a) (b) One or two (Hall A-6) One or two (Grimes ST-250) 4 1bs. each (+35) 4 1bs- each (+21) or (+44) (c) One or two (Grimes ST-1000 or ST-1220) 4 1bs. each (+21) 312. Flap motor flexible drive) (30 amp fuse reguired) 5 ibs. (+45) 313. Cannon plug (for electric starter) 3 1bs. (-2) Or (-8) Interior Equipment 108. 202. Cabin heater Swing-over control column (muff type) 11 1bs. 3 1bs. 1-30 + 0 203. Fire extinguisher (pressure type) (a) (b) Lux - 2 1bs. Iux - 5 1b55C 17 1bs. 12 1bs. (-3) (-13) (c) Pyrene No. 12 1bs. (-10) (a) ACe 10 1bs. (-10) (e) Lux - 5 1bs. (Drawing I-170555) 21 1bs. (+60) 206. Parachute flares (a) Three or four 1-1/2 minute 6 1bs. ea. (+80) or (+108) (International MK-1) (D) One or two - 3 minute (Wiley A-8) 18 1bs. each (+105) 209. Parachutes or parachute type chairs or parachute hammock in. rear seat back 211. Vacuum equipment (a) (Pesco 194, Romec RD-2112 Eclipse 3166B-1) 223 under Engine Accessories) 5 1bs. (-20) or (-26) Venturi tubes 1 1b. (-4) 301- Control column ("T" type) No weight change 309. Folding back seat (may replace standard front seats) 16 1bs. (+21) Miscellaneous (not listed above) Auxiliary seaplane fin (Drawing D17635) (+220) Water rudder control system (+110) 208. Golf compartment (Drawing I-17006) (maximum capacity 70 1bs. baggage allowance) (+100) 212. Extra cabin door on right side (+42) Fuselage alterations for purpose equipment Photographic version (Item 214) Includes front and rear floor windows, camera and viewfinder wells, and change in location of rudder cables (Drawings D17015 and (+33) (b) Ambulance version (Item 215) Includes rear seat center support and litter floor attachments (Drawings I-17073 and I-17077) +2 lbs. (+53) (c) Mailplane version (Item 216) Includes rear seat center support and metal lined baggage compartment and right rear of cabin (Drawings I-170812 and I-170813) +15 1bs. (+73) 214_ Photographic version (See Item 213(a)) (a) Camera and viewfinder Maximum 110 1bs. (+51) Photographers stool 4 1bs. (+65) (These items (a and b) may installed after fuselage altera- tions (Item 213(a)) been made, and standard rear seat, (+67), camera and viewiinder plates, 3 lbs. been removed) 215. Ambulance version (See Item 213(b)) Special right or left half' seat (Drawing I-17073) (may replace standard rear seat, Rev. 3 5 689 31 lbs. (*67), if fuselage alterations (Item 213(b)) have been made) 17 1bs. each (+67) (b) First aid bor installation 7 1bs. (+48) (c) Ambulance litter and two safety belts (may be installed after fuselage alteration (Item 213(b)) and removal of right half rear seat (s), and copilots seat, 14 1bs. (+42) 216- Mailplane version (See Item 213(c)) (a) Same as 215(a) except Drawing I-170812 (b) Removable front and inner sides of forward mail compartment - see (c) 10 1bs. (+52) (C) Mail compartments and capacities: (1) Front laximum 200 1bs. (+54 (2) Rear laximum 150 1bs. (+88 221- Ballast at tailpost (Drawing I-17007) Maximum 25 1bs. (+224) 302. Metal cover for lower wing fuel tank 3 1bs. (+24) 304. Quick door release 1 1b. (+25) Current weight and balance report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certifi- cation and at all times thereafter (except in the case or air carrier operators having an approved weight control system). Fuel restriction placard must state: "Use fuselage tank for take-off and landing. Fill fuselage tank before filling wing tanks. Use wing tanks before using fuselage tank." When upper wing fuel tanks are installed, add, Fill lower wing tanks before filling upper wing Use upper wing tanks before using lower wing tanks„i Prior to original certification, each aircraft manufactured subsequent to August 7, 1945, must satisfactorily pass: An inspection for workmanship, materials and corformity before covering, metal priming or final finish is applied. inspection of the completed aircraft. A check of the flight characteristics. --- END ---