# TCDS TC 770: Hawker Beechcraft Corporation - Type: Type certificate data sheet - Status: Current - Holder: Hawker Beechcraft Corporation - Revision: 1 - Revised: September 1, 2010 - Product: Aircraft, Small Airplane - Certification basis: CAR 4a - Data sheet PDF: https://openairdocs.org/files/sha256/57/74/5774f86b55ddabc10399129176ee1f4494a4cdeb31e474b8172df72799ccd248 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/12F6F313E93B82DE862577C800473B46.0001 - Page: https://openairdocs.org/tcds/TC%20770 ## Models (2) As the data sheet lists them. - D18C-T - 10 PCLM ## What the data sheet says This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TC 770 Revision 1 Hawker Beechcraft D18C-T 10 PCLM September 1, 2010 AIRCRAFT SPECIFICATION NO. 770 Type Certificate Holder Hawker Beechcraft Corporation 9709 East Central Wichita, Kansas 67201 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 MODELS: Peechcraft D18C-T, 10 PCIM T.C. NUMBER: 770 (Approved 6/3/47) Engines 2 Continentals R9-A Fuel 91 minimum octane aviation gasoline Engine limits Maximum continuous, (S.L.) 41.5 in. Hg.. 2300 Ipm (500 hp); (Straight line manifold pressure variation with altitude to 4000 ft.) 40.0 in. Hg . 2300 pm (500 hp) ; Take-off (two minutes) 43 in. Hg., 2800 rpm (525 hp) Airspeed limits Maneuvering 135 mph True Ind. Cruising 205 mph True Ind. Never exceed 256 mph True Ind. Flaps extended 120 mph True Ind. Landing gear extended 134 mph True Ind. C.G. range (+109-8) (*11 at 600. 15 straight Ite (+105.0) or less. variation between points given. Range is with landing gear extended. Retraction of gear yields +11.783 in. lb. Leveling means Leveling lugs on top of fuselage, forward of cabin door Datum Nose of fuselage, most forward point 102 inches forward of centerline of main wing spar (placard denoting datum installed on bottom of fuselage) - Page No. 1 2 3 4 5 Rev. No. 1 770 2 Rev. 1 Maximum weights Landing 9,000 1bs.; take-off 9,000 1bs. No - seats Maximum 10 Maximum baggage Nose compartment: 600 1bs. (+28) . When 47 auxiliary fuel tank is installed, Rear compartment: exceed 600 1bs. (+28) ibs. (+243). When chemical combined weight of fuel and baggage must not toilet is installed capacity reduced to 300 lbs. When 2-place folding seat (Item 402) is installed and occupied, capacity reduced to (+252) - See Item 403 for cabin rack. Fuel capacity 202 gallons usable (four tanks in wings, two 76 gallon tanks at +126 and two 25 gallon tanks at +155) - See NOTE 1 for System Fuel & Oil. oil capacity 17 gallons (8-1/2 gallon tank in each nacelle at Included propeller feathering oil, 9-1/2 1bs. each tank. See NOTE 1 for System Fuel & Oil. Anti-Icer fluid capacity: 3 gallons (20 lbs.) (+97) Control surface Down 25 degrees movements Elevator trim tab Up 20 degrees Down 14 degrees Blevator Up 35 degrees Down 25 degrees Aileron trim tab Up 20 degrees Down 20 degrees Aileron Up 37.5 degrees Down 20 degrees Rudder trim tab Right 30 degrees Left 30 degrees Right 25 degrees Left 25 degrees Serial Nos. eligible AA-1 thru AA-13 and AA-16, AA-17 and AA-18 manufactured prior to 10/1/47. Approval expired as of that date. Reguired equipment Items, '301, 302, 303, 304, 404 and 006 109, 201, Specifications Pertinent to All Models Certification basis Type Certificate No. 770, expired. (Although certificated on basis CAR 4a, Transport Category design complies with CAR ub except for non- compliance with CAR 4b. 2141.) Export eligibility Eligible for export to all countries subject to the provisions of MOP 2-4. Propellers and Propeller Accessories (Except De-Icing Equipment) Hamilton Standard hyd. full feathering blades 6597A-21 or -22. biameter 8" 3-1/8 maximum, g• 1-1/8" minimum. For inter- changeable blade models see Prop. Spec. No. 736 (NOTE 6). degrees, at Station 42. High 86 degreesiacard 'Avoid continuous operation between 1850 and 176 1bs. each (+30) (b) Governor, Hamilton Standard 4G8 P3OM 7 1bs. each (+38) (c) Feathering pump, Hamilton Standard 66094-1 0I 59664-11 (both modified by Beech) 11 1bs. each (+103) Rev. 1 3 770 Engine and Engine Accessories - Fuel and Oil Systems 101- Two 7"x9l oil radiators with air intake system 20 1bs. each (+80) 102- Two wobble fuel pumps: 4 1bs. each (+86) (a) United Aircraft 0-550-BE; or (b) United Aircraft U-550-BO; or (c) Romec Pump Co. RAD-1563-1; or (d) Army Type D-11 and Two engine-driven fuel pumps: 3 1bs. each (+61) (e) Army Type G6; OI (E) AN-4100-1; (g) Romec RD-3890; or (h) Pesco 2P-R400-BRD; or (i) Pesco 2P-R400-BRB; or (3) Pesco 2P-R400-BR; or (k) Chandler Evans 9141; or (1) Chandler Evans 9105; or (m) Chandler Hill H2E3; or (n) Thompson TFD-400-1; oI (0) Thompson TPD-400; or (P) Thompson TFD-900-1 103. Two carburetor air heaters (weight and arm are for one set of heater muffs) 9 1bs. each (*59) 104- Two oil radiator by-pass valves - S80 1 1b. each (+79) 105- Exhaust collector gas analyzer - Cambridge No. 10555-1 10 1bs. each (+77) 10б.- Two vacuum pumps. All of the following pumps are satisfactory for installation using up to 3 air-driven instruments. 5 1bs. each (+65) (a) Army Type B-12; or (b) Eclipse Pioneer 683-3; or (c) Eclipse Pioneer 683-4; or (a) Eclipse Pioneer 549-5; or (e) Pesco 3P-207-JA; OI (E) Pesco 3P-207-J; or (g) Aro Equipment 207-JA; or (h) Aro Eguipment A-505-DD (satisfactory for installations using up to 5 air-driven instru- ments) : or (i) Romec RD-3880 107. Starters - Eclipse E-80 or Army Type J-1 20 lbs. each (+67) 108. Carburetor air filters 2 1bs. each (+73) 109- Engine compartment pressure fire extinguisher and system (including detector system) with two walter Kidde 5 lb. CO2 57 1bs. 1 1b. each (+79 11) 110- Two oil dilution system 111- 47 gallon auxiliary fuel tank in nose compartment. When this item is installed, the combined weight of fuel and baggage shall not exceed 600 1bs. (+28) 45 1bs. (+38) 112- Engine cooling air outlet bartles. Installation in accordance with Continental Motors Drawing No. 516935 1 1b. (+50) 770 4 Rev. 1 Landing Gear 201. 11.00-12 main wheels -- Goodyear L12HBM-wheel assembly No. 530884; brake assembly No. 630886; 11.00-12 8-ply tires and tubes 95 1bs. each 202. 14.50 tail wheel (Hayes or Goodrich D-3-180M) with 6-ply S.C. tire and tube 14 1bs. 203- Hand operated parking brakes 3 1bs. Electrical Equipment 301- Two generators - Eclipse Type 1298-1-75 amp 23 1bs. each 1 302. Two batteries - 24 volt (17 amp hr. min.) 49 1bs. each ( 303. Wing flap motor 5 1bs. (a) Dumore Type KL-5227; or (b) Dumore Type KBL-5367; or (c) Lamb Electric Type 39V; or (d) Black and Decker or Lamb Blectric Type CS No. IS 13820 304- Landing gear motor - Electric Specialty Type HCA3, modified, or Leland Electric Co. 10559 14 1bs. 305. Two landing lights (Grimes G-3001) 7 1bs. each ( Interior 401. Equipment Chemical toilet. "phis room not to be Placard required on lavatory door: occupied during take-off and landing." When this item is installed, rear baggage is reduced to 300 1b. (+243) • 7 lbs. 402- 2-place folding seat in bulkhead No. 9. When this item is installed, rear baggage allowance must be reduced to 200 1bs. (+252). 33 1bs. 403- Pass. cabin baggage rack and tiedown provision installation (maximum baggage allowance 400 1bs.) 6 1bs. 404- Windshield wiper - Marquette with 10 in. blades 11 1bs. 405. Control system lock 1 1b. 406- CAA Approved Airplane Flight Manual (original nomenclature "CAA Approved Airplane Operating Manual") and pertinent rerisions applicable to the particular serial No. (The manual may be carried as part of, or bound with the operator's Approved Operations Manual", but must remain in the airplane and must retain its identity as an individual manual.) 407. Retractable entry step per "installation Procedure and Drawing 62149 and 62150m for kit installation by the Reed Co., Municipal Airport, 3200 Devey Street, Santa Monica, CA Flite Step 9.5 1bs. Pover Unit 5.5 1bs. De-Icing Equipment (Propellers, Wing, and Windshield) 501. Surface de-icer - Goodrich Type 2. Rev. 1 5 770 Two winq boots (removable) 14 lhs. each (+109) Two stabilizer boots (removable) 5 1bs. each (+350) De-icer installation (fixed (+117) Propeller anti-icer 3 gallon fluid tank, pump and lines (+ö5) Two slinger rings - Hamilton Standard 54884C or 54751D or Beech Co. 69206 1 It. each (+35) 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 or original certifi- cation and at all times thereafter (except in the case of air carrier operators having an approved weight control systen). The certificated weight empty and corresponding C.G. location must include the system fuel and oil: Fuel 24 lb. at (+131) (not included in "Fuel Capacity"). Oil 43 1b. at (+70) (includes propeller feathering oil of 9.5 lbs. each tank) . NOTE 2. The following placards must be displayed: (a) Instrument panel in full view of the pilots: "This airplane must be operated in compliance with the operating limitations specified in CAA Approved Airplane Operating Manual. ¿All intentional acrobatic maneuvers prohibited." "Avoid continuous operation between 1,850 and 2,000 rpm" (Tachometer must be marked accordingly). (b) Lavatory door: 'This room not to be occupied during take-off and landing." ** END ** ``` ## ADs (9, in force first) - [AD 75-27-09 R2](https://openairdocs.org/ad/75-27-09-R2): Wing Structure · Textron 18A, 18D, 18S (Army C-45C) and 27 more. Effective Aug 21, 1980 - [AD 77-19-07](https://openairdocs.org/ad/77-19-07): Control Column Assembly · Textron 18A, 18D, 18S (Army C-45C) and 27 more. Effective Sep 29, 1977 - [AD 47-33-06](https://openairdocs.org/ad/47-33-06): Stabilizer Spar Replacement · Textron D18C, D18C-T and D18S - [AD 47-33-07](https://openairdocs.org/ad/47-33-07): Alternate Static Source · Textron D18C, D18C-T and D18S - [AD 47-34-02](https://openairdocs.org/ad/47-34-02): Tail Cone Drain Holes · Textron D18C, D18C-T and D18S - [AD 47-51-10](https://openairdocs.org/ad/47-51-10): Birdproof Windshield · Hawker Beechcraft D18C-T - [AD 48-34-01](https://openairdocs.org/ad/48-34-01): Stabilizer Attachment Fittings · Textron Army AT-11, C18S, D18C and 2 more - [AD 49-29-02](https://openairdocs.org/ad/49-29-02): Rudder Spring Bushings · Textron D18C, D18C-T and D18S - [AD 53-26-01](https://openairdocs.org/ad/53-26-01): Ignition Switch · Briggs & Stratton Ignition Switches, Army AT-11, C18S and 3 more ## STCs approved under this data sheet (3) - [STC SA02930NY](https://openairdocs.org/stc/SA02930NY): Installation of Insight Instrument Corporation Graphic Engine Monitor (GEM 610C) models G3, G2, and G1 and 1200C model G4 as primary Cylinder Head Temperature (CHT), Exhaust Gas Temperature (EGT), and Turbine Inlet Temperature (TIT) Instruments. Insight Instrument Corporation - [STC SA1315WE](https://openairdocs.org/stc/SA1315WE): Installation of Mixture Monitor (exhaust gas temperature probe, gage and selector) in accordance with Delta Products Part Lists A-192 and A-193, or in accordance with Tri-Star Corporation Mixture Monitor Installation Instructions dated December 9, 1981, or later FAA approved revision and/or Drawing List MM-127 dated November 15, 1981, or later FAA approved revision in aircraft models listed in Master Eligibility List P-80-A-6 revised March 29, 1968, copy attached, or later FAA approved revision.. Universal Corporation - [STC SA1512WE](https://openairdocs.org/stc/SA1512WE): Installation of exhaust gas temperature monitoring systems Model EGT-1.. K S Avionics Inc --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.