# TCDS A8PC: Fuji Heavy Industries Ltd. - Type: Type certificate data sheet - Status: Current - Holder: Fuji Heavy Industries Ltd. - Revision: 3 - Revised: March 7, 2022 - Product: Aircraft, Small Airplane - Certification basis: Part 23, Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/b5/50/b5500034fe34f60862e0d0db3895724dcb20f4ddf03f8f8ecf105e57780143ec - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/ED9C8AFBD88BC6F5862587FF0056F575.0001 - Page: https://openairdocs.org/tcds/A8PC ## Models (2) As the data sheet lists them. - 710 - 700 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A8PC This data sheet which is part of type certificate No. A8PC prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Fuji Heavy Industries, Ltd. 2-7, Nishi-Shinjuku 1-chome Shinjuku-ku, Tokyo, Japan I - Model 700 (Normal Category), approved September 30, 1977 Engine Two Lycoming T10-540-R2AD Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations, 2500 r.p.m. (340 hp.) 44.0 in. Hg MP up to 16,800 ft. altitude in standard atmosphere. Above 16,800 ft., the following maximum MP applies for maximum r.p.m.: Altitude Max. Allowable (ft.) MP. (in.Hg) 16,800 44.0 17,000 43.6 18,000 41.8 19,000 40.1 20,000 38.5 21,000 36.9 22,000 35.4 23,000 33.9 24,000 32.6 25,000 31.4 Propeller and Two Hartzell HC-E3YR-2ATF/FC8468-5R 3-blade full feathering propeller limits Pitch setting at 30 in. station: Low 14.8° + 0.1° High 84° + 0.5° (feathered) Diameter: 81 inches to 79 inches Page No. 1 2 3 4 5 6 Rev. No. 3 2 2 2 3 2 A8PC Revision 3 FUJI HEAVY INDUSTRIES 700 710 March 7, 2022 A8PC 2 Airspeed limits KTS (CAS) MPH (CAS) Vne (Never exceed) 243 280 Sea level to 18,000 ft. M = 0.51 above 18,000 ft. Vno (Max. structural cruising) 208 240 Sea level to 18,000 ft. M = 0.44 above 18,000 ft. Va (Maneuvering) Vfe (Max. flap extended) 161 185 Takeoff 156 180 Approach and landing 130 150 Vlo (Landing gear operating) Retraction 139 160 Extension 156 180 Vle (Landing gear extended) 156 180 Vmc (Minimum control) 76 87 C.G. range (landing 19.95% MAC (+ 184.8) to 28% MAC (+ 189.5) at 6,790 lb. gear extended) 19.75% MAC (+ 184.6) to 28% MAC (+ 189.5) at 6,750 lb. 12.50% MAC (+ 180.3) to 28% MAC (+ 189.5) at 5,300 lb. or less Straight line variation between points given. Moment change due to retracting landing gear: M = 3425 in.-lb. 7 , 0 00 C . G . E n v elop e ( L an din g G ear E x ten d ed ) 6 , 79 0 lb . ( r am p ) L B. 6 , 0 0 0 6 , 6 00 lb . ( land in g ) 6 , 7 50 lb . ( tak eo ff) 5 30 0 lb . 5 , 00 0 Empty weight C.G. range None 1 80 1 8 5 1 90 In . ( A f t o f D atum ) Leveling means Across and along floor seat tracks. (Use bubble scale.) Maximum weight Ramp 6,790 lb. Takeoff 6,750 lb. Landing 6,600 lb. No. of seats Maximum 6 (Pilot at + 157.8) See JCAB Approved Airplane Flight Manual for loading instructions. Maximum baggage 700 lb. total (300 lb. at +82.7 and 400 lb. at +303.1) Fuel capacity 210 U.S. gal. total (2 wing tanks at 105 gal. each) 208 U.S. gal. usable at +199.7 See Note 1 for weight of unusable fuel. 3 A8PC Oil capacity 24 qt. (12 qt. in each engine at +133.9) See Note 1 for weight of undrainable oil. Maximum operating 25,000 ft. altitude Control surface movements Wing flaps Maximum Down 35° Main surfaces (Measured normal to hinge line except rudder parallel to WP) Aileron Up 22.5° Down 17.5° Elevator Up 19° Down 15° Rudder Right 25° Left 20° Trim tabs (Measured normal to hinge line) Aileron Up 16° (Aileron in neutral) Down 16° (Aileron in neutral) Elevator Up 10° (Elevator full up) Down 28.5° (Elevator full down) Rudder Left 36° (Rudder full right) Right 20° (Rudder full left) Detail rigging information is contained in Section VII of Fuji 700 Maintenance Manual, FSD-E1864. Serial Nos. eligible The Government of Japan Civil Aviation Bureau Certificate of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for U.S. airworthiness certification is made. II - Model 710 (Normal Category), approved April 1, 1980 Engine Two Lycoming TIGO-541-D1B Fuel 100/130 minimum grade aviation gasoline or 100 L L Engine limits For all operations, 3,200 r.p.m. (450 hp.) 48.4 in. Hg MP up to 18,800 ft. altitude in standard atmosphere. Above 18,800 ft., the following maximum MP applies for maximum r.p.m.: Altitude Max. Allowable (ft.) MP. (in.Hg) 18,800 48.4 19,000 48.0 20,000 46.0 21,000 44.5 22,000 43.2 23,000 41.4 24,000 39.6 25,000 38.3 Propeller and Two Hartzell HC-C3YN-2LDUF/FJC9684-3R 3-blade full feathering propeller limits Pitch setting at 30 in. station: Low 19.0° + 0.1° High 86.1° + 0.5° (feathered) Diameter: 93 inches No cutoff for repairs permitted. A8PC 4 Airspeed limits KTS (CAS) MPH (CAS) Vne (Never exceed) 258 297 Sea level to 17,000 ft. M = 0.54 above 17,000 ft. Vno (Max. structural cruising) 208 240 Sea level to 17,000 ft. M = 0.44 above 17,000 ft. Va (Maneuvering) Vfe (Max. flap extended) 176 202 Takeoff 156 180 Approach and landing 143 165 Vlo (Landing gear operating) 156 180 Vle (Landing gear extended) 156 180 Vmc (Minimum control) 81 93 C.G. range (landing 22.25% MAC (+ 186.1) to 28% MAC (+ 189.5) at 8,360 lb. gear extended) 22.00% MAC (+ 186.0) to 28% MAC (+ 189.5) at 8,300 lb. 12.50% MAC (+ 180.3) to 28% MAC (+ 189.5) at 6,000 lb. or less Straight line variation between points given. Moment change due to retracting landing gear: M = 4,855 in.-lb. 8 , 3 6 0 lb . ( r am p ) 8 , 0 0 0 7 , 0 0 0 L B. 6 , 0 0 0 Empty weight C.G. range None Maximum weight Ramp 8,360 lb. Takeoff 8,300 lb. Landing 8,300 lb. 1 8 0 1 8 5 1 9 0 In . ( A f t o f D a tu m ) No. of seats Maximum 6 (Pilot at + 157.8) See JCAB Approved Airplane Flight Manual for loading instructions. Maximum baggage 700 lb. total (300 lb. at +82.7 and 400 lb. at +303.1) Fuel capacity 282 U.S. gal. total (2 wing tanks, 141 gal. each) 280 U.S. gal. usable at +199.0 See Note 1 for weight of unusable fuel. Oil capacity 38 qt. (19 qt. in each engine at +137.8) See Note 1 for weight of undrainable oil. C . G . E nv e lo p e ( L an d in g G e a r E x t en d ed ) 8 , 3 0 0 lb . ( ta k eo f f & lan d in g ) 6 , 0 0 0 lb . 5 A8PC Maximum operating altitude 25,000 ft. Control surface movements Wing flaps Maximum Down 35° Main surfaces (Measured normal to hinge line except rudder parallel to WP) Aileron Up 22.5° Down 17.5° Elevator Up 19° Down 15° Rudder Right 17.5° Left 22.5° Trim tabs (Measured normal to hinge line) Aileron Up 16° (Aileron in neutral) Down 16° (Aileron in neutral) Elevator Up 5.5° (Elevator full up) Down 27.5° (Elevator full down) Rudder Left 27° (Rudder full right) Right 24° (Rudder full left) Detail rigging information is contained in Section VII of Fuji 710 Maintenance Manual, FSD-E1958. Serial Nos. eligible The Government of Japan Civil Aviation Bureau Certificate of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for U.S. airworthiness certification is made. DATA PERTINENT TO ALL MODELS Datum Sta. 0 is 121.26 in. ahead of baggage compt. side of fwd pressure bulkhead. Leveling means Across and along floor seat tracks. (Use bubble scale) Certification basis FAR 21.29, FAR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-14 inclusive and Special Conditions No. 23-78-PC-1 issued by FAA Headquarters, Washington, D.C., on August 12, 1977, and as amended on March 17, 1980, to include the Fuji Model 710 airplane. Compliance has also been shown with FAR 36 noise requirements. Satisfactory finding under the Noise Control Act of 1972 completed February 17, 1977. Negative Environmental Declaration Statement prepared February 4, 1977. Date of Application for Type Certificate July 29, 1974. Type Certificate A8PC issued September 30, 1977 for the Model 700 and amended on April 1, 1980 to include the Model 710. Import requirements A U.S. Standard Certificate of Airworthiness may be issued on the basis of a Japanese Certificate of Airworthiness for Export signed by an authorized representative of the Japan Civil Aviation Bureau containing the following statement: "The airplane covered by this certificate has been examined, tested, and found to conform to the type design approved under U.S. Type Certificate A8PC and to be in a condition for safe operation." Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Service information Information essential for the proper maintenance of the airplane is contained in Fuji Maintenance Manual: FSD-E1864 for Model 700 FSD-E1958 for Model 710 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. Appendix C to the JCAB Approved Airplane Flight Manual identifies the required and optional equipment approved by the JCAB for each airplane. The Master Equipment List, Fuji Report FSD-E1955, identifies all required and optional equipment for the Models 700 and 710 airplane. A copy of this document is retained at the FAA, Pacific-Asia Region, Engineering and Manufacturing District Office. A8PC 6 In addition, the following items of equipment are required: 1. Japan Civil Aviation Bureau Approved Airplane Flight Manual. 2. In accordance with FAR 45.11 and FAR 45.13, Aircraft Identification Plate, Fuji P/N F-0689-1. 3. Horn-landing gear/stall warning indicator, Safe Flight Instrument Corp. P/N 284. NOTE 1. (a) Current weight and balance report including list of equipment included in the certificated empty weight must be in each aircraft at the time of original airworthiness certification and at all times thereafter. The weight and balance computations are included as Appendix B to the JCAB Approved Airplane Flight Manual. (b) The certificated empty weight and corresponding center of gravity location must include undrainable oil and unusable fuel as follows: Undrainable oil 4.74 lb. (2.53 qt. at +140.2) (700) 6.17 lb. (3.29 qt. at +137.8) (710) Unusable fuel 12.0 lb. (2 gal. at +204.7)(700/710) NOTE 2. All placards, including instrument markings, required in the limitation section of the JCAB Approved Airplane Flight Manual must be installed in the appropriate locations on the aircraft. Each individual aircraft must be identified with a placard which specifies approved types of operation; e.g., VFR or IFR as limited by the equipment installed. No landing is permitted when the cabin is pressurized. Operation into known or forecast icing conditions is prohibited. NOTE 3. An airframe service life has been established: 10,000 flight hours (700) 14,690 flight hours (710) In addition, the following retirement lives of structural components have been established for the Model 710: Forward pressure bulkhead plenum assembly 13,460 hr. Aft pressure bulkhead center beam bolts 11,550 hr. Right-hand side windshield glass 11,550 hr. NOTE 4. Engine tachometer of Model 700 shall be calibrated annually to avoid inadvertent operation above 2500 r.p.m. .....END..... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Fuji 700](https://openairdocs.org/model/fuji-700): 0 aircraft (registry code 3730105) ## STCs approved under this data sheet (4) - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation - [STC SA5159NM](https://openairdocs.org/stc/SA5159NM): Installation of chip detector system.. Northwest Aircraft Inc - [STC SA01435DE](https://openairdocs.org/stc/SA01435DE) (historical): Installation of engines, modified with a Firewall Forward Technologies.. 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