# TCDS A28SO: Day Gene C. - Type: Type certificate data sheet - Status: Current - Holder: Day Gene C. - Revision: 2 - Revised: July 31, 2015 - Product: Aircraft, Large Airplane - Certification basis: Part 21, Part 91 - Data sheet PDF: https://openairdocs.org/files/sha256/9c/f7/9cf7344170ab3f8c3a0f3f81c68993717a2060684ee45106bfcd0573e2cbcd90 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/78540577993C8A2986257E9A0072479A.0001 - Page: https://openairdocs.org/tcds/A28SO ## Models (1) As the data sheet lists them. - R4D-8 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 Rev. No. 2 1 2 Reformatted 6/94. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A28SO Revision 2 GENE C. DAY R4D-8 July 31, 2015 TYPE CERTIFICATE DATA SHEET NO. A28SO This data sheet which is part of Type Certificate No. A28SO, prescribes conditions and limitations under which the product for which the retype certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Gene C. Day Lot 194, 7535 W. Tennessee Tallahassee, Florida 32304 I. - Model R4D-8 (McDonnell Douglas) (Restricted Category), Approved February 3, 1984 Engines 2 Wright Aeronautical 982C9HE2 Fuel Aviation Gasoline: Grade 100/130 Engine Limits HP RPM MP ALT Take-off 2 minutes 1475 2800 54.5 S.L. Take-off 2 minutes 1475 2800 54.0 1700' Max. Continuous 1275 2500 46.5 S.L. Max. Continuous 1275 2500 45.5 3500' (Straight line manifold pressure variation with altitudes shown) Propellers 2 Hamilton Standard 43D51 hubs with 6915-7 blades. Diameter: 10' 11" max., 10'8.5" min. allowable for repairs. Pitch settings at 54" station low pitch stop + 13°, high pitch stop +88° Airspeed Limits Vno (Normal Operating) 233 mph (202 knots) CAS Vne (Never Exceed) 273 mph (237 knots) CAS Vp (Maneuvering) 144 mph (125 knots) CAS Vfe (Flaps Down ¼ to Full) 133 mph (115 knots) CAS Vfe (Flaps Down 0 to ¼) 146 mph (127 knots) CAS Vlo (Landing Gear Operation) 166 mph (144 knots) CAS Vle (Landing Gear Extension) 166 mph (144 knots) CAS C. G. Range Landing Gear Extended: (+244.6) to (+282.3) Landing Gear Retracted: (+240.4) to (+280.8) (Moment change due to retracting gear is -29,000 in.lbs.) Maximum Weights Landing: 29,325 lbs. Takeoff 29,325 lb.s Minimum Crew 2 (Pilot and Co-Pilot) (+31) Fuel Capacity Installed Total 1626 Gallons Usable 1596 Gallons 2 Fwd Ctr Tanks 404 gallons 396 gallons (*240.5) 2 Aft Ctr tanks 400 gallons 382 gallons (*275.9) 2 Outer Wing tanks 822 gallons 818 gallons (*272.1) See NOTE 1(d) for fuel loading and usage. A28SO Page 2 Oil Capacity 55 ½ gallons (1 tank in each nacelle at 27 ¾ gallons each) (*184.5) Other Operating Limitations Military Flight Handbook AN 01-40NK-1 dated September 1, 1953, revised October 15, 1953, and Gene C. Day Airplane Flight Manual Supplement dated February 3, 1984, and revised August 1, 1985. Control Surface Movements Aileron Up 20° ± ½° Down 14° ± ½° Aileron Trim Tab Up 12° ± ½° Down 12° ± ½° Elevator Up 20° ± ½° Down 20° ± ½° Neutral Elevator Spring Tab Down 10° ± ½° Up 18° ± ½° Up 5 ± ½° Elevator Trim Tab Up 25° + 1-0 Down 6° ± ½° Rudder Left 15° ± ½° Right 15° ± ½° Rudder Geared Tab Right 6° ± ½° Left 6° ± ½° Rudder Trim Tab Left 12° ± ½° Right 12° ± ½° Wing Flaps Down 45° ± 2° Serial Numbers Eligible 43378 (USN Serial No. 17119) Only Certification Basis FAR 21 as amended through Amendment 21-56 effective February 8, 1982. Type Certificate No. A28SO issued February 3, 1984, for the special purpose of aerial survey and carriage of cargo. Date of application for Type Certificate: December 1, 1983. Production Basis None; no aircraft may be produced under this approval. Equipment The basic required equipment as prescribed in the applicable airworthiness and operational regulations must be installed in the aircraft for certification. NOTE 1. (a) Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in the aircraft at the time of original certification adn at all times thereafter. (b) System oil, which must be included in the aircraft empty weight, is that amount required to fill both systems and the tanks up to the tank outlets to the engine, when the airplane is in the level altitude. System oil is not included in tank capacity shown on this data sheet. (c) Unusable fuel is the difference between tank capacity and usable fuel shown on this data sheet and must be included in the airplane empty weight or accounted for in the airplane weight and balance report. (d) Fuel must be loaded in the following order: (1) Forward center wing tanks (2) Aft center wing tanks and (3) Outer wing tanks. Fuel must be used in the reverse order of loading except that forward center wing tanks must be used for takeoff, climb and landing. NOTE 2. The following placards are required: (a) On the instrument panel in full view of the pilot: (1) "This airplane is not approved for flight into icing conditions." (2) "Avoid continuous engine operation below 1800 rpm." (3) "AUTOMATIC PROPELLER FEATHERING SYSTEMS ARE NOT INSTALLED." (4) "This airplane must be operated as a restricted category airplane in compliance with FAR 91.39 and the operating limitations stated in the form of placards, markings, and manuals." A28SO Page 3 (b) Adjacent to the fuel filler opening of each tank: "FUEL AVGAS 100/130" (c) At oir near the oil filler openings: "OIL" NOTE 3. On July 29, 2015 a search of all FAA files and records was conducted and no type design records were found. ...END... ``` ## ADs None name its models. --- 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.