TCDS A18SO

Page No. 1 2 3 Rev. No. 6 6 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A18SO Revision 6 Piper Aircraft, Inc PA-38-112 March 4, 2022 TYPE CERTIFICATION DATA SHEET A18SO This data sheet which is a part of Type Certificate No. A18SO, 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 Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida 32960 Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC A18SO to Piper Aircraft, Inc on August 7, 2006. I. - Model PA-38-112 (Tomahawk), 2 PCLM (Normal and Utility Category), Approved December 20, 1977. Engine Lycoming O-235-L2C (Slick Magnetos) with carburetor setting 10-5199 or Lycoming O-235-L2A (Bendix Magnetos) with carburetor setting 10-5199 Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2600 r.p.m. (112 hp) Propeller and Propeller Limits Sensenich 72CK-0-56 Static r.p.m. at maximum permissible throttle setting not over 2350 r.p.m., not under 2200 r.p.m. No additional tolerance permitted. Diameter: Not over 72 inches, not under 70 inches. Propeller Spinner Piper P/N 77710 See NOTE 4 for spinner removal. Airspeed Limits (CAS) Never exceed 143 knots Maximum structural cruising 108 knots Maneuvering 101 knots Flaps extended 87 knots A18SO Page 2 of 3 Center of Gravity Range Normal and Utility Category (+72.4) to (+78.5) at 1277 lb. or less (+73.5) to (+78.5) at 1670 lb. Straight line variation between points given. FUSELAGE STATION - INCH LB. 1700 1600 1500 1400 1300 1200 1100 1000 72 73 74 75 76 77 78 79 Empty Weight C. G. Range None Datum 66.25 inches forward of wing leading edge. Leveling Means Top of tailcone behind rear window. Maximum Weight 1670 lb. (Normal and Utility Category) Number of Seats 2 (2 at +85.5) Maximum Baggage 100 lb. (+115.0) Fuel Capacity 32 gallons at (+75.4) (2 wing tanks) See NOTE 1 for data on unusable fuel. Oil Capacity 6 quarts at (+24.4) (4 quarts usable) See NOTE 1 for data on unusable oil. Control Surface Movements Wing Flaps ( 2°) Up 0° Down 34° Ailerons ( 2°) Up 26° Down 14° Rudder ( 1°) Left 29° Right 29° Elevator ( 2°) Up 34° Down 20° Nose Wheel Travel ( 2°) Left 30° Right 30° Serial Numbers Eligible 38-78A0001 through 38-82A0122 (See NOTE 6). Certification Basis Type Certificate Number A18SO, issued December 20, 1977, obtained by the manufacturer under delegation option procedures. Date of application for Type Certificate, June 1, 1976. FAR Part 23, effective February 1, 1965, as amended by Amendment by 23-16, effective February 14, 1975, and FAR 36 including Amendments through 36-7, effective October 1, 1977. Finding of equivalent safety was made for the airspeed indicator (FAR 23.1545(a)). Production Basis Approved for manufacture of spare parts only under Production Certificate No. 206. Page 3 of 3 A18SO Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following document is required: 1. Pilot's Operating Handbook, Piper Report Number 2126, dated Janu ary 20, 1978. NOTE 1. Current weight and balance report, including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center-of-gravity locations must include undrainable system oil (not included in oil capacity) and unusable fuel as noted below: Unusable Fuel & Oil Quantity Fuel 12.0 lb. at (+75.4) Oil 1.90 lb. at (+24.4) NOTE 2. The following placard must be displayed in clear view of the pilot: "EXCEPT AS MAY BE OTHERWISE INDICATED ON A PLACARD, THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE NORMAL CATEGORY. OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THIS CATEGORY OR IN THE UTILITY CATEGORY ARE CONTAINED IN THE PILOT'S OPERATING HANDBOOK. FLAPS UP SPINS ARE APPROVED FOR UTILITY CATEGORY OPERATION. FOR SPIN RECOVERY, USE FULL RUDDER AGAINST THE SPIN FOLLOWED IMMEDIATELY BY FORWARD WHEEL. THIS AIRPLANE IS APPROVED FOR FLIGHT IN DAY/NIGHT VFR/IFR WHEN EQUIPPED IN ACCORDANCE WITH F.A.R. 91. FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED. FLAPS EXTENDED SPINS PROHIBITED." NOTE 3. Refer to Airplane Maintenance Manual 761-660 for Instructions for Continued Airworthiness. Life limited components are identified in Airplane Maintenance Manual 761-660, Chapter 4 Airworthiness Limitations section. NOTE 4. The Model PA-38-112, S/N 38-78A0001 through 38-82A0122 may be operated with the spinner dome removed, or with the spinner dome and rear bulkhead removed. NOTE 5. Inboard flow strips installed per Piper Drawing No. 61927-2, are installed on S/N 38-78A0017, 38-78A0786, 38-78A0812, and 38-78A0815. All S/Ns are eligible for installation of inboard flow strips per Piper Drawing No. 61927-2. Pilot's Operating Handbook, Piper Report Number 2126, Revision 3, is required with this installation. NOTE 6. The following serial numbers are not eligible for airworthiness certification in the United States: 38-78A0344, 38-78A0358, 38-78A0424, 38-78A0439, 38-78A0624, 38-78A0639, 38-78A0734, 38-78A0749, 38-78A0829, 38-78A0844, 38-79A0058, 38-79A0088, 38-79A0156, 38-79A0221, 38-79A0236, 38-79A0271, 38-79A0301, 38-79A0699, 38-79A0713, 38-79A1042, , 38-79A1051, 38-79A1056, 38-79A1061, 38-79A1115, 38-79A1117, 38-79A1122, 38-79A1126, 38-79A1131, 38-79A1134, 38-79A1158, 38-79A1162, 38-79A1165, 38-79A1168, 38-80A0015, 38-80A0019, 38-80A0022, 38-80A0025, 38-80A0035, 38-80A0038 through 38-80A0051, 38-80A0054, 38-80A0056, 38-80A0057, 38-80A0060, 38-80A0063, 38-80A0077, 38-80A0080, 38-80A0083, 38-80A0086, 38-80A0104, 38-80A0113, 38-80A0120, 38-80A0123 through 38-80A0165, 38-80A0169 through 38-80A0198, 38-81A0136 through 38-81A0138, and 38-81A0191 through 38-81A0210. ...END...