# TCDS A52NM: Seeker Aviation Australia Pty Ltd - Type: Type certificate data sheet - Status: Current - Holder: Seeker Aviation Australia Pty Ltd - Revision: 5 - Revised: July 8, 2021 - Product: Aircraft, Small Airplane - Certification basis: Part 21, Part 23, Part 36 - Data sheet PDF: https://openairdocs.org/files/sha256/5c/8e/5c8eed98597946e1556f3d401ec235a44e374001abd30cacd49889b3e984e320 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/EF3D4D13814A3B298625870C0061BFD8.0001 - Page: https://openairdocs.org/tcds/A52NM ## Models (1) As the data sheet lists them. - SB7L-360A ## 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 4 Rev. No. 5 3 5 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A52NM Revision 5 Seeker Aviation SB7L-360A July 8, 2021 TYPE CERTIFICATE DATA SHEET NO. A52NM This data sheet which is part of Type Certificate No. A52NM 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 Seeker Aviation Australia Pty Ltd Don Adams drive, Hervey Bay Airport PO BOX 7618 Urangan, QLD 4655 Australia Type Certificate Holder Record: Seabird Aviation Australia Pty Ltd. changed the TC holder name to Seeker Aviation Australia Pty Ltd. on July 10, 2018. I. SB7L-360A 'Seeker' (Primary Category) Approved April 17, 1997 Engine Textron Lycoming O-360-B2C (one engine) Type Certificate: E-286, Approved October 21, 1992 Fuel 80/87 minimum grade aviation gasoline Engine Limits 2500 r.p.m. for all operations (160 h.p.) Propeller and Seabird Aviation Propeller Limits Model: Bishton 177 Type Certificate: P10BO Approved July 19, 1996 Diameter: not over 69.7", not under 69.5" No further reduction permitted. Static r.p.m. at permissible throttle setting: not over 2300, not under 2200. No additional tolerance permitted. Airspeed Limits (CAS) Maneuvering 121 mph (105 knots) Maximum structural cruising 121 mph (105 knots) Never exceed 153 mph (133 knots) Flaps extended 109 mph (97 knots) Center of Gravity Forward: 88.6" aft of datum at all weights (C.G). Range Aft: 93.9" aft of datum at 1764 lbs. or less 93.0" aft of datum at 1977 lbs., linear variation between 1764 lbs. and 1977 lbs. Empty Weight C.G. Range None Maximum Weights Takeoff 1977 lbs. (899 kg.) (see NOTE 5) A52NM Page 2 of 4 Landing 1977 lbs. (899 kg.) Datum 80.4" forward of the wing leading edge at butt line 83.5" Leveling Means Plumb bob from drilled bolt in cockpit overhead bow to center mark on forward undercarriage bay cross member. Minimum Crew One Number of Seats Two Pilot Seat Arm Forward 50.6" aft of datum Aft 56.9" aft of datum Passenger Seat Arm Forward 50.6" aft of datum Aft 64.8" aft of datum Maximum Baggage 100 lbs. at 82.3" aft of datum Fuel Capacity 2 x 24.3 US gals. 45.4 US gals. usable (22.7 US gals. each tank) 3.2 US gals. unusable (1.6 US gals. each tank) Fuel weight in one tank Fuel arm aft of datum 22 lbs. 87.6” 33 lbs. 89.2” 44 lbs. 90.8” 55 lbs. 91.5” 66 lbs. 91.9” 77 lbs. 92.0” 88 lbs. 91.3” 99 lbs. 90.6” 110 lbs. 90.7” 121 lbs. 90.7” 132 lbs. 90.8” See Note 1. Oil Capacity Total Capacity 8 US quarts (6 US quarts useable) Oil arm 110.4" aft of datum See Note 1 for data on system oil. Maximum Operation Altitude 12,500 ft above mean sea level Control Surface Movements Aileron Up 4.4" ± 0.2" at trailing edge Down 2.9" ± 0.2" at trailing edge Elevator Up 6.3" + 0, -0.2" at trailing edge Down 3.3" ± 0.2" at trailing edge Elevator fixed tabs Trailing edge of tabs 1.6" to 2" below plane of elevator upper surface Rudder L & R 6.7" ± 0.2" at trailing edge Control Surface Move. (cont.) Wing flaps retracted 0° ± 1° 3 A52NM first notch 20° ± 1° full 40° ± 1° Manufacturer's Serial Numbers 070010 to 070014 (see NOTE 5 for restriction for US TC) Import Requirements A United States airworthiness certificate may be issued on the basis of an Australian Export Certificate of Airworthiness signed by a representative of the Civil Aviation Safety Authority containing the following statement: 'The aircraft covered by this certificate has been examined, tested and found to comply with the Master Drawing List SBR 06/96 at issue 1 or later FAA approved revisions approved under US Type Certificate No. A52NM and to be in a condition for safe operation.' The U.S. airworthiness certification basis for this aircraft type certificated under FAR § 21.29 and exported by the country of manufacture is FAR § 21.184 (b). 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 Certification Basis For the Model SB7L-360A (Primary Category) airplane, issuance of a U.S. Type Certificate is based on compliance with the following applicable regulations and amendments: FAR 21.17(f), FAR 21.29, and FAR 23, dated December 18, 1964, with Amendments 1 through 34 "Airworthiness Standards: for Normal Category Airplanes"; and FAR 36 through amendment 36-21 effective December 25, 1995. Noise Control Act of 1972. TC A52NM issued on April 17, 1997. Date of application for the Type Certificate (Primary Category): February 21, 1995; amended on June 24, 1996. Production Basis None 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 approved (for FAA) Flight Manual, document SBR 03/96, or later approved version, must be carried. NOTE 1 A current weight and balance report including a list of equipment included in the 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 the corresponding center of gravity location must include full oil and unusable fuel (19.2 pounds at 89.7 inches). NOTE 2 All required placards are specified in the FAA Approved Flight Manual and must be displayed in the airplane in the appropriate locations. NOTE 3 Mandatory retirement lives, required inspections, and inspection intervals of components are contained in the Airworthiness Limitations Section of the Instructions for Continued Airworthiness. Revisions to the Airworthiness A52NM Page 4 of 4 Limitations Section must be approved by the Australian Civil Aviation Safety Authority on behalf of the FAA. NOTE 4 Instructions for Continued Airworthiness, which contain the Seabird Seeker SB7L-360A Maintenance Manual and the Airworthiness Limitations Section, must be completed and acceptable to the Administrator prior to delivery of the first aircraft under the U.S. Type Certificate. NOTE 5 Increased maximum take-off weight (MTOW) modification to maximum 2034 lbs. (925 kg) and increased fuel capacity per CASA TCDS VA502 Revision 1, dated January 17, 2006, Note 7 b) is not allowed on this US type certificate at this time. ...END.... ``` ## ADs None name its models. ## STCs approved under this data sheet (1) - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications 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.