# TCDS A00070CE: 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 - Registered aircraft: 1, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/4b/9f/4b9f1c6e2168da889174e49b9bd90554a325d8fc6bb7efc641182f45a8ad41e2 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/FB338CD57E3C71D88625870C00618BA5.0001 - Page: https://openairdocs.org/tcds/A00070CE ## Models (2) As the data sheet lists them. - SB7L-360A - SB7L-360A2 ## 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 5 6 7 8 Rev. No. 5 0 5 3 0 5 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00070CE Revision 5 Seeker Aviation SB7L-360A SB7L-360A2 July 8, 2021 TYPE CERTIFICATE DATA SHEET NO. A00070CE This data sheet which is part of Type Certificate No. A00070CE 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 9, 2018. I. SB7L-360A (Seeker), Normal Category, Approved June 7, 2016 Engine Textron Lycoming O-360-B2C (one engine) FAA Type Certificate: E-286 Fuel 80/87 minimum grade aviation gasoline. Unleaded automotive gasoline. Engine Limits 2700 rpm (No time limit) Oil As specified in the latest revision of Textron Lycoming Service Instruction No.1014. Propeller and Seabird Aviation Propeller Limits Model: Bishton BB177 Two bladed Fixed Pitch wooden, pusher FAA Type Certificate: P10BO Diameter: 69.7 in. (1770 mm). Pitch: 53.2 in. (1350 mm) at 29.5 in. (750 mm) radius. Static rpm at full throttle: Maximum: 2300 rpm. Minimum: 2200 rpm. Airspeed Limits (KIAS) (KCAS) Never exceed (VNE) Maneuvering (VA) Max structural cruise (VNO) Max flaps extended (VFE) 134 133 107 105 107 105 95 93 A00070CE Page 2 of 8 Center of Gravity Forward: 88.6" (2251mm) aft of datum at all weights (C.G). Range Aft: 93.9" (2384 mm) aft of datum at 1764 lbs. (800kg) or less 93.0" (2362mm) aft of datum at 2039 lbs. (925 kg) Variation is liner between 1764 lbs. and 2039 lbs. Empty Weight C.G. Range None Datum 80.4" (2043mm) forward of the wing leading edge at butt line 83.5" (2122 mm) Leveling Means Plumb bob from drilled bolt in cockpit overhead bow to center mark on forward undercarriage bay cross member. Maximum Weights Takeoff 2039 lbs. (925 kg.) Landing 2039 lbs. (925 kg.) Minimum Crew One pilot Number of Seats Two. Pilot Seat Arms seat forward 50.6" aft of datum seat aft 56.9" aft of datum Passenger Seat Arms seat forward 50.6" aft of datum seat aft 64.8" aft of datum Maximum Baggage 100 lbs. (45 kg) at 82.3" (2090mm ) aft of datum Fuel Capacity Total 48.6 gallon (184 liters) (2 x 24.3 gal tanks at 91 mean fuel inch). Usable 48.1 gallon (182 liters). Refer to flight manual for fuel distribution weight and balance data. See Note 1. Oil Capacity Total Capacity 8 US quarts (7.6 liters) (6 US quarts useable) Oil arm 110.4" aft of datum See Note 1 for data on system oil. Maximum Operation Altitude 15,000 feet AMSL 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 Wing flaps retracted 0° ± 1° first notch 20° ± 1° full 40° ± 1° Manufacturer's Serial Numbers 070009 and SA01100, SA01101 and subsequent. 3 A00070CE A CASA Certificate of Airworthiness for Export must be submitted for each individual airplane. See “Import Requirements.” 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 CASA approved Seabird Master Drawing List SBR 07/14 issue 3 or later revisions, approved under US Type Certificate No. A00070CE 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 § 21.183 (c). Per 21.50(b), Instructions for Continued Airworthiness (ICA) complying with FAR 23.1529, must be furnished before delivery of the first airplane or issuance of a US standard certificate of airworthiness, whichever occurs later. (Note 4) 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 The regulations (unless otherwise stated) are Title 14 of the Code of Federal Regulations (14CFR): 1) FAR 21.29, 21.183(c) and FAR 23 dated February 1, 1965, as amended through Amendment 23-34 effective 2/17/87 with the exception of: 14 CFR part 23 sections 23.331, 23.445 and 23.1163 at Amendment 42; 14 CFR part 23 sections 23.993, 23.1103, 23.1147, 23.1193, 23.1322, 23.1385, 23.1387, 23.1389, 23.1391, 23.1393 and 23.1395 at Amendment 43; 14 CFR part 23 sections 23.251, 23.773, 23.1525, 23.1549 and 23.1557 at Amendment 45; 14 CFR part 23 sections 23.335, 23.371 and 23.572 at Amendment 48; 14 CFR part 23 sections 23.867, 23.1307, 23.1321, 23.1323, 23.1326, 23.1351, 23.1353, 23.1383 and 23.1401 at Amendment 49; 14 CFR part 23 sections 23.71, 23.145, 23.161, 23.201, 23.203, 23.1521, 23.1543, 23.1583, 23.1585, 23.1587 and 23.1589 at Amendment 50; 14 CFR part 23 sections 23.955, 23.1041, 23.1043, 23.1047, 23.1091, 23.1093, 23.1107, 23.1141, 23.1143, 23.1181, 23.1183, 23.1203 and 23.1337 at Amendment 51; 14 CFR part 23 sections 23.1305 at Amendment 52; A00070CE Page 4 of 8 14 CFR part 23 sections 23.1308 at Amendment 57; 14 CFR part 23 sections 23,777, 23.853, 231301, 23.1303, 23.1309, 23.1310, 23.1311, 23.1331, 23.1431 and 23.1559 at Amendment 62. 2) 14 CFR Part 36, effective December 1969, including Amendments 36-1 through 36-30. 3) Equivalent Level of Safety per 21.21(b)(1): a) TC00381CE-A-S-1 dated May 16, 2016, Pitot Heat Indication System, § 23.1326 (b)(1) at amendment 23-49; b) TC00381CE-A-P-3 dated May 16, 2016, Fuel Quantity Indication, § 23.1337(b)(1) at amendment 23-51. 4) No Exemptions 5) No Special Conditions 6) The airplane is not approved for ditching 7) The airplane is not approved for flight into known or forecasted icing. 8) CASA issued CASA Amended Type Certificate No. VA502 on January 24, 1994 for this model and revised it on 5 May 2016 as identified on Revision 7 of CASA TCDS VA502. Date of application for original FAA type certificate: January 10, 2011 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 12/16 Issue date June 7, 2016 or later approved version, must be carried. Service Information Each of the documents listed below must state that it is approved by the Civil Aviation Safety Agency (CASA): • Aircraft flight manuals, and • Airworthiness Limitations Section of the Service Manual. The FAA accepts such documents and considers them FAA-approved for type design data only unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or •The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to CASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Available documents for the SB7L-360A model: FAA approved Aircraft Flight Manual Document SBR 12/16 Issue date June 7, 2016, or later approved version, must be carried. (See Note 2) Instructions for Continued Airworthiness (ICA) {AMM} Document SBR 10/16 Issue 1, dated June 7, 2016, or later accepted versions. Chapter 4 Airworthiness Limitations are dated June 7, 2016 (See Note 3 and Note 4) 5 A00070CE II. SB7L-360A2 (Seeker), Normal Category, Approved June 7, 2016 Engine Textron Lycoming I0-390-A1B6 Type Certificate: E00006NY Fuel Avgas 100LL (Blue) Avgas 100 (Green) Engine Limits 2700 rpm (No time limit). Oil As specified in the latest revision of Textron Lycoming Service Instruction No.1014. Propeller and Seabird Aviation Propeller Limits Model: Bishton BB177-70-55 Two bladed Fixed Pitch wooden, pusher FAA Type Certificate: P10BO Diameter: 69.7 in. (1770 mm). Pitch: 55.1 in. (1400 mm) at 29.5 in. (750 mm) radius. Static rpm at full throttle: Maximum: 2450 rpm. Minimum: 2350 rpm. Airspeed Limits (KIAS) (KCAS) Never exceed (VNE) Maneuvering (VA) Max structural cruise (VNO) Max flaps extended (VFE) 134 133 107 105 107 105 95 93 Center of Gravity Forward: 89.5" (2274mm) aft of datum at all weights (C.G). Range Aft: 94.8" (2409 mm) aft of datum at all weights. Empty Weight C.G. Range None Datum 80.4" (2043mm) forward of the wing leading edge at butt line 83.5" (2122 mm) Leveling Means Plumb bob from drilled bolt in cockpit overhead bow to center mark on forward undercarriage bay cross member. Maximum Weights Takeoff 2147 lbs. (974 kg.) Landing 2039 lbs. (925 kg.) Minimum Crew One pilot Number of Seats Two. Pilot Seat Arms seat forward 50.6" aft of datum seat aft 56.9" aft of datum Passenger Seat Arms seat forward 50.6" aft of datum seat aft 64.8" aft of datum Maximum Baggage 100 lbs. (45 kg) at 82.3" (2090mm ) aft of datum A00070CE Page 6 of 8 Fuel Capacity Total 48.6 gallon (184 liters) (2 x 24.3 gal tanks at 91 mean fuel inch). Usable 48.1 gallon (182 liters). Refer to flight manual for fuel distribution weight and balance data. See Note 1. Oil Capacity Total Capacity 8 US quarts (7.6 liters) (6 US quarts useable) Oil arm 110.4" aft of datum See Note 1 for data on system oil. Maximum Operation Altitude 15,000 feet AMSL 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 Wing flaps retracted 0° ± 1° first notch 20° ± 1° full 40° ± 1° Manufacturer's Serial Numbers SA02100 and subsequent. A CASA Certificate of Airworthiness for Export must be submitted for each individual airplane. See “Import Requirements.” 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 CASA approved Seabird Master Drawing List SBR 07/14 issue 3 or later revisions, approved under US Type Certificate No. A00070CE 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 § 21.183 (c). Per 21.50(b), Instructions for Continued Airworthiness (ICA) complying with FAR 23.1529, must be furnished before delivery of the first airplane or issuance of a US standard certificate of airworthiness, whichever occurs later. (Note 4) 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 7 A00070CE Certification Basis The regulations (unless otherwise stated) are Title 14 of the Code of Federal Regulations (14CFR): 1) FAR 21.29, 21.183(c) and FAR 23 dated February 1, 1965, as amended through Amendment 23-34 effective 2/17/87 with the exception of: 14 CFR part 23 sections 23.331, 23.445 and 23.1163 at Amendment 42; 14 CFR part 23 sections 23.993, 23.1103, 23.1147, 23.1193, 23.1322, 23.1385, 23.1387, 23.1389, 23.1391, 23.1393 and 23.1395 at Amendment 43; 14 CFR part 23 sections 23.251, 23.773, 23.1525, 23.1549 and 23.1557 at Amendment 45; 14 CFR part 23 sections 23.335, 23.371 and 23.572 at Amendment 48; 14 CFR part 23 sections 23.867, 23.1307, 23.1321, 23.1323, 23.1326, 23.1351, 23.1353, 23.1383 and 23.1401 at Amendment 49; 14 CFR part 23 sections 23.71, 23.145, 23.161, 23.201, 23.203, 23.1521, 23.1543, 23.1583, 23.1585, 23.1587 and 23.1589 at Amendment 50; 14 CFR part 23 sections 23.955, 23.1041, 23.1043, 23.1047, 23.1091, 23.1093, 23.1107, 23.1141, 23.1143, 23.1181, 23.1183, 23.1203 and 23.1337 at Amendment 51; 14 CFR part 23 sections 23.1305 at Amendment 52; 14 CFR part 23 sections 23.1308 at Amendment 57; 14 CFR part 23 sections 23,777, 23.853, 231301, 23.1303, 23.1309, 23.1310, 23.1311, 23.1331, 23.1431 and 23.1559 at Amendment 62. 2) 14 CFR Part 36, effective December 1969, including Amendments 36-1 through 36-30. 3) Equivalent Level of Safety per 21.21(b)(1): c) TC00381CE-A-S-1 dated May 16, 2016, Pitot Heat Indication System, § 23.1326 (b)(1) at amendment 23-49; d) TC00381CE-A-P-3 dated May 16, 2016, Fuel Quantity Indication, § 23.1337(b)(1) at amendment 23-51. 4) No Exemptions 5) No Special Conditions 6) The airplane is not approved for ditching 7) The airplane is not approved for flight into known or forecasted icing. 8) CASA issued CASA Amended Type Certificate No. VA502 on September 24, 2013 for this model and revised it on 5 May 2016 as identified on Revision 7 of CASA TCDS VA502. Date of application for FAA for the SB7L-360A2 model: March 10, 2014 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 A00070CE Page 8 of 8 certification. In addition the approved (for FAA) Flight Manual, document SBR 13/16 or later approved version, must be carried. Service Information Each of the documents listed below must state that it is approved by the Civil Aviation Safety Agency (CASA): • Aircraft flight manuals, and • Airworthiness Limitations Section of the Service Manual. The FAA accepts such documents and considers them FAA-approved for type design data only unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or •The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to CASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Available documents for the SB7L-360A2 model: FAA approved Aircraft Flight Manual Document SBR 13/16 Issue date June 7, 2016 or later approved version, must be carried. (See Note 2) Instructions for Continued Airworthiness (ICA) {AMM} Document SBR 11/16 Issue 1, dated June 7, 2016, or later accepted versions. Chapter 4 Airworthiness Limitations are dated June 7, 2016. (See Note 3 and Note 4) NOTES 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 (17.5 pounds at 106.9 inches). NOTE 2 Airplane operation must be in accordance with the CASA-approved Aircraft Flight Manual listed above. All placards listed in Section 2 of the FAA approved AFM must be displayed in the appropriate locations. The US versions of the SB7L-360A and SB7L-360A2 AFM limitations may not be changed without CASA and direct FAA approval. NOTE 3 Mandatory retirement lives, required inspections, and inspection intervals of components are contained in the Airworthiness Limitations Section (Chapter 4) of the Airplane Maintenance Manual dated June 7, 2016 are part of (SB7L-360A model Doc: SBR10/16 Issue 1 or later versions) and (SB7L -360A2 model Doc: SBR 11/16 Issue 1 or later versions). The US versions of the SB7L-360A and -360A2 limitations may not be changed without CASA and direct FAA approval. NOTE 4 August 12, 2016, the FAA accepted the complete set of ICAs which includes the previously approved ALS section of the ICA, chapter 4, dated June 7, 2016 for both models. ...END.... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Seabird Avn Australia PTY SB7L-360A2](https://openairdocs.org/model/seabird-avn-australia-pty-sb7l-360a2): 1 aircraft (registry code 8690003) ## STCs approved under this data sheet (2) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [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.