# TCDS Q00018LA: AeroVironment Inc. - Type: Type certificate data sheet - Status: Current - Holder: AeroVironment Inc. - Revision: 4 - Revised: July 9, 2015 - Product: Aircraft, Unmanned Aircraft System - Certification basis: Part 21, Part 25, Part 36, Part 91 - Registered aircraft: 2, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/67/8f/678f9d8b42b04336cc756b671ce751fc6e0aef1c9e26c9c68d16fce3f89c0d21 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C165EA6F86BD46B286257E8200635398.0001 - Page: https://openairdocs.org/tcds/Q00018LA ## Models (1) As the data sheet lists them. - PUMA AE ## 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 Rev. No. 4 3 4 4 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION Q00018LA Revision 4 AeroVironment, Inc. PUMA AE July 9, 2015 TYPE CERTIFICATE DATA SHEET No. Q00018LA This data sheet, which is part of Type Certificate No. Q00018LA, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of Title 14 Code of Federal Aviation Regulations (14 CFR). Type Certificate Holder AeroVironment, Inc. 181 W. Huntington Dr. Monrovia, CA 91016 USA I. Model PUMA AE (Restricted Category UAS), Approved July 19, 2013 (See NOTES Section) UAS This is an Unmanned Aircraft System (UAS) that is comprised of the air vehicle and the ground control station (hand controller). Unmanned Aircraft Dimensions Wingspan: 9.2 ft. Length: 4.7 ft. Engine (Propulsive Unit) (1) AeroVironment, Inc., Model 50333 (Electric) FAA Engine Type Certificate: None Propulsive Unit Type: 25 V, Lithium battery powered, direct drive electric motor Motor, Electric Sub-Assembly: Manufacturer: NeuMotor Model: 1910 1.0 HP Peak Power Direct Drive 10.0 oz. Wt. Motor, Controller Sub-Assembly: Manufacturer: Castle Creation Model: Phoenix HV-45 Type: Speed Controller 45 Amps Maximum 1.9 oz. Wt. Motor, Battery: See information listed under Battery section Q00018LA 2 Fuel Not applicable NOTE: The Puma AE is powered by a Lithium rechargeable battery, see information listed under Battery section Engine (Propulsive Unit) Limits Maximum power output: 1.0 HP Maximum RPM: 10,000 RPM Maximum motor temperature: 180 °F NOTE: The motor temperature is managed by the Puma AE system and not displayed to the operator. Maximum motor, controller sub-assembly temperature: 194 °F (90 °C) Minimum voltage, motor battery during pre-flight engine run up after 3 secs at max throttle: 20.0 V Propeller and Propeller Limits (1) AeroVironment, Inc., Model 50330 FAA Propeller Type Certificate: None Propeller Type: 2-blade, hinged (folding), carbon fiber reinforced plastic, fixed pitch, tractor Propeller Sub-Assembly: Manufacturer: Aeronaut Model: CAM 13 x 10 Diameter (Nominal): 13.3 in. Battery Lithium rechargeable battery Manufacturer: AeroVironment, Inc 13.5 Amp hour, 22.2 V (nominal) – P/N 50318; or 21.7 Amp hour, 21.6 V (nominal) – P/N 67881 Note: The battery supplies power for the motor, command and control, and payload modules Airspeed Limits (IAS) VNE (Never Exceed Speed) 58 knots (30 m/s) VNO (Maximum Cruising Structural Speed) 41 knots (21 m/s) VA (Maneuvering Speed) 41 knots (21 m/s) Landing Speed: The landing configuration can be engaged (autoland) at any speed. Center of Gravity (C.G.) Range 12.75 - 13.75 inches aft of datum Empty Weight C.G. Range Not applicable Datum Front of motor case Mean Aerodynamic Chord (MAC) 10.23 inches (259.8 mm) long with leading edge 9.11 inches (231.4 mm) from datum Leveling Means Not Applicable Maximum Weights Ramp 15.5 lbs. Takeoff 15.5 lbs. Landing 15.5 lbs. 3 Q00018LA Empty Weight 8.0 lbs. Note: Empty weight excludes weight of the battery and payload modules Frequencies 1625-1725 MHz, 1755 -1850 MHz Notes: FCC license is required to utilize the above frequencies; Uplink, downlink, and video are on the same frequency Computer Software Motor Controller Interface Board Software: PN 58841 Revision A, Software Version 1.0.6 Avionics CPU, C-Code, Puma AE PN 64321 Revision A, Software Version 52.02.27 Minimum Crew (1) The Puma AE system can be operated by a single operator. Number of Seats (0) Not Applicable Fuel Capacity Not Applicable Oil Capacity Not Applicable Max. Operating Altitude a) For operations in the designated Arctic Area as defined by the FAA Modernization and Reform Act of 2012, Section 332(d)(1): 2000 ft. AGL (610 m). (See Flight Limitations Section below – Item 10.a) b) For all other operations: Limited to line of sight. (See Flight Limitations Section below – Item 10.b) Control Surface Movements Nominal Endurance 13.5 amp hr battery: 120 minutes above 32 °F (0 °C); 60 minutes below 32 °F (0 °C) 21.7 amp hr battery: 200 minutes above 32 °F (0 °C); 100 minutes below 32 °F (0 °C) Flight Limitations 1. Day Visual Flight Rules (VFR) in visual meteorological conditions (VMC) 2. Deleted 3. Flight operations in icing conditions at assigned operational altitudes: PROHIBITED 4. Ambient Outside Air Temperature (OAT) a. Maximum OAT: 120°F/49°C b. Minimum OAT at Altitude: -20°F/-29°C 5. Wind. See Note 5. 6. Flight Operations. See Note 4. 7. For this operation only one Puma AE can be airborne at any given time. 8. Over water operation: PERMITTED 9. Over land operation: PERMITTED Elevator Up 50° Down 24° Flaps Rudder N/A Left 45° N/A Right 45° Q00018LA 4 10. Flight operations permitted: a) In the designated Arctic Area as defined by the FAA Modernization and Reform Act of 2012, Section 332(d)(1) (See Max. Operating Altitude Section above - Item a); or b) In those areas which meet the “remote and/or rural” definition in the Remote Area UAS Operations Safety Case Assessment Puma All Environment Digital Data Link (Puma AE DDL) Rev B. dated 11 Nov 2014. All operations in these areas are limited to line of sight only. (See Max. Operating Altitude Section above – Item b). 11. An authorization for the specific location of operation issued by the Administrator is required and must be available at the control station. AFM number 72373, dated July 16, 2013 or later FAA approved revision, and certificate of airworthiness (C of A) must be available at the control station (reference FAA Memorandum, “Certification of Unmanned Aircraft”, from AAL-7 to ANM-100L, dated June 19, 2013). Additionally, any certificates of authorizations or waivers must be available at the control station. 12. Operation with any inoperative instruments or equipment: PROHIBITED Serial Numbers Approved: Air Vehicle: 1723, 1726, 1728, 835, 836, 837, 838, 847, 502, 504 Hand Controller: 07532, 07528, 06922, 04706, 04446, 04772 Certification Basis Restricted Category Only 14 CFR part 21.25(a) (2) for the special purpose of aerial survey, 14 CFR part 36, amendment 29, Appendix G Production Basis None Hand Controller P/N 64303 UAS Support Equipment: Use of PUMA AE launcher, P/N 68674 is optional. See Notes 15 and 16. NOTES: NOTE 1 A current weight and balance report must be provided for each aircraft at the time of original certification. The maximum aircraft weight with payload and battery is 15.5 lb. NOTE 2 Placards Required: None NOTE 3 This UAS must be maintained in accordance with AV Puma AE Maintenance Operation Manual, 72407_10X, or later FAA accepted revision NOTE 4 UAS shall be operated under 14 CFR part 91, operating requirements, as mitigated. Operations shall be conducted in accordance with a waiver of flight regulations applicable to the operation, including but not limited to 14 CFR § 91.113, issued by the Administrator and specific to the intended operation, including geographical limitations. NOTE 5 Wind Limitations: 25 knots NOTE 6 Personnel Keep Out Zones. Typical exclusion zones apply for Launch and Recovery as described in the AFM. 5 Q00018LA NOTE 7 This Type Certificate Data Sheet (TCDS) is the principal document for Puma AE Operation. For any operational discrepancies among the TCDS, AFM 72373, etc., this TCDS takes precedence. NOTE 8 Restricted category aircraft may not be operated in a foreign country without the express approval of that country. NOTE 9 This aircraft has not been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 of the Convention on International Civil Aviation. This aircraft meets14 CFR § 21.25(a)(2). NOTE 10 Deleted NOTE 11 Operations shall be conducted by properly certificated airmen who have completed training, checking, currency, and recency of experience requirements as approved by the Administrator. NOTE 12 The Flight Standards Board (FSB) report is available on request. Contact the Long Beach AEG (LGB-AEG-NM17). NOTE 13 No aircraft may be manufactured under this approval. NOTE 14 Compliance to §21.25 (a) (2) was shown by following the deviation Memo dated July 5, 2013, in lieu of Order 8110.56 Revision A. NOTE 15 When using optional PUMA AE launcher, P/N 68674, instructions in the “PUMA AE TACTICAL LAUNCHER USER’S GUIDE”, document 70188_13, dated May 2014 or later FAA accepted revision, must be used. NOTE 16 The launcher, when used, must be that listed under UAS Support Equipment of this Type Certificate Data Sheet. --END-- ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Aerovironment PUMA AE](https://openairdocs.org/model/aerovironment-puma-ae): 2 aircraft (registry code 0610024) --- 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.