TCDS A49NM

A9WE Page 1 of 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A49NM This data sheet, which is a part of type certificate A49NM, 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 Jetcruzer International, LLC 37350 Sky Canyon Drive Murrieta, California 92563 Advanced Aerodynamics & Structures, Inc. 10703 Vanowen Street North Hollywood, California Transferred to Jetcruzer International, LLC TC A49NM on February 8, 2024 1. Model Jetcruzer 450 (Normal Category), Approved June 14, 1994 Engine Pratt & Whitney Canada PT6A-27 Fuel Jet A Fuel used must contain anti-icing fuel additive in compliance with MIL-I-27686 Engine limits For all operations, 2200 RPM (599 SHP) Propeller and Propeller Limits Hartzell Constant Speed, Model HC-B3TN-3UL Blade, Model LT10173N-21R Pitch Limits (at 30” station) Low Pitch 19.0° ± 0.1º Feather 82.1° ± 0.5° Reverse -13.0° ± 0.5° Diameter: 80 3/8” maximum, 79 3/8” minimum, no further reduction permitted. Governor: Woodward 8210-003 Spinner: Hartzell C-3065-3 Limitations: None Page No. 1 2 3 4 5 Rev. No. 1 A49NM Jetcruzer 450 February 8, 2024 Revision 1 A9WE Page 2 of 5 Airspeed Limits Max. operating speed (VMO) 155 KTS CAS Maneuvering (Normal 4300 lbs) (Va) 132 KTS CAS C. G. Range Normal Category Forward: 254.0 inches aft of datum at 4300 lbs. 253.0 inches aft of datum at 4200 lbs. Aft: 256.5 inches aft of datum at 4300 lbs. (See Figure 1) Empty Weight C.G. Range None Datum 92.0 inches forward of nose jack pad attachment on fuselage bottom fwd. of nose wheel well. Leveling Means Seat tracks, behind pilot station Maximum Weight 4300 lbs. Minimum Crew One Pilot Maximum Occupants Five (includes crew) Number of Seats 2 Occupants at 190.8” 1 Occupant at 221.3” 2 Occupants at 251.8” Maximum Baggage None Fuel Capacity Capacity Gal. Usable Gal. Arm 68.5 60.5 +286.0 See Note 1 for data on unusable fuel Oil Capacity Capacity Qts. Usable Qts. Arm 11 7.8 +295.6 Control Surface Movements Airler 27.0°/23.0° Up 17.0°/14.0° Down Rudder (Each) 19.0°/16.0° Left 19.0°/16.0° Right Elevator 10.0°/8.0° Up 42.0°/40.5° Down Elevator Tab 33.0°/31.0° Up 17.0°/16.0° Down (All surfaces must be within 2° left to right) A9WE Page 3 of 5 Nose Wheel Movement Steering ± 15° Castoring ±30° Serial Numbers Eligible 2 & Up SPECIFICATIONS PERTINENT TO ALL MODELS Certification Basis The certification basis for the AASI Jetcruzer 450 is: 14 CFR part 23, effective February 1, 1965, as amended by Amendments 23-1 through 23-42; effective February 2, 1991; § 23.905(e) of Amendment 23-43 for protection of the pusher propeller from ice impingement: § 23.905(f) of Amendment 23-43 for pusher propeller disc conspicuity: § 23.905(g) of Amendment 23-43 for protection of the pusher propeller from exhaust gas impingement: § 23.925(b) of Amendment 23-43 for pusher propeller ground clearance: § 23.1203(a) of Amendment 23-43 for engine fire detection system: Part 34, effective September 10, 1990; Part 36, Through Amendment 36-20, effective September 11, 1992; and the following special conditions and exemption (special conditions 1 and 6, as proposed in Notice No. 23-ACE-61, are issued as final special conditions 1 and 2): Special Condition 1. Evaluation of Composite Structure, and Special Condition 2, Protection of Electrical and Electronic Systems from High Intensity Radiated Fields. Exemption No. 5594, grants an exemption from a portion of § 23.903(e)(2) of the FAR which requires, in pertinent part, that means be provided for stopping the rotation of any turbine engine. For the metal structures, conducting of damage tolerance analysis provides an equivalent level of safety as envisioned in the regulations and thus meets the requirements of § 23.572(a)(1). Compliance with § 23.1091(c)(2). Water Ingestion was found by equivalent level of safety by prohibiting takeoff or landing with standing water on the runway. Appropriate testing must be conducted prior to the removal of the limitation. Note: As a result of AASI decision to seek initial certification without advanced electronic system, Special Condition 2 is not considered necessary for initial type certification. For the following certification with advanced electronic system installed, compliance with Special Condition 2 is required. Production Basis: None. Prior to original certification of each aircraft, an FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, and a check of the flight characteristics. Equipment The basic equipment required as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. This equipment must include the following: * A current Airplane Flight Manual * 120 lbs. movable ballast A9WE Page 4 of 5 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 total oil capacity and unusable fuel as noted below. * Unusable fuel (8.0 gal.) 53.6 lbs. at 286.0” NOTE 2 The following placard must be displayed in front of and in clear view of the pilot. “This airplane must be operated as a Normal Category airplane in compliance with operating limitations stated in Airplane Flight Manual”. See Approved Airplane Flight Manual for additional placards. “All placards required in the Approved Airplane Flight Manual must be installed in the appropriate location”. NOTE 3 Aircraft Service Life is limited to 500 flight hours. When the damage tolerance analysis AASI Report Nos. ER-5141 and ER-5142 of the aircraft are submitted and approved, the service life will then be readjusted based upon the determined threshold of each Principal Structural Element together with their inspection intervals. Fuel Quality Measuring Systems Indicator P/N 81-240-1 and Transmitter P/N 75- 169-3, which are not qualified to TSO C-55, are service life limited to 100 hrs. T.B.O. The HC-B3TN-3UL/LT10173N-21R propeller is required to have repetitive blade inspection for erosion and/or corrosion at intervals not to exceed 24 months or 600 hours of operations, whichever occurs first. See Hartzell S/B 181, dated 3/12/93 or later revision for the inspection procedures. NOTE 4 Aircraft is not eligible for installation of avionics equipment (HF, VHF, Nav/Com radios, transponder, etc.) without complete Electromagnetic and Radio Frequency Interference (EMI/RFI) ground and flight test due to know interference with previously approved equipment (Fuel Quantity Gauging System). NOTE 5 Each aircraft produced must be flight tested specifically to show compliance to § 23.207(c) of 14 CFR Part 23, using at least a swiveling pilot boom and sensitive airspeed indicator. Figure 1 A9WE Page 5 of 5 WEIGHT AND CENTER OF GRAVITY LIMITS --END--