TCDS A00018AT

Page No. 1 2 3 4 5 6 7 8 9 10 Rev No. 11 8 11 10 8 11 10 10 10 11 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00018AT Revision 11 Honda Aircraft Company LLC HA-420 December 15, 2025 TYPE CERTIFICATE DATA SHEET NO. A00018AT This data sheet, which is part of Type Certificate No. A00018AT, 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: Honda Aircraft Company LLC 6430 Ballinger Road Greensboro, North Carolina 27410 I – Model HA-420 (6/7/8PCLM, Normal Category) Approved December 8, 2015 Engines: Two (2) GE Honda Aero Engines HF120-H1A turbofan engines Type Certificate E00085EN Fuel: Jet A, Jet A-1, JP-8, PRC No. 3 Jet Fuel, Russian TS-1, and Ukrainian TS-1 For approved and prohibited fuel additives, refer to the FAA Approved Airplane Flight Manual (see NOTE 7) Oil: For approved oils, refer to the FAA Approved Airplane Flight Manual (see NOTE 7) A00018AT Page 2 of 10 Engine Limits: Thrust Setting N1 Fan RPM ITT (1) N2 Turbine RPM Takeoff 100.0% (19,055 RPM) 860°C (2) 100.9% (49,200 RPM) Max Continuous 100.0% (19,055 RPM) 860°C (2) 100.9% (49,200 RPM) The HA-420 is approved for 10 Minutes OEI (see NOTE 5) (1) ITT values are displayed limits and not actual temperature values. (2) Maximum transient for 2 minutes is 885°C HF120-H1A power management de-rated minimum static thrust ratings at sea level and 77°F/25°C with no installation losses: Takeoff 2037 lbs thrust Max Continuous 1922 lbs thrust Airspeed Limits: VMO................................. 270 KIAS MMO ................................ 0.72 Mach VA ................................... 200 KIAS VMCA Flaps UP ................... 105 KIAS Flaps TO/APPR ........ 100 KIAS VMCL Flaps LDG ................ 95 KIAS VFE/FO Flaps TO/APPR ........ 200 KIAS Flaps LDG ................ 160 KIAS VLE/LO ............................. 200 KIAS VTIRE ............................... 165 knots (Max Tire Ground Speed) A00018AT Page 3 of 10 Maximum Weights: Configuration Max Ramp Max Takeoff Max Landing Max Zero Fuel 42000012 thru 42000125 10,680 lbs 10,600 lbs 9,860 lbs 8,800 lbs 42000012 thru 42000125 with SB-420-55-001 installed 10,780 lbs 10,700 lbs 9,960 lbs 8,900 lbs 42000126 thru 42000206 42000126 thru 42000206 with SB-420-32-013 and SB-420-42-017 installed 42000012 thru 42000125 with SB‑420‑55‑001, SB‑420‑32‑013, SB‑420‑31‑004, SB-420-42-023, and SB‑420‑11‑002 installed 10,980 lbs 10,900 lbs 10,160 lbs 9,100 lbs 42000126 thru 42000206 with SB-420-42-016 installed 42000126 thru 42000206 with SB-420-32-013, SB-420-42-018, and SB-420-11-001 installed 42000207 thru 42000234 42000235 and up 11,180 lbs 11,100 lbs 10,360 lbs 9,300 lbs Max Baggage Loading: Configuration Fwd Compartment Aft Compartment Luggage Valet 42000012 thru 42000125 100 lbs (F-Sta 54.5) 400 lbs (F-Sta 328.4) 50 lbs (F-Sta 162.6) 42000012 thru 42000125 with SB-420-52-002 installed 200 lbs (F-Sta 54.5) 400 lbs (F-Sta 328.4) 50 lbs (F-Sta 162.6) 42000012 thru 42000125 with SB-420-55-001 installed 42000126 thru 42000234 42000235 and up 200 lbs (F-Sta 54.5) 550 lbs (F-Sta 328.4) 50 lbs (F-Sta 162.6) For Aft Compartment loading distribution, refer to the latest FAA Approved Airplane Flight Manual Section 6 (see NOTE 7). Datum: (F-Sta 0.00) 69.0 inches forward of the nose jacking position Mean Aerodynamic Chord: 59.72 inches (M.A.C. leading edge is 232.2 inches aft of datum) Leveling Means: Left hand floorboard inside main entry way Empty Weight C.G. Range: None A00018AT Page 4 of 10 CG Range: For approved CG range, refer to the FAA Approved Airplane Flight Manual (see NOTE 7) Fuel Capacity: For 42000012 thru 42000125 430.7 US gal TOTAL (F-Sta 263.5) 423.9 US gal Usable 6.8 US gal Unusable For 42000126 thru 42000234 446.73 US gal TOTAL (F-Sta 264.08) 439.37 US gal Usable 7.36 US gal Unusable For 42000235 and up 479.09 US gal TOTAL (F-Sta 265.66) 471.62 US gal Usable 7.59 US gal Unusable Oil Tank Capacity: Each engine tank: MAX Oil Level (FULL line): 4.99 quarts (F-Sta 320.0) 2.64 quarts Usable, 2.35 quarts Unusable Control Surface Movements: Maximum Deflection Control Surface Trailing Edge Up or Left Trailing Edge Down or Right Elevator 20.5° ±0.5° 6.5° ±0.5° Rudder 34.5° ±0.5° 34.5° ±0.5° Aileron 21.1° +0.5°,-1.5° 19.9° +0.5°,-1.5° Aileron Trim 15° ±1.0° 15° ±1.0° Rudder Trim 25° ±1.0° 25° ±1.0° Elevator Trim 10° ±1.0° 15° ±1.0° Flaps N/A UP: 0.0° ±0.25° TO/APPR: 15.7° ±0.8° LDG: 35° ±1.3° Ground Spoilers 50° +3.0°,-2.0° N/A Manufacturer Serial No. Eligible: 42000012 and up PERTINENT DATA Minimum Crew: One (1) pilot (left seat) -OR- Two (2) pilots Number of Seats: A00018AT Page 5 of 10 For S/N 42000012 thru 42000125 7 Max (Includes pilot(s) and passengers). Refer to the latest FAA Approved Airplane Flight Manual Section 6 (see NOTE 7) for seat configurations and moment arms. For S/N 42000126 and up 8 Max (Includes pilot(s) and passengers). Refer to the latest FAA Approved Airplane Flight Manual Section 6 (see NOTE 7) for seat configurations and moment arms. Maximum Operating Altitude: 43,000 ft MSL Maximum Takeoff Field Elevation: 10,000 ft MSL Temperature Operating Limitation: 55°C -40°C (Starting) Maneuver Limits: Maneuvers are limited to any maneuver incident to normal flying, stalls (except whip stalls) and steep turns in which the angle of bank is not more than 60 degrees. Acrobatic maneuvers, including spins, are prohibited. Other Operating Limitations: The aircraft must be operated in accordance with the FAA approved Airplane Flight Manual (see NOTE 7). Type Certificate Application: October 11, 2006 Type Certificate Issuance: Type Certificate A00018AT Issued December 8, 2015 Certification Basis: 14 CFR Part 23, Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Airplanes, effective February 1, 1965, as amended by Amendments 23-1, dated July 29, 1965, through Amendment 23-62, dated December 2, 2011 14 CFR Part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, effective September 10, 1990, as amended by Amendments 34-1, dated July 31, 1995 through Amendment 34-5, dated December 31, 2012 14 CFR Part 36, Noise Standards: Aircraft Type and Airworthiness Certification • Serial numbers 42000012 thru 42000125 are compliant with Stage 4 noise requirements, as amended by Amendments 36-1 through Amendment 36-29, dated March 11, 2013. • Serial numbers 42000012 thru 42000125 with SB-420-55-001 installed and 42000126 thru 42000206 are compliant with Stage 4 noise requirements, as amended by A00018AT Page 6 of 10 Amendments 36-1 through Amendment 36-30, dated March 4, 2014. • Serial numbers 42000126 thru 42000206 with SB-420-42-013 or SB-420-42-016 installed and 42000207 and up are compliant with Stage 4 noise requirements, as amended by Amendments 36-1 through Amendment 36-31, dated November 03, 2017. • Serial numbers 42000012 thru 42000125 with SB-420-42-023 are compliant with Stage 4 noise requirements, as amended by Amendments 36-1 through Amendment 36-32, dated December 9, 2022. Optional Design Regulations: None Exemptions from 14 CFR Part 23 in accordance with 14 CFR Part 11: Exemption 11123 dated December 16, 2014, 23.181(b), Dynamic Stability Compliance with 23.181(b) during takeoff and landing. Equivalent Safety Findings (ELOS) according to the provisions of 14 CFR part 21.21(b)(1) for the following subjects: ELOS No., date and Subject Regulation modified by ELOS ACE-15-08, dated June 5, 2015: Use of 1-g Stall Speeds in lieu of Minimum Speed in the Stall as a Basis for Determining Compliance §1.1, §1.2, §23.49, §23.51, §23.65, §23.67, §23.69, §23.73, §23.143, §23.145, §23.147, §23.149, §23.157, §23.161, §23.175, §23.177, §23.201, §23.203, §23.207, §23.233, §23.729, §23.735, §23.1001, §23.1323, §23.1325, §23.1545, and §23.1587 ACE-15-09, dated March 26, 2015: Electronic Display of Engine Instruments N1, N2, ITT, Oil Pressure, Oil Temperature, Fuel Flow, and Fuel Quantity on a Garmin G3000 Integrated Flight Deck §23.1305, §23.1337, §23.1549, §23.1553 ACE-15-10, dated March 25, 2015: Storage Battery Design and Installation §23.1353(h) A00018AT Page 7 of 10 ACE-15-11, dated September 14, 2015: Airspeed Indicator (ASI) Flap Markings §23.1545(b)(4) ACE-15-15, dated September 1, 2015: Amendment 23-62 Corrections §23.45, §23.51, §23.63, §23.67, §23.73, §23.77, §23.161, §23.181, §23.221, §23.251, §23.253, §23.571, §23.1195, §23.1197, §23.1199, §23.1201, §23.1545, §23.1583 AT15774AT-A-F-1, dated July 20, 2018: Steep Approach Operations §23.45, §23.67, §23.75, §23.77 AT16447AT-A-A-1, dated October 12, 2022: Material Design Values §23.613 The following Special Conditions (SC) in accordance with 14 CFR Part 11: Special Condition No., Date and Subject Regulation modified by Special Condition Special Condition No. 23-263-SC, dated March 25, 2015, Dynamic Test Requirements for Single Place Side- Facing Seats §23.562, §23.785 Special Condition No. 23-264-SC, dated March 25, 2015, Electronic Engine Control System §23.1309 Special Condition No. 23-265-SC, dated June 9, 2015, Fire Extinguishing Note: This special condition supersedes the ELOS finding of ELOS Memo ACE- 15-15 §23.1195, §23.1197, §23.1199, §23.1201 Special Condition No. 23-269-SC, dated Sept 14, 2015, Lithium-Ion Battery Installation §23.1353 Special Condition No. 23-270-SC, dated August 3, 2015: High Altitude Operations §23.831 A00018AT Page 8 of 10 Special Condition No. 23-271-SC, dated October 26, 2015, Cruise Speed Control §23.1329 Special Condition No. 23-287-SC, dated March 7, 2018, Type Certification of Side Facing Belted Lavatory Seat to meet the modified requirements of 14 CFR Parts 23.562, 23.785, 23.791, and 23.1581 for an area bounded by privacy pocket door and a bulkhead (Note: This special condition is applicable to S/N 42000011, 42000126 and up) §23.562, §23.785, §23.791, §23.1581 Compliance has been shown for Day/Night VFR and Day/Night IFR operations. Compliance has been shown for applicable ditching provisions. S/N 42000049 and up, and S/N’s 42000012 through 42000048 incorporating Honda Aircraft Service Bulletin SB-420-42-001, are eligible for flight into known or forecast icing. Per the type design, S/N 42000012 and up meet the Reduced Vertical Separation Minima (RVSM) technical requirements. Each operator must obtain operational approval for flight in RVSM airspace from their cognizant Flight Standards District Office (FSDO). Compliance has been shown for steep approach operations as an optional kit with appropriate manual supplements. Model HA-420 is defined by drawing, HJ1-10000-000, Rev G or later FAA approved revision. ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: The following design details or information must be maintained to ensure that an unsafe design condition is not present: None Production Basis: Production Certificate No. 348CE, dated July 8, 2016 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 items of equipment are required: 1. FAA Approved Airplane Flight Manual (see NOTE 7) A00018AT Page 9 of 10 For single pilot operations, the following equipment must be operative/ available in addition to those items listed above: 1. Autopilot 2. FAA Approved Quick Reference Handbook (see NOTE 7) NOTES: NOTE 1. Weight and Balance: A current weight and balance report, including a list of equipment included in the certificated empty weight, and loading instructions must be provided for each aircraft at the time of original certification. NOTE 2. Placards Airplane operation must be in accordance with the FAA Approved Airplane Flight Manual (see NOTE 7). All placards required by the Flight Manual, the applicable operating rules, and the Certification Basis must be installed in the airplane. NOTE 3. Service Life Limits and required Maintenance/Inspections Inspection time limits and maintenance checks are included in the Airworthiness Limitation and Inspection Manual (HJ1-29000-013). The retirement times of the life limited components in Section 05-60-00 cannot be altered without FAA Engineering approval. NOTE 4. Interior Components Replacement Seats (crew and passenger) must be demonstrated to comply with installation requirements as established by the Certification Basis (including 14 CFR §23.2, 23.561, 23.562 and 23.785) even if they are previously found to be compliant to TSO C127a (or later amended version). The cushion buildup of all seats (crew and passenger) may not be altered without appropriate qualification as established by the Certification Basis (including 14 CFR §23.562). The cabinet that is installed forward of the RH side-facing seat is an integral part of the certified seat and restraint system (applicable for S/N 42000012 and up). The divider forward of the RH belted lavatory seat is an integral part of the certified seat and restraint system (applicable for S/N 42000126 and up). These items may not be structurally altered unless the changes are shown to comply with the requirements of the Certification Basis (including 14 CFR §23.561, 23.562 and 23.785). NOTE 5. Engine Operation A00018AT Page 10 of 10 The Model HA-420 is approved for One Engine Inoperative 10 minutes thrust capability with the GE Honda Aero Engines HF120-H1A engine, per FAA Policy Memo Policy Statement on Approval for 10-Minute Rated Takeoff Thrust/Power during Takeoff with One-Engine Inoperative (OEI) under 14 CFR Part 23 and 14 CFR Part 33 [PS-ANE33-ACE23-2006-1], dated August 30, 2006. NOTE 6. Aircell CTR System The Aircell CTR System is intended to provide internet connection and email services using portable electronic devices (PEDs). Any other intended function of this equipment will require a reexamination of the certification basis. NOTE 7. Applicable Flight Manuals Configuration Airplane Flight Manual Quick Reference Handbook 42000012 thru 42000125 HJ1-29000-003-001 HJ1-29000-007-001 42000012 thru 42000125 with SB-420-55-001 installed HJ1-29001-003-001 HJ1-29001-007-001 42000126 thru 42000206 42000126 thru 42000206 with SB-420-32-013 and SB-420-42-017 installed HJ1-29003-003-001 HJ1-29003-007-001 Serial numbers 42000012 thru 42000125 with SB-420-42-023 installed HJ1-29004-003-001 HJ1-29004-007-001 42000126 thru 42000206 with SB-420-42-016 installed 42000126 thru 42000206 with SB-420-32-013, SB-420-42-018, and SB-420-11-001 installed 42000207 thru 42000234 42000235 and up HJ1-29002-003-001 HJ1-29002-007-001 ---END---