# TCDS A00018AT: Honda Aircraft Company LLC

- Type: Type certificate data sheet
- Status: Current
- Holder: Honda Aircraft Company LLC
- Revision: 11
- Revised: December 15, 2025
- Product: Aircraft, Small Airplane
- Certification basis: Part 23
- Registered aircraft: 240, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/f3/5c/f35cb50018e59544fd9d1fd04a6c905675440ea88b5d51207b6fcdeea2e27faf
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID186416701520251216163246.0001
- Page: https://openairdocs.org/tcds/A00018AT

## Models (1)

As the data sheet lists them.

- HA-420

## 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 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---
```

## ADs (12, in force first)

- [AD 2026-10-02](https://openairdocs.org/ad/2026-10-02): Fuselage Main, Plate/Skin · Honda HA-420. Effective Jul 2, 2026
- [AD 2026-06-71](https://openairdocs.org/ad/2026-06-71): Trailing Edge Flap Actuator · Honda HA-420. Effective May 8, 2026
- [AD 2026-01-01](https://openairdocs.org/ad/2026-01-01): Aileron Control System · Honda HA-420. Effective Feb 17, 2026
- [AD 2023-11-03](https://openairdocs.org/ad/2023-11-03): Windshield/Door Rain/Ice Removal · Honda HA-420. Effective Jun 16, 2023
- [AD 2022-18-03](https://openairdocs.org/ad/2022-18-03): Windshield/Door Rain/Ice Removal · Honda HA-420. Effective Sep 22, 2022
- [AD 2020-04-14](https://openairdocs.org/ad/2020-04-14): Landing Gear · Honda HA-420. Effective Apr 6, 2020
- [AD 2018-21-13](https://openairdocs.org/ad/2018-21-13): Landing Gear · Honda HA-420. Effective Nov 27, 2018
- [AD 2018-15-06](https://openairdocs.org/ad/2018-15-06): Time Limits · Honda HA-420. Effective Aug 13, 2018
- [AD 2022-05-13](https://openairdocs.org/ad/2022-05-13) (historical): Windshield/Door Rain/Ice Removal · Honda HA-420. Effective Apr 18, 2022
- [AD 2021-22-12](https://openairdocs.org/ad/2021-22-12) (historical): Trailing Edge Flap Actuator · Honda HA-420. Effective Nov 19, 2021
- [AD 2018-11-05](https://openairdocs.org/ad/2018-11-05) (historical): Landing Gear · Honda HA-420. Effective May 29, 2018
- [AD 2018-06-10](https://openairdocs.org/ad/2018-06-10) (historical): Landing Gear · Honda HA-420. Effective Apr 13, 2018

## Registered aircraft by registry model (OpenAirDocs)

- [Honda HA-420](https://openairdocs.org/model/honda-ha-420): 240 aircraft (registry codes 4400000, 05632GI, 056297O)
- [Honda R & D Americas HA-420](https://openairdocs.org/model/honda-r-d-americas-ha-420): 0 aircraft (registry code 056154S)

## STCs approved under this data sheet (5)

- [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc.
- [STC SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica
Cellular Module (avCM. Aircraft Systems and Manufacturing Inc.
- [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH
- [STC SA04214NY](https://openairdocs.org/stc/SA04214NY): Installation of the Gogo AVANCE L3 System. Banyan Air Service
- [STC SA01855WI](https://openairdocs.org/stc/SA01855WI): Installation of the Send Solutions Airtext Router in 14 CFR Part 23 Aircraft. 3S Certification LLC

---
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