# TCDS R00001RC: Bell Textron Canada Limited

- Type: Type certificate data sheet
- Status: Current
- Holder: Bell Textron Canada Limited
- Revision: 6
- Revised: February 11, 2022
- Product: Aircraft, Rotorcraft
- Certification basis: Part 27
- Registered aircraft: 13, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/7b/2c/7b2ce9d6d2f1c26d9f7073c3ccaa9812c8f79a581baec16b68327d012c3af691
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D8FFF38735483EC9862587E9004A6206.0001
- Page: https://openairdocs.org/tcds/R00001RC

## Models (1)

As the data sheet lists them.

- 427

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 TYPE CERTIFICATE DATA SHEET NO. R00001RC 
 
This data sheet which is part of type certificate No. R00001RC prescribes conditions and limitations under which the product for 
which type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
Type Certificate Holder Bell Textron Canada Limited 
12800 rue de l’Avenir 
Mirabel, Quebec 
J7J 1R4 Canada 
Type Certificate Holder Record: Bell Helicopter Textron Canada Limited was the previous name of TC holder. 
The company name history is presented below. 
Type Certificate Holder Period 
Bell Helicopter Textron Canada Limited, Mirabel Quebec Prior to 16 December 2019 
Bell Textron Canada Limited, Mirabel Quebec 16 December 2019 to Present 
 
I. Model 427 (Normal Category), Approved January 24, 2000. 
Engine 2 Pratt and Whitney Canada PW207D 
 
Fuel  ASTM-D-1655, Type Jet B, Jet A and Jet A-1; MIL-T-5624 Grade JP-4; MIL-T-5624 Grade JP-5 
and MIL-T-83133 Grade JP-8. 
See Rotorcraft Flight Manual for fuel mixture and fuel temperature limitations. 
For all operations below 5 C (40F) ambient temperature, all fuel used must contain Phillips PFA- 
55MB or MIL-L-27686 anti-icing additive in concentrations of not less than 0.06% or more than 
0.15% by volume. 
Installed Engine Limits 
 Torque 
Lb-ft (%) 
Turbine Temperature 
oC (oF) Gas Generator Speed % (RPM) 
Twin Engine Operation    
Take-Off (5 Min) 481 (68.6) 900 (1652) 99.8 (5790) 
Max. Continuous 481 (68.6) 850 (1562) 97.2 (56400) 
One Engine Inoperative    
30 sec. OEI 569 (81.2) 990 (1814) 104.3 (60500) 
2 min. OEI 569 (81.2) 950 (1742) 102.2 (59300) 
30 min OEI 481 (68.7) 925 (1697) 101.2 (58700) 
Continuous OEI 481 (68.7) 900 (1652) 99.8 (57900) 
 
See Rotorcraft Flight Manual for transient limits 
Output shaft speed limit is 104.5% (6271 RPM) 
Rotor Limits 
Power Off Power On 
Maximum 423 RPM 107% Maximum 411 RPM 104% 
Minimum 356 RPM 90% Minimum 391 RPM 99% 
Transmission Torque Torque Limits % 
Limits 
Both Engines Operation  
Take Off 100 
Maximum Continuous 100 
One Engine Inoperative OEI  
30 Seconds OEI 81.2 
2 Minute OEI 75.6 
Continuous OEI 57.5 
 
Airspeed Limits Basic VNE (never exceed) is 140 KAIS. Decrease VNE for ambient conditions in accordance with the 
R00001RC 
Revision 6 
Bell 
427 
February 11, 2022

Airspeed Limitations placard in the Rotorcraft Flight Manual. 
Autorotation VNE 80 KIAS 
C.G. Range 
(See NOTE 8 and NOTE 10) 
 
 
| 
Page No. 1 2 3 4 5 6 
Rev. No. 6 1 3 6 3 5

Page 2 of 6 R00001RC 
 
 
 1) For approved MGW configuration of 2722 kg (6,000 lbs.) 
a) Internal Loading 
 Longitudinal C.G. limits cm (in.) 
 Forward limit 
561.3 cm (221.0in) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in) at 2087 
 kg (4600 lb.), 548.6 cm (216.0 in) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.), 
 changing linearly to 551.2 cm (217.0 in) at 2722 kg (6000 lb.). 
 Aft Limit 
 576.6 cm (227.0 in) at 1724 kg (3800 lb.), up to 2495 kg (5500 lb.), changing linearly to 
574.0 cm (226.0 in) at 2722 kg (6000 lb.) 
 Lateral C.G Limits 
 Left 2.8 cm (1.1 in) at 1724 kg (3800 lb.), changing linearly up to 5.3 cm (2.1 in) at 1814 
 kg (4000 lb.), changing linearly to 3.6 cm (1.4in) at 2722 kg (6000 lb.) 
 Right 4.6 cm (1.8 in) at 1724 kg (3800 lb.) changing linearly up to7.1 cm (2.8 in) at 1814 
 kg (4000 lb.), changing linearly up to 4.8 cm (1.9 in) at 2722 kg (6000 lb.) 
b) External Loading 
 Longitudinal C.G. Limits cm (in.) 
 Forward Limit 
 561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in) at 
 2087 kg (4600 lb.), 548.6 cm (216.0 in.) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.) 
changing linearly to 550.2 cm (216.6 in.) at 2948 kg (6500 lb.) 
 Aft Limit 
576.6 cm (227.0 in.) at 1724 kg (3800 lb.) up to 2495 kg (5500 lb.), changing linearly to 
 574.0 cm (226.0 in.) at 2948 kg (6500 lb.) 
 Lateral C.G. Limits 
 Left 2.8 cm (1.1 in.) at 1724 kg (3800 lb.) changing linearly up to 5.3 cm (2.1 in.) at 1814 
kg (4000 lb.), changing linearly to 3.6 cm (1.4 in.) at 2722 kg (6000 lb.), changing 
 linearly to 3.3 cm (1.3 in.) at 2498 kg (6500 lb) 
 Right 4.6 cm (1.8 in.) at 1724 kg (3800 lb.) changing linearly up to 7.1 cm (2.8 in.) at 
 1814 kg (4000 lb.), changing linearly 4.8 cm (1.9 in.) at 2722 kg (6000 lb.), changing 
 linearly to 4.3 cm (1.7 in.) at 2948 kg (6500 lb.) 
2) For approved MGW configuration of 2880 kg (6350 lb.) 
a) Internal Loading 
 Longitudinal C.G. Limits cm (in.) 
 Forward Limit 
 561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0in.) at 
2087 kg (4600 lb.), 548.6 cm (216.0 in0.) from 2087 kg (4600 lb.) up to 2495 kg 
 (5500 lb.), changing linearly to 553.0 cm (217.7 in.) at 2880 kg (6350 lb.) 
 Aft Limit 
 576.6 cm (227.0 in.) at 1724 kg (3800 lb.) to 2495 kg (5500 lb.) varying linearly to 574.4 
 cm (226.15 in.) at 2880 kg (6350 lb.) 
 
C.G. Range (Cont’d) 
(See NOTE 8 and NOTE 10) 
  
Internal Loading (Cont’d) 
  Lateral C.G. Limits 
  Left 2.8 cm (1.1 in.) at 1724 kg. (3800 lb.), changing linearly to 5.3 cm (2.1 in.) at 1814 
  kg (4000 lb.), changing linearly to 3.4 cm (1.3 in.) at 2880 kg (6350 lb.)

Page 3 of 6 R00001RC 
 
Right 4.6 cm (1.8 in.) at 1724 kg (3800 lb.) changing linearly to 7.1 cm (2.8 in.) at 1814 
kg (4000 lb.), changing linearly to 4.5 cm (1.8 in.) at 2880 kg (6350 lb.) 
 
b) External Loading 
Longitudinal C.G. Limits cm (in.) 
Forward Limit 
561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in.) at 
2087 kg (4600 lb.), 548.6 cm (216.0 in.) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.), 
changing linearly to 550.2 cm (216.6 in.) at 2948 kg (6500 lb.) 
 
Aft Limit 
576.6 cm (227.0 in.) at 1724 kg (3800 lb.) up to 2495 kg (5500 lb.), changing linearly to 
574.0 cm (226.0 in.) at 2948 kg (6500 lb.) 
 
Lateral C.G. Limits 
 
Left 2.8 cm (1.1 in.) at 1724 kg (3800 lb.), changing linearly to 5.3 cm (2.1 in.) at 1814 kg 
(4000 lb.), changing linearly to 3.3 cm (1.3 in.) at 2948 kg (6500 lb.) 
 
Right 4.6 cm (1.8 in) at 1724 kg (3800 lb.) changing linearly to 7.1 cm (2.8 in.) at 1814 kg 
(4000 lb.), changing linearly to 4.3 cm (1.7 in.) 2948 kg (6500 lb.) 
 
3) For approved MGW configuration of 2971 kg (6550 lb.) 
 
a) Internal Loading 
Longitudinal C.G. Limits cm (in.) 
Forward Limit 
561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in.) at 
2087 kg (4600 lb.), 548.6 cm (216.0 in.) from 2087 kg (4600 lb.) up to 2495 kg 
(5500 lb.), changing linearly to 554.0 cm (218.1 in.) at 2971 kg (6550 lb.) 
 
Aft Limit 
576.6 cm (227.0 in.) at 1724 kg (3800 lb.) to 2495 kg (5500 lb.) changing linearly to 
573.9 cm (225.95 in.) at 2971 kg (6550 lb.) 
 
Lateral C.G. Limits cm (in.) 
 
Left 2.8 cm (1.1 in.) at 1724 kg. (3800 lb.), changing linearly to 5.3 cm (2.1 in.) at 1814 
kg (4000 lb.), changing linearly to 3.3 cm (1.3 in.) at 2971 kg (6550 lb.) 
 
Right 4.6 cm (1.8 in.) at 1724 kg (3800 lb.) changing linearly up to 7.1 cm (2.8 in.) at 
1814 kg (4000 lb.), changing linearly up to 4.3 cm (1.7in.) at 2971 kg (6550 lb.) 
 
b) External Loading 
Longitudinal C.G. Limits cm (in.) 
Forward Limit 
561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in.) at 
2087 kg (4600 lb.), 548.6 cm (216.0 in.) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.), 
changing linearly to 550.2 cm (216.6 in.) at 2971 kg (6550 lb.) 
 
Aft Limit 
576.6 cm (227.0 in.) at 1724 kg (3800 lb.) up to 2495 kg (5500 lb.), changing linearly to 
573.9 cm (225.95 in.) at 2971 kg (6550 lb.) 
 
 
Lateral C.G. Limits 
 
Left 2.8 cm (1.1 in.) at 1724 kg (3800 lb.), changing linearly to 5.3 cm (2.1 in.) at 1814 kg 
(4000 lb.), changing linearly to 3.3 cm (1.3 in.) at 2971 kg (6550 lb.) 
 
Right 4.6 cm (1.8 in) at 1724 kg (3800 lb.) changing linearly up to 7.1 cm (2.8 in.) at 1814 
kg (4000 lb.), changing linearly to 4.3 cm (1.7 in.) at 2971 kg (6550 lb.)

Page 4 of 6 R00001RC 
 
 
Empty Weight CG Range See Maintenance Manual 
 
Datum Model 427 station 0 datum is 203.2 cm (80 in) forward of the nose of the helicopter. 
 
Leveling Means Plumb line from underside of the engine pan through the access panel in the baggage compartment 
roof to an index plate on the floor of the baggage compartment 
 
Maximum Weight 2722 kg (6000 lb.) Internal Loading 
(Mass) 2948 kg (6500 lb.) External Loading 
 
2880 kg (6350 lb.) Internal Loading (see NOTE 8) 
2948 kg (6500 lb.) External Loading 
 
2971 kg (6550 lb.) Internal Loading (see NOTE 10) 
2971 kg (6550 lb.) External loading 
 
Altitude limits Maximum altitude at 2722 kg (6000 lb.) or less is 9000-ft density altitude. 
(See NOTE 8 
and NOTE 10) Maximum altitude for approved MGW configuration of 2880 kg (6,350 lb.) is 10,000-ft pressure 
altitude. 
 
OAT Limits -20°C (-4°F) to 42.2°C (108°F) or 
(See NOTE 11) -20°C (-4°F) to 51.7°C (125°F) 
 
Minimum crew 1 pilot (right seat) 
 
Maximum occupants 8 (includes crew) 
 
Maximum Baggage Maximum allowable baggage compartment weight is 250 pounds (113.4 kilograms) with a 
maximum deck and cargo loading of 86 pounds per square foot (4.2 kilograms per 100 square 
centimeters). Maximum allowable cabin deck loading for cargo is 75 pounds per square foot (3.7 
kilograms per 100 square centimeters). 
 
Fuel capacity 770.3 litres (203.5 US Gal.) usable, 
12.5 litres (3.3 US Gal.) unusable. 
 
Oil capacity Each Engine 5.1 litres (4.5 Imp. Quarts) (5.4 US Quarts); 
Usable oil 1.1 litres (1 Imp. Quart) (1.16 US Quarts) included in capacity 
Undrainable oil 1.6 lbs. 
Transmission: 8.5 litres (7.5 Imp quarts) (8.98 US Quarts) 
Tail Rotor Gearbox: 0.31 litres (0.27 Imp Quarts) (0.33 US Quarts) 
Rotor blade and For rigging information refer to the 427 Maintenance Manual 
Control movement 
 
Serial numbers eligible 56001 and subsequent. Serial numbers 58001 and subsequent are not eligible for FAA Certificate of 
Airworthiness. 
 
Import Requirements To be considered eligible for operation in the United States, each aircraft manufactured under this 
Type Certificate must have a U.S. Airworthiness Certificate that may be issued on the basis of the 
Canadian Department of Transport Certificate of Airworthiness for Export signed by the Minister of 
Transport containing the following statement: 
 
“The rotorcraft covered by this certificate has been examined, tested and found to comply with the 
type design approved under Type Certificate R00001RC and to be in condition for safe operation.” 
 
The approved type design for the model 427 consists of data listed on Bell top drawing 427-100-001, 
Revision CY, or later approved revision and the incorporation of Bell kit 427-706-018 (fuel shut off 
valve kit). For helicopter serial numbers 56001 through 56043, either ASB 427-01-05 must be 
incorporated or Bell kit 427-706-019 (FAA Type Certification Kit) must be installed. See NOTE 9. 
 
The U.S. airworthiness certification basis for aircraft certificated under FAR section 21.29 and 
exported by the country of manufacture is FAR Section 21.183(c) or 21.185(c). 
 
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.

Page 5 of 6 R00001RC 
 
Certification Basis 1. For approved MGW configuration of 2722 kg (6000 lb.) 
 
a) FAR part 27, dated October 2, 1964, amendment 27-1 through 27-31FAR part 36 Amendment 36-1 
through 36-20 
 
b) The following paragraphs for FAR part 29 at amendment 29-1 through 29-40 (except 29- 
38) as identified in FAA AC 27-1A section 780 are used for engine isolation: 
29.861(a) 29.901(c) 29.903(b)(c)&(e) 
29.908(a) 29.917(b)&(c)(1) 29.927(c)(1) 
29.953(a) 29.1027(a) 29.1045 
29.1047(a) 29.1181(a) 29.1189(c) 
29.1191(a)(1) 29.1193(e) 29.1195(a)&(d) 
29.1197 29.1199 29.1201 
29.1305(a)(6)&(b) 29.1309(b)(2)(i)&(d) 29.1331(b) 
Equivalent Safety Findings made in accordance with FAA part 21.21(b)(1) are as 
follows: 
29.903(b), 29.1181(a), 29.1191(a)(1) – Firewalls and Designated Fire Zones 
 
c) Additional Equivalent Safety Findings made in accordance with FAA part 21.21(b)(1) are 
as follows: 
27.307(b)(5), 27.723, 27.725, 27.727 – Skid Type Undercarriages 
27.963(g) – Fuel Tanks 
27.995 – Fuel Valves 
27.1191 – Firewalls 
27.175(c) - Static Longitudinal Stability in Autorotation 
 
e) Special Condition made in accordance with FAR part 21.16 is as follows: 
27-00S-SC High Intensity Radiated Fields (HIRF), dated May 11, 1999 
 
2. For approved MGW configuration of 2880 kg (6350 lb.) 
 
The basis of certification is the same as in 1. above and in addition the following sections 
of FAA Part 27: 
27.561 at Amendment 27-32 
27.1 and 27.2 at Amendment 27-37 
 
 
Production Basis None. See Import Requirements 
 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see 
certification basis) must be installed in the helicopter for certification. 
 
In addition, the following items of equipment are required: 
1) For approved MGW configuration of 2722 kg (6000 lb.) Transport Canada approved Rotorcraft 
Flight Manual BHT-427-FM-1 dated November 19, 1999 or later approved revision. 
 
2) For approved MGW configuration of 2880 kg (6350 lb.) Transport Canada approved Rotorcraft 
Flight Manual BHT-427-FM-2 dated April 27, 2000, or later approved revision. 
 
3) For approved MGW configuration 2971 kg (6550 lb.) Transport Canada approved Rotorcraft 
Flight Manual BHT-427-FMS-7 dated May 10, 2002, or later approved revision. 
 
NOTE 1 Current weight and balance report including list of required equipment and list of equipment 
included in certificated empty weight, and loading instructions when necessary must be provided for 
each helicopter at the time of original certification. The certificated empty weight and corresponding 
C.G. locations must include undrainable oil and unusable fuel for the appropriate model. 
 
NOTE 2 The following placard must be displayed in front of and in clear view of the pilot: “THIS 
HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS 
SPECIFIED IN THE APPROVED FLIGHT MANUAL”. 
 
All placards listed in the approved flight manual must be installed in the specified locations. 
 
NOTE 3 The service lives of components are listed in the BHT 427 Maintenance Manual Chapter 4. This 
aircraft shall be maintained in accordance with the BHT-427 Maintenance Manual. 
 
NOTE 4 Modifications within the compartment, between the main transmission and the engine accessory 
section, may compromise the mitigating design features approved by an Equivalent Safety Finding 
to FAR part 27.1191.. The FAA Rotorcraft Directorate must approve all design changes in this area.

Page 6 of 6 R00001RC 
 
NOTE 5 The model 427 rotorcraft employs electronic engine controls that are recognized to be more 
susceptible to Electromagnetic Interference (EMI) than manual (non-electronic) controls used on 
other rotorcraft. EMI may be the result of radiated or conducted interference. For this reason, 
modifications that add or change systems that have the potential for EMI, must either be qualified to 
an FAA acceptable standard or tested at the time of installation for interference to the engine 
controls. This type of testing must employ the particular engine control’s diagnostic techniques and 
external diagnostic techniques. This testing must be accomplished in accordance with FAA 
approved  Bell Helicopter report No. 427-099-053 Rev. D, or an equivalent FAA approved alternate 
test plan. 
 
NOTE 6 Any changes to the type design of this helicopter by means of a amended type certificate (TC), 
supplemental type certificate (STC), or amended STC, requiring instructions for continued 
airworthiness (ICA's) must be submitted thru the project certification office for review and 
acceptance by the Fort Worth -Aircraft Evaluation Group (FTW-AEG) Flight Standards District 
Office (FSDO) prior to the aircraft delivery, or upon issuance of the first standard airworthiness 
certificate for the affected aircraft, whichever occurs later as prescribed by Title 14 CFR 21.50. Type 
design changes by means of a field approval that require ICA's must have those ICA's reviewed by 
the field approving FSDO. 
 
NOTE 7 The model 427 incorporates an emergency OEI limit override function. When this feature is 
selected, damage to the engine and transmission is experienced and continued flight is not permitted. 
Use of this emergency power invalidates the airworthiness of the aircraft and maintenance in 
accordance with the model 427 Maintenance Manual is required to return the aircraft to an airworthy 
condition. 
 
NOTE 8 1. Model 427 helicopters s/n 56001 to 56024, initially certificated at maximum gross weight 
(MGW) of 2722 kg (6000 lb), may be operated at MGW of 2880 kg (6350 lb) when Bell Helicopter 
kit number 427-704-002 (or later approved revision) is incorporated. Helicopters, once modified, 
must be operated in accordance with flight manual BHT-427-FM-2. 
 
2. Model 427 helicopters s/n 56025 and subsequent (s/n 58001 and subsequent are not eligible for 
FAA Certificate of Airworthiness) are approved at MGW of 288 kg (6350 lb.) and will have the 
intent of the kit listed in 1. above incorporated during production. 
 
NOTE 9 Model 427 helicopters s/n 56001 through 56043 may be operated without the installation of Bell kit 
427-706-019 (FAA Type Certification Kit) when Bell ASB 427-01-05 is incorporated. Model 427 
helicopters 56044 and subsequent are modified on the production line. 
 
Note 10 Model 427 helicopters s/n 56001 and subsequent (s/n 58001and subsequent are not eligible for FAA 
Certificate of Airworthiness) with kit 427-706-021 (IGW to 6550 lbs) installed may be operated at a 
MGW of 2971 kg (6550 lbs). These helicopters must be operated in accordance with Flight Manual 
Supplement BHT-427-FMS-7. Maintenance instructions and life limited parts are listed in 
Maintenance Manual BHT-427-MMS-7. 
 
Note 11  Model 427 helicopters s/n 56001 through 56035 with kit 427-704-006 (IIDS Cooling Fans) and kit 
427-704-010 (Oil Blower System Plenum Removal) and IIDS Data Acquisition Unit of part no. 427- 
375-001-105 or higher may be operated at the higher OAT limit of 51.7°C (125°F) in accordance 
with BHT-427-FMS-22 including Temporary Revision TR-1. Helicopters of serial number 56036 
and subsequent (s/n 58001 and subsequent are not eligible for FAA Certificate of Airworthiness) 
have the intent of these kits incorporated during production. 
Note 12 Effective December 16, 2019 the name Bell Helicopter Textron Canada Limited was revised to Bell 
Textron Canada Limited. 
….END….
```

## ADs (25, in force first)

- [AD 2025-25-01](https://openairdocs.org/ad/2025-25-01): Main Rotor Drive System · Bell Textron Canada 427. Effective Jan 16, 2026
- [AD 2025-13-01](https://openairdocs.org/ad/2025-13-01): Main Rotor Blades · Bell Textron Canada 407 and 427. Effective Jul 8, 2025
- [AD 2023-11-07](https://openairdocs.org/ad/2023-11-07): Ground Proximity System · Airbus Helicopters 47, 206, 210 and 237 more. Effective Jun 22, 2023
- [AD 2021-19-01](https://openairdocs.org/ad/2021-19-01): Cabin Equipment/Furnishings · Shoulder harness restraint system (Bell Helicopter Textron STC SH2073SO or SH2751SO). Effective Oct 13, 2021
- [AD 2019-23-09](https://openairdocs.org/ad/2019-23-09): Empennage Structure · Bell Helicopter Textron Canada 427. Effective Jan 10, 2020
- [AD 2016-20-01](https://openairdocs.org/ad/2016-20-01): Engine and Transmission Lubrication System · Bell Helicopter Textron Canada 427 and 429. Effective Oct 17, 2016
- [AD 2015-17-02](https://openairdocs.org/ad/2015-17-02): Main Rotor Drive System · Bell Helicopter Textron Canada 206L-4, 407, 427 and 1 more. Effective Sep 24, 2015
- [AD 2013-18-06](https://openairdocs.org/ad/2013-18-06): Main Rotor Control · Bell Helicopter Textron Canada 206A, 206B, 206L and 10 more. Effective Oct 17, 2013
- [AD 2012-14-07](https://openairdocs.org/ad/2012-14-07): Rotorcraft Servo System · Bell Helicopter Textron Canada 407 and 427. Effective Aug 3, 2012
- [AD 2012-10-01](https://openairdocs.org/ad/2012-10-01): Rotorcraft tailboom · Bell Helicopter Textron Canada 427. Effective Jun 29, 2012
- [AD 2011-25-01](https://openairdocs.org/ad/2011-25-01): Liferafts · Agusta AB412, AB412 EP, 206A and 23 more. Effective Jan 17, 2012
- [AD 2011-03-03](https://openairdocs.org/ad/2011-03-03): Tail Rotor Drive · Bell Helicopter Textron Canada 427. Effective Apr 14, 2011
- [AD 2010-26-51](https://openairdocs.org/ad/2010-26-51): Tail rotor blade · Bell Helicopter Textron Canada 206A, 206B, 206L and 10 more. Effective Mar 25, 2011
- [AD 2009-25-08](https://openairdocs.org/ad/2009-25-08): Hydraulic pump driveshaft assembly · Bell Helicopter Textron Canada 407 and 427. Effective Dec 28, 2009
- [AD 2009-22-11](https://openairdocs.org/ad/2009-22-11): Swashplate link assembly bearing · Bell Helicopter Textron Canada 407 and 427. Effective Nov 16, 2009
- [AD 2009-15-15](https://openairdocs.org/ad/2009-15-15): Vertical Stabilizer, Attach Fittings · Bell Helicopter Textron Canada 427. Effective Sep 8, 2009
- [AD 2009-07-52](https://openairdocs.org/ad/2009-07-52): Cyclic control lever assembly · Bell Helicopter Textron Canada 206A, 206A-1 (OH-58A), 206B and 7 more. Effective May 1, 2009
- [AD 2003-04-12](https://openairdocs.org/ad/2003-04-12): Auxiliary Fin Assemblies and Limitations Section of the Rotorcraft Flight Manual (RFM) · Bell Helicopter Textron Canada 427. Effective Apr 4, 2003
- [AD 2003-04-14](https://openairdocs.org/ad/2003-04-14): Hydraulic Solenoid Tee Fitting and Tubes · Bell Helicopter Textron Canada 427. Effective Apr 4, 2003
- [AD 2021-23-13](https://openairdocs.org/ad/2021-23-13) (historical): Ground Proximity System · Airbus Helicopters K-225, K-190A, K-240 and 237 more. Effective Dec 9, 2021
- [AD 2011-15-51](https://openairdocs.org/ad/2011-15-51) (historical): Hydraulic servo actuators · Bell Helicopter Textron Canada 407 and 427. Effective Nov 14, 2011
- [AD 2009-08-03](https://openairdocs.org/ad/2009-08-03) (historical): Tail rotor blade (blade) · Bell Helicopter Textron 206A, 206B, 206L and 10 more. Effective Apr 24, 2009
- [AD 2007-19-52](https://openairdocs.org/ad/2007-19-52) (historical): Tail rotor blade (blade) · Bell Helicopter Textron 206A, 206B, 206L and 10 more. Effective Dec 5, 2007
- [AD 2001-13-51](https://openairdocs.org/ad/2001-13-51) (historical): Driveshafts · Bell Helicopter Textron Canada 206L-4, 407 and 427. Effective Oct 9, 2001
- [AD 2009-07-51](https://openairdocs.org/ad/2009-07-51) (historical): Lever assembly bearing · Bell Helicopter Textron 206A, 206A-1 (OH-58A), 206B and 7 more

## Registered aircraft by registry model (OpenAirDocs)

- [Bell Helicopter Textron Canada 427](https://openairdocs.org/model/bell-helicopter-textron-canada-427): 7 aircraft (registry code 1182152)
- [Bell 427](https://openairdocs.org/model/bell-427): 6 aircraft (registry code 1182207)

## STCs approved under this data sheet (37)

- [STC SR00472DE](https://openairdocs.org/stc/SR00472DE): Installation of mounting hardware to support blade folding kit.. Dart Aerospace USA Inc.
- [STC SR01456LA](https://openairdocs.org/stc/SR01456LA): Installation of Concorde RG407 Batteries. Rotorcraft Support Inc
- [STC SR02496LA](https://openairdocs.org/stc/SR02496LA): Installation of a single Garmin G500H system. Rotorcraft Support Inc
- [STC SR02704SE](https://openairdocs.org/stc/SR02704SE): Installation and maintenance of the Sunspot 36 and 46 series lights. AeroLED's Holdings LLC
- [STC SR01935NY-D](https://openairdocs.org/stc/SR01935NY-D): Installation of a Honeywell Chadwick Model 15175 VXP System. Diagnostic Solution International LLC
- [STC SR02622SE](https://openairdocs.org/stc/SR02622SE): Installation of Garmin G500H TXi Display System (Primary Flight Display (PDF), Multi-Function Display (MFD)). Garmin International Inc
- [STC SR02124SE](https://openairdocs.org/stc/SR02124SE): Installation functionality. of Data Garmin Required: transponders: (1) Garmin GTX Master 345/345R Drawing with List ADS-B (MDL), Out and In 005-00734-A4, functionality;. Garmin International Inc
- [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SR00821DE](https://openairdocs.org/stc/SR00821DE): Installation of Automatic Dependent Surveillance - Broadcast (ADS-B) Out and in functionality using the BendixKing KT74 Transponder and qualified position sensor and ADS-B In Receiver. Peregrine
- [STC SR02487AK](https://openairdocs.org/stc/SR02487AK): Installation of L-3 Communications Avionics Systems ESI-500 Standby Instrument System. ADS-B Technologies, LLC
- [STC SR02381AT](https://openairdocs.org/stc/SR02381AT): Installation of passenger sliding doors.. Bell Helicopter Textron Inc.
- [STC SR02470AK](https://openairdocs.org/stc/SR02470AK): Installation of the L-3 Communications NGT -1000/2000/2500 ADS-B System. ADS-B Technologies, LLC
- [STC SR02471AK](https://openairdocs.org/stc/SR02471AK): Installation of the L-3 Communications NGT -9000/9000R ADS-B System. ADS-B Technologies, LLC
- [STC SR01296NY](https://openairdocs.org/stc/SR01296NY): Installation of Electronic News Gathering System. HAS Corporation
- [STC SR02432NY-D](https://openairdocs.org/stc/SR02432NY-D): Installation Chelton FlightLogic Electronic Flight Instrument System (EFIS). Sikorsky Aircraft Corporation
- [STC SR00418DE](https://openairdocs.org/stc/SR00418DE): Installation of cabin air conditioning system.. Air Comm Corporation
- [STC SR00419DE](https://openairdocs.org/stc/SR00419DE): Installation of cabin heater.. Air Comm Corporation
- [STC SR01813LA](https://openairdocs.org/stc/SR01813LA): Installation of Apical Industries, Inc. Emergency Float Kit.. Apical Industries, Inc. dba Dart Aerospace
- [STC SR01953NY-D](https://openairdocs.org/stc/SR01953NY-D): Installation of a Honeywell Chadwick Model 15175 VXP System. Honeywell International Inc
- [STC SR02070AT](https://openairdocs.org/stc/SR02070AT): Manufacture of Baggage Floor Protector in accordance with Aeronautical Accessories, Inc. Drawing List Report No. AA-98097, no revision, dated October 2, 1998, or later FAA approved revisions, and installation per Aeronautical Accessories, Inc. Report AA-98091, no revision, dated July 27, 1998, or later FAA approved revisions.. Bell Helicopter Textron Inc.
- [STC SR02071AT](https://openairdocs.org/stc/SR02071AT): Manufacture of Replacement Crew Window in accordance with Aeronautical Accessories, Inc. Drawing List Report No. AA-98145, no revision, dated October 5, 1998, or later FAA approved revisions, and installation per Aeronautical Accessories, Inc. Report AA-98111, no revision, dated July 20, 1998, or later FAA approved revisions.. Bell Helicopter Textron Inc.
- [STC SR02072AT](https://openairdocs.org/stc/SR02072AT): Manufacture of replacement passenger window.. Bell Helicopter Textron Inc.
- [STC SR02074AT](https://openairdocs.org/stc/SR02074AT): Manufacture of Automatic Door Opener in accordance with Aeronautical Accessories, Inc. Drawing List Report AA-98109, no revision, dated October 30, 1998, or later FAA approved revisions, and installation per Aeronautical Accessories, Inc. Report AA-98099, no revision, dated July 7, 1998, or Report AA-98100, no revision, dated August 14, 1998, or Report AA-98105, no revision, dated July 9, 1998, or later FAA approved revision.. Bell Helicopter Textron Inc.
- [STC SR02075AT](https://openairdocs.org/stc/SR02075AT): Manufacture of Folding maintenance Step Assembly in accordance with Aeronautical Accessories, Inc. Drawing List Report No. AA-98066, no revision, dated October 1, 1998, or later FAA approved revisions, and installation per Aeronautical Accessories, Inc Report AA-98082, no revision, dated September 16, 1998, or later FAA approved revisions.. Bell Helicopter Textron Inc.
- [STC SR02076AT](https://openairdocs.org/stc/SR02076AT): Manufacture of Pre-Flight Step/Handle in accordance with Aeronautical Accessories, Inc. Drawing List Report No. AA-98110, no revision, dated October 2, 1998, or later FAA approved revisions, and installation per Aeronautical Accessories, Inc. Report AA-98098, no revision, dated July 7, 1998, or later FAA approved revisions.. Bell Helicopter Textron Inc.
- [STC SR02077AT](https://openairdocs.org/stc/SR02077AT): Manufacture of Cyclic support Safety Cover.. Bell Helicopter Textron Inc.
- [STC SR02196AT](https://openairdocs.org/stc/SR02196AT): Manufacture of Flitestep /Floatstep  in accordance with Aeronautical Accessories, Inc. Drawing List Report No. AA-98149, Revision C, dated August 31, 2000, or later FAA approved revisions, and installation per Aeronautical Accessories, Inc. Report 
AA-98150, Revision B, dated April 24, 2000, or installation per Aeronautical Accessories, Inc. Report AA-99093, Revision C, dated April 24, 2000, or installation per Aeronautical Accessories, Inc. Report AA-00011, Revision A, dated April 24, 2000, or later FAA approved revisions.. Bell Helicopter Textron Inc.
- [STC SR02205AT](https://openairdocs.org/stc/SR02205AT): Tail Rotor Pedal Lockout Kit in accordance with Aeronautical Accessories, Inc. Drawing List AA-93088, Revision K, dated August 1, 2000, or later FAA approved revisions.  Installation per Aeronautical Accessories, Inc. Report AA-00052, Revision A, dated August 1, 2000, or later FAA approved revisions.. Bell Helicopter Textron Inc.
- [STC SR02304AT](https://openairdocs.org/stc/SR02304AT): Cabin Floor Protectors manufactured. Bell Helicopter Textron Inc.
- [STC SR02382AT](https://openairdocs.org/stc/SR02382AT): Installation of a cargo mirror in accordance with Aeronautical Accessories, Inc. (AAI) Master Drawing List Report AA-98157, Revision A, dated November 20, 2000, or later FAA approved revision.. Bell Helicopter Textron Inc.
- [STC SR09395RC](https://openairdocs.org/stc/SR09395RC): Installation of Supplemental Baggage Compartment Floor in accordance with Aeronautical Accessories, Inc., Drawing List Report No. AA-03047, Revision A, dated 
September 4, 2003, or later Federal Aviation Administration (FAA) approved revision.. Bell Helicopter Textron Inc.
- [STC SR01266NY](https://openairdocs.org/stc/SR01266NY): Installation of Wire Strike Protection System (WSPS).. Bristol Aerospace Ltd
- [STC SR02287AK](https://openairdocs.org/stc/SR02287AK): Installation of Airglas, Inc., L2700-427 Ski Kit.. Airglas Inc.
- [STC SR01666NY](https://openairdocs.org/stc/SR01666NY): Installation of Helipro Sliding Windows.. ACROHelipro Global Services Inc.
- [STC SR01262NY](https://openairdocs.org/stc/SR01262NY): Installation of a FSI Ultra Media II, III, or Wescam camera and isolation mount.. Helipro International
- [STC SR01532NY](https://openairdocs.org/stc/SR01532NY): Installation of D427-659 bearpaws and skis.. Dart Aerospace Limited
- [STC SR01520NY](https://openairdocs.org/stc/SR01520NY): Installation of bulkhead adapter assembly p/n 427-25-11-901-001.. Helipro International

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