# TCDS A29EU: Britten-Norman Aerospace Ltd.

- Type: Type certificate data sheet
- Status: Current
- Holder: Britten-Norman Aerospace Ltd.
- Revision: 7
- Revised: April 11, 2024
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23
- Registered aircraft: 3, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/36/06/360699c9481bf2dcffcd71b60c5f28fc718fb1d10fbf5da437caba7c760b1604
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID183625816420240425145009.0001
- Page: https://openairdocs.org/tcds/A29EU

## Models (3)

As the data sheet lists them.

- BN2A MK. III (Trislander)
- BN2A MK. III-2 (Trislander)
- BN2A MK. III-3 (Trislander)

## 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 
Rev No. 7 3 3 3 6 3 3 
 
 DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A29EU 
Revision 7 
Britten-Norman 
Aerospace,  Ltd.  
BN2A MK. III 
BN2A MK. III-2 
BN2A MK. III-3 
 
April 11, 2024 
 
TYPE CERTIFICATE DATA SHEET NO. A29EU 
 
This data sheet, which is a part of type  certificate No. A29EU, 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 Britten-Norman Aerospace Ltd  
  Bembridge Airport 
  Isle of Wight, PO35 5PR, United Kingdom 
 
  Type Certificate Holder Record          Britten-Norman (Bembridge) Limited transferred TC A29EU to Pilatus Britten-Norman 
Limited on Septermber 24, 1979.       
   Pilatus Britten-Norman Limited transferred TC A29EU to B-N Group Ltd. on December 9, 
2002.   
   B-N Group Ltd. Transferred TC A29EU to Britten-Norman Aircraft Ltd. on January 12, 
2023. 
                                            Britten-Norman Aircraft Ltd. transferred TC A29EU to Britten-Norman Aerospace Ltd. on 
April 11, 2024. 
 
I. - Model BN-2A MK. III Trislander, 18 PCLM (Normal Category), Approved 4, August 1971 
 
 Engines 3 Lycoming O-540-E4C5 (See NOTE 6) 
 Fuel 91/96 Minimum grade aviation gasoline 
 Engine limits For all operations, 2,700 r.p.m. (260 hp.) 
 Propeller and Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, Hartzell 
   propeller limits HC-C2YK-2C/C8477-4, Hartzell HC-C2YK-2C/C8477A-4 and Hartzell  
  HC-C2YK-2CF/FC8477A-4 (See Note 5). 
  Diameter range 80" maximum, 78" minimum.  No further reduction permitted. 
  Pitch setting at 30 in. station: 
   Low 12.5°          High 78.6° 
  Spinners:  Hartzell 836-29 
  Governors:  Woodward 210275, D210659, 210715, F210444, G210659, or 
   B210715 (See NOTE 7) 
 
 Airspeed limits (IAS) With Modification NB/M/510 airspeed indicator installed 
  Vne (Never exceed) 195 knots  (225 m.p.h.) 
  Vno (Max. structural cruising) 152 knots  (175 m.p.h.) 
  Va  (Maneuvering) 130 knots  (150 m.p.h.) 
  Vfe (Flaps take-off) 113 knots  (130 m.p.h.) 
  Vfe (flaps landing) 106 knots  (122 m.p.h.) 
  Vmc (minimum control)   50 knots  (  58 m.p.h.) 
 
  With Modification NB/M/501 airspeed indicator installed 
  Vmo (Max. operating limits) 152 knots  (175 m.p.h.) 
  Va  (Maneuvering) 130 knots  (150 m.p.h.) 
  Vfe (Flaps take-off) 113 knots  (130 m.p.h.) 
  Vfe (Flaps landing) 106 knots  (122 m.p.h.) 
  Vmc (Minimum control)   50 knots  (  58 m.p.h.)

Page 2 of 7           A29EU 
 
 C.G. range (+20 in.) to (+25.6 in.) at 8,750 lb. 
  (+21.0 in.) to (+25.6 in.) at 9,350 lb. 
  Straight line variation between points. 
 Empty weight C.G. range None 
 Maximum weight 9,350 lb. Maximum takeoff weight. 
  9,350 lb. Maximum landing weight. 
  9,050 lb. Maximum zero fuel weight. 
 Minimum crew One Pilot. 
 Number of seats 18 (2 at -133.5 in) (2 at -103.4 in) 
   (2 at - 74.1 in) (2 at - 45.7 in) 
   (2 at - 15.9 in) (2 at + 14.2 in) 
   (2 at + 43.5 in) (2 at + 71.5 in) 
   (2 at +101.3 in) 
 Maximum baggage 400 lb. (+144.0 in). 
 Fuel capacity 196 U.S. gal. total (two  69 U.S. gal. main wing tanks at +27.0 in. 
  plus two 29 U.S. gal. wing tip tanks at +34.0 in.) 
  (See NOTE 1 for data on unusable fuel) 
 
 Oil capacity 24 U.S. qt. total (two wing engines) (-2.6 in.) 
  12 U.S. qt. total (rear engine) (+164.5 in.) 
  (See NOTE 1 for data on undrainable oil) 
 
 Maximum Operating Altitude 12,000 ft. 
 
 Control surface movements Wing flaps retracted Full Up   6° (down) Full Down 56° (down) 
  Aileron Up 25° Down 15° 
  Elevator Up 25 1/2° Down 19 1/2° 
  Elevator trim tab* Up 23° Down 26° 
  Rudder Right 20° Left 20° 
  Rudder tab Right 20° Left 20° 
 
  *(measured with elevator neutral) 
 
2. Model BN.2A MK. III-2 Trislander, 18 PCLM (Normal Category), Approved December 9, 1976 
 (Same as BN.2A MK III except for elongated nose incorporating baggage compartment, increase in 
 maximum weight and change in C.G. limits). 
 
 Engines Three  Lycoming O-540-E4C5 (See NOTE 6) 
 
 Fuel 91/96 Minimum grade aviation gasoline 
 Engine limits For all operations, 2700 r.p.m. (260 hp) 
 Propeller and Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, Hartzell 
   propeller limits HC-C2YK-2C/C8477-4, Hartzell HC-C2YK-2C/C8477A-4 and Hartzell  
  HC-C2YK-2CF/FC8477A-4 (See Note 5). 
 
  Diameter range 80" maximum, 78" minimum.  No further reduction permitted. 
  Pitch setting at 30 in. station: 
   Low 12.5°          High 78.6° 
  Spinners: Hartzell 836-29 
  Governors: Woodward 210275, D210659, 210715, F210444, G210659, or 
   B210715 (See NOTE 7) 
 
 Airspeed limits (IAS) For operation in FAR Part 135 Category.   
  (See NOTE 9 for FAR 91 operations) 
  Vmo (Max. operating limit) 142 knots  (164 m.p.h.) 
  Va  (Maneuvering) 133 knots  (153 m.p.h.) 
  Vfe (Flaps take-off) 133 knots  (153 m.p.h.) 
  Vfe (flaps landing) 110 knots  (127 m.p.h.) 
  Vmc (minimum control)   50 knots  (  58 m.p.h.)

Page 3 of 7 A29EU 
 
 
 C.G. range (+19 in.) to (+25.6 in.) at 8,750 lb.    (See NOTE 9 for FAR 91 operations) 
  (+19.6 in.) to (+24.95 in.) at 9,500 lb. 
  Straight line variation between points. 
 
 Empty weight C.G. range None 
 
 Maximum weight 9,500 lb. Maximum takeoff weight, maximum landing weight, and 
  maximum zero fuel weight.  (See NOTE 9 for FAR 91 operations.) 
 
 Minimum crew One Pilot. 
 
 Number of seats 18 (2 at -133.5 in)  (2 at -103.4 in) 
   (2 at -  74.1 in)  (2 at - 45.7 in) 
   (2 at -  15.9 in)  (2 at + 14.2 in) 
   (2 at +  43.5 in)  (2 at + 71.5 in) 
   (2 at +101.3 in) 
 
 Maximum baggage 300 lb. (-209.5 in) 
  400 lb. (+144.0 in). 
 
 Fuel capacity 196 U.S. gal. total (two  69 U.S. gal. main tanks at +27.0 in. 
  plus two 29 U.S. gal. wing tip tanks at +34.0 in.) 
  (See NOTE 1 for data on unusable fuel) 
 
 Oil capacity 24 U.S. qt. total (two wing engines) (-2.6 in.) 
  12 U.S. qt. total (rear engine) (+164.5 in.) 
  (See NOTE 1 for data on undrainable oil) 
 
 Maximum Operating Altitude 12,000 ft. 
 
 Control surface movements Wing flaps retracted Full Up   6° (down) Full Down 56° (down) 
  Aileron Up 25° Down 15° 
  Elevator Up 25 1/2° Down 22 1/2° 
  Elevator trim tab* Up 23° Down 26° 
  Rudder Right 20° Left 20° 
  Rudder tab Right 20° Left 20° 
 
  *(measured with elevator neutral) 
 
3. Model BN2A MK. III-3 Trislander, 18 PCLM (Normal Category), Approved February 9, 1977. 
 (Same as BN2A MK. III-2 except for Autofeather system installation and increased weights). 
 
 Engines Three Lycoming O-540-E4C5 (See NOTE 6) 
 
 Fuel 91/96 Minimum grade aviation gasoline 
 Engine limits For all operations, 2700 r.p.m. (260 hp) 
 Propeller and Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, Hartzell 
   propeller limits HC-C2YK-2C/C8477-4, Hartzell HC-C2YK-2C/C8477A-4 and Hartzell  
  HC-C2YK-2CF/FC8477-4 (See Note 5). 
 
  Diameter range 80" maximum, 78" minimum.  No further reduction 
  permitted. 
 
  Pitch setting at 30 in. station: 
   Low 12.5°          High 78.6° 
  Spinner:  Hartzell 836-29 
  Governor:  Woodward 210521 or A210521 (See NOTE 8)

Page 4 of 7           A29EU 
 
 Airspeed limits (IAS) For operation to FAR Part 135 Category. 
   (See NOTE 9 for FAR 91 operations) 
  Vmo (Max. operating limit) 142 knots  (164 m.p.h.) 
  Va  (Maneuvering) 133 knots  (153 m.p.h.) 
  Vfe (Flaps take-off) 133 knots  (153 m.p.h.) 
  Vfe (Flaps landing) 110 knots  (127 m.p.h.) 
  Vmc (Minimum control)   50 knots  (  58 m.p.h.) 
 
  C.G. range (+19.0 in.) to (+25.6 in.) at 8,750 lb. 
  (+20.0 in.) to (+24.5 in.) at 10,000 lb. 
  Straight line variation between points. 
 
 Empty weight C.G. range None 
 
 Maximum weight 10,000 lb. Maximum takeoff weight. 
  10,000 lb. Maximum landing weight. 
    9,700 lb. Maximum zero fuel weight. 
 
 Minimum crew One pilot. 
 
 Number of seats 18 (2 at -133.5 in)  (2 at -103.4 in) 
   (2 at -  74.1 in)  (2 at - 45.7 in) 
   (2 at -  15.9 in)  (2 at + 14.2 in) 
   (2 at + 43.5 in)  (2 at + 71.5 in) 
   (2 at +101.3 in) 
 
 Maximum baggage 300 lb. (-209.5 in) 
  400 lb. (+144.0 in). 
 
 Fuel capacity 196 U.S. gal. total (two  69 U.S. gal. main tanks at +27.0 in. 
  plus two 29 U.S. gal. wing tip tanks at +34.0 in.) 
  (See NOTE 1 for data on unusable fuel) 
 
 Oil capacity 24 U.S. qt. total (two wing engines) (-2.6 in.) 
  12 U.S. qt. total (rear engine) (+164.5 in.) 
  (See NOTE 1 for data on undrainable oil) 
 Maximum Operating Altitude 12,000 ft. 
 
 Control surface movements Wing flaps retracted Full Up   6° (down) Full Down 56° (down) 
  Aileron Up 25° Down 15° 
  Elevator Up 25 1/2° Down 22 1/2° 
  Elevator trim tab* Up 23° Down 26° 
  Rudder Right 20° Left 20° 
  Rudder tab Right 20° Left 20° 
 
  *(measured with elevator neutral) 
 
DATA PERTINENT TO ALL MODELS 
 Datum Wing leading edge (Stn. 234.5 in) 
 
 Leveling means Fore and Aft leveling:  Holes for datum pins on which straight edge is placed are located  
  on the left side of the center fuselage. 
 
  Lateral leveling:  By a lateral leveling plate located on the cabin floor immediately  
  forward of the aft baggage area (fuselage station 345).

Page 5 of 7 A29EU 
 
 
 Serial Numbers eligible The United Kingdom Certificate of Airworthiness for Export endorsed as noted under  
  "Import Requirements" must be submitted for each individual aircraft for which  
  application for certification is made. 
 
 Import requirements A United States Airworthiness Certificate may be issued on the basis of a United  
  Kingdom Certificate of Airworthiness for export signed by a member of the United  
  Kingdom Department of Trade and Industry containing the following statement  "The  
  airplane covered by this certificate has been examined, tested and found to conform to  
  the 14 CFR Part 23 approved under US Type Certificate A29 EU and is to be in condition  
  for safe operation". 
 
 Service Information Each of the documents listed below must state that it is approved by the United Kingdom 
Civil Aviation Authority (CAA) or – for approvals made between September 29, 2003 and 
December 31, 2020 – by the European Union Aviation Safety Agency (EASA). 
 
• Service bulletins, 
• Structural repair manuals, 
• Vender manuals, 
• Aircraft flight manuals, and 
• Overhaul and maintenance manuals. 
 
  The FAA accepts such documents and considers the FAA -approved unless on of the 
following conditions exits: 
 
• The documents change the limitations, performance, or procedures of the FAA 
approved manuals: or 
• The documents make an acoustical or emissions change to this product’s U . S. type  
certificate as defined in 14 CFR 21.93. 
 
The FAA uses the post type validation procedures to approve these documents.  The FAA 
may delegate on case -by-case to the United Kingdom CAA or – between September 29, 
2003 and December 31, 2020 – to EASA, to approve on behalf of the FAA for the  U.S. 
type certificate.  If this is the case it will be noted on the document. 
 
 Certification basis FAR 21.29 and FAR 23 effective February 1, 1965 as amended by amendments 23-1  
  through 23-9 inclusive, plus FAR 135 Appendix A, effective July 19, 1970 plus special  
  conditions number 23-35-EU-7 issued August 4, 1971. 
 
  Type Certificate No. A29 EU issued August 4, 1971 (re-issued to 
  Britten-Norman, Bembridge, Limited on February 23, 1972). 
 
  Date of application for Type Certificate, October 1, 1970. 
 
The United Kingdom CAA originally type certificated this aircraft under is type certificate 
Number BA 8.  The FAA validated this product under U.S. Type Certificate number 
A29EU.  Effective September 28, 2003, the EASA began oversight of this product on 
behalf of the United Kingdom CAA. 
 
Effective January 1, 2021, oversight of this product returned to the United Kingdom CAA. 
The United Kindom CAA issued TCDS UK.TC.A.00043 Issue 1 on September 5, 2022 that 
covers all BN2A MK. III models validated by the FAA.  
 
 
 Validation basis Pursuant to FAR 21.29 (a)(1)(ii) Type Certificate No. A29 EU was issued in validation of  
  the British Air Registration Board's certification of compliance with the following  
`  airworthiness standards which were found to provide a level of safety equivalent to that  
  provided by the aforementioned type certification basis. 
 
  1. The British Certification Basis as stated in Air Registration Board Type  
   Certificate Data Sheet No. BA.6 dated May 14, 1971. 
 
  2. The "FAA additional requirements for UK airplanes 12,500 lbs. or less

Page 6 of 7           A29EU 
 
   maximum weight" dated January 1, 1970. 
 
  3. FAR 23 Section 23.1529 effective February 5, 1970 (Amendment 23-8) and  
   Section 23.1441, 23.1443, 23.1447 and 23.1449 effective June 17, 1970  
   (amendment 23-9). 
 
  4. FAR 135 Appendix "A" effective July 19, 1970. 
 
  5. FAA Special Conditions No. 23-35-EU-7 issued August 4, 1971. 
 
 Equipment 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: 
 
  (a) Stall warning indicator (Safe Flight Type No. 165). 
  (b) A pilot's rear view mirror installed on the forward L.H. fuselage.  
  (c) Model BN.2A MK.III Trislander :  CAA approved airplane Flight Manual,  
   Document No. FM/BN.2A III/1, plus deviations 1 and 2 and subsequent  
   CAA approved revisions. 
 
   Model BN.2A MK.III-2 Trislander :  CAA approved airplane Flight Manual,  
   Document No. FM/BN.2A III/1, plus deviations 1, 2, and 16, and subsequent  
   CAA approved revisions.  For operations under FAR Part 91, Flight  
   Manual supplement No. 17 applies. 
 
   Model BN.2A MK III-3 Trislander :  CAA approved airplane Flight Manual,  
   document No. FM/BN.2A III/1, plus deviations 1, 2 and 16 and subsequent  
   CAA approved revisions.  For operations under FAR Part 91, Flight  
   Manual supplement No. 18 applies. 
 
  For compliance with FAR 135 Appendix A and associated Special Conditions,  
  the following modifications must be incorporated. 
  (a) Airspeed indicator marked to show a maximum operating limit speed  
   (Vmo) Modification no. NB/M/610. 
 
  (b) Rear engine fire detection system, Modification no. NB/M/508. 
 
  (c) Rear engine power loss warning system, Modification NB/M/502 
   (Models BN-2A MK. III and BN-2A MK. III-2 only). 
 
  (d) Auto-feather system to Modification NB/M/872 (BN2A MK. III-3 only). 
 
NOTE 1 : Current Weight and Balance report including list of equipment included in certificated empty weight and  
  loading instructions where 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 the following: - 
 
  (a) 66 lb. of unusable fuel (42 lb. at +27.0 in and 24 lb. at +34.0 in). 
 
  (b) 0 lb. undrainable oil. 
 
NOTE 2 : The following placards must be displayed on the instrument panel in full view of the pilot. 
 
  "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE  
  WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND  
  MANUALS." 
 
  In addition, all placards required in the applicable approved Airplane Flight Manual must be installed in the  
  appropriate location. 
  Also, each individual airplane must be fitted with a placard which specifies approved types of operations  
  (such as V.F.R., I.F.R., day or night) to which the airplane is limited by the equipment installed.

Page 7 of 7 A29EU 
 
 
NOTE 3 : RESERVED. 
 
NOTE 4 : Information essential for proper maintenance of the airplane is contained in the following Britten-Norman  
  Limited documents: 
 
  (a) Maintenance Manual, reference MM/2, dated 14th June 1971 or later revision. 
 
  (b) Maintenance Schedule, reference MS/2 dated 18th June 1971 or later revision. 
 
NOTE 5 : Propellers of the type shown are eligible for the incorporation of Hartzell Service Bulletin 114 and  
  Service Instructions No. 102.  Propellers so modified have the letter U added to their type designation,  
  e.g. HC-C2YK-2CUF/FC 8477A-1. 
 
NOTE 6 : Britten-Norman Modification NB/M/746 introduces the wide deck variant of the Lycoming  
  O-540-E4C5 engine.  There is no change in the engine type designation. 
  Serial numbers of wide deck engines contain the identification letter "A" e.g. standard deck L-13268-48 
  becomes wide deck L-13268-48A.  Britten-Norman Service Bulletin BN.2/SB.87 also refers.  
 
NOTE 7 : For aircraft fitted with wide deck engines (See NOTE 6), the only propeller governors to be fitted  
  are:  G210659 where no unfeathering accumulator is installed and B210715 where an  
  unfeathering accumulator is installed.  For the standard deck engines, propeller governor P/N D210659  
  and F210444 are interchangeable for aircraft without unfeathering accumulators and P/N 210715  
  and 210275 are interchangeable for aircraft with unfeathering accumulators. 
 
NOTE 8 : Propeller governor part numbers listed for BN.2A MK III-3 model Trislander are not interchangeable.   
  P/N 210521 is applicable to standard deck Lycoming engines and P/N A210521 is applicable to wide  
  deck engines. 
 
NOTE 9 BN.2A MK III-2 and -3 airplanes with modification NB/M/579 airspeed indictor installed are eligible  
  for operation under FAR Part 91.  Operations under FAR Part 91 must be conducted in accordance  
  with the CAA approved airplane Flight Manual including the appropriate supplement as noted  
  under equipment, paragraph (c), and the following data sheet information applies in lieu of that  
  appearing under the corresponding heading for the particular model: 
 
Model BN.2A MK III-2 
  Airspeed limits (IAS) 
   Vne (Never exceed) 182 Knots  (210 MPH) 
   Vno (Max structural cruising) 142 Knots  (164 MPH) 
 
  C.G. Range 
   (+19.0 IN) to (25.6 IN) at 8750 LB. 
   (+20.0 IN) to (24.5 IN) at 10,000 LB. 
   Straight line variation between points. 
 
  Maximum weight 
   10,000 LB. - maximum take-off weight 
   10,000 LB. - maximum landing weight 
     9,700 LB. - maximum zero fuel weight 
 
Model BN.2A MK III-3 
  Airspeed Limits (IAS) 
   Vne (Never exceed) 182 Knots  (210 MPH) 
   Vno (Max. structural cruising) 142 Knots  (164 MPH) 
 
 
 
 
....END....
```

## ADs (55, first 50, in force first)

- [AD 2025-01-01](https://openairdocs.org/ad/2025-01-01): Landing Gear System · Britten-Norman Aerospace BN-2, BN-2A, BN-2A-2 and 18 more. Effective Mar 11, 2025
- [AD 2024-08-03](https://openairdocs.org/ad/2024-08-03): Flight Control System Wiring · Britten-Norman BN-2, BN-2A, BN-2A-2 and 18 more. Effective Jun 3, 2024
- [AD 2016-26-09](https://openairdocs.org/ad/2016-26-09): Navigation · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Feb 9, 2017
- [AD 2016-04-05](https://openairdocs.org/ad/2016-04-05): Engine Controls · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Mar 24, 2016
- [AD 2013-13-02](https://openairdocs.org/ad/2013-13-02): Fuel · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Aug 1, 2013
- [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 2002-25-05](https://openairdocs.org/ad/2002-25-05): Universal joint · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Feb 3, 2003
- [AD 2002-25-03](https://openairdocs.org/ad/2002-25-03): Left-hand rudder bar · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Jan 31, 2003
- [AD 2002-24-01](https://openairdocs.org/ad/2002-24-01): Rear Engine-mounting Frame · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Jan 21, 2003
- [AD 2002-22-02](https://openairdocs.org/ad/2002-22-02): Engine Mount Bracket · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Dec 20, 2002
- [AD 2002-03-04](https://openairdocs.org/ad/2002-03-04): Emergency Exit Window Sealant · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Mar 29, 2002
- [AD 2002-02-11](https://openairdocs.org/ad/2002-02-11): Oleo Attachment Brackets · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Mar 25, 2002
- [AD 2002-01-11](https://openairdocs.org/ad/2002-01-11): Throttle Friction-Shaft · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Feb 28, 2002
- [AD 98-18-07](https://openairdocs.org/ad/98-18-07): Generator System · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Oct 12, 1998
- [AD 98-04-17](https://openairdocs.org/ad/98-04-17): Diodes On Terminal Switches · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Mar 23, 1998
- [AD 98-04-21](https://openairdocs.org/ad/98-04-21): Airplane Flight Manual (AFM) - Limitations - Icing · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 16 more. Effective Mar 13, 1998
- [AD 86-07-02 R1](https://openairdocs.org/ad/86-07-02-R1): Main Landing Gear Torque Link Lug & Upper Case Inspection · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Nov 28, 1997
- [AD 84-23-06 R1](https://openairdocs.org/ad/84-23-06-R1): Engine Mounting Brackets · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Nov 24, 1997
- [AD 97-22-02](https://openairdocs.org/ad/97-22-02): Engine Mounting Brackets, Bolts, and Bushes · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Nov 24, 1997
- [AD 96-18-21](https://openairdocs.org/ad/96-18-21): Aileron Mass Balance Clamp Unit · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Oct 25, 1996
- [AD 95-04-09](https://openairdocs.org/ad/95-04-09): Nose Wheel Steering System · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 16 more. Effective Apr 14, 1995
- [AD 87-13-02](https://openairdocs.org/ad/87-13-02): Elevator Trim Tab Assemblies · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Jul 27, 1987
- [AD 83-10-06 R1](https://openairdocs.org/ad/83-10-06-R1): Elevator Trim Tabs · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Feb 12, 1987
- [AD 86-23-02](https://openairdocs.org/ad/86-23-02): Modification NB/M/990 · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Dec 8, 1986
- [AD 83-23-01](https://openairdocs.org/ad/83-23-01): Wing Tank Fuel System Modification · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Dec 8, 1983
- [AD 83-14-02](https://openairdocs.org/ad/83-14-02): Wing-To-Fuselage Attachments · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Aug 19, 1983
- [AD 83-12-02](https://openairdocs.org/ad/83-12-02): Rudder Drive Lever Support Assembly · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Jul 27, 1983
- [AD 83-07-12 R1](https://openairdocs.org/ad/83-07-12-R1): Fuel Transmitter Float Inspection · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Apr 11, 1983
- [AD 83-05-02](https://openairdocs.org/ad/83-05-02): Teleflex Swivel Assembly Inspection · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Mar 7, 1983
- [AD 83-03-05](https://openairdocs.org/ad/83-03-05): Undercarriage Shock Absorber · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Feb 22, 1983
- [AD 82-24-06 R1](https://openairdocs.org/ad/82-24-06-R1): Carburetor Air Box Shutter · B-N Group BN-2, BN-2A, BN-2A-26 and 7 more. Effective Feb 7, 1983
- [AD 80-14-10](https://openairdocs.org/ad/80-14-10): Rudder Balance Arm Brackets · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Jul 14, 1980
- [AD 79-21-03](https://openairdocs.org/ad/79-21-03): Elevator Trim Tab Cable · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Nov 12, 1979
- [AD 79-03-05](https://openairdocs.org/ad/79-03-05): Main Landing Gear Extension Tube Assemblies · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Feb 27, 1979
- [AD 78-11-08](https://openairdocs.org/ad/78-11-08): Elevator and Flap Control Rods · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Jun 6, 1978
- [AD 77-07-10](https://openairdocs.org/ad/77-07-10): Aileron Mass Balance Support Arm · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Apr 18, 1977
- [AD 76-21-07](https://openairdocs.org/ad/76-21-07): Engine Mounting · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Nov 5, 1976
- [AD 76-06-05](https://openairdocs.org/ad/76-06-05): Pilot's Seat · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Apr 19, 1976
- [AD 76-02-04](https://openairdocs.org/ad/76-02-04): Engine Mounting Frame · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Jan 30, 1976
- [AD 75-26-01](https://openairdocs.org/ad/75-26-01): Rudder Control · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Dec 23, 1975
- [AD 75-22-17](https://openairdocs.org/ad/75-22-17): Rudder Trim Control · B-N Group BN2A MK. III, BN2A MK. III-2 and BN2A MK. III-3. Effective Nov 5, 1975
- [AD 71-05-05](https://openairdocs.org/ad/71-05-05): Elevator Trim Tab System · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Jan 26, 1971
- [AD 70-12-11](https://openairdocs.org/ad/70-12-11): Flap Actuating System · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Jun 11, 1970
- [AD 70-07-04](https://openairdocs.org/ad/70-07-04): Tail Plane Front Spar · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Mar 31, 1970
- [AD 70-07-05](https://openairdocs.org/ad/70-07-05): Carburetor Air Box · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Mar 31, 1970
- [AD 70-06-04](https://openairdocs.org/ad/70-06-04): Fuselage Attach Spindles · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Mar 17, 1970
- [AD 70-06-05](https://openairdocs.org/ad/70-06-05): Elevator Trim System Drive · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Mar 17, 1970
- [AD 70-03-06](https://openairdocs.org/ad/70-03-06): Rudder Bar Assembly · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Feb 5, 1970
- [AD 70-02-06](https://openairdocs.org/ad/70-02-06): Elevator Trim Tab Attach · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Jan 11, 1970

All 55: https://openairdocs.org/tcds/A29EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Britten Norman BN-2A MK III](https://openairdocs.org/model/britten-norman-bn-2a-mk-iii): 2 aircraft (registry code 1520203)
- [Britten Norman BN 2A MKIII 2](https://openairdocs.org/model/britten-norman-bn-2a-mkiii-2): 1 aircraft (registry code 1520208)

## STCs approved under this data sheet (77, first 50)

- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position  Light System, and applicable associated power supplies. Whelen Aerospace Technologies
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH
- [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SA615EA](https://openairdocs.org/stc/SA615EA): Installation of a Whelen Anti-Collision Strobe Light System as replacement for originally installed anti-collision lights.. Whelen Aerospace Technologies
- [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine
- [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc.
- [STC SA04424AT](https://openairdocs.org/stc/SA04424AT): Installation of Continental Motors, Inc. (CMI) Shower-of-Sparks  Starting Vibrator Booster Systems. Continental Motors, Inc.
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine
- [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC
- [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation
- [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation
- [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation
- [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc
- [STC SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics
- [STC SA01229SE PAGE 1](https://openairdocs.org/stc/SA01229SE%20PAGE%201): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc
- [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC
- [STC SA01933LA-D PAGE 1](https://openairdocs.org/stc/SA01933LA-D%20PAGE%201): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation
System. Garmin International Inc
- [STC SA02930NY](https://openairdocs.org/stc/SA02930NY): Installation of Insight Instrument Corporation Graphic Engine Monitor (GEM 610C) models G3, G2, and G1 and 1200C model G4 as primary Cylinder Head Temperature (CHT), Exhaust Gas Temperature (EGT), and Turbine Inlet Temperature (TIT) Instruments. Insight Instrument Corporation
- [STC SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc
- [STC SA02717NY PAGE 1](https://openairdocs.org/stc/SA02717NY%20PAGE%201): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC
- [STC SA02149AK](https://openairdocs.org/stc/SA02149AK): Installation of GX50/60 GPS Navigator, Capstone configured MX20 Multi-Function Display and UAT transceiver.. Garmin International Inc
- [STC SA01692SE](https://openairdocs.org/stc/SA01692SE): Installation of a Garmin GMX 200 Multi-Function Display. Garmin International Inc
- [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation
- [STC SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc
- [STC SA00243BO](https://openairdocs.org/stc/SA00243BO): Installation of Centurion Consulting, Inc. GPS Steering Assist Module (SAM) with roll steering (p/n 0025-5100), or without roll steering (p/n 0025-5200).. Icarus Avionics, LLC
- [STC SA02110CH](https://openairdocs.org/stc/SA02110CH): Installation of a Time Trac Data Recorder. P2 Incorporated

All 77: https://openairdocs.org/tcds/A29EU/stcs.md

---
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.