# TCDS A21SO: Embraer S.A.

- Type: Type certificate data sheet
- Status: Current
- Holder: Embraer S.A.
- Revision: 9
- Revised: January 21, 2022
- Product: Aircraft, Small/Large Airplane
- Certification basis: Part 23, Part 25, Part 23, Part 25
- Registered aircraft: 13, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/cc/b2/ccb22eef0401dc71ebac88bb71b6efc29097660829e8ed7b9034c779cdd1af68
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/71C413F8E26DDA50862587D4004EE329.0001
- Page: https://openairdocs.org/tcds/A21SO

## Models (2)

As the data sheet lists them.

- EMB-110P1
- EMB-110P2

## 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 
A21SO 
Revision 9 
Embraer S.A. 
EMB-110P1 
EMB-110P2 
January 21, 2022 
TYPE CERTIFICATE DATA SHEET NO A21SO 
This data sheet which is part of Type Certificate No. A21SO 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 Embraer S.A. 
Av. Brigadeiro Faria Lima, 2.170 
12227-901 São José dos Campos, SP 
Brazil 
Type Certificate Holder Record  Yaborã Indústria Aeroná utica S.A. transferred TC No. A21SO to Embraer S.A. on 
January 1, 2022. 
Embraer S.A. transferred TC No. A21SO to Yaborã Indústria Aeronáutica S.A. on 
January 31, 2020. 
Empresa Brasileira de Aeronáutica S.A. (EMBRAER) changed company name to 
Embraer S.A. effective November 2010. 
I. - Model EMB-110P1 Bandeirante (Normal Category), Approved August 18, 1978 
Engine 2 Pratt & Whitney of Canada Ltd. 
Pratt & Whitney PT6A-34 
Fuel JP-4, JP-5, Jet A, Jet A-1 and Jet B, to conforming to P&W specifications PWA522 or 
CPW 46. See NOTE 4. 
Oil In accordance with P&W Specification PWA521 or CPW202 (MIL-L-23699A). 
Engine Limits PROP N1 GAS 
SHAFT GENERATOR 
SHP SPEED SPEED TIT_(°_C) 
Take-off 750 2200 101.5 790 
Max. Continuous 750 2200 101.5 790 
Starting --- --- --- 1090 (2 sec.) 
925 (10 sec.) 
Max. Reverse (1 min.) 400 2068 790 
Propeller and Propeller Limits 2 Hartzell HC-B3TN-3C/T10178H-8R, 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434- 5, 5P, 6P, 12P, 17P  
or 
2 Hartzell HC-B3TN-3D/T10178HB-8R, 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434-6, 6P, 12P 17P; 
or 
2 Hartzell HC-B3TN-3C/T10178-HB-8R 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434-6, 6P, 12P, 17P 
or 
Page No. 1 2 3 4 5 6 7 
Rev. No. 9 8 7 8 9 8 6

A21SO 
Page 2 
2 Hartzell HC-B3TN-3C/T10178-8R, 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434- 5, 5P, 6P, 12P, 17P  
or 
2 Hartzell HC-B3TN-3D/T10178B-8R, 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434-6, 6P, 12P, 17P 
or 
2 Hartzell HC-B3TN-3C/T10178B-8R 
Diameter:  93 in. (No further reduction permitted.) 
Spinner: Hartzell D3434-6, 6P, 12P, 17P. 
Pitch settings at 30 in. sta. 
Reverse: -11° ± 0.5° 
Feather: +88.1° ± 0.1° 
Primary pick-up angle:  +20.2° ± 0.2° 
Secondary low pitch stop angle:  14° ± 1° 
Airspeed Limits 
Max. Operating Speed 
(See POH and ANAC approved AFM) 
Maneuvering Speed 
(See POH and ANAC approved AFM) 
Maximum Landing Gear Extended 
and Operating 
(Extension and Retraction) Speed 
Maximum Flap Extension Speed 
25% (9.5°) 
100 % (38°) 
265 mph 
195 mph 
168 mph 
207 mph 
170 mph 
(230 knots) 
(169 knots) 
(146 knots) 
(180 knots) 
(148 knots) 
C. G. Range 
(Landing Gear Extended) 
(See NOTE 5) 
(+255.5) to (+272.0) at 12,500 lbs. 
(+251.3) to (+272.0) at 8818 lbs. or less 
Straight line variation between points given. 
Moment change due to retraction of landing gear: 10068 in. lbs. 
(The C. G. is shifted forward with retraction of landing gear). 
Empty Weight C. G. Range 
(See NOTE 5) 
None 
Maximum Weight 
(See NOTE 5) 
Take-off 
Landing 
Zero Fuel 
Ramp 
12,500 lbs. 
12,015 lbs. 
12,015 lbs. 
12,566 lbs. 
(See NOTE 8) 
(See NOTE 1) 
Minimum Crew Day VFR operations - (1) pilot 
All other operations - See POH/AFM. 
Number of Seats 21 seats 
Crew (+19) 
See loading instructions for passenger loading. 
See NOTE 9 for cargo version. 
Maximum Baggage 
(Passenger Configuration) 705 lbs. (+409.0) or, as optional 926 lbs. (+409.0) 
(per EMBRAER Drawing Nos. 110P1-863-40-51 and 110P1-856-24 
Maximum Cargo 
(Cargo Configuration) 
Class "E" Compartment 
3977 lbs. See cargo loading instructions. 
Maximum floor loading 100 lbs. / sq. ft. 
Fuel Capacity 454 gallons (227 gallons each tank) (+283.5)

A21SO 
Page 3 
Unusable fuel 7.4 gallons (3.7 gallons each tank) 
Oil Capacity 9.2 quarts in each engine (+226.4) 
1 quart in each oil radiator (+226.0) 
Max. Operating Altitude 25,000 ft. 
Temperature Operating Limits Maximum: 43°  C or ISA + 40° C, whichever is lower 
Minimum: -50° C 
II - Model EMB-110P2 Bandeirante (Normal Category) Approved October 1, 1979 
Engine 2 Pratt & Whitney of Canada Ltd. 
Pratt & Whitney PT6A-34 
Fuel JP-4, JP-5, Jet A, Jet A-1 and Jet B, conforming to P&W specifications PWA522 or 
CPW46. See NOTE 4. 
Oil In accordance with P&W Specification PWA521 or CPW202 (MIL-L-23699A). 
Engine Limits PROP N1 GAS 
SHAFT GENERATOR
SHP SPEED SPEED TIT(°C) 
Take-off 750 2200 101.5 790 
Max. Conditions 750 2200 101.5 790 
Starting --- --- --- 1090 (2 sec.) 
925 (10 sec.) 
Max. Reverse (1 min.) 400 2068 790 
Propeller and Propeller Limits 2 Hartzell HC-B3TN-3C/T10178H-8R, 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434-5, 5P, 6P, 12P 17P; 
or 
2 Hartzell HC-B3TN-3D/T10178HB-8R, 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434-6, 6P, 12P, 17P; 
or 
2 Hartzell HC-B3TN-3C/T10178HB-8R, 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434-6, 6P, 12P, 17P, 
or 
2 Hartzell HC-B3TN-3C/T10178-8R, 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434- 5, 5P, 6P, 12P, 17P  
or 
2 Hartzell HC-B3TN-3C/T10178B-8R, 
Diameter:  93 in. (No further reduction permitted). 
Spinner: Hartzell D3434-6, 6P, 12P, 17P. 
Pitch settings at 30 in. sta. 
Reverse: -11° ± 0.5° 
Feather: +88.1° ± 0.1° 
Primary pick-up angle:  +20.2° ± 0.2° 
Secondary low pitch stop angle:  14° ± 1° 
Airspeed Limits
 (IAS) Max. Operating Speed 265 mph (230 knots) 
(See POH and ANAC approved AFM) 
Maneuvering Speed 195 mph (169 knots) 
(See POH and ANAC approved AFM)

A21SO 
Page 4 
Maximum Landing Gear Extended 
and Operating 
(Extension and Retraction) Speed 168 (146 knots) 
Maximum Flap Extension Speed 
25% (9.5°) 207 mph (180 knots) 
100 % (38°) 170 mph (148 knots) 
C. G. Range (+255.5) to (+272.0) at 12,500 lbs. 
(Landing Gear Extended) (+251.3) to (+272.0) at 8818 lbs. or less 
(See NOTE 5) Straight line variation between points given. 
Moment change due to retraction of landing gear: 10068 in. lbs. 
(The C. G. is shifted forward with retraction of landing gear). 
Empty Weight C. G. Range None 
(See NOTE 5) 
Maximum Weight Take-off 12,500 lbs. 
(See NOTE 5) Landing 12,015 lbs. (See NOTE 8) 
Zero Fuel 12,015 lbs. 
Ramp 12,566 lbs. (See NOTE 1) 
Minimum Crew Day VFR operations - (1) pilot 
All other operations - See POH/AFM. 
Number of Seats 21 seats 
Crew (+19), passenger variable 
See loading instructions for passenger loading. 
Maximum Baggage 529 lbs. (+417.0) or , as optional 705 lbs.  (+409.0) 
(per EMBRAER Drawing 110P1-856-10) 
Fuel Capacity 454 gallons (227 gallons each tank) (+283.5) 
Unusable fuel 7.4 gallons (3.7 gallons, each tank) 
Oil Capacity 9.2 quarts in each engine (+226.4) 
1 quart in each oil radiator (+226.0) 
Max. Operating Altitude 25,000 ft. 
Temperature Operating Limits Maximum 43° C or ISA + 40° C, whichever is lower 
Minimum -50° C 
DATA PERTINENT TO ALL MODELS 
Datum 269.68 in. forward of the 28% wing chord line (frame 16). 
The 28% wing chord line is 37.13 in. forward of the rear jack points. 
Leveling Means Plumb from the support in the upper internal part of frame 16 using as reference a mark 
on the floor. 
Control Surface Movements Elevator 22° ± 1° Up 
20° ± 1° Down 
Rudder 25° ± 1° Left 
25° ± 1° Right 
Aileron 22° ± 1° Up 
14° ± 1° Down 
Flap 38° ± 1° Down 
Elevator Tab ± 1° 
Left Tab 32° ± 2° Up and Down

A21SO 
Page 5 
Right Tab fixed (non-operational) 
Aileron 
Tab (left): 
Manual 18° ± 3° Up and Down 
       Automatic 
         Aileron Up 22° 
Aileron Tab Up 16° ± 2° (anti servo) 
         Aileron Down 14° 
Aileron Tab Down 8° ± 2° (anti-servo) 
Rudder 
Tab 
Manual Right 12° ± 2° 
Left 11° ± 2° 
       Automatic 
Rudder Right 25° - rudder 
Tab 12° ± 1° Left (servo) 
Rudder Left 25° - rudder tab 
4.5° ± 1° Left (anti-servo) 
Serial Numbers Eligible A Brazilian Certificate of Airworthiness for Export endorsed as noted under "Import 
Requirements" must be submitted for each individual aircraft for which application for 
U.S. certification is made. 
Import Requirements An FAA Standard Airworthiness Certificate may be issued on the basis of a Brazilian 
Certificate of Airworthiness for Export signed by a representative of the Agência 
Nacional de Aviação Civil (ANAC) of Brazil, formerly the Centro Tecnico Aeroespacial 
(CTA) of Brazil, containing the following statement:  "The airplane covered by the 
certificate has been examined, tested, and found to conform to the type design approved 
under Type Certificate No. A21SO and to be in condition for safe operation." 
(See NOTE 6). 
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. 
Certification Basis The EMB-110P1 was certificated showing compliance with: 
FAR 23 through Amendment 7, effective September 14, 1969, FAR 23.1529, 
Amendment 8, effective February 5, 1970:  FAR 23.1441 through 23.1449, 
Amendment 9, effective June 17, 1970; FAR 23.1351(c)(4), Amendment 14, effective 
December 20, 1973; FAR 23.977, Amendment 17, effective February 1, 1977; FAR 
23.785, Amendment 19, effective July 18, 1977; FAR 23.49, 23.65, 23.67, 23.77, and 
23.1581 through 23.1589, Amendment 21, effective March 1, 1978; Equivalent safety 
level for FAR 23.1545(a) (Air Speed Indicator Marked in IAS); FAR 25.1439; Basic, 
effective December 24, 1964; FAR 25.787, 25.853., 25.855, 25.857, Amendment 32, 
effective May 1, 1972; (FAR 25 requirements for all cargo operations only) SFAR 27 
through Amendment 1, effective January 1, 1975; FAR 36 through Amendment 6, 
effective June 24, 1977, FAR 135, Appendix A, effective June 19, 1970. 
Compliance has been shown with the ice protection requirements of FAR 23.1419, 
Amendment 23-14, effective December 20, 1973. 
Service Bulletins are approved by the ANAC.  This approval is considered FAA 
approval. (This approval pertains to the design data only). 
Date of application for EMB-110P1; June 22, 1978.  Type Certificate No. A21SO issued 
August 18, 1978.

A21SO 
Page 6 
Date of application for EMB-110P2 is March 22, 1977. T.C. A21SO amended to include 
P2. 
The EMB-110P2 was certificated showing compliance with the same regulations as 
EMB-110P1, except FAR 25.1439 and 25.857, which are applicable to cargo 
configurations only. 
Certain models of the EMB-110P1 and EMB-110P2 also comply with SFAR 41A, 
effective April 14, 1980. See NOTE 5. 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification. 
The "Basic Equipment Checklist," "Chart A," lists all the required and optional 
equipment and is included in the POH and ANAC approved AFM. 
Notes 
NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight and 
loading instructions must be provided for each aircraft at the time of original certification.  The certificated 
empty weight and corresponding center-of-gravity location must include system (undrainable) oil (not 
included in oil capacity) and unusable fuel (not included in usable fuel) as follows: 
Fuel 93 lbs. at (+285.8) 
Oil 1.1 lbs. at (+226.4) 
NOTE 2. All placards required in the Pilots Operating Handbook and ANAC Approved Airplane Flight Manual must 
be installed in the appropriate locations. 
The following Pilot's Operating Handbook and ANAC Approved Airplane Flight Manual is required:  
EMBRAER Publication No. TP-110P1/176, dated August 18, 1978 (with appropriate revisions). 
In addition, for those aircraft which have been approved for operation at increased weights permitted by 
SFAR 41A, a placard must be installed in the cockpit, in clear view of the pilot, which reads as follows: 
"THIS AIRPLANE IS APPROVED IN ACCORDANCE WITH SFAR 41A FOR MAXIMUM  
  TAKEOFF WEIGHT OF 13,007 LBS. AND MAXIMUM LANDING WEIGHT OF 12,566 LBS." 
NOTE 3. The service life limits of the main structural parts are listed in the EMBRAER Maintenance Planning Guide, 
T.P. 110P2/145. These are summarized below: 
Wing and wing carry-through structure - 30,000 hours 
Front spar, lower boom to fuselage attachments (P/N's 4A-2111.00.03, 4A-2111.00.04, 4A-1231.50.04, 
4A-1231.50.06) - 17,000 hours 
Engine mount - 21,000 hours 
Main landing gear: Piston tube, P/N 14333: 
15,900 landings (for all models), or 
12,700 landings (for SFAR 41A aircraft - See NOTE 5), or 
As determined by the equation: 
N  = (15,900 - Nl)N1 + No 
15,900 
for aircraft modified per SB 110-32-047 (increase in maximum landing weight) or per SB 110-00-
003 (modifications to permit operation according to SFAR 41A) 
N = new life limit of the piston tube. 
Nl = accumulated landings of the piston tube at the date of modification 
No = 12,700 landings for SB 110-00-003, or 13,700 landings for SB 110-32-047 
Half drag strut, P/N 14284-A and 14334-A: 18,750 landings.

A21SO 
Page 7 
NOTE 4. If fuel conforming to specifications PWA522 or CPW46 is not available it is permissible to use aviation 
gasoline MIL-G-7752 of all grades for a total time period not exceeding 150 hours during any overhaul 
period. 
NOTE 5. Aircraft modified in accordance with EMBRAER Drawing Number 110-P1-9000, Rev. 1, or 
S.B. 110-00-003 comply with requirements of SFAR 41A, effective April 14, 1980.  For those aircraft, the 
following C. G. Ranges and Weights are applicable:   
C. G. Range For Landing: (+256. 9) to (+272.0) at 12,566 lbs. 
(Landing Gear (+255.0) to (+272.0) at 12,015 lbs. 
Extended) (+251.3) to (+272.0) at 8,818 lbs. or less 
Straight line variation between points given. 
For Takeoff: (+257.8) to (+272.0) at 13,007 lbs. 
(+256.9) to (+272.0) at 12,566 lbs. 
(+255.6) to (+272.0) at 12,566 lbs. 
(+251.3) to (+272.0) at 8818 lbs. or less 
Straight line variation between points given. 
Moment change due to retraction of landing gear: 10068 in lbs. 
  (The CG is shifted forward with retraction of the landing gear). 
Empty Weight CG Range None 
Maximum Weight Ta keoff:  13,007 lbs. 
Landing: 12,566 lbs. 
Zero Fuel: 12,015 lbs. 
(See NOTE 1) 
Ramp 13,073 lbs. 
NOTE 6. The airworthiness certificate on those aircraft wh ich have been approved for operation at increased weights 
as permitted by SFAR 41A shall be endorsed as follows: 
"This airplane at weights in excess of 5,700 kg does not meet the 
airworthiness requirements of ICAO, as prescribed by Annex 8 of the  
Convention of International Civil Aviation." 
NOTE 7. For cargo version operation, Model EMB-110P1 must be equipped with: 
- Cargo net for 9 g (EMBRAER Drawing 110P1-9878-10-01). 
- Anti-smoke curtain (EMBRAER Drawing 110P1-9878-10-15). 
- Smoke detection system (EMBRAER Drawing 110P1-9788-10-01). 
- Protective breathing system and full face oxygen masks (EMBRAER Drawing 110P1-710-10). 
- Retention cargo net ( 3 g). 
NOTE 8. Models EMB-110P1 and EMB- 110P2 may increase the maximum landing weight to 12,500 lbs. if modified 
in accordance with EMBRAER SB 110-32-047. 
The following C.G. range is applicable. 
C. G. Range For Landing: (+256. 5) to (+272.0) at 12,500 lbs. 
(Landing Gear (+255.0) to (+272.0) at 12,015 lbs. 
Extended) (+251.3) to (+272.0) at 8,818 lbs. or less 
For Takeoff: (+255.6) to (+272.0) at 12,500 lbs. 
(+251.3) to (+272.0) at 8,818 lbs. or less 
Straight line variation between points given. 
NOTE 9. Cargo version must be maintained in accordance w ith the original certification requirements of a 10 or more 
passenger aircraft. 
....END....
```

## ADs (33, in force first)

- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2014-20-05](https://openairdocs.org/ad/2014-20-05): Flight Controls · Embraer EMB-110P1 and EMB-110P2. Effective Oct 27, 2014
- [AD 2008-23-12](https://openairdocs.org/ad/2008-23-12): Wings-to-fuselage attachments · Embraer EMB-110P1 and EMB-110P2. Effective Dec 22, 2008
- [AD 2005-19-02](https://openairdocs.org/ad/2005-19-02): Nose landing gear (NLG) · Embraer EMB-110P1 and EMB-110P2. Effective Oct 19, 2005
- [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005
- [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 2000-02-27](https://openairdocs.org/ad/2000-02-27): Airframe Pneumatic Deicing Boots · Embraer EMB-110P1 and EMB-110P2. Effective Mar 24, 2000
- [AD 98-01-10](https://openairdocs.org/ad/98-01-10): MLG Wheel Axle/ Piston Tube Assembly · Embraer EMB-110P1 and EMB-110P2. Effective Feb 9, 1998
- [AD 97-26-13](https://openairdocs.org/ad/97-26-13): AFM - Limitation Section - Power Levers · Embraer EMB-110P1 and EMB-110P2. Effective Jan 28, 1998
- [AD 97-01-12](https://openairdocs.org/ad/97-01-12): Ground Proximity Warning System · Airtell International Ground Proximity Warning System, Mystere-Falcon 200, EMB-110P1 and 20 more. Effective Feb 25, 1997
- [AD 96-09-12](https://openairdocs.org/ad/96-09-12): AFM - Icing · Embraer EMB-110P1 and EMB-110P2. Effective Jun 11, 1996
- [AD 92-17-02](https://openairdocs.org/ad/92-17-02): Rudder Trim Tab Actuating System · Embraer EMB-110P1 and EMB-110P2. Effective Sep 11, 1992
- [AD 91-25-11](https://openairdocs.org/ad/91-25-11): Rudder Trim Tab System · Embraer EMB-110P1 and EMB-110P2. Effective Feb 10, 1992
- [AD 91-25-09](https://openairdocs.org/ad/91-25-09): Elevator Trim Tab Actuator Support · Embraer EMB-110P1 and EMB-110P2. Effective Dec 23, 1991
- [AD 90-12-01](https://openairdocs.org/ad/90-12-01): Elevator Balance Weight Arms · Embraer EMB-110P1 and EMB-110P2. Effective Oct 15, 1990
- [AD 89-20-11](https://openairdocs.org/ad/89-20-11): AFM Change - Emergency Exit · Embraer EMB-110P1 and EMB-110P2. Effective Oct 24, 1989
- [AD 88-25-10](https://openairdocs.org/ad/88-25-10): Flap Control Switch · Embraer EMB-110P1 and EMB-110P2. Effective Jan 5, 1989
- [AD 87-13-08](https://openairdocs.org/ad/87-13-08): Airplane Flight Manual/Pilot's Operating Handbook Changes · Embraer EMB-110P1 and EMB-110P2. Effective Aug 6, 1987
- [AD 87-01-05](https://openairdocs.org/ad/87-01-05): Bearings - Flight Control Systems · Embraer EMB-110P1 and EMB-110P2. Effective Jan 22, 1987
- [AD 85-17-04](https://openairdocs.org/ad/85-17-04): Elevator Control Rod Tube · Embraer EMB-110P1 and EMB-110P2. Effective Aug 30, 1985
- [AD 85-01-51](https://openairdocs.org/ad/85-01-51): Empennage Assembly · Embraer EMB-110P1 and EMB-110P2. Effective Feb 26, 1985
- [AD 84-24-53 R1](https://openairdocs.org/ad/84-24-53-R1): Empennage Assembly · Embraer EMB-110P1 and EMB-110P2. Effective Jan 17, 1985
- [AD 82-05-01 R2](https://openairdocs.org/ad/82-05-01-R2): Wing Flap Actuators · Embraer EMB-110P1 and EMB-110P2. Effective Oct 26, 1983
- [AD 83-15-10](https://openairdocs.org/ad/83-15-10): Control Surface Balance · Embraer EMB-110P1 and EMB-110P2. Effective Aug 9, 1983
- [AD 83-14-09](https://openairdocs.org/ad/83-14-09): Rivet Attachments · Embraer EMB-110P1 and EMB-110P2. Effective Jul 27, 1983
- [AD 83-04-03 R1](https://openairdocs.org/ad/83-04-03-R1): Control Wheel Failure · Embraer EMB-110P1 and EMB-110P2. Effective Apr 25, 1983
- [AD 79-04-03 R2](https://openairdocs.org/ad/79-04-03-R2): Landing Gear · Embraer EMB-110P1 and EMB-110P2. Effective Feb 7, 1983
- [AD 82-27-09](https://openairdocs.org/ad/82-27-09): Primary Flight Control Cables · Embraer EMB-110P1 and EMB-110P2. Effective Jan 10, 1983
- [AD 82-20-02](https://openairdocs.org/ad/82-20-02): Icing Conditions · Embraer EMB-110P1 and EMB-110P2. Effective Sep 30, 1982
- [AD 82-18-01](https://openairdocs.org/ad/82-18-01): Water In Fuel Tank · Embraer EMB-110P1 and EMB-110P2. Effective Sep 27, 1982
- [AD 81-14-01](https://openairdocs.org/ad/81-14-01): Rudder Upper Hinge Support · Embraer EMB-110P1 and EMB-110P2. Effective Jul 1, 1981
- [AD 79-10-11](https://openairdocs.org/ad/79-10-11): Flight Control Rods · Embraer EMB-110P1 and EMB-110P2. Effective Dec 19, 1979
- [AD 79-24-05](https://openairdocs.org/ad/79-24-05): Wing Flap Supports · Embraer EMB-110P1 and EMB-110P2. Effective Nov 21, 1979

## Registered aircraft by registry model (OpenAirDocs)

- [Embraer EMB-110P1](https://openairdocs.org/model/embraer-emb-110p1): 13 aircraft (registry code 3260122)
- [Embraer EMB-110P2](https://openairdocs.org/model/embraer-emb-110p2): 0 aircraft (registry code 3260124)

## STCs approved under this data sheet (76, first 50)

- [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 SA00039BO](https://openairdocs.org/stc/SA00039BO): Incorporation of cockpit panel modifications to support single pilot operations without an autopilot. Ameriflight LLC
- [STC SA00132BO](https://openairdocs.org/stc/SA00132BO): Removal of right side windshield heating element. Ameriflight LLC
- [STC SA00405BO](https://openairdocs.org/stc/SA00405BO): De-modification of SFAR 41A compliance. Ameriflight LLC
- [STC SA00517NY](https://openairdocs.org/stc/SA00517NY): Modification of air conditioning system.. Ameriflight LLC
- [STC SA01184AT](https://openairdocs.org/stc/SA01184AT): Remove passenger windows and overwing exits and replace with plugs.  Modify airstair steps. Ameriflight LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA814GL](https://openairdocs.org/stc/SA814GL): Installation of nose wheel.. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA02075SE](https://openairdocs.org/stc/SA02075SE): Installation of a Mid-Continent MD835( ) Lithium Ion Battery. Mid-Continent Instrument Co. Inc.
- [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS
- [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 SA04330NY](https://openairdocs.org/stc/SA04330NY): Installation of Pitot Heat Failure Warning System. Kenn Borek Air Limited
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies 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 SA03973NY](https://openairdocs.org/stc/SA03973NY): Replacement of existing TCAS 7.0 by TCAS 7.1. Scandinavian Avionics Design ApS
- [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 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 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 SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc
- [STC SA1330GL](https://openairdocs.org/stc/SA1330GL): Revert to Normal Category (14 CFR 23) aircraft vice SFAR 41A by modifying the aircraft. American Eagle Airlines, 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 SA178NE](https://openairdocs.org/stc/SA178NE): Remove existing starter-generator and install Aircraft Parts starter generator.. Skurka Aerospace Inc.
- [STC ST02540AT-D](https://openairdocs.org/stc/ST02540AT-D): Installation of replacement fuel tank sealant system. FFC Manufacturing
- [STC SA01473SE](https://openairdocs.org/stc/SA01473SE): Installation of a GTX 32 (mode C), GTX 33 (mode S), or GTX 33D (mode S with diversity) Remote Transponde. Garmin AT Inc.
- [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc.
- [STC SP00400SE](https://openairdocs.org/stc/SP00400SE): Installation of various propeller electrical de-icer models. SMR Technologies
- [STC ST01468CH](https://openairdocs.org/stc/ST01468CH): Installation of various SMR Technologies electrical propeller deicer models.. SMR Technologies
- [STC SA01046CH](https://openairdocs.org/stc/SA01046CH): Installation of SMR Technologies engine inlet anti-icer models.. SMR Technologies Inc
- [STC SA01487SE](https://openairdocs.org/stc/SA01487SE): Installation of a GDL 69 or GDL 69A XM Satellite Receiver in accordance with Garmin Supplemental Type Certificate Master Data List, P/N 005-C0217-00, Revision A, dated December 20, 2004, or later FAA approved revision.. Garmin AT Inc.
- [STC SA4381NM](https://openairdocs.org/stc/SA4381NM): Installation of Cockpit Sun Visor.. Rosen Sunvisor Systems LLC
- [STC SA02154AK](https://openairdocs.org/stc/SA02154AK): Installation of the UPS Aviation Technologies Inc. Apollo MX20 multi-function display, P/N 430-0270-500.. Garmin AT Inc.
- [STC SA02217AK](https://openairdocs.org/stc/SA02217AK): Installation of Garmin AT Model GDL90 UAT Data Link System, in accordance with Garmin AT, Inc., GDL 90 UAT Master Data List, P/N 560-0278-01, Revision A, dated November 12, 2004, or later FAA approved revision.. Garmin AT Inc.
- [STC SA4962NM](https://openairdocs.org/stc/SA4962NM): Installation of a NSA sunvisor system for the pilot and copilot.. Rosen Sunvisor Systems LLC
- [STC SA00823CH](https://openairdocs.org/stc/SA00823CH): Installation of various de-icer wire harnesses.. SMR Technologies
- [STC SA00694SE](https://openairdocs.org/stc/SA00694SE): Replacement of certain BF Goodrich pneumatic deicer boots.. SMR Technologies
- [STC SA812NE](https://openairdocs.org/stc/SA812NE): Installation of BF Goodrich Model 6975-1 De-Icer kit or BF Goodrich Model 6975-10 De-Icer kit.. BF Goodrich Aerospace
- [STC SA5576SW](https://openairdocs.org/stc/SA5576SW): Installation of tail floodlight system.. DeVore Aviation Corporation of America, a New Mexico Corporation
- [STC SA00883AT-D](https://openairdocs.org/stc/SA00883AT-D): Installation and operation of an AlliedSignal TCAS CAS 66A System installed.. Air Sunshine, Inc
- [STC ST01558AT](https://openairdocs.org/stc/ST01558AT): Installation of an AlliedSignal MK-VI Ground Proximity Warning System (GPWS).. Air Sunshine, Inc
- [STC SA00231DE](https://openairdocs.org/stc/SA00231DE): Reconfigure aircraft to a maximum seating of Nine (9) passengers.. Leading Edge Aviation Svcs
- [STC SA1167SO](https://openairdocs.org/stc/SA1167SO): Replace existing nickel-cadmium batteries with Teledyne Gill BB638/T series lead-acid battery.. Teledyne Battery Products
- [STC SA00884AT-D](https://openairdocs.org/stc/SA00884AT-D): Installation and operation of an AlliedSignal TCAS CAS 66A System.. East Coast Avionics, Inc
- [STC SA02020AK](https://openairdocs.org/stc/SA02020AK): Installation of ground proximity warning system.. Centaurus Systems, Inc
- [STC SA00634AT](https://openairdocs.org/stc/SA00634AT): Installation of Dayton-Granger dischargers.. Dayton-Granger, Inc.

All 76: https://openairdocs.org/tcds/A21SO/stcs.md

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