# TCDS A68EU: WSK PZL Mielec and OBR SK Mielec

- Type: Type certificate data sheet
- Status: Current
- Holder: WSK PZL Mielec and OBR SK Mielec
- Revision: 1
- Revised: March 1, 2012
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23, Part 36
- Data sheet PDF: https://openairdocs.org/files/sha256/b4/a3/b4a38f8d246128959be140a301cd7cc1af1112acce32fb35d86a1fc51a198a40
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C9689018C346EAF8862579B30071BD1B.0001
- Page: https://openairdocs.org/tcds/A68EU

## Models (1)

As the data sheet lists them.

- PZL M20 03

## 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 
Rev. No. 1 - 1 - - 
  
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A68EU 
Revision 1 
WSK “PZL-MIELEC” 
OBR 
PZL M20 03 
March 1, 2012 
 
 
TYPE CERTIFICATE DATA SHEET NO. A68EU 
 
This data sheet, which is a part of Type Certificate No. A68EU 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: WSK PZL MIELEC and OBR SK MIELEC 
  U1. Wojska Polskiego 3 
  39-301 MIELEC 
  POLAND 
 
Type Certificate Ownership Record 
 
  (1)   This TC was considered not valid by the state of design on March 27, 2007, and has been replaced by 
European Aviation Safety Agency (EASA) Specific Airworthiness Specification (SAS) number 
EASA.SAS.A.064, issued March 27, 2007.  Only standard airworthiness certificates issued prior to 
March 1, 2012 are valid. 
 
(2)   Future unsafe conditions existing in the aircraft may result in the revocation of the airworthiness 
certificates of the aircraft if there is no entity to comply with 14 CFR § 21.99(a), “Required design 
changes.” 
(3)   Replacement parts may not be available in the future. 
 
I.  Model PZL M20 03 “MEWA” (Normal Category) Approved July 19, 1993 
 
 Aircraft manufactured from Polish-made  assemblies (fuselage, wings, empennage, landing gear, control systems), from  
 PA 34-200T SENECA II aircraft assemblie s (electro-navigation equipment, wing spar, accessories, hydraulic, - pneumatic,  
 heating - and ventilation systems), and power ed by L/TSIO 360 KB Continental engines. 
 
 Engines Teledyne Continental TSIO-360-KB (left side) 
  Teledyne Continental LTSIO-360-KB (right side) 
  with fuel injection, turbocharged. 
 
  Rotation as viewed from the rear: 
  TSIO-360-KB CW 
  L/TSIO-360-KB CCW 
 
 Fuel 100/100 LL minimum grade gasoline 
 
 Engine Limits Takeoff (5 minutes), 2800 RP M and 40 in.Hg. Manifold Pressure (220 HP) 
  Maximum continuous, 2600 RPM and 40 in .Hg. Manifold Pressure (200 HP)

A68EU 2 
 
 Propeller and 
   propeller limits Right Engine  Hartze ll Hub Model BHC-C2YF-2CLKUF, Blade Model 
      FJC 8459-8R, with Hartzell E-3-7L governor. 
  Left Engine  Hartzell Hub M odel BHC-C2YF-2CKUF, Blade Model 
      FC 8459 - 8R, Hartzell Governor Model E3-7 (or Model 
      E8-7L with synchrophasing system installed). 
 
  Pitch Setting at 30” of Propeller Diameter : 
  Low 12.9   0.2 High 80  to 81.5 
  Diameter:  Two blade (constant speed) not over 76 in., not under 75 in. 
 
 Airspeed Limits V NE - 195 Knots (CS) 
  V NO - 165 Knots (CAS) 
  V A - 138 Knots (CAS) for 4570 lbs weight 
   - 122 Knots (CAS) for 3068 lbs weight 
  V LE - 130 Knots (CAS) 
  V LO - 130 Knots (CAS) Landing Gear Extended 
   - 109 Knots (CAS) Landing Gear Retracted 
  V FE - 109 Knots (CAS) Flaps Deflected 40  
  V MC -   69 Knots (CAS) 
  Maneuvering speed (Va) is reduced as the airplane weight decreased 
  Straight line interpolation is used for intermediate weight. 
 Center of Gravity 
   (C.G.) Range (in) (+90.6) to (+94.6) at 4570 lbs 
  (+86.7) to (+94.6) at 4250 lbs 
  (  82.0) to (+94.6) at 3400 lbs 
  Straight line variation between points given. 
  Moment due to retracting landing gear (-32 in. lbs) 
 
 Empty Weight C.G. Range None 
 
 Datum 78.4 inches forward of wing leading edge at the inboard edge of the inboard fuel tank  
  (outboard of the engine), with the airp lane in leveling position and the landing gear  
  extended. 
 
 Leveling Means With airplane on scales, block main gear oleo pistons in the fully extended position.   
  Level airplane by deflating nose wheel tire (level point is a horizontal line between two  
  screws on left side of fu selage below pilot’s window). 
 
 Maximum Weight Takeoff  4570 lbs 
  Landing  4342 lbs 
  Zerofuel  4000 lbs 
  All weight over 4000 lbs. must be fuel. 
 
 Minimum Crew One (1) pilot 
 
 Number of Seats 7 (2 at + 85.5; 3 at + 118.1; 2 at + 157.6) 
  6 (2 at + 85.5; 2* at + 119.1; 2 at + 157.6) 
  5**(2 at + 85.5; 1 at 119.9 (1 patient or 1 incubator on a stretcher at +133.8) 
 
  * Optional equipment - Club Seats 
  ** Allowable loading condition with the airplane in ambulance version. 
 
 Maximum Baggage 200 lb. (100 lb at +22.5, 100 lb at +178.7) 
 
 Fuel Capacity 98 gal. (2 wing tanks) at +93.6 (93 gal. usable) 
  Optional Installation:  128 gal. (2 wing tanks) at +93.6 (123 gal. usable) 
  See NOTE 1 on fuel system. 
 
 Oil Capacity 8 qts. per engine  (5 qts. per engine usable) 
  See NOTE 1 for additional data on oil system.

3 A68EU 
 
 
 Maximum Operating Altitude 25,000 feet 
 
 Control Surface Movements 
Ailerons Up 35  2 
 Down 20  2 
Stabilator Up 12.5  0 -1 
 Down   7.5  1 
Stabilator Trim Tab Up   6.5  1 
(Stabilator Neutral)*** Down 10.5  1 
Rudder Left 35  1 
 Right 35  1 
Rudder Trim Tab Left 25  1 
(Rudder in Neutrum) Right 25  1 
Wing Flaps Cruise   0  2 
 Landing 40  2 
Nose Wheel Travel Left 27  1 
 Right 27  1 
 
  ***Stabilator is in neutral position when its chord is parallel to the front seat 
   track upper position 
 
 Serial Numbers Eligible 1AH002-07 and up. 
 
  The General Inspectorate of Civil Aviation (G ICA) Certificate of Airworthiness endorsed  
  as noted below under “Import Requirement s” must be submitted for each individual  
  aircraft, for which application fo r airworthiness certification is made. 
 
Only those aircraft serials holding a standard airworthiness certificate issued prior to 
March 1, 2012 are eligible. 
 
 Import Requirements None elig ible after March 1, 2012.   
 
  Previous to this date: 
 
  A Standard Airworthiness Certificate may be issued on the basis of a Certificate of  
  Airworthiness for Export signed by a repres entative of General Inspectorate of Civil  
  Aviation (GICA) containing the following stat ement:  “The airplane covered by this  
  certificate has been examined, tested and found to conform to the type design approved  
  under Type Certificate No. A68EU a nd is in condition for safe operation.” 
 
 Certification Basis FAR Part 23 e ffective 2-1-65, amended as follows: 
  -Subparts A, B through Amendm ent 23-18 effective May 2, 1977; 
  -Subpart C through Amendment 23-18 (e xcept 23.507 and 23.509 amended through  
   Amendment 23-6 effective August 1, 1967); 
  -Subpart D through Amendment 23-18 (ex cept 23.785 amended through Amendment 23-32  
   effective December 12, 1985); 
  -Subpart E through Amendment 23-6 (except 23.901, 23.909, 23.959, 23.1041, 23.1043,  23.1047,  
   and 23.1143, amended through Amendmen t 23-7 effective September 14,  1969); 
  -Subpart F through Amendment 23-6 (ex cept 23.1305 amended through Amendment 23-7  
   effective September 14, 1969, 23.1323 amende d through Amendment 23-18 effective May 2,  
   1977, 23.1419 amended through Amendment 23-14 effective December 20, 1973, and  
   23.1441 amended through Amendmen t 23-9 effective June 17, 1970); 
  -Subpart G through Amendment 23-18 (excep t 23.1545 (a) amended through Amendment 23-23  
   effective December 1, 1978, and 23.1529 amended through Amendment 23-26 effective  
   October 14, 1980). 
 
  FAR Part 36 effective December 1, 1969, thr ough Amendment 36-20 effective  September 16, 1992.

A68EU 4 
 
 Validation Basis Type Certificate A68E U was issued pursuant to FAR 21.29(a) in validation of General Inspectorate  
  of Civil Aviation (GICA) certification of comp liance when aforementioned Certification Basis. 
 
 Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (see  
  Certification Basis) must be installed in the airc raft for standard airworthiness certification.  In  
  addition, the following items of equipment are required. 
 
  1. Icing protection equipment as sp ecified by manufacturer’s Dwg. No. 37700. 
  2. Model PZL M20 “MEWA” - GICA approve d Airplane Flight Manual Ref. PZL Report  
   M2003/OLP-5/002/88/FAA, dated May 20, 1993, or later GICA approved revision. 
 
NOTE 1. Current weight and balance report including list of  equipment is certificated empty weight, and loading  
  instructions, must be provided for each aircraft at the time of original airworthiness certification. 
 
  The certificated empty weight and corresponding cente r-of-gravity positions must include undrainable oil  
  and unusable fuel as noted below: 
 
  Fuel  30.0 lbs at (+103.0) 
  Oil  12.0 lbs at (+  43.7) 
 
NOTE 2. Required Placards (Refer to Manufacturer’s Specifications for contents): 
 
  (1) The following placard must be lo cated in clear view of the pilot: 
    On side to left of pilot: 
     Limitations 
 
  This airplane must be operated as a normal categor y airplane in compliance with the operating limitations  
  stated in the form of placards, markings, and manuals.  No acrobatic maneuvers (including spins) approved. 
 
  This aircraft approved for VFR, IFR, day, night a nd icing flight when equipped in accordance with FAR 91  
  or FAR 135.  Minimum single engine control speed 66 KIAS. 
  Single engine stalls not permitted. 
  Can cause 500 ft. loss of altitude and 15  pitch angle. 
 
  In addition, all placards required in the approved airplane  flight manual  must be installed in the appropriate  
  location. 
 
  Each individual airplane will be supplied with a placard that specifies the kinds of operation such as VFR, or  
  IFR, DAY or NIGHT, to which the operation of the airplane is limited by the equipment installed. 
 
  (2) Maximum Weight 
  (3) Maneuver Speed 
  (4) Demonstrated Crossword Component 
  (5) Information 
  (6) Flight with Doors Removed 
  (7) Emergency Gear Extension 
  (8) Door Latch 
  (9) Door Release 
  (10) Maximum Baggage (2) 
  (11) Takeoff Checklist 
  (12) Landing Checklist 
  (13) Smoking 
  (14) Storm Window Airspeed 
  (15) Icing Conditions (if applicable) 
  (16) Windshield Heat 
  (17) Pitot Heat 
  (18) Oil Cooler (2) 
  (19) Prop Sync. 
  (20) Table 
  (21) RPM Limits (2) 
  (22) Fire Extinguisher

5 A68EU 
 
  (23) Heating/Ventilation Controls 
  (24) Fuel 
  (25) Flap Step 
   
NOTE 3. Instructions for continued airworthiness are cont ained in Section 3, PZL M-20 MEWA Maintenance Manual  
  (dated December 15, 1992).  Revisions to Airw orthiness Limitations must be FAA approved. 
 
 
 
...END...
```

## ADs (2, in force first)

- [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022
- [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

## STCs approved under this data sheet (58, first 50)

- [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [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 SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [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 SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications 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 SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King)
- [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc.
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [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 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 2](https://openairdocs.org/stc/SA02153LA-D%20PAGE%202): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc.
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [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 2](https://openairdocs.org/stc/SA00352BO%20PAGE%202): 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 2](https://openairdocs.org/stc/SA02119SE%20PAGE%202): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc
- [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 2](https://openairdocs.org/stc/SA02442AK%20PAGE%202): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC
- [STC SA01933LA-D PAGE 2](https://openairdocs.org/stc/SA01933LA-D%20PAGE%202): 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 SA02717NY PAGE 1](https://openairdocs.org/stc/SA02717NY%20PAGE%201): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC
- [STC SA02015SE-D](https://openairdocs.org/stc/SA02015SE-D): Installation of Garmin G500 Primary Flight Display (PFD) and Multifunction Display (MFD) System.. 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 SA02016SE-D](https://openairdocs.org/stc/SA02016SE-D): Installation of Garmin GTS 800, GTS 820 or GTS 850 Traffic System. Garmin International Inc
- [STC SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc
- [STC SA02018SE-D](https://openairdocs.org/stc/SA02018SE-D): Provisions installation of Garmin GPS/XM Antennas in accordance with FAA Approved Model List (AML) SA02018SE-D, dated January 4, 2011, or later FAA approved revision, and FAA Approved GPS/XM Antenna STC Master Drawing List, Document No.: 005-00638-01, Revision 1 , approved on January 4, 2011, or later FAA approved revision.. Garmin International Inc
- [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc.
- [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC
- [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 SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc.
- [STC SA01681SE](https://openairdocs.org/stc/SA01681SE): Installation of vortex generators on the wings, horizontal and vertical tail surfaces (all models), and an increase in maximum zero fuel weight (PA-34-200T and PZL M20 03 only).. Micro AeroDynamics 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 SA01157LA](https://openairdocs.org/stc/SA01157LA): Installation of Electronics International Model FP-5 or FP-5L fuel flow/fuel pressure instrument as a replacement instrument.. Electronics International Inc.
- [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.

All 58: https://openairdocs.org/tcds/A68EU/stcs.md

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