# TCDS G24EU: Blanik Aircraft CZ s.r.o.

- Type: Type certificate data sheet
- Status: Current
- Holder: Blanik Aircraft CZ s.r.o.
- Revision: 12
- Revised: June 15, 2022
- Product: Aircraft, Glider
- Certification basis: Part 21
- Registered aircraft: 38, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/69/0f/690f3692b389c26f5db3cb5046d82f13ec0fa4a951459878e91cace5241b0c3c
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/979AFE3F561CC812862588630045CEFB.0001
- Page: https://openairdocs.org/tcds/G24EU

## Models (2)

As the data sheet lists them.

- Blanik L-13
- Blanik L-13 AC

## 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. 12 12 11 9 12 11 11 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
G24EU 
Revision 12 
Blanik Aircraft CZ 
L-13 BLANIK 
L-13 AC BLANIK 
June 15, 2022 
 
TYPE CERTIFICATE DATA SHEET NO.  G24EU 
 
This data sheet, which is a part of Type Certificate No. G24EU, 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 Blanik Aircraft CZ s.r.o. 
Karolinská 661/4 
186 00 Praha 8 
Czech Republic 
 
Type Certificate Holder Record BLANIK LIMITED transferred TC G24EU to Blanik Aircraft CZ s.r.o. on January 10, 
2017. 
 
Aircraft Industries a.s. transferred TC G24EU to BLANIK LIMITED on June 20, 2013. 
 
LETECKÉ ZÁVODY a.s. transferred TC G24EU to Aircraft Industries a.s. on September 
26, 2005. 
 
LET Aeronautical Works transferred TC G24 EU to LETECKÉ ZÁVODY a.s. on October 
15, 2002. 
 
I - Model L-13 "BLANIK" (Aerobatic Category) approved 10 November 1971 
 
 Airspeed Limits (I.A.S.) Vne (Never exceed) 136 knots (156 m.p.h.) 
Va (Maneuvering) 76 knots ( 87 m.p.h.) 
Vfe (Flaps Extended) 60 knots ( 69 m.p.h.) 
Airplane Tow 76 knots ( 87 m.p.h.) 
Auto-Winch Tow 65 knots ( 75 m.p.h.) 
Dive Brakes Extended 136 knots (156 m.p.h.) 
 
 C.G. Range +96.8 in. (+2458 mm) to +104.2 in.  (+2647 mm) at all weights. 
 
 Empty Weight C.G. Range None 
 
 Datum  Most forward point on fuselage nose. 
 
 Leveling Means Between points marked on side of fuselage. 
 
 Maximum Weight Acrobatic Category (1 occupant):   880 lb. 
Limited Acrobatic Category (2 occupants): 1100 lb. 
Cloud Flying (2 occupants): 1100 lb. 
 
 No. of Seats  2 (one at +43.7 in. (+1110 mm) and one at +87.8 in. (+2229 mm)). 
 
 Maximum Baggage 61 lb. +113.4 in. (+2880 mm). 
 
 Control Surface Movements Elevator Up: 32° + 1° 
 Down: 25° + 1° 
Rudder Right: 30° + 1° 
 Left: 30° + 1° 
Aileron Up: 34° + 1° 
 Down: 13° + 1°

G24EU Page 2 of 7 
 
 
Serial Nos. Eligible 173205, 173213, 173310, 173334, 173337, 173341, 173345, 173404, 173460, 173629,  
173630, 173901, 173920, 173921, 173922, 173924, 173928, 173930, 174130, 174215,  
174216, 174422, 174423, 174525, 174526, 174533, 174534, 174707, 174708, 174712,  
174713, 174714, 174715, 174805, 174806, 174811, 174812, 174930, 175001, 175002,  
175008, 175009 through 175230; 025301 and subsequent up to and i ncluding 027361. (See 
Note 4). 
 
 Import Requirements 1. For glider serial numbers 175008 and before, a U.S. Standard Airworthiness 
Certificate may be issued on the basis of an NAA Export Certificate of Airworthiness 
(Export C of A) signed by a representative of the Civil Aviation Authority of the Czech 
Republic (CAA-CZ) on b ehalf of the European Community  after the following have 
been accomplished: 
a. The glider must be modified in accordance with the list of modifications set  forth 
by LET Infor mation Bulletin No. L13/032, dated 16 December 1971 for  
conformity with the type design approved under Type Certificate G24EU,  except 
paragraph 1.5 tow hook guard, P/N SK -L13.320-01, need not be  installed and/or 
may be removed; and paragraph 1.6, pot pitot head (P/N L1301) need not be 
installed provided the original pitot head is installed and appropriate calibration 
pages are incorporated into the Flight Manual. (See NOTE 5). 
In addition - 
(i) Glider Serial Nos. 174800 and before must be modified in accor dance with 
LET Service Bulletin No.  L13/031, dated 22 December 1970 to improve the 
security of the wing attachment pins. 
(ii) Gliders, Serial Nos. 173404 and before must have the control rod eye -ends 
replaced in accordance with LET Service Bulletin L13/025 dated 23 January 
1967. 
b. All modifications accomplished subsequent to original production (other  than 
those associated with Item (a)) must be FAA-approved. 
c. The glider must be found to be in a condition for safe operation. 
 
2. For gliders Serial Nos. 175009 through 175230 and 025301 through 027361, The FAA 
can issue a U.S. airworthiness certificate based on an NAA Export C of A signed by a 
representative of the CAA-CZ on behalf of the European Community. The Export C 
of A should contain the following statement: ‘The aircraft covered by this certificate 
has been examined, tested, and found to comply with U.S. airworthiness regulations 
14 CFR  Federal Aviation Regulations Part 21.17(b) , U.S. Type Certificate No. 
G24EU and to be in a condition for safe operation.’  
 
3. 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 FAR 21.29 and FAR 21.23, effective 1 February 1965. 
 
British Civil Airworthiness Requirements, Section E, Issue 2, dated 16 May 1960 
(Czechoslovakian Certification Basis) were found to provide a level of safety equivalent 
to provisions of FAR 21.23 to enable certification under the provisions of FAR 21.29. 
 
Type Certificate No.  G24EU issued 10 November 1971. 
 
Date of Application for Type Certificate, 31 May 1971. 
 
The CAA-CZ originally type certificated this glider under its type certificate Number 2725-
59. The FAA validated this product under U.S. Type Certificate Number G24EU. Effective

Page 3 of 7 G24EU 
May 17, 2006, the European Aviation Safety Agency (EASA) began oversight of this 
product on behalf of the Czech Republic. The EASA TCDS number is EASA.A.024. 
 
 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations  (See 
Certification Basis) must be installed in the glider for standard airworthiness certification.  
In addition the following equipment must be installed: 
1. Instruments: 
(a) Airspeed indicator marked as follows: 
 Red Radial: 136 knots (156 m.p.h.) 
 Green arc: 136 knots – 33 knots (156 m.p.h. – 38 m.p.h.) 
 White arc:  60 knots  – 31 knots (69 m.p.h. – 36 m.p.h.) 
(b) Altimeter 
(c) Magnetic Compass 
2. "Pilot's Notes for the L-13 sailplane" (Flight Manual). 
 
 Service Information Each of the documents listed below must state that it is approved by the EASA or – for 
approvals made before May 17, 2006 – by the CAA-CZ.  
• Service bulletins,  
• Structural repair manuals,  
• Vendor manuals,  
• Aircraft flight manuals, and  
• Overhaul and maintenance manuals.  
 
The FAA accepts such documents and considers them FAA-approved for type design data 
only unless one of the following conditions exists: 
• The documents change the limitations, performance, or procedures of the FAA 
approved manuals.  
 
The FAA uses the post type validation procedures to approve these documents.  The FAA 
may delegate on case-by-case 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.  
 
NOTES 
 
NOTE 1. Current weight and balance report including list of equipment in certificated empty weight, and loading  
instructions when necessary, must be provided for each glider at the time of original airworthiness certification. 
 
NOTE 2. The following placards must be installed in full view of the pilot: 
(a) "THIS GLIDER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING 
LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS." 
(b) "Cloud flying: Permitted only when the following instruments are installed: 
• Airspeed indicator 
• Altimeter 
•  Turn and Bank 
•  Variometer 
• Compass” 
(c) "Acrobatic maneuvers including spins must be accomplished in accordance with the "Pilot's Notes" for the 
L-13 sailplanes." 
(d) "Night flying is prohibited." 
(e) Never exceed speed136 knots (156 m.p.h.) 
Maneuvering speed    76 knots ( 87 m.p.h.) 
Flaps extended speed   60 knots ( 69 m.p.h.) 
Airplanes tow speed   76 knots ( 87 m.p.h.) 
Auto-winch tow speed   65 knots ( 75 m.p.h.) 
Dive brakes extended 136 knots (156 m.p.h.) 
(f) "Maximum weight:

G24EU Page 4 of 7 
 
Cloud flying category (2 occupants) 1100 lb. 
Limited acrobatics (2 occupants) 1100 lb. 
Acrobatic category (1 occupant)    880 lb. 
 
C.G. Limits:  96.8 in. to 103.8 in. aft of datum - all weights." 
 
NOTE 3. Information essential for the proper maintenance, inspection, and repair of the glider is contained in the LET  
Document: "Technical Manual of the L-13 Sailplane." 
 
NOTE 4. Six digit serial numbers beginning with “17” precede serial numbers beginning with “02”. 
 
NOTE 5. All serial numbers subsequent to 175008 (See NOTE 4) may utilize exception noted in import requirements  for 
S/B L13/032.  See Let N.P. Operating Bulletin No. L13/038 on Pilots Notes. 
 
 
II - Model L-13 AC BLANIK (Aerobatic Category) approved August 25, 1999 and amended January 14, 2005 
 
Airspeed Limits (I.A.S.) VNE  Speed Limit versus Altitude 
With and without (w/o) wing tip extensions 
 Altitude [knots] Altitude  [km/h] 
 0 - 8200 ft 124  0 – 2500 m 230 
 10,000 ft 120  3000 m 223 
 13,000 ft 113  4000 m 209 
 16,500 ft 105  5000 m 195 
 20,000 ft 98  6000 m 182 
 23,000 ft 92  7000 m 170 
 26,000 ft 85  8000 m 158 
 30,000 ft 79  9000 m 147 
 
 [knots] [km/h] 
VA  (Maneuvering Speed) 
 w/o wing tip extensions 
 with wing tip extensions 
 
86 
81 
 
160 
150 
VRA  (Rough Air Speed) 
 w/o wing tip extensions 
 with wing tip extensions 
 
86 
81 
 
160 
150 
VW  (Winch Launch) 
 w/o wing tip extensions 
 with wing tip extensions 
 
65 
65 
 
120 
120 
VT  (Aero Tow Speed) 
 w/o wing tip extensions 
 with wing tip extensions 
 
81 
81 
 
150 
150 
VLO  (Max. Landing Gear Operating Speed) 
 w/o wing tip extensions 
 with wing tip extensions 
 
124 
124 
 
230 
230 
 
 Datum Wing leading edge at root rib 
 
 C.G. Range Forward limit:  5.63 in (143 mm) aft of datum 
Aft limit:  13.27 in (337 mm) aft of datum

Page 5 of 7 G24EU 
 Empty Weight C.G. Range  
 (measured from datum) w/o wing tip extensions: 27.32 ± 0.51 in (694 ± 13 mm) aft of datum 
With wing tip extensions:  25.67 ± 0.51 in (652 ± 13 mm) aft of datum 
 
 Leveling Means Fuselage leveling points are noted in the Maintenance Manual 
 
 Maximum Take-off Weight 
w/o wing tip extensions: 1100 lbs (500 kg) 
With wing tip extensions:  1125 lbs (510 kg) 
 
No. of Seats 2 
 
Maximum Baggage 22 lb (10 kg) 
 
 Control Surface Movements Elevator: Up 32° + 2° 
 Down 27° + 1° 
 
Rudder: Right 29° + 1° 
 Left 29° + 1° 
 
Aileron: Up 34° + 2° 
 Down 13° + 2° 
 
Balance Tab Up 20° + 1° 
(if installed,  Down 20° + 1° 
left aileron only) 
 
 Serial Nos. Eligible For the L-13 AC: 
S/N 988601, 988603, 008605, 008606, 028902 through 028905, and 029101. 
 
For the L-13 AC with aileron balance tab and option for wing extension: 
S/N 018901, 049102 and subsequent. 
 
 Import Requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of 
Airworthiness (Export C of A) signed by a representative of the Civil Aviation Authority of 
the Czech Republic (CAA-CZ) on behalf of the European Community. The Export C of A 
should contain the following statement: ‘The aircraft covered by this certificate has been 
examined, tested, and found to comply with U.S. airworthiness regulations 14 CFR  Federal 
Aviation Regulations Part 21.17(b) , U.S. Type Certificate No. G24EU and to be in a 
condition for safe operation.’  
 
FAA Type Certificate G24EU was issued pursuant to FAR 21.29 upon validation of the 
Czech Republic Civil Aviation Authority’s certification of compliance with the certification 
basis, and in accordance with the standard airworthiness certificate provisions of FAR 
21.183(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. 
 
 Certification Basis FAR 21.29, Amdt 21-68 effective September 10, 1990 
 
British Civil Airworthiness Requirements, Section E, Issue 2, dated June 6, 1966 
 
FAA Type Certificate No. G24EU Rev. 5, issued August 25, 1999 
 
JAR 22, Change 5, Appendix H: Flight Manual Requirements 
 
Date of application for type certification: March 11, 1998.

G24EU Page 6 of 7 
 
Date of application for amended type certification to include options for wing tip 
extensions and aileron balance tab: June 30, 2003 
 
The CAA-CZ originally type certificated this glider under its type certificate Number 2725-
59. The FAA validated this product under U.S. Type Certificate Number G24EU. Effective 
May 17, 2006, the European Aviation Safety Agency (EASA) began oversight of this 
product on behalf of the Czech Republic. The EASA TCDS number is EASA.A.024. 
 
 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations  (See 
Certification Basis) must be installed in the glider for standard airworthiness certification.  
 
Basic equipment and instruments: 
Day VFR: 
a) (2) Airspeed indicators with markings per Flight Manual 
b) (2) Altimeters 
c) (2) Accelerometers 
d) (1) Registration accelerometer (AMU-1B recording unit, required only for L-
13 AC series with aileron balance tab, S/N 018901, 049102 and subsequent) 
e) (2) Five-point safety harnesses (symmetrical)  
f) (2) Parachutes (aerobatic flights only) or Back Cushions (thickness approx. 
3.9 inches (10 cm) when compressed. 
Cloud flying (day):  
g) (2) Magnetic Compass 
h) (2) Vertical Speed Indicator 
i) (2) Turn and Bank Indicator 
j) Two-way radio communication system 
 
Tow Releases: 
1. Nose tow release mechanism model A 740210 N 
2. Nose tow release mechanism model “E 85”, LBA Data Sheet No. 60.230/1 
(optional) 
3. Safety tow release mechanism model “Europa G 88” (optional), LBA Data Sheet 
No. 60.230/2 
4. Side winch launch release mechanism models (optional): LN-0399 (left), LN-
0400 P (right) 
 
 Service Information Each of the documents listed below must state that it is approved by the EASA or – for 
approvals made before May 17, 2006 – by the CAA-CZ.  
• Service bulletins,  
• Structural repair manuals,  
• Vendor manuals,  
• Aircraft flight manuals, and  
• Overhaul and maintenance manuals.  
 
The FAA accepts such documents and considers them FAA-approved for type design data 
only unless one of the following conditions exists: 
• The documents change the limitations, performance, or procedures of the FAA 
approved manuals.  
 
The FAA uses the post type validation procedures to approve these documents.  The FAA 
may delegate on case-by-case 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.  
 
Available Documents for the L-13 AC BLANIK: 
1. CAA-CZ approved Flight Manual for sailplane model L -13 AC B LANIK, dated 
May 21, 2001. 
2. CAA-CZ approved Maintenance Manual for the L-13 AC BLANIK, original dated 
June 30, 1998 accompanied by all latest updates.

Page 7 of 7 G24EU 
3. Operating instruction for the TOST nose tow release mechanism model “E85”, 
dated March 1989 and LBA approved. 
4. Operating instructions for the TOST safety tow release mechanism model “Europa 
G 88”, dated February 1989 and LBA approved. 
 
NOTES 
 
NOTE 1. A current weight and balance report including a list of equipment included in the certificated empty weight, and 
loading instructions when necessary, must be provided for each glider at the time of original airworthiness 
certification. 
 
NOTE 2. The following placards must be installed in full view of the pilot: 
(a) "THIS GLIDER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING 
LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS." 
(b) "Night flying is prohibited." 
(c) For the aerobatic configuration: 
Aerobatic: the following maneuvers and associated entry speeds are permitted: 
 
Sailplane w/o Wing Tip Extensions 
Max. Gross Weight:  1100 lb 
Empty Weight (standard) 672 lb 
Solo Flights From Front Seat Only 
Approved Maneuvers and Entry Speeds 
 Solo Operation Dual Operation 
Loop 92 knots (170 km/hr) 97 knots (180 km/hr) 
½ Loop & ½ Roll 103-113 knots (190-210 km/hr) 103-113 knots (190-210 km/hr) 
½ Roll & ½ Loop 70 knots (140 km/hr) 81 knots (150 km/hr) 
Lazy Eight 97 knots (180 km/hr) 97 knots (180 km/hr) 
Chandelle (climb) 97-103 knots (180-190 km/hr) 97-103 knots (180-190 km/hr) 
Inverted Flight 70-76 knots (130-140 km/hr) 76-81 knots (140-150 km/hr) 
Slow Roll 92 knots (170 km/hr) 97 knots (180 km/hr) 
Spin 35 knots (65 km/hr) 35 knots (65 km/hr) 
Flick Roll 70 knots (130 km/hr) 70 knots (130 km/hr) 
Flick ½ Roll & ½ Loop 65 knots (120 km/hr) 65 knots (120 km/hr) 
Inverted Spin 49-51 knots (90-95 km/hr) 49-51 knots (90-95 km/hr) 
Steep Turn 92 knots (170 km/hr) 97 knots (180 km/hr) 
Stall Turn 97 knots (180 km/hr) 103 knots (190 km/hr) 
 
NOTE 3. Information essential for the proper maintenance, inspection, and repair of the glider is contained in the LET  
Maintenance Manual for the L-13 AC BLANIK, dated November 1998. 
 
NOTE 4. Major structural repairs must be accomplished in accordance with data that is approved by the FAA. 
 
...END...
```

## ADs (11, in force first)

- [AD 2016-11-13](https://openairdocs.org/ad/2016-11-13): Flight Controls · BLANIK Blanik L-13 and Blanik L-13 AC. Effective Jul 14, 2016
- [AD 2016-11-10](https://openairdocs.org/ad/2016-11-10): Fuselage · BLANIK Blanik L-13 and Blanik L-13 AC. Effective Jul 8, 2016
- [AD 2010-18-05](https://openairdocs.org/ad/2010-18-05): Wings · BLANIK Blanik L-13. Effective Aug 30, 2010
- [AD 2007-25-01](https://openairdocs.org/ad/2007-25-01): forward and aft control sticks · BLANIK Blanik L-13. Effective Jan 7, 2008
- [AD 2005-08-14](https://openairdocs.org/ad/2005-08-14): Original control bridge · BLANIK Blanik L-13 AC. Effective Jun 6, 2005
- [AD 78-23-14 R1](https://openairdocs.org/ad/78-23-14-R1): Tow Release System · BLANIK Blanik L-13 and Blanik L-13 AC. Effective Aug 17, 1984
- [AD 80-16-03](https://openairdocs.org/ad/80-16-03): Horizontal Stabilizer · BLANIK Blanik L-13 and Blanik L-13 AC. Effective Aug 11, 1980
- [AD 77-15-05](https://openairdocs.org/ad/77-15-05): Fin Top Ribs · BLANIK Blanik L-13 and Blanik L-13 AC. Effective Aug 4, 1977
- [AD 2010-14-15](https://openairdocs.org/ad/2010-14-15) (historical): Wings · Aircraft Industries a.s. Blanik L-13. Effective Jul 19, 2010
- [AD 2000-20-11](https://openairdocs.org/ad/2000-20-11) (historical): Tail-fuselage Hinge · Aircraft Industries a.s. Blanik L-13. Effective Nov 27, 2000
- [AD 99-19-33](https://openairdocs.org/ad/99-19-33) (historical): Elevator Drive Bellcrank · Aircraft Industries a.s. Blanik L-13. Effective Nov 8, 1999

## Registered aircraft by registry model (OpenAirDocs)

- [Let BLANIK L-13](https://openairdocs.org/model/let-blanik-l-13): 38 aircraft (registry code 1360306)

## STCs approved under this data sheet (11)

- [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SG03715NY](https://openairdocs.org/stc/SG03715NY): Iunstallation and maintenance of Oratex 6000 Covering and Coating System. Lanitz-Prena Folien Factory GmbH
- [STC SG04702NY](https://openairdocs.org/stc/SG04702NY): Installation and maintenance of Oratex UL600 Covering and Coating System. Lanitz-Prena Folien Factory GmbH
- [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc
- [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc.
- [STC SG01164CH](https://openairdocs.org/stc/SG01164CH): Install Cooper superflite 102 fabric.. Aviation Products Systems Inc.
- [STC SA1736GL](https://openairdocs.org/stc/SA1736GL): Install Cooper superflite 102 fabric.. Cooper Aviation Supply Company, Inc.
- [STC SG4309NM](https://openairdocs.org/stc/SG4309NM): Recover the flaps using large flange Pop Rivets (AD42ASLF) instead of wire lacing to secure the fabric to the leading edge structure.. Burt Donald M
- [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc
- [STC SG228NW](https://openairdocs.org/stc/SG228NW): Installation of an EZ 1-16 Blanik tail-wheel assembly.. Brown A/C Company
- [STC SG12WE](https://openairdocs.org/stc/SG12WE): Removal of canopy and rear control stick.. Deutsch Paul R

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