# TCDS A-813: Piaggio & C.

- Type: Type certificate data sheet
- Status: Current
- Holder: Piaggio & C.
- Revision: 4
- Revised: November 8, 1961
- Product: Aircraft, Small Airplane
- Certification basis: Part 3, CAR 10
- Registered aircraft: 8, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/d0/4c/d04ca867f34dc5f5f8823ff6dc7c3b344627f2c3d1f6db21fcb29623516866f0
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D443EEC7DF6E13808525673D00499C78.0001
- Page: https://openairdocs.org/tcds/A-813

## Models (3)

As the data sheet lists them.

- P.136-L
- P.136-L1
- P.136-L2

## 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. 4 4 4 4 4
FEDERAL AVIATION AGENCY
A-813
Revision 4
PIAGGIO
 P.136-L
P.136-L1
P.136-L2
November 8, 1961
AIRCRAFT SPECIFICATION NO. A-813
Type Certificate Holder Piaggio & C.
Genoa, Liguria, Italy
I - Model Piaggio P.136-L, 5 PCAmM (Utility Category)
Engines 2 Lycoming GO-435-C2B
Fuel Minimum grade 80/87 or 91/98
(with carburetor setting 10-3391-1)
Engine limits Maximum continuous 3000 rpm (240 bhp)
Maximum takeoff 3400 rpm (260 bhp)
Economy cruise 2600 rpm (160 bhp)
Propellers Type: P.1033/G3-S - 3-bladed (metal)
Pitch: Variable (constant speed control)
Diameter: 82-11/16 in. (m.2.10)
Airspeed limits Never exceed speed 249 mph (216 knots)  True Ind.
Max. structural cruising speed 165 mph (144 knots)  True Ind.
Maneuvering speed 163 mph (142 knots)  True Ind.
Max. gear & flap lowering speed 126 mph (109 knots)  True Ind.
Max. speed for 1/2 flap 150 mph (130 knots)  True Ind.
Min. control speed - the min.   90 mph ( 78 knots)  True Ind.
speed at which the airplane is
controllable in flight, with
sudden failure of one engine,
with takeoff power on the other engine.
C.G. range Forward: (+164) (m. 4.15)
Rear: (+176) (m. 4.46)
Maximum weight 5950 lbs. (2700 Kg.)
No. seats 2  (+75)  (m. 1.90)
3  (+110) (m. 2.80)
Maximum baggage See balance charts issued with each individual aircraft.
Fuel capacity 190 U.S. gal. (720 liters)
(Two tanks 95 U.S. gal. each) (+173) (m. 4.40)
Oil capacity Capacity of the sump 12 quarts each motor (+201) (m. 5.12)

A-813 2
I - Model Piaggio P.136-L    (cont'd)
Control surface movements Elevator Up 27° + 1° Down 17° + 1°
Elevator trim tab Up 14° + 0.30' Down 18° + 0.30'
Rudder Right 25° + 1° Left 25° + 1°
Rudder trim tab Right 16° + 0.30' Left 16° + 0.30'
Aileron Up 24° + 1° Down 20° + 1°
Flaps Down 45° + 1°
Stabilizer Fixed
Serial Nos. eligible The Registro Aeronautico Italiano (RAI) Certificate of Airworthiness for Export issued as
noted under "Certification basis" must be submitted for each individual aircraft for which
application for certification is made.
Required equipment 1. Piaggio P.136-L Airplane Flight Manual.
II - Model Piaggio P.136-L1, 5 PCAmM (Utility Category)
Engines 2 Lycoming GO-480-B, GO-480-B1B or GO-480-B1D
Fuel Minimum grade 80/87
Engine limits Maximum continuous 3000 rpm (260 bhp)
Maximum takeoff 3400 rpm (270 bhp)
Economy cruise 2600 rpm (165 bhp)
Propellers Type: Hartzell HC-83x20-2CL/L8433
Pitch: Variable (constant speed control) and feathering
Diameter:84 in. (No cutoff permitted for repairs)
Placard required:  "Avoid continuous operation on ground or on water between 1300
and 1650 rpm and between 2100 and 2500 rpm." 
Airspeed limits Never exceed speed 222 mph (194 knots)  True Ind.
Max. structural cruising speed 164 mph (143 knots)  True Ind.
Maneuvering speed 157 mph (137 knots)  True Ind.
Max. gear & flap lowering speed 126 mph (109 knots)  True Ind.
Max. speed for 1/2 flap 150 mph (130 knots)  True Ind.
Min. control speed - the min.   90 mph ( 78 knots)  True Ind.
speed at which the airplane is
controllable in flight, with
sudden failure of one engine,
with takeoff power on the other engine.
C.G. range Forward: (+164) (m. 4.15)
Rear: (+176) (m. 4.46)
Maximum weight 6000 lbs. (2720 Kg.)
No. seats 2 (+75)  (m. 1.90)
3 (+114) (m. 2.90)
 Maximum baggage See balance charts issued with each individual aircraft.
Fuel capacity 190 U.S. gal. (720 liters)
(Two tanks 95 U.S. gal. each) (+173) (m. 4.40)
Oil capacity Capacity of the sump 12 quarts each motor (+201) (m. 5.12)

3 A-813
II - Model Piaggio P.136-L1    (cont'd)
Control surface movements Elevator Up  27° + 1° Down 17° + 1°
Elevator trim tab Up 14° + 0.30' Down 18° + 0.30'
Rudder Right 25° + 1° Left 25° + 1°
Rudder trim tab Right 16° + 0.30' Left 16° + 0.30'
Aileron Up 24° + 1° Down 20° + 1°
Flaps Down 45° + 1°
Stabilizer Fixed
Serial Nos. eligible The Registro Aeronautico Italiano (RAI) Certificate of Airworthiness for Export issued
as noted under "Certification basis" must be submitted for each individual aircraft for
which application for certification is made.
Required equipment 1. Piaggio P.136-L1 Airplane Flight Manual.
III - Model Piaggio P.136-L2, 5 PCAmM (Normal Category) Approved March 7, 1957.
(Same as Model P.136-L1 except for increased gross weight, engine installation, addition of dorsal fin, redesigned oil system since
engine has dry sump instead of wet sump).
Engines 2 Lycoming GSO-A1A6
Fuel Minimum grade 100/130
Engine limits (Straight line manifold pressure variation with altitudes shown)
HP           RPM        MP          ALT
Takeoff 340 3400 48.0 S.L.
Takeoff 340 3400 44.5 8000
Maximum continuous 320 3200 45.0 S.L.
Maximum continuous 320 3200 43.0 7500
Propellers Type: Hartzell HC-83x20-2CL/L9333C - 3 bladed (metal)
Pitch: Variable (constant speed control and feathering)
Diameter: Max. 88 in., Min. allowable for repairs 87 in.
No further reduction permitted.
Airspeed limits Never exceed speed 212 mph (184 knots) True Ind
Max. structural cruising speed 167 mph (145 knots) True Ind
Maneuvering speed 154 mph (134 knots) True Ind
Max. flap lowering speed 129 mph (112 knots) True Ind
Max. gear extension and extended speed 161 mph (140 knots) True Ind  
Max. speed for 1/2 flap 150 mph (130 knots) True Ind
Min. control speed - the min.   90 mph ( 78 knots) True Ind
speed at which the airplane is
controllable in flight, with
sudden failure of one engine,
with takeoff power on the other engine.
C.G. range Forward: (+164) (m. 4.15)
Rear: (+176) (m. 4.46)
Maximum weight Landplane 6614 lbs.
Seaplane 6393 lbs.
No. seats 2 (+75)  (m. 1.90)
3 (+114) (m. 2.90)
 Maximum baggage See balance charts issued with each individual aircraft.

A-813 4
III - Model Piaggio P.136-L2     (cont'd).
Fuel capacity 190 U.S. gal. (720 liters)
(Two tanks 95 U.S. gal. each) (+173) (m. 4.40)
Oil capacity 8 gal. total (4 gal. each tank) (+189) (m.4.8)
Control surface movements Elevator Up 27° + 1° Down 18° + 1°
Elevator trim tab Up 14° + 1° Down 18° + 1°
Rudder Right 30° + 1° Left 30° + 1°
Rudder trim tab Right 20° + 1° Left 20° + 1°
Aileron Up 24° + 1° Down 19° + 1°
Flaps Down 45° + 1°
Stabilizer Fixed
Serial Nos. eligible The Registro Aeronautico Italiano (RAI) Certificate of Airworthiness for Export issued as
noted under "Certification basis" must be submitted for each individual aircraft for which
application for certification is made.
Required equipment 1. Piaggio P.136-L2 Airplane Flight Manual.
Specifications Pertinent to All Models
Datum Nose of aircraft
Leveling means Datum pads on frame No. 20 and datum pegs at the baggage door frame.
Certification basis CAR 10.  Type Certificate No. 813 issued August 15, 1955.
Each aircraft and any replacement parts manufactured in Italy must be
designated as "import" and clearly labeled as such in accordance with CAR 10.30.
A. U.S. Airworthiness Certificate may be issued on the basis of a
Certificate of Airworthiness for Export signed by a representative
of the Registro Aeronautico Italiano (RAI) containing the
following statement:
(Models P.136-L and P.136-L1) "The airplane covered by this
certificate has been examined and found to comply with U.S. Civil
Air Regulation - Part 3, published November 1, 1949 and conforms
to TC 813." or (Model P.136.L2) "The airplane covered by this
certificate has been examined and found to comply with U.S. Civil
Air Regulation - Part 3, dated November 1, 1949, including
Amendments 3-1 through 3-12, and conforms to TC 813."
NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading
instructions when necessary, must be in each aircraft at the time of original certification and at all times
thereafter (except in the case of air carrier operators having an approved weight control system).
NOTE 2. The following placards must be displayed in front and in clear view of pilot:
A. For Model P.136-L:
(1) "This airplane must be operated as an utility category airplane in compliance with the
operating limitations specified in the Piaggio P.136-L Airplane Flight Manual."
(2) "Utility Category (5950 lbs.) Acrobatic maneuvers including spins not approved."
B. For Model P.136-L1:
(1) "This airplane must be operated as an utility category airplane in compliance with the
operating limitations specified in the Piaggio P.136-L1 Airplane Flight Manual."
(2) "Utility Category (6000 lbs.) Acrobatic maneuvers including spins not approved."
C. For Model P.136-L2:
(1) "This airplane must be operated as a normal category airplane in compliance with the
operating limitations specified in the Piaggio P.136-L2 Airplane Flight Manual."
(2) "Normal Category (6614 lbs.) Acrobatic maneuvers including spins not approved."

5 A-813
NOTE 3. These aircraft must be serviced and maintained in conformance with instructions contained in the
publication listed below:
A. Model P.136-L
(1) Piaggio P.136-L Maintenance and Repair Manual.
(2) Lycoming GO-435-C2B Operation, Maintenance and Overhaul Manual.
(3) Piaggio three-bladed Operation, Maintenance and Overhaul Manual.
B. Model P.136-L1
(1) Piaggio P.136-L1 Maintenance and Repair Manual.
(2) Lycoming GO-480-B Operation, Maintenance and Overhaul Manual.
(3) Hartzell Propeller Operation, Maintenance and Overhaul Manual.
C. Model P.136-L2
(1) Piaggio P.136-L2 Maintenance and Repair Manual.
(2) Lycoming GO-480-A1A6 Operation, Maintenance and Overhaul Manual.
(3) Hartzell Propeller Operation, Maintenance and Overhaul Manual.
.....END.....
```

## ADs (6, 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 61-26-03](https://openairdocs.org/ad/61-26-03): Fuel Vent Lines · Piaggio & C. P.136-L1 and P.136-L2. Effective Jan 16, 1962
- [AD 60-23-03](https://openairdocs.org/ad/60-23-03): Oil Lines · Piaggio & C. P.136-L2. Effective Dec 8, 1960
- [AD 58-17-04](https://openairdocs.org/ad/58-17-04): Water Rudder Modification · Piaggio & C. P.136-L1 and P.136-L2
- [AD 59-22-01](https://openairdocs.org/ad/59-22-01): Oil Breather Lines · Piaggio & C. P.136-L2
- [AD 59-23-01](https://openairdocs.org/ad/59-23-01): Water Rudder Cable Guard · Piaggio & C. P.136-L1 and P.136-L2

## Registered aircraft by registry model (OpenAirDocs)

- [Piaggio P.136-L1](https://openairdocs.org/model/piaggio-p-136-l1): 6 aircraft (registry code 6960104)
- [Piaggio P.136-L2](https://openairdocs.org/model/piaggio-p-136-l2): 2 aircraft (registry code 6960106)
- [Piaggio P.136-L](https://openairdocs.org/model/piaggio-p-136-l): 0 aircraft (registry code 6960102)

## STCs approved under this data sheet (47)

- [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 SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [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 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 SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. 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 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 SA1686WE](https://openairdocs.org/stc/SA1686WE): Installation of Vibration Isolation Products (VIP) engine mount P/Ns VIP 50525-1 and VIP 50545-1 on various aircraft as shown on FAA Approved Model List (AML) No. SA1686WE.. FTG, Inc.
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings 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 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 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 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 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 SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine
- [STC SA01734SE](https://openairdocs.org/stc/SA01734SE): Application of Stewart Systems synthetic fabric covering system to aircraft fuselage, wings, tail surfaces, control surfaces and related parts.. Andrew D. Humphrey
- [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 SA02283SE PAGE 2](https://openairdocs.org/stc/SA02283SE%20PAGE%202): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc.
- [STC SA02402SE PAGE 2](https://openairdocs.org/stc/SA02402SE%20PAGE%202): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics 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 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 SA00432SE](https://openairdocs.org/stc/SA00432SE): Installation of EGT 701 series fuel flow instrument.. J P Instruments
- [STC SA00861SE](https://openairdocs.org/stc/SA00861SE): Installation of J.P. Instruments (JPI) fuel flow indicating system. J P Instruments
- [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc.
- [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc.
- [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International
- [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 SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc.
- [STC SA489EA](https://openairdocs.org/stc/SA489EA): Installation of ARP Inc. carburetor ice detection system. Aircraft & Rotorcraft Products (ARP) Inc
- [STC SA5944NM](https://openairdocs.org/stc/SA5944NM): Replace Lycoming model GSO-480-A246 engine with Lycoming model GSO-480-B2C6. Aero Air Inc
- [STC SA1626NM PAGE 2](https://openairdocs.org/stc/SA1626NM%20PAGE%202): Installation of Electronics Int'l Digital EGT/CHT Instruments and accessories. (201 Series). Electronics International
- [STC SA5074NM](https://openairdocs.org/stc/SA5074NM): Installation of a Shadin fuel computer system.  Limited to installation on serial number 239 ONLY.. Albin Bonnie Jean
- [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International
- [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 SA308EA](https://openairdocs.org/stc/SA308EA): Installation of carburetor ice detection system 105AP in single and twin engine aircraft and single engine helicopters powered by Continental, Franklin, and Lycoming type engines equipped with Marvel-Schebler MA-2, MA-3, MA-4, MA-4-5, MA-6 and HA-6 series carburetors. (Normal,Utility and Acrobatic Category airplanes and helicopters equipped with engines and carburetors as described.). Alfred R Puccinelli
- [STC SA798EA](https://openairdocs.org/stc/SA798EA): Installation of Monitair exhaust gas combustion monitor kit.. Rosemount Engineering Co
- [STC SA3-489](https://openairdocs.org/stc/SA3-489): L2C autopilot with altitude control and approach coupler.. Bendix Corp
- [STC SA61WE](https://openairdocs.org/stc/SA61WE): Full flow oil filter 30409A-12 with element 1A0235.. Winslow Aerofilter Corp
- [STC SA00765DE PAGE 1](https://openairdocs.org/stc/SA00765DE%20PAGE%201) (historical): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA02153LA-D](https://openairdocs.org/stc/SA02153LA-D) (historical): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc
- [STC SA02153LA](https://openairdocs.org/stc/SA02153LA) (historical): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System.. Garmin AT Inc.

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