# TCDS A59EU: Baykar Piaggio Aerospace S.p.A.

- Type: Type certificate data sheet
- Status: Current
- Holder: Baykar Piaggio Aerospace S.p.A.
- Revision: 27
- Revised: September 15, 2026
- Product: Aircraft, Small Airplane
- Certification basis: Part 23
- Registered aircraft: 110, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/1b/8c/1b8c162609b0c7815964c153ccd47d9237b491331f69f7d0ffb96aa56fecca2f
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID119664653220260915184611.0001
- Page: https://openairdocs.org/tcds/A59EU

## Models (1)

As the data sheet lists them.

- P-180

## 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 
 
 
 
 
 
 
TYPE CERTIFICATE DATA SHEET No. A59EU 
 
This Data Sheet which is a part of Type Certificate No. A59EU 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.   Baykar Piaggio Aerospace S.p.A.  
Viale Generale Disegna, 1 
17038 Villanova d’Albenga (SV) - Italy 
 
 
 Type Certificate Holder Record: INDUSTRIE AERONAUTICHE E MECCANICHE RINALDO PIAGGIO S.p.A. 
 Genoa, Italy, transferred TC A59EU to PIAGGIO AERO INDUSTRIES S.p.A. on November 17, 
1998. 
 
                                                                PIAGGIO AERO INDUSTRIES S.p.A 
                                                                Via Cibrario, 4, 16154 Genoa, Italy transferred TC A59EU to PIAGGIO AVIATION S.p.A. on 
May 3, 2022.  
                                                                  
                                                                PIAGGIO AVIATION S.p.A. 
 Viale Generale Disegna, 1, 17038 Villanova d’Albenga (SV), Italy transferred TC A59EU to  
                                                                Baykar Piaggio Aerospace S.p.A. on August 22, 2025 
 
 
Model P-180 (Normal Category), Approved May 7,1990 
 
Engine. Right: Pratt & Whitney of Canada PT6A-66 
3037000 BUILD SPEC 676 flat rated at 850 shp 
Left : Pratt & Whitney of Canada PT6A-66 
3037000 BUILD SPEC 677 flat rated at 850 shp 
For airplanes incorporating the Mod. n. 80-0657 or SB 80-0231: 
Engine. Right: Pratt & Whitney of Canada PT6A-66B 
3072196 BUILD SPEC 1223 flat rated at 850 shp when installed 
on the aircraft . 
Left : Pratt & Whitney of Canada PT6A-66B 
3072196 BUILD SPEC 1224 flat rated at 850 shp when installed 
on the aircraft . 
For airplanes from S/N 3001 to subsequent, incorporating the Mod. n. 80-1117: 
Engine. Right: Pratt & Whitney of Canada PT6A-66B 
3072196 BUILD SPEC 1243 flat rated at 850 shp when installed 
on the aircraft . 
Left : Pratt & Whitney of Canada PT6A-66B 
3072196 BUILD SPEC 1244 flat rated at 850 shp when installed 
on the aircraft . 
 
 
 
 
  
 
Page No. 1 2 3 4 5 6 7 8 9 10  
Rev. No. 27 22 13 24 24 16 25 21 27 25  
A59EU 
Revision 27   
Baykar Piaggio Aerospace 
 P-180 
September 15, 2026

A59EU Page 2 of 10 
 
Fuel. JP4, JP8, JET A, JET A-1, JET B and RP-3 (No.3 Jet Fuel) conforming to 
the latest revision of Pratt & Whitney Service Bulletin No. 14004. 
Fuel Anti-Ice Additive must be used, except for JP-4 and JP-8, in 
accordance with the latest revision of Pratt & Whitney Service Bulletin 
No. 14004. 
 
Oil. Refer to Limitations Section of latest revision of Pilot’s Operating Handbook 
and Airplane Flight Manual. 
 
Engine Limits. 
                                                             Shaft        Torque          N1 Gas                 Prop.          Maximum 
                                                                                                   Generator             Shaft          Permissible 
                                                                                                      Speed                Speed       Interstage Temperature  
(hp) (lb*ft) (%) (rpm) (deg. C) 
Takeoff 
Max. Cont. 
Max. Climb 
 
 
850 
 
 
2230 (2480) [*] 
 
 
104.1 
 
 
2000 (1800) [*] 
 
 
830 
Max. Cruise      
Nor. Climb 
Nor. Cruise 
 
850 
 
2230 (2480) [*] 
 
104.1 
 
2000 (1800) [*] 
 
820 
Starting  (5 sec) --- ---- ---- ---- 1000 
Transient (20 sec) 
Oil Temperature: 
--- 2750 104.1 2205 870 
Minimum Starting -40o C 
Minimum Idle -40o C to 110o C 
Max. Continuous 0o C to 110o C 
Note: The above mentioned engine limits are applicable to both engine models: PT6A-66 and PT6A-66B 
Note [*]: For airplanes from S/N 3001 to subsequent, incorporating the Mod. n. 80-1117 
 
Propeller and Right:  Hartzell HC-E5N-3L or 3AL hub with five Hartzell LE8218 blades. 
Propeller Limits. Left :  Hartzell HC-E5N-3 or 3A hub with five Hartzell HE8218 blades. 
Diameter: 85 in. (Nominal), 84.5 in. (minimum-no further reduction allowed) 
Nominal feather pitch angle 
(at 30 in. station) 89o 
Nominal reverse pitch angle 
(at 30 in. station) -13o 
Stabilized ground operation below 900 
rpm is prohibited, except when feathered 
operation at or below 600 rpm. 
Stabilized ground operation between 
1300 and 1600 rpm is prohibited 
 
(from S/N 3001 to subsequent modified with Mod 80-1117 installed) 
 
Right: Hartzell HC-E5N-3L or 3AL hub with five Hartzell LE8492 blades. 
Left :  Hartzell HC-E5N-3 or 3A hub with five Hartzell HE8492 blades. 
Diameter: 86.5 in. (Nominal), 86 in. (minimum-no further reduction allowed) 
Nominal feather pitch angle 
(at 30 in. station) 87.6o 
Nominal reverse pitch angle 
(at 30 in. station) -8o 
Stabilized ground operation below 900 
rpm is prohibited, except when feathered 
operation at or below 600 rpm. 
Stabilized ground operation between 
1250 and 1550 rpm is prohibited 
Airspeed Limits. KIAS KCAS 
(from S/N 1001 to S/N 1025)

Page 3 of 10 A59EU 
 
Vmo  (maximum operating) 260 258 
Mmo  (maximum operating Mach No.) .67 .665 
Va (maneuvering at 10810 lbs.) 195 194 
Vfe (max. flap extended, t.o. conf.) 175 174 
Vfe (max. flap extended, lnd. conf.) 165 163 
Vfo (max. flap operating, t.o. conf.) 170 169 
Vfo (max. flap operating, lnd. conf.) 150 149 
Vlo (max. landing gear operating) 175 174 
Vle (max. landing gear extended) 185 184 
Vllo/Vlle (maximum landing light 
operating/extended) 160 159 
Vmc   (min. control, prop. feathered) 100 99 
Vmc   (min. control, prop. windmill) 128 127 
 
(from S/N 1026 to subsequent and from S/N 1004 to S/N 1025 modified 
with S.B. 80-0023) 
Vmo (maximum operating) 260 258 
Mmo (maximum operating Mach No.) .67 .665 
Va (maneuvering at 11550 lbs.) 199 198 
Vfe (max. flap extended, t.o. conf.) 180 179 
Vfe (max. flap extended, lnd. conf.) 175 173 
Vfo (max. flap operating, t.o. conf.) 170 169 
Vfo (max. flap operating, lnd. conf.) 150 149 
Vlo (max. landing gear operating) 180 179 
Vle (max. landing gear extended) 185 184 
Vllo/Vlle (maximum landing light 
operating/extended) 160 159 
Vmc   (min. control, prop. feathered) 100 99 
Vmc   (min. control, prop. windmill) 128 127 
 
(from S/N 1004 to subsequent modified with S.B. 80-0215 or with Mod 80-0642 
installed) 
Vmo (maximum operating) 260 258 
Mmo (maximum operating Mach No.) .67 .665 
Va (maneuvering at 12100 lbs) 202 201 
Vfe (max. flap extended, t.o. conf.) 183 182 
Vfe (max. flap extended,lnd conf.) 177 176 
Vfo (max. flap operating, t.o. conf.) 170 169 
Vfo (max. flap operating, lnd. conf.) 150 149 
Vlo (max. landing gear operating) 181 180 
Vle (max. landing gear extended) 185 184 
Vllo/Vlle (maximum landing light 
operating/extended) 160 159 
Vmc   (min. control, prop. feathered) 100 99 
Vmc   (min. control, prop. windmill) 128 127 
(*) From S/N 1063 to subsequent and from S/N 1034 to S/N 1062 modified 
with S.B. 80-0159 
 
 
Mmo  (maximum operating Mach No) .70 .694 
C.G. Range. (from S/N 1001 to S/N 1025)   
(Landing Gear Extended) FS 204.3 to FS 214 at 10,810 lbs   
 FS 195.2 to FS 214 at   8,745 lbs

A59EU Page 4 of 10 
 
 
FS 194 to FS 213 at   8,500 lbs 
FS 194 to FS 209.8 at   7,700 lbs or less 
Straight line variation between points given. 
 
(from S/N 1026 to subsequent and from S/N 1004 to S/N 1025 modified 
with S.B. 80-0023) 
FS 207.6 to FS 214 at 11,550 lbs 
FS 195.2 to FS 214 at   8,745 lbs 
FS 194 to FS 213 at   8,500 lbs 
FS 194 to FS 209.8 at   7,700 lbs or less 
Straight line variation between points given. 
 
Airplanes modified with Mod. 80-0642 or SB-80-0215: 
FS 210.25 to FS 214 at 12,100 lbs 
FS 195.2   to FS 214 at   8,745 lbs 
FS 194 to FS 213 at   8,500 lbs 
FS 194 to FS 209.8 at   7,700 lbs or less 
Straight line variation between points given. 
 
Empty Weight C.G. Range  None 
 
Datum. 236.22 inches forward of the rear pressure bulkhead centerline (at the intersection 
between the forward pressure bulkhead and cockpit floor centerline). 
 
Leveling Means. Three leveling marks are provided to level the airplane:       one is located on the 
forward mast of cabin door, the other two are located each side to the fuselage, 
close to the rearmost baggage compartment frame. The airplane may be leveled 
either on jacks or on wheels using the communicating vessel system and 
deflecting the tires or the shock absorbers. 
Normally the airplane is leveled first laterally then longitudinally. 
Some aircraft may have longitudinal level marks on the external power receptacle 
housing, and lateral level marks on the external power receptacle housing and on 
the ground test refueling panel housing. 
 
Maximum Weight. 
(from S/N 1004 to S/N 1025) 
Ramp 10,900 lbs 
Takeoff 10,810 lbs 
Landing 10,270 lbs 
Zero Fuel (at forward C.G. limit) 9,500 lbs 
(at aft C.G. limit) 9,300 lbs 
Straight line variation between limits given. 
 
(from S/N 1026 to subsequent and from S/N 1004 to S/N 1025 modified 
with S.B. 80-0023) 
Ramp 11,600 lbs 
Takeoff 11,550 lbs 
Landing 10,945 lbs 
Zero Fuel 
(from S/N 1004 to S/N 1015) 
(at forward C.G. limit) 9,500 lbs 
(at aft C.G. limit) 9,300 lbs 
(from S/N 1016 to subsequent) 9,800 lbs 
(from S/N 1016 to 2999 with S.B. 80 -0482) 10,200 lbs 
Straight line variation between limits given.

Page 5 of 10 A59EU 
 
 
 
(S/N 1002 and from S/N 1004 to subsequent modified with Mod. 80-0642 or 
with S.B. 80-0215) 
Ramp 12,150 lbs 
Takeoff 12,100 lbs 
Landing 11,500 lbs 
Zero Fuel 
(from S/N 1004 to S/N 1015) 
(at forward C.G. limit) 9,500 lbs 
(at aft C.G. limit)  9,300 lbs 
(S/N 1002 and from S/N 1016 to subsequent) 9,800 lbs 
(from S/N 1016 to 2999 with S.B.80-0482)  10,200 lbs 
(from S/N 3001 to 3018 with Mod. 80-1440) 10,200 lbs 
(from S/N 3019 and subsequent with Mod. 80-1338)   10,200 lbs 
Straight line variation between limits given 
 
Minimum Crew. 1 Pilot 
 
Number of Seats. Maximum 11 including 2 pilot seats at FS 49.2. See loading instructions in 
AFM/W&BM for approved seating. 
 
Maximum Baggage. Cabin Compartment: 50 lbs at FS 220 
40 lbs on coat Rod at FS 220 
Rear Compartment: 290 lbs at FS 298 (S/N 1001-1002) 
Rear Compartment: 400 lbs at FS 298 (S/N 1004 and up) 
 
Fuel Capacity. 
 
S/N 1004 to S/N 1035 
396.2 U.S.  Gals. at FS 248.2 in 
392.6 U.S.  Gals. Usable 
S/N 1002 and from S/N 1004 to S/N1035 with SB-80-0123 installed and from 
S/N 1036 to subsequent: 
421.9 U.S. Gals. at FS 248.2 in 
418.2 U.S. Gals. usable 
 
S/N 1105 to subsequent with mod. 80-1091 or SB 80-0424 
479.7 U.S. Gals. at FS 244.5 in 
476.0 U.S. Gals. usable 
 
Oil Capacity. 6.7 U.S.  Gals. at FS 274.6 
(2.5 U.S. Gals. usable) 
 
Maximum Operating Altitude 41,000 ft 
 
Control Surface Outboard Wing Flaps 10o  TED(**) 
Movements(*). (t.o. position) 
Outboard Wing Flaps 30o  TED 
(lnd. position) 
Inboard Wing Flaps 20o  TED 
(t.o. position) 
Inboard Wing Flaps 45o  TED 
(lnd. position) 
Aileron 19o  TEU(***) - 15o30 TED 
Aileron Tab  20o  TEU - 19o TED

A59EU Page 6 of 10 
 
 
(only right aileron) 
Forward Wing Flaps 13o  TED 
(t.o. position) 
Forward Wing Flaps 30o  TED 
(lnd. position) 
Rudder 23o RIGHT - 23o LEFT 
Rudder Tab 30o RIGHT - 30o LEFT 
Stabilizer 8o   TEU    -  2o  TED 
Elevator 14o   TEU   - 12o  TED 
(*) Nominal Values 
See P.180 Maintenance Manual for rigging instructions, deflections and 
corresponding tolerances. 
(**) TED = Trailing Edge Down 
(***) TEU = Trailing Edge Up 
 
Serial Nos. Eligible. Each individual aircraft manufactured under this type certificate must be 
accompanied by an Export Certificate of Airworthiness as noted below under 
"Import Requirements" when an application for a U.S. airworthiness certificate is 
made. 
P.180: S/N 1002,1004 to subsequent. 
 
Certification Basis Date of application for type certificate December 29, 1983, revised 
FAR 21.17 November 12, 1986. 
 
(S/N 1001 up to 1104) Federal Aviation Regulations - 14 CFR Part 23, effective February 1, 1965, 
including Amendments 23-1 through 23-33 and Section 23.2 Amendment 36. 
 
 
Special conditions; Piaggio Model P-180 airplanes, No. 23-ACE-29 and 
No. 23-ACE-52. 
 
 
Special Federal Aviation Regulations No. 27, effective February 1, 1974, 
including Amendments 27-1 through 27-5. 
 
S/N 1001 and 1002 
 
 
 
S/N 1004 and up 
 
Equivalent safety findings exist with respect to the following regulations: 
- 14 CFR Section 23.1305(g): Fuel Pressure Indicator 
- 14 CFR Section 23.1321(d): Arrangement of flight instruments 
- 14 CFR Section 23.1545(b)(5): Marking of airspeed indicator for Vyse 
 
Equivalent safety findings exist with respect to the following regulations: 
- 14 CFR Section 23.1305(g): Fuel Pressure Indicator 
- 14 CFR Section 23.1545(b)(5): Marking of airspeed indicator for Vyse 
 
- 14 CFR Part 36, effective December 1, 1969, including Amendments 36-1 
through 36-16 
- 14 CFR Part 36, Appendix G, effective February 7,2004, including 
Amendments 36-25 for A/C’s with SB 80-0215. 
 
(S/N 1105 to subsequent) -14 CFR Part 23.1311 and 23.1309 at Amendment level 23-49 for Avionics 
and Electronic Display; 
 
Special condition FAA CRI SE-1. 
 
- 14 CFR Part 36, Appendix G ,effective February 7,2004, including 
Amendments 36-25, when mod. 80-0642 or SB-80-0215 is installed.

Page 7 of 10 A59EU 
 
 
                                                       - 14 CFR Part 23.2010 and 23.2525 of 14 CFR 23 at Amendment level 23-64. 
 Applicable for the Lithium Main Battery and Lithium Emergency Power Unit  
                                                         (see Note 16). The detailed design standards used as a means of compliance in 
accordance with § 23.2010 are documented in Piaggio P180 DDS summary 
document No. P180-DDS-001, Rev 00, dated March 19, 2025.  
 
The Ente Nazionale per l’Aviazone Civile (ENAC) originally type certificated 
this aircraft under its Type Certificate Number A390. Effective September 28, 
2003, the European Aviation Safety Agency (EASA) began oversight of this 
product under their Type certificate Number A059 on behalf of Italy. 
 
Validation Basis. Type Certificate A59EU was issued pursuant to FAR 21.29 in validation of EASA 
certification of compliance with the aforementioned certification basis, and in 
accordance with the standard airworthiness certificate provisions of FAR 
21.183(c). 
 
Note: The airworthiness provisions of FAR 21.183(d) may be cited as the basis 
for issuance of standard airworthiness certificates for aircraft imported from a 
country other than the country of manufacture. 
 
Equipment. The  basic  required  equipment  as  prescribed  in  the  applicable  airworthiness 
regulations (see Certification Basis) must be installed in the aircraft for 
airworthiness certification. In addition, the following item of equipment is 
required: 
 
1. POH and AFM, Report No. 6591, approved July 7, 1992 (RAI Ltr 
282.378/SCMA), or later approved revision (S/N 1004 through 1025 
incorporating SB 80-0023 or 1026 through 1104). 
2. AFM, Report No. 180-MAN-0010-01100 (EASA approval date: October 
21, 2005) and W&B M, Report No. 180-MAN-0020-01101 (EASA 
approval date: October 21, 2005) (S/N 1002 and 1105 to 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 
the Ente Nazionale per l’Aviazone Civile (ENAC) 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 EASAs TC No A059  approved under U.S. Type Certificate No. 
A 59EU and to be in a condition for safe operation”. 
 
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. 
 
Country other than Manufacturer (U.S. bilateral agreement and the original Export 
Certificate of Airworthiness issued by the country of manufacture must exist): A 
U.S. airworthiness certificate may be issued on the basis of a log book certifying 
statement endorsed by an authorized representative of the civil aviation authority 
of the exporting country. It is incumbent upon the exporting civil aviation 
authority to determine that the certifying statement includes evidence of 
acceptable service history and modification deviations and the following 
statement: "Th e aircraft covered by this certificate has been examined, tested, 
inspected in accordance with the provisions of FAR 21.183)d) or its equivalent, 
and found to conform to the type design approved under Type Certificate A59EU 
and is in a condition for safe operation".

A59EU Page 8 of 10 
 
 
 
Service Information Each of the documents listed below must state that it is approved by the 
European Aviation Safety Agency (EASA) or – for approvals made before 
September 28, 2003- by the Ente Nazionale per l’Aviazone Civile (ENAC) 
 
· 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 
unless one of the following condition exists: 
 
· The documents change the limitations, performance, or procedures 
of the FAA approved manuals; or 
 
· The documents make an acoustical or emissions changes to this 
product’s U.S.type certificate as defined in 14 CFR § 21.93. 
 
 
 
 
 
NOTES. 
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. 
 
Note 1. Current weight and balance data, loading information, and a list of equipment included in empty 
weight must be provided for each airplane at the time of original certification. 
 
(a) Basic empty weight includes unusable fuel of 24.8 lbs at (248.8 in) with 8.7 lbs being 
undrainable at (248.2 in). 
(b) For airplane with mod. 80-1091 or SB 80-0424, basic empty weight includes unusable fuel of 
24.8 lbs at (248.8 in) with 15.4 lbs being undrainable at (236.7 in). 
(c) Basic empty weight includes engine oil of 55 lbs at (274.6 in). 
 
Note 2. Placards (Refer to Manufacturer's Specifications for a complete listing):  All required placards as 
listed in the approved Airplane Flight Manual must be installed in the appropriate locations. 
 
(1) The following placard must be displayed in clear view of the pilot: 
"THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN 
OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN 
OPERATING THIS AIRPLANE IN THE NORMAL CATEGORY. OTHER OPERATING 
LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS 
AIRPLANE IN THIS CATEGORY ARE CONTAINED IN THE AIRPLANE FLIGHT 
MANUAL." 
 
(2) Refer to the Airplane Flight Manual, Section 2, Limitations for a listing of other required 
placards. 
 
Note 3. Instructions for Continued Airworthiness are contained in the applicable Maintenance Manual. 
Airworthiness Limitations are contained in the EASA approved Chapter 4 of the M M. 
Revisions to Airworthiness Limitations must be FAA approved. 
 
All manufacturer's service bulletins (and other manual material) which contain a statement that the 
document is approved by the exporting airworthiness authority (EASA) may be interpreted as FAA 
approved.  These approvals pertain to the type design only.

Page 9 of 10 A59EU 
 
 
 
All service bulletins classified as Mandatory by the EASA are identified to that effect and are 
subject to an Airworthiness directive issued by the FAA. 
 
Note 4. Changing the color and the thickness of the exterior paint (including registration numbers) for 
composite components is only permissible after prior approval of the manufacturer. 
 
Note 5.    All the approved Baykar Piaggio Aerospace type design passenger cabin configurations are listed in: 
 
  S/N up to 1104: “P-180 AVANTI Pilot's Operating Handbook and Airplane Flight Manual”, Report    
  6591, Section 6, Weight and Balance. 
 
  S/N 1105 and up: Weight and Balance Manual, Report No. 180-MAN-0020-01101. 
   
  For all passenger cabin configurations featuring a 2-place “low back” side facing divan the aft seat   
  position must not be occupied during takeoff and landing.  For the relevant required placard refer to: 
 
 S/N up to 1104: “P-180 AVANTI Pilot's Operating Handbook and Airplane Flight Manual”, Report  
 6591, Section 2, Limitations. 
 
 S/N 1105 and up: Airplane Flight Manual, Report No. 180-MAN-0010-01100, Section 2 Limitations. 
 
For any other side facing seats that are not part of the Baykar Piaggio Aerospace type design as 
identified in the above documents, contact the nearest Aircraft Certification Office for approval.   
 
 
Note 6. S/N 1001 and 1002 
Four piece windshield PPG p/n NP-165241-1, p/n NP-165241-2 and Swedlow p/n 6600803-3, 
p/n 6600803-4 is installed 
 
S/N 1004 to 1022 
Two piece windshield PPG p/n NP-165231-01 and p/n NP-165231-02 is installed (3 plies). 
 
S/N 1023 and up 
Two piece windshield PPG p/n NP-165251-01 and p/n NP-165251-02 is installed (2 plies). 
 
Note 7. Oxygen bottle 40 cu.ft. is installed on S/N 1004 and up, in accordance with FAR 91 
Requirements. 
 
Note 8. Airplanes from S/N 1004 up to 1104, modified with the installation of either the RVSM Kit No. 
80KA0075 during manufacturing or the service Bulletin No. 80-0162 per retrofit embodiment, meet 
the initial airworthiness requirements for operation in Reduced Vertical Seperation Minimum 
(RVSM) airspace. 
Airplanes from 1105 and up have basic capability to perform operation in RVSM airspace. 
Each operator must obtain final RVSM operating approval directly from their local FAA Flight 
Standards Office. 
 
Note 9. S/N 1105 and up 
Piaggio Model P-180 airplane manufactured from Serial number 1105 and up will incorporate the 
Piaggio Modification No. DMT 80-0587 that includes an Electronic Flight Instrument System with 
an Integrated Avionics processor System – Rockwell Collins Pro Line 21. 
This modification must use the “P.180 AVANTI II Airplane Flight Manual”, 
Report No. 180-MAN-0010-01100 (EASA approval date: October 21, 2005), and 
the “P.180 AVANTI II Weight and Balance Manual”, Report No. 180-MAN-0020-01101 (EASA 
approval date: October 21, 2005). 
 
Note 10. S/N 1116 and up: 
Approved major change on Piaggio P-180 is: 
Change No. 80-0574, “Wing Root Design” Level 2

A59EU Page 10 of 10 
 
 
 
Note 11. S/N 1105 and up 
Piaggio Model P-180 airplane manufactured from Serial number 1105 and up can incorporate an 
“In Flight Information System” according to the optional Piaggio Modification No. DMT 80-0596 
“PA-05 IFIS.” 
This modification must use the Supplement 16 to “P.180 AVANTI II Airplane Flight Manual,” 
Report No. 180-MAN-0010-01100 (EASA approval date June 13, 2006). 
 
Note 12. Engine model PT6A-66B is installed with Piaggio Modification No. 80-0657 during manufacturing 
or Piaggio Service Bulletin No. 80-0231 per retrofit embodiment. 
 
Airplanes from S/N 1004 up to 1104, modified with Service Bulletin No. 80 -0231, must use the 
Temporary Change No. 2 to the "P.180 Avanti Pilot's Operating Handbook and Airplane Flight 
Manual" Report No. 6591. 
Airplanes from S/N 1105 and up, modified with Mod. No. 80 -0657 or Service Bulletin 80 -0231, 
must use the Temporary Change No. 1 to the "P.180 Avanti II Airplane Flight Manual" Report No. 
180-MAN-0010-01100. 
 
Note 13. S/N 1105 and up 
Piaggio Model P -180 airplane manufactured from Serial number 1105 and up can incorporate a 
“CPDLC system” according to the optional Piaggio Modification No. DMT 80- 1005 “CPDLC – 
Controller Pilot Data Link Communication System”, or relevant Service Bulletin 80-0416. 
This modification must use the Supplement 30 to “P.180 AVANTI II Airplane Flight Manual” 
Report No. 180-MAN-0010-01100 (EASA approval date: February 04, 2014). 
 
Note 14. S/N 1105 and up 
Piaggio Model P -180 airplane manufactured from Serial number 1105 and up can incorporate an 
optional additional fuel tank according to the optional Piaggio Modification No. DMT 80 - 
1091“P.180 Extended range”, or relevant Service Bulletin 80-0424. 
This modification must use the temporary change 49 to “P.180 AVANTI II Airplane Flight Manual” 
Report No. 180-MAN-0010-01100 (EASA approval date: June 3, 2014) and the temporary change 
15 to the “P.180 AVANTI II Weight and Balance Manual”, report no. 180 -MAN-0020-01101 
(EASA approval date: June 3, 2014). 
 
Note 15. S/N 3001 and up 
Piaggio Model P -180 airplane manufactured from Serial number 3001 and up incorporate the 
Piaggio Modifications No.: 
- DMT 80-1117“Community Noise Reduction” 
- DMT 80-1121 “Winglet”. 
These modifications must use the temporary change No. 62 to “P.180 AVANTI II Airplane Flight 
Manual” Report No. 180-MAN-0010-01100 Rev. A4 (EASA approval date: November 28, 2014). 
 
Note 16. S/N 1105 and up  
Piaggio Model P -180 airplane manufactured from Serial number 1105  and up can incorporate the 
Piaggio Modifications No.: 
- DMT 80-1443 “Li-Ion Emergency Power Unit (EPU)”. 
- DMT 80-1432“Li-Ion Main Battery” 
This Modification must use the Supplement 38 to “P.180 AVANTI II / AVANTI EVO Airplane Flight 
Manual” Report No. 180-MAN-0010-01100 Rev. C0 (EASA approval date: Dec. 23, 2022) integrated 
by the temporary change No. 159. 
These modifications must also use the following AMM Temporary Revisions (TR) - TR 204, TR 
205, TR 207, TR 209, TR 210, TR 211 and TR 212 dated April 7, 2025 or later approved revisions. 
 
Note 17. S/N 1105 and up  
Piaggio Model P -180 airplane manufactured from Serial number 1105 and up  can incorporate the 
Piaggio Modifications No.: 
- DMT 80-1457 “Wheel and Brake Assy replacement (from carbon to steel)” 
This Modification must use the Supplement 37 to “P.180 AVANTI II / AVANTI EVO Airplane Flight 
Manual” Report No. 180-MAN-0010-01100 Rev. C0 (EASA approval date: Dec. 23, 2022). 
 
…..END…..
```

## ADs (64, first 50, in force first)

- [AD 2026-06-05](https://openairdocs.org/ad/2026-06-05): Vertical Stabilizer Structure · Baykar Piaggio Aerospace P-180. Effective May 11, 2026
- [AD 2026-05-10](https://openairdocs.org/ad/2026-05-10): Flight Control System · Baykar Piaggio Aerospace P-180. Effective Apr 27, 2026
- [AD 2025-26-05](https://openairdocs.org/ad/2025-26-05): Hydraulic System, Main · Baykar Piaggio Aerospace P-180. Effective Feb 17, 2026
- [AD 2025-15-10](https://openairdocs.org/ad/2025-15-10): Horizontal Stabilizer Structure · Piaggio P-180. Effective Sep 3, 2025
- [AD 2023-16-04](https://openairdocs.org/ad/2023-16-04): Elevator Structure · Piaggio P-180. Effective Aug 30, 2023
- [AD 2022-22-07](https://openairdocs.org/ad/2022-22-07): Fuselage Main, Plate/Skin · Piaggio P-180. Effective Dec 23, 2022
- [AD 2022-19-07](https://openairdocs.org/ad/2022-19-07): Pitot/Static System · Piaggio P-180. Effective Nov 3, 2022
- [AD 2022-17-13](https://openairdocs.org/ad/2022-17-13): Air Data Computer · Piaggio Aero Industries P-180. Effective Oct 11, 2022
- [AD 2020-19-10](https://openairdocs.org/ad/2020-19-10): Landing Gear · Piaggio Aero Industries P-180. Effective Nov 3, 2020
- [AD 2017-20-13](https://openairdocs.org/ad/2017-20-13): Flight Controls · Piaggio Aero Industries P-180. Effective Nov 16, 2017
- [AD 2015-19-11](https://openairdocs.org/ad/2015-19-11): Fuselage · Piaggio Aero Industries P-180. Effective Nov 3, 2015
- [AD 2014-18-01](https://openairdocs.org/ad/2014-18-01): Navigation · Bombardier ATR42-200, ATR42-300, ATR42-320 and 23 more. Effective Oct 14, 2014
- [AD 2014-09-04](https://openairdocs.org/ad/2014-09-04): Landing Gear · Piaggio Aero Industries P-180. Effective Jun 13, 2014
- [AD 2014-03-20](https://openairdocs.org/ad/2014-03-20): Flight Controls · Piaggio Aero Industries P-180. Effective Apr 1, 2014
- [AD 2013-18-04](https://openairdocs.org/ad/2013-18-04): Landing Gear · Piaggio Aero Industries P-180. Effective Oct 18, 2013
- [AD 99-07-10 R1](https://openairdocs.org/ad/99-07-10-R1): Nacelles/Pylons · Piaggio Aero Industries P-180. Effective Sep 19, 2013
- [AD 2000-07-11 R1](https://openairdocs.org/ad/2000-07-11-R1): Landing Gear · Piaggio Aero Industries P-180. Effective Nov 21, 2012
- [AD 2003-17-03 R1](https://openairdocs.org/ad/2003-17-03-R1): Fuel · Piaggio Aero Industries P-180. Effective Nov 14, 2012
- [AD 2012-18-06](https://openairdocs.org/ad/2012-18-06): Flight Controls · Piaggio Aero Industries P-180. Effective Oct 22, 2012
- [AD 2011-26-01](https://openairdocs.org/ad/2011-26-01): Doors · Piaggio Aero Industries P-180. Effective Jan 17, 2012
- [AD 2011-24-01](https://openairdocs.org/ad/2011-24-01): Landing Gear · Piaggio Aero Industries P-180. Effective Dec 22, 2011
- [AD 2011-09-51](https://openairdocs.org/ad/2011-09-51): Fuselage · Piaggio Aero Industries P-180. Effective May 31, 2011
- [AD 2011-05-01](https://openairdocs.org/ad/2011-05-01): Cargo and Accessory Compartments · Piaggio Aero Industries P-180. Effective Mar 31, 2011
- [AD 2010-23-01](https://openairdocs.org/ad/2010-23-01): Stabilizers · Piaggio Aero Industries P-180. Effective Dec 10, 2010
- [AD 2010-21-08](https://openairdocs.org/ad/2010-21-08): Engine oil · Piaggio Aero Industries P-180. Effective Nov 18, 2010
- [AD 2010-21-09](https://openairdocs.org/ad/2010-21-09): Engine oil · Piaggio Aero Industries P-180. Effective Nov 18, 2010
- [AD 2010-21-14](https://openairdocs.org/ad/2010-21-14): Fuselage · Piaggio Aero Industries P-180. Effective Nov 18, 2010
- [AD 2010-09-09](https://openairdocs.org/ad/2010-09-09): Fuel · Piaggio Aero Industries P-180. Effective Jun 3, 2010
- [AD 2010-03-04](https://openairdocs.org/ad/2010-03-04): Electric power · Piaggio Aero Industries P-180. Effective Mar 11, 2010
- [AD 2010-03-09](https://openairdocs.org/ad/2010-03-09): Fuselage · Piaggio Aero Industries P-180. Effective Mar 11, 2010
- [AD 2008-03-14](https://openairdocs.org/ad/2008-03-14): Emergency exit door · Piaggio Aero Industries P-180. Effective Mar 11, 2008
- [AD 2007-24-15](https://openairdocs.org/ad/2007-24-15): Longitudinal flight control cables · Piaggio Aero Industries P-180. Effective Jan 7, 2008
- [AD 2007-18-07](https://openairdocs.org/ad/2007-18-07): Hydraulic fluid of the steering system · Piaggio Aero Industries P-180. Effective Oct 11, 2007
- [AD 2007-13-12](https://openairdocs.org/ad/2007-13-12): Main wing outboard flap · Piaggio Aero Industries P-180. Effective Aug 3, 2007
- [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 2003-04-08](https://openairdocs.org/ad/2003-04-08): Placard (Inside of the lavatory door) · Piaggio Aero Industries P-180. Effective Apr 11, 2003
- [AD 2002-23-10](https://openairdocs.org/ad/2002-23-10): First Outboard Flap Control Rod and the Bleed Air Duct · Piaggio Aero Industries P-180. Effective Dec 17, 2002
- [AD 2002-14-19](https://openairdocs.org/ad/2002-14-19): Collins Air Data Computers (ADC) · Boeing DC-8-11, DC-8-12, DC-8-21 and 36 more. Effective Aug 23, 2002
- [AD 2002-08-04](https://openairdocs.org/ad/2002-08-04): Horizontal Stabilizer Hinge Bushings · Piaggio Aero Industries P-180. Effective Jun 10, 2002
- [AD 2001-05-04](https://openairdocs.org/ad/2001-05-04): Flap Actuators · Piaggio Aero Industries P-180. Effective Apr 27, 2001
- [AD 2000-03-19 REM](https://openairdocs.org/ad/2000-03-19-REM): Pneumatic Deicing Boots · Piaggio Aero Industries P-180. Effective Jan 2, 2001
- [AD 99-11-06](https://openairdocs.org/ad/99-11-06): Environmental Control System Bleed Tubes · Piaggio Aero Industries P-180. Effective Jul 5, 1999
- [AD 99-07-10](https://openairdocs.org/ad/99-07-10): Engine Nacelle Inner Panels · Piaggio Aero Industries P-180. Effective May 10, 1999
- [AD 98-23-14](https://openairdocs.org/ad/98-23-14): Elevator & Aileron Control Retaining Pins · Piaggio Aero Industries P-180. Effective Dec 18, 1998
- [AD 98-13-07](https://openairdocs.org/ad/98-13-07): Lavatory Water Tube/Hose Connections · Piaggio Aero Industries P-180. Effective Aug 1, 1998
- [AD 98-12-13](https://openairdocs.org/ad/98-12-13): Low Pitch Stop Switch Support · Piaggio Aero Industries P-180. Effective Jul 18, 1998
- [AD 98-08-05](https://openairdocs.org/ad/98-08-05): Main Landing Gear Drag Brace Link and Retraction Actuator · Piaggio Aero Industries P-180. Effective May 26, 1998
- [AD 98-06-05](https://openairdocs.org/ad/98-06-05): AFM, POH - Autopilot · Piaggio Aero Industries P-180. Effective Apr 2, 1998
- [AD 97-22-11](https://openairdocs.org/ad/97-22-11): Airplane Flight Manual (AFM) - Limitations Section - Power Levers · Piaggio Aero Industries P-180. Effective Dec 5, 1997
- [AD 97-15-14](https://openairdocs.org/ad/97-15-14): Torque Tube Bottom Flange Assembly · Piaggio Aero Industries P-180. Effective Sep 19, 1997

All 64: https://openairdocs.org/tcds/A59EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Piaggio Aero Industries P180](https://openairdocs.org/model/piaggio-aero-industries-p180): 51 aircraft (registry code 6960206)
- [Piaggio P180](https://openairdocs.org/model/piaggio-p180): 50 aircraft (registry code 6960204)
- [Piaggio Aero Industries P180 AVANTI II](https://openairdocs.org/model/piaggio-aero-industries-p180-avanti-ii): 6 aircraft (registry code 6960220)
- [Iam Piaggio S P A P-180](https://openairdocs.org/model/iam-piaggio-s-p-a-p-180): 2 aircraft (registry code 6960210)
- [Piaggio Aero Industries S P A P180 AVANTI](https://openairdocs.org/model/piaggio-aero-industries-s-p-a-p180-avanti): 1 aircraft (registry code 6960221)

## STCs approved under this data sheet (101, first 50)

- [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc.
- [STC SA11300DS](https://openairdocs.org/stc/SA11300DS): Upgrade previously installed Collins Aerospace Radar Altimeter. BHE & Associates Ltd.
- [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 SA01848WI](https://openairdocs.org/stc/SA01848WI): Modification of a Rockwell Collins Global Positioning System (GPS). Rockwell Collins Inc.
- [STC SA04051CH](https://openairdocs.org/stc/SA04051CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC
- [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 SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH
- [STC SA04348CH](https://openairdocs.org/stc/SA04348CH): Installation of Parker Hannifin Corporation, Aircraft Wheel & Brake Division, Wheel and Brake Conversion Kit, part number 199- 283. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc.
- [STC SA11299DS](https://openairdocs.org/stc/SA11299DS): An update to the exisiting Collins Aerospace Integrated Flight Information System (IFIS) FSU-5010 and upgrade the existing XMWR-1000 to a XMWR-1000S (Sirius XM) in Part 23 aircraf. BHE & Associates LTD
- [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King)
- [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 SA02075SE](https://openairdocs.org/stc/SA02075SE): Installation of a Mid-Continent MD835( ) Lithium Ion Battery. Mid-Continent Instrument Co. Inc.
- [STC SA04199NY](https://openairdocs.org/stc/SA04199NY): Installation of Becker Avionics DVCS6500 Digital Voice Communication System. Becker Avionics Inc.
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [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 SA04336NY](https://openairdocs.org/stc/SA04336NY): Installation of Rockwell Collins TDR-94D Transponder Upgrade-ADS-B Out. Mid Canada Mod Center
- [STC SA03345CH](https://openairdocs.org/stc/SA03345CH): Install air ambulance conversion. Spectrum Aeromed LLC dba Spectrum Aeromed
- [STC SA02878CH](https://openairdocs.org/stc/SA02878CH): Install Air Ambulance conversion. Paul/ Lanna Egan LLC
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc.
- [STC SA01877WI](https://openairdocs.org/stc/SA01877WI): Installation of ADS-B Out.. Intercontinental Jet Service Corporation
- [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation
- [STC SA01684WI](https://openairdocs.org/stc/SA01684WI): Installation of Rockwell Collins, Inc. Aircraft Information Management (AIM) System. Rockwell Collins Inc
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [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 SA1644GL](https://openairdocs.org/stc/SA1644GL): Install Egan Aviation Air Ambulance Stretcher P/N 125 using Installation Kit P/N 805.. Paul/ Lanna Egan LLC
- [STC SA01806WI](https://openairdocs.org/stc/SA01806WI): Modification of Rockwell Collins TCAS II System Installation with DC powered TCAS Transmitter Receiver Processor. Rockwell Collins Inc
- [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 SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics
- [STC SA01229SE PAGE 1](https://openairdocs.org/stc/SA01229SE%20PAGE%201): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc
- [STC SA02442AK PAGE 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 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 SA00269BO](https://openairdocs.org/stc/SA00269BO): Installation of Avidyne Corporation TWX 670 Tactical Weather Detection System P/N 850-00026-000-( ) consisting of Avidyne Processor P/N 700-00033-000-( ), Sensor Systems Inc. Antenna P/N S72-1715-1 with doubler plate P/N S72-171530-1, and Avidyne Mounting Tray P/N 700-00034-000.. Avidyne Corporation
- [STC SA02717NY PAGE 2](https://openairdocs.org/stc/SA02717NY%20PAGE%202): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC
- [STC SA01430WI-D](https://openairdocs.org/stc/SA01430WI-D): Modification of a Rockwell Collins, Inc. Data Base Unit (DBU). Rockwell Collins Inc
- [STC SA10950SC](https://openairdocs.org/stc/SA10950SC): Installation of a 4 place Passenger Seating Arrangement. Piaggio America Inc.
- [STC SA01434WI-D](https://openairdocs.org/stc/SA01434WI-D): Modification of a Rockwell Collins, Inc. Global Positioning System (GPS)
installation. Rockwell Collins 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 SA01676WI](https://openairdocs.org/stc/SA01676WI): Modification of a Rockwell Collins, Inc. File Server Unit (FSU). Rockwell Collins Inc
- [STC SA00674WI-D](https://openairdocs.org/stc/SA00674WI-D): Modification of Collins VHF-22A/VHF-22B VHF COMM Receiver Transmitter with CTL-22 Control Pro Line II System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II system installation.. Rockwell Collins Inc

All 101: https://openairdocs.org/tcds/A59EU/stcs.md

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OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.