# TCDS A19SO: Piper Aircraft Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Piper Aircraft Inc.
- Revision: 23
- Revised: September 29, 2026
- Product: Aircraft, Small Airplane
- Certification basis: Part 23, CAR 3
- Registered aircraft: 600, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/a0/f4/a0f4e7532301960b40c7e4cbcb2d67750c891c648c74133f17e5616b54aba7ee
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID125739696120260930182301.0001
- Page: https://openairdocs.org/tcds/A19SO

## Models (2)

As the data sheet lists them.

- PA-44-180T (Turbo Seminole)
- PA-44-180 (Seminole)

## 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 8 9 10 11 12 13 
Rev. No. 23 9 18 10 17 6 17 17 17 18 23 23 23 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A19SO 
Revison 23 
Piper Aircraft, Inc 
 
PA-44-180 
PA-44-180T  
 
September 29, 2026 
TYPE CERTIFICATE DATA SHEET NO. A19SO 
 
This data sheet, which is part of Type Certificate No. A19SO, prescribes conditions and limitations under which the product for 
which type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder Piper Aircraft, Inc. 
 2926 Piper Drive 
 Vero Beach, Florida 32960 
 
Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC A19SO to Piper Aircraft, Inc on August 7, 
2006. 
 
IA. - Model PA-44-180, Seminole,  4 PCLM  (Normal Category),  Approved March 10, 1978. 
Engine 1 Lycoming O-360-E1A6D with carburetor setting 10-5092, 10-5219, or  
  10-6019 (Left Side) 
 1 Lycoming LO-360-E1A6D with carburetor setting 10-5092, 10-5219, or 
  10-6019 (Right Side) 
 
Fuel 100 or 100LL aviation grade fuel 
 
Engine Limits For all operations, 2700 r.p.m.  (180 hp) 
 
Propeller and Propeller Limits Left Engine: 
 1 Hartzell, Hub Model HC-C2Y(K, R) -2CEUF, Blade Model FC7666A-2R  
 or  Hub Model HC-C3YR-2EUF, Blade Model FC7663-5R 
  
 Right Engine: 
 1 Hartzell, Hub Model HC-C2Y(K, R) -2CLEUF, Blade Model FJC7666A-2R  
 or  Hub Model HC-C3YR-2LEUF, Blade Model FJC7663-5R 
 
 Pitch Setting at 30" Station: 
 Two-Blade Three-Blade 
 High 79° - 81°, Low 12.4° ± 0.2° High 81° - 83°, Low 10.6° ± .1° 
 Diameter:  Not over 74 inches Diameter:  Not over 73 inches 
                   Not under 72 inches                   Not under 72 inches 
   
 Spinner:  
 Two-Blade Three-Blade 
 Hartzell P/N C-2285-3 Spinner Assy 
     (Left) 
Hartzell P/N C-2285-3L Spinner Assy 
     (Right) 
Hartzell P/N C-4558 Spinner Assy 
     (Left) 
Hartzell P/N C4-558 Spinner Assy 
     (Right) 
 See NOTE 4. See NOTE 4. 
 
 Governor Assembly: 1 Hartzell Hydraulic Governor Model E-3-2 (Left) 
      1 Hartzell Hydraulic Governor Model E-3-2L (Right)  
      or 
      1 Hartzell Hydraulic Governor Model E-8-2L (Right) with  
     synchrophaser (Piper Drawing No. 36889 Synchrophaser  
     Installation, S/N 44-7995278 and up)

A19SO Page 2 of 13 
 
Airspeed Limits 
 
VNE (Never Exceed) 202 KIAS 
 VNO (Maximum Structural Cruise) 169 KIAS 
 VA (Maneuvering 3800 lb.) 135 KIAS 
 VA (Maneuvering 2700 lb.) 112 KIAS 
 VFE (Maximum Flaps Extended) 111 KIAS 
 VLO (Maximum Landing Gear Operation)  
       Extension 140 KIAS 
       Retraction 109 KIAS 
 VLE (Maximum Landing Gear   
       Extended) 140 KIAS 
 VMC (Minimum Control Speed) 56 KIAS 
 
C.G. Range (+89.0) to (+93.0) at 3800 lb. 
 (+85.0) to (+93.0) at 3400 lb. 
 (+84.0) to (+93.0) at 2800 lb. or less 
 Straight line variation between points given. 
 Moment change due to retracting landing gear (+819 in-lb.) 
 
1800
2800
3400
LB
89.0 93.0
LB
3800
3400
2800
1800
INCHES
85.0
84.0
 
Empty Weight C.G. Range None 
 
Maximum Weight Ramp 3816 lb. 
 Takeoff 3800 lb. 
 Landing 3800 lb. 
 
Number of Seats 4  (2 at +80.5, 2 at +118.1) 
 
Maximum Baggage 200 lb. at +142.8 
 
Fuel Capacity 110 gallons  (2 nacelle tanks) at +95.0     (108 gallons usable) 
 (See NOTE 1 for data on system fuel) 
 
Oil Capacity 6 quarts per engine (4 quarts per engine usable) 
 (See NOTE 1 for data on system oil) 
 
Control Surface Movements Ailerons Up 23° (±2°) Down 17° (±2°) 
 Stabilator Up 15° (±1°) Down 3° (±1°) 
 Rudder Left 37° (+1°, -0°) Right 37° (+1°, -0°) 
 Stabilator Trim Tab Down 9° (±1°) Up 4° (±1°) 
  (Stabilator neutral)  
 Wing Flaps Up 0° (±1°) Down 10°, 25°, 40° (±2°) 
 Rudder Trim Tab Left 26° (±2°) Right 26° (±2°) 
  (Rudder neutral)  
 Nose Wheel Travel Left 30° (±1°) Right 30° (±1°) 
 
Manufacturer's Serial Numbers 44-7995001 through 44-8195026  (See NOTE 5 for airworthiness certification eligibility 
in the United States)

Page 3 of 13 A19SO 
 
IB. - Model PA-44-180, Seminole, 4 PCLM  (Normal Category),  Approved March 10, 1978. 
Engine (See Note 6) 1      Lycoming O-360-A1H6 with carburetor setting 10-5219 or 10-6019 (Left Side)  
1 Lycoming LO-360-A1H6 with carburetor setting 10-5219 or 10-6019 (Right Side) 
 OR 
 1      Lycoming IO-360-B1G6 (Left Side) with fuel injector model RSA-5AD1,  
(Lycoming Part Number 61J28856) 
1 Lycoming LIO-360-B1G6 (Right Side) with fuel injector model RSA-5AD1 
 (Lycoming Part Number 61J28856) 
 
Fuel 100 or 100LL aviation grade fuel 
       
Engine Limits For all operations, 2700 r.p.m.  (180 hp) 
 
Propeller and Propeller Limits Left Engine: 
 1 Hartzell, Hub Model HC-C2Y(K, R) -2CEUF, Blade Model FC7666A-2R 
 or 1 Hartzell Hub Model HC-C2YR-2CEUFP, Blade Model FC7497 
 *Hubs and blades must be both of same model both left and right; no intermixing 
 
 Right Engine: 
 1 Hartzell, Hub Model HC-C2Y(K, R) -2CLEUF, Blade Model FJC7666A-2R 
 or 1 Hartzell Hub Model HC-C2YR-2CLEUFP, Blade Model FJC7497 
 *Hubs and blades must be both of same model both left and right; no intermixing 
 
Pitch Setting at 30" Station: 
Blade Model FC7666A-2R   Blade Model F(J)C7497 
High 79° - 81°, Low 12.4° ± 0.2°  High 79° - 81°, Low 12.8° ± 0.2° 
Diameter:Not over 74 inches   Diameter:Not over 74 inches 
  Not under 72 inches    Not under 72.5 inches 
 
 Spinner: Hartzell P/N C-2285-3  Spinner Assy (Left)* 
   Hartzell P/N C-2285-3L Spinner Assy (Right)* 
    *See Note 4 for carburated engines only 
    (no intermixing permitted) 
   or  
   Hartzell P/N D-6974-1P (Left & Right) ** 
    **no intermixing permitted with C-2285-3(L) 
      
 
 Governor Assembly: 1 Hartzell Hydraulic Governor Model U-3-15 (Left) with  
      unfeathering accumulator 
      1 Hartzell Hydraulic Governor Model U-3-15L (Right) with  
     unfeathering accumulator 
  
Airspeed Limits VNE (Never Exceed) 202 KIAS 
 VNO (Maximum Structural Cruise) 169 KIAS 
 VA (Maneuvering - 3800 lb.) 135 KIAS 
 VA (Maneuvering - 2700 lb.) 112 KIAS 
 VFE (Maximum Flaps Extended) 111 KIAS 
 VLO (Maximum Landing Gear Operation)  
       Extension 140 KIAS 
       Retraction 109 KIAS 
 VLE (Maximum Landing Gear Extended) 140 KIAS 
 VMC (Minimum Control Speed) 56 KIAS 
 
C.G. Range (+89.0) to (+93.0) at 3800 lb. 
 (+85.0) to (+93.0) at 3400 lb. 
 (+84.0) to (+93.0) at 2800 lb. or less 
 Straight line variation between points given. 
 Moment change due to retracting landing gear (+819 in-lb.)

A19SO Page 4 of 13 
 
 
89.0 93.0
LB
3800
3400
2800
1800
INCHES
85.0
84.0
1800
2800
3400
LB
 
Empty Weight C.G. Range None 
 
Maximum Weight Ramp 3816 lb. 
 Takeoff 3800 lb. 
 Landing 3800 lb. 
 
Number of Seats 4  (2 at +80.5, 2 at +118.1) 
 
Maximum Baggage 200 lb. at +142.8 
 
Fuel Capacity 110 gallons  (2 nacelle tanks) at +95.0     (108 gallons usable) 
 (See NOTE 1 for data on system fuel) 
 
Oil Capacity 8 quarts per engine (6 quarts per engine usable) 
 (See NOTE 1 for data on system oil) 
 
Control Surface Movements Ailerons Up 23° (±2°) Down 17° (±2°) 
 Stabilator Up 15° (±1°) Down 3° (±1°) 
 Rudder Left 37° (+1°, -0°) Right 37° (+1°, -0°) 
 Stabilator Trim Tab Down 9° (±1°) Up 4° (±1°) 
  (Stabilator neutral)  
 Wing Flaps Up 0° (±1°) Down 10°, 25°, 40° (±2°) 
 Rudder Trim Tab Left 26° (±2°) Right 26° (±2°) 
  (Rudder neutral)  
 Nose Wheel Travel Left 30° (±1°) Right 30° (±1°) 
 
Manufacturer's Serial Numbers 4495001 through 4495013, and 4496001 and up 
 
 
II. - Model PA-44-180T, Turbo Seminole, 4 PCLM  (Normal Category),  Approved November 29, 1979. 
Engine 1 Lycoming TO-360-E1A6D with carburetor setting 10-5256 
 1 Lycoming LTO-360-E1A6D with carburetor setting 10-5256 
 
Fuel 100 or 100LL aviation grade fuel 
 
Engine Limits For all operations, 36.5 in. Hg at 2575 r.p.m. (180 hp) 
 
Propeller and Propeller Limits Left Engine: 
 1 Hartzell, Hub Model HC-C2YR -2C ( )UF, Blade Model FC7666A-2R or 
FC7666AB-2R 
 
 Right Engine: 
 1 Hartzell, Hub Model HC-C2YR-2CL ( ) UF, Blade Model FJC7666A-2R or 
FJC7666AB-2R 
 
 Governor Assembly: 
  1 Hartzell Hydraulic Governor Model E-3-5 (Left) 
 or 1 Hartzell Hydraulic Governor Model U-3-10 (Left) with unfeathering accumulator

Page 5 of 13 A19SO 
 
  1 Hartzell Hydraulic Governor Model E-3-5L (Right) 
 or 1 Hartzell Hydraulic Governor Model U-3-10L (Right) with unfeathering 
 accumulator 
 or 1 Hartzell Hydraulic Governor Model E-8-5L (Right) with Synchrophaser 
 Installation, Piper Dwg. 86818-2  
 or 1 Hartzell Hydraulic Governor Model U-8-10L (Right) with unfeathering 
 accumulator and Synchrophaser Installation, Piper Dwg. 86818-2 
 
Propeller and Propeller Limits Pitch Setting at 30" Station: 
(continued) High 79° - 81°, Low 13.1° ± 0.2° 
 Diameter: Not over 74 inches 
                   Not under 72 inches 
 
 Spinner:   Hartzell P/N C-2285-3 Spinner Assy (Left) 
                  Hartzell P/N C-2285-3L Spinner Assy (Right) 
                  See NOTE 4. 
 
 Left Engine: 
 1 Hartzell, Hub Model HC-C3YR -2 ( )UF, Blade Model FC7663-5R or FC7663B-5R 
 
 Right Engine: 
 1 Hartzell, Hub Model HC-C3YR-2L ( ) UF, Blade Model FJC7663-5R or FJC7663B-5R 
 
 Governor Assembly: 
  1 Hartzell Hydraulic Governor Model E-3-5 (Left) 
 or 1 Hartzell Hydraulic Governor Model U-3-10 (Left) with unfeathering accumulator 
  1 Hartzell Hydraulic Governor Model E-3-5L (Right) 
 or 1 Hartzell Hydraulic Governor Model U-3-10L (Right) with unfeathering    
      accumulator 
 or 1 Hartzell Hydraulic Governor Model E-8-5L (Right) with Synchrophaser        
Installation, Piper Dwg. 86818-2 
 or 1 Hartzell Hydraulic Governor Model U-8-10L (Right) with unfeathering        
 accumulator and Synchrophaser Installation, Piper Dwg. 86818-2 
 
 Pitch Setting at 30" Station: 
 High 81° - 83°, Low 11.2° ± 0.1° 
 Diameter:  Not over 73 inches 
                   Not under 72 inches 
  
 Spinner: 
 Hartzell P/N C-4558 Spinner Assy (Left) 
 Hartzell P/N C-4558 Spinner Assy (Right) 
 See NOTE 4. 
 "Avoid continuous operation at manifold pressures below 15" Hg  above 12,000 feet 
altitude." 
 
Airspeed Limits VNE (Never Exceed) 202 KIAS 
 VNO (Maximum Structural Cruise) 170 KIAS 
 VA (Maneuvering - 3925 lb.) 137 KIAS 
 VA (Maneuvering - 2700 lb.) 112 KIAS 
 VFE (Maximum Flaps Extended) 111 KIAS 
 VLO (Maximum Landing Gear Operation)  
       Extension  140 KIAS 
       Retraction 109 KIAS 
 VLE (Maximum Landing Gear Extended) 140 KIAS 
 VMC (Minimum Control Speed) 57 KIAS

A19SO Page 6 of 13 
 
 
C.G. Range (+89.7) to (+93.0) at 3925 lb. 
 (+87.3) to (+93.0) at 3800 lb. 
 (+85.0) to (+93.0) at 3400 lb. 
 (+83.0) to (+93.0) at 2700 lb. or less 
 
89.7 93.0
3925
2400
INCHES
85.0
83.0
2400
87.33925
34003400
27002700
3800
LB.
 
 Empty Weight C.G. Range  None 
 
Maximum Weight Ramp 3943 lb. 
 Takeoff 3925 lb. 
 Landing 3800 lb. 
 
Number of Seats 4 (2 at +80.5, 2 at +118.1) 
 
Maximum Baggage 200 lb. at +142.8 
 
Fuel Capacity 110 gallons  (2 nacelle tanks) at +95.0     (108 gallons usable) 
 (See NOTE 1 for data on system fuel) 
 
Oil Capacity 6 quarts per engine (4 quarts per engine usable) 
 (See NOTE 1 for data on system oil) 
 
Maximum Operating Altitude 20,000 feet 
 
Control Surface Movements Ailerons (±2°) Up 23° Down 17° 
 Stabilator (±1°) Up 15° Down 3° 
 Rudder (+1°, -0°) Left 37° Right 37° 
 Stabilator Trim Tab (±1°) Up 4 Down 9° 
   (Stabilator neutral)  
 Wing Flaps (±2°) Up 0° Down 40° 
 Rudder Trim Tab (±2°) Left 26° Right 26° 
   (Rudder neutral)  
 Nose Wheel Travel (±1°) Left 30° Right 30° 
 
Manufacturer's Serial Numbers 44-8107001 through 44-8207020 
 
 
DATA PERTINENT TO ALL MODELS 
Datum 78.4" forward of wing leading edge at wing station 106. 
 
Leveling Means Two screws left side fuselage below window.

Page 7 of 13 A19SO 
 
Certification Basis Type Certificate No. A19SO issued March 10, 1978. 
 Date of application for Type Certificate, January 17, 1976. 
 
 PA-44-180:  Federal Aviation Regulations (FAR) Part 23 effective February 1, 1965, 
through Amendment 23-16 effective February 14, 1975;  FAR 23.1557(c)(1) as amended 
by Amendment 23-18 effective May 2, 1977;  and FAR 36 effective December 1, 1969, 
through Amendment 36-4, effective February 3, 1975. 
 Equivalent Safety Finding:  FAR 23.1545(a). 
 
 PA-44-180T:  FAR 23 effective February 1, 1965, through Amendment 23-16 effective 
February 14, 1975;  FAR 23.207 and 23.1091 as amended by Amendment 23-7 effective 
September 14, 1969;  FAR 23.201 and 23.203 as amended by Amendment 23-14 
effective December 20, 1973;  FAR 23.1093 and 23.1557(c)(1) as amended by 
Amendment 23-18 effective May 2, 1977;  FAR 23.1581(b)(2) as amended by 
Amendment 23-21 effective March 1, 1978;  FAR 23.1545(a) as amended by 
Amendment 23-23 effective December 1, 1978;  and FAR 36 effective 
December 1, 1969, through Amendment 36-9 effective April 3, 1978. 
 Compliance with FAR 23.1441 as amended by Amendment 23-9 effective June 17, 1970, 
shown with optional supplemental oxygen. 
 
For PA-44-180 aircraft equipped with Piper factory installed Avidyne Entegra Systems 
(see Piper Report VB-1940), the additional certification basis for installation specific 
items only is: FAR 23.1301, 23.1327, and 23.1335 as amended by Amendment 23-20 
effective September 1, 1977; FAR 23.1501 and 23.1541(a)(b) as amended by 
Amendment 23-21 effective March 1, 1978; FAR 23.603 and 23.605(a) as amended by 
Amendment 23-23 effective October 10, 1978; FAR 23.1529 as amended by Amendment 
23-26 effective October 14, 1980; FAR 23.1523 as amended by Amendment 23-34 
effective February 17, 1987; FAR 23.1322, 23.1331 and 23.1357(a)(2)(b)(c)(d) as 
amended by Amendment 23-43 effective May 10, 1993; FAR 23.305, 23.613, 
23.773(a)(1)(2), 23.1525 and 23.1549(a)(b)(c) as amended by Amendment 23-45 
effective September 7, 1993; FAR 23.301, 23.337(a)(1)(b)(1), 23.341(a), 23.473, 
23.561(b)(3)(e), 23.607 and 23.611 as amended by Amendment 23-48 effective March 
11, 1996; FAR 23.1303(a)(b)(f), 23.1307, 23.1309(a)(1)(3)(b)(c)(1)(2)(i)(iii)(3)(d)(e), 
23.1311, 23.1321, 23.1323(a)(c), 23.1329(d)(e)(f)(g)(h), 
23.1351(a)(1)(2)(i)(b)(1)(i)(2)(3)(d), 23.1353(d)(h), 23.1359(c), 23.1361(a)(b), 
23.1365(a)(b)(d)(e)(f) and 23.1431(a)(b)(d)(e) as amended by Amendment 23-49 
effective March 11, 1996; FAR 23.1325(a)(b)(1)(2)(i)(3), 23.1543(b)(c), 23.1545(a)(b), 
23.1553, 23.1555(a)(b), 23.1581(a)(b)(2)(3)(f), 23.1583(m) and 23.1585(j) as amended 
by Amendment 23-50 effective March 11, 1996; FAR 23.777(a)(b), 23.955(a)(3) and 
23.1337(a)(b)(1)(4)(c) as amended by Amendment 23-51 effective March 11, 1996; 
23.1305(a)(1)(2)(3)(b)(2)(3)(i)(4)(i)(5) as amended by Amendment 23-52 effective July 
25, 1996; and Special Condition for HIRF (Docket No. CE238, Special Condition 23-
178-SC), January 13, 2006. Eligible Serial Numbers 4496174, 4496224 and up. 
 
For PA-44-180 aircraft equipped with Piper factory installed Garmin G500 (see Piper 
Report VB-2314), the additional certification basis for installation specific items only is:  
 
{Unless otherwise noted in the table below, all sections are Amendment 23-16} 
Section Amendment  Section Amendment 
23.301 (a),(b),(c) 23-48  23.611 23-48 
23.303   23.771(a)  
23.305(a) 23-45  23.773(a)(2) 23-45 
23.307(a)   23.777(a),(b) 23-51 
23.337 23-48  23.867(a),(b),(c) 23-49 
23.561(a),(b)(3) 23-48  23.1301 23-20 
23.603 23-23  23.1303(a),(b),(c),(f) 23-49 
23.605(a) 23-23  23.1307 23-49 
23.607(a) 23-48  23.1308(a),(b),(c) 23-57 
23.609   23.1309(a)(1)(3),(b) 
             (c),(d),(e) 
23-49

A19SO Page 8 of 13 
 
Additional certification basis for installation specific items only (continued): 
{Unless otherwise noted in the table below, all sections are Amendment 23-16} 
Section Amendment  Section Amendment 
23.1311(a)(1)(2)(3)(4) 
             (5)(6),(b),(c) 
23-49  23.1367  
23.1321(a)(b)(c)(d) 
             (e)(f) 
23-49  23.1381(a),(b)  
23.1322(a),(b),(c),(d) 
             (e) 
23-43  23.1431(a),(b) 23-49 
23.1323(a),(c) 23-49  23.1501 23-21 
23.1325(b)(1),(b)(2)(i),(e) 23-50  23.1523 23-34 
23.1327(a) 23-20  23.1525 23-45 
23.1329(h) 23-49  23.1529 23-26 
23.1331(a),(b)(1) 23-43  23.1541(a),(b) 23-21 
23.1335 23-20  23.1543(b),(c) 23-50 
23.1351(a)(1),(a)(2)(i) 23-49  23.1545(a),(b) 23-50 
23.1353(h) 23-49  23.1559(c) 23-50 
23.1357(a),(b),(d) 23-43  23.1581(a),(b),(c),(f) 23-50 
23.1359(c) 23-49  23.1583(h),(m) 23-50 
23.1365(a),(b),(d),(e) 23-49  23.1585(j) 23-50 
Eligible Serial Numbers 4496325 and up. 
 
 
For PA-44-180 aircraft equipped with Piper factory installed Garmin G1000 Integrated 
Avionics System and 28 Volt Electrical System, the additional certification basis for 
installation specific items only is:  
 
14 CFR Part 23 regulations: 23.21, 23.23(a), 23.25, 23.29, 23.207(a), 23.251, 
23.301(a)(b)(c), 23.303, 23.305, 23.307, 23.337, 23.341(a)(c), 23.421(a), 23.473, 
23.561(a)(b)(3)(e), 23.601, 23.603, 23.605(a), 23.607, 23.609, 23.611, 23.613, 23.625, 
23.627, 23.729(e)(f), 23.771(a), 23.773(a)(1)(2), 23.777(a)(b), 23.867, 23.1041, 
23.1043(a)(b)(c)(d), 23.1047, 23.1163(a)(b)(d),  23.1301, 
23.1305(a)(1)(2)(3)(b)(2)(3)(i)(4)(i)(b)(5), 23.1306, 23.1307, 23.1308(a)(b)(c), 
23.1309(a)(1)(3)(b)(c)(d)(e), 23.1311,  23.1321, 23.1322, 23.1323(a)(c), 
23.1325(a)(b)(1)(2)(i), 23.1326, 23.1327(a), 23.1329(d)(g)(h), 23.1335, 23.1337(b)(1)(4), 
23.1351(a)(1)(2)(i)(b)(1)(i)(3)(c)(4)(d), 23.1353, 23.1357, 23.1359(c), 23.1361(a)(c), 
23.1365, 23.1367, 23.1381, 23.1431(a)(b)(e), 23.1501, 23.1507, 23.1523, 23.1525, 
23.1529, 23.1541(a)(b), 23.1543(b)(c), 23.1545(a)(b), 23.1549(a)(b)(c), 23.1553, 
23.1555(a)(b)(e)(1), 23.1563(a)(b), 23.1567(a), 23.1581(a)(c), 23.1583(g)(h)(m), 
23.1585(j), 23.1589 as amended by Amdt. 23-61; 23.1303(a)(b)(c)(f) as amended by 
Amdt. 23-62. 
Eligible Serial Numbers: 4496331, 4496339 and up. 
 
For PA-44-180 aircraft equipped with Piper factory installed Garmin GFC700 Autopilot, 
the additional certification basis for installation specific items only is:  
 
14 CFR Part 23 regulations: 23.21(b), 23.23(a)(b)(3), 23.25(a)(b), 23.29, 23.143(a)(b), 
23.207(a)(b)(c)(d)(e), 23.301(a)(b)(c), 23.303, 23.305, 23.307, 23.337, 23.341(a)(c), 
23.397, 23.399, 23.473, 23.561(a)(b)(3)(e), 23.601, 23.603, 23.605(a), 23.607, 23.609, 
23.611, 23.613, 23.625, 23.627, 23.681, 23.683, 23.693, 23.771(a), 23.777(a)(b), 
23.779(a)(2), 23.867, 23.1141(d), 23.1301(a)(b)(c)(d), 23.1306,  23.1308(a)(b)(c), 
23.1309(a)(1)(3)(b)(1)(3)(c)(d)(e), 23.1321(c), 23.1322(a)(b)(c)(d)(e), 
23.1329(a)(1)(b)(c)(d)(e)(f)(g)(h), 23.1335, 23.1351(a)(1)(2)(i), 23.1357(a)(b)(c)(d), 
23.1359(c), 23.1365, 23.1367(a)(b)(c)(d), 23.1431(a)(b)(e), 23.1501, 23.1523, 23.1525, 
23.1529, 23.1541(a)(b), 23.1555(a), 23.1581(a), 23.1583(g)(h)(m), 23.1585(a)(1)(j) as 
amended by Amdt. 23-61. 
Eligible Serial Numbers: 4496331, 4496367 and up.

Page 9 of 13 A19SO 
 
 
For PA-44-180 aircraft equipped with Piper factory installed Garmin G1000NXi Phase I 
as installed by Piper drawing number 107600-002, the additional certification basis for 
installation specific items only is:  
 
14 CFR Part 23 regulations: 23.21, 23.23(a), 23.25(a)(b), 23.29, 23.251, 23.301(a)(b)(c), 
23.303, 23.305, 23.307, 23.337, 23.341(a)(c), 23.421(a), 23.473, 23.561(a)(b)(3)(e), 
23.601, 23.603, 23.605(a), 23.607, 23.609, 23.611, 23.613, 23.625, 23.627, 23.729(e)(f), 
23.771(a), 23.773(a)(2), 23.777(a)(b), 23.867, 23.903(a), 23.1041, 23.1043(a)(b)(c), 
23.1047, 23.1163(a)(b)(d), 23.1301(a)(b)(c)(d), 23.1305(a)(1)(2) (3)(b)(2)(3)(i)(4)(i)(5), 
23.1306, 23.1307, 23.1308(a)(b)(c), 23.1309(a)(1)(3)(b)(c)(d)(e), 
23.1311(a)(1)(2)(3)(4)(6)(7)(b)(c), 23.1321(a)(b)(c)(d)(5)(e), 23.1322(a)(b)(c)(d)(e), 
23.1323(a)(c), 23.1325(a)(b)(1)(2)(i), 23.1326(a), 23.1327(a), 23.1329(h), 23.1335, 
23.1337(b)(1)(4), 23.1351(a)(1)(2)(i) (b)(1)(i)(3)(c)(4)(d), 23.1353(h), 
23.1357(a)(b)(c)(d), 23.1359(c), 23.1361(a), 23.1365, 23.1367(a)(b)(c)(d), 
23.1381(a)(b)(c), 23.1383(a)(b)(c)(d), 23.1385(a)(b)(c)(d), 23.1387(a)(b)(c)(d)(e), 
23.1389(a)(b)(c), 23.1391, 23.1393, 23.1395(a)(b), 23.1397(a)(b)(c), 
23.1401(a)(b)(c)(d)(e)(f), 23.1431(a)(b), 23.1523, 23.1525, 23.1529, 23.1541(a)(b), 
23.1543(b)(c), 23.1545(a)(b), 23.1549(a)(b)(c), 23.1553, 23.1555(a)(b)(e)(1), 
23.1563(a)(b), 23.1567(a), 23.1581(a)(c), 23.1583(g)(h)(m), 23.1585(j), 23.1589 as 
amended by Amdt. 23-61. 
14 CFR Part 23 Regulation 23.1303(a)(b)(c)(f) as amended by Amdt. 23-62 
 
Eligible Serial Numbers: 4496395, 4496397 and up. 
 
 
For PA-44-180 aircraft equipped with Piper Lycoming IO-360-B1G6 and LIO-360-B1G6 
Fuel Injected Engines as installed by Piper drawing number 107600-003 the additional 
certification basis for installation specific items only is: 
14 CFR Part 23 Regulations 23.33(a)(d), 23.865, 23.901(a)(1)(2)(b)(1)(2), 
23.903(a)(c)(1)(2)(d), ), 23.905(a)(b)(c), 23.907(a), 23.925(a)(c)(1)(2)(3), 
23.951(a)(b)(1), 23.953(a), 23.954(a)(b)(c), 23.959, 23.961, 23.963, 23.965, 23.967, 
23.969, 23.971, 23.973, 23.975(a), 23.977, 23.991(a)(1)(b), 23.993, 23.994, 23.995, 
23.997, 23.999, 23.1011, 23.1017, 23.1019(b), 23.1021, 23.1023, 23.1027, 
23.1091(a)(b)(1)(2)(3), 23.1103, 23.1121(a)(b)(c)(d)(e)(f), 23.1123, 23.1141(a)(b)(c)(d), 
23.1143, 23.1145, 23.1147, 23.1149, 23.1153, 23.1182, 23.1183, 23.1189, 23.1191, 
23.1193, 23.1521(a)(b)(1)(c)(1)(4)(d),  as amended by Amdt. 23-16 
14 CFR Part 23 Regulations 23.1101 as amended by Amdt. 23-43; 
14 CFR Part 23 Regulations 23.955(a)(c)(1)(3)(e)(3), 23.1093(a)(5), 23.1107  as 
amended by Amdt. 23-51;  
14 CFR Part 23 Regulations 23.21, 23.23, 23.25(a)(b), 23.29, 23.301, 23.303, 23.305, 
23.307, 23.337, 23.341(a)(c), 23.473, 23.561(a)(b)(3)(e), 23.601, 23.603, 23.605(a), 
23.607, 23.609, 23.611, 23.613, 23.625, 23.627, 23.777(a)(b), 23.779(b)(1), 23.1041, 
23.1043, 23.1047, 23.1163, 23.1301(a)(b)(c)(d), 
23.1305(a)(1)(2)(3)(4)(b)(2)(3)(i)(4)(i)(5), 23.1309(a)(1)(a)(3)(b)(f), 
23.1337(a)(1)(2)(3)(b)(1)(4)(c)(d)(1), 23.1351(b)(1)(i), 23.1357(a)(b)(c), 23.1359(c), 
23.1365(c), 23.1431(b), 23.1529, 23.1541(a)(b), 23.1549(a)(b)(c), 23.1553, 
23.1555(a)(b)(c)(1)(3)(4)(d)(e)(1)(2), 23.1581(a), 23.1583(g)(h)(m), 23.1585(j), 23.1589 
as amended by Amdt. 23-61; 
Eligible Serial Numbers: 4496404, 4496417 and up.

A19SO Page 10 of 13 
 
 
For PA-44-180 aircraft equipped with Piper factory installed Garmin G1000NXi Phase II 
as installed by Piper drawing number 107600-002 or 107600-003, the additional 
certification basis for installation specific items only is:  
14 CFR Part 23 Regulation 23.903(d) as amended by Amdt. 23-16 
14 CFR Part 23 Regulations 23.21, 23.23, 23.25(a)(b), 23.29, 23.251, 23.301(a)(b)(c), 
23.303, 23.305(a)(b), 23.307(a), 23.337(a)(b), 23.341(a)(c), 23.473, 23.561(a)(b)(3)(e), 
23.601, 23.603, 23.605(a), 23.607, 23.609, 23.611, 23.613, 23.625, 23.627, 23.729(e)(f), 
23.771(a), 23.773(a)(1)(2), 23.777(a)(b), 23.867, 23.1301(a)(b)(c)(d), 
23.1305(a)(1)(2)(3)(b)(2)(3)(i)(4)(i)(5), 23.1306, 23.1307, 23.1308(a)(b)(c), 
23.1309(a)(1)(3)(b)(c)(d)(e), 23.1311(a)(1)(2)(3)(4)(6)(7)(b)(c), 
23.1321(a)(b)(c)(d)(5)(e), 23.1322(a)(b)(c)(d)(e), 23.1323(a)(c), 23.1325(a)(b)(1)(2)(i), 
23.1326(a)(b), 23.1327(a), 23.1329(d)(e)(g)(h), 23.1335, 23.1337(b)(1)(4), 
23.1351(a)(1)(2)(i)(b)(1)(i)(ii)(iii)(3)(c)(4)(d), 23.1353(h), 23.1357(a)(b)(c)(d), 
23.1359(c), 23.1361(a), 23.1365, 23.1367(c)(d), 23.1381(a)(b)(c), 23.1431(a)(b)(e), 
23.1501, 23.1523, 23.1525, 23.1529, 23.1541(a)(b), 23.1543(b)(c), 23.1545(a)(b), 
23.1549(a)(b)(c), 23.1553, 23.1555(a)(b)(e)(1), 23.1581(a)(c), 23.1583(g)(h)(m), 
23.1585(j), 23.1589(a) as amended by Amdt. 23-61 
14 CFR Part 23 Regulation 23.1303(a)(b)(c)(f) as amended by Amdt. 23-62 
 
Eligible Serial Numbers: 4496432, 4496447 and up. 
 
 
For PA-44-180 aircraft equipped with Piper factory installed Garmin G5 Standby 
Instrument as installed by Piper drawing number 107600-002 or 107600-003, the 
additional certification basis for installation specific items only is: 
 
 14 CFR Part 23.303, 23.307(a), 23.1381(a)(b)  as amended by Amndt. 23-0 
 14 CFR Part 23.771(a) as amended by Amndt. 23-14 
 14 CFR Part 23.1541(a)(b) as amended by Amndt. 23-21 
 14 CFR Part 23.601, 23.603, 23.605(a) as amended by Amndt. 23-23 
 14 CFR Part 23.1529 as amended by Amndt. 23-26 
 14 CFR Part 23.1322(a)(e), 23.1357(a)(b)(c)(d) as amended by Amndt. 23-43 
 14 CFR Part 23.305, 23.613(a)(b), 23.773(a)(2) as amended by Amndt. 23-45 
 14 CFR Part 23.301(a), 23.337(a)(b), 23.607(b) as amended by Amndt. 23-48 
 14 CFR Part 23.1307, 23.1309(b)(1)(e), 23.1321(c)(e), 23.1351(a)(1)(2)(i), 23.1359, 
23.1365(a)(b)(c)(d)(e) as amended by Amndt. 23-49 
 14 CFR Part 23.1325(a)(b), 23.1543(b), 23.1581(a)(b)(d)(f) as amended by Amndt. 23-50 
 14 CFR Part 23.25(a)(b), 23.29 as amended by Amndt. 23-61 
 14 CFR Part 23.251(a), 23.561(a)(b)(3)(c), 23.777(a)(b), 23.853(a), 23.1301(a)(b)(c), 
23.1303(a)(b)(c)(f), 23.1309(a)(1)(2), 23.1311(a)(1)(2)(3)(6)(7)(b), 23.1323(a)(b)(c), 
23.1331(a)(b)(1)(c), 23.1353(h), 23.1431(a)(b), 23.1545(a)(b)(c), 23.1555(a)(b), 23.1583(m), 
23.1585(a) as amended by Amndt. 23-62 
 14 CFR Part 23.2515(a)(b), 23.2520(a)(b) as amended by Amndt. 23-64 
 
Eligible Serial Numbers: 4496471, 4496498, 4496502 and up. 
 
 
For PA-44-180 aircraft equipped with Piper factory installed Hartzell HC-C2YR-
2C(L)EUFP/F(J)C7497 propeller assemblies installed by 89360-010/89360-011 or 
44P72A001-001/ 44P72A001-002 the additional certification basis for installation 
specific items only is: 
 
14 CFR Part 23.33(a)(d), 23.251, 23.925(a)(c), 23.1521(a)(b)(1)(c)(1)(4) as amended by 
Amndt. 23-0 
14 CFR Part 23.49, 23.65, 23.67, 23.75, 23.77, 23.149, 23.1041, 23.1043, 23.1047, 
23.1501(a)(b)(c) as amended by Amndt. 23-7 
14 CFR Part 23.1541(a)(b), 23.1559(a)(1)(b), 23.1581, 23.1583, 23.1585, 23.1587 as amended 
by Amndt. 23-13 
14 CFR Part 23.201 as amended by Amndt. 23-14 
14 CFR Part 23.51(b) as amended by Amndt. 23-16 
14 CFR Part 23.1549 as amended by Amndt. 23-17  
14 CFR Part 23.901 as amended by Amndt. 23-18 
14 CFR Part 23.1529 as amended by Amndt. 23-26

Page 11 of 13 A19SO 
 
14 CFR Part 23.905(a)(b)(c)(d), 23.907 as amended by Amndt. 23-59 
14 CFR Part 23.25(a)(b), 23.301(a)(b)(c), 23.303, 23.305, 23.307, 23.337, 23.341(a)(c), 
23.361(a)(c), 23.363, 23.473, 23.601,23.603, 23.605(a), 23.607, 23.609, 23.611, 23.627 as 
amended by Amndt. 23-61 
 
Eligible Serial Numbers: 4496471, 4496517 and up. 
 
 
For PA-44-180 aircraft equipped with optional non-Halon fire extinguisher additional 
certification basis for installation specific items only is: 
 
14 CFR 23.851, 23.1301, 23.1529, 23.1541 as amended by Amdt. 23-62 
 
Eligible Serial Numbers: 4496631 and up. 
 
 
PA‐44-180 aircraft equipped with Piper factory installed G1000 NXi System upgraded 
with software that incorporates a landing gear warning inhibit function and/or wireless 
local area network capabilities, as installed by Piper Drawing Number 107700-004 Rev K 
or later FAA approved revision, the additional certification basis for installation specific 
items only is:  
 
14 CFR Part 23.2010, 23.2505, 23.2510, 23.2605(b)(c) as amended by Amndt. 23 -64  
14 CFR Part 23 23.2500(b), 23.2600(b) as amended by Amndt. 23 -65 
 
Eligible Serial Numbers: 4496616, 4496659 and up. 
 
 
 
Production Basis Production Certificate No. 206.  Production Limitation Record issued and the 
manufacturer authorized to issue airworthiness certificate under the Delegation Option 
provisions of FAR 21. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification.  In addition, the 
following items of equipment are required: 
 
 PA-44-180:  POH and FAA Approved AFM, VB-860, approved March 23, 1978, for S/N 
44-7995001 through 44-8195026. 
 POH and FAA approved AFM, VB-1380, approved July 20, 1989, for S/N 4495001 
through 4495013. 
 POH, VB-1616, approved July 12, 1995, for S/N 4496001 and up. 
 POH, VB-1942, approved May 26, 2006, for S/N 4496174 and 4496224 and up when 
Avidyne Entegra System (See Piper Report VB-1940) is installed 
 POH, VB-2307, approved  June 5, 2013, for S/N 4496331, 4496339 and up, when the 
Garmin G1000 Integrated Avionics System is installed 
POH, VB-2307 Rev 02 or later, approved  October 28, 2014, for S/N: 4496331, 4496367 
and up, when the Garmin G1000 and/or GFC700 autopilot installed 
POH, VB-2636 Rev 00 or later, approved November 3, 2016, for S/N: 4496395, 4496397 
and up, when the Garmin G1000 is installed by Piper drawing number   107600-002 
POH, VB-2636 Rev 01 or later, approved December 15, 2017, for S/N: 4496404, 
4496417 and up, when the Lycoming Fuel Injected Engines are installed. 
POH, VB-2636 Rev 03 or later, approved October 1, 2018, for S/N: 4496432, 4496447 
and up, when Garmin G1000NXi is installed by Piper Drawing Number 107600-002 or 
107600-003. 
POH, VB-2636, Rev 05 or later, approved April 2, 2020 for SN4496471, 4496517 and up 
when optional Hartzell 2-Blade Scimitar Propeller Model HC-C2YR-
2C(L)EUFP/F(J)C7497 propeller assembly installed by Piper Drawing Number 89360-
010/89360-011 or 44P72A001-001/ 44P72A001-002. 
POH, VB-2636, Rev 05 or later, approved April 2, 2020 for SN4496471, 4496498, 
4496502 and up, when Garmin G5 Standby instrument is installed by Piper Drawing 
Number 107600-002 or 107600-003.

A19SO Page 12 of 13 
 
POH, VB-2636, Rev 9 or later, approved October 10, 2024 for SN4496631 and up, when 
non-Halon fire extinguisher is installed. 
POH, VB-2636, Rev 10 or later, approved September 29, 2026 for SN 4496616, 4496659 
& Up  and up, when G1000 NXi System upgraded with software that incorporates a 
landing gear warning inhibit function and/or wireless local area network capabilities is 
installed by Piper Drawing Number 107700-004 Rev K or later approved revision.  
 
 PA-44-180T:  POH and FAA approved AFM, VB-1100, approved March 14, 1980, for 
S/N 44-8107001 through 44-8207020.

Page 13 of 13 A19SO 
 
NOTE 1. Current Weight and Balance Report, including list of equipment included in certificated 
empty weight and loading instructions when necessary, must be provided for each aircraft 
at the time of original certification. 
 
 The certificated empty weight and corresponding center-of-gravity locations must include 
undrainable system oil (not included in oil capacity) and unusable fuel as noted below: 
 
  Fuel:  12.0 lb. at (+95.0) 
  Oil:      3.6 lb. at (+68.8) 
 
NOTE 2. All placards required in the Pilot's Operating Handbook and FAA Approved Airplane 
Flight Manual must be installed in the appropriate locations. 
 
NOTE 3. Refer to the Airplane Maintenance Manual for Instructions for Continued Airworthiness. 
Life limited components are based on general aircraft usage for this aircraft class and are 
contained in Chapter 4 of the appropriate Airplane Maintenance Manual for the models 
listed below: 
 
a) PA-44-180 
  For S/N 44-7995001 through 44-8195026 and 
  For S/N 4495001 through 4495013 
   Airplane Maintenance Manual 761-664 
  
  For S/N 4496001 and up 
   Airplane Maintenance Manual 761-892 
   
b) PA-44-180T 
  For S/N 44-8107001 through 44-8207020 
   Airplane Maintenance Manual 761-664 
 
NOTE 4. The PA-44-180, S/N 44-7995001 through 44-8195026, may be operated without spinner 
domes or without spinner domes and rear bulkheads, except when equipped with three-
bladed propellers and air conditioning, in which case only the spinner dome may be 
removed. 
 
 The PA-44-180, S/N 4495001 through 4495013, and 4496001 and up, may be operated 
with only the spinner dome removed. 
 
NOTE 5. The following serial numbers are not eligible for airworthiness certification in the United 
States:  44-7995235 and 44-7995298. 
 
NOTE 6.  Engines must be both carbureted or both fuel injected, mixing carbureted with fuel 
injected engines is prohibited as well as mixing spinners. 
 
. . .END. . .
```

## ADs (31, in force first)

- [AD 2024-10-04](https://openairdocs.org/ad/2024-10-04): Wing, Attach Fittings · Piper PA-28-181, PA-28R-201, PA-44-180 and 1 more. Effective Jun 6, 2024
- [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023
- [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 2015-26-08](https://openairdocs.org/ad/2015-26-08): Rudder Control System · Piper PA-44-180 and PA-44-180T. Effective Jan 20, 2016
- [AD 2013-02-13](https://openairdocs.org/ad/2013-02-13): Stabilizer Control System · Piper PA-28-140, PA-28-150, PA-28-151 and 33 more. Effective Mar 11, 2013
- [AD 2010-15-10](https://openairdocs.org/ad/2010-15-10): Control wheel shafts · Piper PA-28-140, PA-28-150, PA-28-151 and 33 more. Effective Aug 31, 2010
- [AD 2009-05-05](https://openairdocs.org/ad/2009-05-05): Primary Flight Displays · Avidyne Primary Flight Display (S-TEC STC SA09543AC-D or 2 others). Effective Apr 3, 2009
- [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006
- [AD 2005-15-10](https://openairdocs.org/ad/2005-15-10): Combustion heater fuel pumps · Piper PA-34-200T, PA-34-220T, PA-44-180 and 1 more. Effective Aug 26, 2005
- [AD 2004-25-16 R1](https://openairdocs.org/ad/2004-25-16-R1): Fuel regulator shutoff valve · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 64 more. Effective Jun 20, 2005
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 2004-14-12](https://openairdocs.org/ad/2004-14-12): Control wheel attaching hardware · Piper PA-28-161, PA-28-181, PA-28R-201 and 8 more. Effective Aug 10, 2004
- [AD 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000
- [AD 85-02-05 R1](https://openairdocs.org/ad/85-02-05-R1): Piper P/N s 81090-02, 683-107 Placard Installation · Lavia Argentina PA-25, PA-25-235, PA-25-260 and 32 more. Effective Nov 21, 1997
- [AD 96-10-03](https://openairdocs.org/ad/96-10-03): Flap Handle Attach Bolt · Piper PA-28-140, PA-28-150, PA-28-151 and 28 more. Effective Jun 14, 1996
- [AD 94-14-14](https://openairdocs.org/ad/94-14-14): Nose Landing Gear Modification · Piper PA-28R-180, PA-28R-200, PA-28R-201 and 5 more. Effective Aug 19, 1994
- [AD 94-13-11](https://openairdocs.org/ad/94-13-11): Main Landing Gear Trunnion · Piper PA-34-200, PA-34-200T, PA-34-220T and 2 more. Effective Aug 12, 1994
- [AD 86-20-11](https://openairdocs.org/ad/86-20-11): Ammeter Replacement · Piper PA-44-180T. Effective Oct 17, 1986
- [AD 81-16-10](https://openairdocs.org/ad/81-16-10): Outboard Leading Edge Skin · Piper PA-44-180 and PA-44-180T. Effective Sep 17, 1981
- [AD 81-10-01](https://openairdocs.org/ad/81-10-01): Nose Cone Spars · Piper PA-44-180. Effective Apr 30, 1981
- [AD 81-10-04](https://openairdocs.org/ad/81-10-04): Aileron Modification · Piper PA-44-180. Effective Apr 30, 1981
- [AD 80-21-11](https://openairdocs.org/ad/80-21-11): Left and Right Ailerons · Piper PA-44-180. Effective Oct 17, 1980
- [AD 80-14-03](https://openairdocs.org/ad/80-14-03): Bendix, King or Narco Transmitters · Piper PA-28-161, PA-28-181, PA-28-201T and 16 more. Effective Jul 1, 1980
- [AD 80-12-03](https://openairdocs.org/ad/80-12-03): Nose Landing Gear · Piper PA-44-180. Effective Jun 3, 1980
- [AD 79-12-11](https://openairdocs.org/ad/79-12-11): Fuel Primer Modification Kits · Piper PA-44-180. Effective Jun 21, 1979
- [AD 79-05-11](https://openairdocs.org/ad/79-05-11): Engine Power Control Loss · Piper PA-44-180. Effective Mar 15, 1979
- [AD 79-02-02](https://openairdocs.org/ad/79-02-02): Fuel Supply Lines · Piper PA-44-180. Effective Jan 24, 1979
- [AD 78-25-03](https://openairdocs.org/ad/78-25-03): Hose Assemblies · Piper PA-23-250, PA-28R-180, PA-28R-200 and 11 more. Effective Jan 15, 1979
- [AD 2008-06-28](https://openairdocs.org/ad/2008-06-28) (historical): Primary flight display · Avidyne Primary Flight Display (S-TEC STC SA09543AC-D or 2 others). Effective Apr 10, 2008
- [AD 2008-06-28 R1](https://openairdocs.org/ad/2008-06-28-R1) (historical): Primary Flight Displays (PFDs) · Avidyne Primary Flight Displays, 441, LC41-550FG and 22 more. Effective Apr 10, 2008
- [AD 2003-11-14](https://openairdocs.org/ad/2003-11-14) (historical): Combustion heater fuel pump · Piper PA-34-200T, PA-34-220T, PA-44-180 and 1 more. Effective Jun 20, 2003

## Registered aircraft by registry model (OpenAirDocs)

- [Piper PA-44-180](https://openairdocs.org/model/piper-pa-44-180): 558 aircraft (registry codes 7104402, 7104406)
- [Piper PA-44-180T](https://openairdocs.org/model/piper-pa-44-180t): 38 aircraft (registry code 7104404)
- [New Piper PA-44-180](https://openairdocs.org/model/new-piper-pa-44-180): 4 aircraft (registry code 7104403)
- [New Piper PA-44-180T](https://openairdocs.org/model/new-piper-pa-44-180t): 0 aircraft (registry code 7104405)

## STCs approved under this data sheet (200, first 50)

- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation
- [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 SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. 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 SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA01147WI](https://openairdocs.org/stc/SA01147WI): Installation of Concorde FLA or VRSLA series batteries in Piper Light Airplanes.. Concorde Battery Corporation
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES 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 SA01120SE](https://openairdocs.org/stc/SA01120SE): Installation of Door Steward.. Mountain View Aviation LLC
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA02760SE](https://openairdocs.org/stc/SA02760SE): Installation of Absolute Solutions LLC Gear Warning System Upgrade. Absolute 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 SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc.
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc
- [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 SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA02725SE](https://openairdocs.org/stc/SA02725SE): Installation of Absolute Solutions LLC Gear Warning System Upgrade. Absolute Solutions LLC
- [STC SA00262AT](https://openairdocs.org/stc/SA00262AT): Installation of flap gap seals.. Whelen Aerospace Technologies
- [STC SA00263AT](https://openairdocs.org/stc/SA00263AT): Installation of 'speed splitter' flap bracket fairings.. Whelen Aerospace Technologies
- [STC SA00264AT](https://openairdocs.org/stc/SA00264AT): Installation of main landing gear fairings.. Whelen Aerospace Technologies
- [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation
- [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. 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 SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA04195NY](https://openairdocs.org/stc/SA04195NY): Installation of the KFC 230 Aerocruze Automatic Flight Control System (FCS) upgraded from KFC 200 FCS. Honeywell International Inc. (Bendix King)
- [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 SA02265SE](https://openairdocs.org/stc/SA02265SE): Installation of a camera housing. Airborne Sensor LLC
- [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 SA04182NY](https://openairdocs.org/stc/SA04182NY): Installation of BendixKing KA 310 Autopilot Adapter. Honeywell International Inc
- [STC SA4235WE](https://openairdocs.org/stc/SA4235WE): Installation of inflatable door seal.. TALCO Aviation Corp.
- [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA1504CE](https://openairdocs.org/stc/SA1504CE): Installation of King KFC 200 automatic flight control system, (2 axis), with or without flight director.. Honeywell International Inc
- [STC SA2321CE-D](https://openairdocs.org/stc/SA2321CE-D): Installation of the Bendix/King KFC 150 two axis Automatic Flight Control System.. Honeywell International Inc
- [STC SA01560WI-D](https://openairdocs.org/stc/SA01560WI-D): Installation of the Honeywell KFD 840 Primary Flight Display System.. Honeywell 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

All 200: https://openairdocs.org/tcds/A19SO/stcs.md

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