# TCDS 7A15: Pilatus Aircraft Ltd.

- Type: Type certificate data sheet
- Status: Current
- Holder: Pilatus Aircraft Ltd.
- Revision: 15
- Revised: July 7, 2021
- Product: Aircraft, Small Airplane
- Certification basis: CAR 3, CAR 10
- Registered aircraft: 22, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/2f/5a/2f5abe020534915b9c2e1f86286afea6f6a5e1b2b0e5917c4347244b0d8d0096
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/12C8A4590B6D64ED8625870B0061E669.0001
- Page: https://openairdocs.org/tcds/7A15

## Models (15)

As the data sheet lists them.

- PC-6/B2-H2
- PC-6/350-H1
- PC-6/C1-H2
- PC-6/B-H2
- PC-6/A-H2
- PC-6/C-H2
- PC-6
- PC-6/A-H1
- PC-6-H2
- PC-6-H1
- PC-6/B2-H4
- PC-6/A
- PC-6/350-H2
- PC-6/350
- PC-6/B1-H2

## 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 
Rev. No. 15 6 14 14 6 14 7 15 14 14 12 
 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION  
 
7A15 
Revision 15 
PILATUS 
PC-6, PC-6-H1, PC-6-H2 
PC-6/350, PC-6/350-H1, PC-6/350-H2 
PC-6/A, PC-6/A-H1, PC-6/A-H2 
PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2 
PC-6/B2-H4, PC-6/C-H2, PC-6/C1-H2 
 
July 07, 2021 
 
TYPE CERTIFICATE DATA SHEET NO. 7A15 
 
This data sheet which is a part of Type Certificate No. 7A15 prescribes conditions and limitations under which the product for 
which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. 
 
Type Certificate Holder.  Pilatus Aircraft Ltd. 
     Stans, Switzerland 
 
I. Model PC-6,    11 PCLM  (Normal Category), Approved:  November 9, 1961 
 Model PC-6-H1, 11 PCLM  (Normal Category), Approved:  January 7, 1964 
 Model PC-6-H2, 11 PCLSM (Normal Category), Approved:  October 16, 1964. 
 
Engine.    Lycoming GSO-480-B1A6 
 
Fuel.    100/130 Minimum grade aviation gasoline. 
 
Engine Limits.   (Straight line manifold pressure variation with altitude shown) 
        HP     R.P.M.    M.P.    Altitude 
     Take-off    340     3400      48.0          S.L.  
     Take-off    340     3400      44.5        7900'  
     Max. Continuous   320     3200      45.5         S.L.  
     Max. Continuous  320     3200      43.0       8000'  
 
Propeller and   Hartzell constant speed propeller 
 Propeller Limits.   Hub HC-83X20-1B or HC-A3X20-1D, blades 9333C-0 to -5 
     Diameter maximum 93 in. minimum 88 in. 
     (no further reduction permitted) 
     Pitch setting at 30 in. station:  low 15 o, high 36o. 
 
Fuel Capacity.   Total capacity 105 US gal. or 127 US gal. 
     (2 tanks of 52.5 or 63.5 US gal.) (+31.1) 
     Usable capacity 104 US gal. or 126 US gal. 
     (2 tanks of 52.0 or 63.0 US gal.) (+31.1) 
 
Oil Capacity.   3.5 US gal. (-43.9).

Page 2 of 11 7A15 
II. Model PC-6/350,    11 PCLM  (Normal Category), Approved:  September 12, 1962 
 Model PC-6/350-H1, 11 PCLSM (Normal Category), Approved:  January 7, 1964 
 Model PC-6/350-H2, 11 PCLSM (Normal Category), Approved:  October 16, 1964. 
 
Engine.    Lycoming IGO-540-A1A. 
 
Fuel.    100/130 Minimum grade aviation gasoline. 
 
Engine Limits.   (Straight line manifold pressure variation with altitude shown) 
         HP      R.P.M. 
     Take-off (Max. 5 min)         350      3400 full throttle at S.L. 
     Max. Continuous               325      3000 full throttle at S.L. 
 
Propeller and   Hartzell constant speed feathering propeller 
 Propeller Limits.   Hub HC-B3Z-30-2B, blades 9349 + 1/2 
     Diameter maximum 93.5 in. minimum 93.5 in. 
     (no reduction permitted) 
     Pitch setting at 30 in. station:  low 15o, high 87o. 
 
Fuel Capacity.   Total capacity 105 US gal. or 127 US gal. 
     (2 tanks of 52.5 or 63.5 US gal.) (+31.1) 
     Usable capacity 104 US gal. or 126 US gal. 
     (2 tanks of 52.0 or 63.0 US gal.) (+31.1). 
 
Oil Capacity.   3.5 US gal. (-43.9) 
 
 
III. Model PC-6/A,  11 PCLM  (Normal Category), Approved:  November 27, 1962 
 Model PC-6/A-H1, 11 PCLM  (Normal Category), Approved:  January 7, 1964 
 Model PC-6/A-H2, 11 PCLSM (Normal Category), Approved:  October 16, 1964 
 
Engine.    Turbomeca Astazou II E or Astazou II G 
 
Fuel.    ASTM-D-1655 Spec. 
       Jet A or Jet A1 (French Air 3405, TR.0) 
       Jet B (French Air 3407, TR.4) 
     MIL-T-5624 Spec. 
       JP-4 
       JP-5, Spec. gravity not over 0.8 (French Air 3404, TR.5) 
        SHP      RPM      Alt.     Power      Max. EGT 
                     %             (C)  
 
     Take-off (max. 5 min)   523      43500      S.L.      100             525  
     Max. Continuous         473      43500      S.L.       88              500  
     Starting transient 
        30 sec.                                                                  550 
        less than 3 sec.                                                        630 
 
Propeller and   Ratier Figeac turbine propeller, electrically controllable 
 Propeller Limits.        feathering and reversing. 
     Hub FH 76-1-07, blades FH 76.207. 
     Diameter maximum 98.4 in. minimum 97.4 in. 
     (no further reduction permitted) 
     Pitch setting at 34.44 in. station: 
      Reverse  -14o (mechanical stop) 
      Starting  - 1.5o 
      Flight minimum + 2.5o (electrical stop) 
      Feathering + 87o  (mechanical stop)

Page 3 of 11 7A15 
III. Model PC-6/A, Model PC-6/A-H1, Model PC-6/A-H2    (cont’d) 
Fuel Capacity.   Total capacity:  130 US gal. or 173 US gal. 
     (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
     Usable capacity:  128 US gal. or 170 US gal. 
     (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
 
Oil Capacity.   2.11 US gal. (-94.8) (engine integral) 
 
IV. Model PC-6/B-H2, 11 PCLSM (Normal Category), Approved:  March 10, 1967 
 
Engine.    United Aircraft of Canada Ltd.  PT6A-6A 
 
Fuel.    JP-1, JP-4 and JP-5 fuels conforming to UACL Specification No. 522 and later revisions. 
 
Engine Limits.                               SHP     Torque      G.G.         Prop.        TIT 
                                                (psi)       RPM         RPM        ( oC) 
     Take-off (max. 5 min)      550        42.5       38.100       2.200        994 
                   (101.5%)     (100%) 
     Max. Continuous            500        38.5       38.100       2.200        952  
                   (101.5%)     (100%) 
     Starting (max. 2 sec)      ---           ---           ---              ---         1038 
     Max. reverse               500        42.5                                           994  
 
Propeller and   Hartzell feathering and reversing constant speed propeller 
 Propeller Limits.   Hub:  HC-B3TN-3C, blades T-10173C or T-10173CH 
     Diameter:  max. 101 in., min. 99 in. 
     (no further reduction permitted) 
     Pitch setting at 30 in. station:  Reverse  -11.5o 
                                       Feathering  +85.5o 
                                       Minimum in flight     0o 
 
Fuel Capacity.   Total capacity:  130 US gal. or 173 US gal. 
     (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
     Usable capacity:  128 US gal. or 170 US gal. 
     (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
 
Oil Capacity.   Total capacity:  2.3 US gal. (-80) (engine integral) 
     Usable capacity: 1.5 US gal.  
 
 
V. Model PC-6/B1-H2, 11 PCLSM (Normal Category), Approved:  March 10, 1967 
 
Engine.    United Aircraft of Canada Ltd.  PT6A-20 
 
Fuel.    JP-1, JP-4 and JP-5 fuels conforming to UACL Specification No. 522 and later revisions. 
 
Engine Limits.                            SHP      Torque      G.G.            Prop.       ITT 
                                            (psi)        RPM            RPM       ( oC) 
     Take-off and maximum    550          42.5       38.100          2.200      750  
     continuous up to                                        (101.5%)       (100%) 
     21o at S.L. 
     Starting (max. 2 sec)   ---             ---            ---                ---        1090 
     Max. reverse            500          42.5                                            750

Page 4 of 11 7A15 
V. Model PC-6/B1-H2    (cont’d) 
Propeller and   Hartzell feathering and reversing constant speed propeller 
 Propeller Limits.   Hub:  HC-B3TN-3C or HC-B3TN-3D, blades;  T-10173C or T-10173CH or T-10178C 
or T-10178CH. 
     Diameter:  max. 101 in., min. 99 in. 
     (no further reduction permitted). 
     Pitch setting at 30 in. station:  Reverse   -11.5o 
         Feathering  +85.5o 
         Minimum in flight             0o 
 
Fuel Capacity.   Total capacity:  130 US gal. or 173 US gal. 
     (2 tanks of 63.5 or 85 US gal.) (+31.1) plus  
     1 booster pump tank of 3 US gal. (+ 111.0) 
     Usable capacity:  128 US gal. or 170 US gal. 
     (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
 
Oil Capacity.   Total capacity:  2.3 US gal. (-80) (engine integral) 
     Usable capacity: 1.5 US gal. 
 
 
VI. Model PC-6/B2-H2, 11 PCSLM (Normal Category), Approved:  August 21, 1973. 
 
Engine.    United Aircraft of Canada Ltd.  PT6A-27 
 
Fuel.    JP-1, JP-4 and JP-5 fuels conforming to UACL Specification No. 522 and later revisions. 
 
Engine Limits.                            SHP       Torque       G.G.          Prop.           ITT 
                                            (psi)       RPM           RPM           ( oC) 
     Take-off                 550         42.5          38.100         2.200          725  
                                                               (101.5%)      (100%) 
     Max. Continuous         550         42.5          38.100         2.200          725  
                                                                (101.5%)      (100%) 
     Starting (max. 2 sec)   ---            ---               ---                 ---          1090 
     Max. reverse            550         42.5                                     725 
 
Propeller and   Hartzell feathering and reversing constant speed propeller 
 Propeller Limits.   Hub:  HC-B3TN-3C or HC-B3TN-3D, blades T-10178C or T-10178CH or T-10173C or 
T-10173CH. 
     Diameter:  max. 101 in., min. 99 in. 
     (no further reduction permitted) 
     Pitch setting at 30 in. station:  Reverse   -10.0o 
         Feathering  +85.5o 
         Minimum in flight         0.5o 
 
Fuel Capacity.   Total capacity:  130 US gal. or 173 US gal. 
     (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
     Usable capacity:  128 US gal. or 170 US gal. 
     (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
 
Oil Capacity.   Total capacity:   2.3 US gal. (-80) (engine integral) 
     Usable capacity:  1.5 US gal.

Page 5 of 11 7A15 
VII. Model PC-6/C-H2, 11 PCLSM (Normal Category), Approved:  March 10, 1967. 
 
Engine.    Airesearch TPE 331-25D. 
 
Fuel.    JP-1, JP-4 and JP-5 fuels conforming to Airesearch Manufacturing Company of Arizona 
Report PE-5064 R. 
 
Engine Limits.                               SHP            Torque         RPM      EGT 
                                                   (psi)                        (0oC) 
  
     Take-off                  575              57.7          41.730           571 
                                                       (100%) 
     Max. Continuous            500                 51.7          41.730           535 
                                                        (100%) 
     Absolute Maximum           ---               ---           43.820 
     (max. 5 sec)                                       (105%) 
     Starting (max. 10 sec)     ---                   ---                       ---             815 
 
Propeller and   Hartzell feathering and reversing constant speed propeller 
 Propeller Limits.   Hub:  HC-B3TN-5C, blades T-10178C or T-10178CH 
     Diameter:  max. 101 in., min. 99 in. 
     (no further reduction permitted) 
     Pitch setting at 30 in. station: Reverse   - 9.5o 
                                        Feathering  +87o 
                                        Start   + 2o 
                       Minimum in flight  + 5o 
 
Fuel Capacity.   Total capacity:  130 US gal. or 173 US gal. 
     (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
     Usable capacity:  128 US gal. or 170 US gal. 
     (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
 
Oil Capacity.   2.9 US gal. (-103) (engine integral) 
 
 
VIII. Model PC-6/C1-H2, 11 PCLSM (Normal Category), Approved:  August 21, 1973. 
 
Engine.    Airesearch TPE 331-1-100 
 
Fuel.    Fuels conforming to Airesearch Manufacturing Company of Arizona Report  
     PE-5064R. 
 
Engine Limits.                                      SHP             Torque             RPM              EGT  
                             (psi)                                         (o) 
 
     Take-off                           576              53.2                41.730             561  
                                                                             (100%) 
     Max. Continuous                    576                53.2               41.730            561  
                                                                             (100%) 
     Absolute Maximum                  ---                 ---                43.816 
     (max. 5 sec)                         ---                   ---                (105%) 
     Starting (max. 1 sec)                 ---                  ---                     ---             815

Page 6 of 11 7A15 
 
Propeller and     Hartzell feathering and reversing constant speed propeller 
 Propeller Limits.   Hub HC-B3TN-5C, blades T-10178C or T-10178CH 
     Diameter:  max. 101 in. minimum 99 in. 
     (no further reduction permitted) 
     Pitch setting at 30 in. station:  Reverse   - 9.5o 
                                         Feathering  +87o 
                                          Start    + 2o 
                                          Minimum in flight + 5o 
 
Fuel Capacity.   Total capacity:  130 US gal. or 173 US gal. 
     (2 tanks of 63.5 or 85 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
     Usable capacity:  128 US gal. or 170 US gal. 
     (2 tanks of 62.5 or 83.5 US gal.) (+31.1) plus 
     1 booster pump tank of 3 US gal. (+ 111.0) 
 
Oil Capacity.   2.9 US gal. (-103) (engine integral). 
 
 
IX. Model PC-6/B2-H4, 11 PCLSM (Normal Category), Approved July 31, 1992 
 
Engine.    United Aircraft of Canada Ltd. PT6A-27 
 
Fuel.    JP-1, JP-4 and JP-5 fuels conforming to UACL Specification No. 522 and later revisions. 
 
Engine Limits.                            SHP         Torque          C.G.          Prop.        ITT 
                                               (psi)             RPM         RPM         ( oC) 
     Take-off                 550            47.3            38.100        2000         725  
                                                            (101.5%)    (100%) 
     Max. Continuous         550            47.3            38.100        2000         725  
                                                            (101.5%)    (100%) 
     Starting (max. 2 sec)    ---              ---                 ---              ---         1090 
     Max. reverse            550            47.3                                         725 
 
Propeller and     Hartzell feathering and reversing constant speed propeller 
  Propeller Limits.   Hub:  HC-B3TN-3C or HC-B3TN-3D, blades T-10178CNR, T-101778CNRK,  
T-10178CR, T-10178CRK or T-101778C, T-10178CK, T-10178CH modified according 
to Pilatus Service Bulletin No. SB 149. 
     Diameter:  max. 101 in., min. 99 in. (No further reduction permitted). 
     Pitch setting at 30 in. station: Reverse   -10.5o 
                                       Feathering  +85.5o 
                                       Minimum in flight  + 0.5o 
 
Fuel Capacity.   Total capacity:  130 US gal. or 173 US gal. 
     (2 tanks of 63.5 or 85 US gal. (+ 31.1) plus 
     1 booster pump tank of 2 US gal. (+ 111.0) 
     Usable capacity: 128 US gal. or 170 US gal. 
     (2 tanks of 62.5 or 83.5 US gal. (+ 31.1) plus 
     1 booster pump tank of 3 US gal (+ 111.0) 
 
Oil Capacity.   Total capacity  : 2.3 US gal. (-80) (engine integral) 
     Usable capacity :  1.5 US gal.

Page 7 of 11 7A15 
DATA PERTINENT TO ALL MODELS 
Airspeed Limits (IAS). 
 All models except B2-H4         B2-H4 
Vne (Never exceed) 
Vno (Max. structural 
           cruising) 
Vp   (Maneuvering) 
Vfe   (Flaps extended) 
Vsk  (Ski system  
           operation) 
174 mph (151 kts) 
137 mph (118 kts) 
 
122 mph (106 kts) 
  94 mph (  82 kts) 
  84 mph (  73 kts) 
174 mph (151 kts) 
138 mph (119 kts) 
 
138 mph (119 kts) 
109 mph (  95 kts) 
    ----          --- 
 
C.G. Range. 
All Models except B2-H4                 Model B2-H4 
+ 18.7” to + 25.4” at 4850 lb. 
+   8.2” to + 25.4” at 3200 lb. or less 
+ 23.9” to + 28.4” at 6173 lbs. 
+   8.2” to 28.4” at 3200 lbs. 
     Straight line variation between points given. 
 
Empty Weight C.G. Range.  None. 
 
Datum.    Leading edge of wing 
 
Leveling Means.   Marks on each side of the fuselage.  Also T-rails on cabin floor horizontal. 
 
Max. weights (take-off)  PC-6, PC-6/350 and PC-6/A   4322 lb. 
 and landing weights  PC-6-H1, PC-6/350-H1, PC-6/A-H1  4444 lb. 
     PC-6-H2, PC-6/350-H2, PC-6/A-H2  4850 lb. 
     PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2 
     PC-6/C-H2, PC-6/C1-H2. 
     PC-6/B2-H4    6173 lb MTOW/5864 lb KLW 
     NOTE:  AFM Supplements as listed on page 8 show increased take-off weights. 
 
Number of Seats.    8 - 2 at (+ 4.5), 2 at (+34.4), 
          2 at (+63.0), 2 at (+91.3), or 
     11 - 2 single seats at (+ 4.5) and 3 triple 
            seats at (+32.7, +60.3, and +85.8). 
     NOTE:  6 seats can be stowed in compartment behind cabin, accessible through a door in  
     fuselage RH side. 
 
Maximum Baggage.  Main cabin, after removal of seats.  See approved loading instructions.  Max. floor 
loading 100 lb. per sq. ft. 
 
Control Surface Movements.  Elevator:    Up    30o ± 1o  Down    25o ± 1o 
       Flettner tab:  Down  57o ± 2o  Up      32o ± 2o 
     Stabilizer:          Nose Down  10o ± .5o  Nose up  2o ± .5o 
        (Serial No. 552 and all H2 models) 
                          Nose Down   8o ± .5o  Nose up  2o ± .5o 
        (Serial No. 524 and up except H2 models) 
     Rudder:   Right 30o ± 1.5o  Left    30o ± 1.5o 
     Rudder tab:  Right  6o ± 1o  Left     6o ± 1o 
     Aileron:   Up    20o ± 1o  Down  13.5o ± 1o 
       Flettner tab:  Down  20o ± 1o  Up    13.5o ± 1o 
     Aileron tab (r.h.)  Up    20o ± 2o  Down    18o Neutral 2o Up 
     Flaps:   Up     0o    Down    45o ± 2o 
           (Ser. No. 522) 
        Up     0o   Down    38o ± 2o 
           (Ser. No. 524 and up)

Page 8 of 11 7A15 
     NOTE: Flettner tabs on aileron and elevator are optional; if not 
      installed, fixed tabs on elevator (up 36o) and aileron (neutral) are mandatory.  Stabilizer 
in neutral position is 3o nose down. 
     For B2-H4 on elevator one flettner tab (set to 0o) and two fixed trim tabs (set 10o up) are 
mandatory. 
 
Maximum Operating Altitude. 25.000 ft. 
 
Certification Basis.   CAR 10.  CAR 3 dated May 15, 1956 including amendments 3-1 through 3-5.  Type 
Certificate No. 7A15, issued November 9, 1961. 
     Date of Application for Type Certificate:  October 11, 1960. 
 
The Swiss Federal Office of Civil Aviation (FOCA) originally type certificated this 
aircraft under its type certificate Number F-56-10. The FAA validated this product under 
U.S. Type Certificate Number 7A15. Effective December 1, 2006, the European Aviation 
Safety Agency (EASA) began oversight of this product on behalf of Switzerland. The 
EASA TCDS No. has not been issued at this time.  
      
     The Swiss Federal Air Office "Certificate of Airworthiness for Export" endorsed as noted 
below under "Import Requirements" must be submitted for each individual aircraft for 
which application for certification is made.  (See NOTE 4). 
 
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 Swiss Federal Office 
of Civil Aviation (FOCA) on behalf of the European Community. The Export C of A 
should contain the following statement: ‘The aircraft covered by this certificate has been 
examined, tested, and found to comply with U.S. Civil Air Regulation Part 3 U.S. Type 
Certificate No. 7A15 and to be in a condition for safe operation.’  
 
     Model PC-6 and PC-6/350 series:  "The airplane covered by this certificate has been 
examined and found to comply with U.S. Civil Air Regulations  
     Part 3, dated May 15, 1956 including Amendment 3-1 through 3-5 and conforms to T.C. 
7A15". 
 
     Model PC-6/A series:  "The airplane covered by this certificate has been examined and 
found to comply with U.S. Civil Air Regulation Part 3, dated May 15, 1956 including 
Amendment 3-1 through 3-5 and Special Conditions notified by FAA, letter dated 
November 14, 1962 to the Swiss Federal Air Office, and conforms to T.C. 7A15". 
 
     Models PC-6/B, /B1, /B2, /C, and /C1 series:  "The airplane covered by this certificate 
has been examined and found to comply with U.S. Civil Air Regulation Part 3, dated 
May 15, 1956 including Amendments 3-1 through 3-5 and Special Conditions notified by 
FAA, letter dated January 4, 1967 and conforms to T.C. 7A15". 
 
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. 
 
 
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: 
 
       (a) Swiss Federal Air Office approved Airplane Flight Manual (as limited below) 
       (b) Stall warning indicator, Safe Flight 1-02-0005, or 164 
       (c) Ratier Figeac Spinner FH 76-400 (PC-6/A series only) 
       (d) Clogged fuel filter warning light (PC-6/A, /B, /B1, /B2, /C, and /C1 series only).

Page 9 of 11 7A15 
       (e) Stabilizer dual motor trim actuator Electro Mech EM 483  
        Mandatory for PC-6/B2-H4 only. 
 
 
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 December 1, 2006 – Swiss Federal 
Office of Civil Aviation (FOCA). 
 
    • Service bulletins,  
    • Structural repair manuals,  
    • Vendor manuals,  
    • Aircraft flight manuals, and  
    • Overhaul and maintenance manuals.  
 
The FAA accepts such documents and considers them FAA-approved for type design data 
only unless one of the following conditions exists: 
 
• The documents change the limitations, performance, or procedures of the FAA approved 
manuals; or 
 
•The documents make an acoustical or emissions changes to this product’s U.S. type 
certificate as defined in 14 CFR § 21.93.  
 
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.  
 
 
Airplane Flight Manual. (a) Swiss Federal Air Office approved Airplane Flight Manuals: 
 
Model 
Report No. 
PC-6 
902 
PC-6-H1 
902-1 
PC-6-H2 
902-2 
Model  
Report No. 
PC-6/350 
920 
PC-6/350-H1 
920-1 
PC-6/350-H2 
920-2 
Model  
Report No. 
PC-6A 
921 
PC-6/A-H1 
921-1 
PC-6/A-H2 
921-2 
Model  
Report No. 
PC-6/B-H2 
1072 
PC-6/B1-H2 
1072-1 
PC-6/B2-H2 
1072-2 
or 1791 
Model 
Report No. 
PC-6/C-H2 
1161 
PC-6/C1-H2 
1161-1 
 
Model 
Report No. 
PC-6/B2-H4 up to MSN 824 
1072-20 
Model 
Report No. 
PC-6/B2-H4 from MSN 825 
1820 
 
     
    (b)  List of Supplements (Swiss Federal Air Office approved). 
 
Report  
No.  
Applicable for 
PORTER Model 
Subject Operating 
Category 
1029 PC-6/350-H1 
 
Seaplane with floats 
EDO 39-4000 
Normal 
1140 PC-6-H2 
PC-6/350-H2 
Seaplane with floats 
EDO 58-4580 
Normal 
1141 
1141-1 
 
PC-6/A-H2 
PC-6/B-H2 
PC-6/B1-H2 
PC-6/B2-H2` 
Seaplane with floats 
EDO 58-4580 
EDO 58-4580 or EDO 679-4930 
Normal

Page 10 of 11 7A15 
1104 PC-6/B1-H2 
PC-6/B2-H2 
Fuel ferry tank 
installation 
Restricted* 
1143-1 
1143-B 
1143-C 
1143-D 
PC-6/C-H2 
PC-6/C1-H2 
 
Agriculture version 
 
  
Restricted* 
1186 
 
All models 
except B2-H4 
Cabin doors removed, 
sliding door and/or hatch 
door open (parachuting) 
Normal 
1242 All models “H2” Wing fuel tanks 
2 x 85 US-gal. 
Normal 
 
1320 
 
All models 
except B2-H4 
 
Ski operation 
 
Normal 
1347-1 All models “H2” External fuel Restricted* 
1421 
 
All models Electrically operated 
landing flaps 
Normal 
1422 PC-6/B1-H2 
PC-6/B2-H2 
Engine Air Intake 
Filter Mk. 38 
Normal 
1424 All models Aileron Trim System Normal 
1490 All TURBO PORTER 
model except B2-H4 
Fuel Ferry tank V-43593 Restricted* 
 
 
Report 
No. 
Applicable for 
PORTER Model 
Subject Operating 
Category 
1504 PC-6/B-H2 
PC-6/B1-H2 
PC-6/B2-H2 
PC-6/B2-H4 
up to MSN 824 
Propeller de-icing 
system 
Normal 
1511 All models Target sack winch 
 
Normal 
1527 PC-6/B1-H2 
PC-6/B2-H2 
up to MSN 824 
Electrical Trim System Normal 
1527-1 PC-6/B2-H2 
from S/N 825 
   
1568 All TURBO PORTER 
Models except H4 
 Operation in overweight 
condition 
Restricted* 
1824 PC-6/B2-H4  Cabin doors removed, sliding 
door/hatch door open (para- 
chuting) 
Normal 
1826 PC-6/B2-H4 
up to MSN 824 
Underwing tanks Normal 
1826-1 PC-6/B2-H4 
from MSN 825 
  
1850 PC-6/B2-H4   Emergency battery system Normal  
 1887 PC-6/B2-H4  Quiet operation Normal 
1904 PC-6/B2-H4 Air intake filter system Normal 
1914 PC-6/B2-H2 
PC-6/B2-H4 
from S/N 825 
 Hot prop  Normal 
    * Aircraft must be certificated under FAR 21.185 or FAR 21.187 in Restricted Category. 
 
 
AFM (cont.)   (c) FAA-approved Airplane Flight Manuals and also approved by Swiss Federal  
     Air Office. 
      Model  Date of Issue  Including Revision

Page 11 of 11 7A15 
      PC-6/B-H2 March 12, 1965  Rev 4, July 21, 1971 
      PC-6/B1A-H2 December 1, 1967  Rev 4, July 21, 1971 
      PC-6/B2-H2 May 13, 1968  Rev 2, July 21, 1971 
      PC-6/C-H2 April 20, 1966  Rev 5, May 20, 1971 
 
    (d) FAA-approved Airplane Flight Manual Supplement issued to 
     Fairchild Industries and also approved by Swiss Federal Air Office. 
 
Applicable for Heli 
Porter Model 
 
     Date of Issue Supplement No. 
PC-6/B-H2 
PC-6/B-H2 
PC-6/B-H2 
 
     July 8, 1966 
     April 3, 1969 
     April 18, 1969 
1 
2 
3 
 
PC-6/B1-H2 
 
     September 3, 1966 
     January 4, 1966 
     February 13, 1967 
 
1 
2 
3 
 
PC-6/B1A-H2 
     April 3, 1969 
     April 18, 1969 
     July 8, 1965 
 
1 
2 
3 
 
 
Applicable for Heli 
Porter Model 
     Date of Issue Supplement No. 
PC-6/B2-H2      April 18, 1969 
     April 3, 1969 
 
1 
2 
 
 
PC-6/C-H2 
     July 8, 1966 
     January 4, 1966 
     May 14, 1968 
     April 3, 1969 
     April 18, 1969 
 
1 
2 
3 
4 
5 
PC-6/B1-H2      April 18, 1969 Associated with 
STC SA747EA 
PC-6/B1-H2      April 3, 1969 Associated with 
STC SA743EA 
PC-6/B1-H2      July 10, 1969 Associated with 
STC SA743EA 
 
NOTES 
 
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. 
 
NOTE 2.  Placards must be displayed as listed in the approved Airplane Flight Manual. 
 
NOTE 3.  Doors: Cabin door RH side, either double doors or sliding doors.  
    Optional: double doors LH side additional. 
    Optional: cockpit doors on both sides. 
 
NOTE 4.  Spare parts and aircraft manufactured by Fairchild Republic Company, Farmingdale, New York and  
   Hagerstown, Maryland under a licensing agreement are produced under the Fairchild Republic Company  
   production certificate No. 1, and are eligible for standard airworthiness certificates. 
 
NOTE 5.   Manufacturer Serial Numbers (MSN) 2001 thru 2092 were manufactured by Fairchild Republic Company 
(also identified as Fairchild Industries, Fairchild Heli Porter and Fairchild-Hiller Corporation) in the United 
States of America under a license agreement and are covered by this Type Certificate No. 7A15.    
.....END......
```

## ADs (62, first 50, in force first)

- [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026
- [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 2021-24-22](https://openairdocs.org/ad/2021-24-22): Flight Control System, Aileron Control System, Rudder Control System, Elevator Control System · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Jan 25, 2022
- [AD 2021-11-08](https://openairdocs.org/ad/2021-11-08): Time Limits/Maintenance Checks · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Jul 12, 2021
- [AD 2020-16-02](https://openairdocs.org/ad/2020-16-02): Stabilizers · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Sep 9, 2020
- [AD 2020-11-06](https://openairdocs.org/ad/2020-11-06): Flight Controls · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Jun 30, 2020
- [AD 2019-10-07](https://openairdocs.org/ad/2019-10-07): Stabilizers · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Jul 10, 2019
- [AD 2017-04-03](https://openairdocs.org/ad/2017-04-03): Wings · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Apr 7, 2017
- [AD 2016-22-12](https://openairdocs.org/ad/2016-22-12): Fuselage · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Nov 4, 2016
- [AD 2013-14-01](https://openairdocs.org/ad/2013-14-01): Fuselage · Pilatus PC-6/B2-H4. Effective Aug 5, 2013
- [AD 2009-18-03 R1](https://openairdocs.org/ad/2009-18-03-R1): Wings · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Feb 16, 2011
- [AD 2008-23-03](https://openairdocs.org/ad/2008-23-03): Brake pedals · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Dec 11, 2008
- [AD 2008-16-19](https://openairdocs.org/ad/2008-16-19): Self-locking stop nuts · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Sep 17, 2008
- [AD 2008-16-03](https://openairdocs.org/ad/2008-16-03): Leaf springs · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Aug 11, 2008
- [AD 2008-13-18](https://openairdocs.org/ad/2008-13-18): Tail landing gear · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Jul 30, 2008
- [AD 2007-26-11](https://openairdocs.org/ad/2007-26-11): High-pressure oxygen cylinder · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 45 more. Effective Jan 28, 2008
- [AD 2006-15-02](https://openairdocs.org/ad/2006-15-02): Aileron control bellcrank assemblies · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Aug 23, 2006
- [AD 2006-15-03](https://openairdocs.org/ad/2006-15-03): Integral fuel tank wing ribs · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Aug 23, 2006
- [AD 2006-13-11](https://openairdocs.org/ad/2006-13-11): Aileron assembly · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Aug 7, 2006
- [AD 2006-13-12](https://openairdocs.org/ad/2006-13-12): Fuel starvation during maximum climb · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Aug 7, 2006
- [AD 68-17-03 R1](https://openairdocs.org/ad/68-17-03-R1): Rudder end rib · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Aug 3, 2006
- [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 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 2001-02-04](https://openairdocs.org/ad/2001-02-04): Stabilizer Trim Actuator · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Mar 13, 2001
- [AD 97-22-08](https://openairdocs.org/ad/97-22-08): Airplane Flight Manual (AFM) - Limitations Section - Power Levers · Pilatus PC-12, PC-6/B1-H2, PC-6/B2-H2 and 1 more. Effective Dec 5, 1997
- [AD 96-22-13](https://openairdocs.org/ad/96-22-13): Hinge Brackets On Horizontal Stabilizer · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Dec 27, 1996
- [AD 90-19-01](https://openairdocs.org/ad/90-19-01): Rudder Pedal Support · Pilatus PC-6, PC-6-H1, PC-6-H2 and 11 more. Effective Oct 15, 1990
- [AD 85-16-09](https://openairdocs.org/ad/85-16-09): Vertical/Horizontal Stabilizer · Pilatus PC-6, PC-6-H1, PC-6-H2 and 11 more. Effective Aug 31, 1985
- [AD 77-20-06](https://openairdocs.org/ad/77-20-06): Wing Strut Corrosion · Pilatus PC-6, PC-6-H1, PC-6-H2 and 11 more. Effective Nov 3, 1977
- [AD 77-13-06](https://openairdocs.org/ad/77-13-06): Landing Flaps · Pilatus PC-6, PC-6-H1, PC-6-H2 and 11 more. Effective Jul 25, 1977
- [AD 76-01-09](https://openairdocs.org/ad/76-01-09): Elevator Attach Brackets · Pilatus PC-6, PC-6-H1, PC-6-H2 and 11 more. Effective Feb 6, 1976
- [AD 75-27-07](https://openairdocs.org/ad/75-27-07): Rudder Bars · Pilatus PC-6, PC-6-H1, PC-6-H2 and 11 more. Effective Jan 21, 1976
- [AD 75-27-06](https://openairdocs.org/ad/75-27-06): Fuel Leak Fittings · Pilatus PC-6, PC-6-H1, PC-6-H2 and 11 more. Effective Jan 19, 1976
- [AD 75-26-17](https://openairdocs.org/ad/75-26-17): Engine Mount · Pilatus PC-6/A. Effective Jan 17, 1976
- [AD 70-18-03](https://openairdocs.org/ad/70-18-03): Flight Manual and Switch · Pilatus PC-6/B1-H2. Effective Aug 31, 1970
- [AD 69-20-01](https://openairdocs.org/ad/69-20-01): Rudder Trim Control Cable · Pilatus PC-6, PC-6-H1, PC-6-H2 and 9 more. Effective Oct 27, 1969
- [AD 69-19-01](https://openairdocs.org/ad/69-19-01): Pivot Bolt Rotation · Pilatus PC-6, PC-6-H1, PC-6-H2 and 9 more. Effective Sep 20, 1969
- [AD 69-07-02](https://openairdocs.org/ad/69-07-02): Aileron Balance Unit · Pilatus PC-6, PC-6-H1, PC-6-H2 and 9 more. Effective Apr 1, 1969
- [AD 69-05-05](https://openairdocs.org/ad/69-05-05): Power Lever Travel · Pilatus PC-6/B-H2 and PC-6/B1-H2. Effective Mar 12, 1969
- [AD 69-04-04](https://openairdocs.org/ad/69-04-04): Aileron Balance Bolt · Pilatus PC-6, PC-6-H1, PC-6-H2 and 9 more. Effective Feb 14, 1969
- [AD 68-10-06](https://openairdocs.org/ad/68-10-06): Horizontal Stabilizer · Pilatus PC-6, PC-6-H1, PC-6-H2 and 9 more. Effective Jun 10, 1968
- [AD 67-32-04](https://openairdocs.org/ad/67-32-04): Stabilizer Cable Trim Control Clamps · Pilatus PC-6, PC-6-H1, PC-6-H2 and 9 more. Effective Dec 17, 1967
- [AD 67-21-02](https://openairdocs.org/ad/67-21-02): Elevator Attachment Bracket · Pilatus PC-6, PC-6-H1, PC-6-H2 and 9 more. Effective Aug 13, 1967
- [AD 67-12-05](https://openairdocs.org/ad/67-12-05): Pulley Fairleads · Pilatus PC-6, PC-6-H1, PC-6-H2 and 6 more. Effective May 4, 1967
- [AD 67-13-03](https://openairdocs.org/ad/67-13-03): Rudder Control Lever Rivets · Pilatus PC-6, PC-6-H1, PC-6-H2 and 6 more. Effective May 4, 1967
- [AD 66-28-05](https://openairdocs.org/ad/66-28-05): Rudder Pedal Support · Pilatus PC-6, PC-6-H1, PC-6-H2 and 6 more. Effective Nov 19, 1966
- [AD 66-01-03](https://openairdocs.org/ad/66-01-03): Fuel Valve · Pilatus PC-6, PC-6-H1, PC-6-H2 and 6 more
- [AD 71-23-01](https://openairdocs.org/ad/71-23-01): Safety of Aileron Cable Turnbuckles · Pilatus PC-6, PC-6-H1, PC-6-H2 and 9 more
- [AD 2014-25-04](https://openairdocs.org/ad/2014-25-04) (historical): Time Limits · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Jan 16, 2015
- [AD 2013-11-08](https://openairdocs.org/ad/2013-11-08) (historical): Time Limits · Pilatus PC-6, PC-6-H1, PC-6-H2 and 12 more. Effective Jul 29, 2013

All 62: https://openairdocs.org/tcds/7A15/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Pilatus PC-6/B2-H4](https://openairdocs.org/model/pilatus-pc-6-b2-h4): 11 aircraft (registry codes 7090215, 7090217)
- [Pilatus PC-6/B2-H2](https://openairdocs.org/model/pilatus-pc-6-b2-h2): 8 aircraft (registry code 7090213)
- [Pilatus PC-6/B1-H2](https://openairdocs.org/model/pilatus-pc-6-b1-h2): 2 aircraft (registry code 7090212)
- [Pilatus PC-6](https://openairdocs.org/model/pilatus-pc-6): 1 aircraft (registry code 7090102)
- [Pilatus PC-6 PORTER](https://openairdocs.org/model/pilatus-pc-6-porter): 0 aircraft (registry code 7090112)
- [Pilatus PC-6-H1](https://openairdocs.org/model/pilatus-pc-6-h1): 0 aircraft (registry code 7090106)
- [Pilatus PC-6-H2](https://openairdocs.org/model/pilatus-pc-6-h2): 0 aircraft (registry code 7090110)
- [Pilatus PC-6/350](https://openairdocs.org/model/pilatus-pc-6-350): 0 aircraft (registry code 7090114)
- [Pilatus PC-6/350-H1](https://openairdocs.org/model/pilatus-pc-6-350-h1): 0 aircraft (registry code 7090118)
- [Pilatus PC-6/350-H2](https://openairdocs.org/model/pilatus-pc-6-350-h2): 0 aircraft (registry code 7090122)
- [Pilatus PC-6/A](https://openairdocs.org/model/pilatus-pc-6-a): 0 aircraft (registry code 7090202)
- [Pilatus PC-6/A-H1](https://openairdocs.org/model/pilatus-pc-6-a-h1): 0 aircraft (registry code 7090204)
- [Pilatus PC-6/A-H2](https://openairdocs.org/model/pilatus-pc-6-a-h2): 0 aircraft (registry code 7090206)
- [Pilatus PC-6/B-H2](https://openairdocs.org/model/pilatus-pc-6-b-h2): 0 aircraft (registry code 7090210)
- [Pilatus PC-6/C1-H2](https://openairdocs.org/model/pilatus-pc-6-c1-h2): 0 aircraft (registry code 7090211)
- [Pilatus Porter PC-6/C-H2](https://openairdocs.org/model/pilatus-porter-pc-6-c-h2): 0 aircraft (registry code 7090214)

## STCs approved under this data sheet (146, first 50)

- [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 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 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 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 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 SA39CH](https://openairdocs.org/stc/SA39CH): Installation of an Amphibian Landing Gear Position Advisory System/Laser Gear Advisory System. Wipaire Inc.
- [STC SA614EA](https://openairdocs.org/stc/SA614EA): Installation of UACL engine Model PT6A-27 with Hartzell propeller Model HC-B3TN-3D/T10178C(H) on aircraft configured with cockpit doors.. PC6-AU23 Spares, LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA1004EA](https://openairdocs.org/stc/SA1004EA): Installation of engine fuel purge system-engine shutdown.. PC6-AU23 Spares LLC
- [STC SA1005EA](https://openairdocs.org/stc/SA1005EA): Installation of fuel collector tank - engine shutdown fuel discharge.. PC6-AU23 Spares LLC
- [STC SA1022EA](https://openairdocs.org/stc/SA1022EA): Installation of Aerosmith C-129-65 pilot's and co-pilot's seats and modified control sticks.. PC6-AU23 Spares LLC
- [STC SA273EA](https://openairdocs.org/stc/SA273EA): Installation of United Aircraft of Canada engine PT6A-6A and Hartzell propeller HC-B3TN-3/10173 combination.. PC6-AU23 Spares LLC
- [STC SA307EA](https://openairdocs.org/stc/SA307EA): Removal of either or both of the right hand cabin door and/or opening of the fuselage bottom hatch in flight.. PC6-AU23 Spares LLC
- [STC SA368EA](https://openairdocs.org/stc/SA368EA): Installation of AiResearch engine Model TPE 331-25D, TPE 331-25DA, TPE-25DB, or TPE 331-71 and Hartzell propeller Model HC-B3TN-5C/T10178C.. PC6-AU23 Spares LLC
- [STC SA397EA](https://openairdocs.org/stc/SA397EA): Installation of fuel collector tank vent line.. PC6-AU23 Spares LLC
- [STC SA433EA](https://openairdocs.org/stc/SA433EA): Installation of dual brake valves.. PC6-AU23 Spares LLC
- [STC SA465EA](https://openairdocs.org/stc/SA465EA): Installation of UAT-1 Transponder, MBT-R Marker Beacon, KN-60 DME, KX-160 and KX-160-1 Nav/Comm, KR-80ADF, Headset Microphone and Speaker.. PC6-AU23 Spares LLC
- [STC SA493EA](https://openairdocs.org/stc/SA493EA): Installation of Randolph Mfg. Co. Model 133 vacuum regulator.. PC6-AU23 Spares LLC
- [STC SA498EA](https://openairdocs.org/stc/SA498EA): Installation of Zep Aero oxygen system.. PC6-AU23 Spares LLC
- [STC SA526EA](https://openairdocs.org/stc/SA526EA): Installation of pilot's and co-pilot's shoulder harness.. PC6-AU23 Spares LLC
- [STC SA528EA](https://openairdocs.org/stc/SA528EA): Installation of KX-160 NAV/COM, 618M-1A VHF COM., T-10-R HF COMM, ARC Type 21A ADF headsets, microphones and speakers.. PC6-AU23 Spares LLC
- [STC SA545EA](https://openairdocs.org/stc/SA545EA): Installation of Hartzell propeller Model HC-B3TN-3D/T10178C(H).. PC6-AU23 Spares LLC
- [STC SA612EA](https://openairdocs.org/stc/SA612EA): Installation of EDO-58-4580 floats.. PC6-AU23 Spares LLC
- [STC SA743EA](https://openairdocs.org/stc/SA743EA): Installation of a sliding door on the left side of fuselage.. PC6-AU23 Spares LLC
- [STC SA747EA](https://openairdocs.org/stc/SA747EA): Installation of two external fuel tanks of fifty gallons capacity each, mounted.. PC6-AU23 Spares LLC
- [STC SA753EA](https://openairdocs.org/stc/SA753EA): Installation of dual ARC 21A ADF's, and ARC 131B VHF's and one SA14RA HF avionics equipment.. PC6-AU23 Spares LLC
- [STC SA755EA](https://openairdocs.org/stc/SA755EA): Installation of polyurethane Reticulated Foam in the aircraft's integral and collector fuel tanks in addition to check valves in the fuel lines between the integral tanks and the collector and sediment tanks.. PC6-AU23 Spares LLC
- [STC SA830EA](https://openairdocs.org/stc/SA830EA): Installation of fiberglass protective boot on leading edge of horizontal stabilizer.. PC6-AU23 Spares LLC
- [STC SA906EA](https://openairdocs.org/stc/SA906EA): Installation of elevator reinforcement.. PC6-AU23 Spares LLC
- [STC SA907EA](https://openairdocs.org/stc/SA907EA): Installation of outboard aileron reinforcement.. PC6-AU23 Spares LLC
- [STC SA908EA](https://openairdocs.org/stc/SA908EA): Installation of rudder reinforcement.. PC6-AU23 Spares LLC
- [STC SA909EA](https://openairdocs.org/stc/SA909EA): Installation of vertical stabilizer reinforcement.. PC6-AU23 Spares LLC
- [STC SA910EA](https://openairdocs.org/stc/SA910EA): Installation of horizontal/stabilizer reinforcement.. PC6-AU23 Spares LLC
- [STC SA911EA](https://openairdocs.org/stc/SA911EA): Installation of Bulkhead 12A reinforcement.. PC6-AU23 Spares LLC
- [STC SA912EA](https://openairdocs.org/stc/SA912EA): Nose Ballast installation.. PC6-AU23 Spares LLC
- [STC SA937EA](https://openairdocs.org/stc/SA937EA): Cabin Floor, Special Installation - Structural Provisions.. PC6-AU23 Spares LLC
- [STC SA938EA](https://openairdocs.org/stc/SA938EA): Wing Flap and Aileron Reinforcement.. PC6-AU23 Spares LLC
- [STC SA939EA](https://openairdocs.org/stc/SA939EA): Substitution of AN Hardware in lieu of Metric Hardware.. PC6-AU23 Spares LLC
- [STC SA940EA](https://openairdocs.org/stc/SA940EA): Left Wing Reinforcement.. PC6-AU23 Spares LLC
- [STC SA941EA](https://openairdocs.org/stc/SA941EA): Wing Hard Point Modification.. PC6-AU23 Spares LLC
- [STC SA945EA](https://openairdocs.org/stc/SA945EA): Installation of longitudinal out of trim warning system.. PC6-AU23 Spares LLC
- [STC SA946EA](https://openairdocs.org/stc/SA946EA): Relocation of wing landing light between left wing rib stations 11 and 12 to left wing rib stations21 and 22.. PC6-AU23 Spares LLC
- [STC SA961EA](https://openairdocs.org/stc/SA961EA): Installation of battery over- temperature warning system.. PC6-AU23 Spares LLC
- [STC SA986WE](https://openairdocs.org/stc/SA986WE): Removal of landing gear and installation of seaplane conversion.. PC6-AU23 Spares LLC
- [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

All 146: https://openairdocs.org/tcds/7A15/stcs.md

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