# TCDS E4EA: Pratt & Whitney Canada Corp.

- Type: Type certificate data sheet
- Status: Current
- Holder: Pratt & Whitney Canada Corp.
- Revision: 30
- Revised: June 16, 2021
- Product: Engine
- Certification basis: Part 21, CAR 13
- Registered aircraft: 4,105, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/66/76/6676b2d439c54061e79b398716624033c287e5280255bca6e44ff782638982b2
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C0D4C6893F4D7871862586F6005B8B8B.0001
- Page: https://openairdocs.org/tcds/E4EA

## Models (54)

As the data sheet lists them.

- PT6A-35
- PT6A-38
- PT6A-20B
- PT6A-21
- PT6A-42
- PT6A-29
- PT6A-45B
- PT6A-60AG
- PT6A-6B
- PT6A-6/C20
- PT6A-36
- PT6A-11AG
- PT6A-60A
- PT6A-45R
- PT6A-121
- PT6A-27
- PT6A-41
- PT6A-61
- PT6A-65AG
- PT6A-6
- PT6A-110
- PT6A-140
- PT6B-9
- PT6A-65B
- PT6A-116
- PT6A-34
- PT6A-25
- PT6D-114A
- PT6A-34B
- PT6A-65R
- PT6A-135A
- PT6A-42A
- PT6A-41AG
- PT6A-20A
- PT6A-65AR
- PT6A-45
- PT6A-52
- PT6A-34AG
- PT6A-25A
- PT6A-135
- PT6A-25C
- PT6A-112
- PT6A-114
- PT6A-28
- PT6A-45A
- PT6A-114A
- PT6A-11
- PT6A-50
- PT6A-15AG
- PT6A-6A
- PT6A-20
- PT6A-140A
- PT6A-140AG
- PT6A-65SC

## 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 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 
 REV. 30  28 28 28 29 29 28 28 28 29 28 29 29 28 29 29 29 29 28 29 29 29 30 29  29 29 
 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
              "---" NOT APPLICABLE  
NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN 
 
 
 
 
U.S. DEPARTMENT OF 
TRANSPORTATION 
 
FEDERAL AVIATION ADMINISTRATION 
 
TYPE CERTIFICATE DATA SHEET 
 
E4EA 
 
 
TCDS NUMBER  E4EA  
REVISION:  30  
DATE:  June 16, 2021 
 
PRATT & WHITNEY CANADA CORP. 
MODELS: 
PT6A-6 PT6A-6A PT6A-6B PT6A-6/C20 
PT6A-11 PT6A-11AG PT6A-15AG PT6A-20 
PT6A-20A PT6A-20B PT6A-21 PT6A-25 
PT6A-25A PT6A-25C PT6A-27 PT6A-28 
PT6A-29 PT6A-34 PT6A-34B PT6A-34AG 
PT6A-35 PT6A-36 PT6A-38 PT6A-41 
PT6A-41AG PT6A-42 PT6A-42A  PT6A-45 
PT6A-45A PT6A-45B PT6A-45R  PT6A-50 
PT6A-52 PT6A-60A  PT6A-60AG PT6A-61 
PT6A-65B  PT6A-65R PT6A-65AR PT6A-65AG 
PT6A-65SC PT6A-110  PT6A-112 PT6A-114 
PT6A-114A PT6A-116  PT6A-121 PT6A-135 
PT6A-135A PT6A-140  PT6A-140A  PT6A-140AG 
 
PT6B-9 PT6D-114A 
 
Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E4EA) and other 
approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance 
with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and 
maintained as prescribed by the approved manufacturer's manuals and other approved instructions. 
 
TYPE CERTIFICATE (TC) HOLDER: Pratt & Whitney Canada Corp. 
 1000 Marie-Victorin 
 Longueuil, Quebec, Canada J4G 1A1 
 
TYPE I Free turbine turbo-prop / 3 axial plus one centrifugal stage compressor / single annular combustion 
chamber, single-stage gas generator turbine / single-stage power turbine 
MODELS PT6A-6, -6A, -6B, -6/C20, -11, -11AG, -15AG, -20, -20A -20B, -21, -25, -25A, -25C, -27, -28, -29, -34, 
-34B, -34AG, -35, -36, -110, -112, -114, -114A, -116, -121, -135, -135A, -140,  -140A, -140AG,  
PT6D-114A 
 
 
TYPE II Free turbine turbo-prop / 3 axial plus one centrifugal stage comp / single annular combustion chamber / 
single stage gas generator turbine / two stage power turbine 
MODELS PT6A-38, -41, -41AG, -42, -42A, -45, -45A, -45B, -45R, -50, -52, -60A, 
-60AG, -61 
 
 
TYPE III Free turbine turbo-prop / 4 axial plus one centrifugal stage comp / single annular combustion chamber / 
single stage gas generator turbine / two stage power turbine 
MODELS PT6A-65B, -65R, -65AR, -65AG, -65SC 
 
 
TYPE IV Free turbine turboshaft 3 axial plus one centrifugal stage comp / single annular combustion chamber / 
single stage gas generator turbine / single stage power turbine 
MODELS PT6B-9

TCDS   E4EA           PAGE 2 
I. MODELS PT6A-6 PT6A-6A PT6A-6B PT6A-11, -11AG PT6A-20, -20A, -
20B,-6/C20 
RATINGS  
 
Maximum continuous at sea level 
 Equivalent shaft hp. 
  
 Shaft hp. 
  
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Takeoff (5 min.) at sea level 
 Equivalent shaft hp. 
  
 Shaft hp. 
  
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Maximum reverse 
 Shaft hp. 
 Output rpm (max) 
 
 
 
 
525 
 
500 
 
62 
2,200 
38,100 
 
 
578 
 
550 
 
70 
2,200 
38,100 
 
 
 
 
 
 
- - 
 
- - 
 
- - 
- - 
- - 
 
 
- - 
 
- - 
 
- - 
- - 
- - 
 
 
500 
2,100 
 
 
 
- - 
 
- - 
 
- - 
- - 
- - 
 
 
- - 
 
- - 
 
- - 
- - 
- - 
 
 
- - 
- - 
 
 
 
528(580,11AG) 
 
500(550,-11AG) 
 
70(75,-11AG) 
- - 
- - 
 
 
528(580,-11AG) 
 
500(550,-11AG) 
 
- -(75, 11AG) 
- - 
- - 
 
 
475 
- - 
 
 
 
 
579 
 
550 
 
72 
- - 
- - 
 
 
579 
 
550 
 
72 
- - 
- - 
 
 
500 
- - 
 
 
 
 
 
 
I. MODELS (Cont.) PT6A-21,-
25, -25A 
PT6A-25C PT6A-15AG, 
-27, -28 
PT6A-29 PT6A-34,-34AG, -
34B, -36 
RATINGS  
 
Maximum continuous at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator  rpm 
 
Takeoff (5 min.) at sea level 
 Equivalent shaft hp 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Maximum reverse 
 Shaft hp 
 Output rpm (max) 
 
 
 
 
580 
550 
75 
2,200 
38,100 
 
 
580 
550 
75 
2,200 
38,100 
 
 
500 
2,100 
 
 
 
 
783 
750 
82 
- - 
- - 
 
 
783 
750 
82 
- - 
- - 
 
 
720 
- - 
 
 
 
 
715 
680 
90 
- - 
- - 
 
 
715 
680 
90 
- - 
- - 
 
 
620 
- - 
 
 
 
 
778 
750 
71 
- - 
- - 
 
 
778 
750 
71 
- - 
- - 
 
 
750 
- - 
 
 
 
 
783 
- - 
82 
- - 
- - 
 
 
783 
- - 
82 
- - 
- - 
 
 
720 
- -

TCDS   E4EA           PAGE 3 
I. MODELS (Cont.) PT6A-35 PT6A-110 PT6A-112 PT6A-114 PT6A-114A 
RATINGS  
 
Maximum continuous at sea level 
 Equivalent shaft hp 
 Shaft hp 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Takeoff (5 min.) at sea level 
 Equivalent shaft hp 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator  rpm 
 
Maximum reverse 
 Shaft hp. 
 Output rpm (max) 
 
 
 
 
787 
750 
93 
2,190 
38,100 
 
 
787 
750 
93 
2,190 
38,100 
 
 
720 
2,100 
 
 
 
 
502 
475 
68 
1,900 
- - 
 
 
502 
475 
68 
1,900 
- - 
 
 
455 
1,825 
 
 
 
 
528 
500 
70 
- - 
- - 
 
 
528 
500 
70 
- - 
- - 
 
 
475 
- - 
 
 
 
 
632 
600 
79 
- - 
- - 
 
 
632 
600 
79 
- - 
- - 
 
 
600 
- - 
 
 
 
 
725 
675 
124 
- - 
- - 
 
 
725 
675 
124 
- - 
- - 
 
 
675 
- - 
 
 
 
 
 
 
I. MODELS (Cont.) PT6A-116 
 
PT6A-121 PT6A-135,-
135A 
PT6D-114A PT6A-140 
RATINGS  
 
Maximum continuous at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Takeoff (5 min.) at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Maximum reverse 
 Shaft hp. 
 Output rpm (max) 
 
 
 
 
736 
700 
89 
1,900 
38,100 
 
 
736 
700 
89 
1,900 
38,100 
 
 
672 
1,825 
 
 
 
 
647 
615 
80 
- - 
- - 
 
 
647 
615 
80 
- - 
- - 
 
 
591 
- - 
 
 
 
 
787 
750 
93 
- - 
- - 
 
 
787 
750 
93 
- - 
- - 
 
 
720 
- - 
 
 
 
 
729 
680 
124 
6,188 
38,100 
 
 
729 
680 
124 
6,188 
- - 
 
 
680 
5,940 
 
 
 
 
912 
867 
119 
1900 
38,850 
 
 
912 
867 
119 
1900 
38850 
 
 
867 
1825

TCDS   E4EA           PAGE 4 
 
I. MODELS (Cont.) PT6A-140AG PT6A-140A 
 
RATINGS  
 
Maximum continuous at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Takeoff (5 min.) at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Maximum reverse 
 Shaft hp. 
 Output rpm (max) 
 
 
 
 
911 
867 
117 
1900 
38850 
 
 
911 
867 
117 
1900 
38850 
 
 
867 
1825 
 
 
 
 
945 
900 
113 
- - 
- - 
 
 
945 
900 
113 
- - 
- - 
 
 
900 
- - 
 
 
 
 
 
 
II. MODELS (Cont.) PT6A-38 
 
PT6A-41, 
-41AG, -42 
-42A 
PT6A-45 PT6A-45A, 
-45B 
RATINGS  
 
Maximum continuous at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Takeoff (5 min.) at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Maximum reverse 
 Shaft hp. 
 Output rpm (max) 
 
 
 
 
801 
750 
127 
2,000 
38,100 
 
 
801 
750 
127 
2,000 
38,100 
 
 
700 
1,900 
 
 
 
 
903 
850 
134 
- - 
38,100 
 
 
903 
850 
134 
- - 
38,100 
 
 
800 
- - 
 
 
 
 
1,070 
1,020 
127 
1,700 
- - 
 
 
1,174 
1,120 
136 
1,700 
- - 
 
 
900 
1,650 
 
 
 
 
- - 
- - 
- - 
- - 
39,000 
 
 
1,229 
1,173 
- -    140(-45B) 
- - 
39,000 
 
 
- - 
- -

TCDS   E4EA           PAGE 5 
II.  MODELS (Cont.) PT6A-45R 
 
PT6A-50 PT6A-52 PT6A-60A PT6A-60AG PT6A-61 
RATINGS  
Maximum continuous at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Takeoff (5 min.) at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Maximum reverse 
 Shaft hp. 
 Output rpm (max) 
 
 
 
1,070 
1,020 
127 
1,700 
39,000 
 
 
1,254 
1,197 
141 
1,700 
39,000 
 
 
900 
1,650 
 
 
 
1,022 
973 
124 
1,210 
38,100 
 
 
1,174 
1,120 
136 
1,210 
38,500 
 
 
1,120 
1,210 
 
 
 
898 
850 
120 
2000 
39,000 
 
 
898 
850 
120 
2000 
39,000 
 
 
800 
1900 
 
 
 
1,113 
1,050 
157 
1,700 
- - 
 
 
1,113 
1,050 
157 
1,700 
- - 
 
 
900 
1,650 
 
 
 
1,081 
1,020 
154 
- - 
- - 
 
 
- - 
- - 
- - 
- - 
- - 
 
 
- - 
- - 
 
 
 
902 
850 
132 
2,000 
- - 
 
 
902 
850 
132 
2,000 
- - 
 
 
800 
1,900 
 
 
 
 
 
 
III. MODELS PT6A-65B 
 
PT6A-65R PT6A-65AR PT6A-65AG PT6A-65SC 
RATINGS  
 
Maximum continuous at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Takeoff (5 min.) at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Alternative takeoff 
 (5 min. at sea level) 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
Maximum reverse 
 Shaft hp. 
 Output rpm (max) 
 
 
 
 
1,249 
1,173 
189 
1,700 
39,000 
 
 
1,249 
1,173 
189 
1,700 
39,000 
 
 
 
--- 
--- 
--- 
--- 
--- 
 
 
900 
1,650 
 
 
 
 
- - 
- - 
- - 
- - 
- - 
 
 
1,459 
1,376 
209 
- - 
- - 
 
 
 
1,308 
1,230 
195 
1,700 
39,000 
 
 
- - 
- - 
 
 
 
 
1,298 
1,220 
194 
- - 
- - 
 
 
1,509 
1,424 
214 
- - 
- - 
 
 
 
- - 
- - 
- - 
- - 
- - 
 
 
- - 
- - 
 
 
 
 
- - 
- - 
- - 
- - 
- - 
 
 
1,381 
1,300 
202 
- - 
- - 
 
 
 
--- 
--- 
--- 
--- 
--- 
 
 
- - 
- - 
 
 
 
 
1167 
1110 
143 
- - 
- - 
 
 
1167 
1110 
143 
- - 
- - 
 
 
 
--- 
--- 
--- 
--- 
--- 
 
 
- - 
- -

TCDS   E4EA           PAGE 6 
 
IV. MODELS (Cont.) PT6B-9 
RATINGS  
 
 Maximum continuous at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
 Takeoff (5 min.) at sea level 
 Equivalent shaft hp. 
 Shaft hp. 
 Jet thrust, lb. 
 Output rpm 
 Gas generator rpm 
 
 
 
 
--- 
500 
124 
6,230 
38,100 
 
 
--- 
550 
136 
6,230 
38,100 
 
 
COMPONENTS/ 
CONFIGURATION 
Includes basic engine, fuel and ignition systems but excludes propeller governor (-6, -20  
and PT6D-114A models only) and ignition power source. 
 
FUEL 
 
Fuels conforming to the current P&WC specification CPW 204, CPW46 and CPW381 
(for AG engines). Refer to the current revision of Service Bulletins or Maintenance 
manuals as follows for approved fuel types: 
SB 1244 - PT6A-6, 6A, 6B, 6/C20, 20, 20A, 20B, 21, 27, 28, 34, 34B, 36, 114, 114A, 
 116, 135, 135A, 35, 25, 25A, 25C 
SB 12044 - PT6A-110, 112, 121, 11 
SB 12144 - PT6A-15AG, 11AG 
SB 1344  - PT6A-34AG  
SB 1604  - PT6D-114A 
SB 3044  - PT6A-38, 41, 42, 42A, 45A, 45B, 45R 
SB 13044 - PT6A-52, 60A, 61, 65B, 65R, 65AR 
SB 13244 - PT6A-60AG, 65AG 
SB 4044  - PT6A-50 
Maintenance Manual 3075742  PT6A-140 
Maintenance Manual 3079582  PT6A-140AG 
Maintenance Manual 3077182  PT6A-140A 
Maintenance Manual 3135622  PT6A-65SC 
 
Emergency use of MIL-G-5572, Grades 80/07, 91/98, 100/130 and 115/145 is permitted 
for a total time period not exceeding 150 hours during any overhaul period.  It is not 
necessary to purge the unused fuel from the system when switching fuel type 
 
LUBRICATING OILS 
 
The following oils are eligible for these engines:  Refer to the current revision of Service 
Bulletins or Maintenance manuals as follows for approved fuel types: 
SB 1001 - PT6A-6, 6A, 6B, 6/C20, 20, 20A, 20B, 21, 27, 28, 34, 34AG, 34B, 36, 114, 
 114A, 116, 135, 135A, 35, 25, 25A, 25C 
SB 12001 - PT6A-11, 11AG, 15AG, 110, 112, 121 
SB 1601  - PT6D-114A 
SB 3001  - PT6A-38, 41, 42, 42A, 45A, 45B, 45R 
SB 13001 - PT6A-52, 60A, 60AG, 61, 65AG, 65B, 65R, 65AR 
SB 4001  - PT6A-50 
Maintenance Manual 3075742  PT6A-140 
Maintenance Manual 3079582  PT6A-140AG 
Maintenance Manual 3077182  PT6A-140A 
Maintenance Manual 3135622  PT6A-65SC

TCDS   E4EA           PAGE 7 
 
PRINCIPLE DIMENSIONS AND WEIGHT 
 
I. MODELS PT6A-6 PT6A-6A PT6A-6B PT6A-11,  
-11AG 
PT6A-20, -20A, 
-20B,-6/C20 
PRINCIPAL DIMENSIONS, in. 
  Length 
  Nominal diameter 
  Maximum radius 
  (excluding exhaust ports) 
 
 
61.89 
18.29 
10.85 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
11.50 
 
- - 
- - 
-10.85 
WEIGHT (DRY)  
 
280 284 - - 339 
340(-11AG) 
286(20, 6/C20) 
289(20A, 20B) 
CENTER OF GRAVITY  
(dry weight) (in.) 
 
  Forward of mount plane 
 
 
  Aft of forward mount plane 
 
  Below engine centerline 
 
  Right of engine centerline 
 
 
 
4.20 
 
 
--- 
 
0.34 
 
0.32 
 
 
 
4.40 
 
 
--- 
 
- - 
 
- - 
 
 
 
- - 
 
 
--- 
 
- - 
 
- - 
 
 
 
3.18 
 
 
--- 
 
0.26 
 
0.36 
 
 
 
4.14(20, 6/C20 
4.58(20A, 20B) 
 
--- 
 
0.45 
 
0.07(20, 6/C20) 
0.08(20A, 20B) 
REDUCTION GEAR RATIO .0668:1 - - - - - - - - 
 
 
 
 
I. MODELS (Continued) PT6A-21, 
-25, -25A 
PT6A-25C PT6A-15AG, 
-27, -28 
PT6A-29 PT6A-34, 
-34AG, -34B,-36 
PRINCIPAL DIMENSIONS, in. 
  Length 
 
  Nominal diameter 
 
  Maximum radius 
   (excluding exhaust ports) 
 
 
61.89((62.91,-
25,-25A) 
18.29(23.00, -
25, -25A) 
10.85(16.00, -
25, -25A) 
 
62.91 
 
23.00 
 
16.00 
 
61.89 
 
18.29 
 
11.50 
 
- - 
 
- - 
 
- - 
 
- - 
 
- - 
 
- - 
WEIGHT (DRY)  
 
 
 
337 (-21) 
362 (-25) 
352 (-25A) 
355 337 - - 340 (353 -34B) 
CENTER OF GRAVITY  
(dry weight) (in.) 
 
  Forward of mount plane 
 
  Aft of forward mount plane 
 
  Below engine centerline 
 
  Right of engine centerline 
 
 
 
3.04(-21) 
3.00(-25, -25A) 
--- 
 
0.32(-21) 
0.47(-25, -25A) 
0.20(-21) 
0.29(-25, -25A) 
 
 
 
 
3.00 
 
--- 
 
0.47 
 
0.29 
 
 
 
3.04 
 
--- 
 
0.32 
 
0.20 
 
 
 
- - 
 
--- 
 
- - 
 
- - 
 
 
 
 
- -(3.38 -34B) 
 
--- 
 
- -(0.37 -34B) 
 
- -(0.38 -34B) 
REDUCTION GEAR RATIO .0668:1 .0663:1 - - - - - -

TCDS   E4EA           PAGE 8 
 
I. MODELS (Continued) PT6A-110 PT6A-112 PT6A-114 PT6A-114A PT6A-116 
 
PRINCIPAL DIMENSIONS, in. 
 Length, in. 
 Nominal diameter 
 Maximum radius 
 (excluding exhaust ports) 
 
61.89 
18.29 
11.50 
 
- - 
- - 
- - 
 
61.89 
18.29 
11.73 
 
 
 
- - 
18.06 
11.50 
WEIGHT (DRY)  
 
343 - - 359 360 348 
CENTER OF GRAVITY  
(dry weight) (in.) 
 
  Forward of mount plane 
 
  Aft of forward mount plane 
 
  Below engine centerline 
 
  Right of engine centerline 
 
 
 
 
3.80 
 
--- 
 
0.26 
 
0.34 
 
 
 
- - 
 
--- 
 
- - 
 
- - 
 
 
 
3.88 
 
--- 
 
- - 
 
0.38 
 
 
 
- - 
 
- - 
 
- - 
 
- - 
 
 
 
3.87 
 
--- 
 
0.25 
 
0.35 
REDUCTION GEAR RATIO 0.0576:1 - - - - - - - - 
 
 
 
 
I. MODELS (Continued) PT6A-121 PT6A-135, 
-135A 
PT6D-114A PT6A-35 PT6A-140 
PRINCIPAL DIMENSIONS, in. 
 Length 
 Nominal diameter 
 Maximum radius 
 (excluding exhaust ports) 
 
 
61.89 
18.29 
11.50 
 
- - 
- - 
- - 
 
52.8 
18.29 
11.73 
 
61.89 
- - 
- - 
 
64.14 
18.92 
14.32 
WEIGHT (DRY)  
 
343 347 297 334 416.7 
CENTER OF GRAVITY  
(dry weight) (in.) 
 
  Forward of mount plane 
 
  Aft of forward mount plane 
 
  Below engine centerline 
 
  Right of engine centerline 
 
 
 
 
3.8 
 
--- 
 
0.26 
 
0.34 
 
 
 
3.87 
 
--- 
 
0.25 
 
0.35 
 
 
 
0.19 
 
--- 
 
0.31 
 
0.25 
 
 
 
3.87 
 
--- 
 
0.25 
 
0.35 
 
 
 
4.27 
 
--- 
 
0.47 
 
0.36 
REDUCTION GEAR RATIO 0.0576:1 - - 0.1875 0.0663:1 0.0582:1

TCDS   E4EA           PAGE 9 
 
I. MODELS (Continued) PT6A-140AG PT6A-140A 
PRINCIPAL DIMENSIONS, in. 
 Length 
 Nominal diameter 
 Maximum radius 
 (excluding exhaust ports) 
 
64.14 
18.62 
11.40 
 
- - 
- - 
- - 
WEIGHT (DRY)  
 
385 
 
 - - 
CENTER OF GRAVITY  
(dry weight) (in.) 
 
  Forward of mount plane 
 
  Aft of forward mount plane 
 
  Below engine centerline 
 
 
 
 
4.47 
 
0.33 
 
0.26 
 
 
 
- - 
 
- - 
 
- - 
REDUCTION GEAR RATIO 0.0582:1 - - 
 
 
 
 
II. MODELS (Continued) PT6A-38 
 
PT6A-41, 
-41AG, -42 
-42A 
PT6A-45 PT6A-45A, 
-45B 
PRINCIPAL DIMENSIONS, in. 
 Length 
 Nominal diameter 
 Maximum radius 
 (excluding exhaust ports) 
 
66.47 
18.29 
12.84 
 
- - 
- - 
- - 
 
72.62 
- - 
- - 
 
- - 
- - 
- - 
WEIGHT (DRY) 
 
405 419 445 - - 
CENTER OF GRAVITY 
(dry weight)(in.) 
 
  Forward of mount plane 
 
  Aft of forward mount plane 
 
  Below engine centerline 
 
  Right of engine centerline 
 
 
 
2.49 
 
--- 
 
0.32 
 
0.19 
 
 
 
 
- - 
 
--- 
 
- - 
 
- - 
 
 
 
5.38 
 
--- 
 
0.12 
 
0.27 
 
 
 
5.38 
 
--- 
 
0.12 
 
0.27 
REDUCTION GEAR RATIO 0.0663:1 - - 0.0568:1 - -

TCDS   E4EA           PAGE 10 
II.  MODELS (Continued) PT6A-
45R 
PT6A-50 PT6A-60A PT6A-61 PT6A-
60AG 
PT6A-52 
PRINCIPAL DIMENSIONS, in. 
 Length 
 Nominal diameter 
 Maximum radius 
 (excluding exhaust ports) 
 
72.62 
18.29 
12.84 
 
79.89 
- - 
15.44 
 
72.09 
18.29 
12.84 
 
66.76 
- - 
- - 
 
72.09 
- - 
- - 
 
66.76 
- - 
- - 
WEIGHT (DRY)  459 622 487 443 489 449 
  
CENTER OF GRAVITY  
(dry weight) (in.) 
  Forward of mount plane 
 
  Aft of forward mount plane 
 
  Below engine centerline 
 
  Right of engine centerline 
 
 
5.38 
 
--- 
 
0.12 
 
0.27 
 
 
--- 
 
See NOTE 
 
See NOTE 
 
See NOTE 
 
 
 
5.22 
 
--- 
 
.300 
 
.28 
 
 
2.630 
 
--- 
 
- - 
 
.29 
 
 
5.22 
 
--- 
 
- - 
 
.28 
 
 
2.51 
 
--- 
 
.260 
 
.330 
REDUCTION GEAR RATIO 0.0568:1 0.0438:1 0.0568:1 0.0663:1 0.0568:1 0.0663:1 
 
NOTE: For PT6A-50 C.G. location (dry weight) is 27.69 in. behind forward mounting ring, 0.27 in. below horizontal centerline and 
0.15 in. left of vertical centerline. 
 
III. MODELS PT6A-65B PT6A-65R PT6A-65AR PT6A-65AG PT6A-65SC 
PRINCIPAL DIMENSIONS, in. 
 Length 
 Nominal diameter 
 Maximum radius 
 
74.79 
18.29 
12.84 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
73.64 
18.77 
15.08 
WEIGHT (DRY)  
 
495 496 501 - - 517 
CENTER OF GRAVITY  
(dry weight) (in.) 
 
  Forward of mount plane 
 
  Aft of forward mount plane 
 
  Below engine centerline 
 
  Right of engine centerline 
 
 
 
3.75 
 
--- 
 
0.29 
 
.17 
 
 
 
- - 
 
--- 
 
- - 
 
- - 
 
 
 
- - 
 
--- 
 
- - 
 
- - 
 
 
 
- - 
 
--- 
 
- - 
 
- - 
 
 
 
3.5 
 
--- 
 
.31 
 
.24 
REDUCTION GEAR RATIO 0.0568:1 - - - - - - - - 
 
IV. MODELS  PT6B-9 
PRINCIPAL DIMENSIONS, in. 
 Length 
 Nominal diameter 
 Maximum radius 
 (excluding exhaust ports) 
 
58.68 
18.06 
10.85 
WEIGHT (DRY)  
 
255 
CENTER OF GRAVITY  
(dry weight) (in.) 
 
  Forward of mount plane 
 
  Aft of forward mount plane 
 
  Below engine centerline 
 
  Right of engine centerline 
 
 
 
 
--- 
 
22.08 
 
0.13 
 
0.52 
REDUCTION GEAR RATIO 0.1889:1

TCDS   E4EA           PAGE 11 
 
 
CERTIFICATION BASIS 
Applicable to the following engines and serial numbers:  FAR 21.29, CAR 13.  (Except Serial numbers shown below which were certified 
under FAR 21.21, FAR Part 33 and amendments 33-1 to 33-5 see NOTE below. 
 
MODEL SERIAL NUMBER APPLICATION ISSUED/REVISED WITHDRAWN  
PT6A-6 
PT6A-6A 
PT6A-6B 
PT6B-9 
PT6A-11 
PT6A-11AG 
PT6A-15AG 
PT6A-20 
PT6A-20A 
PT6A-20B 
PT6A-6/C20 
PT6A-21 
PT6A-25 
 
 
 
 
 
 
 
PT6A-25A 
PT6A-25C 
PT6A-27 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
PT6A-28 
 
PT6A-29 
PT6A-34 
 
 
 
PT6A-34B 
 
PT6A-34AG 
PT6A-35 
PT6B-35F 
PT6A-36 
All 
All 
All 
All 
All 
All 
All 
All 
All except 024103-024160 
All 
All 
All 
All except 058013-058018 
058025-058040 
058042-058047 
058049-058055 
058059-058064 
058068-058073 
058077-058084 
058089-058204 
All 
All 
All except 044878-040879 
040883-040884 
040894-040895 
040899-040921 
040929-040934 
040937-040943 
040946-040949 
040982-040988 
040993-040999 
041006-041007 
041015-041021 
041027-041032 
041036 
041041-041044 
041050-041053 
041060-041063 
041067-041098 
041105-041110 
041113-041146 
041152-041156 
041162-041175 
041180-041194 
041199-041201 
All except 050676-050925 
050928-050934 
All  
All except 056071-056075 
056080-056081 
056086-056090 
056098-056107 
054011, 054012 only 
prior to 054007 
All 
All 
All 
All 
June 4, 1962 
April 6, 1965 
November 30, 1967 
June 4, 1962 
August 19, 1977 
January 10, 1979 
January 9, 1978 
April 9, 1965 
February 19, 1973 
August 20, 1973 
February 19, 1973 
December 2, 1974 
May 5, 1976 
 
 
 
 
 
 
 
December 13, 1976 
March 5, 1990 
November 15, 1966  
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
January 27, 1969 
 
October 6, 1967 
April 29, 1971 
 
 
 
July 20, 1976 
 
February 3, 1977 
October 24, 2001 
August 10, 1979 
December 13, 1973 
December 31, 1963 
May 28, 1965 
December 20, 1967 
May 28, 1965 
September 16, 1977 
May 17, 1979 
January 27, 1978 
October 29, 1965 
March 9, 1973 
October 2, 1973 
March 9, 1973 
December 10, 1974 
May 6, 1976 
 
 
 
 
 
 
 
December 28, 1976 
June 8, 1990 
December 20, 1967 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
March 11, 1969 
 
October 28, 1968 
November 11, 1971 
 
 
 
August 4, 1976 
 
February 14, 1977 
May 29, 2002 
March 26, 1982 
December 13, 1973 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
July 17, 2020

TCDS   E4EA           PAGE 12 
 
PT6A-38 
 
PT6A-40  
PT6A-41  
PT6A-41AG 
PT6A-42  
PT6A-42A 
PT6A-45  
PT6A-45A 
PT6A-45B 
PT6A-45  
PT6A-50  
PT6A-60  
PT6A-60A 
PT6A-60AG 
PT6A-61  
PT6A-61A 
PT6A-65B 
PT6A-65R 
PT6A-65AR 
PT6A-65AG 
PT6A-110  
PT6A-112  
PT6A-114  
PT6A-114A 
PT6A-116  
PT6A-121  
PT6A-135  
PT6A-135A 
PT6D-114A 
PT6A-52 
PT6A-65SC 
079156, 079157 only  
prior to 079153 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
All 
May 12, 1975 
 
April 19, 1983 
August 30, 1973 
December 21, 1978 
July 11, 1979 
September 21, 1998 
May 12, 1975 
March 25, 1976 
March 2, 1979 
June 25, 1980 
September 21, 1976 
April 20, 1982 
April 19, 1983 
October 1, 1996 
April 20, 1982 
January 6, 1984 
April 20, 1982 
April 20, 1982 
January 6, 1984 
July 23, 1987 
August 8, 1980 
October 12, 1978 
December 21, 1982 
October 4, 1989 
October 4, 1984 
April 12, 1982 
September 9, 1977 
February 3, 1982 
October 30, 1996 
May 26, 2006 
January 27, 2020 
May 30, 1975 
 
July 13, 1983 
October 2, 1973 
May 17, 1979 
October 12, 1979 
December 4, 1998 
May 30, 1975 
April 22, 1976 
March 29, 1979 
August 1, 1980 
October 22, 1976 
March 15, 1983 
November 7, 1983 
October 10, 1996 
March 15, 1983 
May 1, 1985 
September  17, 1982 
September  17, 1982 
May 1, 1985 
August 19, 1987 
February 15, 1981 
October 30, 1978 
May 21, 1984 
March 19, 1990 
May 1, 1985 
August 3, 1982 
September 12, 1977 
April 29, 1982 
September 22, 1997 
May 31, 2007 
April 12, 2021 
 
 
 
July 17, 2020 
 
 
 
 
 
 
 
 
 
July 17, 2020 
 
 
 
July 17, 2020 
 
 
 
 
 
 
 
 
 
 
 
The PT6A-65SC model complies with 14 CFR Part 34, Amendment 5A, effective October 23, 2013.  See Note 11 for detailed summary 
of the certification basis for fuel venting and exhaust emissions. 
 
14 CFR Part 33, effective February 1, 1965, including Amendments 33-1 through 33-20. 
The following models comply with 14 CFR Part 34, Amendment 5A, effective October 23, 2013.  See Note 11 for detailed summary of 
the certification basis for fuel venting and exhaust emissions. 
 
MODEL  S/N DATE OF APPLICATION DATE OF TYPE CERTIFICATE 
 NO. E4EA ISSUED/REVISED 
PT6A-140 ALL March 9, 2011 December 17, 2012 
 
PT6A-140AG ALL May 15, 2014 October 1, 2015 
 
PT6A-140A ALL May 15, 2014 October 1, 2015 
 
NOTE: This Type Certificate Data Sheet reflects the certification basis and approval for those serial numbered model PT6A, PT6B and 
PT6D series engines listed under "Certification Basis".  Two Type Certificates have been issued for administrative purposes:  E4EA 
under FAR 21.29 for engines produced in Canada and E2NE under FAR 21.21 for engines produced in the United States.  The type 
design for each model engine, regardless of where produced, is identical.  The information on this Type Certificate Data Sheet applies to 
all Pratt & Whitney model PT6A, PT6B and PT6D series engines, including: 
 
(A)  Those serial numbered engines listed on and certificated under FAA Type Certificate E2NE, originally issued to Pratt & Whitney 
Aircraft Division of United Technologies Corporation, East Hartford, Connecticut, U.S.A. and reissued to Pratt & Whitney of  Canada 
Ltd. (Formerly United Aircraft of Canada, Ltd.), Longueuil, Quebec, Canada. 
 
(B)  Those serial numbered engines listed above under "Certification Basis," certificated under this Type Certificate, E4EA, issued to 
Pratt & Whitney Canada Corp, Longueuil, Quebec, Canada.

TCDS   E4EA           PAGE 13 
 
NOTES 
 
 
  
NOTE 1.            ENGINE RATINGS: 
 
The engine ratings are based on static sea level condition 29.92 in Hg pressure, compressor intake screen installed, no external 
accessory loads and no airbleed.  These ratings are available up to the following compressor inlet air (dry) temperatures. 
 
 Maximum 
Continuous 
 
Takeoff 
 Maximum 
Continuous 
 
Takeoff 
PT6A-6, -6A, -6B 64oF 70oF PT6A-60AG 63oF 79oF 
PT6A-20, -20A, -20B,-6/C20 70 70 PT6A-61 115 115 
PT6A-11 108 108 PT6A-65B 101 110 
PT6A-11AG 90 90 PT6A-65R 101 82, 76(1) 
PT6A-21 91 91 PT6A-65AR 101 82, 84(1) 
PT6A-25,-25A 93  93 PT6A-65AG 101 71 
PT6A-25C 87 87 PT6A-65SC 131 131 
PT6A-15AG, -27 71 71 PT6A-110 101 101 
PT6A-28 70 70 PT6A-112 133 133 
PT6A-29 73 73 PT6A-114 136 136 
PT6A-34, -34B,-34AG 86 86 PT6A-114A 115 115 
PT6A-35,-135A 93 93 PT6A-116 105 105 
PT6A-36 97 97 PT6A-121 104 104 
PT6A-38 102 102 PT6A-135 85 85 
PT6A-41, -41AG, -42 106 106 PT6A-140 80 102 
PT6A-42A 106 106 PT6A-140A 87.8 98.6 
PT6A-45 79 59 PT6A-140AG 78.8 111.2 
PT6A-45A 79 46    
PT6A-45B 84 52 PT6B-9 72 77 
PT6A-45R 92 73, 52(1)    
PT6A-50 90 59, 93(2) PT6D-114A 104 104 
PT6A-52 142 142    
PT6A-60A 77 77    
      
      
 
1. Alternative Takeoff 
2. Takeoff with Augmentation Fluid

TCDS   E4EA           PAGE 14 
NOTE  2.      TEMPERATURES: 
 
MODELS PT6A-20, -20A, -20B, -6/C20 
PT6A-6, -6A, -6B, -28, -29 
PT6B-9 PT6A-11, -11AG 
 Measured Rated Turbine 
Temperature as Indicated by the 
Average of 24 Gas Temp. 
Thermocouples 
Measured Rated Inter-Turbine 
Temperature as Indicated by the 
Average of 8 or 10 Gas Temp. 
Thermocouples 
- - 
 
Takeoff 1821oF (994oC) 
1382ºF(750ºC) 
(PT6A-20,-20A,-20B,-6/C20) 
1382oF (750oC) 
 
 
1292oF (700oC) 
 
 
Maximum Continuous 1745oF (952oC) 
1382ºF(750ºC) 
(PT6A-20,-20A,-20B,-6/C20) 
1382oF (750oC) 
1319oF (715oC) (PT6B) 
 
1292oF (700oC) 
 
 
Starting Transient 
(2 sec.) 
1900oF (1038oC) 
1994ºF(1090ºC) 
(PT6A-20,-20A,-20B,-6/C20) 
1994oF (1090oC) 
 
- - 
 
 
MODELS (cont.) PT6A-21 PT6A-25, -25A 
 
PT6A-15AG, -27, -112, -121 
 
 Measured Rated Inter-Turbine 
Temperature as Indicated by the 
Average of 8 or 10 Gas Temp. 
Thermocouples 
- - - - 
Takeoff 1283oF (695oC) 1283oF (695oC) 1336oF (725oC) 
Maximum Continuous 1283oF (695oC) 1283oF (695oC) 1336oF (725oC) 
Starting Transient 
(2 sec.) 
1994oF (1090oC) - - 1994oF (1090oC) 
 
MODELS (cont.) PT6A-34, -34B, -34AG, -25C PT6A-35,-36,-114,-114A, 
-116,-135,-135A, 
PT6D-114A 
PT6A-110 
 Measured Rated Inter-Turbine 
Temperature as Indicated by the 
Average 8 or 10 Gas Temp. 
Thermocouples 
Measured Rated Inter-
Turbine Temperature as 
Indicated by the Average of 8 
Gas Temp. Thermocouples 
- - 
Takeoff 1454oF (790oC) 1481oF (805oC) 1265oF (685oC) 
Maximum Continuous 1454oF (790oC) 1481oF (805oC) 1265oF (685oC) 
Starting Transient 
(2 sec.) 
1994oF (1090oC) - - - - 
 
 
MODELS (cont.) 
 
PT6A-38 PT6A-41, -41AG PT6A-45 PT6A-42, -42A, 
-45A,-45B, -50 
 Measured Rated Inter-
Turbine Temperature as 
Indicated by the Average of 8 
Gas Temp. Thermocouples 
- - - - 
(8 or 10) 
- - 
Takeoff 1301oF (705oC) 1382oF (750oC) 1400oF (760oC) 1472oF (800oC) 
Maximum Continuous 1301oF (705oC) 1382oF (750oC) 1400oF (760oC) 1472oF (800oC) 
Starting Transient  
(5 sec.) 
1832oF (1000oC) - - - - - -

TCDS   E4EA           PAGE 15 
NOTE  2.(cont.) 
 
MODELS (continued) 
 
PT6A-45R PT6A-61 PT6A-60A, -60AG, -52 
 Measured Rated Inter-
Turbine Temperature as 
Indicated by the Average of 
8 Gas Temp. Thermocouples 
Measured Rated Inter-Turbine 
Temperature as Indicated by 
the Average of 8 or 10 Gas 
Temp. Thermocouples 
- - 
Takeoff 1553oF (845oC) 1472ºF (800ºC) 1508ºF(820ºC) 
Maximum Continuous 1494oF (812oC) 1472oF (800oC) 1508oF (820oC) 
1472ºF(775ºC)(-60AG) 
Starting Transient (5 
sec.) 
1832oF (1000oC)  - - - - 
Alternate Takeoff 1472oF (800oC) --- --- 
 
MODELS (continued) PT6A-65B 
 
PT6A-65R PT6A-65AR PT6A-65AG PT6A-65SC 
 Measured Rated Inter-
Turbine Temperature as 
Indicated by the Average 
of 8 or 10 Gas Temp. 
Thermocouples 
- - 
 
- - 
 
- - - - 
Takeoff 1508ºF(820ºC) 1553ºF(845ºC) 1571oF (855oC) 1508oF (820oC) 1526oF (830 oC) 
Maximum Continuous 1490oF (810oC) 1539oF (835oC) 1544oF (840oC) 1508oF (820oC) 1499 oF (815 oC) 
Starting Transient  1832oF (1000oC) - - - - - - - - 
Alternate Takeoff --- 1490oF (810oC) 1508oF (820oC) --- --- 
 
 
 
MODELS (continued) 
 
PT6A-140 PT6A-140AG  PT6A-140A 
 Measured Rated Inter-
Turbine Temperature as 
Indicated by the Average 
of 8 Gas Temp. 
Thermocouples 
- - 
 
- - 
 
Takeoff 1562oF (850 oC) 1598 oF (870 
oC)  
- - 
Maximum Continuous 1517 oF (825 oC) - - 1580 oF (860 oC) 
Starting Transient  1994 oF (1090 oC) - -   - - 
  
 
OIL TEMPERATURE LIMITS 
All except PT6A-41,-42,-42A,-45,-45A,-45B,-45R,-60A,-60AG,-61,-65AG,-65AR,-65B, 65R, -140,-140AG and-140A models, 
Oil Temperature Continuous minus 40oF (-40oC) to 210oF (99oC) except for MIL-L-7808 (where approved; See NOTE 9) for 
which the maximum allowable temperature is 185oF (85oC).  Limited periods of 10 minutes of 220oF (104oC) are allowable, 
except on A-25, A-25A, A-25C, A-11 and A-11AG (5 minute maximum),  A-50 (15 minutes maximum), and PT6A-65SC where 
limited periods of 10 minutes of 230oF (110oC) are allowable. 
 
PT6A-41,-42 and -42A, Oil Temperature Continuous minus 40ºF(-40ºC) to 220ºF(104ºC).  Maximum ground operation 
230ºF(110ºC).

TCDS   E4EA           PAGE 16 
PT6A-45,-45A,-45B,-45R,-52,-60A,-60AG,-61,-65AG,-65AR,-65B, 65R.  Oil Temperature Continuous minus 40ºF(-40ºC) to 
230ºF(110ºC). 
 
PT6A-140, -140AG, and -140A, Oil temperature continuous at idle minus 40ºF(-40ºC) to 210oF (99oC).  Oil temperature 
continuous at Take off and Max continuous 90 ºF (32 ºC ) to 210oF (99oC).  Limited periods of 10 minutes of 220oF (104oC) are 
allowable 
 
FUEL TEMPERATURE LIMITS 
Fuel temperature maximum fuel pump inlet of 135oF (57oC).  Fuel temperature minimum fuel pump inlet of minus 65oF (-54oC) 
or 12 centistokes. See the specific installation manuals for additional details. 
 
NOTE 3. 
 
 
PRESSURES: 
 
Fuel:  Minimum pressure at inlet to the engine fuel system shall not be less than 5 p.s.i. above true vapor 
pressure of the fuel.  For emergency operation, with airframe boost pump inoperative, it must be such that vapor 
liquid ratio does not exceed 0.1 for continuous operation and does not exceed 0.3 for more than 10 hours in a 
pump overhaul life. PT6A-140, -140AG, -140A and PT6A-65SC refer to the installation manual. 
 
 Oil:    Operating range:  
 PT6A-6, -6A, -6B, -20, -20A, -20B, -6/C20, PT6B-9 
28000 rpm gas generator speed and above: 
Below 28000 rpm gas generator speed: 
 
65-85 p.s.i.g., 80 p.s.i.g. (max. B-9) 
40 p.s.i.g. (min.) 
  PT6A-11, -11AG, -15AG, -21, -27, -28, -29, -50, -110, -112, -121 
27000 rpm gas generator speed and above, with an oil temperature 
of 140-158oF: 
Below 27000 rpm gas generator speed: 
 
 
80-100 p.s.i.g. 
40 p.s.i.g. (min) 60 p.s.i.g. (-50) 
 
   
 PT6A-25, -25A, -25C 
27000 rpm gas generator speed and above, with an oil temperature 
of 140-160oF: 
Below 27000 rpm gas generator speed: 
 
 
65-85 p.s.i.g. 75-95 p.s.i.g. (A-25C) 
40 p.s.i.g. (min) 
 
  
PT6A-34, -34B, -34AG, -35,-135, -135A, -36, -114, -114A, -116, 
PT6D-114A, PT6A-140, -140AG, -140A 
27000 rpm gas generator speed and above, with an oil temperature 
of 140-158oF: 
 
 
Below 27000 rpm gas generator speed: 
 
 
 
 
85-105 p.s.i.g. 75-100 p.s.i.g. (B-35F) 
85-120 p.s.i.g. (A-140, A-140AG) 
90-130 p.s.i.g. (A-140A) 
 
40 p.s.i.g. (min) 
 
 PT6A-38, -41, -41AG, -42, -42A 
27000 rpm gas generator speed and above, with an oil temperature 
of 140-160oF: 
 
 
Below 27000 rpm gas generator speed: 
 
 
85-135  p.s.i.g. (PT6A-38) 
105-135 p.s.i.g. (PT6A-41, -41AG) 
100-135 p.s.i.g. (PT6A-40, -42, -42A) 
60 p.s.i.g. (min) 
 
 PT6A-45, -45A, -45B, -45R,-52, -60A, -60AG, -61, -65B, 65R,-
65AR, -65AG, -65SC 
27000 rpm gas generator speed and above, with an oil temperature 
of 140-160oF: 
Below 27000 rpm gas generator speed:  
 
 
90-135 p.s.i.g. 
 
60 p.s.i.g. (min)

TCDS   E4EA           PAGE 17 
 
NOTE  4. ACCESSORY DRIVE PROVISIONS:  (All Models except -50 which is at bottom of this Note)  
The following accessory drive provisions are available and are included in the basic engine weight. 
 
    Maximum 
Driven by Gas Rotating Facing Speed Ratio Maximum Torque Overhang 
Generator Turbine Drive Pad (to Turbine) Continuous Static (in. - lbs.) 
Tachometer, 
Accessory Gearbox 
CC 0.112 
 
7 100 10 
Starter and/or 
Generator 
C 0.293 170 
 
1600 
 
150 (PT6A-6, 6A, 6B, 
6/C20, 20, 20A, 20B, 25, 
25A, 25C, 34B) 
 
150 or  250 when engine has 
a wet spline starter generator 
arrangenment -see 
installation manuals for 
details (PT6A-11, 11AG, 
15AG, 21, 27, 28, 34, 
34AG, 36, 110, 112, 135) 
 
250  (PT6A-35, 38, 41, 42, 
42A,41AG, 45, 45A, 45B, 
45R, 52, 60A, 60AG, 61, 
65B, 65R, 65AR, 65AG, 
65SC, 114, 114A, 116, 121, 
135A,  140, 140AG, 140A 
PT6B-35F, PT6D-114A) 
Vacuum Pump CC 0.103 
0.1019 (-140, -140AG, -
140A, 65SC) 
 
60 800 25 
Hydraulic Pump CC 0.203 
0.2041 (-140, -140AG, -
140A, 65SC) 
150 800 25 
Aircraft Accessory 
Drive 
C 0.321 135 800 25

TCDS   E4EA           PAGE 18 
NOTE  4.(continued) 
    Maximum 
Overhang 
(in. - lbs.) 
Driven by  Rotating Facing Speed Ratio Maximum Torque 
Power Turbine 
 
Drive Pad 
 
(to Turbine) 
 
Continuous 
 
Static 
 
Tachometer 
(Tachometer and 
overspeed 
governor for 
PT6A-6,-6A,-6B 
and-20 only) 
C 0.1264 (PT6A-15AG, -25C,-27,-28,-29,-34, 
-34B,-34AG,-35,-36,-38,-41,-41AG,-42, 
-42A,-52, -61) 
0.1273 (PT6A-6,-6A,-6B,-11,-11AG,-20,  
-20A,-20B,-6/C20,-21,-25,-25A,-110,-112 
-114, 114A, -116, 121,-135,-135A); 
0.1405 (45, 45A, 45B, 45R, 60A, 60AG, 65B, 
65R, 65AR, 65AG, 65SC) 
0.1286 (-140, -140AG, -140A) 
7 100 10 
 Propeller 
Governor and 
Overspeed 
Governor* 
C 0.1264 (PT6A-15AG, -25C,-27,-28,-29,-34,-34B, 
-34AG,-35,-36,-38,-41,-41AG,-42,-42A,-52, -61) 
0.1273 (PT6A-6,-6A,-6B,-11,-11AG,-20,-20A,-
20B,-6/C20,-21,-25,-25A,-110,-112, -114, 114A, 
 -116, 121,-135,-135A); 
0.1405 (PT6A-45, 45A, 45B, 45R, 60A, 60AG, 
65B, 65R, 65AR, 65AG, 65SC) 
0.1286 (-140, -140AG, -140A) 
50 850 25 
*  May be an optional drive, which is not included in the basic engine weight, is included. 
The hydraulic pump drive requires the aircraft accessory drive to complete the train. 
Cabin pressurization may be provided by the approved combination of the Beech Aircraft Corporation Gearbox No. 50-9903 with 
the Godfrey Engineering type 9 cabin supercharger, mounted directly on the accessories gearbox. 
 
PT6A-38,-41,-41AG,-42,-42A are approved for operation with an accessory mounted on the reduction gearbox and belt driven from 
the propeller assembly provided that the accessory is mounted and driven in accordance with the location dimensions and weight 
prescribed in Sheet 5 of Drawing Number 3018500, revision dated August 20, 1973. 
 
C = Clockwise 
CC = Counterclockwise 
 
PT6A-50 only 
    Maximum 
Driven by Gas Rotating Facing Speed Ratio Maximum Torque Overhang 
Generator Turbine Drive Pad (to Turbine) Continuous Static (in. - lbs.) 
Tachometer 
Accessory Gearbox 
CC 0.112 7 100 10 
Starter and/or 
Generator 
C 0.293 170 1600 230 
Hydraulic Pump* CC 0.204 150 800 30 
Driven by 
Power Turbine 
     
Tachometer CC 0.1400 7 100 10 
Alternator C 0.529 120 1600 105 
Prop. Governor CC 0.1400 100 1700 40 
Prop. Overspeed 
Governor 
CC 0.1400 50 850 25

TCDS   E4EA           PAGE 19 
NOTE  5 MODEL DESCRIPTION: 
 
 Model Characteristics 
 
 PT6A-6 Basic model 
 PT6A-6A Incorporates provisions for reversing propeller. 
 PT6A-6B Incorporates provisions for reversing propeller, PT6A-20 mechanism. 
 PT6B-9 Single stage reduction gearing.  (Output shaft speed 6,230 r.p.m.) 
 PT6A-20 Maximum continuous rating equal to takeoff.  Provisions for reversing. 
 PT6A-20A Similar to PT6A-20 except for exhaust port configuration and optional propeller reversing 
system. 
 PT6A-20B Similar to PT6A-20 except for optional propeller reversing system. 
 PT6A-11 Similar to PT6A-21 except derated. 
 PT6A-11AG Similar to PT6A-11, intended for agricultural aviation.  Permissible rotor component lives, 
overhaul, inspection intervals and fuel requirements are listed in PWC Engine Service Bulletin 
Nos. 12102, 12103, and12144 respectively. 
 PT6A-15AG Similar to PT6A-27, intended for agricultural aviation.  Permissible rotor component lives, 
overhaul inspection intervals and fuel requirements are listed in PWC Engine Service Bulletin 
Nos. 12102, 12103, and 12144 respectively. 
 PT6A-6/C20 Similar to PT6A-20 except this configuration previously PT6A-6 converted to PT6A-20 by 
service bulletin. 
 PT6A-21 Similar to PT6A-27 except derated. 
 PT6A-25 Similar to PT6A-27 except for modifications required for inverted flight optional torque 
controller, and aluminum alloy castings. 
 PT6A-25A Similar to PT6A-25 except for magnesium alloy major castings in place of  aluminum 
alloy. 
 PT6A-25C Similar to PT6A-25A except for A-34 hot section; T-3B first stage compressor blades and long 
inducer propeller; A-100 large bore reduction gears; and A-25A installation features.  Ratings 
and limits are the same as the A-34. 
 PT6A-27  Features higher ratings, revised engine parts and integrated propeller reversing control. 
 PT6A-28 Similar to PT6A-27 except for higher inter-turbine temperature limit. 
 PT6A-29 Features higher ratings, revised first stage reduction gearing. 
 PT6A-34 Similar to PT6A-27 except incorporates a compressor turbine similar to PT6T-3 for higher 
ratings. 
 PT6A-34B Similar to PT6A-34, except for aluminum alloy major castings in place of magnesium alloy. 
 PT6A-34AG Similar to PT6A-34, intended for agricultural aviation.  Permissible rotor component lives, 
overhaul, inspection intervals and fuel requirements are listed in P&WACL Engine Service 
Bulletin Nos. 1302, 1303, and 1344 respectively. 
 PT6A-35 Similar to PT6A-135 but incorporating the reduction gearbox of the PT6A-34. 
 PT6A-36 Similar to PT6A-34 except for increased turbine inlet temperature limits. 
 PT6A-38 Similar to PT6A-41 except derated. 
 PT6A-40 Similar to PT6A-42 except for increased flat rating and manual fuel control override. This model 
is withdrawn. 
 PT6A-41 Features an enlarged compressor and two stage power turbine for higher ratings. 
 PT6A-41AG Similar to PT6A-41, intended for agricultural aviation. 
 PT6A-42  Similar to PT6A-41 except for increased cruise rating and increased inter-turbine temperature 
limits with improved compressor and reduced loss exhaust ducts. 
 PT6A-42A Same as PT6A-42 except for addition of fuel control unit with manual override, compressor 
wash ring, accessory gearbox chip detector, P3 filter drain, and oil filler neck with check valve. 
 PT6A-45 Similar to PT6A-41 except for increased ratio reduction gearbox and higher ratings. 
 PT6A-45A Similar to PT6A-45 except for increased takeoff rating and increased inter-turbine temperature 
limits. 
 PT6A-45B Similar to PT6A-45A except for increased augmentation fluid flow for takeoff rating to a higher 
air inlet temperature. 
 PT6A-45R Similar to PT6A-45B except for provision for automatic power increase from alternate takeoff 
power to takeoff power. 
 PT6A-50 Similar to PT6A-45A except for new reduction gearbox. 
 PT6A-112 Similar to PT6A-27 except incorporates PT6A-41 fuel system concepts and PT6A-135 reduction 
gearbox. 
 PT6A-114 Similar to PT6A-135 with a single port exhaust and PT6A-41 fuel system concepts and PT6A-
135 reduction gearbox.

TCDS   E4EA           PAGE 20 
 
NOTE 5: (continued) 
 Model Characteristics 
 PT6A-114A Throttle push version of -114 incorporating the -135A compressor, and a new strengthened 
propeller shaft. 
 PT6A-135 Similar to PT6A-36 except for new reduction gearbox and higher cruise rating. 
 PT6A-135A Similar to PT6A-135 except for increased thermodynamic capability compressor. 
 PT6A-110 Similar to PT6A-11 except for incorporation of PT6A-135 reduction gearbox. 
 PT6A-65B Similar to PT6A-45 except for additional axial compressor stage and increased diameter gas 
producer turbine wheel. 
 PT6A-65R Identical to PT6A-65B except for reserve takeoff rating. 
 PT6A-65AR Uprated maximum continuous power PT6A-65R. 
 PT6A-65AG Similar to PT6A-65, intended for Agricultural Aviation.  Ratings similar to the 65AR without 
automatic reserve power. 
 PT6A-60 Uprated PT6A-42, featuring new first stage compressor gas producer turbine from PT6A-65 and 
gearbox from PT6A-45.  This model is withdrawn. 
 PT6A-60A Uprated altitude performance PT6A-60. 
 PT6A-60AG Similar to PT6A-60A, but with derated max continuous power, and intended for agricultural 
aviation. 
 PT6A-61 Similar to PT6A-60 except for PT6A-42 gearbox. 
 
 PT6A-61A Updated altitude performance PT6A-61.  This model is withdrawn. 
 PT6A-116 Similar to PT6A-135 except for reduced takeoff and maximum continuous power and torque 
limit with PT6A-121 externals. 
 PT6A-121 Similar to PT6A-21 except for a PT6A-135 reduction gearbox and a PT6A-112 power turbine. 
 PT6B-35F Combines the aerodynamic components of the PT6A-135, the mechanical layout of the PT6A-34 
and the PT6T-3 generator and exhaust case.  Intended for remote drive propeller applications.  
This model is withdrawn. 
 PT6D-114A Based on the PT6A-114A with the main difference being the deletion of the second stage 
reduction gearing and output shaft.  Intended for integration with a combining gearbox 
incorporated power turbine governors and a propeller output shaft. 
 
 PT6A-52 Similar to the PT6A-61 with the PT6A-60A thermal rating. 
 PT6A-140 Similar to the PT6A-114A with a new RGB for increased mechanical power and improved 
turbomachinery for increased thermodynamic power. 
 PT6A-
140AG 
Similar to PT6A-140 with a dual port exhaust duct and intended for agricultural aviation. 
 PT6A-140A Similar to PT6A-140 with a dual port exhaust duct. 
 PT6A-65SC Similar to PT6A-65B 
 
NOTE 6 ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES PROVIDED AS PART OF ENGINE 
TYPE DESIGN: 
 
Not Applicable 
 
NOTE 7 ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES NOT PROVIDED AS PART OF ENGINE 
TYPE DESIGN: 
 
Not Applicable 
 
NOTE 8. SPECIAL  ANTI-ICING OR DE-ICING REQUIREMENTS: 
 
These engines meet FAA requirements for operation in icing conditions when the intake system conforms with the 
PWC Installation Manual instruction for inertial separation of snow and icing particles; when the alternative 
approved alcohol system is used, flight in visible moisture is restricted as specified in the PWC Installation 
Manual.  These engines also meet FAA requirements for adequate disk integrity and rotor blade containment and 
do not require external armoring. 
 
Fuel anti-icing additives conforming to specifications 3GP526A PFA 55MB, MIL-I-27686E may be used, at a 
concentration not exceeding 0.15% by volume.

TCDS   E4EA           PAGE 21 
NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS: 
 
Refer to Installation Manuals for the engine mount system. 
  
NOTE 10 POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS: 
 
Augmentation fluid, when used, must meet the requirements of PWC Specification CPW No. 328. 
 
 SPECIAL INSTALLATION REQUIREMENTS: 
 
Reversing application the PT6A-6A and PT6A-20 engines must be equipped with Woodward Propeller Governor Type 
X210XXX. 
 
For PT6A-34, PT6A-34B, PT6A-36, PT6A-45, PT6A-45A and PT6A-45B power may be restored in hot day 
conditions by means of water or water/methanol injection when accomplished in accordance with the requirements of 
the PWC Installation Manual. 
 
The following emissions standards promulgated in 14 CFR Part 34, Amendment 5a, effective October 23, 2013, and 
40 CFR Part 87, effective October 31, 2012, have been complied with for:  PT6A-140, -140AG, -140A and PT6A-
65SC. 
Fuel Venting Emission Standards:  14 CFR §§ 34.10(b) and 34.11; in addition 40 CFR §§ 87.10(b) and 87.11. 
For the PT6A-140, -140AG, -140A and PT6A-65SC the engine manufacturer has declared that compliance has also 
been demonstrated with the CAEP/6 emission standards in ICAO’s Annex 16, Volume II, Third Edition, dated July 
2008.   The fuel venting requirements are applicable.  The smoke and emissions requirements are not applicable 
because the PT6A-140 and -140AG at 867 shp (647 kw), the PT6A-140A at 900shp (671 kw) and the PT6A-65SC at 
1110 shp (828 kw), are under the power threshold of 1000 KW for applicability to turboprops. 
 
 Oil Tank Capacity 
Total capacity Useable 
2.3 U.S. gallons 1.5 U.S. gallons 
 
For PT6A-25, -25A, -25C 
Total capacity Useable Useable when inverted 
2.8 U.S. gallons 1.5 U.S. gallons 0.25 U.S. gallons 
 
For PT6A-140, -140A, -140AG 
Total capacity Useable 
2.36 U.S. gallons 0.98 U.S. gallons 
 
PT6A-50 
Total capacity Useable 
3.0 U.S. gallons 1.0 U.S. gallons 
 
For PT6A-65B, -65R, -65AR, -65AG, -65SC 
Total capacity Useable 
2.5 U.S. gallons 1.5 U.S. gallons 
 
  
Output Shaft 
Flanged 4.250" B.C., 8 holes 0.594 + 0.005" diameter (See P&WC Installation Drawing) 
 
PT6A-50 
Flanged 5.125" B.C., 8 holes 0.594 + 0.005" diameter (See PWC Installation Drawing) 
 
PT6B-9 
SAE Aero Std. 84d Spline 1.5 in P.D (See PWC Installation Drawing) 
 
PT6B-35F 
36 teeth, 1.5 in. P.D. (See PWC Installation Manual)

TCDS   E4EA           PAGE 22 
 
NOTE  12. 
 
MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF 
INTEREST: 
 
Service Bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, overhaul and maintenance 
manuals, which contain a statement that the document is Transport Canada approved, are accepted by the FAA and are 
considered FAA approved.  These approvals pertain to the type design only. 
 
Fuel controls approved for each engine model are listed in the applicable Parts Catalog. 
 
NOTE 13. SPECIAL OPERATING PROCEDURES: 
 
Not applicable 
 
NOTE 14.  SPECIAL REPAIR OR OVERHAUL LIMITATIONS: 
Permissible overhaul and inspection intervals are listed in PWC Engine Service Bulletins, or for the PT6A-140, -140A  
-140AG and -65SC in the Maintenance Manuals: 
 
Engine 
Model 
Operating Time Between Overhaul 
and Hot Section Inspection 
PT6A-6, 6A, 6B,-34B, -25,-25A,-25C 1003 
PT6A-6/C20,-20,-20A,-20B,-21, 27, 28,-135, -135A 1803 
PT6A-11, -110, -112, -121 12003 
PT6A-11AG 12103 
PT6A-15AG 12103 
PT6A-34AG 1303 
PT6A-34,-35,-36 1403 
PT6A-38,-41,-42,-42A 3003 
PT6A-45A,-45B,-45R 3303 
PT6A-50 4003 
PT6A-52, -60A,-61 13303 
PT6A-60AG,-65AG 13203 
PT6A-65AR,-65B,-65R 13003 
PT6A-65SC 3135622 
PT6A-114, -114A, ,  1703 
PT6A-140 3075742 
PT6A-140A 3077182 
PT6A-140AG 3079582 
PT6D-114A 1603 
 
  
 
 
 
 
 
The following engines may be overhauled or maintained as two modules, the gas generator module and the power 
section module. The separation point is the "C" flange. The module part numbers are listed below. 
 
Engine Model Gas Generator Module Power Section Module 
PT6A-45A A 3030300 A 3030200 
PT6A-45B 2A 3030300 A 3030200 
PT6A-45R 3A 3030300 A 3030200 
PT6A-50 3031300 3031200 
PT6A-52 3072558 3072555 
PT6A-60A, -60AG 3102600 3102000 
PT6A-61 3102600 3103300 
PT6A-65B, -65R,-65AR,-65AG 3100800 3100900 
PT6A-65SC 3134857 3134856 
PT6A-140 3076223 3076225 
PT6A-140A 3079592 3079593 
PT6A-140AG 3079409 3079410

TCDS   E4EA           PAGE 23 
 APPLICABLE INSTALLATION, MAINTENANCE & OVERHAUL MANUALS: 
 
Applicable Installation manual (Pratt & Whitney Canada part numbers) are: 
 
Engine 
Model 
Engine 
Installation 
Manual 
PT6A-140 3075740 
PT6A-140A 3079605 
PT6A-140AG 3079575 
PT6A-65SC 3135675 
. 
Applicable Maintenance Manuals and Overhaul manuals (Pratt & Whitney Canada part numbers) are:  
 
Engine 
Model 
Engine 
Maintenance 
Manual 
Engine 
Overhaul 
Manual 
PT6A-6, 6A, 6B 3015442 3008103 
PT6A-11,-11AG 3030442 3030443 
PT6A-20, 20A, 20B, 6/C20 3015442 3011403 
PT6A-15AG 3030442 3030443 
PT6A-21, 27, 28 3013242 3013243 
PT6A-25,-25A 3027542 3027543 
PT6A-25C 3032142 3032143 
PT6A-34,-34B,-34AG,-36 3021242 3021243 
PT6A-35 3058362 3021243 
PT6A-38,-41,-42,-42A 3021442 3021443 
PT6A-45A,-45B,-45R 3027042 3027043 
PT6A-50 3023342 3023343 
PT6A-52 3072862 3072863 
PT6A-60A,-60AG,-61 3034342 3034343 
PT6A-65AG,-65AR,-65B,-65R 3032842 3032843 
PT6A-65SC 3135622 3135623 
PT6A-110, -112, -121 3030442 3030443 
PT6A-114, -114A, -116, -135, -135A 3043512 3021243 
PT6A-140 3075742 3075743 
PT6A-140A 3077182 3077183 
PT6A-140AG 3079582 3079583 
   
 
Transport Canada approved Parts List for the first production PT6A-140 engine – Engine assembly drawing no, 
3076226 change A and subsequent. 
 
Transport Canada approved Parts List for the first production PT6A-140A engine – Engine assembly drawing no, 
3079594 change A and subsequent. 
 
Transport Canada approved Parts List for the first production PT6A-140AG engine – Engine assembly drawing no, 
3079411 change A and subsequent. 
 
Transport Canada approved Parts List for the first production PT6A-65SC engine – Engine assembly drawing no, 
3134858 change G and subsequent.

TCDS   E4EA           PAGE 24 
NOTE 16.  IMPORT REQUIREMENTS: 
To be considered eligible for installation on U.S. registered aircraft, each engine to be exported to the United States 
shall be accompanied by a Certificate of Airworthiness for export or certifying statement endorsed by the exporting 
cognizant civil airworthiness authority which contains the following language: 
 
 (1) This engine conforms to its United States type design (Type Certificate Number E4EA) and is in a condition for 
safe operation. 
 (2) This engine has been subjected by the manufacturer to a final operational check and is in a proper state of 
airworthiness. 
 
Reference FAR Section 21.500, which provides for the airworthiness acceptance of aircraft engines or propellers 
manufactured outside of the U.S. for which a U.S. type certificate has been issued. 
 
Additional guidance is contained in FAA Advisory Circular 21.23, Airworthiness Certification of Civil Aircraft, 
Engines, Propellers and Related Products, Imported into the United States. 
  
 
 
 
NOTE 17.  LIFE  LIMITED PART INFORMATION: 
Certain parts are life limited.  Life limits are listed in PWC Engine Service Bulletins, or for the PT6A-140, -140A,  
-140AG and PT6A-65SC in the AWL section of the Maintenance Manuals: 
Engine Model Rotor Components Service Lives 
PT6A-6, 6A, 6B, 6/C20,-20,-20A,-20B,-21, 27, 28, 34,-34B,-35,-36,  
-114,-114A,-135,-135A 
1002 
PT6A-25,-25A,-25C, 1402 
PT6A-11,-110,-112,-121 12002 
PT6A-11AG,-15AG 12102 
PT6A-34AG  1302 
PT6A-38,-41,-42,-42A,-45A,-45B,-45R 3002 
PT6A-50 4002 
PT6A-52,-60A,-61,-62,-65AR,-65B,-65R 13002 
PT6A-65SC 3135622 
PT6A-60AG,-65AG 13202 
PT6A-140 3075742 
PT6A-140A 3077182 
PT6A-140AG 3079582 
PT6D-114A 1602

TCDS   E4EA           PAGE 25 
NOTE 18 MILITARY MODEL INFORMATION; 
 
 
 
NOTE 19.  
 
Not applicable 
 
ROTOR SPEEDS: 
 
The maximum output shaft overspeed limit is 110 percent (except 100% for PT6A-38, 41, 41AG, 42 and 42A only) 
at all ratings and may be employed for sustained periods in emergencies.   
 
The normal steady state output shaft operating limit speeds are defined as;  
2200 rpm (100%) for the PT6A-6, 6A, 6B, 6/C20, 11, 11AG, -15AG, -20, -20A, -20B, -21, -25, -25A, -25C, -27, -
28, -29, -34, -34B, -34AG, -36,  
2190 rpm (99.6%) for the PT6A-35,  
2000 rpm (90.7%) for the PT6A-38, -41, -41AG, -42, -42A, -52, and -61,  
1700 rpm (100%) for the PT6A-45,-45A,-45B,-45R,-65B,-65R,-60A,-60AG,-65AR,-65AG, -65SC, 
1900 rpm for the -135, 135A, 110, 112, 114, 114A, 121, 116,  140, 140AG, 140A,  
1210 rpm (100%) for the PT6A-50,  
6230 rpm (100%) for the PT6B-9 and  
6188 rpm (100%) for the PT6B-35F and PT6D-114A and is the normal steady state operating limit.   
 
The normal steady state operating limit speed rises linearly as power is decreased, reaching a maximum of 105% at 
idle power for the PT6B-9.  
 
100% gas generator speed is defined as 37,468 rpm.  Unlimited and limited gas generator speeds are: 
 
Model Unlimited Speed, rpm Limited Speed, rpm Duration 
PT6A-6,-6A,-6B,-11,-11AG,-
20,-20A,-20B,-6/C20,-21,-25,-
25A,-25C,-27,-28,-29,-34,-
34B,-34AG,-36,-38,-41 
38,100 (101.7%) 38,500 (102.8%) 10 Sec 
PT6A-35,-110,-112,-114,-
114A,-116,-121,-135,-135A, 
PT6D-114A 
38,100 (101.7%) 38,500 (102.8%) 2 Sec 
PT6A-50 38,500 (102.8%) --- --- 
PT6A-42,-42A 38,100 (101.7%) 39,000 (104.1%) 10 Sec 
PT6A-45,-45A,-45B,-45R,-52, 
-60A,-60AG,-61,-65B,-65R,-
65AR,-65AG, -65SC 
39,000 (104.1%) --- --- 
PT6A-140, -140AG, -140A 38,850 (103.7%) 40,000 (106.8%) 20 Sec

TCDS   E4EA           PAGE 26 
 
NOTE  20.  OUTPUT/PROPELLER SHAFT TORQUE LIMITS: 
 
The Maximum allowable steady state and acceleration torque, as measured by the torquemeter, are: 
 
 Model Continuous lb. Ft. Transient 
Acceleration lb. Ft.  PT6A-11, 11AG 1194 1500  PT6A-6, 6A, 6B, 20, 20A, 20B, 
6/C20, 21, 25, 25A 
1315 1500 
 PT6A-15AG, 27 1628 2100 
 PT6A-28 1786 2100 
 PT6A-29, 34, 34B, 34AG, 35, 36, 25C 1970 2100 
 PT6A-38 1970 2750 
 PT6A-41, 41AG, 42, 42A 2230 2750 
 PT6A-45, 45A, 45B 3625 5100 
 PT6A-45R 3625 5100 
 PT6A-50 4860 5900 
 PT6A-135, 135A 2080 2400 
 PT6B-9 464 --- 
 PT6A-112 1480 1900 
 PT6A-110 1313 1700 
 PT6A -60A, 60AG 3625 5100 
 PT6A-61 2230 2750 
 PT6A-65B, -65SC 3625 5100 
 PT6A-65R 4250 (3800 Alternative Takeoff) 5100 
 PT6A-114, 114A 1980 2400 
 PT6A-121 1710 2200 
 PT6A-65AR 4400(3800 Alternative Takeoff) 5100 
 PT6A-116  1940 2400 
 PT6A-65AG 3800 5100 
 PT6D-114A 610 740 
 PT6A-52 2230 2750 
 PT6A-140 2500 2625 
 PT6A-140A 2600 2950 
 PT6A-140AG 2500 2800 
    
    
NOTE 21.  
 
 
MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS: 
External airbleed shall not exceed 5.25%, except as specified in specific installation manuals.  A maximum of 1.5 
lbs. per minute may be bled during starting.  Bleed air meets the requirements of Paragraph 3.18 of MIL-E-5007C. 
 
NOTE 22.  ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT:(where special requirements apply) 
 
Not applicable 
 
 
----END----
```

## ADs (26, in force first)

- [AD 2022-08-13](https://openairdocs.org/ad/2022-08-13): Turbine Section · Pratt & Whitney Canada PT6A-34, PT6A-34B, PT6A-34AG and 2 more. Effective May 27, 2022
- [AD 2016-05-13](https://openairdocs.org/ad/2016-05-13): Corrosion and perforation of the two-ply Cu-Be bellows in Woodward FCUs. · Pratt & Whitney Canada PT6A-60AG, PT6A-65AG, PT6A-67AF and 1 more. Effective Apr 22, 2016
- [AD 2014-17-08 R1](https://openairdocs.org/ad/2014-17-08-R1): Compressor turbine (CT) blades · Pratt & Whitney Canada PT6A-114 and PT6A-114A. Effective Jun 5, 2015
- [AD 2014-11-05](https://openairdocs.org/ad/2014-11-05): Reinforcement liner to the power turbine (PT) containment   
  ring and, for certain PT containment rings, adding scallops · Pratt & Whitney Canada PT6A-11, PT6A-110, PT6A-112 and 18 more. Effective Aug 5, 2014
- [AD 2012-09-10](https://openairdocs.org/ad/2012-09-10): First stage sun gears · Pratt & Whitney Canada PT6A-110, PT6A-112, PT6A-114 and 12 more. Effective May 23, 2012
- [AD 2011-25-12](https://openairdocs.org/ad/2011-25-12): Sun gear · Pratt & Whitney Canada PT6A-15AG, PT6A-27, PT6A-28 and 4 more. Effective Dec 28, 2011
- [AD 2011-20-51](https://openairdocs.org/ad/2011-20-51): Gears · Pratt & Whitney Canada PT6A-15AG, PT6A-27, PT6A-28 and 4 more. Effective Nov 1, 2011
- [AD 2004-25-18](https://openairdocs.org/ad/2004-25-18): Propeller governor assemblies · Pratt & Whitney Canada PT6A-60A and PT6A-65B. Effective Jan 18, 2005
- [AD 2002-23-13](https://openairdocs.org/ad/2002-23-13): Turbine Exhaust Ducts · Pratt & Whitney Canada PT6A-11, PT6A-110, PT6A-112 and 20 more. Effective Dec 31, 2002
- [AD 2001-20-01](https://openairdocs.org/ad/2001-20-01): Compressor Bleed Valve Assembly · Pratt & Whitney Canada PT6A-114A and PT6A-25C. Effective Nov 5, 2001
- [AD 97-04-12](https://openairdocs.org/ad/97-04-12): Compressor Bleed-off Valve · Pratt & Whitney Canada PT6A-11, PT6A-110, PT6A-112 and 52 more. Effective Mar 14, 1997
- [AD 93-23-06](https://openairdocs.org/ad/93-23-06): Airframe Chip Detector Flag System · Pratt & Whitney Canada PT6A-50. Effective Jan 26, 1994
- [AD 92-15-11](https://openairdocs.org/ad/92-15-11): Compressor Delivery Air Line (P3) Filter Assembly · Pratt & Whitney Canada PT6A-20, PT6A-20A, PT6A-21 and 7 more. Effective Aug 17, 1992
- [AD 90-12-05](https://openairdocs.org/ad/90-12-05): Engine Overhaul · Pratt & Whitney Canada PT6A-15AG, PT6A-27, PT6A-28 and 3 more. Effective May 30, 1990
- [AD 86-10-05](https://openairdocs.org/ad/86-10-05): First Stage Compressor Hub · Pratt & Whitney Canada PT6A-42. Effective Jun 5, 1986
- [AD 80-08-12](https://openairdocs.org/ad/80-08-12): Fuel Pump Drive Coupling Splines · Pratt & Whitney Canada PT6A-11, PT6A-112, PT6A-135 and 24 more. Effective Apr 18, 1980
- [AD 80-04-02](https://openairdocs.org/ad/80-04-02): Push-Pull Control Terminal · Pratt & Whitney Canada PT6A-20, PT6A-6A, PT6A-6B and 1 more. Effective Feb 8, 1980
- [AD 78-17-07](https://openairdocs.org/ad/78-17-07): Fuel Control Unit · Pratt & Whitney Canada PT6A-38, PT6A-41 and PT6A-45A. Effective Aug 31, 1978
- [AD 78-12-04](https://openairdocs.org/ad/78-12-04): No. 2 Bearing Pressure Oil Transfer Tube Assembly · Pratt & Whitney Canada PT6A-38, PT6A-41 and PT6A-45A. Effective Jun 19, 1978
- [AD 75-06-01](https://openairdocs.org/ad/75-06-01): Gearbox Deterioration · Pratt & Whitney Canada PT6A-20, PT6A-20A, PT6A-20B and 11 more. Effective Apr 1, 1977
- [AD 75-11-04](https://openairdocs.org/ad/75-11-04): Reduction Gearbox Engine Distress · Pratt & Whitney Canada PT6A-20, PT6A-20A, PT6A-20B and 8 more. Effective May 20, 1975
- [AD 70-16-01](https://openairdocs.org/ad/70-16-01): Turbo Propeller Governors · Pratt & Whitney Canada PT6A-11, PT6A-11AG, PT6A-15AG and 5 more. Effective Aug 4, 1970
- [AD 69-23-06](https://openairdocs.org/ad/69-23-06): Fuel Pumps · Pratt & Whitney Canada PT6A-20, PT6A-27, PT6A-28 and 4 more. Effective Nov 15, 1969
- [AD 68-05-03](https://openairdocs.org/ad/68-05-03): Reverse Mode · Pratt & Whitney Canada PT6A-20 and PT6A-6B. Effective Feb 28, 1968
- [AD 2014-17-08](https://openairdocs.org/ad/2014-17-08) (historical): Compressor turbine (CT) blades · Pratt & Whitney Canada PT6A-114 and PT6A-114A. Effective Oct 8, 2014
- [AD 88-24-02](https://openairdocs.org/ad/88-24-02) (historical): Airframe Chip Detector Flag System · Pratt & Whitney Canada PT6A-50

## Registered aircraft by registry model (OpenAirDocs)

- [Pratt & Whitney Canada PT6A-60A](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-60a): 1,180 aircraft (registry codes 52043, 51999)
- [Pratt & Whitney Canada PT6A-65AG](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-65ag): 429 aircraft (registry code 52109)
- [Pratt & Whitney Canada PT6A-42A](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-42a): 383 aircraft (registry code 52268)
- [Pratt & Whitney Canada PT6A-34AG](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-34ag): 269 aircraft (registry code 52251)
- [Pratt & Whitney Canada PT6A-52](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-52): 266 aircraft (registry code 52200)
- [Pratt & Whitney Canada PT6A-114A](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-114a): 251 aircraft (registry code 52257)
- [Pratt & Whitney Canada PT6A-140](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-140): 238 aircraft (registry code 51499)
- [Pratt & Whitney Canada PT6A-42](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-42): 172 aircraft (registry code 52062)
- [Pratt & Whitney Canada PT6A-135A](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-135a): 160 aircraft (registry code 52260)
- [Pratt & Whitney Canada PT6A-60AG](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-60ag): 90 aircraft (registry code 52101)
- [Pratt & Whitney Canada PT6A-65B](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-65b): 77 aircraft (registry code 52115)
- [Pratt & Whitney Canada PT6A-21](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-21): 76 aircraft (registry code 52172)
- [Pratt & Whitney Canada PT6A-140AG](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-140ag): 75 aircraft (registry code 51800)
- [P&Wc PT6A-65SC](https://openairdocs.org/engine/p-wc-pt6a-65sc): 54 aircraft (registry code 51759)
- [Pratt & Whitney Canada PT6A-41](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-41): 42 aircraft (registry code 52265)
- [U/A Canada PT6A-41](https://openairdocs.org/engine/u-a-canada-pt6a-41): 42 aircraft (registry code 61541)
- [Pratt & Whitney Canada PT6A-15AG](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-15ag): 40 aircraft (registry code 52246)
- [Pratt & Whitney Canada PT6A-140A](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-140a): 33 aircraft (registry code 51805)
- [Pratt & Whitney Canada PT6A-45](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-45): 33 aircraft (registry code 52105)
- [Pratt & Whitney Canada PT6A-135](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-135): 28 aircraft (registry code 52173)
- [Pratt & Whitney Canada PT6A-65AR](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-65ar): 27 aircraft (registry code 52277)
- [Pratt & Whitney Canada PT6A-20](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-20): 21 aircraft (registry code 52239)
- [Pratt & Whitney Canada PT6A-112](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-112): 20 aircraft (registry code 52255)
- [Pratt & Whitney Canada PT6A-61](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-61): 19 aircraft (registry code 52274)
- [Pratt & Whitney Canada PT6A-60](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-60-series): 14 aircraft (registry code 52273)
- [Pratt & Whitney Canada PT6A-114](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-114): 10 aircraft (registry code 52256)
- [Pratt & Whitney Canada PT6A-25C](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-25c): 8 aircraft (registry code 52245)
- [Pratt & Whitney Canada PT6A-35](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-35): 7 aircraft (registry code 52262)
- [Pratt & Whitney Canada PT6A-45R](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-45r): 7 aircraft (registry code 52271)
- [Pratt & Whitney Canada PT6A-11](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-11): 5 aircraft (registry code 52237)
- [Pratt & Whitney Canada PT6A-25A](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-25a): 5 aircraft (registry code 52244)
- [Pratt & Whitney Canada PT6A-36](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-36): 4 aircraft (registry code 52253)
- [Pratt & Whitney Canada PT6A-11AG](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-11ag): 3 aircraft (registry code 52238)
- [Pratt & Whitney Canada PT6A-25](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-25): 3 aircraft (registry code 52243)
- [Pratt & Whitney Canada PT6A-65R](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-65r): 2 aircraft (registry code 52276)
- [U/A Canada PT6A-20](https://openairdocs.org/engine/u-a-canada-pt6a-20): 2 aircraft (registry code 61568)
- [U/A Canada PT6A-34AG](https://openairdocs.org/engine/u-a-canada-pt6a-34ag): 2 aircraft (registry code 61578)
- [U/A Canada PT6A-65AG](https://openairdocs.org/engine/u-a-canada-pt6a-65ag): 2 aircraft (registry code 61609)
- [Pratt & Whitney Canada PT6A-41AG](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-41ag): 1 aircraft (registry code 52266)
- [Pratt & Whitney Canada PT6A-50](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-50): 1 aircraft (registry code 52272)
- [U/A Canada PT6A-135](https://openairdocs.org/engine/u-a-canada-pt6a-135): 1 aircraft (registry code 61587)
- [U/A Canada PT6A-135A](https://openairdocs.org/engine/u-a-canada-pt6a-135a): 1 aircraft (registry code 61588)
- [U/A Canada PT6A-25](https://openairdocs.org/engine/u-a-canada-pt6a-25): 1 aircraft (registry code 61525)
- [U/A Canada PT6A-6](https://openairdocs.org/engine/u-a-canada-pt6a-6): 1 aircraft (registry code 61505)
- [Pratt & Whitney Canada PT6A-110](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-110): 0 aircraft (registry code 52254)
- [Pratt & Whitney Canada PT6A-116](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-116): 0 aircraft (registry code 52258)
- [Pratt & Whitney Canada PT6A-121](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-121): 0 aircraft (registry code 52259)
- [Pratt & Whitney Canada PT6A-20B](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-20b): 0 aircraft (registry code 52241)
- [Pratt & Whitney Canada PT6A-29](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-29): 0 aircraft (registry code 52249)
- [Pratt & Whitney Canada PT6A-34B](https://openairdocs.org/engine/pratt-whitney-canada-pt6a-34b): 0 aircraft (registry code 52252)

All 96: https://openairdocs.org/tcds/E4EA/aircraft.md

## STCs approved under this data sheet (53, first 50)

- [STC SE12225AC](https://openairdocs.org/stc/SE12225AC): This STC will incorporate P&W 1700 rpm propeller reduction gearbox on P&WC engines to allow 1700 rpm propeller installation. High Cotton Aircraft Conversions, LLC
- [STC SE00010EN](https://openairdocs.org/stc/SE00010EN): Instructions for Continued Airworthiness for the PT6A-25, and, -25A engine models that define specific maintenance tasks and their associated maintenance schedules, and that are used as a supplement to the applicable Pratt & Whitney Canada manuals.. MORE Company Inc
- [STC SE000010EN](https://openairdocs.org/stc/SE000010EN): Instructions for Continued Airworthiness for the PT6A-25 and PT6A-25A engine models that define specific maintenance tasks and their associated maintenance schedules, and that are used as a supplement to the applicable Pratt & Whitney Canada manuals.. MORE Company, Inc.
- [STC SE000011EN](https://openairdocs.org/stc/SE000011EN): Instructions for Continued Airworthiness for the PT6A-25C engine models that define specific maintenance tasks and their associated maintenance schedules, and that are used as a supplement to the applicable Pratt & Whitney Canada manuals.. MORE Company, Inc.
- [STC SE00001EN](https://openairdocs.org/stc/SE00001EN): Engines will be maintained IAW 'Maintenance or Reliable Engines(MORE) Program,' Rev 2, 8/16/95.. MORE Company Inc
- [STC SE00002EN](https://openairdocs.org/stc/SE00002EN): Instructions for Continued Airworthiness for the PT6A-34, -34AG, -34B, -36, -114,  -114A, -116, -135, and -135A engine models that define specific maintenance tasks and their associated maintenance schedules, and that are used as a supplement to the applicable Pratt & Whitney Canada manuals.. MORE Company Inc
- [STC SE00003EN](https://openairdocs.org/stc/SE00003EN): Instructions for Continued Airworthiness for the PT6A-6/C20, -20, -20A and, -20B engine models that define specific maintenance tasks and their associated maintenance schedules, and that are used as a supplement to the applicable Pratt & Whitney Canada manuals.. MORE Company Inc
- [STC SE00004EN](https://openairdocs.org/stc/SE00004EN): Instructions for Continued Airworthiness for the PT6A-11, -11AG, -15AG, -110 and-112 engine models that define specific maintenance tasks and their associated maintenance schedules, and that are used as a supplement to the applicable Pratt & Whitney Canada manuals.. MORE Company Inc
- [STC SE00006EN](https://openairdocs.org/stc/SE00006EN): Instructions for Continued Airworthiness for the PT6A-45A, -45B, and, -45R engine models that define specific maintenance tasks and their associated maintenance schedules, and that are used as a supplement to the applicable Pratt & Whitney Canada manuals.. MORE Company Inc
- [STC SE00011EN](https://openairdocs.org/stc/SE00011EN): Instructions for Continued Airworthiness for the PT6A-25C engine model that define specific maintenance tasks and their associated maintenance schedules, and that are used as a supplement to the applicable Pratt & Whitney Canada manuals.. MORE Company Inc
- [STC SE000EN](https://openairdocs.org/stc/SE000EN): Engines will be maintained IAW 'Maintenance or Reliable Engines(MORE) Program,' Rev 4, dated 8/16/95.. MORE Company Inc
- [STC SE10947SC](https://openairdocs.org/stc/SE10947SC): The conversion of the Pratt & Whitney Canada, Model PT6A-21 to a PT6A-28 turboprop engine. Prime Turbines
- [STC SE00482SE](https://openairdocs.org/stc/SE00482SE): Incorporation of turbine engine into a twin power section turboprop assembly.. Fifty-Ten-Yankee LLC
- [STC SE10552SC](https://openairdocs.org/stc/SE10552SC): Conversion  of Pratt & Whitney Canada Corp. Model PT6A-27 or -28 to a Model PT6A-34 turboprop engine.. Prime Turbines LLC
- [STC SE11139SC](https://openairdocs.org/stc/SE11139SC): The conversion of the Pratt & Whitney Canada, Model PT6A-135 to a PT6A-135A turboprop engine. Airforce Turbine Service
- [STC SE11141SC](https://openairdocs.org/stc/SE11141SC): The conversion of the Pratt & Whitney Canada, Model PT6A-15AG to a PT6A-34AG turboprop engine. RT Turbines Inc
- [STC SE02170AT](https://openairdocs.org/stc/SE02170AT): Installation of Pc Safety Valve Kit. Bell Helicopter Textron Inc.
- [STC SE11095SC](https://openairdocs.org/stc/SE11095SC): The conversion of the Pratt & Whitney Canada, Model PT6A-27 to a PT6A-34 turboprop engine. R.T. Turbines, Inc.
- [STC SE01624WI](https://openairdocs.org/stc/SE01624WI): Conversion of Pratt & Whitney Canada, Model PT6A-60A to a North Star Aviation PT6A-60AG turboprop engine.  
Data required: 
1.	A copy of this certificate
2. 	North Star Aviation document, NSA No. 1200, Turboprop Engine Conversion of PT6A-60A Model to PT6A-60AG Configuration per FAA Approved STC , dated March 15, 2011, or later FAA approved revision
3. 	The ICA supplement for North Star Aviation PT6A-60AG models, Instructions for Continued Airworthiness,  NSA No. 1200-ICA, Rev NC, dated March 9, 2011 or later applicable revision.. North Star Aviation Inc.
- [STC SE02837NY](https://openairdocs.org/stc/SE02837NY): The conversion of the Pratt & Whitney Canada PT6A-21 engine to operate as a PT6A-28 engine to be done.. Rocky Mountain Aircraft
- [STC SE02290NY](https://openairdocs.org/stc/SE02290NY): Conversion of a Pratt & Whitney Canada PT6A-21 engine to operate as a PT6A-27 or -28  engine. Vector Aerospace Engine Services Atlantic Inc.
- [STC SE02501NY](https://openairdocs.org/stc/SE02501NY): Conversion of the PT6A-11 engine. Vector Aerospace Engine Services Atlantic Inc.
- [STC SE00014EN](https://openairdocs.org/stc/SE00014EN): Installation of the Pratt & Whitney Engine Services, Inc. CrossCheck Engine Monitor Kit P/N HUMS-K-071-1, Rev. A on the specified PT6A engine models and kit P/N HUMS-K-071-2 on the specified A250 engine models.. Pratt & Whitney Engine Services Inc.
- [STC SE00020EN](https://openairdocs.org/stc/SE00020EN): Installation of the Pratt & Whitney Engine Services, Inc. TrendCheck/ TrendCheck Plus Engine Monitor Kit P/N TREND-K-010-1. Pratt & Whitney Engine Services Inc.
- [STC SE8652SW](https://openairdocs.org/stc/SE8652SW): Installation of a flexible hose from the Propeller Primary Governor to the Fuel Control Unit.. Air Tractor Inc
- [STC SE02357NY](https://openairdocs.org/stc/SE02357NY): Installation of the Pratt & Whitney Canada, PT6A-135, dual fuel feed line configuration. Standard Aero Inc
- [STC SE2960SO](https://openairdocs.org/stc/SE2960SO): Installation of an oil filler cap safety adapter.. Jet Avion Corporation
- [STC SE615GL](https://openairdocs.org/stc/SE615GL): Incorporation of a fuel flow transducer.. Shadin Avionics
- [STC SE01805NY](https://openairdocs.org/stc/SE01805NY): Installation of Fuel Nozzle Adapters using studs and nuts.. Atlantic Turbines International Inc.
- [STC SE09413SC](https://openairdocs.org/stc/SE09413SC): Install modified gas generator module.. Airforce Turbine Service
- [STC SE00856NY](https://openairdocs.org/stc/SE00856NY): Conversion of PT6A-41 engine model to PT6A-42 engine model.. Standard Aero Limited
- [STC SE00691NY](https://openairdocs.org/stc/SE00691NY): Conversion of engine models PT6A-27 and -28 to Model PT6A-34 as described in Temporary Overhaul Data Revision.. Standard Aero Limited
- [STC SE09286SC](https://openairdocs.org/stc/SE09286SC): Installation of an alternate gas generator case.. Airforce Turbine Service
- [STC SE09257SC](https://openairdocs.org/stc/SE09257SC): Convert P&W Engine Models PT6A-15AG, -27, and -28, into PT6A-34 configuration.. Covington Aircraft Engines, Inc.
- [STC SE659NE](https://openairdocs.org/stc/SE659NE): Installation of oil tank filler neck check valve, P/N TSA-76A.. Aviation Components Support
- [STC SE09144SC](https://openairdocs.org/stc/SE09144SC): Installation of an alternate gas generator case.. Airforce Turbine Service
- [STC SE1122EA](https://openairdocs.org/stc/SE1122EA): Repair of combustion chamber small exit duct, P/N 3012060.. Airwork Corporation
- [STC SE8319SW](https://openairdocs.org/stc/SE8319SW): Conversion of P&W Canada PT6A-15AG to PT6A-27 model configuration.. Airforce Turbine Service
- [STC SE7677SW](https://openairdocs.org/stc/SE7677SW): Modifiy the P&W Canada PT-6A-27, -28, -15AG to the PT6A-34 configuration.. Airforce Turbine Service
- [STC SE1251GL](https://openairdocs.org/stc/SE1251GL): Conversion of engine Model PT6A-27 to Model PT6A-34.. Turbines, Inc
- [STC SE539NE](https://openairdocs.org/stc/SE539NE): Modification of compressor turbine sealing segments to incorporate honeycomb material on the inside diameter thereby providing an abradable surface for turbine blade contact.. Airwork Corporation
- [STC SE1269EA](https://openairdocs.org/stc/SE1269EA): Stripping and recoating of compressor turbine blades, P/N 3023401, with Walbar Metals, Inc.. Airwork Corporation
- [STC SE386NE](https://openairdocs.org/stc/SE386NE): Installation of Turbo Products PMA parts.. Audco Corporation
- [STC SE355NE](https://openairdocs.org/stc/SE355NE): Conversion of engine model PT6A-27 to model PT6A-34.. Van Dusen Turbine Products
- [STC SE241NE](https://openairdocs.org/stc/SE241NE): Conversion of engine Models PT6A-27 and -28 to 01/157/3.. Airwork Corporation
- [STC SE260NE](https://openairdocs.org/stc/SE260NE): Conversion of engine PT6A-34 to PT6A-36.. Comerford-Audet Corporation
- [STC SE5601SW](https://openairdocs.org/stc/SE5601SW): Replacement splined end and oil mist lubrication on accessory drive gearshaft.. Aviall of Texas, Inc
- [STC SE79NE](https://openairdocs.org/stc/SE79NE): Conversion to an aircooled compressor turbine vane ring configuration.. Airwork Corporation
- [STC SE621GL](https://openairdocs.org/stc/SE621GL): Modify PT6A-112 fuel inlet line and primary fuel pressure tube bracket.. General Aviation, Inc
- [STC SE1165EA](https://openairdocs.org/stc/SE1165EA): Assembly and installation of AW10262 wet spline starter gear seal.. Airwork Corporation

All 53: https://openairdocs.org/tcds/E4EA/stcs.md

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