# TCDS E2EA: Pratt & Whitney

- Type: Type certificate data sheet
- Status: Current
- Holder: Pratt & Whitney
- Revision: 31
- Revised: August 28, 2007
- Product: Engine
- Certification basis: CAR 13
- Registered aircraft: 44, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/5a/4b/5a4bd89f0a01bb6df9a6d5e22a358f82afc2c6934a88aab26ae54082fcdd0bed
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D63B4DD4434FDACE862586B80050164D.0001
- Page: https://openairdocs.org/tcds/E2EA

## Models (16)

As the data sheet lists them.

- JT8D-17AR
- JT8D-1
- JT8D-17R
- JT8D-15A
- JT8D-15
- JT8D-17
- JT8D-7
- JT8D-17A
- JT8D-5
- JT8D-11
- JT8D-9
- JT8D-7A
- JT8D-1B
- JT8D-1A
- JT8D-9A
- JT8D-7B

## 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
 REV. 31 31 31 31 31 31 31 31 25 31
 LEGEND:    "- -" INDICATES "SAME AS PRECEDING MODEL" 
                 "---" NOT APPLICABLE 
 
 
 
 
 
 
U.S. DEPARTMENT OF TRANSPORTATION 
 
FEDERAL AVIATION ADMINISTRATION 
 
TYPE CERTIFICATE SHEET NO. E2EA 
 
 
TCDS NUMBER E2EA 
REVISION:  31 
DATE:    AUGUST 28, 2007 
 
PRATT & WHITNEY  
 
MODELS:        
 
TURBO WASP 
JT8D-1  JT8D-7B  JT8D-17 
JT8D-1A  JT8D-9  JT8D-17A 
JT8D-1B  JT8D-9A  JT8D-17R 
JT8D-5  JT8D-11  JT8D-17AR 
JT8D-7  JT8D-15  
JT8D-7A  JT8D-15A 
 
Engines  of models described herein conforming with this data sheet (which is part of Type Certificate Number E2EA) 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 
    United Technologies Corporation 
    East Hartford, Connecticut  06108 
 
I. MODELS JT8D-1, -1A,  
-7, -7A 
JT8D-1B,  
-7B 
JT8D-5 JT8D-9 JT8D-9A 
TYPE Dual, axial 13-stage compressor / four-stage turbine / nine can-annular 
combustion chambers 
RATINGS  
 
Sea Level Static Thrust (lbs) 
 
  Maximum continuous  
  Normal takeoff (5 min.) (See  
  NOTE 19) 
  Maximum takeoff (5 min.) (See 
  NOTE 19)  
 
 
 
 
12,600 
14,000 
 
14,000 
 
 
 
 
- - 
- - 
 
- - 
 
 
 
 
12,250 
12,250 
 
12,250 
 
 
 
 
12,600 
14,500 
 
14,500 
 
 
 
 
- - 
- - 
 
- - 
FUEL CONTROL  (See NOTE 17) 
   (Hamilton Standard) 
JFC60-1 or 
JFC60-2 
- - - - - - - - 
FUEL PUMP 
   (Argo-Tech Corp.) 
P/N 243600, 
358200, 
371900,  
378200, or 
835800 
- - - - - - - - 
AIR BLEED CONTROL (P&W) P/N 492143, 
492143-001, 
564651, 
564651-001, 
593764 
593764-001, 
658385, 
658385-001, 
658490, or 
658490-001 
- - - - 564651, 
564651-
001, 
593764, 
593764-
001, 
658385, or 
658385-001 
- - 
FUEL See Note 11 - - - - - - - - 
OIL See Note 12 - - - - - - - -

TCDS E2EA           PAGE 2  
 
I. MODELS (cont.) JT8D-1,  
-1A, -7, -7A 
JT8D-1B,  
-7B 
JT8D-5 JT8D-9 JT8D-9A 
PRINCIPAL DIMENSIONS: 
 
  Length, in. 
  Width, in. 
  Height, in. 
   
 
 
123.56 
42.50 
53.450 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
WEIGHT (dry), lb. (includes basic 
engine with all essential access., 
with fuel heater, oil tank and fuel oil 
cooler, but excluding starter exhaust 
nozzle and power source for the 
ignition system 
3205 - - - - 3252 3402 
CENTER OF GRAVITY, INCHES 
 
  Aft of front mount area 
   centerline 
  Below engine centerline  
    
 
 
23.54 
 
1.86 
 
 
- - 
 
- - 
 
 
- - 
 
- - 
 
 
- - 
 
- - 
 
 
23.08 
 
2.02 
IGNITORS Unison type TCFN-2, TCFN-4, TFN- 32, 42074, 49965, or 49988 exciter with two 
igniters:  P&W P/N 518367 or 709520 
NOTES 1-8, 10-15, 
& 19 
- - - - - - - - 
  
II. MODELS JT8D-11 JT8D-15 JT8D-15A JT8D-17 JT8D-17A 
TYPE Dual, axial 13-stage compressor / four-stage turbine / nine can-annular 
combustion chambers 
RATINGS  
 
Sea Level Static Thrust (lbs) 
 
  Maximum continuous  
  Normal takeoff (5 min.) (See  
  NOTE 19) 
  Maximum takeoff (5 min.) (See 
  NOTES 19)  
 
 
 
 
 
12,600 
15,000 
 
15,000 
 
 
 
 
13,750 
15,500 
 
15,500 
 
 
 
 
- - 
- - 
 
- - 
 
 
 
 
15,200 
16,000 
 
16,000 
 
 
 
 
- - 
- - 
 
- - 
FUEL CONTROL 
   (Hamilton Standard) 
JFC60-1 or 
JFC60-2 
- - - - JFC60-2 - - 
FUEL PUMP 
   (Argo-Tech Corp.) 
P/N 358200, 
371900,  
378200, or 
835800 
P/N 
378200 or 
835800 
- - P/N 384300 
or 835900 
- - 
AIR BLEED CONTROL (P&W) P/N 658385 or 
658385-001 
- - - - - - - - 
FUEL See Note 11 - - - - - - - - 
OIL See Note 12 - - - - - - - -

TCDS E2EA           PAGE 3  
 
II. MODELS (cont.) JT8D-11 JT8D-15 JT8D-15A JT8D-17 JT8D-17A 
PRINCIPAL DIMENSIONS: 
 
  Length, in. 
  Width, in. 
  Height, in. 
   
 
 
123.56 
42.50 
53.450 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
WEIGHT (dry), lb. (includes basic 
engine with all essential access., 
with fuel heater, oil tank and fuel oil 
cooler, but excluding starter exhaust 
nozzle and power source for the 
ignition system 
3389 3414 3474 3430 3475 
CENTER OF GRAVITY, INCHES 
 
  Aft of front mount area 
   centerline 
  Below engine centerline  
    
 
 
23.07 
 
1.76 
 
 
23.10 
 
1.75 
 
 
23.80 
 
- - 
 
 
23.70 
 
1.90 
 
 
24.40 
 
- - 
IGNITORS Unison type TCFN-2, TCFN-4, TFN- 32, 42074, 49965, or 49988 exciter with two 
igniters:  P&W P/N 518367 or 709520 
NOTES 1-8, 10-15, 
& 19 
- - 1-8, 10-15, 
& 18-19 
1-8, 10-15, 
& 19 
1-8, 10-15, & 18-
19 
 
III. MODELS JT8D-17R JT8D-17AR      
TYPE Dual, axial 13-stage compressor / four-stage turbine / nine can-annular 
combustion chambers 
RATINGS  
 
Sea Level Static Thrust (lbs) 
 
  Maximum continuous  
  Normal takeoff (5 min.) (See  
  NOTE 19) 
  Maximum takeoff (5 min.) (See 
  NOTE 19)  
 
 
 
 
 
15,200 
16,400 
 
17,400 
 
  
 
 
 
- - 
- - 
 
- - 
      
FUEL CONTROL 
   (Hamilton Standard) 
JFC60-3 - -       
FUEL PUMP 
   (Argo-Tech Corp.) 
P/N 384300 or 
835900 
- -       
AIR BLEED CONTROL (P&W) P/N 658385 or 
658385-001 
- -       
FUEL See Note 11 - -       
OIL See Note 12 - -

TCDS E2EA           PAGE 4  
 
III. MODELS (cont.) JT8D-17R JT8D-17AR    
PRINCIPAL DIMENSIONS: 
 
  Length, in. 
  Width, in. 
  Height, in. 
   
 
 
123.56 
42.50 
53.450 
 
 
- - 
- - 
- - 
     
WEIGHT (dry), lb. (includes basic 
engine with all essential access., 
with fuel heater, oil tank and fuel oil 
cooler, but excluding starter exhaust 
nozzle and power source for the 
ignition system 
3495 3500       
CENTER OF GRAVITY, INCHES 
 
  Aft of front mount area 
   centerline 
  Below engine centerline  
    
 
 
23.50 
 
1.80 
 
 
24.00 
 
- - 
      
IGNITORS Unison type TCFN-2, TCFN-4, TFN- 32, 42074, 49965, or 49988 exciter with two 
igniters:  P&W P/N 518367 or 709520 
NOTES 1-8, 10-16, 
& 19 
1-8, 10-16, & 
18-19 
      
 
CERTIFICATION BASIS CAR 13 effective June 15, 1956, as amended by 13-1, 13-2, 13-3, 13-4, and 13-5. 
 
     DATE OF TYPE CERTIFICATE 
MODEL  DATE OF APPLICATION  NO. E2EA ISSUED/REVISED  
 
JT8D-1  July 5, 1962  February 1, 1963 
JT8D-1A  February 25, 1971  April 7, 1971 
JT8D-1B  July 1, 1975  August 14, 1975 
JT8D-5  January 24, 1963  February 1, 1963 
JT8D-7  January 30, 1966  March 24, 1966   
JT8D-7A  July 1, 1970  August 4, 1970 
JT8D-7B  July 1, 1975  August 14, 1975 
JT8D-9  September 16, 1966 May 23, 1967  
JT8D-9A  March 28, 1973  May 30, 1973 
JT8D-11  April 19, 1968  September 25, 1968  
JT8D-15  October 14, 1969  April 7, 1971 
JT8D-15A March 13, 1980  January 26, 1982 
JT8D-17  January 15, 1973  February 1, 1974 
JT8D-17A March 13, 1980  January 26, 1982 
JT8D-17R May 15, 1974  April 29, 1976 
JT8D-17AR March 13, 1980  January 26, 1983 
 
PRODUCTION BASIS Producti on Certificate No. 2

TCDS E2EA           PAGE 5  
 
 
NOTES 
 
 
NOTE 1. Rotor Speeds - Maximum permissible engi ne operating speeds for the engine rotors are as 
follows: 
 
 JT8D-1,  
-1A, -1B,  
-7A, -7B,  
-9, -9A, -11 
JT8D-5 JT8D-15,  
-15A, -17,  
-17A 
JT8D-17R, 
-17AR 
 Low Pressure rotor (N), rpm 
  Maximum takeoff 
  Normal takeoff 
 
High pressure rotor (N2), rpm 
  Maximum takeoff 
  Normal takeoff 
  
--- 
8,600 
 
 
--- 
12,250 
 
--- 
8,500 
 
 
--- 
12,100 
 
--- 
8,800 
 
 
--- 
12,250 
 
9,250 
8,900 
 
 
12,600 
12,280 
 
NOTE 2. 
 
   
Temperatures - Maximum permissible temperatures are as follows: 
 
Turbine outlet gas temperature, °C/°F: 
 JT8D-1, -7 JT8D-5 JT8D-1A,  
-7A, -9 
JT8D-1B,  
-7B 
JT8D-9A 
  
Normal Takeoff (5 minutes) 
Maximum continuous 
Maximum for acceleration (2  
  minutes) 
Starting (for 59oF ambient   
  temperature and above) 
  (for 58oF ambient  
  temperature and below) 
Oil Inlet:  
    continuous operation 
    transient operation 
 
570/1058 
535/995 
570/1058 
 
420/788 
 
350/662 
 
 
120/250 
157/315 
 
555/1031 
- - 
555/1031 
 
- - 
 
- - 
 
 
- - 
- - 
 
580/1076 
540/1004 
580/1076 
 
- - 
 
- - 
 
 
- - 
- - 
 
590/1094 
545/1013 
590/1094 
 
- - 
 
- - 
 
 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
 
- - 
 
 
- - 
- - 
 JT8D-11 JT8D-15 JT8D-15A JT8D-17 JT8D-17A 
  
Normal takeoff (5 min.) 
Takeoff (5 min.) 
Maximum continuous 
Max. for accel. (2 min) 
Starting (ground) 
            (inflight) 
Oil Inlet:  
    continuous operation 
    transient operation 
 
- - 
595/1103 
550/1022 
595/1103 
510/950* 
550/1022 
 
130/266 
165/329 
 
- - 
620/1148 
580/1076 
630/1166 
550/1022 
620/1148 
 
- - 
- - 
 
- - 
- - 
- - 
- - 
575/1067 
- - 
 
- - 
- - 
 
- - 
650/1202 
610/1130 
660/1220 
550/1022 
650/1202 
 
- - 
- - 
 
- - 
- - 
- - 
- - 
575/1067 
- - 
 
- - 
- -

TCDS E2EA           PAGE 6  
 
NOTE 2. 
(Cont.) 
   
Temperatures - Maximum permissible temperatures are as follows: 
 
Turbine outlet gas temperature, °C/°F: 
 
 JT8D-17R JT8D-17AR       
  
Maximum takeoff (5 min.) 
Normal takeoff (5 min.) 
Maximum continuous 
Max. for accel. (2 min) 
Starting (ground) 
            (inflight) 
Oil Inlet:  
    continuous operation 
    transient operation 
 
690/1274 
650/1202 
610/1130 
660/1220 
550/1022 
650/1202 
 
130/266 
165/329 
 
- - 
- - 
- - 
- - 
575/1067 
- - 
 
- - 
- - 
   
  
NOTE: *Maximum starting limit (ground) is 530ºC/986ºF for JT8D-11 engines that have incorporated 
P&W Service Bulletin 5455. 
 
Transient operation above 120°C (250°F) JT8D-1, -1A, -5, -7, -7A, -7B, -9, -9A 130oC (266oF) JT8D-
11, -15, -15A, -17, -17A, -17R, and -17AR is limited to 15 minutes.  External engine components 
maximum temperature (limiting temperature of specific components) are specified in the engine 
installation and operating manual. 
 
NOTE 3. Pressures - Fuel and oil pressure limits are as follows: 
 
Fuel Pressure - At inlet to engine system pump, not less than 5 p.s.i. above the true  
vapor pressure of the fuel and not greater than 50 p.s.i. with a vapor  
liquid ratio of zero. 
 
Oil Pressure -   Minimum 35 psig 
Normal Range 40-55 psig 
 
Note:  During cold weather starting, oil pressure in excess of 55 psig may be evidenced until oil 
viscosities are reduced by increasing oil temperature.  Engine operation is limited to idle power when oil 
pressure is in excess of 55 psig during cold weather starts.

TCDS E2EA           PAGE 7  
 
NOTE 4. Air Bleed Extraction - Maximum permissible air bleed extraction is as follows: 
 Percentage of Primary Engine Airflow 
 
 
 
Station 
Individual Bleeding  
at a Single Station 
Normal  Maximum * 
Simultaneous Bleeding  
of Two or More Stations 
Normal  Maximum * 
 
1.  High-Pressure Bleed: 
     a. At 70% maximum continuous 
         thrust and below 
     b. From 70% maximum continuous 
         thrust to maximum continuous thrust 
     c. Above maximum continuous thrust 
 
2.  Eighth-Stage Bleed: 
     a. At and below maximum 
         continuous thrust 
     b. Above maximum continuous thrust 
 
3.  Low Pressure Bleed: 
     a. At 20% maximum continuous 
        thrust and above 
     b. Below 20% maximum 
         continuous thrust 
 
 
6.7 
 
3.5 
 
2.8 
 
 
4.0 
 
2.75 
 
 
5.0 
 
4.0 
 
 
 
8.0 
 
5.5 
 
3.0 
 
 
4.0 
 
3.25 
 
 
5.0 
 
4.0 
 
 
 
6.7 
 
3.5 
 
2.8 
 
 
4.0 
 
2.75 
 
 
4.5 
 
3.5 
 
 
 
8.0 
 
5.5 
 
3.0 
 
 
4.0 
 
3.25 
 
 
4.5 
 
3.5 
 
Percentage of Secondary Airflow 
 
4.  Fan Air Bleed: 
     a. At and below maximum continuous 
         thrust 
     b. Above maximum continuous thrust 
 
 
3.0 
 
2.0 
 
 
5.0 
 
2.0 
 
 
3.0 
 
2.0 
 
 
3.0 
 
2.0 
NOTE:  *Usable only when malfunction requires and only until next landing. 
 
NOTE 5. The ratings are based on static te st stand operation under the following conditions: 
 
 Compressor inlet air at 59°F and 29.92 in. Hg. 
Nozzle exhaust pipe per P&W Drawing PWA 12202 (JT8D-1, -1A, -1B, -5, -7, -7A, -7B, -9,  
-9A, -11, -15 and -15A); PWA 33811 (JT8D-15 and -15A);  PWA 33475 (JT8D-17, -17A, -17R, 
and -17AR); or PWA 12202  with PWA 33400 extender (JT8D-17, -17A, -17R, and -17AR) 
 P&WA bellmouth on air inlet. 
 No aircraft accessory l oads or air extraction. 
 No anti-icing air flow. 
 Turbine outlet gas temperature limit s and engine rotor speed limits not exceeded.

TCDS E2EA           PAGE 8  
 
NOTE 6.  The following accessory drive provisions are incorporated: 
 
 
 
Drive 
 
Rotation 
Speed Ratio to 
Turbine Shaft 
 
Torque (lb-in.) 
Overhang 
(in.-lb.) 
   Cont.  Static   
Low Rotor:  
  Tachometer 
C 0.489:1 7 50 --- 
      
High Rotor: 
Starter 
C 0.597:1 --- * 625 
Generator C  0.700:1 1500 6600** 2500 
Fluid Power Pump C  0.292:1 1000 4400 400 
 
Tachometer CC  0.343:1 7 50 --- 
 
  
C - Clockwise:  CC – Counterclockwise, facing engine pad 
*  - Maximum starter torque is 550 lb-ft.  The shear section will fracture at 850 - 0 + 100 lb. ft. 
** - Maximum torque when used as a starter is 4920 lb-in. 
 
NOTE 7.  Power setting, power checks, and control of engine output in all operations is to be based upon P&W engine charts 
referring to turbine discharge section gas pressures.  Pressure probes are included in the engine assembly for this 
reason. 
 
NOTE 8. These engines meet FAA requirements for adequate tu rbine disk integrity and rotor blade containment and do not 
require external armoring.  These engines have demonstrated satisfactory operation in icing conditions as defined in 
Civil Air Regulations (Amended August 25, 1955) 4b.1(b)7 and 8. 
 
NOTE 9. DELETED. 
 
NOTE 10. The maximum continuous st atic thrust at sea level at 29oF (JT8D-1, -1A, -1B, -7, -7A, -7B), 69oF (JT8D-5), 26oF (JT8D-
9, -9a), 21oF (JT8D-11) and 30oF (JT8D-15, -15A, -17, -17A, -17R, -17AR) temperature and below is 14,000 lbs. 
(JT8D-1, -1A, -1B, -7, -7A, -7B), 12,250 lbs. (JT8D-5), 14,500 lbs. (JT8D-9, -9A), 15,000 lbs. (JT8D-11), 15,500, lbs. 
(JT8D-15, -15A), 16,000 lbs. (JT8D-17, -17A), and 17,400 lbs.  (JT8D-17R, -17AR), respectively.  The engine 
installation and operating manual should be consulted for variation in thrust between standard and 29oF (JT8D-1, -1A, -
1B, -7, -7A, -7B), 26oF (JT8D-9, -9A), 21oF (JT8D-11), 30oF (JT8D-15, -15A), 39oF(JT8D-17, -17A), 19oF (JT8D-17R, 
-17AR). 
 
NOTE 11. Fuels approved for these engines are listed in FAA approved P&W Service Bulletin No. 2016 and its later revisions.  
Approved fuel additives and their allowable concentrations are also listed in P&W Service Bulletin No. 2016 and its 
later revisions. 
 
NOTE 12. The following oils are eligible for these engine: 
 
P&W Service Bulletin No. 238 lists approved brand oils.

TCDS E2EA           PAGE 9  
 
NOTE 13. The above models incorporate the following general characteristics: 
 
 JT8D Model  
 
Characteristics 
 
 JT8D-1 Basic model. 
 JT8D-1A Same as -1 except for increased tu rbine outlet gas temperature limits with the 
incorporation of improved engine parts. 
 JT8D-1B Same as -1A except for increased tu rbine outlet gas temperature limits with the 
incorporation of improved engine parts. 
 JT8D-5 Same as -1 except for minor diffe rences due to installation requirements, reduced 
ratings and increased disk life.  The D-5 engine may be operated at D-1 takeoff 
ratings and limitations for engine-out emergency use during takeoff and/or aborted 
landing procedures only. 
 JT8D-7 Same as -1 except 14,000 lb. takeoff static thrust at sea level flat rated to 84oF 
ambient temperature and other minor altitude thrust increases with the incorporation 
of improved engine parts. 
 JT8D-7A Same as -7 except for increased tu rbine outlet gas temperature limit with the 
incorporation of improved engine parts. 
 JT8D-7B Same as -7A except for increased tu rbine outlet gas temperature limits with the 
incorporation of improved engine parts. 
 JT8D-9 Same as -7 except 14,500 lb. takeoff static thrust at sea level flat rated to 84oF 
ambient temperature and other minor altitude thrust increases with the incorporation 
of improved engine parts. 
 JT8D-9A Same as -9 except for increased tu rbine outlet gas temperature limits with the 
incorporation of improved engine parts. 
 JT8D-11 Same as -9 except for 15,000 lb. takeo ff static thrust at sea level flat rated to 84oF 
ambient temperature with the incorporation of improved engine parts. 
 JT8D-15 Same as -11 except 15,500 lb. takeoff static thrust at sea level flat rated to 84oF 
ambient temperature and other minor altitude thrust increases with the incorporation 
of improved engine parts. 
 JT8D-15A Same as -15 except reduced fuel consumption by incorporation of improved engine 
parts. 
 JT8D-17 Same as -15 except 16,000 lb. takeoff static thrust at sea level flat rated to 84oF 
ambient temperature and other minor altitude thrust increases with the incorporation 
of improved engine parts. 
 JT8D-17A Same as -17 except reduced fuel consumption by incorporation of improved engine 
parts. 
 JT8D-17R Same as -17 except 16,400 lb. normal tak eoff static thrust at sea level flat rated to 
77oF ambient temperature, 17,400 lb. maximum takeoff static thrust at sea level flat 
rated to 77oF ambient temperature and a takeoff thrust reset mechanism incorporated 
in the fuel control along with improved engine parts. 
 JT8D-17AR 
 
Same as -17R except reduced fuel consumption by incorporation of improved engine 
parts. 
 
NOTE 14. Certain engine parts are life limited.  These limits are listed in the FAA-approved Pratt & Whitney JT8D 
Series Turbofan Engine Manual, Part No. 481672, Time Limit Section. 
 
NOTE 15. The following engines meet the February 1,  1974, smoke and emission requirements of SFAR-27: 
 
1.  All JT8D-11, -15, -15A, -17, -17A, -17R, and -17AR engines. 
2.  JT8D-1, -1A, -1B, -7, -7A, -7B, -9, and -9A engines modified in accordance with Pratt & Whitney 
Engineering Change 197707 or Service Bulletins 2417 or 2531. 
 
The following engines meeting the January 1, 1975, fuel venting emission requirements of SFAR-27: 
 
1.  All JT8D-15A, -17, -17A, -17R, and -17AR engines. 
2.  JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, and -15 engines modified in accordance with Pratt & 
Whitney Engineering Change 275159 or Service Bulletin 3757.

TCDS E2EA           PAGE 10  
 
NOTE 16. A takeoff thrust setting limited to the normal takeoff rating of 16,400 lb. static thrust at sea level, flat rated 
to 77oF ambient temperature has been established for normal takeoff operation. 
 
When the automatic reset mechanism in the fuel control is utilized, operation to the normal takeoff 
operating limits will prevent the engine from exceeding the maximum takeoff rating operating limits when 
the reset mechanism is actuated. 
 
The time limit at the normal takeoff rating is 5 minutes and shall include any time accumulated at the 
maximum takeoff rating. 
 
NOTE 17. DELETED. 
 
NOTE 18.  Turbine outlet gas temperature thermocouple box P/N 792863, cable assemblies P/N 792864 or P/N 
798380, and turbine discharge gas pressure averaging probe assemblies P/N 793272 or P/N 793274 
should be used for JT8D-15A, -17A, and -17AR engines and for JT8D-11 engines that have incorporated 
P&W Service Bulletin No. 5455. 
 
NOTE 19. The 5 minute takeoff time may be extended to 10 minutes for one engine inoperative or shutdown for 
engines which have incorporated all the features specified in P&W Service Bulletin Numbers 5514, 5643 
and Alert Service Bulletin Number 6196. 
 
----END----
```

## ADs (45, in force first)

- [AD 2011-03-01](https://openairdocs.org/ad/2011-03-01): Critical life- limited parts · Pratt & Whitney Division JT8D-11, JT8D-15, JT8D-15A and 9 more. Effective Mar 4, 2011
- [AD 2010-21-17](https://openairdocs.org/ad/2010-21-17): Fan blade · Pratt & Whitney Division JT8D-11, JT8D-15, JT8D-17 and 3 more. Effective Nov 12, 2010
- [AD 2009-24-01](https://openairdocs.org/ad/2009-24-01): Fan blade · Pratt & Whitney Division JT8D-11, JT8D-15, JT8D-17 and 5 more. Effective Jan 4, 2010
- [AD 2006-17-07 R1](https://openairdocs.org/ad/2006-17-07-R1): High pressure compressor (HPC) front hubs and HPC disk · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 18 more. Effective Nov 2, 2006
- [AD 2005-17-16](https://openairdocs.org/ad/2005-17-16): Critical life-limited rotating parts · Pratt & Whitney Division JT8D-209, JT8D-217, JT8D-217A and 17 more. Effective Sep 30, 2005
- [AD 2003-12-07](https://openairdocs.org/ad/2003-12-07): 12th Stage high pressure compressor · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 12 more. Effective Jul 18, 2003
- [AD 2003-05-07](https://openairdocs.org/ad/2003-05-07): Low pressure compressor (LPC) · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 12 more. Effective Apr 17, 2003
- [AD 2001-15-18](https://openairdocs.org/ad/2001-15-18): Stage Compressor Disks · Pratt & Whitney Division JT8D-11, JT8D-15, JT8D-15A and 6 more. Effective Sep 4, 2001
- [AD 2000-22-06](https://openairdocs.org/ad/2000-22-06): Main Fuel Pump · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 8 more. Effective Dec 4, 2000
- [AD 99-01-08](https://openairdocs.org/ad/99-01-08): Stage 7 through Stage 15 High-Pressure Compressor (HPC) Disks · Pratt & Whitney Division JT3D-1, JT3D-1-MC6, JT3D-1-MC7 and 30 more. Effective Jan 5, 1999
- [AD 98-21-24](https://openairdocs.org/ad/98-21-24): Compressor Disks · Pratt & Whitney Division JT8D-209, JT8D-217, JT8D-217A and 17 more. Effective Nov 16, 1998
- [AD 98-04-39](https://openairdocs.org/ad/98-04-39): Combustion Chamber Outer Case · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 12 more. Effective Feb 25, 1998
- [AD 97-19-12](https://openairdocs.org/ad/97-19-12): Hub Inspection · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 9 more. Effective Nov 18, 1997
- [AD 97-19-14](https://openairdocs.org/ad/97-19-14): Low Pressure Turbine (LPT) Blade Sets · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 9 more. Effective Oct 24, 1997
- [AD 96-23-14](https://openairdocs.org/ad/96-23-14): Combustion Chamber Outer Cases · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 12 more. Effective Jan 2, 1997
- [AD 95-26-03](https://openairdocs.org/ad/95-26-03): High Pressure Compressor Disks · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 12 more. Effective Jan 11, 1996
- [AD 86-09-02 R2](https://openairdocs.org/ad/86-09-02-R2): Combustion Chamber Liners · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 12 more. Effective Nov 17, 1995
- [AD 95-16-07](https://openairdocs.org/ad/95-16-07): High Pressure Compressor (HPC) Disks · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 11 more. Effective Sep 11, 1995
- [AD 95-10-10](https://openairdocs.org/ad/95-10-10): Compressor Fan Hub · Pratt & Whitney Division JT8D-11, JT8D-15, JT8D-15A and 6 more. Effective Jul 21, 1995
- [AD 94-25-07](https://openairdocs.org/ad/94-25-07): Combustion Chamber Outer Case · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 12 more. Effective Mar 30, 1995
- [AD 95-02-16](https://openairdocs.org/ad/95-02-16): Fuel Nozzle and Support Assembly · Pratt & Whitney Division JT8D-209, JT8D-217, JT8D-217A and 17 more. Effective Feb 21, 1995
- [AD 94-20-09](https://openairdocs.org/ad/94-20-09): Low Pressure Turbine Blade Sets · Pratt & Whitney Division JT8D-15A, JT8D-17A and JT8D-17AR. Effective Nov 14, 1994
- [AD 91-24-14](https://openairdocs.org/ad/91-24-14): Bearing Seal Spacer · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 18 more. Effective Jan 21, 1992
- [AD 89-25-11](https://openairdocs.org/ad/89-25-11): Fan Blade Retaining Plates · Pratt & Whitney Division JT8D-11, JT8D-15, JT8D-15A and 6 more. Effective Jan 15, 1990
- [AD 89-24-02](https://openairdocs.org/ad/89-24-02): Fan Disk · Pratt & Whitney Division JT8D-7, JT8D-7A and JT8D-7B. Effective Nov 13, 1989
- [AD 86-08-04 R1](https://openairdocs.org/ad/86-08-04-R1): HPC Removable Sleeve Spacers · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 12 more. Effective Nov 4, 1986
- [AD 86-02-52 R1](https://openairdocs.org/ad/86-02-52-R1): Combustion Chamber · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 12 more. Effective Apr 14, 1986
- [AD 85-19-51 R1](https://openairdocs.org/ad/85-19-51-R1): Second Stage Turbine Disk · Pratt & Whitney Division JT8D-15, JT8D-17 and JT8D-17R. Effective Dec 26, 1985
- [AD 78-17-02 R3](https://openairdocs.org/ad/78-17-02-R3): Compressor Front Hubs · Pratt & Whitney Division JT8D-11, JT8D-15, JT8D-15A and 6 more. Effective Mar 30, 1984
- [AD 80-15-51](https://openairdocs.org/ad/80-15-51): Engine Rear Compressor Front Hubs · Pratt & Whitney Division JT8D-209, JT8D-1, JT8D-11 and 11 more. Effective Aug 21, 1980
- [AD 78-23-12](https://openairdocs.org/ad/78-23-12): Third Stage Turbine Blade Rivet · Pratt & Whitney Division JT8D-1, JT8D-1A, JT8D-1B and 5 more. Effective Dec 20, 1978
- [AD 77-16-12](https://openairdocs.org/ad/77-16-12): Low Turbine Shaft · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 8 more. Effective Aug 31, 1977
- [AD 76-24-01](https://openairdocs.org/ad/76-24-01): Eighth Stage Compressor Disk · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-1A and 6 more. Effective Jun 22, 1977
- [AD 77-07-11](https://openairdocs.org/ad/77-07-11): Fourth Stage Turbine Stator And Rotor · Pratt & Whitney Division JT8D-9 and JT8D-9A. Effective Apr 15, 1977
- [AD 77-03-06](https://openairdocs.org/ad/77-03-06): Compressor Front Hubs · Pratt & Whitney Division JT8D-1, JT8D-1A, JT8D-1B and 3 more. Effective Feb 25, 1977
- [AD 75-05-06](https://openairdocs.org/ad/75-05-06): Fuel Manifold Leakage · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 18 more. Effective Feb 24, 1977
- [AD 76-20-02](https://openairdocs.org/ad/76-20-02): Second Stage Fan Blades · Pratt & Whitney Division JT8D-1, JT8D-1A, JT8D-1B and 3 more. Effective Oct 10, 1976
- [AD 75-01-01](https://openairdocs.org/ad/75-01-01): Low Turbine Shaft Spline · Pratt & Whitney Division JT8D-1, JT8D-1A, JT8D-7 and 1 more. Effective Sep 17, 1975
- [AD 71-25-07](https://openairdocs.org/ad/71-25-07): Fuel Nozzle Support Assemblies · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-1A and 3 more. Effective Dec 14, 1971
- [AD 71-07-01](https://openairdocs.org/ad/71-07-01): Front Compressor Front Hub · Pratt & Whitney Division JT8D-1, JT8D-1A, JT8D-7 and 1 more. Effective Sep 7, 1971
- [AD 70-26-05](https://openairdocs.org/ad/70-26-05): First Stage Compressor Rotor Blades · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 18 more. Effective Dec 29, 1970
- [AD 70-25-08](https://openairdocs.org/ad/70-25-08): Seventh Stage Compressor Rotor Disc · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 18 more. Effective Dec 15, 1970
- [AD 70-11-03](https://openairdocs.org/ad/70-11-03): Sixth Stage Compressor Discs · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 18 more. Effective Jun 12, 1970
- [AD 70-02-02](https://openairdocs.org/ad/70-02-02): Sixth Stage Compressor Rotor Disc · Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15 and 18 more. Effective Apr 15, 1970
- [AD 76-12-06](https://openairdocs.org/ad/76-12-06): Second Stage Fan Blades · Pratt & Whitney Division JT8D-11, JT8D-15, JT8D-17 and 1 more

## Registered aircraft by registry model (OpenAirDocs)

- [Pratt & Whitney JT8D-9 series](https://openairdocs.org/engine/pratt-whitney-jt8d-9-series): 9 aircraft (registry code 52048)
- [Pratt & Whitney JT8D-1](https://openairdocs.org/engine/pratt-whitney-jt8d-1): 8 aircraft (registry code 52044)
- [Pratt & Whitney JT8D-17 series](https://openairdocs.org/engine/pratt-whitney-jt8d-17-series): 7 aircraft (registry code 52049)
- [Pratt & Whitney JT8D-15](https://openairdocs.org/engine/pratt-whitney-jt8d-15): 6 aircraft (registry code 52051)
- [Pratt & Whitney JT8D-17](https://openairdocs.org/engine/pratt-whitney-jt8d-17): 6 aircraft (registry code 51732)
- [Pratt & Whitney JT8D-9A](https://openairdocs.org/engine/pratt-whitney-jt8d-9a): 5 aircraft (registry code 51729)
- [Pratt & Whitney JT8D-15A](https://openairdocs.org/engine/pratt-whitney-jt8d-15a): 1 aircraft (registry code 51731)
- [Pratt & Whitney JT8D-17A](https://openairdocs.org/engine/pratt-whitney-jt8d-17a): 1 aircraft (registry code 51733)
- [Pratt & Whitney JT8D-9](https://openairdocs.org/engine/pratt-whitney-jt8d-9): 1 aircraft (registry code 51728)
- [Pratt & Whitney JT8D-11](https://openairdocs.org/engine/pratt-whitney-jt8d-11): 0 aircraft (registry code 51730)
- [Pratt & Whitney JT8D-17AR](https://openairdocs.org/engine/pratt-whitney-jt8d-17ar): 0 aircraft (registry code 51735)
- [Pratt & Whitney JT8D-17R](https://openairdocs.org/engine/pratt-whitney-jt8d-17r): 0 aircraft (registry code 51734)
- [Pratt & Whitney JT8D-1A](https://openairdocs.org/engine/pratt-whitney-jt8d-1a): 0 aircraft (registry code 51723)
- [Pratt & Whitney JT8D-1B](https://openairdocs.org/engine/pratt-whitney-jt8d-1b): 0 aircraft (registry code 51726)
- [Pratt & Whitney JT8D-5](https://openairdocs.org/engine/pratt-whitney-jt8d-5): 0 aircraft (registry code 52046)
- [Pratt & Whitney JT8D-7](https://openairdocs.org/engine/pratt-whitney-jt8d-7): 0 aircraft (registry code 51724)
- [Pratt & Whitney JT8D-7A](https://openairdocs.org/engine/pratt-whitney-jt8d-7a): 0 aircraft (registry code 51725)
- [Pratt & Whitney JT8D-7B](https://openairdocs.org/engine/pratt-whitney-jt8d-7b): 0 aircraft (registry code 51727)

## STCs approved under this data sheet (26)

- [STC SE1622GL](https://openairdocs.org/stc/SE1622GL): Installation of Ametek 8TJ124GGR1 digital mass fuel flow transmitter.. ABX Air Incorporated
- [STC SE00429AT](https://openairdocs.org/stc/SE00429AT): Incorporate an alternate gear box stud installation.. Jet Avion Corporation
- [STC SE2117SO](https://openairdocs.org/stc/SE2117SO): Installation of an oil tank safety cap adapter which prevents loss of oil in the event of loss or damage to the oil filler cap.. Jet Avion Corporation
- [STC SE3318SO](https://openairdocs.org/stc/SE3318SO): Incorporate an alternate gear box cover seal utilizing an aluminum retainer and elastomeric seal.. Jet Avion Corporation
- [STC SE00024EN](https://openairdocs.org/stc/SE00024EN): Installation of oil tank filler neck check valve.. Helicopter Support Inc Services Div
- [STC SE2798CE](https://openairdocs.org/stc/SE2798CE): Installation of P/N T92871 first stage turbine vanes.. Kellstrom Defense Aerospace Inc.
- [STC SE01588AT](https://openairdocs.org/stc/SE01588AT): Installation of McClain International JT8D first stage turbine airseal as documented.. McClain International, Inc.
- [STC SE2930SO](https://openairdocs.org/stc/SE2930SO): Installation of an alternate gearbox cover seal utilizing an aluminum retainer .040-inch thick with a molded-in-place elastomeric seal contoured to fit the main housing/cover flange interface.. Parker O-Seal Division
- [STC SE497NE](https://openairdocs.org/stc/SE497NE): Installation of oil tank filler neck check valve assembly.. Aviation Components Support
- [STC SE3916NM](https://openairdocs.org/stc/SE3916NM): Installation of CADC bleed valve supports brackets, P/N B10002 or RB10003, as a replacement part for P&W P/N 578273.. Aeroparts Mfg & Repair
- [STC SE79WE](https://openairdocs.org/stc/SE79WE): Installation of CADC bleed valve support brackets, P/N B10001 or RB10006, as a replacement part for P&W P/N 493317 used on JT8D-1, -5, -7, -9, -9A, -15 and -17 engines.. Aeroparts Mfg & Repair
- [STC SE00049AT-D](https://openairdocs.org/stc/SE00049AT-D): Installation of Intermediate Compressor Case (JT8D SERIES). Aero Component Technologies
- [STC SE00048AT-D](https://openairdocs.org/stc/SE00048AT-D): Modification of compressor intermediate case diaphragm to permit acceptable of a 7th stage airseal ring.. Aero Component Technologies
- [STC SE2787CE](https://openairdocs.org/stc/SE2787CE): Installation of P/N T92871 first stage turbine vanes.. Trans World Airlines Inc
- [STC SE59GL](https://openairdocs.org/stc/SE59GL): Installation of O-ring face seal P/N-s 1-1337-700, -701, 1-1633-700, -701, 1-1738-700, -701; and/or 1-2233-700, 701.. Rexnord, Inc
- [STC SE86WE](https://openairdocs.org/stc/SE86WE): Replace the airoils on P&WA P/Ns 495051, 478351, 583751, 653851, 653951, 572451, 583351, 653751, 653151, 676951, 728951, 709951, 710751, 627751, 737271, 578551, 738271, 747171, 792871, 786471, 583751, 777971, 780591, 782571, 793181, 799771, 794481, 794491 , 798781, and 799191.. Chromizing Company
- [STC SE557NE](https://openairdocs.org/stc/SE557NE): Installation of oil tank shuttle valve.. Stockbridge William D
- [STC SE2666SO](https://openairdocs.org/stc/SE2666SO): Modification of the anti-ice mount bracket.. Cook Airtomic
- [STC SE593NE](https://openairdocs.org/stc/SE593NE): Installation of a Select Controls Inc. Engine Oil Shuttle Valve, P/N 2057-1-001. (See Eligibility List). Basken Valve Corporation
- [STC SE1930SO](https://openairdocs.org/stc/SE1930SO): Installation of power control shaft bushing.. Cook Airtomic Division
- [STC SE97WE](https://openairdocs.org/stc/SE97WE): Installation of Hughes Helicopters Heat Shield
Assembly. Hughes Helicopter
- [STC SE83WE](https://openairdocs.org/stc/SE83WE): Installation of heat shield assembly P/N 408-007 as a replacement part for P&W P/N499941 or 749609 used on JT8D-1, -5, -7, -9, -9A, -15 and -17 engines.. Hughes Helicopter
- [STC SE84WE](https://openairdocs.org/stc/SE84WE): Installation of heat shield assembly 408-008 as a replacement part for P&W No. 586918 used on JT8D-1, -5, -7, -9, -9A, -15 and -17 engines.. Hughes Helicopter
- [STC SE67WE](https://openairdocs.org/stc/SE67WE): Installation of fuel control rod end bearings.. Triumph Corporation
- [STC SA2627WE](https://openairdocs.org/stc/SA2627WE): Installation of fuel control rod end bearings.. Triumph Corporation
- [STC SE5058NM](https://openairdocs.org/stc/SE5058NM): Incorporation of feather seals into platforms of the first stage nozzle guide vanes, P&W P/N 653751, 737271, 738271, 747171, 792871, 786471, and 798771.. Chromizing Company

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