# TCDS E3NE: Pratt & Whitney

- Type: Type certificate data sheet
- Status: Current
- Holder: Pratt & Whitney
- Revision: 16
- Revised: July 15, 2019
- Product: Engine
- Certification basis: Part 33
- Registered aircraft: 6, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/a6/be/a6be6b7fa9ba7b0c155e8d28d6e2760e0dfe7c1bcb26d4c5109e50ad1263e87c
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4A0A9ABD64FCCE4F862586B800638847.0001
- Page: https://openairdocs.org/tcds/E3NE

## Models (11)

As the data sheet lists them.

- JT9D-7Q
- JT9D-7Q3
- JT9D-7R4E4
- JT9D-7R4E
- JT9D-70A
- JT9D-7R4H1
- JT9D-7R4D1
- JT9D-7R4D
- JT9D-7R4E1
- JT9D-7R4G2
- JT9D-59A

## 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. 16 14 11 11 16 16 11 11 16 16 
 
LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
               "---" NOT APPLICABLE 
NOTE:  ALL PAGES ARE REFORMATTED.  SIGNIFICANT CHANGES IF ANY, 
            ARE BLACK-LINED IN THE LEFT MARGIN. 
 
 
 
U.S. DEPARTMENT OF TRANSPORTATION 
 
FEDERAL AVIATION ADMINISTRATION 
 
TYPE CERTIFICATE SHEET E3NE  
 
 
TCDS NUMBER E3NE  
 
REVISION:  16 
DATE:  July 25, 2019  
 
PRATT & WHITNEY 
 
MODELS:        
 
JT9D-59A JT9D-70A JT9D-7Q 
JT9D-7Q3 JT9D-7R4D JT9D-7R4D1 
JT9D-7R4E JT9D-7R4E1 JT9D-7R4G2 
JT9D-7R4H1 JT9D-7R4E4 
 
Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E3NE) 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  JT9D-59A JT9D-70A JT9D-7Q  
TYPE Turbofan, dual axial 16 stage compressor, annular combustion 
chamber, and 6 stage turbine. 
RATINGS  (See NOTE 5) 
 
   Maximum continuous at sea level,  
    static thrust, lb. 
   Takeoff static thrust at sea level, lb. 
   Dry (5 min.) (See NOTE 13) 
 
 
44,770 
 
51,720 
 
 
44,290 
 
51,140 
 
 
44,920 
 
51,900 
 
COMPONENTS 
  Fuel Control 
 
  Fuel Pump   
  High Compressor Stator Vane 
Control/ 
   3.0 Bleed Control 
 
                   or 
  Engine Vane and Modulating Bleed  
   Control 
  Start Bleed Control (3.5 bleed control) 
 
  Electronic Engine Control 
 
Ham. Std. 
JFC68-6 
TRW 385200 
Ham. Std./ 
EVC 3-5/ 
674977 
or 
Ham. Std. 
GTA9-1 
PWA P/N 
773456 
--- 
 
 
- - 
 
- - 
- - 
 
 
 
- - 
 
- - 
 
--- 
 
- - 
 
TRW 386900 
- - 
 
 
 
- - 
 
- - 
 
--- 
 
FUEL See NOTE 10 - - - -  
OIL See NOTE 11 - - - -

TCDS E3NE             PAGE 2 
 
I. MODELS  (CONT.) JT9D-59A JT9D-70A JT9D-7Q   
PRINCIPAL DIMENSIONS 
 
 Maximum length, in. (including  
   spinner) 
 Width, in. 
 Weight (dry), lb. ( includes basic  
   engine with all essential accessories;  
   with fuel heater, oil tank, fuel oil  
   cooler, and CSD fuel oil cooler; but  
   excluding starter, exhaust nozzle and  
   power source for the ignition systems) 
 Center of gravity, in. 
   Forward of engine reference plane 
   Below engine center line 
 IGNITION 
   Exciters 
 
 
154.256 
 
97.030 
9,140 
 
 
 
 
 
 
5.2+1.0 
3.3+0.5 
 
Unison 
5005907-01 
(two) 
 
 
- - 
 
- - 
9,155 
 
 
 
 
 
 
- - 
- - 
 
- - 
 
 
- - 
 
- - 
9,295 
 
 
 
 
 
 
2.5+1.0 
1.4+0.5 
 
- - 
 
Igniters (two each) Champion 
709520 
- - - -  
 
II. MODELS  JT9D-7Q3 JT9D-7R4D JT9D-7R4D1 JT9D-7R4E 
TYPE Turbofan, dual axial 16 stage compressor, annular combustion chamber, 
and 6 stage turbine. 
RATINGS  (See NOTE 5) 
 
   Maximum continuous at sea level,  
    static thrust, lb. 
   Takeoff static thrust at sea level, lb. 
   Dry (5 min.) (See NOTE 13) 
 
 
44,920 
 
51,900 
 
 
45,800 
 
48,000 
 
 
45,800 
 
48,000 
 
 
47,500 
 
50,000 
COMPONENTS 
  Fuel Control 
 
  Fuel Pump  
  
  High Compressor Stator Vane Control/  
   3.0 Bleed Control 
 
                   or 
  Engine Vane and Modulating Bleed  
   Control 
  Start Bleed Control (3.5 bleed control) 
 
  Electronic Engine Control 
   (See NOTE 19) 
 
Ham. Std. 
JFC68-6 
TRW 386900 
 
Ham. Std./ 
EVC 3-5/ 
674977 
or 
Ham. Std. 
GTA9-1 
PWA P/N 
773456 
--- 
 
 
Ham. Std. 
JFC68-7 
TRW 706800 
 
- - 
 
or 
GTA9-3 
 
793396 
 
Ham. Std. 
780170-6 
780170-5 
780170-2 
780170-8 
 
Ham. Std. 
JFC68-10 
- - 
 
- - 
 
 
- - 
 
- - 
 
Ham. Std. 
769370-3 
 
Ham. Std. 
JFC68-7 
- - 
 
- - 
 
 
- - 
 
 
769486 
Ham. Std. 
780170-6 
780170-8 
FUEL NOZZLES --- --- --- --- 
EEC PROGRAMMING PLUG 
  (PWA P/N) 
 
--- 
 
795034 
 
795354 
 
795035 
FUEL See NOTE 10 - - - - - - 
OIL See NOTE 11 - - - - - -

TCDS E3NE             PAGE 3 
 
II. MODELS (CONT.) JT9D-7Q3 JT9D-7R4D JT9D-7R4D1 JT9D-7R4E 
PRINCIPAL DIMENSIONS 
 
 Maximum length in. (including 
   spinner) 
 Width, in. 
 Weight (dry), lb. (includes basic  
   engine with all essential accessories;  
   with fuel heater, oil tank, fuel oil  
   cooler, and CSD fuel oil cooler; but  
   excluding starter, exhaust nozzle and  
   power source for the ignition systems) 
 Center of gravity, in. 
   Forward of engine reference plane 
   Below engine center line 
 IGNITION 
   Exciters 
 
 
154.256 
 
97.03 
9,295 
 
 
 
 
 
 
2.5+1.0 
1.4+0.5 
 
Simmonds 
Precision 
P/N 43925 
 
 
- - 
 
96.00 
8,935 
 
 
 
 
 
 
3.3+1.0 
- - 
 
Simmonds  
Precision 
RH P/N 43925 
LH P/N 44933 
 
 
- - 
 
- - 
8,915 
 
 
 
 
 
 
- - 
- - 
 
- - 
 
 
- - 
 
- - 
- - 
 
 
 
 
 
 
- - 
- - 
 
- - 
Igniters (two each) Champion 
AA134S-1 or 
AC S611809 
- - - - - - 
 
III. MODELS  JT9D-7R4E1 JT9D-7R4G2 JT9D-7R4H1 JT9D-7R4E4 
TYPE Turbofan, dual axial 16 stage compressor, annular combustion chamber, 
and 6 stage turbine. 
RATINGS  (See NOTE 5) 
 
   Maximum continuous at sea level,  
   static thrust, lb. 
   Takeoff static thrust at sea level, lb. 
   Dry (5 min.) (See NOTE 13) 
 
 
47,500 
 
 
50,000 
 
 
50,200 
 
 
54,750 
 
 
50,000 
 
 
56,000 
 
 
47,500 
 
 
50,000 
COMPONENTS 
 
  Fuel Control 
 
  Fuel Pump  
  
  High Compressor Stator Vane Control/  
   3.0 Bleed Control 
 
                   or 
  Engine Vane and Modulating Bleed  
   Control 
  Start Bleed Control (3.5 bleed control) 
 
  Electronic Engine Control 
   
 
 
Ham. Std. 
JFC68-10 
TRW 706800 
 
Ham. Std. 
/EVC 3-5/ 
674977 
or 
GTA9-3 
 
793396 
 
(See NOTE 20) 
 
 
- - 
JFC68-8 
- -   
 
- - 
 
 
 
- - 
 
769486 
 
--- 
 
 
- - 
JFC68-10 
- - 
 
- - 
 
 
 
- - 
 
793396 
Ham. Std. 
787240-1 
 
 
 
 
- - 
JFC68-7 
- - 
 
- - 
 
 
 
- - 
 
769486 
Ham. Std. 
780170-8 
FUEL NOZZLES --- --- --- (See NOTE 18) 
EEC PROGRAMMING PLUG 
  (PWA P/N) 
 
795035 
 
--- 
 
795036 
 
798873 
FUEL See NOTE 10 - - - - - - 
OIL See NOTE 11 - - - - - -

TCDS E3NE             PAGE 4 
 
III MODELS  (CONT.) JT9D-7R4E1 JT9D-7R4G2 JT9D-7R4H1 JT9D-7R4E4 
PRINCIPAL DIMENSIONS 
 
 Maximum length in. (including 
   spinner) 
 Width, in. 
 Weight (dry), lb. (includes basic 
   engine with all essential accessories;  
   with fuel heater, oil tank, fuel oil  
   cooler, and CSD fuel oil cooler; but  
   excluding starter, exhaust nozzle and  
   power source for the ignition systems) 
 Center of gravity, in. 
   Forward of engine reference plane 
   Below engine center line 
 IGNITION 
   Exciters 
 
 
154.295 
 
96.00 
8,935 
 
 
 
 
 
 
3.3+1.0 
1.4+0.5 
 
Simmonds 
Precision 
RH P/N 43925 
LH P/N 44933 
 
 
- - 
 
- - 
9,170 
 
 
 
 
 
 
- - 
- - 
 
- - 
 
 
- - 
 
- - 
8,915 
 
 
 
 
 
 
- - 
- - 
 
- - 
 
 
 
 
- - 
 
- - 
8,935 
 
 
 
 
 
 
- - 
- - 
 
- - 
Igniters (two each) Champion 
AA134S-1 or 
AC S611809 
- - - - - - 
 
CERTIFICATION BASIS FAR 33 effective February 1, 1965, as amended by 33-1, 33-2, 33-3, and 33-4, and 
Special Condition No. 33-8-EA-3. 
Type Certificate No. E3NE, issued December 12, 1974 (JT9D-59A, 70, 70A); and 
subsequent revisions issued March 19, 1976 (JT9D-59B, 70B); issued October 31, 
1978 (JT9D-7Q, 7Q1); issued October 22, 1979 (JT9D-7Q3); issued June 4, 1980 
(JT9D-59D, 70D, 7Q2); issued November 25, 1980 (JT9D-7R4A, 7R4D); issued 
April 1, 1981 (JT9D-7R4D1, 7R4E1); issued July 23, 1982 (JT9D-7R4G2, 7R4H1, 
7R4H2); issued March 29, 1985 (JT9D-7R4E4). 
Dates of Application for Type Certificate:  May 2, 1973 (JT9D-70); September 4, 
1974 (JT9D-59A); October 17, 1974 (JT9D-70A); February 20, 1976 (JT9D-59B, 
70B); October 28, 1977 (JT9D-7Q); June 15, 1978 (JT9D-7Q1); July 6, 1978 
(JT9D-59D, 70D); August 14, 1978 (JT9D-7Q2); October 10, 1979 (JT9D-7Q3); 
February 14, 1979 (JT9D-7R4A, 7R4D); December 22, 1980 (JT9D-7R4D1); 
February 10, 1981 (JT9D-7R4E1); February 14, 1979 (JT9D-7R4G2, 7R4H1, 
7R4H2); and October 11, 1984 (JT9D-7R4E4). 
 
PRODUCTION BASIS Production Certificate Number 2

TCDS E3NE             PAGE 5 
         
NOTES 
 
NOTE 1. Maximum permissible engine operating speeds for the engine rotors are as follows: 
                  
      JT9D- JT9D-  JT9D- JT9D- JT9D- 
    JT9D-59A/70A 7Q 7Q3  7R4D+ 7R4D1 7R4E1 
     Low pressure rotor (N1), rpm 3780  3888 3960  3770 3810 3810 
     High pressure rotor (N2), rpm 8011  8000 8000  8000 8000 8000 
             
    JT9D-  JT9D- JT9D-  JT9D- 
    7R4E+  7R4G2 7R4H1  7R4E4 
     Low pressure rotor (N1), rpm 3770  3825 3810  3810 
     High pressure rotor (N2), rpm 8000  8080 8080  8080 
 
     For inadvertent exceedances of certified overspeed limits, see Chapter 72-00-00 of the appropriate maintenance manual. 
 
+Engines converted from JT9D-7R4E4 per Service Bulletin JT9D-7R4-72-331 or Special Instruction 34F-87 (EC86EA123) and 
operated to either JT9D-7R4D or JT9D-7R4E ratings will have the engine model identifier of “(DM)” or “(EM)” after the 
engine model name and will have maximum permissible rotor speeds as follows: 
 
 Low Pressure Rotor (N1), rpm 3810 
 High Pressure Rotor (N2), rpm 8080 
 
NOTE 2.   Maximum permissible temperatures are as follows: 
 
Turbine gas temperature (Tt7) total temperature immediately downstream from the low pressure turbine discharge. 
 
   JT9D-59A/7Q3   JT9D-70A/7Q  
 
Takeoff (5 minutes)  (685˚C) 1265˚F   (685˚C) 1265˚F    
Maximum continuous (650˚C) 1202˚F   (650˚C) 1202˚F    
Maximum accleration (685˚C) 1265˚F   (685˚C) 1265˚F    
Ground Starting  (505˚C)  941˚F               - -    
Inflight Starting++  (505˚C)  941˚F    - - 
 
Oil Inlet   (135˚C) 275˚F (continuous operation)  - - 
   (163˚C) 325˚F (transient operation  - - 
               limited to 20 minutes) 
 
         JT9D-  JT9D-   JT9D- 
   JT9D-7R4D+     7R4D1  7R4E1   7R4E+ 
 
Takeoff (5 minutes)  (625˚C) 1157˚F     (625˚C) 1157˚F (635˚C) 1175˚F  - - 
Maximum continuous (600˚C) 1112˚F     (600˚C) 1112˚F (610˚C) 1130˚F  - - 
Maximum accleration (625˚C) 1157˚F     (625˚C) 1157˚F (635˚C) 1175˚F  - - 
Ground Starting  (535˚C) 995˚F     (535˚C)  995˚F - - - -  - - 
Inflight Starting++  (625˚C) 1157˚F     (625˚C) 1157˚F (635˚C) 1175˚F  - - 
 
Oil Inlet   Maximum oil inlet temperature is not to exceed 275˚F (135˚C). - - 
   During idle descent, a 325˚F (163˚C) limit is permissible for up to 20 minutes. 
 
++ If during an inflight start, the normal ground starting EGT is exceeded, maximum EGT and duration must be recorded for 
maintenance action.

TCDS E3NE             PAGE 6 
 
NOTE 2. 
(Continued)   
Maximum permissible temperatures are as follows: 
 
   JT9D-   JT9D-    JT9D- 
   7R4G2   7R4H1    7R4E4 
 
Takeoff (5 minutes)  (685˚C) 1265˚F  (680˚C) 1256˚F   - - 
Maximum continuous (620˚C) 1148˚F  (635˚C) 1175˚F   - - 
Maximum accleration (660˚C) 1220˚F  (675˚C) 1247˚F   - - 
Ground Starting  (535˚C) 995˚F  - - - -   - - 
Inflight Starting++  (535˚C) 995˚F  (680˚C) 1256˚F   - - 
 
Oil Inlet   Maximum oil inlet temperature is not to exceed 275˚F (135˚C). - - 
   During idle descent, a 325˚F (163˚C) limit is permissible for up to 20 minutes. 
 
For inadvertent exceedances fo certified temperature limits see Chapter 72-00-00 of the appropriate maintenance manual.  
External engine limiting temperatures for specific components are specified in the engine installation and operation manual. 
 
+Engines converted from -7R4E4 per Service Bulletin JT9D-7R4-72-331 or Special Instruction 34F-87 (EC86EA123) and 
operated to either -7R4D or -7R4E ratings will have the engine model identifier of “(DM)” or “(EM)” after the engine model 
name and will have an EGT limit as follows: 
 
   o  Takeoff (680˚C)  1256˚F 
   o  Max Cont. (635˚C)  1175˚F 
   o  Max Accel (675˚C)  1247˚F 
 
++If during an inflight start, the normal ground starting EGT is exceeded, maximum EGT and duration must be recorded for 
maintenance action. 
  
NOTE 3. 
 
   
Fuel and oil pressures are as follows: 
 
Fuel pressure: At inlet to engine system pump, not less than 5 psi above the true vapor pressure of the  
  fuel and not greater than 70 psig with a vapor/liquid ratio of zero. 
 
Oil pressure: Minimum 35 psig (normal range 40-60 psig) 
  NOTE: During cold weather starting, oil pressure in excess of 60 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 
   60 psig during cold weather starts. 
 
NOTE 4. Maximum permissible air bleed extraction is as follows: 
 
    JT9D-59A/7Q  JT9D-7R4D/7R4D1/7R4E1 
        70A/7Q3  7R4E/7R4G2/7R4H1/7R4E4 
   Percent of Primary Engine Airflow Percent of Primary Engine Airflow 
   Normal Bleed Maximum Bleed Normal Bleed Maximum Bleed 
High compressor bleed 
 
a.  Idle to 40% max cont.       10%                 13%                  9%           9% 
b.  40% max cont. to takeoff*           5%                6.5%                          5%                           5% 
 
*5% is the maximum allowable from the 8th stage in this thrust range.  The 6.5% listed is allowable from 
the15th stage alone or from a combination of 8th and 15th stage bleeds.

TCDS E3NE             PAGE 7 
 
NOTE 5. Ratings, with the exception of the -7R4 models, are based on static test stand operation under the following 
conditions: 
 
Compressor inlet air at 59ºF and 29.92 in. Hg. 
Engine air inlet, jet nozzle exhaust pipe, and fan exit nozzle per P&W Drawing P/N 758201(-59A); 760701 (-70A); 
808801 (7Q and 7Q3). 
No aircraft accessory loads or air extraction. 
No anti-icing airflow. 
Turbine gas temperature limits and engine rotor speed limits not exceeded. 
Rating for -7R4 models are based on ideal nozzles. 
 
NOTE 6.  The following accessory drive provisions are incorporated: 
 
     JT9D-7Q/7Q3/59A/70A 
  ________________________________________________________________________ 
  Rotation (facing pad)  Speed Ratio 
  (C - Clockwise, CC -        to  Torque (in-lb)     Overhang 
Drive  Counter Clockwise)  Turbine Shaft Continuous Static     (in-lb) 
 
Starter  CC   1.091:1  (a) (a)        500 
Generator -   -  - -      1,575 
Constant Speed  CC   1.091:1  (b) 15,960     1,575 
    Drive 
Tachometer C     .538:1  7   50         - 
Fluid Power CC     .500:1  1,890 9,450        400 
Pumps (2)  CC     .499:1  1,890 9,450        400 
 
(a) 750 ft-lb engine starter drive shear section is designed to fail at a static torque of 1,400 - 1,610  ft-lb 
(b) Maximum allowable continuous torque values are equivalent to 210 horsepower at any engine speed at or  
 above sea level ground idle. 
(c) "-" indicates "does not apply" 
  
 
  
   JT9D-7R4D/7R4D1/7R4E1/7R4E/7R4G2/7R4H1/7R4E4 
  _______________________________________________________________________ 
  Rotation (facing pad)  Speed Ratio 
  (C - Clockwise, CC -        to  Torque (in-lb)     Overhang 
Drive  Counter Clockwise)  Turbine Shaft Continuous Static     (in-lb) 
 
Starter  CC   1.091:1  (a) (a)        500 
Generator -   -  - -      1,575 
Constant Speed  CC   1.091:1  (b) 15,960     1,575 
   Drive 
Tachometer C     .538:1  7   50         - 
Fluid Power CC     .500:1  1,890 9,450        400 
Pumps (2)  CC     .499:1  1,300 6,500        400 
IDGS  CC   1.121:1   12,620     2,000 
 
(a) 910 ft-lb engine starter drive shear section is designed to fail at a static torque of 1,400 - 1,610 ft-lb 
(b) Maximum allowable continuous torque values are equivalent to 210 horsepower at any engine speed at or  
 above sea level ground idle. 
(c) "-" indicates "does not apply"

TCDS E3NE             PAGE 8 
 
NOTE 7.  Power setting, power checks, and control of engine output in all operations are to be used based upon P&W engine 
charts referring to turbine discharge section gas pressure.  Pressure probes are included in the engine assembly for 
this purpose. 
 
NOTE 8. For inflight operation during icing conditions, the minimum N1 rpm is 20% for JT9D-7R4 series engines.  For JT9D-
59 series, 70 series, and 7Q series engines, maintain at least 50% N1 rpm above 10,000 feet and at least 45% N1 
rpm below 10,000 feet. 
 
NOTE 9. This model engine meets Item 1 in Special Condition No. 33-8EA-3 in the uncowled configuration. 
 
NOTE 10. Fuels meeting the requirements of the latest applicable issue of Turbojet Engine Service Bulletin No. 2016, which 
includes other fuel information requirements of PW Specification No. 522, are acceptable for these engines.  
Approved fuel additives and allowable concentrations are also included in Service Bulletin No. 2016. 
 
NOTE 11. The following oils are eligible for these engines: 
 
Synthetic type conforming to P&W Specification No. 521C, or later revision.  Approved brand oils listed in P&W 
Turbojet Engine Service Bulletin No. 238. 
 
NOTE 12. Certain engine parts are life limited.  These limits are listed in the "FAA approved" time limits section of the P&W 
Engine Manuals P/N 754459 for the JT9D-59/70 series; P/N 777210 for the -7Q series; P/N 785058 for the -7R4D1, 
-7R4E1 and -7R4H1; P/N 785059 for the -7R4D, -7R4E and -7R4E4; P/N 789328 for the -7R4G2.

TCDS E3NE             PAGE 9 
NOTE 13. JT9D Model Characteristics 
 
-59A  Takeoff rating of 51,720 lb at and below 86ºF ambient temperature, sea level static. 
 
-70A  Takeoff rating of 51,140 lb at and below 86ºF ambient temperature, sea level static. 
 
-7Q  Internally the same as JT9D-50/-70 series engines, but externally configured to fit in Boeing 
  747-200 nacelle.  Takeoff rating of 51,900 lb at and below 86ºF ambient temperature, sea level  
  static. 
 
-7Q3  Basically the same as JT7D-7Q except for revised fan case for the increased maximum low 
rotor  
  speed. 
 
-7R4D  Bascially the same as JT9D-7 (see TCDS E20EA) except incorporates an improved fan, higher 
  efficiency 4 stage LPC, single crystal first stage turbine blades, improved use of turbine cooling 
  air and a supervisory Electronic Engine Control.  Takeoff rating of 48,000 lb at and below 
  92ºF ambient temperature, sea level static. 
 
-7R4D1  Same as -7R4D except for external arrangement required for installation. 
 
-7R4E1  Same as -7R4D1 except takeoff rating of 50,000 lb at and below 92ºF ambient temperature, sea 
  level static. 
 
-7R4E  Same as -7R4D except takeoff rating of 50,000 lb at and below 92ºF ambient temperature, sea 
  level static. 
 
-7R4G2  Same as -7R4D except incorporates an improved durability hot section including wide chord 
  vanes.  Takeoff rating 54,750 lb at and below 86ºF ambient temperature, sea level static. 
 
-7R4H1  Same as -7R4G2 except for external arrangement required for installation and also incorporates 
  single crystal first and second stage turbine blades and single crystal second turbine vanes.   
  Takeoff rating 56,000 lb at and below 86ºF ambient temperture, sea level static. 
 
-7R4E4  Same as -7R4E except incorporates burner and high turbine configuration of the -7R4H1. 
  Takeoff rating of 50,000 lb at and below 114ºF ambient temperature, sea level static.  
The -7R4E4 if derated to the (EM) in accordance wuth P&W Special Instrcution 34F-87 will 
have takeoff rating of 50,000 lb. at and below 92ºF ambient temperature, sea level static; and 
have the engine model identifier of -7R4E4(EM) on the engine dataplate.  
The –7R4E4 if derated to the (DM) in accordance with P&W Special Instrcution 34F-87 will 
have takeoff rating of 48,000 lb. at and below  92ºF ambient temperature, sea level static; and 
have the engine model identifier of -7R4E4(DM) on the engine dataplate.

TCDS E3NE             PAGE 10 
 
NOTE 14. All JT9D-7R4 series engines meet the Smoke and Gaseous Emission requirements of 40 CFR Part 87, dated 
December 30, 1982. 
 
NOTE 15. All JT9D-7R4 series engines meet the January 1, 1975, fuel venting emission requirements of  SFAR-27. 
 
NOTE 16. For JT9D-7R4D engines, EEC software versions -007 or -010, there exists, within the EEC, logic which will result in 
the Maximum Continuous thrust rating being limited during enroute climb.  This condition will occur only when 
setting Maximum Continuous thrust directly from takeoff thrust with the EEC on, the thrust level positioned full 
forward, and following a climb of more than 3,000 feet above the runway.  The difference between the limit and the 
Maximum Continuous thrust when taking off from a sea level airport is as follows: 
 
 For engines incorporating the 154CF3 P2T2 probe (P/N 786464) and resistor harness (P/N 795644) the  
 Difference varies from 0 at 3,000 feet to a maximum of 0.15 EPR at 14,000 feet. 
 
 For engine incorporating the 154CF7 P2T2 (P/N 798133) the difference varies from 0 at 3,000 feet to a 
 Maximum of 0.06 EPR at 14,000 feet. 
 
 Thrust will not be limited if taking off from an airport of 4,300 feet or higher. 
 
For either engine configuration, Maximum Continuous thrust will not be limited when either an altitude of 14,000 
feet or a Mn of .47 has been attained or if maximum climb thrust has been set.  Maximum Continuous thrust is not 
limited with the EEC turned off. 
 
NOTE 17. Electronic Engine Control JT9D-7R4E1 (AI500) JT9D-7R4E1 (AI600) 
   Ham. Std.   Ham. Std. 
   769370-3   787240-1 
 
NOTE 18. For JT9D-7R4E4 engines fitted with P&W P/N 792842 and 794731 fuel nozzles, the nozzles must be replaced with 
new or shop cleaned nozzles, or on-wing cleaned per the approved maintenance manual procedures at intervals not to 
exceed 700 flight cycles. 
 
NOTE 19. The following JT9D engine models and their associated data have been removed from this Type Certificate Data 
Sheet as of revision 11, since they are not currently installed on certificated aircraft: 
 
 JT9D-70  JT9D-59D 
 JT9D-70D JT9D-70B 
 JT9D-7Q1 JT9D-7R4A 
 JT9D-7Q2 JT9D-7R4H2 
 JT9D-59B 
NOTE 20. Use of takeoff thrust for more than five minutes (not to exceed ten minutes) is approved for use only in the event of an 
inoperative engine due to shutdown or failure. 
----END----
```

## ADs (46, in force first)

- [AD 2021-09-10](https://openairdocs.org/ad/2021-09-10): Turbine Engine Compressor Section · Pratt & Whitney JT9D-20, JT9D-20J, JT9D-3A and 17 more. Effective May 27, 2021
- [AD 2012-06-14](https://openairdocs.org/ad/2012-06-14): HPT 1st stage air seals · Pratt & Whitney Division JT9D-7R4G2 and JT9D-7R4H1. Effective Apr 27, 2012
- [AD 2011-25-10](https://openairdocs.org/ad/2011-25-10): High-pressure compressor (HPC) shafts · Pratt & Whitney Division JT9D-7R4H1. Effective Jan 17, 2012
- [AD 2009-10-01](https://openairdocs.org/ad/2009-10-01): High-pressure turbine (HPT) vane assemblies · Pratt & Whitney Division JT9D-7R4E1, JT9D-7R4E4, JT9D-7R4G2 and 1 more. Effective May 18, 2009
- [AD 2007-18-06](https://openairdocs.org/ad/2007-18-06): Inspection of the blade root thickness · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Oct 5, 2007
- [AD 2005-05-13](https://openairdocs.org/ad/2005-05-13): High pressure turbine (HPT) second stage airseals · Pratt & Whitney Division JT9D-59A, JT9D-70A, JT9D-7Q and 1 more. Effective Apr 14, 2005
- [AD 2004-01-08](https://openairdocs.org/ad/2004-01-08): One-piece fan case shield · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Feb 10, 2004
- [AD 2002-07-04](https://openairdocs.org/ad/2002-07-04): Low Pressure Turbine (LPT) 5th Stage Disks · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective May 14, 2002
- [AD 2001-17-30](https://openairdocs.org/ad/2001-17-30): High Pressure Turbine 1st Stage Disk Aft Lugs · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Oct 4, 2001
- [AD 2001-04-11](https://openairdocs.org/ad/2001-04-11): High Pressure Turbine (HPT) Disks · Pratt & Whitney Division JT9D-20, JT9D-7, JT9D-7A and 7 more. Effective May 7, 2001
- [AD 2000-23-14](https://openairdocs.org/ad/2000-23-14): No. 4 Bearing Area · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 11 more. Effective Jan 19, 2001
- [AD 98-21-22 R1](https://openairdocs.org/ad/98-21-22-R1): High Pressure Compressor Disks · Pratt & Whitney Division JT9D-59A, JT9D-70A, JT9D-7Q and 8 more. Effective Jan 18, 2000
- [AD 99-20-04](https://openairdocs.org/ad/99-20-04): High Pressure Turbine Disks · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Oct 29, 1999
- [AD 99-14-08](https://openairdocs.org/ad/99-14-08): Pratt & Whitney Division JT9D-59A, JT9D-70A, JT9D-7Q and 1 more. Effective Sep 13, 1999
- [AD 99-11-09](https://openairdocs.org/ad/99-11-09): Diffuser Case Rear Rail · Pratt & Whitney Division JT9D-59A, JT9D-70A, JT9D-7Q and 1 more. Effective Jul 26, 1999
- [AD 99-04-05](https://openairdocs.org/ad/99-04-05): Rear Skirt Ddiffuser Case Inspection · Pratt & Whitney Division JT9D-59A, JT9D-70A, JT9D-7Q and 1 more. Effective Apr 12, 1999
- [AD 97-25-10 R1](https://openairdocs.org/ad/97-25-10-R1): (HPT) Disks · Pratt & Whitney Division JT9D-59A, JT9D-70A, JT9D-7Q and 5 more. Effective Jul 29, 1998
- [AD 96-25-10](https://openairdocs.org/ad/96-25-10): Design Turbine Exhaust Case · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 17 more. Effective Feb 18, 1997
- [AD 96-17-11](https://openairdocs.org/ad/96-17-11): Low pressure turbine (LPT) vane · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Nov 18, 1996
- [AD 94-15-16](https://openairdocs.org/ad/94-15-16): Engine Control System Accessories · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 9 more. Effective Oct 14, 1994
- [AD 94-08-06](https://openairdocs.org/ad/94-08-06): Fan Blade · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Jul 5, 1994
- [AD 93-15-04](https://openairdocs.org/ad/93-15-04): Fuel Nozzle And Support Assembly · Pratt & Whitney Division JT9D-59A, JT9D-70A, JT9D-7Q and 1 more. Effective Nov 19, 1993
- [AD 93-14-20](https://openairdocs.org/ad/93-14-20): Vane Cluster Assembly · Pratt & Whitney Division JT9D-59A, JT9D-70A, JT9D-7Q and 1 more. Effective Aug 27, 1993
- [AD 91-03-03](https://openairdocs.org/ad/91-03-03): High Pressure Compressor Turbine Driveshaft · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Feb 22, 1991
- [AD 90-23-19](https://openairdocs.org/ad/90-23-19): Air Seal · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 13 more. Effective Nov 23, 1990
- [AD 90-15-11](https://openairdocs.org/ad/90-15-11): Fuel Control Unit · Pratt & Whitney Division JT9D-7R4D1, JT9D-7R4E1 and JT9D-7R4H1. Effective Jul 16, 1990
- [AD 90-14-08](https://openairdocs.org/ad/90-14-08): High Pressure Compressor · Pratt & Whitney Division JT9D-7R4D and JT9D-7R4E. Effective Jul 2, 1990
- [AD 87-23-05 R1](https://openairdocs.org/ad/87-23-05-R1): Fan Case Assembly · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Mar 23, 1990
- [AD 86-09-01 R1](https://openairdocs.org/ad/86-09-01-R1): Turbine Vane Antirotation Pin Failure · Pratt & Whitney Division JT9D-20, JT9D-3A, JT9D-59A and 9 more. Effective Jul 6, 1988
- [AD 86-25-51](https://openairdocs.org/ad/86-25-51): Low Altitude Surges · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 3 more. Effective Mar 20, 1987
- [AD 86-23-03](https://openairdocs.org/ad/86-23-03): Second Stage High Pressure Turbine Rotor (HPTR) Airseal · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 1 more. Effective Dec 8, 1986
- [AD 86-07-12](https://openairdocs.org/ad/86-07-12): Engine Support Clevis · Pratt & Whitney Division JT9D-7R4G2. Effective Apr 11, 1986
- [AD 86-03-03](https://openairdocs.org/ad/86-03-03): Fuel Nozzle Flow And Spray Cone Angle · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4E and JT9D-7R4E4. Effective Mar 14, 1986
- [AD 83-22-52 R1](https://openairdocs.org/ad/83-22-52-R1): Refurbishing Fuel Nozzles · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Feb 21, 1984
- [AD 78-16-05](https://openairdocs.org/ad/78-16-05): Sixth Stage Turbine Disks · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 17 more. Effective Sep 12, 1978
- [AD 76-24-03](https://openairdocs.org/ad/76-24-03): Fan Blades · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 17 more. Effective Dec 30, 1976
- [AD 76-12-03](https://openairdocs.org/ad/76-12-03): Sixth Stage Turbine Disk · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 17 more. Effective Jun 22, 1976
- [AD 73-16-05](https://openairdocs.org/ad/73-16-05): Fourth and Fifth Stage Turbine Discs · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 17 more. Effective Aug 15, 1973
- [AD 2012-04-15](https://openairdocs.org/ad/2012-04-15) (historical): Engine · Pratt & Whitney Division JT9D-20J, JT9D-3A, JT9D-59A and 16 more. Effective Apr 23, 2012
- [AD 2007-17-21](https://openairdocs.org/ad/2007-17-21) (historical): High pressure turbine (HPT) vane assemblies · Pratt & Whitney Division JT9D-7R4E1, JT9D-7R4E4, JT9D-7R4G2 and 1 more. Effective Sep 28, 2007
- [AD 2007-05-17](https://openairdocs.org/ad/2007-05-17) (historical): Airworthiness Limitations Section (ALS) · Pratt & Whitney Division JT9D-20J, JT9D-3A, JT9D-7 and 15 more. Effective Apr 12, 2007
- [AD 2005-26-09](https://openairdocs.org/ad/2005-26-09) (historical): 1st stage fan blades. · Pratt & Whitney Division JT9D-7R4D, JT9D-7R4D1, JT9D-7R4E and 4 more. Effective Jan 11, 2006
- [AD 2002-10-07](https://openairdocs.org/ad/2002-10-07) (historical): High Pressure Turbine (HPT) Second Stage Airseals · Pratt & Whitney Division JT9D-59A, JT9D-70A, JT9D-7Q and 1 more. Effective Jun 27, 2002
- [AD 2002-08-11](https://openairdocs.org/ad/2002-08-11) (historical): Airworthiness Limitations Section (ALS) - Critical Life-Limited Parts · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 17 more. Effective May 28, 2002
- [AD 2000-01-13](https://openairdocs.org/ad/2000-01-13) (historical): Pratt & Whitney Division JT9D-7, JT9D-70A, JT9D-7A and 13 more. Effective Feb 23, 2000
- [AD 99-08-12](https://openairdocs.org/ad/99-08-12) (historical): Maintenance Program, Mandatory Inspections · Pratt & Whitney Division JT9D-20J, JT9D-3A, JT9D-59A and 16 more. Effective May 13, 1999

## Registered aircraft by registry model (OpenAirDocs)

- [Pratt & Whitney JT9D-7R4D](https://openairdocs.org/engine/pratt-whitney-jt9d-7r4d): 4 aircraft (registry code 51553)
- [Pratt & Whitney JT9D-59A](https://openairdocs.org/engine/pratt-whitney-jt9d-59a): 1 aircraft (registry code 51549)
- [Pratt & Whitney JT9D-7R4E](https://openairdocs.org/engine/pratt-whitney-jt9d-7r4e): 1 aircraft (registry code 51555)
- [Pratt & Whitney JT9D-70A](https://openairdocs.org/engine/pratt-whitney-jt9d-70a): 0 aircraft (registry code 51550)
- [Pratt & Whitney JT9D-7Q](https://openairdocs.org/engine/pratt-whitney-jt9d-7q): 0 aircraft (registry code 51551)
- [Pratt & Whitney JT9D-7Q3](https://openairdocs.org/engine/pratt-whitney-jt9d-7q3): 0 aircraft (registry code 51552)
- [Pratt & Whitney JT9D-7R4D1](https://openairdocs.org/engine/pratt-whitney-jt9d-7r4d1): 0 aircraft (registry code 51554)
- [Pratt & Whitney JT9D-7R4E1](https://openairdocs.org/engine/pratt-whitney-jt9d-7r4e1): 0 aircraft (registry code 51556)
- [Pratt & Whitney JT9D-7R4E4](https://openairdocs.org/engine/pratt-whitney-jt9d-7r4e4): 0 aircraft (registry code 51559)
- [Pratt & Whitney JT9D-7R4G2](https://openairdocs.org/engine/pratt-whitney-jt9d-7r4g2): 0 aircraft (registry code 51557)
- [Pratt & Whitney JT9D-7R4H1](https://openairdocs.org/engine/pratt-whitney-jt9d-7r4h1): 0 aircraft (registry code 51558)

## STCs approved under this data sheet (9)

- [STC SE2338SO](https://openairdocs.org/stc/SE2338SO): Installation of an oil tank safety cap adapter which prevents oil loss in the event of loss or damage to the filler cap.. Jet Avion Corporation
- [STC SE00024EN](https://openairdocs.org/stc/SE00024EN): Installation of oil tank filler neck check valve.. Helicopter Support Inc Services Div
- [STC SE497NE](https://openairdocs.org/stc/SE497NE): Installation of oil tank filler neck check valve assembly.. Aviation Components Support
- [STC SE00054AT-D](https://openairdocs.org/stc/SE00054AT-D): Modification of the turbine exhaust case to provide increased wall thickness for the purpose of improved blade containment.. Aero Component Technologies
- [STC SE00047AT-D](https://openairdocs.org/stc/SE00047AT-D): Modification of turbine exhaust case to provide increased wall thickness for the purpose of improved blade containment.. Aero Component Technologies
- [STC SE00045AT-D](https://openairdocs.org/stc/SE00045AT-D): Modify -59A LPT case to reduce the thickness of four bosses to eliminate interference with the turbine case cooling manifold installed on -7Q engines. This modification permits use of the -59A LPT case on-7Q engines.. Aero Component Technologies
- [STC SE435NE](https://openairdocs.org/stc/SE435NE): Installation of an oil tank filler opening shuttle valve.. Stockbridge William D
- [STC SE133NE](https://openairdocs.org/stc/SE133NE): Incorporation of Hamilton Standard EDM 110-3 Engine Data Multiplexer. United Technologies
- [STC SE118NE](https://openairdocs.org/stc/SE118NE): Thrust reverser system P/N 221D0065, consisting of 4 major installations.. Pratt & Whitney

---
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