# TCDS E20EA: Pratt & Whitney

- Type: Type certificate data sheet
- Status: Current
- Holder: Pratt & Whitney
- Revision: 14
- Revised: February 10, 2000
- Product: Engine
- Certification basis: Part 33, Part 33, Part 33, Part 33, Part 33, Part 33, Part 33, Part 33, Part 33
- Registered aircraft: 5, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/6d/f8/6df88650e179de06c4ebb42a5e646a6b5e1aab79d93079925bd4e1b07b4ac374
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D36293C19EE399B7862586B80063500E.0001
- Page: https://openairdocs.org/tcds/E20EA

## Models (9)

As the data sheet lists them.

- JT9D-7
- JT9D-7AH
- JT9D-7J
- JT9D-3A
- JT9D-7F
- JT9D-7A
- JT9D-20
- JT9D-7H
- JT9D-20J

## 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
 REV. 14 10 13 10 10 14 14
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 DATA SHEET E20EA
TCDS NUMBER E20EA
REVISION:  14
DATE:    February 10, 2000
PRATT & WHITNEY
MODELS:
JT9D-3A JT9D-7A JT9D-20
JT9D-7 JT9D-7AH JT9D-7J
JT9D-7H JT9D-7F JT9D-20J
Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E20EA) 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
Commercial Products Division
East Hartford, Connecticut  06108
I. MODELS JT9D-3A JT9D-7, -7H JT9D-7A, -7AH JT9D-7F
TYPE Turbofan, dual axial 15 stage compressor, annular combustion chambers,
and 6 stage turbine.
RATINGS (See NOTE 5)
  Maximum Continuous at sea
   level, static thrust, lb
   Takeoff static thrust at sea
   level, lb (See NOTES 14 & 15)
   Dry (5 minutes)
   With water injection
36,400
43,500
45,000
39,650
45,500
47,000
40,080
46,150
47,670
40,200
46,750
48,650
COMPONENTS
  Fuel Control (See NOTE 7)
  Fuel Pump
  Low compressor bleed
   Actuator
  High compressor stator vane
   Control
  Start bleed control/
   3.0 bleed control
Hamilton Std.
JFC68-3
Thompson Ramo
Wooldridge Inc.
373400
PW P/N 647977
Hamilton Std.
EVC3-2
PW P/N 694927/
694926
- -
- -
- -
- -
711483/
711484
- -
- -
- -
- -
- -
- -
389400
- -
- -
- -
FUEL See NOTE 11 - - - - - -
OIL See NOTE 12 - - - - - -

TCDS E20EA                                                                                                                                                     PAGE 2
I. MODELS (Continued) JT9D-7J JT9D-20 JT9D-20J
TYPE Turbofan, dual axial 15 stage compressor, annular combustion chambers,
and 6 stage turbine.
RATINGS (See NOTE 5)
  Maximum Continuous at sea
   level, static thrust, lb
  Takeoff static thrust at sea
   level, lb (See NOTES 14 & 15)
   Dry (5 minutes)
   With water injection
40,200
48,650
---
39,240
44,500*
47,500
39,240*
48,050*
---
COMPONENTS
  Fuel Control (See NOTE 7)
  Fuel Pump
  Low compressor bleed
   Actuator
  High compressor stator vane
   Control
  Start bleed control/
   3.0 bleed control
Hamilton Std.
JFC68-3
Thompson Ramo
Wooldridge Inc.
373400
PW P/N 674977
Hamilton Std.
EVC3-2
PW P/N 694927/
694926
JFC68-4
373400
- -
EVC3-4
719306/
719306
- -
389400
- -
- -
- -
FUEL See NOTE 11 - - - -
OIL See NOTE 12 - - - -
*As installed in a DC-10-40 nacelle
I. MODELS JT9D-3A JT9D-7, -7H JT9D-7A, -7AH,
-7F, -7J
JT9D-20 JT9D-20J
PRINCIPAL DIMENSIONS
  Maximum length, in. (including
   spinner)
  Width, in.
154.89
95.60
- -
- -
- -
- -
- -
96.61
- -
- -
WEIGHT (Dry), lb
  (Includes basic engine with
  all essential accessories; with
  fuel heater, oil tank and fuel oil
  cooler; but excluding starter,
  exhaust nozzle, and power
  source for the ignition system).
  Standard equipment included
  in engine dry weight. (SEE
  NOTE 17)
8713 8880 - - 8470 8580
CENTER OF GRAVITY, in.
  Forward of K-flange ( +1.0)
  Below engine center line (+0.5)
2.1
1.0
2.1
1.2
- -
- -
3.7
2.8
3.5
2.8
IGNITION
  Exciters
  Igniters
Two GLA P/N 43572,
43925
Champion AA72S-A,
AA117S, AA134S,
AA134S-1, AA143S-2
- -
- -
- -
- -
Champion
AA72S-A,
AA134S-1,
AA143S-2
- -

TCDS E20EA                                                                                                                                                     PAGE 3
CERTIFICATION BASIS FAR 33 effective February 1, 1965, as amended by 33-1, 33-2, and 33-3 and Special
Condition No. 33-8-EA-3.
Type Certificate No. E20EA issued May 13, 1969; and subsequent revisions Model JT9D-
3A added January 9, 1970; Model JT9D-7 added June 14, 1971; Model JT9D-7A added
September 22, 1972; Model JT9D-20 added October 16, 1972; Models JT9D-7H and -7AH
added June 19, 1974; Model JT9D-7F added September 30, 1974; Model JT9D-7J added
August 31, 1976; Model JT9D-20J added December 29, 1986.
Dates of Applications for Type Certificate:  May 10, 1968; November 19, 1969 (JT9D-3A);
September 9, 1970 (JT9D-7); July 28, 1972 (JT9D-7A); August 31, 1982 (JT9D-20); April
26, 1974 (JT9D-7H, -7AH); February 4, 1974 (JT9D-7F); October 29, 1974 (JT9D-7J);
and April 22, 1986 (JT9D-20J).
PRODUCTION BASIS Production Certificate Number 2
NOTES
NOTE 1. Maximum permissible engine operating speeds for the engine rotors are as follows:
JT9D-3A JT9D-7, -7A, -7F, -7J, -20J JT9D-7H, -7AH, -20
Low pressure rotor (N1), rpm 3650 3750 3650
High pressure rotor (N2), rpm 7850 8000 8000
NOTE 2. Maximum permissible temperatures are as follows:
Turbine gas temperature (Tt6)
JT9D-3A JT9D-7, -7H, -7A, -7AH JT9D-7F
Takeoff (5 min.) (846oC) 1555oF (915oC) 1679oF (950oC) 1742oF
Maximum continuous (816oC) 1500oF (880oC) 1616oF (910oC) 1670oF
Maximum acceleration (846oC) 1555oF (915oC) 1679oF (950oC) 1742oF
Starting (650oC) 1202oF (650oC) 1202oF (650oC) 1202oF
JT9D-7J JT9D-20 JT9D-20J
Takeoff (5 min.) (985oC) 1805oF (915oC) 1679oF (985oC) 1805oF
Maximum continuous (925oC) 1697oF (875oC) 1607oF (925oC) 1679oF
Maximum acceleration (985oC) 1805oF (915oC) 1679oF (985oC) 1805oF
Starting (650oC) 1202oF (650oC) 1202oF (650oC) 1202oF
JT9D-3A JT9D-7, -7H, -7A, -7AH JT9D-7F, -7J JT9D-20, -20J
Oil Inlet (135oC) 275oF (continuous operation) - - - - - -
(162oC) 325oF (transient operation)* - - - - - -
*Transient operation above 135oC, (275oF) is limited to 20 minutes.
Pratt & Whitney Service Bulletin JT9D 6352 is available to increase JT9D-7A series EGT margin by 20°C.  This is accomplished by
reducing indicated EGT by 20ºC using a shunt device.  Service Bulletin 6352 also defines required hardware changes , which must be
accomplished prior to installation of the shunt.  Operating procedures and maintenance requirements shall be conducted per indicated
EGT.
External engine component maximum temperature (limiting temperature of specific components is as specified in the engine installation
and operating manual.)

TCDS E20EA                                                                                                                                                     PAGE 4
NOTE 3. Fuel and oil pressure limits 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: 40 to 60 psig
NOTE 4. Maximum permissible air bleed extraction is as follows:
JT9D-3A/7/7H/7A
    7AH/7F/7J                JT9D-20/20J
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% 10% 13%
b.  40% max. cont. to takeoff * 5% 5% 5% 6.5%
*5% is the maximum allowable from the 8th stage in this thrust range.  The 6.5% listed in allowable is from the 15th stage alone or from
a combination of 8th and 15th stage bleeds.
NOTE 5. These installation ratings are based on static test stand operation under the following conditions:
Compressor inlet air at 59oF and 29.92 in. hg.
Jet nozzle exhaust pipe per PW Drawing P/N 676701 (-3A); 636901 (-7, -7A, -7AH, -7F, -7J); 654001 (-20, -20J).
Fan exit nozzle per PW Drawing P/N 676701 (-3A); 636901 (-7, -7A, -7AH, -7F, -7J); 654001 (-20, -20J).
PW bellmouth engine inlet.
No aircraft accessory loads or air extraction.
No anti-icing airlfow.
Turbine gas temperature limits and engine rotor speed limits not exceeded.
For sea level static ideal thrust of -7F and -7J models, see NOTE 15.
NOTE 6. The following accessory drive provisions are incorporated:
JT9D-3A, -7, -7H, -7A, -7AH, -7F, -7J
________________________________________________________________________
 Speed Ratio
DRIVE        to Torque (in-lb) Overhang
HIGH ROTOR Rotation Turbine Shaft Continuous Static (in-lb)
Starter CC 1.091:1 --- *    500
C.S.C. Generator**  CC 1.091:1 *** 15,960 1,575
Fluid Power Pump CC   .500:1 1890   9,450    400
Fluid Power Pump CC   .499:1 1890   9,450    400
Tachometer C   .538:1 7   50     ---
C - Clockwise; CC - Counterclockwise
* Maximum Starter torque 750 ft-lb, shear section will fail at 1400 to 1610 ft-lb.
** Generator driven by co-axial shaft from constant speed drive.
*** Maximum allowable continuous torque values are equivalent to 210 hp at any engine speed at or above sea level
ground idle.

TCDS E20EA                                                                                                                                                     PAGE 5
NOTE 7. Fuel controls for model designations:
Model HSD Fuel Control P/N PW P/N Description
JT9D-3A 734500-3 711622 Wet Control
734499-4 711623 Dry Control
JT9D-7/7A/7AH 748000-5 770019 Wet Control - Accel cam
Different from D-3A
747999-5 770020 Dry Control
JT9D-7F 759100-1 750832 Wet Control - Accel cam
Different from D-3A or
D-7J engines
759000-1 750818 Dry Control
JT9D-7J 759000-1 750818 Dry Control - same cam as D-7F
JT9D-20/20J 743699-3 747544 Wet Control - D-20 only
743555-3 747543 Dry control
NOTE 8. Power setting, power checks and control of engine output in all operations are to be based upon PW engine charts
referring to turbine discharge section gas pressures.  Pressure probes are included in the engine assembly for this
purpose.
NOTE 9. Whenever engine anti-ice is used to maintain at least 50 percent N1 RPM above 10,000 feet, and at least 45 percent
N1 rpm below 10,000 feet.
NOTE 10. These engine models meet Item 1 in Special Condition No. 33-8-EA-3 in the uncowled configuration.
NOTE 11. Fuels meeting the requirements of the latest applicable issue of FAA approved PW Turbojet Engine Service Bulletin
No. 2016, which includes with other fuel information requirements of PW Specification No. 522, are acceptable for
these engines.  Approved fuel additives and allowable concentrations for each are also included in Service Bulletin No.
2016.
NOTE 12. The following oils are eligible for these engines:
Synthetic type conforming to PW Specification No. 521 as revised.  Approved brand oils listed in PW Turbojet Engine
Service Bulletin No. 238.
NOTE 13. Certain engine parts are life limited.  These limits are listed in the FAA Approved Pratt & Whitney JT9D Series
Turbofan Overhaul Manual Part No. 646028 (-3A, -7, -7H, -7A, -7AH, -7F, -7J, -20, -20J) Time Limits Section.
These limits are also listed in the FAA Approved Pratt & Whitney JT9D Turbofan Overhaul Manuals Part Number
770407 (-3A, -7) and Part Number 770408 (-7) Time Limits Section.
NOTE 14. For water injection, the following water flow rate is utilized:
JT9D-3A JT9D-7, -7H, -7A, -7AH, -7F, -20
Constant water flow - lb/hr 20,000 -23,000 26,000 - 30,000
Feed pressure - psia 507 -700 534 - 750
Water alone is specified and should contain no more than 10 (ppm) parts per million impurities.  Use of water is
limited to takeoff operation up to an altitude of 8,000 feet for D-3A, and 10,000 feet for D-7, -7H, -7A, -7AH, -7F and
-20, at the minimum ambient temperatures of 32 oF.  Takeoff using both water injection and dry takeoff power is
limited to a maximum period of 5 minutes including operation with water injection for not more than 2 1/2 minutes
(JT9D-3A, -7, -7H, -7A, -7AH, -7F) and 5 minutes (JT9D-20).

TCDS E20EA                                                                                                                                                     PAGE 6
NOTE 15.
JT9D Model
The following models incorporate the following general characteristics:
Characteristics
-3A Same as -3 except for dry takeoff rating extended to 80 oF ambient temperature sea level static with thrust frame and
other improved engine parts.  With water injection (equipment an additional 40 lb) takeoff rating of 45,000 lb is
available to 80oF ambient temperature sea level static.  The JT9D-3 engine model was deleted on December 29, 1986,
since it is no longer in service and the manufacturer has no plans to produce any more engines of that model.
-7 Same as -3A except for dry takeoff rating extended to 80 oF ambient temperature sea level static with thrust frame wet
takeoff rating of 47,000 lb is available to 86oF ambient temperature sea level static.  Engines equipped with water
injection systems may be operated at wet takeoff rating without activating the water injection system when ambient
temperatures are 32oF and below.
-7H Same as -7 except for fan hub which is -3A engine fan hub.  Ratings are same as those for -7.
-7A Same as -7 except dry takeoff rating of 46,150 lb is available to 80 oF ambient temperature sea level static, and wet
takeoff rating of 47,670 lb is available to 86oF ambient temperature sea level static.  Engines equipped with water
injection systems may be operated at wet takeoff rating without activating the water injection system when ambient
temperatures are 32oF and below.
-7AH Same as -7A except for fan hub which is -3A engine fan hub.  Ratings are same as those for -7A.
-7F Same as -7A except for dry takeoff rating of 46,750 lb (48,000 lb ideal) is available to 80 oF ambient temperature sea
level static, and wet takeoff rating 48,650 lb (50,000 lb ideal) is available to 86oF ambient temperature sea level static.
Engines equipped with water injection systems may be operated at wet takeoff rating without activating the water
injection system when ambient temperature are 32oF and below.
-7J Same as -7F except no wet rating.  Dry takeoff thrust is available to 86 oF ambient temperature sea level static.  The
thrust is 48,560 lb (50,000 lb ideal) and Max. EGT is 985 oC Tt6, due to an improved high pressure turbine (See
NOTE 5.)
-20 Same as -7 except for gearbox and certain accessories are mounted external to the fan case and the thrust attachment
points are located on the intermediate case.  Dry takeoff rating of 44,500 lb  is available to 84 oF ambient temperature
sea level static, and wet takeoff rating of 47,500 lb is available to 86 oF ambient temperature sea level static.  Engines
equipped with water injection system may be operated at wet takeoff rating without activating the water injection
system when ambient temperatures are at standard +6 oF and below.  These ratings represent McDonnell Douglas DC-
10 aircraft installed performance.
-20B This engine model has never been produced and no future manufacturing is contemplated, thus it is deleted.
-20J Same as -20 except no wet rating.  Dry takeoff thrust is available to 86 oF ambient temperature sea level static.  The
thrust is 48,050 lb (5,000 lb ideal) and Max. EGT is 985 oF Tt6 due to an improved burner and improved high and low
pressure turbine.
The JT9D-7F, JT9D-7J, Sea Level Static Ratings are ideal and are based on ICAO Standard Atmosphere conditions,
the specified fuel and oil, a Pratt & Whitney hardwall bellmouth inlet, no fan or compressor airbleed or load on
accessory drives, an exhaust system having no internal pressure or external scrubbing losses and fan duct and primary
nozzle velocity coefficients equal to 1.0.

TCDS E20EA                                                                                                                                                     PAGE 7
NOTE 16. The smoke requirements of SFAR 27.2 have been met by these engine models:  JT9D-7A, -7F, and -7J.
NOTE 17. For standard equipment, refer to Pratt & Whitney specification numbers listed below:
MODEL PW SPEC. NUMBER
JT9D-3A 6157
JT9D-7 1994
JT9D-7H 6212
JT9D-7A 6165
JT9D-7AH 6222
JT9D-7F 6211
JT9D-7J 6239
JT9D-20 6190
JT9D-20J 6426
NOTE 18. 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 shut down.
----END----
```

## ADs (35, 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 2009-04-18](https://openairdocs.org/ad/2009-04-18): 2nd stage high pressure turbine (HPT) · Pratt & Whitney Division JT9D-7, JT9D-7A, JT9D-7AH and 3 more. Effective May 5, 2009
- [AD 2004-10-01](https://openairdocs.org/ad/2004-10-01): 6th Stage Low Pressure Turbine (LPT) Air Seals · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 6 more. Effective Jun 15, 2004
- [AD 2003-24-12 R1](https://openairdocs.org/ad/2003-24-12-R1): Gearbox Pressure Tube · Pratt & Whitney Division JT9D-3A, JT9D-7, JT9D-7A and 4 more. Effective Dec 18, 2003
- [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 99-15-02](https://openairdocs.org/ad/99-15-02): Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 6 more. Effective Aug 16, 1999
- [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 93-19-02 R1](https://openairdocs.org/ad/93-19-02-R1): Diffuser Cases · Pratt & Whitney Division JT9D-20, JT9D-20J, JT9D-3A and 6 more. Effective Oct 17, 1994
- [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 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 89-10-07](https://openairdocs.org/ad/89-10-07): Strut Insert Assembly · Pratt & Whitney Division JT9D-20, JT9D-3A, JT9D-7 and 5 more. Effective May 30, 1989
- [AD 88-24-05](https://openairdocs.org/ad/88-24-05): Inner Airseal · Pratt & Whitney Division JT9D-20, JT9D-3A, JT9D-7 and 5 more. Effective Dec 15, 1988
- [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 86-10-01](https://openairdocs.org/ad/86-10-01): Second Stage Turbine Disk · Pratt & Whitney Division JT9D-3A. Effective Jun 5, 1986
- [AD 85-12-02](https://openairdocs.org/ad/85-12-02): Centrifugal Oil Filter (COF) Bearings · Pratt & Whitney Division JT9D-3A, JT9D-7, JT9D-7A and 4 more. Effective Jul 17, 1985
- [AD 82-26-03](https://openairdocs.org/ad/82-26-03): Manifold Assembly · Pratt & Whitney Division JT9D-7, JT9D-7A, JT9D-7AH and 3 more. Effective Jan 27, 1983
- [AD 82-16-10](https://openairdocs.org/ad/82-16-10): Fan Exit Case Assembly · Pratt & Whitney Division JT9D-20. Effective Aug 16, 1982
- [AD 74-10-05 R1](https://openairdocs.org/ad/74-10-05-R1): Turbine Nozzle Guide Vane · Pratt & Whitney Division JT9D-20, JT9D-7 and JT9D-7A. Effective Nov 17, 1980
- [AD 78-08-13](https://openairdocs.org/ad/78-08-13): Main Gearbox · Pratt & Whitney Division JT9D-3A, JT9D-7, JT9D-7A and 4 more. Effective Apr 18, 1980
- [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 78-17-08](https://openairdocs.org/ad/78-17-08): Fifteenth Stage Compressor Disks · Pratt & Whitney Division JT9D-20, JT9D-3A, JT9D-7 and 5 more. Effective Sep 1, 1978
- [AD 76-20-03](https://openairdocs.org/ad/76-20-03): Seal Clearances · Pratt & Whitney Division JT9D-20, JT9D-3A, JT9D-7 and 4 more. Effective Nov 16, 1977
- [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 74-10-04](https://openairdocs.org/ad/74-10-04): Main Gearbox · Pratt & Whitney Division JT9D-3A and JT9D-7. Effective May 14, 1974
- [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 71-24-03](https://openairdocs.org/ad/71-24-03): Diffuser Case Assembly · Pratt & Whitney Division JT9D-3A. Effective May 19, 1972
- [AD 77-01-07](https://openairdocs.org/ad/77-01-07): Fifth Stage Turbine Hubs · Pratt & Whitney Division JT9D-20, JT9D-3A, JT9D-7 and 4 more
- [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 2007-05-17](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 2003-24-12](https://openairdocs.org/ad/2003-24-12) (historical): Gearbox pressure tube · Pratt & Whitney Division JT9D-3A, JT9D-7, JT9D-7A and 4 more. Effective Dec 18, 2003
- [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-3A](https://openairdocs.org/engine/pratt-whitney-jt9d-3a): 4 aircraft (registry code 52050)
- [Pratt & Whitney JT9D-7](https://openairdocs.org/engine/pratt-whitney-jt9d-7): 1 aircraft (registry code 51541)
- [Pratt & Whitney JT9D-20](https://openairdocs.org/engine/pratt-whitney-jt9d-20): 0 aircraft (registry code 51547)
- [Pratt & Whitney JT9D-20J](https://openairdocs.org/engine/pratt-whitney-jt9d-20j): 0 aircraft (registry code 51548)
- [Pratt & Whitney JT9D-7A](https://openairdocs.org/engine/pratt-whitney-jt9d-7a): 0 aircraft (registry code 51543)
- [Pratt & Whitney JT9D-7AH](https://openairdocs.org/engine/pratt-whitney-jt9d-7ah): 0 aircraft (registry code 51544)
- [Pratt & Whitney JT9D-7F](https://openairdocs.org/engine/pratt-whitney-jt9d-7f): 0 aircraft (registry code 51545)
- [Pratt & Whitney JT9D-7H](https://openairdocs.org/engine/pratt-whitney-jt9d-7h): 0 aircraft (registry code 51542)
- [Pratt & Whitney JT9D-7J](https://openairdocs.org/engine/pratt-whitney-jt9d-7j): 0 aircraft (registry code 51546)

## STCs approved under this data sheet (14)

- [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 SE01543CH](https://openairdocs.org/stc/SE01543CH): Replace Hamilton Sundstrand P/N 778839-13, 778839-14, 778839-19, 778839-20, 778839-37, 778839-38, 816682-1, 840618-2, 880724 carbon bushings with Cook Airtomic P/N AIR22947 Slotted Entry Busing in the High Pressure Shutoff Valve.. Cook Airtomic
- [STC SE00402NY](https://openairdocs.org/stc/SE00402NY): Installation of corrosion resistant steel replacement Chip Detectors.. Vickers Inc
- [STC SE497NE](https://openairdocs.org/stc/SE497NE): Installation of oil tank filler neck check valve assembly.. Aviation Components Support
- [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 SE00046AT-D](https://openairdocs.org/stc/SE00046AT-D): State 1 LPC Stator: Provide a seamless one piece rubber airflow surface at the inner shroud.. Aero Component Technologies
- [STC SE2888SO-D](https://openairdocs.org/stc/SE2888SO-D): Modify turbine exhaust case to incorporate Model -20 mount features.. Aero Component Technologies
- [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 SE435NE](https://openairdocs.org/stc/SE435NE): Installation of an oil tank filler opening shuttle valve.. Stockbridge William D
- [STC SA2227SO](https://openairdocs.org/stc/SA2227SO): Installation of wiring and associated components for utilization of the Rolls Royce, Inc., ARINC, interface/readers UT1317 or UT1317/1, for the purpose of acquisition, recording, and analysis in real time of engine/aircraft/ systems. (767 SERIES POWERED BY RR RB-11-524 SERIES. Rolls Royce, Inc
- [STC SE1141CE](https://openairdocs.org/stc/SE1141CE): Removal of 15th stage bleeds and surge detector system.. Trans World Airlines Inc
- [STC SE33NE](https://openairdocs.org/stc/SE33NE): Incorporation of improved combustor and turbine components which permit operation at increased EGT limits.. Pratt & Whitney Aircraft Grp
- [STC SE11CE](https://openairdocs.org/stc/SE11CE): Installation of aircraft integrated data system components on engine.. Trans World Airlines Inc

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