TCDS NUMBER E20EA
REVISION: 14
U.S. DEPARTMENT OF TRANSPORTATION DATE: February 10, 2000
FEDERAL AVIATION ADMINISTRATION PRATT & WHITNEY
TYPE CERTIFICATE DATA SHEET E20EA 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 36,400 39,650 40,080 40,200
Takeoff static thrust at sea
level, lb (See NOTES 14 & 15)
Dry (5 minutes) 43,500 45,500 46,150 46,750
With water injection 45,000 47,000 47,670 48,650
COMPONENTS
Fuel Control (See NOTE 7) Hamilton Std. -- -- --
JFC68-3
Fuel Pump Thompson Ramo -- -- 389400
Wooldridge Inc.
373400
Low compressor bleed PW P/N 647977 -- -- --
Actuator Hamilton Std.
High compressor stator vane EVC3-2 -- -- --
Control
Start bleed control/ PW P/N 694927/ 711483/
3.0 bleed control 694926 711484 -- --
FUEL See NOTE 11 -- -- --
OIL See NOTE 12 -- -- --
*
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.
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 40,200 39,240 39,240*
Takeoff static thrust at sea
level, lb (See NOTES 14 & 15)
Dry (5 minutes) 48,650 44,500* 48,050*
With water injection --- 47,500 ---
COMPONENTS
Fuel Control (See NOTE 7) Hamilton Std. JFC68-4 --
JFC68-3
Fuel Pump Thompson Ramo 373400 389400
Wooldridge Inc.
373400
Low compressor bleed PW P/N 674977 -- --
Actuator Hamilton Std.
High compressor stator vane EVC3-2 EVC3-4 --
Control
Start bleed control/ PW P/N 694927/ 719306/
3.0 bleed control 694926 719306 --
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, JT9D-20 JT9D-20J
-7F, -7J
PRINCIPAL DIMENSIONS
Maximum length, in. (including
spinner) 154.89 -- -- -- --
Width, in. 95.60 -- -- 96.61 --
WEIGHT (Dry), lb 8713 8880 -- 8470 8580
(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)
CENTER OF GRAVITY, in.
Forward of K-flange (+1.0) 2.1 2.1 -- 3.7 3.5
Below engine center line (+0.5) 1.0 1.2 -- 2.8 2.8
IGNITION
Exciters Two GLA P/N 43572, -- -- Champion --
Igniters 43925 AA72S-A,
Champion AA72S-A, -- -- AA134S-1,
AA117S, AA134S, AA143S-2
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 32oF. 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. The following models incorporate the following general characteristics:
JT9D Model Characteristics
-3A Same as -3 except for dry takeoff rating extended to 80oF 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 80oF 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 80oF 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 80oF 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 86oF ambient temperature sea level static . The
thrust is 48,560 lb (50,000 lb ideal) and Max. EGT is 985oC 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 84oF ambient temperature
sea level static, and wet takeoff rating of 47,500 lb is available to 86oF 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 +6oF 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 86oF ambient temperature sea level static . The
thrust is 48,050 lb (5,000 lb ideal) and Max. EGT is 985oF 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.
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