ponle números es mas facil..

Hola Gente;

Este es el manual de procedimientos de mantenimientos sobre la serie TFE 731 en TODAS SUS VERSIONES.
Como es costumbre de este foro, de no tratar como ganado a sus miembros e invitados.
Trataremos de aportar datos concretos que ayuden al libre albedrío y analisis.

European Aviation Safety Agency
EASA
TYPE-CERTIFICATE
DATA SHEET
Number: IM.E.011
Issue: 05
Date: 27 May 2010
Type: Honeywell International Inc.
TFE731-20, -40, -50, -60 series engines
Models:
TFE731-20
TFE731-20AR
TFE731-20BR
TFE731-20R
TFE731-40
TFE731-40R
TFE731-40ARTFE731-50R
TFE731-60
List of effective Pages:
Page 1 2 3 4 5 6 7 8 9
Issue 5 5 5 5 5 5 5 5 5
TCDS IM.E. 011 TFE731-20, -40, -50, -60 series engines Page 2
Issue 5, 27 May 2010 Models -20, -20AR, -20BR, -20R,
-40, -40R, -40AR, -50R, -60
Intentionally left blank
TCDS IM.E. 011 TFE731-20, -40, -50, -60 series engines Page 3
Issue 5, 27 May 2010 Models -20, -20AR, -20BR, -20R,
-40, -40R, -40AR, -50R, -60
I. General
1. Type/Models:
TFE731-20, TFE731-20AR, TFE731-20BR, TFE731-20R, TFE731-40, TFE731-40R, TFE731-40AR,
TFE731-50R, TFE731-60
2. Type Certificate Holder:
Honeywell International Inc.
111 South 34th Street
Phoenix
AZ 85034
USA
3. Manufacturer: Honeywell International Inc.
4. EASA/JAA Validation Application Date:
TFE731-20, -20R, -40, -40R, -60 TFE731-20AR TFE731-20BR TFE731-40AR TFE731-50R
10 March 1994 26 May 1999 19 March 2004 01 November 2005 20 December 2004
5. Validation Reference Date: 19 January 1993
6. JAA Validation Recommendation Date:
TFE731-20, -20R TFE731-20AR TFE731-40, -40R TFE731-60
18 March 1998 18 October 1999 20 June 1996 31 May 1996
7. EASA Certification Date:
TFE731-20, -20R TFE731-20AR TFE731-40, -40R TFE731-60 TFE731-20BR
17 August 1998 17 November 1999 13 January 1997 10 July 1998 01 September 2004
TFE731-40AR TFE731-50R
01 June 2007 07 December 2007
EASA Type Certification for the TFE731-20, TFE731-20AR, TFE731-20R, TFE731-40, TFE731-40R and TFE731-
60 engine models is granted, in accordance with article 2 paragraph 3 (a)(i) of EU Commission Regulation EC
1702/2003, based on the CAA United Kingdom validation letter issued following the JAA Validation
Recommendation.
I
I. Certification Basis
1. FAA Certification Basis details:
See FAA TCDS E1NM.
2. EASA Certification Basis:
2.1 Airworthiness Standards:
JAR-E change 8 dated 4 May 1990 plus Orange Paper E/91/1 published 27 May 1991 and JAR-E850
as amended by Orange Paper E/93/1 effective 17 May 1993.
TCDS IM.E. 011 TFE731-20, -40, -50, -60 series engines Page 4
Issue 5, 27 May 2010 Models -20, -20AR, -20BR, -20R,
-40, -40R, -40AR, -50R, -60
In addition, for TFE731-40AR and TFE731-50R, CS-E Original Issue, dated 24 October 2003,
paragraph CS-E 790.
I
n addition, for TFE731-50R, CS-E Original Issue, dated 24 October 2003, paragraphs CS-E 100(c),
CS-E 650, CS-E 800, applicable to the fan rotor assembly only, and CS-E 890, applicable to the
whole engine.
2.2 Special Conditions:
2.2.1 TFE731-20, -20R, -20 AR, -20BR, -40, -40R, -60
PC338-1: Ingestion of Rain and Hail
2.2.2 TFE731-40AR, -50R
None.
2.3 Deviations:
None.
2.4 Equivalent Safety Findings:
2.4.1 TFE731-20, -20R, -20 AR, -20BR, -40, -40R, -40AR, -60
JAR-E890(b)(1): Thrust Reverser Endurance Tests
2.4.2 TFE731 -50R
None.
2.5. Environmental Standards:
2.5.1 TFE731-20, -20R, -20 AR, -40, -40R, -60
Emissions and Fuel Venting : ICAO Annex 16, Volume II, 2nd Edition, 1993.
2.5.2 TFE731-20BR, -40AR, -50R
Emissions and Fuel Venting : EC1702/2003 Annex Part 21A.18(b), 27 September, 2003.
III. Technical Characteristics
1. Type Design Definition:
The Type Design Definition is in accordance with the following Honeywell Engine Parts Lists:
TFE731-20 3060080-1
TFE731-20AR 3060082-2
TFE731-20BR 3060084-1
TFE731-20R 3060020-6
TFE731-40 3060050-1
TFE731-40R 3060040-4
TFE731-40AR 3062020-1TFE731-50R 3060090-1
TFE731-60 3060000-4
and later approved Engine Parts Lists published in the applicable Light Maintenance Manual.
TCDS IM.E. 011 TFE731-20, -40, -50, -60 series engines Page 5
Issue 5, 27 May 2010 Models -20, -20AR, -20BR, -20R,
-40, -40R, -40AR, -50R, -60
3. Description:
Turbofan, one stage geared fan, four stage axial flow pressure compressor, one stage centrifugal high pressure
compressor, annular combustor, one stage high pressure turbine and three stage low pressure turbine.
Fuel control is by means of a Digital Electronic Engine Control (DEEC) with back up hydromechanical control.
The starter, thrust reverser and engine mounts are not part of the engine definition.
3. Equipment:
Engine equipment is specified by the Engine Equipment List part number as referenced in the Light Maintenance
Manual.
4. Dimensions:
TFE731-20,-20AR,-20BR,-
20R,-40,-40R,-40AR
TFE731-50R TFE731-60
Overall Length 1.547m (60.91 inches) 1.975m (77.77 inches) 2.083m (81.99 inches)
Overall Width 0.847m (33.35 inches) 0.893m (35.16 inches) 0.932m (36.68 inches)
Overall Height 1.00m (39.36 inches) 1.027m (40.44 inches) 1.076m (42.37 inches)
5. Dry Weight:
TFE731-20,-20AR,-20BR,-20R TFE731-40,-40R,-40AR TFE731-50R TFE731-60
405.97kg (895lb) 401.43kg (885lb) 443 448.15kg (988lb)
See Note 4
6. Ratings:
Maximum Continuous
at Sea Level (1)
Take off (5 minutes)
at Sea Level (1)(2)
TFE731-20 15.57kN (3500lb) 15.57kN (3500lb)
TFE731-20AR 15.57kN (3500lb) 16.24kN (3650lb)
TFE731-20BR 15.57kN (3500lb) 16.24kN (3650lb)
TFE731-20R 15.57kN (3500lb) 16.24kN (3650lb)
TFE731-40 18.90kN (4250lb) 18.90kN (4250lb)
TFE731-40R 18.90kN (4250lb) 19.84kN (4462lb)
TFE731-40AR 18.90kN (4250lb) 19.66kN (4420lb)
TFE731-50R 22.24kN (5000lb) 22.24kN(5000lb)
TFE731-60 20.13kN (4525lb) 22.24kN (5000lb)
(1) See Note 1, Section VI.
(2) See Note 9, Section VI.
7. Control System:
Fuel controls and power management are controlled by a Digital Electronic Engine Control (DEEC) with a backup
hydromechanical control. The hardware and software configuration of this system and the associated engine fuel
pump and hydromechanical unit are controlled by the approved engine equipment list for each specific engine
model and aircraft application.
8. Fluids (Fuel/Oil/Additives)
See applicable Installation Manual.
TCDS IM.E. 011 TFE731-20, -40, -50, -60 series engines Page 6
Issue 5, 27 May 2010 Models -20, -20AR, -20BR, -20R,
-40, -40R, -40AR, -50R, -60
9. Aircraft Accessory Drives:
Accessory Max.
Torque Nm (lb-in)
Note (e)
Accessory
Drive
Drive Type
(one each)
Internal
Spline
Config.
RPM and
Rotation
Facing
Drive End Tc To Ts
Weight
kg (lb)
maximu
m
Note (b)
Overhung
Moment
Nm(lb-in)
Starter or
Starter
Generator
D2*
Note (c)
AND20002
Type XII-D
modified as
follows: RPM,
torques,
accessory
weight, and
moment as
shown
AND20002 12,602
Note (a)
CW
12,728
Note (f)
CW
22.60
(200)
33.90
(300)
180.78
(1600)
20.41
(45)
45.19
(400)
Aircraft
Accessory
D3*
AND20002
Type XII-D
modified as
follows: RPM,
torques,
accessory
weight, and
moment as
shown
AND20002 12,602
Note (a)
CW
12,728
Note (f)
CW
22.60
(200)
33.90
(300)
112.98
(1000)
18.14
(40)
45.19
(400)
Aircraft
Accessory
D1*
(For engines
without motive
fuel pump)
AND20001
Type XI-B
modified as
follows: RPM,
torques,
accessory
weight, and
moment as
shown
AND20001
6,300
Note (a)
CW
6,364
Note (f)
CW
27.12
(240)
40.67
(360)
186.42
(1650)
6.80
(15)
11.30
(100)
Aircraft
Accessory
D1*
(For engines
with motive
flow fuel pump)
Note(d)
AND20001
Type XI-B
modified as
follows: RPM,
torques,
accessory
weight, and
moment as
shown
AND20001
6,300
Note (a)
CW
6,364
Note (f)
CW
11.30
(100)
18.64
(165)
112.98
(1000)
3.18
(7)
2.03
(18)
CW = clockwise (looking aft) To = torque overload (5 minutes per 4 hour period)
Tc = continuous torque Ts = static torque
* Accessory pads are identified by these symbols on the applicable installation drawings.
Notes:
(a) All models except TFE731-50R: drive speeds are based on a maximum steady state HP rotor speed
of 31485 rpm.
(b) Total weight of the accessories is not to exceed 43.06 kg (95 lb) for engines without motive fuel
pump or 39.46 kg (87 lb) for engines with motive fuel pump.
(c) The estimated torsional spring constant for the starter generator drive is 790.89 Nm/radian (7000 lbin/
radian).
(d) Drive is located on engine auxilliary motive flow fuel pump.
(e) Total combined accessory power extraction limits are specified in the applicable engine installation
manual.
(f) TFE731-50R only: drive speeds are based on a maximum steady state HP rotor speed of 31800
rpm.
TCDS IM.E. 011 TFE731-20, -40, -50, -60 series engines Page 7
Issue 5, 27 May 2010 Models -20, -20AR, -20BR, -20R,
-40, -40R, -40AR, -50R, -60
10. Maximum Permissible Air Bleed Extraction:
For all engine models, the bleed extraction limits are specified in the applicable engine installation manual.
IV. Operational Limits
1. Temperature Limits:
1.1 Maximum Interstage Turbine Temperature (ITT) Limits oC (oF):
Maximum Continuous Take off (5 minutes) Starting (Ground/Air)
TFE731-20 941 (1726) 963 (1766) 941 (1726)
TFE731-20AR 941 (1726) 963 (1766) 941 (1726)
TFE731-20BR 991 (1816) 1022 (1871) 994 (1822)
TFE731-20R 941 (1726) 963 (1766) 941 (1726)
TFE731-40 991 (1816) 1022 (1871) 994 (1822)
TFE731-40R 991 (1816) 1022 (1871) 994 (1822)
TFE731-40AR 991 (1816) 1022 (1871) 994 (1822)
TFE731-50R 991 (1816) 1022 (1871) 994 (1822)
TFE731-60 991 (1816) 1022 (1871) 994 (1822)
External engine components maximum temperatures are as specified in the applicable engine
installation manual.
1.2 Maximum Oil Inlet Temperature Range oC (oF):
Sea Level to
9144m (30000 ft)
Above
9144m (30000 ft)
Fan Gearbox Inlet
maximum
127 (260) 140 (284)
Accessory Gearbox
maximum
149 (300) 157 (315)
1.3 Fuel Inlet Temperature oC (oF):
Maximum 57 (135) with a vapour volume to liquid volume ratio (V/L) equal to 0.45.
Minimum -54 (-65) with fuel at a viscosity of 12 centistokes or less during starting.
For use of anti-icing additives and limitations for installation with and without fuel heaters and which may
or may not extract motive flow for aircraft injector systems refer to the applicable engine installation
manual.
2. Maximum Permissible Rotor Speeds:
High Pressure Rotor (N2) rpm (%) Low Pressure Rotor (N1)
rpm (%) All models except TFE731-50R TFE731-50R
Take off 21000 (100) 31485 (100) 31800 (101)
Maximum Continuous 21000 (100) 31485 (100) 31800 (101)
Transient (10 seconds
maximum duration)
21105 (100.5) 31957 (101.5) 32277 (102.5)
3. Pressure Limits:
3.1 Fuel Pump Inlet pressure:
Minimum absolute pressure: 34.47 kPa (5 psi) above the true vapour pressure of the fuel used.
Maximum gauge pressure: 344.74 kPa (50 psi).
TCDS IM.E. 011 TFE731-20, -40, -50, -60 series engines Page 8
Issue 5, 27 May 2010 Models -20, -20AR, -20BR, -20R,
-40, -40R, -40AR, -50R, -60
3.2 Oil Pressure Limits:
Normal operating gauge pressure: 448.16 - 551.58 kPa (65-80 psi)
Minimum gauge pressure at idle: 344.74 kPa (50 psi)
4. Installation Assumptions:
The installation assumptions are quoted in the applicable Engine Installation Manual.
5. Dispatch Limitations:
TFE731-20,-20AR,-20BR,-20R,-40,-40R, -40AR, -50R and –60 engines are not herein approved for Time Limited
Dispatch with the electronic control system inoperative (manual mode).
For installed engines, consult the applicable Engine Installation Manual and aircraft MMEL.
V
. Operating and Service Instructions
TFE731-20,-20AR,
-20BR,-20R
TFE731-40, -40R,
-40AR
TFE731-50R TFE731-60
Installation Manual IM-8300 IM-8010 IM-8024 IM-8009
Operating Instructions IM-8300 IM-8010 IM-8024 IM-8009
Light Maintenance Manual Report No. 72-03-06 (See Note 3)
Heavy Maintenance Manual Report No. 72-03-07
Service Bulletins Published as required
VI. Notes
Note 1: Ratings
The thrust ratings are based on static test stand operation under the following conditions:
(a) No loading of accessory drives
(b) No compressor bleed airflow
(c) Bellmouth inlet conforming to Honeywell International Inc drawing SKP 17308 for the TFE 731-
20/20AR/20BR/20R and -40/40R/40AR, SKP 23600 for the TFE731-50R, and 5837113 for the
TFE731-60.
(d) Fan exhaust and turbine exhaust nozzles conforming to Honeywell International Inc drawing
SKP 23199 for the TFE 731-40/40R/40AR, SKP 23202 for the TFE731-60, SKP 23196 for the
TFE 731-20/20AR/20BR/20R and SKP 24973 for the TFE731-50R.
(e) No anti-icing airflow
(f) Interstage Turbine Gas Temperature (ITT) and rotor speed limits not exceeded.
(g) Dry inlet air
Note 2: For additional authorised operation and installation detailed information, refer to FAA approved
sections of the applicable engine Installation Manual.
Note 3: Certain engine parts are life-limited. These limits are published in the Light Maintenance Manual,
Chapter 5, and referenced in the Honeywell International Inc Service Bulletin TFE 731-72-5101.
Note 4: The engine weight shown is that of the power section and all components coded "E" in the Engine
Equipment List. The total engine weight, including the weight of items coded "A" in the Engine
Equipment List is included on the engine installation drawing for each specific aircraft configuration.
Note 5: Variations in engine configuration and installation components are identified by a suffix to the basic
model number on the engine nameplate, ie TFE 731-60-XX, and an Engine Equipment List number.
Certain features of these components are influenced by aircraft design considerations. In the Engine
Equipment List, those items coded "E" are basic engine items as defined in JAR-E as Group 1
Equipment. Items coded "A" have been demonstrated as compatible with the basic engine during
TCDS IM.E. 011 TFE731-20, -40, -50, -60 series engines Page 9
Issue 5, 27 May 2010 Models -20, -20AR, -20BR, -20R,
-40, -40R, -40AR, -50R, -60
engine certification testing. However, operation, functioning, and performance of these in a specific
aircraft installation must be demonstrated during aircraft certification. Subsequent design control
associated with these factors is the responsibility of the aircraft manufacturer.
Note 6: Power setting, power checks and control of engine thrust output in all operations is to be based on
Honeywell International Inc engine charts referring to low pressure rotor speed (N1). Speed sensors
are included in the engine assembly for this purpose.
Note 7: The TFE 731-20/20AR/20BR/20R engines are approved for use with the Nordam (formerly Dee
Howard Company) thrust reverser designated TR 5045.
The TFE 731-40R and -40AR engines are approved for use with the Nordam thrust reverser
designated TR 5040AS.
The TFE 731-40 engine is approved for use with the Dassault (formerly Alenia) thrust reverser
designated F50B-583-D3.The TFE 731-60 engine is approved for use with the Dassault thrust reverser designated FGFB-583-
D1.
The TFE731-50R is approved for use with the Nordam thrust reverser designated TR5050.
Note 8: The software contained in the DEEC has been designed and developed in accordance with
RTCA/DO178B, criticality Level A.
Note 9: The normal 5-minute take off time may be extended to 10 minutes for engine-out contingencies.

Espero que con esto alcance para demostrar que nuestro querido PAMPA no utiliza un motor especialmente echo para él.

sAludos

Asi es...un motor "civilacho" en un entrenador militar avanzado, con todos los pro y contras que ello significa.

Pero es lo que hay....

Alguién podría traducir lo expuesto, aunque sea brevemente

Muchas gracias.

Sigo emperrado en mostrarles a nuestros miembros e invitados, que el TFE 731-40, NO es un motor especialmente fabricado para el Pampa, sino que es un motor desarrollado por la propia empresa, en afan de darle una versión moderna, de control digitalizado y optimizada, para el lógico reemplazo de los viejos motores TFE731-20, que circulan por el mundo






Ahora pregunto ¿Fuentes? ¿Cuales las que hacen agua?
Derrapeitor JC.
Suerte con la cobranza

Gracias Marcelo por tú atención y muy buena la aclaración, en el foro aviacionargentina.net se decia que estos motores como eran en pedidos muy chicos se tardaba en entregar de ahí que se debia trabajar en lo cascarones para luego colocar los motores una ves que vengan.

Un abrazo Marce