# TCDS E25NE: Rolls-Royce Deutschland Ltd & Co KG

- Type: Type certificate data sheet
- Status: Current
- Holder: Rolls-Royce Deutschland Ltd & Co KG
- Revision: 12
- Revised: December 17, 2014
- Product: Engine
- Certification basis: Part 21, Part 33, Part 34
- Registered aircraft: 287, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/c9/10/c910a18a19b47ef4848a0cd92a5f42b1ed397ad77d50f23f6f94bd8c13338905
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/EF03510ABFC40C6F86257DC6006730FA.0001
- Page: https://openairdocs.org/tcds/E25NE

## Models (5)

As the data sheet lists them.

- TAY 651-54
- TAY 650-15
- TAY 611-8C
- TAY 620-15
- TAY 611-8

## 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. 12 12 12 12 12 12 11 12 12 11 
   LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
                 "---" NOT APPLICABLE 
NOTICE:  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 
 
E25NE 
 
 
TCDS NUMBER E25NE 
 
REVISION:  12* 
 
DATE:   December 17, 2014 
 
ROLLS-ROYCE DEUTSCHLAND Ltd & Co KG 
 
MODELS:        
 
TAY 611-8 
TAY 620-15 
TAY 651-54 
TAY 650-15 
TAY 611-8C 
 
Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E25NE) 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: Rolls-Royce Deutschland Ltd & Co KG 
    Eschenweg 11, Dahlewitz 
    15827 Blankenfelde-Mahlow  
Germany 
    (Formerly Rolls-Royce plc, Derby, England) 
 
I. MODELS                (TAY) 620-15 611-8 650-15 651-54 611-8C 
TYPE Dual rotor, axial flow high bypass turbofan, single-stage fan, three-stage low pressure 
compressor, 12-stage high pressure compressor, 10 cannular combustion chambers, two-stage 
high pressure turbine, and three-stage low pressure turbine. 
RATINGS  
 
   Maximum continuous at sea 
      level, static thrust, lb 
 
   Takeoff (5 min.) at sea 
     level, static thrust, lb 
 
   Takeoff (10 min. OEI) at  
      sea level, static thrust, lb 
 
 
 
13,475 
 
 
13,850 
 
 
13,850 
 
 
 
12,420 
 
 
- - 
 
 
- - 
 
 
 
14,000 
 
 
15,100 
 
 
15,100 
 
 
 
- - 
 
 
15,400 
 
 
15,400 
 
 
 
12,420 
 
 
13,850 
 
 
13,850

TCDS   E25NE           PAGE 2 
 
I. MODELS (CONT.)   (TAY) 620-15 611-8 650-15 651-54 611-8C 
 
COMPONENTS* 
 
FADEC:  EEC  Goodrich (1)P/N 
 
  Fuel control:   Goodrich (1) 
 or:   Goodrich (1) P/N 
 or:   Goodrich (1) P/N 
 or:   Goodrich (1)P/N 
 
 
  Fuel pump (LP): 
     FR-HiTemp (2) P/N 
 
  Fuel pump (HP):  Goodrich P/N 
 
  Ignitor Plugs:  Smiths P/N 
   or:  Smiths P/N 
 
   or:  Champion (3) P/N 
   or:  Champion  (3) P/N 
 
 
N/A 
 
CASC501 
CASC512 
 
 
 
 
 
BP230/6 MK5 
 
GD500 
 
1401/RIG 1 
1401/RIG 2 
 
Y183-5 
 
 
N/A 
 
CASC504 
CASC514 
CASC515 
CASC516 
 
 
 
BP230/6 MK5 
 
GD501 
 
1401/RIG 1 
1401/RIG 2 
 
Y183-5 
 
 
N/A 
 
CASC506 
CASC508 
CASC509 
 
 
 
 
BP230/6 MK5 
 
GD501 
 
1401/RIG 1 
1401/RIG 2 
 
Y183-5 
Y183-6 
 
 
N/A 
 
CASC510 
CASC506 
CASC508 
 
 
 
 
BP230/6 MK5 
 
GD501 
 
1401/RIG 2 
 
 
Y183-5 
Y183-6 
 
 
TEEC2000-04-AE 
 
FMU1101 & 
TMB101 
 
 
 
 
 
BP230-6 MK5 
 
GD502 
 
 
 
 
Y183-5 
* or later approved standards 
(1)  formerly TRW and Lucas 
(2)  formerly Bae Systems & Plessey 
(3)  formerly Auburn 
 
      
PRINCIPAL DIMENSIONS, IN. 
  Length, front flange to rear 
     flange 
  Maximum diameter, encircling  
     diameter 
 
94.75 
 
70.72 
 
- - 
 
- - 
 
 
- - 
 
- - 
 
- - 
 
- - 
 
- - 
 
- - 
WEIGHT (dry) (lbs.) 3,310 3,255 3,516 3,590 3,390 
 Basic engine with all essential accessories necessary for engine operation, but excludes intake, jet 
pipe, and nozzle assembly and hydraulic pumps.  Starter is included for models TAY 620-15, 650-
14, 650-15, and 651-54. 
CENTER OF GRAVITY, IN. 
 Aft front suspension centerline 
 Below engine centerline 
 Starboard from engine centerline 
 
13.8 
3.4 
0.6 
 
- - 
2.9 
0.4 
 
14.2 
3.3 
0.6 
 
14.5 
3.5 
- - 
 
14.3 
2.1 
-0.8 
 
FUEL  See NOTE 10 
OIL  See NOTE 11 
Oil Capacity 13.6 Liters/5.1 Liters usable

TCDS   E25NE           PAGE 3 
CERTIFICATION BASIS Tay 611-8, Tay 620-15, Tay 650-15 and Tay 651-54: 
  
14 CFR 21.29 and part 33 effective Feb. 1, 1965, amended by 14 CFR 33-1 through 14 CFR 33-
9  and 14 CFR part 34, amendment 5, effective 12/31/2012  
  
Pursuant to 14 CFR 21.29(a)(1)(ii), Type Certificate E25NE was issued in validation of the 
British Civil Aviation Authority's certification of compliance with BCAR standards, which were 
found to provide a level of safety equivalent to the above "Certification Basis", as follows: 
  
Airworthiness and Environmental Protection Requirements: 
JAR-E, Change 6, dated August 28, 1981 (BCAR Section C, Issue 13) 
Emissions: ICAO Annex 16, Volume II, First Edition, 1981 
 
Special Conditions: 
Blue Paper C798, C3-4, 6.6.4 – “Endurance Tests, Temperatures (Hot Oil Running)” 
 
TAY 611-8C: 
14 CFR 21.29 and part 33, effective Feb. 1, 1965, amended by 14 CFR 33-1 through 14 CFR 33-
9, § 33.28, Amendment 15, § 33.76, Amendment 20, § 33.78, Amendment 19, § 33.88, 
Amendment 18 and 14 CFR part 34, amendment 5, effective 12/31/2012.  See note 13 for 
detailed summary of the certification basis for fuel venting and exhaust emissions. 
 
Pursuant to 14 CFR 21.29(a)(1)(ii), Type Certificate E25NE was issued in validation of the 
British Civil Aviation Authority's certification of compliance with BCAR standards, which were 
found to provide a level of safety equivalent to the above "Certification Basis", as follows: 
 
Airworthiness and Environmental Protection Requirements: 
JAR-E, Change 6 
JAR-E, Change 10, E20 and E25 
JAR-E, Change 10 for all new parts of the engine control system and its associated accessories 
ICAO Annex 16, Volume II, Second Edition, July 1993 – Emissions and venting 
Later compliance has been shown with CS-34 in accordance with ICAO Annex 16, Volume II, 
Third Edition 2008 incl. Amendment 6 –Aircraft Engine Emissions (approved 29/06/2011) 
 
Special Conditions: 
JAR-E790 at Change 10, Ingestion of Rain and Hail 
JAR-E540 and E800 at Amendment 11, Bird Strike / Ingestion 
JAR-E530(f) at Change 10 and AMJ 20X- 1, EEC Fire & Overheat Protection 
 
Equivalent Safety Findings: 
JAR-E, Change 6, C3-4, Paragraph 6, 150 hour endurance test 
JAR-E, Change 6, C3-4, Paragraph 2.2.1 and JAR-E, Change 10, E640(b)(1), static pressure tests  
JAR-E, Change 6, C3-4, Paragraph 22, Compressor and turbine rotor integrity tests 
 
  DATE OF  DATE TC ISSUED          DATE  TC  
MODEL  APPLICATION    OR REVISED         CANCELLED 
 
TAY 610-8 MAR 06, 1984   OCT 30, 1986         OCT 21, 2002 
TAY 620-15 MAR 06, 1984   OCT 30, 1986 
TAY 611-8 SEP 09, 1987   OCT 15, 1987 
TAY 611-8B MAY 02, 1989   JUN 30, 1989         OCT 21, 2002 
TAY 650-14 JAN 26, 1988   MAR 16, 1990         OCT 21, 2002 
TAY 650-15 JUN 02, 1987   OCT 05, 1988 
TAY 651-54 MAR 20, 1991   MAY 20, 1992 
TAY 611-8C DEC 12, 2001   MAR 5, 2003 
 
The aviation authority for Germany, Luftfahrt-Bundesamt, type certificated this engine.  The 
FAA validated this product under U.S. Type Certificate Number E25NE. Effective September 
28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on 
behalf of Germany.

TCDS   E25NE           PAGE 4 
 
IMPORT REQUIREMENTS 
 
 
To be considered eligible for installation on U.S. registered aircraft, each new engine to be 
exported to the United States with Luftfahrt-Bundesamt (Germany) or EASA airworthiness 
approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Authorized Release 
Certificate.  The JAA or EASA Form 1 should state that the engine conforms to the type design 
approved under the U.S. Type Certificate E25NE, is in a condition for safe operation and has 
undergone a final operational check. 
 
Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification 
of Civil Aircraft, Engines, Propellers, and Related Products, Imported into the United States. 
 
 
 
NOTES 
 
I. MODELS    (TAY) 620-15 611-8 650-15 651-54 611-8C 
 
NOTE 1. MAXIMUM PERMISSIBLE ENGINE OPERATING SPEEDS (See NOTES 8, 14, and 18) 
 Models 611-8, 611-8C 100% HP=12,484 rpm, 100% LP=8,393 rpm 
 Models 620-15, 650-15, 651-54 100% HP=12,136 rpm, 100% LP=8,393 rpm 
LOW PRESSURE ROTOR 
(N1) 
  Takeoff (5 min.) 
  Takeoff (10 min. OEI) 
  Maximum continuous 
  Transient (20 sec.) 
 Maximum for  reverse thrust 
 
 
8,100 
8,100 
8,100 
8,343 
 
 
8,015 
8,015 
8,015 
8,250 
 
 
 
- - 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
8,100 
5,457 
 
HIGH PRESSURE ROTOR 
(N2) 
  Takeoff (5 min.) 
  Takeoff (10 min. OEI) 
  Maximum continuous 
  Transient (20 sec.) 
  Minimum idle, ground 
   and flight 
  Maximum for reverse 
   thrust 
 
 
12,560 
12,560 
12,197 
12,937 
5,813 
 
11,602 
 
 
12,446 
12,446 
12,172 
12,809 
5,818 
 
11,485 
 
 
 
12,560 
12,560 
12,197 
12,937 
5,813 
 
11,310 
 
 
12,670 
12,670 
- - 
- - 
- - 
 
11,650 
 
 
12,560 
12,560 
12,172 
12,684 
6,130 
 
N/A 
  
Operational Limitations: 
 
 Tay 
611-8 
Tay 620-15 Tay   650-15 Tay 651-54 Tay 611-8C 
Static Ground Running 
and Taxiing 
  Stabilized operation is not permitted in the 
Low Pressure rotor speed (N1) range 57% 
to 75% LP during all static ground running 
operations in forward thrust, and during 
taxiing. It is permitted to pass through this 
range whilst increasing or decreasing thrust. 
During static 
ground running the 
park brake must be 
used. For ground 
checks with the 
aircraft stationary 
and during taxiing 
the use of reverse 
thrust is limited to 
idle.

TCDS   E25NE           PAGE 5 
Reverse Thrust  Stabilized 
operation is not 
permitted in 
the Low 
Pressure rotor 
speed (N1) 
range 54% to 
72% 
Stabilized 
operation is not 
permitted in the 
Low Pressure 
rotor speed (N1) 
range 57% to 
75%  
Stabilized operation at 
any intermediate 
position between idle 
and maximum reverse 
thrust is prohibited  
 
Take-off    For take-off, the thrust 
levers must be initially 
being set to 1.15 
Engine Pressure Ratio 
(EPR) or below, then 
set the required take-
off EPR between 40 
and 80 kts forward 
speed  
 
Powerback The use of powerback is prohibited. 
See applicable Operating Instructions identified in note 12 for a complete list of operating limitations 
 
NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES (See NOTE 14) 
TURBINE GAS TEMP. Measured at first stage low pressure turbine nozzle guide vane 
 oC/oF oC/oF oC/oF oC/oF °C/°F 
 Takeoff (5 min.) 
 Takeoff (10 min. OEI) 
 Maximum continuous 
 Overtemperature (20 sec.) 
 Starting, ground (2 sec.) 
 Starting, inflight (2 sec.) 
800/1472 
800/1472 
735/1355 
820/1508 
700/1292 
780/1436 
- - 
- - 
715/1319 
- - 
- - 
- - 
850/1562 
850/1562 
795/1463 
870/1598 
740/1364 
780/1436 
865/1589 
865/1589 
- - 
885/1625 
- - 
- - 
800/1472 
800/1472 
715/1319 
820/1508 
700/1292 
- - 
  
FUEL TEMPERATURE Measured at inlet to high pressure stage of fuel pump (See NOTE 10) 
 oC/oF oC/oF oC/oF oC/oF °C/°F 
 Continuous operation 
 Transient operation (15 min.) 
90/194 
120/248 
- - 
- - 
95/203 
130/266 
- - 
- - 
- - 
- - 
  
OIL INLET 
TEMPERATURE 
Measured at oil pump exit (See NOTE 11) 
 oC/oF oC/oF oC/oF oC/oF °C/°F 
 Continuous operation 
 Transient operation (15 min.) 
105/221 
120/248 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
120/248 
  
NOTE 3. FUEL AND OIL PRESSURE LIMITS / ALL MODELS 
FUEL Measured at inlet to low pressure stage of fuel pump 
  Minimum operation 
  Minimum starting 
  Maximum 
12 psia or 6 psi above tank pressure, which ever is lower, but not less than 2 psig 
10 psia 
40 psig 
OIL Measured at oil pump exit. 
  Minimum for takeoff 
  Maximum continuous 
  Idle to 9500 rpm (1) 
30 psig 
25 psig 
16 psig 
 
 (1) Oil pressure increase follows a straight line relationship between 9500 rpm N2 
 and maximum continuous condition.

TCDS   E25NE           PAGE 6 
 
I. MODELS    (TAY) 620-15 611-8 650-15 651-54 611-8C 
NOTE 4. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTIONS 
 Compressor air bleed may be used in accordance with Rolls-Royce instructions such that the 
operating limitations are not exceeded, up to either the individual or combined non-dimensional 
bleed extraction defined.  Bleed air for nose cowl anti-icing is included. 
  T1 = total temperature at engine intake (K) 
 P1 = total pressure at engine intake (psia) 
 M7 = HP stage 7 offtake mass flow (lb/sec) 
M12 = HP stage 12 offtake mass flow (lb/sec) 
 MT = M7+M12 offtake mass flow (lb/sec) 
 MF = LP (fan) offtake mass flow (lb/sec) 
7th-Stage HPC Bleed 
((M7)(T1**.5))/P1 
  Maximum takeoff 
  Maximum continuous 
    and below 
12th-Stage HPC Bleed 
((M12)(T1**.5))/P1 
  Maximum takeoff 
  Maximum continuous 
   and below 
HPC Total Bleed 
((MT)(T1**.5))/P1 
  Maximum takeoff  (a) 
  Maximum continuous 
   and below           (b) 
Fan Bleed ((MF)(T1**.5))/P1 
  Maximum takeoff 
  Maximum continuous 
   and below 
 
 
7.0 
7.0 
 
 
 
--- 
10.0 
 
 
 
7.0 
 
10.0 
 
10.5 
10.5 
 
 
- - 
- - 
 
 
 
- - 
- - 
 
 
 
- - 
 
- - 
 
-- 
-- 
 
 
- - 
- - 
 
 
 
- - 
- - 
 
 
 
- - 
 
- - 
 
6.5 
6.5 
 
 
9.69 
9.10 
 
 
 
- - 
12.9 
 
 
 
9.69 
 
12.9 
 
14.51 
13.94 
 
 
7.0 
7.0 
 
 
 
- - 
6.9 
 
 
 
7.0 
 
10.0 
 
10.5 
10.5 
 (a) For maximum takeoff, the bleed air may be extracted from 7th stage only. 
(b) For maximum continuous, the bleed air may be extracted either from 12th 
 stage or from combination of 7th and 12th stages. 
 
NOTE 5. BASIS OF RATINGS 
 
Use of the 10-minute one engine inoperative (OEI) takeoff rating is approved for use only in the 
event of an inoperative engine(s) due to shutdown or failure, and is limited to periods of not more 
than 10-minutes.  Takeoff thrust under normal conditions, i.e. when all engines are operative, is 
limited to periods of not more than 5-minutes. 
 
Ratings are based on static test stand operation under the following conditions: 
(a) compressor inlet air at 15°C (59°F) and 29.92 in-Hg 
(b) Rolls-Royce test bed flaremeter TA1, TA2 or TA3 (ATF9476) for the TAY 611-8 and 
 620-15 and TA10 or TA11 (ATF10173) for the TAY 650-15, 651-54 and 611-8C. 
(c) Rolls-Royce Jet Pipe/Final Nozzle Assembly JP2 or JP3 (ATF9786) for the TAY 611-8 
 and 620-15, 650-15 and 651-54 and JP4 or JP5 (ATF9786) for the TAY 611-8C. 
(d) turbine gas temperature measured by 9 pairs of thermocouples mounted in 
 the first stage low pressure turbine nozzle guide vane (NGV) with ballast 
 resistor, specified in the applicable engine manual 
(e) no aircraft accessory loads or bleed air extraction 
(f) turbine gas temperature limits and engine rotor speed limits are not exceeded 
(g) 100% air intake recovery

TCDS   E25NE           PAGE 7 
 
NOTE 6.  ACCESSORY DRIVE PROVISIONS 
 
 
DRIVE 
 
 
Rotation 
Speed Ratio 
To HP 
Rotor Speed 
TORQUE (lb - in) 
 
Maximum Continuous      Instantaneous 
 
Overhang 
(lb - in) 
Starter 
   All models 
Main Hydraulic pump  
   611-8 /611-8C 
   620-15 / 650-15 
   651-54 
Auxiliary hydraulic pump 
   620-15 / 650-15 
IDG 
   620-15 / 650-15 
   611-8C 
AC generator 
   611-8 
 
CSD and alternator 
   651-54 
 
CW 
 
CCW 
CCW 
CW 
 
CW 
 
CW 
CW 
 
CCW 
 
 
CW 
 
1.0398 
 
0.2615 
0.3397 
0.2880 
 
0.3176 
 
0.5088 
0.5088 
 
0.8821 
 
 
0.6846 
 
2592 
 
732 
461 
732 
 
176 
 
659 
659 
 
500 
 
 
1230 
 
2981 
 
3000 
1455 
3000 
 
500 
 
4286 
7140 
 
2310 
 
 
5900 
 
153 
 
140 
36 
140 
 
11 
 
743 
743 
 
250 
 
 
2154 
 NOTES:   CW = clockwise, looking into the appropriate gearbox face 
              CCW = counter-clockwise 
  
NOTE 7.  Thrust setting, thrust check and control of engine output in all operations are to be based on Rolls-
Royce engine charts included in the relevant operating instructions.  On the hydromechanically 
controlled engines, pressure ratio (EPR) indication is not reliable as the primary thrust setting 
parameter due to the EPR probe's susceptibility to icing.  N1 thrust setting procedures must be used 
for the TAY 620-15 model unless the EPR probes are modified in accordance with Rolls-Royce 
Service Bulletins 75-1036 and 75-1055 or the equivalent and with appropriate EPR thrust setting 
charts. 
 
NOTE 8. For inflight operation during icing conditions, the minimum allowable fan speed (N1) for the TAY 
611-8C is 21.1% (1770rpm) and for the other variants is 21% (1760 rpm). 
 
NOTE 9. Certain engine parts are life-limited.  These parts are listed in time limit section of the relevant 
Engine Manuals.  Maintenance is to be carried out in accordance with the manual (See NOTE 12). 
 
NOTE 10. Approved fuels and fuel additives are listed in the appropriate Rolls-Royce Operating Instructions 
(See NOTE 12.) 
 
For the TAY 611-8 and 651-54 and 611-8C, minimum fuel temperature measured at inlet to low 
pressure stage of fuel pump is -40°C (-40°F). 
 
For the TAY 620-15 and 650-15, minimum fuel temperature measured at inlet to low pressure stage 
of fuel pump is -50°C (-58°F). 
 
NOTE 11. Approved oils are listed in the appropriate Rolls-Royce Operating Instructions (See NOTE 12).  Oils 
of the approved types when reclaimed to the approved Rolls-Royce standards are approved for use.  
Minimum oil temperatures, measured at oil pump exit, are as follows: 
 
  MINIMUM OIL TEMPERATURE 
              ACCELERATION 
       STARTING           FROM IDLE 
 TAY MODEL oC oF oC oF 
 611-8 / 611-8C 
620-15 / 650-15 
651-54 
-40 
-50 
-40 
-40 
-58 
-40 
-30 
-30 
-30 
-22 
-22 
-22

TCDS   E25NE           PAGE 8 
 
NOTE 12. TAY MODEL OPERATING 
INSTRUCTIONS 
MAINTENANCE 
MANUAL 
ENGINE 
MANUAL 
INSTALLATION 
MANUAL 
  
611-8 
 
620-15 
 
650-15 
 
651-54 
 
611-8C 
 
F-TAY-1RR 
 
F-TAY-2RR 
 
F-TAY-3RR 
 
F-TAY-5RR 
 
F-TAY-6RR 
 
M-TAY-1RR 
 
M-TAY-2RR 
 
M-TAY-3RR 
 
M-TAY-5RR 
 
M-TAY-6RR 
 
E-TAY-1RR 
 
E-TAY-2RR 
 
E-TAY-3RR 
 
E-TAY-5RR 
 
E-TAY-6RR 
 
EL2825 
 
EL1716 
 
EL2823 
 
EL2834 
 
O-TR0817/03 
  
NOTE 13.  
The following emissions standards promulgated in 14 CFR part 34, Amendment 5, effective 
December 31, 2012 and 40 CFR part 87, effective July 18, 2012 have been complied with for the Tay 
611-8C engine model. 
 
Fuel Venting Emission Standards:  14 CFR 34.10(a) and § 34.11; in addition, 40 CFR 87.10(a) and 
§ 87.11. 
 
Smoke Number (SN) Emission Standards:  14 CFR 34.21(e)(2); in addition, 40 CFR 87.23(c)(1). 
 
Carbon Monoxide (CO) Emission Standards:  14 CFR 34.21(d)(1)(ii); in addition, 
40 CFR 87.23(c)(1). 
 
Hydrocarbons (HC) Emission Standards:  14 CFR 34.21(d)(1)(i); in addition, 40 CFR 87.23(c)(1). 
 
Oxides of Nitrogen (NOx) Emission Standards:  14 CFR 34.23(a)(2); in addition, 
40 CFR 87.23(c)(2). 
 
In addition to the FAA’s finding of compliance based on the certification requirements defined in this 
TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 
16, Volume II, Third Edition, Part III, Chapter 2, Section 2.2.2 for SN, Section 2.3.2 for CO and HC, 
Section 2.3.2.d for NOx (also known as CAEP/6), and Part II Chapter 2 for fuel venting have also 
been demonstrated. 
  
NOTE 14. Limits regarding transient rotor shaft overspeed and transient gas temperature and number of 
occurrences are specified in the appropriate Rolls-Royce Maintenance Manual (See NOTE 12). 
 
NOTE 15. The engines are approved for use to the following ambient temperatures in Column 1 and 2 and are 
flat rated to the values in column 3 and 4. 
 
  MAXIMUM 
AMBIENT 
FLAT 
TAKEOFF 
 TAY MODEL oC oF oC oF 
 611-8 
 
620-15 
 
55 
 
55 
131 
 
131 
30 
 
30 
86 
 
86 
 650-15 
 
651-54 
 
611-8C 
55 
 
50 
 
52 
131 
 
122 
 
131 
30 
 
30 
 
30 
86 
 
86 
 
86 
  
NOTE 16. The maximum inlet throat area of the engines including aircraft air intake is limited to 1405 square 
inches for the TAY 611-8C and 1500 square inches for all other variants. 
 
NOTE 17. The maximum engine inlet distortion limit is specified in the appropriate Rolls-Royce Installation 
Manual (See NOTE 12).

TCDS   E25NE           PAGE 9 
NOTE 18. The limits quoted are relative to the engines equipped with one of the following thrust reverser types. 
 
  TAY 611-8: Grumman Aerospace type 1159P41460-1 / -2 
 
  TAY 620-15: Grumman Aerospace type 1159P41530-1 / -2 / -9 /-10 and  
  1159RDP41530-51 / -52. 
 
  TAY 650-15: Grumman Aerospace type 1159RDP41530-7 / -8 / -9 / -10. 
 
  TAY 651-54: Dee Howard thrust reverser type TR6510 with the engine side mount  
  configuration, and Dee Howard jet pipe P/N Qf 781.1000 for center engine  
  mount configuration. 
 
  TAY 611-8C: Nordam thrust reverser P/N 08ND78006-1 for left hand installation and P/N  
                                 08ND78006-2 for right hand installation.  
 
Approval for operation in reverse thrust does not imply approval of the thrust reversers themselves. 
    
 
NOTE 19. These engine models incorporate the following general characteristics: 
 
610-8:  Base Engine with Installation features to suit Gulfstream IV series aircraft. 
  No longer in service. 
 
TAY 620-15: Same as 610-8, except takeoff and maximum continuous static thrust increase  
                                 at sea level flat rated to 86°F ambient temperature.  Installation features to suit 
  Fokker 70 and Fokker 100 series aircraft. 
 
 
TAY 611-8: Same as 610-8, except takeoff static thrust increase at sea level flat rated to  
  86°F ambient temperature.  Installation features to suit Gulfstream IV and 
  IV-SP series aircraft. 
 
 
TAY 650-15: Same as 620-15, except with increased diameter fan, improved combustors,  
  new high pressure turbine blades and vanes, and other minor hardware changes 
  to accommodate higher thrust.  Installation features to suit Fokker 100 series 
  aircraft. 
 
 
TAY 651-54: Same as 650-15, except with installation features and gearbox to suit the 
  Boeing 727-100 series aircraft and either a Dee Howard thrust reverser (side- 
  mounted engines) or a Dee Howard jet pipe P/N Qf 781.1000 (center engine). 
 
TAY 611-8C: Same as 611-8, except with Fan system from TAY 650-15 and the introduction 
  Of a FADEC control system.

TCDS   E25NE           PAGE 10 
NOTE 20. Each of the documents listed below must state that it is approved by the European Aviation Safety 
Agency (EASA) or, for approvals made before September 28, 2003 by Luftfahrt-Bundesamt 
(Germany) or CAA (UK). Any such documents including those approved under a delegated 
authority, are accepted by the FAA and are considered FAA approved, as appropriate. 
 
• Service bulletins, 
• Structural repair manuals, 
• Vendor manuals, 
• Aircraft flight manuals, and 
• Overhaul and maintenance manuals. 
• Technical Variances 
These approvals pertain to the type design only 
 
 
----END----
```

## ADs (35, in force first)

- [AD 2022-26-05](https://openairdocs.org/ad/2022-26-05): Turbine Engine Combustion Section · Rolls-Royce Deutschland TAY 620-15 and TAY 650-15. Effective Jan 12, 2023
- [AD 2020-23-08](https://openairdocs.org/ad/2020-23-08): Turbine Engine Compressor Section · Rolls-Royce Deutschland TAY 611-8C. Effective Dec 18, 2020
- [AD 2019-14-01](https://openairdocs.org/ad/2019-14-01): Turbine Engine Compressor Section · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Aug 26, 2019
- [AD 2018-17-13](https://openairdocs.org/ad/2018-17-13): Turbine Engine Compressor Section · Rolls-Royce Deutschland TAY 620-15. Effective Oct 16, 2018
- [AD 2017-19-18](https://openairdocs.org/ad/2017-19-18): Turbine Engine Compressor Section · Rolls-Royce Deutschland TAY 620-15. Effective Oct 31, 2017
- [AD 2016-17-01](https://openairdocs.org/ad/2016-17-01): Stage 1 HPT disks · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Sep 27, 2016
- [AD 2014-06-05](https://openairdocs.org/ad/2014-06-05): Low-pressure (LP) compressor module · Rolls-Royce Deutschland TAY 620-15, TAY 650-15 and TAY 651-54. Effective May 8, 2014
- [AD 2014-03-16](https://openairdocs.org/ad/2014-03-16): Low-pressure compressor (LPC) fan blades · Rolls-Royce Deutschland TAY 620-15, TAY 650-15 and TAY 651-54. Effective Mar 18, 2014
- [AD 2013-23-01](https://openairdocs.org/ad/2013-23-01): High-pressure (HP) air bleed valve · Rolls-Royce Deutschland TAY 620-15, TAY 650-15 and TAY 651-54. Effective Dec 30, 2013
- [AD 2013-05-19](https://openairdocs.org/ad/2013-05-19): Bolts · Rolls-Royce Deutschland TAY 611-8. Effective Apr 24, 2013
- [AD 2013-06-01](https://openairdocs.org/ad/2013-06-01): Low-pressure compressor (LPC) rotor disc assemblies · Rolls-Royce Deutschland TAY 620-15 and TAY 650-15. Effective Apr 24, 2013
- [AD 2012-27-01](https://openairdocs.org/ad/2012-27-01): Llow-pressure compressor (LPC) fan blades · Rolls-Royce Deutschland TAY 620-15. Effective Jan 25, 2013
- [AD 2012-24-01](https://openairdocs.org/ad/2012-24-01): LPC fan blades · Rolls-Royce Deutschland TAY 620-15. Effective Dec 14, 2012
- [AD 2012-06-17](https://openairdocs.org/ad/2012-06-17): HP turbine stage 2 disc · Rolls-Royce Deutschland TAY 611-8 and TAY 611-8C. Effective Mar 23, 2012
- [AD 2010-17-12 R1](https://openairdocs.org/ad/2010-17-12-R1): Engine · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Nov 18, 2010
- [AD 2010-20-22](https://openairdocs.org/ad/2010-20-22): Disc · Rolls-Royce Deutschland TAY 620-15, TAY 650-15 and TAY 651-54. Effective Nov 9, 2010
- [AD 2007-26-19](https://openairdocs.org/ad/2007-26-19): Low pressure (LP) compressor case · Rolls-Royce Deutschland TAY 611-8, TAY 611-8C, TAY 620-15 and 2 more. Effective Feb 11, 2008
- [AD 2005-26-18](https://openairdocs.org/ad/2005-26-18): High pressure compressor (HPC) stage 12 disc assembly · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Feb 3, 2006
- [AD 2005-03-06](https://openairdocs.org/ad/2005-03-06): LP fuel tubes · Rolls-Royce Deutschland TAY 611-8, TAY 620-15, TAY 650-15 and 1 more. Effective Mar 17, 2005
- [AD 2003-22-14](https://openairdocs.org/ad/2003-22-14): Fan blades · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Dec 18, 2003
- [AD 2003-08-01](https://openairdocs.org/ad/2003-08-01): Rotor discs · Rolls-Royce Deutschland TAY 650-15. Effective May 20, 2003
- [AD 2002-09-02](https://openairdocs.org/ad/2002-09-02): Airworthiness Limitations Section (ALS) - Critical Life-Limited Rotating Engine Part · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Jun 6, 2002
- [AD 99-24-01](https://openairdocs.org/ad/99-24-01): Rolls-Royce Deutschland TAY 620-15, TAY 650-15 and TAY 651-54. Effective Jan 18, 2000
- [AD 2010-17-12](https://openairdocs.org/ad/2010-17-12) (historical): Low- pressure turbine disks · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Sep 27, 2010
- [AD 2009-22-01](https://openairdocs.org/ad/2009-22-01) (historical): Low-pressure turbine disk stage 2 or stage 3 · Rolls-Royce Deutschland TAY 650-15. Effective Nov 12, 2009
- [AD 2008-10-14](https://openairdocs.org/ad/2008-10-14) (historical): Excessively corroded low pressure turbine disks stage 2 and stage 3 · Rolls-Royce Deutschland TAY 650-15. Effective Jun 25, 2008
- [AD 2007-03-02](https://openairdocs.org/ad/2007-03-02) (historical): LP compressor fan blades · Rolls-Royce Deutschland TAY 611-8, TAY 620-15, TAY 650-15 and 1 more. Effective Mar 5, 2007
- [AD 2006-18-14](https://openairdocs.org/ad/2006-18-14) (historical): Cyclic life of stage 1 HPT discs, and stage 1 LPT discs · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Oct 13, 2006
- [AD 2004-26-10](https://openairdocs.org/ad/2004-26-10) (historical): Ice-impact Panels Installed in the Low Pressure (LP) Compressor Case · Rolls-Royce Deutschland TAY 611-8, TAY 620-15, TAY 650-15 and 1 more. Effective Jan 21, 2005
- [AD 2004-05-22](https://openairdocs.org/ad/2004-05-22) (historical): Low pressure (LP) compressor case · Rolls-Royce Deutschland TAY 611-8, TAY 611-8C, TAY 620-15 and 2 more. Effective Mar 25, 2004
- [AD 2003-05-04](https://openairdocs.org/ad/2003-05-04) (historical): Low pressure (LP) fuel tubes · Rolls-Royce Deutschland TAY 611-8, TAY 620-15, TAY 650-15 and 1 more. Effective Mar 26, 2003
- [AD 2002-24-06](https://openairdocs.org/ad/2002-24-06) (historical): Low pressure (LP) fuel tubes · Rolls-Royce Deutschland TAY 620-15 and TAY 650-15. Effective Dec 18, 2002
- [AD 2002-01-29](https://openairdocs.org/ad/2002-01-29) (historical): High Pressure Compressor (HPC) Stage 11/12 Disc Spacer · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Feb 15, 2002
- [AD 2001-22-18](https://openairdocs.org/ad/2001-22-18) (historical): Fan Blades · Rolls-Royce Deutschland TAY 650-15 and TAY 651-54. Effective Dec 18, 2001
- [AD 2000-08-01](https://openairdocs.org/ad/2000-08-01) (historical): Turbine Disks · Rolls-Royce Deutschland TAY 650-15. Effective Jun 19, 2000

## Registered aircraft by registry model (OpenAirDocs)

- [Rolls-Royce TAY-611-8C](https://openairdocs.org/engine/rolls-royce-tay-611-8c): 229 aircraft (registry code 54073)
- [Rolls-Royce TAY-611-8](https://openairdocs.org/engine/rolls-royce-tay-611-8): 56 aircraft (registry code 54072)
- [Rolls-Royce TAY-651-54](https://openairdocs.org/engine/rolls-royce-tay-651-54): 2 aircraft (registry code 54564)
- [Roll-Royc TAY-620-15](https://openairdocs.org/engine/roll-royc-tay-620-15): 0 aircraft (registry code 04564)
- [Rolls-Royce TAY-620-15](https://openairdocs.org/engine/rolls-royce-tay-620-15): 0 aircraft (registry code 54071)
- [Rolls-Royce TAY-650-15](https://openairdocs.org/engine/rolls-royce-tay-650-15): 0 aircraft (registry code 54557)

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.