TYPE-CERTIFICATE DATA SHEET · Pressure Transmitter, Blow-off P1/P2 Switch, Oil Tank Pressurising Valve, Starter Generator (Starter Aspects Only), Anti-icing valve, Thrust Limiter,

TCDS No.: E.236 Rolls-Royce Deutschland Ltd & Co KG Issue: 01 Viper series engines Date: 21 February 2019

TE.CERT.00052-001 © European Union Aviation Safety Agency, 2019. All rights reserved. ISO9001 Certified. Page 1 of 12 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

An agency of the European Union

TYPE-CERTIFICATE DATA SHEET

EASA.E.236

for Viper series engines

Type Certificate Holder Rolls-Royce Deutschland Ltd & Co KG

Eschenweg 11 Dahlewitz

15827 Blankenfelde-Mahlow Germany

For Models: Viper 521 Viper 522 Viper 601-22




Intentionally left blank




TABLE OF CONTENTS

I. General ................................................................................................................................................. 4 1. Type/ Model ......................................................................................................................................... 4 2. Type Certificate Holder ......................................................................................................................... 4 3. Manufacturer ....................................................................................................................................... 4 4. Date of Application ............................................................................................................................... 4 5. Certification Reference Date ................................................................................................................. 4 6. EASA Type Certification Date ................................................................................................................. 4 II. Certification Basis ................................................................................................................................. 5 1. EASA Certification Basis ........................................................................................................................ 5 1.1. Airworthiness Standards .................................................................................................................... 5 1.2. Special Conditions (SC) ....................................................................................................................... 5 1.3. Equivalent Safety Findings (ESF) ......................................................................................................... 5 1.4. Deviations .......................................................................................................................................... 5 1.5. Environmental Protection................................................................................................................... 5 III. Technical Characteristics ...................................................................................................................... 5 1. Type Design Definition .......................................................................................................................... 5 2. Description ........................................................................................................................................... 6 3. Equipment ............................................................................................................................................ 6 4. Dimensions (mm) .................................................................................................................................. 6 5. Dry Weight (kg) ..................................................................................................................................... 7 6. Ratings ................................................................................................................................................. 7 7. Control System ..................................................................................................................................... 7 8. Fluids (Fuel, Oil, Coolant, Additives) ...................................................................................................... 7 9. Aircraft Accessory Drives ....................................................................................................................... 7 10. Maximum Permissible Air Bleed Extraction .......................................................................................... 8 IV. Operating Limitations .......................................................................................................................... 8 1. Temperature Limits ............................................................................................................................... 8

1.1 Exhaust Gas Temperature (°C) ............................................................................................................... 8

1.2 Oil Inlet Temperature (C) ...................................................................................................................... 9

1.3 Fuel Inlet Temperature (C) .................................................................................................................... 9 1.4 Climatic Operating Envelope ................................................................................................................ 10

2. Rotational Speed Limits (%) ................................................................................................................. 10 3. Pressure Limits.................................................................................................................................... 10

3.1 Fuel Pressure Limits .............................................................................................................................. 10 3.2 Oil Pressure Limits ................................................................................................................................ 11

4. Time Limited Dispatch ......................................................................................................................... 11 5. ETOPS Capability ................................................................................................................................. 11 V. Operating and Service Instructions ...................................................................................................... 12 VI. Notes ................................................................................................................................................ 12 SECTION: ADMINISTRATIVE ..................................................................................................................... 12 I. Acronyms and Abbreviations................................................................................................................ 12 II. Type Certificate Holder Record ............................................................................................................ 12 III. Change Record ................................................................................................................................... 12




I. General

1. Type/ Model Type: Viper Models: Viper 521, Viper 522, Viper 601-22 2. Type Certificate Holder Rolls-Royce Deutschland Ltd & Co KG Eschenweg 11 Dahlewitz 15827 Blankenfelde-Mahlow Germany DOA ref.: EASA.21J.065 formerly (until 20 February 2019): Rolls-Royce plc 62 Buckingham Gate Westminster London SW1E 6AT United Kingdom former Design Organisation Approval No.: EASA.21J.035 3. Manufacturer Rolls-Royce plc 4. Date of Application Not identified. 5. Certification Reference Date Not identified1

1 As the application date for the individual models could not be identified (see 4.), the reference date for determining the applicable airworthiness

requirements is also not identified.

6. EASA Type Certification Date Viper 521: 13 August 1964 Viper 522: 17 May 1966 Viper 601-22: 21 August 1972




II. Certification Basis

1. EASA Certification Basis 1.1. Airworthiness Standards

Note: Application was made to UK CAA before EASA was established. The applicable airworthiness standards were established in accordance with the rule in the UK at the time of application. The applicable UK CAA TC number is 029/2 for models Viper 521 and Viper 522 and 041 for model Viper 601-22. Up to the issuance of the present TCDS, the applicable UK CAA Type Certificate Data Sheets were as follows:

Viper 521 UK CAA TCDS No. 1025, Issue 15, 30 November 1998

Viper 522 UK CAA TCDS No. 1033, Issue 14, 30 November 1998

Viper 601-22 UK CAA TCDS No. 1038, Issue 08, April 1984

The applicable airworthiness standards are as follows:

Viper 521 BCAR Section C issue 5 dated 1 July 1962

Viper 522 BCAR Section C issue 5 dated 1 July 1962

Viper 601-22 BCAR Section C issue 6 dated 15 June 1966 together with Blue Papers 415, 435, 436, 464, 468, 474, 476, 480, 481, 482, 499, 506, 544, 550 and 551 (paragraph 3.2.2 only)

1.2. Special Conditions (SC) None 1.3. Equivalent Safety Findings (ESF) None 1.4. Deviations None

1.5. Environmental Protection

No environmental protection requirements were applicable at the date of certification.

III. Technical Characteristics

1. Type Design Definition Viper 521: DIS 738 and DIS 739 for Port and Starboard engines respectively, with

modifications CV7038, CV8272 and CV8273 Viper 522: DIS 738 and DIS 751 for Port and Starboard engines respectively, with modifications

CV8272 and CV8273 Viper 601-22: DIS 804 and DIS 805 for Port and Starboard engines respectively




2. Description Turbojet comprising an 8 stage axial compressor, annular combustion chamber, single (Viper 521 and Viper 522) stage or 2 stage (Viper 601-22) axial flow turbine and mechanical control system. 3. Equipment The following equipment is part of the engine Type Design:

Viper 521

Fuel Pump, Flow Control, Air Fuel Ratio Control, Pressure Increasing Valve, Rate Reset Valve, JPT Control Amplifier (airframe mounted), Datum Selector Plug, Oil Filter, LP Fuel Filter, Thermocouple Harness, Thermocouples, Lucas Pressure Control, High Energy Igniter Plugs, Micro Metering Pumps, Solenoid Valve, Alternator (Tachometer), Fuel Low Pressure Warning Switch, Oil Low Pressure Warning Switch, Oil Pressure Transmitter, Fuel Filter Differential Pressure Switch, Blow-off P1/P2 Switch, Glow Plug, Oil Tank Pressurising Valve, Starter Generator (Starter Aspects Only), Anti-icing valve, Oil Temperature Bulb, Synchroniser Corrector Motor

Viper 522

Fuel Pump, Flow Control, Air Fuel Ratio Control, Pressure Increasing Valve, Rate Reset Valve, JPT Control Amplifier and Datum Selector Plug, Oil Filter, Firewire, Lucas Pressure Control, High Energy Igniter Plugs, Micro Metering Pumps, Solenoid Valve, Compacted JPT Harness Assembly, Alternator (Tachometer), Fuel Low Pressure Warning Switch, Oil Low Pressure Warning Switch, Oil Pressure Transmitter, Blow-off P1/P2 Switch, Oil Tank Pressurising Valve, Starter Generator (Starter Aspects Only), Anti-icing valve, Thrust Limiter, Oil Temperature Bulb, Synchroniser Corrector Motor, LP Fuel Filter Assembly

Note: Identification of approved equipment types is given in the Maintenance Manual in the section dealing with the particular system. Notification of any change will be given initially by Service Bulletin.

The engine has been tested satisfactorily with the following equipment fitted:

Viper 521 Hydraulic Pump Lockheed Mk. 9 AIR 111500 AC Generator Rotax 0904 Flowmeter Meterflow M.3/05/0625/B8

Viper 522 Hydraulic Pump Lockheed Mk. 9 AIR 111500 AC Generator Rotax 0904 Flowmeter Meterflow M.3/05/0625/B8 or M.3/05/0625/B8/V

With respect to model Viper 601—22, refer to the Overhaul Manual for engine driven equipment. 4. Dimensions (mm) Overall dimensions are:

Length

(*including front bullet) Width Height

Viper 521 2160.3 716.3 834.4

Viper 522 2160.3 716.3 834.4

Viper 601-22 2893* 731.5 816.6




5. Dry Weight (kg) Viper 521: 366 (left-hand engine) or 362 (right-hand engine) Viper 522: 370 (left-hand engine) or 360 (right-hand engine) Viper 601-22: 379 6. Ratings

Minimum Thrust kN (lbf)

Viper 521 Viper 522 Viper 601-22

Maximum Take-Off Power

13.79 (3100) 14.81 (3330) 16.35 (3675)

Maximum Continuous Power

13.79 (3100) 13.79 (3100) 16.35 (3675)

(See note 1) 7. Control System The engine features a mechanical control system. 8. Fluids (Fuel, Oil, Coolant, Additives) Fuel and Fuel Additives approved for use in Viper 521 and Viper 522 are listed in Rolls-Royce engine handling notes document TP257/BR and TP243/BR respectively. For the Viper 601-22, fuels and fuel additives approved for use are listed in Rolls-Royce Engine Handling Notes Viper 601-22 document. For both the Viper 521 and the Viper 522, the maximum aviation gasoline accumulation quantity which may be used in any one overhaul period is 36.3 m3 (8000 Imperial gallons). For the Viper 601-22 the use of aviation gasoline is restricted to a maximum accumulated time of 25 hours or 28.4 m3 (62590 Imperial gallons). Minimum fuel drainage period after false start is 1 minute. Approved oil types for all models are Aeroshell 500, Royco 500, Aeroshell 560, Royco 560, Arpolube 23699, Mobil Jet II, Castrol 599 and Castrol 580. For models Viper 521 and Viper 522 oil system capacity is 7384 cm3 (13 Imperial Pints), maximum oil tank capacity is 6284 cm3 (11 Imperial Pints) and usable oil is 3976 cm3 (7 Imperial Pints). For model Viper 601-22 total oil tank capacity including expansion space is 9656 cm3 (17 Imperial Pints), maximum oil tank capacity to full is 7384 cm3 (13 Imperial Pints) and usable oil is 5112 cm3 (9 Imperial Pints). For all models, overall maximum oil consumption in flight is 710 cm3 / hr (1.25 Imperial Pints / hr) and overall minimum oil consumption in flight is 511 cm3 / hr (0.9 Imperial Pints / hr). 9. Aircraft Accessory Drives With respect to the Viper 601-22 engine model, refer to the Overhaul Manual for identification of engine-driven equipment.




10. Maximum Permissible Air Bleed Extraction The following compressor air bleeds may be used within the range 40%-100% of the reference speed (see. also 2.):

(a) Maximum for intake an engine de-icing 4% of intake mass flow for Viper 521 and Viper 522 2,5% of intake mass flow or Viper 601-22

(b) Maximum for aircraft services

3,5% of intake mass flow for Viper 521 and Viper 522 3% of intake mass flow for Viper 601-22

IV. Operating Limitations

The following operating limitations are applicable only when the engine is fitted with a light propelling nozzle as defined in the Type Design Definition (see III.1) and when the installed engine instrument accuracies are in accordance with BSEL report PFG/GM/1468, dated 10 August 1964 for the Viper 521, BSEL report PFG/JAW/38050/3 dated 27 January 1966 for the Viper 522 and Rolls-Royce (BED) Report reference RCP/DRL/14900 dated 19 November 1971 for the Viper 601-22.

1. Temperature Limits

1.1 Exhaust Gas Temperature (°C) For the Viper 521 and the Viper 522, the Exhaust Gas Temperature is the mean of 5 thermocouples as defined in the Type Design Definition III.1. For the Viper 601-22, the Exhaust Gas Temperature is the mean of 6 thermocouples as defined in the Type Design Definition III.1.

(a) Viper 521 Maximum during starts: 800* Maximum for take-off and Maximum Continuous: 695 Maximum for ground idling: 610

*Maximum Exhaust Gas Temperature during start up or flight relighting is 800°C provided that 695°C is not exceeded for more than 5 seconds.

(b) Viper 522 Maximum during starts: 800* Maximum for take-off (5 minute limit): 695 Maximum Continuous: 715 Maximum for ground idling: 630




*Maximum Exhaust Gas Temperature during start up or flight relighting is 800°C provided that 740°C is not exceeded for more than 5 seconds.

(c) Viper 601-22 Maximum during starts and relights (5 second limit): 700 Maximum for take-off (5 minute limit): 725 Maximum Continuous: 715 Maximum for ground idling: 550

1.2 Oil Inlet Temperature (C)

(a) Viper 521 Minimum for starting: -40 Minimum for opening up: -26 Maximum (unrestricted): 125 Maximum with anti-icing selected: 135

(b) Viper 522

Minimum for starting: -40 Minimum for opening up*: -26 Maximum (unrestricted): 125 Maximum with anti-icing selected: 135

*Subject to low oil pressure warning light remaining off.

(c) Viper 601-22 Minimum for starting: -26 Minimum for opening up (cold)*: -26 Maximum (unrestricted): 145 *Subject to low oil pressure warning light remaining off.

1.3 Fuel Inlet Temperature (C)

(a) Viper 521 and Viper 522 Maximum with kerosene or wide-cut fuel: 50 Maximum with aviation gasoline: 30

(b) Viper 601-22 with aviation gasoline

Maximum under normal boost pressure: 30 Maximum under suction feed (restriction detailed in Rolls-Royce report RCP/DRL/39654 13 September 1973): 15




(c) Viper 601-22 with any approved fuel other than aviation gasoline

Maximum: 50

1.4 Climatic Operating Envelope

The Viper 522 and the Viper 601-22 may be used in ambient temperatures up to ISA +35°C and the Viper 521 may be used in ambient temperatures up to ISA +30°C. 2. Rotational Speed Limits (%) The following rotational speed limits are expressed in percentage of indicated rpm and 100% indicated rpm correspond to 13760 rpm for all models.

(a) Viper 521 Maximum for take-off and Maximum Continuous: 100 Ground idling at sea level: 40 to 41 Minimum for approach: 60 Maximum over speed (20 second limit): 103

(b) Viper 522

Maximum for take-off (5 minute limit): 100 Maximum Continuous: 98.5 Ground idling at sea level minimum: 40 Minimum for approach: 60 Maximum over speed (20 second limit): 103

(c) Viper 601-22 Maximum for take-off: 100 Maximum Continuous: 100 Ground idling, minimum: 40

3. Pressure Limits 3.1 Fuel Pressure Limits The minimum pressure at engine fuel pump inlet is defined in BSEL report PFG/EJM/51092 for models Viper 521 and Viper 522 as well as RR (BED) Graph reference FSDS 2443 for model Viper 601-22.




3.2 Oil Pressure Limits

(a) Viper 521 and Viper 522 Normal with modification CV7291 and oil temperature up to 80°C*: 145-262 kPa (21-38 lbf/in2)

Normal with modification CV7291 and oil temperature above 80°C*: 103-262 kPa (15-38 lbf/in2) Normal without modification CV7291*: 186-262 kPa (27-38 lbf/in2) * at 95% of reference speed (see also 2.) Minimum to complete flight: 34.5 kPa (5 lbf/in2)

(b) Viper 601-22 Normal at 95% of reference speed (see also 2.) and oil temperature above 60°C: 138-241 kPa (20-35 lbf/in2) Minimum at ground idling (at 40% of reference speed, see also 2.): 69 kPa (10 lbf/in2) Minimum to complete flight: 34.5 kPa (5 lbf/in2)

4. Time Limited Dispatch

The engine is not approved for Time Limited Dispatch.

5. ETOPS Capability

The engine is not approved for ETOPS capability.




V. Operating and Service Instructions

Operating Instructions are part of the aircraft crew manual. Maintenance instructions are part of the aircraft maintenance manual. Overhaul, Viper 521 and Viper 522: Rolls-Royce Viper MK.522 Overhaul Manual Overhaul, Viper 601-22: Rolls-Royce Viper 601-22 Overhaul Manual Performance, Viper 521: PS 198/S/2 Performance, Viper 522: PS218/A

VI. Notes

1. Static sea-level ratings under the following conditions: (a) International standard atmospheric conditions at sea level. (b) All optional air bleeds closed (c) Aircraft service equipment drives unloaded. (d) Test bed Venturi intake pipe Part no. RL.51795/RM.56950 (e) Exhaust cone with integral propelling nozzle together with trimmers as defined in the applicable type

design definition (see III.1.). (f) Exhaust temperature measured by thermocouples defined the applicable type design definition (see

III.1.). (g) 100% indicated rpm corresponding to 13760 rpm. (h) Thrust measured with engine angled on test bed to BSEL drawing RM81236 for models Viper 521 and

Viper 522 and Rolls-Royce drawing V2401 for model Viper 601-22.

SECTION: ADMINISTRATIVE

I. Acronyms and Abbreviations

TCDS Type-Certificate Data Sheet UK CAA United Kingdom Civil Aviation Authority

II. Type Certificate Holder Record

Rolls-Royce Deutschland Ltd & Co KG formerly (until 20 February 2019): Rolls-Royce plc

III. Change Record

Issue Date Changes TC issue date

Issue 01 21 February 2019

Initial Issue, products previously covered by UK CAA TCDS as listed in section II.1.1; Transfer of TC from Rolls-Royce plc to Rolls-Royce Deutschland Ltd & Co KG

Initial Issue, 21 February 2019

-END-

Documents

TYPE-CERTIFICATE DATA SHEET · Pressure Transmitter, Blow-off P1/P2 Switch, Oil Tank Pressurising Valve, Starter Generator (Starter Aspects Only), Anti-icing valve, Thrust Limiter,