TCDS E-297

Page No 1 2 3 4 5 6 7 8 9 Revision No 27 26 25 27 25 26 26 26 27 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "NOT APPLICABLE" NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRAITON TYPE CERTIFICATE DATA SHEET E 297 TCDS E 297 REVISION: 27 DATE: March 23, 2007 Rolls-Royce Deutschland Ltd & Co KG Model: Dart 525, 528-7E, 528D-7E, 529-7E, 529D-7E, 529-7H 529D-7H, 529-8E, 529D-8E, 529-8H, 529D-8H, 529-8X, 529D-8X, 529-8Y, 529D-8Y, 529-8Z, 529D-8Z, 531 532-7, 532-2L, 532-7L, 532-7N, 532-7P, 532-7R, 535-2 535-7R, 551-7, 551-7R, 552-2, 552-7, 552-7R TYPE CERTIFICATE DATA SHEET NO. E 297 Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E 297) 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 Holder: Rolls-R oyce Deutschland Ltd & Co KG Postfach 1536 D-15827 Dahlewitz Germany (formerly Rolls-Roy ce, Ltd., Derby, England) Model: Dart 525 528-7E, 528D-7E, 531 529-7E, 529D-7E, 529-7H, 529D- 7H, 529-8E, 529D-8E 529-8H, 529D-8H, 529-8X, 529D-8X, 529-8Y, 529D-8Y, 529-8Z, 529D-8Z Type: Turboprop 2-stage centrifugal compressor; 3-stage turbine; 7 combustion chambers; 0.093 to 1 reduction gearing - - - - Rating Max. Continuous at sea level, equivalent shaft hp., shaft hp., jet thrust (lb.) rpm 1755-1585-424-14500 2027-1835-479-15000 2103-1910-482-15000 2152-1955-493-15000 (Mod 1860) Takeoff (5 min.) at sea level, equivalent shaft hp., shaft hp., jet thrust (lb.), rpm 1920-1730-474-15000 2027-1835-479-15000 2103-1910-482-15000 2152-1955-493-15000 (Mod 1860) TCDS E 297 2 Model: Dart (Continued) 525 528-7E, 528D-7E, 531 529-7E, 529D-7E, 529-7H, 529D-7H, 529- 8E, 529D-8E 529-8H, 529D-8H, 529-8X, 529D-8X, 529-8Y, 529D-8Y, 529-8Z, 529D-8Z Takeoff (5 min.) at sea level, with w/m injection: equivalent shaft hp. shaft hp., jet thrust (lb.) rpm (529-8K, 529D-8K, 529-8Y, 529D-8Y, 529-8Z, 529D-8Z) (532-7, 532-7N, 532-7P) (532-2L, 532-7L, 535-2) (532-7R, 535-7R) 1955-1765-474-15000 2062-1870-479-15000 2143-1950-482-15000 (For Models above except 529-8X, 529D- 8X, 529-8Y, 529D-8Y, 529-8Z, 529D-8Z) *2183-1990-482-15000 (See NOTE 13) *2196-1990-514-15000 (See NOTE 13) *2250-2040-524-15000 (See NOTE 13) *2293-2080-532-15000 (See NOTE 13) 2297-2085-529-15000 (535-7R Mod 1860) (*Applies only to models listed at left side of page). Propeller Shaft Type SBAC No. 4 - - - - Fuel Control Lucas CCU 39/30AM Lucas CCU 36/27 AS for 531 Lucas CCU 39/38 AY for 528 series Lucas CCU 69/55 AY for 529-8 series Lucas CCU 39/38 AY for 529-7 series Water Methanol Control Unit RK 39831 RK 40195 for 528 series; RK 39831 for 531. RK 40196 for 529-8 series; RK 40195 for 529-7 series. Fuel See NOTE 6 - - - - Oil Types See relevant Rolls- Royce Operating Instructions Manual (NOTE 14) - - - - Oil Capacity 4 U.S. gal. integral tank - - - - Principal Dimensions Length overall (in.) 97.6 - - - - Diameter (in.) 37.9 - - - - C.G. Location Aft of mounting feet (in.) 2.4 - - - - Weight (dry), (lb.) Includes all controls, exhaust unit, igniters, thermocouples, oil tank and fuel pump 1260 1270 for 528 series 1270 for 531 1260 1273 (Mod 1860) Ignition System Alternatives High energy type with transformers LUCAS NB34, NB38, NB2503, NB5707, NB5706, NB5714. - - - - HE units LUCAS C10/TS, C63/TS, C65/TS, C67/TS, C69/TS - - - - HE igniters SMITHS LR 104series SMITHS KR 104 series Champion CR 104 series (Champion FHE- 19-6H) AC Type YA20 1 through 12 - - - - - - - - - - - - - - - - - - - - TCDS E 297 3 Model: Dart (Cont'd) 532-2L, 532-7, 532-7L 532-7N, 532-7P, 532-7R 535-2, 535-7R 551-7, 551-7R 552-2, 552-7, 552-7R Type: Turboprop 2-stage centrifugal compressor; 3-stage turbine; 7 combustion chambers; 0.093 to 1 reduction gearing - - - - Rating Max. Continuous at sea level, equivalent shaft hp., shaft hp., jet thrust (lb.) rpm 2075-1880-488-15000 (for models above except 535-2 & 535-7R) 2225-2030-487-15000 (for models 535-2 & 535-7R only) 2346-2164-455-15000 2370-2167-508-15000 Takeoff (5 min.) at sea level equivalent shaft hp., shaft hp., jet thrust (lb.) rpm 2260-2060-500-15000 (535-7R Mod 1860) 2027-1835-479-15000 2346-2164-455-15000 2370-2167-508-15000 Takeoff (5 min.) at sea level, with w/m injection: equivalent shaft hp. Shaft hp, jet thrust (lb.) rpm - - 2417-2225-479-15000 (For Model 551-7) 2319-2136-457-15000 (For Model 551-7R) 2390-2185-512-15000 2433-2225-519-15000 2343-2140-508-15000 Propeller Shaft Type SBAC No. 4 - - SBAC No. 4 Fuel Control Lucas CCU 82/67AS or 36/27AS Lucas CCU509-110-CA Mk552-2 Lucas CCU520- /113CB or CCU519/112CB Mk552-7, -7R Lucas CCU509/110CA or CCU504/108CA Water Methanol Control Unit RK 40195 for 532-7, 537-7L, 532-7R, 532-7P, 535-7R; RK 42153 for 532-7N; RK 39831 for 532-2L and 535-2. RK 44317A Mk552-2 Rolls-Royce RK48264A Mk552-7, -7R Rolls-Royce RK30403A Fuel See NOTE 6 - - - - Oil Types See relevant Rolls-Royce Operating Instructions Manual (NOTE 14) - - - - Oil Capacity 4 U.S. gal. integral tank - - - - Principal Dimensions Length overall (in.) 97.6 - - - - Diameter (in.) 37.9 - - 38.0 C.G. Location Aft of mounting feet (in.) 2.4 1.7 Mk552-2 +1.4 Mk552-7, -7R + 1.6 Weight (dry), (lb.) Includes all controls, exhaust unit, igniters, thermocouples, oil tank and fuel pump 1270 1273 (535-7R Mod 1860) 1264 1273 Ignition System Alternatives High energy type with transformers LUCAS NB34, NB38, NB2503, NB5707, NB5706, NB5714. - - - - HE units LUCAS C10/TS, C63/TS, C65/TS, C67/TS, C69/TS - - - - HE igniters SMITHS LR 104 series SMITHS KR 104 series Champion CR 104 series (Champion FHE-19-6H) AC Type YA20 - - - - - - - - - - - - - - - - NOTES: 1 through 12 - - - - TCDS E 297 4 Certification Basis 1. For Dart 525 series, 528 series, 529-7E, 529D-7 E, 529-8E, 529D-8E, and 531: CAR Part 10 and British Civil Airworthiness Requirements Section C Issue 4. Section C Issue 4 is equivalent to the applicab le parts of CAR 13 effective June 15, 1956. Special Conditions equivalent to PART 13 Amendment 13-1 and 13-2 were applied in addition to Section C issue 4. 2. For Dart 529-7H, 529D-7H, 529-8H, 529D-8 H, 529-8X, 529D-8X, 529-8Y, 529D-8Y, 529-8Z, 529D-8Z, 532-2L, 532-7, 532-7L, 532-7N, 532-7P, 532-7R, 535-2, 535-7R CAR Part 10 and British Civil Airworthiness Requirement Section C issue 5, dated July 1, 1962. Section C Issue 5 is equivalent to the applicab le parts of CAR Part 13 effective June 15, 1956, and Amendments 13-1 through 13-5. 3. For Dart 551-7, 551-7R, 552-2, 552-7, 552-7R CAR Part 10 and British Civil Airworthiness Requirement Section C Issue 6, dated June 15, 1966. Section C Issue 6 contains all the requirements of I ssue 5 and is therefore equivalent to the applicable parts of CAR Part 13 effective June 15, 1956 and Amendments 13-1 through 13-5. Date of Application for Type Certificate May 17, 1956. Engine Type Certificate No. 297 issued December 2, 1957. For subsequent additions see NOTE 12. The aviation authority for Germany, Luftfahrt-Bundesamt, originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E-297. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. 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 Relea se Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E-297, is in a condition for safe operation and has und ergone a final operational check. Additional guidance is contained in FAA Adviso ry Circular 21.23, Airworthiness Certification of Civil Aircraft, Engines, Propellers and Related Products, Imported into the United States. N O T E S NOTE 1. Maximum permissible temperatures: Turbine gas temperature, (°C) 525 528-7E 528D-7E 529-7E, 529D-7E, 529-8E, 529D-8E, 529-7H, 529D-7H, 529-8H, 529D-8H 529-8X 529D-8X 529-8Y 529D-8Y 529-8Z 529D-8Z Takeoff (wet) 810 860 860 - - - - - - Takeoff (dry) 780 810 825 - - - - - - Maximum Continuous 760 850 850 870 910 920 Maximum Transient for starts 930 - - - - - - - - - - Max. Overtemperature (5 sec. limit) 950 - - - - - - 1000 - - Oil inlet temperature range, °C minus 15 to + 115 minus 15 to + 120 - - - - - - - - Min. start minus 30 - - - - - - - - - - Min. wet takeoff - aircraft static 40 - - - - - - - - - - - aircraft rolling 40 - - - - - - - - - - TCDS E 297 5 NOTE 1 (Continued) Maximum permissible temperatures:Turbine gas temperature, (°C) 531 532-7 532-7L 532-7R 532-7N 532-2L 535-2 Takeoff (wet) 875 860 905 - - - - 920 Takeoff (dry) 810 - - - - - - - - - - Maximum Continuous 850 - - 885 - - - - 920 Maximum Transient for starts 930 - - - - - - - - - - Max. Overtemperature (5 sec. limit) 950 - - 1000 - - - - - - Oil inlet temperature range, °C minus 15 - - - - - - - - - - to + 120 Min. start minus 30 - - - - - - - - - - Min. wet takeoff - aircraft static 50 40 50 40 60 - - - aircraft rolling 40 - - 50 40 - - - - Maximum permissible temperatures:Turbine gas temperature, (°C) 532-7P 535-7R 551-7 551-7R 552-2, 552-7, 552-7R Takeoff (wet) 925 920 940 - - 930 Takeoff (dry) - - - - 910 - - 900 Maximum Continuous 910 920 930 - - 920 Maximum Transient for starts - - - - - - - - 930 Max. Overtemperature (5 sec. limit) - - - - - - - - 1000 Oil inlet temperature range, °C - - - - - - - - - - Min. start - - - - - - - - - - Min. wet takeoff 552-2 552-7 552-7R - aircraft static 40 50 65 50 60 65 50 - aircraft rolling 40 50 65 50 40 65 50 NOTE 2. Fuel & Oil Pressure Limits: Fuel supply pressure at engine fuel inlet varies with flow per latest approved issue of RR curve HK 23643. Oil pressure varies with oil inlet temp erature. Normal for 525 series, 13 to 35 psig; for all other models, 12 to 35 psig. 9 psig is minimum in-flight for all models. NOTE 3. The engine ratings are based on standard conditions with no ai r bleed or aircraft accessory power extraction, 60°F, 29.92 in. Hg., and PW/PO=.01 at sea level within limiting gas temperatures. On dry air, T.O. power is increased less than .5% and M.C. power by 1.3%. Jet thrust is converted to equivalent shaft hp by dividing the thrust value by a factor of 2.5. The output values are the minimum acceptable and are based on the use of Rolls-Royce exhaust cone RK 21556, RK 25226 or approved equivalent and with 12 thermocouples located in the intermediate turbine guide vanes. NOTE 4. Water/methanol injection is optional and is utilized through auto matically varied flow to provide a constant level of power output for take-off. The w/m fluid should be a 63/37 mixture of water and methyl alcohol for all models, (Rolls-Royce MSRR 9359 latest approved issue). The water used is distilled or contains a maximum of 10 ppm solids, and the methyl alcohol is British D.Eng.RD.2491 or equivalent. The w/m flow varies up to a maximum for the different models as follows: 525 series: 493 gph (U.S.); 529-8X, 529D-8X, 529-8Y, 529D -8Y, 529-8Z, 529D-8Z, 532-2L, 532-7, 532-7N, 532-7P,: 660 gph (U.S.); 532-7L, 532-7R, 535-7R: 673 gph (U.S.); 535-2: 696 gph (U.S.); 551-7, 551-7R, 552-2, 552-7, 552-7R: 627 gph (U.S.); Remaining models: 564.5 gph (U.S.) Refer to appropriate Rolls-Royce Operations Instructions for additional operating limits, characteristics and procedures when using W/M selection (NOTE 14). TCDS E 297 6 NOTE 5. Accessory provisions on engine (oil c ooler and air inlet are engine-mounted) Drive Rotation (facing drive) Speed Ratio Continuous Static Maximum (C-clockwise) (CC-counter clockwise) to turbine Torque* (in. lb.) Torque** (in. lb.) Overhang (in. lb.) Power takeoff (120hp) CC .345 1510 6300 101 Propeller Governor CU 84 for 525 series 528 series 529-7E, 529D-7E, 529-7H, 529D-7H, 532-2L, 532-7 series, 535 series, 551 series, and 552-7, 552-7R CC .192 138 1380 102 CU 88 for 529-8 series and 529D-8 series, CU 91 for 531 CU 99 for 552-2 Starter (Rotax C5104) CC 2.0 272 1000 84 Fuel pump (Lucas GB 222/3AU series) CC .192 108 780 34 * Continuous torque values are based on takeoff power at sea level. ** Maximum torque of weak link without permanent set, or the clutch setting for the starter. NOTE 6. Approved fuels and fuel additives given in Rolls-Royce Operating Instructions. (See NOTE 14). NOTE 7. These engines meet FAA requirements for ic ing protection, for adequate turbine disk integrity, for rotor blade containment, and do not require external armoring. NOTE 8. Propellers used with this engine must have functioning characteristics which are compatible with the engine and its control system. NOTE 9. Maximum air bleed for aircraft servi ces is 1.55% of the no-bleed mass flow. NOTE 10. Maximum overspeed limit is 17000 rpm for 20 seconds. If these limits are exceeded, the engine will require inspection as detailed in the Rolls-Royce Maintenance Manual. NOTE 11. The maximum allowable horsepower cleared for the engine to cover operation at low ambient air temperature and/or ram conditions is 3000 HP for the 529 series, 532 series, 535 series, 551 and 552 series and is 2075 HP for all other models. NOTE 12. The above models incorporate the following general characteristics. Model: Characteristics: 1A Dart 525 Basic model for use in Viscount 800 Series aircraft. 10' 0" Propeller. Approved December 2, 1957 B Dart 525F As 525 with improved turbine blading and higher TCT operating limitations. Added April 7, 1961 Cancelled December 9, 2002 (See note 15) C Dart 525D As 525F but with a modi fication to the nozzle box affecting interchangeability. Added February 7, 1962 Cancelled December 9, 2002 (See note 15) 2 Dart 526 Variant for installation in Ar mstrong Whitworth Argosy aircraft. Take- off and Maximum continuous ratings are higher than 525. 11' 6" Propeller. Added November 23, 1959 Cancelled December 9, 2002 (See note 15) TCDS E 297 7 NOTE 12. (Continued) Model: Characteristics: 3 Dart 527 Variant for installation in Handley Page Herald aircraft. Ratings as Dart 526. 12' 6" Propeller Added September 17, 1956 Cancelled December 9, 2002 (See note 15) 4A Dart 528 Variant for installation in F okker & Fairchild F.27 Friendship aircraft. ISA rating same as Dart 526 but lower takeoff and max. continuous temperature limit as fitted with early standard of turbine blading 11' 6" Propeller. Added June 22, 1960 Canceled September 9, 1980 (See Note 15) B 528-7E As 528 with improved turbine blading and higher TGT operating limitations. Added June 22, 1960 C 528D-7E As 528-7E but with nozzle box m odification affecting interchangeability. Added February 7, 1962 D 532-7 AS 528-7E but with various mech anical improvements and with a higher wet rating. Added June 1, 1965 E 532-7L As 532-7 but with improved turb ine blading and higher rating/operating limitations. Added January 15, 1968 F 532-7N As 532-7 but with modified wate r methanol unit, improved HP turbine blade material and higher T.G.T. limitations, to permit use of w/m up to 15,000 ft. Added March 24, 1969 G 532-7P As 532-7 but with improved turbine blading and higher wet takeoff and MC T.G.T. limits Added March 24, 1969 H 532-2L As 532-7L but with installation features for Hawker Siddeley, HSA 748 aircraft. Added April 7, 1972 I 532-7R As 532-7L but with w/m unit set to provide higher wet takeoff rating. Added February 19, 1976 J 535-2 As 532-2L but with improved turbine blading, higher T.G.T. limitations, and higher max. continuous rating. Added May 22, 1980 K 535-7R As 532-7R but with improved turbine blading, higher T.G.T. limitations, and a higher maximum continuous rating. Added September 3, 1980 5A Dart 529 Variant for installation in the Grumman Gulfstream aircraft. As Dart 526 but with higher takeoff and maximum continuous rating. 11 6" Propeller. Added September 17, 1958 Cancelled September 9, 1980 (See Note 15) B 529D As 529 but with nozzle box mod. affecting interchangeablity. Added February 7, 1962 Cancelled Sept 9, 1980 (see Note 15) C 529-8E As 529 but with improved turbin e bladeing and higher T.G.T. operating limitations. Added February 7, 1962 D 529D-8E As 529-8E but with nozzle box mod. affecting interchangeability. Added February 7, 1962 E 529-8H As 529-8E but with various m echanical improvements and higher cruise T.C.T. limitations. Added June 1, 1965 F 529D-8H As 529-8H but with nozzle box mod. affecting interchangeability. Added June 1, 1965 G 529-7E As 529-8E but for installation in Fokker and Fairchild Executive Friendship aircraft. 11' 6" Propeller. Added February 7, 1962 H 529-7E As 529-7E with nozzle box mod. affecting interchangeability. Added February 7, 1962 I 529-7H As 529-7E but with various mech anical improvements and higher cruise T.G.T. limitations. Added June 1, 1965 TCDS E 297 8 NOTE 12. (Continued) Models: (Cont'd) Characteristics: J 529D-7H As 529-7H with nozzle box mod. affecting interchangeability. Added June 1, 1965 K 529-8X Variant for installation in Gru mman Gulfstream executive aircraft. As 529-8H but with higher wet take-off ratings. Added October 1, 1965 L 529D-8X As 529-8X with nozzle box mod. affecting interchangeability. Added October 1, 1965 M 529-8Y As 529-8X but with improved turbine blading and higher max continuous TGT limit. Added June 16, 1981 N 529D-8Y As 529-8Y but with nozzle box mod affecting interchangeability Added June 16, 1981 P 529-8Z As 529-8Y but with improved turbine blading and higher max continuous TGT limit Added June 16, 1981 Q 529D-8Z As 529-8Z but with nozzle box mod affecting interchangeably. Added June 16, 1981 6 Dart 531 Variant for installation in Avro 748 aircraft. Ratings and limitations as Dart 526 but with increased wet TO TCT limit. 12' 0" dia. propeller. Added February 7, 1962 7 Dart 530 Variant for installation in Viscount aircraft. Uprated 525F with increased wet and dry Takeoff and Maximum Continuous power ratings. Added December 28, 1982 Cancelled December 9, 2002 (see note 15) 8A Dart 551-7 Variant with new impellers and turbines for installation in Fokker F27 aircraft. Updated 535-7R with increased wet and dry takeoff and maximum continuous power ratings and improved specific fuel consumption. Added January 14, 1985 B Dart 551-7R As 551-7 but with lower wet power rating. Added January 14, 1985 9A Dart 552-2 Variant for installation in HSA 748 aircraft. Uprated and improved s.f.c. Derivative of Mk536-2. Added August 30, 1985 B Dart 552-7R Improved fuel burn derivative of Mk551-7R. Added August 30, 1985 C Dart 552-7 Improved fuel burn derivativ e of Mk551-7, mechanically similar to Mk552-7R but with a higher water-methanol power rating. Added August 30, 1985 NOTE 13. Ratings shown give HP at the propeller shaft conditions per NOTE 3. Corresponding ratings at the turbine shaft with 40 HP gearbox offtake for these models are: 529-8X, 529D-8X, 529-8Y, 529D-8Y, 529-8Z, 529D-8Z 532-7, -7N, -7P 532-2L, -7L, 535-2 532-7R, 535-7R 2239-2030-522-15000 2239-2030-522-15000 2293-2080-532-15000 2336-2120-539-15000 TCDS E 297 9 NOTE 14. ENGINE MARK NO. AIRCRAFT MAINTENANCE MANUAL OPERATING INSTRUCTIONS 525 Vickers Viscount M-Da7-V F-Da7-V 528-7E, 528D-7E Friendship Fairchild and Fokker M-Da7-F F-Da7-FaF F-Da7-FoF 529-7E, 529D-7E, 529-7H, 529D-7H Fairchild Friendship M-Da7-F F-Da7-FaF 529-8E, 529D-8E Grumman Gulf stream M-Da7-G F-Da7-G 529-8H, 529D-8H 529-8X, 529D-8X 529-8Y, 529D-8Y 529-8Z, 529D-8Z 531, 532-2L, 535-2, 552-2 H.S.A. 748 M-Da7-Av F-Da7-Av 532-7, 532-7L, 532-7N Friendship Fairchild and Fokker M-Da7-F F-Da7-FaF F-Da7-FoF 532-7P, 532-7R, 535-7R, 551-7, 551-7R, 552-7, 552-7R Fokker Friendship M-Da7-F F-Da7-FoF OVERHAUL MANUAL: ALL MARK NOS. 0-Da7-AC NOTE 15. The 528, 529, and 529D are no longer in service and were deleted from this TCDS on September 9, 1980. The 525D, 525F,526, 527 and 530 are no longer in service and were deleted from this TCDS on December 9, 2002. NOTE 16. Life limits, established for critical rotating components, ar e published in Chapter 5 of the maintenance and overhaul manuals. NOTE 17.. Each of the documents listed below must state that it is a pproved 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. • 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. ---E N D---