TCDS E-307

Page No. 1 2 3 4 5 Rev. No. 14 14 14 14 14 Reformatted 1/94 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-307 Revision 15 Rolls-Royce, Ltd. Avon 522 524B 525B 526 527 531 532R-B 533R 533R-11A April 6, 2011 NOTE 11. This type certificate is cancelled effective April 6, 2011 and is not valid for aircraft manufactured after this date. This cancellation also invalidates, and precludes issuance of, any U.S. Certificates of Airworthiness. TYPE CERTIFICATE DATA SHEET NO. E-307-14 Engine of models described herein conforming with this data sheet (which is part of Type Certificate No. E-307) 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. Manufacturer: Rolls-Royce, Ltd. Derby, England Model Avon 522 524B 525B 526 527 Type Turbojet 16 stage axial compressor - - - - - - - - 3 stage turbine - - - - - - - - Turbo-annular combustion - - - - - - - - with eight flame tubes Ratings Max. continuous static thrust, lb., and rpm at sea level 9125 at 7650 8765 at 7600 - - 9125 at 7650 9500 at 7750 Takeoff (5 min.) static thrust, lb., and rpm at sea level 10500 at 8050 10250 at 8050 - - 10500 at 8050 11400 at 8050 Max. reverse thrust (1 min.), rpm — 8050 - - — — Fuel Control Lucas RTC Lucas RTC - - Lucas RTC Lucas RTC 102 32/33AJ control 25/26AJ control 32/33AJ control control with with Lucas with Lucas w ith Lucas pump Lucas GDS pump GDS 2/2B pump GDS 1/1A pump GDS 2/28 6/28 Fuel See NOTE 9 - - - - - - - - Oil See NOTE 10 - - - - - - - - E-307 2 Principal Dimensions 522 524B 525B 526 527 Length, in. (from front of nose cone to rear of exhaust unit) 125.975 - - - - - - - - Diameter, in. (max.) (see installation dwg. 47.5 (approx.) - - - - - - - - C.G. location, in: Rearward of front suspension C/L 21.8 21.5 - - 21.8 22.0 Weight (dry (including fuel system oil tank, igniters, bleed valves and fittings) lb. 3328 3343 3383 3328 3347 Ignition Systems Igniters LR.103 or Igniters LR.103 or - - Igniters LR.103 or Igniters LR.103 or LR.741 and high LR.741 and high LR.741 and high LR.741 and high energy boxes BTH energy igniter energy boxes BTH energy boxes BTH C10/TS/3 or boxes BTH C10/TS/3 C 10/TS/3 or Rotax C10/TS/3 or Rotax Rotax NB.25/2 or Champion FH E176 NB.25/2 NB.25/2; or (Rolls-Royce Champion FHE176 P/N CR103) (Rolls-Royce P/N CR103) NOTES 1 to 10 - - - - - - - - Model Avon 531 532R-B 533R 533R-11A Type Turbojet 17 stage axial compressor - - - - - - 3 stage turbine - - - - - - Turbo-annular combustion with eight flame tubes - - - - - - Ratings Max. continuous static thrust, lb., and rpm at sea level 10820 at 7900 10710 at 7950 - - 11070 at 7900 Takeoff (5 min.) static thrust, lb., and rpm at sea level 12200 at 8050 12080 at 8050 12600 at 8150 13000 at 8150 Max. reverse thrust (1 min.), rpm — 8150 - - - - Fuel Control Lucas RTC 102 Lucas RTC 121 - - - - control with Lucas control with Lucas pump GDS 6/2B pump GDS 102 Fuel See NOTE 9 - - - - - - Oil See NOTE 10 - - - - - - Principal Dimensions: Length, in. (from front of nose cone to rear of exhaust unit) 134.000 - - - - - - Diameter, in. (max.) (See installation dwg.) 47.5 (approx.) - - - - - - C.G. location, in: Rearward of front suspension C/L 19.4 19.25 - - - - Weight (dry) (including fuel system oil tank, ingniters, bleed valves, and fitting), lb. 3488 3478 - - - - E-307 3 531 532R-B 533R 533R-11A Ignition System Igniters LR.103 Igniters LR.103C - - - - with high energy with high energy C10/TS/3 or Rotax boxes BTH C10/TS/3 NB.25/2 or Champion or Rotax NB.25/2 FHE176 (Rolls-Royce or Champion FHE 176 P/N CR103) (Rolls Royce P/N CR103) NOTES 1 to 10 - - - - - - "- -" indicates "same as previous model" "—" indicates "not applicable" Certification Basis CAR 10, Engine Type Certificat e No. 307 issued September 17, 1958. Date of Application for Type Certificate - March 5, 1956. Import Requirements Each individually imported engine must be accompanied by a Rolls-Royce, Ltd./CAA approved "Inspection and Test Certificate" signed by a person authorized by the CAA and containing the following statement: "The engine covered by this certificate conforms to Type Certificate E-307 and is in condition for safe operation and has been s ubjected by the manufacturer to a final operational check." NOTE 1. Maximum permissible temperatures: 522, 526 524B, 525B 527 531 Turbine gas temperatures: Takeoff 1157°F (625) - - 1247°F (675°C) 1220°F (670°C) Maximum continuous 1067°F (575°C) 1058°F (570°C) 1076°F (580°C) 1103°F (595°C) Maximum transient starts 1292°F (700°C) - - - - - - Maximum reverse — 1157°F (625°C) — — Oil inlet temperature: -40°F to + 103°F - - - - - - (-40°C to +95°C) Maximum 15 min. 212°F (100°C) - - - - - - Maximum fuel temperature 149°F (65°C) - - - - - - 532R-B 533R 533R-11A Turbine gas temperatures: Takeoff 1238°F (670°C) 1283°F (695°C 1292°F (700°C) Maximum continuous 1103°F (595°C) - - - - Maximum transient starts 1292°F (700°C) - - - - Maximum reverse — — — Oil inlet temperature: -40°F to +203°F - - - - (-40°C to +95°C) Maximum 15 min. 212°F (100°C) - - - - Maximum fuel temperature 149°F (65°C) - - - - (Actual operating exhaust gas temperatures will vary to meet environmental operating conditions in accordance with the manufacturer's approved instructions.) E-307 4 NOTE 2. Fuel and oil pressure limits: Fuel supply at engine inlet: In accordance with HK 23372 iss. 5. Oil pressure: All models - 30 to 45 p.s.i.g. with 20 p.s.i.g. minimum in flight. NOTE 3. The ratings are based on standard conditions with no air bleed or accessory power drive, 60°F and 29.92" Hg. pw/po = .01 and with turbine outlet gas temperature within limits. Engine to be fitted as follows: 522, 526 524B, 525B 527 531 532R-B 533R 533R-11A Intake Flare J 58900 - - - - J 86958 J58900 J 86958 - - Jet Pipe J 68956 - - - - - - - - - - - - Final Nozzle J 68973-L J 69873-G J 84355 J 84355-A - - J 84355-B J 84355-C Equiv. Diams. (in.) 21.15 21.285 20.65/21.15 21.165/21. 68 - - 21.08/21.68 20.93/21.535 The thrusts quoted for the 532R-B, 533R, and 533R-11A are for the engine and thrust reverser combination. NOTE 4. The following accessory drive provisions are incorporated: (2) (3) Weak Speed Cont. Inst. Link, Maximum Rotation Ratio to Torque Torque Eng. or Overhang Drive Type (1) Turbine (lb.-i n.) (lb.-in.) Access. (in.-lb.) a) Avon 524B, 535B Elec. Starter Rotax C6811 C 6 264 816 ACC 56 x 6 = 336 Alternator (4) BTH LA.3016 C 1.3099 138.5 Max 2388 ENG Not overhung 369.0 Idling (80 x 8 = 640) Governor Pump Plessey GP . 078C C .58 33 330 ACC 3.5 x 1.5 = 5.25 Fuel Pump Lucas GDS.1/1A CC .454 476 (5) ENG 43.5 x 5.5 = 240 Hyd. Pump Lockheed MK.9 TF CC .4935 144 384 ENG 8 x 2.4 = 19.2 Hyd. Pump (6) MK.8 TF CC .4935 288 768 ENG 16 x 3.5 = 56 Synch Alt. Rotol S.N.A.11 CC .681 3.7 Max 389 ENG 4.8 x 2.25 = 11 Tachometer Smiths RN.106.KP CC .5013 0.25 450 ENG 2.8 x 2 = 5.6 b) Avon 522, 526, 527, 531, 532R-B, 533R, 533R-11A Gearbox Drive Rotol GD.9/85 C .6 966 655 Max 3852 ENG 909 Idling Elec. Starter Rotax C.6811 C 6 264 816 ACC 56 x 6 = 336 Alternator (4) Auxilee C 1.3099 159 Max. 1289 ENG Not overhung 308 Idling (46 x 7.5 = 345) Governor Pump Plessey GP . 073C C .58 33 330 ACC 3.5 x 1.5 = 5.25 Fuel Pump Lucas GDS.2/2B CC .454 476 310 ENG 38.25 x 5.5 = 205 GDS-102 GDS 6/2B CC .454 476 310 ENG 42.25 x 5.5 = 233 Synch Alt. Rotol S.N.A.11 C .6729 1.5 220 ENG 4.8 x 2.25 = 11 Tachometer Laegar 545/681 C . 5018 0.25 450 ENG 2.75 x 2 = 5.5 (1) "C" - Clockwise, "CC" - Counterclockwise: facing drive. (2) Continuos torque values are based on takeoff power at sea level. (3) Max. Instantaneous torque of weak link without permanent set. (4) Supported by independent mounting. (5) 2550 (when MK. 9 = hyd. pump shear neck fails). 2000 (when MK. 8 = hyd. pump shear neck fails). (6) Alternatives. Two each per aircraft. E-307 5 NOTE 5. The maximum air blend for aircraft services at maximum continuous r.p.m. is 6% of the no-bleed engine mass flow for 524B and 525B; 9% of the no-bleed mass flow for 522, 526, and 527; 10% of the no-bleed mass flow for 531, 532R-B, 533R, and 533R- 11A. NOTE 6. This engine meets FAA requirements for icing protection, for adequate turbine disk integrity, for rotor blade containment, and does not require external armoring. NOTE 7. Maximum overspeed limits for 20 seconds are: 8300 r.p.m. for 522, 524B, and 525B; 8350 r.p.m. for 526 and 531; 8400 r.p.m. for 527 and 533R-11A; and 8450 r.p.m. for 532R-B and 533R. If these limits are exceeded, the engine shall be overhauled. NOTE 8. The maximum permissible engine speed for takeoff when operating above sea level or with high ambient air temperature is 8100 r.p.m. for the 526 and 8150 r.p.m. for the 532R-B. For the 533R and 533R-11A, the maximum r.p.m. is 8150 under all conditions. For all other models, the maximum r.p.m. is 8050. NOTE 9. The following fuels and additives are eligible for these engines: (Fuels shall conform to the specifications as listed or to subsequent revisions thereof.) Aviation Kerosene Specifications Aviation Wide-Cut Specifications British D Eng. R.D. 2453, 2494, 2498 British D Eng. R.D. 2486, 2454 Canadian 3-GP-23C Type I Canadian 3-GP-22C Type II American MIL-J-5624E Type JP-5 American MIL-J-5624F Grade JP-4 A.S.T.M. D.1655-59T Type A or Ty pe A-1 A.S.T.M. D.1655-59T Type B United Airlines UA-1 I.A.T.A. Wide-cut fuel I.A.T.A. Kerosene Type Fuel ASTM emergency fuel Specification ES2-74 is alternative speci fication for use on an exception basis where local fuel supplies so dictate. "TOLAD 245" corrosion inhibitor additive up to a concen tration not exceeding 12 pounds per 35,000 imperial gallons. NOTE 10. The following oils are eligible for these engines: (11.5 U.S. pints integral oil tank) Esso/Exxon Turbo Oil 2380 Aeroshell Turbine Oil 390 Aeroshell Turbine Oil 750 Texaco TSATO 15 Castrol 98 Turbine Oil Castrol 3C Oil Castrol 325 Oil Turbonycoil 13B Mobil Jet Oil II Chevron Jet Engine Oil 5 Caltex RPM Jet Engine Oil 5 ....END....