Service Instruction No. 1257G

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ISSUED REVISED PAGE NO. REVISION MO DAY YEAR MO DAY YEAR 11 24 72 05 16 08 1 of 3 G ©2008 by Lycoming “All Rights Reserved 652 Oliver Street Williamsport, PA. 17701 U.S.A. Tel. 5703 23 6181 Fax. 5703 27 7101 www.lycoming.com DATE: May 16, 2008 Service Instruction No. 1257G (Supersedes Service Instruction No. 1257F) Engineering Aspects are FAA Approved SUBJECT: Horsepower, Manifold Pressure and RPM Values MODELS AFFECTED: Lycoming supercharged and turbocharged aircraft engines. TIME OF COMPLIANCE: During engine maintenance. To assist maintenance personnel and pilots, the manifold pressure (M.P.) and RPM at which the supercharged and turbocharged Lycoming engines attain their rated horsepower (H.P.) are listed below. It is important to note that all Lycoming supercharged (GSO and IGSO) engines attain take off power at less than full throttle, while some turbocharged engines attain take off power only at full throttle and others at part throttle. It is the operator’s responsibility to know the type being operated. MECHANICAL SUPERCHARGED – (TakeOf f Rating) CAUTION THE INSTRUCTIONS IN TABLE 1 BELOW ONLY APPLY TO LYCOMING ENGINES THAT ARE SUPERCHARGER EQUIPPED AS AN INTEGRAL PART OF THE ENGINE AT THE FACTORY. THE MODEL DESIGNATION, APPEARING ON THE ENGINE NAMEPLATE, INCLUDES THE LETTER “S” AS PART OF THE ENGINE MODEL DESIGNATION. TABLE 1 ENGINE MODEL H.P. M.P. (in. Hg.) RPM GSO 480 B Series IGSO 480 A Series IGSO 540 A, B Series 340 340 340 48 48 47 3400 3400 3400 TURBOCHARGED ENGINES CAUTION THE INSTRUCTIONS IN TABLES 2 AND 3 ONLY APPLY TO LYCOMING ENGINES THAT ARE TURBOCHARGER EQUIPPED AS AN INTEGRAL PART OF THE ENGINE AT THE FACTORY. THE MODEL DESIGNATION, APPEARING ON THE ENGINE NAMEPLATE, INCLUDES THE LETTER “T” AS PART OF THE ENGINE MODEL DESIGNATION. SERVICE INSTRUCTION ISSUED REVISED PAGE NO. REVISION MO DAY YEAR MO DAY YEAR 11 24 72 05 16 08 2 of 3 G S.I.1257 TURBOCHARGED ENGINES (CONT.): TABLE 2 ENGINE MODEL H.P. M.P. (in.Hg.) RPM NOTE, Also see Table 3 TIO540 AH1A (L)TIO540 R2AD (L)TIO540 V2AD 300 340 350 38 44 42 2500 2500 2500 Engine has an alternate rating of 40 in. Hg. manifold pressure at 2500 RPM to 5000 feet pressure altitude. Engine has an alternate rating of 350 H.P. at 2575 RPM at standard altitude conditions. Horsepower listed is delivered to propeller; 10 additional horsepower is available for accessories. TABLE 3 AIRCRAFT MODEL NOTES ENGINE MODEL H.P. M.P. (in. Hg.) RPM Mooney Mustang 1 TIO541 A1A 310 37 2575 Beech Baron 1 TIO541 E1B4, E1D4 380 41 2900 Beech Duke 1 TIO541 E1A4, E1C4 380 41 2900 Piper Navajo (PA 31 P) 1 TIGO541 E1A 425 45 *2133 Piper Navajo (PA 31) 2 TIO540 A1A, A2A, A1B, A2B 310 38.6 2575 Piper Navajo (PA 31 B) 2 TIO540 A1C, A2C 310 40 2575 Piper Aztec (PA 23 250T) 2 TIO540 C1A 250 33 2575 Piper T 1020 2 LTIO & TIO540 J2B 350 43 2575 Piper Navajo (PA 31 II) 2 LTIO & TIO540 J2BD 350 43 2575 Piper Navajo (PA 31 II) 2 LTIO & TIO540 F2BD 325 43.5 2575 Rockwell Commander 112TC 3 TO360 C1A6D 210 42 2575 Partenavia P68 TC 3 TO360 C1A6D 210 42 2575 Partenavia P68 TC 3 TIO360 C1A6D 210 44 2575 Maule Star Rocket (M 5 210TC) 3 TO360 C1A6D 210 42 2575 Siai Marchetti (S 210) 3 TIO360 A1B 200 34 2575 Riley Cessna Conversion (S 210) 2 LTIO & TIO540 N2BD 350 43 2575 Rockwell Commander 700 1 LTIO & TIO540 R2AD 340 44 2500 Piper Turbo Lance (PA 32 RT) 3 TIO540 S1AD 300 36 2700 Trident Aircraft Tri Gull 2 TIO540 T2AD 330 40.5 2400 Piper Aerostar 700 1 LTIO & TIO540 U2A 350 42 2500 Piper Mojave (PA 31P 350) 1, 4 LTIO & TIO540 V2AD 350 42 2600 Aero Mercantil Gavilan 1, 4 LTIO & TIO540 W2A 350 42.5 2600 Piper Mirage (PA 46 350P) 1 TIO540 AE2A 350 42 2500 Mooney “TLS” M20M 2 TIO540 AF1A, AF1B 270 35 2575 Rockwell Commander 114TC 2 TIO540 AG1A 270 35 2575 ISSUED REVISED PAGE NO. REVISION MO DAY YEAR MO DAY YEAR 11 24 72 05 16 08 3 of 3 G S.I.1257 TABLE 3 (CONT.) AIRCRAFT MODEL NOTES ENGINE MODEL H.P. M.P. (in. Hg.) RPM Piper Saratoga II TC 5 TIO540 AH1A 300 38 2500 Gippsland Aeronautics GA8 Airvan 5,6 TIO540 AH1A 300 38 2500 Cessna 206T Turbo Stationair 5 TIO540 AJ1A 310 39 2500 Cessna Turbo Skylane T182T 5 TIO540 AK1A 235 32 2400 Lake Aircraft Model 250 2 TIO540 AA1AD 270 32.5 2575 Socata Trinidad TC (TB 21) 2 TIO540 AB1AD 250 32.5 2575 Schweizer 2 TIO540 AB1BD 250 32.5 2575 * Propeller RPM as indicated on tachometer. Actual engine RPM is 3200. NOTE 1 – These engines are equipped with an adjustable variablepr essure controller, which must be set in accordance with the latest revision of Service Instructions No. 1211 or No. 1431 and with the airframe manufacturer’s recommendations. NOTE 2 – These engines are equipped with an adjustable density controller, which must be set in accordance with the latest revision of Service Instruction No. 1187. NOTE 3 – These engines are equipped with a turbo waste gate control interconnected with the throttle. The interconnect linkage must be adjusted in accordance with the latest revision of Service Instruction No. 1431. Normal take offs are not at full throttle. The operator controls manifold pressure with the throttle and must avoid exceeding red line manifold pressure. NOTE 4 – Horsepower listed is delivered to propeller; 10 additional horsepower is available for accessories. NOTE 5 – These engines are equipped with a slope controller which must be set by measuring manifold pressure at rated power and engine speed. NOTE 6 – Replace absolute pressure relief valve assembly P/N LW 14445 12 with P/N LW 14445 2. In Notes 1 and 2, the pilot must not routinely control take off manifold pressure overboost by use of part throttle. Instead, the cause for high manifold pressure must be corrected.