APPENDIX 2, CHANGE 1
ESTIMATED MAXIMUM A-WEIGHTED SOUND LEVELS MEASURED IN ACCORDANCE WITH PART-36 APPENDIX -C- PROCEDURES
TOGW MLW TO APP APP MANUFACTURER AIRPLANE ENGINE 1000 LBS 1000 LBS dBA dBA FLAPS NOTES MCDONNELL DOUG. MD-87 JT8D-217C 125.00 120.00 74.5 83.3 28* 8,15 MCDONNELL DOUG. MD-87 JT8D-217C 125.00 120.00 74.5 83.7 40 8,15 MCDONNELL DOUG. MD-87 JT8D-217C 149.50 130.00 80.6 83.6 28* 8,15 MCDONNELL DOUG. MD-87 JT8D-217C 149.50 130.00 80.6 84.3 40 8,15 MCDONNELL DOUG. MD-87 JT8D-219 140.00 128.00 77.4 83.5 28* 8,15 MCDONNELL DOUG. MD-87 JT8D-219 140.00 128.00 77.4 84.2 40 8,15 MCDONNELL DOUG. MD-87 JT8D-219 149.50 130.00 79.7 83.6 28* 8,15 MCDONNELL DOUG. MD-87 JT8D-219 149.50 130.00 79.7 84.3 40 8,15 MCDONNELL DOUG. MD-90-30 V2525-D5 156.00 142.00 71.1 83.3 40 8,15 MCDONNELL DOUG. MD-90-30 V2525-D5 166.00 142.00 73.0 83.3 40 8,15 MCDONNELL DOUG. MD-90-30 V2528-D5 156.00 142.00 69.0 83.3 40 8,15 MCDONNELL DOUG. MD-90-30 V2528-D5 166.00 142.00 71.0 83.3 40 8,15 MESSERSCHMITT HFB-320 HANSA CJ610-9 20.30 19.40 89.7 99.0 - 13 MITSUBISHI MU-2B-26A TPE-331-5-252M 10.00 10.00 64.0 76.0 - 4 MITSUBISHI MU-2B-36A TPE-331-5-252M 11.00 10.20 66.0 76.0 - 4 MITSUBISHI MU300 DIAMOND I JT15D-4 14.10 13.20 71.9 77.2 30 12 MITSUBISHI MU300-10 DIAMOND II JT15D-5 15.80 14.20 71.8 83.0 - 15 MOONEY M20C 0-360-A1D 2.60 2.60 65.0 62.0 - 11 MOONEY M20F w/MODWORK STC# IO-360-E5 2.74 2.74 74.4 62.0 - 11,21 SA02204AT MOONEY M20J I0-360-A1B6D 2.70 2.70 58.0 62.0 - 4 MOONEY M20M TIO-540-AF1A 3.20 3.20 63.9 63.3 - 11,21 MOONEY M20M TIO-540-AF1A 3.37 3.37 64.8 63.3 - 11,21 MORANE-SAULNIER MS 760B (PARIS II) MARBORE VI C2 8.65 6.96 80.9 91.5 55 19 NIHON YS-11A-200 DART MK 542 54.00 52.90 81.0 90.0 - 5 OSTMECKLENBURGISCH OMF-100-160 O-320-D2A 1.96 1.96 61.0 61.0 - 11,21
E FLUGZEUGBAU PIPER 601P IO-540-S1A5 6.00 6.00 70.0 73.0 - 11 PIPER CHEYENNE 400LS TPE-331-14 12.05 11.10 57.0 78.5 - 11 PAGE 49
AC36-3H 4/5/2012 APPENDIX 2, CHANGE 1
ESTIMATED MAXIMUM A-WEIGHTED SOUND LEVELS
MEASURED IN ACCORDANCE WITH PART-36 APPENDIX -C- PROCEDURES
TOGW MLW TO APP APP MANUFACTURER AIRPLANE ENGINE 1000 LBS 1000 LBS dBA dBA FLAPS NOTES PIPER PA-18-150 0-320-A2B 1.80 1.80 53.0 61.0 - 11 PIPER PA-23-250 IO-540-C4B5 5.20 4.94 68.0 73.0 - 11 PIPER PA-24-260 IO-540-B1A5 3.20 3.20 65.0 63.0 - 11 PIPER PA-28-140 O-320-E3D 2.20 2.20 60.0 61.0 - 11 PIPER PA-28-151 O-320-E3D 2.20 2.20 60.0 61.0 - 11 PIPER PA-28-161 O-320-D3G 2.40 2.40 59.0 61.0 - 11 PIPER PA-28-181 O-360-A4M 2.55 2.50 60.0 62.0 - 11 PIPER PA-28-200 I0-360-C1C 2.70 2.70 63.0 61.0 - PIPER PA-28-235 O-540-B4B5 3.00 3.00 72.0 63.0 - 11 PIPER PA-28-236 O-540-J3A5D 3.00 3.00 68.0 63.0 - 11 PIPER PA-28RT-201(2BLD) I0-360-C1C6 2.80 2.80 67.0 62.0 - 11 PIPER PA-28RT-201T(3BLD) TSIO-360-FB 2.90 2.90 67.0 62.0 - 11 PIPER PA-30 TWIN COMANCHE IO-320-B 3.60 3.60 56.0 70.6 - 11 PIPER PA-31-310 TI0-540-A2C 6.50 6.50 69.0 73.0 - 11 PIPER PA-31-325 TIO-540-F2BD 6.50 6.50 70.0 74.0 - 11 PIPER PA-31-350 TI0-540-J2BD 7.00 7.00 71.0 74.0 - 11 PIPER PA-31T PT6A-28 9.00 9.00 62.0 74.0 - 4 PIPER PA-32-300 IO-540-K1G5D 3.40 3.40 71.0 64.0 - PIPER PA-32R-300 IO-540-K1G5D 3.60 3.60 71.0 64.0 - 11 PIPER PA-32R-301 IO-540-K1G5D 3.60 3.60 70.0 64.0 - 11 PIPER PA-32R-301T TIO-540-S1AD 3.60 3.60 69.0 64.0 - 11 PIPER PA-32RT-300 IO-540-K1A5D 3.60 3.60 71.0 64.0 - 11 PIPER PA-34-200T TSI0-360-E 4.80 4.50 64.0 72.0 - 11 PIPER PA-34-220T TSIO-360-KB 4.75 4.50 64.0 72.0 - 11 PIPER PA-38-112 O-235-L2C 1.70 1.70 56.0 60.0 - 11 PIPER PA-42 CHEYENNE PT6A-41 10.50 9.40 70.3 77.1 - 10,11 PIPER PA-44-180 O-360-E1A6D 3.80 3.80 62.0 71.0 - 11 PAGE 50
APPENDIX 2, CHANGE 1
ESTIMATED MAXIMUM A-WEIGHTED SOUND LEVELS MEASURED IN ACCORDANCE WITH PART-36 APPENDIX -C- PROCEDURES
TOGW MLW TO APP APP MANUFACTURER AIRPLANE ENGINE 1000 LBS 1000 LBS dBA dBA FLAPS NOTES PIPER PA-44-180T(2BLD) TO-360-E1A6D 3.90 3.90 62.0 71.0 - 11 PIPER PA-44-180T(3BLD) TO-360-E1A6D 3.90 3.90 60.0 71.0 - 11 PIPER PA-46-31P MALIBU TSIO-520-BE 4.10 4.10 70.0 63.9 - 11 PIPER PA-602P IO-540-AA1A5 6.00 6.00 66.0 73.0 - 11 PIPER PA-60-600 IO-540-K1J5 5.50 5.50 66.0 73.0 - 11 RAYTHEON HAWKER 125- 1A TFE731-3-1H 21.20 19.55 70.4 83.3 25* 8,15 RAYTHEON HAWKER 125- 1A TFE731-3-1H 21.20 19.55 70.4 85.8 45 8,15 RAYTHEON HAWKER 125- 1A TFE731-3-1H 21.70 19.55 71.2 83.3 25* 8,15 RAYTHEON HAWKER 125- 1A TFE731-3-1H 21.70 19.55 71.2 85.8 45 8,15 RAYTHEON HAWKER 125- 1A VIPER-522 21.20 19.60 83.1 98.5 50 8,15 RAYTHEON HAWKER 125- 3A TFE731-3-1H 21.70 20.00 71.2 83.5 25* 8,15 RAYTHEON HAWKER 125- 3A TFE731-3-1H 21.70 20.00 71.2 86.0 45 8,15 RAYTHEON HAWKER 125- 3A/R VIPER-522 22.70 20.00 84.8 98.7 50 8,15 RAYTHEON HAWKER 125- 3A/RA TFE731-3-1H 23.60 20.00 72.4 83.0 25* 8,15 RAYTHEON HAWKER 125- 3A/RA TFE731-3-1H 23.60 20.00 72.4 85.5 45 8,15 RAYTHEON HAWKER 125- 3A/RA VIPER-522 22.70 20.00 84.8 98.7 45 8,15 RAYTHEON HAWKER 125- 400A TFE731-3-1H 23.60 20.00 72.4 83.0 25* 8,15 RAYTHEON HAWKER 125- 400A TFE731-3-1H 23.60 20.00 72.4 85.5 45 8,15 RAYTHEON HAWKER 125- 400A VIPER-522 23.60 20.00 85.3 98.7 45 8,15 RAYTHEON HAWKER 125- 600A TFE731-3-1H 25.50 22.00 75.8 83.6 25* 8,15 RAYTHEON HAWKER 125- 600A TFE731-3-1H 25.50 22.00 75.8 86.1 45 8,15 RAYTHEON HAWKER 125- 600A VIPER 601-22 25.50 22.00 81.9 96.0 45 8,15,16 RAYTHEON HAWKER 125- 700A TFE731-3-1H 24.20 22.00 75.4 83.6 25* 8,15,26 RAYTHEON HAWKER 125- 700A TFE731-3-1H 24.20 22.00 75.4 86.1 45 8,15,26 RAYTHEON HAWKER 125- 700A TFE731-3-1H 25.50 22.00 75.8 83.6 25* 8,15,26 RAYTHEON HAWKER 125- 700A TFE731-3-1H 25.50 22.00 75.8 86.1 45 8,15,26 RAYTHEON HAWKER 125- 700A TFE731-3R-1H 25.50 22.00 76.1 83.5 25* 8,15,20,26 PAGE 51
AC36-3H 4/5/2012 APPENDIX 2, CHANGE 1
ESTIMATED MAXIMUM A-WEIGHTED SOUND LEVELS MEASURED IN ACCORDANCE WITH PART-36 APPENDIX -C- PROCEDURES
TOGW MLW TO APP APP MANUFACTURER AIRPLANE ENGINE 1000 LBS 1000 LBS dBA dBA FLAPS NOTES RAYTHEON HAWKER 125- 700A TFE731-3R-1H 25.50 22.00 76.1 86.0 45 8,15,20,26 RAYTHEON HAWKER 125- 800A TFE731-5R-1H 27.40 23.35 69.7 82.5 25* 8,15 RAYTHEON HAWKER 125- 800A TFE731-5R-1H 27.40 23.35 69.7 82.5 25* 8,15,20 RAYTHEON HAWKER 125- 800A TFE731-5R-1H 27.40 23.35 69.7 85.0 45 8,15 RAYTHEON HAWKER 125- 800A TFE731-5R-1H 27.40 23.35 69.7 85.0 45 8,15,20 RAYTHEON HAWKER 125- 800XP TFE731-5BR-1H 28.00 23.35 68.2 82.6 45 8,15 RAYTHEON HAWKER 125-1000A PW305 31.00 25.00 71.8 82.2 25* 8,15 RAYTHEON HAWKER 125-1000A PW305 31.00 25.00 71.8 82.9 45 8,15 SAAB 2000 AE2100A 49.60 47.40 63.5 78.9 20 8,15 SAAB SF340A (Dowty props) GE CT7-5A2 27.27 26.50 62.7 75.8 20 8,15 SAAB SF340A (Dowty props) GE CT7-5A2 28.00 27.20 62.9 82.0 20 8,15 SAAB SF340B (Dowty props) GE CT7-9B 28.50 28.00 63.4 82.0 20 8,15 SAAB SF340B (Dowty props) GE CT7-9B 29.00 28.50 64.1 82.0 20 8,15 SAAB SF340B (HS14RF-19 props) GE CT7-9B 28.50 28.00 63.5 78.8 20 8,15 SAAB SF340B (HS14RF-19 props) GE CT7-9B 29.00 28.50 64.2 78.8 20 8,15 SAAB FAIRCHILD SF340 GE CT7-5A2 27.30 26.50 65.3 80.0 35 12 SABRELINER CORP. SABRE 40A JT12A-8 19.60 17.50 83.4 92.0 - 8,12 SABRELINER CORP. SABRE 60 JT12A-8 20.10 17.50 84.7 92.0 24 8,12 SABRELINER CORP. SABRE 60A JT12A-8 22.70 20.60 83.8 95.4 - 8,12 SABRELINER CORP. SABRE 65 TFE731-3R-1D 24.00 21.80 70.8 81.7 - 8,12 SABRELINER CORP. SABRE 70 JT12A-8 21.00 18.50 87.9 93.8 - 8,12 SABRELINER CORP. SABRE 75A CF700-2D-2 23.00 22.00 77.7 90.3 25 4 SABRELINER CORP. SABRE 80 CF700-2D-2 23.30 22.00 79.6 90.3 25 12 SABRELINER CORP. SABRE 80A CF700-2D-2 25.50 22.00 80.5 91.0 - 12 SHORTS 3-30 PT6A-45A 22.40 22.10 71.2 81.8 - 8,15 SHORTS 3-60 PT6A-65R 26.40 26.10 67.9 80.1 30 8,15 SHORTS SD3-60-300 PT6A-67R 27.10 26.50 68.3 84.0 30 13 PAGE 52
4/5/2012 APPENDIX 2, CHANGE 1 AC 36-3H MEASURED IN ACCORDANCE WITH PART-36 APPENDIX -C- PROCEDURES
ESTIMATED MAXIMUM A-WEIGHTED SOUND LEVELS
MANUFACTURER SHORTS
AIRPLANE SKYVAN ENGINE TPE-331-201 TOGW 1000 LBS
12.50 MLW 1000 LBS
12.50 TO dBA
71.6 APP dBA
77.3 FLAPS APP 46 NOTES VICKERS ARMSTRONGS VISCOUNT 745 RR DART6 MK510 72.50 64.00 78.1 84.6 - 11 PAGE 53
Reference Notes * Less than maximum flap setting.
1. Engines equipped with P-36 acoustical treatment.
2. Quiet nacelles and double wall fan duct treatment.
3. Double wall fan duct treatment.
4. Retain from AC 36-3A.
5. Estimated using non-certification measurement data.
6. Nacelle with fixed lip inlet.
7. Increased takeoff thrust rating.
8. Thrust cutback used.
9. ICAO Annex 16 certification data source.
10. DOT/FAA noise measurements.
11. Propeller noise estimation model.
12. Certification spectra analyzed to obtain dBA.
13. Estimated using certification data from aircraft with similar engines.
14. Estimated using the Integrated Noise Model (INM).
15. Based on manufacturer’s data.
16. Equipped with hushkit.
17. Equipped with Learavia engine suppressor nozzle and ECR 936.
18. Equipped with Learavia engine suppressor nozzle.
19. DGAC noise measurements.
20. Equipped with thrust reversers.
21. Estimated using 14 CFR part 36, Appendix G certification data.
22. Airbrake open on approach.
23. Equipped with Noise Reduction Inlet.
24. Fed Ex lightweight hushkit
25. Fed Ex heavyweight hushkit
26. Data for TFE-731-3R-1H also applies to TFE-731-3-1H
27. Equipped with modification M3530
28. Equipped with Boeing inlet.
29. Equipped with Burbank Aeronautical Corporation inlet.
30. AvAero lightweight hushkit
31. AvAero heavyweight hushkit
32. AvAero heavyweight hushkit with lightweight hushkit nozzle
33. Equipped with STAR3 STC ST00258SE
34. Equipped with STAR3 STC ST00259SE
35. Engines equipped with 48 fan outlet guide vanes Page 1
AC 36-3H, Change 1 04/05/2012 Reference Notes
37. Re-engined with JT8D-200 series engines and MD-80 nacelles in the outboard positions. Original JT8D engine retained in center position with new internal exhaust gas mixer and new acoustically treated tailpipe.
38. Auxiliary power unit off for approach.
39. Data for PW2037 (BG-3) also applies to PW2037 (BG-12).
40. Engines equipped with Cutback Fan Blades and Quiet Fan Case.
41. Engines equipped with non-Cutback Fan Blades and Quiet Fan Case.
42. Mod Sup 39; Propeller RPM limited to 850 for approach.
43. Equipped with Modification HCM00020R
44. Equipped with auxiliary power unit.
45. Not equipped with auxiliary power unit.
46. Data also applies to center engine JT8D-9A/-15/-15A/-17/-17A/-17R/-17AR(APR Deactivated) derated to JT8D-9 thrust rating.
47. Data also applies to center engine JT8D-15A/-17/-17A/-17R/-17AR(APR Deactivated) derated to JT8D-15 thrust rating.
48. Data also applies to center engine JT8D-17A/-17R/-17AR(APR Deactivated) derated to JT8D-17 thrust rating.
49. Data also applies to center engine JT8D-9A/-15/-15A/-17/-17A/-17R/-17AR(APR Deactivated) derated per AFM Supplement.
50. Data also applies to center engine JT8D-15A/-17/-17A/-17R/-17AR(APR Deactivated) derated per AFM Supplement.
51. Center Engine Takeoff Thrust Is Derated.
52. Original Production configuration (treated tailcone).
53. Modified Production configuration (hardwall tailcone).
54. DAC Engines (Dual Annular Combustor).
55. 737-700 IGW (Increased Gross Weight).
56. Equipped With Winglets (W).
57. Engine build G01 through G06.
58. Engine build G07, G08, G09, G12, G13 or G15.
59. Engine build configuration PW4090 or PW4090-3.
60. Short Field Performance (SFP).