P.180 Avanti II/EVO Airplane Flight Manual

P.180 AVANTI EVO - MSN 3001+ P.180 AVANTI II - MSN 1105 - 2999 AIRPLANE FLIGHT MANUAL Airplanes Serial Numbers 1105 - 2999; 3001 and up Report No. 180-MAN-0010-01100 Serial No. ________________________ Issue Date: October 21, 2005 Registration No. __________________ THIS AIRPLANE FLIGHT MANUAL IS APPROVED BY THE EUROPEAN AVIATION SAFETY AGENCY. FOR THE U.S. REGISTERED AIRPLANES THIS HANDBOOK IS APPROVED IN ACCORDANCE WITH THE PROVISIONS OF 14 CFR SECTION 21.29, AND IS REQUIRED BY FAA TYPE CERTIFICATE DATA SHEET NO. A59EU. EASA Approval Date: October 21, 2005 THIS MANUAL CONSTITUTES THE EASA APPROVED AIRPLANE FLIGHT MANUAL. THIS MANUAL MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES. Piaggio Aviation Headquarters - Viale Generale Disegna, 1 17038 Villanova d’Albenga, SV Italy Rev. B0: Mar. 04, 2019 All Cover 1 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Cover 2 Issued: October 21, 2005 All Rev. B0 : Mar. 04, 2019 P.180 AVANTI EVO - MSN 3001+ P.180 AVANTI II - MSN 1105 - 2999 AIRPLANE FLIGHT MANUAL Airplanes Serial Numbers 1105 - 2999; 3001 and up Report No. 180-MAN-0010-01100 Serial No. ________________________ Issue Date: October 21, 2005 Registration No. __________________ THIS AIRPLANE FLIGHT MANUAL IS APPROVED BY THE EUROPEAN AVIATION SAFETY AGENCY. EASA Approval Date: October 21, 2005 THIS MANUAL CONSTITUTES THE EASA APPROVED AIRPLANE FLIGHT MANUAL. THIS MANUAL MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES. Piaggio Aviation Headquarters - Viale Generale Disegna, 1 17038 Villanova d’Albenga, SV Italy Rev. B0: Mar. 04, 2019 1105-2999 Canadian a/c Cover 1 .a P.180 AVANTI II AIRPLANE FLIGHT MANUAL INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Cover 2 .a 1105-2999 Canadian a/c Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 P.180 AVANTI EVO - MSN 3001+ P.180 AVANTI II - MSN 1105 - 2999 AIRPLANE FLIGHT MANUAL Airplanes Serial Numbers 1105 - 2999; 3001 and up Report No. 180-MAN-0010-01100 Serial No. ________________________ Issue Date: October 21, 2005 Registration No. __________________ THIS AIRPLANE FLIGHT MANUAL IS APPROVED BY THE EUROPEAN AVIATION SAFETY AGENCY ON BEHALF OF THE “AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL” FOR BRAZILIAN REGISTERED AIRCRAFT, IN ACCORDANCE WITH THE "REGULAMENTOS BRASILEIROS DE HOMOLOGAÇÃO AERONÁUTICA" (RBHA) 21, SECTION 21.29. Brazilian AFM: EASA Approval No. 10031940 Date: September 23, 2010 THIS AIRCRAFT SHALL BE OPERATED IN ACCORDANCE WITH THE LIMITATION AND INSTRUCTIONS HEREIN ESTABLISHED. Piaggio Aviation Headquarters - Viale Generale Disegna, 1 17038 Villanova d’Albenga, SV Italy Rev. B0: Mar. 04, 2019 1105-2999 Brazilian a/c Cover1 .b P.180 AVANTI II AIRPLANE FLIGHT MANUAL INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Cover 2 .b 1105-2999 Brazilian a/c Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II / EVO LIST OF EFFECTIVE PAGES Re-Issue ...... B0 ............... March 04, 2019 Page Rev. Appl.(MSN) Cover-1 Cover-2 Cover-1.a B0 B0 B0 Cover-2.a B0 Cover-1.b B0 Cover-2.b B0 LOEP-1 LOEP-2 LOEP-3 LOEP-4 LOEP-5 LOEP-6 LOEP-7 LOEP-8 LOR-1 LOR-2 LOM-1 LOM-2 ROER-1 ROER-2 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 1-i 1-ii 1-1 1-2 1-3 1-4 1-5 1-6 1-7 1-8 1-9 1-10 1-11 1-12 1-13 1-14 1-15 1-16 1-17 1-18 2-i 2-ii 2-1 2-2 2-3 2-4 2-5.A B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 2-5.B B0 2-6 2-7.A B0 B0 All All 1105-2999 Canadian a/c 1105-2999 Canadian a/c 1105-2999 Brazilian a/c 1105-2999 Brazilian a/c All All All All All All All All All All All All All All 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 1105-2999 Page Rev. Appl.(MSN) 2-7.B B0 2-8 2-9 2-10.A B0 B0 B0 2-10.B B0 2-10.A.a B0 2-10.B.a B0 2-11 2-12 2-13 2-14 2-15 2-16.A B0 B0 B0 B0 B0 B0 2-16.B B0 2-17 2-18 2-19 2-20.A B0 B0 B0 B0 2-20.B B0 2-21 2-22 2-23 2-24 2-25 2-26 2-26.b B0 B0 B0 B0 B0 B0 B0 2-27 2-28 2-27.b B0 B0 B0 2-28.b B0 2-29 2-30 2-30.a B0 B0 B0 2-31 2-32 2-33 2-33.a B0 B0 B0 B0 2-34 2-35 2-35.a B0 B0 B0 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66+Canadian a/c 1105-2999 PT6A-66B+Canadian a/c 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 1105-2999 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 Brazilian a/c 1105-2999 1105-2999 1105-2999 Brazilian a/c 1105-2999 Brazilian a/c 1105-2999 1105-2999 1105-2999 Canadian a/c 1105-2999 1105-2999 1105-2999 1105-2999 Canadian a/c 1105-2999 1105-2999 1105-2999 Page Rev. Appl.(MSN) 2-36 2-37 2-38 2-38.a B0 B0 B0 B0 2-39 2-40 2-41 2-42 2-43 2-44 2-45 2-46 2-47 2-48 2-49 2-50 2-51 2-52 2-53 2-54 3-i 3-ii 3-iii 3-iv 3-1 3-2 3-3 3-4 3-5 3-6 3-7 3-8 3-9.A B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 3-10.A B0 3-9.B B0 3-10.B B0 3-11 3-12 3-13 3-14 3-15 3-16 3-17 3-18 3-19 3-20 3-21 3-22 3-23 3-24 3-25 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 Canadian a/c 1105-2999 1105-2999 1105-2999 1105-2999 Canadian a/c 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 Rep. 180-MAN-0010-01100 All Page LOEP-1 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL Page Rev. Appl.(MSN) Page Rev. Appl.(MSN) Page Rev. Appl.(MSN) 3-26 3-27 3-28 3-29 3-30 3-31 3-32 3-33 3-34 3-35 3-36 3-37 3-38 3-39 3-40 3-41 3-42 3-43 3-44 3-45 3-46 3-47 3-48 3-49 3-50 3-51 3-52 3-53 3-54 3-55 3-56 3-57 3-58 3-61 3-62 3-63 3-64 3-65 3-66 3-67 3-68.A B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 4-28.B B0 B0 3-69.A B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 4-26 4-27 4-28.A 3-68.B 3-85 3-86 3-87 3-88 3-89 3-90 3-91 3-92 3-93 3-94 3-95 3-96 3-97 3-98 3-99 3-100 3-101 3-102 3-103 3-104 3-105 3-106 3-107 3-108 3-109 3-110 3-111 3-112 3-113 3-114 3-115 3-116 3-117 3-118 4-i 4-ii 4-iii 4-iv 4-1 4-2 4-3 4-4 4-5 4-6 4-7 4-8 4-9 4-10 4-11 4-12 4-13 4-14 4-15 4-16 4-17 4-18 4-19 4-20 4-21 4-22 4-23 4-24 4-25 4-29 4-30 4-31 4-32 4-33 4-34 4-35 4-36 4-37 4-38 4-39 4-40 4-41 4-42 4-43 4-44 4-45 4-46 4-47 4-48 4-49 4-50 4-51 4-52 4-53 4-54 4-55 4-56 4-57 4-58 4-59 4-60 4-61 4-62 4-63 4-64 4-65 4-66 4-67 4-68 4-69 4-70 4-71 4-72 4-73 4-74 4-75 4-76 4-77 4-78.A 4-77 4-78.B 4-79 4-80 4-81 4-82 4-83 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 3-69.B B0 3-70 3-71 3-72 3-73 3-74 3-75 3-76 3-77 3-78 3-79 3-80 3-81 3-82 3-83 3-84 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 Rep. 180-MAN-0010-01100 Page LOEP-2 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 Issued: October 21, 2005 All Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL Page Rev. Appl.(MSN) Page Rev. Appl.(MSN) 4-84 4-85 4-86 4-87 4-88 4-89 4-90 4-91 4-92 4-93 4-94 4-95 4-96 4-97 4-98 4-99 4-100 4-101 4-102 4-103 4-104 4-105 4-106 4-107 4-108 4-109 4-110 4-111 4-112 4-113 4-114 4-115 4-116 5-i 5-ii 5-iii 5-iv 5-1 5-2 5-3 5-4 5-5 5-6 5-7 5-8 5-9 5-10 5-11 5-12 5-13 5-14 5-15 5-16 5-17 5-18 5-19 5-20 5-21 5-22 5-23.A B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 5-25.A B0 5-24.A B0 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 5-26.A B0 5-27.A B0 5-28.A B0 5-29.A B0 5-30.A B0 5-31.A B0 5-32.A B0 5-33.A B0 5-34.A B0 5-35.A B0 5-36.A B0 5-37.A B0 5-38.A B0 5-39.A B0 5-40.A B0 5-41.A B0 5-42.A B0 5-43.A B0 5-44.A B0 5-45.A B0 5-46.A B0 5-47.A B0 5-48.A B0 5-49.A B0 5-50.A B0 5-51.A B0 5-52.A B0 5-53.A B0 5-54.A B0 5-55.A B0 5-56.A B0 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 P.180 AVANTI II / EVO Page Rev. Appl.(MSN) 5-57.A B0 5-58.A B0 5-59.A B0 5-60.A B0 5-61.A B0 5-62.A B0 5-63.A B0 5-64.A B0 5-65.A B0 5-66.A B0 5-67.A B0 5-68.A B0 5-69.A B0 5-70.A B0 5-71.A B0 5-72.A B0 5-73.A 5-74.A B0 B0 5-75.A 5-76.A B0 B0 5-77.A B0 5-78.A B0 5-79.A B0 5-80.A B0 5-81.A B0 5-82.A B0 5-83.A B0 5-84.A B0 5-85.A 5-86.A 5-87.A B0 B0 B0 5-88.A B0 5-89.A B0 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 1105-2999 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 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Appl.(MSN) Page 5-90.A B0 5-91.A B0 5-92.A B0 5-23.B B0 5-24.B B0 5-25.B B0 5-26.B B0 5-27.B B0 5-28.B B0 5-29.B B0 5-30.B B0 5-31.B B0 5-32.B B0 5-33.B B0 5-34.B B0 5-35.B B0 5-36.B B0 5-37.B B0 5-38.B B0 5-39.B B0 5-40.B B0 5-41.B B0 5-42.B B0 5-43.B B0 5-44.B B0 5-45.B B0 5-46.B B0 5-47.B B0 5-48.B B0 5-49.B B0 5-50.B B0 5-51.B B0 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66 eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 Rev. Appl.(MSN) 5-52.B B0 5-53.B B0 5-54.B B0 5-55.B B0 5-56.B B0 5-57.B B0 5-58.B B0 5-59.B B0 5-60.B B0 5-61.B B0 5-62.B B0 5-63.B B0 5-64.B B0 5-65.B B0 5-66.B B0 5-67.B B0 5-68.B B0 5-69.B B0 5-70.B B0 5-71.B B0 5-72.B B0 5-73.B B0 5-74.B B0 5-75.B B0 5-76.B B0 5-77.B B0 5-78.B B0 5-79.B 5-80.B 5-81.B 5-82.B B0 B0 B0 B0 5-83.B B0 5-84.B B0 Rep. 180-MAN-0010-01100 Page LOEP-4 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 1105-2999 1105-2999 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 Page Rev. Appl.(MSN) 5-85.B B0 5-86.B B0 5-87.B B0 5-88.B B0 5-89.B B0 5-90.B B0 5-91.B 5-92.B 5-93.B B0 B0 B0 5-94.B B0 5-95.B B0 5-96.B B0 5-97.B B0 5-98.B B0 5-92.C A5 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 1105-2999 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. 1105-2999 PT6A-66B eng. MSN 3001+ 1-i.C 1-ii.C 1-1.C 1-2.C 1-3.C 1-4.C 1-5.C 1-6.C 1-7.C 1-8.C 1-9.C 1-10.C 1-11.C 1-12.C 1-13.C 1-14.C 1-15.C 1-16.C 1-17.C 1-18.C 2-i.C 2-ii.C 2-1.C 2-2.C 2-3.C 2-4.C 2-5.C 2-6.C 2-7.C 2-8.C 2-9.C 2-10.C 2-11.C B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ Issued: October 21, 2005 All Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II / EVO Page Rev. Appl.(MSN) Page Rev. Appl.(MSN) Page Rev. Appl.(MSN) 2-12.C 2-13.C 2-14.C 2-15.C 2-16.C 2-17.C 2-18.C 2-19.C 2-20.C 2-21.C 2-22.C 2-23.C 2-24.C 2-25.C 2-26.C 2-27.C 2-28.C 2-29.C 2-30.C 2-31.C 2-32.C 2-33.C 2-34.C 2-35.C 2-36.C 2-37.C 2-38.C 2-39.C 2-40.C 2-41.C 2-42.C 2-43.C 2-44.C 2-45.C 2-46.C 2-47.C 2-48.C 2-49.C 2-50.C 2-51.C 2-52.C 2-53.C 2-54.C 2-55.C 2-56.C 3-i.C 3-ii.C 3-iii.C 3-iv.C 3-1.C 3-2.C 3-3.C 3-4.C 3-5.C 3-6.C 3-7.C 3-8.C 3-9.C 3-10.C 3-11.C 3-12.C 3-13.C 3-14.C B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 3-15.C 3-16.C 3-17.C 3-18.C 3-19.C 3-20.C 3-21.C 3-22.C 3-23.C 3-24.C 3-25.C 3-26.C 3-27.C 3-28.C 3-29.C 3-30.C 3-31.C 3-32.C 3-33.C 3-34.C 3-35.C 3-36.C 3-37.C 3-38.C 3-39.C 3-40.C 3-41.C 3-42.C 3-43.C 3-44.C 3-45.C 3-46.C 3-47.C 3-48.C 3-49.C 3-50.C 3-51.C 3-52.C 3-53.C 3-54.C 3-55.C 3-56.C 3-57.C 3-58.C 3-59.C 3-60.C 3-61.C 3-62.C 3-63.C 3-64.C 3-65.C 3-66.C 3-67.C 3-68.C 3-69.C 3-70.C 3-71.C 3-72.C 3-73.C 3-74.C 3-75.C 3-76.C 3-77.C B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 3-78.C 3-79.C 3-80.C 3-81.C 3-82.C 3-83.C 3-84.C 3-85.C 3-86.C 3-87.C 3-88.C 3-89.C 3-90.C 3-91.C 3-92.C 3-93.C 3-94.C 3-95.C 3-96.C 3-97.C 3-98.C 3-99.C 3-100.C 3-101.C 3-102.C 3-103.C 3-104.C 3-105.C 3-106.C 3-107.C 3-108.C 3-109.C 3-110.C 3-111.C 3-112.C 3-113.C 3-114.C 3-115.C 3-116.C 3-117.C 3-118.C 3-119.C 3-120.C 3-121.C 3-122.C 4-i.C 4-ii.C 4-iii.C 4-iv.C 4-1.C 4-2.C 4-3.C 4-4.C 4-5.C 4-6.C 4-7.C 4-8.C 4-9.C 4-10.C 4-11.C 4-12.C 4-13.C 4-14.C B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ Rep. 180-MAN-0010-01100 All Page LOEP-5 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL Page Rev. Appl.(MSN) Page Rev. Appl.(MSN) Page Rev. Appl.(MSN) 4-15.C 4-16.C 4-17.C 4-18.C 4-19.C 4-20.C 4-21.C 4-22.C 4-23.C 4-24.C 4-25.C 4-26.C 4-27.C 4-28.C 4-29.C 4-30.C 4-31.C 4-32.C 4-33.C 4-34.C 4-35.C 4-36.C 4-37.C 4-38.C 4-39.C 4-40.C 4-41.C 4-42.C 4-43.C 4-44.C 4-45.C 4-46.C 4-47.C 4-48.C 4-49.C 4-50.C 4-51.C 4-52.C 4-53.C 4-54.C 4-55.C 4-56.C 4-57.C 4-58.C 4-59.C 4-60.C 4-61.C 4-62.C 4-63.C 4-64.C 4-65.C 4-66.C 4-67.C 4-68.C 4-69.C 4-70.C 4-71.C 4-72.C 4-73.C 4-74.C 4-75.C 4-76.C 4-77.C B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 4-78.C 4-79.C 4-80.C 4-81.C 4-82.C 4-83.C 4-84.C 4-85.C 4-86.C 4-87.C 4-88.C 4-89.C 4-90.C 4-91.C 4-92.C 4-93.C 4-94.C 4-95.C 4-96.C 4-97.C 4-98.C 4-99.C 4-100.C 4-101.C 4-102.C 4-103.C 4-104.C 4-105.C 4-106.C 4-107.C 4-108.C 4-109.C 4-110.C 4-111.C 4-112.C 4-113.C 4-114.C 4-115.C 4-116.C 4-117.C 4-118.C 4-119.C 4-120.C 5-i.C 5-ii.C 5-1.C 5-2.C 5-3.C 5-4.C 5-5.C 5-6.C 5-7.C 5-8.C 5-9.C 5-10.C 5-11.C 5-12.C 5-13.C 5-14.C 5-15.C 5-16.C 5-17.C 5-18.C B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 5-19.C 5-20.C 5-21.C 5-22.C 5-23.C 5-24.C 5-25.C 5-26.C 5-27.C 5-28.C 5-29.C 5-30.C 5-31.C 5-32.C 5-33.C 5-34.C 5-33.C 5-34.C 5-35.C 5-36.C 5-37.C 5-38.C 5-39.C 5-40.C 5-41.C 5-42.C 5-43.C 5-44.C 5-45.C 5-46.C 5-49.C 5-50.C 5-51.C 5-52.C 5-53.C 5-54.C 5-55.C 5-56.C 5-57.C 5-58.C 5-59.C 5-60.C 5-61.C 5-62.C 5-63.C 5-64.C 5-65.C 5-66.C 5-67.C 5-68.C 5-69.C 5-70.C 5-71.C 5-72.C 5-73.C 5-74.C 5-75.C 5-76.C 5-77.C 5-78.C 5-79.C 5-80.C 5-81.C B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 B0 MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ Rep. 180-MAN-0010-01100 Page LOEP-6 MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ Issued: October 21, 2005 All Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL Page Rev. Appl.(MSN) 5-82.C 5-83.C 5-84.C 5-85.C 5-86.C 5-87.C 5-88.C 5-89.C 5-90.C B0 A5 A7 A5 A5 A5 A5 A5 A5 Supplements i-B0 Supplements ii-B0 P.180 AVANTI II / EVO MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ MSN 3001+ All All Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Rep. 180-MAN-0010-01100 All Page LOEP-7 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page LOEP-8 Issued: October 21, 2005 All Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II / EVO LOG OF REVISIONS Rev. No. Revised Pages B0 -- Description of Revision Approved under the Authority of DOA N. EASA.21J.685 NOTE: AFM Re-issue B0 introduces the following Temporary Changes that have Appr. Form N. FM-PA-180-0010 been applied on last AFM Rev. A7: 75, 79, 80 (80EC), 81, 82, 83, 84, 85, 86, Date: Mar. 08, 2019 88, 89 (89EC), 91, 94, 95, 96, 99, 100,101. First Re-Issue Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Approval Date Rep. 180-MAN-0010-01100 All Page LOR-1 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page LOR-2 Issued: October 21, 2005 All Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II / EVO LIST OF MODIFICATIONS In the following a list of EASA approved Design Changes to the Type Design (Modifications) which are mentioned in the AFM is reported. Where applicable, relating Service Bulletin is listed. Mod. No. S.B. No. Description Note 80-0743 80-0226 Integrated Stand-by Instrument upgrade 80-0932 80-0286 Avanti II Steering System Electrical Integration Design Change 80-0953 80-0317 Introduction of RP-3 fuel (“Jet 3 fuel”) in the list of applicable fuels 80-0983 - Installation of safety belt provided with dual Y type shoulder harness on the side facing two place divan (low back) 80-0947 80-0339 (80-0332) FMS upgrade to 4.0 status & GPS for SBAS 80-1038 80-0376 Introduction of fuels as per GOST 10227-86 in the list of applicable fuels 80-1091 81-0014 80-0424 P.180 Extended Range - Additional fuselage tank 80-1123 - Installation of new Nose Wheel Steering (NWSS) 80-1283 80-0430 TAT heater inhibition on-ground when Magnaghi Landing Gear is installed 80-1312 80-0457 TAT heater inhibition on-ground when Dowty Landing Gear is installed 80-1295 - (1) New 50 cu.ft. oxygen bottle (1) 81-0014 applicable to MSN 3001+ only Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Rep. 180-MAN-0010-01100 All Page LOM-1 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page LOM-2 Issued: October 21, 2005 All Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II / EVO RECORD OF EMBODIMENT OR REMOVAL Retain this Record inside the Manual. On receipt of embodiment pages (i.e. Manual Revisions, Optional Supplements, Temporary Revisions, etc.) make an entry in the Record Table inserting Description, Issue Date, Embodiment Date and Initials. In case of removal pages (Temporary Revisions, Supplements, etc.) make an entry in the Record Table inserting Description, Issue Date, Removal Date and Initials. RECORD OF EMBODIMENT OR REMOVAL Description Issue Date Embodim. Date Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 By Removal Date By Rep. 180-MAN-0010-01100 All Page ROER-1 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL RECORD OF EMBODIMENT OR REMOVAL (CONT.) Description Issue Date Embodim. Date Rep. 180-MAN-0010-01100 Page ROER-2 By Removal Date By Issued: October 21, 2005 All Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL TABLE OF CONTENTS SECTION 1 - GENERAL TABLE OF CONTENTS Paragraph No. 1.0 1.1 1.2 1.3 Page No. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-1 Applicability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-1 Revisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-2 Airplane Flight Manual Contents . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-4 Three View . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-5 Symbols, Abbreviations and Terminology . . . . . . . . . . . . . . . . . . . .1-6 General Airspeed Terminology and Symbols. . . . . . . . . . . . . . . . . .1-6 Meteorological Terminology . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-8 Power Terminology . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-9 Engine Controls and Instruments . . . . . . . . . . . . . . . . . . . . . . . . . .1-10 Airplane Performance and Flight Planning Terminology . . . . . . . .1-11 Weight and Balance Terminology . . . . . . . . . . . . . . . . . . . . . . . . .1-12 Cabin Pressure Control Terminology . . . . . . . . . . . . . . . . . . . . . . .1-14 Avionics System Acronyms and Abbreviations . . . . . . . . . . . . . . .1-16 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-i P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL TABLE OF CONTENTS INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page 1-ii 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL INTRODUCTION SECTION 1 - GENERAL 1.0 INTRODUCTION APPLICABILITY Applicability of this Airplane Flight Manual is limited to the specific P.180 AVANTI II model airplane designated by the serial number and registration number on the face of the title page of this Manual. This Manual cannot be used for operation purposes unless kept in a current status. Starting from Revision A4 of this Airplane Flight Manual, alternative pages, dedicated to airplanes installing certain modifications or registered in certain Countries, are introduced. Dedicated pages are identified by an Identification Code (located near the page number) and by a flag on the page footer. The Identification Code, also reported in the List of Effective Pages (LOEP), allows a quick identification of the affected pages. In the following, a list of involved modifications or Countries is reported, with relevant page Identification Code. Country Modification Modification reference Ident. Code Canada - - .a Brazil - - .b - PT6A-66 engines (basic P.180 engines) .A - PT6A-66B engines Mod. 80-0657 or S.B. 80-0231 .B Referring to the List of Effective Pages (LOEP), a tailored AFM can be prepared for P.180 Avanti II that installs modifications and/or is registered in one of the Countries above reported: the AFM is composed by pages listed with the suffix “1105-2999” plus the pages listed with relating Identification Code. Pages with an Identification Code as per the list above, supersede the pages with the same number without Identification Code. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-1 P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL INTRODUCTION When a page is affected by multiple modifications or Countries, a multiple Identification Code is reported. Examples: - for a P.180 Avanti II airplane installing PT6A-66B engines: page 2-5.A -> not applicable page 2-5.B -> applicable - for a P.180 Avanti II Canadian registered airplane : page 2-33 -> not applicable page 2-33.a -> applicable - for a P.180 Avanti II Canadian registered airplane installing PT6A-66 engines: page 2-10.A -> not applicable page 2-10.B -> not applicable page 2-10.A.a -> applicable page 2-10.B.a -> not applicable REVISIONS The information compiled in the Airplane Flight Manual will be kept current by revisions distributed to the airplane owners. Revision material will consist of information necessary to update the text of the present manual and/or to add information to cover added airplane modifications. REVISIONS The original issue is identified by the revision code A0. Subsequent revisions are identified by the revision date and code: A1 for the first, A2 for the second, etc. A complete reissue of the manual will be identified by the revision code B0. Subsequent revisions of the reissue will be identified as follows: B1 the first, B2 the second, etc. Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the manual in accordance with the instructions given below: a. Revision pages will replace only pages with the same page number. b. Insert all additional pages in proper numerical order within each section. NOTE It is the responsibility of the owner to maintain this handbook in a current status when it is being used for operational purposes. Rep. 180-MAN-0010-01100 Page 1-2 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL INTRODUCTION IDENTIFICATION OF REVISED MATERIAL Revised text and illustrations shall be indicated by a black vertical line along the external margin of the page, opposite revised, added or deleted material. A line along the external margin of the page opposite the page number will indicate that an entire page was either renumbered or added. Black lines will indicate only current revisions with changes and additions to or deletions of existing text and illustrations. Changes in capitalization, spelling, punctuation or the physical location of material on a page will not be identified by symbols. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-3 P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL AIRPLANE FLIGHT MANUAL CONTENTS 1.1 AIRPLANE FLIGHT MANUAL CONTENTS The AFM content is constituted by the following sections: – Section 1: GENERAL – Section 2: LIMITATIONS EASA Approved (*) – Section 3: EMERGENCY PROCEDURES EASA Approved (*) – Section 4: NORMAL PROCEDURES EASA Approved Pages: (*) Pages approved to meet Type Certification requirements: from 4-1 to 4-112, (Including 4-28.A,4-28.B,4-78.A and 4-78.B) 4-116. – Section 5: PERFORMANCE EASA Approved Pages (*): Pages approved to meet Type Certification requirements: 5-17, 5-18, 5-20, 5-21, 5-23.A, 5-25.A, 5-26.A, 5-30.A, 5-32.A, 5-39.A, 5-41.A, 5-76.A, 5-77.A, 5-78.A, 5-80.A, 5-81.A, 5-82.A, 5-91.A,5-92.A 5-23.B,5-25.B, 5-27.B, 5-32.B, 5-35.B,5-36.B,5-37.B, 5-39.B, 5-40.B, 5-44.B,5-46.B, 5-47.B,5-82.B,5-84.B, 5-86.B,5-88.B,5-97.B,5-98.B. – SUPPLEMENTS EASA Approved (*) NOTE Embodiment of each supplement is required only when the related optional system is installed on the airplane. (*) = or approved by a suitable Design Organisation Approval (DOA). Rep. 180-MAN-0010-01100 Page 1-4 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL THREE VIEW 1.2 THREE VIEW Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-5 P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY 1.3 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and terminology used throughout the Manual and those which may be of added operational significance to the pilot. GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS CAS Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. KCAS Calibrated Airspeed expressed in "Knots". GS Ground Speed is the speed of an airplane relative to the ground IAS Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error. IAS values published in this handbook assume zero instrument error. KIAS Indicated Airspeed expressed in "Knots". M Mach Number is the ratio of true airspeed to the speed of sound. TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility. KTAS True Airspeed expressed in "Knots". VA Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane. VFE Maximum Flap Extended Speed is the highest speed permissible with flaps in a prescribed extended position. VFO Maximum Flap Operating Speed is the maximum speed at which the flaps can be safely extended or retracted. VLE Maximum Landing Gear Extended Speed is the maximum speed at which an aircraft can be safely flown with the landing gear extended. VLLE Maximum Landing Light Extended Speed is the maximum speed at which the aircraft can be safely flown with the landing light extended. Rep. 180-MAN-0010-01100 Page 1-6 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS (CONT.) VLO Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted. VMCA Air Minimum Control Speed is the minimum flight speed at which the airplane is directionally controllable as determined in accordance with Federal Aviation Regulations. Airplane certification conditions include one engine becoming inoperative and windmilling; not more than a 5° bank towards the operative engine; takeoff power on operative engine; landing gear up; flaps in takeoff position; and most rearward C.G. VMO/MMO Maximum Operating Limit Speed is the speed limit that may not be deliberately exceeded in normal flight operations. V is expressed in knots and M in a Mach number. VS Stalling Speed or the minimum steady flight speed at which the airplane is controllable. VSI Stalling speed or the minimum steady speed obtained in a specific configuration. VSO Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration. VSSE Intentional One Engine Inoperative Speed is a minimum speed selected by the manufacturer for intentionally rendering one engine inoperative in flight for pilot training. VX Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. VY Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-7 P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY METEOROLOGICAL TERMINOLOGY ISA International Standard Atmosphere in which: 1. The air is a dry perfect gas; 2. The temperature at sea level is 15° Celsius (59° Fahrenheit); 3. The pressure at sea level is 29.92 inches hg. (1013.2 mb); 4. The temperature gradient from sea level to the altitude at which the temperature is – 56.5°C ( – 69.7°F) is – 0.00198°C ( – 0.003564°F) per foot and zero above that altitude. SAT Static Air Temperature is the free air static temperature obtained either from inflight temperature indications or ground meteorological sources, adjusted for instrument error and compressibility effects. TAT Total Ar Temperature. The air temperature including heat rise due to compressibility. Pressure Altitude Altitude measured from standard sea-level pressure (29.92 in. Hg) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. In this handbook, altimeter instrument errors are assumed to be zero. Station Pressure Actual atmospheric pressure at field elevation. Wind The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds. Rep. 180-MAN-0010-01100 Page 1-8 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY POWER TERMINOLOGY Takeoff Power Maximum power permissible during takeoff Maximum Continuous Power Maximum power periods of use. permissible for unrestricted Maximum Climb Power Maximum power permissible during climb. Maximum Cruise Power Maximum power possible during cruise Reverse Thrust The thrust produced when the propeller blades are rotated past flat pitch into the beta range Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-9 P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY ENGINE CONTROLS AND INSTRUMENTS Power Control Lever The lever which modulates engine power from reverse thrust through takeoff power. Condition Lever The lever which requests the propeller governor to maintain propeller rpm at a selected value or feathers the propeller. The lever which controls fuel flow during engine start and selects ground idle and flight idle. Propeller Governor Maintains propeller rpm at selected value. Overspeed Governor Limits propeller speed to 104% of maximum limit in case of a propeller governor failure. Beta Range The region where the propeller blade angle is between the fine pitch stop and the maximum reverse pitch setting and is controlled by the power lever. ITT Indication Indicates Inter-turbine temperature temperature immediately upstream of the free turbine vanes. Gas Generator RPM (NG) Indicates the percent of gas generator rpm Propeller RPM (NP) Indicates propeller speed in rpm. Engine Torquemeter Indicates shaft output torque in %. Rep. 180-MAN-0010-01100 Page 1-10 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Climb Gradient The demonstrated ratio of the change in height during a portion of climb, to the horizontal distance traversed in the same time interval. Demonstrated Crosswind Velocity The demonstrated crosswind velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests, but is not considered a limitation. Accelerate-Stop Distance The distance required to accelerate an airplane to a specified speed and, assuming failure of an engine at the instant that speed is attained, to bring the airplane to a stop. Accelerate-Go Distance The distance required to accelerate an airplane to a specified speed and, assuming failure of an engine at the instant that speed is attained, continue takeoff on the remaining engine to a height of 50 feet. Route Segment A part of a route. Each end of that part is identified by: (1) a geographical location; or (2) a point at which a definite radio fix can be established. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-11 P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY WEIGHT AND BALANCE TERMINOLOGY Reference Datum An imaginary vertical plane from which all horizontal distances are measured for balance purposes. Station A location along the airplane fuselage usually given in terms of distance in inches from the reference datum. Arm The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. Moment The product of the weight of an item multiplied by its arm. (Moment divided by a constant is used to simplify balance calculations by reducing the number of digits). Center of Gravity (C.G.) The point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. C.G. Arm The arm obtained by adding the airplane’s individual moments and dividing the sum by the total weight of the airplane. C.G. Limits The extreme center of gravity locations within which the airplane must be operated at a given weight. Usable Fuel Fuel available for flight planning. Unusable Fuel Fuel remaining after a runout test has been completed in accordance with governmental regulations. Standard Empty Weight Weight of a standard airplane including unusable fuel, full operating fluids and full oil. Basic Empty Weight Standard empty weight plus optional equipment. Payload Weight of occupants, cargo and baggage. Useful Load Difference between takeoff weight or ramp weight if applicable, and basic empty weight. This includes payload and fuel. Rep. 180-MAN-0010-01100 Page 1-12 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY WEIGHT AND BALANCE TERMINOLOGY (CONT.) Maximum Ramp Weight Maximum weight approved for ground maneuver. (It includes weight of start, taxi and run up fuel.) Maximum Takeoff Weight Maximum weight approved for the start of the takeoff run Maximum Landing Weight Maximum weight touchdown. approved for the landing Maximum Zero Fuel Weight Maximum weight exclusive of usable fuel. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-13 P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY CABIN PRESSURE CONTROL TERMINOLOGY Atmospheric Pressure Pressure surrounding the outside of the aircraft and into which primary and secondary outflow valves discharge cabin outflow. Cabin Pressure Pressure within the cabin that is maintained by the cabin pressure control system. Cabin Altitude Control An automatic operation performed by the cabin pressure controller. Differential Pressure (Dp) The difference in pressure between cabin pressure and atmospheric pressure. Depressurization The condition in which cabin altitude is rapidly raised. This emergency measure overrides all automatic functions without affecting the safety features of the outflow/safety valves. Maximum Positive Differential Pressure Control Pneumatic control of cabin pressure when cabin-toatmosphere differential pressure exceeds the normal positive differential pressure setting of the controller logic. This function is controlled by the primary and secondary outflow/safety valves. Minimum Differential Pressure Control Minimum cabin-to-atmosphere differential pressure with the aircraft on the ground and the primary and secondary outflow/safety valves full-open. Negative Differential Pressure Control The pneumatic control of cabin pressure when atmospheric pressure exceeds cabin pressure. This condition can occur during rapid aircraft descent. Normal Positive Differential Control The control of cabin pressure when the cabin-toatmosphere differential pressure exceeds the normal control value generated by the controller. Rep. 180-MAN-0010-01100 Page 1-14 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY CABIN PRESSURE CONTROL TERMINOLOGY (CONT.) "PIP" Mark Describes alignment of the arrowhead used to indicate the position of the rate selection (R) knob and the mark on the face of the cabin pressure selector. Pressurization Control of cabin pressure to an altitude 150 feet below minimum differential pressure control. This is a control function established by throttle advancement for takeoff with the aircraft on the ground. Rate-of-Change The rate at which cabin altitude climbs or descends. Reference Pressure The pressure, retained in the primary and secondary outflow valve head chambers, established as a motivating force for valve movement. Selected Altitude The landing field altitude dialed on the cabin pressure selector with the use of cabin altitude selection (A) knob. True Static Atmosphere The true air pressure outside the aircraft provided to the system by a true static atmosphere pickup at a specific location on the aircraft. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-15 P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY AVIONICS SYSTEM ACRONYMS AND ABBREVIATIONS ACC Acceleration ADC Air Data Computer ADS Air Data System AGL Above Ground Level AHC Attitude Heading Computer AHRS Attitude Heading Reference System ALT Altitude AP Autopilot APPR Approach ATC Air Traffic Control ATT Attitude BARO Barometric Pressure Setting B-RNAV Basic Area Navigation CAT2 Operational Performance Category II CCP Cursor Control Panel CDU Control Display Unit CPA Closest Point of Approach CPL Couple DCP Display Control Panel DH Decision Height DISC Disconnect DME Distance Measuring Equipment DR Dead Reckoning EIS Engine Indicating System EPU Emergency Power Unit FAF Final Approach Fix FD Flight Director FGC Flight Guidance Computer FGP Flight Guidance Panel FGS Flight Guidance System FL Flight Level Rep. 180-MAN-0010-01100 Page 1-16 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY AVIONICS SYSTEM ACRONYMS AND ABBREVIATIONS (CONT.) FLC Flight Level Change FMS Flight Management System GA Go Around GPS Global Positioning System GS Glideslope HDG Heading ILS Instrument Landing System ISI Integrated Standby Instrument LDA Localizer Directional Aid LOC Localizer MDA Minimum Descent Altitude MFD Multifunction Display MNPS Minimum Navigation Performance Specification MSW Master Switch Wheel NAT North Atlantic Tracks NAV Navigation P-RNAV Precision Area Navigation PFD Primary Flight Display PIT Pitch RAD ALT Radio Altimeter RNAV Area Navigation RNP Required Navigation Performance ROL Roll RTU Radio Tuning Unit RVSM Reduced Vertical Separation Minima SDF Simplified Directional Facility SID Standard Instrument Departure SSR Secondary Surveillance Radar STBY Standby SYS System SYNC Synchronization Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 1-17 P.180 AVANTI II AIRPLANE FLIGHT MANUAL GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY AVIONICS SYSTEM ACRONYMS AND ABBREVIATIONS (CONT.) V/UHF Very/Ultra High Frequency VHF Very High Frequency VNAV Vertical Navigation VOR VHF Omnidirectional Radio Range VS Vertical Speed WGS World Geodetic System YD Yaw Damper Rep. 180-MAN-0010-01100 Page 1-18 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS TABLE OF CONTENTS SECTION 2 - LIMITATIONS TABLE OF CONTENTS Paragraph No. Page No. 2.0 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-1 2.1 Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-2 2.2 Airspeed Indication Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-4 2.3 Power Plant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-5 2.4 Starter Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-11 2.5 Power Plant Indication Markings . . . . . . . . . . . . . . . . . . . . . . . . . . .2-12 2.6 System Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-15 2.7 Weight Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-16 2.8 Center of Gravity Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-17 2.9 Maximum Fuel Imbalance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-19 2.10 Maneuver Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-19 2.11 Flight Load Factor Limits (Maneuvering). . . . . . . . . . . . . . . . . . . . .2-19 2.12 Flight Crew Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-19 2.13 Fuel Quantity Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-20 2.14 Maximum Operating Altitude Limits . . . . . . . . . . . . . . . . . . . . . . . .2-20 2.15 Outside Air Temperature Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-21 2.16 Cabin Pressurization Limit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-21 2.17 Maximum Occupancy Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-21 2.18 Systems and Equipment Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-22 2.18.1 Nickel-Cadmium Battery Limitation . . . . . . . . . . . . . . . . . . . . . . . . .2-22 2.18.2 Flap System Limitation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-22 2.18.3 Hydraulic Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-22 2.18.4 Steering System Limitation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-22 2.18.5 Fuel System Limitation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-22 2.18.6 Maximum Tyre Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-22 2.18.7 Cabin Electrical Power Provisions . . . . . . . . . . . . . . . . . . . . . . . . . .2-23 2.18.8 Air Conditioning System Limitation . . . . . . . . . . . . . . . . . . . . . . . . . .2-23 2.18.9 Ferromagnetic Baggage Loads . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-23 2.18.10 Cabin Wireless System Aviator 200 . . . . . . . . . . . . . . . . . . . . . . . . .2-23 2.18.11 Avionics System Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-24 General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-24 Flight Guidance System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-25 Flight Management System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-26 VHF Communication System (for Brazilian A/C only) . . . . . . . . . .2-26 Integrated Stand-by Instrument . . . . . . . . . . . . . . . . . . . . . . . . . . .2-28 Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-29 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 2-i P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS TABLE OF CONTENTS 2.19 2.20 2.21 2.22 2.23 2.24 2.25 2.26 2.27 VNAV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-29 Operation on Unpaved Runways . . . . . . . . . . . . . . . . . . . . . . . . . . 2-30 Cold Weather Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-30 Operation in Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-30 Category II Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-31 Reduced Vertical Separation Minima (RVSM) Operations . . . . . . 2-32 Steep Approach Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-33 Noise Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-34 Kinds of Operations Equipment List (KOEL). . . . . . . . . . . . . . . . . 2-35 Additional Equipment for Cat II Operations . . . . . . . . . . . . . . . . . 2-41 Additional Equipment for RVSM Operations. . . . . . . . . . . . . . . . . 2-42 Additional Equipment for P-RNAV Operations . . . . . . . . . . . . . . . 2-42 Additional Equipment for U.S. RNAV Operations . . . . . . . . . . . . . 2-42 Placards. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-43 Flight Compartment Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-43 Passenger Compartment Placards . . . . . . . . . . . . . . . . . . . . . . . . 2-46 Baggage Compartment Placards . . . . . . . . . . . . . . . . . . . . . . . . . 2-50 External Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-51 Rep. 180-MAN-0010-01100 Page 2-ii 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS GENERAL SECTION 2 - LIMITATIONS 2.0 GENERAL This section provides design limitations, operating limitations, instrument markings, color coding and basic placards necessary for operation of the airplane. Compliance with the limitations of this section is required by regulation. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-1 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS AIRSPEED LIMITATIONS 2.1 AIRSPEED LIMITATIONS SPEED KCAS KIAS DESIGN MANEUVERING SPEED - VA Do not make full or abrupt control movements above this speed 11,550 lb. 7,700 lb. 198 176 199 177 NOTE Linear interpolation may be used for intermediate gross weights. MAXIMUM FLAP OPERATING SPEED - VFO Do not extend or retract flap at the given setting above this speed UP to MID MID to DN 169 149 170 150 MAXIMUM FLAP EXTENDED SPEED - VFE Do not exceed this speed at the given flap setting Flap MID Flap DN 179 173 180 175 MAXIMUM LANDING GEAR OPERATING SPEED - VLO Do not extend or retract landing gear above this speed 179 180 MAXIMUM LANDING GEAR EXTENDED SPEED - VLE Do not extend this speed with landing gear extended 184 185 MAXIMUM LANDING LIGHT OPERATING SPEED - VLLO Do not extend or retract landing light above this speed 159 160 MAXIMUM LANDING LIGHT EXTENDED SPEED - VLLE Do not exceed this speed with landing light extended 159 160 AIR MINIMUM CONTROL SPEED - VMCA This is the minimum flight speed at which the airplane is directionally and laterallly controllable, determined in accordance with the Federal Aviation Regulations and Regolamento Tecnico (ENAC) Autofeather system operative (propeller feathered) Propeller windmilling 99 127 100 128 MAXIMUM OPERATING SPEED LIMIT - VMO/MMO Do not exceed this airspeed in any operation (See Figure 2-1 on page 2-3) Rep. 180-MAN-0010-01100 Page 2-2 Appr. DOA EASA.21J.685 1105-2999 258/.694 260/.70 Mach Mach Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS AIRSPEED LIMITATIONS Figure 2-1. Maximum Operating Speed Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-3 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS AIRSPEED INDICATION MARKINGS 2.2 AIRSPEED INDICATION MARKINGS Airspeed Markings on the Primary Flight Display: MARKING SIGNIFICANCE KIAS White “MID” Pointer Maximum Flap Operating Speed with flaps in MID setting 170 White “DN” Pointer Maximum Flap Operating Speed with flaps in Down setting 150 Horizontal Blue Line One-Engine-Inoperative Best Rate-ofClimb Speed 140 Horizontal Red Line Air Minimum Control Speed (VMCA) Autofeather system ON 100 Red Line Maximum Operating Speed (VMO) Rep. 180-MAN-0010-01100 Page 2-4 – Sea level - 30,500 feet – 30,500 - 41,000 feet Appr. DOA EASA.21J.685 1105-2999 260 260 to 205 (0.70 Mach) Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 2.3 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS POWER PLANT LIMITATIONS LIMITATIONS POWER PLANT LIMITATIONS a. Number of Engines 2 b. Engine Manufacturer Pratt & Whitney Canada c. Engine Model Number PT6A-66 d. Engine Operating Limits OPERATING CONDITION (1) OPERATING LIMITS OIL PRESS. PSIG (3) OIL TEMP. °C (10) (11) 830 (8) 104.1 2000 90 to 135 0 to 104 830 (8) 104.1 2000 90 to 135 0 to 104 TORQUE % (2) MAX N % N P OBSERV. G 2000 1900 1800 (7) RPM POWER SETTING SHP ITT°C RPM RPM RPM TAKEOFF 850 100.0 MAX. CONT. MAX. CLIMB AND MAX. CRUISE 850 100.0 806 100.0 762 100.0 NORMAL CLIMB AND NORMAL CRUISE - - 850 100.0 806 100.0 762 100.0 MIN. IDLE - - - STARTING - - - TRANSIENT 123.3 123.3 123.3 (5) (5) (5) MAX. REVERSE Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 - - - 820 (8) Climb 0 to 104 104.1 2000 90 to 135 Cruise 20 to 104 750 (6) 1000 (4) 870 (5) - 60 (MIN) -40 to 110 - - 200 (MAX) -40 (MIN) 104.1 2205 40 to 200 (9) (5) 760 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. 51 - 1900 90 to 135 0 to 110 0 to 104 Rep. 180-MAN-0010-01100 Page 2-5 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT LIMITATIONS 1. Engine inlet condition limits for engine operation: Altitude: – 1,000 to 41,000 feet. 2. 100% torque corresponds to 2230 lb·ft. Torque limit applies within a range of 1600 to 2000 propeller rpm; below 1600 rpm torque is limited to 49.3% (1100 lb·ft). Torquemeter - Power Calculations SHP = RPM (NP) x torque (lb·ft) x K Where: NP = propeller RPM K = 0.00019 3. Normal oil pressure is 90 to 135 psig at gas generator speeds above 72% and with a normal oil temperature of 60 to 70°C (140 to 158°F). Oil pressures under 90 psig are undesirable. Under emergency conditions, to complete a flight, a lower oil pressure limit of 60 psig is permissible at reduced power settings not exceeding 49.3% (1100 lb·ft) torque. Oil pressures below 60 psig are unsafe and require that the engine be shutdown and land as soon as practical performing the SINGLE ENGINE APPROACH AND LANDING Procedure. 4. This value is time limited to 5 seconds. 5. These values are time limited to 20 seconds. 6. Applies to a speed range between 54% and 61% NG. 7. 100% gas generator speed corresponds to 37,468 rpm. 100% power turbine speed corresponds to 33,235 rpm. 8. The temperatures shown are the maximum ITTs permissible under the Certification limitations. For normal operations, power management during takeoff, climb and cruise as shown in the power setting tables of Section 5 should be observed for warranted engine life. However, lower temperatures (785°C for Takeoff Maximum Continuous Climb and Maximum Cruise) will produce rated horsepower (ISA) when the engine is new and result in longer engine life. 9. May be used in emergency conditions to complete the flight. 10. Oil temperature above 104°C or below 20°C must only be tolerated in accordance with the procedure contained in this manual. Oil temperature limits are -40°C to 104°C (-40°F to 219°F) with limited periods of 10 minutes at 104°C to 110°C (219°F to 230°F): 11. For increased service life of engine oil, an oil temperature below 80°C (176°F) is recommended. A minimum oil temperature of 55°C (130°F) is recommended for fuel heater operation at takeoff power. Rep. 180-MAN-0010-01100 Page 2-6 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 2.3 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS POWER PLANT LIMITATIONS LIMITATIONS POWER PLANT LIMITATIONS a. Number of Engines 2 b. Engine Manufacturer Pratt & Whitney Canada c. Engine Model Number PT6A-66B d. Engine Operating Limits OPERATING CONDITION (1) OPERATING LIMITS OIL PRESS. PSIG (3) OIL TEMP. °C (10) (11) 830 (8) 104.1 2000 90 to 135 0 to 104 830 (8) 104.1 2000 90 to 135 0 to 104 TORQUE % (2) MAX N % N P OBSERV. G 2000 1900 1800 (7) RPM POWER SETTING SHP ITT°C RPM RPM RPM TAKEOFF 850 100.0 MAX. CONT. MAX. CLIMB AND MAX. CRUISE 850 100.0 806 100.0 762 100.0 NORMAL CLIMB AND NORMAL CRUISE - - 850 100.0 806 100.0 762 100.0 MIN. IDLE - - - STARTING - - - TRANSIENT 123.3 123.3 123.3 (5) (5) (5) MAX. REVERSE Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 - - - 820 (8) Climb 0 to 104 104.1 2000 90 to 135 Cruise 20 to 104 750 (6) 1000 (4) 870 (5) - 60 (MIN) -40 to 110 - - 200 (MAX) -40 (MIN) 104.1 2205 40 to 200 (9) (5) 760 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. 51 - 1900 90 to 135 0 to 110 0 to 104 Rep. 180-MAN-0010-01100 Page 2-5 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT LIMITATIONS 1. Engine inlet condition limits for engine operation: Altitude: – 1,000 to 41,000 feet. 2. 100% torque corresponds to 2230 lb·ft. Torque limit applies within a range of 1600 to 2000 propeller rpm; below 1600 rpm torque is limited to 49.3% (1100 lb·ft). Torquemeter - Power Calculations SHP = RPM (NP) x torque (lb·ft) x K Where: NP = propeller RPM K = 0.00019 3. Normal oil pressure is 90 to 135 psig at gas generator speeds above 72% and with a normal oil temperature of 60 to 70°C (140 to 158°F). Oil pressures under 90 psig are undesirable. Under emergency conditions, to complete a flight, a lower oil pressure limit of 60 psig is permissible at reduced power settings not exceeding 49.3% (1100 lb·ft) torque. Oil pressures below 60 psig are unsafe and require that the engine be shutdown and land as soon as practical performing the SINGLE ENGINE APPROACH AND LANDING Procedure. 4. This value is time limited to 5 seconds. 5. These values are time limited to 20 seconds. 6. Applies to a speed range between 54% and 61% NG. 7. 100% gas generator speed corresponds to 37,468 rpm. 100% power turbine speed corresponds to 33,235 rpm. 8. The temperatures shown are the maximum ITTs permissible under the Certification limitations. For normal operations, power management during takeoff, climb and cruise as shown in the power setting tables of Section 5 should be observed for warranted engine life. However, lower temperatures (785°C for Takeoff Maximum Continuous Climb and Maximum Cruise) will produce rated horsepower (ISA) when the engine is new and result in longer engine life. 9. May be used in emergency conditions to complete the flight. 10. Oil temperature above 104°C or below 20°C must only be tolerated in accordance with the procedure contained in this manual. Oil temperature limits are -40°C to 104°C (-40°F to 219°F) with limited periods of 10 minutes at 104°C to 110°C (219°F to 230°F): 11. For increased service life of engine oil, an oil temperature below 80°C (176°F) is recommended. A minimum oil temperature of 55°C (130°F) is recommended for fuel heater operation at takeoff power. Rep. 180-MAN-0010-01100 Page 2-6 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS POWER PLANT LIMITATIONS 2.0 POWER PLANT LIMITATIONS RECOMMENDED AIR START ENVELOPE PROPELLER FEATHERED Minimum NG for Airstart 13% NOTE Air start may be attempted outside of the envelope, or lower NG provided ITT starting limit is monitored and not exceeded. e. Generator Limits Limit the load on each generator as follows, except during starting: ALTITUDE (FT) On Ground S.L. to 41,000 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 GEN. LOAD (AMPS) 200 400 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 2-7 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT LIMITATIONS f. Fuel Specifications JP-4, JP-8, Jet A, Jet A-1 and Jet B and RP-3 (as per GB6537), PT (or RT) and TC-1(or TS-1) (as per GOST 10227) fuels conforming to the latest revision of P&WC Service Bulletin No. 14004. It is not necessary to purge the unused fuel from the system when switching fuel types. Aviation Gasoline is not permitted. CAUTION Fuel Anti-ice additive must be used as per the latest revision of P&WC Service Bulletin No. 14004 (including Phillips PFA 55 MB, MIL-I-27686D and MIL-I-27686E)except for JP-4 and JP-8. Refer to the Airplane Maintenance Manual for blending instruction. Some fuel suppliers blend anti-icing additive in their storage tanks. Prior to refueling check with the fuel supplier to determine if fuel has been blended. To assure proper concentration by volume of fuel on board, blend only enough additive for the unblended fuel. g. Oil Specifications Only MOBIL JET OIL II, AEROSHELL TURBINE OIL 500, CASTROL 5000 and EXXON TURBO OIL 2380 engine oils have been tested and are approved for use on the P.180 airplane within the recommendations of the latest revision of P&WC Engine Service Bulletin No. 14001. The other oils listed in the above P&WC Engine Service Bulletin are not approved for use on the P.180 airplane. h. Number of Propellers i. Propeller Manufacturer j. Propeller Hub Models 2 Hartzell Left (CW Rotating) Right (CCW Rotating) HC-E5N-3 or HC-E5N-3A HC-E5N-3L or HC-E5N-3AL k. Propeller Blade Models Left (CW Rotating, inner tip down) Right (CCW Rotating, inner tip down) Rep. 180-MAN-0010-01100 Page 2-8 Appr. DOA EASA.21J.685 1105-2999 HE8218 LE8218 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS POWER PLANT LIMITATIONS 2.0 POWER PLANT LIMITATIONS RECOMMENDED AIR START ENVELOPE PROPELLER FEATHERED Minimum NG for Airstart 10% NOTE Air start may be attempted outside of the envelope, or lower NG provided ITT starting limit is monitored and not exceeded. e. Generator Limits Limit the load on each generator as follows, except during starting: ALTITUDE (FT) On Ground S.L. to 41,000 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 GEN. LOAD (AMPS) 200 400 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 2-7 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT LIMITATIONS f. Fuel Specifications JP-4, JP-8, Jet A, Jet A-1 and Jet B and RP-3 (as per GB6537), PT (or RT) and TC-1(or TS-1) (as per GOST 10227) fuels conforming to the latest revision of P&WC Service Bulletin No. 14004. It is not necessary to purge the unused fuel from the system when switching fuel types. Aviation Gasoline is not permitted. CAUTION Fuel Anti-ice additive must be used as per the latest revision of P&WC Service Bulletin No. 14004 (including Phillips PFA 55 MB, MIL-I-27686D and MIL-I-27686E)except for JP-4 and JP-8. Refer to the Airplane Maintenance Manual for blending instruction. Some fuel suppliers blend anti-icing additive in their storage tanks. Prior to refueling check with the fuel supplier to determine if fuel has been blended. To assure proper concentration by volume of fuel on board, blend only enough additive for the unblended fuel. g. Oil Specifications Only MOBIL JET OIL II, AEROSHELL TURBINE OIL 500, CASTROL 5000 and EXXON TURBO OIL 2380 engine oils have been tested and are approved for use on the P.180 airplane within the recommendations of the latest revision of P&WC Engine Service Bulletin No. 14001. The other oils listed in the above P&WC Engine Service Bulletin are not approved for use on the P.180 airplane. h. Number of Propellers i. Propeller Manufacturer j. Propeller Hub Models 2 Hartzell Left (CW Rotating) Right (CCW Rotating) HC-E5N-3 or HC-E5N-3A HC-E5N-3L or HC-E5N-3AL k. Propeller Blade Models Left (CW Rotating, inner tip down) Right (CCW Rotating, inner tip down) Rep. 180-MAN-0010-01100 Page 2-8 Appr. DOA EASA.21J.685 1105-2999 HE8218 LE8218 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS POWER PLANT LIMITATIONS l. 2.0 Number of Blades POWER PLANT LIMITATIONS 5 m. Propeller Diameter, nominal 85 in. (2.16 m.) n. Propeller Blade Angles at 30 in. Station (nominal) Feathered Reverse 89° –13° o. Propeller Speed (rpm) Takeoff and Climb Cruise 2000 1800/2000 WARNING Stabilized ground operation below 900 RPM is prohibited, except when feathered operation at or below 600 RPM. Stabilized ground operation between 1300 and 1600 RPM is prohibited. CAUTION Feather operation for training purposes should be limited to speeds below 150 KIAS. Sustained ground operation (more than 30 minutes), especially at power settings higher than Ground Idle or with frequent application of power should be avoided. Static operation at torque settings higher than 22.4% (500 lb·ft) must not last for more than 2 minutes, after that a cooling period of 20 minutes at Ground Idle or 10 minutes with engines OFF must be observed. p. Autofeather System Limits WARNING No takeoff authorized with autofeather inoperative 1. The autofeather system must be pre flight checked operational prior to takeoff 2. The autofeather system must be used for takeoff and landing operations. It is recommended to disengage the autofeather system at speeds above 150 KIAS. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-9 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT LIMITATIONS q. Use of the reverse thrust (condition levers fully forward). WARNING Positioning of power levers below the flight idle stop in flight is prohibited. Such positioning may lead to loss of airplane control or may result in an engine overspeed condition and consequent loss of engine power. CAUTION The reverse thrust must be initiated only after the propeller speed has dropped 5% from the set value (for example, 1900 RPM with condition lever at MAX RPM). Use of reverse before the 5% propeller RPM drop may result in asymmetrical thrust. Refer to Section 5 of this AFM for recommended airspeed. Ground static operation at full reverse power for more than 12 seconds is prohibited, to avoid propeller blade overtemperature. Cool down 20 minutes at Ground Idle before repeating. WARNING If the airplane is equipped with S.B. 80-0286 (mod. 80-0932), use of reverse thrust is prohibited below 40 KIAS r. Power handling at altitude. When flying above 30000 ft with two engines operating and one bleed OFF or one engine running at NG lower than 86% and the other at full power, the power lever of the engine at zero bleed or at low power must be advanced slowly in the range from idle to 86% NG. Rep. 180-MAN-0010-01100 Page 2-10 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS POWER PLANT LIMITATIONS l. 2.0 Number of Blades POWER PLANT LIMITATIONS 5 m. Propeller Diameter, nominal 85 in. (2.16 m.) n. Propeller Blade Angles at 30 in. Station (nominal) Feathered Reverse 89° –13° o. Propeller Speed (rpm) Takeoff and Climb Cruise 2000 1800/2000 WARNING Stabilized ground operation below 900 RPM is prohibited, except when feathered operation at or below 600 RPM. Stabilized ground operation between 1300 and 1600 RPM is prohibited. CAUTION Feather operation for training purposes should be limited to speeds below 150 KIAS. Sustained ground operation (more than 30 minutes), especially at power settings higher than Ground Idle or with frequent application of power should be avoided. Static operation at torque settings higher than 22.4% (500 lb·ft) must not last for more than 2 minutes, after that a cooling period of 20 minutes at Ground Idle or 10 minutes with engines OFF must be observed. p. Autofeather System Limits WARNING No takeoff authorized with autofeather inoperative 1. The autofeather system must be pre flight checked operational prior to takeoff 2. The autofeather system must be used for takeoff and landing operations. It is recommended to disengage the autofeather system at speeds above 150 KIAS. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-9 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT LIMITATIONS q. Use of the reverse thrust (condition levers fully forward). WARNING Positioning of power levers below the flight idle stop in flight is prohibited. Such positioning may lead to loss of airplane control or may result in an engine overspeed condition and consequent loss of engine power. CAUTION The reverse thrust must be initiated only after the propeller speed has dropped 5% from the set value (for example, 1900 RPM with condition lever at MAX RPM). Use of reverse before the 5% propeller RPM drop may result in asymmetrical thrust. Refer to Section 5 of this AFM for recommended airspeed. Ground static operation at full reverse power for more than 12 seconds is prohibited, to avoid propeller blade overtemperature. Cool down 20 minutes at Ground Idle before repeating. WARNING If the airplane is equipped with S.B. 80-0286 (mod. 80-0932), use of reverse thrust is prohibited below 40 KIAS r. Power handling at altitude. When flying above 30000 ft with two engines operating and one bleed OFF, the power lever of the engine with bleed OFF must be advanced slowly. When flying above 35000 ft with one engine running at low NG and the other one at full power, the power lever of the engine running at lower NG must be advanced slowly. Rep. 180-MAN-0010-01100 Page 2-10 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS POWER PLANT LIMITATIONS l. 2.0 Number of Blades POWER PLANT LIMITATIONS 5 m. Propeller Diameter, nominal 85 in. (2.16 m.) n. Propeller Blade Angles at 30 in. Station (nominal) Feathered Reverse 89° –13° o. Propeller Speed (rpm) Takeoff and Climb Cruise 2000 1800/2000 WARNING Stabilized ground operation below 900 RPM is prohibited, except when feathered operation at or below 600 RPM. Stabilized ground operation between 1300 and 1600 RPM is prohibited. CAUTION Feather operation for training purposes should be limited to speeds below 150 KIAS. Sustained ground operation (more than 30 minutes), especially at power settings higher than Ground Idle or with frequent application of power should be avoided. Static operation at torque settings higher than 22.4% (500 lb·ft) must not last for more than 2 minutes, after that a cooling period of 20 minutes at Ground Idle or 10 minutes with engines OFF must be observed. p. Autofeather System Limits WARNING No takeoff authorized with autofeather inoperative 1. The autofeather system must be pre flight checked operational prior to takeoff 2. The autofeather system must be used for takeoff and landing operations. It is recommended to disengage the autofeather system at speeds above 150 KIAS. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-9 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT LIMITATIONS q. Use of the reverse thrust (condition levers fully forward). WARNING Positioning of power levers below the flight idle stop in flight is prohibited. Such positioning may lead to loss of airplane control or may result in an engine overspeed condition and consequent loss of engine power. CAUTION The reverse thrust must be initiated only after the propeller speed has dropped 5% from the set value (for example, 1900 RPM with condition lever at MAX RPM). Use of reverse before the 5% propeller RPM drop may result in asymmetrical thrust. Refer to Section 5 of this AFM for recommended airspeed. Ground static operation at full reverse power for more than 12 seconds is prohibited, to avoid propeller blade overtemperature. Cool down 20 minutes at Ground Idle before repeating. Go-around after selecting reverse thrust on the ground is prohibited WARNING If the airplane is equipped with S.B. 80-0286 (mod. 80-0932), use of reverse thrust is prohibited below 40 KIAS r. Power handling at altitude. When flying above 30000 ft with two engines operating and one bleed OFF or one engine running at NG lower than 86% and the other at full power, the power lever of the engine at zero bleed or at low power must be advanced slowly in the range from idle to 86% NG. Rep. 180-MAN-0010-01100 Appr. DOA EASA.21J.685 Issued: October 21, 2005 Page 2-10 .A.a 1105-2999 PT6A-66+Canadian a/c Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS POWER PLANT LIMITATIONS l. 2.0 Number of Blades POWER PLANT LIMITATIONS 5 m. Propeller Diameter, nominal 85 in. (2.16 m.) n. Propeller Blade Angles at 30 in. Station (nominal) Feathered Reverse 89° –13° o. Propeller Speed (rpm) Takeoff and Climb Cruise 2000 1800/2000 WARNING Stabilized ground operation below 900 RPM is prohibited, except when feathered operation at or below 600 RPM. Stabilized ground operation between 1300 and 1600 RPM is prohibited. CAUTION Feather operation for training purposes should be limited to speeds below 150 KIAS. Sustained ground operation (more than 30 minutes), especially at power settings higher than Ground Idle or with frequent application of power should be avoided. Static operation at torque settings higher than 22.4% (500 lb·ft) must not last for more than 2 minutes, after that a cooling period of 20 minutes at Ground Idle or 10 minutes with engines OFF must be observed. p. Autofeather System Limits WARNING No takeoff authorized with autofeather inoperative 1. The autofeather system must be pre flight checked operational prior to takeoff 2. The autofeather system must be used for takeoff and landing operations. It is recommended to disengage the autofeather system at speeds above 150 KIAS. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-9 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT LIMITATIONS q. Use of the reverse thrust (condition levers fully forward). WARNING Positioning of power levers below the flight idle stop in flight is prohibited. Such positioning may lead to loss of airplane control or may result in an engine overspeed condition and consequent loss of engine power. CAUTION The reverse thrust must be initiated only after the propeller speed has dropped 5% from the set value (for example, 1900 RPM with condition lever at MAX RPM). Use of reverse before the 5% propeller RPM drop may result in asymmetrical thrust. Refer to Section 5 of this AFM for recommended airspeed. Ground static operation at full reverse power for more than 12 seconds is prohibited, to avoid propeller blade overtemperature. Cool down 20 minutes at Ground Idle before repeating. Go-around after selecting reverse thrust on the ground is prohibited WARNING If the airplane is equipped with S.B. 80-0286 (mod. 80-0932), use of reverse thrust is prohibited below 40 KIAS r. Power handling at altitude. When flying above 30000 ft with two engines operating and one bleed OFF, the power lever of the engine with bleed OFF must be advanced slowly. When flying above 35000 ft with one engine running at low NG and the other one at full power, the power lever of the engine running at lower NG must be advanced slowly. Rep. 180-MAN-0010-01100 Appr. DOA EASA.21J.685 Issued: October 21, 2005 Page 2-10 .B.a 1105-2999 PT6A-66B+Canadian a/c Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS STARTER LIMITATIONS SECTION 2 - LIMITATIONS 2.4 STARTER LIMITATIONS Use of the starters is limited to 50 seconds ON, three minutes OFF, 40 seconds ON, 30 minutes OFF before a further start may be attempted. Starter operation is limited to 30 seconds if in the meantime at least 13% NG is not reached. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-11 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT INDICATION MARKINGS 2.5 POWER PLANT INDICATION MARKINGS a. Propeller RPM Total Scale Red radial line 0 to 2300 RPM 2000 RPM OPERATING CONDITION NORMAL RANGE (WHITE / GREEN) CAUTION/TRANSIENT RANGE (YELLOW) All 0 to 600 (white) 600 to 900 900 to 1300 (white) 1300 to 1600 RED DISPLAY 1600 to 1800 (white) 1800 to 2000 (green) 2000 to 2050 (green)  15 s 2050 to 2200  15 s 2000 to 2200 > 15 s (steady) > 2200 (flashing) b. Gas Generator NG (%) Total Scale Blue Triangle Red radial line 0 to 109.9% 13% 104.1% OPERATING CONDITION NORMAL RANGE (WHITE / GREEN) Starting  104.1 (white) Eng. running 54 to 104.1 (green) Rep. 180-MAN-0010-01100 Page 2-12 CAUTION/TRANSIENT RANGE (YELLOW) > 104.1 < 54 Appr. DOA EASA.21J.685 1105-2999 RED DISPLAY > 104.1 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS POWER PLANT INDICATION MARKINGS c. Engine Torque (%) Total Scale Red radial line Red Triangle 0 to 125.5% 100.0% 123.3% OPERATING CONDITION NORMAL RANGE (WHITE / GREEN) CAUTION/TRANSIENT RANGE (YELLOW) RED DISPLAY Prop RPM  1600 or Oil Press  90 0 to 100.0 (green) 100.0 to 123.3  15 s 100.0 to 123.3 > 15 s Prop RPM < 1600 or Oil Press < 90  49.3 (green) > 123.3 > 49.3 d. Oil Pressure (PSI) Total Scale Red line 0 to 200 PSI 60 PSI OPERATING CONDITION NORMAL RANGE (WHITE / GREEN) Starting 0 to 200 (white) Eng. running 90 to 135 (green) CAUTION/TRANSIENT RANGE (YELLOW) RED DISPLAY > 200 60 to 90 < 60 135 to 150 > 150 e. Oil Temperature (°C) Total Scale Red line -50° to 120°C 104°C OPERATING CONDITION NORMAL RANGE (WHITE / GREEN) CAUTION/TRANSIENT RANGE (YELLOW) RED DISPLAY All 20 to 104 (green) -40 to 20 < -40 104 to 110  10 m 104 to 110 > 10 m > 110 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-13 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS POWER PLANT INDICATION MARKINGS f. Inter Turbine Temperature - ITT (°C) Total Scale Red radial line Red Dot 0° to 1100°C 830°C 1000°C OPERATING CONDITION NORMAL RANGE (WHITE / GREEN) Starting 0 to 830 (white) CAUTION/TRANSIENT RANGE (YELLOW) RED DISPLAY 830 to 870 (white)  15 s 830 to 870 > 15 s 870 to 1000 (white) 5s 870 to 1000 >5s > 1000 Eng. running 0 to 200 (white) 200 to 820 (green) 820 to 830 830 to 870  15 s 830 to 870 > 15 s > 870 NOTE See Engine Operating Limits for explanation of instrument markings. Rep. 180-MAN-0010-01100 Page 2-14 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS SYSTEM INSTRUMENT MARKINGS 2.6 SYSTEM INSTRUMENT MARKINGS a. Cabin Altitude Differential Pressure Indicator Green Arc (Normal Operating Range) Yellow Arc (Caution) Red Radial (Maximum) 0 to 9.0 PSI 9.0 to 9.7 PSI 9.7 PSI b. Oxygen Pressure Gauge Green Arc (Usable range) Yellow arc (Caution Empty) Yellow arc (Caution Maximum) 250 to 1850 PSI 0 to 250 PSI 1850 to 2000 PSI c. Hydraulic System Pressure Green Arc (Normal Operating Range) Yellow Arc (Caution) 0 to 3050 PSI 3050 to 3600 PSI d. Longitudinal Trim Indicator Green Arc (Takeoff Range) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 2 NU to 6 NU Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-15 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS WEIGHT LIMITS 2.7 WEIGHT LIMITS It is the responsibility of the airplane owner and pilot to assure that the airplane is properly loaded. Maximum allowable weights are listed below. Refer to the "Weight and Balance Manual" for loading instructions. a. Maximum Ramp Weight 11,600 LBS (5262 kg) b. Maximum Takeoff Weight 11,550 LBS (5239 kg) c. Maximum Landing Weight 10,945 LBS (4965 kg) d. Maximum Zero Fuel Weight 9800 LBS (4445 kg) e. Maximum Weight in Rear Baggage Comp. f. 350 LBS (159 kg) Maximum Weight in Cabin Baggage Comp. 90 LBS (41 kg) g. Maximum Specific Load in Rear Baggage Comp. 50 LBS/SQ.FT. (244 kg/sq.m.) h. Maximum Weight in Forward Cabinet (if installed) 34 LBS (15.4 kg) i. Maximum Weight in Refreshment Cabinets (if installed): Refer to applicable Loading Chart of the “Weight and Balance Manual" j. Maximum Weight in Pyramid Cabinet (each) (if installed) Rep. 180-MAN-0010-01100 Page 2-16 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. 10 LBS (4.5 kg) Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS SYSTEM INSTRUMENT MARKINGS 2.6 SYSTEM INSTRUMENT MARKINGS a. Cabin Altitude Differential Pressure Indicator Green Arc (Normal Operating Range) Yellow Arc (Caution) Red Radial (Maximum) 0 to 9.0 PSI 9.0 to 9.7 PSI 9.7 PSI b. Oxygen Pressure Gauge Green Arc (Usable range) Yellow arc (Caution Empty) Yellow arc (Caution Maximum) 250 to 1850 PSI 0 to 250 PSI 1850 to 2000 PSI c. Hydraulic System Pressure Green Arc (Normal Operating Range) Yellow Arc (Caution) 0 to 3050 PSI 3050 to 3600 PSI d. Longitudinal Trim Indicator Green Arc (Takeoff Range) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 2 NU to 6 NU Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-15 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS WEIGHT LIMITS 2.7 WEIGHT LIMITS It is the responsibility of the airplane owner and pilot to assure that the airplane is properly loaded. Maximum allowable weights are listed below. Refer to the "Weight and Balance Manual" for loading instructions. a. Maximum Ramp Weight 11,600 LBS (5262 kg) b. Maximum Takeoff Weight 11,550 LBS (5239 kg) or, in case of Anti-ice ON, as limited by “Maximum Takeoff Weight to achieve Takeoff Climb Requirements” graph (ref. to Figure 5-15/1.) c. Maximum Landing Weight 10,945 LBS (4965 kg) d. Maximum Zero Fuel Weight 9800 LBS (4445 kg) e. Maximum Weight in Rear Baggage Comp. f. 350 LBS (159 kg) Maximum Weight in Cabin Baggage Comp. 90 LBS (41 kg) g. Maximum Specific Load in Rear Baggage Comp. 50 LBS/SQ.FT. (244 kg/sq.m.) h. Maximum Weight in Forward Cabinet (if installed) 34 LBS (15.4 kg) i. Maximum Weight in Refreshment Cabinets (if installed): Refer to applicable Loading Chart of the “Weight and Balance Manual" j. Maximum Weight in Pyramid Cabinet (each) (if installed) Rep. 180-MAN-0010-01100 Page 2-16 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. 10 LBS (4.5 kg) Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS CENTER OF GRAVITY LIMITS 2.8 CENTER OF GRAVITY LIMITS Pounds Weight Kilograms 11,600 8,745 8,500 7,700 6,000 5,262 3,967 3,856 3,493 2,722 Forward Limit Inches Aft of Datum Rearward Limit Inches Aft of Datum 207.80 195.22 194.00 194.00 194.00 214.00 214.00 213.00 209.80 209.80 NOTE Straight line variation between points indicated. The Datum Line is located 236.22 inches (6,000 millimeters) forward of the rear pressure bulkhead centerline (at the intersection between the forward pressure bulkhead and cockpit floor centerlines). Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-17 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS CENTER OF GRAVITY LIMITS Figure 2-2. Airplane Weight vs. Center of Gravity Rep. 180-MAN-0010-01100 Page 2-18 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS MAXIMUM FUEL IMBALANCE 2.9 MAXIMUM FUEL IMBALANCE Maximum allowable fuel imbalance between wing fuel systems is 2.10 200 lbs. MANEUVER LIMITS This is a Normal Category Airplane, no acrobatic maneuvers, including spins, allowed. 2.11 FLIGHT LOAD FACTOR LIMITS (MANEUVERING) a. Positive Load Factor (Flaps Up) 3.22 g b. Negative Load Factor (Flaps Up) –1.29 g c. Positive Load Factor (Flaps Down) 2.00 g 2.12 FLIGHT CREW LIMITS Minimum crew (left seat) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 One Pilot Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-19 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS FUEL QUANTITY LIMITATIONS 2.13 FUEL QUANTITY LIMITATIONS a. Total Fuel Capacity if Mod. 80-1091 or S.B. 80-0424 (“Extended Range”) installed: 421.9 U.S. Gallons (1597 LTS) 479.7 U.S. Gallons (1816 LTS) b. Usable Fuel: Total Fuel System if Mod. 80-1091 or S.B. 80-0424 (“Extended Range”) installed: 418.2 U.S. Gallons (1583 LTS) Each Side Fuel System if Mod. 80-1091 or S.B. 80-0424 (“Extended Range”) installed: 209.1 U.S. Gallons (791.5 LTS) 476 U.S. Gallons (1802 LTS) 238 U.S. Gallons (901 LTS) c. Unusable Fuel: 2.14 Total Fuel System 3.7 U.S. Gallons (14 LTS) Each Side Fuel System 1.85 U.S. Gallons (7 LTS) MAXIMUM OPERATING ALTITUDE LIMITS a. Enroute 41,000 FT b. Take off and Landing 10,000 FT Rep. 180-MAN-0010-01100 Page 2-20 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS MAXIMUM FUEL IMBALANCE 2.9 MAXIMUM FUEL IMBALANCE Maximum allowable fuel imbalance between wing fuel systems is 2.10 200 lbs. MANEUVER LIMITS This is a Normal Category Airplane, no acrobatic maneuvers, including spins, allowed. 2.11 FLIGHT LOAD FACTOR LIMITS (MANEUVERING) a. Positive Load Factor (Flaps Up) 3.22 g b. Negative Load Factor (Flaps Up) –1.29 g c. Positive Load Factor (Flaps Down) 2.00 g 2.12 FLIGHT CREW LIMITS Minimum crew (left seat) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 One Pilot Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-19 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS FUEL QUANTITY LIMITATIONS 2.13 FUEL QUANTITY LIMITATIONS a. Total Fuel Capacity if Mod. 80-1091 or S.B. 80-0424 (“Extended Range”) installed: 421.9 U.S. Gallons (1597 LTS) 479.7 U.S. Gallons (1816 LTS) b. Usable Fuel: Total Fuel System if Mod. 80-1091 or S.B. 80-0424 (“Extended Range”) installed: 418.2 U.S. Gallons (1583 LTS) Each Side Fuel System if Mod. 80-1091 or S.B. 80-0424 (“Extended Range”) installed: 209.1 U.S. Gallons (791.5 LTS) 476 U.S. Gallons (1802 LTS) 238 U.S. Gallons (901 LTS) c. Unusable Fuel: 2.14 Total Fuel System 3.7 U.S. Gallons (14 LTS) Each Side Fuel System 1.85 U.S. Gallons (7 LTS) MAXIMUM OPERATING ALTITUDE LIMITS a. Enroute 41,000 FT b. Take off and Landing 12,000 FT Rep. 180-MAN-0010-01100 Page 2-20 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS OUTSIDE AIR TEMPERATURE LIMITS 2.15 OUTSIDE AIR TEMPERATURE LIMITS a. Minimum (Sea Level) -40°C (-40°F) b. Minimum Temperature for Engine Starting: 1. Engine Oil -40°C (-40°F) 2. JP4, JET B Fuel -54°C (-65°F) 3. JP8, JET A, JET A1, RP-3 Fuel -34°C (-29°F) 4. PT(or RT), TC-1 (or TS-1) Fuel -34°C (-29°F) c. Minimum Temperature for Takeoff -30°C (-22°F) d. Maximum Sea level to 12000 ft pressure altd. Above 12000 ft pressure altd. 2.16 ISA +35°C ISA +21°C CABIN PRESSURIZATION LIMIT a. Maximum Normal Cabin Differential Pressure 9.0 PSI b. Maximum Cabin Differential Pressure 9.7 PSI Do not land when airplane cabin is pressurized 2.17 MAXIMUM OCCUPANCY LIMITS 11 people including crew Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-21 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS 2.18 SYSTEMS AND EQUIPMENT LIMITS 2.18.1 NICKEL-CADMIUM BATTERY LIMITATION No battery engine starting must be attempted if the bus voltage is lower than 23.0 VDC or battery temperature is over 120°F (BAT TEMP caution light ON). No takeoffs authorized with temperature indication over 150°F (BAT OVHT warning light ON). 2.18.2 FLAP SYSTEM LIMITATION No takeoff authorized without flaps or with non symmetrical flap configuration or annunciated flap asymmetry. Maximum operating altitude 2.18.3 20,000 FT HYDRAULIC PUMP Operate continuously only with at least one engine running. Hydraulic pump must be on and operating and nosewheel steering on and operating for single engine taxiing. 2.18.4 STEERING SYSTEM LIMITATION NOTE The following limitations must be observed only for airplanes NOT installing Mod. S.B.80-0454 or 80-0425 (new NWSS): Steering in TAXI position only for ground taxi. Maximum Speed (in T.O. mode) Steering engagement during landing is prohibited. 2.18.5 60 KTS FUEL SYSTEM LIMITATION Crossfeed operation is not approved for takeoff or landing. 2.18.6 MAXIMUM TIRE SPEED The maximum tire speed is Rep. 180-MAN-0010-01100 Page 2-22 154 KTS Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS 2.18.7 CABIN ELECTRICAL POWER PROVISIONS The use of auxiliary cabin electrical power sockets is subject to the manufacturer approval with reference to electrical loads, kind of operations, and compatibility of the connected equipment. 2.18.8 AIR CONDITIONING SYSTEM LIMITATION Cooling Air Conditioning System Maximum Operating Altitude 2.18.9 20,000 FT FERROMAGNETIC BAGGAGE LOADS The Towing bar TRONAIR p/n 01-1227-0000 or other ferromagnetic masses with comparable mass and length are prohibited to be carried in the baggage compartment. 2.18.10 CABIN WIRELESS SYSTEM AVIATOR 200 The Aviator 200 system performance and reliability have not been demonstrated. The flight cannot be scheduled upon the availability of this equipment. The Airworthiness Approval of the wireless system does not constitute Operational Approval for the use of transmitting PEDs (Portable Electronic Devices) on board of the aircraft. Approval must be obtained from the responsible division of the operational Authority of the aircraft’s country of registration prior to conducting this kind of operation. Taken into account what above, the use of the T-PED (Transmitting-PED) is possible also in the passenger cabin. The T-PED use is cleared only for the Wi-fi connection compliant with the standard IEEE 802.11b/g/a/n. The crew must warn the passengers that, before flight, in accordance with national operational requirement, the T-PED shall be set in "FLIGHT" mode. Only the Wi-fi Mode can be activated during flight. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-23 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS 2.18.11 AVIONICS SYSTEM LIMITATIONS GENERAL a. The following documents, at the latest revision, must be carried onboard the airplane at all times: 1. Collins Pro Line 21 Avionics System Operator’s Guide for the Piaggio Avanti P.180, Document Number 523-0806-484 . 2. Collins FMS 3000 Flight Management System Operator’s Guide for the Piaggio Avanti P.180, Document Number 523-0806-485 or 523-0818-105 if Mod. 80-0947 (or S.B. 80-0332 or S.B. 80-0339) is installed. NOTE The Collins Operator’s Guides are published by Collins and has not been approved by ENAC or FAA; they have been written specifically for the P.180 but a specific airplane could not install all the features there described. b. The MFD must be operational prior to engine start. c. Takeoff not authorized if reversionary function fails operating. d. Operating in the composite mode is limited to training and display failure conditions. e. The two Air Data Computers (ADC) must be operative for takeoff. f. The two Attitude Heading Computers (AHC) must be operative for takeoff. g. The Integrated Standby Instrument (ISI) must be operative for takeoff. WARNING Sunglasses with polarized lenses or lenses that are designed to filter specific colors/frequencies of light may adversely affect a pilot’s ability to see some colors shown on PFD/MFD displays. Some elements on the display can be completely invisible while wearing these types of sunglasses. Also, the color of some elements may be changed. For example, some blue light filtering lenses can change magenta to red. For a radar target this represents a reduction in the level of intensity of the target. Rep. 180-MAN-0010-01100 Page 2-24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS SISTEMS AND EQUIPMENT LIMITS 2.0 SISTEMS AND EQUIPMENT LIMITS FLIGHT GUIDANCE SYSTEM a. During autopilot and flight director operation, the pilot must be seated at the controls with seat belt fastened. b. The autopilot is certified for Category II - ILS Approaches. c. Autopilot and yaw damper must be disengaged during takeoff and landing. d. Manual electric trim system PREFLIGHT CHECK must be satisfactorily accomplished prior to the flight. e. Do not engage the autopilot if the airplane is out of trim. f. Maximum speed for autopilot operation is VMO/MMO. g. Minimum speed for autopilot operation is stall warning speed. h. Minimum speed for autopilot operation during single engine flight is stall warning speed. i. Maximum altitude for autopilot operation is 41,000 ft pressure altitude. j. Minimum altitude AGL for autopilot operation (with or without yaw damper engaged) is: 1000 ft (cruise and descent) 400 ft (climb after takeoff) 250 ft (non precision approach) 200 ft (ILS CAT I precision approach - normal or single engine) k. VOR coupled approaches must be conducted in the APPR mode. l. Single engine go around must be performed with autopilot disengaged. m. Coupled approaches, with yaw damper inoperative, must be performed in clean or MID flap configuration. n. Do not override the autopilot to change pitch attitude. NOTE Overriding the autopilot in pitch does not cancel the autopilot automatic trim. If a force is applied to the column with the autopilot engaged, the automatic trim will run to oppose the applied force. This can lead to a severe out-of-trim condition during any phase of flight. o. ILS coupled approaches must be performed at 2000 prop RPM. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-25 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS SISTEMS AND EQUIPMENT LIMITS FLIGHT MANAGEMENT SYSTEM a. IFR enroute and terminal navigation is prohibited unless the pilot verifies either the currency of the database or the accuracy of each selected waypoint and navaid by reference to current approved data. b. The FMS position must be checked for accuracy prior to use as a means of navigation. c. When using the FMS, the airplane must have other approved navigation equipment installed and operating appropriate to the route of flight. d. During oceanic, enroute and terminal area operation with the FMS DR annunciator illuminated, the flight crew must verify the FMS position using VOR/DME raw data or other appropriate means e. During periods of dead reckoning, the FMS shall not be used for navigation. f. All FMS navigation operations are approved within the latitudes bounded by 60° North latitude and 60° South latitude at any longitude. 1. Operation to 70° North latitude is acceptable East of 75° West longitude and West of 120° West longitude. 2. Operation to 80° North latitude is acceptable East of 50° West longitude and West of 70° East longitude. 3. Operation to 70° South latitude is acceptable except for the 45° between 120° East and 165° East longitude. 4. The WGS-84 coordinate reference datum in accordance with the criteria of EASA AMC20-5, FAA AC20-130A, FAA AC91-49 CHG 1, and FAA AC 20-138 must be used. Satellite navigation data is based upon use of only the Global Positioning System (GPS) operated by the United States. Rep. 180-MAN-0010-01100 Page 2-26 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS SISTEMS AND EQUIPMENT LIMITS 2.0 SISTEMS AND EQUIPMENT LIMITS FLIGHT GUIDANCE SYSTEM a. During autopilot and flight director operation, the pilot must be seated at the controls with seat belt fastened. b. The autopilot is certified for Category II - ILS Approaches. c. Autopilot and yaw damper must be disengaged during takeoff and landing. d. Manual electric trim system PREFLIGHT CHECK must be satisfactorily accomplished prior to the flight. e. Do not engage the autopilot if the airplane is out of trim. f. Maximum speed for autopilot operation is VMO/MMO. g. Minimum speed for autopilot operation is stall warning speed. h. Minimum speed for autopilot operation during single engine flight is stall warning speed. i. Maximum altitude for autopilot operation is 41,000 ft pressure altitude. j. Minimum altitude AGL for autopilot operation (with or without yaw damper engaged) is: 1000 ft (cruise and descent) 400 ft (climb after takeoff) 250 ft (non precision approach) 200 ft (ILS CAT I precision approach - normal or single engine) k. VOR coupled approaches must be conducted in the APPR mode. l. Single engine go around must be performed with autopilot disengaged. m. Coupled approaches, with yaw damper inoperative, must be performed in clean or MID flap configuration. n. Do not override the autopilot to change pitch attitude. NOTE Overriding the autopilot in pitch does not cancel the autopilot automatic trim. If a force is applied to the column with the autopilot engaged, the automatic trim will run to oppose the applied force. This can lead to a severe out-of-trim condition during any phase of flight. o. ILS coupled approaches must be performed at 2000 prop RPM. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-25 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS SISTEMS AND EQUIPMENT LIMITS VHF COMMUNICATION SYSTEM (FOR BRAZILIAN A/C ONLY) When operating the VHF/COMM system in Brazilian territory, the use of the 8.33 kHz canals spacing will be able to cause the loss of communication with the Air Traffic Control (ATC). FLIGHT MANAGEMENT SYSTEM a. IFR enroute and terminal navigation is prohibited unless the pilot verifies either the currency of the database or the accuracy of each selected waypoint and navaid by reference to current approved data. b. The FMS position must be checked for accuracy prior to use as a means of navigation. c. When using the FMS, the airplane must have other approved navigation equipment installed and operating appropriate to the route of flight. d. During oceanic, enroute and terminal area operation with the FMS DR annunciator illuminated, the flight crew must verify the FMS position using VOR/DME raw data or other appropriate means e. During periods of dead reckoning, the FMS shall not be used for navigation. f. All FMS navigation operations are approved within the latitudes bounded by 60° North latitude and 60° South latitude at any longitude. 1. Operation to 70° North latitude is acceptable East of 75° West longitude and West of 120° West longitude. 2. Operation to 80° North latitude is acceptable East of 50° West longitude and West of 70° East longitude. 3. Operation to 70° South latitude is acceptable except for the 45° between 120° East and 165° East longitude. 4. The WGS-84 coordinate reference datum in accordance with the criteria of EASA AMC20-5, FAA AC20-130A, FAA AC91-49 CHG 1, and FAA AC 20-138 must be used. Satellite navigation data is based upon use of only the Global Positioning System (GPS) operated by the United States. Rep. 180-MAN-0010-01100 Page 2-26 .b Appr. DOA EASA.21J.685 1105-2999 Brazilian a/c Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS 2.0 SYSTEMS AND EQUIPMENT LIMITS g. Provided the FMS is receiving adequate usable sensor inputs, it has been demonstrated capable of, and has been shown to meet the accuracy specifications of: 1. VFR / IFR enroute RNAV operation in accordance with the criteria of EASA AMC 20-4 and FAA AC 20-130A. 2. VFR / IFR enroute, terminal, and approach operations. 3. The FMS-3000, as installed on the P.180, is approvable for operations in NAT-MNPS “ICE-GREEN” published routes when used in conjunction with the Rockwell Collins Prediction Program, P/N 837-3443-005, or equivalent, which must assure that sufficient GPS integrity will exist for the proposed route of flight. The previous statement is in accordance with the criteria of ENAC/RAI Circular Letter No. 48 dated October 23, 1997, but it does not constitute an operational approval. 4. Operation in European B-RNAV / RNP-5 airspace in accordance with EASA AMC 20-4, FAA AC 90-96 and FAA AC 20-130A. This does not constitute an operational approval to operate in such airspace. 5. Operation in European P-RNAV airspace in accordance with JAA TGL-10 Rev.1 except, if the airplane does not install FMS 3000 ver. 4.1 as per Mod. 80-0947 (or S.B. 80-0332 or S.B. 80-0339), in the final segment of the approach i.e. from the FAWP (FAF) down to the runway. This does not constitute an operational approval to operate in such airspace. 6. Operation in U.S. Terminal and En Route Area Navigation (RNAV1) airspace in accordance with FAA AC No. 90-100A. This does not constitute an operational approval to operate in such airspace. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-27 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS h. FMS based instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the FMS-3000 database. The FMS-3000, as installed on the P.180, is approved for IFR Non-Precision Approach limited to published approaches within the National Airspace System where the A/C is operating and in accordance with the State of operator/registry (as applicable) Aviation Authority requirements. 1. GPS instrument approaches must be conducted with GPS integrity monitoring (RAIM) and must be available by the Final Approach Fix. 2. FMS instrument approaches must be conducted in the approach mode (Flight Guidance System selected APPR), and the FMS APPR (green) annunciator in the PFD must be illuminated at the FAF in order to conduct the instrument approach procedure. Use of FMS guidance for conducting instrument approach procedures is prohibited with the FMS annunciation NO APPR (white or amber) illuminated. 3. Accomplishment of ILS, LOC, LOC-BC, LDA and SDF approaches are not authorized utilizing the FMS from the FAF to the MAP. 4. When an alternate airport is required by the applicable rules, it must be served by an approach based on other than GPS navigation, the airplane must have operational equipment capable of using that navigation aid, and the required navigation aid must be operational. 5. FMS based approaches that are retrieved from the navigation database with an approach name of RNVxxx or VORxxx may be flown provided the VHF navigation receiver is tuned to the reference facility. i. Use of FMS to capture and track a DME arc outside the published end points is prohibited j. Fuel management parameters are advisory only and do not replace the primary fuel quantity indications. INTEGRATED STAND-BY INSTRUMENT When Integrated Stand-By Instrument model GH-3100 is installed, the heading information shown on the Stand-by Instrument (when not upgraded by modification 80-0743 or S.B. 80-0226) is not reliable and must not be used for navigation. Rep. 180-MAN-0010-01100 Page 2-28 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS 2.0 SYSTEMS AND EQUIPMENT LIMITS g. Provided the FMS is receiving adequate usable sensor inputs, it has been demonstrated capable of, and has been shown to meet the accuracy specifications of: 1. VFR / IFR enroute RNAV operation in accordance with the criteria of EASA AMC 20-4 and FAA AC 20-130A. 2. VFR / IFR enroute, terminal, and approach operations. 3. The FMS-3000, as installed on the P.180, is approvable for operations in NAT-MNPS “ICE-GREEN” published routes when used in conjunction with the Rockwell Collins Prediction Program, P/N 837-3443-005, or equivalent, which msut assure that sufficient GPS integrity will exist for the proposed route of flight. The previous statement is in accordance with the criteria of ENAC/RAI Circular Letter No. 48 dated October 23, 1997, but it does not constitute an operational approval. 4. Operation in European B-RNAV / RNP-5 airspace in accordance with EASA AMC 20-4, FAA AC 90-96 and FAA AC 20-130A. This does not constitute an operational approval to operate in such airspace. 5. Operation in European P-RNAV airspace in accordance with JAA TGL-10 Rev.1 except, if the airplane does not install FMS 3000 ver. 4.1 as per Mod. 80-0947 (or S.B. 80-0332 or S.B. 80-0339), in the final segment of the approach i.e. from the FAWP (FAF) down to the runway. This does not constitute an operational approval to operate in such airspace. 6. Operation in U.S. Terminal and En Route Area Navigation (RNAV1) airspace in accordance with FAA AC No. 90-100A. This does not constitute an operational approval to operate in such airspace. h. FMS based instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the FMS-3000 database. The FMS-3000, as installed on the P.180, is approved for IFR Non-Precision Approach limited to published approaches within the National Airspace System where the A/C is operating and in accordance with the State of operator/registry (as applicable) Aviation Authority requirements. 1. GPS instrument approaches must be conducted with GPS integrity monitoring (RAIM) and must be available by the Final Approach Fix. 2. FMS instrument approaches must be conducted in the approach mode (Flight Guidance System selected APPR), and the FMS APPR (green) annunciator in the PFD must be illuminated at the FAF in order to conduct the instrument approach procedure. Use of FMS guidance for conducting Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Brazilian a/c Rep. 180-MAN-0010-01100 Page 2-27 .b P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS instrument approach procedures is prohibited with the FMS annunciation NO APPR (white or amber) illuminated. 3. Accomplishment of ILS, LOC, LOC-BC, LDA and SDF approaches are not authorized utilizing the FMS from the FAF to the MAP. 4. When an alternate airport is required by the applicable rules, it must be served by an approach based on other than GPS navigation, the airplane must have operational equipment capable of using that navigation aid, and the required navigation aid must be operational. 5. FMS based approaches that are retrieved from the navigation database with an approach name of RNVxxx or VORxxx may be flown provided the VHF navigation receiver is tuned to the reference facility. i. Use of FMS to capture and track a DME arc outside the published end points is prohibited j. Fuel management parameters are advisory only and do not replace the primary fuel quantity indications. k. In accordance with Brazilian Information Circular CI 21-013C: 1. Use of FMS based on GPS only is prohibited as primary means for navigation. FMS based on GPS is approved as supplemental means for navigation. 2. FMS approaches based on GPS must be performed with auto-pilot or flight director engaged; 3. The pilot must review the complete transition-approach, comparing the waypoints and altitudes displayed on the FMS with those on the published procedure prior to activation, to insure that the correct procedure and transition are selected. If “RAIM” becomes not available in enroute phase of flight, revert to an alternate means of navigation other than GPS appropriate to the route and phase of flight. When continuing to use GPS navigation, position must be verified every 15 minutes using other IFR approved navigation system. INTEGRATED STAND-BY INSTRUMENT When Integrated Stand-By Instrument model GH-3100 is installed, the heading information shown on the Stand-by Instrument (when not upgraded by modification 80-0743 or S.B. 80-0226) is not reliable and must not be used for navigation. Rep. 180-MAN-0010-01100 Page 2-28 .b Appr. DOA EASA.21J.685 1105-2999 Brazilian a/c Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL SECTION 2 - LIMITATIONS P.180 AVANTI II LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS TRANSPONDER The installed SSR Mode S System satisfies the data requirements of ICAO Doc. 7030/4 Regional Supplementary Procedures for SSR Mode S Enhanced Surveillance in designated European airspace. NOTE The capability to transmit the “Track Angle Rate” data parameter is not available. VNAV CAUTION 1. When using coupled VNAV, the procedure should be flown as retrieved from the navigation database, without manually editing the altitudes in the flight plan. 2. If the database altitude must be changed, the crew should deselect VNAV and use the Altitude pre-selector to comply with the required altitude. a. When using the VNAV system, the barometric altimeters must be used as the primary altitude reference for all operations. b. Use of VNAV guidance for a V-MDA approach that includes a step-down fix between the final approach fix and missed approach point is prohibited. c. VNAV altitudes must be displayed on the MFD map page or CDU legs page when utilizing VNAV for flight guidance. d. Use of VNAV while conducting a missed approach procedure is prohibited. e. Provided the FMS is receiving adequate usable sensor inputs, it has been demonstrated capable of and has been shown to meet the accuracy specifications of VNAV operation in accordance with FAA AC 20-129. Such VNAV approaches must be flown utilizing either the flight director or autopilot. f. VNAV approach guidance to a DA is not authorized if the reported surface temperature is below the Baro-VNAV minimum temperature limitation specified on the applicable RNAV approach procedure chart. NOTE Barometric VNAV guidance during approach including the approach transition, final approach segment and the missed approach procedure is not temperature compensated. Operating at uncompensated minimum IFR altitudes will not provide expected terrain and obstacle clearance for temperature below ISA. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-29 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS OPERATION ON UNPAVED RUNWAYS 2.19 OPERATION ON UNPAVED RUNWAYS When the airplane is equipped with the prescribed protection Kit, operations on unpaved runways are allowed under the limitations requirements, procedures, performance, weight & balance information presented in the Supplement No. 12 "Unpaved Runways Operations" of this Airplane Flight Manual. 2.20 COLD WEATHER OPERATION If ambient temperature is below –25°C, it is necessary to operate the main wing anti-ice and the engine ice vane systems before applying full power to ensure that the autofeather is armed. 2.21 OPERATION IN ICING CONDITIONS Landing must be performed with the flaps in MID position. Minimum Ambient Temperature for operation of engine deicing boots –40°C No takeoff authorized with frost, snow or ice adhering to the propellers, windshields, powerplant installation and pitot/static ports, or with snow or ice adhering to the wings, vertical and horizontal stabilizer or control surfaces. Rep. 180-MAN-0010-01100 Page 2-30 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL SECTION 2 - LIMITATIONS P.180 AVANTI II LIMITATIONS SYSTEMS AND EQUIPMENT LIMITS TRANSPONDER The installed SSR Mode S System satisfies the data requirements of ICAO Doc. 7030/4 Regional Supplementary Procedures for SSR Mode S Enhanced Surveillance in designated European airspace. NOTE The capability to transmit the “Track Angle Rate” data parameter is not available. VNAV CAUTION 1. When using coupled VNAV, the procedure should be flown as retrieved from the navigation database, without manually editing the altitudes in the flight plan. 2. If the database altitude must be changed, the crew should deselect VNAV and use the Altitude pre-selector to comply with the required altitude. a. When using the VNAV system, the barometric altimeters must be used as the primary altitude reference for all operations. b. Use of VNAV guidance for a V-MDA approach that includes a step-down fix between the final approach fix and missed approach point is prohibited. c. VNAV altitudes must be displayed on the MFD map page or CDU legs page when utilizing VNAV for flight guidance. d. Use of VNAV while conducting a missed approach procedure is prohibited. e. Provided the FMS is receiving adequate usable sensor inputs, it has been demonstrated capable of and has been shown to meet the accuracy specifications of VNAV operation in accordance with FAA AC 20-129. Such VNAV approaches must be flown utilizing either the flight director or autopilot. f. VNAV approach guidance to a DA is not authorized if the reported surface temperature is below the Baro-VNAV minimum temperature limitation specified on the applicable RNAV approach procedure chart. NOTE Barometric VNAV guidance during approach including the approach transition, final approach segment and the missed approach procedure is not temperature compensated. Operating at uncompensated minimum IFR altitudes will not provide expected terrain and obstacle clearance for temperature below ISA. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-29 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS OPERATION ON UNPAVED RUNWAYS 2.19 OPERATION ON UNPAVED RUNWAYS NOTE Unpaved runways operations are prohibited 2.20 COLD WEATHER OPERATION If ambient temperature is below –25°C, it is necessary to operate the main wing anti-ice and the engine ice vane systems before applying full power to ensure that the autofeather is armed. 2.21 OPERATION IN ICING CONDITIONS Landing must be performed with the flaps in MID position. Minimum Ambient Temperature for operation of engine deicing boots –40°C No takeoff authorized with frost, snow or ice adhering to the propellers, windshields, powerplant installation and pitot/static ports, or with snow or ice adhering to the wings, vertical and horizontal stabilizer or control surfaces. Rep. 180-MAN-0010-01100 Page 2-30 .a Appr. DOA EASA.21J.685 1105-2999 Canadian a/c Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS CATEGORY II OPERATIONS 2.22 CATEGORY II OPERATIONS a. CAT II approaches are approved only with dual qualified pilot, both engines operating and in mid or full flaps configurations. b. Autopilot and yaw damper must be coupled and both FD1 and FD2 bars in view. CAUTION CAT II monitoring status indication on PFD1 and PFD2 (CAT2 indication green) will be ON even if the autopilot is OFF with either FDs in view or one of the two FDs intentionally disconnected with the autopilot engaged. c. The autopilot, the yaw damper and the FD must be off at and below 100 feet above ground level. d. All the required instrumentation on the pilot's and copilot's side instrument panel must be serviceable before starting a CAT II approach (refer to the KOEL - "Additional Equipment for Cat II Operations" paragraph, page 2-41). e. Radio Altimeter test must be performed during preflight operations and in flight before initiating the approach phase. f. CAT II approaches with pilot’s or copilot’s PFD in failure condition and/or MFD in composite mode are not allowed. g. CAT II approaches must be performed at 2000 prop RPM. h. The Category II operations information, contained in this AFM, does not constitute an operational approval to conduct Category II operations. Crew qualification and equipment maintained per the approved Operator’s Category II Manual are required for conducting CAT II operations. NOTE CAT II operations were demonstrated under the following maximum wind conditions: – Headwind 7 KTS – Crosswind 24 KTS – Tailwind 8 KTS Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-31 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS REDUCED VERTICAL SEPARATION MINIMA (RVSM) OPERATIONS 2.23 REDUCED VERTICAL SEPARATION MINIMA (RVSM) OPERATIONS a. The Static Pressure Selector Valve, of the Alternate Static Air Source System, must remain in the STATIC TUBE setting during normal operation in RVSM airspace. b. The Pilot’s and Co-pilot’s displayed altitude must remain within ± 200 feet, at all times, during RVSM operation. If the Pilot’s and Co-pilot’s displayed altitude deviates by more than ± 200 feet, RVSM operations are not permitted. c. If the RVSM Critical Region Visual Inspection criteria (see Paragraph 4.3.9 in Section 4 of this AFM) are not met, the airplane is not allowed to operate in RVSM airspace. NOTE The static port of the Alternate Static Air Source System does not affect the smoothness requirement of the RVSM Critical Region. d. All the required instrumentation must be installed and operational to enter and operate in RVSM airspace (refer to the KOEL - "Additional Equipment for RVSM Operations" paragraph on page 2-42). e. ENAC approval of the RVSM operations information, contained in this AFM, constitutes Airworthiness Approval. Approval alone does not authorise flight into airspace for which an RVSM Operational Approval is required by an ICAO Regional Navigation Agreement. Rep. 180-MAN-0010-01100 Page 2-32 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS STEEP APPROACH OPERATIONS 2.24 STEEP APPROACH OPERATIONS a. The airplane is approved for flown steep approaches in visual or instrument meteorological conditions. A glide path reference system is required in case of IFR conditions. b. Max Approach Gradient (FULL FLAP) 15.8% (9°) c. Max Approach Gradient (MID FLAP) 12% (7°) d. Max Crosswind 25 KTS e. Max Tail Wind 10 KTS f. Minimum altitude for Autopilot operation 400 feet AGL g. Minimum ILS guidance intercept 1800 feet AGL h. Minimum go-around altitude 400 feet AGL i. Deliberate Single Engine Approaches are prohibited. j. The Steep Approach operations information, contained in this AFM, does not constitute operational approval to conduct Steep Approach operations. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-33 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS NOISE LEVEL 2.25 NOISE LEVEL ICAO/ANNEX 16 The allowable noise level according to ICAO/Annex 16, Edit. 1988, Chap. 10, for the Piaggio P.180 aircraft at the max certificated TO weight is 88.0 dB(A). The corrected noise level determined according to the mentioned regulation is 86.4 dB(A). FAR 36 The corrected noise level of the Piaggio P.180 aircraft according to FAR 36, Appendix F, amdt. 13, and Appendix G, amdt. 16, is respectively 76.0 dB(A) and 81.8 dB(A). No determination has been made by the ENAC / Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into or out of, any airport. Rep. 180-MAN-0010-01100 Page 2-34 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS STEEP APPROACH OPERATIONS 2.24 STEEP APPROACH OPERATIONS NOTE Steep approach operations are prohibited Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Canadian a/c Rep. 180-MAN-0010-01100 Page 2-33 .a P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS 2.25 NOISE LEVEL ICAO/ANNEX 16 The allowable noise level according to ICAO/Annex 16, Edit. 1988, Chap. 10, for the Piaggio P.180 aircraft at the max certificated TO weight is 88.0 dB(A). The corrected noise level determined according to the mentioned regulation is 86.4 dB(A). FAR 36 The corrected noise level of the Piaggio P.180 aircraft according to FAR 36, Appendix F, amdt. 13, and Appendix G, amdt. 16, is respectively 76.0 dB(A) and 81.8 dB(A). No determination has been made by the ENAC / Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into or out of, any airport. Rep. 180-MAN-0010-01100 Page 2-34 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS KINDS OF OPERATIONS EQUIPMENT LIST (KOEL) 2.26 KINDS OF OPERATIONS EQUIPMENT LIST (KOEL) This airplane may be operated in day or night VFR, IFR and into known icing conditions when the appropriate equipment is installed and operable. The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated. The systems and items of equipment listed must be installed and operable unless: a. The airplane is approved to be operated in accordance with a current Minimum Equipment List (MEL) issued or approved by the Airworthiness Authority. or: b. An alternate procedure is provided in the Approved Airplane Flight Manual for the inoperative state of the listed equipment and all limitations are complied with. NOTE The following systems and equipment list does not include all equipment required by the National Operating Regulations. It also does not include components obviously required for the airplane to be airworthy such as wings, empennage, engine, etc. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-35 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS KINDS OF OPERATIONS EQUIPMENT LIST (KOEL) Number of items installed VFR Day SYSTEM VFR Night and/or IFR Day IFR Night COMPONENT Known Icing Conditions REMARKS and/or EXCEPTIONS ATA 100 CHAPTER 21 AIR CONDITIONING L/R Bleed Air Valves Pressurization Controller, Auto Safety Valve Outflow Valve CAB PRESS - Altitude Warning Cabin Rate of Climb Pressurization Air Source Pressurization Control, Manual Suction Source DOOR SEAL Caution Light 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 1 -- -- -- -- -- ATA 100 CHAPTER 22 AUTO FLIGHT Flight Guidance System ATA 100 CHAPTER 23 COMMUNICATIONS VHF Communication System Static Discharge Wicks 2 1 1 2 2 2 16 7(1) 7(1) 7(1) 7(1) 7(1) (1)Minimum required: one at the outb. end of each control surface. ATA 100 CHAPTER 24 ELECTRICAL POWER Battery Battery Temperature Light DC Generator DC Generator Caution Light DC Distrib. Busses Caut. Light 1 2 2 2 1 Rep. 180-MAN-0010-01100 Appr. DOA EASA.21J.685 Page 2-36 1 2 2 2 1 1 2 2 2 1 1 2 2 2 1 1 2 2 2 1 1105-2999 1 2 2 2 1 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS KINDS OF OPERATIONS EQUIPMENT LIST (KOEL) 2.26 KINDS OF OPERATIONS EQUIPMENT LIST (KOEL) This airplane may be operated in day or night VFR, IFR and into known icing conditions when the appropriate equipment is installed and operable. The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated. The systems and items of equipment listed must be installed and operable unless the KOEL is provided in the Approved Airplane Flight Manual for the inoperative state of the listed equipment and all limitations are complied with. NOTE The following systems and equipment list does not include all equipment required by the National Operating Regulations. It also does not include components obviously required for the airplane to be airworthy such as wings, empennage, engine, etc. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Canadian a/c Rep. 180-MAN-0010-01100 Page 2-35 .a P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS KINDS OF OPERATIONS EQUIPMENT LIST (KOEL) Number of items installed VFR Day SYSTEM VFR Night and/or IFR Day IFR Night COMPONENT Known Icing Conditions REMARKS and/or EXCEPTIONS ATA 100 CHAPTER 21 AIR CONDITIONING L/R Bleed Air Valves Pressurization Controller, Auto Safety Valve Outflow Valve CAB PRESS - Altitude Warning Cabin Rate of Climb Pressurization Air Source Pressurization Control, Manual Suction Source DOOR SEAL Caution Light 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 2 1 1 1 1 -- -- -- -- -- ATA 100 CHAPTER 22 AUTO FLIGHT Flight Guidance System ATA 100 CHAPTER 23 COMMUNICATIONS VHF Communication System Static Discharge Wicks 2 1 1 2 2 2 16 7(1) 7(1) 7(1) 7(1) 7(1) (1)Minimum required: one at the outb. end of each control surface. ATA 100 CHAPTER 24 ELECTRICAL POWER Battery Battery Temperature Light DC Generator DC Generator Caution Light DC Distrib. Busses Caut. Light 1 2 2 2 1 Rep. 180-MAN-0010-01100 Appr. DOA EASA.21J.685 Page 2-36 1 2 2 2 1 1 2 2 2 1 1 2 2 2 1 1 2 2 2 1 1105-2999 1 2 2 2 1 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST (KOEL) 2.19 KINDS OF OPERATION EQUIPMENT LIST (KOEL) Number of items installed VFR Day SYSTEM VFR Night and/or IFR Day IFR Night COMPONENT Known Icing Conditions REMARKS and/or EXCEPTIONS ATA 100 CHAPTER 24 ELECTRICAL POWER (CONT.) Elect. Power Indications (MFD) Emergency Power Unit 1 1 1 1 1 1 1 1 1 1 1 1 2 2 2 2 2 2 3 3 3 3 3 3 3 3 3 3 3 3 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 Main Fuel Boost Pump Standby Fuel Boost Pump Firewall Shutoff Valve Firewall Shutoff Light Crossfeed Valve Crossfeed Light Fuel Quantity Indication (MFD) Fuel Flow Indication (MFD) Fuel Pressure Warning Light 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 Issued: October 21, 2005 Appr. DOA EASA.21J.685 All functions must be operating ATA 100 CHAPTER 26 FIRE PROTECTION Fire Detector System ATA 100 CHAPTER 27 FLIGHT CONTROLS Trim Actuator Trim Indicator - Rudder, Aileron, Horizontal Stabilizer Flap System Position Indication (MFD/PFD) Flap System Stall Warning System Provided the reversionary mode panel is operative ATA 100 CHAPTER 28 FUEL EQUIPMENT Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 2-37 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST (KOEL) Number of items installed VFR Day SYSTEM VFR Night and/or IFR Day IFR Night COMPONENT Known Icing Conditions REMARKS and/or EXCEPTIONS ATA 100 CHAPTER 30 ICE AND RAIN PROTECTION Engine Inlet Deicer System Eng. Inlet Deicer System Indication (MFD) Engine Inertial Ice Vane Ice Vane Syst. Indication (MFD) Oil Inlet Heating System Indication (MFD) Windshield Heat, Left & Right Pitot and Static Heater Ice Detector & Lights Monitoring System Stall Warning Heater Main Wing A/I System Main Wing A/I Lights Main Wing A/I System Indication (MFD) FWD Wing A/I System FWD Wing A/I Lights FWD Wing A/I System Indication (MFD) Main Wing Inspection Light 2 1 2 1 2 1 2 1 2 1 2 1 2 1 1 2 1 1 2 1 1 2 1 1 2 1 1 2 1 1 2 2 1 2 1 -- 2 1 -- 2 2 1 2 2 1 2 2 1 1 2 2 1 ----- ----- 1 ---- 1 ---- 1 2 2 1 2 2 1 ---- ---- ---- ---- 2 2 1 1 -- -- -- -- 1 Aural Warning System Annunciator System 1 1 1 1 1 1 1 1 1 1 1 1 Rep. 180-MAN-0010-01100 Appr. DOA EASA.21J.685 ATA 100 CHAPTER 31 INDICATING/RECORDING SYSTEMS Page 2-38 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST (KOEL) 2.19 KINDS OF OPERATION EQUIPMENT LIST (KOEL) Number of items installed VFR Day SYSTEM VFR Night and/or IFR Day IFR Night COMPONENT Known Icing Conditions REMARKS and/or EXCEPTIONS ATA 100 CHAPTER 24 ELECTRICAL POWER (CONT.) Elect. Power Indications (MFD) Emergency Power Unit 1 1 1 1 1 1 1 1 1 1 1 1 2 2 2 2 2 2 3 3 3 3 3 3 3 3 3 3 3 3 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 Main Fuel Boost Pump Standby Fuel Boost Pump Firewall Shutoff Valve Firewall Shutoff Light Crossfeed Valve Crossfeed Light Fuel Quantity Indication (MFD) Fuel Flow Indication (MFD) Fuel Pressure Warning Light 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 2 2 2 4 1 2 2 2 2 Issued: October 21, 2005 Appr. DOA EASA.21J.685 All functions must be operating ATA 100 CHAPTER 26 FIRE PROTECTION Fire Detector System ATA 100 CHAPTER 27 FLIGHT CONTROLS Trim Actuator Trim Indicator - Rudder, Aileron, Horizontal Stabilizer Flap System Position Indication (MFD/PFD) Flap System Stall Warning System Provided the reversionary mode panel is operative ATA 100 CHAPTER 28 FUEL EQUIPMENT Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 2-37 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST (KOEL) Number of items installed VFR Day SYSTEM VFR Night and/or IFR Day IFR Night COMPONENT Known Icing Conditions REMARKS and/or EXCEPTIONS ATA 100 CHAPTER 30 ICE AND RAIN PROTECTION Engine Inlet Deicer System Eng. Inlet Deicer System Indication (MFD) Engine Inertial Ice Vane Ice Vane Syst. Indication (MFD) Oil Inlet Heating System Indication (MFD) Windshield Heat, Left & Right Pitot and Static Heater Ice Detector & Lights Monitoring System Stall Warning Heater Main Wing A/I System Main Wing A/I Lights Main Wing A/I System Indication (MFD) FWD Wing A/I System FWD Wing A/I Lights FWD Wing A/I System Indication (MFD) Main Wing Inspection Light 2 1 2 1 2 1 2 1 2 1 2 1 2 1 1 2 1 1 2 1 1 2 1 1 2 1 1 2 1 1 2 2 1 2 1 -- 2 1 -- 2 2 1 2 2 1 2 2 1 1 2 2 1 ----- ----- 1 ---- 1 ---- 1 2 2 1 2 2 1 ---- ---- ---- ---- 2 2 1 1 -- -- -- -- 1 Aural Warning System Annunciator System 1 1 1 1 1 1 1 1 1 1 1 1 Rep. 180-MAN-0010-01100 Appr. DOA EASA.21J.685 Right side may be inoperative ATA 100 CHAPTER 31 INDICATING/RECORDING SYSTEMS Page 2-38 .a 1105-2999 Canadian a/c Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST (KOEL) 2.19 KINDS OF OPERATION EQUIPMENT LIST (KOEL) Number of items installed VFR Day SYSTEM VFR Night and/or IFR Day IFR Night COMPONENT Known Icing Conditions REMARKS and/or EXCEPTIONS ATA 100 CHAPTER 32 LANDING GEAR Hydraulic Power Unit Pressure Monitoring Unit Landing Gear Position Indication Lights Steering Fail Light Hydraulic Pressure Gauge Steering Taxi Indication (PFD) Steering Takeoff Indication (PFD) 1 1 3 1 1 3 1 1 3 1 1 3 1 1 3 1 1 3 1 1 1 1 1 1 1 1 1 1 1 1 2 1(1) 1(1) 1(1) 1(1) 1(1) (1) Right side may be inoperative 2 1(1) 1(1) 1(1) 1(1) 1(1) (1) Right side may be inoperative ATA 100 CHAPTER 33 LIGHTS Cockpit Lights Instrument Light System Taxi Light Landing Light Anticollision Strobe Light Position Light Passenger Notice System (Fasten Seat Belts and No Smoking) Cabin Door Warning Light Baggage Door Warning Light Portable Flash Light 2 1 1 2 2 4 1 ------1 1 1 1 2 2 4 1 1 1 ----1 1 1 1 2 2 4 1 1 1 1 2 2 4 1 1 1 1 1 1 -- 1 1 1 1 1 -- 1 1 1 1 1 1 Issued: October 21, 2005 Appr. DOA EASA.21J.685 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 2-39 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST (KOEL) Number of items installed VFR Day SYSTEM VFR Night and/or IFR Day IFR Night COMPONENT Known Icing Conditions REMARKS and/or EXCEPTIONS ATA 100 CHAPTER 34 NAVIGATION INSTRUMENTS 2 1(1) 1(1) 1 1 1 2 1(1) 1(1) 2 2 2 2 2 2 1 1 1 1 -- -2 1 1 2 -- -1 -- -1 -- -1 -- -1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 2 1 1 2 1 2 2 2 1 1 2 1 1 1 -1 1 1 1 1 1 2 1 2 2 2 1 1 2 1 1 1 -1 1 1 1 1 1 2 1 2 2 2 1 1 2 1 1 1 -1 1 1 1 1 1 Oxygen System 1 1 1 1 Rep. 180-MAN-0010-01100 Appr. DOA EASA.21J.685 Primary Flight Display (PFD) Multifunction Display (MFD) Display Control Panel (DCP) Air Data Computer (ADC) Attitude Heading Computer (AHC) Magnetic Compass Radio Altimeter VOR/LOC, GS (NAV) Marker Beacon (NAV) ADF (NAV) DME GPS Transponder Control Display Unit (CDU) Radio Tuning Unit (RTU) Reversionary Panel Integrated Standby Instrument Clock (1) Right side may be inoperative (1) Right side may be inoperative (required for VNAV) (for radios tuning) ATA 100 CHAPTER 35 OXYGEN Page 2-40 1 1 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST (KOEL) Number of items installed VFR Day SYSTEM VFR Night and/or IFR Day IFR Night COMPONENT Known Icing Conditions REMARKS and/or EXCEPTIONS ATA 100 CHAPTER 61 PROPELLERS Prop. Primary Low Pitch Stop Propeller Overspeed Governor Overspeed Governor Test Switch Autofeathering System Autofeath. Armed Indication (MFD) Autofeathering Not Armed Light 2 2 2 2 2 1 2 2 2 2 2 1 2 2 2 2 2 1 2 2 2 2 2 1 2 2 2 2 2 1 2 2 2 2 2 1 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 Oil Pressure Indication (MFD) 2 Oil Temperature Indication (MFD) 2 2 2 2 2 2 2 2 2 2 2 ATA 100 CHAPTER 77 ENGINE INDICATIONS Propeller RPM Indication (MFD) Gas Generator Indication (MFD) ITT Indication (MFD) Torque Indication (MFD) ATA 100 CHAPTER 79 ENGINE OIL INDICATIONS ADDITIONAL EQUIPMENT FOR CAT II OPERATIONS In addition to the information provided in the KOEL for “IFR Night” and flight into “Known Icing Conditions”, the airplane may be operated in Category II Approaches when the following equipment is installed and operable: SYSTEM AND/OR COMPONENT NUMBER OF ITEMS INSTALLED CAT II APPROACHES 1 1 Flight Guidance System Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-41 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST (KOEL) ADDITIONAL EQUIPMENT FOR RVSM OPERATIONS In addition to the information provided in the KOEL for “IFR Night”, the airplane may enter and operate in RVSM airspace when the following equipment is installed and operable: SYSTEM AND/OR COMPONENT NUMBER OF ITEMS INSTALLED RVSM OPERATIONS 1 1 (*) Flight Guidance System (*) With or without Yaw Damper engaged. ADDITIONAL EQUIPMENT FOR P-RNAV OPERATIONS In addition to the information provided in the KOEL for “IFR Night” and flight into “known icing conditions”, the airplane may enter and operate in P-RNAV airspace when the following equipment is installed and operable: SYSTEM AND/OR COMPONENT NUMBER OF ITEMS INSTALLED P-RNAV OPERATIONS Flight Guidance System (Flight Director) 1 1 Flight Management System 1 1 GPS or DME 1 1 ADDITIONAL EQUIPMENT FOR U.S. RNAV OPERATIONS In addition to the information provided in the KOEL for “IFR Night” and flight into “known icing conditions”, the airplane may enter and operate in U.S. Terminal and En Route Area Navigation - RNAV1 - airspace when the following equipment is installed and operable: SYSTEM AND/OR COMPONENT NUMBER OF ITEMS INSTALLED RNAV OPERATIONS Flight Guidance System (Flight Director) 1 1 Flight Management System 1 1 GPS 1 1 Rep. 180-MAN-0010-01100 Page 2-42 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 2 - LIMITATIONS LIMITATIONS PLACARDS 2.27 PLACARDS NOTE In addition and close to the standard (English language) passenger-addressed placards listed below, directly-translated placards in the language of the country in which the airplane is registered can be installed, if required by the specific country’s regulation. FLIGHT COMPARTMENT PLACARDS 1. On the left side of the instrument panel: THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE NORMAL CATEGORY. OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THIS CATEGORY ARE CONTAINED IN THE AIRPLANE FLIGHT MANUAL. THIS AIRPLANE IS APPROVED FOR VFR-IFR-DAY AND NIGHT OPERATION AND KNOWN ICING CONDITIONS. NO AEROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. 2. Close to the Pressurization parameters gauges: AIRCRAFT NOT APPROVED FOR LANDING WHEN PRESSURIZED 3. Close to both PFDs (Pilot’s and Copilot’s side):: If Mod. SB 80-0454 or 80-0425 (new If Mod. SB 80-0454 or 80-0425 (new NWSS) are NOT installed NWSS) are installed MAXIMUM SPEED – KIAS MAXIMUM SPEED – KIAS DESIGN MANEUVERING VA = 199 AT 11500 LBS VA = 177 AT 7700 LBS FLAP OPERATING VFO = 170 UP/MID/UP VFO = 150 MID/DN/MID FLAP EXTENDED DN VFE = 175 LDG GEAR OPERAT VLO= 181 STEERING V = 60 DESIGN MANEUVERING VA = 199 AT 11500 LBS VA = 177 AT 7700 LBS FLAP OPERATING VFO = 170 UP/MID/UP VFO = 150 MID/DN/MID FLAP EXTENDED DN VFE = 175 LDG GEAR OPERAT VLO= 180 MINIMUM CONTROL VMC= 100 (ONE ENGINE INOPERATIVE) MINIMUM CONTROL VMC= 100 (ONE ENGINE INOPERATIVE) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-43 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS PLACARDS 4. On the instrument panel (If S.B 80-0454 or 80-0425 are installed): OPERATION ON UNPAVED RUNWAYS IS PROHIBITED 5. On both the rudder pedal adjustment control handle: RUDDER PEDAL ADJ 6. On the Control Pedestal: EMERGENCY LANDING GEAR EXTENSION 1. 2. 3. 4. 7. GEAR SELECTOR - DOWN HYDRAULIC PUMP SWITCH - OFF EMERG LDG SELECTOR - PULL HAND PUMP - OPERATE UNTIL 3 GREEN LIGHTS COME ON (ABOUT 60 STROKES REQUIRED) Close to the power levers: REVERSE ONLY WITH ENGINES RUNNING ENGAGE REVERSE BELOW 1900 PROP. RPM 8. Close to the Magnetic Compass: CAUTION STANDBY COMPASS ERRATIC WHEN WINDSHIELD, PITOT/ STATIC, FWD WING HEATING OR LANDING LIGHTS ARE ON 9. On the Fuel Control Panel: Rep. 180-MAN-0010-01100 Page 2-44 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS PLACARDS if Mod. 80-1091 or S.B. 80-0424 (“Extended Range”) is installed: 10. Below the left section of the instrument panel, in front of the pilot’s control column: 11. If portable fire extinguisher is installed: On fire extinguisher cabinet: On pilot partition: 12. Near each oxygen panel or plug: WARNING: DO NOT SMOKE WHILE OXYGEN IS IN USE 13. When Integrated Stand-By Instrument model GH-3100 is installed, close to the Integrated Stand-by Instrument (when not upgraded by Mod. 80-0743 or S.B. 80-0226): HDG INFORMATION SHOWN ON TO THE INTEGRATED STAND-BY INSTRUMENT MUST BE DISREGARDED BECAUSE NOT RELIABLE Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-45 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS PLACARDS 14. Close to each 115 Vac Auxiliary Power Socket (if installed): 115 VAC / 60 HZ / 1 A MAX 15. On the left side of the Instrument Panel, when "TAT heater inhibition onground" change is installed (ref. para 4.0): A/C CONFIGURATION ALLOWS PITOT HEATERS SWITCH ON DURING GROUND OPERATIONS (REF. AFM SEC. 4) PASSENGER COMPARTMENT PLACARDS 1. Near the emergency exit: EXIT 2. On the red emergency door handle: EXIT PULL AND TURN LEFT 3. Near the passenger door: EXIT 4. Close to the passenger upper door handle: 5. Close to the passenger bottom door handle (each side of the handle): OPEN Rep. 180-MAN-0010-01100 Page 2-46 CLOSED Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS PLACARDS and if Mod. 80-1098 or related S.B. is installed, on each side: 6. Near each swivel forward facing seat: SEAT MUST BE OUTBOARD WITH SEATBACK IN UPRIGHT POSITION FOR TAKE-OFF AND LANDING 7. Near each swivel aft facing seat: SEAT MUST BE OUTBOARD WITH SEATBACK IN UPRIGHT POSITION AND HEADREST UP FOR TAKE-OFF AND LANDING 8. On the rearward place of the 2-place sidefacing divan, when the low back divan is installed (see Weight and Balance Manual - Rep. 180-MAN-002001101, Section #3 “Equipment List” for installed divan), except when a “Lap Belt & Dual Shoulder Harness” (Y type shoulder harness) seat belt is used. NOTE Operators must verify if relating National Aviation Authority approved/validated the EASA approved Mod. 80-0983 “Installation of safety belt provided with dual Y type shoulder harness on the side facing two place divan (low back)” . If not, the following limitation remains applicable. THIS SEAT MUST NOT BE OCCUPIED DURING TAKE-OFF AND LANDING No placards and no seating limitations when the 2-place sidefacing high back divan (see Weight and Balance Manual - Rep. 180-MAN-002001101, Section #3 “Equipment List” for installed divans) is installed. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-47 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS PLACARDS 9. On each folding work table: LEAF MUST BE STOWED FOR TAKE-OFF AND LANDING 10. Near each cabinet: CABINET MUST BE CLOSED FOR TAKE-OFF AND LANDING 11. On the sliding door: DOOR MUST BE OPEN AND LATCHED FOR TAKE-OFF AND LANDING 12. Close to each privacy curtain when installed: CURTAIN MUST BE OPEN AND LATCHED FOR TAKE-OFF AND LANDING 13. In the lavatory: NO SMOKING WHEN LAVATORY IS IN USE 14. In the coat closet of the cabin baggage compartment: CLOSET CAPACITY 90 LBS (40.8 KG) COAT ROD 40 LBS (18.1 KG) FLOOR 50 LBS (22.7 KG) When cabin additional fuel tank (“Extended Range” modification) is installed: CLOSET CAPACITY 50 LBS (22.7 KG) FLOOR 50 LBS (22.7 KG) 15. On the forward cabinet drawers (if installed): MAX. WT. CAPACITY THIS AREA 24 LBS (10.9 KG) MAX. WT. CAPACITY THIS AREA 10 LBS (4.5 KG) Rep. 180-MAN-0010-01100 Page 2-48 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS PLACARDS 16. On each drawer of the refreshment cabinets as applicable (when optional refreshment cabinets are installed, suitable placards must be provided on each drawer stating the allowable maximum weight capacity): MAX. WT. CAPACITY THIS AREA XX LBS (YY KG) 17. On both rear pyramidal cabinets (if installed): MAX. WT. CAPACITY THIS AREA 10 LBS (4.5 KG) 18. Inside the toilet compartment close to the trash holder: TRASH NO CIGARETTE DISPOSAL 19. Close to each 14 Vdc Auxiliary Power Socket (if installed): 14 VDC, 4 A MAX 20. Close to each 115 Vac Auxiliary Power Socket (if installed): 115 VAC / 60 HZ / 1.5 A MAX 21. On the right FWD partition, when Option #1 or Corporate #1 or Option #19 or Corporate #3 interiors configuration is installed and when two place side facing divan equipped with a “Lap Belt single shoulder harness” seat belt is installed on the FWD right side of the cabin: Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-49 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS PLACARDS BAGGAGE COMPARTMENT PLACARDS 1. On front of the rear baggage compartment door as applicable: When no optional equipment is installed in the Baggage Compartment: MAX LOAD : MAX SPEC. LOAD : 350 lb 159 kg 50 lb/ft2 244 kg/m2 When optional equipment is installed in the Baggage Compartment: MAX LOAD : MAX SPEC. LOAD : xxx lb yyy kg 50 lb/ft2 244 kg/m2 Where xxx lb (yyy kg) is the maximum weight allowed for baggage load defined according to the National Aviation Authority. 2. On the left baggage compartment door: FILLING INSTRUCTION 1. OPEN OVERFILLING VALVE ON L.G. BAY 2. REMOVE PLUG FROM FILLING PORT AND CONNECT HOSE FROM HAND PUMP VALVE 3. PUMP OIL MIL-H-5606 OR EQUIVALENT TO OVERFLOW FROM OVERFILLING 4. OIL CAPACITY FROM LOW LEVEL TO MAX LEVEL 200 CC 5. REMOVE HOSE AND PLUG FILLING PORT 6. CLOSE OVERFILLING VALVE 3. In the hydraulic system filling area: EXTERNAL PRESSURIZATION HYD. OIL FILLING PORT 4. In the front of the baggage compartment door: DO NOT CARRY THE TOWING BAR TRONAIR P/N 01-1227-0000 OR OTHER FERROMAGNETIC MASSES COMPARABLE IN LENGTH AND MASS Rep. 180-MAN-0010-01100 Page 2-50 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS PLACARDS EXTERNAL PLACARDS 1. On the top right side of the fuselage, respectively over and below the refueling cap: When Mod. 80-0953 or S.B. 80-0317 is NOT installed: When Mod. 80-0953 or S.B. 80-0317 is installed: FUEL FUEL JET A, JET A1, JET B PER ASTM D1655 PFA-55MB OR MIL-I-27686 ADDITIVE MUST BE BLENDED JET A, JET A1, JET B PER ASTM D1655 RP-3 PER GB6537 PFA-55MB OR MIL-I-27686 ADDITIVE MUST BE BLENDED MIL-T-5624 GRADE JP4 MIL-T-83133 GRADE JP8 MIL-T-5624 GRADE JP4 MIL-T-83133 GRADE JP8 When Mod. 80-1038 is installed: FUEL JET A, JET A1, JET B PER ASTM D1655 RP-3 PER GB6537 PT (OR RT), TC-1 (OR TS-1) PER GOST 10227 PFA-55MB OR MIL-I-27686 ADDITIVE MUST BE BLENDED MIL-T-5624 GRADE JP4 MIL-T-83133 GRADE JP8 SEE AIRPLANE FLT. MANUAL FOR APPROVED FUELS QUANTITY OF ADDITIVE AND FUELING PROCEDURE 2. On the right side of the fuselage close to landing gear: PRESSURE REFUELING Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-51 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS PLACARDS 3. On the back side of the pressure refueling door (right side of the fuselage): MAXIMUM FUELING PRESSURE 60 PSIG NO DEFUELING ALLOWED FILLING PROCEDURE 1. GROUND TEST SWITCH: "LAMP". VERIFY LAMPS ILLUMINATION 2. REFUEL SWITCH: OPEN TK INTCON INT LAMP MOMENTARILY ON THEN TANK INTCON LAMP ON 3. APPLY TANK TRUCK NOZZLE AND FILL 4. GROUND TEST SWITCH: "SYST" VERIFY FUELING FLOW INTERRUPTION 5. COMPLETE FUELING PROCEDURE 6. REFUEL SWITCH: CLOSED TANK INTCON LAMP OFF THEN TK INTCON INT LAMP MOMENTARILY ON SEE AIRPLANE FLT. MANUAL FOR APPROVED FUEL, QUANTITY OF ADDITIVE AND FUELING PROCEDURE When Mod. 80-0953 or S.B. 80-0317 is NOT installed: When Mod. 80-0953 or S.B. 80-0317 is installed: FUEL FUEL JET A, JET A1, JET B PER ASTM D1655 PFA-55MB OR MIL-I-27686 ADDITIVE MUST BE BLENDED JET A, JET A1, JET B PER ASTM D1655 RP-3 PER GB6537 PFA-55MB OR MIL-I-27686 ADDITIVE MUST BE BLENDED MIL-T-5624 GRADE JP4 MIL-T-83133 GRADE JP8 MIL-T-5624 GRADE JP4 MIL-T-83133 GRADE JP8 When Mod. 80-1038 is installed: FUEL JET A, JET A1, JET B PER ASTM D1655 RP-3 PER GB6537 PT (OR RT), TC-1 (OR TS-1) PER GOST 10227 PFA-55MB OR MIL-I-27686 ADDITIVE MUST BE BLENDED MIL-T-5624 GRADE JP4 MIL-T-83133 GRADE JP8 Rep. 180-MAN-0010-01100 Page 2-52 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II LIMITATIONS PLACARDS 4. On the left and right panels of forward wing, close to the flaps: NO STEP 5. Above the emergency door handle (right side of the fuselage): OPEN 6. On the emergency door handle (right side of the fuselage): PUSH 7. Close to the passenger door handle (left side of the fuselage): OPEN CLOSE 8. On the back side of the GPU plug door (left side of the fuselage): 28 VDC 1200 A PEAK FOR STARTING 400 A MAX CONT. FOR SERVICE 9. Horizontal Stabilizer reference markings on top of the left side of fin: Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 2-53 P.180 AVANTI II AIRPLANE FLIGHT MANUAL LIMITATIONS PLACARDS 10. On the left and right side of the fuselage marking RVSM Critical Region of the Static Port (left side shown): * * * Rep. 180-MAN-0010-01100 Page 2-54 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES TABLE OF CONTENTS SECTION 3 - EMERGENCY PROCEDURES TABLE OF CONTENTS Paragraph No. 3.0 3.1 3.2 3.2.1 3.2.2 3.2.3 3.2.4 3.2.5 3.2.6 Page No. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-1 Airspeeds for Emergency Operations . . . . . . . . . . . . . . . . . . . . . . . .3-2 Emergency Procedures Check List . . . . . . . . . . . . . . . . . . . . . . . . . .3-3 Engine Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-3 Engine Securing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-3 Engine Torching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-3 Engine Failure During Takeoff Before Rotation . . . . . . . . . . . . . . . .3-4 Engine Failure During Takeoff At or After Rotation . . . . . . . . . . . . .3-4 Engine Failure in Flight Below Vmca . . . . . . . . . . . . . . . . . . . . . . . .3-6 Engine Fire (Ground) (L or R FIRE LIGHT ON) . . . . . . . . . . . . . . . .3-6 Engine Failure or Fire in Flight (L or R FIRE LIGHT ON). . . . . . . . .3-7 Engine Failure During Autopilot Operation. . . . . . . . . . . . . . . . . . . .3-8 Engine Failure During Autopilot Operation Coupled Approach/Coupled Go Around. . . . . . . . . . . . . . . . . . . . . .3-8 Air Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-9 Normal Air Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-9 Air Start Without Starter Assist. . . . . . . . . . . . . . . . . . . . . . . . . . . .3-10 Smoke in Cockpit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-11 Electrical Fire or Smoke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-12 Environmental System Smoke . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-13 Emergency Descent. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-14 Maximum Glide . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-14 Landing Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-15 Landing Without Engine Power . . . . . . . . . . . . . . . . . . . . . . . . . . .3-15 Single Engine Approach and Landing . . . . . . . . . . . . . . . . . . . . . .3-16 Single Engine Go-Around. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-17 Landing with Primary Longitudinal Control Failed . . . . . . . . . . . . .3-18 Landing with Stabilizer Jammed. . . . . . . . . . . . . . . . . . . . . . . . . . .3-19 Landing with Longitudinal Control Spring Failed . . . . . . . . . . . . . .3-20 Landing with Autofeather System Inoperative (Amber autofeather light on). . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-21 Gear up Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-22 Nose Gear up or Unlocked Landing . . . . . . . . . . . . . . . . . . . . . . . .3-23 Main Gear Unlocked Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-23 Asymmetric Flap Landing (FLAP SYNC LIGHT ON) . . . . . . . . . . .3-24 Landing with Flaps Retracted. . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-25 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 3-i P.180 AVANTI II AIPLANE FLIGHT MANUAL EMERGENCY PROCEDURES TABLE OF CONTENTS 3.2.7 System Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-26 Engine System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-26 Propeller System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-27 Fuel System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-28 Electrical System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-30 Hydraulic System Failure (HYD PRESS light on) . . . . . . . . . . . . . 3-34 Steering System Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-36 Longitudinal Control System Malfunction . . . . . . . . . . . . . . . . . . . 3-39 Flap System Malfunctions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-40 Pressurization and Environmental System Malfunction . . . . . . . . 3-41 Ice Protection Systems Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-44 Windshield Heat System Failure. . . . . . . . . . . . . . . . . . . . . . . . . . 3-47 Pitot/Static System Failure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-48 Cabin Door Annunciator Illuminated (CAB DOOR light on) . . . . . 3-49 Baggage Door Annunciator Illuminated (BAG DOOR light on). . . 3-49 Emergency Exit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-49 Airplane Evacuation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-49 3.2.8 Avionics System Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-50 Flight Guidance System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . 3-50 Pilot Primary Flight Display (PFD) Failure . . . . . . . . . . . . . . . . . . 3-52 Multifunction Display (MFD) Failure . . . . . . . . . . . . . . . . . . . . . . . 3-52 Control Display Unit (CDU) Failure . . . . . . . . . . . . . . . . . . . . . . . . 3-52 Radio Tuning Unit (RTU) Failure . . . . . . . . . . . . . . . . . . . . . . . . . 3-53 Single Air Data Computer (ADC) Failure . . . . . . . . . . . . . . . . . . . 3-53 Dual Air Data Computer (ADC) Failure. . . . . . . . . . . . . . . . . . . . . 3-53 Single Attitude Heading Computer (AHC) Failure. . . . . . . . . . . . . 3-54 Dual Attitude Heading Computer (AHC) Failure . . . . . . . . . . . . . . 3-54 Failure Flags (red / yellow) on primary Flight Display . . . . . . . . . . 3-55 Comparator Flags (yellow) on primary Flight Display . . . . . . . . . . 3-56 3.2.9 Category II Operations Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . 3-57 Malfunctions During Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-57 3.2.10 Reduced Vertical Separation Minima (RVSM) Operations Emergencies3-58 Autopilot Altitude Mode Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-58 ADC1 Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-58 ADC2 Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-59 3.2.11 P-RNAV Operation Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-60 Flight Guidance System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . 3-60 Flight Management System Failure . . . . . . . . . . . . . . . . . . . . . . . 3-60 GPS and DME Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-60 3.2.12 U.S. RNAV Operation Emergencies. . . . . . . . . . . . . . . . . . . . . . . . . . 3-60 Rep. 180-MAN-0010-01100 Page 3-ii 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES TABLE OF CONTENTS 3.3 3.3.1 3.3.2 3.3.3 3.3.4 3.3.5 3.3.6 3.3.7 Flight Guidance System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . .3-60 Flight Management System Failure . . . . . . . . . . . . . . . . . . . . . . . .3-60 GPS Failure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-60 Amplified Emergency Procedures . . . . . . . . . . . . . . . . . . . . . . . . . .3-61 General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-61 Engine Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-62 Identifying Dead Engine and Verifying Power Loss . . . . . . . . . . . .3-62 Engine Securing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-62 Engine Failure During Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-63 Engine Failure in Flight Below VMCA . . . . . . . . . . . . . . . . . . . . . .3-65 Engine Fire (On Ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-65 Engine Failure or Fire in Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-66 Engine Failure during Autopilot Operation . . . . . . . . . . . . . . . . . . .3-67 Engine Failure during Autopilot Operation Coupled Approach/Coupled Go Around. . . . . . . . . . . . . . . . . . . . .3-67 Air Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-68 Normal Air Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-68 Air Start Without Starter Assist. . . . . . . . . . . . . . . . . . . . . . . . . . . .3-69 Smoke in Cockpit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-70 Emergency Descent. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-72 Glide. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-72 Landing Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-73 Landing Without Engine Power . . . . . . . . . . . . . . . . . . . . . . . . . . .3-73 Single Engine Approach and Landing . . . . . . . . . . . . . . . . . . . . . .3-74 Single Engine Go-Around. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-75 Landing with Primary Longitudinal Control Failed . . . . . . . . . . . . .3-75 Landing with Stabilizer Jammed. . . . . . . . . . . . . . . . . . . . . . . . . . .3-76 Landing with Longitudinal Control Spring Failed . . . . . . . . . . . . . .3-77 Landing with Autofeather System Inoperative . . . . . . . . . . . . . . . .3-78 Landing with Gear Up or Unlocked . . . . . . . . . . . . . . . . . . . . . . . .3-78 Asymmetric Flap Condition Landing. . . . . . . . . . . . . . . . . . . . . . . .3-80 Landing with Flaps Retracted. . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-81 System Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-82 Engine System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-82 Propeller System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-83 Fuel System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-84 Electrical System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-86 Hydraulic System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-89 Steering System Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-91 Longitudinal Control System Malfunction . . . . . . . . . . . . . . . . . . . .3-94 Flap System Malfunction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-95 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 3-iii P.180 AVANTI II AIPLANE FLIGHT MANUAL EMERGENCY PROCEDURES TABLE OF CONTENTS Pressurization and Environmental System Malfunction . . . . . . . . 3-97 Ice Protection System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-99 Windshield Heat System Failure. . . . . . . . . . . . . . . . . . . . . . . . . 3-101 3.3.8 Avionics System Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-102 Flight Guidance System Failure . . . . . . . . . . . . . . . . . . . . . . . . . 3-102 Pilot Primary Flight Display (PFD) Failure . . . . . . . . . . . . . . . . . 3-105 Multifunction Display (MFD) Failure . . . . . . . . . . . . . . . . . . . . . . 3-105 Control DIsplay Unit (CDU) Failure. . . . . . . . . . . . . . . . . . . . . . . 3-106 Radio Tuning Unit (RTU) Failure . . . . . . . . . . . . . . . . . . . . . . . . 3-106 Single Air Data Computer (ADC) Failure . . . . . . . . . . . . . . . . . . 3-107 Dual Air Data Computer (ADC) Failure. . . . . . . . . . . . . . . . . . . . 3-107 Single Attitude Heading Computer (AHC) Failure. . . . . . . . . . . . 3-108 Dual Attitude Heading Computer (AHC) Failure . . . . . . . . . . . . . 3-109 Failure Flags on Primary Flight Display . . . . . . . . . . . . . . . . . . . 3-110 Comparator Flags on Primary Flight Display . . . . . . . . . . . . . . . 3-115 3.3.9 Category II Operations Emergencies . . . . . . . . . . . . . . . . . . . . . . . . 3-117 3.3.10 Reduced Vertical Separation Minima (RVSM) Operations Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-117 3.3.11 P-RNAV Operation Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-117 3.3.12 U.S. RNAV Operation Emergencies. . . . . . . . . . . . . . . . . . . . . . . . . 3-117 Rep. 180-MAN-0010-01100 Page 3-iv 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES GENERAL SECTION 3 - EMERGENCY PROCEDURES 3.0 GENERAL The recommended procedures for coping with various types of emergencies or critical situations are provided in this section. These procedures are suggested as a course of action for coping with the particular condition described, but are not a substitute for sound judgment and common sense. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-1 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AIRSPEEDS FOR EMERGENCY OPERATIONS 3.1 AIRSPEEDS FOR EMERGENCY OPERATIONS SPEED KIAS One Engine Air Minimum Control Speed (Propeller feathered) 100 One Engine Air Minimum Control Speed (Propeller Windmilling) 128 One Engine Best Rate of Climb Speed (Flaps UP, L/G UP) 140 One Engine Best Angle of Climb Speed (Flaps UP, L/G UP) 132 Rep. 180-MAN-0010-01100 Page 3-2 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2 EMERGENCY PROCEDURES CHECK LIST 3.2.1 ENGINE FAILURES ENGINE SECURING 1. Power lever - IDLE 2. Condition lever - CUT OFF 3. Ignition switch - CHECK NORM 4. Fuel firewall shut-off valve - CLOSED 5. Fuel pump switch - OFF 6. SYNCPH switch - OFF 7. Autofeather - OFF 8. Generator - OFF 9. Bleed - OFF 10. Crossfeed - AS REQUIRED ENGINE TORCHING 1. Condition lever (affected engine) - CUT OFF 2. Starter switch - KEEP to START position as necessary CAUTION Have maintenance personnel check engine and propeller. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-3 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ENGINE FAILURE DURING TAKEOFF BEFORE ROTATION 1. Directional control - MAINTAIN 2. Power levers - IDLE 3. Brakes - AS REQUIRED 4. Power levers - REVERSE as required 5. Stop straight ahead. If insufficient runway remains for a safe stop: 6. Condition levers - CUT OFF 7. Generators - OFF 8. Fuel firewall shut-off valves - CLOSED 9. Battery switch (when the airplane has stopped) - OFF 10. EPU - OFF WARNING No attempt should be made to continue the takeoff if the engine failure occurs prior to becoming airborne. ENGINE FAILURE DURING TAKEOFF AT OR AFTER ROTATION If sufficient runway remains for a safe stop: 1. Directional control - MAINTAIN 2. Power levers - IDLE 3. Land straight ahead 4. Brakes - AS REQUIRED 5. Power levers - REVERSE as required Rep. 180-MAN-0010-01100 Page 3-4 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST If insufficient runway remains or if the decision is made to continue the takeoff: 6. Directional control - MAINTAIN (Bank 5° max. towards operative engine when airborne) 7. Power levers - TAKEOFF 8. Landing gear (after climb established) - UP 9. Airspeed - ACCELERATE TO "ONE ENGINE 50 FEET HEIGHT SPEED" (Figure 5-18) 10. Airspeed - INCREASE TO 125 KIAS MINIMUM 11. Flaps - UP (Best angle of climb speed 132 KIAS or max. rate of climb 140 KIAS as appropriate) 12. Obstacles - CLEAR 13. Inoperative engine - PERFORM ENGINE SECURING Procedure NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. 14. Taxi/Landing lights (if applicable) - OFF 15. Airspeed - INCREASE as required 16. Land at nearest suitable airport, performing the SINGLE ENGINE APPROACH AND LANDING Procedure WARNING The decision to continue a takeoff, single engine is primarily predicated upon, but not necessarily limited to, the aircraft’s ability to climb on a single engine with the gear extended and flaps in the takeoff position. Prior to flight, review airfield requirements and determine that adequate single engine climb performance exists, considering aircraft weight, ambient conditions, and pilot proficiency, to safely complete the takeoff should an engine fail at or after rotation. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-5 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ENGINE FAILURE IN FLIGHT BELOW VMCA 1. Power lever (operative engine) - REDUCE power to maintain control 2. Airspeed - INCREASE above VMCA 3. Power lever (operative engine) - AS REQUIRED 4. Inoperative engine - SECURE as per ENGINE SECURING Procedure ENGINE FIRE (GROUND) (L OR R FIRE LIGHT ON) Affected Engine: 1. Condition lever - CUT OFF 2. Ignition switch - CHECK NORM 3. Fuel firewall shut-off valve - CLOSED 4. Fuel pump switch - OFF 5. Fire extinguisher button - PUSH (if installed) 6. Radio - CALL FOR ASSISTANCE 7. AIRPLANE EVACUATION Procedure - PERFORM (when the airplane has stopped) 8. External Fire Extinguisher - USE NOTE If engine fire has spread to the ground, it may be possible to taxi clear of fire zone. If fire continues, shut down both engines and evacuate. Rep. 180-MAN-0010-01100 Page 3-6 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ENGINE FAILURE OR FIRE IN FLIGHT (L OR R FIRE LIGHT ON) 1. Directional control - MAINTAIN (Bank 5° max. towards operative engine) Affected Engine: 2. Power lever - IDLE 3. Condition lever - CUT OFF 4. Ignition switch - CHECK NORM 5. Firewall shut-off valve - CLOSED 6. Fuel pump switch - OFF 7. SYNCPH switch - OFF 8. Autofeather - OFF 9. Generator - OFF 10. Bleed air - OFF 11. Fire extinguisher button (if ENG FIRE light illuminates) - PUSH (if installed) 12. Electrical load - MONITOR 13. Fuel crossfeed - CONSIDER 14. Land as soon as practical, performing the SINGLE ENGINE APPROACH AND LANDING Procedure NOTE The engine fire extinguisher is a single shot system with one cylinder for each engine. CAUTION When conducting a practice run through these procedures, do not close fuel firewall shut-off valves and do not actuate engine fire extinguishers. Fire extinguisher capability has not been evaluated by Airworthiness Authority. NOTE Operation in icing conditions above 14000 ft. is limited to 5 minutes, due to a possible lack of efficiency of the engine inlet de-ice boot system. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-7 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ENGINE FAILURE DURING AUTOPILOT OPERATION 1. Control Wheel/Rudder Pedals - HOLD firmly to prevent further deviation 2. MSW Button - DEPRESS 3. ENGINE SECURING Emergency Procedure - ACCOMPLISH 4. Aileron/Rudder Trim - MANUALLY RETRIM 5. Autopilot - RE-ENGAGE 6. Autopilot Modes - RESELECT AS DESIRED NOTE Large power changes during single engine operations may require disengaging the autopilot and retrimming the airplane prior to resuming autopilot operation. ENGINE FAILURE DURING AUTOPILOT OPERATION COUPLED APPROACH/COUPLED GO AROUND NOTE Single engine CAT II coupled approaches are not allowed. 1. Control Wheel/Rudder Pedals - HOLD firmly to prevent further deviation 2. MSW Button - DEPRESS 3. SINGLE ENGINE GO AROUND Em. Procedure - ACCOMPLISH/COMPLETE 4. ENGINE SECURING Emergency Procedure - ACCOMPLISH 5. Aileron/Rudder Trim - MANUALLY RETRIM 6. Autopilot - RE-ENGAGE 7. Autopilot Modes - RESELECT AS DESIRED NOTE Large power changes during single engine operations may require disengaging autopilot and retrimming the airplane prior to resuming autopilot operation. Rep. 180-MAN-0010-01100 Page 3-8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.2 AIR START CAUTION The pilot should determine the reason for engine failure before attempting an air start. Do not attempt a relight if the NG display indicates zero percent. RECOMMENDED AIR START ENVELOPE PROPELLER FEATHERED Minimum NG for Airstart 13% NOTE Air start may be attempted outside of the envelope, or lower NG provided ITT starting limit is monitored and not exceeded. SECTION 3 - EMERGENCY PROCEDURES NORMAL AIR START 3.2 EMERGENCY PROCEDURES CHECK LIST 1. Cooling system main control switch - OFF 2. Fuel firewall shut-off valve (inoperative engine) - OPEN 3. Fuel pump switch (inoperative engine) - MAIN (FUEL PRESS light - OFF) 4. Engine start switch - START 5. Condition lever - GROUND IDLE (at 13% NG) 6. Engine oil press - CHECK 7. ITT and NG - CHECK Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 3-9 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 8. Engine start switch - CHECK OFF 9. Condition lever - AS REQUIRED 10. Power lever - AS REQUIRED 11. Generator - ON 12. Bleed air - ON NOTE In case of an unsuccessful start, pull the condition lever to CUT OFF and power lever to IDLE. CHECK OFF engine start switch. Slow down the airplane to 140 KIAS and after approximately one minute, repeat the NORMAL AIR START Procedure, using manual ignition (IGN) switch, which must be set to NORM after NG reaches 54%. AIR START WITHOUT STARTER ASSIST 1. Cooling system main control switch - OFF 2. Fuel firewall shut-off valve (inoperative engine) - OPEN 3. Fuel pump switch (inoperative engine) - MAIN (FUEL PRESS light - OFF) 4. NG (inoperative engine) - 13% MIN. 5. Ignition switch (inoperative engine) - IGN 6. Condition lever (inoperative engine) - GROUND IDLE 7. ITT, Oil Pressure - MONITOR 8. Ignition switch - NORM (NG min 54%) 9. Condition lever - AS REQUIRED 10. Power lever - AS REQUIRED 11. Generator - ON 12. Bleed air - ON Rep. 180-MAN-0010-01100 Page 3-10.A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.2 AIR START CAUTION The pilot should determine the reason for engine failure before attempting an air start. Do not attempt a relight if the NG display indicates zero percent. RECOMMENDED AIR START ENVELOPE PROPELLER FEATHERED Minimum NG for Airstart 10% NOTE Air start may be attempted outside of the envelope, or lower NG provided ITT starting limit is monitored and not exceeded. SECTION 3 - EMERGENCY PROCEDURES 3.2 EMERGENCY PROCEDURES CHECK LIST NORMAL AIR START 1. Cooling system main control switch - OFF 2. Fuel firewall shut-off valve (inoperative engine) - OPEN 3. Fuel pump switch (inoperative engine) - MAIN (FUEL PRESS light - OFF) 4. Engine start switch - START 5. Condition lever - GROUND IDLE (at 13% NG) 6. Engine oil press - CHECK 7. ITT and NG - CHECK Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 3-9 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 8. Engine start switch - CHECK OFF NOTE in case of unsuccessful start, pull the condition lever to CUT OFF. Wait 3 minutes and repeat steps from 1 to 8 and perform the following: 8.a Condition lever - FLIGHT IDLE (at 50% Ng) 9. Condition lever - AS REQUIRED 10. Power lever - AS REQUIRED 11. Generator - ON 12. Bleed air - ON NOTE In case of an unsuccessful start, pull the condition lever to CUT OFF and power lever to IDLE. CHECK OFF engine start switch. Slow down the airplane to 140 KIAS and after approximately one minute, repeat the NORMAL AIR START Procedure, using manual ignition (IGN) switch, which must be set to NORM after NG reaches 54%. AIR START WITHOUT STARTER ASSIST 1. Cooling system main control switch - OFF 2. Fuel firewall shut-off valve (inoperative engine) - OPEN 3. Fuel pump switch (inoperative engine) - MAIN (FUEL PRESS light - OFF) 4. NG (inoperative engine) - 10% MIN. 5. Ignition switch (inoperative engine) - IGN 6. Condition lever (inoperative engine) - GROUND IDLE 7. ITT, Oil Pressure - MONITOR 8. Ignition switch - NORM (NG min 54%) 9. Condition lever - AS REQUIRED 10. Power lever - AS REQUIRED 11. Generator - ON 12. Bleed air - ON Rep. 180-MAN-0010-01100 Page 3-10.B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.3 SMOKE IN COCKPIT 1. Cooling system main control switch - OFF 2. Cockpit curtain (if installed) - KEEP OPEN 3. Crew and passenger oxygen - MANUAL MASK RELEASE/DON MASK 4. Oxygen mask microphone - MASK 5. Crew air outlet - OPEN 6. Cockpit blower switch - CKPT BLOWER 7. Source of smoke - IDENTIFY AND ELIMINATE as per the following ELECTRICAL FIRE OR SMOKE Procedure or ENVIRONMENTAL SYSTEM SMOKE Procedure CAUTION If it cannot be readily confirmed if the source of the smoke or fire has been eliminated, then land as soon as practical. SECTION 3 - EMERGENCY PROCEDURES 3.2 EMERGENCY PROCEDURES CHECK LIST Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-11 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ELECTRICAL FIRE OR SMOKE 1. Flashlight (at night) - LOCATE 2. Cabin press. selector - MAN Perform CABIN PRESS AUTO MODE FAILURE procedure 3. Bus disconnect switch - BUS DISC Perform the following, pausing momentarily after each step to isolate faulty circuits: a. L/R generator (one at a time) - OFF If smoke persists: b. Left and Right Generator - ON CAUTION In case of FUEL PUMP light ON, before performing the following steps, descend to altitudes below 25000 ft with JET-A, JET A-1, JP-8 or RP-3 fuel and below 14000 ft with other types of fuel. c. L/R ESNTL BUS circuit breakers - PULL d. Battery switch - OFF WARNING In case both AHC1 and AHC2 are inoperative, the following step will interrupt the power to Stand-by Instrument and consequently will cause the loss of all attitude references. e. EPU switch - OFF WARNING With battery OFF, the loads of essential bus will be inoperative. If fire persists extinguish with portable fire extinguisher, if available. 4. Land as soon as practical. Rep. 180-MAN-0010-01100 Page 3-12 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ENVIRONMENTAL SYSTEM SMOKE 1. Left bleed air switch - OFF 2. Left bleed air switch - ON 3. Right bleed air switch - OFF If smoke persists: 4. Left bleed air switch - OFF 5. Bleed air emergency switch - EMER 6. EMERGENCY DESCENT Procedure - PERFORM 7. Cabin press selector - MAN 8. Manual controller switch - UP 9. Rate control knob - AS REQUIRED 10. Dump switch (at 12000 ft) - DUMP 11. Bleed air emergency switch - OFF 12. Land as soon as practical Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-13 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.4 EMERGENCY DESCENT 1. Power levers - IDLE 2. Condition levers - MAX RPM 3. Seat belts and no smoking signs - ON 4. Airplane attitude - NOSE DOWN in order to reach VMO/MMO as soon as possible 3.2.5 MAXIMUM GLIDE 1. Airspeed - per Maximum Glide Speed Chart (see below) 2. Gear - UP 3. Flaps - UP 4. Condition levers - CUT OFF MAXIMUM GLIDE SPEED CHART WEIGHT (LBS) SPEED (KIAS) 11550 155 11000 151 10000 144 9000 137 8000 129 Glide Ratio (Refer also to BEST GLIDE DISTANCE graph in Section 5 ("Performance") . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3 NM/1000 ft NOTE When operating in sustained icing condition, the Glide Ratio may be reduced up to 50% approximately. Rep. 180-MAN-0010-01100 Page 3-14 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.6 LANDING EMERGENCIES LANDING WITHOUT ENGINE POWER CAUTION With both generators inoperative only essential, battery and hot battery busses are fed by the battery, for approximately 30 minutes depending on loads and battery charge, while the Integrated Stand-by Instrument is fed by the Emergency Power Unit. 1. Airplane configured - Per MAXIMUM GLIDE Procedure (if altitude permits) When landing site assured: 2. Approach Speed - INCREASE the flaps DN approach speed (Figure 5-69) by 20 KIAS 3. Condition levers - CUT OFF 4. Fuel firewall shut-off valves - CLOSED 5. Fuel pumps switches - OFF If gear is to be extended: NOTE For particular terrain conditions it may be required to land with gear up. 6. Gear - DN (PER EMERGENCY GEAR EXTENSION Procedure) NOTE Gear extension requires approximately 60 handpump strokes: this procedure requires normally 90 sec. NOTE When S.B. 80-0454 or 80-0425 (new NWSS) are installed, after Emergency Gear extension, PFD will show T/O steering mode but steering system will remain in free castor mode as hydraulic remains OFF. 7. Emergency gear selector - PUSH 8. Hydraulic pump switch - HYD Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-15 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 9. Landing distance - INCREASE the flaps DN landing distance (Figure 5-69) by approximately 125% NOTE When operating in sustained icing condition, assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 15 KIAS. The landing distance, as compared with the flaps MID landing distance (Figure 5-73), must be increased approximately by 90%. SINGLE ENGINE APPROACH AND LANDING WARNING Do not exceed maximum fuel imbalance (200 lbs). 1. Inoperative engine - COMPLETE ENGINE SECURING Procedure 2. Condition lever (operating engine) - MAX RPM 3. Flaps - MID NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. 4. Airspeed - 129 KIAS MIN. 5. Landing gear (when landing assured) - DN 6. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) When it is certain there is no possibility of go-around: CAUTION Coupled approaches, with yaw damper inoperative, must be performed in clean or MID flap configuration. 7. Flaps - DN 8. Approach speed - AS PER Figure 5-69 9. Power lever - AS REQUIRED Rep. 180-MAN-0010-01100 Page 3-16 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST After touchdown: 10. Brakes and reverse - AS REQUIRED 11. Landing distance - INCREASE the flaps DN landing distance (Figure 5-69) approximately: 30% if reverse thrust is not applied, or 25% if reverse thrust is applied NOTE When operating in sustained icing condition assume the same procedure except: flap position must be MID, and approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. The flaps MID landing distance (Figure 5-73) must be increased approximately by 30% if reverse thrust is not applied and by 25% if reverse thrust is applied. SINGLE ENGINE GO-AROUND 1. Autopilot - DISENGAGE (if engaged) 2. Power - TAKE OFF 3. Airspeed - Minimum 120 KIAS 4. Flaps - MID 5. Landing gear - UP 6. Airspeed - INCREASE TO 125 KIAS MINIMUM 7. Flaps - UP NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. 8. Taxi/Landing lights (if applicable) - OFF 9. Airspeed - INCREASE as required WARNING When operating in sustained icing conditions, insufficient performance may exist to successfully carry out a single engine go-around. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-17 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST LANDING WITH PRIMARY LONGITUDINAL CONTROL FAILED When ready for approach: 1. Trim - IN LEVEL FLIGHT TO 134 KIAS 2. Runway - Select longest in area suitable for a low angle descent 3. Landing gear - DN 4. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) 5. Flaps - MID 6. Trim - TO 130 KIAS 7. Power - AS REQUIRED 8. Condition levers - MAX RPM 9. Flaps - DN 10. Trim - TO 121 KIAS NOTE When operating in sustained icing condition assume the same procedure except: flap position must be MID, and approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. When positioned over the runway, flare airplane with longitudinal trim and slowly reduce power: 11. Brakes (after nose wheel touchdown) - AS REQUIRED 12. Reverse - AS REQUIRED Rep. 180-MAN-0010-01100 Page 3-18 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST LANDING WITH STABILIZER JAMMED 1. Condition levers - MAX RPM 2. Power levers - AS REQUIRED 3. Landing gear - DN 4. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) Stabilizer jammed in nose down trim position: 5. Flaps - MID 6. Approach Speed - INCREASE the flaps DN approach speed (Figure 5-69) by 15 KIAS 7. Brakes and reverse - AS REQUIRED 8. Landing distance - INCREASE the flaps DN landing distance (Figure 5-69) by approximately 45% Stabilizer jammed in nose up trim position: 9. Flaps - DN 10. Approach speed - AS PER Figure 5-69 11. Brakes and reverse - AS REQUIRED NOTE When operating in sustained icing conditions assume the same procedure except: flap position must be MID, whatever is the stabilizer position, and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 10 KIAS. The flaps MID landing distance (Figure 5-73) must be increased approximately by 25%. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-19 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST LANDING WITH LONGITUDINAL CONTROL SPRING FAILED 1. Condition levers - MAX RPM 2. Power levers - AS REQUIRED 3. Landing gear - DN 4. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) 5. Flap - MID 6. Approach Speed - INCREASE the flaps DN approach speed (Figure 5-69) by 15 KIAS 7. Brakes and reverse - AS REQUIRED 8. Landing distance - INCREASE the flaps DN landing distance (Figure 5-69) by approximately 40% if the reverse thrust is not applied NOTE When operating in sustained icing condition, assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 10 KIAS. The flaps MID landing distance (Figure 5-73) must be increased approximately by 20%. Rep. 180-MAN-0010-01100 Page 3-20 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST LANDING WITH AUTOFEATHER SYSTEM INOPERATIVE (AMBER AUTOFEATHER LIGHT ON) 1. Condition lever - MAX RPM 2. Power levers - AS REQUIRED 3. Landing gear - DN 4. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) 5. Flap - MID 6. Approach Speed - INCREASE the flaps DN approach speed (Figure 5-69) by 15 KIAS 7. Brakes and reverse - AS REQUIRED 8. Landing distance - INCREASE the flaps DN landing distance (Figure 5-69) by approximately: 35% if reverse thrust is not applied, or 26% if reverse thrust is applied NOTE When operating in sustained icing condition, assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. The flaps MID landing distance (Figure 5-73) must be increased approximately by 10% if reverse thrust is not applied or by 5% if reverse thrust is applied. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-21 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST GEAR UP LANDING When normal and emergency gear extension procedures have failed: 1. Select a suitable landing area 2. Ground personnel - INFORM 3. Passengers - BRIEF on use of emergency exit; CHECK properly fastened with seat belts 4. Fuel - BURN OFF EXCESS, if condition permits 5. AURAL WARN circuit breaker - PULL 6. Emergency gear selector - PUSH 7. Hydraulic pump switch - HYD 8. Gear selector - UP 9. Flaps - DN 10. Make a normal approach. When landing is assured: 11. Cabin Pressurization - DUMP 12. Generators - OFF 13. Condition levers - CUT OFF 14. Fuel pumps - OFF 15. Fuel firewall shut-off valves - CLOSED 16. Battery switch - OFF 17. EPU switch - OFF 18. Evacuate as per "Airplane Evacuation" Procedure when the airplane comes to a stop. NOTE When operating in sustained icing condition assume the same procedure except: flap position must be MID, and approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. Rep. 180-MAN-0010-01100 Page 3-22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST NOSE GEAR UP OR UNLOCKED LANDING 1. Final approach according with normal procedure 2. Touch down in nose up attitude 3. Mantain nose up to the lowest practicable speed 4. After the nose touch down use maximum brake and reverse 5. Evacuate as per "Airplane Evacuation" Procedure when the airplane comes to a stop. NOTE When operating in sustained icing condition assume the same procedure except: flap position must be MID, and approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. MAIN GEAR UNLOCKED LANDING When normal and emergency gear extension procedures have failed: 1. Emergency gear selector - PUSH 2. Hydraulic pump switch - HYD If both main landing gear legs are extended: 3. Final approach according with normal procedure 4. Touch down in nose up attitude 5. After touch down apply reverse and brakes cautiously 6. Evacuate as per "Airplane Evacuation" Procedure when the airplane comes to a stop. If one main landing gear leg remains retracted: 7. Perform GEAR UP LANDING Procedure NOTE When operating in sustained icing condition assume the same procedure except: flap position must be MID, and approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-23 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ASYMMETRIC FLAP LANDING (FLAP SYNC LIGHT ON) 1. FLAP SYSTEM MALFUNCTION Procedure - COMPLETE 2. Condition levers - MAX RPM 3. Power levers - AS REQUIRED 4. Landing gear - DN 5. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) 6. Approach speed - INCREASE the flaps DN approach speed (Figure 5-69) as indicated in the table below 7. Brakes and reverse - AS REQUIRED 8. Landing distance - if the reverse thrust is not applied INCREASE the flaps DN landing distance (Figure 5-69) approximately as indicated in the table below: OUTBOARD FLAP POSITION SPEED INCREASE LANDING DISTANCE INCREASE DN 5 KIAS 10% MID 15 KIAS 40% UP 20 KIAS 65% NOTE When operating in sustained icing conditions assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 5-73), must be increased as indicated in the table below: OUTBOARD FLAP POSITION SPEED INCREASE LANDING DISTANCE INCREASE (Figure 5-73) MID 10 KIAS 20% UP 15 KIAS 40% Rep. 180-MAN-0010-01100 Appr. DOA EASA.21J.685 Page 3-24 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST LANDING WITH FLAPS RETRACTED 1. Approach Speed - INCREASE the flaps DN approach speed (Figure 5-69) by 20 KIAS 2. Condition levers - MAX RPM 3. Power levers - AS REQUIRED 4. Landing gear - DN 5. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) After touchdown: 6. Reverse - AS REQUIRED 7. Landing distance - INCREASE the flaps DN landing distance (Figure 5-69) by approximately: 65% if reverse thrust is not applied, or 55% if reverse thrust is applied NOTE When operating in sustained icing conditions assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 15 KIAS. The landing distance, as compared with the flaps MID landing distance (Figure 5-73), must be increased approximately by 40% if reverse thrust is not applied or by 30% if reverse thrust is applied. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-25 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.7 SYSTEM EMERGENCIES ENGINE SYSTEM FAILURE LOW OIL PRESSURE Between 60 and 90 PSI (yellow indication on MFD): 1. Power - REDUCE below 49.3% torque Below 60 PSI and L or R OIL PRESS red light on: 1. ENGINE SECURING Procedure - PERFORM 2. Land as soon as practical, performing the SINGLE ENGINE APPROACH AND LANDING Procedure HIGH OIL PRESSURE Between 135 PSI and 150 PSI: 1. Power - REDUCE 2. Land as soon as practical. Above 150 PSI: 1. ENGINE SECURING Procedure - PERFORM 2. Land as soon as practical, performing the SINGLE ENGINE APPROACH AND LANDING Procedure HIGH OIL TEMPERATURE (MORE THAN 104° C - L/R OIL TEMP LIGHT ON) 1. OIL COOL switch - CHECK L and R position (on the ground only) 2. Airspeed - INCREASE as required 3. Power - REDUCE as required If the temperature exceeds the limit (110°C or 104°C for more than 10’) 4. ENGINE SECURING Procedure - PERFORM 5. Land as soon as practical, performing the SINGLE ENGINE APPROACH AND LANDING Procedure Rep. 180-MAN-0010-01100 Page 3-26 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST PROPELLER SYSTEM FAILURE OVERSPEEDING PROPELLER If prop exceeds 2000 RPM steady state (for more than 15 sec.) remaining below 2200 RPM (red steady indication) 1. Condition lever - REDUCE RPM 2. Power lever - REDUCE as practical 3. Airspeed - REDUCE TO LOWEST PRACTICAL If prop exceeds 2200 RPM (red flashing indication): 4. Power lever - IDLE 5. Condition lever - CUT OFF 6. ENGINE SECURING Procedure - COMPLETE 7. Land as soon as practical, performing the SINGLE ENGINE APPROACH AND LANDING Procedure. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-27 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST FUEL SYSTEM FAILURE FUEL PUMP FAILURE (L OR R FUEL PUMP LIGHT ON) 1. FUEL PRESS light - CHECK 2. Fuel pump switch - CHECK MAIN 3. Main pump circuit breaker - CHECK PUSHED If FUEL PRESS light is not illuminated, the Main fuel pump has failed but the Stand-by fuel pump is working properly. 4. Fuel pump switch - STAND BY LOW FUEL PRESS (L OR R FUEL PRESS LIGHT ON) 1. Fuel pump switch - CHECK MAIN 2. Main pump circuit breaker - CHECK IN 3. Fuel pump switch - STAND BY 4. Power (affected engine) - REDUCE as practical 5. Fuel quantity gauges - COMPARE rate of change with other side If rate of change is equal: 6. Continue the flight If rate of change is higher (on the affected side): 7. ENGINE SECURING Procedure - PERFORM 8. Land as soon as practical, performing the SINGLE ENGINE APPROACH AND LANDING Procedure Rep. 180-MAN-0010-01100 Page 3-28 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST FUEL FILTER OBSTRUCTED (L OR R FUEL FILTER LIGHT ON) 1. FUEL PRESS light - CHECK If not illuminated: 2. CONTINUE the flight and have a maintenance check If illuminated: 3. Power (affected engine) - REDUCE as practical 4. Land as soon as practical FUEL FIREWALL SHUTOFF VALVE FAILED IN TRANSIT (L OR R F/W V INTRAN LIGHT ON) On the ground have a maintenance check. Takeoff is not authorized. If failure occurs during flight, land as soon as practical. WING FUEL BALANCING PROCEDURE NOTE The following procedure can be performed only before takeoff or during cruise. At high fuel flow rate, the L/R FUEL PRESS amber light may illuminate. 1. CROSSFEED knob - TURN HORIZONTAL 2. Fuel pump (low fuel level side) - OFF 3. Fuel quantity - MONITOR FUEL CROSSFEED FAILED IN TRANSIT (X FEED INTRAN LIGHT ON) 1. Fuel quantity - MONITOR On the ground have a maintenance check. Takeoff is not authorized. If failure occurs during flight, land as soon as practical. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-29 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ELECTRICAL SYSTEM FAILURE SINGLE GENERATOR FAILURE (GEN LIGHT ON) 1. Generator switch - RESET then L or R position If the generator does not reset: 2. Generator switch - OFF 3. Operating Generator - DO NOT EXCEED 400 Amps LOAD NOTE With only one generator operating all busses are fed. ELECTRICAL OVERLOAD (Yellow digital readout “GEN xxx” on MFD) 1. MFD - MONITOR SYS page 2. Electrical load - REDUCE Rep. 180-MAN-0010-01100 Page 3-30 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST DUAL GENERATOR FAILURE (L GEN, R GEN AND BUS DISC LIGHTS ON) CAUTION With both generators inoperative only essential, battery and hot battery busses are fed by the battery, for approximately 30 minutes depending on loads and battery charge, while the Integrated Stand-by Instrument is fed by the Emergency Power Unit. 1. Both Generator Switches - RESET then L or R position If the generators do not reset: 2. Generators switches - OFF 3. Bus connecting switch - EMER if necessary NOTE With bus connecting switch in EMER position, L/R DUAL FEED BUSSES are powered: limit this operation to prevent further reduction of battery life time. 4. Land as soon as practical (normal gear extension and flap operation are not possible), extending the gear as per EMERGENCY GEAR EXTENSION Procedure and performing both the LANDING WITH FLAPS RETRACTED and the CABIN PRESS AUTO MODE FAILURE Procedures. If in the above condition also battery fails: 5. Battery switch - OFF then BAT If battery does not reset: 6. Battery switch - OFF 7. EMER COMM 1 (on Reversionary panel) - PUSH 8. EMG (on audio panel) - PUSH NOTE In case of dual generator failure and battery failure, only Integrated Stand-by Instrument, landing gear position lights, emergency lights (for ISI and Magnetic Compass) and VHF COMM1 are powered by the Emergency Power Unit. Limit VHF COMM1 transmissions to avoid EPU discharge. Issued: October 21, 2005 Appr. DOA EASA.21J.685 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 3-31 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST BATTERY OVERTEMPERATURE CONDITION (BAT TEMP LIGHT ON) (BAT OVHT LIGHT ON) On the Ground: 1. MFD - SELECT AND MONITOR BATTERY TEMPERATURE With BAT TEMP light illuminated (at or above 120°F (49°C)) 2. DO NOT TAKE OFF With BAT OVHT light illuminated (at or above 150°F (66°C)) 3. Battery switch - OFF 4. DO NOT TAKE OFF During Flight: If BAT TEMP light is illuminated (120°F; 49°C) 1. Battery temperature - MONITOR If BAT OVHT light is illuminated (150°F; 66°C): 2. Battery switch - OFF 3. Land as soon as possible at nearest suitable airport CAUTION If Battery Temperature reached 150°F (66°C), either during start or in flight, battery must be removed for bench test and inspection prior to the next flight. Rep. 180-MAN-0010-01100 Page 3-32 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ANY CIRCUIT BREAKER TRIPPED 1. Circuit breaker - PUSH TO RESET 2. If Circuit Breaker trips again - DO NOT RESET CAUTION Circuit Breakers should not be reset more than once until the cause of circuit malfunction has been determined and corrected. AUDIO CONTROL PANEL FAILURE 1. EMG red button - PUSH NOTE When in emergency mode, the audio control panel allows normal use of transmit and receive functions, with or without power to the system. Page and interfone functions are lost, while mask/boom microphone can be utilized. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-33 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST HYDRAULIC SYSTEM FAILURE (HYD PRESS LIGHT ON) CAUTION With the hydraulic pressure at 3000 PSI it is possible to operate the system but hydraulic pump motor must operate for not more than 1 minute. Do not operate the parking brake with the hydraulic pressure above 1200 PSI. With the hydraulic pressure above normal value the steering will be more sensitive. With the hydraulic pump off the steering is inoperative and the brakes are less effective. If landing gear is down: 1. Hyd pump switch - CHECK HYD 2. HYDR WARNING/PRESS and HYDR CONT circuit breakers - CHECK IN 3. Hyd pressure - CHECK If out of range (700 ÷ 1300 PSI) then: 4. Hyd pump switch - OFF If landing gear is up: 1. Hyd pump switch - OFF Immediately before landing gear extension: 2. Hyd pump switch - HYD EMERGENCY GEAR EXTENSION 1. Gear selector - DN 2. Hyd pump switch - OFF 3. Emergency selector - PULL 4. Hand pump - OPERATE (until the 3 green lights illuminate) (about 60 strokes) 5. Landing distance - INCREASE the flaps DN landing distance (Figure 5-69) by 55% if reverse thrust in not applied Rep. 180-MAN-0010-01100 Page 3-34 Appr. DOA EASA.21J.685 Issued: October 21, 2005 1105-2999 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 6. Brakes - refer to EMERGENCY BRAKE OPERATION Procedure CAUTION After an emergency Landing Gear extension, do not re-engage hydraulic pump and do not push emergency landing gear selector. NOTE Steering will not be operative. NOTE When S.B. 80-0454 or 80-0425 (new NWSS) are installed, after Emergency Gear extension, PFD will show T/O steering mode but steering system will remain in free castor mode as hydraulic remains OFF. EMERGENCY BRAKE OPERATION Pedal brake operation becomes harder than normal (about 50% increase). 1. Brakes - APPLY 2. Reverse thrust - AS REQUIRED Normal ground roll (Figure 5-69) will increase approximately by 55% if reverse thrust is not applied. NOTE When operating in icing condition the ground roll with flaps MID (Figure 5-73) will increase approximately by 80% if reverse thrust is not applied. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-35 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST STEERING SYSTEM FAILURES If the airplane is NOT equipped with S.B. 80-0286 (mod. 80-0932) and NOT equipped with S.B. 80-0454 or 80-0425: STEERING SYSTEM FAILURE (STEER FAIL LIGHT ON) 1. 2. 3. Control Wheel Master Switch - PRESS Directional control - MAINTAIN (as necessary) with differential braking Steering indication on PFD - CHECK OFF NOSE WHEEL STEER RUNAWAY If an uncontrolled heading change occurs: 1. Control Wheel Master Switch - PRESS 2. Directional control - MAINTAIN with differential braking and asymmetrical power If the airplane is equipped with S.B. 80-0286 (mod. 80-0932): STEER FAIL LIGHT “ON” 1. Control Wheel Master Switch - PRESS and RELEASE NOTE If autopilot is operating, pressing the Control Wheel Master Switch, it will be disengaged. 2. 3. 4. 5. Directional control - MAINTAIN (as necessary) Steering indication on PFD - VERIFY STEER FAIL light - VERIFY After landing do not engage the steering system NOSE WHEEL STEER RUNAWAY If an uncontrolled heading change occurs on-ground: 1. 2. 3. 4. Control Wheel Master Switch - PRESS and RELEASE Directional control - MAINTAIN (as necessary) Steering indication on PFD - VERIFY STEER FAIL light - VERIFY Rep. 180-MAN-0010-01100 Page 3-36 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST If the airplane is equipped with S.B. 80-0454 or 80-0425: CAUTION When the Steering System is in failure mode (STEER FAIL light ON), the Antiskid System (if installed) must be switched OFF. 1. 2. STEER FAIL LIGHT “ON” DURING TAKEOFF CWMS - press Directional control - MAINTAIN (as necessary) with differential braking - If sufficient runway remains and speed is not excessive for a safe stop: 3.Power Levers – IDLE 4.Brakes – AS REQUIRED 5.Power Levers – REVERSE as required. - Otherwise if NO sufficient runway remains for a safe stop: 3.perform take off and refer to the procedures below for landing. STEER FAIL LIGHT “ON” DURING LANDING NOTE CWMS switch does not affect the steering while the airplane is in flight. - If NO Mode indications on PFD appears: 1.Hyd. Switch - OFF 2.Steer CB - PULL NOTE Steer fail light will go off and steering system will be inoperative. Emergency braking will be available (ref. to "Emergency Brake Operation" procedure) 3.Directional Control - MAINTAIN (as necessary) with rudder and differential braking. When airplane stopped and runway vacated (if possible): 4.Do not taxi - TOWING REQUIRED. - Otherwise if TAKE OFF indication on PFD appears: NOTE The Steering System is operative but it is not possible to disengage it Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-37 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 1.Final approach according with normal procedures at minimum Vref. NOTE NWSS will be operative during landing roll. It will operate in TO mode only with no mode change possible. When airplane stopped and runway vacated (if possible): 2.Do not taxi - TOWING REQUIRED. “TAXI” INDICATION ON PFD DURING LANDING 1. Control Wheel Master Switch - PRESS 2. Directional Control - MAINTAIN with differential braking. NOSE WHEEL STEERING RUNAWAY (uncontrolled heading change) 1. Control Wheel Master Switch - PRESS 2. Directional control - MAINTAIN with differential braking and asymmetrical power Rep. 180-MAN-0010-01100 Page 3-38 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST LONGITUDINAL CONTROL SYSTEM MALFUNCTION LONGITUDINAL TRIM RUNAWAY 1. Control Wheel Master Switch - PRESS 2. Longitudinal trim switch - SEC CAUTION Trim in motion aural warning will not be operative when in secondary mode. PRIMARY LONGITUDINAL TRIM FAILURE 1. PRI PITCH TRIM breaker - CHECK IN 2. Longitudinal trim switch - SEC CAUTION Trim in motion aural warning will not be operative when in secondary mode. LONGITUDINAL CONTROL SPRING FAILURE 1. Speed - REDUCE to 210 KIAS (if flying at high speed and altitude above 30,000 feet with aft C.G.) 2. Land performing the LANDING WITH LONGITUDINAL CONTROL SPRING FAILED Procedure. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-39 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST FLAP SYSTEM MALFUNCTIONS FLAP SYNCHRO FAILURE (FLAP SYNC LIGHT ON) NOTE During flap deployment or retraction, any significant asymmetric condition results in abnormal control forces which could be detected by the pilot earlier than the FLAP SYNC light becomes illuminated (and the “FLAPS” indications on PFD and MFD become yellow). 1. Maintain control using primary and secondary flight control systems 2. Flap selector lever and flap position indicator - CHECK POSITION If any flap is not in the correct position (asymmetry): 3. Analyse the malfunction on the flap position indicator on the MFD SYS Page and, if necessary, reconfigure the remaining flap systems to minimize the asymmetry. 4. Land performing ASYMMETRIC FLAP LANDING Procedure If all flaps are in the correct position: 5. Do not move the flap selector lever and land assuming ASYMMETRIC FLAP LANDING Procedure from step 2. Rep. 180-MAN-0010-01100 Page 3-40 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST PRESSURIZATION AND ENVIRONMENTAL SYSTEM MALFUNCTION RAPID OR EXPLOSIVE DECOMPRESSION (CAB PRESS LIGHT ON) 1. Crew and passenger oxygen - MANUAL MASK RELEASE/DON MASKS 2. Oxygen mask microphone - MASK 3. Emergency bleed air switch - EMER 4. "Emergency Descent" Procedure - PERFORM down to 12000 ft. 5. Emergency bleed air switch - OFF CABIN ALTITUDE ABOVE 9,500 FEET (CAB PRESS LIGHT ON) 1. Crew and passenger oxygen - MANUAL MASK RELEASE/DON MASK 2. Oxygen mask microphone - MASK 3. Bleed air switches - VERIFY L and R position 4. Cab sel/Auto sched switch - MAN 5. Manual controller switch - DN 6. Rate control knob - AS DESIRED If cabin altitude continues to increase: 7. Emergency bleed air switch - EMER 8. "Emergency Descent" Procedure - PERFORM IF REQUIRED down to 12000 ft. 9. Emergency bleed air switch - OFF Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-41 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST CABIN DIFFERENTIAL PRESSURE ABOVE 9.4 PSID (CAB PRESS LIGHT ON) 1. Bleed air switches - OFF 2. Crew oxygen - AUTO NORMAL/DON MASK When differential pressure reaches 8 psid 3. Bleed air switches - L and R position 4. CABIN PRESS AUTO MODE FAILURE - PERFORM If the cabin pressure differential cannot be controlled: 5. CABIN DEPRESSURIZATION (DUMP) Procedure - PERFORM if necessary 6. "Emergency Descent" Procedure - PERFORM CABIN PRESS AUTO MODE FAILURE 1. Cabin press switch - MAN 2. Manual controller - AS REQUIRED 3. Rate control knob - AS REQUIRED 4. Cabin altitude / p - CHECK 5. Cabin rate - CHECK 6. Below 10000 ft and Before Landing: – Rate control knob - SET to MAX RATE – Manual control lever - UP 7. Cabin altitude / p - CHECK Landing Field / Zero 8. After touchdown and before opening the door, dump switch - DUMP CAUTION Aircraft is not approved for landing when pressurized DOOR SEAL FAILURE (DOOR SEAL LIGHT ON) 1. Flying altitude - DESCEND or limit altitude to 30000 ft or below 2. Cabin altitude/p - CHECK 3. Cabin rate - CHECK Rep. 180-MAN-0010-01100 Page 3-42 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST If cabin pressure variation is rapid: 4. "Emergency Descent"- CONSIDER 5. Crew and passenger oxygen - AS REQUIRED CABIN DEPRESSURIZATION (DUMP) PROCEDURE 1. Crew and passenger oxygen - MANUAL MASK RELEASE 2. Masks - DON if necessary 3. Dump switch - DUMP BLEED AIR OVERTEMPERATURE (L/R BLEED TEMP LIGHT ON) 1. Affected engine - REDUCE NG If light persists illuminated 2. Affected side bleed air switch - OFF ENVIRONMENTAL AUTO CONTROL FAILURE (OR DUCT TEMP LIGHT ON) 1. AUTO/OFF/MAN switches - MAN 2. Manual HI/LO switches - LO NOTE The temperature modulating valves require about 15 seconds operating time from full hot to full cold. If the DUCT TEMP light is ON and persists for further 15 seconds then: 3. Bleed air switches - OFF 4. Emergency bleed air switch - EMER 5. Flying altitude - REDUCE down to 9500 ft 6. Emergency bleed air switch - OFF Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-43 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ICE PROTECTION SYSTEMS FAILURE ICE DETECTOR FAILURE (ICE LIGHT OFF OR ALWAYS ON) 1. ENG ICE VANE and OIL COOLER INTK switches - CHECK to L and R position 2. Determine ice forming condition by visual inspection Heavy ice conditions: 3. BOOTS DE ICE switch - TIMER Light ice conditions: 4. BOOTS DE ICE switch - CYCLE TIMER/OFF (every 6 minutes approximately) CAUTION Continuous cycling of boots during some types of ice encounters may result in failure to remove ice. ENGINE AIR INTAKE BOOTS (BOOTS “ON” Indication Steady WHITE or Steady GREEN - on MFD) 1. ENG ICE VANE and OIL COOLER INTK switches - CHECK to L and R position If the system is operating in AUTO mode: 2. Determine ice accretion by visual inspection Heavy ice conditions: 3. BOOTS DE ICE switch - TIMER Light ice conditions: 4. BOOTS DE ICE switch - CYCLE TIMER/OFF (every 6 minutes approximately) CAUTION Continuous cycling of boots during some types of ice encounters may result in failure to remove ice. If ON indications persist white (or green): 5. Leave ice condition as soon as possible Rep. 180-MAN-0010-01100 Page 3-44 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ENGINE INERTIAL SEPARATOR (ENG “ON” Indication off - on MFD) If the torque drop is not similar to the other engine, an engine inertial separator is suspected: 1. ENG ICE VANE switches - SET to OFF then to L or R position If the normal operating condition is not restored: 2. Leave ice condition as soon as possible OIL COOLER AIR INLET (OIL “ON” Indication off - on MFD) 1. Power levers - INCREASE POWER MOMENTARILY If the indication persists off, an oil cooler air inlet heater failure is suspected: 2. Oil temperature (affected side) - CHECK If the oil temperature increases abnormally: 3. Leave ice condition as soon as possible. MAIN WING OVERHEAT (L OR R MN WG OVHT LIGHT ON) 1. Affected side main wing anti-ice switch - OFF If light (after 20 seconds) persists ON 2. Power levers - REDUCE POWER as practical 3. Leave ice condition as soon as practical If light extinguishes: 4. Affected side main wing anti-ice switch - MANUAL and check the MN WG OVHT light. CAUTION In light ice conditions, in order to avoid overheat, a NG between 88% and 91% is recommended. Should the red MN WG OVHT light illuminate, the affected system must be turned OFF for one minute approximately. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-45 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST MAIN WING A/ICE FAILURE a. “MW” Indication YELLOW and Left or Right ON indication off (on MFD): 1. Power lever - INCREASE POWER MOMENTARILY If normal condition is not restored: 2. L or R MAIN WING switches - OFF (for approx. 10 seconds) then MANUAL checking the ITT variation If the ON indication, after approx. 30 seconds, is still off and ITT has not increased by 20°C approx.: 3. Main and forward wings anti-ice systems - SWITCH OFF 4. Leave ice condition as soon as possible If the ON indication comes green, or remains off but the ITT has increased by 20°C approx.: 5. L or R MAIN WING switches - MANUAL and check the MN WG OVHT light CAUTION In light ice conditions, in order to avoid overheat, a NG between 88% and 91% is recommended. Should the red MN WG OVHT light illuminate, the affected system must be turned OFF for one minute approximately. b. “MW” Indication and Left or Right ON indication flashing (on MFD): The system is operating: 1. Do not select MANUAL mode Rep. 180-MAN-0010-01100 Page 3-46 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST FORWARD WING OVERHEAT (L OR R FD WG OVHT LIGHT ON) 1. Affected side FWD WING switch - SET to OFF position 2. Leave ice condition as soon as practical FORWARD WING A/ICE FAILURE (“FW” Indication YELLOW and Left or Right ON indication off - on MFD) 1. FWD WING HTR and FWD WG HTR CONT circuit breakers - CHECK IN 2. Affected side electrical current variation - CHECK switching ON and OFF If the current variation is 30-40 Amp. 3. Flight - CONTINUE and check periodically the current variation If the electrical current variation is less than 30 Amp. approximately: 4. Leave ice condition as soon as practical WINDSHIELD HEAT SYSTEM FAILURE WINDSHIELD ZONE OVERHEAT L WSHLD ZONE LIGHT ON: 1. WSHLD HEAT PRI switch - SET to LO position R WSHLD ZONE LIGHT ON: 2. WSHLD HEAT SEC switch - SET to LO position If the affected zone light does not extinguish: 3. Affected zone switch - CYCLE LO/OFF when necessary Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-47 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST PITOT/STATIC SYSTEM FAILURE L/R PITOT HEAT Annunciator (L or R PITOT HTR Caution light ON) 1. PITOT/STATIC HTR switches - CHECK L & STALL and R & TAT 2. L/R PITOT ST HTR circuit breakers - CHECK IN 3. PITOT/STATIC HTR switches - OFF then L & STALL and R & TAT If L/R PITOT caution light persists illuminated rely on the other pilot’s instruments. LEFT NORMAL STATIC AIR SOURCE MALFUNCTION 1. Static pressure selector valve - ALTERNATE SOURCE after lifting the spring-clip retainer 2. Airspeed and altitude calibration - Apply the appropriate correction NOTE Refer to Section 5 of this AFM for Airspeed and Mach calibration. For altitude calibration add (data valid for zero sideslip): – 50 feet (maximum inaccuracy) up to 30000 feet – 80 feet (maximum inaccuracy) above 30000 feet Rep. 180-MAN-0010-01100 Page 3-48 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST CABIN DOOR ANNUNCIATOR ILLUMINATED (CAB DOOR LIGHT ON) WARNING Do not attempt to check the security of the cabin door in flight. Remain as far from the door as possible with seat belts securely fastened until the airplane has landed. If the CAB DOOR red light is illuminated or if an unlatched cabin door is suspected: 1. All occupants - SEATED WITH SEAT BELTS SECURELY FASTENED 2. Seat belts and no smoking switch - SET TO NO SMOKING FAST BELT position 3. Cabin Differential Pressure - REDUCE TO LOWEST VALUE PRACTICAL selecting MAN mode or DUMP 4. Oxygen - AS REQUIRED CAUTION If the light remains illuminated, land as soon as practical. BAGGAGE DOOR ANNUNCIATOR ILLUMINATED (BAG DOOR LIGHT ON) If no abnormal engine parameters or vibrations are present: 1. Land as soon as practical If a LEFT propeller strike is supposed and abnormal engine parameters or vibrations on LEFT engine are noted: 1. 2. Perform the ENGINE SECURING Procedure on the LEFT ENGINE Land as soon as practical performing the SINGLE ENGINE APPROACH AND LANDING Procedure EMERGENCY EXIT 1. Emergency exit (first window aft of the windshield on right side) - LOCATE 2. 3. Handle - PULL AND TURN LEFT Emergency exit window - PULL IN NOTE The cabin must be depressurized before attempting to open the emergency exit. AIRPLANE EVACUATION 1. Perform ENGINE SHUT-DOWN Procedure 2. Battery switch - OFF 3. Passengers Door - OPEN If passengers door does not open, perform the EMERGENCY EXIT Procedure. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-49 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.8 AVIONICS SYSTEM EMERGENCIES FLIGHT GUIDANCE SYSTEM FAILURE AUTOPILOT MISSING DISENGAGEMENT 1. Control Wheel/Rudder Pedals - HOLD firmly and OVERPOWER if necessary 2. MSW Button - DEPRESS and HOLD 3. Longitudinal trim switch (pedestal) - SEC 4. Secondary pitch trim control - OPERATE as necessary to reduce control forces 5. MSW Button - RELEASE If necessary: 6. A/P SERVO ELEV and AIL/RUD circuit breakers - PULL AUTOPILOT SERVO HARDOVER 1. Control Wheel/Rudder Pedals - OVERPOWER to prevent further deviation 2. MSW Button - DEPRESS (and HOLD if autopilot fails to disengage) 3. A/P SERVO ELEV and AIL/RUD circuit breakers - PULL WARNING Do not attempt to re-engage the autopilot following an autopilot servo hardover. Rep. 180-MAN-0010-01100 Page 3-50 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST AUTOPILOT AUTOTRIM MALFUNCTION 1. Control wheel - HOLD firmly to prevent further deviation 2. MSW Button - DEPRESS 3. SEC PITCH circuit breaker - PULL WARNING Do not attempt to re-engage the autopilot following an autopilot/ autotrim malfunction. FLIGHT GUIDANCE COMPUTER (FGC) FAILURE If FGC fails or PITCH/ROLL OUTPUTS from FGC missing or invalid (Red FD flag on PFD and Flight Director Bars out of view) 1. Cross-side FGC - SELECT FLIGHT GUIDANCE SYSTEM TRIM FAILURE (red TRIM flag on PFD) 1. Disengage autopilot if necessary 2. Use control wheel trim switch to manually trim the elevator NOTE An elevator trim failure does not automatically disengage autopilot. CAUTION The autopilot cannot be engaged if a TRIM failure exists. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-51 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST PILOT PRIMARY FLIGHT DISPLAY (PFD) FAILURE Pilot PFD failure may be presented as a blank PFD. 1. PFD/MFD switch (on REVERSIONARY panel) - IMMEDIATELY SELECT MFD NOTE Primary flight information will be displayed on the MFD. 2. LPFD Circuit Breaker - CHECK CAUTION ILS CAT II approaches are not allowed. MULTIFUNCTION DISPLAY (MFD) FAILURE MFD failure may be presented as a blank MFD. 1. PFD/MFD switch (on REVERSIONARY panel) - IMMEDIATELY SELECT PFD NOTE Powerplant instruments will be displayed at the top of the pilot and copilot PFD. 2. MFD Circuit Breaker - CHECK NOTE Have maintenance personnel check before the next flight. CONTROL DISPLAY UNIT (CDU) FAILURE 1. CDU Circuit Breaker - CHECK 2. RTU/CDU switch (on REVERSIONARY panel) - SELECT RTU NOTE Tune radios from the RTU. Rep. 180-MAN-0010-01100 Page 3-52 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST RADIO TUNING UNIT (RTU) FAILURE 1. RTU Circuit Breaker - CHECK 2. RTU/CDU switch (on REVERSIONARY panel) - SELECT CDU NOTE Tune radios from the CDU. SINGLE AIR DATA COMPUTER (ADC) FAILURE 1. ADC switch (on REVERSIONARY panel) - SELECT operative ADC 2. Affected side ADC Circuit Breaker - CHECK CAUTION If an ADC1 failure occurs land at the nearest suitable airport. NOTE The autopilot, if engaged, will continue to function in basic roll/ pitch modes. Couple FGC to the operating ADC, as necessary, to recover autopilot full operational condition. ADC comparators will be inoperative. CAUTION ILS CAT II approaches are not allowed. DUAL AIR DATA COMPUTER (ADC) FAILURE 1. Use the Integrated Stand-by Instrument 2. ADC Circuit Breakers - CHECK 3. Land at the nearest suitable airport NOTE Transponder Mode C will be inoperative. Autopilot and Yaw Damper will be inoperative. CAUTION ILS CAT II approaches are not allowed. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-53 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST SINGLE ATTITUDE HEADING COMPUTER (AHC) FAILURE 1. AHC switch (on REVERSIONARY panel) - SELECT operative AHC NOTE AHC comparators and weather radar stabilization will be inoperative. The autopilot and yaw damper will disconnect and will be inoperative. CAUTION ILS CAT II approaches are not allowed. 2. Affected side AHC Circuit Breaker - CHECK NOTE When power is applied to AHC following a loss of electrical power, airborne initialization takes place automatically. The pilot should maintain straight and level flight during airborne initialization. DUAL ATTITUDE HEADING COMPUTER (AHC) FAILURE 1. Use Stand-by Instruments NOTE Weather radar stabilization will be inoperative. The autopilot and yaw damper will disconnect and will be inoperative. CAUTION ILS CAT II approaches are not allowed. 2. AHC Circuit Breakers - CHECK NOTE When power is applied to AHC following a loss of electrical power, airborne initialization takes place automatically. The pilot should maintain straight and level flight during airborne initialization. 3. Land at the nearest suitable airport Rep. 180-MAN-0010-01100 Page 3-54 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST FAILURE FLAGS (RED / YELLOW) ON PRIMARY FLIGHT DISPLAY Refer also to Amplified Emergency procedures section ("Failure Flags on Primary Flight Display"paragraph). FLAG ASSOCIATED WITH FLIGHT CONTROL TRIM If a flight control MISTRIM indication Flag appears: 1. Trim the pertinent control in the direction of the arrow to correct the mistrim FLAG ASSOCIATED WITH FLIGHT NAVIGATION PARAMETERS If any red flag as ACC.-- (Acceleration Flag - gray ACC), ALT, ATT (Attitude Flag), HDG, IAS, M.--- (gray Mach), VS appears: 1. Select on the reversionary panel the pertinent source FLAG ASSOCIATED WITH ILS If any red flag as GS or LOC appears: 1. Localizer frequency - CHECK 2. Cross-side NAV receiver - SELECT as NAV source FLAG ASSOCIATED WITH RADIO NAVIGATION SYSTEM If any red flag as LOC1, LOC2, VOR1, VOR2, FMS1 appears: 1. Different NAV source - SELECT Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-55 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST COMPARATOR FLAGS (YELLOW) ON PRIMARY FLIGHT DISPLAY 1. Monitor the pertinent flagged item on both PFD sides Refer to Amplified Emergency procedures section ("Comparator Flags on Primary Flight Display" paragraph). Rep. 180-MAN-0010-01100 Page 3-56 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.9 CATEGORY II OPERATIONS EMERGENCIES MALFUNCTIONS DURING APPROACH Should any of the following malfunctions be observed for more than 2 seconds, in the absence of reliable visual references perform a go around/missed approach procedure: 1. Loss of power of either engine 2. Autopilot and Yaw Damper disengagement 3. Flight Director flag in view 4. Transition from green CAT II annunciation to yellow CAT II annunciation 5. Loss of Autopilot approach mode 6. Excess deviation alert 7. Comparator alert 8. Any air data parameters flag in view Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-57 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.10 REDUCED VERTICAL SEPARATION MINIMA (RVSM) OPERATIONS EMERGENCIES CAUTION During RVSM operations, the pilot should notify ATC of contingencies (equipment failures, weather) which affect the airplane capabilities to maintain the cleared flight level, and coordinate a plan of action appropriate to the airspace concerned, as soon as possible. AUTOPILOT ALTITUDE MODE FAILURE 1. Airplane Attitude and Altitude - MAINTAIN AS DESIRED 2. Attitude Deviation - MONITOR NOTE The airplane must be maintained within ± 300 feet of desired flight level. An aural warning will be generated if the Altitude Deviation is greater than ± 200 feet. ADC1 FAILURE ADC/AIR DATA flags ON (Any Red flag as ACC.--, ALT, IAS, M.---, VS on pilot’s PFD and white “XADC” flag on copilot’s PFD) a. AP/FD coupled to left side: 1. ADC1/ADC2 switch (on REVERSIONARY panel) - SELECT ADC2 2. CPL button (on FGP) - PUSH 3. Altitude Mode - SELECT as required 4. Airplane Attitude and Altitude - MAINTAIN AS DESIRED b. AP/FD coupled to right side: 1. ADC1/ADC2 switch (on REVERSIONARY panel) - SELECT ADC2 Rep. 180-MAN-0010-01100 Page 3-58 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST ADC2 FAILURE ADC/AIR DATA flags ON (Any Red flag as ACC.--, ALT, IAS, M.---, VS on copilot’s PFD and white “XADC” flag on pilot’s PFD) a. AP/FD coupled to right side: 1. ADC1/ADC2 switch (on REVERSIONARY panel) - SELECT ADC1 2. CPL button (on FGP) - PUSH 3. Altitude Mode - SELECT as required 4. Airplane Attitude and Altitude - MAINTAIN AS DESIRED b. AP/FD coupled to left side: 1. ADC1/ADC2 switch (on REVERSIONARY panel) - SELECT ADC1 Issued: October 21, 2005 Rep. 180-MAN-0010-01100 Page 3-59 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.2.11 P-RNAV OPERATION EMERGENCIES CAUTION During P-RNAV operations, the pilot should notify ATC of any problem with the systems and sensors for P-RNAV that results in the loss of the required navigation capability, and coordinate a plan of action appropriate to the airspace concerned, as soon as possible. FLIGHT GUIDANCE SYSTEM FAILURE P-RNAV operations not allowed. Refer to the CAUTION above reported. FLIGHT MANAGEMENT SYSTEM FAILURE P-RNAV operations not allowed. Refer to the CAUTION above reported. GPS AND DME FAILURE In case both GPS and DME are not available though Flight Management System is operative, P-RNAV operations are not allowed. Refer to the CAUTION above reported. In case of single failure of GPS or DME, P-RNAV operations are allowed. 3.2.12 U.S. RNAV OPERATION EMERGENCIES CAUTION During RNAV operations, the pilot should notify ATC of any problem with the systems and sensors for RNAV that results in the loss of the required navigation capability, and coordinate a plan of action appropriate to the airspace concerned, as soon as possible. FLIGHT GUIDANCE SYSTEM FAILURE RNAV operations not allowed. Refer to the CAUTION above reported. FLIGHT MANAGEMENT SYSTEM FAILURE RNAV operations not allowed. Refer to the CAUTION above reported. GPS FAILURE RNAV operations not allowed. Refer to the CAUTION above reported. Rep. 180-MAN-0010-01100 Page 3-60 Issued: October 21, 2005 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES 3.3 AMPLIFIED EMERGENCY PROCEDURES GENERAL The following paragraphs are presented to supply additional information for the purpose of providing the pilot with a more complete understanding of the recommended course of action in an emergency situation. During these emergency procedures, it is imperative that the pilot continue good flying technique regardless of the situation. A complete knowledge of the procedures set forth in this section will enable the pilot to cope with various emergencies that may be encountered. However, this does not diminish the pilots’ responsibility to maintain aircraft control at all times. SECTION 3 - EMERGENCY PROCEDURES 3.3 AMPLIFIED EMERGENCY PROCEDURES Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-61 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES 3.3.1 ENGINE FAILURES IDENTIFYING DEAD ENGINE AND VERIFYING POWER LOSS If it is suspected that an engine has lost power, the faulty engine must be identified, and power loss must be verified. First check engine indications displayed on the MFD for a drop in ITT and torque. When the wings are level, the rudder pressure required to maintain directional control will be on the side of the operating engine. ENGINE SECURING Begin the securing procedure by pulling the power lever to IDLE and the condition lever to CUT OFF. Check if ignition switch is set to NORM. On the fuel control panel, switch to CLOSED position the firewall shut-off valve and switch OFF the fuel pump. Switch OFF the synchrophaser. Switch OFF the Autofeather. Switch OFF the generator and bleed. Reduce the electrical loads, and consider the use of crossfeed if the fuel quantity dictates. Rep. 180-MAN-0010-01100 Page 3-62 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES ENGINE FAILURE DURING TAKEOFF GENERAL The information given in this section provides procedures to be used by the pilot should an engine fail during take off. The pilot must have a thorough knowledge of these procedures so that in the event of a real emergency, the pilot actions will be correct and precise. These skills are best developed through frequent practice of emergency and simulated single engine procedures. Should an engine failure occur prior to rotation, the takeoff should be immediately aborted. Should an engine failure occur after rotation, the decision must be made immediately whether to continue the takeoff, single engine, or to abort the takeoff and land straight ahead. This decision can be greatly facilitated by careful preflight planning primarily considering available aircraft performance as affected by weight, ambient conditions, pilot proficiency and the required aircraft performance dictated by airfield requirements. NOTE The published Accelerate/Go and Accelerate/Stop distances are Manufacturer data. ENGINE FAILURE DURING TAKEOFF BEFORE ROTATION If an engine failure occurs before rotation and there is sufficient runway remaining, maintain directional control, reduce power to idle, and stop straight ahead using brakes and reverse thrust as required. If insufficient runway remains, pull the condition levers to CUT OFF, switch OFF both generators and close the fuel firewall valves. Maneuver to avoid obstacles and when the airplane has stopped switch OFF the battery and the EPU. WARNING No attempt should be made to continue the takeoff if the engine failure occurs prior to becoming airborne. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-63 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES ENGINE FAILURE DURING TAKEOFF AT OR AFTER ROTATION If sufficient runway remains for a safe stop or the decision is made to abort the takeoff, maintain directional control. Pull the power lever of the engines to IDLE and land straight ahead. After touch down use brakes and reverse as required, engaging reverse below 1900 Prop RPM or 5% drop from the set value. Should a suitable landing area exist, and the decision is made to land the airplane following an engine failure at, or after rotation initiation, the pilot should be aware that performance charts are not presented in this manual for this condition and that the total distance required to stop will exceed the published Accelerate/Stop performance shown in Section 5. If insufficient runway remains or if the decision is made to continue the takeoff, maintain directional control (banking the plane 5° max toward the operative engine when airborne) and maintain the maximum takeoff power while maintaining torque and ITT within limits. After assuring that the aircraft will not settle back to the runway, retract the landing gear and accelerate to the "one engine 50 feet height speed" as per Figure 5-18 (Accelerate/Go Distance Over 50 Feet Obstacle graph) at Section 5 of this AFM. Accelerate to a speed of 125 KIAS minimum, then retract the flaps and the taxi/ landing lights (if applicable) to achieve the “best angle of climb speed” of 132 KIAS or the max. rate of climb speed of 140 KIAS, as appropriate. Maintain this speed until clearing all obstacles within the immediate vicinity of the airport. After all these obstacles have been cleared, perform the ENGINE SECURING procedure. NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. Place the autofeather arm switch in the OFF position and increase airspeed as required. Rep. 180-MAN-0010-01100 Page 3-64 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES Once the above procedures have been completed and the aircraft is at a safe altitude, an airstart may be attempted. (If the start is unsuccessful, complete the "Engine Securing" Procedure on the inoperative engine). Whether the start is successful or unsuccessful the aircraft should be landed at the nearest suitable airport performing the "Single Engine Approach and Landing" Procedure. WARNING The decision to continue a takeoff, single engine is primarily predicated upon, but not necessarily limited to, the aircraft’s ability to climb on a single engine with the gear extended and flaps in the takeoff position. Prior to flight, review airfield requirements and determine that adequate single climb performance exists, considering aircraft weight, ambient conditions and pilot proficiency, to safely complete the takeoff should an engine fail at or after rotation. ENGINE FAILURE IN FLIGHT BELOW VMCA If an engine failure occurs at speed below the VMCA, reduce power on the operating engine to maintain control, then lower the airplane nose to increase speed. Adjust power as required and secure the inoperative engine as per the "Engine Securing" Procedure. ENGINE FIRE (ON GROUND) If the fire is on the ground near the airplane, it may be possible to taxi to safety. If engine fire occurs during start or ground operations, immediately place the condition lever of the affected engine in the CUT OFF position. Check the ignition switch in the NORM position. Brake to a stop if the airplane is moving and CLOSE the firewall shut-off valve. Switch OFF the fuel pump. If a fire extinguisher is installed PUSH the fire extinguisher button. Call for assistance and, when the airplane has stopped, perform the "Airplane Evacuation" Procedure. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-65 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES ENGINE FAILURE OR FIRE IN FLIGHT Should an engine fail or fire in flight, maintain 140 KIAS minimum and maintain directional control banking the plane 5° max toward the operative engine. IDENTIFY and VERIFY the affected engine. Place the power lever of the affected engine to IDLE and the condition lever to CUT OFF; close the firewall shut-off valve and switch OFF the fuel pump, synchrophaser, autofeather, generator and bleed. Check if the ignition switch is in NORM position. If the L or R FIRE light illuminates and the fire extinguisher system is installed, PUSH the fire extinguisher button. Monitor the electrical load and, according to condition of flight (instrument, night, icing, etc.) consider the possibility to reduce the electrical loads. Crossfeed could be used as desired. NOTE The engine fire extinguisher is a single shot system with one cylinder for each engine. In case of engine failure, follow the appropriate AIR START Procedure in an attempt to start the engine. If the starting attempt is unsuccessful, complete the ENGINE SECURING Procedure for the failed engine. Trim the airplane as necessary and land as soon as practical at a suitable airport. CAUTION When conducting a practice run through these procedures, do not close fuel firewall shut-off valves and do not actuate engine fire extinguishers. Fire extinguisher capability has not been evaluated by Airworthiness Authority. NOTE Operation in icing conditions above 14000 ft. is limited to 5 minutes, due to a possible lack of efficiency of the engine inlet de-ice boot system. When operating in icing conditions at high altitudes, the pressure to inflate the engine inlet de-ice boot may not be sufficient and consequently the “BOOTS” left and right ON indications on the MFD, may remain steady white. For this reason, if it is necessary to stay in icing condition for a long time, descend below 14000 ft. approximately, in order to increase the pressure delivered to the system. Rep. 180-MAN-0010-01100 Page 3-66 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES ENGINE FAILURE DURING AUTOPILOT OPERATION If an engine failure occurs while the autopilot is engaged, disengage the autopilot pushing the MSW button and accomplish the ENGINE SECURING Procedure. Following engine securing, the aileron and rudder trim should be manually readjusted and the autopilot may be re-engaged. Selection of the "1/2 BANK" (angle) mode during single engine operation may be applied to reduce the autopilot roll authority. All autopilot modes are usable during single engine operation. NOTE Large power change during single engine operations may require disengaging the autopilot and retrimming the airplane prior to resuming autopilot operation. ENGINE FAILURE DURING AUTOPILOT OPERATION COUPLED APPROACH/COUPLED GO AROUND NOTE Single engine CAT II coupled approaches are not allowed. If an engine failure occurs while the autopilot is engaged, disengage the autopilot pushing the MSW button. Accomplish the SINGLE ENGINE GO AROUND emergency procedure and then the ENGINE SECURING Procedure. Following engine securing, the aileron and rudder trim should be manually readjusted and the autopilot may be re-engaged. Selection of the "1/2 BANK" (angle) mode during single engine operation may be applied to reduce the autopilot roll authority. All autopilot modes are usable during single engine operation. NOTE Large power change during single engine operations may require disengaging the autopilot and retrimming the airplane prior to resuming autopilot operation. SECTION 3 - EMERGENCY PROCEDURES 3.2 AMPLIFIED EMERGENCY PROCEDURES Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-67 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES 3.3.2 AIR START CAUTION The pilot should determine the reason for engine failure before attempting an air start. Do not attempt a relight if the NG tachometer indicates zero percent. RECOMMENDED AIR START ENVELOPE PROPELLER FEATHERED Minimum NG for Airstart 13% NOTE Air start may be attempted outside of the envelope, or lower NG provided ITT starting limit is monitored and not exceeded. NORMAL AIR START Prior to attempting an air start, ensure that the airspeed and altitude fall WITHIN the AIR START ENVELOPE. Check that the cooling system main control switch is OFF, the generator of the operative engine is ON and the generator of the inoperative engine is OFF. Turn OFF the bleed air of the inoperative engine and check the corresponding power lever to IDLE and the condition lever to CUT OFF. OPEN the firewall shut-off valve of the inoperative engine and place its pump switch to MAIN: FUEL PRESS light on the annunciator panel should be OFF. Turn the inoperative engine start switch to START. After NG stabilizes above a minimum of 13%, advance the condition lever to Rep. 180-MAN-0010-01100 Page 3-68.A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES ENGINE FAILURE DURING AUTOPILOT OPERATION If an engine failure occurs while the autopilot is engaged, disengage the autopilot pushing the MSW button and accomplish the ENGINE SECURING Procedure. Following engine securing, the aileron and rudder trim should be manually readjusted and the autopilot may be re-engaged. Selection of the "1/2 BANK" (angle) mode during single engine operation may be applied to reduce the autopilot roll authority. All autopilot modes are usable during single engine operation. NOTE Large power change during single engine operations may require disengaging the autopilot and retrimming the airplane prior to resuming autopilot operation. ENGINE FAILURE DURING AUTOPILOT OPERATION COUPLED APPROACH/COUPLED GO AROUND NOTE Single engine CAT II coupled approaches are not allowed. If an engine failure occurs while the autopilot is engaged, disengage the autopilot pushing the MSW button. Accomplish the SINGLE ENGINE GO AROUND emergency procedure and then the ENGINE SECURING Procedure. Following engine securing, the aileron and rudder trim should be manually readjusted and the autopilot may be re-engaged. Selection of the "1/2 BANK" (angle) mode during single engine operation may be applied to reduce the autopilot roll authority. All autopilot modes are usable during single engine operation. NOTE Large power change during single engine operations may require disengaging the autopilot and retrimming the airplane prior to resuming autopilot operation. SECTION 3 - EMERGENCY PROCEDURES 3.2 AMPLIFIED EMERGENCY PROCEDURES Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-67 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES 3.2.2 AIR START CAUTION The pilot should determine the reason for engine failure before attempting an air start. Do not attempt a relight if the NG tachometer indicates zero percent. RECOMMENDED AIR START ENVELOPE PROPELLER FEATHERED Minimum NG for Airstart 10% NOTE Air start may be attempted outside of the envelope, or lower NG provided ITT starting limit is monitored and not exceeded. NORMAL AIR START Prior to attempting an air start, ensure that the airspeed and altitude fall WITHIN the AIR START ENVELOPE. Check that the cooling system main control switch is OFF, the generator of the operative engine is ON and the generator of the inoperative engine is OFF. Turn OFF the bleed air of the inoperative engine and check the corresponding power lever to IDLE and the condition lever to CUT OFF. OPEN the firewall shut-off valve of the inoperative engine and place its pump switch to MAIN: FUEL PRESS light on the annunciator panel should be OFF. Turn the inoperative engine start switch to START. After NG stabilizes above a minimum of 13%, advance the condition lever to Rep. 180-MAN-0010-01100 Page 3-68.B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST GROUND IDLE and check the engine oil pressure, gas generator temperature and NG. CHECK OFF engine start switch. Advance the condition lever as required after the propeller has come out from feather and adjust power lever as required. Above 54% NG turn ON the starting engine generator and bleed air. NOTE In case of an unsuccessful start, pull the condition lever to CUT OFF and the power lever to IDLE. Check OFF engine start switch. Slow down the airplane to 140 KIAS and after approximately one minute, repeat the AIR START Procedure, using manual ignition (IGN) switch which must be set to NORM after NG reaches 54%. AIR START WITHOUT STARTER ASSIST Prior to attempting an air start, ensure that the airspeed and altitude fall WITHIN the AIR START ENVELOPE. Check that the cooling system main control switch is OFF, the generator of the operative engine is ON and the generator of the inoperative engine is OFF. Turn OFF the bleed air of the inoperative engine and check the corresponding power lever to IDLE and the condition lever to CUT OFF. OPEN the firewall shut-off valve of the inoperative engine and place its pump switch to MAIN: FUEL PRESS light on the annunciator panel should be OFF. At 13% NG set the ignition switch to IGN. Advance the condition lever to GROUND IDLE and monitor I.T.T. and oil pressure. With an idle of 54% NG or greater, place to NORM the ignition switch and turn ON the generator. Adjust condition and power levers as required and turn ON the bleed air. SECTION 3 - EMERGENCY PROCEDURES 3.2 EMERGENCY PROCEDURES CHECK LIST Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 3-69 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST 3.3.3 SMOKE IN COCKPIT Check that the cooling system main control switch is OFF. Keep in open position the cockpit curtain, if installed, to help the smoke evacuation. Actuate MANUAL MASK RELEASE and don mask to supply oxygen to passengers. Open crew air outlets, set the COCKPIT BLOWER switch to CKPT BLOWER position to increase the air flow in the cockpit area helping smoke evacuation. Determine if smoke has been originated from electrical system (distinctive odor of smouldering insulation) or from environmental system. If the smoke originates from electrical system isolate the electrical busses operating the BUS DISC switch and switch OFF one generator at a time in order to identify the faulty circuit. AHC2 will be lost. The cabin press controller is not operational in AUTOSCHED and manual operations will be necessary. Perform CABIN PRESS AUTO MODE FAILURE procedure If the smoke stops, continue the flight and land as soon as practical. If the smoke does not stop, the cause could be the battery. Since the stand-by fuel pumps are fed by the battery, it is necessary, before switching OFF the battery and if the FUEL PUMP light is ON, to descend below 25000 ft with JET A, JET A-1, JP-8 or RP-3 fuel and below 14000 ft with other types of fuel, in order to avoid the possibility of an engine flame out. Restore both generators ON. AHC2 airborne initialization takes place automatically when RH generator is restored. Pull both ESNTL BUS red breakers on left and right circuit breaker panels and, then, switch OFF the battery. Switching OFF the battery, if AHC2 operation has not been restored the Stand-by Instrument only is available. WARNING With battery OFF, the loads of the essential bus will be inoperative. AHC2 shoud be available before proceding with the following steps: Switch OFF the EPU. Switching OFF the EPU the electrical power to the Standby instrument will be interrupted. If fire persists, attempt to extinguish it with the portable fire extinguisher, if available. Land as soon as practical. Rep. 180-MAN-0010-01100 Page 3-70 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES GROUND IDLE and check the engine oil pressure, gas generator temperature and NG. CHECK OFF engine start switch. NOTE In case of unsuccessful start, pull the condition lever to CUT OFF, wait 3 minutes and attempt another start advancing the condition lever to FLIGHT IDLE when NG reaches 50%. As pilot reference, 50% NG will be reached during engine acceleration right after engine start switch automatic switch OFF (about 48% NG). Advance the condition lever as required after the propeller has come out from feather and adjust power lever as required. Above 54% NG turn ON the starting engine generator and bleed air. NOTE In case of no light up, pull the condition lever to CUT OFF and the power lever to IDLE. CHECK OFF engine start switch. Slow down the airplane to 140 KIAS and after approximately one minute, repeat the AIR START Procedure, using manual ignition (IGN) switch which must be set to NORM after NG reaches 54%. AIR START WITHOUT STARTER ASSIST Prior to attempting an air start, ensure that the airspeed and altitude fall WITHIN the AIR START ENVELOPE. Check that the cooling system main control switch is OFF, the generator of the operative engine is ON and the generator of the inoperative engine is OFF. Turn OFF the bleed air of the inoperative engine and check the corresponding power lever to IDLE and the condition lever to CUT OFF. OPEN the firewall shut-off valve of the inoperative engine and place its pump switch to MAIN: FUEL PRESS light on the annunciator panel should be OFF. At 10% NG set the ignition switch to IGN. Advance the condition lever to GROUND IDLE and monitor I.T.T. and oil pressure. With an idle of 54% NG or greater, place to NORM the ignition switch and turn ON the generator. Adjust condition and power levers as required and turn ON the bleed air. SECTION 3 - EMERGENCY PROCEDURES 3.2 AMPLIFIED EMERGENCY PROCEDURES Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 3-69 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES 3.3.3 SMOKE IN COCKPIT Check that the cooling system main control switch is OFF. Keep in open position the cockpit curtain, if installed, to help the smoke evacuation. Actuate MANUAL MASK RELEASE and don mask to supply oxygen to passengers. Open crew air outlets, set the COCKPIT BLOWER switch to CKPT BLOWER position to increase the air flow in the cockpit area helping smoke evacuation. Determine if smoke has been originated from electrical system (distinctive odor of smouldering insulation) or from environmental system. If the smoke originates from electrical system isolate the electrical busses operating the BUS DISC switch and switch OFF one generator at a time in order to identify the faulty circuit. AHC2 will be lost. The cabin press controller is not operational in AUTOSCHED and manual operations will be necessary. Perform CABIN PRESS AUTO MODE FAILURE procedure If the smoke stops, continue the flight and land as soon as practical. If the smoke does not stop, the cause could be the battery. Since the stand-by fuel pumps are fed by the battery, it is necessary, before switching OFF the battery and if the FUEL PUMP light is ON, to descend below 25000 ft with JET A, JET A-1, JP-8 or RP-3 fuel and below 14000 ft with other types of fuel, in order to avoid the possibility of an engine flame out. Restore both generators ON. AHC2 airborne initialization takes place automatically when RH generator is restored. Pull both ESNTL BUS red breakers on left and right circuit breaker panels and, then, switch OFF the battery. Switching OFF the battery, if AHC2 operation has not been restored the Stand-by Instrument only is available. WARNING With battery OFF, the loads of the essential bus will be inoperative. AHC2 shoud be available before proceding with the following steps: Switch OFF the EPU. Switching OFF the EPU the electrical power to the Standby instrument will be interrupted. If fire persists, attempt to extinguish it with the portable fire extinguisher, if available. Land as soon as practical. Rep. 180-MAN-0010-01100 Page 3-70 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES If the smoke originates from environmental system, determine if the source is the engine: this can be isolated by the relative air BLEED valve. Switch BLEED OFF one at a time and when smoke stops, continue the flight with one bleed only. If the smoke persists, the source could be the ECS package and must be used EMER air bleed. NOTE EMER bleed air increases the passenger compartment temperature and it is recommended to avoid prolonged operation at cruise power. To continue the flight in such a condition it is necessary to descent and fly with cabin unpressurized with emergency bleed OFF. To increase the ventilation perform the DUMP Procedure. Land as soon as practical. SECTION 3 - EMERGENCY PROCEDURES 3.2 AMPLIFIED EMERGENCY PROCEDURES Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-71 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES 3.3.4 EMERGENCY DESCENT If it becomes necessary to descent rapidly to a lower altitude, move the power levers to IDLE and the condition lever to MAX RPM. Switch ON the seat belts and no smoking signs. Assume an airplane attitude with nose down in order to reach the Maximum Operating Speed Limit VMO/MMO as soon as possible. Follow the speed limit VMO/MMO envelope. 3.3.5 GLIDE With the flaps and the landing gear UP, the propellers feathered (condition lever in CUT OFF position) the chart below shows the airspeed to be used to attain the least loss in altitude. Consult the BEST GLIDING DISTANCE diagram on Section 5 "Performance" of this AFM to know the horizontal distance covered. MAXIMUM GLIDE SPEED CHART WEIGHT (LBS) SPEED (KIAS) 11550 155 11000 151 10000 144 9000 137 8000 129 Glide Ratio (Refer also to BEST GLIDE DISTANCE graph in Section 5 ("Performance") . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3 NM/1000 ft When operating in sustained icing conditions, the ice build-up on the unprotected parts and the runback ice on the forward and main wings will cause a strong drag increment. In these conditions (ice accretion of approximately 3 inches on the main wing tips) the Glide Ratio may decrease up to 50%. Rep. 180-MAN-0010-01100 Page 3-72 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES 3.3.6 LANDING EMERGENCIES LANDING WITHOUT ENGINE POWER CAUTION With both generators inoperative only essential, battery and hot battery busses are fed by the battery, for approximately 30 minutes depending on loads and battery charge, while the Integrated Stand-by Instrument is fed by the Emergency Power Unit. If an emergency indicates the need to make an approach and landing without the use of engine power, the airplane should first be configured per the MAXIMUM GLIDE Procedure if sufficient altitude permits. When both engines have failed, hydraulic and flap systems are not operative in flight since their circuits are not fed by the battery. In this condition landing gear has to be lowered as per EMERGENCY GEAR EXTENSION Procedure and flaps will be in UP position. NOTE Gear extension requires approximately 60 handpump strokes: this procedure requires normally 90 sec. NOTE For particular terrain conditions it may be required to land with gear up. When the landing gear extension has been completed and only if the gear is confirmed to be down and locked, push in the emergency gear selector and switch to HYD position the hydraulic pump. Once it is assured that the selected landing site will be reached, assume an approach speed increased by 20 KIAS as compared with the flaps DN approach speed (Figure 5-69). Place the condition levers in CUT OFF, CLOSE the firewall shut-off valves, switch OFF the fuel pumps and the synchrophaser system. After touchdown a particular attention has to be paid since brake operation will become harder and landing distances will increase approximately by 125% as compared with the flaps DN landing distance (Figure 5-69). The procedure just described applies also when operating in sustained icing conditions with the exception that the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 15 KIAS. The landing distance, as compared with the flaps MID landing distance (Figure 573), must be increased approximately by 90%. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-73 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES SINGLE ENGINE APPROACH AND LANDING WARNING Do not exceed maximum fuel imbalance (200 lb.). Ensure that the ENGINE SECURING Procedure is complete. Turn OFF the crossfeed valve if open and advance the condition lever to MAX RPM, extend the flap to MID position and maintain a speed of 129 KIAS minimum. NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. If conditions permit, burn as much fuel as possible. When landing site is assured lower the landing gear.Only if S.B. 80-0454 or 800425 (new NWSS) are installed, check that steering system is automatically armed (STEER T-O message on PFD). NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. When it is certain there is no possibility of go-around, extend the flaps to DN and assume approach speed as per Figure 5-69. CAUTION Coupled approaches, with yaw damper inoperative, must be performed in clean or MID flap configuration. Adjust the power as required and after touching down, if necessary, apply reverse thrust slowly and cautiously. Reverse thrust must be applied when the prop RPM has dropped to 1900 RPM. The landing distance, as compared with the flaps DN landing distance (Figure 569), will increase by 30% if reverse thrust is not applied and by 25% if reverse thrust is applied. The procedure just described applies also when operating in sustained icing conditions with the exception that the flap position must be MID and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), Rep. 180-MAN-0010-01100 Page 3-74 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES must be increased by 6 KIAS. The flaps MID landing distance (Figure 5-73) must be increased by 30% if reverse thrust is not applied or by 25% if reverse thrust is applied. SINGLE ENGINE GO-AROUND To execute a single engine go-around, apply takeoff power to the operating engine. Attain a minimum speed of 120 KIAS and retract flaps to MID position, if they are fully down. Retract landing gear and increase airspeed to 125 KIAS minimum, then retract the flaps and the taxi/landing lights (if applicable). Increase the airspeed as required. NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. WARNING When operating in sustained icing conditions, insufficient performance may exist to successfully carry out a single engine go-around. LANDING WITH PRIMARY LONGITUDINAL CONTROL FAILED In the event it becomes necessary to use trim for longitudinal control, trim the airplane to 134 KIAS in level flight. Select the longest runway in the area suitable for a low angle approach. Extend landing gear and if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that it is automatically armed (STEER T-O message on PFD). NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. Set flaps to MID position, maintain 130 KIAS and adjust power for a low angle approach, lower the flaps to DN and trim the plane to 121 KIAS. When positioned over the landing runway, flare the airplane using the reduction of power and the longitudinal trim. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-75 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES After landing and when the nose gear is on the runway, apply reverse as required, when the propeller speed has dropped to 1900 RPM. The procedure just described applies also when operating in sustained icing conditions with the exception that the flap position must be MID and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. LANDING WITH STABILIZER JAMMED If elevator pull force is encountered, the stabilizer is jammed in a nose down trim position. Move, if possible, the center of gravity aft and land as soon as practical to minimize the forward C.G. movement due to fuel-burned. Extend landing gear, if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that it is automatically armed (STEER T-O message on PFD) and set flaps to MID. NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. Assume an approach speed increased by 15 KIAS as compared with the flaps DN approach speed (Figure 5-69). The flaps DN landing distance (Figure 5-69) shall be increased by approximately 45% if reverse is not applied. If elevator push force is encountered, the stabilizer is jammed in nose up trim position. Move center of gravity forward if possible. Extend landing gear and set flaps to DN. Assume the approach speed as per Figure 5-69. The procedure just described applies also when operating in sustained icing conditions with the exception that the flap position must be MID, whatever is the stabilizer position, and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 10 KIAS. The flaps MID landing distance (Figure 5-73) must be increased by 25% if reverse thrust is not applied. Rep. 180-MAN-0010-01100 Page 3-76 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES LANDING WITH LONGITUDINAL CONTROL SPRING FAILED Having assumed the up-down spring failure (refer to LONGITUDINAL CONTROL SPRING FAILURE Procedure), land with flaps in MID position. Assume an approach speed increased by 15 KIAS as compared with the flaps DN approach speed (Figure 5-69). After touchdown, engage reverse as required. The landing distance, as compared with the flaps DN landing distance Figure 569), must be increased by 40% if the reverse thrust is not applied. The procedure just described applies also when operating in sustained icing conditions with the exception that the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 10 KIAS. The flaps MID landing distance (Figure 5-73) must be increased approximately by 20%. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-77 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES LANDING WITH AUTOFEATHER SYSTEM INOPERATIVE The amber AUTOFEATHER light on the annunciator panel is normally illuminated when the system is not armed and the landing gear is down. If S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that it is automatically armed (STEER T-O message on PFD) and set flaps to MID. NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. If, after having armed the system, the light remains illuminated, the autofeather system has to be assumed inoperative and the landing will be performed with flaps in MID position. Assume an approach speed increased by 15 KIAS as compared with the flaps DN approach speed (Figure 5-69). After touchdown, engage brakes and reverse. The landing distance, as compared with the flaps DN landing distance (Figure 569), will increase approximately by 35% if reverse thrust is not applied and by 26% if reverse thrust is applied. The procedure just described applies also when operating in sustained icing conditions with the exception that the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. The flaps MID landing distance (Figure 5-73) must be increased approximately by 10% if reverse thrust is not applied or by 5% if reverse thrust is applied. LANDING WITH GEAR UP OR UNLOCKED The event of one or more red UNSAFE lights staying illuminated after a normal landing gear extraction may be originated by a failure of the switch controlling the gear position light: if the hydraulic pressure reading is about 3000 psi a possible jamming has occured: applying positive load factors or sideslipping the airplane may help to solve the problem. If the hydraulic pressure reading is stabilized around 1000 psi, the gear can be assumed down and locked. However, if the green light does not illuminate (red UNSAFE still lit), it is necessary to lower the gear as per the EMERGENCY GEAR EXTENSION Procedure. Should this procedure be unsuccessful too, a tower fly-by probably will allow to know the status of the landing gear legs. Rep. 180-MAN-0010-01100 Page 3-78 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES If it has been assumed that the nose gear is up or unlocked, land following the normal procedure, maintaining a nose up attitude to the lowest practical speed. After the nose touches the ground apply maximum brake and reverse. If a main gear leg is assumed to be extended, but probably unlocked, perform a landing with normal procedure, touching down on the locked gear, in a nose up attitude. After touch down sustain the unlocked gear wing, apply reverse cautiously and, when the speed has considerably decreased, apply brakes. If one or both main gear legs remain retracted, it is recommended to PUSH the emergency gear selector, to switch ON the hydraulic pump and to perform a GEAR UP LANDING Procedure. Select a suitable landing area, inform ground personnel, brief passengers on use of emergency exit and be sure that all occupants have seat belts and shoulder harnesses secured properly. If condition permits burn off excess fuel and when ready to land, complete the landing check list as for a normal landing, except that the gear selector lever should be in UP position. In order to silence the gear warning horn, pull the AURAL WARN circuit breaker prior to extending the flaps. NOTE In this case no AURAL STALL WARNING signal is provided. The flap should be DN for final approach and landing. Make a normal approach and, when landing is assured, depressurize the airplane, switch off both generators, place the condition lever to CUT OFF, select fuel pumps OFF and fuel firewall shut off valves CLOSED. Switch off the battery and the EPU. Land smoothly, touching down in a level attitude. All occupants should evacuate as soon as the airplane has stopped. The procedure just described applies also when operating in sustained icing conditions with the exception that the flap position must be MID and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-79 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES ASYMMETRIC FLAP CONDITION LANDING In case of a flap system failure complete the FLAP SYSTEM MALFUNCTIONS Procedure. 1. Prior to reaching an altitude of 50 ft. above runway, assure that the landing gear is extended and adjust power as required. The flaps DN approach speeds and landing distances (Figure 5-69) shall be increased, depending on the position of outboard wing flaps, as indicated in the following table: OUTBOARD FLAP POSITION SPEED INCREASE LANDING DISTANCE INCREASE (if reverse thrust is not applied) DN 5 KIAS 10% MID 15 KIAS 40% UP 20 KIAS 65% The procedure just described applies also when operating in sustained icing conditions with the exception that the flaps MID approach speeds and landing distances (Figure 5-73), must be increased as indicated in the table below: OUTBOARD FLAP POSITION SPEED INCREASE LANDING DISTANCE INCREASE (Figure 5-73) MID 10 KIAS 20% UP 15 KIAS 40% Rep. 180-MAN-0010-01100 Appr. DOA EASA.21J.685 Page 3-80 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES LANDING WITH FLAPS RETRACTED In case of an electrical failure in the feeding circuit of the flap systems or a failure in the outboard wing flap system, a landing with no flaps has to be considered. If conditions permit, burn as much fuel as possible. Set the condition levers to MAX RPM and use power levers as required. Assume an approach speed increased by 20 KIAS as compared with the flaps DN approach speed (Figure 5-69). Lower the landing gear. Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that steering system is automatically armed (STEER T-O message on PFD) NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. After touchdown, engage reverse when the propeller speed has dropped to 1900 RPM. The landing distance, as compared with the flaps DN landing distance (Figure 569), will increase approximately by 65% if the reverse thrust is not applied or by 55% if reverse thrust is applied. The procedure just described applies also when operating in sustained icing conditions with the exception that the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 15 KIAS. The landing distance, as compared with the flaps MID landing distance (Figure 573), must be increased approximately by 40% if reverse thrust is not applied or by 30% if reverse thrust is applied. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-81 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES 3.3.7 SYSTEM EMERGENCIES ENGINE SYSTEM FAILURE LOW OIL PRESSURE If oil pressure falls between 60 and 90 psi (yellow indication on the MFD) the power should be reduced below 49,3% torque. An oil pressure below 60 psi, as indicated by the red readout on the MFD and OIL PRESS red annunciator light, is unsafe: the ENGINE SECURING Procedure should be performed for the affected engine and a landing made as soon as practical performing the SINGLE ENGINE APPROACH AND LANDING Procedure. HIGH OIL PRESSURE If oil pressure rises between 135 psi and 150 psi (yellow indication on the MFD) REDUCE the power on the affected engine and land as soon as practical. If the oil pressure exceeds 150 psi (red indication) complete the ENGINE SECURING Procedure for the affected engine and prepare for a SINGLE ENGINE APPROACH AND LANDING Procedure as soon as practical at the nearest suitable airport. HIGH OIL TEMPERATURE Normally on the ground the engine OIL COOL switches, on the ENGINE/ PROPELLER control panel, are set to L and R position when the oil temperature reaches 80°C. When on the ground and the engine oil temperature exceeds 104°C check that the switch of the affected engine is in the L or R position. If the airplane is airborne, an INCREASE in airspeed and a REDUCTION in power will assist in cooling. If oil temperature exceeds the limit (110°C or 104°C more than 10’) perform the ENGINE SECURING Procedure and land as soon as practical, performing the SINGLE ENGINE APPROACH AND LANDING Procedure. Rep. 180-MAN-0010-01100 Page 3-82 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES PROPELLER SYSTEM FAILURE OVERSPEEDING PROPELLER If propeller speed exceeds 2000 RPM steady state (for more than 15 sec.), remaining below 2200 RPM (red steady indication on the MFD) pull power lever to a lower setting, reduce the propeller speed, and reduce airspeed to the lowest practical airspeed for the flight conditions. If propeller RPM exceeds 2200 RPM (red flashing indication) pull Power lever to IDLE. Pull the condition lever to CUT OFF and complete the ENGINE SECURING Procedure. Prepare for a SINGLE ENGINE APPROACH AND LANDING Procedure as soon as practical at the nearest suitable airport. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-83 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES FUEL SYSTEM FAILURE FUEL PUMP FAILURE If the L or R FUEL PUMP amber light illuminates on the annunciator panel, it is necessary to CHECK if the corresponding FUEL PRESS light is ON, if the selected pump is the MAIN and the circuit breaker is PUSHED. If the FUEL PRESS light is not illuminated, the failure is in the main pump, but the stand-by pump is working properly, since this last is automatically engaged. In order to avoid a possible switching between main and stand-by pumps, set the fuel pump switch to STBY. LOW FUEL PRESSURE The L or R FUEL PRESS amber light will illuminate whenever the fuel pressure drops below 7 psi. If this should occur, CHECK if the fuel pump switch is set on MAIN and the circuit breaker is PUSHED. Select the STBY pump to overcome possible poor performance of the main pump. If the light persists two possibilities have to be considered: a faulty pressure switch or a leaking in the engine feeding line. If the rate of change on the fuel quantity indicator is higher on the affected side a presence of a leakage could be possible. In this event perform the ENGINE SECURING Procedure and proceed to a landing as soon as practical performing the SINGLE ENGINE APPROACH AND LANDING Procedure. Otherwise a faulty indication has to be assumed and the flight continued. FUEL FILTER OBSTRUCTED If the L or R FUEL FILTER amber annunciator light is illuminated, the filter is partially obstructed and the fuel bypass is open. CHECK the fuel pressure annunciator light: – if it is not illuminated continue the flight and have maintenance check; – if it is illuminated reduce power on the affected engine and land as soon as practical. Rep. 180-MAN-0010-01100 Page 3-84 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES WING FUEL BALANCING PROCEDURE The fuel crossfeed system may be used if during flight it becomes necessary to balance the fuel load or to extend the range as in the case of single engine operations. Do not take off or land with the crossfeed system engaged. To operate in crossfeed, turn the "CROSSFEED" knob horizontal, then switch OFF the fuel pump of the low fuel level side. Monitor the fuel quantity. NOTE At high fuel flow rate, the L/R FUEL PRESS amber light may illuminate. A power reduction will produce the extinguishing of the low fuel pressure light. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-85 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES ELECTRICAL SYSTEM FAILURE SINGLE GENERATOR FAILURE A generator failure is indicated if a GEN amber light is illuminated on the annunciator panel. If this condition occurs, set the switch of the affected generator to RESET, then ON. If the generator does not reset, place the switch of the affected generator to the OFF position; do not exceed 400 Amp. load on the operating generator. Reduce loads if necessary. NOTE With only one generator operating, all busses are fed. ELECTRICAL OVERLOAD An electrical overload is indicated by a yellow digital readout (GEN xxx) flashing for five seconds under the SYS box in the MFD lower right corner. Where xxx is the generator load actual value in Amperes. In this case, monitor the load on the MFD SYS sub-page: the electrical overload is indicated in Amperes by a yellow digital readout under the corresponding “L GEN AMPS” or “R GEN AMPS” legend on the MFD SYS sub-page. Reduce the electrical load. Before reducing the load on the airplane electrical system, consider the condition of flight (instrument, meteorological condition, night, icing, etc.). A selective method of reducing an electrical load is to remove a system that is not required for the existing flight conditions by turning OFF the corresponding control switch. DUAL GENERATOR FAILURE CAUTION With both generators inoperative only essential, battery and hot battery busses are fed by the battery, for approximately 30 minutes depending on loads and battery charge, while the Integrated Stand-by Instrument is fed by the Emergency Power Unit. If both GEN and BUS DISC amber annunciator lights are illuminated, dual generator failure is indicated. Rep. 180-MAN-0010-01100 Page 3-86 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES Move both generator switches to RESET then ON to attempt to bring the generators back on line. If only one generator resets, proceed with "Single Generator Failure" procedure. If neither generator resets, select the generator switches to OFF. In this condition, only the essential and hot busses are fed by the battery. Move the bus connecting switch (on left side of the MASTER SWITCHES panel) to EMER, if necessary. NOTE With bus connecting switch in EMER position, L/R DUAL FEED BUSSES are powered: limit this operation to prevent further reduction of battery life time. With both generators failed, normal landing gear extension and flap operation are not possible and only the secondary trim actuator is available for longitudinal trim. With both generator inoperative and the bus connecting switch not in the EMER position, the angle of attack transmitter is not heated, STALL FAIL amber light will be illuminated and the stall indication will not be reliable. Land as soon as practical extending the gear as per "Emergency Gear Extension" Procedure and performing both the "Landing with Flaps Retracted" and the "Cabin Press Auto Mode Failure" Procedures. If the battery fails when both generators are inoperative, move the battery switch to OFF then to BAT. If the battery does not reset, switch to OFF. Push the EMER COMM1 button, on the reversionary panel, and the EMG red button on the audio panel, if necessary. NOTE In case of dual generator failure and battery failure, only Integrated Stand-by Instrument, landing gear position lights, emergency lights (for ISI and Magnetic Compass) and VHF COMM1 are powered by the Emergency Power Unit. Limit VHF COMM1 transmissions to avoid EPU discharge. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-87 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES BATTERY OVERTEMPERATURE Battery temperature in excess of the limits is indicated by two annunciator lights: one, amber, labeled BAT TEMP, will illuminate when temperature reaches 120°F (49°C); the other, red, and labeled BAT OVHT will illuminate at and above 150°F (66°C). If the airplane is on the ground and the BAT TEMP amber light is on, select the Multifunction Display (MFD) System page and check the battery temperature (“BATT °F”): do not take off until BATT °F indication turns green and the amber BAT TEMP turns OFF. If the BAT OVHT red light is on, switch OFF the battery and do not take off. During flight, if the BAT TEMP amber light is illuminated, monitor the temperature. If BAT OVHT red light is ON, it is necessary to switch off the battery and land as soon as possible. CAUTION If battery temperature reached 150°F (66°C), either during start or in flight, battery must be removed for bench test and inspection prior to the next flight. AUDIO CONTROL PANEL FAILURE The total loss of receive and transmit functions may be originated by the audio control panel failure. Should the pilot recognize this condition, the emergency mode of operation must be selected pushing the EMG red button located on the audio control panel. NOTE When in emergency mode, the audio control panel allows normal use of transmit and receive functions, with or without power to the system. Page and interphone functions are lost, while mask/boom microphone can be utilized. Rep. 180-MAN-0010-01100 Page 3-88 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES HYDRAULIC SYSTEM FAILURE When an incorrect pressure of significant duration in the hydraulic system is detected, the HYD PRESS caution (amber) light will illuminate on the annunciator panel. CAUTION With the hydraulic pressure at 3000 PSI it is possible to operate the system but hydraulic pump motor must operate for not more than 1 minute. Do not operate the parking brake with the hydraulic pressure above 1200 PSI. With the hydraulic pressure above normal value the steering will be more sensitive. With the hydraulic pump off the steering is inoperative and the brakes are less effective. When the landing gear is down, check that the hydraulic pump switch is set to HYD position and the breakers labeled HYDR WARNING/PRESS and HYDR CONT on the left circuit breaker panel are in. If the pressure gauge reading is outside of the 700 ÷ 1300 PSI range, switch OFF the hydraulic pump. When the landing gear is up, switch OFF the hydraulic pump. Immediately before landing gear extension, set the pump switch to HYD position. EMERGENCY GEAR EXTENSION If an emergency landing gear extension has to be performed, a hand pump provides hydraulic pressure for emergency landing gear extension. CAUTION When performing the procedure for training purpose, after completion ascertain the landing gear selector handle has been positively returned to the full down position, to avoid bleeding of hydraulic pressure with subsequent failure of landing gear retraction. Select the gear handle DN and the hydraulic pump OFF. PULL the emergency landing gear selector. Note that the emergency procedure is printed on a placard fitted on the control pedestal. Issued: October 21, 2005 Appr. DOA EASA.21J.685 Rev. B0 : Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 3-89 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES Operate the hand pump handle until all the three green lights illuminate: about 60 strokes and normally 90 seconds are required. During the hand pump operation, no pressure shall be indicated by the pressure indicator on the control panel. Normal ground roll (Figure 5-69) will increase approximately 55% if reverse thrust in not applied. Brake action will be less effective than normal: land performing "Emergency Brake Operation" procedure. CAUTION After an emergency Landing Gear extension, do not re-engage hydraulic pump and do not re-engage emergency landing gear selector NOTE With the hydraulic pump off the steering is inoperative NOTE When S.B. 80-0454 or 80-0425 (new NWSS) is installed, after Emergency Gear extension, PFD will show T/O steering mode but steering system will remain in free castor mode as hydraulic remains OFF. NOTE Maintenance check on ground is required after an emergency LG extraction. EMERGENCY BRAKE OPERATION In case of hydraulic system failure, emergency brake operation is possible with about 50% increase in pedal force. After touchdown engage reverse as required: normal ground roll (Figure 5-69) will increase approximately 55% if reverse thrust is not applied. NOTE When operating in icing conditions, since the landing procedures are performed with flaps MID and higher speed, the ground roll distance with flaps MID (Figure 5-73) will increase approximately 80% if reverse thrust is not applied. Rep. 180-MAN-0010-01100 Page 3-90 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES STEERING SYSTEM FAILURES If the airplane is NOT equipped with S.B. 80-0286 (mod. 80-0932) and NOT equipped with S.B 80-0454 or 80-0425 (mod. 80-1123) If the STEER FAIL red warning light is on, the steering system automatically disengages: nevertheless it is suggested to press the Control Wheel Master Switch. Check off the steering indications on the PFD. Steering of the airplane is achieved through the use of differential brakes and/or power. NOSE WHEEL STEER RUNAWAY As soon as an uncontrolled heading change occurs, press the Control Wheel Master Switch (red button) located on the outboard horn of each control wheel. Directional control can be maintained using differential braking and asymmetrical power. If the airplane is equipped with S.B. 80-0286 (mod. 80-0932) STEER FAIL LIGHT ON If the STEER FAIL red warning light is on, the hydraulic power to the steering system automatically disengages: nevertheless it is suggested to press and release the Control Wheel Master Switch (to reset the control system) and verify the steering indication on the PFD and the STEER FAIL light. NOTE If autopilot is operating, pressing the Control Wheel Master Switch, it will be disengaged. A STEER FAIL light that remains ON after press and release the Control Wheel Master Switch could indicate a permanent damage of the steering command potentiometer, feedback potentiometer or a relay in the electrical circuitry. A STEER FAIL light that turns OFF after press and release of the Control Wheel Master Switch, could indicate a transient damage to the command potentiometer or feedback potentiometer (such as the lost of contact in a given section of the potentiometer track). When the hydraulic power to the steering system is not selected or disengaged by the pilot (through the Control Wheel Master Switch), steering of the airplane on-ground is achieved through the use of the pedals (differential braking and rudder control), the control wheel, and/or asymmetrical power. If a STEER FAIL light has become on, after landing do not engage the steering system in any case (i.e.: for taxi operations). Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-91 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES NOSE WHEEL STEER RUNAWAY As soon as an uncontrolled heading change occurs on-ground, press the Control Wheel Master Switch (red button) located on the outboard horn of each control wheel. Directional control can be maintained (as necessary) through Pedals, Control Wheel and asymmetrical power. If the airplane is equipped with S.B. 80-0454 S.B. or 80-0425 (mod. 80-1123) CAUTION When the Steering System is in failure mode (STEER FAIL light ON), the Antiskid System (if installed) must be switched OFF. STEER FAIL LIGHT “ON” DURING TAKEOFF Press the Control Wheel Master Switch button. Steering of the airplane is achieved through the use of differential brakes. If sufficient runway remains and the speed is not excessive to allow a safe stop, reduce power levers to IDLE, apply brakes as required and, once the airplane is stopped on runway, refer to the procedures below in order to perform taxi. If NO sufficient runway remains, perform takeoff and refer to the procedures below for landing. STEER FAIL LIGHT “ON” DURING LANDING NOTE CWMS switch does not affect the steering while the airplane is in flight. When Steer Fail light illuminates during landing, two cases are possible: If NO Mode indication is displayed on the PFD: Switch OFF the Hydraulic switch and pull STEER Circuit Breaker (located on the Pilot CB panel). NOTE Steer fail light will go off and steering system will be inoperative (free caster). Emergency braking will be operative (refer to "Emergency Brake Operation" procedure). Rep. 180-MAN-0010-01100 Page 3-92 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES Directional control can be maintained using rudder differential braking and asymmetrical power. When the airplane is stopped and runway is vacated (if possible), do not perform Taxi and require towing of the airplane. If TO indication is displayed on the PFD: Perform final approach with normal procedures at minimum Vref. NOTE NWSS will be operative during landing roll. It will operate in TO mode only with no mode change possible. When airplane is stopped and runway is vacated (if possible), do not perform Taxi and require towing of the airplane. “TAXI” INDICATION ON PFD DURING LANDING If during Landing procedure the STEER FAIL red warning light is OFF and indication on PFD is TAXI, press the Control Wheel Master Switch to disengage the system. Directional Control can be maintained using differential braking. NOSE WHEEL STEER RUNAWAY As soon as an uncontrolled heading change occurs, press the Control Wheel Master Switch (red button) located on the outboard horn of each control wheel. Directional control can be maintained using differential braking and asymmetrical power. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-93 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES LONGITUDINAL CONTROL SYSTEM MALFUNCTION LONGITUDINAL TRIM RUNAWAY An uncommanded pitch trim motion, when the system is set to PRI mode, is easily detected by an aural warning signal associated with the stabilizer movement. Press immediately the Control Wheel Master Switch (red button), located on the outboard horn of each control wheel: this action disconnects the electrical power and the movement will stop. Select on the PITCH TRIM panel, the SEC mode and trim the airplane moving both halves of the dual switch together to UP or DN as required. CAUTION Trim in motion aural warning is not operative when in secondary mode. PRIMARY LONGITUDINAL TRIM FAILURE In case of primary longitudinal trim inoperative, check if the PRI PITCH TRIM breaker is IN, then select the longitudinal trim switch, on the pedestal, in SEC mode; in SEC mode the stabilizer movement rate is constant in all the range. CAUTION Trim in motion aural warning will not be operative when in secondary mode. LONGITUDINAL CONTROL SPRING FAILURE Mechanical failure of the up-down longitudinal control spring could produce: – at forward C.G. longitudinal control forces slightly more than usual; – at full rear C.G., high altitude and high speed a light control feel on longitudinal control. In this case reduce airspeed to 210 KIAS above 30,000 feet. In any case landing procedure should be in accordance with "Landing with Longitudinal Control Spring Failed" Procedure. Rep. 180-MAN-0010-01100 Page 3-94 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES FLAP SYSTEM MALFUNCTION FLAP SYNCHRO FAILURE If, during flight or after a maneuver of the flaps has been performed, the FLAP SYNC light will illuminate (and the “FLAPS” indications on the PFD and MFD become yellow), or abnormal control forces are experienced, check the position of the selector lever and the position of the flaps on the flap position indicator display (on MFD System Page). 1. If it has been assumed that an asymmetry exists between the flaps, maintain control using primary and secondary flight control systems. NOTE During flap extension or retraction the most extreme combinations of failures could be: a. Outboard flaps DOWN, forward wing flaps UP: in this situation a strong pitch down will develop. The recommended recovering maneuver is: maintain pitch control using wheel, reduce forces with longitudinal trim, then reduce power and airspeed. b. Outboard flaps UP, one or both forward wing flaps DOWN: in this situation a pitch up and a yawing moment (in case of one only forward wing flap down) will develop. The recommended recovering procedure is: control pitch attitude using wheel, reduce forces with longitudinal trim, apply pedal as necessary and increase power. Allow airspeed to decrease. c. One forward wing flap run away when in landing configuration: in this case a pitch down and a yaw moment will develop. The recommended recovering procedure is: maintain longitudinal control using wheel and directional control as required. Reduce forces with trim and reduce power as required. Intermediate asymmetries result in lower control forces than the above and are easily trimmed down. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-95 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES After having regained the control of the airplane, reconfigure, if necessary, the remaining flap systems to minimize the asymmetry, considering that: a. If the asymmetry was originated after a single step command (normal flap maneuvering procedure: UP to MID, MID to DN and vice-versa), any position of the flap lever can be selected to reposition the working flap systems toward the failed one. b. If the asymmetry was originated after a direct command UP to DN or vice-versa, the reconfiguration is possible only setting the flap lever in the original position (before the failure occurred). 2. If the flap positions correspond to the lever setting and/or no significant trim change is detected, do not move the lever any further. Service before next flight. Landing is performed considering speeds and distances higher than the normal as indicated in the "Asymmetric Flap Condition Landing" Procedure. Rep. 180-MAN-0010-01100 Page 3-96 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES PRESSURIZATION AND ENVIRONMENTAL SYSTEM MALFUNCTION The cabin pressure control system (CPCS) working in the AUTO mode, normally maintains a differential pressure regulated up to 9 psid. When a failure occurs, the red warning CAB PRESS light is activated on the annunciator panel respectively if the differential pressure exceeds 9.4 psid or the cabin altitude is higher than 9500 ft. When the cabin altitude gauge indicates an altitude higher than 9500 ft, select the MANUAL MASK RELEASE, don masks, oxygen mask microphone to MASK and verify if both bleed air switches are ON. Set the cabin pressure control switch to MAN and the manual controller toggle switch to DN. This allows the cabin altitude to decrease at a rate governed by the position of the control knob: increase or decrease as desired assuming a failure on the autoschedule mode. If the cabin altitude continues to increase, set the emergency bleed air switch to EMER and initiate an emergency descent if required or if the decompression is rapid or explosive. When a comfortable altitude is reached (12000 ft) switch OFF the emergency bleed. In case of failure of cabin door seal, an amber DOOR SEAL light will illuminate on the annunciator panel. In this case it is necessary to descent or limit the altitude to 30000 ft or below. Check the pressurization indicators, and, if the variations indicate rapid change, consider an emergency descent as per "Emergency Descent" procedure. Supply oxygen to crew and passenger as required. When the cabin p gauge indicates a differential pressure above 9.4 psid, set to OFF the bleed air switches and to IDLE the power levers, until the cabin differential pressure reaches about 8 psid: at this point the pressurization system can be selected to MAN to perform "Cabin Press Auto Mode Failure" Procedure. In case it becomes necessary to unload (DUMP) cabin pressure, select, on the oxygen panel, MANUAL MASK RELEASE and don masks if necessary, lift the guard cover of the dump switch and select the DUMP position. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-97 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES A rapid depressurization will occur until the cabin altitude reaches approximately 13000 ft, when the flight level is higher than 13000 ft. This limit is governed by mechanical pressure relief valves that work independently from the pressurization mode selected (automatic or manual). After a failure of the autocontroller, perform the following when the airplane is below 10000 ft and before landing: set the cabin pressure control switch to MAN and the manual controller toggle switch to UP; set the manual rate control knob to max rate. The Airplane is not approved for landing when pressurized. After touchdown and before opening the door, set the dump switch to DUMP. CAUTION Aircraft is not approved for landing when pressurized. The environmental control of the cockpit and cabin is ensured through a Heating Unit, for hot air supply only, operated by the engines bleed air, coupled to a Freon Airconditioner for cold air supply. If an overheating or a leakage occurs to the left or right bleed ducts a corresponding red warning light will illuminate on the annunciator panel (L or R BLEED TEMP). Reducing the power of the affected side engine will extinguish the corresponding light, but if this does not occur, it is necessary to set the bleed air switch to OFF. When a failure occurs to the temperature automatic control or when an overheating in the cabin air supply duct (red annunciator DUCT TEMP light ON) is detected, set to MAN the temperature controls and then the HI/LO momentarily switches to LO. Maintaining for a while the switch to LO position also the DUCT TEMP light should extinguish: the temperature modulating valves require about 15 seconds operating time from full hot to full cold. If the DUCT TEMP light is ON and persists for further 15 seconds set the emergency bleed air switch to EMER and descent to a comfortable altitude (below 9500 ft), then switch OFF the emergency bleed. Rep. 180-MAN-0010-01100 Page 3-98 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES ICE PROTECTION SYSTEM FAILURE Normal operation of the airplane ice protection system is generally indicated by the Anti-Ice Status Display (on MFD System Page) and/or the anti-ice panel. When a failure or abnormal operation of the forward and main wings ice protection systems, of the engine inertial separator or of the oil cooler inlet lip heater occurs, under the SYS box on the MFD lower right corner an amber indication of “ANTICE” will be flashing for five seconds. In addition, if flying in actual icing condition, the ICE light, on the Master Warning panel, will flash when one of the above mentioned systems is inoperative or switched off. Selecting the MFD SYS sub-page the associated left or right green “ON” indication goes off, the associated anti-ice legend (“FW”, “MW”, “ENG” or “OIL”) shows in yellow. If the amber ICE light does not illuminate in icing condition or remains illuminated for more than 5 seconds (even in clear air), a failure of the sensing probe has occurred and the monitoring capability of the ICE light is completely lost: in this conditions, as first, the L/R ENG ICE VANE and L/R OIL COOLER INTK switches must be checked to the L and R positions, then it is necessary to determine the ice accretion by visual inspection of the probe located on the windshield. In addition, with the failure of the ice detector, the engine inlet de-ice boot cannot operate in AUTO mode. When one or more of the aforementioned system have not been switched on. If the ice accretion rate, on the probe, is approximately 1/4 inch (6 mm) per minute, a heavy ice condition may be assumed: the BOOTS DE ICE switch must set to the TIMER position. If the accretion is lower, a light ice condition may be assumed, and the boots switch has to be operated cycling TIMER/OFF every 6 minutes approximately. CAUTION Continuous cycling of boots during some types of ice encounters may result in failure to remove ice. A “BOOTS” ON indication (left or right) steady white or steady green depends on a controller failure, on the ice detector failure, on a failure of the control valve or of the boot itself. Check the L/R ENG ICE VANE and L/R OIL COOLER INTK switches are set to the L and R positions. If the system was operating in AUTO mode, it is necessary to determine the ice forming by visual inspection of the ice accretion probe. Again, if it is determined that heavy ice conditions exist (accretion rate higher than 1/4 inch per minute) set the BOOTS DE ICE switch to the TIMER position, Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-99 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES and, in case of light ice, cycle TIMER/OFF every 6 minutes approximately (see CAUTION above). When the engine inertial separators are operated and fully deployed (after 30 seconds approximately), the “ENG” green ON indications will show; if one fails to appear, observe the engine torque drop of the affected side: if it is not similar to the other engine, a failure of the engine inertial separator is suspected. Reset the affected side system setting the L or R ENG ICE VANE switch to OFF then L or R position: if the normal operating conditions are not restored, leave the ice conditions as soon as possible. An “OIL” green ON indication which does not appear could depend also on an insufficient air temperature of the oil cooler inlet, on a failure of the shut off valve or the thermal switch. If the indication persists off even with the corresponding NG above 86%, a failure of the oil cooler inlet heater monitoring system is suspected: flight in icing condition is possible only if the oil temperature has no abnormal increase. An overtemperature warning light is included in the main wing anti-ice circuit and when it becomes lit, it is necessary to switch OFF the affected side system. If after 20 seconds approximately the light is still illuminated, power must be reduced as much as possible to sustain flight and ice condition must be left as soon as practical. If the light extinguishes, switch the system to MANUAL and check the MN WG OVHT light. CAUTION In light ice conditions, in order to avoid overheat, a NG between 88% and 91% is recommended. Should the red MN WG OVHT light illuminate, the affected system must be turned OFF for one minute approximately. If the green ON indications of the main wing anti-ice system (“MW” legend) are not on, increase power momentarily: if the indication remains off, switch the system to OFF for approximately 10 seconds, then MANUAL and check the ITT variation. If after approximately 30 seconds the indication is still off and ITT has not increased by 20°C approximately, a control valve failure has occurred: switch OFF both forward and main wings anti-ice systems and leave ice conditions as soon as possible. Rep. 180-MAN-0010-01100 Page 3-100 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES If the green ON indication appear or remains off, but the ITT increases approximately 20°C, leave the affected system to MANUAL, paying attention to the MN WG OVHT warning light (see CAUTION above). A main wing anti-ice green ON indication, flashing when the system operates in AUTO mode, indicates that an overheat sensor has failed. Operation in AUTO mode is still possible owing to the redundancy of the overheat warning circuits, but operation in MANUAL mode must be avoided. An overtemperature warning light is also included in the forward wing anti-ice circuit and when it becomes lit, it is necessary to switch OFF the affected side system: disregarding this procedure, damage could result to the forward wing leading edge structure. Leave ice condition as soon as practical. In case of a forward wing anti-ice system failure check on the MFD System Page (L or R GEN AMPS) the variation of electrical current switching the affected system ON and OFF. If the variation is 30-40 Amp., continue the flight; if the variation is less than 30 Amp. approximately, leave ice condition as soon as practical. WINDSHIELD HEAT SYSTEM FAILURE When the heating sensor detects an overheating condition, the red L or R WSHLD ZONE light will illuminate on the annunciator panel. If the light does not extinguish after primary or secondary heating systems are switched to LO mode (PRI or SEC WSHLD HEAT switches to LO) it is necessary to cycle the affected zone switch to LO then OFF position, when necessary, to obtain clear view. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-101 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES 3.3.8 AVIONICS SYSTEM EMERGENCIES FLIGHT GUIDANCE SYSTEM FAILURE The following paragraphs are presented to supply additional information for the purpose of providing the pilot with a more complete understanding of the recommended course of action and probable cause of an emergency situation. a. The autopilot can be disengaged by any of the following methods: 1. Push the MSW button on pilot's or copilot's control wheel. 2. Push the AP switch on the Flight Guidance Panel. 3. Operate the AP/YD DISC lever on the Flight Guidance Panel. 4. Put the trim selector switch in the OFF or SECONDARY trim position. 5. Operate the trim switch on the outboard side of the pilot's or copilot's control wheel. 6. Pull the A/P SERVO ELEV and AIL/RUD circuit breakers or the SEC PITCH circuit breaker (pilot's CB panel). The most effective method for disengaging the autopilot is pressing the MSW button until disengagement is recognized by the pilot. However, if upon releasing the MSW button the controls are still loaded (like the autopilot has not disengaged) press and hold the MSW button to fully unload the controls. Then setting the longitudinal trim switch to SEC, longitudinal trimming is allowed with the secondary control (pedestal). b. The following conditions will cause the autopilot to disengage automatically 1. Any major degradation, interruption or failure of input electrical power. 2. Detection of a failure in the autopilot system by the internal monitors. 3. Loss of Attitude Heading Reference System (AHRS) or coupled Air Data System (ADS). 4. Roll attitudes in excess of approximately 45 degrees and/or pitch attitudes in excess of approximately 25 pitch up or 18 pitch down degrees. 5. Indicated airspeed below stall warning speed or with the stall warning activated for more than 1 sec. Rep. 180-MAN-0010-01100 Page 3-102 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES c. The yaw damper can be disconnected by any of the following methods: 1. Push the MSW button on pilot's or copilot's control wheel. 2. Push the YD switch on the Flight Control Panel. 3. Operate the AP/YD DISC lever on the Flight Guidance Panel. 4. Pull the A/P SERVO AIL/RUD circuit breaker on the pilot's breaker panel. d. The following conditions will cause the yaw damper to disengage automatically: 1. Detection of a failure in the Autopilot System by the internal monitors. 2. Any major degradation, interruption or failure of input electrical power. e. In the unlikely event of any servo becoming mechanically jammed, control of the airplane can still be maintained by overpowering the servo capstan slip clutch. The maximum overpower forces on the controls are as follows: Roll 5 kg (12 lbs) Yaw 27 kg (60 lbs) Pitch 20 kg (45 lbs) NOTE The pitch force represents the initial overpower force of the pitch servo. After approximately 2 seconds, the autotrim system will run in a direction to oppose the overpower force, thereby increasing the overpower force as a function of time and airspeed: for this reason it is imperative to disengage the autopilot as soon as a malfunction is detected. AUTOPILOT SERVO HARDOVER An autopilot servo hardover occurs when a servo runs without being commanded to do so. This type of malfunction is recognizable by the airplane deviating from a preprogrammed flight path in either pitch, roll or yaw depending on which servo malfunctioned. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-103 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES Should this type of malfunction be observed or suspected, immediately grasp the control wheel and disconnect the autopilot with the MSW button on the yoke, then pull the A/P SERVO ELEV and AIL/RUD circuit breakers located on the pilot's panel. WARNING Do not attempt to re-engage the autopilot following an autopilot servo hardover. The autopilot system incorporates internal monitors in the roll and pitch axes which will automatically disengage the autopilot if the roll angle exceeds ± 45° or pitch exceeds +25° (pitch up) or -18° (pitch down). If the roll rate exceeds 10 deg/s, or the bank angle exceeds 40°, or the pitch rate exceeds 3.5 deg/s, or the yaw rate exceeds 9 deg/s, or the acceleration exceeds a +0.7 or -0.375 "g" change, a monitor will remove the torque from the servo until the rate or the load factor are below those established limit before re-applying the torque. AUTOPILOT AUTOTRIM MALFUNCTION An autotrim malfunction is extremely improbable. However, if the pilot observes a steady illumination of the red TRIM PFD flag an autotrim malfunction may have occurred. An autopilot autotrim malfunction occurs when the elevator trim servo runs uncommanded or a malfunction is detected in the trim system with the autopilot engaged. The airplane initially will not deviate from the selected vertical mode as the elevator servo compensates for the out of trim condition until the trim forces overpower it. If any of the above indications are observed, hold the control wheel firmly to prevent pitch excursions, and disconnect the autopilot with the MSW button, then pull the SEC PITCH circuit breaker located on the pilot circuit breaker panel. To retrim, if necessary, the airplane, only the primary pitch trim should be used. WARNING Do not attempt to re-engage the autopilot following an autopilot/ autotrim malfunction. FLIGHT GUIDANCE COMPUTER (FGC) FAILURE (Self explanatory) FLIGHT GUIDANCE SYSTEM TRIM FAILURE (Self explanatory) Rep. 180-MAN-0010-01100 Page 3-104 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES PILOT PRIMARY FLIGHT DISPLAY (PFD) FAILURE Pilot PFD failure may be presented as a blank PFD. If a PFD malfunction occurs, select MFD on the reversionary PFD/MFD switch (on the REVERSIONARY panel) to show the PFD/MFD composite format on the MFD. Check and try to reset, if necessary, the LPFD circuit breaker, on the Pilot’s CB panel. CAUTION ILS CAT II approaches are not allowed. MULTIFUNCTION DISPLAY (MFD) FAILURE MFD failure may be presented as a blank MFD. If a MFD failure occurs, an immediate selection of PFD on the reversionary PFD/ MFD switch (on the REVERSIONARY panel) is required in order to have powerplant instruments displayed at the top of the pilot’s and copilot’s PFDs. Check and try to reset, if necessary, the MFD circuit breaker, on the Pilot’s CB panel. In the event of MFD failure, if reversion on PFD is not immediate, a suspected overtorque or overtemperature of the engines, could be assumed depending on flight conditions. NOTE Have maintenance personnel check before the next flight. Report the maintenance personnel about event conditions (i.e. balked landing, take off, climb, power lever setting operations). Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-105 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES CONTROL DISPLAY UNIT (CDU) FAILURE In case of a CDU failure, the RTU loses normal full tuning capability of the crossside (side 2) radios. The message CROSS-SIDE RADIO TUNING INOPERATIVE shows in yellow on the RTU when cross-side tuning capability is lost. Check and try to reset, if necessary, the CDU circuit breaker, on the Pilot’s CB panel. If the malfunction persists select RTU on the reversionary RTU/CDU switch (on the reversionary panel) to enable RTU tuning on both on-side and cross-side radios. RADIO TUNING UNIT (RTU) FAILURE In case of a RTU failure, the CDU loses normal full tuning capability of the crossside side 1) radios. The message CROSS-SIDE RADIO TUNING INOPERATIVE shows in yellow on the CDU when cross-side tuning capability is lost. Check and try to reset, if necessary the RTU circuit breaker, on the Pilot’s CB panel. If the malfunction persists select CDU on the reversionary RTU/CDU switch (on the reversionary panel) to re-enable CDU tuning on both on-side and cross-side radios. Rep. 180-MAN-0010-01100 Page 3-106 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES SINGLE AIR DATA COMPUTER (ADC) FAILURE If an Air Data Computer failure occurs, select the operative ADC (ADC1 or ADC2) with the reversionary ADC switch (on the reversionary panel) and check that the relevant ADC# reversion message appears on the PFD: both pilot’s and copilot’s PFD will receive air data from the operative ADC. Information received from the onside ADC is displayed in white; information received from the cross-side ADC is displayed in yellow. Check and try to reset, if necessary, the relevant ADC circuit breaker. CAUTION If an ADC1 failure occurs land at the nearest suitable airport. NOTE The autopilot, if engaged, will continue to function in basic roll/ pitch modes. Couple FGC to the operating ADC, as necessary, to recover autopilot full operational condition. ADC comparators will be inoperative. CAUTION ILS CAT II approaches are not allowed. DUAL AIR DATA COMPUTER (ADC) FAILURE If dual Air Data Computer failure occurs, check both ADC circuit breakers. If the malfunction persists, rely on the Integrated Stand-By Instrument and land at the nearest suitable airport. NOTE Transponder Mode C will be inoperative. Autopilot and Yaw Damper will be inoperative. CAUTION ILS CAT II approaches are not allowed. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-107 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES SINGLE ATTITUDE HEADING COMPUTER (AHC) FAILURE If an Attitude Heading Computer failure occurs, select the operative AHC (AHC1 or AHC2) with the reversionary AHC switch (on the reversionary panel) and check that the relevant AHC# reversion message appears on the PFD: both pilot’s and copilot’s PFD will receive attitude and heading data from the operative AHC. Information received from the onside AHC is displayed in white; information received from the cross-side AHC is displayed in yellow. NOTE AHC comparators and weather radar stabilization will be inoperative. The autopilot and yaw damper will disconnect and will be inoperative. CAUTION ILS CAT II approaches are not allowed. Check and try to reset, if necessary, the relevant AHC circuit breaker. NOTE When power is applied to AHC following a loss of electrical power, an airborne initialization takes place automatically. The pilot should maintain straight and level flight during airborne initialization. In a normal airborne initialization.valid heading and attitude information is available after at least 35 to 50 seconds with DG mode deselected (“DG/Slave” switch on Reversionary Panel in Slave position). Errors in pitch and roll attitude that are shown on the display may result if the aircraft accelerates or decelerates during airborne initialization. If such errors do occur, they will slowly diminish with continued steady-state flight. During an airborne initialization, the pilot should perform always a cross-check with the Stand-by Attitude Indicator to detect any initialization errors. Rep. 180-MAN-0010-01100 Page 3-108 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES DUAL ATTITUDE HEADING COMPUTER (AHC) FAILURE If dual Attitude Heading Computer failure occurs, check and try to reset both AHC Circuit Breakers. NOTE When power is applied to AHC following a loss of electrical power, an airborne initialization takes place automatically. The pilot should maintain straight and level flight during airborne initialization. In a normal airborne initialization valid heading and attitude information is available after at least 35 to 50 seconds with DG mode deselected (“DG/Slave” switch on Reversionary Panel in Slave position). Errors in pitch and roll attitude that are shown on the display may result if the aircraft accelerates or decelerates during airborne initialization. If such errors do occur, they will slowly diminish with continued steady-state flight. During an airborne initialization, the pilot should perform always a cross-check with the Stand-by Attitude Indicator to detect any initialization errors. If the malfunction persists use the Integrated Stand-By Instrument for attitude data and Magnetic Compass for heading data, and land at the nearest suitable airport. NOTE Magnetic Compass calibration data, identified with “Avionics ON”, are available for heading information readings provided that windshield and pitot/static heating systems, FWD wing A/I system and landing lights are momentarily switched off. NOTE Weather radar stabilization will be inoperative. The autopilot and yaw damper will disconnect and will be inoperative. CAUTION ILS CAT II approaches are not allowed. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-109 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES FAILURE FLAGS ON PRIMARY FLIGHT DISPLAY FLAG ASSOCIATED WITH FLIGHT CONTROL TRIM a. Aileron Mistrim Yellow and Red Flags The YELLOW aileron mistrim shows when the aileron is moderately out of trim. The mistrim flashes for five seconds then becomes steady. The arrow that shows above the A in the box points left or right to indicate the direction of the mistrim. If the annunciation persist for more than 10 seconds hold firmly the wheel, disengage the autopilot, trim the aileron in the direction of the mistrim and reengage the autopilot. The RED aileron mistrim shows when the aileron is significantly out of trim. The mistrim flashes for five seconds then becomes steady. The arrow that shows above the A, in the box, points left or right to indicate the direction of the mistrim. Hold firmly the wheel, disengage the autopilot, trim the aileron in the direction of the mistrim and re-engage the autopilot. b. Elevator Mistrim Yellow and Red Flags The YELLOW elevator mistrim shows when the elevator is moderately out of trim. The mistrim flashes for five seconds then becomes steady. The arrow that shows next to the E, in the box, points up or down to indicate the direction of the mistrim. If the annunciation persist for more than 10 seconds hold firmly the column, disengage the autopilot, trim the elevator in the direction of the mistrim and re-engage the autopilot. The RED elevator mistrim shows when the elevator is significantly out of trim. The mistrim flashes for five seconds then becomes steady. The arrow that shows next to the E in the box points up or down to indicate the direction of the mistrim. Hold firmly the column, disengage the autopilot, trim the elevator in the direction of the mistrim and re-engage the autopilot. Rep. 180-MAN-0010-01100 Page 3-110 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES c. Rudder Mistrim Yellow and Red Flags The YELLOW rudder mistrim shows when the rudder is moderately out of trim.The mistrim flashes for five seconds then becomes steady. The arrow that shows above the R in the box points left or right to indicate the direction of the mistrim. The RED rudder mistrim shows when the rudder is significantly out of trim. The mistrim flashes for five seconds then becomes steady. The arrow that shows above the R in the box points left or right to indicate the direction of the mistrim. Trim the rudder in the direction of the arrow to correct the mistrim. FLAG ASSOCIATED WITH FLIGHT NAVIGATION PARAMETERS a. ACC (Acceleration) RED Flag When the longitudinal acceleration indication function is failed or missing a red decimal point and two red dashes shall be displayed flashing for five seconds and then become steady. NOTE The acceleration flag shows, only when on ground, in the same location as the Mach flag and the two are mutually exclusive. When the acceleration is displayed a gray scaled ACC legend shows in front of the readout at all times. Select the cross-side AHC (AHC1 or AHC2) with the reversionary AHC switch (on the reversionary panel) and refer to the "Single Attitude Heading Computer (AHC) Failure" Procedure. b. ALT (Altitude) RED Flag The ALT red flag shows when altitude data from the selected ADC is missing or invalid or there is no barometric pressure available. The red, boxed "ALT” will flash for five seconds, then become steady, in place of the Barometric Altitude Pointer. Barometric Altitude tapes, digital thousands readout, and metric altitude (if selected) shall be removed Select the cross-side ADC (ADC1 or ADC2) with the reversionary ADC switch (on the reversionary panel) and refer to the "Single Air Data Computer (ADC) Failure" Procedure. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-111 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES c. ATT (Attitude) RED Flag The ATT flag flashes for five seconds, then becomes steady, when attitude data (roll and pitch angle) from the selected AHC is missing or invalid. The attitude ball is removed from the display. Select the cross-side AHC (AHC1 or AHC2) with the reversionary AHC switch (on the reversionary panel) and refer to the "Single Attitude Heading Computer (AHC) Failure" Procedure. d. IAS (Indicated Air Speed) Red Flag A red, boxed "IAS" flag, which flashes for five seconds and then becomes steady, will replace the airspeed pointer when airspeed data from the selected ADC is missing or invalid or when VMO/MMO values are missing or invalid. The airspeed digital readout, airspeed scale, overspeed marker, and low speed cue markers are removed from the display. Select the cross-side ADC (ADC1 or ADC2) with the reversionary ADC switch (on the reversionary panel) and refer to the "Single Air Data Computer (ADC) Failure" Procedure. e. MACH Red Flag When the Mach data is failed or missing a red decimal point and three red dashes flash for 5 seconds and then become steady. NOTE The Mach flag shows, only when in flight at speed higher than M=0.45, in the same location as the Acceleration flag and the two are mutually exclusive. When the Mach is displayed a gray scaled “M” legend shows in front of the readout at all times. Select the cross-side ADC (ADC1 or ADC2) with the reversionary ADC switch (on the reversionary panel) and refer to the "Single Air Data Computer (ADC) Failure" Procedure. Rep. 180-MAN-0010-01100 Page 3-112 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES f. VS (Vertical Speed) Red Flag The VS flag shows when vertical speed data from the selected ADC is missing or invalid. The VS flag flashes for five seconds then becomes steady. The vertical speed scale and pointer, and the vertical speed digital readout are removed from the display. Select the cross-side ADC (ADC1 or ADC2) with the reversionary ADC switch (on the reversionary panel) and refer to the "Single Air Data Computer (ADC) Failure" Procedure. g. HDG (Heading) Red Flag The red boxed “HDG” flashes for five seconds and then become steady when heading data from the selected AHC are missing or invalid. The Compass Rose or Partial Arc (depending on the selected format) rotates to a north-up display and the lubber line index for the heading is removed. Select the cross-side AHC (AHC1 or AHC2) with the reversionary AHC switch (on the reversionary panel) and refer to the "Single Attitude Heading Computer (AHC) Failure" Procedure. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-113 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES FLAG ASSOCIATED WITH ILS a. GS (Glideslope) Red Flag The red boxed “GS” annunciation indicates that the glideslope data is invalid and the glideslope pointer is removed. Check that correct localizer frequency is tuned Select the cross-side NAV receiver as NAV source (if LOC1 shows GS flag, select LOC2 tuned to the same localizer). b. LOC (Localizer) Red Flag The red boxed “LOC” annunciation indicates that the lateral deviation data is invalid. The lateral deviation scale and pointer are removed. if the data is valid on the other PFD, the approach should be flown by selecting the operable NAV source. FLAG ASSOCIATED WITH RADIO NAVIGATION SYSTEM a. LOC#, VOR#, FMS1 (Active NAV Source) Red Flag When the navigation source input fails, the navigation source is annunciated in red in a red box. The possible annunciations are LOC1, VOR1, LOC2, VOR2, FMS1. The following displays are removed: lateral deviation bar, lateral deviation scale, and to/from indication. If navigation source data are valid on the other PFD, select the operable NAV source. NOTE If course pointer and lateral deviation bar are removed without the red VOR# flag showing, check the VOR operational condition by selecting another available station. NOTE If course pointer and lateral deviation bar are removed without the red FMS1 flag showing, check if flight plan has been enabled. Rep. 180-MAN-0010-01100 Page 3-114 Appr. DOA EASA.21J.685 Issued: October 21, 2005 1105-2999 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES COMPARATOR FLAGS ON PRIMARY FLIGHT DISPLAY Comparator flags are displayed on the PFD to alert the pilot that redundant data from dual system is not agreeing within limits. HDG (HEADING) COMPARATOR FLAG The HDG comparator flag shows when independent heading data from two attitude/heading computers differs by more than 6°. 1. Establish airplane in straight and level, unaccelerated flight 2. Determine if pilot’s or copilot’s heading display is in error 3. AHC switch (on REVERSIONARY panel) - SELECT operative AHC ATT, PIT, ROL (ATTITUDE, PITCH, ROLL) COMPARATOR FLAGS The ATT or ROL or PIT comparator warn flag show when independent attitude data from the attitude heading computers differs by more than 4°, or by more than 3° in glideslope capture mode. 1. Establish airplane in straight and level, unaccelerated flight 2. Compare indications with the Integrated Stand-by Instrument 3. Determine if pilot’s or copilot’s attitude display is in error 4. AHC switch (on REVERSIONARY panel) - SELECT operative AHC ALT (ALTITUDE) COMPARATOR FLAG The ALT comparator flag shows when the independent altitude data from the two Air Data Computers differs more than the limit. 1. Establish airplane in straight and level, unaccelerated flight 2. Compare indications with the Integrated Stand-by Instrument 3. Determine if pilot’s or copilot’s altitude is in error 4. ADC switch (on REVERSIONARY panel) - SELECT operative ADC Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-115 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES IAS (INDICATED AIRSPEED) COMPARATOR FLAG The IAS comparator flag shows when independent airspeed data from two air data computers differs by more than 10 knots. 1. Establish airplane in straight and level, unaccelerated flight 2. Compare indications with the Electronic Stand-by Instrument System 3. Determine if pilot’s or copilot’s airspeed is in error 4. ADC switch (on REVERSIONARY panel) - SELECT operative ADC NOTE Following take off and climb in heavy rain conditions, if an increasing difference between pilot and copilot IAS is noted, and the IAS displayed on the co-pilot PFD (latched to the right ADC) is the same as on the Stand-By instrument, water/ice contamination may have been occurred. Evaluate descending to lower flight levels in order to melt possible ice accretion in the pitot pipes. Once a pitot line is clogged, the ADC connected to that line always receives the same value of dynamic pressure, i.e., the pressure that is trapped between the “ice cap” and the ADC. Following this, airspeed can only change following a change to the static pressure, increasing as the altitude increases and viceversa. To identify which ADC is sensing the actual dynamic pressure, increasing actual airspeed while keeping same flight level, will cause IAS to increase only on the ADS not fed by the clogged line and, on the contrary, will show a constant IAS on the ADS fed by the clogged line. A further check can be performed: since the right pitot feeds both the StBy Instrument and the RH ADC (provided the Copilot PFD is connected to the RH ADS, as per normal configuration), an ice-cap on the RH pitot line will cause an unreliable IAS both on the copilot PFD and on the StdBy instrument. Viceversa, if – following an IAS miscompare warning – the LH ADC and the StBy system are providing the same IAS, different from that provided by the RH ADC, a different failure may be assumed (e.g., a RH ADC internal failure). NOTE If the IAS displayed on the Stand-By instrument is the same displayed on the pilot PFD (latched to the left ADC), but is different from the IAS displayed on the copilot PFD (latched to the right ADC), the IAS miscompare is probably not related to water/ice contamination. Rep. 180-MAN-0010-01100 Page 3-116 Appr. DOA EASA.21J.685 Issued: October 21, 2005 1105-2999 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES LOC (LOCALIZER) COMPARATOR FLAG The LOC comparator flag shows when the localizer is the selected NAV source, and independent course/lateral deviation data from the two NAV receivers differs by more than the allowable system limits. NOTE The LOC comparator flag only shows for CAT II monitored approaches. 1. Determine correct NAV source and select as necessary 2. If unable to determine the correct source, proceed visually if able or execute a missed approach GS (GLIDESLOPE) COMPARATOR FLAG The GS comparator flag shows when the localizer is the selected navigation source, and independent glideslope deviation data from the two NAV receivers differs by more than the allowable system limits. NOTE The GS comparator flag is enabled during CAT II monitored approaches. 1. Determine correct NAV source and select as necessary 2. If unable to determine the correct source, proceed visually if able and either descend to localizer only minimums or execute a missed approach 3.3.9 CATEGORY II OPERATIONS EMERGENCIES Refer to simplified procedure, Paragraph 3.2.9. 3.3.10 REDUCED VERTICAL SEPARATION MINIMA (RVSM) OPERATIONS EMERGENCIES Refer to simplified procedures, Paragraph 3.2.10. 3.3.11 P-RNAV OPERATION EMERGENCIES Refer to simplified procedures, Paragraph 3.2.11. 3.3.12 U.S. RNAV OPERATION EMERGENCIES Refer to simplified procedures, Paragraph 3.2.12. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 3-117 P.180 AVANTI II AIRPLANE FLIGHT MANUAL EMERGENCY PROCEDURES AMPLIFIED EMERGENCY PROCEDURES INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page 3-118 Appr. DOA EASA.21J.685 Issued: October 21, 2005 1105-2999 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES TABLE OF CONTENTS SECTION 4 - NORMAL PROCEDURES TABLE OF CONTENTS Paragraph No. Page No. 4.0 4.1 4.2 4.2.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-1 Airspeeds for Normal Operations . . . . . . . . . . . . . . . . . . . . . . . . . . .4-2 Normal Procedures Checklist . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-4 Preflight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-4 Cockpit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-5 Forward Wing and Nose Section . . . . . . . . . . . . . . . . . . . . . . . . . . .4-6 Fuselage (Right Side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-7 Right Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-8 Rear Fuselage (Right Side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-9 Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-9 Rear Fuselage (Left Side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-10 Left Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-10 Fuselage (Left Side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-11 Further Checks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-12 4.2.2 Before Engine Starting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-13 4.2.3 Engine Starting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-15 Normal Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-15 Engine Dry Run (Motoring). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-17 Cross-start Procedure (One Engine Operating) . . . . . . . . . . . . . . .4-17 GPU Start Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-19 4.2.4 Before Taxi. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-20 4.2.5 Taxiing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-24 4.2.6 Engine Run Up. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-25 4.2.7 Before Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-27 4.2.8 Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-28 4.2.9 Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-29 4.2.10 Cruise. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-30 4.2.11 Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-30 4.2.12 Approach (for non-precision or ILS CAT I Approaches) . . . . . . . . . . .4-30 4.2.13 Before Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-31 4.2.14 Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-32 4.2.15 Go Around . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-33 4.2.16 Balked Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-33 4.2.17 After Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-34 4.2.18 Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-35 4.2.19 After Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-36 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Rep. 180-MAN-0010-01100 1105-2999 Page 4-i P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES TABLE OF CONTENTS 4.2.20 Category II Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-37 Airspeeds for Category II Operations . . . . . . . . . . . . . . . . . . . . . . 4-37 Before Taxi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-37 Approach and Landing Preparation . . . . . . . . . . . . . . . . . . . . . . . 4-37 4.2.21 Operation in Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-41 4.3 Amplified Normal Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-43 4.3.1 Preflight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-43 Cockpit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-44 Forward Wing and Nose Section . . . . . . . . . . . . . . . . . . . . . . . . . 4-47 Fuselage (Right side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-48 Right Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-50 Rear Fuselage (Right Side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-51 Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-52 Rear Fuselage (Left Side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-52 Left Wing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-52 Fuselage (Left Side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-53 Further Checks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-53 4.3.2 Before Engine Starting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-55 4.3.3 Engine Starting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-57 Normal Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-57 Engine Dry Run (Motoring) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-59 Cross Start Procedure (One Engine Operating) . . . . . . . . . . . . . . 4-59 GPU Start Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-61 4.3.4 Before Taxi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-62 4.3.5 Taxiing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-74 4.3.6 Engine Run Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-75 4.3.7 Before Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-76 4.3.8 Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-77 4.3.9 Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-79 4.3.10 Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-80 4.3.11 Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-81 4.3.12 Approach (for non-precision or ILS CAT I approaches) . . . . . . . . . . . 4-82 4.3.13 Before Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-85 4.3.14 Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-86 4.3.15 Go Around . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-87 4.3.16 Balked Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-87 4.3.17 After Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-88 4.3.18 Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-89 4.3.19 After Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-90 4.3.20 Category II Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-91 Approach and Landing preparation . . . . . . . . . . . . . . . . . . . . . . . 4-91 Rep. 180-MAN-0010-01100 Page 4-ii Issued: October 21, 2005 1105-2999 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES TABLE OF CONTENTS 4.3.21 Operation in Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-93 4.3.22 Cold Weather Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-96 Preflight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-96 Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-97 After Shutdown. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-98 4.3.23 VSSE - Intentional One Engine Operative Speed . . . . . . . . . . . . . . . . .4-98 4.3.24 VMCA - Air Minimum Control Speed . . . . . . . . . . . . . . . . . . . . . . . . . . .4-99 4.3.25 Stall Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-100 4.3.26 Rough Air Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-101 4.3.27 Oxygen System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-102 4.3.28 External Noise Reduction Procedures . . . . . . . . . . . . . . . . . . . . . . . .4-107 Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-107 Before Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-107 Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-108 4.3.29 Reduced Vertical Separation Minima (RVSM) Operations . . . . . . . .4-109 Preparation for Flight in RVSM airspace . . . . . . . . . . . . . . . . . . .4-109 4.3.30 Steep Approach Operations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-110 Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-110 4.3.31 Operation on Contaminated Runways . . . . . . . . . . . . . . . . . . . . . . . .4-113 Taxiing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-113 Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-114 Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-114 4.3.32 P-RNAV Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-116 4.3.33 U.S. RNAV Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-116 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Rep. 180-MAN-0010-01100 1105-2999 Page 4-iii P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES TABLE OF CONTENTS INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page 4-iv Issued: October 21, 2005 1105-2999 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES GENERAL SECTION 4 - NORMAL PROCEDURES 4.0 GENERAL This section describes the recommended procedures for the conduct of normal operations for P.180 Avanti II airplanes. Normal procedures associated with those optional systems and equipment which require AFM supplements are presented in the relevant Supplement. These procedures are provided as a source of reference and review and to supply information on procedures which are not the same for all airplanes. Pilots should familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane. The first portion of this section is a short form checklist which supplies an action sequence for normal procedures with little emphasis on the operation of the systems. The second portion of the section is devoted to amplified normal procedures which provide detailed information and explanations of the procedures and how to perform them. This portion of the section is not intended for use as an in-flight reference due to the lengthy explanations. The short form checklist should be used for expeditious reference or response. In addition, a discussion of normal systems operation, stall characteristics, VMC demonstration, intentional single engine operations, cold weather operation and external noise reduction procedures, is presented in the amplified procedures. NOTE In the following procedures, "TAT heater inhibition on-ground" change is to be considered installed if: - for Avanti II/EVO airplanes with Magnaghi L/G installed: DMT 80-1283 or SB 80-0430 has been embodied, - for Avanti II/EVO airplanes with Dowty L/G installed: DMT 80-1312 or SB 80-0457 has been embodied. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-1 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AIRSPEEDS FOR NORMAL OPERATIONS 4.1 AIRSPEEDS FOR NORMAL OPERATIONS The following airspeeds are those which are significant to the operation of the airplane. These figures are for standard airplanes flown at maximum take off weight (or otherwise specified) under normal condition at sea level. For additional airspeed information see Section 2. SPEED KIAS a. Two engines Recommended Climb Speed up to 30000 ft. Reduce speed 1 KIAS for each 1000 ft. above 30000 ft. 160 b. Two engines Best Angle of Climb Speed 133 c. Two engines Best Rate of Climb Speed 154 d. Two engines Approach Speed at Maximum Landing Weight For different weights refer to Section 5 Figure 5-73 (flap MID) and Figure 5-69 (flap DN) Flap MID Flap DN 129 121 e. Balked Landing Climb Speed Flap MID Flap DN 130 115 f. 25 Maximum Demonstrated Crosswind Velocity g. Maximum Operating Mach Number .70 h. Maximum Operating Speed (See VMO/MMO chart in Section 2) 260 i. Design Maneuvering Speed At 11550 lb At 7700 lb 199 177 j. Maximum Flap Operating Speed UP to MID MID to DN 170 150 k. Maximum Flap Extended Speed Flap MID Flap DN 180 175 l. 180 Maximum Landing Gear Operating Speed Rep. 180-MAN-0010-01100 Page 4-2 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AIRSPEEDS FOR NORMAL OPERATIONS SPEED KIAS m. Maximum Landing Gear Extended Speed 185 n. Maximum Landing Light Operating Speed 160 o. Maximum Landing Light Extended Speed 160 p. Rough Air Penetration Speed at or below 25000 ft. Reduce speed 5 KIAS for each 5000 ft above 25000 ft. 195 Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-3 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2 NORMAL PROCEDURES CHECKLIST 4.2.1 PREFLIGHT CHECK Figure 4-1. Walk-around NOTE Ensure the battery clamp has been reconnected to the battery, if previously disconnected for prolonged airplane ground parking. NOTE During ground operation with a Ground Power Unit (GPU) only (both generators OFF) keep AVIONICS master switch OFF during the Cooling Air Conditioner start phase. Rep. 180-MAN-0010-01100 Page 4-4 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST COCKPIT 1. Airplane records - CHECK 2. Parking brake - SET LOCKED 3. Control locks - REMOVE 4. Flight controls - CHECK FREE 5. Electrical switches - OFF 6. Circuit breakers left and right panel - IN 7. Gear handle - DN 8. Battery switch - BAT 9. MFD System Page - CHECK 10. Bus voltage - CHECK CAUTION If bus voltage is less than 21.5 VDC, the battery must be serviced or replaced before flight. If bus voltage is between 21.5 and 23.0 VDC, allow 15 minutes of ground power unit battery recharging. 11. CAB DOOR warning light - CHECK ON (with door open) 12. Engine exceedance - TEST 13. Battery temperature - TEST AND CHECK CONSISTENCY 14. Annunciator panel - TEST 15. Engine fire detector - TEST 16. Fuel quantity system - TEST AND CHECK QUANTITY 17. Gear lights - CHECK THREE GREEN AND TEST 18. Fuel crossfeed valve - CHECK OFF 19. Trim surfaces - NEUTRAL 20. Battery switch - OFF 21. Oxygen pressure - CHECK 22. Oxygen masks - CHECK 23. Windshield and lateral windows - CHECK FOR CLEANLINESS Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-5 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST FORWARD WING AND NOSE SECTION 1. Windshield left side - CHECK CONDITION AND CLEANLINESS 2. Flap - CHECK 3. Static wicks - IN PLACE, CONDITION 4. Surface - CHECK CONDITION AND CLEANLINESS 5. Nose gear - CHECK 6. 6a. (If S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed): Steering connecting pin - CHECK properly installed 6b. (If S.B. 80-0454 or 80-0425 (new NWSS) - are installed): Nose Landing gear torque link- CHECK connected 7. Tires - CONDITION AND SLIPPAGE 8. Tires - CONDITION AND SLIPPAGE 9. Gear doors - CHECK 10. Chock - REMOVE 11. Antenna - CHECK 12. TAT probe - CHECK 13. LH pitot tube - CHECK 14. Landing lights door - CHECK CLOSED 15. Nose radome - CHECK 16. Surface - CHECK CONDITION AND CLEANLINESS 17. RH pitot tube - CHECK 18. Flap - CHECK 19. Static wicks - IN PLACE, CONDITION 20. Ice detector - CHECK 21. Antennas - CHECK 22. Windshield right side - CHECK CONDITION AND CLEANLINESS Rep. 180-MAN-0010-01100 Page 4-6 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST FUSELAGE (RIGHT SIDE) 1. General condition - CHECK 2. Emergency exit - CHECK LOCKED 3. Antennas - CHECK 4. Static ports - CLEAR 5. Stall warning cone - CHECK 6. Windows - CHECK 7. Landing gear - CHECK 8. Tire - CONDITION AND SLIPPAGE 9. Brake lining wear indicators - CHECK FOR MINIMUM 10. Ventral strobe light - CHECK 11. Antennas - CHECK 12. Chock - REMOVE 13. Gear doors - CHECK 14. Fuel vent - CLEAR 15. Fuel tank sump - DRAIN 16. Fuel vent system - DRAIN (before first flight of the day) 17. Battery vent - CLEAR 18. Ground test/refueling panel - TEST NOTE If any annunciator light is already illuminated before the test or remains illuminated after the test consider for applicable maintenance action before flight. CAUTION A real chip detection condition occurs, in the related engine oil, if the L ENG OIL or R ENG OIL annunciator light is flashing (3 Hz rate, 40% on and 60% off) while the GROUND TEST switch is held in the SYST position. Have an immediate maintenance check as per the applicable Engine Manual. 19. Ground test/refueling panel door - CLOSE 20. Single point refueling port cap - CHECK INSTALLED AND SECURED 21. Single point refueling panel door - CLOSE Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-7 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST RIGHT WING 1. Surface - CHECK CONDITION AND CLEANLINESS 2. Generator cooling intake - CHECK 3. Air intake and de-ice boot - CHECK 4. Oil cooler intake - CHECK 5. Nacelle - CHECK CONDITION 6. Ice bypass vane - CHECK 7. Engine oil vent - CLEAR 8. Engine fuel pump drain - CHECK FOR LEAKAGE 9. Starter generator pad drain - CHECK FOR LEAKAGE 10. Stall strip - CHECK 11. Position light - CHECK 12. Static wicks - IN PLACE, CONDITION 13. Aileron - CHECK 14. Aileron trim tab - CHECK 15. Outboard flap and flap track fairings - CHECK 16. Nacelle cowling - CHECK 17. Fire extinguisher pressure gauge - CHECK (if installed) 18. Air conditioning precooler intake - CHECK 19. Propeller bearing vent - CHECK 20. Combustion chamber drain - CHECK FOR LEAKAGE 21. Engine exhaust ducts - CHECK 22. Propeller blades and spinner - CHECK CONDITION AND FREE MOVEMENT 23. Inboard flap - CHECK Rep. 180-MAN-0010-01100 Page 4-8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST REAR FUSELAGE (RIGHT SIDE) 1. General condition - CHECK 2. Gravity fuel filler cap - CHECK CLOSED 3. Air conditioning intake - CLEAR 4. Air conditioning outlet - CLEAR 5. Cooling system condenser air-intake - FREE FROM OBSTRUCTION 6. Cooling system condenser air-outlet - FREE FROM OBSTRUCTION 7. Ventral fin - CHECK 8. Tail cone - CHECK CONDITION EMPENNAGE 1. Surface - CHECK CONDITION 2. VHF/NAV antennas - CHECK 3. Rudder - CHECK 4. Rudder trim tab - CHECK 5. Static wick - IN PLACE, CONDITION 6. Elevator - CHECK 7. Stabilizer position - CHECK 8. Static wicks - IN PLACE, CONDITION 9. Antennas - CHECK 10. Recognition and strobe lights - CHECK Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-9 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST REAR FUSELAGE (LEFT SIDE) 1. General condition - CHECK 2. Ventral fin - CHECK 3. Tail cone - CHECK CONDITION 4. Main junction box (baggage comp.) - CHECK circuit breakers IN 5. Baggage - SECURED with the restrain net 6. Baggage door - LOCK LEFT WING 1. Inboard flap - CHECK 2. Air conditioning precooler intake - CHECK 3. Propeller bearing vent - CHECK FOR LEAKAGE 4. Combustion chamber drain - CHECK 5. Engine exhaust ducts - CHECK 6. Propeller blades and spinner - CONDITION AND FREE MOVEMENT 7. Fire extinguisher pressure gauge - CHECK (if installed) 8. Nacelle cowling - CHECK 9. Engine oil vent - CLEAR 10. Engine fuel pump drain - CHECK FOR LEAKAGE 11. Starter generator pad drain - CHECK FOR LEAKAGE 12. Outboard flap and flap track fairings - CHECK 13. Aileron - CHECK 14. Static wicks - IN PLACE, CONDITION 15. Position lights - CHECK 16. Surface - CHECK CONDITION AND CLEANLINESS 17. Stall strip - CHECK 18. Oil cooler air intake - CHECK 19. Wing ice inspection light - CHECK Rep. 180-MAN-0010-01100 Page 4-10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 20. Air intake and de-ice boot - CHECK 21. Nacelle - CHECK 22. Generator cooling air intake - CHECK 23. Ice bypass vane - CHECK FUSELAGE (LEFT SIDE) 1. Landing gear - CHECK 2. Tire - CONDITION AND SLIPPAGE 3. Brake linings wear indicators - CHECK FOR MINIMUM 4. Chock - REMOVE 5. Fuel vent - CLEAR 6. Fuel vent system - DRAIN (before first flight of the day) 7. Fuel tank sump - DRAIN 8. Battery vent - CLEAR 9. Ground power unit (GPU) receptacle door - LOCKED 10. Gear doors - CHECK 11. General condition - CHECK 12. Windows - CHECK 13. Static ports - CLEAR 14. Oxygen safety discharge indicator - CHECK GREEN 15. Entrance door - CHECK Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-11 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST FURTHER CHECKS Before first flight of the day: 1. EPU switch - ARM 2. Gear lights - CHECK THREE GREEN 3. EPU switch - OFF 4. Condition levers - CUT OFF 5. Battery switch - BAT 6. L/R fuel firewall shutoff valves - TEST, THEN CHECK OPEN NOTE Depending on airplane configuration, the INTRAN warning light may temporarily illuminate during SOV test 7. Crossfeed - TEST, THEN CHECK OFF NOTE The XFEED INTRAN warning light should momentarily illuminate during Crossfeed test WARNING Takeoff is not authorized if during the tests of fuel firewall valves and crossfeed valve the corresponding INTRAN lights remain illuminated. 8. L/R fuel pump switches - MAIN 9. L/R fuel filters - DRAIN 10. L/R fuel pump switches - OFF 11. External lights - CHECK (Prior to night flight) 12. Battery switch - OFF Rep. 180-MAN-0010-01100 Page 4-12 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.2 1. BEFORE ENGINE STARTING Entrance door - SECURE handles and check indicators WARNING Assurance that the door is locked is by correct alignment of all visual indicator marks. 2. Emergency exit handle - PROPERLY POSITIONED 3. Handle lock pin - REMOVED 4. Crew/passenger briefing - COMPLETE 5. Belt - SECURE 6. Seats - ADJUST 7. Rudder pedals - ADJUST 8. Switches - CHECK OFF CAUTION Failure to select AVIONICS master switch to the OFF or COM1 ONLY position during the engine start up or shutdown may result in equipment failure. 9. Static Pressure Selector Valve - CHECK STATIC TUBE and secured with the spring-clip retainer 10. Engine control lever friction - ADJUST 11. Emergency gear selector - PROPERLY POSITIONED 12. Battery switch - BAT 13. Volt - CHECK NOTE If bus voltage is between 23.0 - 23.5 VDC, it is recommended to connect a ground power unit before attempting engine start. 14. Battery temperature - CHECK CAUTION No battery engine starting must be attempted if battery temperature is over 120°F (BAT TEMP caution light ON). Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-13 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 15. Fuel quantity - CHECK 16. Parking brake - CHECK LOCKED 17. Seat belts and no smoking signs - ON 18. Avionics master switch - COM1 ONLY if engine start up clearance is required NOTE If engine start up clearance requires prolonged period of time, battery charge can be saved switching the MASTER switch from NORMAL to BUS DISC. Select NORMAL just before engine start. Rep. 180-MAN-0010-01100 Page 4-14 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.3 ENGINE STARTING WARNING During ground operation with engine at low NG, depending on ambient temperature and/or altitude, check ITT and advance condition lever to maintain ITT under 750°C. NORMAL START First engine start may be made using either the aircraft battery or the ground power unit (GPU). A GPU start is made with the battery switch set to BAT. When the GPU is connected, the green EXT POWER indication on the MFD comes ON. CAUTION Whenever the gas generator fails to light up within 10 sec. after moving the condition lever, shut fuel off by retarding the condition lever and setting the starter switch to OFF. Allow a 30 sec. fuel draining period followed by a 15 sec. dry motoring run before attempting another start. If, for any reason, a starting attempt is discontinued, allow the engine to come to a complete stop and then accomplish a dry motoring run. 1. Anti Coln light - GND 2. Power lever - IDLE 3. Condition lever - CUT OFF 4. Firewall shut off valve - CHECK OPEN 5. Fuel pump - TEST AND CHECK MAIN 6. Fuel pressure light - CHECK OFF 7. Bleed air switches - CHECK OFF 8. Ignition switch - CHECK NORM 9. Propeller - CLEAR 10. Engine start switch - START 11. Condition lever - (at 13% NG) GROUND IDLE 12. ITT - MONITOR (1000°C Max. 5 sec.) 13. Oil pressure - CHECK INCREASING Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-15 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 14. NG RPM - CHECK INCREASING 15. Engine start switch - CHECK OFF (at about 40% NG) NOTE At first starting of the day a starting cycle time exceeding 30 seconds may be observed on some engines. In this event, an alternate ground starting procedure is suggested, rearranging the above steps from 10 to 15 as follows: – Engine start switch - START – Condition lever - (at 13% NG) FLIGHT IDLE – ITT - MONITOR (1000°C Max. 5 sec.) – Oil pressure - CHECK INCREASING – NG RPM - CHECK INCREASING – Engine start switch - CHECK OFF (at about 40% NG) – Condition lever - (at 50% NG) GROUND IDLE With engine at ground idle setting check the following conditions: a. ITT - 750°C Max. b. Oil pressure - 60 psi Min. c. Oil temperature - 110°C Max. d. NG RPM - 54% Min. e. NP RPM - 900 RPM Min. 16. Condition lever - ADVANCE TO FLIGHT IDLE 17. GPU (unless needed for second engine start) - DISCONNECT 18. Generator (if GPU is not used or disconnected) - ON 19. Generator Load - CHECK 20. Hydraulic pump switch - HYD (Pressure - CHECK; light OFF) Rep. 180-MAN-0010-01100 Page 4-16 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST ENGINE DRY RUN (MOTORING) 1. Power lever - IDLE 2. Condition lever - CUT OFF 3. Ignition breaker (IGN SYS) - OUT 4. Fuel pump - OFF 5. Engine start switch - START 6. Engine start switch (after 15 sec.) - OFF Second engine start may be made using either the GPU or the cross-start procedure. CROSS-START PROCEDURE (ONE ENGINE OPERATING) CAUTION Whenever the gas generator fails to light up within 10 sec. after moving the condition lever, shut fuel off by retarding the condition lever and setting the starter switch to OFF. Allow a 30 sec. fuel draining period followed by a 15 sec. dry motoring run before attempting another start. If, for any reason, a starting attempt is discontinued, allow the engine to come to a complete stop and then accomplish a dry motoring run. 1. Condition lever (operative engine) - FLIGHT IDLE 2. Generator (operative engine) - CHECK ON 3. Generator Load - CHECK below 160 Amp (below 140 Amp after a first engine prolonged starting) 4. Firewall shutoff valves - CHECK OPEN 5. Power lever (inoperative engine) - IDLE 6. Condition lever (inoperative engine) - CUT OFF 7. Fuel pumps - MAIN 8. Fuel pressure light - CHECK OFF 9. Bleed air - OFF 10. Ignition switch - CHECK NORM 11. Propeller - CLEAR Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-17 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 12. Engine start switch - START 13. Condition lever (inoperative engine) - (at 13% NG) GROUND IDLE 14. ITT - MONITOR (1000°C Max. 5 sec) 15. Oil pressure - CHECK INCREASING 16. NG RPM - CHECK INCREASING 17. Engine start switch - CHECK OFF (at about 40% NG) NOTE At first starting of the day a starting cycle time exceeding 30 seconds may be observed on some engines. In this event, an alternate ground starting procedure is suggested, rearranging the above steps from 12 to 17 as follows: – Engine start switch - START – Condition lever - (at 13% NG) FLIGHT IDLE – ITT - MONITOR (1000°C Max. 5 sec.) – Oil pressure - CHECK INCREASING – NG RPM - CHECK INCREASING – Engine start switch - CHECK OFF (at about 40% NG) – Condition lever - (at 50% NG) GROUND IDLE With engine at ground idle setting check the following conditions: a. ITT - 750°C Max. b. Oil pressure - 60 psi Min. c. Oil temperature - 110°C Max. d. NG RPM - 54% Min. e. NP RPM - 900 RPM Min. 18. Condition lever - BOTH GROUND IDLE 19. Generator - ON 20. Generator Load - CHECK CAUTION Avoid GROUND IDLE setting with electrical load above 200 A. Rep. 180-MAN-0010-01100 Page 4-18 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST GPU START PROCEDURE A GPU start is made with battery switch set to BAT. Use first engine start procedure. After both engines have been started: 1. GPU - DISCONNECT 2. EXT POWER green indication on MFD - CHECK OFF 3. Generators - ON Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-19 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.4 BEFORE TAXI 1. EPU - TEST 2. EPU switch - ARM 3. Avionics switch - ON 4. Environmental temperature - AUTO AND TEMP SELECT AS NECESSARY 5. Cockpit blower - AS REQUIRED NOTE Depending on ambient temperature, combined operation of both the Heating and Cooling Systems up to 20,000 ft. may be required. 6. Cooling system main control switch - ON (if desired) 7. FAN CKPT and FAN CABIN switches - AS REQUIRED NOTE When on ground, during hot day operation, it may be necessary to increase NG up to 58% maximum in order to maintain the ITT within limits or temporarily to switch the bleed air OFF (in this case no outside air is circulating in the cabin). 8. Bleed air switches - SET to L and R positions 9. Pressurization Auto/Man switch - AUTO and CHECK SELF TEST NOTE The FAULT indication light on the control panel should momentarily illuminate (3 seconds maximum) during self test. If FAULT indication light fails to extinguish or re-illuminate, set AUTO/MAN switch to MAN and then back to AUTO to repeat self test. CAUTION No flight should be initiated in the automatic mode if the FAULT light fails to extinguish. 10. Auto Sched/Cab sel switch - AUTO SCHED 11. Landing altitude - SET Rep. 180-MAN-0010-01100 Page 4-20 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 12. Barometric correction - SET 13. Rate selection - SET (PIP mark) 14. Engine oil coolers - AS REQUIRED 15. Integrated Stand-by Instrument - CHECK INITIALIZATION COMPLETED then SET brightness 16. ADC1 and ADC2 - CHECK 17. AHC1 and AHC2 - CHECK 18. Avionics fan - TEST 19. Radio altimeter - TEST 20. Overspeed warning - TEST 21. Hydraulic system - TEST 22. Steering system - TEST 23. Steering - TAXI 24. Pitot/stall/static heat - CHECK NOTE If operations in heavy rain or snow or icing conditions are envisaged: 24 a. Pitot HTR L&STALL - ON 24 b. [If TAT heater inhibition on-ground (ref. para 4.0) is installed ]: Pitot HTR R & TAT - ON CAUTION If TAT heater inhibition on-ground (ref. para 4.0) is NOT installed: Pitot HTR R&TAT must be kept OFF 25. Stall warning - TEST 26. Flap system - TEST WARNING No takeoff authorized with non symmetrical flap configuration or annunciated failure. 27. Flaps - MID 28. Trim systems - TEST and set for take-off Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-21 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST CAUTION Failure to set the correct trim for take-off may result in high rotation forces, delayed rotation and a substantial increase in take-off distance. 29. Ice detector - TEST 30. WSHLD heat - CHECK 31. Engine ice vane and oil cooler intake - CHECK 32. Engine inlet de-ice boots - CHECK WARNING Do not operate engine inlet de-ice boots below –40°C. No takeoff authorized with frost, snow or ice adhering to propellers, windshields, powerplant installation and pitot/static ports, or with snow or ice adhering to the wings, vertical and horizontal stabilizer or control surfaces. NOTE Perform Main and Fwd wing anti ice tests if ice conditions are known or expected. 33. Anti ice Main wing - TEST 34. Anti ice Fwd wing - TEST 35. PFD/MFD display reversion - CHECK WARNING Takeoff not authorized if reversionary function fails operating. 36. ADC1/ADC2 reversion - CHECK 37. AHC1/AHC2 reversion - CHECK 38. RTU/CDU reversion - CHECK 39. Autopilot - TEST a. Battery switch - CHECK BAT b. Circuit Breakers - CHECK IN c. PFD - CHECK Attitude and Heading flags out of view d. Autopilot Engage Button - PUSH and check ON YD and AP lights e. Autopilot Disengagement Checks - ACCOMPLISH Verify that each of the following actions will disengage the autopilot: Rep. 180-MAN-0010-01100 Page 4-22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 1. Depressing control wheels MSW buttons (yaw damper also disengages) 2. Activating Manual Electric Trim 3. Depressing AP Button on the Flight Guidance Panel 4. Trim Selector in the OFF or SEC position. 5. Operating the AP/YD DISC lever on the Flight Guidance Panel f. Heading Mode Checks - ACCOMPLISH (Before the first flight of the day) 1. Engage Heading Mode 2. Position heading marker 10° left of lubber line 3. Verify that the command bars indicate a left turn and that the control wheel turns to the left. 4. Repeat check to the right. g. Autotrim Checks - ACCOMPLISH (Before the first flight of the day) 1. Apply back pressure to the control wheel. 2. Verify that the elevator trim indicator moves nose down after approximately 2 seconds. 3. Repeat check with forward pressure, and check that the trim indicator moves nose up. h. Approach Mode Checks - ACCOMPLISH (Before the first flight of the day) 1. Tune the No. 1 VOR receiver to an active VOR frequency. 2. Center the lateral deviation bar. 3. Engage Approach Mode. 4. Verify that the command bars turn in the direction of the course and the control wheel turns to satisfy the command. i. Aircraft Flight Controls - CHECK free and correct j. Elevator Trim - SET for takeoff CAUTION Failure to set the correct trim for take-off may result in high rotation forces, delayed rotation and a substantial increase in take-off distance. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-23 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 40. FMS - SET and CHECK 41. Radios/NAV - SET and CHECK 42. Radar - TEST-ST.BY 43. Display System (PFD and MFD) - CHECK 44. Annunciator panel - TEST and CHECK CAB DOOR warning light flashing 45. BAG DOOR AND CAB DOOR warning lights - CHECK OFF 46. Steering system - TAXI NOTE With airplane configuration CG Fwd and S.B. 80-0454 or 800425 (new NWSS) installed, avoid to steer with pedals up to end-of-travel position when airplane is stopped. NOTE During Taxi maneuvers, for airplane heading changes greater than 90°, it is recommended to not exceed a speed of 10 KTS. 47. Parking brake - RELEASE 4.2.5 TAXIING 1. Brakes - CHECK (avoid excessive use) 2. Steering system - OFF on a level runway 3. Airplane - CHECK no tendency to yaw left or right 4. Steering system - TAXI NOTE With airplane configuration CG Fwd and S.B. 80-0454 or 800425 (new NWSS) installed, avoid to steer with pedals up to end-of-travel position when airplane is stopped. NOTE During Taxi maneuvers, for airplane heading changes greater than 90°, it is recommended to not exceed a speed of 10 KTS. 5. Prop reverse - CHECK 6. Prop feathering - CHECK 7. Flight instruments - CHECK Rep. 180-MAN-0010-01100 Page 4-24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.6 ENGINE RUN UP 1. Parking brake - SET LOCKED 2. Condition levers - MAX RPM 3. Power levers - Advance to 2000 RPM 4. Propeller overspeed - TEST 5. Propeller governing - CHECK to minimum RPM 6. Autofeather system - TEST WARNING No takeoff authorized with autofeather inoperative. 7. Autofeather switch - ARM 8. Parking brake - RELEASE Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-25 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page 4-26 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.7 BEFORE TAKEOFF 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. Circuit breakers - CHECK IN Anti coln lights - AIR Windshield heat - AS REQUIRED Seat belts and no smoking signs - ON Flight instruments - SET and CHECK Weather Radar - CHECK Engine indications - CHECK Warning and caution lights - CHECK OFF Transponder - SET Bleed air switches - CHECK to L and R positions NOTE When operating from high altitude airports with high SAT, it may be necessary to switch off both bleed air to reduce engine ITT. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. Fuel pumps - CHECK MAIN Condition levers - CHECK MAX RPM Autopilot and Yaw Damper - DISENGAGE Flaps - CHECK MID Longitudinal trim - CHECK TAKEOFF SET Aileron trim - CHECK NEUTRAL Rudder trim - CHECK NEUTRAL Flight controls - CHECK FREE Steering - TAKEOFF Oil cool - OFF Taxi/landing lights - AS REQUIRED Navigation lights - AS REQUIRED Ice protection systems - AS REQUIRED Pitot/Static HTR L&STALL and R&TAT - ON NOTE If "TAT heater inhibition on-ground" change (ref. para 4.0) is NOT installed, it is recommended to set R&TAT ON before line up and takeoff. When TAT heater is selected a total air temperature increase may be detected on ground until the system is stabilized after airborne. Thereafter TAT indication is valid. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-27 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST CAUTION If "TAT heater inhibition on-ground" change (ref. para 4.0) is NOT installed, switching "ON" RH pitot and TAT heater on ground for a long time, it may cause temporary unavailability of the Flight Director 25. L/R PITOT HTR caution lights - CHECK OFF 4.2.8 1. TAKEOFF Power levers - ADVANCE to MAXIMUM TAKE-OFF power WARNING Before applying full power, be sure that the condition levers are set to MAX RPM: takeoff distance given in Sec. 5 may not be assured. 2. Autofeather - CHECK ARMED (green AFX indication, on MFD, ON) WARNING If ambient temperature is below –25°C, it is necessary to operate the main wing anti-ice and the engine ice vane systems before applying full power to ensure that the autofeather is armed. When takeoff is completed and autofeather disengaged, the ice protection can be switched OFF. 3. Engine indications - WITHIN LIMITS 4. (Only if S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed): Steering (not over 60 KIAS) - OFF 5. Rotation - REFER to Section 5 of this Manual Figure 5-16 6. (Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed): Steering - CHECK that automatically disengages (no mode indication on PFD) 7. Airspeed - Accelerate to 120 KIAS until above 50 ft. 8. Taxi/landing lights (below 160 KIAS) - OFF 9. Gear (below 180 KIAS) - UP 10. Autofeather (above 150 KIAS) - OFF 11. Flaps (below 170 KIAS) - UP 12. Flight Director - SELECT desired modes Rep. 180-MAN-0010-01100 Page 4-28 .A Appr. DOA EASA.21J.685 Issued: October 21, 2005 1105-2999 PT6A-66 eng. Rev. B0: Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.7 BEFORE TAKEOFF 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. Circuit breakers - CHECK IN Anti coln lights - AIR Windshield heat - AS REQUIRED Seat belts and no smoking signs - ON Flight instruments - SET and CHECK Weather Radar - CHECK Engine indications - CHECK Warning and caution lights - CHECK OFF Transponder - SET Bleed air switches - CHECK to L and R positions NOTE When operating from high altitude airports with high SAT, it may be necessary to switch off both bleed air to reduce engine ITT. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. Fuel pumps - CHECK MAIN Condition levers - CHECK MAX RPM Autopilot and Yaw Damper - DISENGAGE Flaps - CHECK MID Longitudinal trim - CHECK TAKEOFF SET Aileron trim - CHECK NEUTRAL Rudder trim - CHECK NEUTRAL Flight controls - CHECK FREE Steering - TAKEOFF Oil cool - OFF Taxi/landing lights - AS REQUIRED Navigation lights - AS REQUIRED Ice protection systems - AS REQUIRED Pitot/Static HTR L&STALL and R&TAT - ON NOTE If "TAT heater inhibition on-ground" change (ref. para 4.0) is NOT installed, it is recommended to set R&TAT ON before line up and takeoff. When TAT heater is selected a total air temperature increase may be detected on ground until the system is stabilized after airborne. Thereafter TAT indication is valid. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-27 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST CAUTION If "TAT heater inhibition on-ground" change (ref. para 4.0) is NOT installed, switching "ON" RH pitot and TAT heater on ground for a long time, it may cause temporary unavailability of the Flight Director 25. L/R PITOT HTR caution lights - CHECK OFF 4.2.8 1. TAKEOFF Power levers - ADVANCE to MAXIMUM TAKE-OFF power WARNING Before applying full power, be sure that the condition levers are set to MAX RPM: takeoff distance given in Sec. 5 may not be assured. 2. Autofeather - CHECK ARMED (green AFX indication, on MFD, ON) WARNING If ambient temperature is below –25°C, it is necessary to operate the main wing anti-ice and the engine ice vane systems before applying full power to ensure that the autofeather is armed. When takeoff is completed and autofeather disengaged, the ice protection can be switched OFF. 3. Engine indications - WITHIN LIMITS 4. (Only if S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed): Steering (not over 60 KIAS) - OFF 5. Rotation - REFER to Section 5 of this Manual Figure 5-16 6. (Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed): Steering - CHECK that automatically disengages (no mode indication on PFD) 7. Airspeed - Accelerate to 122 KIAS until above 50 ft. 8. Taxi/landing lights (below 160 KIAS) - OFF 9. Gear (below 180 KIAS) - UP 10. Autofeather (above 150 KIAS) - OFF 11. Flaps (below 170 KIAS) - UP 12. Flight Director - SELECT desired modes Rep. 180-MAN-0010-01100 Page 4-28 .B Appr. DOA EASA.21J.685 Issued: October 21, 2005 1105-2999 PT6A-66B eng. Rev. B0: Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 13. Autopilot and Yaw Damper - ENGAGE above 400 feet AGL if desired CAUTION A continuous annunciated amber elevator mistrim indication will anticipate that the airplane could be significantly out of trim. In this case the pilot should brace the flight controls and disconnect the autopilot. Upon disconnection the pilot will experience a force of between 7 kg (15 lbs) and 9 kg (20 lbs). Re-engagement of the autopilot should not be attempted until the reason for the out of trim state has been isolated and rectified, and the airplane has been returned to a trimmed condition. A temporary annunciated amber elevator mistrim indication during an acceleration/deceleration phase and/or configuration changes could be disregarded if it lasts not more than about 10 seconds. 4.2.9 CLIMB 1. Climb power - SET 2. Airspeed - REFER to Section 5 of this Manual NOTE If operations in heavy rain conditions are performed: 2a. MONITOR PILOT and COPILOT AIRSPEED 3. Seat belts and no smoking signs - AS REQUIRED 4. SYNCPH switch - SYNCPH NOTE Whenever the synchrophaser system is to be engaged, at the maximum propeller RPM, the condition levers must be retarded to a position corresponding to about 1980 RPM in order to maintain 2000 RPM. 5. Pressurization - CHECK 6. Cooling system main control switch - ON (if desired) NOTE During flight, when the Cooling System is used the Heating System should also be ON in order to guarantee adequate pressurization and ventilation. 7. Windshield heat - LO or HI as necessary Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-29 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 8. Autopilot and Yaw Damper - ENGAGE if desired 4.2.10 CRUISE 1. Cruise power - SET 2. Airspeed - REFER to Section 5 of this Manual NOTE If operations in heavy rain conditions are performed: 2a. MONITOR PILOT and COPILOT AIRSPEED 3. Engine indications - CHECK 4. Pressurization - CHECK 5. Environmental control system - CHECK 6. Above 1000 feet AGL - ENGAGE autopilot if desired. 7. Modes - SELECT as desired. 4.2.11 DESCENT 1. Windshield heat - AS REQUIRED 2. Pressurization - CHECK 3. Environmental control system - CHECK 4. Above 1000 feet AGL - ENGAGE autopilot if desired. 5. Modes - SELECT as desired. 4.2.12 APPROACH (FOR NON-PRECISION OR ILS CAT I APPROACHES) 1. Approach modes - COUPLED if desired 2. For non-precision approach: – 250 feet AGL - DISENGAGE autopilot For ILS CAT I approach: – 200 feet AGL - DISENGAGE autopilot NOTE VOR approaches must be conducted in APPR mode. Rep. 180-MAN-0010-01100 Page 4-30 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.13 BEFORE LANDING 1. Seat belts and no smoking signs - ON 2. SYNCPH switch - OFF 3. Condition levers - MAX RPM 4. Gear (below 180 KIAS) - DN; CHECK 3 GREEN 5. (Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed): Steering - CHECK armed (T/O message on PFD) 6. Flaps (below 170 KIAS) - MID 7. Autofeather (below 150 KIAS) - ARM, CHECK amber AUTOFEATHER light OFF 8. Landing lights (below 160 KIAS) - AS REQUIRED 9. Flaps on final (below 150 KIAS) - DN CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. 10. Autopilot-Yaw Damper-Steering - OFF 11. (Only S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed): Steering OFF 12. Cabin pressure barometric condition - CHECK Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-31 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.14 LANDING Prior to reaching 50 ft. above landing surface: 1. Landing gear - CHECK DN (3 green lights) 2. Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) Steering CHECK armed (T/O message on PFD) 3. Flaps - CHECK DN CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. Steering engagement during landing is prohibited. 4. Approach speed - REFER to Section 5 of this Manual Figure 5-69. 5. Power - AS REQUIRED 6. Condition levers - CHECK MAX RPM After touchdown: 7. Brakes - AS REQUIRED 8. Reverse - AS REQUIRED; engage reverse below 1900 prop RPM or 5% drop from the set value NOTE When landing at aft C.G. initiate flaps retraction before actuating reverse power. 9. Reverse - DO NOT USE below 40 KIAS At landing completed: 10. Condition levers - GROUND IDLE 11. Steering - ENGAGE TAKE OFF (if necessary) NOTE If “TAT heater inhibition on-ground” change (ref. para 4.0) is NOT installed, a total air temperature increase may be detected until the TAT heater is turned off. Rep. 180-MAN-0010-01100 Page 4-32 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.15 GO AROUND 1. GA button - PUSH. If autopilot engaged GA will be coupled 2. Power Levers - Apply balked landing climb power as per Figure 5-67 on page 5-82 at Section 5 of this AFM 4.2.16 BALKED LANDING 1. Power levers - MAX POWER 2. Engine indications - WITHIN LIMITS 3. Airspeed - 115 KIAS 4. Flaps (below 150 KIAS) - MID CAUTION When operating in icing conditions, the balked landing procedure must be performed with flaps MID and the airspeed must be 130 KIAS. 5. Gear (after climb established) - UP 6. Landing Lights (below 160 KIAS) - OFF 7. Flaps (below 170 KIAS) - UP 8. Airspeed - 160 KIAS Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-33 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.17 AFTER LANDING 1. Power levers - IDLE 2. Steering - TAXI (if necessary) NOTE With airplane configuration CG Fwd and S.B. 80-0454 or 800425 (new NWSS) installed, avoid to steer with pedals up to end-of-travel position when airplane is stopped NOTE During Taxi maneuvers, for airplane heading changes greater than 90°, it is recommended to not exceed a speed of 10 KTS. 3. Flaps - UP 4. Ice protection equipment heat - OFF (if applicable) NOTE Following operations in heavy rain or snow or icing conditions, if water ingestion in the pitot probes may have occurred: 4a. Pitot HTR L & STALL and R & TAT - keep ON 5. Radar - OFF 6. Transponder - STBY 7. Anticollision lights - GROUND 8. Taxi/landing lights - AS REQUIRED 9. Autofeather - OFF 10. Cabin altitude / p - CHECK Landing Field / Zero NOTE In the event of landing with severe brake use an adequate brakes cooling time is required before a successive takeoff. Rep. 180-MAN-0010-01100 Page 4-34 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.18 1. SHUTDOWN Parking brake - SET NOTE If brakes are very hot, do not set parking brake. 2. Avionics switch - OFF 3. CAUTION Failure to select AVIONICS master switch to the OFF position during the engine shutdown may result in equipment failure. Pitot HTR L & STALL and R & TAT - OFF 4. EPU switch - OFF 5. Bleed air - OFF 6. Power lever - CHECK IDLE 7. Condition lever - CHECK GROUND IDLE NOTE Allow the engine to stabilize for a minimum of two minutes at minimum obtainable ITT. 8. Hydraulic pump - OFF 9. Condition lever - CUT OFF WARNING If there is any evidence of fire within the engine after shutdown, proceed immediately as described under "Engine Dry Run (Motoring)" Procedure. 10. Fuel pump switches - OFF NOTE If OAT > 30°C perform 30 sec. motoring as per “ENGINE DRY RUN” Procedure. 11. All electrical switches - OFF 12. Battery switch - OFF NOTE During the shutdown ensure that the compressor decelerates freely. CAUTION The passenger door may be opened 10 seconds after the passenger upper door handle has been rotated to OPEN position. 13. Passenger door - OPEN Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-35 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.19 1. AFTER SHUTDOWN Engine oil level - CHECK (after the last flight of the day) NOTE Perform the engine oil level check within 30 minutes after engine shutdown. Ideal interval is 15 to 20 minutes. 2. Control locks - INSTALL 3. Emergency exit handle lock pin - INSTALL 4. Wheels chocks - PLACE CAUTION If Pitot probes, Static ports and TAT/AOA sensors have been heated, be sure that such equipment have cooled down before installing covers. 5. Covers - INSTALL 6. Propeller restrainers - ATTACH 7. Tie-down ropes - AS REQUIRED NOTE If the airplane is supposed to be parked for more than 2 days unplug the battery clamp from the battery in the baggage compartment. NOTE Propellers blades cleaning is recommended after the last flight of the day. CAUTION Following suspected water contamination, have both pitot lines cleaned and drained at the earliest opportunity. Rep. 180-MAN-0010-01100 Page 4-36 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.20 CATEGORY II OPERATIONS AIRSPEEDS FOR CATEGORY II OPERATIONS Two engines Approach Speed for CAT II operations (VREF): SPEED KIAS a. FLAP MID At 10945 lbs (4965 kg) weight At 10270 lbs (4658 kg) weight or below 129 125 b. FLAP DN At 10945 lbs (4965 kg) weight At 10270 lbs (4658 kg) weight or below 125 121 BEFORE TAXI 1. Radio Altimeter - TEST and CHECK for proper operation APPROACH AND LANDING PREPARATION AFTER TRANSITION ALTITUDE: 1. Altimeters - CHECK IF MORE THAN 20 NM FROM THE ILS STATION: 1. Autopilot - DISENGAGE (if engaged) 2. Radio Altimeter - TEST and SET DH 3. Autopilot - ENGAGE 4. FD Command Bars - IN VIEW on both sides 5. Mode selection - HDG 6. Speed - MAINTAIN 7. ILS frequency - SELECT (LOC1 on PFD1 and LOC2 on PFD2) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-37 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 8. Selected course - SET and CHECK (PFD1 equal to PFD2) 9. Intercept heading and distance - WITHIN 60 degrees IF 20 NM OR LESS FROM THE STATION: 1. Mode selection - APPR 2. Condition levers - 2000 RPM NOTE Any erroneous autopilot lateral mode selection other than APPR will not switch ON or will switch OFF CAT II approach monitoring green light and will not activate the "loss of approach" warning tone. 3. CAT II Indication - CHECK green light ON PRIOR TO GLIDE SLOPE CAPTURE: NOTE Glide Slope must be captured above 1500 ft. 1. Autopilot engaged - APPR 2. Landing Gear - DWN 3. (Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed): Steering - CHECK armed (T/O message on PFD) 4. Flap setting - MID 5. CAT II Indication - CHECK green light ON WHEN BETWEEN 1 AND 1.5 DOT BELOW GLIDE SLOPE: 1. Flap Setting - DN (MID if in icing conditions) 2. VREF - SET and HOLD AT 1000 FEET: 1. Approach speed - STABILIZED Rep. 180-MAN-0010-01100 Page 4-38 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 2. Localizer and Glide Slope - CENTERED 3. Altimeters and Radio Altimeters - CROSS CHECKED FROM 300 FEET AND BELOW: 1. Approach airspeed - MAINTAIN STABILIZED 2. Cockpit procedures to include instrument monitoring - PERFORM 3. Call out of any deficiency (see below) and Radio Altimeter read-outs as follows: 300 - 200 - 150 - DH - 50 - 30 AT DH (DECISION HEIGHT CERTIFIED FOR CAT II): Decision - LAND or GO AROUND a. If Land is decided: 1. Autopilot at not less than 100 feet - DISENGAGED NOTE Lateral realignment maneuvers are prohibited below 50 feet regardless of existing conditions. b. If Go Around is decided (execute GO AROUND procedure below): 1. GA Push Button - DEPRESS 2. Power setting - FULL POWER 3. Autopilot - VERIFY GA green indications ON 4. Aircraft - MONITOR ATTITUDE AND BANK 5. Two-engines go around speed - MAINTAIN (120 KIAS minimum) CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID. In this condition the go around speed is 130 KIAS. 6. Airplane Configuration - AS REQUIRED Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-39 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST CAT II DEFICIENCIES The following are excessive deviations from normal and must be called out: – Airspeed 5 kts above or below the approach speed – Angle of bank above 15 degrees – Pitch Attitude below -2 or above +8 degrees – Rate of Descent in excess of 1000 ft/min – Excessive Deviation in Localizer and Glideslope – Any CAT II Instrument System flag in view – FD Command Bars out of view. Rep. 180-MAN-0010-01100 Page 4-40 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST 4.2.21 OPERATION IN ICING CONDITIONS 1. ENG ICE VANE and OIL COOLER INTK switches - SET to L and R positions 2. BOOTS DE ICE switch - AUTO NOTE The surface ice protection systems must be activated approximately 30 seconds after the actuation of engine ice protection systems to avoid a quick increase of engine ITT. 3. L and R MAIN WING switches - AUTO 4. FWD WING switches - SET to L and R position 5. WSHLD HEAT PRI and SEC switches - CHECK LO 6. NP RPM - MAINTAIN 2000 RPM. 7. Ice protection systems advisory indications - CHECK occasionally Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-41 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES NORMAL PROCEDURES CHECKLIST INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page 4-42 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3 AMPLIFIED NORMAL PROCEDURES The following paragraphs are provided to supply detailed information and explanation of the normal procedures necessary for the operation of the aircraft. 4.3.1 PREFLIGHT CHECK The airplane should be given a thorough preflight and walk-around check. To expedite certain checks, a person in the cockpit may operate certain controls and switches, which are observed by a ground observer. The preflight should include a determination of airplane’s operational status, a check that necessary papers are on board and in order, and a computation of weight and center of gravity limits, take-off and landing distances and inflight performance. Baggage should be weighed, stowed and tied down. NOTE Ensure the battery clamp has been reconnected to the battery, if previously disconnected for prolonged airplane ground parking (more than two days). NOTE During ground operation with a Ground Power Unit (GPU) only (both generators OFF) keep AVIONICS master switch OFF during the Cooling Air Conditioner start phase. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-43 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES COCKPIT Check that necessary papers are on board and in order. After entering the cockpit, remove the control locks, if installed, and check flight controls for proper movement. Set the parking brake, pressing on the pedals while pulling out and rotating in vertical position the PARKING BRAKE handle. Check that all electrical switches are OFF; circuit breakers should be IN. Ensure that the gear selector handle is in the DN position. Turn the battery switch to BAT and check the MFD is on. Select the System Page on the MFD and check the bus voltage. CAUTION If bus voltage is less than 21.5 VDC, the battery must be serviced or replaced before flight. If bus voltage is between 21.5 and 23.0 VDC, allow 15 minutes of ground power unit battery recharging. With the door open check that the CAB DOOR warning light is illuminated. The preflight tests of certain system essential to safe operation of the airplane should be performed selecting the proper function on the SYS TEST panel and momentarily pressing the button located in the center of the rotary selector switch, as described in the following. Set the rotary switch of the SYS TEST panel to ENG EXCEED, press and hold the central pushbutton: this activates the aural warning associated to the engine torque or ITT warning threshold exceedance. The battery temperature test is performed selecting ANN on the SYS TEST panel and pressing the pushbutton located in the center of the selector knob. This activates the illumination of the amber BAT TEMP, the red BAT OVHT and the red L and R OIL TEMP lights on the annunciator panel. The battery temperature is displayed on the MFD System Page; check the battery temperature value consistency in comparison with the outside air temperature. Set the rotary switch of the SYS TEST panel to LAMP, press and hold the central button: this activates the annunciator panel and the MASTER WARNING/ MASTER CAUTION lamps test and the cabin door annunciator circuitry. On the annunciator panel all the lights should illuminate steady while L and R FIRE and CAB DOOR should flash; on the instrument panel the red MASTER WARNING should flash and the amber MASTER CAUTION should light up steady. Rep. 180-MAN-0010-01100 Page 4-44 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Releasing the button on the rotary switch all the annunciator panel lights will return in the original condition, while MASTER WARNING/MASTER CAUTION will be reset pressing on the light itself. Set the rotary switch of the SYS TEST panel to the FIRE DET position and press the test button: the two red lights on the annunciator panel, labeled L FIRE/ R FIRE should start to blink, together with the L and R ENG FIRE EXT lighted pushbuttons, if the optional fire extinguisher system is installed. Perform the fuel quantity system test selecting on the SYS TEST panel the FUEL QTY position and pressing the central button. On the annunciator panel the L and R LOW FUEL amber light should be illuminated up to the end of the test. Check the fuel quantity on the MFD. The three green landing gear lights should be illuminated. The three red lights GEAR UNSAFE can be checked setting the switch, on SYS TEST panel, to LDG GR position and pressing the test button: this will light up the UNSAFE lamps and activate the gear warning horn. NOTE Setting the AVIONICS master switch to the COM1 ONLY or ON position is required for the actuation of the warning horn. Verify fuel CROSSFEED valve knob OFF. Set the trim surfaces to neutral. Turn the battery switch OFF after these checks. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-45 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Check the oxygen pressure gauge on the left side of the cockpit to ascertain that there is sufficient oxygen for the intended flight. Full service is 12.76 MPa (1850 PSI) at 21°C (70° F). Check the minimum oxygen quantity as reported at Paragraph 4.3.27 according to the number of occupants. The pilot/passenger oxygen system control should be in the AUTO-NORMAL position. Check for oxygen flow to the pilot and copilot oxygen masks by placing masks on face and breathing. Assure, by the flow indicators, that all oxygen flow has ceased. Be sure that there is a functional oxygen mask for each occupant and that all masks are properly stowed. Verify if the windshield and lateral windows are clean. Rep. 180-MAN-0010-01100 Page 4-46 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES A complete walk-around check should be continually performed during each preflight. A set pattern should be established as in Figure 4-1, starting at the cabin door and proceeding forward, completely around the airplane, and terminating upon return to the cabin door. FORWARD WING AND NOSE SECTION Check the condition and cleanliness of the windshield, then proceed along the trailing edge of the left forward wing trailing edge. Visual check the wing, flap and hinges for damage. Static wicks should be firmly attached and in good condition. Surface should be free of ice, snow, frost, debris or other extraneous substances: particular attention must be paid on the cleanliness of the top and bottom wing surface in order to achieve an extended laminar flow. The nose landing gear should be examined. The condition of the components of the strut, the gear doors, the gear micro switches etc. should appear sound, and fittings, attachments, hoses, lines, screws, hinges etc., should be secure. There should be no sign of hydraulic fluid leakage in the area of strut or in the wheel well. Examine the tires for cuts, bruises, cracks and excessive wear. If S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed: check if steering connecting pin is properly installed. If S.B. 80-0454 or 80-0425 (new NWSS) are installed: check if NLG Torque Link is connected. Check if steering connecting pin is properly installed. If the wheel chocks have been employed, they should be removed before taxing. Check the antennas for condition. Check the TAT probe for condition. If the pitot tubes covers have been installed, they must be removed and the pitot head openings checked and ensured they are clear of any obstruction. If the pitots and static ports heat operation is to be checked, the battery switch must be turned to BAT and the corresponding switches, on the ANTI ICE panel to ON: use caution since pitots and static ports can become very hot. Check the radome for damage. The landing light door should be closed. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-47 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES FUSELAGE (RIGHT SIDE) Check the general condition of the right side of the fuselage. The emergency exit window should be secure and flush with the fuselage skin. All side windows should be clean and without defects. Check the conditions of DME and transponder antennas. The openings in the static port should be clean and unobstructed. The stall warning transducer should be checked for security and freedom of movement. The landing gear should be examined with care. Refer to placard for correct servicing instruction and tire pressure. The condition of the components of the strut, the gear doors, the brakes, the gear micro-switches etc., should appear sound, and fittings, attachments, hoses, lines, screws, hinges etc. should be secure. There should be no sign of hydraulic fluid leakage in the wheel well, nor in the area of strut and brake. Check the brake lining wear indicator: they must protrude from their housing. The tire should be examined for cuts, bruises, cracks and excessive wear. Remove wheel chock, if employed. Check gear doors and actuating mechanism for excessive play. Check the integrity of the ventral strobe light and antennas. Fuel vent, located on the bottom-side of the fuselage should be clear of obstruction. Before the first flight of the day, drain the fuel vent system operating the drain valve through the hole located on the side of the fuselage close to the gear doors: the outlet is located inside the wheel well. Battery vent outlet should be clear. Drain the fuel tank sump, operating the relative valve located in the wheel well: it is recommended, as a general rule, that at each fuel drain, fuel be collected and examined in a clear container so that it can be visually checked for water and sediment: use the draining tool P/N 80-909172-801 or equivalent. Rep. 180-MAN-0010-01100 Page 4-48 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Open the ground test/refueling panel door and perform the hydraulic and engine oil system test. NOTE If any annunciator light is already illuminated before the test or remains illuminated after the test consider for applicable maintenance action before flight. Turn and hold the momentary GROUND TEST switch to the LAMP position checking the following: – all the four red and the two amber annunciator lights will come on: failed lights should be replaced and re-tested before flight; – the L and R ENG OIL annunciator lights should flash with a rate of 3 Hz (40% on and 60% off) showing the proper operation of the panel chip detection monitoring circuitry: a simulated chip detection condition is generated allowing the warning system test. Turn and hold the momentary GROUND TEST switch to the SYST position checking the following: L and R ENG OIL, HYD FILTER and, after a few seconds, HYD LEVEL red lights should illuminate and then extinguish releasing the switch. CAUTION A real chip detection condition occurs, in the related engine oil, if the L ENG OIL or R ENG OIL annunciator light is flashing (3 Hz rate, 40% on and 60% off) while the GROUND TEST switch is held in the SYST position. Have an immediate maintenance check as per the applicable Engine Manual. NOTE The "Low Engine Oil Level Condition" is automatically displayed by the steady illumination of the related L or R ENG OIL light, a "Chip Detection Condition", if any, is displayed by the flashing of the related L or R ENG OIL light only after moving and holding the GROUND TEST switch to the SYST position. After the test, close the panel door. Pilot must check that the single point refueling port cap is installed and properly secured, then close the single point refueling access door. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-49 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES RIGHT WING Check the general condition of the right wing and make the same checks and procedures as performed on the forward wing. At the nacelle, check the condition of the surface. If the protective caps were installed in the air inlet and in the exhausts openings, they should be removed. Inlet and exhaust openings should be checked for obstruction. Check the condition of inlet pneumatic deicer boots: it should be free from defects and flat against the inlet cowling. Oil cooler, generator and precooler air inlet should be free of obstructions. Check the ice bypass vane for correct alignment and clear of obstruction. Oil vent, engine fuel pump drain and starter generator pad drain should be clear of obstruction. Stall strip on the leading edge and position lights at the tip of the wing should be intact. Check the aileron gap seal for integrity. The right aileron includes a trim tab which must be checked for neutral position, proper movement, excessive free play and security. Tab neutral position corresponds, when the aileron is aligned with the wing, to a downward setting of approximately 3/8" (10 mm.). Static wicks should be firmly attached and in good condition. Check outboard and inboard flaps for correct alignment and free play: check also the flap track fairings. Check the pressure of the fire extinguisher bottle: nominal value at 21°C (70°F) ambient temperature is 360 ± 25 psig (2.48 ± 0.17 MPa): for other temperature refer to the following graph: Rep. 180-MAN-0010-01100 Page 4-50 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES FIRE EXTINGUISHER BOTTLE PRESSURE Vs. AMBIENT TEMPERATURE Check the rear cowling of the nacelle for integrity and the air conditioning precooler intake for obstruction. Propeller bearing vent should be checked for obstruction and combustion chamber drain for leakage. Exhaust-stubs should be secure. The propeller blades and spinner should be free of cracks, nicks, dents and other defect and should spin freely. There should be no indication of leakage of fluid in the area of hub or on the engine nacelle. REAR FUSELAGE (RIGHT SIDE) Check the general condition of the fuselage surface. Verify if the air conditioning air intakes and outlets are free from obstructions. Check on top of the fuselage if the gravity fuel filler cap is properly closed. Verify the condition of tail cone and ventral fin. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-51 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES EMPENNAGE All surfaces of the empennage should be examined for damage, cleanliness and operational interference. Check rudder and rudder trim tab for proper movement and excessive free play. Tab neutral position corresponds, when the rudder is aligned with the fin, to a deflection to the right of approximately 3/8" (10 mm). Stabilizer position, when longitudinal trim indicator is 0° (neutral), is approximately horizontal and the reference line, marked on stabilizer is aligned with 0° reference mark on vertical fin. Verify the condition of recognition and strobe light, antennas and static wicks. REAR FUSELAGE (LEFT SIDE) Check the general condition of the fuselage surface. Verify the condition of tail cone and ventral fin. Check IN the circuit breakers of the main junction box located inside the baggage compartment. Ascertain the baggage is properly secured with the prescribed restrain net. Lock the baggage door. Verify if the ground power unit (GPU) receptacle is locked. LEFT WING Repeat the same checks and procedures as already performed on right wing in the reverse order. Check the ice inspection light on the nacelle for integrity. Rep. 180-MAN-0010-01100 Page 4-52 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES FUSELAGE (LEFT SIDE) Repeat the same checks and procedures followed during the inspection of the right side of the forward fuselage. Check that the battery vent is clear of obstruction. Check that the entrance door attachments are secure and hinges operational. Check the oxygen overpressure safety discharge disk indicator. This green disk, when missing or ruptured, indicates bottle pressure has exceeded about 2800 psi and is empty. This overpressure system will actuate only under the most adverse circumstances: therefore determine the cause of the overpressure, and replenish oxygen before flight. FURTHER CHECKS Before the first flight of the day it is required to verify the automatic exchange of COM1 and LDG gear position lights power supply, between the Essential Bus and the Emergency Power Bus, and that the fuel filters are drained, while the fuel firewall shutoff valves and the crossfeed valve are checked for proper operation. Set the EPU switch to the ARM position, verify that the three green landing gear lights illuminate and then switch OFF the EPU. Ensure that the condition levers are set to CUT OFF. Set the battery switch to the BAT position. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-53 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES The fuel firewall shutoff valves are tested moving the corresponding switch (L or R FW VALVE) from CLOSE to OPEN position. The transit amber lights (L and R F/W V INTRAN) depending on airplane configuration, may temporarily illuminate, while the position amber lights (L and R F/W V CLSD) shall turn off. After the test has been performed check the fuel firewall shutoff valves are set to OPEN position. The crossfeed system is tested turning the crossfeed knob either left or right. Depending on the airplane configuration, the transit amber light (XFEED INTRAN) should momentarily illuminate and the position amber light (FUEL XFEED) should be on. Set the knob to OFF position: again, depending on the airplane configuration, the transit light (XFEED INTRAN) should illuminate momentarily, while the position light (FUEL XFEED) should be off. WARNING Take off is not authorized if during the tests of fuel firewall valves and crossfeed valve the corresponding INTRAN lights remain illuminated. The fuel filters are located at the bottom of each nacelle, close to the ice vane bypass opening. Draining operation requires that the battery and both fuel pumps are switched on: for this reason the draining is accomplished at this step of the preflight check, in order to save the battery power and to leave the airplane unguarded, with electrical power ON, for a minimum time. Before finishing the ground check, and if a night flight is anticipated, ensure that all exterior lights are operational: for this check the battery switch should be positioned to BAT and the various systems tested one at a time. After completed the above checks switch OFF the battery. Check the ground in the area of the airplane for evidence of fuel, oil, or operating fluid leakage. Rep. 180-MAN-0010-01100 Page 4-54 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.2 BEFORE ENGINE STARTING After the preflight interior and exterior checks have been completed and the airplane is determined ready for flight, the entrance door should be secured and all occupants seated. When all occupants are boarded, the pilot should check that the cabin door is properly closed and latched. The lower door support cables should be held in position, if necessary, so that they will not interfere with the closing of the door. Insert the locking pin in the lower door handle and ensure the correct alignment of the two overcentre indicators, observing through the inspection windows. Close the upper passenger door rotating the handle anticlockwise then clockwise to the STOW position and secure the handle with the spring loaded guard. Ensure the correct alignment of the two overcentre indicators and of the pin position indicator, observing through the inspection windows. WARNING Assure that the door is locked is by correct alignment of all visual indicator marks. Ensure that the emergency exit handle is in the correct position and that the red flagged emergency exit handle lock pin is removed. Passengers should be briefed on the use of seat belts, the emergency exit, supplementary oxygen, ventilation control, seat adjustment, comfort facilities, etc. Secure belts, adjust seats and rudder pedals. All the switches should be OFF. CAUTION Failure to select AVIONICS master switch to the OFF or COM1 ONLY position during the engine start up or shutdown may result in equipment failure. Ensure that the Static Pressure Selector Valve handle, of the alternate static air source, is held in the normal (STATIC TUBE) position by the spring-clip retainer. Adjust the engine control lever friction. Emergency gear selector should be checked if properly positioned. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-55 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Switch the battery to BAT and check the voltage, which should not be less than 23.5 VDC. To accomplish this check it is necessary to select the System Page on the MFD. NOTE If bus voltage is between 23.0 and 23.5 VDC, it is recommended to connect a ground power unit before attempting engine start. Check the battery temperature on the MFD. CAUTION No battery engine starting must be attempted if battery temperature is over 120°F (BAT TEMP caution light ON). Check the fuel quantity. Before starting the engines check the parking brake is locked and turn the seat belts and no smoking signs ON. If engine start up clearance is required set the avionics master switch to the COM1 ONLY position. NOTE If engine start up clearance requires prolonged period of time, battery charge can be saved switching the MASTER switch from NORMAL to BUS DISC. Select NORMAL just before engine start. Rep. 180-MAN-0010-01100 Page 4-56 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.3 ENGINE STARTING NORMAL START WARNING During ground operation with engine at low NG, depending on ambient temperature and/or altitude, check ITT and advance condition lever to maintain ITT under 750°C. First engine start may be made using either the aircraft battery or the ground power unit (GPU). GPU start is made with the battery switch set to BAT. When the GPU is connected, the green EXT POWER indication on the MFD comes ON. CAUTION Whenever the gas generator fails to light up within 10 sec. after moving the condition lever, shut fuel off by retarding the condition lever and setting the starter switch to OFF. Allow a 30 sec. fuel draining period followed by a 15 sec. dry motoring run before attempting another start. If, for any reason, a starting attempt is discontinued, allow the engine to come to a complete stop and then accomplish a dry motoring run. Set the anticollision light to GND. Power lever should be set to IDLE and condition lever to CUT OFF. The fuel firewall shutoff valves should be OPEN. Fuel pumps should be checked for proper operation. Set left pump switch to STBY position: amber L FUEL PRESS light should be off and amber L FUEL PUMP light should be on: set the switch to MAIN position, both lights should be off. Repeat the same procedure for the right pump. Turn the fuel pump switch to MAIN and check off the fuel pressure amber light. Bleed air switches should be OFF. Ignition switch should be in NORM position. Verify if the propeller is clear and set the engine start switch to START. When engine speed reaches 13% NG advance the condition lever to GROUND IDLE. Engine temperature ITT must not exceed a maximum of 1000°C for more than 5 seconds. Observe NG and oil pressure rise; at about 40% NG, the engine start switch will automatically disengage. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-57 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES NOTE At first starting of the day a starting cycle time exceeding 30 seconds may be observed on some engines. In this event, an alternate ground starting procedure is suggested, rearranging the above steps as follows. Set the start switch to START; when engine speed reaches 13% NG advance the condition lever to FLIGHT IDLE. Engine temperature ITT must not exceed a maximum of 1000°C for more than 5 seconds; observe NG and oil pressure rise; at about 40% NG, the engine start switch will automatically disengage. Retard the condition lever to GROUND IDLE. With the engine at ground idle setting, the following indications should be read on the MFD (engine indication section): a. engine temperature (ITT) 750°C maximum, b. oil pressure minimum 60 psi, c. oil temperature 110°C maximum, d. engine speed 54% NG minimum, e. propeller speed 900 RPM minimum. Advance the condition lever to FLIGHT IDLE. Disconnect the GPU unless needed for second engine start. If GPU has not been used or is disconnected turn ON the generator: the corresponding amber light on the annunciator panel will extinguish. Check for a positive generator load reading (L/R GEN AMPS) and a voltage level reading (BUS VOLTS) of 27.5 to 28 volts: these checks are accomplished selecting the System Page on the Multifunction Display (MFD). Turn the hydraulic pump switch to HYD and observe a reading of about 1000 PSI; check off the amber HYD PRESS light on the annunciator panel. Rep. 180-MAN-0010-01100 Page 4-58 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES ENGINE DRY RUN (MOTORING) To perform an engine dry run, set the power lever to IDLE and condition lever to CUT OFF; pull out the ignition breaker (IGN SYS). Fuel pump switch should be set to OFF. Turn the start switch to START and after 15 seconds to OFF. Observe the starter operating limits set forth in Paragraph 2.4 of this AFM. CROSS START PROCEDURE (ONE ENGINE OPERATING) Second engine start may be made using either the GPU or the cross start procedure. CAUTION Whenever the gas generator fails to light up within 10 sec. after moving the condition lever, shut fuel off by retarding the condition lever and setting the starter switch to OFF. Allow a 30 sec. fuel draining period followed by a 15 sec. dry motoring run before attempting another start. If, for any reason, a starting attempt is discontinued, allow the engine to come to a complete stop and then accomplish a dry motoring run. The condition lever of the operating engine should be set at FLIGHT IDLE. Check ON the generator of the operating engine. Before starting the second engine, allow one or two minutes for battery recharging: observe on the MFD System Page a Generator Load reading of less than 160 Amp. In the event of a first engine prolonged (more than 40 seconds) starting a longer battery recharging time should be allowed waiting for a Generator Load reading of less than 140 Amp. before the second engine start. The fuel firewall valves should be OPEN. The power lever of the inoperative engine should be at IDLE and the condition lever at CUT OFF. Set the fuel pump switch of the inoperative engine to MAIN and check OFF the fuel pressure light. The bleed air switch should be OFF. Ignition switch should be in NORM position. Verify if the propeller is clear. Turn the engine start switch to START and when the engine speed reaches 13% NG advance condition lever to GROUND IDLE. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-59 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Engine temperature ITT must not exceed a maximum of 1000°C for more than 5 seconds. Observe NG and oil pressure rise; at about 40% NG start switch will automatically disengage. NOTE At first starting of the day a starting cycle time exceeding 30 seconds may be observed on some engines. In this event, an alternate ground starting procedure is suggested, rearranging the above steps as follows. Set the start switch to START; when engine speed reaches 13% NG advance the condition lever to FLIGHT IDLE. Engine temperature ITT must not exceed a maximum of 1000°C for more than 5 seconds; observe NG and oil pressure rise; at about 40% NG, the engine start switch will automatically disengage. Retard the condition lever to GROUND IDLE. With the engine at ground idle setting, the engine indications on the MFD should be as in the normal start. Set both engine condition levers to GROUND IDLE. CAUTION Avoid GROUND IDLE setting with electrical load above 200 Amp. Rep. 180-MAN-0010-01100 Page 4-60 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES GPU START PROCEDURE A GPU start is made with the battery switch set to BAT. NOTE The ground power unit circuitry of the airplane is capable of accepting 400 amperes continuously and current surges up to 1200 amperes for short durations (few sec), that may occur during engine starts. NOTE Since the airplane is equipped with an overvoltage protection on the external power supply line, the D.C. system automatically disconnects from the ground power unit should an overvoltage condition occur. The ground power unit operation is automatically recovered as soon as the voltage goes down to approximately 30 volts D.C. Use first engine start procedure. After both engines have been started disconnect the GPU (the green EXT POWER indication on the MFD System Page will extinguish) and switch both generators ON. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-61 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.4 BEFORE TAXI Before taxiing be sure that wheel chocks have been removed and the GPU disconnected. Check that battery switch is to BAT and generators are ON. Perform the Emergency Power Unit test. The EPU DRAIN caution light should be ON (EPU switch set to OFF). Set the EPU switch to the TEST position and hold for at least 5 seconds: check that the EPU DRAIN light is OFF while holding the switch in the TEST position. Set the EPU switch to ARM: check the EPU DRAIN amber light is OFF. Turn the avionics switch ON. Set the environmental mode selector to AUTO and select temperature as necessary. The cockpit blower can be selected as required. NOTE Depending on ambient temperature, combined operation of both the Heating and Cooling Systems up to 20,000 ft. may be required. Set the Cooling main control switch to FAN or COOL position, if necessary. Set the cockpit and cabin blowers operating mode to HIGH or LOW speed as desired. NOTE When on ground, during hot day operation, it may be necessary to increase NG up to 58% maximum in order to maintain the ITT within limits or temporarily to switch the bleed air OFF (in this case no outside air is circulating in the cabin). Both bleed air switches should be ON (L and R position respectively). Rep. 180-MAN-0010-01100 Page 4-62 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES On the cabin pressurization control panel, set the mode switch to AUTO and check the self test. NOTE The FAULT indication light on the control panel should momentarily illuminate (3 seconds maximum) during self test. If FAULT indication light fails to extinguish or re-illuminate, set AUTO/MAN switch to MAN and then back to AUTO to repeat self test. CAUTION No flight should be initiated in the automatic mode if the fault light fails to extinguish. AUTO SCHED/CAB SEL switch should be turned to AUTO SCHED and landing altitude, barometric correction and rate selection should be set turning the three knobs labeled, respectively A, B and R. Set ON the OIL COOL switch when the oil temperature reaches approximately 80°C. Verify the Integrated Standby Instrument has successfully completed the initialization and set the brightness. Check Air Data Computers and Attitude Heading Computers for proper operation. The operation of the Air Data System is automatic when the power is applied to the system and the initialization process has been completed. Verify unflagged conditions on the PFD and MFD display system. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-63 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Set the rotary switch of the SYS TEST panel to AVCS FAN, press and hold the central pushbutton: after about 7 seconds the AVCS FAN FAIL amber light on the annunciator panel will illuminate. Releasing the button the light will extinguish. To perform the Radio Altimeter test, select the RAD ALT position on the SYS TEST panel, press and hold the central pushbutton: the PFD displays the radio altitude generated by the radio altimeter when in self-test (50 ft.). The decision height warning flag is also displayed on the PFD if the DH set value is greater than the test altitude. Select on the SYS TEST panel the OVSP WRN position and press the test button: the aural OVERSPEED WARNING tone is activated, first from the left side ADC then, after about 2 seconds, from the right side ADC. Select on the SYS TEST panel the HYD position to perform the hydraulic system test: pushing the button the amber HYD PRESS light will illuminate and the pressure gauge reading increases about 1300 PSI. Releasing the button the light will extinguish and the pressure indication will return at the initial value. To test the steering system press the momentarily two steps control wheel button (black) to the first step: the system is not engaged. Press the button to the second step: the STEER T-O white message will appear on the PFD. Pressing again to the first step the STEER TAXI white flashing message will appear on the PFD, while pressing to the second step the take off position will be engaged and the PFD will show the white STEER T-O message. Pressing the control wheel Master Switch red button the steering will be disengaged (if S.B. 80-0286 or Mod. 80.0932 is installed, just the hydraulic power to the steering will be interrupted) and the steering indications (STEER T-O or STEER TAXI, depending on the mode selected) will extinguish. Set the knob of the SYS TEST panel to STEER position and push and release the central button: the STEER FAIL red light on the annunciator panel will illuminate when the steering is engaged in either takeoff or taxi condition and remains illuminated until the control wheel Master Switch is pressed. After completed this procedure the steering can be set for taxiing: position to TAXI the steering switch. Verify that when the left and right PITOT/STATIC HTR switches are set to the OFF position the L and R PITOT HTR caution lights on the annunciator panel illuminate. Rep. 180-MAN-0010-01100 Page 4-64 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Check the continuity of pitots, static ports, angle of attack transducer and TAT probe heating system by operating, on the ANTI ICE panel, the PITOT/STATIC HTR switches: an appreciable electrical current increment should be read on the MFD System Page when the left switch is set to the L & STALL position (about 15 Amp.) and a further increase should be observed when the right switch is set to the R & TAT position (10 Amp. approx. if “TAT heater inhibition on-ground” is installed; 18 Amp. approx. if “TAT heater inhibition on-ground” is NOT installed). If the angle of attack sensor heater has failed, the STALL FAIL amber light will illuminate on the annunciator panel: verify the STALL FAIL amber light is not illuminated, then proceed to the stall warning system test. NOTE If operations in heavy rain or snow or icing conditions are envisaged, switch the LH pitot heater and, if “TAT heater inhibition on-ground” (ref. para 4.0) is installed, the RH Pitot heater too) ON, before flight, with the aircraft steady on ground. CAUTION If “TAT heater inhibition on-ground” (ref. para 4.0) is NOT installed Pitot HTR R & TAT must be kept OFF The stall warning test is a computer-automated sequence, initiated by closure of the test button, after having selected the STALL position on the SYS TEST panel: a transmitter failure is simulated and the amber STALL FAIL light on the annunciator panel will illuminate then extinguish after a time interval between 15 and 20 seconds. The red STALL light on the pilot instrument panel will illuminate then extinguish, after 2 ÷ 4 seconds, and the aural warning horn will be activated. Thereafter the STALL FAIL amber light will illuminate again (while CPU resets) and extinguish after one or two seconds. After the test, set to OFF position the L & STALL switch. Select on the SYS TEST panel the FLAPS position and perform the flap system test. With the flap lever in UP position press the test button located in the center of selector switch: the FLAP SYNC amber light, on the annunciator panel, will illuminate and the white FLAP message on the PFD and on the MFD System Page becomes yellow and flashes for 5 seconds; releasing the button the FLAP SYNC amber light must extinguish and the FLAP message must return white. Move the flap lever to MID position and check proper deployment of each surface on flap monitor display: forward wing flaps shall start to move approximately 9 seconds after the outboard panels. Move for about one second, stop for 3 seconds then start again together with the inboard surfaces. During the flaps deployment and after the stop in the MID position, the FLAP SYNC light will not illuminate and the FLAP message on the PFD and MFD will remain white. Press the test button: FLAP SYNC light will not illuminate and the FLAP message Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-65 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES on the PFD and MFD will remain white. Move the flap lever to DOWN position and check the operation on flap monitor: all flap surfaces start together and during the deployment and after the stop, the FLAP SYNC light will not illuminate and the FLAP message on the PFD and MFD will remain white. Press the test button: FLAP SYNC light will illuminate and the white FLAP message on the PFD and on the MFD System Page becomes yellow and flashes for 5 seconds. Set the flap lever in MID position and check the operation: during the retraction and after the MID position has been reached, the FLAP SYNC light will not illuminate and the FLAP message on the PFD and MFD will remain white. Return the flap lever to UP position and check the operation on the flap monitor display: again during the movement and after the UP position has been reached, the FLAP SYNC light will not illuminate and the FLAP message on the PFD and MFD will remain white. WARNING No takeoff authorized with non symmetrical flap configuration or annunciated failure. Having completed this procedure, the flaps can be positioned for take-off: select MID and check for the FLAP SYNC light not illuminated and the white FLAP message on the PFD and on the MFD System Page. Longitudinal trim system test is accomplished by first turning the PITCH TRIM switch to SEC: trim motion shall be easily checked observing the indicator and the movement of the control column. The up-down spring, which connects the elevator to the horizontal stabilizer, when the stabilizer is in the range between full nose down and approximately -4° nose up, pushes the control column against the forward stop. As the pitch trim is operated toward nose up position and the stabilizer reaches approximately -6° nose up, the control column moves aft, giving a positive check of the spring integrity. WARNING If the control column does not move as described, do not take off and have a maintenance check. Continue the longitudinal trim system test moving each half of the NOSE DNOFF-NOSE UP switch separately to NOSE UP then NOSE DN: trim motion shall not occur. Rep. 180-MAN-0010-01100 Page 4-66 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Move both halves simultaneously to each position: trim motion shall occur. Operate trim switches on either control wheel to NOSE UP then NOSE DN: trim motion shall not occur. Turn the PITCH TRIM switch to PRI: with the primary system operating an aural trim in motion signal is activated for the longitudinal trim. Operate both halves of the pedestal trim switch simultaneously to NOSE UP, then NOSE DN: trim motion shall not occur. Check the proper operation of pilot’s control wheel longitudinal and lateral trim switch. Without depressing arming button, move switch to LWD, RWD, NOSE UP and NOSE DN: trim motion shall not occur. Depress arming button: again no trim motion shall occur. Depress arming button and move the switch to LWD, RWD, NOSE UP and NOSE DN: trim motion shall occur as shown by the appropriate indicator. Repeat this procedure for copilot’s control wheel trim switch. Move the copilot’s control wheel trim switch and trim in the opposite direction using pilot’s control wheel trim switch: this action shall override copilot’s trim. Repeat for each switch position. Check the proper operation of the pilot’s control wheel Master Switch (MSW). Move the control wheel trim switch to NOSE UP, then press the MSW switch (below trim switch): trim motion shall stop. Same behavior shall occur trimming to NOSE DN. Move the rudder trim switch on the pedestal to NOSE LEFT: press MSW on pilot’s control wheel, trim motion shall stop. Same behavior shall occur trimming to NOSE RIGHT. Repeat the procedure for co-pilot’s control wheel Master Switch. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-67 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Figure 4-2. Takeoff Pitch Trim Vs. Center of Gravity Rep. 180-MAN-0010-01100 Page 4-68 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Rudder trim system is tested moving each half of the rudder trim switch, on the pedestal, separately to NOSE LEFT then NOSE RIGHT: trim motion shall not occur. Moving both halves simultaneously to each position, trim motion shall occur as shown by the YAW TRIM indicator. Trim all axes for takeoff. Determine stabilizer takeoff setting by referring to Figure 4-2 on page 4-68. CAUTION Failure to set the correct trim for take-off may result in high rotation forces, delayed rotation and a substantial increase in take-off distance. Verify the correct operation of the ice detector selecting the ICE DET position on the SYS TEST panel and pressing momentarily the central button: the ICE amber lights located in the upper left and right side of the instrument panel will illuminate and, after a few seconds, will blink until one of the two ICE lighted pushbuttons is not pressed: then will extinguish. To perform windshield heat test, select on the ANTI-ICE panel the WSHLD HTR PRI system to LO position: on the MFD System Page an electrical load increment between 20 and 30 Amp. should be read; a similar behavior occurs when the SEC system is selected to LO position: the increment should be between 25 ÷ 35 Amp. The higher values correspond to peak condition or to low ambient temperature, the lower to stabilized condition or high ambient temperature. To perform the engine ice vane and the oil cooler intake heater test select, on the ANTI-ICE panel, the L/R ENG ICE VANE and the L/R OIL COOL INTK positions and observe the corresponding green ON indications are displayed on the MFD System Page (left and right side of the “ENG” and “OIL” legends) when the vane reaches the correct position after 30 seconds approximately and when the temperature of the oil cooler intake lip reaches the correct value: depending on the ambient conditions the power lever should be advanced between 82 and 86% NG approximately. Engine inlet de-ice boots correct operation is checked setting the BOOTS switch to TIMER position: the white ON indications, displayed on the MFD System Page (left and right side of the “BOOTS” legend), shall become green for 5 seconds to show the inflation cycle. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-69 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Depending on the ambient conditions the power levers should be advanced to Flight Idle or above. WARNING Do not operate engine inlet de-ice boots below –40°C. No takeoff authorized with frost, snow or ice adhering to propellers, windshields, powerplant installation and pitot/static ports, or with snow or ice adhering to the wings, vertical and horizontal stabilizer or control surfaces. NOTE Perform Main and Fwd wing anti ice tests if ice conditions are known or expected. To perform the main wing anti-ice test set, on the ANTI-ICE panel, to AUTO position the L/R MAIN WING switches and on the SYS TEST panel the MN WG A/I mark: press momentarily the central test button. After approximately 20 seconds both green ON indications shall be displayed on the MFD System Page (left and right side on the “MW” legend). Should the green ON indications appear immediately after the pushbutton has been pressed, that would indicate a control valve failure. The ON indications and “MW” legend flashing indicates the failure of a temperature sensor which does not affect the proper operation of the system: however the flight is allowed due to the redundancy of the system. Have a maintenance check as soon as practical. After the test switch OFF the main wing anti-ice system to exit the test mode (the control valve closes). To perform the forward wing anti-ice system test, select the FW WG A/I mark on the SYS TEST panel and then turn ON the appropriate L/R FWD WING switch, on the ANTI-ICE panel: depending on the ambient temperature, the green ON indications could be displayed on the left and right side of the “FW” legend, on the MFD System Page. This does not indicate that the system is working properly, but only that the skin temperature is in the normal operating range. Press the test button momentarily and check on the MFD System Page an increase of power absorption of approximately 30 ÷ 40 Amp. for each de-ice system: do not wait for the green ON indications to be displayed. Rep. 180-MAN-0010-01100 Page 4-70 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Perform the avionics system reversion tests and the Autopilot test as explained in the following. Display reversion powers down the failed flight display and enables a combined PFD/MFD format to show on the remaining display. Set PFD to power down the MFD and show the composite format on both pilot and copilot PFDs. In this situation, in addition to the normal PFD format, Engine Indicating System shows on top of the display and System Page is also available. Set MFD to power down the Pilot PFD and show the composite format on the MFD; copilot PFD remains in the normal format. The MFD operation with PFD reversion is identical to the PFD operation with loss the MFD. WARNING Take off not authorized if reversionary function fails operating. Failure of reversionary function while in case of MFD malfunction results in a complete loss of powerplant parameters indication. ADC reversion allows both pilot and copilot to select an alternate source of air data in case of an onside air data failure. Upon selection of ADC reversion, on-side ADC data are replaced with cross-side ADC data. ADC reversion message (on both PFDs) is ADC1 when the pilot’s ADC is the common air data source, and ADC2 when the copilot’s ADC is the common source. AHC reversion allows both pilot and copilot to select an alternate Attitude/ Heading sensor in case of an on-side AHC data failure. When the pilot side AHC is the common attitude and heading data source the message AHC1 shows on both the PFDs. When the copilot side AHC is the common attitude and heading data source the message AHC2 shows on both the PFDs. The Radio Tuning Unit/Control Display Unit reversion allows for restoring full tuning capability of cross-side radios, in case of RTU/CDU failure, in accordance with the selection performed. RTU or CDU selection on reversionary panel automatically powers down the disabled unit. The autopilot preflight and functional checks should be conducted before each flight to assure proper operation. NOTE If the V-bars are in view and no FD mode is selected, to remove V-bars out of view select and then deselect a lateral mode. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-71 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES The battery switch should be on BAT, the circuit breakers checked, attitude and heading flags out of view before accomplishing the preflight checks. Depressing the autopilot engage button activates an internal test sequence within the Flight Guidance System that must be completed satisfactorily before the autopilot will engage. Unsatisfactory test will be shown by central AP red light on the PFDs. During ground check, depress the MSW button and verify that the autopilot and the yaw damper disengage. Re-engage the autopilot and verify that activating the control wheel manual electric trim switch will disengage the autopilot. Reengage the autopilot and verify that by re-pressing the engage button on the Flight Guidance Panel, the autopilot will disengage. Reengage the autopilot and verify that it will be disengaged by actuating the trim selector out of the PRI position. By engaging the HDG on the Flight Guidance Panel, the Flight Director Command bars will drop into sight on the pilot's and copilot's PFD. The heading bug should be centered below the lubber line on the PFDs. This will result in a wings level display by the command bars. By rotating the heading marker 10° left and right of the lubber line, the flight director will display left and right turns accordingly. The autopilot will also follow these commands resulting in the control wheel turning in the corresponding directions. Autotrim checks should be accomplished by manually pulling back on the control wheel and verifying that the trim runs automatically (approximately after 2 seconds) in the nose down direction as the autopilot attempts to relieve the load imposed by the pilot. Pushing forward on the control wheel will result in the trim running nose up for the same reason. The APPR Mode checks are accomplished with the No. 1 VOR tuned to an active VOR frequency for a station which is within receiving range. Center the lateral deviation bar on the PFDs; engage Approach Mode; change course in order to displace the deviation bar on right or left and confirm that the flight director displays a turn in the direction of the course indicated by the PFDs and that the autopilot attempts to follow the command by turning the control wheel in the direction of the course. Disengage the yaw damper and verify that all controls operate freely and in the correct direction. Set the trim to the takeoff position. CAUTION Failure to set the correct trim for take-off may result in high rotation forces, delayed rotation and a substantial increase in take-off distance. Rep. 180-MAN-0010-01100 Page 4-72 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Check and set communication radios, radio navigation equipment and FMS. Complete descriptions of activities needed in order to initialize and to operate correctly the FMS is available in the Collins FMS 3000 Flight Management System Operator’s Guide for the Piaggio Avanti P.180 as reported in Section 2 (page 2-24). NOTE The Collins Operator’s Guides are published by Collins and has not been approved by ENAC or FAA; they have been written specifically for the P.180 but a specific airplane could not install all the features there described. Radar test should be performed rotating the selector in TEST position. Then the system will perform an automatic test. A possible failure is addressed with an indication of radar failure on PFD and MFD. In this case radar system will not be operative for flight. If test is successful set radar in ST-BY position. Check for the absence of air data flags on the PFD and MFD display system. In order to detect a possible dormant failure in the cabin door monitoring circuit, it is necessary to repeat the annunciator panel test. Select the LAMP position on the SYS TEST panel and press the test button: check that the CAB DOOR red warning light is flashing. Verify the CAB DOOR and the BAG DOOR lights not illuminated after releasing the test button. Engage the steering system to TAXI position. Having BEFORE TAXI procedure COMPLETED release the parking breake as required. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-73 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.5 TAXIING While taxiing, apply brakes to determine their effectiveness. Avoid excessive brakes use to prevent overheating with possible tire deflation. Use beta range propeller setting, if required, for reducing running speed. NOTE Keep brakes warm during taxi operation in snow, slush and water conditions. When running on a level surface, disengage the steering system and check the airplane has no tendency to yaw left or right: a deviation tendency may reveal an incorrect brake release. Reengage the steering system to the TAXI position. NOTE With airplane configuration CG Fwd and S.B. 80-0454 or 800425 (new NWSS) installed, avoid to steer with pedals up to end-of-travel position when airplane is stopped. NOTE During Taxi maneuvers, for airplane heading changes greater than 90°, it is recommended to not exceed a speed of 10 KTS. Set the power levers at IDLE for a reverse check: move the power levers toward REVERSE and observe NG and NP increase. While taxiing with the power levers at IDLE, exercise the propeller controls moving the condition levers from MAX RPM to FEATHER to check the propeller controls and the response to the governor. Rep. 180-MAN-0010-01100 Page 4-74 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.6 ENGINE RUN UP Prior to engine run up, set the parking brake locked by pulling and turning the handle in vertical position. To test the propeller overspeed governors, advance condition lever to MAX RPM and power lever to obtain 2000 RPM. Select the momentarily PROP OVSP TEST switch alternatively to LEFT and RIGHT: observe a drop of approximately 150 RPM and a torque rise. Release the switch to normal position and check that the propeller speed returns to 2000 RPM. Check propeller governing to minimum RPM by retarding condition lever. Proceed to autofeather system test: with the autofeather switch set to OFF position the amber AUTOFEATHER light must be illuminated: setting the switch to ARM position, the light must extinguish. Advance both power levers to obtain approximately 33.6% torque. Set the autofeather switch to TEST position and hold: both left and right autofeather AFX green message, on the MFD Engine Indicating System display, should appear approximately after two seconds, indicating a fully armed system. Retard power levers individually: between 30.5% and 21.5% torque, opposite AFX indication should extinguish and between 21.1% and 13% the AFX indication of the engine being retarded will flash as prop cycles through feather then, after TEST button release, should extinguish. The difference between high torque pressure transducer and low torque pressure transducer values shall be at least of 3.1%. This separation is required for both the individual engine and for the two engines together (i.e. LH high torque vs. RH low torque and vice versa). Retard power levers simultaneously: both AFX indications should extinguish, neither propeller feathers. WARNING If the autofeather system does not function in accordance with the pre-flight test procedure, takeoff is not authorized. After the autofeather system test has been successfully completed, set the autofeather switch to ARM position and release the parking brake. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-75 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.7 BEFORE TAKEOFF Check that all circuit breakers are IN and set the anticollision lights to AIR. Select windshield heat as required by weather condition. Set the seat belts and no smoking sign ON. Flight instruments should be checked and set. Weather Radar should be checked for proper operation. NOTE Possibility exists that signal returns become visible on the radar map as either three separated echoes at 10, 12 and 2 o’clock (flying over the sea surface) or a single “horse shoe” (flying over the ground), at a distance equivalent to the airplane altitude while looking for weather at short distance (25 NM and lower ranges) and tilt up. Intensity of the false echoes increases with the gain setting. The engine indicating system should be checked. Be sure that all warning and caution lights are not illuminated. Transponder set as required. Check ON the bleed air switches. NOTE When operating from high altitude airports with high SAT, it may be necessary to switch OFF both bleed air to reduce engine ITT. Check if the fuel pumps are to MAIN. Check condition levers are MAX RPM. Check Autopilot and Yaw Damper are disengaged. Check MID position for flaps. Check longitudinal trim properly set for takeoff according to Figure 4-2 (take off pitch trim vs. C. G.), aileron and rudder trim in NEUTRAL position. Check flight controls for freedom of movement. Steering should be positioned for TAKEOFF and oil cool switches set to OFF. Switch on the navigation and the taxi/landing lights if conditions require. If ice conditions are known, activate the ice protection systems following the procedure indicated in the "Operation in Icing Conditions" Paragraph. Rep. 180-MAN-0010-01100 Page 4-76 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Switch ON pitot, static ports, stall warning device and total air temperature probe heaters. NOTE If “TAT heater inhibition on-ground” (ref. para 4.0) is NOT installed” it is recommended to set R&TAT ON before line up and takeoff. When TAT heater is selected a total air temperature increase may be detected on ground until the system is stabilized after airborne. Thereafter TAT indication is valid. CAUTION If "TAT heater inhibition on-ground" change (ref. para 4.0) is NOT installed, switching "ON" RH pitot and TAT heater on ground for a long time, it may cause temporary unavailability of the Flight Director Check that the L PITOT HTR and R PITOT HTR caution lights on the annunciator panel are off. 4.3.8 TAKEOFF Hold the brakes and advance power lever until about 89.7% torque. WARNING Before applying full power, be sure the condition levers are set to MAX RPM. Disregarding this procedure, a remarkable increment of ground roll will result. Check autofeather armed (green left and right AFX indications on the MFD EIS display), release brakes, increase power up to 96.4% torque and check engine instruments. NOTE Torque limit of 96.4% is the static value to be applied for takeoff in order to obtain the normal 100% (2230 lb.ft.) at takeoff speed for ram effect during the takeoff run. WARNING If ambient temperature is below –25°C, it is necessary to operate the main wing anti-ice and the engine ice vane systems before applying full power to ensure that the autofeather is armed. When takeoff is completed and autofeather disengaged, the ice protection can be switched OFF. At low ambient temperature (below –25°C), in order to ensure that the autofeather is armed, it is necessary to select, on the ANTI ICE panel, AUTO Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-77 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES position for L/R MAIN WING and L and R position for ENG ICE VANE and OIL COOL INTK switches. When takeoff is completed and the autofeather system disengaged, the wing and engine anti ice systems can be switched OFF. As the aircraft accelerates, an increase in torque at a fixed power lever position is normal. Adjust power setting as required to maintain engine gauges within limits. Only if S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed, disengage steering not over 60 KIAS. Disengage steering not over 60 KIAS. Before rotation attain a minimum airspeed as per Figure 5-16. Rotate approximately between 10° to 15° nose up according to the weight and, after lift off, accelerate to and maintain an airspeed of 120 KIAS until above 50 ft. Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that the steering system automatically disengage after lift off (no mode indication on PFD). Below 160 KIAS switch off the taxi/landing lights, if applicable, and check LTS DOOR OPEN green advisory indication, on the MFD System Page, is off. Retract landing gear below 180 KIAS and flaps below 170 KIAS. Do not retract the landing gear prematurely. Disengage the autofeather system above 150 KIAS. Flight Director Modes may be selected as desired by the pilot. With any lateral mode selected, the FD SYNC switch will synchronize the pitch commands to the attitude of the airplane at the time FD SYNC switch is released. The autopilot may be engaged above 400 feet AGL during climb. CAUTION A continuous annunciated amber elevator mistrim indication will anticipate that the airplane could be significantly out of trim. In this case the pilot should brace the flight controls and disconnect the autopilot. Upon disconnection the pilot will experience a force of between 7 kg (15 lbs) and 9 kg (20 lbs). Re-engagement of the autopilot should not be attempted until the reason for the out of trim state has been isolated and rectified, and the airplane has been returned to a trimmed condition. A temporary annunciated amber elevator mistrim indication during an acceleration/deceleration phase and/or configuration changes could be disregarded if it lasts not more than about 10 seconds. Rep. 180-MAN-0010-01100 Page 4-78 .A Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES Switch ON pitot, static ports, stall warning device and total air temperature probe heaters. NOTE If “TAT heater inhibition on-ground” (ref. para 4.0) is NOT installed” it is recommended to set R&TAT ON before line up and takeoff. When TAT heater is selected a total air temperature increase may be detected on ground until the system is stabilized after airborne. Thereafter TAT indication is valid. CAUTION If "TAT heater inhibition on-ground" change (ref. para 4.0) is NOT installed, switching "ON" RH pitot and TAT heater on ground for a long time, it may cause temporary unavailability of the Flight Director Check that the L PITOT HTR and R PITOT HTR caution lights on the annunciator panel are off. 4.3.8 TAKEOFF Hold the brakes and advance power lever until about 89.7% torque. WARNING Before applying full power, be sure the condition levers are set to MAX RPM. Disregarding this procedure, a remarkable increment of ground roll will result. Check autofeather armed (green left and right AFX indications on the MFD EIS display), release brakes, increase power up to 96.4% torque and check engine instruments. NOTE Torque limit of 96.4% is the static value to be applied for takeoff in order to obtain the normal 100% (2230 lb.ft.) at takeoff speed for ram effect during the takeoff run. WARNING If ambient temperature is below –25°C, it is necessary to operate the main wing anti-ice and the engine ice vane systems before applying full power to ensure that the autofeather is armed. When takeoff is completed and autofeather disengaged, the ice protection can be switched OFF. At low ambient temperature (below –25°C), in order to ensure that the autofeather is armed, it is necessary to select, on the ANTI ICE panel, AUTO Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-77 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES position for L/R MAIN WING and L and R position for ENG ICE VANE and OIL COOL INTK switches. When takeoff is completed and the autofeather system disengaged, the wing and engine anti ice systems can be switched OFF. As the aircraft accelerates, an increase in torque at a fixed power lever position is normal. Adjust power setting as required to maintain engine gauges within limits. Only if S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed, disengage steering not over 60 KIAS. Disengage steering not over 60 KIAS. Before rotation attain a minimum airspeed as per Figure 5-16. Rotate approximately between 10° to 15° nose up according to the weight and, after lift off, accelerate to and maintain an airspeed of 122 KIAS until above 50 ft. Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that the steering system automatically disengage after lift off (no mode indication on PFD). Below 160 KIAS switch off the taxi/landing lights, if applicable, and check LTS DOOR OPEN green advisory indication, on the MFD System Page, is off. Retract landing gear below 180 KIAS and flaps below 170 KIAS. Do not retract the landing gear prematurely. Disengage the autofeather system above 150 KIAS. Flight Director Modes may be selected as desired by the pilot. With any lateral mode selected, the FD SYNC switch will synchronize the pitch commands to the attitude of the airplane at the time FD SYNC switch is released. The autopilot may be engaged above 400 feet AGL during climb. CAUTION A continuous annunciated amber elevator mistrim indication will anticipate that the airplane could be significantly out of trim. In this case the pilot should brace the flight controls and disconnect the autopilot. Upon disconnection the pilot will experience a force of between 7 kg (15 lbs) and 9 kg (20 lbs). Re-engagement of the autopilot should not be attempted until the reason for the out of trim state has been isolated and rectified, and the airplane has been returned to a trimmed condition. A temporary annunciated amber elevator mistrim indication during an acceleration/deceleration phase and/or configuration changes could be disregarded if it lasts not more than about 10 seconds. Rep. 180-MAN-0010-01100 Page 4-78 .B Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.9 CLIMB Set climb power and maintain the climbing speed in accordance with the performance information presented in Section 5 of this AFM. NOTE Following take off and climb in heavy rain conditions, monitor IAS and cross-check pilot and co-pilot data. If any increasing difference between pilot and copilot IAS is noted, and the IAS displayed on the co-pilot PFD (latched to the right ADC) is the same as on the Stand-By instrument, water/ice contamination may have been occurred. In this case refer to emergency procedures in Sect. 3 (IAS COMPARATOR FLAG). After takeoff, the seat belt and no smoking sign may be turned OFF as required. Engage the synchrophaser system by setting the SYNCPH switch, on the Engine/Propeller panel, to SYNCPH position. NOTE Whenever the synchrophaser system is to be engaged, at the maximum propeller RPM, the condition levers must be retarded to a position corresponding to about 1980 RPM in order to maintain 2000 RPM. Check cabin pressurization. Set the Cooling main control switch to FAN or COOL position if desired. NOTE During flight, when the Cooling System is used the Heating System should also be ON in order to guarantee adequate pressurization and ventilation. Set the windshield heat control switches to the LO or, if necessary, the HI position. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-79 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.10 CRUISE Select cruise power and speed in accordance with the performance information presented in Section 5 of this AFM. NOTE Following take off and climb in heavy rain conditions, monitor IAS and cross-check pilot and co-pilot data. If any increasing difference between pilot and copilot IAS is noted, and the IAS displayed on the co-pilot PFD (latched to the right ADC) is the same as on the Stand-By instrument, water/ice contamination may have been occurred. In this case refer to emergency procedures in Sect. 3 (IAS COMPARATOR FLAG). Check the indications on the MFD Engine Indicating System display and monitor fuel quantity during flight: if necessary use crossfeed. To operate in crossfeed, turn the CROSSFEED knob horizontal and then switch OFF the fuel pump of the engine located on the same side as the wing tank with less fuel quantity. Check pressurization and set cabin comfort controls as desired. When cruising at 1000 feet AGL or above, the autopilot may be engaged if the airplane is trimmed, roll attitude is less than 45 deg and pitch attitude is less than +25 deg, pitch up, and -18 deg, pitch down, approximately. The existing pitch and roll attitudes will be maintained until lateral and vertical modes are selected. The heading bug should be aligned with the airplane heading or desired heading prior to selecting HDG Mode. The navigation radio should be tuned and the course arrow set to the desired VOR radial before selecting NAV. Turning the altitude preselector knob always arms the ALTS mode. Before engaging FLC or VS select the desired altitude on the preselector, otherwise the mode will not engage. FLC, VS may be used during climbout to maintain the desired vertical profile. The vertical trim switch may be used in Pitch Hold, FLC or VS to modify the climb profile. When using ALTS, the autopilot will automatically capture the preselected altitude for level off. If another vertical mode is used for the climb and ALT is to be selected at the desired level off altitude, the best autopilot performance will be obtained by reducing the airplane's vertical speed to approximately 500 feet per minute before engaging ALT. Using the FLC, VS, DSC mode will automatically arm the ALTS mode, when the altitude indicated in the preselector is different from the airplane altitude. To establish the airplane on a desired VOR radial, perform the following: Rep. 180-MAN-0010-01100 Page 4-80 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES a. Tune the navigation receiver to the desired VOR frequency. b. Set the course arrow on the PFD to the desired VOR radial. c. Set the heading bug on the PFD to the desired intercept heading. d. Press the NAV button on the Flight Guidance Panel. The HDG and NAV annunciators will light, indicating that the system is still in the heading mode and is armed for VOR radial capture. With the above procedure completed, the flight guidance system maneuvers the airplane to fly the selected heading to the point of beam capture. At beam capture, the HDG and ARM annunciators extinguish and smooth turn and rollout on the VOR radial is initiated. For optimum performance, conduct VOR intercepts at angles less than 60°. After capture of the selected VOR radial, the system provides automatic crosswind correction for proper tracking of the radial. Bank angles are limited to ± 10° in the NAV mode. When passing a VOR station, DR (Dead Reckoning) will be annunciated as the autopilot calculates the proper heading to fly to assure smooth station passage. Outbound course change may be commanded when overflying the VOR station if the course change is ± 30° or less. Set the course arrow to the new outbound radial at the time the to-from arrow changes from inbound to outbound. The flight guidance system will maneuver the airplane to attain the new selected course, and station passage will be as described above. To place the airplane directly on a VOR radial, select the NAV mode after the course indicator deviation bar indicates the width of one deviation bar or less. The FGS will begin to track the center of the beam. FLC, VS may be used during descent to maintain the desired vertical profile. The pitch wheel may be used in Pitch Hold, FLC or VS to modify the descent profile. 4.3.11 DESCENT Set the windshield heat as required. Shortly after letdown is initiated turn the knob labeled A on the CABIN PRESS panel to read the pressure altitude of the landing field and, with the knob B set the QNH. PIP mark on knob R allows a cabin rate of not less than 300 ft/min. A higher setting should be selected for rapid descents so that the aircraft altitude does not catch up with cabin altitude. Check pressurization and set cabin comfort controls as desired. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-81 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.12 APPROACH (FOR NON-PRECISION OR ILS CAT I APPROACHES) a. ILS Approaches The localizer and glide slope are captured automatically on an ILS front-course approach. The localizer must be captured before glide slope capture can occur. The localizer is always captured from a selected heading, but the glide slope may be captured from any of the vertical modes. Perform a front-course approach as follows: For optimum autopilot performance, limit localizer intercepts to angles less than 60° and airspeed below 200 KIAS. Plan the approach to intercept the localizer 5 to 10 NM outside the outer marker or final approach fix. 1. Tune the navigation receiver to the ILS frequency and set the course arrow to the published inbound course. 2. Set the heading bug to the desired intercept heading, and select HDG on the Flight Guidance Panel. Any vertical mode may be selected during localizer intercept. 3. Select APPR on the Flight Guidance Panel to arm the system for automatic localizer and glide slope capture. The HDG green annunciator and APPR LOC white annunciator illuminate to verify that proper switching has occurred. 4. As the airplane nears the center of the localizer, the HDG annunciator extinguish, the APPR LOC annunciator illuminates green, and the localizer course is captured. When localizer capture occurs, the GS and ALTS white annunciators illuminate to verify that the system is armed for glide slope capture. NOTE As soon as localizer capture occurs (APPR LOC green annunciations ON), the published missed approach heading may be set on the PFD's heading bug. 5. Before glide slope capture, the system remains in any vertical mode selected on the Flight Guidance Panel. When the glide slope is captured, the ALTS annunciator extinguishes and the GS annunciator illuminates green. Any selected vertical mode automatically disengages at GS capture. All steering commands (lateral and vertical) are to maintain the center of the localizer and glide slope. 6. Lateral and vertical slew switch has no effect after glideslope and localizer capture. Rep. 180-MAN-0010-01100 Page 4-82 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES b. VOR Approaches VOR approaches are accomplished in the same manner as ILS front course approaches except no glide slope signals are available. NOTE VOR approaches must be conducted in APPR mode. 1. Tune No. 1 NAV to proper VOR or VORTAC frequency. 2. Set course pointer to published inbound course. 3. Set heading bug to desired intercept angle and select the HDG mode; HDG green annunciator comes ON. For optimum performance, limit VOR intercepts to angles less than 60° and speeds at or below 200 KIAS. 4. Select APPR on the Flight Guidance Panel to arm the system for automatic VOR capture. The APPR VOR annunciator illuminates white to verify that proper switching has occurred. 5. As the airplane nears the center of the selected radial, the HDG green annunciator extinguish and the APPR VOR annunciator illuminates green as the autopilot intercepts the selected course. 6. Adjust the pitch wheel as desired, to descend in accordance with published instructions. 7. Go-Around and landing procedures are the same as for an ILS approach. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-83 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES c. Vectored Approaches When a radar vectored approach is required, the pilot may use the flight control system to maintain the vector headings and altitudes. To fly a radar-vectored approach, first set the heading bug under the lubber line, then select HDG on the Flight Guidance Panel. Maintain the vector heading received from approach control by setting the heading bug to the appropriate heading. The course arrow may be set to the runway heading being approached to provide a visual reference of runway position in relation to the aircraft heading. The desired vertical mode may be utilized to follow vertical commands during vectoring. Rep. 180-MAN-0010-01100 Page 4-84 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.13 BEFORE LANDING Switch ON the seat belts and no smoking signs. Turn OFF the synchrophaser system. Set the condition levers to MAX RPM. At speed below 180 KIAS, lower the landing gear and check for three green lights. Moreover, if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that steering system is automatically armed (STEER T-O message on PFD). NOTE S.B. 80-0454 or 80-0425 (new NWSS): When armed, steering will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. Extend flaps as required and check, at the end of the maneuver, the SYNC LIGHT OFF; the maximum speed for flaps extension is 170 KIAS for the MID position and 150 KIAS for full flap. ARM autofeather below 150 KIAS. Check amber AUTOFEATHER annunciator panel light is off. Switch ON landing light if required below 160 KIAS. CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. For more information about airplane operation in icing conditions consult Paragraph 4.3.21 of this Section. Autopilot and yaw damper and steering must be OFF for landing. Compare cabin altitude with aircraft altitude. If necessary, depressurize cabin with the DUMP switch before landing; aircraft is not approved for landing when pressurized. NOTE Demonstrated crosswind component for landing is 25 KIAS. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-85 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.14 LANDING Prior to reaching 50 ft above landing surface verify that the gear and flaps are down. Assume an approach speed as per Figure 5-69 at Section 5. CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. Only if S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed, steering engagement during landing is prohibited. The landing distance with flaps MID (Figure 5-73) must be increased approximately by 10% if reverse thrust is not applied or by 5% if reverse thrust is applied. For more information about airplane operation in icing conditions consult Paragraph 4.3.21 of this Section. Use power as required and reduce during the flare, check condition lever for MAX RPM. After touch down use brakes and reverse as required. Engage reverse thrust below 1900 prop RPM, or 5% drop from the set value, and disengage when the speed has decreased to: 40 KIAS, in order to avoid damages to the propellers and, particularly if S.B. 80-0286 or Mod. 80-0932 is NOT installed, in order to avoid transmission of rudder induced oscillations to the pedals. NOTE When landing at aft C.G. initiate flaps retraction before actuating reverse power. When landing at light weights, use caution when applying brakes, as excessive pedal pressure will result in skidding the tires with a resultant loss in braking effectiveness. When landing is completed and reverse has been disengaged retard the condition levers to GROUND IDLE. Engage Steering in TAKE OFF mode (if necessary). NOTE If “TAT heater inhibition on-ground” change (ref. para 4.0) is NOT installed, a total air temperature increase may be detected until the TAT heater is turned off. Rep. 180-MAN-0010-01100 Page 4-86 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.15 GO AROUND Execute a Go-Around by the following procedure: 1. Press the GA button on the left power lever while increasing power to the balked landing climb power setting (Refer to Section 5 of this AFM). The GA mode can be selected only from the APPR mode; if the autopilot is engaged, the GA mode will maneuver the aircraft to an approximately 8° nose up pitch attitude. The APPR Mode is canceled, GA green indications will come ON and steering commands are provided for a wings level, fixed 8° pitch-up. Selecting a lateral or vertical mode cancels the Go-Around mode. The pitch attitude will remain at that used for Go-Around until changed with the selection of a vertical mode. 2. After airplane cleanup, Go-Around power settings and airspeed are established, select the HDG or NAV mode on the Flight Guidance Panel to fly the missed approach procedure. 4.3.16 BALKED LANDING In a balked landing situation, apply takeoff power, maintain torque and engine temperature within allowable limits. Maintain an airspeed of 115 KIAS. CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID. The balked landing speed, in icing conditions, with flaps MID is 130 KIAS. For more information about airplane operation in icing conditions consult Paragraph 4.3.21 of this Section. After climb is established, accelerate the airplane then retract the flaps to MID (below 150 KIAS), retract the landing gear, switch off the landing lights (below 160 KIAS) then retract flap to UP position (below 170 KIAS). Accelerate to and maintain a speed of 160 KIAS. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-87 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.17 AFTER LANDING When clear of active runway, set the power levers to IDLE and, if necessary, select the steering to TAXI. NOTE With airplane configuration CG Fwd and S.B. 80-0454 or 800425 (new NWSS) installed, avoid to steer with pedals up to end-of-travel position when airplane is stopped. NOTE During Taxi maneuvers, for airplane heading changes greater than 90°, it is recommended to not exceed a speed of 10 KTS. Retract the flap. Turn the radar equipment OFF as well as the transponder and ice protection equipments (if applicable). NOTE Following operations in heavy rain or snow or icing conditions, or when water ingestion may have occurred, keep the LH and RH pitot heaters ON after landing, with the aircraft steady on ground. Anticollision light should be turned to GROUND and the taxi light should be switched on if required. Switch OFF the autofeather. Verify cabin altitude equals landing field elevation. In the event of landing with severe brake use an adequate brakes cooling time is required before a successive takeoff. Rep. 180-MAN-0010-01100 Page 4-88 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.18 SHUTDOWN After the airplane is taxied to a stop, set the parking brakes: they should not be set if they are very hot or if the ambient temperature is below freezing and the brakes are wet. Switch OFF avionic equipment. CAUTION Failure to select avionics power switches to the OFF position during the engine shutdown may result in equipment failure. Switch OFF Pitot HTR L & STALL and R & TAT Switch OFF EPU and bleed air. Check power levers at IDLE and condition levers at GROUND IDLE. NOTE Allow the engine to stabilize for a minimum of two minutes at minimum obtainable ITT. During the shutdown ensure that the compressor decelerates freely. Switch OFF the hydraulic pump and pull the condition levers to CUT OFF. Set fuel pump, all electrical and battery switches to OFF. WARNING If there is an evidence of fire within the engine after shutdown, proceed immediately as described under "Engine Dry Run (Motoring)" Procedure. NOTE If OAT > 30°C perform 30 sec. motoring as per “ENGINE DRY RUN” Procedure. CAUTION The passenger door may be opened 10 seconds after the passenger upper door handle has been rotated to OPEN position. Rotate the upper door handle to OPEN position, wait that the door seal has deflated (about 10 seconds, i.e. until external/internal background passes through the frame/door gap), push/pull the upper door open and relocate the handle to STOW position. Pull the safety pin from the lower handle and rotate the handle to OPEN position. Pull and hold firmly the cable handle knob, then lower gently the lower door. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-89 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.19 AFTER SHUTDOWN The engine oil level must be checked daily according to Maintenance procedure. NOTE Perform the engine oil level check within 30 minutes after engine shutdown. Ideal interval is 15 to 20 minutes. After the last flight of the day, cleaning of the propellers blades is recommended to remove engine exhaust residue. Refer to Section 3 of Pilot’s Operating Handbook, para 3.4.5 “Propeller Service” for instructions and allowed solvent/ cleaner list. Before leaving the airplane, install the control locks, lock the emergency exit by installing the handle lock pin, place the wheel chocks, install the covers on the pitot tubes, engine and oil cooler intakes and exhaust ducts. CAUTION If Pitot probes, Static ports and TAT/AOA sensors have been heated, be sure that such equipment have cooled down before installing covers. NOTE Do not install covers on a warm engine. Attach propeller restrainers to prevent windmilling and, if necessary, install tiedown ropes. NOTE If the airplane is supposed to be parked for more than 2 days unplug the battery clamp from the battery in the baggage compartment. CAUTION Following suspected water contamination, have both pitot lines cleaned and drained at the earliest opportunity. Rep. 180-MAN-0010-01100 Page 4-90 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.20 CATEGORY II OPERATIONS APPROACH AND LANDING PREPARATION AFTER TRANSITION ALTITUDE Set the correct value of pressure referenced in the PFD1 and PFD2 and the Standby Instrument. IF MORE THAN 20 NM FROM THE ILS STATION Set the DH (on both the PFD control panels) and Test the Radio Altimeter not earlier than 5 min. before initiating the approach phase. The test will be performed on the copilot's station as previously described in "BEFORE TAXI". As the test feature is inhibited while the autopilot is engaged, disengaging the autopilot is required before starting the test. The Autopilot can be momentarily disengaged by depressing and holding the FD SYNC button on the control wheel, or, if preferred, by pressing the MSW button on the control wheel. After the Radio Altimeter test has been completed, reengage the Autopilot by pushing the AP engage switch on the Flight Control Panel or releasing the FD SYNC. IF 20 NM OR LESS FROM THE ILS STATION Select the APPR Mode and adjust the condition levers to obtain 2000 RPM. NOTE Any erroneous autopilot lateral mode selection other than APPR will not switch ON or will switch OFF CAT II approach monitoring green light and will not activate the "loss of approach" warning tone. Verify CAT II indication by checking the CAT II green light ON on either the pilot's and copilot's PFD. The Radio Altimeter is set to operate up to 2500 ft: if the airplane is flying above 2500 ft, the CAT II annunciator, when pushed, will be in the AMBER condition. Check the CAT II AMBER light comes off and the GREEN light comes on, when the airplane reaches an altitude equal to or below 2500 ft. NOTE Glide Slope must be captured above 1500 ft. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-91 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES FROM 300 FEET AND BELOW Maintain established approach airspeed and monitor instruments until the airplane touches down. Call out Radio Altimeter read-outs as follows. 300 - 200 - 150 - DH - 50 - 30 When the airplane reaches the decision height, a MIN (minimum altitude annunciation) inscription appears close to the GS box on both the pilot’s and copilot’s PFDs. Decide if landing the airplane or performing a go around. If the decision to land has been taken, disengage the Autopilot at an altitude not less than the DH (100 ft) and manually land the airplane. IF GO AROUND IS DECIDED In go around situation, press the GA button on the left power lever while increasing power to the bulked landing climb power setting (refer to Section 5 for power setting and to Paragraph 4.3.15 for further information on autopilot go around). Maintain torque and engine temperature within allowable limits. Maintain an airspeed of 120 KIAS (minimum). CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID. In this condition the go around speed is 130 KIAS. For more information about airplane operation in icing conditions refer to Paragraph 4.2.21 of this AFM. After climb is established, accelerate the airplane than retract the flap to MID (below 150 KIAS), retract the landing gear, then retract the flap to UP (below 170 KIAS). Accelerate to and maintain a speed of 160 KIAS. Rep. 180-MAN-0010-01100 Page 4-92 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.21 OPERATION IN ICING CONDITIONS If icing conditions are encountered (amber ICE caution lights illuminated for 5 seconds), set to L and R position the ENG ICE VANE and OIL COOLER INTK switches and to AUTO position the BOOTS DE ICE switch. After approximately 30 seconds the “ENG” and “OIL” white ON indications, on the MFD System Page, will become green and an engine torque drop will be observed; after few minutes from the actuation, depending on the severity of the ice encounters, the “BOOT” white ON indications will become green during the inflation cycle. WARNING Do not operate the engine de-ice boots below – 40°C. NOTE The surface ice protection systems must be activated approximately 30 seconds after the actuation of engine ice protection systems to avoid a quick increase of engine ITT. Set the L and R MAIN WING switches to the AUTO position: the “MW” white ON indications will become green approximately 30 seconds after the actuation: an engine torque drop is normal. CAUTION The MANUAL mode of operation of the main wing anti-ice system must be selected only in case of failure of the AUTO mode to avoid a possible leading edge skin overtemperature. Set the FWD WING switches to L and R positions and operate the windshield heater. Check that both WSHLD HEAT PRI and SEC switches are set to the LO position or move to the HI position if the heating is inadequate. Maintain the propeller speed (NP) at 2000 RPM. Correct operation of the surfaces and engines anti-ice systems can be checked observing the corresponding advisory indications on the MFD System Page, Anti-Ice System status display. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-93 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES NOTE a. During descent, or in cruise at low power settings and/or low ambient temperatures, the “MW” and “OIL” ON indications may remain white, indicating that the temperature of the heating air is below the reference value. b. During cruise at 25000 feet or higher altitudes and low power settings, the cabin altitude may increase. In both cases an increase of power may restore the normal conditions. The P.180 AVANTI airplane is certified for flight in the icing conditions defined by the Appendix "C" to FAR 25. Nevertheless, icing conditions exceeding the capabilities of the anti-icing and de-icing systems (defined as "severe" by the Aviation Weather Services) may be encountered. For this reason, the pilot should avoid such severe ice conditions and should exit the icing cloud if an abnormal accretion rate is recognized (visually or by means of the ice detector). In addition, as freezing rain conditions have not been tested but only evaluated by analysis, freezing rain encounters should be avoided and, in any case, flight in these conditions should be limited to short periods of time. Some handling and performance changes can be experienced with ice build up on unprotected parts and run-back ice on forward and main wings. The most noticeable characteristics are a mild continuous airframe buffet and a significant increase in power required to maintain a specific cruise speed. Stall speeds should increase with ice accumulation: with an ice build-up corresponding to sustained ice accretion (3 inches approximately on the main wing tips), the increment will be approximately 6% for all flap setting: however stall warning margins remain adequate. The power loss associated with the operation of the ice protection systems depends on speed, altitude and temperature and could reach 20% approximately: however the pilot may reset the power without exceeding the ITT (red line) or torque limits. Exiting icing conditions, deactivate anti/de-ice systems and check on PFD or MFD system page advisory indications OFF. Rep. 180-MAN-0010-01100 Page 4-94 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES CLIMB PERFORMANCE If the power cannot be reset and if the ice accretion on the unprotected parts corresponds to one inch approximately on the main wing tips, the following may result: a. the normal two engines rate of climb (Figure 5-26) will be reduced by 800 ft/ min. at sea level and 1800 ft/min. at 20000 feet and the ceiling will be approximately 27000 feet. b. the normal one engine inoperative rate of climb (Figure 5-32) will be reduced by 500 ft/min. at sea level and 700 ft/min. at 10000 feet and the ceiling will be approximately 11200 feet. LANDING PERFORMANCE. WARNING The icing limitation requiring flaps in MID position for landing is necessary since landing with flaps DN, with heavy residual ice accumulation, may result in a decrease of longitudinal stability or limited trim capability if the C.G. position is, respectively, fully aft or forward. The balked landing climbing speed, with flaps in MID position is 130 KIAS: if the power cannot be reset and if the ice accretion on the unprotected parts corresponds to three inches approximately on the main wing tips, the balked landing rate of climb with flaps in MID position (Figure 5-72) will be reduced by 900 ft/min. maximum. The approach speed, as compared with the flaps MID approach speed (Figure 573), must be increased by 6 KIAS. The landing distance with flaps in MID position will be increased approximately by 10%. NOTE For other information on performance in icing conditions consult the Section 5 (Performance) of this AFM. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-95 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.22 COLD WEATHER OPERATION NOTE Operation of the airplane has been demonstrated after prolonged exposure to a ground ambient temperature of –30°C (with takeoff at –24°C): this was the minimum value achieved during cold weather testing, and is not considered limiting. Other information related to cold weather operation are reported under “Operation on Contaminated Runways” paragraph which follows. PREFLIGHT Check the brakes and tires to the ground contact for freeze lock-up. Anti-ice solutions may be used on the brakes or tires if freeze-up occurs. No anti-ice solution which contains a lubricant, such as oil, should be used on the brakes. It will decrease the effectiveness of the brake friction areas. In addition to the normal preflight exterior inspection, special attention should be given to all vents, openings, control surfaces, hinge points, and wing, tail, and fuselage surfaces for accumulation of ice or snow. Removal of these accumulations is necessary prior to takeoff. Snow and ice on an airplane will seriously affect its performance. The wing contour may be sufficiently altered by the ice and snow that its lift qualities are seriously impaired. Snow may be removed with a soft brush or mop. Chipping or mechanical removal of frozen deposits is not recommended. The use of glycol based deicing fluids is recommended. Material conforming to MIL-A-8243, Anti-Icing and DeicingDefrosting Fluids, are acceptable. More information about the use of these fluids can be found in the Chapter 12 of the P.180 AVANTI Maintenance Manual. Inspect the propeller blades and hubs for ice and snow: the propellers should be turned by hand, in the direction of normal rotation, to be sure they are free to rotate prior to starting the engines. Operation of some equipments installed in the cockpit (as, for example, digital data instrumentation, stall warning computer, etc.) may be sluggish at very low temperature (typically after a cold soak). For this reason, it is recommended to perform the various preflight tests and checks, and to takeoff after approximately fifteen minutes from the environmental control system actuation. Rep. 180-MAN-0010-01100 Page 4-96 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES NOTE For low temperatures the MFD may experience a delay in displaying information including engine parameters indications. Few minutes could be required to the internal heaters to raise the MFD internal temperature to its operating value. Wait until engines parameters indications are visible on the display before commencing engine start procedure. NOTE Even if the battery installed in the airplane (nickel-cadmium, sintered plate type) gives excellent performance over a wide temperature range, in order to prevent a heavy discharge and to increase the battery life time, it is recommended to use a ground power unit, to start the engines, if the ambient temperature is lower than –15°C. To facilitate the engine start, at 13% NG advance the condition lever to the flight idle position, as long as necessary, monitoring the ITT during engine run up. NOTE During the engine start, the oil pressure may increase at a rate slower than normal. After engine start, exercise the propellers through low and high pitch, beta range, ground fine range, and into reverse range to flush any congealed oil through the system. TAKEOFF WARNING If ambient temperature is below –25°C it is necessary to operate the main wing anti-ice and the engine ice vane systems before applying full power to ensure that the autofeather is armed. When the takeoff is completed and the autofeather disengaged, the ice protection can be switched off. The micro switch which enables the operation of the autofeather, has a fixed position relative to the power lever, and, for the same lever setting, the power delivered by the engine is much more at low temperature that at high temperature. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-97 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES For this reason, during takeoff at low temperature, it will be necessary to operate the main wing anti-ice and the engine ice vane systems to be sure that the autofeather is armed. If encountering any visible moisture during takeoff, the engine anti-ice should be turned on to preclude the possibility of ice going into the engine air inlet. AFTER SHUTDOWN If the airplane is expected to be soaked at temperatures below freezing remove water and other freezable liquids from the airplane. 4.3.23 VSSE - INTENTIONAL ONE ENGINE OPERATIVE SPEED VSSE is a speed selected by the aircraft manufacturer for training pilots in the handling of multi-engine aircraft. It is the minimum speed for intentionally rendering one engine inoperative in flight. This speed provides the margin the manufacturer recommends for use when intentionally performing engine inoperative maneuvers during training. Condition levers are to be set to MAX RPM and the power lever of the simulated inoperative engine near the IDLE position: this setting approximate zero thrust at low altitude and at VSSE speed. The intentional one engine inoperative speed, VSSE, is 140 KIAS. Rep. 180-MAN-0010-01100 Page 4-98 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.24 VMCA - AIR MINIMUM CONTROL SPEED VMCA is the minimum flight speed at which a twin-engine airplane is directionally controllable as determined in accordance with the EASA/FAA Certification Regulations. Airplane certification conditions include one engine inoperative and propeller windmilling; not more than a 5° bank toward the operative engine; landing gear up; flaps in takeoff position and most rearward center of gravity. VMCA has been determined to be 100 KIAS with the propeller feathered and 128 KIAS with propeller windmilling. The demonstration and all intentional one engine operations shall be performed at a safe altitude of at least 7000 feet above the ground in clear air only. The recommended procedure for VMCA demonstration is to reduce the power approximately to idle and set the condition lever to MAX RPM on the simulated inoperative engine at or above the intentional one engine inoperative speed, VSSE. Slow down at a rate of approximately one knot per second until the VMCA, or stall warning is obtained. CAUTION Use rudder to maintain directional control and ailerons to maintain 5° bank toward the operative engine. At the first sign of either VMCA (inability to maintain heading or lateral attitude) or stall warning (aerodynamic stall buffet or stall warning horn sound) immediately initiate recovery: reduce power to idle on the operative engine and lower the nose to regain airspeed. As recovery ability is gained with practice, the starting speed may be lowered in small increments until the feel of the airplane in emergency condition is well known. It should be noted that as the speed is reduced, directional control becomes more difficult. Under no circumstances should a VMCA demonstration be attempted at a speed lower than 128 KIAS with propeller windmilling or 100 KIAS with propeller feathered. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-99 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.25 STALL CHARACTERISTICS Power off stall in all configurations, weights and centers of gravity are characterized by the reaching of minimum speed with full back control, before an aerodynamic stall with slight pitch down developing; a moderate buffet develops about 15 kts above stalling speed in clean configuration, and 10 kts above stall speed for T.O. and landing configurations. At minimum speed full aircraft control on all axes can be maintained, and recovery can be performed releasing nose up pull on longitudinal control. Altitude loss is no more than 1000 ft for a normal recovery with power application when 1.2 VS is reached. Immediate power application is possible, allowing a reduction of altitude loss. Power on stalls are characterized by extreme nose high pitch attitudes (over 30°) but handling is in other respects similar to the power off condition. Stall is again defined by a minimum speed condition with full back longitudinal control, with the aircraft fully controllable on all 3 axes, and recovery can be promptly obtained by a release of control pull. Altitude loss can be contained to no more than 500 ft with a normal recovery action. Single engine stalls are characterized by the same warning of two engine stalls. Full control of the aircraft can be achieved without reducing power on the operative engine. Altitude loss is no more than 600 ft. Rep. 180-MAN-0010-01100 Page 4-100 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.26 ROUGH AIR OPERATION The Rough Air Penetration Speed has been selected in order to reduce the stresses to which the airplane is subjected by turbulent air, still providing a safe airspeed margin above stalling as a result of turbulence. In condition of extreme turbulence, slow the airplane to Rough Air Penetration Speed of 195 KIAS at or below 25000 ft. At higher altitudes decrease this speed 5 KIAS for each 5000 ft above 25000 ft. A linear variation may be used for altitudes between 25000 ft and 41000 ft. Fly attitude (do not change trim) and avoid abrupt maneuvers. Turn ON the FASTEN SEAT BELT sign as a precaution against buffeting and lurching. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-101 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.27 OXYGEN SYSTEM Should the need arise for oxygen to be employed, the pilot and copilot masks are stowed in a recess on the left and right side of oxygen panel and the passenger masks are stored in the overhead panels. The crew need only to don their masks to start breathing oxygen. As required, the crew can select normal (N) (diluted oxygen) or 100% oxygen on the mask-mounted regulator. The presence of the green pellet in the flow indicator on each mask hose indicates that oxygen is flowing through the mask. When the cabin altitude exceeds approximately 14,000 feet, the passenger oxygen masks will automatically deploy from the overhead panels when the selector on the left side panel is set to AUTO NORMAL position. The passengers must PULL the lanyards attached to their masks to start the flow of oxygen. Inflation of the small green compartment built into the oxygen accumulator bag on the passenger masks indicates oxygen flow. Occupants should don the masks, checking the flow indicator frequently. The pilot should monitor the oxygen pressure gauge to determine oxygen supply and consumption. Passenger masks may be manually deployed by the pilot at any time by selecting the MANUAL MASK RELEASE position. WARNING Certain petroleum base substances (mustache wax, lipstick, etc.) are combustible in the presence of 100% oxygen. Donning mask set at 100% oxygen could cause burns to areas where petroleum base substances have been applied. If the 40 cu. ft. (1.13 m3) oxygen cylinder has a pressure of 1850 psi (12.76 MPa) at 70°F (21°C) when the use of oxygen is begun, oxygen will be available as listed in the following Tables. In Table 1 and 2, the duration has been calculated with the 1850 psig (12.76 MPa) cylinder (charged) discharging to 250 psig (1.72 MPa) (empty) considering that the occupants masks are in operation at the different cabin altitudes. The cylinder pressure read on the cockpit gauge indicates that there is still a 10 minutes oxygen duration before the cylinder is fully empty. Rep. 180-MAN-0010-01100 Page 4-102 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES OXYGEN DURATION - TABLE 1 FAR 91 REQUIREMENTS CREW: 1 CABIN ALTITUDE (FT.) 15000 25000 35000 40000 NUMBER OF PASSENGER 0 1 2 3 4 5 6 7 8 9 16 15 DURATION 384 102 59 41 32 26 22 19 CYL. PRESS 295 410 525 640 755 870 980 1090 1212 1325 18 DURATION 195 83 52 38 30 25 21 CYL. PRESS 335 450 560 670 780 890 1000 1110 1220 1335 16 17 15 DURATION 297 99 60 43 33 27 23 20 CYL. PRESS 310 412 520 630 735 840 950 1055 1160 1270 18 16 DURATION 417 111 64 45 35 28 24 21 CYL. PRESS 290 400 500 610 715 815 920 1028 1130 1240 16 OXYGEN DURATION - TABLE 2 CREW: 2 CABIN ALTITUDE 15000 25000 35000 40000 NUMBER OF PASSENGER (FT.) 0 1 2 3 4 5 6 7 8 9 DURATION 192 81 51 37 29 24 21 18 16 14 CYL. PRESS 335 450 565 680 795 910 1025 1240 1255 1370 DURATION 97 58 41 32 26 22 19 CYL. PRESS 415 525 640 750 860 972 1080 1195 1300 1415 17 19 15 16 14 DURATION 148 74 50 37 30 25 21 CYL. PRESS 360 470 575 680 790 895 1000 1108 1215 1330 17 15 DURATION 208 88 56 41 32 26 22 20 CYL. PRESS 330 430 540 645 750 855 960 1065 1170 1275 16 DURATION (min.):1850 psig. (12.76 MPa) charged cylinder discharging to 250 psig. (1.72 MPa) at 70°F (21°C). CYL. PRESS (psi):pressure required to have an oxygen supply of 10 minutes duration. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-103 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES The following Table 3 shows the oxygen duration for flight over 35000 ft. with a single pilot at the aircraft controls (FAR 91 requirements). In this case only one crew mask is in operation. An oxygen reserve of ten minutes duration has been considered. The cylinder pressure is the pressure read on the cockpit gauge assuring the above reserve necessary to descend from flight altitude to 12500 ft. with different number of passengers. Passenger masks are in operation only during the descent. OXYGEN DURATION - TABLE 3 OXYGEN DURATION FOR FLIGHT OVER 35000 FT. PRESSURIZED CABIN SINGLE PILOT ONE CREW MASK DISPENSING NUMBER OF PASSENGERS OXYGEN DURATION Minutes CYL. PRESS. FOR 10 MIN. 0 323 300 1 300 415 2 276 530 3 251 645 4 228 760 5 204 875 6 180 985 7 156 1100 8 132 1215 9 108 1330 DURATION (min.):calculated considering a supplemental oxygen reserve of 10 minutes. CYL. PRESS (psi):pressure assuring an oxygen reserve of 10 minutes. NOTE Crew oxygen durations are based on NORMAL (N) oxygen setting on mask-mounted regulator. Rep. 180-MAN-0010-01100 Page 4-104 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES When 50 cu.ft (1,41 m3) oxygen bottle (increased capacity as per Mod. 80-1295) or related S.B. is installed, refer to the following duration Tables: OXYGEN DURATION FOR 50 CU.FT BOTTLE - TABLE 1 FAR 91 REQUIREMENTS CREW: 1 CABIN ALTITUDE 15000 25000 35000 40000 NUMBER OF PASSENGER (FT.) 0 1 2 3 4 5 6 7 8 9 DURATION 480 127 73 51 40 32 27 23 20 18 CYL. PRESS 236 328 420 512 604 696 784 872 970 1060 DURATION 244 103 65 47 37 31 26 22 20 18 CYL. PRESS 268 360 448 536 624 712 800 888 976 1068 DURATION 371 123 75 53 41 33 28 25 21 20 CYL. PRESS 248 330 416 504 588 672 760 844 928 1016 DURATION 522 139 80 56 43 35 30 26 22 20 CYL. PRESS 232 320 400 488 572 652 736 823 904 992 8 9 17 OXYGEN DURATION FOR 50 CU.FT BOTTLE - TABLE 2 CREW: 2 CABIN ALTITUDE (FT.) 15000 25000 35000 40000 NUMBER OF PASSENGER 0 1 2 3 4 5 6 7 DURATION 240 101 63 46 36 30 26 22 20 CYL. PRESS 268 360 452 544 636 728 820 992 1004 1096 DURATION 121 72 51 40 32 27 23 21 18 CYL. PRESS 332 500 512 600 688 778 864 596 1040 1132 17 DURATION 185 92 62 46 37 31 26 23 20 18 CYL. PRESS 288 376 460 544 632 716 800 886 972 1064 DURATION 260 110 70 51 40 32 27 25 21 20 CYL. PRESS 264 344 432 416 600 684 768 852 936 1020 DURATION (min.):1850 psig. (12.76 MPa) charged cylinder discharging to 250 psig. (1.72 MPa) at 70°F (21°C). CYL. PRESS (psi):pressure required to have an oxygen supply of 10 minutes duration. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-105 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES OXYGEN DURATION FOR 50 CU.FT BOTTLE - TABLE 3 OXYGEN DURATION FOR FLIGHT OVER 35000 FT. PRESSURIZED CABIN SINGLE PILOT ONE CREW MASK DISPENSING NUMBER OF PASSENGERS OXYGEN DURATION Minutes CYL. PRESS. FOR 10 MIN. 0 404 240 1 375 332 2 345 424 3 314 516 4 285 608 5 255 700 6 225 788 7 195 880 8 165 972 9 135 1064 DURATION (min.):calculated considering a supplemental oxygen reserve of 10 minutes. CYL. PRESS (psi):pressure assuring an oxygen reserve of 10 minutes. NOTE Crew oxygen durations are based on NORMAL (N) oxygen setting on maskmounted regulator. Rep. 180-MAN-0010-01100 Page 4-106 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.28 EXTERNAL NOISE REDUCTION PROCEDURES NOTE The certificated noise levels of Section 2 (Paragraph 2.25) have been determined using normal procedures. Do not apply the External Noise Reduction procedure where it would conflict with safety or Air Traffic Control clearances or instructions and in icing conditions. Increased emphasis on improving the quality of our environment requires renewed effort on the part of all pilots to minimize the effect of airplane noise on the public. A pilot can demonstrate concern for environmental improvement by application of the procedure defined below. Approach to and departure from an airport should be made so as to avoid prolonged flight at low altitude near noise sensitive areas. Because the P.180 airplane external noise is higher at higher propellers RPM and with the flaps in full down position, the following procedures are suggested to reduce external noise. TAKEOFF 1. Perform the normal takeoff 2. Flaps - UP as soon as practical 3. Power - Reduce as practical (torque below 89.7% (2000 lb.ft)) 4. Condition levers - 1800 RPM (Check maximum torque 100% (2230 lb.ft.)) NOTE With the condition lever to 1800 RPM, the two engines rate of climb (Figure 5-26) will be reduced by 18% maximum when the power available is torque limited. BEFORE LANDING 1. Seat belts and no smoking signs - ON 2. Condition levers - 1800 RPM 3. Landing Gear (below 180 KIAS) - DN; CHECK 3 GREEN 4. (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed): SteeringCHECK armed (T/O message on PFD) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-107 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 5. Flaps (below 170 KIAS) - MID 6. Autofeather (below 150 KIAS) - ARM; CHECK LIGHT 7. Landing lights (below 160 KIAS) - AS REQUIRED 8. Autopilot/Steering - OFF 9. (Only if the airplane is NOT equipped with S.B. 80-0454 or 80-0425 (new NWSS)): Steering - OFF 10. Cabin pressure barometric condition - CHECK LANDING Prior to reaching 50 feet above landing surface: 1. Landing Gear - CHECK DN (3 green lights) 2. (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) Steering CHECK armed (T/O message on PFD) 3. Flaps - CHECK MID 4. Approach speed - Refer to Figure 5-73 at Section 5 of this Manual 5. Condition levers - CHECK 1800 RPM CAUTION If max power is required (balked landing, single engine, etc.) advance the condition levers forward to 2000 RPM then the power levers to max torque or ITT. After touchdown: 6. Brakes - AS REQUIRED 7. Reverse - AS REQUIRED engage reverse below 1700 propeller RPM, or 5% drop from the set value 8. DO NOT USE below 40 KIAS At landing completed: 9. Condition levers - GROUND IDLE 10. Steering - ENGAGE TAKE OFF (if necessary) NOTE With the condition levers to 1800 RPM the flaps MID landing distance (Figure 5-73) must be increased approximately by 20% at 10945 lbs., 30% at 8500 lbs. Rep. 180-MAN-0010-01100 Page 4-108 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.29 REDUCED VERTICAL SEPARATION MINIMA (RVSM) OPERATIONS PREPARATION FOR FLIGHT IN RVSM AIRSPACE During the pre-flight and walk-around check procedure a visual inspection of the Static Port region (RVSM Critical Region), on the Left and Right side of the fuselage, must be performed prior to all flights in RVSM airspace. In particular: a. the skin surface inside the region (refer to Figure 4-3) must be inspected for visible damage or deformation, perhaps due to walkway damage, foreign object damage, service vehicles, etc.; b. the round static plate should be checked for dimpling, damage, cracks or other surface irregularities; c. the static port orifices must be inspected for elongation, deformation and/or obstruction from foreign matter. Figure 4-3. RVSM Critical Region (Left side shown) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-109 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.30 STEEP APPROACH OPERATIONS LANDING WARNING Deliberate single engine approaches are not allowed. If engine failure occurs during a steep approach, after final descent but before MDA, or DA, make a GO AROUND and proceed to the alternate airport. If it occurs below MDA, or DA, continue and land. In case of Flap System malfunction it is necessary to proceed to the alternate airport. CAUTION Minimum altitude for initiating a go-around is 400 feet AGL or the airfield approach minimum, whichever is higher. a. The airplane must be in the appropriate flaps and landing gear configuration before glide intercept at the appropriate approach speed. CAUTION Configuration changes during approach may result in excessive path deviation requiring a go around. b. Stabilize the airplane at high rate of descent in final configuration with the aid of a suitable glide path reference system, if available. In case an external aid is not available the glide path angle can be controlled through the vertical speed indicator according to the following table: Rep. 180-MAN-0010-01100 Page 4-110 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 0 Wind 10 KTS Tail Wind 10 KTS Head Wind 20 KTS Head Wind KIAS R/D at 3° glide slope (ft/min) R/D at 5° glide slope (ft/min) R/D at 7° glide slope (ft/min) R/D at 9° glide slope (ft/min) 117 620 1030 1440 1850 121 640 1070 1490 1920 125 660 1100 1540 1980 129 680 1140 1590 2050 131 694 1156 1616 2075 117 670 1120 1570 2010 121 690 1160 1620 2075 125 715 1190 1670 2140 129 740 1230 1715 2200 131 750 1240 1740 2230 117 570 940 1320 1690 121 590 980 1370 1760 125 610 1015 1420 1820 129 630 1050 1470 1885 131 640 1068 1490 1920 117 510 860 1200 1540 121 535 890 1250 1600 125 560 930 1300 1660 129 580 960 1345 1730 131 590 980 1370 1760 Note: These values are valid in ISA sea level conditions. For airport altitude higher than sea level the rate of descent should be increased of 1.5% every 1000 ft of airport altitude. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-111 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES If the distance from the glide slope is available the following chart could be used in order to plan the descent: Figure 4-4. Altitude loss at different glide slope angles c. Adjust engine power before flare, as required. d. Flare out of high rate of descent. e. After touch-down basic normal procedures are applicable. Rep. 180-MAN-0010-01100 Page 4-112 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4.3.31 OPERATION ON CONTAMINATED RUNWAYS NOTE The level of safety is decreased when operating on contaminated runways and therefore every effort should be made to ensure that the runway surface is cleared of any significant precipitation. The provision of information for contaminated runways should not be taken as implying that ground handling characteristics on these surface will be as good as can be achieved on dry runways, in particular, in cross wind and when using reverse thrust. Certification splash tests, performed in a 50 m long, 25 m wide water bed with a water level variable up to 30 mm, have shown that droplets trajectory of the water did not affect the engines air inlets neither their operating characteristics; water spray pattern neither affected the accuracy of the airspeed system. Analysis has shown that for density of precipitations less than one (slush, wet snow, dry snow), the spray pattern generated from forward wheels, is not critical. TAXIING When possible, taxiing in deep snow, slush or water should be avoided. Under these conditions the contamination can be forced into the brake assemblies. Keep the flaps retracted during taxiing, to avoid throwing water, snow or slush into the flap mechanisms and to minimize damage to the flap surfaces, until lineup for takeoff. If ground ambient temperature is low, keep the brakes warm during taxi operation, proceed slowly and allow more clearance in maneuvering the airplane, since spotty ice cover is difficult to see. Directional control is achieved using the steering wheel and differential thrust. Applying nose-down elevator while taxiing on iced surfaces may be helpful. This loads the nose wheels and increases directional control stability. Turns must be made at reduced speed. NOTE Engine run up test performed on iced runways may cause the airplane to slip. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-113 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES TAKEOFF Before the takeoff, ensure the runway is free from hazards, such as snow drifts, glazed ice and ruts. Verify the current conditions of entire runway as closely as possible to the planned departure time. Depth of standing water, slush or snow should be measured in a sufficient number of places to be representative of the entire length of runway required, particularly at the high speed of takeoff roll. Make a special point of being sure parking brake is released before starting takeoff on an icy or snow covered runway. A moderate nose-up elevator during the takeoff ground run on contaminated runways, decreases the load on nose wheels improving the takeoff performance. If flight conditions permit, leave the landing gear extended (without braking the wheels) for a short time after takeoff to remove most of the moisture, snow or slush. LANDING NOTE If frozen brakes are suspected, when landing, carry out a positive landing to ensure wheel spin-up and breakout of frozen brakes NOTE If frozen brakes are suspected avoid touch-and-go landings Braking and steering are less effective on contaminated and/or slippery runways. Also hydroplaning may occur on contaminated runways. Use of the rudder to maintain directional control until the tires make solid contact with the runway surface may be necessary. Prior to reaching 50 ft. above landing surface: 1. Landing gear - CHECK DN (3 green lights) 2. (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) Steering CHECK armed (T/O message on PFD) 3. Flaps - CHECK DN CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID and the approach speed, as compared with the flaps MID approach speed (Figure 5-73), must be increased by 6 KIAS. Rep. 180-MAN-0010-01100 Page 4-114 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES 4. Approach speed - REFER to Section 5 of this AFM Figure 5-69 5. Power - AS REQUIRED 6. Condition levers - CHECK MAX RPM After touchdown: 7. Brakes - AS REQUIRED CAUTION Improper use of brakes at high speed and low airplane weight on wheels may cause wheel stoppage particularly on low friction runway. Use brakes at low speed if possible. 8. Reverse - Below 1900 prop RPM, or 5% drop from set value, slowly move the power levers approximately 3/4 in. back from the idle detent into the beta range; apply further reverse thrust only if required CAUTION Asymmetrical reverse thrust may be difficult to control on a slippery runway. NOTE When landing at aft C.G. initiate flaps retraction before actuating reverse power. 9. Reverse - DO NOT USE below 40 KIAS At landing completed: 10. Condition levers - GROUND IDLE 11. Steering - ENGAGE TAKE OFF (if necessary) NOTE If “TAT heater inhibition on-ground” change (ref. para 4.0) is NOT installed, a total air temperature increase may be detected until the TAT heater is turned off. If disc brakes have been exposed to moisture or water, during landing roll and subsequent taxi, use brakes to prevent progressive build-up of ice on the wheels and brakes. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 4-115 P.180 AVANTI II AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES When parking the airplane, parking brake should not be set immediately, if not necessary: chocks or sandbags can be used to prevent the airplane from rolling. Following take-off or landing on wet, snow or slush covered runways and taxiways, inspect tires for flat spots and damage. 4.3.32 P-RNAV OPERATIONS P-RNAV operations with Autopilot disengaged are allowed provided that Flight Guidance System (Fight Director) indications are followed. During P-RNAV SID (Standard Instrumental Departure) operations it is recommended to set FD in basic HDG and PITCH mode for take off with NAV armed and HDG preset value aligned with the runway to minimize the pilot workload. 4.3.33 U.S. RNAV OPERATIONS RNAV operations with Autopilot disengaged are allowed provided that Flight Guidance System (Fight Director) indications are followed. During RNAV SID (Standard Instrumental Departure) operations it is recommended to set FD in basic HDG and PITCH mode for take off with NAV armed and HDG preset value aligned with the runway to minimize the pilot workload. For GPS 4000A installation, the pilot must confirm GPS RAIM availability for the intended route in accordance with AC 90-100A. This requirement is not necessary for GPS-4000S installation if SBAS coverage is confirmed to be available along the entire route of flight. Rep. 180-MAN-0010-01100 Page 4-116 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE TABLE OF CONTENTS SECTION 5 - PERFORMANCE TABLE OF CONTENTS Paragraph No. 5.0 5.1 5.1.1 5.2 5.3 5.3.1 Page No. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-1 Introduction to Performance and Flight Planning . . . . . . . . . . . . . .5-2 Flight Planning Example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-2 Effect of Boundary Layer Degradation on Performance . . . . . . . . .5-8 Performance Graphs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-9 How to use the graphs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-9 Fig. 5-1 Temperature Conversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-10 Fig. 5-2 Feet vs. Meters Conversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11 Fig. 5-3 Inches vs. Millimeters Conversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12 Fig. 5-4 U.S. Gallons vs. Liters Conversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13 Fig. 5-5 Pounds vs. Kilograms Conversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14 Fig. 5-6 ISA Conversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-15 Fig. 5-7 Wind Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-16 Fig. 5-8 Airspeed Calibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-17 Fig. 5-9 Mach Calibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-18 Fig. 5-10 Cabin Altitude vs. Airplane Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-19 Fig. 5-11 Stall Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-20 Fig. 5-12 Buffet Onset Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-21 Fig. 5-13 Torque vs. Shaft Horsepower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-22 Fig. 5-14 Takeoff Power Torque . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-23.A Fig. 5-15 Takeoff Weight - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-24.A Fig. 5-16 Takeoff Distance over 50 feet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-25.A Fig. 5-17 Takeoff Ground Run . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-26.A Fig. 5-18 Accelerate and Go Distance over 50 feet . . . . . . . . . . . . . . . . . . . . . . . . 5-27.A Fig. 5-19 Accelerate and Stop Distance without Reverse . . . . . . . . . . . . . . . . . . . 5-28.A Fig. 5-20 Accelerate and Stop Distance with Reverse. . . . . . . . . . . . . . . . . . . . . . 5-29.A Fig. 5-21 Twin Engine Climb Torque - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . . . 5-30.A Fig. 5-22 Twin Engine Climb Fuel Flow - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . 5-31.A Fig. 5-23 Twin Engine Climb - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-32.A Fig. 5-24 Twin Engine Climb Torque - Flaps Retracted . . . . . . . . . . . . . . . . . . . . . 5-33.A Fig. 5-25 Twin Engine Climb Fuel Flow - Flaps Retracted . . . . . . . . . . . . . . . . . . . 5-34.A Fig. 5-26 Twin Engine Climb - Flaps Retracted . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-35.A Fig. 5-27 Time to Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-36.A Fig. 5-28 Fuel to Climb. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-37.A Fig. 5-29 Distance to Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-38.A Fig. 5-30 One Engine Inoperative Climb Torque - Flaps Retracted . . . . . . . . . . . . 5-39.A Fig. 5-31 One Engine Inoperative Climb Fuel Flow - Flaps Retracted . . . . . . . . . . 5-40.A Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 5-i P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE TABLE OF CONTENTS Fig. 5-32 One Engine Inoperative Climb - Flaps Retracted . . . . . . . . . . . . . . . . . . 5-41.A Fig. 5-33 One Engine Inoperative Service Ceiling - Flaps Retracted. . . . . . . . . . . 5-42.A Fig. 5-34 Maximum Cruise Power - 2000 RPM - ISA -30°C . . . . . . . . . . . . . . . . . 5-43.A Fig. 5-35 Maximum Cruise Power - 2000 RPM - ISA -20°C . . . . . . . . . . . . . . . . . 5-44.A Fig. 5-36 Maximum Cruise Power - 2000 RPM - ISA -10°C . . . . . . . . . . . . . . . . . 5-45.A Fig. 5-37 Maximum Cruise Power - 2000 RPM - ISA. . . . . . . . . . . . . . . . . . . . . . . 5-46.A Fig. 5-38 Maximum Cruise Power - 2000 RPM - ISA +10°C . . . . . . . . . . . . . . . . . 5-47.A Fig. 5-39 Maximum Cruise Power - 2000 RPM - ISA +20°C . . . . . . . . . . . . . . . . . 5-48.A Fig. 5-40 Maximum Cruise Power - 2000 RPM - ISA +30°C . . . . . . . . . . . . . . . . . 5-49.A Fig. 5-41 Recommended Cruise Power - 1800 RPM - ISA -30°C . . . . . . . . . . . . . 5-50.A Fig. 5-42 Recommended Cruise Power - 1800 RPM - ISA -20°C . . . . . . . . . . . . . 5-51.A Fig. 5-43 Recommended Cruise Power - 1800 RPM - ISA -10°C . . . . . . . . . . . . . 5-52.A Fig. 5-44 Recommended Cruise Power - 1800 RPM - ISA . . . . . . . . . . . . . . . . . . 5-53.A Fig. 5-45 Recommended Cruise Power - 1800 RPM - ISA +10°C. . . . . . . . . . . . . 5-54.A Fig. 5-46 Recommended Cruise Power - 1800 RPM - ISA +20°C. . . . . . . . . . . . . 5-55.A Fig. 5-47 Recommended Cruise Power - 1800 RPM - ISA +30°C. . . . . . . . . . . . . 5-56.A Fig. 5-48 Maximum Range Power - 2000 RPM - ISA -30°C . . . . . . . . . . . . . . . . . 5-57.A Fig. 5-49 Maximum Range Power - 2000 RPM - ISA -20°C . . . . . . . . . . . . . . . . . 5-58.A Fig. 5-50 Maximum Range Power - 2000 RPM - ISA -10°C . . . . . . . . . . . . . . . . . 5-59.A Fig. 5-51 Maximum Range Power - 2000 RPM - ISA. . . . . . . . . . . . . . . . . . . . . . . 5-60.A Fig. 5-52 Maximum Range Power - 2000 RPM - ISA +10°C . . . . . . . . . . . . . . . . . 5-61.A Fig. 5-53 Maximum Range Power - 2000 RPM - ISA +20°C . . . . . . . . . . . . . . . . . 5-62.A Fig. 5-54 Maximum Range Power - 2000 RPM - ISA +30°C . . . . . . . . . . . . . . . . . 5-63.A Fig. 5-55 Maximum Range Power - 1800 RPM - ISA -30°C . . . . . . . . . . . . . . . . . 5-64.A Fig. 5-56 Maximum Range Power - 1800 RPM - ISA -20°C . . . . . . . . . . . . . . . . . 5-65.A Fig. 5-57 Maximum Range Power - 1800 RPM - ISA -10°C . . . . . . . . . . . . . . . . . 5-66.A Fig. 5-58 Maximum Range Power - 1800 RPM - ISA. . . . . . . . . . . . . . . . . . . . . . . 5-67.A Fig. 5-59 Maximum Range Power - 1800 RPM - ISA +10°C . . . . . . . . . . . . . . . . . 5-68.A Fig. 5-60 Maximum Range Power - 1800 RPM - ISA +20°C . . . . . . . . . . . . . . . . . 5-69.A Fig. 5-61 Maximum Range Power - 1800 RPM - ISA +30°C . . . . . . . . . . . . . . . . . 5-70.A Fig. 5-62 Speed vs. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-71.A Fig. 5-63 Holding Time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-72.A Fig. 5-64 Time. Fuel, Distance to descend - 3000 FPM Rate of Descent . . . . . . . 5-73.A Fig. 5-65 Time. Fuel, Distance to descend - 1500 FPM Rate of Descent . . . . . . . 5-74.A Fig. 5-66 Best Glide Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-75.A Fig. 5-67 Balked Landing Climb Torque - Flaps DOWN . . . . . . . . . . . . . . . . . . . . 5-76.A Fig. 5-68 Balked Landing Climb - Flaps DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . 5-77.A Fig. 5-69 Landing Distance over 50 feet w/o Propeller Reversing - Flaps DOWN. 5-78.A Fig. 5-70 Landing Distance over 50 feet with Propeller Reversing - Flaps DOWN 5-79.A Fig. 5-71 Balked Landing Climb Torque - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . 5-80.A Fig. 5-72 Balked Landing Climb - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-81.A Fig. 5-73 Landing Distance over 50 feet w/o Propeller Reversing - Flaps MID . . . 5-82.A Fig. 5-74 Landing Distance over 50 feet with Propeller Reversing - Flaps MID. . . 5-83.A 5.4 Takeoff and Landing Distance on Contaminated Runways . . . .5-85.A 5.4.1 Takeoff Distance on Contaminated Runways . . . . . . . . . . . . . . . .5-87.A Rep. 180-MAN-0010-01100 Page 5-ii 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE TABLE OF CONTENTS 5.4.2 Landing Distance on Contaminated Runways . . . . . . . . . . . . . . . 5-88.A 5.4.3 Landing Distance on Icy Runways . . . . . . . . . . . . . . . . . . . . . . . . 5-90.A 5.5 Additional Performance for Category II Operations . . . . . . . . . . 5-91.A Fig. 5-75 Landing Weight - Single Engine Go Around . . . . . . . . . . . . . . . . . . . . . . 5-92.A Fig. 5-14 Takeoff Power Torque . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-23.B Fig. 5-15 Takeoff Weight - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-24.B Fig. 5-15 Takeoff Weight - Flaps MID (Gear UP) . . . . . . . . . . . . . . . . . . . . . . . . . . 5-25.B Fig. 5-16 (& 5-17) Takeoff Ground Run and Distance over 50 feet . . . . . . . . . . . . 5-27.B Fig. 5-18 Accelerate and Go Distance over 50 feet . . . . . . . . . . . . . . . . . . . . . . . . 5-29.B Fig. 5-19 Accelerate and Stop Distance without Reverse . . . . . . . . . . . . . . . . . . . 5-30.B Fig. 5-20 Accelerate and Stop Distance with Reverse. . . . . . . . . . . . . . . . . . . . . . 5-31.B Fig. 5-21 Twin Engine Climb Torque - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . . . 5-32.B Fig. 5-22 Twin Engine Climb Fuel Flow - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . 5-33.B Fig. 5-23 Twin Engine Gradient of Climb - Flaps MID . . . . . . . . . . . . . . . . . . . . . . 5-34.B Fig. 5-23/1One Engine Inoperative Takeoff Climb Torque . . . . . . . . . . . . . . . . . . . 5-35.B Fig. 5-23/2One Engine Inoperative Takeoff Climb . . . . . . . . . . . . . . . . . . . . . . . . . 5-36.B Fig. 5-24 Twin Engine en-route Climb Torque - Flaps Retracted. . . . . . . . . . . . . . 5-37.B Fig. 5-25 Twin Engine Climb Fuel Flow - Flaps Retracted . . . . . . . . . . . . . . . . . . . 5-38.B Fig. 5-26 Twin Engine en-route Rate of Climb/Descent - Flaps Retracted . . . . . . 5-39.B Fig. 5-26 Twin Engine En-route Gradient of Climb/Descent . . . . . . . . . . . . . . . . . 5-40.B Fig. 5-27 Time to Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-41.B Fig. 5-28 Fuel to Climb. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-42.B Fig. 5-29 Distance to Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-43.B Fig. 5-30 One Engine Inoperative en-route Climb/Descent Torque . . . . . . . . . . . . 5-44.B Fig. 5-31 One Engine Inoperative Climb Fuel Flow - Flaps Retracted . . . . . . . . . . 5-45.B Fig. 5-32 One Engine Inoperative en-route Rate of Climb/Descent. . . . . . . . . . . . 5-46.B Fig. 5-32/1One Engine Inoperative en-route Gradient of Climb/Descent . . . . . . . . 5-47.B Fig. 5-33 One Engine Inoperative Service Ceiling - Flaps Retracted. . . . . . . . . . . 5-48.B Fig. 5-34 Maximum Cruise Power - 2000 RPM - ISA -30°C . . . . . . . . . . . . . . . . . 5-49.B Fig. 5-35 Maximum Cruise Power - 2000 RPM - ISA -20°C . . . . . . . . . . . . . . . . . 5-50.B Fig. 5-36 Maximum Cruise Power - 2000 RPM - ISA -10°C . . . . . . . . . . . . . . . . . 5-51.B Fig. 5-37 Maximum Cruise Power - 2000 RPM - ISA. . . . . . . . . . . . . . . . . . . . . . . 5-52.B Fig. 5-38 Maximum Cruise Power - 2000 RPM - ISA +10°C . . . . . . . . . . . . . . . . . 5-53.B Fig. 5-39 Maximum Cruise Power - 2000 RPM - ISA +20°C . . . . . . . . . . . . . . . . . 5-54.B Fig. 5-40 Maximum Cruise Power - 2000 RPM - ISA +30°C . . . . . . . . . . . . . . . . . 5-55.B Fig. 5-41 Recommended Cruise Power - 1800 RPM - ISA -30°C . . . . . . . . . . . . . 5-56.B Fig. 5-42 Recommended Cruise Power - 1800 RPM - ISA -20°C . . . . . . . . . . . . . 5-57.B Fig. 5-43 Recommended Cruise Power - 1800 RPM - ISA -10°C . . . . . . . . . . . . . 5-58.B Fig. 5-44 Recommended Cruise Power - 1800 RPM - ISA . . . . . . . . . . . . . . . . . . 5-59.B Fig. 5-45 Recommended Cruise Power - 1800 RPM - ISA +10°C. . . . . . . . . . . . . 5-60.B Fig. 5-46 Recommended Cruise Power - 1800 RPM - ISA +20°C. . . . . . . . . . . . . 5-61.B Fig. 5-47 Recommended Cruise Power - 1800 RPM - ISA +30°C. . . . . . . . . . . . . 5-62.B Fig. 5-48 Maximum Range Power - 2000 RPM - ISA -30°C . . . . . . . . . . . . . . . . . 5-63.B Fig. 5-49 Maximum Range Power - 2000 RPM - ISA -20°C . . . . . . . . . . . . . . . . . 5-64.B Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 1105-2999 Rep. 180-MAN-0010-01100 Page 5-iii P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE TABLE OF CONTENTS Fig. 5-50 Maximum Range Power - 2000 RPM - ISA -10°C . . . . . . . . . . . . . . . . . 5-65.B Fig. 5-51 Maximum Range Power - 2000 RPM - ISA. . . . . . . . . . . . . . . . . . . . . . . 5-66.B Fig. 5-52 Maximum Range Power - 2000 RPM - ISA +10°C . . . . . . . . . . . . . . . . . 5-67.B Fig. 5-53 Maximum Range Power - 2000 RPM - ISA +20°C . . . . . . . . . . . . . . . . . 5-68.B Fig. 5-54 Maximum Range Power - 2000 RPM - ISA +30°C . . . . . . . . . . . . . . . . . 5-69.B Fig. 5-55 Maximum Range Power - 1800 RPM - ISA -30°C . . . . . . . . . . . . . . . . . 5-70.B Fig. 5-56 Maximum Range Power - 1800 RPM - ISA -20°C . . . . . . . . . . . . . . . . . 5-71.B Fig. 5-57 Maximum Range Power - 1800 RPM - ISA -10°C . . . . . . . . . . . . . . . . . 5-72.B Fig. 5-58 Maximum Range Power - 1800 RPM - ISA. . . . . . . . . . . . . . . . . . . . . . . 5-73.B Fig. 5-59 Maximum Range Power - 1800 RPM - ISA +10°C . . . . . . . . . . . . . . . . . 5-74.B Fig. 5-60 Maximum Range Power - 1800 RPM - ISA +20°C . . . . . . . . . . . . . . . . . 5-75.B Fig. 5-61 Maximum Range Power - 1800 RPM - ISA +30°C . . . . . . . . . . . . . . . . . 5-76.B Fig. 5-62 Speed vs. Altitude (for PT6A-66 engines only) . . . . . . . . . . . . . . . . . . . 5-77.B Fig. 5-63 Holding Time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-78.B Fig. 5-64 Time. Fuel, Distance to descend - 3000 FPM Rate of Descent . . . . . . . 5-79.B Fig. 5-65 Time. Fuel, Distance to descend - 1500 FPM Rate of Descent . . . . . . . 5-80.B Fig. 5-66 Best Glide Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-81.B Fig. 5-67 Balked Landing Climb Torque - Flaps DOWN . . . . . . . . . . . . . . . . . . . . 5-82.B Fig. 5-68 Balked Landing Rate of Climb - Flaps DOWN . . . . . . . . . . . . . . . . . . . . 5-83.B Fig. 5-69 Landing Distance over 50 feet w/o Propeller Reversing - Flaps DN . . . . 5-84.B Fig. 5-70 Landing Distance over 50 feet with Propeller Reversing - Flaps DN . . . 5-85.B Fig. 5-71 Balked Landing Climb Torque - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . 5-86.B Fig. 5-72 Balked Landing Rate of Climb - Flaps MID . . . . . . . . . . . . . . . . . . . . . . . 5-87.B Fig. 5-73 Landing Distance over 50 feet w/o Propeller Reversing - Flaps MID . . . 5-88.B Fig. 5-74 Landing Distance over 50 feet with Propeller Reversing - Flaps MID. . . 5-89.B 5.4 Takeoff and Landing Distance on Contaminated Runways . . . .5-91.B 5.4.1 Takeoff Distance on Contaminated Runways . . . . . . . . . . . . . . . .5-93.B 5.4.2 Landing Distance on Contaminated Runways . . . . . . . . . . . . . . .5-94.B 5.4.3 Landing Distance on Icy Runways . . . . . . . . . . . . . . . . . . . . . . . .5-96.B 5.5 Additional Performance for Category II Operations . . . . . . . . . .5-97.B Fig. 5-75 Landing Weight - Single Engine Go Around . . . . . . . . . . . . . . . . . . . . . . 5-98.B Rep. 180-MAN-0010-01100 Page 5-iv 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE GENERAL SECTION 5 - PERFORMANCE 5.0 GENERAL This section provides all of the required (EASA and FAA regulations) and complementary performance information applicable to the airplane. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-1 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING 5.1 INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING The performance information in this section is based on calculations and design data. Effects of conditions not considered on the charts must be evaluated by the pilot. Tabulated performance information is presented in increments of temperature, altitude and any other variables involved. To obtain exact performance values from tables, it is necessary to linearly interpolate between the incremental values. The information provided in "Flight Planning Example" paragraph outlines a detailed flight plan using the performance charts in this section. Each chart includes its own example to show how it is used. 5.1.1 FLIGHT PLANNING EXAMPLE The following Flight Planning Example illustrates the correct utilization of pertinent data presented in this section. a. Associated Conditions Basic information such as departure and destination airport conditions, enroute conditions, basic airplane conditions and factors such as weather, status of the runway, distance of the flight, number of passengers, etc., are known when planning a flight. Assume, for example, the following conditions: 1. Departure Airport Conditions Static Air Temperature Pressure Altitude Wind and Direction Runway Direction 19°C 3000 ft. 20 kts and 120° 170° 2. Cruise Conditions Static Air Temperature Pressure Altitude Enroute Distance Power Setting -44°C 35,000 ft. 800 naut. mi. Maximum Cruise (2000 RPM) 3. Destination Airport Conditions Static Air Temperature Pressure Altitude Wind and Direction Runway Direction Rep. 180-MAN-0010-01100 Page 5-2 17°C 4000 ft. 13 kts and 80° 120° Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING 4. Airplane Configuration Basic Weight (Assumed) Fuel Tanks Occupants Baggage 7370 lbs. 303 gal. 5 at 170 lbs. each 200 lbs. b. Airplane Loading Use the information given in the Weight and Balance Manual to determine the airplane weight and center of gravity. After proper utilization of the information provided, assume the following weights have been determined for consideration in the Flight Planning Example: 1. Basic Weight 7370 lbs. 2. Occupants(5 at 170 lbs. each) 850 lbs. 3. Baggage 200 lbs. 4. Fuel (303 gal at 6.7 lbs./gal.) 2030 lbs. 5. Ramp Weight (total of above) 10450 lbs. 6. Landing Weight (Takeoff Weight minus Total Fuel Required) 9117 lbs. The landing weight cannot be determined until the weight of the fuel to be used has been established. Check the ramp weight is below the approved maximum. Determine that weight and balance calculations have shown the C.G. position to be within the approved limits. c. Takeoff Distance Conditions of the departure airport and takeoff weight should be applied to the appropriate Takeoff Distance graph to determine the length of runway necessary. Takeoff conditions for the Flight Planning Example are listed below: 1. Wind 20 kts 2. Angle between Flight Path and Wind 50° 3. Head Wind Component (from Wind Component Graph) 13 kts 4. Static Air Temperature 19°C 5. Pressure Altitude 3000 ft. 6. Takeoff Weight (Ramp Weight – Fuel for Taxi) (10450 – 50) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 10400 lbs. Rep. 180-MAN-0010-01100 Page 5-3 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING Using the Normal Takeoff over 50 feet graph the takeoff distances are as follows: 1. Total Distance 2910 ft. 2. Ground Run 1970 ft. d. Climb Entering the example conditions of the departure airport and the cruise altitude into the Time, Fuel and Distance to Climb graph yields the following: 1. Time to Climb 17 minutes 2. Fuel to Climb 208 lbs. 3. Distance to Climb 66 naut. mi. The effect of winds aloft must be considered by the pilot when computing climb, cruise, and descent performance. e. Descent Entering the cruise and destination airport conditions into the Time, Fuel and Distance to Descend graph yields the following: 1. Rate of Descent 3000 FPM 2. Time to Descend 11 minutes 3. Fuel to Descend 67 lbs. 4. Distance to Descend Rep. 180-MAN-0010-01100 Page 5-4 58 naut. mi. Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING f. Cruise The total cruise distance can be obtained by subtracting the previously calculated distance to climb and distance to descend from the total enroute distance. For example: Cruise Distance = Enroute Distance – Climb Distance – Descent Distance = 800 – 66 – 58 = 676 nautical miles From Pressure Altitude vs SAT Chart and Power Setting Table for Maximum Cruise (2000 RPM, ISA +10° C) the cruise airspeeds are 358 knots at 10000 lbs. and 364 knots at 9000 lbs. Extrapolating these values for 9700 lbs. (estimated average cruise weight), the cruise speed is 360 knots. From the same table, Fuel Flow is 536 lbs./hr. (total) Cruise time and fuel may be calculated as follows: Cruise Time = Cruise Distance/Cruise Speed = 676/360 = 1.88 hours or 113 minutes Cruise Fuel = Fuel Flow x Cruise Time = 536 x 1.88 = 1008 lbs. The above data can be used to verify the estimated average cruise weight as follows: Average Cruise Weight = Ramp Weight – (Fuel for Taxi and Takeoff + Climb Fuel) – Cruise Fuel/2 = 10450 – (50 + 208) – 1008/2 = 9688 lbs. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-5 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING From the Power Setting Table, the cruise speed is 360 knots for 9688 lbs. Applying the above cruise time and cruise fuel formula results in the following figures: Cruise Time = 1.88 hours or 113 minutes Cruise Fuel = 536 x 1.88 = 1008 lbs. g. Total Flight Time The total flight time is determined by adding the time to climb, cruise time, and time to descend. The following flight time is required for this Flight Planning Example: Total Flight Time = Time to Climb + Cruise Time + Time to Descend = 17 + 113 + 11 = 141 minutes h. Total Fuel Required The total fuel required can be determined by adding fuel for taxi and takeoff, fuel to climb, cruise fuel, and fuel to descend. The determined total fuel in pounds, divided by 6.7 will give the total fuel in gallons to be used for the flight. Total Fuel Required = Fuel for taxi and takeoff + Fuel to climb + Cruise fuel + Fuel to descend = 50 + 208 + 1008 + 67 = 1333 lbs. (200 gallons) Rep. 180-MAN-0010-01100 Page 5-6 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING i. Landing Distance Subtracting the total fuel required from the takeoff weight of the airplane gives the landing weight: Landing Weight = Ramp Weight – Total Fuel Required = 10450 – 1333 = 9117 lbs. Destination airport conditions applied to the Wind Component graph gives the following head wind component for the Flight Planning Example: The angle between the flight path and wind is 120° – 80° = 40°. Therefore, the Head Wind Component is 10 knots. From the Landing Distance over 50 Feet (with Reversing) graph with the destination airport conditions, the distances required for landing for the Flight Planning Example are as follows: 1. Total Distance 2435 ft. 2. Total Roll 1425 ft. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-7 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE EFFECT OF BOUNDARY LAYER DEGRADATION ON PERFORMANCE 5.2 EFFECT OF BOUNDARY LAYER DEGRADATION ON PERFORMANCE This airplane is characterized by extensive natural laminar flow over the forward and main wings. Insect debris, dirt in general or rain, may force the boundary layer to become turbulent prematurely and the performances are affected by the loss of laminar flow. The extension of laminar flow as function of the surface contamination is very difficult to determine; however, loss of performance, substantiated by flight test data, relative to the condition of fully turbulent flow from five percent of the chord, are indicated, if significant, in each performance graph or table contained in this section. Rep. 180-MAN-0010-01100 Page 5-8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS 5.3 5.3.1 PERFORMANCE GRAPHS HOW TO USE THE GRAPHS a. A reference line indicates where to begin following the guidelines. Always project to the reference line first, then follow the guidelines to the next known item by maintaining the same PROPORTIONAL DISTANCE between the guideline above and guideline below the projected line. For instance, if the projected line intersects the reference line in the ratio of 30% down/70% up between the guidelines, then maintain this same 30%/70% relationship between the guidelines all the way to the next known item or answer. b. The associated conditions define the specific conditions from which performance parameters have been determined. They are not intended to be used as instructions; however, performance values determined from charts can only be achieved if the specified conditions exist. c. Notes have been provided to approximate performance with the anti-ice systems on and no ice accretion on the unprotected parts. The effect will vary, depending upon airspeed, temperature and altitude. At lower altitudes, where operation on the torque limit is possible, the effect of turning the anti-ice systems on will be less, depending upon how much power can be recovered without exceeding the ITT or torque limits. d. The takeoff and landing performance contained in this Section was obtained using the procedures outlined in Section 4 of this Airplane Flight Manual. The takeoff and accelerate-stop graphs are based on the power value obtained from the associated TAKEOFF POWER graph. Torque was allowed to increase with increasing airspeed. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-9 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-1. Temperature Conversion Rep. 180-MAN-0010-01100 Page 5-10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-2. Feet vs. Meters Conversion Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-11 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-3. Inches vs. Millimeters Conversion Rep. 180-MAN-0010-01100 Page 5-12 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-4. U.S. Gallons vs. Liters Conversion Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-13 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-5. Pounds vs. Kilograms Conversion Rep. 180-MAN-0010-01100 Page 5-14 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-6. ISA Conversion Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-15 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-7. Wind Components Rep. 180-MAN-0010-01100 Page 5-16 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS NOTE When the alternate static air source is selected, add 1.5 KIAS (value valid for zero sideslip) to the graph. Figure 5-8. Airspeed Calibration Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-17 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS NOTE When the alternate static air source is selected, add 0.006 (value valid for zero sideslip) to the graph. Figure 5-9. Mach Calibration Rep. 180-MAN-0010-01100 Page 5-18 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-10. Cabin Altitude vs. Airplane Altitude Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-19 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-11. Stall Speed Rep. 180-MAN-0010-01100 Page 5-20 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-12. Buffet Onset Limits Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-21 P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-13. Torque vs. Shaft Horsepower Rep. 180-MAN-0010-01100 Page 5-22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS NOTE Torque limit of 96.4% (2150 lb.ft) is the static value to be applied for takeoff in order to obtain the normal 100% (2230 lb.ft) at takeoff speed for ram effect during the takeoff run. Figure 5-14. Takeoff Power Torque Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-23 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-15. Takeoff Weight - Flaps MID Rep. 180-MAN-0010-01100 Page 5-24 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-16. Takeoff Distance over 50 feet Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-25 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-17. Takeoff Ground Run Rep. 180-MAN-0010-01100 Page 5-26 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-18. Accelerate and Go Distance over 50 feet Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-27 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-19. Accelerate and Stop Distance without Reverse Rep. 180-MAN-0010-01100 Page 5-28 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-20. Accelerate and Stop Distance with Reverse Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-29 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-21. Twin Engine Climb Torque - Flaps MID Rep. 180-MAN-0010-01100 Page 5-30 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-22. Twin Engine Climb Fuel Flow - Flaps MID Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-31 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-23. Twin Engine Climb - Flaps MID Rep. 180-MAN-0010-01100 Page 5-32 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-24. Twin Engine Climb Torque - Flaps Retracted Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-33 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-25. Twin Engine Climb Fuel Flow - Flaps Retracted Rep. 180-MAN-0010-01100 Page 5-34 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-26. Twin Engine Climb - Flaps Retracted Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-35 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-27. Time to Climb Rep. 180-MAN-0010-01100 Page 5-36 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-28. Fuel to Climb Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-37 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-29. Distance to Climb Rep. 180-MAN-0010-01100 Page 5-38 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-30. One Engine Inoperative Climb Torque - Flaps Retracted Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-39 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-31. One Engine Inoperative Climb Fuel Flow - Flaps Retracted Rep. 180-MAN-0010-01100 Page 5-40 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-32. One Engine Inoperative Climb - Flaps Retracted Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-41 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-33. One Engine Inoperative Service Ceiling - Flaps Retracted Rep. 180-MAN-0010-01100 Page 5-42 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 5 - PERFORMANCE PERFORMANCE PERFORMANCE GRAPHS 5.0 PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA -30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. FEET °C °F % 0 -15 5 65.0 TOTAL FUEL FLOW LBS/HR LBS/HR 448 AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 244 260 244 260 244 260 896 5000 -25 -13 69.9 418 836 262 260 262 260 262 260 10000 -35 -31 74.4 393 786 281 260 281 260 281 260 15000 -45 -48 78.9 374 748 302 260 302 260 302 260 20000 -55 -66 82.9 362 724 325 260 325 260 325 260 23000 -61 -77 85.9 361 722 340 260 340 260 340 260 25000 -65 -84 88.5 362 724 350 260 350 260 350 260 27000 -68 -91 91.4 368 736 361 260 361 260 361 260 28000 -70 -95 93.1 373 746 366 260 366 260 366 260 29000 -72 -98 91.2 366 732 367 256 367 256 367 256 31000 -76 -106 84.7 342 684 363 245 363 245 363 245 33000 -80 -113 78.6 321 642 360 234 360 234 360 234 35000 -84 -120 73.0 301 602 356 223 356 223 356 223 37000 -86 -123 68.3 284 568 354 213 354 213 354 213 39000 -86 -123 64.3 271 542 354 203 354 203 354 203 41000 -86 -123 60.7 259 518 354 194 354 194 354 194 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-34. Maximum Cruise Power - 2000 RPM - ISA -30°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-43 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA -20°C PRESS. ALT. FEET SAT ENG. FUEL TORQUE FLOW PER ENG. °C °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 -5 23 66.3 454 908 249 260 249 260 249 260 5000 -15 5 71.3 425 850 267 260 267 260 267 260 10000 -25 -13 76.0 401 802 286 260 286 260 286 260 15000 -35 -30 80.6 382 764 308 260 308 260 308 260 20000 -45 -48 84.8 370 740 332 260 332 260 332 260 23000 -51 -59 87.9 370 740 348 260 348 260 348 260 25000 -55 -66 90.6 372 744 358 260 358 260 358 260 27000 -58 -73 93.6 379 758 370 260 370 260 370 260 28000 -60 -77 95.3 384 768 375 260 375 260 375 260 29000 -62 -80 93.5 377 754 376 256 376 256 376 256 31000 -66 -88 86.8 353 706 373 245 373 245 373 245 33000 -70 -95 80.6 331 662 369 234 369 234 369 234 35000 -74 -102 75.0 311 622 365 223 365 223 365 223 37000 -76 -105 70.1 293 586 363 213 363 213 363 213 39000 -76 -105 66.0 279 558 363 203 363 203 363 203 41000 -76 -105 56.8 246 492 351 187 357 190 363 194 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-35. Maximum Cruise Power - 2000 RPM - ISA -20°C Rep. 180-MAN-0010-01100 Page 5-44 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA -10°C PRESS. ALT. FEET SAT ENG. FUEL TORQUE FLOW PER ENG. °C °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 5 41 67.5 460 920 253 260 253 260 253 260 5000 -5 23 72.6 432 864 272 260 272 260 272 260 10000 -15 5 77.5 410 820 292 260 292 260 292 260 15000 -25 -12 82.2 392 784 315 260 315 260 315 260 20000 -35 -30 86.6 381 762 339 260 339 260 339 260 23000 -41 -41 89.9 381 762 355 260 355 260 355 260 25000 -45 -48 92.6 383 766 366 260 366 260 366 260 27000 -48 -55 95.8 391 782 378 260 378 260 378 260 28000 -50 -59 97.6 396 792 384 260 384 260 384 260 29000 -52 -62 95.7 389 778 385 256 385 256 385 256 31000 -56 -70 88.9 364 728 381 245 381 245 381 245 33000 -60 -77 82.6 341 682 378 234 378 234 378 234 35000 -64 -84 75.8 317 634 373 222 374 223 374 223 37000 -66 -87 67.1 285 570 363 207 369 211 373 213 39000 -66 -87 57.0 249 498 349 189 355 193 361 197 41000 -66 -87 48.6 218 436 – – 341 176 348 180 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-36. Maximum Cruise Power - 2000 RPM - ISA -10°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-45 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA PRESS. ALT. SAT FEET °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 15 59 68.7 468 936 258 260 258 260 258 260 5000 5 41 73.9 442 884 277 260 277 260 277 260 10000 -5 23 79.0 419 838 298 260 298 260 298 260 15000 -15 6 83.9 401 802 321 260 321 260 321 260 20000 -25 -12 88.4 391 782 346 260 346 260 346 260 23000 -31 -23 91.8 391 782 363 260 363 260 363 260 25000 -35 -30 94.6 394 788 374 260 374 260 374 260 27000 -38 -37 97.9 401 802 386 260 386 260 386 260 28000 -40 -41 94.7 390 780 386 255 389 257 392 259 29000 -42 -44 90.5 374 748 383 249 386 251 390 253 31000 -46 -52 82.6 345 690 377 236 382 239 385 241 33000 -50 -59 74.9 318 636 370 223 375 226 380 230 35000 -54 -66 67.7 291 582 363 211 368 214 374 217 37000 -56 -69 59.2 260 520 351 195 357 199 363 202 39000 -56 -69 50.5 228 456 335 177 343 181 350 186 41000 -56 -69 42.5 199 398 – – – – 335 168 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-37. Maximum Cruise Power - 2000 RPM - ISA Rep. 180-MAN-0010-01100 Page 5-46 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA +10°C PRESS. ALT. FEET SAT °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 25 77 69.9 477 954 262 260 262 260 262 260 5000 15 59 75.2 452 904 282 260 282 260 282 260 10000 5 41 80.4 430 860 303 260 303 260 303 260 15000 -5 24 85.5 413 826 327 260 327 260 327 260 20000 -15 6 90.1 401 802 353 260 353 260 353 260 23000 -21 -5 93.7 401 802 370 260 370 260 370 260 25000 -25 -12 96.6 403 806 382 260 382 260 382 260 27000 -28 -19 90.4 379 758 381 250 384 252 387 254 28000 -30 -23 86.5 364 728 379 244 382 246 385 248 29000 -32 -26 82.6 350 700 376 238 379 240 383 243 31000 -36 -34 74.9 322 644 369 225 374 229 378 231 33000 -40 -41 67.5 295 590 361 212 367 216 372 219 35000 -44 -48 60.3 268 536 351 198 358 202 364 206 37000 -46 -51 52.8 240 480 338 183 346 187 353 191 39000 -46 -51 44.8 210 420 – – 329 169 338 174 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-38. Maximum Cruise Power - 2000 RPM - ISA +10°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-47 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA +20°C PRESS. ALT. FEET SAT °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 35 95 71.0 489 978 267 260 267 260 267 260 5000 25 77 76.5 464 928 287 260 287 260 287 260 10000 15 59 81.8 441 882 309 260 309 260 309 260 15000 5 42 87.0 423 846 333 260 333 260 333 260 20000 -5 24 91.8 411 822 360 260 360 260 360 260 23000 -11 13 95.0 408 816 377 259 377 260 377 260 25000 -15 6 87.9 378 756 374 248 377 250 379 252 27000 -18 -1 80.5 350 700 370 237 373 239 376 241 28000 -20 -5 76.9 336 672 367 231 370 233 374 236 29000 -22 -8 73.3 323 646 365 225 368 228 371 230 31000 -26 -16 66.3 296 592 357 212 362 216 366 218 33000 -30 -23 59.3 270 540 347 199 353 203 359 206 35000 -34 -30 53.2 247 494 336 185 344 190 351 194 37000 -36 -33 46.7 221 442 319 168 331 174 340 180 39000 -36 -33 38.8 192 384 – – – – 317 159 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-39. Maximum Cruise Power - 2000 RPM - ISA +20°C Rep. 180-MAN-0010-01100 Page 5-48 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA +30°C PRESS. ALT. FEET SAT ENG. FUEL TORQUE FLOW PER ENG. °C °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 45 113 72.2 500 1000 271 260 271 260 271 260 5000 35 95 77.8 475 950 291 260 291 260 291 260 10000 25 77 83.3 452 904 314 260 314 260 314 260 15000 15 60 88.6 432 864 339 260 339 260 339 260 20000 5 42 88.4 402 804 359 254 360 255 361 256 23000 -1 31 80.0 363 726 357 240 360 242 361 243 25000 -5 24 73.9 337 674 354 230 357 232 360 234 27000 -8 17 67.2 311 622 349 218 352 221 356 223 28000 -10 13 63.9 298 596 345 212 349 215 353 217 29000 -12 10 60.6 285 570 341 206 346 209 350 211 31000 -16 2 53.9 259 518 329 191 338 196 342 199 33000 -20 -5 48.4 237 474 315 176 327 183 336 188 35000 -24 -12 43.2 216 432 291 156 314 169 326 176 37000 -26 -15 38.3 195 390 – – – – 306 157 39000 – – – – – – – – – – – 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-40. Maximum Cruise Power - 2000 RPM - ISA +30°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-49 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA -30°C PRESS. ALT. FEET SAT °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 -15 5 72.7 443 886 244 260 244 260 244 260 5000 -25 -13 78.6 415 830 262 260 262 260 262 260 10000 -35 -31 83.3 390 780 281 260 281 260 281 260 15000 -45 -48 87.6 370 740 302 260 302 260 302 260 20000 -55 -66 91.8 359 718 325 260 325 260 325 260 23000 -61 -77 95.4 359 718 340 260 340 260 340 260 25000 -65 -84 98.6 362 724 350 260 350 260 350 260 27000 -68 -91 100.0 364 728 358 257 361 260 361 260 28000 -70 -95 100.0 364 728 361 255 364 258 366 260 29000 -72 -98 100.0 363 726 364 253 367 256 367 256 31000 -76 -106 94.3 344 688 363 245 363 245 363 245 33000 -80 -113 86.5 319 638 360 234 360 234 360 234 35000 -84 -120 79.4 296 592 356 223 356 223 356 223 37000 -86 -123 73.2 276 552 354 213 354 213 354 213 39000 -86 -123 68.0 260 520 354 203 354 203 354 203 41000 -86 -123 63.3 245 490 354 194 354 194 354 194 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-41. Recommended Cruise Power - 1800 RPM - ISA -30°C Rep. 180-MAN-0010-01100 Page 5-50 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA -20°C PRESS. ALT. FEET SAT ENG. FUEL TORQUE FLOW PER ENG. °C °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 0 -5 23 74.1 449 898 249 260 249 260 249 260 5000 -15 5 80.1 422 844 267 260 267 260 267 260 10000 -25 -13 85.0 398 796 286 260 286 260 286 260 15000 -35 -30 89.5 379 758 308 260 308 260 308 260 20000 -45 -48 93.9 368 736 332 260 332 260 332 260 23000 -51 -59 97.6 369 738 348 260 348 260 348 260 25000 -55 -66 100.0 371 742 357 259 358 260 358 260 27000 -58 -73 100.0 368 736 364 255 367 257 370 260 28000 -60 -77 100.0 368 736 367 253 370 256 373 258 29000 -62 -80 100.0 367 734 370 251 373 254 376 256 31000 -66 -88 96.6 356 712 373 245 373 245 373 245 33000 -70 -95 88.7 330 660 369 234 369 234 369 234 35000 -74 -102 81.5 306 612 365 223 365 223 365 223 37000 -76 -105 75.2 285 570 363 213 363 213 363 213 39000 -76 -105 69.2 267 534 362 202 363 203 363 203 41000 -76 -105 59.1 234 468 342 182 352 187 358 191 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-42. Recommended Cruise Power - 1800 RPM - ISA -20°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-51 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA -10°C PRESS. ALT. FEET SAT °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 5 41 75.4 454 908 253 260 253 260 253 260 5000 -5 23 81.7 429 858 272 260 272 260 272 260 10000 -15 5 86.7 407 814 292 260 292 260 292 260 15000 -25 -12 91.3 389 778 315 260 315 260 315 260 20000 -35 -30 95.9 379 758 339 260 339 260 339 260 23000 -41 -41 99.8 381 762 355 260 355 260 355 260 25000 -45 -48 100.0 375 750 362 257 365 259 366 260 27000 -48 -55 100.0 373 746 369 253 372 255 375 258 28000 -50 -59 100.0 372 744 372 251 375 253 379 256 29000 -52 -62 100.0 371 742 375 249 379 251 382 254 31000 -56 -70 94.9 354 708 376 241 379 243 381 245 33000 -60 -77 86.7 327 654 371 229 375 232 378 234 35000 -64 -84 78.9 301 602 365 218 370 220 373 223 37000 -66 -87 69.6 271 542 355 202 361 206 366 209 39000 -66 -87 59.2 237 474 334 181 344 187 352 191 41000 -66 -87 50.3 207 414 – – 324 167 336 174 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-43. Recommended Cruise Power - 1800 RPM - ISA -10°C Rep. 180-MAN-0010-01100 Page 5-52 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA PRESS. ALT. SAT FEET °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 15 59 76.8 462 924 258 260 258 260 258 260 5000 5 41 83.1 439 878 277 260 277 260 277 260 10000 -5 23 88.4 417 834 298 260 298 260 298 260 15000 -15 6 93.1 399 798 321 260 321 260 321 260 20000 -25 -12 97.9 389 778 346 260 346 260 346 260 23000 -31 -23 100.0 386 772 360 258 363 260 363 260 25000 -35 -30 100.0 380 760 367 254 370 257 373 258 27000 -38 -37 100.0 377 754 374 251 377 253 381 256 28000 -40 -41 98.5 371 742 375 247 379 250 383 253 29000 -42 -44 94.2 357 714 373 241 377 244 381 247 31000 -46 -52 85.9 329 658 367 229 371 232 376 235 33000 -50 -59 77.9 303 606 360 216 365 220 370 223 35000 -54 -66 70.2 277 554 351 203 358 207 364 211 37000 -56 -69 61.4 248 496 336 186 346 192 353 196 39000 -56 -69 52.3 217 434 312 164 326 172 338 178 41000 -56 -69 43.6 188 376 – – – – 316 158 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-44. Recommended Cruise Power - 1800 RPM - ISA Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-53 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA +10°C PRESS. ALT. FEET SAT °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 25 77 78.1 472 944 262 260 262 260 262 260 5000 15 59 84.6 450 900 282 260 282 260 282 260 10000 5 41 90.0 428 856 303 260 303 260 303 260 15000 -5 24 94.9 410 820 327 260 327 260 327 260 20000 -15 6 99.9 400 800 353 260 353 260 353 260 23000 -21 -5 100.0 390 780 365 256 368 258 369 259 25000 -25 -12 100.0 383 766 372 252 375 255 378 256 27000 -28 -19 94.2 363 726 371 243 375 246 379 248 28000 -30 -23 90.0 349 698 368 237 372 240 376 243 29000 -32 -26 85.9 335 670 366 231 370 234 374 237 31000 -36 -34 77.8 307 614 358 218 364 222 368 225 33000 -40 -41 69.9 281 562 348 204 355 209 362 213 35000 -44 -48 62.2 255 510 335 189 345 194 353 199 37000 -46 -51 54.7 229 458 317 171 330 178 341 184 39000 -46 -51 46.0 199 398 – – 306 157 322 165 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-45. Recommended Cruise Power - 1800 RPM - ISA +10°C Rep. 180-MAN-0010-01100 Page 5-54 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA +20°C PRESS. ALT. FEET SAT °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 35 95 79.4 484 968 267 260 267 260 267 260 5000 25 77 86.1 462 924 287 260 287 260 287 260 10000 15 59 91.6 440 880 309 260 309 260 309 260 15000 5 42 96.7 421 842 333 260 333 260 333 260 20000 -5 24 100.0 405 810 358 258 359 259 360 260 23000 -11 13 99.6 393 786 369 253 372 256 373 257 25000 -15 6 92.2 364 728 366 243 369 245 372 247 27000 -18 -1 84.3 337 674 361 231 364 233 368 236 28000 -20 -5 80.6 324 648 358 225 362 228 366 230 29000 -22 -8 76.8 311 622 355 219 359 222 363 225 31000 -26 -16 69.3 285 570 345 205 353 210 357 213 33000 -30 -23 61.7 259 518 332 190 342 196 350 201 35000 -34 -30 55.7 237 474 318 175 330 182 341 188 37000 -36 -33 48.7 212 424 295 155 313 165 327 172 39000 -36 -33 39.7 182 364 – – – – 299 150 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-46. Recommended Cruise Power - 1800 RPM - ISA +20°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-55 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA +30°C PRESS. ALT. FEET SAT ENG. FUEL TORQUE FLOW PER ENG. °C °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 45 113 80.7 496 992 271 260 271 260 271 260 5000 35 95 87.5 474 948 291 260 291 260 291 260 10000 25 77 93.2 451 902 314 260 314 260 314 260 15000 15 60 98.4 431 862 339 260 339 260 339 260 20000 5 42 93.5 390 780 352 249 354 250 356 252 23000 -1 31 84.4 352 704 350 235 353 237 355 239 25000 -5 24 77.9 327 654 346 225 350 227 353 229 27000 -8 17 70.9 301 602 340 213 344 216 349 218 28000 -10 13 67.3 288 576 337 207 341 210 346 212 29000 -12 10 63.8 276 552 332 200 337 204 342 207 31000 -16 2 56.8 251 502 317 184 329 191 334 194 33000 -20 -5 51.1 229 458 300 167 316 176 328 184 35000 -24 -12 45.6 209 418 278 149 299 160 316 170 37000 -26 -15 38.6 184 368 – – – – 293 151 39000 – – – – – – – – – – – 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-47. Recommended Cruise Power - 1800 RPM - ISA +30°C Rep. 180-MAN-0010-01100 Page 5-56 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA -30°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET 0 SAT 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °C °F % -15 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 5 59.6 433 237 251 56.2 424 233 248 52.8 414 230 245 -25 -13 57.0 383 242 240 53.8 374 239 237 50.5 365 236 233 10000 -35 -31 54.2 338 248 229 50.9 329 245 226 47.9 321 241 222 15000 -45 -48 51.4 298 254 218 48.3 290 250 214 45.2 282 247 211 20000 -55 -66 48.1 263 260 206 45.2 255 256 203 42.4 248 252 200 23000 -61 -77 46.6 246 264 200 43.2 237 260 196 40.5 230 256 193 25000 -65 -84 45.7 235 267 195 42.4 226 262 192 39.2 217 258 189 27000 -68 -91 44.7 225 269 191 41.5 216 265 187 38.3 207 260 184 28000 -70 -95 44.1 221 271 189 41.0 212 266 185 37.9 203 262 182 29000 -72 -98 43.6 216 272 186 40.5 207 267 183 37.4 198 263 180 31000 -76 -106 43.4 210 275 182 39.5 198 270 179 36.5 189 265 175 33000 -80 -113 42.9 204 277 177 39.1 192 272 174 35.4 181 267 171 35000 -84 -120 42.2 198 280 173 38.7 186 275 170 35.1 175 270 166 37000 -86 -123 41.7 193 284 168 38.3 181 279 165 34.8 170 273 162 39000 -86 -123 41.3 189 290 164 37.9 178 284 161 34.5 166 278 157 41000 -86 -123 40.8 186 295 160 37.4 174 289 156 34.1 163 283 153 5000 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-48. Maximum Range Power - 2000 RPM - ISA -30°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-57 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA -20°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °C °F % 0 -5 23 58.1 431 237 247 54.7 421 234 244 51.2 411 231 240 5000 -15 5 56.0 382 243 237 52.7 372 240 233 49.4 363 237 230 10000 -25 -13 53.6 338 250 226 50.3 329 246 223 47.2 321 243 219 15000 -35 -30 51.2 300 257 215 48.0 291 253 212 44.8 282 249 209 20000 -45 -48 48.3 266 264 205 45.3 258 260 201 42.4 250 256 198 23000 -51 -59 47.0 250 269 198 43.5 240 264 195 40.8 232 260 192 25000 -55 -66 46.3 239 272 194 42.9 230 267 191 39.6 220 262 187 27000 -58 -73 45.3 230 275 190 42.1 221 270 186 38.8 211 265 183 28000 -60 -77 44.8 225 276 188 41.7 216 271 184 38.4 207 267 181 29000 -62 -80 44.4 221 278 186 41.2 212 273 182 38.1 202 268 179 31000 -66 -88 44.3 216 281 181 40.2 203 276 178 37.2 194 271 175 33000 -70 -95 43.9 210 284 177 40.0 198 279 174 36.2 186 274 170 35000 -74 -102 43.3 204 287 173 39.7 192 282 170 35.9 180 277 166 37000 -76 -105 42.9 199 292 169 39.3 187 286 165 35.7 176 281 162 39000 -76 -105 42.5 196 298 164 39.0 184 292 161 35.5 172 286 158 41000 -76 -105 42.1 192 304 160 38.6 180 298 157 35.2 168 292 153 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2:During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-49. Maximum Range Power - 2000 RPM - ISA -20°C Rep. 180-MAN-0010-01100 Page 5-58 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA -10°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT °C 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °F % LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 0 5 41 55.4 422 236 241 51.8 411 232 237 48.2 400 228 234 5000 -5 23 53.9 378 243 231 50.5 368 239 228 47.1 358 235 224 10000 -15 5 52.2 337 250 222 48.7 327 246 218 45.5 318 242 214 15000 -25 -12 50.4 300 258 212 47.1 291 254 208 43.8 281 250 205 20000 -35 -30 48.0 268 267 202 45.0 259 262 199 41.9 251 257 195 23000 -41 -41 47.2 253 272 196 43.5 242 267 193 40.5 234 262 189 25000 -45 -48 46.6 242 275 192 43.0 232 271 189 39.6 222 266 185 27000 -48 -55 45.9 234 279 189 42.5 224 274 185 39.0 213 269 181 28000 -50 -59 45.4 230 281 187 42.1 220 276 183 38.7 210 271 179 29000 -52 -62 45.1 226 283 185 41.7 215 278 181 38.4 206 272 178 31000 -56 -70 45.1 221 287 181 40.9 208 281 177 37.7 198 276 174 33000 -60 -77 44.9 216 291 177 40.9 203 285 173 36.9 190 279 170 35000 -64 -84 44.5 210 295 173 40.7 198 289 170 36.8 185 283 166 37000 -66 -87 44.2 206 300 169 40.4 193 294 166 36.7 181 288 162 39000 -66 -87 43.9 203 307 165 40.3 190 301 162 36.6 177 295 158 41000 -66 -87 – – – 187 308 158 36.4 174 301 154 – 40.0 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-50. Maximum Range Power - 2000 RPM - ISA -10°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-59 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. SAT FEET °C 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °F % LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 0 15 59 53.0 416 234 235 49.2 404 230 231 45.5 391 226 228 5000 5 41 52.0 374 242 226 48.4 363 238 222 44.9 352 234 219 10000 -5 23 50.9 335 250 217 47.2 324 246 213 43.8 315 241 210 15000 -15 6 49.6 301 259 208 46.1 291 254 204 42.6 280 250 201 20000 -25 -12 47.7 270 268 199 44.4 260 263 195 41.2 251 258 192 23000 -31 -23 47.1 256 274 194 43.2 244 269 190 40.1 235 264 186 25000 -35 -30 46.7 246 279 190 42.9 235 273 187 39.3 224 268 183 27000 -38 -37 46.1 238 283 187 42.6 227 277 183 38.8 216 272 179 28000 -40 -41 45.8 234 285 185 42.3 223 279 181 38.7 212 274 177 29000 -42 -44 45.5 230 287 183 42.0 219 281 179 38.5 208 276 176 31000 -46 -52 45.7 225 292 180 41.3 211 286 176 37.9 201 280 172 33000 -50 -59 45.6 220 296 176 41.4 207 290 172 37.2 193 284 168 35000 -54 -66 45.3 215 301 173 41.3 202 294 169 37.2 189 288 165 37000 -56 -69 45.1 211 307 169 41.2 198 300 165 37.3 185 294 161 39000 -56 -69 45.0 209 315 165 41.2 195 308 162 37.3 182 301 158 41000 -56 -69 – – – – – 180 308 154 – – – 37.2 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-51. Maximum Range Power - 2000 RPM - ISA Rep. 180-MAN-0010-01100 Page 5-60 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA +10°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT °C 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °F % LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 0 25 77 50.3 409 232 229 46.4 396 227 225 42.6 382 223 221 5000 15 59 49.9 370 240 221 46.2 357 236 217 42.5 345 231 212 10000 5 41 49.4 334 249 213 45.5 322 245 209 42.0 310 240 204 15000 -5 24 48.7 301 259 205 45.0 290 254 200 41.3 279 249 196 20000 -15 6 47.3 272 270 197 43.9 261 265 192 40.4 251 259 188 23000 -21 -5 47.0 258 277 192 42.9 246 271 188 39.6 236 265 183 25000 -25 -12 46.9 250 282 189 42.9 237 276 184 39.0 226 270 180 27000 -28 -19 46.5 242 286 185 42.7 230 280 181 38.7 218 274 177 28000 -30 -23 46.2 238 289 184 42.5 227 283 180 38.7 215 276 175 29000 -32 -26 46.0 235 291 182 42.2 223 285 178 38.6 211 279 174 31000 -36 -34 46.4 230 297 179 41.7 216 290 175 38.2 204 283 171 33000 -40 -41 46.5 226 302 176 42.1 212 295 172 37.6 197 288 167 35000 -44 -48 46.3 221 307 172 42.1 207 300 168 37.8 193 293 164 37000 -46 -51 46.2 218 314 169 42.1 204 307 165 38.0 190 300 161 39000 -46 -51 – – – – 42.2 201 315 162 38.2 187 308 158 41000 – – – – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-52. Maximum Range Power - 2000 RPM - ISA +10°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-61 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA +20°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT °C 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °F % LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 0 35 95 47.2 402 228 222 43.3 387 224 217 39.4 372 219 213 5000 25 77 47.5 365 238 215 43.7 352 233 210 40.0 338 228 206 10000 15 59 47.6 332 248 208 43.6 319 243 203 40.0 307 238 199 15000 5 42 47.7 302 259 201 43.8 290 254 196 40.0 278 248 192 20000 -5 24 46.8 274 271 194 43.3 263 265 189 39.7 252 259 185 23000 -11 13 47.0 262 279 190 42.6 248 273 185 39.2 238 267 181 25000 -15 6 47.1 254 285 187 42.9 241 278 182 38.8 228 272 178 27000 -18 -1 46.9 247 290 184 42.9 234 284 180 38.8 221 277 175 28000 -20 -5 46.7 243 293 183 42.8 231 286 178 38.9 218 280 174 29000 -22 -8 46.6 240 296 181 42.7 227 289 177 38.8 215 282 173 31000 -26 -16 47.2 236 302 179 42.4 220 295 174 38.7 208 288 170 33000 -30 -23 47.4 232 308 176 42.9 217 301 171 38.3 202 294 167 35000 -34 -30 47.5 228 315 173 43.1 213 307 169 38.7 198 300 164 37000 -36 -33 46.3 220 317 167 43.3 210 315 166 39.0 195 307 161 39000 -36 -33 – – – – – – – – 39.3 193 316 159 41000 – – – – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-53. Maximum Range Power - 2000 RPM - ISA +20°C Rep. 180-MAN-0010-01100 Page 5-62 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA +30°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °C °F % LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 0 45 113 45.7 402 227 217 41.6 386 222 212 37.7 369 217 208 5000 35 95 46.3 366 237 211 42.4 351 232 206 38.6 337 227 201 10000 25 77 46.8 334 248 204 42.6 319 243 200 39.0 306 237 195 15000 15 60 47.2 305 260 198 43.2 292 254 193 39.2 279 248 189 20000 5 42 46.7 279 273 192 43.0 267 267 187 39.3 255 261 182 23000 -1 31 47.1 267 282 188 42.5 252 275 183 39.0 241 269 179 25000 -5 24 47.3 259 288 185 42.9 245 281 181 38.7 232 274 176 27000 -8 17 47.2 252 294 183 43.1 239 287 178 38.8 226 280 174 28000 -10 13 47.1 248 297 181 43.1 236 290 177 39.0 223 283 172 29000 -12 10 47.1 245 300 180 43.0 232 293 176 39.0 220 286 171 31000 -16 2 47.8 241 307 178 42.8 225 299 173 38.9 213 292 169 33000 -20 -5 48.2 236 314 175 43.5 221 306 171 38.7 206 298 166 35000 -24 -12 43.0 215 289 155 43.8 217 313 168 39.1 202 305 163 37000 -26 -15 – – – – – – – – 38.0 194 304 156 39000 – – – – – – – – – – – – – – 41000 – – – – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-54. Maximum Range Power - 2000 RPM - ISA +30°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-63 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA -30°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET 0 SAT 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °C °F % -15 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 5 68.1 432 238 253 64.1 422 236 250 60.0 412 233 247 -25 -13 65.1 382 243 241 61.3 373 240 238 57.6 364 237 235 10000 -35 -31 61.4 336 248 229 58.1 328 245 226 54.6 320 242 223 15000 -45 -48 57.2 295 253 217 54.1 287 250 214 51.0 279 246 211 20000 -55 -66 52.7 258 258 205 49.9 251 255 202 47.0 244 251 199 23000 -61 -77 50.9 241 261 197 47.2 232 257 194 44.5 225 254 191 25000 -65 -84 49.8 230 263 193 46.2 221 259 190 42.8 212 255 187 27000 -68 -91 48.5 220 265 188 45.1 211 261 185 41.7 202 257 182 28000 -70 -95 47.8 215 266 185 44.5 206 262 182 41.2 198 258 179 29000 -72 -98 47.3 211 267 183 43.9 202 263 180 40.6 193 259 177 31000 -76 -106 47.2 205 269 178 42.6 193 265 175 39.5 184 261 172 33000 -80 -113 47.0 200 271 173 42.6 188 267 170 38.2 176 262 167 35000 -84 -120 46.7 196 273 168 42.3 183 268 165 37.9 170 264 162 37000 -86 -123 46.6 193 276 164 42.2 179 271 161 37.9 167 267 158 39000 -86 -123 46.5 191 281 159 42.2 177 276 156 37.9 164 271 153 41000 -86 -123 46.3 189 285 154 42.1 175 280 151 37.9 162 275 148 5000 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-55. Maximum Range Power - 1800 RPM - ISA -30°C Rep. 180-MAN-0010-01100 Page 5-64 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA -20°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °C °F % 0 -5 23 65.9 428 238 249 61.7 417 235 245 57.5 406 232 242 5000 -15 5 63.6 380 244 237 59.6 370 241 234 55.6 360 237 230 10000 -25 -13 60.5 336 250 226 56.9 327 246 222 53.2 318 242 219 15000 -35 -30 56.8 296 255 214 53.5 288 252 211 50.2 280 248 207 20000 -45 -48 52.7 261 261 203 49.7 253 257 199 46.6 246 253 196 23000 -51 -59 51.2 244 265 196 47.3 235 261 192 44.4 227 257 189 25000 -55 -66 50.2 234 268 191 46.5 224 263 188 42.9 215 259 185 27000 -58 -73 49.1 224 270 186 45.6 215 265 183 41.9 205 261 180 28000 -60 -77 48.5 220 271 184 45.0 211 267 181 41.4 201 262 178 29000 -62 -80 48.0 216 272 182 44.5 206 268 179 41.0 197 263 175 31000 -66 -88 48.1 211 275 177 43.4 198 270 174 40.0 188 265 171 33000 -70 -95 48.0 207 277 173 43.4 193 272 170 38.8 180 267 166 35000 -74 -102 47.9 202 280 168 43.3 189 275 165 38.7 175 270 162 37000 -76 -105 47.8 200 284 164 43.3 185 278 160 38.7 172 273 157 39000 -76 -105 47.9 198 289 159 43.4 183 283 156 38.9 169 278 153 41000 -76 -105 47.8 196 294 155 43.4 182 288 151 39.0 168 282 148 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-56. Maximum Range Power - 1800 RPM - ISA -20°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-65 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA -10°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °C °F % 0 5 41 62.6 418 236 242 58.4 406 233 239 54.3 394 230 236 5000 -5 23 61.1 375 243 231 57.1 365 239 228 53.2 354 236 225 10000 -15 5 58.8 334 249 221 55.2 325 246 218 51.5 316 242 214 15000 -25 -12 55.7 296 256 210 52.5 288 252 207 49.2 279 249 204 20000 -35 -30 52.3 262 263 200 49.3 254 259 196 46.2 247 255 193 23000 -41 -41 51.1 247 268 193 47.2 236 264 190 44.3 229 259 187 25000 -45 -48 50.4 236 271 189 46.6 226 266 186 43.0 217 262 183 27000 -48 -55 49.5 228 274 185 45.9 218 269 182 42.2 208 265 179 28000 -50 -59 49.0 224 275 183 45.5 214 271 180 41.8 204 266 176 29000 -52 -62 48.6 220 277 181 45.0 210 272 178 41.5 200 268 174 31000 -56 -70 48.8 216 280 176 44.0 202 275 173 40.6 193 271 170 33000 -60 -77 49.0 212 283 172 44.2 198 278 169 39.6 185 273 166 35000 -64 -84 49.0 208 286 168 44.3 194 281 165 39.6 181 276 162 37000 -66 -74 49.1 206 291 164 44.5 191 286 161 39.9 177 280 158 39000 -66 -74 49.3 205 297 160 44.8 190 291 156 40.2 175 286 153 41000 -66 -74 – – – 189 297 152 40.4 174 291 149 LBS/HR KTS KTS – % LBS/HR KTS KTS 44.8 % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-57. Maximum Range Power - 1800 RPM - ISA -10°C Rep. 180-MAN-0010-01100 Page 5-66 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. SAT FEET °C 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °F % LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 0 15 59 59.2 410 234 235 55.2 397 231 232 51.0 385 228 229 5000 5 41 58.4 370 241 225 54.5 358 238 222 50.5 347 234 219 10000 -5 23 56.8 331 248 216 53.2 322 245 212 49.5 312 241 209 15000 -15 6 54.3 295 256 206 51.1 287 252 203 47.8 278 248 199 20000 -25 -12 51.4 263 264 196 48.4 255 260 193 45.3 247 256 190 23000 -31 -23 50.6 248 269 190 46.5 237 265 187 43.7 230 260 184 25000 -35 -30 50.1 239 272 186 46.2 228 268 183 42.5 218 264 180 27000 -38 -37 49.4 231 276 182 45.7 220 271 179 41.9 210 267 176 28000 -40 -41 49.0 227 278 180 45.4 217 273 177 41.7 206 269 174 29000 -42 -44 48.7 223 280 178 45.0 213 275 175 41.4 203 270 172 31000 -46 -52 49.0 219 283 174 44.2 205 278 171 40.7 195 274 168 33000 -50 -59 49.3 216 287 170 44.5 201 282 167 39.9 188 277 164 35000 -54 -66 49.5 212 291 167 44.8 198 286 163 40.0 184 281 160 37000 -56 -69 49.8 210 296 163 45.1 195 291 160 40.4 181 285 156 39000 -56 -69 50.1 210 303 159 45.5 195 297 156 40.8 180 291 153 41000 -56 -69 – – – – – 179 297 149 – – – 41.1 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-58. Maximum Range Power - 1800 RPM - ISA Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-67 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA +10°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT °C 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °F % LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 0 25 77 56.5 404 232 229 52.3 390 229 226 48.2 376 225 223 5000 15 59 56.1 366 239 220 52.1 354 236 217 48.1 341 232 213 10000 5 41 55.0 330 247 211 51.3 319 243 207 47.4 308 240 204 15000 -5 24 53.0 295 255 201 49.6 285 251 198 46.1 276 247 195 20000 -15 6 50.4 263 264 192 47.3 255 260 189 44.1 246 255 186 23000 -21 -5 50.0 250 270 187 45.7 238 265 183 42.7 230 260 180 25000 -25 -12 49.7 241 273 183 45.6 229 269 180 41.7 219 264 176 27000 -28 -19 49.1 233 277 179 45.3 222 272 176 41.3 211 267 173 28000 -30 -23 48.8 229 279 177 45.0 219 274 174 41.1 208 269 171 29000 -32 -26 48.5 226 281 175 44.8 215 276 172 40.9 204 271 169 31000 -36 -34 48.9 222 285 172 44.0 208 280 168 40.4 197 275 165 33000 -40 -41 49.3 219 289 168 44.4 204 284 165 39.7 190 279 161 35000 -44 -48 49.6 216 294 164 44.7 200 288 161 39.9 186 282 158 37000 -46 -51 50.0 214 299 161 45.2 198 293 157 40.3 183 287 154 39000 -46 -51 – – – – 45.7 198 300 154 40.9 182 294 150 41000 – – – – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-59. Maximum Range Power - 1800 RPM - ISA +10°C Rep. 180-MAN-0010-01100 Page 5-68 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA +20°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT °C 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °F % LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 0 35 95 53.5 398 229 223 49.1 383 225 219 44.6 367 221 215 5000 25 77 53.8 363 237 214 49.5 348 233 211 45.2 334 229 207 10000 15 59 53.4 329 246 206 49.3 316 242 202 45.2 303 237 198 15000 5 42 52.1 296 255 198 48.3 285 251 194 44.5 274 246 190 20000 -5 24 50.1 266 265 189 46.6 256 260 186 43.1 246 255 182 23000 -11 13 50.0 253 272 184 45.3 240 266 181 42.0 230 261 177 25000 -15 6 50.0 245 276 181 45.5 232 271 177 41.2 220 265 173 27000 -18 -1 49.6 238 281 178 45.4 226 275 174 41.0 213 269 170 28000 -20 -5 49.3 234 283 176 45.2 222 277 172 41.0 210 271 168 29000 -22 -8 49.1 231 285 174 45.1 219 279 171 40.9 207 273 167 31000 -26 -16 49.7 227 290 171 44.5 212 284 167 40.6 200 278 163 33000 -30 -23 50.3 224 295 168 45.0 208 289 164 40.0 193 282 160 35000 -34 -30 50.8 222 300 165 45.5 205 294 161 40.4 190 287 157 37000 -36 -33 48.3 211 293 154 46.1 204 300 157 41.0 188 293 153 39000 -36 -33 – – – – – – – – 41.1 185 297 149 41000 – – – – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-60. Maximum Range Power - 1800 RPM - ISA +20°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-69 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA +30°C 11000 LBS (4990 KG) 10000 LBS (4536 KG) PRESS. ALT. FEET SAT 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS °C °F % LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 0 45 113 53.9 406 232 222 49.2 389 228 218 44.6 371 223 214 5000 35 95 53.7 368 239 213 49.2 352 235 209 44.8 337 230 205 10000 25 77 53.0 333 247 204 48.7 319 243 200 44.4 305 238 196 15000 15 60 51.3 299 256 195 47.4 287 251 191 43.5 275 245 187 20000 5 42 49.1 268 265 186 45.5 257 259 182 41.9 246 254 177 23000 -1 31 49.0 255 271 180 44.0 241 265 176 40.6 231 259 172 25000 -5 24 49.0 247 275 176 44.3 233 268 172 39.7 220 262 168 27000 -8 17 48.7 240 279 173 44.3 227 272 169 39.6 213 266 165 28000 -10 13 48.4 236 281 171 44.1 223 274 167 39.6 210 268 163 29000 -12 10 48.2 232 283 169 43.9 220 276 165 39.6 207 270 161 31000 -16 2 48.5 227 287 166 43.4 212 280 162 39.3 200 273 158 33000 -20 -5 48.8 223 291 162 43.7 208 284 158 38.7 193 277 154 35000 -24 -12 45.2 207 276 148 43.9 204 288 154 38.9 188 281 150 37000 -26 -15 – – – – – – – – 39.3 185 286 147 39000 – – – – – – – – – – – – – – 41000 – – – – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 5-61. Maximum Range Power - 1800 RPM - ISA +30°C Rep. 180-MAN-0010-01100 Page 5-70 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-62. Speed vs. Altitude Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-71 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-63. Holding Time Rep. 180-MAN-0010-01100 Page 5-72 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-64. Time. Fuel, Distance to descend - 3000 FPM Rate of Descent Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-73 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-65. Time. Fuel, Distance to descend - 1500 FPM Rate of Descent Rep. 180-MAN-0010-01100 Page 5-74 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-66. Best Glide Distance Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-75 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-67. Balked Landing Climb Torque - Flaps DOWN Rep. 180-MAN-0010-01100 Page 5-76 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-68. Balked Landing Climb - Flaps DOWN Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-77 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-69. Landing Distance over 50 feet w/o Propeller Reversing - Flaps DOWN Rep. 180-MAN-0010-01100 Page 5-78 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-70. Landing Distance over 50 feet with Propeller Reversing - Flaps DOWN Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-79 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-71. Balked Landing Climb Torque - Flaps MID Rep. 180-MAN-0010-01100 Page 5-80 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-72. Balked Landing Climb - Flaps MID Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-81 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-73. Landing Distance over 50 feet w/o Propeller Reversing - Flaps MID Rep. 180-MAN-0010-01100 Page 5-82 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-74. Landing Distance over 50 feet with Propeller Reversing - Flaps MID Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-83 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page 5-84 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS 5.4 TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS The effects of precipitation on takeoff and landing performance vary with its density and thickness on the runway; density of precipitation characterizes the various types of contamination: Dry snow Recent snow fall; crystallization is evident. The characteristics of such snow have not varied. It has not been exposed to temperature exceeding 0°C and therefore has not melted. (Density from 0.2 to 0.35). Wet snow This snow has fallen at a temperature very lightly above 0°C. The crystal pattern is partly destroyed and snow has begun to melt under the effect of ambient temperature. (Density from 0.2 to 0.35). Slush Water content in this snow is high, however the whole layer is stabilized by its lighter elements. Its surface has a dirty white coloration. (Density from 0.35 to 0.5). Standing water Snow which has reached a melting point where it looks like water rather than snow. (Density from 0.8 to 1). or Rain which is falling so abundantly that it cannot be absorbed or evacuated by the ground. (Density = 1). Operation on icy runways are not recommended due to the significant increase in the stopping distance. The performance information assumes any standing water, slush or snow to be of uniform depth and density. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-85 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS The maximum precipitation depth, for which performance calculation has been performed, is given by the following table: CONDITION Dry snow 20mm Wet snow 15mm Slush 12mm Standing water 12mm Rep. 180-MAN-0010-01100 Page 5-86 .A MAXIMUM DEPTH Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS 5.4.1 TAKEOFF DISTANCE ON CONTAMINATED RUNWAYS NOTE The distance corrections are based on calculation and are advisory in nature. CONDITIONS: Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MID Runway: . . . . Paved and covered with precipitation to known mean depth Apply the following factors to the takeoff distance on paved, dry runway (Figure 5-16 on page 5-25.A) to find the corresponding takeoff distance on contaminated runway: CORRECTION FACTORS Precipitation Depth mm Dry Snow Wet Snow Slush/ Standing Water up to 3 1.04 1.06 1.08 5 1.07 1.10 1.15 10 1.17 1.28 1.44 12 1.23 1.40 1.66 15 1.35 1.72 – 20 1.75 – – EXAMPLE: Precipitation depth: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10mm Precipitation involved: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Wet Snow Takeoff distance on paved, dry runway:. . . . . . . . . . . . . . 2850 ft (869 m) Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.28 Takeoff distance on contaminated runway: . . . . . . 2850 x 1.28 = 3648 ft (1112 m) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-87 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS 5.4.2 LANDING DISTANCE ON CONTAMINATED RUNWAYS NOTE The distance corrections are based on calculation and are advisory in nature. Landing performance are obtained using the procedure outlined in Paragraph 4.3.31 at Section 4 of this Manual. CONDITIONS: Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MID or DN Runway: . . . Paved and covered with precipitation to known mean depth The landing distance on paved, dry runway (Figure 5-69 on page 5-78.A or Figure 5-73 on page 5-82.A if landing procedure is performed with flaps DN or flaps MID respectively) must be extended by the following correction factors if reverse thrust is not applied: CORRECTION FACTORS (BRAKES ONLY) Precipitation Depth mm Dry Snow Wet Snow Slush/ Standing Water up to 3 2.00 1.93 1.87 5 1.93 1.83 1.75 10 1.79 1.64 1.53 12 1.74 1.57 1.46 15 1.67 1.49 – 20 1.57 – – Rep. 180-MAN-0010-01100 Page 5-88 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS or by the following correction factors if reverse thrust is applied: CORRECTION FACTORS (WITH REVERSE THRUST) Precipitation Depth mm Dry Snow Wet Snow Slush/ Standing Water up to 3 1.73 1.68 1.65 5 1.68 1.61 1.55 10 1.58 1.46 1.38 12 1.54 1.41 1.33 15 1.49 1.35 – 20 1.41 – – EXAMPLE: Precipitation depth: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10mm Precipitation involved: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Wet Snow Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MID Landing distance on paved, dry runway: . . . . . . . . . . . . . 3471 ft (1058 m) (Figure 5-73 on page 5-82.A) If landing procedure will be performed without using reverse thrust: Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1.64 Landing distance on contaminated runway: . . . . . 3471 x 1.64 = 5692 ft (1735 m) If landing procedure will be performed using reverse thrust: Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1.46 Landing distance on contaminated runway: . . . . . 3471 x 1.46 = 5068 ft (1545 m) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-89 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS 5.4.3 LANDING DISTANCE ON ICY RUNWAYS NOTE The distance corrections are based on calculation and are advisory in nature. Landing performance are obtained using the procedure outlined in Paragraph 4.3.31 at Section 4 of this Manual. CONDITIONS: Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MID or DN Runway: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Icy runway The landing distance on paved, dry runway (Figure 5-69 on page 5-78.A or Figure 5-73 on page 5-82.A if landing procedure is performed with flaps DN or flaps MID respectively) must be extended by a factor of 2.7 if reverse thrust is not applied, or by a factor of 2.2 if reverse thrust is applied. EXAMPLE: Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MID Landing distance on paved, dry runway: . . . . . . . . . . . . . 3471 ft (1058 m) (Figure 5-73 on page 5-82.A) If landing procedure will be performed without using reverse thrust: Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7 Landing distance on icy runway: . . . . . . . . 3471 x 2.7 = 9372 ft (2856 m) If landing procedure will be performed using reverse thrust: Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2 Landing distance on icy runway: . . . . . . . . 3471 x 2.2 = 7636 ft (2328 m) Rep. 180-MAN-0010-01100 Page 5-90 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE ADDITIONAL PERFORMANCE FOR CATEGORY II OPERATIONS 5.5 ADDITIONAL PERFORMANCE FOR CATEGORY II OPERATIONS Performance data provided in this section of the Airplane Flight Manual are to be corrected as follows when CAT II approaches are conducted: a. For Landing Weight in Single Engine Go Around refer to Figure 5-75 on page 5-92.A; b. Landing Distance with Flap Down and without Propeller Reversing, as per Figure 5-69 on page 5-78.A, must be increased by approximately 7.2%; c. Landing Distance with Flap Down and with Propeller Reversing, as per Figure 5-70 on page 5-79.A, must be increased by approximately 8.5%. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Rep. 180-MAN-0010-01100 Page 5-91 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE ADDITIONAL PERFORMANCE FOR CATEGORY II OPERATIONS Figure 5-75. Landing Weight - Single Engine Go Around Rep. 180-MAN-0010-01100 Page 5-92 .A Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS NOTE Torque limit of 96.4% (2150 lb.ft) is the static value to be applied for takeoff in order to obtain the normal 100% (2230 lb.ft) at takeoff speed for ram effect during the takeoff run. Figure 5-14. Takeoff Power Torque Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-23 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-15. Takeoff Weight - Flaps MID Rep. 180-MAN-0010-01100 Page 5-24 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-15/1. Takeoff Weight - Flaps MID (Gear UP) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-25 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page 5-26 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-16. (& 5-17) Takeoff Ground Run and Distance over 50 feet Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-27 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS INTENTIONALLY LEFT BLANK 1 2 2 2 Rep. 180-MAN-0010-01100 Page 5-28 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-18. Accelerate and Go Distance over 50 feet Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-29 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-19. Accelerate and Stop Distance without Reverse Rep. 180-MAN-0010-01100 Page 5-30 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-20. Accelerate and Stop Distance with Reverse Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-31 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-21. Twin Engine Climb Torque - Flaps MID Rep. 180-MAN-0010-01100 Page 5-32 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-22. Twin Engine Climb Fuel Flow - Flaps MID Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-33 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-23. Twin Engine Gradient of Climb - Flaps MID Rep. 180-MAN-0010-01100 Page 5-34 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS 1 23/2 24 NOTE This graph is also applicable for CAT II - One Engine Inoperative Go-Around, flown at 120 KIAS, for any weight from 9500 lbs (4309 kg) to 10945 lbs (4965 kg). Figure 5-23/1. One Engine Inoperative Takeoff Climb Torque Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-35 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-23/2. One Engine Inoperative Takeoff Climb Rep. 180-MAN-0010-01100 Page 5-36 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS 2 2 /1 2 8 9 0 Figure 5-24. Twin Engine en-route Climb Torque - Flaps Retracted Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-37 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-25. Twin Engine Climb Fuel Flow - Flaps Retracted Rep. 180-MAN-0010-01100 Page 5-38 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-26. Twin Engine en-route Rate of Climb/Descent - Flaps Retracted Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-39 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-26/1. Twin Engine En-route Gradient of Climb/Descent Rep. 180-MAN-0010-01100 Page 5-40 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-27. Time to Climb Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-41 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-28. Fuel to Climb Rep. 180-MAN-0010-01100 Page 5-42 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-29. Distance to Climb Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-43 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-30. One Engine Inoperative en-route Climb/Descent Torque Rep. 180-MAN-0010-01100 Page 5-44 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-31. One Engine Inoperative Climb Fuel Flow - Flaps Retracted Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-45 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-32. One Engine Inoperative en-route Rate of Climb/Descent Rep. 180-MAN-0010-01100 Page 5-46 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-32/1. One Engine Inoperative en-route Gradient of Climb/Descent Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-47 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-33. One Engine Inoperative Service Ceiling - Flaps Retracted Rep. 180-MAN-0010-01100 Page 5-48 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II SECTION 5 - PERFORMANCE PERFORMANCE PERFORMANCE GRAPHS 5.0 PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA -30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) FEET °C °F % TAS IAS TAS IAS TAS IAS 0 -15 5 65.1 497 994 244 260 244 260 244 260 5000 -25 -13 69.9 459 918 262 260 262 260 262 260 10000 -35 -31 74.4 426 852 281 260 281 260 281 260 15000 -45 -48 78.9 406 812 302 260 302 260 302 260 20000 -55 -66 82.9 384 768 325 260 325 260 325 260 23000 -61 -77 86.0 377 754 340 260 340 260 340 260 25000 -65 -84 88.5 375 750 350 260 350 260 350 260 27000 -68 -91 91.5 379 758 361 260 361 260 361 260 29000 -72 -98 95.0 387 774 372 260 372 260 372 260 31000 -76 -106 96.5 391 782 380 257 380 257 380 257 33000 -80 -113 89.5 368 736 376 245 376 245 376 245 35000 -84 -120 83.1 346 692 372 234 372 234 372 234 37000 -87 -124 77.6 326 652 370 224 370 224 370 224 39000 -87 -124 73.0 310 620 370 213 370 213 370 213 41000 -87 -124 68.1 291 582 369 203 370 203 370 203 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-34. Maximum Cruise Power - 2000 RPM - ISA -30°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-49.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA -20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1012 249 260 249 260 249 260 468 936 267 260 267 260 267 260 76.0 434 868 286 260 286 260 286 260 80.6 415 830 308 260 308 260 308 260 -48 84.8 393 786 332 260 332 260 332 260 -51 -59 88.0 387 774 348 260 348 260 348 260 25000 -55 -66 90.6 385 770 358 260 358 260 358 260 27000 -58 -73 93.7 390 780 370 260 370 260 370 260 29000 -62 -80 97.3 399 798 381 260 381 260 381 260 31000 -66 -88 98.9 403 806 389 257 389 257 389 257 33000 -70 -95 91.8 379 758 386 245 386 245 386 245 35000 -74 -102 85.2 355 710 382 234 382 234 382 234 37000 -77 -106 79.6 334 668 380 224 380 224 380 224 39000 -77 -106 72.3 307 614 374 210 380 213 380 213 41000 -77 -106 62.2 269 538 361 192 367 196 373 200 FEET °C °F % LBS/HR LBS/HR 0 -5 23 66.3 506 5000 -15 5 71.3 10000 -25 -13 15000 -35 -30 20000 -45 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-35. Maximum Cruise Power - 2000 RPM - ISA -20°C Rep. 180-MAN-0010-01100 Page 5-50 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA -10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1028 253 260 253 260 253 260 477 954 272 260 272 260 272 260 FEET °C °F % LBS/HR LBS/HR 0 5 41 67.5 514 5000 -5 23 72.6 10000 -15 5 77.5 443 886 292 260 292 260 292 260 15000 -25 -12 82.3 424 848 315 260 315 260 315 260 20000 -35 -30 86.6 402 804 339 260 339 260 339 260 23000 -41 -41 89.9 396 792 355 260 355 260 355 260 25000 -45 -48 92.7 395 790 366 260 366 260 366 260 27000 -48 -55 95.8 400 800 378 260 378 260 378 260 29000 -52 -62 99.6 410 820 390 260 390 260 390 260 31000 -56 -70 99.8 410 820 397 256 399 257 399 257 33000 -60 -77 93.6 387 774 394 245 395 245 395 245 35000 -64 -84 85.5 357 714 389 232 391 234 391 234 37000 -67 -88 75.9 321 642 378 216 383 220 389 223 39000 -67 -88 64.1 278 556 363 198 369 201 375 205 41000 -67 -88 53.5 239 478 345 178 352 182 359 186 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-36. Maximum Cruise Power - 2000 RPM - ISA -10°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-51.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1044 258 260 258 260 258 260 970 277 260 277 260 277 260 FEET °C °F % LBS/HR LBS/HR 0 15 59 68.7 522 5000 5 41 74.0 485 10000 -5 23 79.0 452 904 298 260 298 260 298 260 15000 -15 6 83.9 433 866 321 260 321 260 321 260 20000 -25 -12 88.4 412 824 346 260 346 260 346 260 23000 -31 -23 91.8 406 812 363 260 363 260 363 260 25000 -35 -30 94.7 405 810 374 260 374 260 374 260 27000 -38 -37 97.9 411 822 386 260 386 260 386 260 29000 -42 -44 99.8 415 830 396 258 399 260 399 260 31000 -46 -52 95.4 397 794 395 248 400 251 404 254 33000 -50 -59 87.3 366 732 389 236 394 239 399 242 35000 -54 -66 79.5 337 674 383 223 388 226 393 230 37000 -57 -70 69.2 299 598 371 207 377 210 382 214 39000 -57 -70 58.1 259 518 354 187 361 191 368 195 41000 -57 -70 47.5 220 440 329 166 339 171 348 175 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-37. Maximum Cruise Power - 2000 RPM - ISA Rep. 180-MAN-0010-01100 Page 5-52 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA +10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. FEET °C °F % 0 25 77 69.9 531 5000 15 59 75.3 494 TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1062 262 260 262 260 262 260 988 282 260 282 260 282 260 LBS/HR LBS/HR 10000 5 41 80.4 462 924 303 260 303 260 303 260 15000 -5 24 85.5 442 884 327 260 327 260 327 260 20000 -15 6 90.2 421 842 353 260 353 260 353 260 23000 -21 -5 93.7 416 832 370 260 370 260 370 260 25000 -25 -12 96.6 415 830 382 260 382 260 382 260 27000 -28 -19 99.6 420 840 394 259 395 260 395 260 29000 -32 -26 92.7 393 786 391 248 394 251 397 253 31000 -36 -34 84.6 361 722 385 235 389 238 393 241 33000 -40 -41 77.0 332 664 378 223 383 226 388 229 35000 -44 -48 69.6 303 606 370 210 376 213 381 217 37000 -47 -52 60.3 269 538 356 193 363 197 369 201 39000 -47 -52 49.6 231 462 332 171 342 176 350 181 41000 -47 -52 38.5 192 384 – – – – 317 155 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-38. Maximum Cruise Power - 2000 RPM - ISA +10°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-53.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA +20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1080 267 260 267 260 267 260 503 1006 287 260 287 260 287 260 81.9 470 940 309 260 309 260 309 260 87.1 451 902 333 260 333 260 333 260 24 91.9 430 860 360 260 360 260 360 260 13 95.6 425 850 377 260 377 260 377 260 FEET °C °F % LBS/HR LBS/HR 0 35 95 71.1 540 5000 25 77 76.6 10000 15 59 15000 5 42 20000 -5 23000 -11 25000 -15 6 96.8 419 838 387 258 390 260 390 260 27000 -18 -1 88.7 386 772 382 246 385 248 388 250 29000 -22 -8 80.9 355 710 377 234 381 236 384 238 31000 -26 -16 73.4 326 652 370 221 375 224 379 226 33000 -30 -23 66.2 298 596 361 208 367 211 373 214 35000 -34 -30 59.3 271 542 351 194 358 198 364 202 37000 -37 -34 50.5 239 478 331 175 341 180 349 185 39000 -37 -34 39.9 201 402 – – 296 148 319 160 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-39. Maximum Cruise Power - 2000 RPM - ISA +20°C Rep. 180-MAN-0010-01100 Page 5-54 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM CRUISE POWER 2000 RPM ISA +30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1098 271 260 271 260 271 260 513 1026 291 260 291 260 291 260 83.3 479 958 314 260 314 260 314 260 88.7 460 920 339 260 339 260 339 260 42 93.6 438 876 367 260 367 260 367 260 -1 31 88.1 404 808 370 249 373 251 374 252 25000 -5 24 82.0 373 746 368 239 371 241 373 243 27000 -8 17 74.5 343 686 362 227 366 229 369 232 29000 -12 10 67.3 314 628 356 215 360 217 363 220 31000 -16 2 60.4 286 572 345 201 352 205 356 208 33000 -20 -5 53.7 259 518 331 185 340 191 348 195 35000 -24 -12 47.2 233 466 310 166 325 175 335 181 37000 -27 -16 38.5 202 404 – – – – 307 158 39000 – – – – – – – – – – – 41000 – – – – – – – – – – – FEET °C °F % LBS/HR LBS/HR 0 45 113 72.2 549 5000 35 95 77.8 10000 25 77 15000 15 60 20000 5 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-40. Maximum Cruise Power - 2000 RPM - ISA +30°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-55.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA -30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 966 244 260 244 260 244 260 451 902 262 260 262 260 262 260 83.3 418 836 281 260 281 260 281 260 87.6 398 796 302 260 302 260 302 260 -66 91.8 377 754 325 260 325 260 325 260 -61 -77 95.4 373 746 340 260 340 260 340 260 25000 -65 -84 98.6 372 744 350 260 350 260 350 260 27000 -68 -91 100.0 372 744 358 257 361 260 361 260 29000 -72 -98 100.0 369 738 364 253 367 256 371 259 31000 -76 -106 100.0 369 738 370 249 373 252 377 254 33000 -80 -113 100.0 369 738 376 245 376 245 376 245 35000 -84 -120 92.6 347 694 372 234 372 234 372 234 37000 -87 -124 86.1 327 654 370 224 370 224 370 224 39000 -87 -124 80.6 309 618 370 213 370 213 370 213 41000 -87 -124 73.1 283 566 365 200 370 203 370 203 FEET °C °F % LBS/HR LBS/HR 0 -15 5 72.7 483 5000 -25 -13 78.6 10000 -35 -31 15000 -45 -48 20000 -55 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-41. Recommended Cruise Power - 1800 RPM - ISA -30°C Rep. 180-MAN-0010-01100 Page 5-56 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA -20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 984 249 260 249 260 249 260 460 920 267 260 267 260 267 260 85.1 427 854 286 260 286 260 286 260 89.5 407 814 308 260 308 260 308 260 -48 93.9 387 774 332 260 332 260 332 260 -51 -59 97.7 383 766 348 260 348 260 348 260 25000 -55 -66 100.0 380 760 357 259 358 260 358 260 27000 -58 -73 100.0 376 752 363 255 367 258 370 260 29000 -62 -80 100.0 374 748 370 251 373 254 377 256 31000 -66 -88 100.0 372 744 376 247 379 249 383 252 33000 -70 -95 100.0 373 746 382 243 385 245 386 245 35000 -74 -102 95.0 357 714 382 234 382 234 382 234 37000 -77 -106 86.8 329 658 377 222 380 224 380 224 39000 -77 -106 76.0 293 586 367 205 372 208 377 211 41000 -77 -106 65.1 257 514 354 188 360 192 366 195 FEET °C °F % LBS/HR LBS/HR 0 -5 23 74.1 492 5000 -15 5 80.1 10000 -25 -13 15000 -35 -30 20000 -45 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-42. Recommended Cruise Power - 1800 RPM - ISA -20°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-57.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA -10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1004 253 260 253 260 253 260 936 272 260 272 260 272 260 FEET °C °F % LBS/HR LBS/HR 0 5 41 75.5 502 5000 -5 23 81.7 468 10000 -15 5 86.8 435 870 292 260 292 260 292 260 15000 -25 -12 91.3 416 832 315 260 315 260 315 260 20000 -35 -30 96.0 396 792 339 260 339 260 339 260 23000 -41 -41 99.8 393 786 355 260 355 260 355 260 25000 -45 -48 100.0 384 768 362 257 365 259 366 260 27000 -48 -55 100.0 380 760 369 253 372 255 375 258 29000 -52 -62 100.0 377 754 375 249 379 251 382 254 31000 -56 -70 99.9 375 750 382 245 385 247 389 250 33000 -60 -77 96.1 362 724 382 236 386 239 390 242 35000 -64 -84 87.2 332 664 375 224 380 227 384 230 37000 -67 -88 77.2 299 598 367 209 371 212 376 215 39000 -67 -88 65.9 261 522 353 192 359 195 364 198 41000 -67 -88 55.7 228 456 336 173 343 178 350 181 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-43. Recommended Cruise Power - 1800 RPM - ISA -10°C Rep. 180-MAN-0010-01100 Page 5-58 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1022 258 260 258 260 258 260 954 277 260 277 260 277 260 FEET °C °F % LBS/HR LBS/HR 0 15 59 76.8 511 5000 5 41 83.2 477 10000 -5 23 88.4 444 888 298 260 298 260 298 260 15000 -15 6 93.2 425 850 321 260 321 260 321 260 20000 -25 -12 97.9 406 812 346 260 346 260 346 260 23000 -31 -23 100.0 398 796 360 258 363 260 363 260 25000 -35 -30 100.0 388 776 367 254 370 257 373 259 27000 -38 -37 100.0 385 770 374 251 377 253 381 256 29000 -42 -44 100.0 382 764 381 247 384 249 388 252 31000 -46 -52 96.6 368 736 382 239 385 241 390 245 33000 -50 -59 87.6 337 674 375 226 379 229 384 232 35000 -54 -66 79.1 308 616 368 213 372 216 377 219 37000 -57 -70 69.5 276 552 357 198 363 202 368 205 39000 -57 -70 58.4 240 480 340 179 347 183 354 187 41000 -57 -70 48.2 206 412 309 155 324 163 334 168 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-44. Recommended Cruise Power - 1800 RPM - ISA Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-59.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA +10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1040 262 260 262 260 262 260 485 970 282 260 282 260 282 260 90.0 453 906 303 260 303 260 303 260 95.0 434 868 327 260 327 260 327 260 6 99.9 415 830 353 260 353 260 353 260 -21 -5 100.0 402 804 365 256 367 258 369 259 25000 -25 -12 100.0 393 786 372 252 375 255 378 257 27000 -28 -19 100.0 389 778 379 249 382 251 386 254 29000 -32 -26 96.0 372 744 379 240 383 243 388 246 31000 -36 -34 87.0 341 682 373 227 377 230 381 233 33000 -40 -41 78.5 311 622 365 215 370 218 375 221 35000 -44 -48 70.5 283 566 356 201 362 205 367 208 37000 -47 -52 61.4 253 506 343 185 350 190 356 193 39000 -47 -52 49.9 215 430 312 160 325 167 335 173 41000 -47 -52 38.3 179 358 – – – – 291 142 FEET °C °F % LBS/HR LBS/HR 0 25 77 78.1 520 5000 15 59 84.7 10000 5 41 15000 -5 24 20000 -15 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-45. Recommended Cruise Power - 1800 RPM - ISA +10°C Rep. 180-MAN-0010-01100 Page 5-60 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA +20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1058 267 260 267 260 267 260 494 988 287 260 287 260 287 260 91.7 462 924 309 260 309 260 309 260 96.7 443 886 333 260 333 260 333 260 24 100.0 420 840 357 258 359 259 360 260 13 99.1 404 808 368 253 371 255 372 256 FEET °C °F % LBS/HR LBS/HR 0 35 95 79.4 529 5000 25 77 86.1 10000 15 59 15000 5 42 20000 -5 23000 -11 25000 -15 6 98.9 394 788 375 249 378 251 381 254 27000 -18 -1 91.8 367 734 371 238 375 241 379 243 29000 -22 -8 83.5 337 674 365 226 369 228 373 231 31000 -26 -16 75.3 308 616 357 213 363 216 367 219 33000 -30 -23 67.8 281 562 348 199 354 203 360 207 35000 -34 -30 60.4 255 510 337 185 344 190 351 194 37000 -37 -34 51.5 225 450 311 164 325 171 335 177 39000 -37 -34 39.6 187 374 – – – – 294 147 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-46. Recommended Cruise Power - 1800 RPM - ISA +20°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-61.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS RECOMMENDED CRUISE POWER 1800 RPM ISA +30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 1076 271 260 271 260 271 260 503 1006 291 260 291 260 291 260 93.2 470 940 314 260 314 260 314 260 98.4 452 904 339 260 339 260 339 260 42 99.1 422 844 360 255 362 256 363 257 -1 31 90.1 381 762 359 241 362 243 363 245 25000 -5 24 84.1 353 706 356 231 360 234 363 236 27000 -8 17 76.2 324 648 349 219 354 221 358 224 29000 -12 10 68.7 296 592 342 206 347 209 351 212 31000 -16 2 61.4 269 538 330 192 338 197 343 200 33000 -20 -5 54.4 244 488 312 174 325 181 334 187 35000 -24 -12 47.4 218 436 – – 303 163 319 171 37000 -27 -16 – – – – – – – – – 39000 – – – – – – – – – – – 41000 – – – – – – – – – – – FEET °C °F % LBS/HR LBS/HR 0 45 113 80.7 538 5000 35 95 87.6 10000 25 77 15000 15 60 20000 5 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 5-47. Recommended Cruise Power - 1800 RPM - ISA +30°C Rep. 180-MAN-0010-01100 Page 5-62 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA -30°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -15 5 52.2 457 225 239 49.7 448 223 237 47.2 439 221 235 -25 -13 51.4 404 233 230 48.7 395 230 228 46.1 386 228 225 10000 -35 -31 50.3 357 241 222 47.3 347 237 219 44.6 338 234 216 15000 -45 -48 49.1 322 249 213 46.0 312 245 210 42.9 302 241 206 20000 -55 -66 47.2 283 258 204 44.1 274 253 201 41.1 265 249 197 23000 -61 -77 46.5 264 264 199 42.7 253 259 195 39.7 244 253 191 25000 -65 -84 46.1 252 268 196 42.3 241 262 192 38.7 230 256 187 27000 -68 -91 45.4 243 272 192 41.8 233 266 188 38.1 222 260 183 29000 -72 -98 44.8 235 276 189 41.1 224 269 184 37.5 213 263 180 31000 -76 -106 44.9 229 280 185 40.4 216 273 181 36.8 205 266 176 33000 -80 -113 44.8 223 284 182 40.4 210 277 177 35.9 196 269 172 35000 -84 -120 43.7 214 286 177 39.9 202 280 173 36.0 190 274 169 37000 -87 -124 42.8 207 289 171 39.4 197 284 168 36.0 186 279 165 39000 -87 -124 42.0 202 293 166 39.1 192 290 164 36.1 183 286 162 41000 -87 -124 41.2 197 297 161 38.7 188 295 160 36.1 180 294 159 5000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-48. Maximum Range Power - 2000 RPM - ISA -30°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-63.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA -20°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -5 23 53.0 465 229 239 50.2 454 227 236 47.3 444 224 234 5000 -15 5 52.2 412 237 230 49.3 402 234 227 46.4 391 231 224 10000 -25 -13 51.3 365 245 221 48.0 354 242 218 45.1 344 238 215 15000 -35 -30 50.0 329 254 213 46.8 319 250 209 43.5 308 246 206 20000 -45 -48 48.2 289 264 204 45.0 280 259 200 41.8 270 254 196 23000 -51 -59 47.5 270 270 199 43.7 259 264 195 40.5 250 259 191 25000 -55 -66 47.1 258 274 196 43.3 247 268 191 39.6 236 262 187 27000 -58 -73 46.5 249 278 192 42.8 238 272 188 39.0 227 266 183 29000 -62 -80 45.9 241 283 189 42.2 230 276 184 38.5 219 270 180 31000 -66 -88 46.0 235 287 185 41.4 221 280 181 37.8 210 273 176 33000 -70 -95 45.9 229 292 182 41.4 215 284 177 37.0 202 277 172 35000 -74 -102 44.9 220 293 177 40.9 208 287 173 37.0 196 281 169 37000 -77 -106 43.9 213 296 171 40.5 202 292 168 37.0 191 287 165 39000 -77 -106 43.1 207 301 166 40.1 197 297 164 37.1 187 294 162 41000 -77 -106 42.3 201 305 161 39.7 193 303 160 37.1 184 301 159 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-49. Maximum Range Power - 2000 RPM - ISA -20°C Rep. 180-MAN-0010-01100 Page 5-64 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA -10°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 5 41 53.9 472 233 238 50.6 460 230 235 47.4 449 227 232 5000 -5 23 53.1 419 241 230 49.9 408 238 227 46.7 396 234 223 10000 -15 5 52.2 372 250 221 48.7 360 246 218 45.5 349 242 214 15000 -25 -12 51.0 336 259 213 47.6 325 255 209 44.1 314 250 205 20000 -35 -30 49.1 295 269 204 45.9 286 264 200 42.6 276 259 196 23000 -41 -41 48.6 277 276 199 44.6 265 270 195 41.4 255 265 191 25000 -45 -48 48.2 264 280 196 44.2 252 274 191 40.4 241 268 187 27000 -48 -55 47.5 255 285 192 43.8 244 278 188 40.0 233 272 184 29000 -52 -62 46.9 246 289 189 43.1 235 283 184 39.5 224 276 180 31000 -56 -70 47.1 240 294 185 42.5 226 287 181 38.8 215 280 176 33000 -60 -77 47.0 234 299 182 42.5 220 291 177 38.0 207 284 173 35000 -64 -84 46.0 225 301 177 42.0 213 295 173 38.0 201 288 169 37000 -67 -88 45.0 218 304 171 41.5 207 299 168 38.0 196 294 166 39000 -67 -88 44.2 212 308 166 41.2 202 305 164 38.0 192 301 162 41000 -67 -88 43.4 207 313 161 40.7 197 311 160 37.9 188 308 158 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-50. Maximum Range Power - 2000 RPM - ISA -10°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-65.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 15 59 54.6 479 237 238 51.0 466 233 235 47.5 453 230 231 5000 5 41 53.9 426 245 230 50.4 414 241 226 47.0 402 238 222 10000 -5 23 53.0 379 254 221 49.3 366 250 217 46.0 355 246 213 15000 -15 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 6 51.9 342 264 213 48.3 331 259 209 44.7 319 255 205 20000 -25 -12 50.1 302 275 204 46.7 291 269 200 43.3 281 264 196 23000 -31 -23 49.6 283 281 199 45.4 270 276 195 42.2 260 270 191 25000 -35 -30 49.1 270 286 196 45.2 258 280 191 41.3 247 274 187 27000 -38 -37 48.6 261 291 192 44.8 249 284 188 40.9 237 278 184 29000 -42 -44 47.9 252 296 189 44.1 240 289 184 40.4 229 282 180 31000 -46 -52 48.2 245 301 185 43.5 231 294 181 39.8 220 287 177 33000 -50 -59 48.1 239 306 182 43.6 225 299 178 39.1 212 291 173 35000 -54 -66 47.1 231 308 177 43.0 218 302 173 39.0 205 296 169 37000 -57 -70 46.1 223 311 171 42.6 212 306 169 39.0 201 301 166 39000 -57 -70 45.3 218 316 166 42.2 207 312 164 39.0 197 308 162 41000 -57 -70 44.4 211 320 161 41.6 202 318 160 38.8 193 316 158 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged and speed remains unchanged. Figure 5-51. Maximum Range Power - 2000 RPM - ISA Rep. 180-MAN-0010-01100 Page 5-66 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA +10°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 25 77 54.6 484 239 236 51.2 471 236 233 47.8 458 233 230 5000 15 59 54.0 432 248 228 50.7 419 245 225 47.4 407 241 221 10000 5 41 53.3 384 258 220 49.7 371 254 216 46.4 360 250 213 15000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS -5 24 52.4 348 268 212 48.8 336 264 208 45.2 324 259 204 20000 -15 6 50.8 307 279 203 47.4 297 274 199 43.9 286 269 195 23000 -21 -5 50.3 288 286 198 46.2 276 281 194 42.9 265 275 190 25000 -25 -12 50.0 275 291 195 45.9 263 285 191 42.1 251 279 187 27000 -28 -19 49.4 266 296 192 45.6 254 290 188 41.6 242 284 183 29000 -32 -26 48.9 257 302 189 45.0 245 295 184 41.2 233 288 180 31000 -36 -34 49.1 251 307 185 44.4 236 300 181 40.6 225 293 176 33000 -40 -41 49.2 245 313 182 44.6 230 305 177 39.9 216 298 173 35000 -44 -48 48.3 236 315 177 44.1 223 309 173 39.9 210 302 169 37000 -47 -52 47.4 229 319 172 43.7 217 314 169 39.9 205 309 166 39000 -47 -52 46.6 222 324 167 43.3 212 320 165 40.0 201 316 162 41000 -47 -52 – – – – – 192 317 155 – – – 38.5 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-52. Maximum Range Power - 2000 RPM - ISA +10°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-67 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA +20°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 35 95 54.5 488 241 235 51.2 476 239 232 48.0 464 236 229 5000 25 77 54.2 437 251 227 50.9 425 248 224 47.7 413 244 221 10000 15 59 53.6 389 261 219 50.1 377 257 215 46.9 366 253 212 15000 5 42 52.9 354 272 211 49.4 342 267 207 45.8 330 263 204 20000 -5 24 51.4 313 284 203 48.0 302 279 199 44.6 291 273 195 23000 -11 13 51.0 293 291 198 46.9 280 286 194 43.6 270 280 190 25000 -15 6 50.8 280 297 195 46.7 268 291 191 42.8 255 284 187 27000 -18 -1 50.3 270 302 192 46.4 259 296 187 42.4 246 289 183 29000 -22 -8 49.8 261 308 188 45.9 250 301 184 42.0 238 294 180 31000 -26 -16 50.1 255 313 185 45.3 241 306 181 41.4 229 299 176 33000 -30 -23 50.2 249 319 182 45.5 235 312 178 40.8 220 304 173 35000 -34 -30 49.4 241 322 177 45.1 228 316 173 40.8 214 309 170 37000 -37 -34 48.6 233 327 172 44.8 221 321 169 40.9 209 316 166 39000 -37 -34 – – – – 38.9 199 296 148 39.9 201 319 160 41000 – – – – – – – – – – – LBS/HR KTS KTS % LBS/HR KTS KTS – % – LBS/HR KTS KTS – Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-53. Maximum Range Power - 2000 RPM - ISA +20°C Rep. 180-MAN-0010-01100 Page 5-68 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 2000 RPM ISA +30°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 45 113 54.3 492 244 233 51.3 481 241 231 48.2 469 238 228 5000 35 95 54.2 441 253 225 51.1 430 250 222 48.0 418 247 220 10000 25 77 53.9 394 264 218 50.4 382 260 214 47.3 371 257 211 15000 15 60 53.3 360 276 210 49.9 348 271 206 46.3 336 267 203 20000 5 42 52.0 319 288 202 48.6 308 283 198 45.2 297 278 195 23000 -1 31 51.7 298 296 197 47.5 286 290 194 44.3 276 285 190 25000 -5 24 51.5 285 302 194 47.4 273 296 190 43.5 261 290 186 27000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS -8 17 51.1 275 307 191 47.2 263 301 187 43.1 251 295 183 29000 -12 10 50.7 265 313 188 46.7 253 306 184 42.8 242 300 180 31000 -16 2 51.1 259 319 185 46.1 244 312 181 42.2 233 305 176 33000 -20 -5 51.3 253 326 182 46.4 238 318 178 41.6 224 310 173 35000 -24 -12 46.0 231 310 166 46.1 231 323 174 41.7 217 316 170 37000 -27 -16 – – – – – – – – 38.5 202 307 158 39000 – – – – – – – – – – – – – – 41000 – – – – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-54. Maximum Range Power - 2000 RPM - ISA +30°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-69.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA -30°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -15 5 55.4 436 220 234 51.6 423 218 231 47.8 411 215 228 -25 -13 55.0 389 227 225 51.3 377 224 222 47.6 365 221 219 10000 -35 -31 53.9 345 234 216 50.4 334 231 213 46.7 323 227 209 15000 -45 -48 51.9 309 242 207 48.6 299 238 204 45.2 289 234 200 20000 -55 -66 51.8 276 256 203 47.8 266 250 198 43.9 255 243 193 23000 -61 -77 52.5 262 265 200 47.2 248 257 194 42.9 236 249 188 25000 -65 -84 52.9 252 272 199 47.4 238 262 192 42.2 224 253 185 27000 -68 -91 53.1 246 278 197 47.4 231 268 190 41.8 217 258 182 29000 -72 -98 51.5 236 280 192 46.4 223 271 185 41.4 210 261 179 31000 -76 -106 50.7 229 282 187 45.3 214 274 181 40.9 202 265 175 33000 -80 -113 49.7 221 284 182 44.9 208 277 177 40.2 195 269 172 35000 -84 -120 48.5 212 285 176 44.3 201 279 173 40.2 189 274 169 37000 -87 -124 47.4 205 288 171 43.9 195 284 168 40.2 185 279 165 39000 -87 -124 46.5 200 293 166 43.4 190 290 164 40.2 182 286 162 41000 -87 -124 45.6 195 297 161 42.9 187 295 160 40.2 179 294 159 5000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-55. Maximum Range Power - 1800 RPM - ISA -30°C Rep. 180-MAN-0010-01100 Page 5-70 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA -20°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -5 23 55.1 440 222 232 51.1 426 219 229 47.2 413 216 225 5000 -15 5 54.9 394 230 223 51.1 381 226 220 47.3 368 223 216 10000 -25 -13 54.0 350 238 214 50.4 338 234 211 46.7 327 230 208 15000 -35 -30 52.3 314 246 206 48.9 304 242 202 45.5 294 238 199 20000 -45 -48 52.2 281 260 201 48.3 270 254 196 44.4 259 248 191 23000 -51 -59 52.9 266 269 199 47.7 252 262 193 43.5 241 254 187 25000 -55 -66 53.3 257 276 197 47.9 242 267 191 42.8 229 258 184 27000 -58 -73 53.5 250 282 195 48.0 236 273 188 42.6 221 263 181 29000 -62 -80 52.1 241 285 190 47.0 227 276 184 42.2 215 267 178 31000 -66 -88 51.4 234 287 186 46.1 219 279 180 41.7 207 271 175 33000 -70 -95 50.5 226 290 181 45.8 213 283 176 41.1 200 276 172 35000 -74 -102 49.5 217 292 176 45.3 206 286 172 41.1 194 280 168 37000 -77 -106 48.6 211 296 171 44.9 200 291 168 41.2 190 286 165 39000 -77 -106 47.8 206 301 166 44.6 196 297 164 41.3 186 294 162 41000 -77 -106 46.9 201 306 161 44.1 192 304 160 41.3 184 302 159 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-56. Maximum Range Power - 1800 RPM - ISA -20°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-71.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA -10°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 5 41 54.7 443 224 229 50.6 429 221 226 46.5 416 218 223 5000 -5 23 54.8 398 232 221 50.9 384 229 218 46.9 371 225 214 10000 -15 5 54.2 354 240 213 50.5 342 237 209 46.7 330 233 206 15000 -25 -12 52.6 319 249 204 49.2 309 245 201 45.8 298 241 197 20000 -35 -30 52.6 285 264 200 48.7 274 258 195 44.8 264 252 190 23000 -41 -41 53.2 271 273 197 48.1 257 266 192 44.0 245 258 186 25000 -45 -48 53.6 261 280 195 48.4 247 271 189 43.4 233 263 183 27000 -48 -55 53.8 255 287 194 48.5 241 277 187 43.2 226 268 181 29000 -52 -62 52.6 245 290 189 47.7 232 281 183 43.0 219 273 178 31000 -56 -70 52.1 238 292 184 46.8 223 285 179 42.5 212 277 174 33000 -60 -77 51.4 230 295 180 46.7 217 289 176 41.9 204 282 171 35000 -64 -84 50.5 222 298 175 46.3 210 293 172 42.0 198 287 168 37000 -67 -88 49.7 216 303 171 46.0 205 298 168 42.2 194 293 165 39000 -67 -88 49.0 211 308 166 45.7 201 305 164 42.3 191 301 162 41000 -67 -88 48.2 206 314 161 45.3 197 312 160 42.4 188 309 159 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-57. Maximum Range Power - 1800 RPM - ISA -10°C Rep. 180-MAN-0010-01100 Page 5-72 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 15 59 54.3 446 226 227 50.0 432 222 224 45.9 418 219 220 5000 5 41 54.7 402 234 219 50.6 388 231 216 46.5 374 227 212 10000 -5 23 54.3 359 243 211 50.5 347 239 208 46.6 334 235 204 15000 -15 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 6 53.0 324 253 203 49.5 313 248 200 46.0 303 244 196 20000 -25 -12 52.8 290 267 198 49.0 279 261 194 45.2 268 255 189 23000 -31 -23 53.5 275 277 196 48.5 261 270 190 44.5 250 263 185 25000 -35 -30 53.9 265 284 194 48.8 251 276 188 43.9 238 268 183 27000 -38 -37 54.1 259 290 192 49.0 245 282 186 43.8 231 273 180 29000 -42 -44 53.0 249 294 188 48.3 236 286 182 43.6 223 278 177 31000 -46 -52 52.7 241 297 183 47.5 227 290 179 43.3 215 283 174 33000 -50 -59 52.2 234 301 179 47.5 221 294 175 42.7 208 288 171 35000 -54 -66 51.4 227 304 175 47.2 215 299 171 42.9 202 293 168 37000 -57 -70 50.8 221 309 170 47.0 210 305 168 43.1 199 300 165 39000 -57 -70 50.2 216 316 166 46.8 206 312 164 43.4 196 308 162 41000 -57 -70 46.6 202 309 155 46.5 201 319 160 43.4 193 317 159 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-58. Maximum Range Power - 1800 RPM - ISA Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-73.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA +10°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 25 77 57.0 460 233 230 52.4 445 229 226 47.8 429 225 222 5000 15 59 56.7 413 240 221 52.2 397 236 217 47.8 382 232 213 10000 5 41 55.6 367 248 212 51.4 354 244 208 47.2 340 239 204 15000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS -5 24 53.6 330 257 202 49.8 318 252 198 46.0 306 247 194 20000 -15 6 53.7 296 272 198 49.7 285 266 193 45.7 273 259 189 23000 -21 -5 54.6 282 283 196 49.4 267 275 190 45.2 255 268 185 25000 -25 -12 55.2 272 290 194 49.9 257 281 188 44.8 243 273 183 27000 -28 -19 55.5 265 297 192 50.2 251 288 186 44.9 236 279 180 29000 -32 -26 54.4 255 301 188 49.5 242 293 183 44.8 228 284 177 31000 -36 -34 54.2 248 305 184 48.7 233 297 179 44.3 221 290 174 33000 -40 -41 53.7 241 309 180 48.8 227 302 176 43.8 213 295 171 35000 -44 -48 53.0 233 313 175 48.6 220 307 172 44.0 208 301 168 37000 -47 -52 52.3 227 318 171 48.3 215 313 168 44.3 204 308 165 39000 -47 -52 48.9 213 312 160 48.2 211 320 165 44.5 200 316 162 41000 -47 -52 – – – – – 179 291 142 – – – 38.3 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-59. Maximum Range Power - 1800 RPM - ISA +10°C Rep. 180-MAN-0010-01100 Page 5-74 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA +20°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 35 95 59.9 474 240 233 54.8 457 235 229 49.8 440 231 224 5000 25 77 58.8 424 246 223 53.9 407 241 218 49.1 391 237 214 10000 15 59 56.9 376 253 212 52.4 361 248 208 47.8 346 243 203 15000 5 42 54.3 336 261 202 50.1 323 255 197 46.0 310 249 193 20000 -5 24 54.6 303 277 198 50.4 290 270 193 46.1 278 263 188 23000 -11 13 55.7 288 288 196 50.2 272 280 190 45.9 260 272 185 25000 -15 6 56.4 278 296 194 50.9 262 287 188 45.7 248 279 183 27000 -18 -1 56.8 271 304 193 51.4 256 294 187 46.0 241 285 181 29000 -22 -8 55.7 261 308 189 50.7 247 299 183 45.8 234 291 178 31000 -26 -16 55.6 253 312 184 50.0 238 304 180 45.4 226 296 175 33000 -30 -23 55.2 246 316 180 50.0 232 309 176 44.9 218 302 172 35000 -34 -30 54.5 239 321 176 49.9 225 314 172 45.2 212 308 169 37000 -37 -34 50.1 222 311 164 49.7 220 321 169 45.4 208 315 166 39000 -37 -34 – – – – – – – – 39.6 187 294 147 41000 – – – – – – – – – – – – – LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS – Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-60. Maximum Range Power - 1800 RPM - ISA +20°C Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-75.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS MAXIMUM RANGE POWER 1800 RPM ISA +30°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 45 113 62.9 488 247 236 57.3 470 242 231 51.8 452 236 226 5000 35 95 60.9 435 252 224 55.6 417 247 219 50.4 399 241 214 10000 25 77 58.3 385 258 213 53.3 368 252 208 48.4 352 246 203 15000 15 60 54.8 342 264 201 50.4 328 258 196 45.9 313 251 191 20000 5 42 55.5 310 282 198 51.0 296 274 192 46.5 282 267 187 23000 -1 31 56.7 294 294 196 51.1 279 285 190 46.6 265 277 184 25000 -5 24 57.5 283 302 194 51.9 268 293 189 46.6 254 284 183 27000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS -8 17 58.0 276 310 193 52.6 261 301 187 47.0 247 291 181 29000 -12 10 57.1 265 315 189 51.9 251 306 184 46.9 238 297 178 31000 -16 2 57.0 258 319 185 51.2 242 311 180 46.5 230 303 175 33000 -20 -5 53.3 241 312 174 51.3 236 316 177 46.0 221 309 172 35000 -24 -12 – – – – 46.6 217 303 163 46.3 215 315 169 37000 -27 -16 – – – – – – – – – – – – 39000 – – – – – – – – – – – – – – 41000 – – – – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 5-61. Maximum Range Power - 1800 RPM - ISA +30°C Rep. 180-MAN-0010-01100 Page 5-76 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-62. Speed vs. Altitude (for PT6A-66 engines only) INTENTIONALLY LEFT BLANK Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-77.B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS ASSOCIATED CONDITIONS: GEAR AND FLAP RETRACTED - 1800 RPM ICE PROTECTION OFF - BLEED AIR NORMAL STANDARD DAY EXAMPLE: PRESSURE ALTITUDE AIRPLANE WEIGHT HOLDING TIME HOLDING FUEL 5000 FT 9500 LBS 30 MIN 293 LBS (133 KG) SPEED WEIGHT NOTE: WHEN OPERATING IN ICING CONDITIONS, HOLDING SPEED MUST BE INCREASED BY 6 KTS. DURING OPERATION WITH ANTI-ICE SYSTEM ON, HEAVY ICE ACCRETION ON UNPROTECTED AREAS AND POWER TO MAINTAIN THE HOLDING SPEED REQUIRED IN ICING CONDITIONS, HOLDING TIME MAY DECREASE 30% APPROXIMATELY. PRESS. ALT. FEET 135 KIAS 138 KIAS 140 KIAS 142 KIAS 11000 LBS (4990 KG) 10500 LBS (4763 KG) 10000 LBS (4536 KG) 9500 LBS (4309 KG) HOLDING TIME 0 5000 10000 15000 20000 25000 30000 0 5000 10000 15000 20000 25000 30000 0 5000 10000 15000 20000 25000 30000 0 5000 10000 15000 20000 25000 30000 Figure 5-63. HOLDING FUEL LBS 5 MIN. 56 49 44 40 37 33 32 57 50 44 41 38 35 33 57 51 45 42 38 36 34 58 51 46 43 39 37 36 25 22 20 18 17 15 15 26 23 20 19 17 16 15 26 23 21 19 17 16 16 26 23 21 20 18 17 16 LBS KG 10 MIN. 112 98 87 81 73 66 65 113 99 89 83 75 69 67 115 101 91 85 77 72 69 116 103 93 87 78 75 72 51 44 39 37 33 30 29 51 45 40 38 34 31 30 52 46 41 38 35 33 31 53 47 42 39 35 34 32 LBS KG 30 MIN. 335 293 261 243 220 199 194 339 298 266 249 225 208 200 344 303 272 254 230 216 206 349 308 279 260 235 224 215 152 133 118 110 100 90 88 154 135 121 113 102 94 91 156 137 123 115 104 98 93 158 140 126 118 106 102 97 LBS KG 45 MIN. 502 440 392 364 331 298 291 509 447 399 373 338 312 301 516 455 408 382 345 324 309 523 462 418 390 352 336 322 228 199 178 165 150 135 132 231 203 181 169 153 141 136 234 206 185 173 156 147 140 237 210 190 177 160 153 146 LBS KG 60 MIN. 669 586 522 485 441 397 388 678 596 532 497 450 416 401 688 606 544 509 460 433 412 697 616 557 520 469 448 430 304 266 237 220 200 180 176 308 270 241 226 204 188 182 312 275 247 231 209 196 187 316 280 253 236 213 203 195 Holding Time Rep. 180-MAN-0010-01100 Page 5-78 .B KG Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-64. Time. Fuel, Distance to descend - 3000 FPM Rate of Descent Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-79 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-65. Time. Fuel, Distance to descend - 1500 FPM Rate of Descent Rep. 180-MAN-0010-01100 Page 5-80 .B Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-66. Best Glide Distance Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-81 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-67. Balked Landing Climb Torque - Flaps DOWN Rep. 180-MAN-0010-01100 Page 5-82 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS 8 69 70 71 72 73 74 Figure 5-68. Balked Landing Rate of Climb - Flaps DOWN Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-83 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-69. Landing Distance over 50 feet w/o Propeller Reversing - Flaps DN Rep. 180-MAN-0010-01100 Page 5-84 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-70. Landing Distance over 50 feet with Propeller Reversing - Flaps DN Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-85 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-71. Balked Landing Climb Torque - Flaps MID Rep. 180-MAN-0010-01100 Page 5-86 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-72. Balked Landing Rate of Climb - Flaps MID Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-87 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS Figure 5-73. Landing Distance over 50 feet w/o Propeller Reversing - Flaps MID Rep. 180-MAN-0010-01100 Page 5-88 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE PERFORMANCE GRAPHS Figure 5-74. Landing Distance over 50 feet with Propeller Reversing - Flaps MID Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-89 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE PERFORMANCE GRAPHS INTENTIONALLY LEFT BLANK Rep. 180-MAN-0010-01100 Page 5-90 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS 5.4 TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS The effects of precipitation on takeoff and landing performance vary with its density and thickness on the runway; density of precipitation characterizes the various types of contamination: Dry snow Recent snow fall; crystallization is evident. The characteristics of such snow have not varied. It has not been exposed to temperature exceeding 0°C and therefore has not melted. (Density from 0.2 to 0.35). Wet snow This snow has fallen at a temperature very lightly above 0°C. The crystal pattern is partly destroyed and snow has begun to melt under the effect of ambient temperature. (Density from 0.2 to 0.35). Slush Water content in this snow is high, however the whole layer is stabilized by its lighter elements. Its surface has a dirty white coloration. (Density from 0.35 to 0.5). Standing water Snow which has reached a melting point where it looks like water rather than snow. (Density from 0.8 to 1). or Rain which is falling so abundantly that it cannot be absorbed or evacuated by the ground. (Density = 1). Operation on icy runways are not recommended due to the significant increase in the stopping distance. The performance information assumes any standing water, slush or snow to be of uniform depth and density. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 Rep. 180-MAN-0010-01100 Page 5-91 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE TAKEOFF AND LANDING DISTANCE ON CONTAMINATED RUNWAYS The maximum precipitation depth, for which performance calculation has been performed, is given by the following table: CONDITION Dry snow 20mm Wet snow 15mm Slush 12mm Standing water 12mm Rep. 180-MAN-0010-01100 Page 5-92.B MAXIMUM DEPTH Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE TAKEOFF DISTANCE ON CONTAMINATED RUNWAYS 5.4.1 TAKEOFF DISTANCE ON CONTAMINATED RUNWAYS NOTE The distance corrections are based on calculation and are advisory in nature. CONDITIONS: Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MID Runway: . . . . Paved and covered with precipitation to known mean depth Apply the following factors to the takeoff distance on paved, dry runway (Figure 5-16 on page 5-27.B) to find the corresponding takeoff distance on contaminated runway: CORRECTION FACTORS Precipitation Depth mm Dry Snow Wet Snow Slush/ Standing Water up to 3 1.04 1.06 1.08 5 1.07 1.10 1.15 10 1.17 1.28 1.44 12 1.23 1.40 1.66 15 1.35 1.72 – 20 1.75 – – EXAMPLE: Precipitation depth: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10mm Precipitation involved: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Wet Snow Takeoff distance on paved, dry runway:. . . . . . . . . . . . . . 2850 ft (869 m) Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.28 Takeoff distance on contaminated runway: . . . . . . 2850 x 1.28 = 3648 ft (1112 m) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-93 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE TAKEOFF DISTANCE ON CONTAMINATED RUNWAYS 5.4.2 LANDING DISTANCE ON CONTAMINATED RUNWAYS NOTE The distance corrections are based on calculation and are advisory in nature. Landing performance are obtained using the procedure outlined in Paragraph 4.3.31 at Section 4 of this Manual. CONDITIONS: Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MID or DN Runway: . . . Paved and covered with precipitation to known mean depth The landing distance on paved, dry runway (Figure 5-69 on page 5-84.B or Figure 5-73 on page 5-88.B if landing procedure is performed with flaps DN or flaps MID respectively) must be extended by the following correction factors if reverse thrust is not applied: CORRECTION FACTORS (BRAKES ONLY) Precipitation Depth mm Dry Snow Wet Snow Slush/ Standing Water up to 3 2.00 1.93 1.87 5 1.93 1.83 1.75 10 1.79 1.64 1.53 12 1.74 1.57 1.46 15 1.67 1.49 – 20 1.57 – – Rep. 180-MAN-0010-01100 Page 5-94 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE TAKEOFF DISTANCE ON CONTAMINATED RUNWAYS or by the following correction factors if reverse thrust is applied: CORRECTION FACTORS (WITH REVERSE THRUST) Precipitation Depth mm Dry Snow Wet Snow Slush/ Standing Water up to 3 1.73 1.68 1.65 5 1.68 1.61 1.55 10 1.58 1.46 1.38 12 1.54 1.41 1.33 15 1.49 1.35 – 20 1.41 – – EXAMPLE: Precipitation depth: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10 mm Precipitation involved: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Wet Snow Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MID Landing distance on paved, dry runway: . . . . . . . . . . . . . 3471 ft (1058 m) (Figure 5-73 on page 5-88.B) If landing procedure will be performed without using reverse thrust: Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1.64 Landing distance on contaminated runway: . . . . . 3471 x 1.64 = 5692 ft (1735 m) If landing procedure will be performed using reverse thrust: Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1.46 Landing distance on contaminated runway: . . . . . 3471 x 1.46 = 5068 ft (1545 m) Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-95 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE TAKEOFF DISTANCE ON CONTAMINATED RUNWAYS 5.4.3 LANDING DISTANCE ON ICY RUNWAYS NOTE The distance corrections are based on calculation and are advisory in nature. Landing performance are obtained using the procedure outlined in Paragraph 4.3.31 at Section 4 of this Manual. CONDITIONS: Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MID or DN Runway: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Icy runway The landing distance on paved, dry runway (Figure 5-69 on page 5-84.B or Figure 5-73 on page 5-88.B if landing procedure is performed with flaps DN or flaps MID respectively) must be extended by a factor of 2.7 if reverse thrust is not applied, or by a factor of 2.2 if reverse thrust is applied. EXAMPLE: Flaps: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MID Landing distance on paved, dry runway: . . . . . . . . . . . . . 3471 ft (1058 m) (Figure 5-73 on page 5-88.B) If landing procedure will be performed without using reverse thrust: Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7 Landing distance on icy runway: . . . . . . . . 3471 x 2.7 = 9372 ft (2856 m) If landing procedure will be performed using reverse thrust: Correction factor: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2 Landing distance on icy runway: . . . . . . . . 3471 x 2.2 = 7636 ft (2328 m) Rep. 180-MAN-0010-01100 Page 5-96 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 AIRPLANE FLIGHT MANUAL P.180 AVANTI II PERFORMANCE ADDITIONAL PERFORMANCE FOR CATEGORY II OPERATIONS 5.5 ADDITIONAL PERFORMANCE FOR CATEGORY II OPERATIONS Performance data provided in this section of the Airplane Flight Manual are to be corrected as follows when CAT II approaches are conducted: a. For Landing Weight in Single Engine Go Around refer to Figure 5-75 on page 5-98.B; b. Landing Distance with Flap Down and without Propeller Reversing, as per Figure 5-69 on page 5-84.B, must be increased by approximately 7.2%; c. Landing Distance with Flap Down and with Propeller Reversing, as per Figure 5-70 on page 5-85.B, must be increased by approximately 8.5%. Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Rep. 180-MAN-0010-01100 Page 5-97 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL PERFORMANCE ADDITIONAL PERFORMANCE FOR CATEGORY II OPERATIONS Figure 5-75. Landing Weight - Single Engine Go Around Rep. 180-MAN-0010-01100 Page 5-98 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: October 21, 2005 Rev. B0 : Mar. 04, 2019 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SUPPLEMENTS LIST OF SUPPLEMENTS No. Title Rev. Date Mark if installed 1 Portable Supplementary Oxygen (8 Pages) Rev. 4: Mar. 04, 2019 2 Cargo and Combi Configurations (24 Pages) Rev. 4: Mar. 04, 2019 3 Protective Breathing Equipment (8 Pages) Rev. 4: Mar. 04, 2019 4 First Aid Oxygen Equipment (10 Pages) Rev. 4: Mar. 04, 2019 5 Ballast Kit for Airplane Balancing (10 Pages) Rev. 4: Mar. 04, 2019 6 Air Ambulance Configuration (22 Pages) Rev. 5: Mar. 04, 2019 7 SeaFLIR II System (22 Pages) Rev. 6: Mar. 04, 2019 8 KHF990 HF Communication System (8 Pages) Rev. 5: Mar. 04, 2019 9 FA2100 Cockpit Voice Recorder (8 Pages) Rev. 4: Mar. 04, 2019 10 TCAS I (10 Pages) Rev. 5: Mar. 04, 2019 11 TAWS (10 Pages) Rev. 6: Mar. 04, 2019 12 Unpaved Runways Operations (12 Pages) Rev. 7: Mar. 04, 2019 13 Turbulence Weather Radar (8 Pages) Rev. 6: Mar. 04, 2019 14 Sec. Diversity Mode-S Transponder (8 Pages) Rev. 5: Mar. 04, 2019 15 Increased MTOW - 12100 lbs (112 Pages) Rev. 10:Mar. 04, 2019 16 Integrated Flight Information System (8 Pages) Rev. 5: Mar. 04, 2019 17 V/UHF Wulfsberg Comm. System (4 Pages) Rev. 3: Mar. 04, 2019 18 Stretcher Kit on Interiors Corp.1,2, 3 (40/44 Pg.) Rev. 5: Mar. 04, 2019 19 IFF Transponder System Installation (4 Pages) Rev. 3: Mar. 04, 2019 20 Reserved Rev. 0: Reserved Issued: October 21, 2005 Rev. B0: Mar. 04, 2019 SUPPLEMENTS All Page i P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 21 Operation in CIS (46 Pages) Rev. 2: Mar. 04, 2019 22 KTR 909B UHF-AM Comm. System (6 Pages) Rev. 3: Mar. 04, 2019 23 ACAS II (14 Pages) Rev. 7: Mar. 04, 2019 24 EGPWS (16 Pages) Rev. 6: Mar. 04, 2019 25 FA2100 CVDR (8 Pages) Rev. 5: Mar. 04, 2019 26 HF-9000 Comm. System (8 Pages) Rev. 5: Mar. 04, 2019 27 Concorde Battery RG-380E/40L (8 Pages) Rev. 4: Mar. 04, 2019 28 LPV, APV-BARO temp. compensation (8 Pages) Rev. 5: Mar. 04, 2019 29 LPV, APV-BARO for FIS equipped a/c (10 Pages) Rev. 4: Mar. 04, 2019 30 CPDLC System (8 Pages) Rev. 3: Mar. 04, 2019 31 MTOW 11550 lbs for Avanti EVO (42 Pages) Rev. 1: Mar. 04, 2019 32 New A/C config. MSN 3005 (22 Pages) Rev. 2: Mar. 04, 2019 33 Flight Inspection Syst. provision (10 Pages) Rev. 1: Mar. 04, 2019 34 ADS-B OUT Transponders (8 Pages) Rev. 2: Mar. 04, 2019 35 Emerg. Exit Proc. for Uganda reg. A/C (4 Pages) Rev. 0: Jan 14, 2019 SUPPLEMENTS Page ii Issued: October 21, 2005 All Rev. B0 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 1 Portable Supplementary Oxygen (8 Pages) SUPPLEMENT NO. 1 FOR PORTABLE SUPPLEMENTARY OXYGEN CYLINDER SCOTT AVIATION PRODUCTS EXECUTIVE MARK I Rev. 4: Mar. 04, 2019 LOG OF REVISIONS Rev. Revised Pages No. Description of Revision Approval Date 0 -- First Issue October 21, 2005 1 ALL Editorial changes April 10, 2006 2 1, All pages with suffix “.C” Revision issued for P.180 Avanti “EVO” MSN 3001 and up, introducing a complete AFM applicable to MSN 3001 + airplanes. Rev. 2 is approved under the authority of DOA No. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 4 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 List of Effective Pages: Page 1 2 3 4 5 6 7 8 Rev. 4 4 4 4 4 4 4 4 -> Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 SUPPLEMENT 1 All Page 1 of 8 P.180 AVANTI II / EVO Page 3.C 4.C 5.C 6.C 7.C 8.C Rev. 4 4 4 4 4 4 SUPPLEMENT 1 Page 2 of 8 Issued: October 21, 2005 All Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the Scott Aviation Executive MARK I portable supplementary oxygen cylinder is installed. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement, consult the Approved Airplane Flight Manual. The portable oxygen cylinder provides a supplementary oxygen source for crew and passengers use, if requested, during flights at each cabin altitude when the cabin pressurization control system is operative or below 16500 feet cabin altitude in the event the cabin pressurization control system is inoperative. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 1 Page 3 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS a. Use of supplementary oxygen is allowed only when the cabin is pressurized or the cabin altitude is below 16500 feet. b. Oxygen bottle must be stowed during takeoff and landing. c. No smoking allowed while oxygen is being used by anyone in the airplane. PLACARDS On the inner side of the cabinet door: PORTABLE OXYGEN BOTTLE USE ONLY WHEN CABIN IS PRESSURIZED OR CABIN ALT. BELOW 16500 FT OXYGEN BOTTLE MUST BE STOWED DURING TAKE-OFF AND LANDING SECTION 3 - EMERGENCY PROCEDURES No changes to the emergency procedures provided by the Section 3 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 4 - NORMAL PROCEDURES WARNING Use only when cabin is pressurized or cabin altitude below 16500 feet. Do not smoke in cabin when oxygen is in use. Keep combustible oils, greases, dusts, lint, metal chips, or other contaminants away from oxygen equipment, because they may become the initial cause of spontaneous fire or explosion. Oxygen bottle must be stowed during takeoff and landing. PREFLIGHT Check the pressure gauge on the cylinder for oxygen amount indication. NOTE Full cylinder registers 1800 psig. on pressure gauge. SUPPLEMENT 1 Page 4 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 IN-FLIGHT a. Attach masks tube over outlet fittings of the cylinder. CAUTION When using only one mask, disconnect the plug-in fitting from the outlet not in use, to be sure oxygen does not flow from that outlet. b. Open cylinder valve approximately 1/2 turn counterclockwise NOTE When cylinder valve is open, oxygen is constantly flowing into masks and will continue to flow until valve is closed or cylinder is empty. c. Check the flow indicator in the mask line for oxygen flow. When the red indicator is visible, oxygen is not available at the mask. d. Don the mask and breathe normally. e. To conserve the oxygen when not in use, turn off the oxygen supply by turning the cylinder valve clockwise until finger tight. NOTE When not in use the cylinder must be installed on its support brackets located inside the closet compartment, attached to the forward partition. SECTION 5 - PERFORMANCE No changes to the basic performance provided by the Section 5 of the Approved Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 1 Page 5 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 1 Page 6 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the Portable Supplementary Oxygen Cylinder is installed. ATA No. 35 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. OXYGEN 35-30 PORTABLE OXYGEN PORTABLE SUPPLEMENTARY CYLINDER SCOTT AVIATION EXECUTIVE MARK I – Oxygen Unit Scott Aviation Products 900019-01 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 9.00 210.00 Appr. DOA EASA.21J.685 1105-2999 18.90 1 SUPPLEMENT 1 Page 7 of 8 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 1 Page 8 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 2 Cargo and Combi Configurations (24 Pages) SUPPLEMENT NO. 2 FOR CARGO (OPTION #13) AND COMBI (OPTION #14) CONFIGURATIONS [Mod. 80-0140] Rev. 4: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- Description of Revision First Issue Approval Date October 21, 2005 1 1 to 2, 13 to 22 Editorial changes 2 1, All pages with suffix “.C” April 10, 2006 Rev. 2 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 4 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 SUPPLEMENT 2 All Page 1 of 24 P.180 AVANTI II / EVO List of Effective Pages: Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 Rev. 4 4 4 4 4 4 4 4 4 4 Page 24 Rev. 4 Page Rev. 4 4 4 4 4 4 4 4 4 4 4 4 4 3.C 4.C 5.C 6.C 7.C 8.C 9.C 10.C 11.C 12.C 13.C 14.C 15.C 16.C 17.C 18.C 19.C 20.C 21.C 22.C 23.C 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 Page 24.C Rev. 4 SUPPLEMENT 2 Page 2 of 24 Issued: October 21, 2005 All Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the airplane is equipped for cargo operations. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement consult the Approved Airplane Flight Manual. A CARGO Kit and a COMBI Kit are available for installation in the cabin compartment, after removal of passenger accomodations. Full cargo or combined cargo/passenger operations are possible when respectively the CARGO or the COMBI Kit is installed. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 2 Page 3 of 24 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS SEATING LIMITS CARGO CONFIGURATION The maximum permissible number of seats, including flight crew is 2. COMBI CONFIGURATION The maximum permissible number of seats, including flight crew is 4. FLIGHT CREW LIMITS Minimum Crew: 1 pilot and 1 operator (or copilot). NOTE The operator (or copilot) should be familiarized with load restrain system and cargo related tasks: i.e. cargo security, cargo fire inspection and fire fighting procedures. LOADING LIMITATIONS MAXIMUM LOADS a. Maximum Load for each net is 800 LBS. (363 Kg.). b. Maximum Load for each set of four straps is 800 LBS. (363 Kg.). c. Structural load must not exceed 800 LBS. (363 Kg.) for each Cargo Section. – Cargo Sections A, B and C for CARGO Configuration (ref. to page 16). – Cargo Sections A and B for COMBI Configuration (ref. to page 18). d. Maximum Specific Load on each Cargo Section must not exceed 153 LBS/ SQ.FT. (747 Kg./sq.m.) SUPPLEMENT 2 Page 4 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LOAD MAXIMUM SIZES Due to the entry door dimensions and in order to ensure the accessibility, the following load sizes must be considered: a. Maximum Height 37.40 in. (950 mm) b. Maximum Width 31.50 in. (800 mm) c. Maximum Length for each Cargo Section: – CARGO Configuration Refer to Figure 2 on page 7. – COMBI Configuration Refer to Figure 6 on page 11. d. The Maximum Forward Limit for load edge in the COMBI Configuration is at F.S. 136.6 in. (3469 mm) (Figure 6 on page 11). The Maximum Forward Limit for load edge in the CARGO Configuration is at F.S. 95.6 in. (2428 mm). e. Maximum Height of each bin or container is a function of its overall weight and must be limited in accordance with the following diagram (Figure 1) in order to avoid overload on the attachment structure Figure 1. Container Height vs. Weight Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 2 Page 5 of 24 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LOAD RESTRAINT WARNING All loads must be stowed into approved bins or containers. Loosened parcels restrained with nets are not allowed. Do not superimpose bins or containers. a. Each approved close bin or container will be restrained with a set of 4 straps (Figure 2 on page 7). b. Each approved top-open bin or container will be restrained with a net and a set of 4 straps (Figure 5 on page 10). In this event, for a safe tie-down, the minimum size of each contained parcel will be not less than 10x10x10 in. CAUTION When the airplane is configured in either CARGO or COMBI configuration the floor loading panels not utilized for cargo must be arranged in a stack and positively secured to the floor rails with a set of 4 straps. PLACARDS On the right aft partition: MAXIMUM STRUCTURAL LOAD FOR EACH CARGO SECTION 800 LBS (363 KG) ---------MAXIMUM CONCENTRATED CARGO LOAD 153 LBS/SQ.FT. (747 KG/M2) ---------MAX CARGO HEIGHT: 37.4 IN (950 MM) MAX CARGO WIDTH: 31.5 IN (800 MM) SUPPLEMENT 2 Page 6 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 2. Load restraint - Maximum lenght and width Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 2 Page 7 of 24 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 3. Load restraint - Fittings and retaining angle SUPPLEMENT 2 Page 8 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 4. Load restraint - Maximum height Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 2 Page 9 of 24 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 5. Load restraint - Nets and straps SUPPLEMENT 2 Page 10 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 6. Load restraint - Combi load arrangement Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 2 Page 11 of 24 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 3 - EMERGENCY PROCEDURES SMOKE OR FIRE IN CARGO COMPARTMENT 1. Pilot - DON MASK AND GOGGLES 2. Copilot/Operator - DON Protective Breathing Equipment NOTE Refer to the "Protective Breathing Equipment" Supplement for the use and limitations of the Emergency Escape Hood EROS P/N 15-40F. 3. Passenger oxygen (COMBI Configuration) - MANUAL MASK RELEASE 4. Pilot oxygen mask microphone - MASK 5. Bleed air switches - OFF 6. Cabin Pressurization - DUMP 7. EMERGENCY DESCENT Procedure - PERFORME After Portable Breathing Equipment donning and during the emergency descent the copilot or operator must perform the following: 8. Flashlight (at night) - LOCATE/USE 9. Portable fire extinguisher - LOCATE/USE After fire extinguished and smoke evacuation: 10. Bleed air switches - L & R 11. Passengers oxygen (COMBI Configuration) - NORMAL (if cabin altitude below 13000 ft) 12. Land as soon as pratical SUPPLEMENT 2 Page 12 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 4 - NORMAL PROCEDURES PREFLIGHT CHECK CABIN A load check has to be performed to ensure that: – all tie-down fittings are inserted and secured in the seat rails – all hooks, at the end of all straps, are safely engaged in the tie-down fittings rings – all strap-buckles are tight. – all floor loading panels not utilized for loads are arranged in a stack and safely secured to the floor rails with a set of 4 straps. A check has to be performed to ensure that the bins or the containers in each cargo section, are located against the retaining angle, previously installed in forward position of each cargo section (see detail A of Figure 3 on page 8). Figure 3 on page 8 shows a typical arrangement of two cargo sections loading for the CARGO configuration. Figure 2 on page 7 shows a typical arrangement, location, maximum dimension and restraining of the maximum cargo weight (800 lbs) on each cargo section. Figure 4 on page 9 shows a typical arrangement, location and restraining of maximum cargo volume on each cargo section. Figure 6 on page 11 shows a typical arrangement of the two cargo section loading for the COMBI configuration, with the longitudinal limitations of the forward cargo section. SECTION 5 - PERFORMANCE No changes to the basic performances provided by Section 5 of the Approved Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 2 Page 13 of 24 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 2 Page 14 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 2. LOADING INSTRUCTIONS Weight and balance data included in the Weight and Balance Manual must be completed with the following data when the airplane is arranged in either the CARGO or COMBI Configuration. CARGO AND COMBI LOADING The method of loading cargo, its placement in the airplane and the method of restraint should each be determined before starting the actual loading. For loads that are evenly distributed in a given section, the CARGO/COMBI Loading Charts for the maximum forward loading location are supplied. For any other useful load rearward location it will be necessary to determine its own C.G. and its location in the airplane. Determine the C.G. arm (Fuselage Station) by measuring in inches, from a known location in the cabin to the C.G. of the load. Determine the "moment" for the load by multiplying the weight by the C.G. arm (Fuselage Station). This resultant should be divided by 100 to be compatible with other loading data. Weight and C.G. position must be controlled during cargo operation to avoid exceeding the weight and C.G. limits. Baggage compartment can be loaded, if required, to maintain the airplane C.G. within limits. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 2 Page 15 of 24 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 CARGO CABIN CONFIGURATION (OPTION #13 ) NOTE The assumed centroid, for each cargo section, is defined by the maximum cargo load length (see Figure 2 on page 7) assuming that the bins or containers are located against the retaining angle installed in forward position of each cargo section. OCCUPANTS AND CARGO LOADING CHARTS WEIGHT LBS CREW SEATS ARM 49.20 IN WEIGHT LBS SECTION A CENTROID 177.70 IN MOMENT (LBS*IN/100) 100 110 120 130 140 150 160 170 180 190 200 210 220 49.20 54.12 59.04 63.96 68.88 73.80 78.72 83.64 88.56 93.48 98.40 103.32 108.24 SUPPLEMENT 2 Page 16 of 24 SECTION B CENTROID 142.70 IN SECTION C CENTROID 107.70 IN MOMENT (LBS*IN/100) 20 40 60 80 100 200 300 400 500 600 700 800 35.54 71.08 106.62 142.16 177.70 355.40 533.10 710.80 888.50 1066.20 1243.90 1421.60 Appr. DOA EASA.21J.685 1105-2999 28.54 57.08 85.62 114.16 142.70 285.40 428.10 570.80 713.50 856.20 998.90 1141.60 21.54 43.08 64.62 86.16 107.70 215.40 323.10 430.80 538.50 646.20 753.90 861.60 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 BAGGAGE LOADING CHARTS WEIGHT LBS REAR BAGGAGE COMPARTMENT FS 275 TO 320 ARM 298 IN WEIGHT LBS MOMENT (LBS*IN/100) 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 29.80 59.60 89.40 119.20 149.00 178.80 208.60 238.40 268.20 298.00 327.80 357.60 387.40 417.20 447.00 476.80 506.60 536.40 568.20 596.00 625.80 655.60 685.40 715.20 745.00 774.80 804.60 834.40 864.20 894.00 923.80 953.60 983.40 1013.20 1043.00 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 FORWARD CABINET FS 55 TO 70 ARM 62.5 IN MOMENT (LBS*IN/100) 5 10 15 20 25 30 34 3.13 6.25 9.38 12.50 15.63 18.75 21.25 WEIGHT LBS CABIN BAGGAGE COMPARTMENT FS 208 TO 232 ARM 220 IN MOMENT (LBS*IN/100) 10 20 30 40 50 60 70 80 90 Appr. DOA EASA.21J.685 1105-2999 22.00 44.00 66.00 80.00 110.00 132.00 154.00 176.00 198.00 SUPPLEMENT 2 Page 17 of 24 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 COMBI CABIN CONFIGURATION (OPTION # 14) NOTE The assumed centroid, for each cargo section, is defined by the maximum cargo load lenght (Figure 6 on page 11) assuming that the bins or containers are located against the retaining angle installed in forward position of each cargo section. OCCUPANTS AND CARGO LOADING CHARTS WEIGHT LBS CREW SEATS ARM 49.20 IN 100 110 120 130 140 150 160 170 180 190 200 210 220 49.20 54.12 59.04 63.96 68.88 73.80 78.72 83.64 88.56 93.48 98.40 103.32 108.24 SEATS (*) 1&2 ARM 107.70 IN SEATS (**) 1&2 ARM 107.84 IN WEIGHT LBS 107.84 118.62 129.41 140.19 150.98 161.76 172.54 183.33 194.11 204.90 215.68 226.46 237.25 SECTION B CENTROID 142.70 IN MOMENT (LBS*IN/100) MOMENT (LBS*IN/100) 107.70 118.47 129.24 140.01 150.78 161.55 172.32 183.09 193.86 204.63 215.40 226.17 236 94 SECTION A CENTROID 177.70 IN 20 40 60 80 100 200 300 400 500 600 700 800 35.54 71.08 106.62 142.16 177.70 355.40 533.10 710.80 888.50 1066.20 1243.90 1421.60 29.54 59.08 88.62 118.16 147.70 295.40 443.10 590.80 738.50 886.20 1033.90 1181.60 (*) Use these data for C.G. calculation with ERDA high comfort seats installed as per Equipment List. (**) Use these data for C.G. calculation with ERDA or GEVEN light seats installed as per Equipment List. SUPPLEMENT 2 Page 18 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 BAGGAGE LOADING CHARTS WEIGHT LBS REAR BAGGAGE COMPARTMENT FS 275 TO 320 ARM 298 IN WEIGHT LBS MOMENT (LBS*IN/100) 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 29.80 59.60 89.40 119.20 149.00 178.80 208.60 238.40 268.20 298.00 327.80 357.60 387.40 417.20 447.00 476.80 506.60 536.40 566.20 596.00 625.80 655.60 685.40 715.20 745.00 774.80 804.60 834.40 864.20 894.00 923.80 953.60 983.40 1013.20 1043.00 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 FORWARD CABINET FS 55 TO 70 ARM 62.5 IN MOMENT (LBS*IN/100) 5 10 15 20 25 30 34 3.13 6.25 9.38 12.50 15.63 18.75 21.25 WEIGHT LBS CABIN BAGGAGE COMPARTMENT FS 208 TO 232 ARM 220 IN MOMENT (LBS*IN/100) 10 20 30 40 50 60 70 80 90 Appr. DOA EASA.21J.685 1105-2999 22.00 44.00 66.00 80.00 110.00 132.00 154.00 176.00 198.00 SUPPLEMENT 2 Page 19 of 24 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST The following items, not included in the Weight and Balance Manual must be considered integral part of the Equipment List when the airplane is arranged in either the CARGO or COMBI Configuration. ATA No. 25 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. EQUIPMENT/FURNISHINGS 25-20 PASSENGER COMPARTMENT CARGO CONFIGURATION OPTION #13 – Loading Panel with Retaining Angle Piaggio 80K191241-405 8.30 99.42 8.25 1 – Loading Panel Piaggio 80K191241-401 7.00 117.06 8.19 1 – Loading Panel with Retaining Angle Piaggio 80K191241-405 8.30 134.42 11.16 1 – Loading Panel Piaggio 80K191241-401 7.00 152.06 10.64 1 – Loading Panel with Retaining Angle Piaggio 80K191241-405 8.30 169.42 14.06 1 – Loading Panel Piaggio 80K191241-401 7.00 187.06 13.09 1 – Fully Equipped Strap Piaggio S3S15BV125HRS 7.90 107.70 8.51 4 – Fully Equipped Strap Piaggio S3S15BV125HRS 7.90 142.70 11.27 4 – Fully Equipped Strap Piaggio S3S15BV125HRS 7.90 177.70 14.04 4 – Strap Fitting Piaggio 40340-14 0.88 107.70 0.95 8 SUPPLEMENT 2 Page 20 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 ATA No. ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. CARGO CONFIGURATION OPTION #13 (cont.) – Strap Fitting Piaggio 40340-14 0.88 142.70 1.26 8 – Strap Fitting Piaggio 40340-14 0.88 177.70 1.56 8 – Armrest Protection, Left Piaggio 80M09TEMATARM 1.23 145.00 1.78 1 – Armrest Protection, Right Piaggio 80M10TEMATARM 1.45 135.00 1.96 1 – Emergency Escape Hood Eros 15-40F 2.80 61.02 1.71 1 – Goggles Eros MXP210-00 0.22 52.76 0.12 1 77.94 139.28 108.55 TOTAL CARGO Configuration (*) (*) Nets and items below are not included in the TOTAL: – Net Piaggio SK1375-B 11.68 a.r. a.r. a.r. – Door Inflatable Seal Protection Piaggio 80-909781-001 0.93 a.r. a.r. 1 – Portable Cabin Fire Extinguisher Amerex Corporation Model 352 4.80 58.60 2.81 1 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 2 Page 21 of 24 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 ATA No. ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. 25-20 PASSENGER COMPARTMENT (cont.) COMBI CONFIGURATION OPTION # 14 – Fwd facing seat (RH) including belts: 1 ERDA 303267-16 (1) 43.00 107.70 46.31 ERDA 303558-12 (2) 29.00 107.84 31.27 GEVEN AV03-2102-01 (3) 29.80 107.84 32.14 – Fwd facing seat (LH) including belts: 1 ERDA 303267-15 (1) 43.00 107.70 ERDA 303558-11 (2) 29.00 107.84 31.27 GEVEN AV03-1102-01 (3) 29.80 107.84 32.14 – Loading Panel with Retaining Angle Piaggio 80K191241-405 8.30 136.00 11.29 1 – Loading Panel Piaggio 80K191241-401 7.00 152.06 10.64 1 – Loading Panel with Retaining Angle Piaggio 80K191241-405 8.30 169.42 14.06 1 – Loading Panel Piaggio 80K191241-401 7.00 187.06 13.09 1 – Fully Equipped Strap Piaggio S3S15BV125HRS 7.90 147.70 11.67 4 – Fully Equipped Strap Piaggio S3S15BV125HRS 7.90 177.70 14.04 4 – Strap Fitting Piaggio 40340-14 0.88 147.70 1.30 8 – Armrest Protection, Left Piaggio 80M09TEMATARM 1.23 145.00 1.78 1 – Armrest Protection, Right Piaggio 80M10TEMATARM 1.45 135.00 1.96 1 – Emergency Escape Hood Eros 15-40F 2.80 1.71 1 61.02 46.31 (1) Arrangement with high comfort seats. (2) Arrangement with ERDA light seats. (3) Arrangement with GEVEN light seats. SUPPLEMENT 2 Page 22 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 ATA No. ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. COMBI CONFIGURATION (cont.) OPTION # 14 – Goggles Eros MXP210-00 0.22 TOTAL COMBI Configuration (*) (1) (2) (3) 52.76 0.12 139.86 125.73 111.86 130.32 113.46 130.00 75.85 145.77 147.50 1 (*) Nets and items below are not included in the TOTAL: – Net Piaggio SK1375-B 11.68 a.r. a.r. a.r. – Door Inflatable Seal Protection Piaggio 80-909781-001 0.93 a.r. a.r. 1 – Portable Cabin Fire Extinguisher Amerex Corporation Model 352 4.80 58.60 2.81 1 (1) Arrangement with high comfort seats. (2) Arrangement with ERDA light seats. (3) Arrangement with GEVEN light seats. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 2 Page 23 of 24 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 2 Page 24 of 24 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 3 Protective Breathing Equipment (8 Pages) SUPPLEMENT NO. 3 FOR PROTECTIVE BREATHING EQUIPMENT EMERGENCY ESCAPE HOOD EROS P/N 15-40F [Mod. 80-0150] Rev. 4: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- First Issue October 21, 2005 1 ALL Editorial changes April 10, 2006 2 1, All pages with suffix “.C” Description of Revision Approval Date Rev. 2 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 4 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 SUPPLEMENT 3 All Page 1 of 8 P.180 AVANTI II / EVO List of Effective Pages: Page 1 2 3 4 5 6 7 8 Rev. 4 4 4 4 4 4 4 4 Page 3.C 4.C 5.C 6.C 7.C 8.C Rev. 4 4 4 4 4 4 SUPPLEMENT 3 Page 2 of 8 Issued: October 21, 2005 All Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the EROS P/N 15-40F Emergency Escape Hood is installed. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement consult the Approved Airplane Flight Manual. The emergency escape hood provides automatic oxygen flow and smoke protection to crew members in case of smoke detection and fire extinguishing in the cabin, if requested. The hood may be used during flight at each cabin altitude when the cabin pressurization control system is operative or up to 25000 feet cabin altitude in the event the cabin pressure control system is inoperative. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 3 Page 3 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS Use of emergency escape hood is allowed only when the cabin is pressurized or the cabin altitude is below 25000 feet. PLACARDS On the outside of cabinet where the hood is stowed: PROTECTIVE BREATHING EQUIPMENT INSIDE On the inside of cabinet where the hood is stowed: USE ONLY WHEN CABIN IS PRESSURIZED OR CABIN ALTITUDE BELOW 25000 FT (RAI APPROVED) SECTION 3 - EMERGENCY PROCEDURES SMOKE OR FIRE IN CABIN If smoke or fire is located in the cabin compartment: 1. Locate the source of smoke or fire. 2. Don the emergency escape hood following the operating instruction pictograms located on the hood box. a. Oxygen is automatically supplied after donning. Oxygen flow noise inside the hood must be heard. b. Autonomy depends on work load, but it shall be not less than 15 minutes. WARNING Use Emergency Escape Hood only when cabin is pressurized or cabin altitude below 25000 feet. SUPPLEMENT 3 Page 4 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 4 - NORMAL PROCEDURES WARNING Use Emergency Escape Hood only when cabin is pressurized or cabin altitude below 25000 feet. PREFLIGHT CHECK 1. "Good Condition" indicator on upper side of cover - CHECK GREEN SECTION 5 - PERFORMANCE No changes to the basic performances provided by Section 5 of the Approved Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 3 Page 5 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 3 Page 6 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the Protective Breathing Equipment is installed. ATA No. 35 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. OXYGEN 35-30 PORTABLE OXYGEN PROTECTIVE BREATHING EQUIPMENT – Emergency Escape Hood EROS 15-40F Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 2.80 Appr. DOA EASA.21J.685 1105-2999 61.02 1.71 1 SUPPLEMENT 3 Page 7 of 8 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 3 Page 8 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 4 First Aid Oxygen Equipment (10 Pages) SUPPLEMENT NO. 4 FOR FIRST AID OXYGEN EQUIPMENT [Mod. 80-0150] Rev. 4: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- First Issue October 21, 2005 1 ALL Editorial changes April 10, 2006 2 1, All pages with suffix “.C” Description of Revision Approval Date Rev. 2 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 4 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 List of Effective Pages: Page 1 2 3 4 5 6 7 8 9 10 Rev. 4 4 4 4 4 4 4 4 4 4 Page 3.C 4.C 5.C 6.C 7.C 8.C 9.C 10.C Rev. 4 4 4 4 4 4 4 4 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 SUPPLEMENT 4 All Page 1 of 10 P.180 AVANTI II / EVO INTENTIONALLY LEFT BLANK SUPPLEMENT 4 Page 2 of 10 Issued: October 21, 2005 All Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the first aid medical oxygen mask (EROS P/N MW37-33) and the additional outlet valve (EROS P/N DPB181-01) are installed. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement consult the the Approved Airplane Flight Manual. The First Aid Oxygen system consists in an additional outlet valve connected to the pilot’s main oxygen line and located in a convenient position in the airplane cabin depending on the type of airplane interior configuration. A medical oxygen mask with a metered two flow selector provides oxygen flow at 2 lpm NTPD or at 4 lpm NTPD. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 4 Page 3 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS 1. Do not use the first aid oxygen equipment when the cabin altitude exceeds 31000 feet. 2. When in use, the metering selector of the first aid oxygen mask must be set to 4 in the event of cabin decompression and when the cabin altitude is above 17000 feet. PLACARDS On the outside of cabinet where the mask is stowed: FIRST AID MEDICAL OXYGEN MASK INSIDE On the oxygen outlet valve cover: OXYGEN Close to the oxygen outlet valve: DO NOT SMOKE WHILE OXYGEN IS IN USE SUPPLEMENT 4 Page 4 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 3 - EMERGENCY PROCEDURES Change the corresponding Approved Airplane Flight Manual procedures as follows: RAPID OR EXPLOSIVE DECOMPRESSION (CAB PRESS LIGHT ON) 1. Crew and passenger oxygen - MANUAL MASK RELEASE/DON MASKS 2. Oxygen mask microphone - MASK 3. Emergency bleed air switch - EMER 4. EMERGENCY DESCENT Procedure - PERFORM down to 12000 ft. 5. Emergency bleed air switch - OFF If first aid oxygen is needed: 6. EMERGENCY DESCENT Procedure - PERFORM down to 8000 ft if possible 7. Crew and passengers oxygen - PILOT ONLY 8. First aid oxygen mask - DON CABIN ALTITUDE ABOVE 9,500 FETT (CAB PRESS LIGHT ON) 1. Crew and passenger oxygen - MANUAL MASK RELEASE/DON MASK 2. Oxygen mask microphone - MASK 3. Bleed air switches - VERIFY L and R position 4. Cab sel/Auto sched switch - MAN 5. Manual controller switch - DN 6. Rate control knob - AS DESIRED If cabin altitude continues to increase: 7. Emergency bleed air switch - EMER 8. EMERGENCY DESCENT Procedure - PERFORM IF REQUIRED down to 12000 ft. 9. Emergency bleed air switch - OFF Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 4 Page 5 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 If first aid oxygen is needed: 10. EMERGENCY DESCENT Procedure - PERFORM down to 8000 ft if possible 11. Crew and passengers oxygen - PILOT ONLY 12. First aid oxygen mask - DON NOTE During Emergency Descent to 8000 ft the oxygen flow supplied by the normal passengers’ oxygen masks is higher than the oxygen flow supplied by the first aid mask. To guarantee adequate first aid oxygen duration, following an Emergency Descent, switch to PILOT ONLY as soon as 8000 ft flight altitude are reached. SECTION 4 - NORMAL PROCEDURES The first aid oxygen is available at any time, during flight, connecting the appropriate oxygen mask (P/N MW37-33) to the outlet valve. The oxygen flow can be set to 2 lpm or 4 lpm. In case of use of the first aid oxygen for all the flight duration with cabin pressurization operative, in order to maintain the main oxygen system compliance with FAR 91, set the metering selector to 2 lpm. CAUTION Do not use First Aid Oxygen Equipment when cabin altitude exceeds 31000 feet. Set flow selector to 4 lpm when cabin altitude is above 17000 feet. Do not smoke while oxygen is in use. SUPPLEMENT 4 Page 6 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 5 - PERFORMANCE No changes to the basic performances provided by Section 5 of the Approved Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 4 Page 7 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 4 Page 8 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the First Aid Oxygen Equipment is installed. ATA No. 35 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. OXYGEN 35-20 PASSENGER FIRST AID OXYGEN EQUIPMENT – Oxygen Mask, First Aid Medical EROS MW37-33 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 1.00 Appr. DOA EASA.21J.685 1105-2999 61.02 0.61 1 SUPPLEMENT 4 Page 9 of 10 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 4 Page 10 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 5 Ballast Kit for Airplane Balancing (10 Pages) SUPPLEMENT NO. 5 FOR BALLAST KIT FOR AIRPLANE BALANCING Rev. 4: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- First Issue October 21, 2005 1 ALL Editorial changes April 10, 2006 2 1, All pages with suffix “.C” Description of Revision Approval Date Rev. 2 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 4 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 List of Effective Pages: Page 1 2 3 4 5 6 7 8 9 10 Rev. 4 4 4 4 4 4 4 4 4 4 -> Page 3.C 4.C 5.C 6.C 7.C 8.C 9.C 10.C Rev. 4 4 4 4 4 4 4 4 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 SUPPLEMENT 5 All Page 1 of 10 P.180 AVANTI II / EVO INTENTIONALLY LEFT BLANK SUPPLEMENT 5 Page 2 of 10 Issued: October 21, 2005 All Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when Ballast as per S.B. 80-0058 is installed. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement consult the Approved Airplane Flight Manual. In order to make easier the airplane balancing for particular cabin arrangements and load configurations the use of removable ballast may be required. A Ballast Kit is available for installation at the tailcone: a number of Weight/Arm/ Moment combinations can be obtained through a set of weights to be arranged, in a variety of amount and positions, on a suitable mounting plate. Refer to S.B. 80-0058 for ballast mounting plate installation. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 5 Page 3 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS AUTHORIZED BALLAST CAUTION Only the ballast units and related configurations listed at Section 6 of this Supplement are authorized when the suitable mounting plate is installed in the airplane tail cone as per Service Bulletin 80-0058. CAUTION When tail ballast is installed as per this Supplement, flight with no or low cabin loads (i.e. ferry fligths) may result critical for C.G. position. In such condition the pilot should carefully evaluate the needing of removable ballast to be suitably arranged in the cabin. PLACARDS In the ballast compartment, stating the maximum allowable ballast weight: MAX. BALLAST WEIGHT IS 66 LBS (30 KG) (REFER TO AFM SUPPLEMENT NO. 5 OR TO S.B. NO. 80-0058 FOR BALLAST LOADING) BALLAST MUST BE POSITIVELY FASTENED The following placard must be screwed on left side of the pilot instrument panel only when ballast is installed as per this Supplement (remove the placard when ballast is removed): BALLAST IN THE TAIL SUPPLEMENT 5 Page 4 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 3 - EMERGENCY PROCEDURES No changes to the basic information provided by Section 3 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 4 - NORMAL PROCEDURES No changes to the basic information provided by Section 4 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 5 - PERFORMANCE No changes to the basic performance provided by the Section 5 of the Approved Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 5 Page 5 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 5 Page 6 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 2. LOADING INSTRUCTIONS Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when ballast is installed as per this Supplement. NOTE The ballast management may vary depending on airworthiness regulations of the Country where the airplane is operated. WEIGHT AND BALANCE RECORD The allowable ballast configurations are listed in the Ballast Configurations Table that follows. For each numbered configuration the ballast units and associated positions are given (refer to sketches in the table). Each configuration weight, arm and moment includes the ballast only whitout the mounting plate and related hardware to be separately recorded in the "Weight and Balance Record" form. 1. After installing the ballast mounting plate enter the related weight, arm and moment (see the following "Equipment List") in the Weight and Balance Record form at page 5 of the Weight and Balance Manual. Calculate the new airplane basic weight, arm and moment. 2. Determine the required ballast. 3. From the "Ballast Configurations Table" find the appropriate ballast configuration. 4. Install the ballast units then enter the corresponding ballast configuration weight, arm and moment in the Weight and Balance Record form at page 5 of the Weight and Balance Manual. Calculate the new airplane basic weight and moment. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 5 Page 7 of 10 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 BALLAST CONFIGURATIONS TABLE SUPPLEMENT 5 Page 8 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST The following items must be considered integral part of the Equipment List as per the ballast configuration installed. ATA No. 53 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. FUSELAGE 53-80 TAIL CONE BALLAST KIT – Ballast Mounting Plate (complete with hardware) Piaggio 80K561100-401 1.05 406.41 4.27 1 – Ballast Unit Piaggio 80K561100-403 17.35 411.65 71.42 1 – Ballast Unit Piaggio 80K561100-005 12.53 (*) 1 – Ballast Unit Piaggio 80K561100-005 12.53 (*) 1 – Ballast Unit Piaggio 80K561100-005 12.53 (*) 1 – Ballast Unit Piaggio 80K561100-007 9.03 (*) 1 – Ballast Unit Piaggio 80K561100-007 9.03 (*) 1 – Ballast Unit Piaggio 80K561100-007 9.03 (*) 1 – Ballast Unit Piaggio 80K561100-011 16.10 (*) 1 – Ballast Unit Piaggio 80K561100-011 16.10 (*) 1 – Ballast Unit Piaggio 80K561100-011 16.10 (*) 1 (*) Refer to the "Ballast Configurations Table" Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 5 Page 9 of 10 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 5 Page 10 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 6 Air Ambulance Configuration (22 Pages) SUPPLEMENT NO. 6 FOR AIR AMBULANCE CONFIGURATION (OPTIONS #20 AND #21) [Mod. 80-0584 / 80-0615] Rev. 5: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- 1 2 Description of Revision First Issue October 21, 2005 1 to 2, 11 to 20 Editorial changes 1 18, 19 Approval Date April 10, 2006 March 12, 2012 Updated LOR and LOEP Equipment List updated for alternative stretchers p/n Piaggio 80-929041-801, installed with Mod. 80-1002 or S.B. 80-0316 3 1, All pages with suffix “.C” Rev. 3 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 4 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 4 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 5 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 5 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 SUPPLEMENT 6 All Page 1 of 22 P.180 AVANTI II / EVO List of Effective Pages:: Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 Rev. 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 Page 2.C 3.C 4.C 5.C 6.C 7.C 8.C 9.C 10.C 11.C 12.C 13.C 14.C 15.C 16.C 17.C 18.C 19.C 20.C 21.C 22.C Rev. 4 5 5 5 5 5 5 5 5 5 SUPPLEMENT 6 Page 2 of 22 5 5 5 5 5 5 5 5 5 5 5 Issued: October 21, 2005 All Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the airplane is equipped for Air Ambulance operations (Option #20 or #21 cabin configuration). The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement consult the Approved Airplane Flight Manual. ABBREVIATIONS BLS Basic Life Support PLUS Patient Loading and Utility System Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 6 Page 3 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS CAUTION Use of any equipment connected to the BLS must be approved by the National Aviation Authority. Compliance with FAA AC 135-15 is considered acceptable. WEIGHT LIMITS 1. 2. The following weight limitations apply to the Opt. #20 and #21 Cabinets and Cabin Baggage Compartment: a. Maximum weight in Cabin Baggage Compartment 110 lbs (49,8 kg) b. Maximum weight in Right Side Rear Cabinet 22 lbs (10,0 kg) c. Maximum weight in Left Side Rear Cabinet 61,6 lbs (28,0 kg) Electromedical equipment can be installed on each TS Side Arch (P/N 1004279-CF2-002) and TS Arch (P/N 100-4123-02-CF2-002) with the following weight limitations: a. Maximum load on TS Side Arch 25 lbs (11,3 kg) b. Maximum load on TS Side Arch (Taxi,Takeoff and Landing) 15 lbs (6,8 kg) c. Maximum load on TS Arch 3. 50 lbs (22,7 kg) A maximum of two 10 lt. oxygen bottles can be installed inside each 6’ PLUS and one on the oxygen vessel rack near the LH rear cabinet with the following weight limitation: a. Oxygen bottle (completely filled) maximum weight 44 lbs (20 kg) SEATING/LITTER LIMITS CAUTION Patients and stretchers shall be installed so that the patient’s head is in forward position. The stretcher backrest must be in the fully lowered position during taxi, take-off and landing. SUPPLEMENT 6 Page 4 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 CREW LIMITS In addition to the normal flight crew limits, a minimum of one attendant for each stretcher occupant who is incapable of independently exiting the airplane. NOTE The attendant/medical personnel should be familiarized with the use of the medical equipment installed. PLACARDS 1. On the Cabin Baggage Compartment: In the upper bay: 13.6 kg WEIGHT CAPACITY ———— MAX 30 Lbs In the middle bay: 20.4 kg WEIGHT CAPACITY ———— MAX 45 Lbs In the lower bay: 15.8 kg WEIGHT CAPACITY ———— MAX 35 Lbs 2. On the Left Side Rear Cabinet: Above the drawers: ALL DRAWERS MUST BE CLOSED WHEN NOT IN USE On the first upper drawer: 2 kg WEIGHT CAPACITY ———— MAX 4.4 Lbs On the second drawer: 3 kg WEIGHT CAPACITY ———— MAX 6.6 Lbs Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 6 Page 5 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 On each of the two lower drawers: 0.5 kg WEIGHT CAPACITY ———— MAX 1.1 Lbs In the lower bay: 20 kg WEIGHT CAPACITY ———— MAX 44 Lbs Inside each bay of the lateral compartment: 0.5 kg WEIGHT CAPACITY ———— MAX 1.1 Lbs On the Oxygen vessel rack: 20 kg WEIGHT CAPACITY ———— MAX 44 Lbs 3. On the Right Side Rear Cabinet: On the upper drawer: 6 kg WEIGHT CAPACITY ———— MAX 13.2 Lbs On the lower drawer: 4 kg WEIGHT CAPACITY ———— MAX 8.8 Lbs 4. On top of the small foldable table (when closed): PUSH TO OPEN 5. On the 2’ PLUS Unit: 40 LBS (18 KG) MAX DOOR MUST BE LATCHED DURING TAXI, TAKEOFF AND LANDING DO NOT USE AS A SEAT DURING TAXI, TAKE-OFF OR LANDING SUPPLEMENT 6 Page 6 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 6. Near the 2’ PLUS Unit: THIS SEAT MUST NOT BE OCCUPIED DURING TAKE OFF AND LANDING 7. On each 6’ PLUS Unit: On the upper area: EMERGENCY SLED RELEASE PUSH IN, TILT SLED OUT PUSH On the system control panel: AIR SUCTION PNL LTS 230 VAC CONV 12 VDC OXYGEN AIR SUCTION 230 VAC 1,4 AMPS TOTAL On both lateral sides: REMOVE HANDLES BEFORE FLIGHT On the load bay door panels: OXYGEN SHUTOFF INBOARD & OUTBOARD CLOCK-WISE OFF HIGH PRESSURE OXYGEN FILL 200 BAR MAX CAUTION USE NO OIL NO SMOKING BACKREST IN LOWEST POSITION FOR TAXI, TAKE-OFF AND LANDING ENSURE LIFELOCKS ARE FULLY ENGAGED BEFORE FLIGHT NO STORAGE ALLOWED WITH OXYGEN BOTTLE INSTALLED Inside the load bay on the oxygen shutoff panel: INBOARD OFF OUTBOARD OXYGEN Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 6 Page 7 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 On the rear side: OXYGEN AIR SUCTION LOW PSI OXYGEN CLOSE VALVE BEFORE DISCONNECTING HIGH PSI OXYGEN CLOSE VALVE BEFORE DISCONNECTING INV REMOTE LIGHTS 28 VDC 8. On each Side Arch: On the leg: TOTAL LOAD OF 25 LBS MAXIMUM INSTALLED ON THE ARCH HEAD EXTRUSION. 15 LBS FOR TAXI, TAKEOFF AND LANDING. THE CENTER OF GRAVITY MUST NOT BE MORE THAN 4" INBOARD AND ABOVE THE UPPER SURFACE. On the box: 12 VDC 230 VAC AIR OXYGEN 9. On the TS arch: 50 LBS MAXIMUM. THE CENTER OF GRAVITY MUST NOT BE MORE THAN 2" ABOVE THE UPPER SURFACE. CAUTION: IT IS THE RESPONSIBILITY OF THE OPERATOR TO ENSURE THE AIRWORTHINESS OF ANY LOAD OR EQUIPMENT MOUNTED ON THIS ARCH INCLUDING EMI, RMI, FLAMMABILITY EMERGENCY EGRESS, STRUCTURAL INTEGRITY OR ANY OTHER POTENTIAL HAZARD. SUPPLEMENT 6 Page 8 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 3 - EMERGENCY PROCEDURES EVACUATION OF NON-AMBULATORY PATIENTS In the event of an emergency evacuation, the attendant/medical personnel required at Section 2 "Limitations" of this Supplement is responsible for evacuating the non-ambulatory stretcher occupants. EVACUATION VIA CABIN DOOR 1. Open cabin door. 2. Prepare each patient for evacuation. 3. Remove each patient from the stretcher. 4. Drag each patient by lifting under both arms and backing through the door. EVACUATION VIA EMERGENCY EXIT DOOR 1. Open emergency exit door. 2. Prepare each patient for evacuation. 3. Allow pilot exit first. 4. Remove each patient from the stretcher. 5. Drag each patient by lifting under both arms and backing towards the emergency exit. 6. Put the patient leg through the emergency exit. 7. Lift the patient and allow sliding through the emergency exit. 8. The pilot lowers the patient to the ground. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 6 Page 9 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 IN THE EVENT OF EXCESSIVE ELECTRICAL LOAD 1. Pilot informs attendant/medical personnel and request for a BLS electrical load reduction. 2. Reduce electrical load. 3. Monitor electrical load. If excessive electrical load continues: 4. Pilot informs attendant/medical personnel and request to switch off all electrical loads. IN THE EVENT OF DUAL GENERATOR FAILURE 1. Pilot informs attendant/medical personnel of a zero electrical power situation and request to switch off all electrical loads. IN THE EVENT OF LITTER BREAKER TRIPPED 1. Push to reset the circuit breaker. 2. If the circuit breaker trips again do not reset until the cause of the circuit malfunction is determined and corrected. SUPPLEMENT 6 Page 10 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 4 - NORMAL PROCEDURES PREFLIGHT CHECK Referring to the Air Ambulance interior configuration approved by the National Aviation Authority, the operator must verify the correct location of the interior components. Slide Aerosled on the BLS base until fastening pins engage the latches. Check the correct engagement of all the four pins: trying to rock the stretcher from each end is an acceptable checking method. Stretchers occupants must be head forward oriented in the airplane. Each stretcher occupant shall be secured by means of the restraint harness during taxi, takeoff and landing operations.Each restraint harness is installed as required to fit each individual occupant. The shoulder straps are passed over the occupant shoulders and fastened through the buckle of the torso belt. The thigh belt is secured over the lover limbs of the occupant. Check the electromedical equipment are positively secured and related supporting frame properly fastened. Check the electrical cables for correct connection to the BLS power sockets and to the electromedical equipment rack sockets. CAUTION The installed medical equipment, as approved by the National Aviation Authority, should be checked operative as per the proper applicable operator’s manuals. NOTE Primary airplane electrical loads shall take precedence on medical system loads when an electrical load shedding is required. SECTION 5 - PERFORMANCE No changes to the basic performances provided by Section 5 of the Approved Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 6 Page 11 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 6 Page 12 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 2. LOADING INSTRUCTIONS Weight and balance data included in the Weight and Balance Manual must be completed with the following data when the airplane is arranged in the Air Ambulance Configuration. The operator must ensure the airplane is loaded within the Weight, Moment and Center of Gravity limits envelope at Section 2 of the Approved Airplane Flight Manual. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 6 Page 13 of 22 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 OPTION # 20 CABIN CONFIGURATION NOTE Seat 6 can be occupied during takeoff or landing only if the optional belted lavatory seat is installed OCCUPANTS LOADING CHART WEIGHT LBS CREW SEATS ARM 49.20 IN SEAT 1 ARM 96.25 IN LITTER 2 ARM 133.44 IN SEAT 3 ARM 129.36 IN SEAT 4 ARM 187.95 IN SEAT 5 ARM 165.36 IN SEAT 6 ARM 218.18 IN 187.95 206.75 225.54 244.34 263.13 281.93 300.72 319.52 338.31 357.11 375.90 394.70 413.49 165.36 181.90 198.43 214.97 231.50 248.04 264.58 281.11 297.65 314.18 330.72 347.26 363.79 218.18 240.00 261.82 283.63 305.45 327.27 349.09 370.91 392.72 414.54 436.36 458.18 480.00 MOMENT (LBS*IN/100) 100 110 120 130 140 150 160 170 180 190 200 210 220 49.20 54.12 59.04 63.96 68.88 73.80 78.72 83.64 88.56 93.48 98.40 103.32 108.24 SUPPLEMENT 6 Page 14 of 22 96.25 105.88 115.50 125.13 134.75 144.38 154.00 163.63 173.25 182.88 192.50 202.13 211.75 133.44 146.78 160.13 173.47 186.82 200.16 213.50 226.85 240.19 253.54 266.88 280.22 293.57 129.36 142.30 155.23 168.17 181.10 194.04 206.98 219.91 232.85 245.78 258.72 271.66 284.59 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 BAGGAGE LOADING CHARTS WEIGHT LBS REAR BAGGAGE COMPARTMENT FS 275 TO 320 ARM 298 IN WEIGHT LBS MOMENT (LBS*IN/100) 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 29.80 59.60 89.40 119.20 149.00 178.80 208.60 238.40 268.20 298.00 327.80 357.60 387.40 417.20 447.00 476.80 506.60 536.40 566.20 596.00 625.80 655.60 685.40 715.20 745.00 774.80 804.60 834.40 864.20 894.00 923.80 953.60 983.40 1013.20 1043.00 WEIGHT (*) LBS 6’ PLUS STOWAGE COMPT. ARM 131.2 IN. MOMENT (LBS*IN/100) 5 10 15 20 25 30 34 3.13 6.25 9.38 12.50 15.63 18.75 21.25 WEIGHT LBS CABIN BAGGAGE COMPARTMENT FS 208 TO 232 ARM 220 IN MOMENT (LBS*IN/100) 10 20 30 40 50 60 70 80 90 100 110 22.00 44.00 66.00 80.00 110.00 132.00 154.00 176.00 198.00 220.00 242.00 WEIGHT LBS 2’ PLUS CABINET FS 71 TO 95 ARM 83.2 IN MOMENT (LBS*IN/100) 5 10 15 20 25 30 35 40 MOMENT (LBS*IN/100) 5 10 15 20 6.56 13.12 19.68 26.24 Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 FORWARD CABINET FS 55 TO 70 ARM 62.5 IN 4.16 8.32 12.48 16.64 20.80 24.96 29.12 33.28 (*) Payload when no oxygen bottle is installed inside the stowage compartment. Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 6 Page 15 of 22 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 BAGGAGE LOADING CHARTS (Cont.) WEIGHT LBS LEFT SIDE REAR CABINET FS 192 TO 206 ARM 197 IN. WEIGHT LBS MOMENT (LBS*IN/100) 5 10 15 20 25 30 35 40 45 50 55 60 SUPPLEMENT 6 Page 16 of 22 RIGHT SIDE REAR CABINET FS 198 TO 206 ARM 200 IN. MOMENT (LBS*IN/100) 9.85 19.70 29.55 39.40 49.25 59.10 68.95 78.80 88.65 98.50 108.35 118.20 5 10 15 20 22 Appr. DOA EASA.21J.685 1105-2999 10.00 20.00 30.00 40.00 44.00 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 OPTION # 21 CABIN CONFIGURATION NOTE Seat 5 can be occupied during takeoff or landing only if the optional belted lavatory seat is installed. OCCUPANTS LOADING CHART WEIGHT LBS CREW SEATS ARM 49.20 IN SEAT 1 ARM 96.25 IN 100 110 120 130 140 150 160 170 180 190 200 210 220 49.20 54.12 59.04 63.96 68.88 73.80 78.72 83.64 88.56 93.48 98.40 103.32 108.24 96.25 105.88 115.50 125.13 134.75 144.38 154.00 163.63 173.25 182.88 192.50 202.13 211.75 LITTER 2 ARM 133.44 IN LITTER 3 ARM 150.00 IN SEAT 4 ARM 187.95 IN SEAT 5 ARM 218.18 IN 187.95 206.75 225.54 244.34 263.13 281.93 300.72 319.52 338.31 357.11 375.90 394.70 413.49 218.18 240.00 261.82 283.63 305.45 327.27 349.09 370.91 392.72 414.54 436.36 458.18 480.00 MOMENT (LBS*IN/100) Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 133.44 146.78 160.13 173.47 186.82 200.16 213.50 226.85 240.19 253.54 266.88 280.22 293.57 150.00 165.00 180.00 195.00 210.00 225.00 240.00 255.00 270.00 285.00 300.00 315.00 330.00 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 6 Page 17 of 22 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 BAGGAGE LOADING CHARTS REAR BAGGAGE COMPARTMENT FS 275 TO 320 ARM 298 IN WEIGHT LBS WEIGHT LBS MOMENT (LBS*IN/100) 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 SUPPLEMENT 6 Page 18 of 22 29.80 59.60 89.40 119.20 149.00 178.80 208.60 238.40 268.20 298.00 327.80 357.60 387.40 417.20 447.00 476.80 506.60 536.40 566.20 596.00 625.80 655.60 685.40 715.20 745.00 774.80 804.60 834.40 864.20 894.00 923.80 953.60 983.40 1013.20 1043.00 FORWARD CABINET FS 55 TO 70 ARM 62.5 IN MOMENT (LBS*IN/100) 5 10 15 20 25 30 34 3.13 6.25 9.38 12.50 15.63 18.75 21.25 WEIGHT LBS CABIN BAGGAGE COMPARTMENT FS 208 TO 232 ARM 220 IN MOMENT (LBS*IN/100) 10 20 30 40 50 60 70 80 90 100 110 22.00 44.00 66.00 80.00 110.00 132.00 154.00 176.00 198.00 220.00 242.00 WEIGHT LBS 2’ PLUS CABINET FS 71 TO 95 ARM 83.2 IN MOMENT (LBS*IN/100) 5 10 15 20 25 30 35 40 Appr. DOA EASA.21J.685 1105-2999 4.16 8.32 12.48 16.64 20.80 24.96 29.12 33.28 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 BAGGAGE LOADING CHARTS (Cont.) WEIGHT (*) LBS 6’ PLUS STOWAGE COMPT. (RH) ARM 131.2 IN. WEIGHT LBS MOMENT (LBS*IN/100) MOMENT (LBS*IN/100) 5 10 15 20 6.56 13.12 19.68 26.24 WEIGHT (*) LBS 6’ PLUS STOWAGE COMPT. (LH) ARM 144.8 IN. 5 10 15 20 25 30 35 40 45 50 55 60 9.85 19.70 29.55 39.40 49.25 59.10 68.95 78.80 88.65 98.50 108.35 118.20 WEIGHT LBS RIGHT SIDE REAR CABINET FS 198 TO 206 ARM 200 IN. MOMENT (LBS*IN/100) 5 10 15 20 7.24 14.48 21.72 28.96 (*) Payload when no oxygen bottle is installed inside the stowage compartment. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 LEFT SIDE REAR CABINET FS 192 TO 206 ARM 197 IN. MOMENT (LBS*IN/100) 5 10 15 20 22 Appr. DOA EASA.21J.685 1105-2999 10.00 20.00 30.00 40.00 44.00 SUPPLEMENT 6 Page 19 of 22 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST The following items, not included in the Weight and Balance Manual must be considered integral part of the Equipment List when the airplane is arranged in the AIR AMBULANCE Configuration (Options # 20 or # 21). ATA No. 25 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. 28.52 83.20 23.73 1 28.70 96.25 27.62 1 – 6’ PLUS Unit (1) 125.30 129.20 LifePort Inc. 366-4300-CF2-002 or (if Mod. 80-1002 or S.B. 80-0316 installed)Piaggio 80-929041-801 161.89 1 – Aerosled TS Side Arch LifePort Inc. 100-4279-CF2-002 25.00 151.00 37.75 1 – Aerosled TS Stretcher LifePort Inc. 100-4065-CF2-002 with 36.60 133.44 48.84 1 – Aerosled TS Arch LifePort Inc. 100-4049-CF2-002 or – Aerosled TD Strecher LifePort Inc. 100-4123-02-CF2-002 4.85 139.00 6.74 1 35.00 133.44 46.70 1 – FWD Facing Seat (LH) ERDA 303453-4 47.80 129.36 61.83 1 – FWD Facing Seat (LH) ERDA 303453-4 47.80 165.36 79.04 1 – FWD Facing Seat (RH) GEVEN AV03-2113-02 30.10 187.95 56.57 1 EQUIPMENT/FURNISHINGS 25-20 PASSENGER COMPARTMENT OPTION #20 CABIN CONFIGURATION – 2’ PLUS Unit LifePort Inc. 100-4568-CF2-002 (1) – Side facing seat GEVEN AV11-3521-00 – Rear Cabinet, LH side Piaggio 80-909820-803 (2) 41.88 197.00 82.50 1 – Cabin Baggage Compartment Piaggio 80-909942-801 (3) 50.70 220.00 111.54 1 (1) Mounting plates weight included. (2) Includes Rear Cabinet assy P/N 80-909818803 and Rear Cabinet support assy P/N 80909946-801. (3) Includes Cabinet assy P/N 80-909943-801. SUPPLEMENT 6 Page 20 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 ATA No. ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. 25-20 PASSENGER COMPARTMENT OPTION #20 CABIN CONFIGURATION (cont.) – Rear Cabinet, RH side LifePort Inc. 180-2360-CF2-02 20.80 200.00 41.60 1 – Oxygen Vessel Rack Piaggio 80-909947-801 5.40 187.47 10.12 1 – Loading Ramp LifePort Inc. 100-4472 or LR2-077-53-270-390 – 33.00 298.00 98.34 1 28.52 83.20 23.73 1 28.70 96.25 27.62 1 – 6’ PLUS Unit (RH) (1) 125.30 129.20 LifePort Inc. 366-4300-CF2-002 or (if Mod. 80-1002 or S.B. 80-0316 installed) Piaggio 80-929041-801 161.89 1 – Aerosled TS Side Arch (RH) LifePort Inc. 100-4279-CF2-002 25.00 151.00 37.75 1 – Aerosled TS Stretcher (RH) LifePort Inc. 100-4065-CF2-002 with 36.60 133.44 48.84 1 – Aerosled TS Arch LifePort Inc. 100-4049-CF2-002 or – Aerosled TD Strecher (RH) LifePort Inc. 100-4123-02-CF2-002 4.85 139.00 6.74 1 35.00 133.44 46.70 1 – 6’ PLUS Unit (LH) (1) 125.30 152.76 LifePort Inc. 366-4300-CF2-002 or (if Mod. 80-1002 or S.B. 80-0316 installed) Piaggio 80-929041-801 191.41 1 – Aerosled TS Stretcher (LH) LifePort Inc. 100-4065-CF2-002 or – Aerosled TD Strecher (LH) LifePort Inc. 100-4123-02-CF2-002 36.60 150.00 54.90 1 35.00 150.00 52.50 1 OPTION # 21 CABIN CONFIGURATION – 2’ PLUS Unit LifePort Inc. 100-4568-CF2-002 (1) – Side facing seat GEVEN AV11-3521-00 (1) Mounting plates weight included. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 6 Page 21 of 22 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 ATA No. ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. 25-20 PASSENGER COMPARTMENT OPTION #21 CABIN CONFIGURATION (cont.) – FWD Facing Seat GEVEN AV03-2113-02 30.10 187.95 56.57 1 – Rear Cabinet, LH side Piaggio 80-909820-803 (2) 41.88 197 82.50 1 – Cabin Baggage Compartment Piaggio 80-909942-801 (3) 50.70 220.00 111.54 1 – Rear Cabinet, RH side LifePort Inc. 180-2360-CF2-02 20.80 200.00 41.60 1 – Oxygen Vessel Rack Piaggio 80-909947-801 5.40 187.47 10.12 1 – Loading Ramp LifePort Inc. 100-4472 or LR2-077-53-270-390 33.00 298.00 98.34 1 (2) Includes Rear Cabinet assy P/N 80-909818803 and Rear Cabinet support assy P/N 80909946-801. (3) Includes Cabinet assy P/N 80-909943-801. SUPPLEMENT 6 Page 22 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 7 SeaFLIR II System (22 Pages) SUPPLEMENT NO. 7 FOR SEAFLIR II SYSTEM [Mod. 80-0490, 80-0560, 80-0704, 80-0705, 80-1010] Rev. 6: Mar. 04, 2019 Supplement 7 IS NOT applicable to MSN 3001 + (EVO) airplanes LOG OF REVISIONS Rev. No. Revised Pages 0 -- 1 1 to 2, 19 to 20 2 3 Description of Revision Approval Date First Issue October 21, 2005 Editorial changes April 10, 2006 1 19 20 Update LOR and LOEP Add alternate P/N Rearrange material June 28, 2006 1,2 Design Changes reference updated; LOR and LOEP updated Limitations Section updated Eq. List updated Mar. 12, 2012 3 19,20 4 1 Revision issued for P.180 Avanti “EVO” MSN 3001 and up, introducing a complete AFM applicable to MSN 3001 + airplanes. Rev. 4 is only issued for documental traceability. Supplement 7 at Rev. 4 IS NOT applicable to EVO airplanes 5 ALL Revision issued for re-arrange material Rev. 5 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 SUPPLEMENT 7 All Page 1 of 22 P.180 AVANTI II / EVO Rev. No. Revised Pages Description of Revision Approval Date 6 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 6 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 List of Effective Pages: Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 Rev. 6 6 6 6 6 6 6 6 6 6 6 SUPPLEMENT 7 Page 2 of 22 6 6 6 6 6 6 6 6 6 6 6 Issued: October 21, 2005 All Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the SeaFLIR II Imaging System is installed on the airplane as per Mod. 80-0490, 80-0560, 80-0704, 80-0705, 80-1010 or as per relevant Service Bulletins.. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement, consult the basic Airplane Flight Manual. The SeaFLIR II Imaging System is certified for installation with the Option #10 Cabin Configuration. Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 3 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS SeaFLIR II Imaging System performance and functionalities have not been demonstrated as part of the civil certification process. SEAFLIR II SYSTEM LIMITATIONS During Take-off and Landing the SeaFLIR II Cockpit Display must be positioned close to the cockpit right sidewall and properly secured with the related locking strip. During operation of the SeaFLIR II Cockpit Display: – the display, in operating position, must be properly secured with the locking strip in order not to interfere with the copilot flight controls and not to disturb pilot visibility of the right side instruments; – the operator sitting in front of the display, on the right side of the flight compartment, is not allowed to perform copilot operations; – dual pilot certified operations are not allowed. PLACARDS 1. On the right side of the cabin flight compartment, close to the SeaFLIR II Display: STOW AND SECURE DURING TAKE OFF AND LANDING SECURE DURING OPERATION 2. In the cabin passenger compartment, on the FLIR/TV Monitor Console leaf: LEAF MUST BE STOWED FOR TAKE OFF AND LANDING SECTION 3 - EMERGENCY PROCEDURES No changes to the emergency procedures provided by Section 3 of the Approved Airplane Flight Manual are necessary for this Supplement. SUPPLEMENT 7 Page 4 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 4 - NORMAL PROCEDURES OPERATIONS WITH SEAFLIR II SYSTEM INSTALLED For the correct FLIR/TV Camera operation and to assure the Stabilized Gimbal Assembly service and operational life, it is recommended not to exceed the following Airspeed, Altitude and Air Temperature values: 1. Maximum speed 2. Maximum Altitude 3. 4. 218 KCAS 219 KIAS a. FLIR non-operating 25,000 FT b. FLIR operating 15,000 FT Minimum Static Air Temperature a. FLIR non-operating -46°C (-51°F) b. FLIR operating -20°C (-4°F) a. FLIR non operating +71°C (+160°F) b. FLIR operating +55°C (+131°F) Maximum Static Air Temperature PREFLIGHT CHECK - REAR FUSELAGE (LEFT SIDE) During the preflight walk-around check the conditions of the Stabilized Gimbal Assembly (SGA) and related Installation Assembly on the Rear Fuselage (Left Side). Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 5 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 5 - PERFORMANCE Performance data provided by Section 5 of the basic Airplane Flight Manual are to be corrected as follows when the SeaFlir II system is installed on the airplane: – Take-off Weight (Flaps MID) - ref. to Figure 1 of this Supplement; – Twin Engine Climb (Flaps MID) - ref. to Figure 2 of this Supplement; – Twin Engine Climb (Flaps Retracted) - ref. to Figure 3 of this Supplement; – One Engine Inoperative Climb (Flaps Retracted) - ref. to Figure 4 of this Supplement; – Maximum Cruise Power - 2000 RPM (ISA -30° ÷ ISA +30°) - ref. to Figures from 5 to 11 of this Supplement; – Maximum Range Power - 2000 RPM (ISA -30° ÷ ISA +30°) - ref. to Figures from 12 to 18 of this Supplement; – Balked Landing Climb Torque (Flaps Down) - ref. to Figure 19 of this Supplement; – For Single Engine Go Around Landing Weight, during CAT II approaches, performance data reported in Figure 5-75 of Section 5 of the Airplane Flight Manual are to be corrected with those reported in Figure 20 of this Supplement. SUPPLEMENT 7 Page 6 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED Figure 1. Takeoff Weight - Flaps MID Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 7 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED Figure 2. Twin Engine Climb - Flaps MID SUPPLEMENT 7 Page 8 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED Figure 3. Twin Engine Climb - Flaps Retracted Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 9 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED Figure 4. One Engine Inoperative Climb - Flaps Retracted SUPPLEMENT 7 Page 10 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED MAXIMUM CRUISE POWER - 2000 RPM ISA -30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. FEET °C °F % 0 -15 5 46.3 TOTAL FUEL FLOW LBS/HR LBS/HR 397 794 AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 206 219 206 219 206 219 5000 -25 -13 50.0 364 728 221 219 221 219 221 219 10000 -35 -31 53.7 337 674 238 219 238 219 238 219 15000 -45 -48 57.4 315 630 256 219 256 219 256 219 21000 -57 -70 60.9 295 590 280 219 280 219 280 219 23000 -61 -77 62.6 292 584 289 219 289 219 289 219 25000 -65 -84 64.1 288 576 298 219 298 219 298 219 Figure 5. Maximum Cruise Power - 2000 RPM - ISA -30°C MAXIMUM CRUISE POWER - 2000 RPM ISA -20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. FEET °C °F % 0 -5 23 47.2 TOTAL FUEL FLOW LBS/HR LBS/HR 400 800 AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 210 219 210 219 210 219 5000 -15 5 51.0 368 736 226 219 226 219 226 219 10000 -25 -13 54.8 342 684 243 219 243 219 243 219 15000 -35 -30 58.6 321 642 261 219 261 219 261 219 21000 -47 -52 62.3 302 604 287 219 287 219 287 219 23000 -51 -59 64.0 299 598 296 219 296 219 296 219 25000 -55 -66 65.6 296 592 305 219 305 219 305 219 Figure 6. Maximum Cruise Power - 2000 RPM - ISA -20°C Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 11 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED MAXIMUM CRUISE POWER - 2000 RPM ISA -10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS FEET °C °F % 0 5 41 48.1 400 800 214 219 214 219 214 219 5000 -5 23 52.0 373 746 230 219 230 219 230 219 10000 -15 5 55.9 348 696 247 219 247 219 247 219 15000 -25 -12 59.8 327 654 267 219 267 219 267 219 21000 -37 -34 63.6 309 618 293 219 293 219 293 219 23000 -41 -41 65.4 307 614 302 219 302 219 302 219 25000 -45 -48 67.1 304 608 312 219 312 219 312 219 Figure 7. Maximum Cruise Power - 2000 RPM - ISA -10°C MAXIMUM CRUISE POWER - 2000 RPM ISA PRESS. ALT. SAT FEET °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 15 59 48.9 403 806 218 219 218 219 218 219 5000 5 41 53.0 377 754 234 219 234 219 234 219 10000 -5 23 57.0 354 708 252 219 252 219 252 219 15000 -15 6 61.0 335 670 272 219 272 219 272 219 21000 -27 -16 65.0 317 634 299 219 299 219 299 219 23000 -31 -23 66.8 315 630 309 219 309 219 309 219 25000 -35 -30 68.5 312 624 319 219 319 219 319 219 Figure 8. Maximum Cruise Power - 2000 RPM - ISA SUPPLEMENT 7 Page 12 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED MAXIMUM CRUISE POWER - 2000 RPM ISA +10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS FEET °C °F % 0 25 77 49.8 408 816 222 219 222 219 222 219 5000 15 59 53.9 384 768 238 219 238 219 238 219 10000 5 41 58.1 361 722 257 219 257 219 257 219 15000 -5 24 62.2 342 684 277 219 277 219 277 219 21000 -17 2 66.3 325 650 305 219 305 219 305 219 23000 -21 -5 68.2 323 646 315 219 315 219 315 219 25000 -25 -12 70.0 320 640 325 219 325 219 325 219 Figure 9. Maximum Cruise Power - 2000 RPM - ISA +10°C MAXIMUM CRUISE POWER - 2000 RPM ISA +20°C PRESS. ALT. FEET SAT °C ENG. FUEL TORQUE FLOW PER ENG. °F % TOTAL FUEL FLOW LBS/HR LBS/HR AIRSPEED KNOTS 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS TAS TAS IAS IAS IAS 0 35 95 50.6 416 832 225 219 225 219 225 219 5000 25 77 54.8 391 782 243 219 243 219 243 219 10000 15 59 59.1 370 740 261 219 261 219 261 219 15000 5 42 63.3 351 702 282 219 282 219 282 219 21000 -7 20 67.5 334 668 311 219 311 219 311 219 23000 -11 13 69.5 332 664 321 219 321 219 321 219 25000 -15 6 71.3 329 658 332 219 332 219 332 219 Figure 10. Maximum Cruise Power - 2000 RPM - ISA +20°C Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 13 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED MAXIMUM CRUISE POWER - 2000 RPM ISA +30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. FEET °C °F % 0 45 113 51.4 TOTAL FUEL FLOW AIRSPEED KNOTS LBS/HR LBS/HR 425 850 11000 LBS 10000 LBS 9000 LBS (4990 KG) (4536 KG) (4082 KG) TAS IAS TAS IAS TAS IAS 229 219 229 219 229 219 5000 35 95 55.7 401 802 247 219 247 219 247 219 10000 25 77 60.1 379 758 266 219 266 219 266 219 15000 15 60 64.4 361 722 287 219 287 219 287 219 21000 3 38 68.8 342 684 317 219 317 219 317 219 23000 -1 31 70.8 3 38 327 219 327 219 327 219 25000 -5 24 72.7 334 668 338 219 338 219 338 219 Figure 11. Maximum Cruise Power - 2000 RPM - ISA +30°C MAXIMUM RANGE POWER - 2000 RPM ISA -30°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -15 5 46.3 397 206 219 44.8 392 206 219 43.2 388 206 219 -25 -13 50.0 364 221 219 48.7 361 221 219 47.3 357 221 219 10000 -35 -31 53.7 337 238 219 51.0 330 236 217 48.3 322 233 214 15000 -45 -48 51.2 298 244 208 48.2 290 240 206 44.5 280 236 201 21000 -57 -70 46.7 256 249 194 43.9 248 245 191 41.3 241 242 188 23000 -61 -77 47.3 249 255 192 42.4 235 247 186 40.0 228 244 184 25000 -65 -84 47.4 240 260 190 43.2 228 254 185 38.4 215 245 179 5000 Figure 12. % LBS/HR KTS KTS % LBS/HR KTS KTS Maximum Range Power - 2000 RPM - ISA -30°C SUPPLEMENT 7 Page 14 of 22 LBS/HR KTS KTS Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED MAXIMUM RANGE POWER - 2000 RPM ISA -20°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -5 23 47.2 400 210 219 45.6 395 210 219 44.0 390 210 219 5000 -15 5 51.0 368 226 219 49.6 364 226 219 48.2 360 226 219 10000 -25 -13 53.7 339 241 217 50.0 329 237 214 47.8 323 235 212 15000 -35 -30 51.1 300 246 206 47.9 291 243 203 44.8 283 239 200 21000 -47 -52 47.4 260 254 193 44.3 251 249 190 41.6 244 246 187 23000 -51 -59 48.3 254 260 192 42.9 239 251 185 40.3 231 248 183 25000 -55 -66 47.9 245 264 189 43.7 232 258 184 38.9 219 250 178 Figure 13. LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Maximum Range Power - 2000 RPM - ISA -20°C MAXIMUM RANGE POWER - 2000 RPM ISA -10°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 5 41 48.1 400 214 219 46.5 395 214 219 44.8 390 214 219 5000 -5 23 52.0 373 230 219 50.5 368 230 219 49.1 364 230 219 10000 -15 5 52.2 337 240 213 49.0 328 237 210 46.2 320 234 207 15000 -25 -12 50.4 301 248 203 47.1 291 244 200 43.9 282 240 197 21000 -37 -34 47.3 262 256 191 44.6 254 253 189 41.9 246 250 186 23000 -41 -41 48.3 256 263 190 43.3 242 255 184 40.6 234 252 181 25000 -45 -48 48.5 248 269 188 43.6 234 260 182 39.2 221 253 177 Figure 14. LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Maximum Range Power - 2000 RPM - ISA -10°C Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 15 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED MAXIMUM RANGE POWER - 2000 RPM ISA 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 15 59 48.9 403 218 219 47.3 398 218 219 45.6 392 218 219 5000 5 41 51.9 374 232 217 49.0 365 230 215 46.0 355 227 212 10000 -5 23 51.9 339 242 210 48.1 328 238 207 45.7 320 236 205 15000 -15 6 50.8 305 251 202 46.8 293 246 197 43.5 283 242 194 21000 -27 -16 47.7 266 260 190 44.4 256 255 186 41.7 248 252 184 23000 -31 -23 48.8 261 267 189 43.6 246 259 183 40.3 236 253 179 25000 -35 -30 49.1 253 273 187 43.9 238 264 180 39.5 225 257 175 Figure 15. LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Maximum Range Power - 2000 RPM - ISA MAXIMUM RANGE POWER - 2000 RPM ISA +10°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 25 77 48.9 405 220 218 45.8 394 218 215 42.6 383 215 212 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 5000 15 59 49.7 370 231 212 46.1 358 227 208 43.0 347 223 205 10000 5 41 49.9 336 241 205 46.0 323 236 201 42.7 313 232 198 15000 -5 24 50.0 306 252 198 46.6 295 248 195 43.0 284 244 192 21000 -17 2 48.0 270 264 189 44.8 260 259 185 41.3 250 254 181 23000 -21 -5 49.2 265 271 188 43.4 248 261 181 40.6 239 257 178 25000 -25 -12 49.6 258 277 185 44.4 242 269 180 39.2 226 259 173 Figure 16. Maximum Range Power - 2000 RPM - ISA +10°C SUPPLEMENT 7 Page 16 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED MAXIMUM RANGE POWER - 2000 RPM ISA +20°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 35 95 46.7 401 218 212 43.1 387 214 208 39.8 374 211 205 5000 25 77 47.7 367 229 206 44.0 353 224 203 40.7 341 221 199 10000 15 59 48.5 336 240 201 43.9 320 234 196 40.6 309 230 192 15000 5 42 49.3 308 253 195 45.2 295 247 191 41.4 283 242 187 21000 -7 20 47.4 272 265 186 44.5 263 261 183 41.1 252 256 179 23000 -11 13 49.7 271 275 187 43.3 251 263 178 40.3 241 259 175 25000 -15 6 50.5 265 283 185 44.8 247 272 178 39.5 231 263 172 Figure 17. LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Maximum Range Power - 2000 RPM - ISA +20°C MAXIMUM RANGE POWER - 2000 RPM ISA +30°C 11000 LBS (4990 KG) PRESS. ALT. SAT 10000 LBS (4536 KG) 9000 LBS (4082 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 45 113 45.9 LBS/HR KTS KTS 404 % 218 209 42.0 LBS/HR KTS KTS 388 % LBS/HR KTS KTS 214 205 38.2 372 210 201 5000 35 95 46.3 367 228 202 42.6 352 223 198 38.6 337 218 194 10000 25 77 47.2 336 239 197 42.5 319 233 191 39.1 307 228 188 15000 15 60 49.6 313 256 194 44.8 298 248 189 40.0 282 241 183 21000 3 38 47.8 278 268 185 44.3 267 263 181 40.2 254 255 175 23000 -1 31 50.7 278 280 187 43.5 256 266 177 40.1 245 261 173 25000 -5 24 51.5 272 288 185 45.6 254 277 178 39.2 234 264 170 Figure 18. Maximum Range Power - 2000 RPM - ISA +30°C Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 17 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED Figure 19. Balked Landing Climb - Flaps Down SUPPLEMENT 7 Page 18 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SEAFLIR II SYSTEM INSTALLED Figure 20. Landing Weight - Single Engine Go Around Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 19 of 22 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 7 Page 20 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the SeaFLIR II System Imaging System in installed. The SeaFLIR II System is certified for installation with the Option #10 Cabin Configuration. ATA No. 93 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. SURVEILLANCE SEAFLIR II IMAGING SYSTEM – Stabilized Gimbal Assembly (SGA) FLIR Systems Inc. 18531-201 28.70 298.00 85.53 1 – FLIR/TV Camera Install. Assembly Piaggio 80K341324-801 7.90 310.70 24.55 1 – 5.6 in. Display Rosen 5601-064 or 7 in. Display Rosen 7002-062 2.20 8.00 0.62 1 – Display Base Receptacle Rosen 0100-002 0.32 8.00 0.02 1 – FLIR/TV Display Console Install. Piaggio 80-909894-803 (Mod. 80-0705/Mod. 80-1010) which includes: – Control Electronics Unit (CEU) FLIR Systems Inc. 18528-200 – Hand Control Unit (HCU) FLIR Systems Inc. 18217-200 – Signal Data Converter Shadin Company 933609 or (if Mod. 80-1010 installed) Shadin Avionics 933612-02 – 15 in. Display Barco K9343012 61.70 90.20 55.65 1 – Hatch (FLIR/TV Camera not installed) Piaggio 80K341331-001 0.50 298.00 1.50 1 – or Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 7 Page 21 of 22 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 7 Page 22 of 22 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 8 KHF990 HF Communication System (8 Pages) SUPPLEMENT NO. 8 FOR BENDIX/KING KHF990 HF COMMUNICATION SYSTEM [Mod. 80-0261, 80-0597] Rev. 5: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- First Issue October 21, 2005 1 ALL Editorial changes April 10, 2006 2 3 Normal Procedures - clarification note March 12, 2012 Revision issued for P.180 Avanti “EVO” MSN 3001 and up, introducing a complete AFM applicable to MSN 3001 + airplanes. Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: Dec. 12, 2014 3 1, All pages with suffix “.C” Description of Revision Approval Date 4 ALL Revision issued for re-arrange material Rev. 4 is approved due to applicability MSN 1105-2999 under the authority of and 3001+ DOA No. EASA.21J.220 Date: March 09, 2015 5 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Rev. 5 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 SUPPLEMENT 8 All Page 1 of 8 P.180 AVANTI II / EVO List of Effective Pages: : Page 1 2 3 4 5 6 7 8 Rev. 5 5 5 5 5 5 5 5 Page 3.C 4.C 5.C 6.C 7.C 8.C Rev. 5 5 5 5 5 5 SUPPLEMENT 8 Page 2 of 8 Issued: October 21, 2005 All Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the Bendix/King KHF990 HF Radio Communication System is installed. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement consult the basic Airplane Flight Manual High Frequency radio communications allow reliable long range transmission and reception over distances of thousands of miles. This makes HF radio particularly useful when flying over vast water surfaces or desert land areas where VHF communications, limited to line of sight transmission, are out of reach. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 8 Page 3 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS No changes to the limitations provided by Section 2 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 3 - EMERGENCY PROCEDURES No changes to the emergency procedures provided by Section 3 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 4 - NORMAL PROCEDURES WARNING When performing a HF radio check on the ground, make certain that all personnel are clear of the HF probe antenna before transmitting. Serious HF burns can result from direct contact with the antenna when the system is transmitting. NOTE ADF and Torque indications may be affected during HF COM transmission. NOTE When the airplane is flown in “single pilot” configuration, the pilot can achieve HF control panel if pilot Autopilot is engaged. PREFLIGHT CHECK REAR FUSELAGE HF probe antenna - CHECK FOR INSTALLATION AND CONDITION BEFORE ENGINE STARTING HF communication system -CHECK OFF BEFORE ENGINE SHUTDOWN HF communication system -CHECK OFF SUPPLEMENT 8 Page 4 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 5 - PERFORMANCE No changes to the performance data provided by Section 5 of the Approved Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 8 Page 5 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 8 Page 6 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the Bendix/King KHF990 HF Communication System is installed. ATA No. 23 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. COMMUNICATIONS 23-10 SPEECH COMMUNICATIONS HF COMM SYSTEM – Transceiver KTR993 Bendix/King 063-01007-0000 13.01 335.94 43.70 1 – Mounting Kit Bendix/King 050-02121-0001 1.01 335.94 3.61 1 – Control Panel KFS594 Bendix/King 071-01274-0002 0.80 51.40 0.41 1 – Antenna Coupler KAC992 Bendix/King 064-01029-0000 7.90 411.61 32.11 1 – Antenna KAC992 Bendix/King 071-01272-0001 1.00 464.00 4.64 1 Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 8 Page 7 of 8 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 8 Page 8 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 9 FA2100 Cockpit Voice Recorder (8 Pages) SUPPLEMENT NO. 9 FOR L-3 COMMUNICATIONS FA2100 COCKPIT VOICE RECORDER [Mod. 80-0267, 80-0599] Rev. 4: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- First Issue October 21, 2005 1 ALL Editorial changes April 10, 2006 2 1, All pages with suffix “.C” Description of Revision Approval Date Rev. 2 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 4 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 Issued: October 21, 2005 Rev. 4: Mar. 04. 2019 SUPPLEMENT 9 All Page 1 of 8 P.180 AVANTI II / EVO List of Effective Pages: : Page 1 2 3 4 5 6 7 8 Rev. 4 4 4 4 4 4 4 4 Page 3.C 4.C 5.C 6.C 7.C 8.C Rev. 4 4 4 4 4 4 SUPPLEMENT 9 Page 2 of 8 Issued: October 21, 2005 All Rev. 4 : Mar. 04. 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the L-3 Communications FA2100 Cockpit Voice Recorder is installed. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement consult the basic Approved Airplane Flight Manual. The FA2100 Cockpit Voice Recorder allows storing up to one hundred and twenty (120) minutes of cockpit audio and is provided with an Underwater Locator Beacon (ULB). Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 9 Page 3 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS No changes to the limitations provided by Section 2 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 3 - EMERGENCY PROCEDURES No changes to the emergency procedures provided by Section 3 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 4 - NORMAL PROCEDURES PREFLIGHT CHECK Conduct Preflight Self Test as follows: 1. Press and hold the CVR control unit TEST button firmly for at least five seconds and then release. This initiates the CVR Self Test. 2. Self test is passed if the CVR control unit green TEST lamp stays ON as long as the TEST button is pressed. NOTE The recording will resume if the shutdown signal goes inactive or upon activation of the "Push-to-test" function. If the recording is resumed due to execution of the "Push-to-test", the recording will again cease within 10 minutes if the shutdown signal is still active. 3. Should self test fail and it is desired to perform another self test, repeat the procedure. IMPACT SWITCH CHECK After either a flight in turbulent air or a hard landing the impact switch warning light should be checked: the unit resetting is required if the warning light is illuminated. SUPPLEMENT 9 Page 4 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 5 - PERFORMANCE No changes to the performance data provided by Section 5 of the Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 9 Page 5 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 9 Page 6 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the FA2100 Cockpit Voice Recorder is installed. ATA No. 23 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. COMMUNICATIONS 23-70 AUDIO MONITORING COCKPIT VOICE RECORDER – FA2100 Recorder w/ ULB L-3 Communications 2100-1020-00 10.50 328.50 34.50 1 – Cockpit Area Microphone S056 L-3 Communications S056-0048-00 0.20 16.70 0.03 1 – Control Unit S261 L-3 Communications S261-1120-00 0.50 48.50 0.24 1 – Impact Switch Aerodyne Control Corp. 6895-S-4-X-3-3 1.00 212.00 2.12 1 Issued: October 21, 2005 Rev. 4: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 9 Page 7 of 8 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 9 Page 8 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 4 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 10 TCAS I (10 Pages) SUPPLEMENT NO. 10 FOR TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS I) [Mod. 80-0440, 80-0594, 80-0922] [80-1355 for MSN 3001+] Rev. 5: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- 1 1 to 2, 5 to 8 2 1, All pages with suffix “.C” Description of Revision Approval Date First Issue October 21, 2005 Editorial changes April 10, 2006 Rev. 2 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 Cover page Revision issued to add Design Change number following Design Change number re-identification campaign (for MSN 3001+ airpl.) Rev. 4 is approved under the authority of DOA No. EASA.21J.685 Date: Nov. 08, 2018 5 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 5 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 SUPPLEMENT 10 All Page 1 of 10 P.180 AVANTI II / EVO List of Effective Pages: Page 1 2 3 4 5 6 7 8 9 10 Rev. 5 5 5 5 5 5 5 5 5 5 Page 3.C 4.C 5.C 6.C 7.C 8.C 9.C 10.C Rev. 5 5 5 5 5 5 5 5 SUPPLEMENT 10 Page 2 of 10 Issued: October 21, 2005 All Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) to perform TCAS I operations when the Traffic Alert and Collision Avoidance System (TCAS I) Optional System is installed (with Mod. N. 80-0440 and 80-0594) on the airplane. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement, consult the basic Approved Airplane Flight Manual. The SKY899 (TCAS I) is an on-board traffic situation system which monitors the surrounding airspace, by interrogating any intruding aircraft transponder. The traffic information, which include relative range, altitude, bearing and closure rate of other transponder-equipped aircrafts, are then computed to predict collision threats. The SKY899 displays traffic information on the cockpit displays (PFDs and MFD) and generates aural warning through the Cockpit Audio System. TCAS I functions control is performed through the “TCAS” section on the Miscellaneous/ Reversionary Panel, the DCP “Range” knob and the cockpit displays softkeys. ABBREVIATIONS OPR Operating Mode OT Other Traffic TA Traffic Advisory TCAS Traffic Alert and Collision Avoidance System TFC TCAS Traffic Display Mode TRC Transmitter Receiver Computer TEST Test Mode WOW Weight On Wheel DEFINITIONS TRAFFIC ADVISORY Threat information given to the pilot pertaining to the position of intruding aircraft in the immediate vicinity. PROXIMATE TRAFFIC Any traffic not generating a TA but which is within 4 nmi range and within ± 1200 feet vertically. OTHER TRAFFIC Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Any traffic within approximately 35 nmi range and within ± 9900 feet vertically (max. range), that is not proximate traffic or traffic generating a TA. Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 10 Page 3 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS The following limitations apply to the P.180 airplane when conducting TCAS I operations: a. The Pilot should not manoeuvre the aircraft based solely on the traffic displayed by TCAS I. Information shown on the display is provided to the Pilot as an aid to visually acquiring traffic. Manoeuvring the aircraft should be based only on ATC guidance or positive visual acquisition of the conflicting traffic. b. TCAS I system provides no indication of aircrafts without operative transponders. c. Besides the TCAS I components, all the IFR required instruments must be installed and operating to operate TCAS I system. SECTION 3 - EMERGENCY PROCEDURES If a TCAS computer failure occurs, the yellow "TCAS-FAIL" flag appears on the PFDs and the MFD. If "TCAS-FAIL" is annunciated on the PFDs and the MFD or the "Traffic Advisory System Test Failed" aural annunciation occurs, turn the TCAS I System OFF through the dedicated CB. SUPPLEMENT 10 Page 4 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 4 - NORMAL PROCEDURES INITIALIZATION (SELF-TEST) 1. After Engine starting verify that the TCAS I Circuit Breaker is engaged and set the Avionics Switch to ON. 2. The TCAS system automatically cycles through a power-on SELF-TEST. 3. The Traffic screen appears and the following annunciations are displayed, provided that the TCAS display mode is selected through the cockpit displays soft-keys: – Yellow “TRAFFIC” annunciation – OT, PT and TA traffic symbols 4. After the completion of the test the “Traffic Advisory System Test Passed” aural message is broadcast. 5. If the system passes the test: On ground: – The system goes automatically in Stand-by (STBY) mode. – To switch to Operating mode, depress the OPR/STBY pushbutton on the Miscellaneous/Reversionary Panel. In flight: – The system goes automatically in Operating (OPR) mode. 6. The TCAS power-on self-test result is not significant before the avionics initialization is completed, including, for instance, valid altitude data. SYSTEM SELF-TEST 1. Prior to initiate the TCAS self-test, ensure that all avionics are turned ON and operational. 2. With the TCAS in standby mode and TFC selected on PFDs/MFD perform the TCAS I self-test pushing the “ALT/TEST” pushbutton on the Miscellaneous/ Reversionary Panel: – Yellow "TRAFFIC" annunciation is displayed – OT, PT and TA traffic symbols are displayed 3. After the completion of the test the aural "Traffic Advisory System Test Passed " is broadcast. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 10 Page 5 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 TRAFFIC ADVISORY ANNUNCIATION A TA is annunciated by an aural "TRAFFIC TRAFFIC" message on the Cockpit Audio System and a yellow filled circle shown on the TCAS display. A TA is generated when the following conditions occur: a. Cruise (altitude above 2000 feet AGL): – the intruder is within a 0,2 nmi horizontal radius and a ± 600 feet relative altitude range, or – the intruder is approximately within 15 -20 seconds from CPA. b. Takeoff and Landing (altitude below 2000 feet AGL): – the intruder is within a 0,55 nmi horizontal radius and a ± 800 feet relative altitude range, or – the intruder is approximately within 20 -30 seconds from CPA. Below 400 feet AGL the aural "TRAFFIC TRAFFIC" message is inhibited. When the own aircraft altitude is below 1700 feet AGL, ground intruders (below 380 feet AGL) are filtered out. A TA symbol remains on the screen for at least 8 seconds even if the intruder aircraft no longer meets the TA criteria. RECOMMENDED FLIGHT CREW PROCEDURES When a TCAS I Traffic Advisory (TA) is issued: a. The flightcrew should attempt to visually acquire the intruder aircraft and to attain/ maintain safe separation in accordance with regulatory requirements and good operating practices. b. When the flightcrew cannot visually acquire the intruder aircraft but perceives the intruder as a threat, the crew may contact ATC to obtain information that might help in locating the intruder aircraft. c. TCAS I TA display information is inadequate for collision avoidance manoeuvres. Pilots should not manoeuvre based solely on TA information. A Pilot manoeuvre based only on this information might result in a loss of separation with the intruder (e.g., a turn toward the intruder). Pilots should manoeuvre only on receiving guidance from ATC or on acquiring visual contact with the intruder. SUPPLEMENT 10 Page 6 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 GENERAL RECOMMENDATIONS a. Pilots will operate TCAS at all times when airborne, in all meteorological conditions. b. TCAS does not diminish or otherwise alter the pilot's authority or responsibility to ensure safe separation. The pilot should maintain frequent outside visual scan and "see and avoid" vigilance. c. TCAS should not be activated until cleared for takeoff. TCAS should be deactivated after clearing an active runway following a landing (select the STBY mode). TCAS is not designed to assist in taxiing across active runways or at any other time for ground operations. d. To enhance situational awareness during flight, the TCAS display should be used in a range setting appropriate to the phase of flight. e. TCAS I can only detect aircrafts which are transponder equipped. COMBINED TCAS I & TAWS OPERATIONS When both TAWS and TCAS I Systems are installed on the airplane, if a TAWS alert or altitude callout condition and a Traffic Advisory condition exist at the same time, the Traffic Advisory aural message is delayed with respect to the TAWS alert or callout aural annunciation. SECTION 5 - PERFORMANCE No changes to the performance data provided by Section 5 of the Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 10 Page 7 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 10 Page 8 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the TCAS I optional system is installed: ATA No. 34 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. NAVIGATION 34-40 INDEPENDENT POSITION DETERMINING TCAS I SYSTEM – Transceiver/Computer Unit TRC899 L-3 Communications 805-11900-001 9.88 -17.90 -1.77 1 with: – System Configuration Module L-3 Communications 814-18005-001 – Directional Antenna NY156 L-3 Communications 805-10003-001 Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 1 2.29 117.00 Appr. DOA EASA.21J.685 1105-2999 2.68 1 SUPPLEMENT 10 Page 9 of 10 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 10 Page 10 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 11 TAWS (10 Pages) SUPPLEMENT NO. 11 FOR TERRAIN AWARENESS AND WARNING SYSTEM (TAWS) [Mod. 80-0459, 80-0595, 80-1364 for MSN 3001+] Rev. 6: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- 1 1 to 2, 7 to 8 2 1, All pages with suffix “.C” Description of Revision Approval Date First Issue October 21, 2005 Editorial changes April 10, 2006 Rev. 2 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 Cover page Revision issued to add Design Change number following Design Change number re-identification campaign (for MSN 3001+ airpl.) Rev. 4 is approved under the authority of DOA No. EASA.21J.220 Date: May 29, 2018 5 Cover page, 9, 9.C Rev. 5 is approved Revision issued to add Design under the authority of Change number following Design DOA No. Change number re-identification EASA.21J.685 campaign (for MSN 3001+ airpl.). Date: Nov. 08, 2018 Furthermore Equipment List is updated to remove OCM Module p/n Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 SUPPLEMENT 11 All Page 1 of 10 P.180 AVANTI II / EVO Rev. No. Revised Pages Description of Revision Approval Date 6 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 6 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 List of Effective Pages: Page 1 2 3 4 5 6 7 8 9 10 Rev. 6 6 6 6 6 6 6 6 6 6 Page 3.C 4.C 5.C 6.C 7.C 8.C 9.C 10.C Rev. 6 6 6 6 6 6 6 6 SUPPLEMENT 11 Page 2 of 10 Issued: October 21, 2005 All Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the Terrain Awareness and Warning System (TAWS) Class B Optional System is installed (with Mod. No. 80-0459 and 80-0595) on the airplane. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement consult the basic Approved Airplane Flight Manual. The BF Goodrich TAWS8000 is a Class B Terrain Awareness and Warning System (TAWS) designed to provide terrain situational awareness relative to current and predicted aircraft position compared with terrain information stored into a Database integrated with the system. Based upon information from FMS, Air Data Computer, landing gear position and Heading source, the TAWS is able to determine the airplane state and intent and to provide warnings and alerts in advance of potential hazards. The system provides the following functions: Reduced Required Terrain Clearance (RTC), Imminent Terrain Impact (ITI), Premature descent, Excessive descent rate, Negative Climb Rate or Altitude Loss After Takeoff and Altitude of 500 ft. The alert information is provided to the flight crew both visually and aurally. TAWS functions control is performed through the “TAWS” section on the Miscellaneous/Reversionary Panel, the DCP “Range” knob and the cockpit displays (PFDs and MFD). ABBREVIATIONS GND Ground ITI Imminent Terrain Impact PROX Proximity RTC Reduced Required Terrain Clearance TAWS Terrain Awareness and Warning System TERR Terrain Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 11 Page 3 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS a. Navigation must not be predicated upon the use of the Terrain Awareness Display. The Terrain Awareness Display is intended to serve as a situational awareness tool only, and may not provide the accuracy and/or fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions. b. The Goodrich Avionics Systems, Inc. LANDMARK™ TAWS8000 Terrain Awareness and Warning System Pilot's Guide, part number 009-18000-001, latest revision, must be immediately available to the pilot when operating the aircraft with the LANDMARK™ TAWS8000 system. The software status stated in the Pilot's Guide should match that displayed on the equipment ID tag. c. The use of the terrain awareness warning and terrain display functions is prohibited during QFE (atmospheric pressure at airport elevation) operations. d. The area of intended operation is identified by the proper Terrain Database P/N recorded in the Equipment List of this Supplement. e. During operations at certain locations, where it is known that caution/warning thresholds may be exceeded due to specific terrain or operating procedures, the TAWS system must be manually inhibited. NOTE To avoid giving unwanted alerts the TAWS system must be inhibited, through the INHIB pushbutton, when performing Steep Approaches. f. Besides the TAWS components, all the IFR required instrumentation must be installed and operating to operate the TAWS system. SECTION 3 - EMERGENCY PROCEDURES If a TWAS computer failure occurs, the yellow "TERRAIN FAIL" flag appears on the PFDs and MFD. If "TERRAIN FAIL" is annunciated on the displays or if "TAWS System Test Failed" aural annunciation occurs, turn the TAWS system OFF through the dedicated circuit breaker. SUPPLEMENT 11 Page 4 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 4 - NORMAL PROCEDURES SYSTEM INITIALIZATION 1. After Engine starting set the Avionics Switch to ON. 2. Verify the TAWS Circuit Breaker is engaged and the terrain display enabled. 3. The TAWS System begins its power-up Self-Test. The TAWS Control Panel switches and indicator lights should light up and then extinguish after a few seconds. If the system passes the test and all the lights are off the TAWS is operational. 4. Result of TAWS initial built-in-test is not significant before avionics initialization is completed, including valid GPS signal receiver. SYSTEM SELF-TEST 1. Prior to initiate the TAWS Self-Test, ensure that all avionics are turned ON and operational. a. Set altitude to an indicative value of 100-200 feet. b. Ensure GPS data are available. c. Monitor PFDs/MFD annunciations during test. 2. On the Reversionary Panel push the TAWS "Test" pushbutton . a. Yellow "TERR", yellow "GND PROX" and red "PULL-UP" are sequentially displayed on PFDs. b. Graphical Terrain test pattern is displayed on PFDs/MFD. c. Software version (e.g. “LANDMARK software version 1.10"), terrain database (e.g. "LANDMARK Database: World. Effective date: March 22, 2004”) and altitude (e.g. "MSL 150") are announced d. After completion of the test "LANDMARK System Test Passed" is announced NOTE Perform the system self-test before the first flight of the day and whenever the system shows a failure condition. The system self-test function is available only when the aircraft is on the ground. Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 11 Page 5 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 ADVISORY CALLOUTS The following advisory callout is provided: – "FIVE HUNDRED" occurs at 500 feet AGL CAUTION AND WARNING ALERTS According to the different Alert Conditions, the TAWS system generates the following Caution and Warning Alerts: Caution Alert Warning Alert Alert Condition (Aural) (Visual) (Aural) (Visual) Reduced Required "Caution, terrain; Terrain Clearance caution, terrain” (RTC) "TERR” (Amber) "Terrain, terrain; "PULL UP” pull up, pull up” (Red) Imminent Terrain Impact (ITI) "Caution, terrain; caution, terrain” "TERR” (Amber) "Terrain, terrain; "PULL UP” pull up, pull up” (Red) Premature Descent "Too low, terrain” "TERR” (Amber) [None] [None] Excessive Descent Rate "Sink Rate” "TERR” (Amber) "Pull up” "PULL UP” (Red) Negative Climb Rate or Altitude Loss after Tafeoff "Don't Sink” "TERR” (Amber) [None] [None] SUPPLEMENT 11 Page 6 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RESPONSE TO A TAWS CAUTION When a Terrain Awareness Caution occurs take positive action until the alert ceases. Stop descending or initiate either a climb or a turn, or both, as necessary, based on analysis of all available instruments and information. RESPONSE TO A TAWS WARNING If a terrain awareness Warning occurs, immediately initiate and continue a climb that will provide maximum terrain clearance, or any similar approved vertical terrain escape manoeuver, until all alerts cease. Only vertical manoeuvers are recommended, unless either operating in visual meteorological conditions (VMC), or the pilot determines, based on all available information, that turning in addition to the vertical escape manoeuver is the safest course of action, or both. COMBINED TCAS I & TAWS OPERATIONS When both TAWS and TCAS I Systems are installed on the airplane, if a TAWS alert or altitude callout condition and a Traffic Advisory condition exist at the same time, the Traffic Advisory aural message is delayed with respect to the TAWS alert or callout aural annunciation. SECTION 5 - PERFORMANCE No changes to the performance data provided by Section 5 of the Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 11 Page 7 of 10 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 11 Page 8 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II WEIGHT AND BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the TAWS Optional System is installed: ATA No. 34 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. NAVIGATION 34-40 INDEPENDENT POSITION DETERMINING TERRAIN AWARENESS AND AVOIDANCE SYSTEM (TAWS) – TAWS8000 Remote Computer L-3 Communications 805-18000-001 4.10 -17.90 -0.73 1 with: – System Configuration Module L-3 Communications 814-18005-001 1 and – 67DC Terrain Database Cartridge L-3 Communications 805-18200-( ) (1) – OCM-3100 Option Control Module 1 negl. -- -- 1 (1) The suffix ( ) is related to the world regional coverage (e.g. -001 for North America, -002 for worldwide coverage). Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 11 Page 9 of 10 P.180 AVANTI II WEIGHT AND BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 11 Page 10 of 10 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 12 Unpaved Runways Operations (12 Pages) SUPPLEMENT NO. 12 FOR UNPAVED RUNWAYS OPERATIONS [Mod. 80-0358, 80-0609] Rev. 7: Mar. 04, 2019 Supplement 12 IS NOT applicable to MSN 3001 + (EVO) airplanes and airplane equipped with S.B.80-0454 or 80-0425 LOG OF REVISIONS Rev. No. Revised Pages 0 -- First Issue October 21, 2005 1 ALL Editorial changes April 10, 2006 2 1 6,7 Updated LOR and LOEP Landing procedure updated March 12, 2012 3 1, All pages with suffix “.C” Description of Revision Approval Date Rev. 3 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 4 1 to 10 and 3.Cto 10.C Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ 5 1 to 2 and 3.C to 10.C Rev. 5 is approved Revision issued to update applicability to MSN 1105-2999 only. within approval of TC54: REMOVED pages 3.C to 12.C Rev. 4 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 EASA n. 10054744 Date: Sept. 14, 2015 Issued: October 21, 2005 Rev. 7: Mar. 04, 2019 SUPPLEMENT 12 All Page 1 of 12 P.180 AVANTI II / EVO Rev. No. Revised Pages Description of Revision Approval Date 6 1, 2 and 8 Revision issued to update supp. applicability and landing procedure due to new steering. S.B. 80-0454 or 80-0425 Rev. 6 is approved under the authority of DOA No. EASA.21J.220 Date: March 03, 2017 7 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 7 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 LIST OF EFFECTIVE PAGES: Page 1 2 3 4 5 6 7 8 9 10 11 12 Rev. 7 7 7 7 7 7 7 7 7 7 7 SUPPLEMENT 12 Page 2 of 12 7 Issued: October 21, 2005 All Rev. 7: Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) for conducting Operations on Unpaved Runways when the required equipment is installed on the airplane. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement consult the Approved Airplane Flight Manual. Operations on Unpaved Runways are limited to the airfield surfaces defined in Section 2 of this supplement, the information herein contained does not constitute operational approval. Further limitations could be defined by the Airfield Operators in terms of maximum allowable aircraft weight and maximum allowable tire pressure. The following tire pressure must be used for comparison to the airfield limitation: Main landing gear wheel: 119 psi (8.4 Kg/cm2) The Airfield Operator should provide adequate information of the airfield surface characteristics. For aircraft safe operation, these should be equivalent to a firm soil, or grass surface on firm soil with maximum grass length of 5 cm (2 inches). The soil is considered firm when there are wheel impressions but no rutting. Maximum wheel impression measured during flight test to demonstrate performance of Section 5 of this supplement, was about 1.5 cm (0.5 inches). The method used to measure the surface strength expressed as a California Bearing Ratio (CBR), or other accepted runway strength measurement systems, can be used to evaluate the airplane wheel impression depth as a function of the tire pressure. It must be reminded that surface bearing strength can vary from part to part of an airfield and as a consequence of the environmental conditions. Issued: October 21, 2005 Rev. 7: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 12 Page 3 of 12 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS Operations on Unpaved Runways are limited to the following equivalent airfield surfaces: – firm bare soil; – grass on firm soil up to 5 cm (2 inches) long. NOTE The soil is firm when there are wheel impressions but no rutting. With reference to landing gear operating life limit, each operating cycle (a takeoff and landing) on an unpaved runway is to be taken in account as four operating cycles on a paved runway. SECTION 3 - EMERGENCY PROCEDURES No changes to the emergency procedures provided by the Section 3 of the Approved Airplane Flight Manual are necessary for this supplement. SUPPLEMENT 12 Page 4 of 12 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 7 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 4 - NORMAL PROCEDURES CAUTION The level of safety may be decreased when operating on unpaved runways and therefore proper efforts should be made to ensure adequacy of the runway surface for operational use. Pay particular attention that the runway surface should be even i.e. free of ruts, troughs or holes, stones and large vegetation tufts that may decrease performances or damage external equipment and main aerodynamic surfaces. Wet unpaved runways may be slippery; in such case landing ground run and engine-out stop distance may increase significantly over those indicated in Section 5 of this supplement. NOTE When operating on unpaved surfaces dust particles could be suspended in the air, especially with windy weather or following other airplanes operations. In such conditions it could be advisable to deploy anti-ice vanes in order to prevent any engine FOD. In this case performance changes due to icevanes deployment, outlined in Section 5 of this AFM, are to be added to the performance changes due to the unpaved surface, outlined in Section 5 of this Supplement. PREFLIGHT CHECK NOSE SECTION The gravel protection on the nose gear is to be checked for proper installation and absence of damages. Issued: October 21, 2005 Rev. 7: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 12 Page 5 of 12 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 TAXIING NOTE During taxi the required power setting may result in a propeller RPM increase into yellow range (1300 to 1600 RPM). Prolonged NP RPM operations in this range should be avoided with a proper use of engine power levers. Keep the flaps retracted when taxiing to avoid throwing dirtiness (stones, grass, heavy dust or others) in the flap mechanisms and to minimize damages to the flap surfaces, until line-up for takeoff. Taxi speed should be kept as slow as possible to assure propellers integrity if sand or gravel is present on the airfield surface. Follow normal procedures for engines run up and checks before takeoff. TAKEOFF NOTE Under particularly slippery conditions the normal procedure for engine ground check may be difficult to be performed. Operating from an unpaved runway may result in a wheels slipping while holding brakes as per a normal takeoff procedure. In order to avoid slipping, it is recommended to advance the power levers smoothly while holding brakes up to the maximum power without slipping. After brake release, advance power levers to the maximum takeoff power as per Figure 5-14 at Section 5 of the Approved Airplane Flight Manual. A moderate nose up elevator during takeoff ground run, decreases the load on nose wheels improving the takeoff performance. If flight condition permits, leave the landing gear extended (without braking the wheels) for a short time after takeoff to remove most of dirtiness (stones, grass, heavy dust or others). Have a brief operational check of the radio/navigation equipment with the antennas located on the belly of the airplane. SUPPLEMENT 12 Page 6 of 12 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 7 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING NOTE When operating on unpaved runways the landing procedure must be performed with FLAPS DN. Prior to reaching 50 ft. above landing surface: 1. Landing Gear - CHECK DN (3 green lights) 2. Flaps - CHECK DN CAUTION Steering engagement during landing is prohibited. 3. Approach speed - REFER to Figure 5-69 at Section 5 of the AFM 4. Power - AS REQUIRED 5. Condition Levers - CHECK MAX RPM NOTE After touch down a moderate nose up elevator must be applied until 60 to 70 KIAS speed has been reached in order to avoid damages to external surfaces and equipment. CAUTION Braking is less effective on unpaved runways. 6. Brakes - AS REQUIRED 7. Reverse - Below 1900 NP, or 5% drop from the set value, slowly retard power levers approximately 3/4 from idle detent into the beta range CAUTION Asymmetrical reverse thrust may be difficult to control on a slippery runway. It is recommended to avoid full reverse on landing and to limit beta range or min. reverse only. When landing at aft C.G. initiate flaps retraction before actuating reverse power. Issued: October 21, 2005 Rev. 7: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 12 Page 7 of 12 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 8. Reverse - DO NOT USE below 40 KIAS At landing completed: 9. Condition Levers - GROUND IDLE 10. Steering - ENGAGE TAKE OFF (if necessary). NOTE During taxi the required power setting may result in a propeller RPM increase into yellow range (1300 to 1600 RPM). Prolonged NP RPM operations in this range should be avoided with a proper use of engine power levers. AFTER SHUTDOWN Check landing gear, gravel protection kit, wheels, fuselage and wing lower surfaces, fuselage belly antennas and lights, flaps lower surfaces and propellers blades for absence of damages. After flight if a prolonged stay is foreseen or in case of windy conditions full covers on all engines, statics and pitot should be applied in order to prevent FOD. SECTION 5 - PERFORMANCE Performance data provided by Section 5 of the Airplane Flight Manual are to be corrected as follows when operating on unpaved runways: TAKEOFF AND LANDING DISTANCE ON UNPAVED RUNWAYS NOTE All performance data are based on runways as specified in Section 2 of this Supplement. Distance correction factors are based on experimental data of representative surfaces and are for guidance only. Specific runway conditions may result in improved or degraded performance. The information herein contained does not constitute an operational approval. SUPPLEMENT 12 Page 8 of 12 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 7 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 TAKEOFF DISTANCE ON UNPAVED RUNWAYS The Takeoff Ground Run Distance, as per Figure 5-17 on page 5-25 of the AFM, must be increased by 25% (correction factor = 1.25) for takeoff on unpaved runway. EXAMPLE: – Takeoff Ground Run on dry paved runway 2050 ft (625 m) – Takeoff Ground Run on unpaved runway 2050x1.25 = 2563 ft (781 m) The Takeoff Total Distance, as per Figure 5-16 on page 5-25 of the AFM, must be increased by 15% (correction factor = 1.15) for takeoff on unpaved runway. EXAMPLE: – Takeoff Distance on dry paved runway 2850 ft (850 m) – Takeoff Distance on unpaved runway 2850x1.15 = 3278 ft (999 m) ACCELERATE AND STOP DISTANCES ON UNPAVED RUNWAYS The Accelerate and Stop Distance, as per Figure 5-19 on page 5-28 of the AFM must be increased by 40% (correction factor = 1.40) when operating on unpaved runway. EXAMPLE: – Accelerate and Stop Distance on dry paved runway 4360 ft (1329 m) – Accelerate and Stop Distance on unpaved runway 4360x1.40 = 6104 ft (1861 m) Issued: October 21, 2005 Rev. 7: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 12 Page 9 of 12 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING DISTANCE ON UNPAVED RUNWAYS CAUTION When operating on unpaved runways the Landing procedure is to be performed only with FLAPS DN. The Landing Ground Run Distance, as per Figure 5-69 on page 5-78 of the AFM, must be increased as follows when landing on unpaved runway: – at idle power setting by 60% (correction factor = 1.60) – at beta range power setting by 20% (correction factor = 1.20) EXAMPLE: Landing Ground Run on dry paved runway 1870 ft (570 m) Landing Ground Run on unpaved runway: – at idle power setting 1870x1.60 = 2992 ft (912 m) – at beta range power setting 1870x1.20 = 2244 ft (684 m) The Total Landing Distance, as per Figure 5-69 on page 5-78 of the AFM, must be increased as follows when landing on unpaved runway: – at idle power setting by 40% (correction factor = 1.40) – at beta range power setting by 12% (correction factor = 1.12) EXAMPLE: Total Landing Distance on dry paved runway 2860 ft (872 m) Total Landing Distance on unpaved runway: – at idle power setting 2860x1.40 = 4004 ft (1220 m) – at beta range power setting 2860x1.12 = 3203 ft (976 m) SUPPLEMENT 12 Page 10 of 12 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 7 : Mar. 04, 2019 P.180 AVANTI II WEIGHT AND BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST The following items, not included in the weight and balance information presented in the Weight and Balance Manual, must be considered integral part of the Equipment List when the airplane is equipped with the gravel protection for unpaved runways operations. ATA No. 32 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. LANDING GEAR 32-20 NOSE GEAR AND DOORS GRAVEL PROTECTION KIT – Gravel Protection Piaggio 80K174108-801 Issued: October 21, 2005 Rev. 7: Mar. 04, 2019 1.64 Appr. DOA EASA.21J.685 1105-2999 -17.80 -0.29 1 SUPPLEMENT 12 Page 11 of 12 P.180 AVANTI II WEIGHT AND BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 12 Page 12 of 12 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 7 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 13 Turbulence Weather Radar (8 Pages) SUPPLEMENT NO. 13 FOR TURBULENCE WEATHER RADAR [Mod. 80-0664 or 80-1359 for MSN 3001+] Rev. 6: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- First Issue October 21, 2005 1 ALL Editorial changes April 10, 2006 2 1, All pages with suffix “.C” Description of Revision Approval Date Rev. 2 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 1, 7 and 7.C Cover page updated Update Eq. List Rev. 4 is approved under the authority of DOA No. EASA.21J.220 Date: Jan. 09, 2017 5 Cover page Revision issued to add Design Change number following Design Change number re-identification campaign (for MSN 3001+ airpl.) Rev. 5 is approved under the authority of DOA No. EASA.21J.220 Date: May 29, 2018 Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 SUPPLEMENT 13 All Page 1 of 8 P.180 AVANTI II / EVO Rev. No. Revised Pages Description of Revision Approval Date 6 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 6 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 List of Effective Pages: Page 1 2 3 4 5 6 7 8 Rev. 6 6 6 6 6 6 6 6 Page 3.C 4.C 5.C 6.C 7.C 8.C Rev. 6 6 6 6 6 6 SUPPLEMENT 13 Page 2 of 8 Issued: October 21, 2005 All Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) when the TWR-852 Turbulence Weather Radar Optional System is installed (with Mod. N. 80-0664) on the airplane. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement, consult the basic Approved Airplane Flight Manual. Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 13 Page 3 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS No changes to the limitations provided by Section 2 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 3 - EMERGENCY PROCEDURES No changes to the emergency procedures provided by Section 3 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 4 - NORMAL PROCEDURES The TWR-852 Turbulence Weather Radar is equivalent to the basic WXR-800 Weather Radar except for the following additional operating modes: a. Weather plus Turbulence (WX+T) and Turbulence only (TURB) modes which can be selected through the radar menu shown on the cockpit displays (PFDs/MFD); b. AUTOTILT function selectable through the dedicated additional pushbutton on the Display Control Panel. SUPPLEMENT 13 Page 4 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 5 - PERFORMANCE No changes to the performance data provided by Section 5 of the Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 13 Page 5 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 13 Page 6 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the TWR-852 Turbulence Weather Radar Optional System is installed: ATA No. 34 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. – Receiver Transmitter Antenna RTA-852 Collins 622-8439-004 (1) 19.80 -42.30 -8.38 1 – Display Control Panel DCP-3030 Collins 822-1828-062 (2) 1.50 20.16 0.30 2 NAVIGATION 34-40 INDEPENDENT POSITION DETERMINING TURBULENCE WEATHER RADAR COLLINS TWR-852 (1) Replaces the basic RTA-800, P/N 8221050-004. (2) Replaces the basic DCP P/N 822-1828162. Issued: October 21, 2005 Rev. 6: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 13 Page 7 of 8 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 13 Page 8 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 6 : Mar. 04, 2019 P.180 AVANTI II / EVO EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 14 Sec. Diversity Mode-S Transponder (8 Pages) SUPPLEMENT NO. 14 FOR SECONDARY DIVERSITY MODE-S TRANSPONDER [Mod. 80-0598, 80-0905] Rev. 5: Mar. 04, 2019 LOG OF REVISIONS Rev. No. Revised Pages 0 -- First Issue October 21, 2005 1 ALL Editorial changes April 10, 2006 2 1, All pages with suffix “.C” Description of Revision Approval Date Rev. 2 is approved Revision issued for P.180 Avanti under the authority of “EVO” MSN 3001 and up, DOA No. introducing a complete AFM applicable to MSN 3001 + airplanes. EASA.21J.220 Date: Dec. 12, 2014 3 ALL Revision issued for re-arrange material due to applicability MSN 1105-2999 and 3001+ Rev. 3 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 4 1, 7, 7.C Cover page updated Update Eq. List Rev. 4 is approved under the authority of DOA No. EASA.21J.220 Date: Jan. 09, 2017 5 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) Rev. 5 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 SUPPLEMENT 14 All Page 1 of 8 P.180 AVANTI II / EVO List of Effective Pages: Page 1 2 3 4 5 6 7 8 Rev. 5 5 5 5 5 5 5 5 Page 3.C 4.C 5.C 6.C 7.C 8.C Rev. 5 5 5 5 5 5 SUPPLEMENT 14 Page 2 of 8 Issued: October 21, 2005 All Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101 when the second TDR-94D Transponder is installed (with Mod. N. 80-0598) on the airplane. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement, consult the basic Approved Airplane Flight Manual. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 14 Page 3 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 2 - LIMITATIONS No changes to the limitations provided by Section 2 of the Approved Airplane Flight Manual are necessary for this supplement. SECTION 3 - EMERGENCY PROCEDURES If a TRANSPONDER failure occurs, the yellow "XPDR FAIL" flag appears on the RTU and CDU. In this case select the other available Transponder. NOTE The same mode A and Flight ID codes previously active on the failed unit must be maintained on the active transponder. SECTION 4 - NORMAL PROCEDURES The secondary TDR-94D Transponder is equivalent to the primary (basic) Transponder including the Enhanced Surveillance capability. To use the secondary Transponder instead of the primary, select ATC2 on the RTU or CDU Radio control units. NOTE When the secondary transponder is activated, the same mode A and Flight ID codes previously active on the primary unit must be maintained on the active transponder. SUPPLEMENT 14 Page 4 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 5 - PERFORMANCE No changes to the performance data provided by Section 5 of the Airplane Flight Manual are necessary for this supplement. Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 14 Page 5 of 8 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 14 Page 6 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 3. EQUIPMENT LIST Weight and balance data included in the basic Weight and Balance Manual must be completed with the following data when the Optional secondary TDR-94D Transponder is installed: ATA No. 34 ITEM DESCRIPTION AND PART NUMBER WEIGHT LBS ARM IN MOMENT Q.TY MARK IF LBS*IN/100 INSTL. NAVIGATION 34-50 DEPENDENT POSITION DETERMINING SECONDARY DIVERSITY MODE-S TRANSPONDER – Secondary Transponder TDR-94D Collins 622-9210-008 or 622-9210-309 8.50 -18.60 -1.58 1 – Transponder Mount MMT-150 Collins 622-9672-003 0.90 -18.60 -0.17 1 Issued: October 21, 2005 Rev. 5: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 14 Page 7 of 8 P.180 AVANTI II WEIGHT & BALANCE MANUAL Rep. 180-MAN-0020-01101 INTENTIONALLY LEFT BLANK SUPPLEMENT 14 Page 8 of 8 Appr. DOA EASA.21J.685 1105-2999 Issued: October 21, 2005 Rev. 5 : Mar. 04, 2019 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 EASA APPROVED AIRPLANE FLIGHT MANUAL Supplement 15 Increased MTOW - 12100 lbs (112 Pages) SUPPLEMENT NO. 15 FOR INCREASED MAXIMUM TAKEOFF WEIGHT - MTOW 12100 LBS [Mod. 80-0642] Rev. 10: Mar. 04, 2019 Supplement 15 IS NOT applicable to MSN 3001 + (EVO) airplanes LOG OF REVISIONS Rev. No. 0 1 2 Revised Pages Description of Revision -1, 14 1 34, 41 First Issue Editorial change LOR and LOEP updated Procedure on use of reverse thrust updated depending on installation of Mod. 80-0932/SB 80-0286 Time to Climb, Fuel to Climb and Distance to Climb graphics updated Performance tables divided in .A and .B blocks, respectively applicable to airplanes installing PT6A-66 and PT6A66B engines Equipment list updated (new MLG shock absorber p/n added) Revision issued for P.180 Avanti “EVO” MSN 3001 and up, introducing a complete AFM applicable to MSN 3001 + airplanes. 64, 65, 66 71 thru 100 112 3 1 4 1 to 4, 47.A to 71.A, 100.A to 110.A and 47.B to 110.B(except page 48 and 49) 1,2 and 9 5 Revision issued for re-arrange material and for changes of limitations and performance applicable to airplanes installing engine model PT6A-66B Typing errors correction Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Approval Date January 10, 2006 March 20, 2008 March 12, 2012 Rev. 3 is only issued for documental traceability. Supplement 15 IS NOT applicable to EVO airplanes Rev. 4 is approved under the authority of DOA No. EASA.21J.220 Date: March 09, 2015 Rev. 5 is approved under the authority of DOA No. EASA.21J.220 Date: Jan. 05, 2016 SUPPLEMENT 15 All Page 1 of 112 P.180 AVANTI II / EVO AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Rev. No. Revised Pages Description of Revision Approval Date 6 1,2 69.A, 70.A, 71.A update cover and LOR update “Associated Conditions” on OEI diagrams update “Associated Conditions” on OEI diagram Rev. 6 is approved under the authority of DOA No. EASA.21J.220 Date: Jan. 09, 2017 71.B 7 8 9 1,2,8,12,13,from Update page due to new steering 15 to 20, from 24 to S.B. 80-0454 or 80-0425 27,29, from 32 to 34, 40,41 1,2,112 Equipment List pages modified due to: -update LG Manufacturer brand name from “Dowty Rotol ltd.” to “SAFRAN LS” -additional “SAFRAN LS” MLG p/n installing new Lever Hinge Fitting (Mod. 80-1195), -add reference to basic WBM for “Magnaghi” LG system p/n’s 1,2, 34 and 41 Update page due to design change “TAT heater inhibition on-ground” : - Mod. 80-1283 or SB 80-0430 when Magnaghi Landing Gear is installed, - Mod. 80-1312 or SB SB 80-0457 when Dowty Landing Gear is installed 10 ALL Revision issued for page Logo updating (Piaggio Aviation, DOA No. EASA.21J.685) and due to basic AFM complete re-issuing (Rev. B0) continued Rev. 7 is approved under the authority of DOA No. EASA.21J.220 Date: Mar. 03, 2017 Rev. 8 is approved by EASA n. 10065141 Date: Apr. 05, 2018 Rev. 9 is approved under the authority of DOA No. EASA.21J.685 Date: Sept. 25, 2018 Rev. 10 is approved under the authority of DOA No. EASA.21J.685 Date: Mar. 04, 2019 List of Effective Pages: Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 Rev. 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 Page 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 Rev. 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 Page 47A 48 49 50A 51A 52A 53A 54A 55A 56A 57A 58A 59A 60A 61A 62A 63A 64A 65A 66A 67A 68A 69A Rev. 10 10 Page 70A 71A 72A 73A 74A 75A 76A 77A 78A 79A 80A 81A 82A 83A 84A 85A 86A 87A 88A 89A 90A 91A 92A 10 10 10 10 10 10 10 SUPPLEMENT 15 Page 2 of 112 10 10 10 10 10 10 10 10 Rev. 10 10 10 10 10 10 10 10 97B 98B 99B 100B 101B 102B 103B 104B 105B 106B 107B 108B 109B 110B 111 112 10 10 10 Page 10 10 10 10 Rev. 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 47B 48 49 50B 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 74B 75B 76B 77B 78B 79B 80B 81B 82B 83B 84B 85B 86B 87B 88B 89B 90B 91B 92B 93B 94B 95B 96B 10 10 10 10 10 Page 10 10 10 10 10 Rev. 10 10 10 10 10 10 10 10 10 10 10 51B 52B 53B 54B 55B 56B 57B 58B 59B 60B 61B 62B 63B 64B 65B 66B 67B 68B 69B 70B 71B 72B 73B 10 10 10 10 Page 10 10 10 10 Rev. 10 10 10 10 10 10 10 10 10 93A 94A 95A 96A 97A 98A 99A 100A 101A 102A 103A 104A 105A 106A 107A 108A 109A 110A 10 10 10 10 Page 10 10 10 10 Rev. 10 10 10 10 10 10 10 Issued: January 10, 2006 All Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 1 - GENERAL This supplement contains the information that must be attached to the Approved Airplane Flight Manual (rep. 180-MAN-0010-01100) and Weight and Balance Manual (rep. 180-MAN-0020-01101) to perform Increased Maximum Takeoff Weight (to 12100 lbs) operations when the Mod. No. 80-0642 has been embodied on the airplane. The information contained herein supplements or supersedes the basic Approved Airplane Flight Manual and Weight and Balance Manual, and the Supplement No. 12 “Unpaved Runways Operations”, only in those items listed herein. For limitations, procedures and performance information not contained in this supplement, consult the basic Approved Airplane Flight Manual. ABBREVIATIONS MLW Maximum Landing Weight MTOW Maximum Takeoff Weight SECTION 2 - LIMITATIONS The following limitations apply to the P.180 airplane when performing increased MTOW, to 12100 lbs, operations. 2.1 AIRSPEED LIMITATIONS SPEED KCAS KIAS DESIGN MANEUVERING SPEED - VA Do not make full or abrupt control movements above this speed 12,100 lb. (5,489 kg) 11,550 lb. (5,239 kg) 7,700 lb. (3,493 kg) 201 198 176 202 199 177 NOTE Linear interpolation may be used for intermediate gross weights. MAXIMUM FLAP EXTENDED SPEED - VFE Do not exceed this speed at the given flap setting Flap MID Flap DN 182 176 183 177 MAXIMUM LANDING GEAR OPERATING SPEED - VLO Do not extend or retract landing gear above this speed 180 181 Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 3 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 2.7 WEIGHT LIMITS a. Maximum Ramp Weight 12,150 LBS (5511 kg) b. Maximum Takeoff Weight or as limited by “Maximum Takeoff Weight to achieve Takeoff Climb Requirements” graph (ref. to Figure 5) 12,100 LBS (5489 kg) c. Maximum Landing Weight 11,500 LBS (5216 kg) 2.8 CENTER OF GRAVITY LIMITS Pounds Weight Kilograms 12,150 8,745 8,500 7,700 6,000 5,511 3,967 3,856 3,493 2,722 Forward Limit Inches Aft of Datum Rearward Limit Inches Aft of Datum 210.25 195.22 194.00 194.00 194.00 214.00 214.00 213.00 209.80 209.80 NOTE Straight line variation between points indicated. The Datum Line is located 236.22 inches (6,000 millimeters) forward of the rear pressure bulkhead centerline (at the intersection between the forward pressure bulkhead and cockpit floor centerlines). SUPPLEMENT 15 Page 4 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 1. Airplane Weight vs. Center of Gravity Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 5 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 2.11 FLIGHT LOAD FACTOR LIMITS (MANEUVERING) a. Positive Load Factor (Flaps Up) 3.19 g b. Negative Load Factor (Flaps Up) –1.28 g 2.19 UNPAVED RUNWAYS OPERATIONS NOTE Unpaved runways operations are prohibited. 2.21 OPERATION IN ICING CONDITIONS No takeoff authorized with frost, snow or ice adhering to the propellers, windshields, powerplant installation and pitot/static ports, or with frost, snow or ice adhering to the wings, vertical and horizontal stabilizer or control surfaces. Flight in meteorological conditions described as freezing rain or freezing drizzle is prohibited. Although not directly experienced on P.180, some of the following visual cues, in order to early detect any possibility of encountering severe icing condition, may be used (all or at least one of them): 1. Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice. 2. Accumulation of ice on surface of wings. 3. Visible rain at temperatures below +5°C outside air temperature (OAT). 4. Droplets that splash or splatter on impact at temperatures below +5°C OAT. NOTE The prohibition on flight in freezing rain or freezing drizzle is not intended to prohibit purely inadvertent encounters with the specified meteorological conditions; however, pilots should make all reasonable efforts to avoid such encounters and must immediately exit the conditions if they are encountered. SUPPLEMENT 15 Page 6 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Use of the autopilot is prohibited when any unusual ice (e.g. unusual runback ice) is observed forming aft of the protected surfaces of the wing, or when unusual lateral trim requirements or autopilot trim warnings are encountered. NOTE The autopilot may mask tactile cues that indicate adverse changes in handling characteristics; therefore, the pilot should consider not using the autopilot when any ice is visible on the airplane. Wing ice inspection light must be operable prior to flight into known or forecast icing at night. NOTE This supersedes any relief provided by the Master Minimum Equipment List (MMEL), whenever applicable. 2.24 STEEP APPROACH OPERATIONS NOTE Steep Approach Operations are prohibited for Maximum Landing Weight (MLW) greater than 10945 lbs (4965 kg). 2.25 NOISE LEVEL The corrected noise level according to EASA-CS36, based on ICAO Annex 16, vol. I, Ed. 1993, Amdt. 7, Chapter 10, and according to FAR 36, Appendix G, Amdt 36-24 for the Piaggio P.180 aircraft at the Max Certificated T.O. weight of 12100 lbs, is 87. 37 dB(A). The allowed noise level according to both the mentioned regulations is 88. 00 dB(A). No determination has been made by the Federal Aviation Administration that the noise level of the airplane is or should be acceptable or unacceptable for operation at, into or out of, any airport. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 7 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 2.27 3. PLACARDS Close to both PFDs (Pilot’s and Copilot’s side): If Mod. SB 80-0454 or 80-0425 (new NWSS) are NOT installed If Mod. SB 80-0454 or 80-0425 (new NWSS) are installed MAXIMUM SPEED – KIAS MAXIMUM SPEED – KIAS DESIGN MANEUVERING VA = 202 AT 12100 LBS VA = 177 AT 7700 LBS FLAP OPERATING VFO = 170 UP/MID/UP VFO = 150 MID/DN/MID FLAP EXTENDED DN VFE = 177 LDG GEAR OPERAT VLO= 181 STEERING V = 60 DESIGN MANEUVERING VA = 202 AT 12100 LBS VA = 177 AT 7700 LBS FLAP OPERATING VFO = 170 UP/MID/UP VFO = 150 MID/DN/MID FLAP EXTENDED DN VFE = 177 LDG GEAR OPERAT VLO= 181 MINIMUM CONTROL VMC= 100 (ONE ENGINE INOPERATIVE) MINIMUM CONTROL VMC= 100 (ONE ENGINE INOPERATIVE) 3a. On the instrument panel, if the Gravel Protection Kit P/N 80K174108-801 is installed: OPERATION ON UNPAVED RUNWAYS IS PROHIBITED FOR WEIGHTS GREATER THAN: MTOW= 11550 LBS / 5239 KG MLW= 10945 LBS / 4965 KG 3b. On the left side of the glareshield: STEEP APPROACH OPERATIONS ARE PROHIBITED FOR MAXIMUM LANDING WEIGHT (MLW) GREATER THAN 10945 LBS (4965 KG) SUPPLEMENT 15 Page 8 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 3 - EMERGENCY PROCEDURES 3.1 AIRSPEEDS FOR EMERGENCY OPERATIONS SPEED KIAS One Engine Recommended Climb Speed (Flaps UP, L/G UP) 3.2 140 EMERGENCY PROCEDURES CHECKLIST 3.2.1 ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF AT OR AFTER ROTATION If sufficient runway remains for a safe stop: 1. Directional control - MAINTAIN 2. Power levers - IDLE 3. Land straight ahead 4. Brakes - AS REQUIRED 5. Power levers - REVERSE as required If insufficient runway remains or if the decision is made to continue the takeoff: 6. Directional control - MAINTAIN (Bank 5° max. towards operative engine when airborne) 7. Power levers - TAKEOFF 8. Landing gear (after climb established) - UP 9. Airspeed - ACCELERATE TO "ONE ENGINE 50 FEET HEIGHT SPEED" (Figure 7) 10. Procedure Airspeed - INCREASE TO 130 KIAS MINIMUM 11. Flaps - UP (One engine inoperative recommended climb speed 140 KIAS) 12. Obstacles - CLEAR Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 9 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 13. Inoperative engine - PERFORM ENGINE SECURING Procedure NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. 14. Taxi/Landing lights (if applicable) - OFF 15. Airspeed - INCREASE as required 16. Land at nearest suitable airport, performing the SINGLE ENGINE APPROACH AND LANDING Procedure WARNING The decision to continue a takeoff, single engine is primarily predicated upon, but not necessarily limited to, the aircraft’s ability to climb on a single engine with the gear extended and flaps in the takeoff position. Prior to flight, review airfield requirements and determine that adequate single engine climb performance exists, considering aircraft weight, ambient conditions, and pilot proficiency, to safely complete the takeoff should an engine fail at or after rotation. SUPPLEMENT 15 Page 10 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 3.2.5 MAXIMUM GLIDE 1. Airspeed - per Maximum Glide Speed Chart (see below) 2. Gear - UP 3. Flaps - UP 4. Condition levers - CUT OFF MAXIMUM GLIDE SPEED CHART WEIGHT (LBS) SPEED (KIAS) 12100 158 11550 155 11000 151 10000 144 9000 137 8000 129 Glide Ratio (Refer also to BEST GLIDE DISTANCE graph in Section 5 ("Performance") . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3 NM/1000 ft NOTE When operating in sustained icing condition, the Glide Ratio may be reduced up to 50% approximately. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 11 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 3.2.6 LANDING EMERGENCIES LANDING WITHOUT ENGINE POWER CAUTION With both generators inoperative only essential, battery and hot battery busses are fed by the battery, for approximately 30 minutes depending on loads and battery charge, while the Integrated Stand-by Instrument is fed by the Emergency Power Unit. 1. Airplane configured - Per MAXIMUM GLIDE Procedure (if altitude permits) When landing site assured: 2. Approach Speed - INCREASE the flaps DN approach speed (Figure 56) by 20 KIAS 3. Condition levers - CUT OFF 4. Fuel firewall shut-off valves - CLOSED 5. Fuel pumps switches - OFF If gear is to be extended: NOTE For particular terrain conditions it may be required to land with gear up. 6. Gear - DN (PER EMERGENCY GEAR EXTENSION Procedure) NOTE Gear extension requires approximately 60 handpump strokes: this procedure requires normally 90 sec. NOTE When S.B. 80-0454 or 80-0425 (new NWSS) are installed, after Emergency Gear extension, PFD will show T/O steering mode but steering system will remain in free castor mode as hydraulic remains OFF. 7. Emergency gear selector - PUSH 8. Hydraulic pump switch - HYD 9. Landing distance - INCREASE the flaps DN landing distance (Figure 56) by approximately 125% NOTE When operating in sustained icing condition, assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 60), must be increased by 20 KIAS. The landing distance, as compared with the flaps MID landing distance (Figure 60), must be increased approximately by 90%. SUPPLEMENT 15 Page 12 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SINGLE ENGINE APPROACH AND LANDING 1. 2. 3. 4. 5. 6. WARNING Do not exceed maximum fuel imbalance (200 lbs). Inoperative engine - COMPLETE ENGINE SECURING Procedure Condition lever (operating engine) - MAX RPM Flaps - MID NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. Airspeed - 132 KIAS MIN. Landing gear (when landing assured) - DN Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) When it is certain there is no possibility of go-around: 7. 8. 9. CAUTION Coupled approaches, with yaw damper inoperative, must be performed in clean or MID flap configuration. Flaps - DN Approach speed - AS PER Figure 56 Power lever - AS REQUIRED After touchdown: 10. Brakes and reverse - AS REQUIRED 11. Landing distance - INCREASE the flaps DN landing distance (Figure 56) approximately: 30% if reverse thrust is not applied, or 25% if reverse thrust is applied NOTE When operating in sustained icing condition assume the same procedure except: flap position must be MID, and approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. The flaps MID landing distance (Figure 60) must be increased approximately by 30% if reverse thrust is not applied and by 25% if reverse thrust is applied. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 13 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SINGLE ENGINE GO-AROUND 1. Autopilot - DISENGAGE (if engaged) 2. Power - TAKE OFF 3. Airspeed - Minimum 125 KIAS 4. Flaps - MID 5. Landing gear - UP 6. Airspeed - INCREASE TO 130 KIAS MINIMUM 7. Flaps - UP NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. 8. Taxi/Landing lights (if applicable) - OFF 9. Airspeed - INCREASE as required WARNING When operating in sustained icing conditions, insufficient performance may exist to successfully carry out a single engine go-around. SUPPLEMENT 15 Page 14 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING WITH PRIMARY LONGITUDINAL CONTROL FAILED When ready for approach: 1. Trim - IN LEVEL FLIGHT TO 140 KIAS 2. Runway - Select longest in area suitable for a low angle descent 3. Landing gear - DN 4. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) 5. Flaps - MID 6. Trim - TO 135 KIAS 7. Power - AS REQUIRED 8. Condition levers - MAX RPM 9. Flaps - DN 10. Trim - TO 125 KIAS NOTE When operating in sustained icing condition assume the same procedure except: flap position must be MID, and approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. When positioned over the runway, flare airplane with longitudinal trim and slowly reduce power: 11. Brakes (after nose wheel touchdown) - AS REQUIRED 12. Reverse - AS REQUIRED Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 15 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING WITH STABILIZER JAMMED 1. Condition levers - MAX RPM 2. Power levers - AS REQUIRED 3. Landing gear - DN 4. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) Stabilizer jammed in nose down trim position: 5. Flaps - MID 6. Approach Speed - INCREASE the flaps DN approach speed (Figure 56) by 15 KIAS 7. Brakes and reverse - AS REQUIRED 8. Landing distance - INCREASE the flaps DN landing distance (Figure 56) by approximately 50% Stabilizer jammed in nose up trim position: 9. Flaps - DN 10. Approach speed - AS PER Figure 56 11. Brakes and reverse - AS REQUIRED NOTE When operating in sustained icing conditions assume the same procedure except: flap position must be MID, whatever is the stabilizer position, and the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 10 KIAS. The flaps MID landing distance (Figure 60) must be increased approximately by 25%. SUPPLEMENT 15 Page 16 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING WITH LONGITUDINAL CONTROL SPRING FAILED 1. Condition levers - MAX RPM 2. Power levers - AS REQUIRED 3. Landing gear - DN 4. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) 5. Flap - MID 6. Approach Speed - INCREASE the flaps DN approach speed (Figure 56) by 15 KIAS 7. Brakes and reverse - AS REQUIRED 8. Landing distance - INCREASE the flaps DN landing distance (Figure 56) by approximately 50% if the reverse thrust is not applied NOTE When operating in sustained icing condition, assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 60), must be increased by 10 KIAS. The flaps MID landing distance (Figure 60) must be increased approximately by 20%. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 17 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING WITH AUTOFEATHER SYSTEM INOPERATIVE (AMBER AUTOFEATHER LIGHT ON) 1. Condition lever - MAX RPM 2. Power levers - AS REQUIRED 3. Landing gear - DN 4. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) 5. Flap - MID 6. Approach Speed - INCREASE the flaps DN approach speed (Figure 56) by 15 KIAS 7. Brakes and reverse - AS REQUIRED 8. Landing distance - INCREASE the flaps DN landing distance (Figure 56) by approximately: 50% if reverse thrust is not applied, or 26% if reverse thrust is applied NOTE When operating in sustained icing condition, assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. The flaps MID landing distance (Figure 60) must be increased approximately by 10% if reverse thrust is not applied or by 5% if reverse thrust is applied. SUPPLEMENT 15 Page 18 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 ASYMMETRIC FLAP LANDING (FLAP SYNC LIGHT ON) 1. FLAP SYSTEM MALFUNCTION Procedure - COMPLETE 2. Condition levers - MAX RPM 3. Power levers - AS REQUIRED 4. Landing gear - DN 5. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) 6. Approach speed - INCREASE the flaps DN approach speed (Figure 56) as indicated in the table below 7. Brakes and reverse - AS REQUIRED 8. Landing distance - if the reverse thrust is not applied INCREASE the flaps DN landing distance (Figure 56) approximately as indicated in the table below: OUTBOARD FLAP POSITION SPEED INCREASE LANDING DISTANCE INCREASE DN 5 KIAS 10% MID 15 KIAS 50% UP 20 KIAS 65% NOTE When operating in sustained icing conditions assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 60), must be increased as indicated in the table below: OUTBOARD FLAP POSITION SPEED INCREASE LANDING DISTANCE INCREASE (Figure 60) MID 10 KIAS 20% UP 20 KIAS 40% Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 19 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING WITH FLAPS RETRACTED 1. Approach Speed - INCREASE the flaps DN approach speed (Figure 56) by 20 KIAS 2. Condition levers - MAX RPM 3. Power levers - AS REQUIRED 4. Landing gear - DN 5. Steering - Check armed (T/O message on PFD) (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) After touchdown: 6. Reverse - AS REQUIRED 7. Landing distance - INCREASE the flaps DN landing distance (Figure 56) by approximately: 65% if reverse thrust is not applied, or 55% if reverse thrust is applied NOTE When operating in sustained icing conditions assume the same procedure except approach speed which, as compared with the flaps MID approach speed (Figure 60), must be increased by 20 KIAS. The landing distance, as compared with the flaps MID landing distance (Figure 60), must be increased approximately by 40% if reverse thrust is not applied or by 30% if reverse thrust is applied. SUPPLEMENT 15 Page 20 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 3.3 3.3.1 AMPLIFIED EMERGENCY PROCEDURES ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF AT OR AFTER ROTATION If sufficient runway remains for a safe stop or the decision is made to abort the takeoff, maintain directional control. Pull the power lever of the engines to IDLE and land straight ahead. After touch down use brakes and reverse as required, engaging reverse below 1900 Prop RPM or 5% drop from the set value. Should a suitable landing area exist, and the decision is made to land the airplane following an engine failure at, or after rotation initiation, the pilot should be aware that performance charts are not presented in this manual for this condition and that the total distance required to stop will exceed the published Accelerate/Stop performance shown in Section 5 of this Supplement. If insufficient runway remains or if the decision is made to continue the takeoff, maintain directional control (banking the plane 5° max toward the operative engine when airborne) and maintain the maximum takeoff power while maintaining torque and ITT within limits. After assuring that the aircraft will not settle back to the runway, retract the landing gear and accelerate to the "one engine 50 feet height speed" as per Figure 8 (Accelerate/Go Distance Over 50 Feet Obstacle graph) at Section 5 of this Supplement. Accelerate to a speed of 130 KIAS minimum, then retract the flaps and the taxi/ landing lights (if applicable) to achieve the one engine inoperative recommended climb speed of 140 KIAS. Maintain this speed until clearing all obstacles within the immediate vicinity of the airport. After all these obstacles have been cleared, perform the ENGINE SECURING procedure. NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. Place the autofeather arm switch in the OFF position and increase airspeed as required. Once the above procedures have been completed and the aircraft is at a safe altitude, an airstart may be attempted. (If the start is unsuccessful, complete the ENGINE SECURING Procedure on the inoperative engine). Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 21 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Whether the start is successful or unsuccessful the aircraft should be landed at the nearest suitable airport performing the SINGLE ENGINE APPROACH AND LANDING Procedure. WARNING The decision to continue a takeoff, single engine is primarily predicated upon, but not necessarily limited to, the aircraft’s ability to climb on a single engine with the gear extended and flaps in the takeoff position. Prior to flight, review airfield requirements and determine that adequate single climb performance exists, considering aircraft weight, ambient conditions and pilot proficiency, to safely complete the takeoff should an engine fail at or after rotation. 3.3.5 MAXIMUM GLIDE With the flaps and the landing gear UP, the propellers feathered (condition lever in CUT OFF position) the chart below shows the airspeed to be used to attain the least loss in altitude. Consult the BEST GLIDING DISTANCE diagram on Section 5 "Performance" of the basic AFM to know the horizontal distance covered. MAXIMUM GLIDE SPEED CHART WEIGHT (LBS) SPEED (KIAS) 12100 158 11550 155 11000 151 10000 144 9000 137 8000 129 Glide Ratio (Refer also to BEST GLIDE DISTANCE graph in Section 5 ("Performance") . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3 NM/1000 ft When operating in sustained icing conditions, the ice build-up on the unprotected parts and the runback ice on the forward and main wings will cause a strong drag increment. In these conditions (ice accretion of approximately 3 inches on the main wing tips) the Glide Ratio may decrease up to 50%. SUPPLEMENT 15 Page 22 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 3.3.6 LANDING EMERGENCIES LANDING WITHOUT ENGINE POWER CAUTION With both generators inoperative only essential, battery and hot battery busses are fed by the battery, for approximately 30 minutes depending on loads and battery charge, while the Integrated Stand-by Instrument is fed by the Emergency Power Unit. If an emergency indicates the need to make an approach and landing without the use of engine power, the airplane should first be configured per the MAXIMUM GLIDE Procedure if sufficient altitude permits. When both engines have failed, hydraulic and flap systems are not operative in flight since their circuits are not fed by the battery. In this condition landing gear has to be lowered as per EMERGENCY GEAR EXTENSION Procedure and flaps will be in UP position. NOTE Gear extension requires approximately 60 handpump strokes: this procedure requires normally 90 sec. NOTE For particular terrain conditions it may be required to land with gear up. When the landing gear extension has been completed and only if the gear is confirmed to be down and locked, push in the emergency gear selector and switch to HYD position the hydraulic pump. Once it is assured that the selected landing site will be reached, assume an approach speed increased by 20 KIAS as compared with the flaps DN approach speed (Figure 56). Place the condition levers in CUT OFF, CLOSE the firewall shut-off valves, switch OFF the fuel pumps and the synchrophaser system. After touchdown a particular attention has to be paid since brake operation will become harder and landing distances will increase approximately by 125% as compared with the flaps DN landing distance (Figure 56). The procedure just described applies also when operating in sustained icing conditions with the exception that the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 20 KIAS. The landing distance, as compared with the flaps MID landing distance (Figure 60), must be increased approximately by 90%. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 23 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SINGLE ENGINE APPROACH AND LANDING WARNING Do not exceed maximum fuel imbalance (200 lb.). Ensure that the ENGINE SECURING Procedure is complete. Turn OFF the crossfeed valve if open and advance the condition lever to MAX RPM, extend the flap to MID position and maintain a speed of 132 KIAS minimum. NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. If conditions permit, burn as much fuel as possible. When landing site is assured lower the landing gear. Only if S.B. 80-0454 or 800425 (new NWSS) are installed, check that steering system is automatically armed (STEER T-O message on PFD). NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. When it is certain there is no possibility of go-around, extend the flaps to DN and assume approach speed as per Figure 56. CAUTION Coupled approaches, with yaw damper inoperative, must be performed in clean or MID flap configuration. Adjust the power as required and after touching down, if necessary, apply reverse thrust slowly and cautiously. Reverse thrust must be applied when the prop RPM has dropped to 1900 RPM. The landing distance, as compared with the flaps DN landing distance (Figure 56), will increase by 30% if reverse thrust is not applied and by 25% if reverse thrust is applied. The procedure just described applies also when operating in sustained icing conditions with the exception that the flap position must be MID and the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. The flaps MID landing distance (Figure 60) must be increased by 30% if reverse thrust is not applied or by 25% if reverse thrust is applied. SUPPLEMENT 15 Page 24 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SINGLE ENGINE GO-AROUND To execute a single engine go-around, apply takeoff power to the operating engine. Attain a minimum speed of 125 KIAS and retract flaps to MID position, if they are fully down. Retract landing gear and increase airspeed to 130 KIAS minimum, then retract the flaps and the taxi/landing lights (if applicable). Increase the airspeed as required. NOTE If the left engine is shut down (power lever to IDLE) the landing gear aural warning is activated all the time with the landing gear UP and the flap to MID. In this case no engine exceedance aural warning is provided. WARNING When operating in sustained icing conditions, insufficient performance may exist to successfully carry out a single engine go-around. LANDING WITH PRIMARY LONGITUDINAL CONTROL FAILED In the event it becomes necessary to use trim for longitudinal control, trim the airplane to 140 KIAS in level flight. Select the longest runway in the area suitable for a low angle approach. Extend landing gear and, if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that it is automatically armed (STEER T-O message on PFD). NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. Set flaps to MID position, maintain 135 KIAS and adjust power for a low angle approach, lower the flaps to DN and trim the plane to 125 KIAS. When positioned over the landing runway, flare the airplane using the reduction of power and the longitudinal trim. After landing and when the nose gear is on the runway, apply reverse as required, when the propeller speed has dropped to 1900 RPM. The procedure just described applies also when operating in sustained icing conditions with the exception that the flap position must be MID and the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 25 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING WITH STABILIZER JAMMED If elevator pull force is encountered, the stabilizer is jammed in a nose down trim position. Move, if possible, the center of gravity aft and land as soon as practical to minimize the forward C.G. movement due to fuel-burned. Extend landing gear, if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that it is automatically armed (STEER T-O message on PFD) and set flaps to MID. NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. Assume an approach speed increased by 15 KIAS as compared with the flaps DN approach speed (Figure 56). The flaps DN landing distance (Figure 56) shall be increased by approximately 50% if reverse is not applied. If elevator push force is encountered, the stabilizer is jammed in nose up trim position. Move center of gravity forward if possible. Extend landing gear and set flaps to DN. Assume the approach speed as per Figure 56. The procedure just described applies also when operating in sustained icing conditions with the exception that the flap position must be MID, whatever is the stabilizer position, and the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 10 KIAS. The flaps MID landing distance (Figure 60) must be increased by 25% if reverse thrust is not applied. LANDING WITH LONGITUDINAL CONTROL SPRING FAILED Having assumed the up-down spring failure (refer to LONGITUDINAL CONTROL SPRING FAILURE Procedure), land with flaps in MID position. Assume an approach speed increased by 15 KIAS as compared with the flaps DN approach speed (Figure 56). After touchdown, engage reverse as required. The landing distance, as compared with the flaps DN landing distance Figure 56), must be increased by 50% if the reverse thrust is not applied. The procedure just described applies also when operating in sustained icing conditions with the exception that the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 10 KIAS. The flaps MID landing distance (Figure 60) must be increased approximately by 20%. SUPPLEMENT 15 Page 26 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING WITH AUTOFEATHER SYSTEM INOPERATIVE The amber AUTOFEATHER light on the annunciator panel is normally illuminated when the system is not armed and the landing gear is down. If S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that it is automatically armed (STEER T-O message on PFD) and set flaps to MID. NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. If, after having armed the system, the light remains illuminated, the autofeather system has to be assumed inoperative and the landing will be performed with flaps in MID position. Assume an approach speed increased by 15 KIAS as compared with the flaps DN approach speed (Figure 56). After touchdown, engage brakes and reverse. The landing distance, as compared with the flaps DN landing distance (Figure 56), will increase approximately by 50% if reverse thrust is not applied and by 26% if reverse thrust is applied. The procedure just described applies also when operating in sustained icing conditions with the exception that the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. The flaps MID landing distance (Figure 60) must be increased approximately by 10% if reverse thrust is not applied or by 5% if reverse thrust is applied. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 27 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 ASYMMETRIC FLAP CONDITION LANDING In case of a flap system failure complete the FLAP SYSTEM MALFUNCTIONS Procedure. Prior to reaching an altitude of 50 ft. above runway, assure that the landing gear is extended and adjust power as required. The flaps DN approach speeds and landing distances (Figure 56) shall be increased, depending on the position of outboard wing flaps, as indicated in the following table: OUTBOARD FLAP POSITION SPEED INCREASE LANDING DISTANCE INCREASE (if reverse thrust is not applied) DN 5 KIAS 10% MID 15 KIAS 50% UP 20 KIAS 65% The procedure just described applies also when operating in sustained icing conditions with the exception that the flaps MID approach speeds and landing distances (Figure 60), must be increased as indicated in the table below: OUTBOARD FLAP POSITION SPEED INCREASE LANDING DISTANCE INCREASE (Figure 60) MID 10 KIAS 20% UP 20 KIAS 40% SUPPLEMENT 15 Page 28 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING WITH FLAPS RETRACTED In case of an electrical failure in the feeding circuit of the flap systems or a failure in the outboard wing flap system, a landing with no flaps has to be considered. If conditions permit, burn as much fuel as possible. Set the condition levers to MAX RPM and use power levers as required. Assume an approach speed increased by 20 KIAS as compared with the flaps DN approach speed (Figure 56). Lower the landing gear. Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that steering system is automatically armed (STEER T-O message on PFD) NOTE When armed, new NWSS (S.B. 80-0454 or 80-0425) will automatically engage in TAKEOFF mode at touch down. CWMS does not affect steering while in flight. After touchdown, engage reverse when the propeller speed has dropped to 1900 RPM. The landing distance, as compared with the flaps DN landing distance (Figure 56), will increase approximately by 65% if the reverse thrust is not applied or by 55% if reverse thrust is applied. The procedure just described applies also when operating in sustained icing conditions with the exception that the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 20 KIAS. The landing distance, as compared with the flaps MID landing distance (Figure 60), must be increased approximately by 40% if reverse thrust is not applied or by 30% if reverse thrust is applied. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 29 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 15 Page 30 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 4 - NORMAL PROCEDURES 4.1 AIRSPEEDS FOR NORMAL OPERATIONS SPEED KIAS b. Two engines Best Angle of Climb Speed 135 c. Two engines Best Rate of Climb Speed 157 d. Two engines Approach Speed at Maximum Landing Weight Flap MID Flap DN 132 125 e. Balked Landing Climb Speed at Maximum Landing Weight Flap MID Flap DN 132 125 i. Design Maneuvering Speed At 12100 lb At 7700 lb 202 177 k. Maximum Flap Extended Speed Flap MID Flap DN 183 177 l. 181 Maximum Landing Gear Operating Speed p. Rough Air Penetration Speed at or below 25000 ft. Reduce speed 5 KIAS for each 5000 ft above 25000 ft. 200 q. Minimum Speed for Intentional One Engine Inoperative 140 Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 31 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 4.2 NORMAL PROCEDURES CHECKLIST 4.2.4 BEFORE TAXI No changes except for the following: WARNING Do not operate engine inlet de-ice boots below –40°C. No takeoff authorized with frost, snow or ice adhering to propellers, windshields, powerplant installation and pitot/static ports, or with frost, snow or ice adhering to the wings, vertical and horizontal stabilizer or control surfaces. 4.2.8 1. TAKEOFF Power levers - ADVANCE to MAXIMUM TAKE-OFF power WARNING Before applying full power, be sure that the condition levers are set to MAX RPM: takeoff distance given in Sec. 5 may not be assured. 2. Autofeather - CHECK ARMED (green AFX indication, on MFD, ON) WARNING If ambient temperature is below –25°C, it is necessary to operate the main wing anti-ice and the engine ice vane systems before applying full power to ensure that the autofeather is armed. When takeoff is completed and autofeather disengaged, the ice protection can be switched OFF. 3. Engine indications - WITHIN LIMITS 4. (Only if S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed): Steering (not over 60 KIAS) - OFF 5. Rotation - REFER to Section 5 of this Supplement, Figure 6 6. Airspeed - Accelerate to 126 KIAS until above 50 ft. 7. (Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed): Steering - CHECK that automatically disengages (no mode indication on PFD) 8. Taxi/landing lights (below 160 KIAS) - OFF 9. Gear (below 180 KIAS) - UP 10. Autofeather (above 150 KIAS) - OFF SUPPLEMENT 15 Page 32 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 11. Flaps (below 170 KIAS) - UP 12. Flight Director - SELECT desired modes 13. Autopilot and Yaw Damper - ENGAGE above 400 feet AGL if desired CAUTION A continuous annunciated amber elevator mistrim indication will anticipate that the airplane could be significantly out of trim. In this case the pilot should brace the flight controls and disconnect the autopilot. Upon disconnection the pilot will experience a force of between 7 kg (15 lbs) and 9 kg (20 lbs). Re-engagement of the autopilot should not be attempted until the reason for the out of trim state has been isolated and rectified, and the airplane has been returned to a trimmed condition. A temporary annunciated amber elevator mistrim indication during an acceleration/deceleration phase and/or configuration changes could be disregarded if it lasts not more than about 10 seconds. 4.2.14 LANDING Prior to reaching 50 ft. above landing surface: 1. Landing gear - CHECK DN (3 green lights) 2. (Only if S.B. 80-0454 or 80-0425 -new NWSS- are installed) Steering CHECK armed (T/O message on PFD) 3. Flaps - CHECK DN CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID and the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. Steering engagement during landing is prohibited. NOTE The landing distance with flaps MID (Figure 60) must be increased approximately by 10% if reverse thrust is not applied or by 5% if reverse thrust is applied. 4. Approach speed - REFER to Section 5 of this Supplement Figure 56. 5. Power - AS REQUIRED 6. Condition levers - CHECK MAX RPM After touchdown: 7. Brakes - AS REQUIRED Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 33 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 8. Reverse - AS REQUIRED; engage reverse below 1900 prop RPM or 5% drop from the set value NOTE When landing at aft C.G. initiate flaps retraction before actuating reverse power. 9. Reverse - DO NOT USE below 40 KIAS At landing completed: 10. Condition levers - GROUND IDLE 11. Steering - ENGAGE TAKE OFF (if necessary) NOTE If "TAT heater inhibition on-ground" change (ref. para 4.0) is NOT installed, a total air temperature increase may be detected until the TAT heater is turned off. 4.2.15 1. 2. GA button - PUSH. If autopilot engaged GA will be coupled Power Levers - Apply balked landing climb torque as per Figure 54 (Flaps DOWN) and Figure 58 (Flaps MID) at Section 5 of this Supplement 4.2.16 1. GO AROUND BALKED LANDING 2. 3. 4. Power levers - Apply balked landing climb torque as per Figure 54 (Flaps DOWN) and Figure 58 (Flaps MID) at Section 5 of this Supplement Engine indications - WITHIN LIMITS Airspeed - 125 KIAS Flaps (below 150 KIAS) - MID 5. 6. 7. 8. CAUTION When operating in icing conditions, the balked landing procedure must be performed with flaps MID and the airspeed must be 138 KIAS. Gear (after climb established) - UP Landing Lights (below 160 KIAS) - OFF Flaps (below 170 KIAS) - UP Airspeed - 160 KIAS SUPPLEMENT 15 Page 34 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 4.2.20 CAT II OPERATIONS AIRSPEEDS FOR CATEGORY II OPERATIONS Two engines Approach Speed for CAT II operations (VREF): SPEED KIAS a. FLAP MID At 11500 lbs (5216 kg) weight At 10945 lbs (4965 kg) weight At 10270 lbs (4658 kg) weight or below 132 129 125 b. FLAP DN At 11500 lbs (5216 kg) weight At 10945 lbs (4965 kg) weight At 10270 lbs (4658 kg) weight or below 130 125 121 APPROACH AND LANDING PREPARATION AT DH (DECISION HEIGHT CERTIFIED FOR CAT II): Decision - LAND or GO AROUND b. If Go Around is decided (execute GO AROUND procedure below): 1. GA Push Button - DEPRESS 2. Power setting - FULL POWER 3. Autopilot - VERIFY GA green indications ON 4. Aircraft - MONITOR ATTITUDE AND BANK 5. Two-engines go around speed - MAINTAIN (125 KIAS minimum) CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID. In this condition the go around speed is 138 KIAS. 6. Airplane Configuration - AS REQUIRED Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 35 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 4.2.21 OPERATION IN ICING CONDITIONS WEATHER CONDITIONS THAT MAY BE CONDUCIVE TO SEVERE IN-FLIGHT ICING WARNING If unusual ice (e.g. unusual runback ice) is observed forming aft of the protected surfaces of the wing or if unusual lateral trim requirements or autopilot trim warnings are encountered, accomplish the following: – If the flaps are extended, do not retract them until the airframe is clear of ice. – The flight crew should reduce the angle-of-attack by increasing speed as much as the airplane configuration and weather allow, without exceeding design maneuvering speed. – If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot. Do not re-engage the autopilot until the airframe is clear of ice. – Exit the icing area immediately by changing altitude or course; and – Report these weather conditions to air traffic control. CAUTION Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in hazardous ice build-up on protected surfaces exceeding the capability of the ice protection system, and it may seriously degrade the performance and controllability of the airplane. The following shall be used to identify freezing rain/freezing drizzle icing conditions: a. Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice. b. Unusual accumulation of ice on the surfaces of the wings aft of the protected area. The following may be used to identify possible freezing rain/freezing drizzle conditions: a. Visible rain at temperatures below +5°C static air temperature (SAT). b. Droplets that splash or splatter on impact at temperatures below +5°C SAT. c. Performance losses larger than normally encountered in icing conditions. It is possible to experience severe ice accretions not visible to the flight crew, such as wing ice accretion on the non visible wing surface. SUPPLEMENT 15 Page 36 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 PROCEDURES FOR EXITING THE FREEZING RAIN/FREEZING DRIZZLE ENVIRONMENT These procedures are applicable to all flight phases from takeoff to landing. Monitor the outside air temperature. While ice may form in freezing drizzle or freezing rain at temperatures as cold as –18°C, increased vigilance is warranted at temperatures around freezing with visible moisture present. If the visual cues specified in this Supplement for identifying possible freezing rain or freezing drizzle conditions are observed, accomplish the following: a. Exit the freezing rain or freezing drizzle icing conditions immediately to avoid extended exposure to flight conditions outside of those for which the airplane has been certificated for operation. Asking for priority to leave the area is fully justified under these conditions. b. Avoid abrupt and excessive maneuvering that may exacerbate control difficulties. c. Do not engage the autopilot. The autopilot may mask unusual control system forces. d. If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot. e. If an unusual roll response or uncommanded control movement is observed, reduce the angle-of-attack by increasing airspeed or rolling wings level (if in a turn), and apply additional power, if needed. f. Avoid extending flaps during extended operation in icing conditions. Operation with flaps extended can result in a reduced wing angle-of-attack, with unusual ice forming on the upper surface further aft on the wing than normal. g. If the flaps are extended, do not retract them until the airframe is clear of ice. h. Report these weather conditions to ATC. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 37 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 CLIMB PERFORMANCE NOTE If the power cannot be reset and if the ice accretion on the unprotected parts corresponds to one inch approximately on the main wing tips, the following may result: a. the normal two engines rate/gradient of climb (Figure 16 and Figure 17) will be reduced by 800 ft/min. at sea level and 1800 ft/min. at 20000 feet and the ceiling will be approximately 24000 feet. b. the normal one engine inoperative rate/gradient of climb (Figure 23 and Figure 24) will be reduced by 500 ft/min. at sea level and 700 ft/min. at 10000 feet and the ceiling will be approximately 5000 feet. LANDING PERFORMANCE WARNING The icing limitation requiring flaps in MID position for landing is necessary since landing with flaps DN, with heavy residual ice accumulation, may result in a decrease of longitudinal stability or limited trim capability if the C.G. position is, respectively, fully aft or forward. The balked landing climbing speed, with flaps in MID position is 138 KIAS: if the power cannot be reset and if the ice accretion on the unprotected parts corresponds to three inches approximately on the main wing tips, the balked landing rate of climb with flaps in MID position (Figure 59) will be reduced by 1350 ft/min. maximum. The approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. The landing distance with flaps in MID position will be increased approximately by 10%. SUPPLEMENT 15 Page 38 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 4.3 4.3.4 AMPLIFIED NORMAL PROCEDURES BEFORE TAXI No changes except for the following: WARNING Do not operate engine inlet de-ice boots below –40°C. No takeoff authorized with frost, snow or ice adhering to propellers, windshields, powerplant installation and pitot/static ports, or with frost, snow or ice adhering to the wings, vertical and horizontal stabilizer or control surfaces. 4.3.8 TAKEOFF Hold the brakes and advance power lever until about 89.7% torque. WARNING Before applying full power, be sure the condition levers are set to MAX RPM. Disregarding this procedure, a remarkable increment of ground roll will result. Check autofeather armed (green left and right AFX indications on the MFD EIS display), release brakes, increase power up to 96.4% torque and check engine instruments. NOTE Torque limit of 96.4% is the static value to be applied for takeoff in order to obtain the normal 100% (2230 lb.ft.) at takeoff speed for ram effect during the takeoff run. WARNING If ambient temperature is below –25°C, it is necessary to operate the main wing anti-ice and the engine ice vane systems before applying full power to ensure that the autofeather is armed. When takeoff is completed and autofeather disengaged, the ice protection can be switched OFF. At low ambient temperature (below –25°C), in order to ensure that the autofeather is armed, it is necessary to select, on the ANTI ICE panel, AUTO position for L/R MAIN WING and L and R position for ENG ICE VANE and OIL COOL INTK switches. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 39 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 When takeoff is completed and the autofeather system disengaged, the wing and engine anti ice systems can be switched OFF. As the aircraft accelerates, an increase in torque at a fixed power lever position is normal. Adjust power setting as required to maintain engine gauges within limits. Only if S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed, disengage steering not over 60 KIAS. Before rotation attain a minimum airspeed as per Figure 6. Rotate approximately between 10° to 15° nose up according to the weight and, after lift off, accelerate to and maintain an airspeed of 126 KIAS until above 50 ft. Only if S.B. 80-0454 or 80-0425 (new NWSS) are installed, check that the steering system automatically disengage after lift off (no mode indication on PFD). Below 160 KIAS switch off the taxi/landing lights, if applicable, and check LTS DOOR OPEN green advisory indication, on the MFD System Page, is off. Retract landing gear below 180 KIAS and flaps below 170 KIAS. Do not retract the landing gear prematurely. Disengage the autofeather system above 150 KIAS. Flight Director Modes may be selected as desired by the pilot. With any lateral mode selected, the FD SYNC switch will synchronize the pitch commands to the attitude of the airplane at the time FD SYNC switch is released. The autopilot may be engaged above 400 feet AGL during climb. CAUTION A continuous annunciated amber elevator mistrim indication will anticipate that the airplane could be significantly out of trim. In this case the pilot should brace the flight controls and disconnect the autopilot. Upon disconnection the pilot will experience a force of between 7 kg (15 lbs) and 9 kg (20 lbs). Re-engagement of the autopilot should not be attempted until the reason for the out of trim state has been isolated and rectified, and the airplane has been returned to a trimmed condition. A temporary annunciated amber elevator mistrim indication during an acceleration/deceleration phase and/or configuration changes could be disregarded if it lasts not more than about 10 seconds. SUPPLEMENT 15 Page 40 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 4.3.14 LANDING Prior to reaching 50 ft above landing surface verify that the gear and flaps are down. Assume an approach speed as per Figure 56 at Section 5 of this Supplement. CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID and the approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. Only if S.B. 80-0454 or 80-0425 (new NWSS) are NOT installed, steering engagement during landing is prohibited. The landing distance with flaps MID (Figure 60) must be increased approximately by 10% if reverse thrust is not applied or by 5% if reverse thrust is applied. For more information about airplane operation in icing conditions consult Paragraph 4.2.21 of the AFM and of this Supplement. Use power as required and reduce during the flare, check condition lever for MAX RPM. After touch down use brakes and reverse as required. Engage reverse thrust below 1900 prop RPM, or 5% drop from the set value, and disengage when the speed has decreased to 40 KIAS, in order to avoid damages to the propellers and, particularly if S.B. 80-0286 or Mod. 80-0932 is NOT installed, in order to avoid transmission of rudder induced oscillations to the pedals. NOTE When landing at aft C.G. initiate flaps retraction before actuating reverse power. When landing at light weights, use caution when applying brakes, as excessive pedal pressure will result in skidding the tires with a resultant loss in braking effectiveness. When landing is completed and reverse has been disengaged retard the condition levers to GROUND IDLE. Engage Steering in TAKE OFF mode (if necessary). NOTE If "TAT heater inhibition on-ground" change (ref. para 4.0) is NOT installed, a total air temperature increase may be detected until the TAT heater is turned off. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 41 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 4.3.15 GO AROUND Execute a Go-Around by the following procedure: 1. Press the GA button on the left power lever while increasing power to the balked landing climb torque as per Figure 54 (Flaps DOWN) and Figure 58 (Flaps MID) at Section 5 of this Supplement. The GA mode can be selected only from the APPR mode; if the autopilot is engaged, the GA mode will maneuver the aircraft to an approximately 8° nose up pitch attitude. The APPR Mode is canceled, GA green indications will come ON and steering commands are provided for a wings level, fixed 8° pitch-up. Selecting a lateral or vertical mode cancels the Go-Around mode. The pitch attitude will remain at that used for Go-Around until changed with the selection of a vertical mode. 2. After airplane cleanup, Go-Around power settings and airspeed are established, select the HDG or NAV mode on the Flight Guidance Panel to fly the missed approach procedure. 4.3.16 BALKED LANDING In a balked landing situation, apply Balked Landing climb torque as per Figure 54 (Flaps DOWN) and Figure 58 (Flaps MID), maintain torque and engine temperature within allowable limits. Maintain an airspeed of 125 KIAS. CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID. The balked landing speed, in icing conditions, with flaps MID is 138 KIAS. For more information about airplane operation in icing conditions consult Paragraph 4.2.21 of the AFM and of this Supplement. After climb is established, accelerate the airplane then retract the flaps to MID (below 150 KIAS), retract the landing gear, switch off the landing lights (below 160 KIAS) then retract flap to UP position (below 170 KIAS). Accelerate to and maintain a speed of 160 KIAS. SUPPLEMENT 15 Page 42 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 4.3.20 CATEGORY II OPERATIONS APPROACH AND LANDING PREPARATION IF GO AROUND IS DECIDED In go around situation, press the GA button on the left power lever while increasing power to the bulked landing climb power setting (refer to Section 5 of this Supplement for power setting and to Paragraph 4.3.15 of the AFM for further information on autopilot go around). Maintain torque and engine temperature within allowable limits. Maintain an airspeed of 125 KIAS (minimum). CAUTION When operating in icing conditions, the landing procedure must be performed with flaps MID. In this condition the go around speed is 138 KIAS. For more information about airplane operation in icing conditions refer to Paragraph 4.2.21 of the basic AFM and of this Supplement. After climb is established, accelerate the airplane than retract the flap to MID (below 150 KIAS), retract the landing gear, then retract the flap to UP (below 170 KIAS). Accelerate to and maintain a speed of 160 KIAS. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 43 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 4.3.21 OPERATION IN ICING CONDITIONS WEATHER CONDITIONS THAT MAY BE CONDUCIVE TO SEVERE IN-FLIGHT ICING WARNING If unusual ice (e.g. unusual runback ice) is observed forming aft of the protected surfaces of the wing or if unusual lateral trim requirements or autopilot trim warnings are encountered, accomplish the following: – If the flaps are extended, do not retract them until the airframe is clear of ice. – The flight crew should reduce the angle-of-attack by increasing speed as much as the airplane configuration and weather allow, without exceeding design maneuvering speed. – If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot. Do not re-engage the autopilot until the airframe is clear of ice. – Exit the icing area immediately by changing altitude or course; and – Report these weather conditions to air traffic control. CAUTION Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in hazardous ice build-up on protected surfaces exceeding the capability of the ice protection system, and it may seriously degrade the performance and controllability of the airplane. The following shall be used to identify freezing rain/freezing drizzle icing conditions: a. Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice. b. Unusual accumulation of ice on the surfaces of the wings aft of the protected area. The following may be used to identify possible freezing rain/freezing drizzle conditions: a. Visible rain at temperatures below +5°C static air temperature (SAT). b. Droplets that splash or splatter on impact at temperatures below +5°C SAT. c. Performance losses larger than normally encountered in icing conditions. It is possible to experience severe ice accretions not visible to the flight crew, such as wing ice accretion on the non visible wing surface. SUPPLEMENT 15 Page 44 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 PROCEDURES FOR EXITING THE FREEZING RAIN/FREEZING DRIZZLE ENVIRONMENT These procedures are applicable to all flight phases from takeoff to landing. Monitor the outside air temperature. While ice may form in freezing drizzle or freezing rain at temperatures as cold as –18°C, increased vigilance is warranted at temperatures around freezing with visible moisture present. If the visual cues specified in this Supplement for identifying possible freezing rain or freezing drizzle conditions are observed, accomplish the following: a. Exit the freezing rain or freezing drizzle icing conditions immediately to avoid extended exposure to flight conditions outside of those for which the airplane has been certificated for operation. Asking for priority to leave the area is fully justified under these conditions. b. Avoid abrupt and excessive maneuvering that may exacerbate control difficulties. c. Do not engage the autopilot. The autopilot may mask unusual control system forces. d. If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot. e. If an unusual roll response or uncommanded control movement is observed, reduce the angle-of-attack by increasing airspeed or rolling wings level (if in a turn), and apply additional power, if needed. f. Avoid extending flaps during extended operation in icing conditions. Operation with flaps extended can result in a reduced wing angle-of-attack, with unusual ice forming on the upper surface further aft on the wing than normal. g. If the flaps are extended, do not retract them until the airframe is clear of ice. h. Report these weather conditions to ATC. CLIMB PERFORMANCE If the power cannot be reset and if the ice accretion on the unprotected parts corresponds to one inch approximately on the main wing tips, the following may result: a. the normal two engines rate/gradient of climb (Figure 16 and Figure 17) will be reduced by 800 ft/min. at sea level and 1800 ft/min. at 20000 feet and the ceiling will be approximately 24000 feet. b. the normal one engine inoperative rate/gradient of climb (Figure 23 and Figure 24) will be reduced by 500 ft/min. at sea level and 700 ft/min. at 10000 feet and the ceiling will be approximately 5000 feet. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 SUPPLEMENT 15 Page 45 of 112 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 LANDING PERFORMANCE WARNING The icing limitation requiring flaps in MID position for landing is necessary since landing with flaps DN, with heavy residual ice accumulation, may result in a decrease of longitudinal stability or limited trim capability if the C.G. position is, respectively, fully aft or forward. The balked landing climbing speed, with flaps in MID position is 138 KIAS: if the power cannot be reset and if the ice accretion on the unprotected parts corresponds to three inches approximately on the main wing tips, the balked landing rate of climb with flaps in MID position (Figure 59) will be reduced by 1350 ft/min. maximum. The approach speed, as compared with the flaps MID approach speed (Figure 60), must be increased by 6 KIAS. The landing distance with flaps in MID position will be increased approximately by 10%. 4.3.24 VMCA - AIR MINIMUM CONTROL SPEED VMCA is the minimum flight speed at which a twin-engine airplane is directionally controllable as determined in accordance with the EASA CS 23 Certification Regulations. Airplane certification conditions include one engine inoperative and propeller windmilling; not more than a 5° bank toward the operative engine; flaps takeoff with landing gear up and flaps landing with landing gear down and most rearward center of gravity. VMCA has been determined to be 100 KIAS with the propeller feathered, for both takeoff and landing configurations, and 128 KIAS with propeller windmilling. 4.3.26 ROUGH AIR OPERATION In condition of extreme turbulence, slow the airplane to Rough Air Penetration Speed of 200 KIAS at or below 25000 ft. 4.3.30 STEEP APPROACH OPERATIONS NOTE Steep Approach Operations are prohibited for Maximum Landing Weight (MLW) greater than 10945 lbs (4965 kg). SUPPLEMENT 15 Page 46 of 112 Appr. DOA EASA.21J.685 1105-2999 Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 5 - PERFORMANCE 5.0 GENERAL List of EASA approved figures: 2, 3, 4, 5, 6, 10, 12, 13, 14, 16, 17, 21, 23, 24, 54, 56, 58, 60, 62. NOTE EASA approved figures 4, 10, 14, 21, 54 and 58 are equivalent to the corresponding figures in the basic Airplane Flight Manual and are not affected by weight; these figures are included in this supplement for pilot’s convenience and in order to maintain the operative sequence. EASA approved figure 5-12 of the basic Airplane Flight Manual is no more applicable. EASA not approved figures are 7, 8, 9, 11, 15, 18, 19, 20, 22, 25, from 26 to 53, 55, 57, 59 and 61, and are included in this Supplement for pilot’s convenience and arranged in a reasonable operative sequence. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 47 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 WEIGHT 12,100 LBS (5490 KGS) BANK ANGLE FLAPS UP FLAPS MID FLAPS DN DEG KIAS KCAS KIAS KCAS KIAS KCAS 0 114 113 106 104 99 98 10 115 114 106 105 99 99 20 118 116 109 108 102 101 30 123 121 113 112 106 105 40 130 129 120 119 113 112 50 142 141 131 130 123 122 60 161 160 149 147 139 139 ASSOCIATED CONDITIONS: IDLE POWER - FORWARD C.G. GEAR POSITION HAS NO EFFECT ON STALLING SPEEDS. MAXIMUM ALTITUDE LOSS DURING STALL IS 1,000 FT. WEIGHT 11,551 LBS (5240 KGS) BANK ANGLE FLAPS UP FLAPS MID FLAPS DN DEG KIAS KCAS KIAS KCAS KIAS KCAS 0 112 110 104 102 98 96 10 113 111 105 103 99 97 20 115 114 107 105 101 100 30 120 119 111 109 105 104 40 128 126 118 116 112 110 50 139 138 129 127 122 120 60 158 156 146 144 138 136 Figure 2. Stall Speed (For lower weights refer to Fig. 5-11 of the basic AFM) 12 14 15 16 18 19 19b 21 23 21b 23b 24 25 26 26b 27 28 29 30 31 32 32b33 C SUPPLEMENT 15 Page 48 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 3. Buffet Onset Limits (This figure supersedes Fig. 5-12 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 49 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 NOTE Torque limit of 96.4% (2150 lb.ft) is the static value to be applied for takeoff in order to obtain the normal 100% (2230 lb.ft) at takeoff speed for ram effect during the takeoff run. Figure 4. Takeoff Power Torque (Equivalent to Fig. 5-14 of the basic AFM) SUPPLEMENT 15 Page 50 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 NOTE When operating in icing conditions add 22°C to the SAT before entering this graph. Figure 5. Maximum Takeoff Weight to achieve One Engine Inoperative Takeoff Climb Requirements - Flaps MID, Landing Gear Retracted Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 51 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 6. Takeoff Ground Run and Takeoff Distance over 50 feet (For lower weights refer to Fig. 5-16 and 5-17 of the basic AFM) SUPPLEMENT 15 Page 52 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 7. Accelerate and Go Distance over 50 feet (For lower weights refer to Fig. 5-18 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 53 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 8. Accelerate and Stop Distance (For lower weights refer to Fig. 5-19 of the basic AFM) SUPPLEMENT 15 Page 54 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 9. Brake Energy and Associated Weights for Rejected Takeoff Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 55 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 10. Twin Engine Climb Torque - Flaps MID (Equivalent to Fig. 5-21 of the basic AFM) SUPPLEMENT 15 Page 56 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 11. Twin Engine Gradient of Climb - Flaps MID Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 57 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 NOTE This graph is also applicable for CAT II - One Engine Inoperative Go-Around, flown at 125 KIAS, for any weight from 10945 lbs (4965 kg) to 11500 lbs (5216 kg). Figure 12. One Engine Inoperative Takeoff Climb Torque SUPPLEMENT 15 Page 58 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 13. One Engine Inoperative Takeoff Climb Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 59 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 14. Twin Engine En-Route Climb Torque (Equivalent to Fig. 5-24 of the basic AFM) SUPPLEMENT 15 Page 60 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 15. Twin Engine Climb Fuel Flow - Flaps Retracted (Equivalent to Fig. 5-25 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 61 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 16. Twin Engine En-Route Rate of Climb/Descent (For lower weights refer to Fig. 5-26 of the basic AFM) SUPPLEMENT 15 Page 62 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 17. Twin Engine En-Route Gradient of Climb/Descent Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 63 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 18. Time to Climb (This graph supersedes Fig. 5-27 of the basic AFM) SUPPLEMENT 15 Page 64 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 19. Fuel to Climb (This graph supersedes Fig. 5-28 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 65 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 20. Distance to Climb (This graph supesedes Fig. 5-29 of the basic AFM) SUPPLEMENT 15 Page 66 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 21. One Engine Inoperative En-Route Climb/Descent Torque (Equivalent to Fig. 5-30 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 67 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 22. One Engine Inoperative En-Route Climb Fuel Flow (Equivalent to Fig. 5-31 of the basic AFM) SUPPLEMENT 15 Page 68 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 23. One Engine Inoperative En-Route Rate of Climb/Descent (For lower weights refer to Fig. 5-32 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 69 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 24. One Engine Inoperative En-Route Gradient of Climb/Descent SUPPLEMENT 15 EASA Approved Page 70 of 112 .A 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 6 : Jan. 09, 2017 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 25. One Engine Inoperative Service Ceiling - Flaps Retracted (For lower weights refer to Fig. 5-33 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 71 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA -30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 900 244 260 244 260 244 260 419 838 262 260 262 260 262 260 75.0 394 788 281 260 281 260 281 260 79.3 375 750 302 260 302 260 302 260 -66 83.2 363 726 325 260 325 260 325 260 -61 -77 86.6 363 726 340 260 340 260 340 260 25000 -65 -84 89.2 364 728 350 260 350 260 350 260 27000 -68 -91 92.2 371 742 361 260 361 260 361 260 28000 -70 -95 94.0 376 752 366 260 366 260 366 260 29000 -72 -98 96.1 383 766 372 260 372 260 372 260 31000 -76 -106 97.3 387 774 379 256 379 256 379 256 33000 -80 -113 90.4 363 726 375 245 375 245 375 245 35000 -84 -120 83.9 341 682 372 234 372 234 372 234 37000 -87 -124 78.4 322 644 369 223 369 223 369 223 39000 -87 -124 73.7 307 614 369 213 369 213 369 213 41000 -87 -124 63.7 271 542 358 196 364 200 369 203 FEET °C °F % LBS/HR LBS/HR 0 -15 5 65.7 450 5000 -25 -13 70.4 10000 -35 -31 15000 -45 -48 20000 -55 23000 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 26. Maximum Cruise Power - 2000 RPM - ISA -30°C (ref. Fig. 5-34) SUPPLEMENT 15 Page 72 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA -20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 912 249 260 249 260 249 260 426 852 267 260 267 260 267 260 76.5 402 804 286 260 286 260 286 260 81.0 384 768 308 260 308 260 308 260 -48 85.1 371 742 332 260 332 260 332 260 -51 -59 88.7 373 746 348 260 348 260 348 260 25000 -55 -66 91.3 375 750 358 260 358 260 358 260 27000 -58 -73 94.5 382 764 370 260 370 260 370 260 28000 -60 -77 96.3 388 776 375 260 375 260 375 260 29000 -62 -80 98.5 395 790 381 260 381 260 381 260 31000 -66 -88 99.7 399 798 389 256 389 256 389 256 33000 -70 -95 92.6 374 748 385 245 385 245 385 245 35000 -74 -102 86.1 352 704 381 234 381 234 381 234 37000 -77 -106 76.7 318 636 373 219 378 222 379 223 39000 -77 -106 66.0 280 560 361 202 367 205 372 209 41000 -77 -106 56.6 246 492 348 185 354 189 360 192 FEET °C °F % LBS/HR LBS/HR 0 -5 23 66.9 456 5000 -15 5 71.8 10000 -25 -13 15000 -35 -30 20000 -45 23000 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 27. Maximum Cruise Power - 2000 RPM - ISA -20°C (ref. Fig. 5-35) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 73 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA -10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 924 253 260 253 260 253 260 868 272 260 272 260 272 260 FEET °C °F % LBS/HR LBS/HR 0 5 41 68.2 462 5000 -5 23 73.1 434 10000 -15 5 78.1 411 822 292 260 292 260 292 260 15000 -25 -12 82.7 393 786 315 260 315 260 315 260 20000 -35 -30 86.9 382 764 339 260 339 260 339 260 23000 -41 -41 90.6 383 766 355 260 355 260 355 260 25000 -45 -48 93.4 386 772 366 260 366 260 366 260 27000 -48 -55 96.7 394 788 378 260 378 260 378 260 28000 -50 -59 98.6 400 800 384 260 384 260 384 260 29000 -52 -62 99.6 403 806 389 258 390 260 390 260 31000 -56 -70 91.1 372 744 383 246 387 249 391 251 33000 -60 -77 83.2 344 688 377 233 382 236 386 239 35000 -64 -84 75.7 316 632 370 221 375 224 380 227 37000 -67 -88 66.9 285 570 361 206 366 209 371 212 39000 -67 -88 56.8 249 498 346 188 352 191 358 195 41000 -67 -88 48.4 218 436 - - 337 174 345 178 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 28. Maximum Cruise Power - 2000 RPM - ISA -10°C (ref. Fig. 5-36) SUPPLEMENT 15 Page 74 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 940 258 260 258 260 258 260 888 277 260 277 260 277 260 FEET °C °F % LBS/HR LBS/HR 0 15 59 69.4 470 5000 5 41 74.5 444 10000 -5 23 79.6 421 842 298 260 298 260 298 260 15000 -15 6 84.3 403 806 321 260 321 260 321 260 20000 -25 -12 88.7 392 784 346 260 346 260 346 260 23000 -31 -23 92.6 394 788 363 260 363 260 363 260 25000 -35 -30 95.4 396 792 374 260 374 260 374 260 27000 -38 -37 98.8 404 808 386 260 386 260 386 260 28000 -40 -41 94.5 389 778 384 254 387 256 390 258 29000 -42 -44 90.3 374 748 381 247 385 250 388 252 31000 -46 -52 82.4 345 690 375 235 380 238 384 240 33000 -50 -59 74.7 317 634 368 222 373 225 378 228 35000 -54 -66 67.4 291 582 360 209 366 212 371 216 37000 -57 -70 59.0 260 520 348 193 354 197 360 200 39000 -57 -70 50.3 228 456 331 175 339 179 347 184 41000 -57 -70 42.1 198 396 - - - - 330 166 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 29. Maximum Cruise Power - 2000 RPM - ISA (ref. Fig. 5-37) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 75 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA +10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 960 262 260 262 260 262 260 454 908 282 260 282 260 282 260 81.0 432 864 303 260 303 260 303 260 86.0 414 828 327 260 327 260 327 260 6 90.5 402 804 353 260 353 260 353 260 -21 -5 94.4 403 806 370 260 370 260 370 260 25000 -25 -12 97.4 406 812 382 260 382 260 382 260 27000 -28 -19 90.3 379 758 379 249 382 251 385 253 28000 -30 -23 86.3 364 728 377 243 380 245 383 247 29000 -32 -26 82.3 349 698 374 237 378 239 381 241 31000 -36 -34 74.7 321 642 367 224 372 227 376 230 33000 -40 -41 67.3 294 588 358 210 364 214 369 217 35000 -44 -48 60.0 267 534 348 196 354 200 361 204 37000 -47 -52 52.6 239 478 334 180 342 185 350 189 39000 -47 -52 44.5 209 418 - - 323 166 334 172 41000 - - - - - - - - - - - FEET °C °F % LBS/HR LBS/HR 0 25 77 70.5 480 5000 15 59 75.8 10000 5 41 15000 -5 24 20000 -15 23000 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 30. Maximum Cruise Power - 2000 RPM - ISA +10°C (ref. Fig. 5-38) SUPPLEMENT 15 Page 76 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA +20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 984 267 260 267 260 267 260 465 930 287 260 287 260 287 260 82.5 443 886 309 260 309 260 309 260 87.5 425 850 333 260 333 260 333 260 24 92.2 412 824 360 260 360 260 360 260 13 94.8 407 814 375 258 377 260 377 260 FEET °C °F % LBS/HR LBS/HR 0 35 95 71.7 492 5000 25 77 77.1 10000 15 59 15000 5 42 20000 -5 23000 -11 25000 -15 6 87.8 378 756 373 248 375 249 378 251 27000 -18 -1 80.4 350 700 368 236 371 238 374 240 28000 -20 -5 76.8 336 672 366 230 369 232 372 234 29000 -22 -8 73.1 322 644 362 224 366 227 370 229 31000 -26 -16 66.1 296 592 354 211 360 214 364 217 33000 -30 -23 59.1 270 540 343 196 350 201 357 205 35000 -34 -30 53.0 246 492 331 182 340 187 347 192 37000 -37 -34 46.5 221 442 311 164 325 171 335 177 39000 -37 -34 39.2 193 386 - - - - 308 155 41000 - - - - - - - - - - - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 31. Maximum Cruise Power - 2000 RPM - ISA +20°C (ref. Fig. 5-39) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 77 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA +30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1006 271 260 271 260 271 260 477 954 291 260 291 260 291 260 83.9 454 908 314 260 314 260 314 260 89.1 433 866 339 260 339 260 339 260 42 88.4 402 804 358 253 360 254 361 255 -1 31 79.8 363 726 356 239 359 241 361 243 25000 -5 24 73.8 337 674 352 229 356 231 359 233 27000 -8 17 67.1 310 620 347 217 350 220 354 222 28000 -10 13 63.8 298 596 343 211 347 214 351 216 29000 -12 10 60.4 284 568 337 204 344 208 348 210 31000 -16 2 53.7 259 518 323 188 333 194 340 198 33000 -20 -5 48.1 236 472 307 171 321 180 332 186 35000 -24 -12 43.7 217 434 - - 305 164 320 172 37000 -27 -16 38.0 194 388 - - - - 294 151 39000 - - - - - - - - - - - 41000 - - - - - - - - - - - FEET °C °F % LBS/HR LBS/HR 0 45 113 72.9 503 5000 35 95 78.4 10000 25 77 15000 15 60 20000 5 23000 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 32. Maximum Cruise Power - 2000 RPM - ISA +30°C (ref. Fig. 5-40) SUPPLEMENT 15 Page 78 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA -30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 892 244 260 244 260 244 260 417 834 262 260 262 260 262 260 83.9 391 782 281 260 281 260 281 260 88.1 372 744 302 260 302 260 302 260 -66 92.3 360 720 325 260 325 260 325 260 -61 -77 96.4 362 724 340 260 340 260 340 260 25000 -65 -84 99.6 366 732 350 260 350 260 350 260 27000 -68 -91 100.0 364 728 356 256 360 259 361 260 28000 -70 -95 100.0 364 728 359 254 362 257 366 259 29000 -72 -98 100.0 363 726 363 253 365 255 369 257 31000 -76 -106 100.0 363 726 370 250 372 251 375 253 33000 -80 -113 97.0 354 708 375 245 375 245 375 245 35000 -84 -120 88.3 326 652 372 234 372 234 372 234 37000 -87 -124 80.7 301 602 369 223 369 223 369 223 39000 -87 -124 74.2 281 562 369 213 369 213 369 213 41000 -87 -124 67.5 260 520 367 202 369 203 369 203 FEET °C °F % LBS/HR LBS/HR 0 -15 5 73.6 446 5000 -25 -13 79.3 10000 -35 -31 15000 -45 -48 20000 -55 23000 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 33. Recommended Cruise Power - 1800 RPM - ISA -30°C (ref. Fig. 5-41) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 79 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA -20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 902 249 260 249 260 249 260 424 848 267 260 267 260 267 260 85.7 400 800 286 260 286 260 286 260 90.0 380 760 308 260 308 260 308 260 -48 94.4 369 738 332 260 332 260 332 260 -51 -59 98.6 372 744 348 260 348 260 348 260 25000 -55 -66 100.0 371 742 356 258 358 260 358 260 27000 -58 -73 100.0 368 736 362 254 365 256 368 259 28000 -60 -77 100.0 368 736 365 252 368 254 372 257 29000 -62 -80 100.0 367 734 368 250 371 252 375 255 31000 -66 -88 100.0 367 734 376 247 378 249 381 251 33000 -70 -95 98.6 363 726 384 244 385 245 385 245 35000 -74 -102 90.1 335 670 380 233 381 234 381 234 37000 -77 -106 80.4 303 606 374 220 377 222 379 223 39000 -77 -106 68.9 266 532 358 200 364 204 369 207 41000 -77 -106 58.7 233 466 336 178 347 185 355 189 FEET °C °F % LBS/HR LBS/HR 0 -5 23 75.0 451 5000 -15 5 80.9 10000 -25 -13 15000 -35 -30 20000 -45 23000 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 34. Recommended Cruise Power - 1800 RPM - ISA -20°C (ref. Fig. 5-42) SUPPLEMENT 15 Page 80 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA -10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 912 253 260 253 260 253 260 432 864 272 260 272 260 272 260 FEET °C °F % LBS/HR LBS/HR 0 5 41 76.4 456 5000 -5 23 82.4 10000 -15 5 87.4 409 818 292 260 292 260 292 260 15000 -25 -12 91.9 390 780 315 260 315 260 315 260 20000 -35 -30 96.4 380 760 339 260 339 260 339 260 23000 -41 -41 100.0 381 762 354 259 355 260 355 260 25000 -45 -48 100.0 375 750 361 255 364 258 366 260 27000 -48 -55 100.0 373 746 367 252 371 254 374 256 28000 -50 -59 100.0 372 744 371 250 374 252 377 255 29000 -52 -62 100.0 371 742 374 248 377 250 381 253 31000 -56 -70 94.7 354 708 374 240 377 242 381 244 33000 -60 -77 86.5 327 654 369 228 373 231 376 233 35000 -64 -84 78.7 301 602 363 216 368 219 372 221 37000 -67 -88 69.3 270 540 351 200 358 204 363 207 39000 -67 -88 58.8 236 472 328 177 340 184 349 189 41000 -67 -88 49.8 206 412 - - 316 163 331 171 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 35. Recommended Cruise Power - 1800 RPM - ISA -10°C (ref. Fig. 5-43) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 81 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 930 258 260 258 260 258 260 884 277 260 277 260 277 260 FEET °C °F % LBS/HR LBS/HR 0 15 59 77.8 465 5000 5 41 83.9 442 10000 -5 23 89.1 418 836 298 260 298 260 298 260 15000 -15 6 93.7 400 800 321 260 321 260 321 260 20000 -25 -12 98.4 391 782 346 260 346 260 346 260 23000 -31 -23 100.0 386 772 359 257 362 259 363 260 25000 -35 -30 100.0 380 760 366 253 369 255 372 258 27000 -38 -37 100.0 377 754 373 250 376 252 379 254 28000 -40 -41 98.3 371 742 374 246 377 249 381 252 29000 -42 -44 94.0 356 712 371 240 375 243 379 246 31000 -46 -52 85.7 329 658 365 228 369 231 374 234 33000 -50 -59 77.6 302 604 357 215 363 218 368 221 35000 -54 -66 69.9 276 552 347 201 355 205 361 209 37000 -57 -70 61.1 247 494 330 183 341 189 350 194 39000 -57 -70 51.9 216 432 303 159 319 168 332 175 41000 -57 -70 43.1 187 374 - - - - 307 154 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 36. Recommended Cruise Power - 1800 RPM - ISA (ref. Fig. 5-44) SUPPLEMENT 15 Page 82 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA +10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. FEET °C °F % 0 25 77 79.1 475 5000 15 59 85.5 453 TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 950 262 260 262 260 262 260 906 282 260 282 260 282 260 LBS/HR LBS/HR 10000 5 41 90.7 430 860 303 260 303 260 303 260 15000 -5 24 95.5 412 824 327 260 327 260 327 260 20000 -15 6 100.0 400 800 353 259 353 260 353 260 23000 -21 -5 100.0 390 780 364 255 366 257 368 258 25000 -25 -12 100.0 384 768 371 251 374 253 377 256 27000 -28 -19 94.0 362 724 369 242 373 244 377 247 28000 -30 -23 89.8 348 696 366 236 370 238 374 241 29000 -32 -26 85.6 334 668 363 229 368 232 372 235 31000 -36 -34 77.5 307 614 354 216 361 220 366 223 33000 -40 -41 69.6 280 560 343 201 352 206 359 211 35000 -44 -48 61.9 254 508 329 185 340 192 349 197 37000 -47 -52 54.2 228 456 309 166 324 175 336 182 39000 -47 -52 45.4 198 396 - - 296 151 314 161 41000 - - - - - - - - - - - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 37. Recommended Cruise Power - 1800 RPM - ISA +10°C (ref. Fig. 5-45) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 83 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA +20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 976 267 260 267 260 267 260 465 930 287 260 287 260 287 260 92.3 442 884 309 260 309 260 309 260 97.3 423 846 333 260 333 260 333 260 24 100.0 405 810 357 257 358 258 360 259 13 99.5 392 784 367 252 370 254 373 256 FEET °C °F % LBS/HR LBS/HR 0 35 95 80.4 488 5000 25 77 86.9 10000 15 59 15000 5 42 20000 -5 23000 -11 25000 -15 6 92.0 364 728 364 241 367 244 371 246 27000 -18 -1 84.2 337 674 359 230 363 232 366 235 28000 -20 -5 80.4 323 646 356 224 360 226 364 229 29000 -22 -8 76.6 310 620 351 217 357 221 361 223 31000 -26 -16 69.0 284 568 341 202 349 208 355 211 33000 -30 -23 61.4 258 516 326 186 337 193 346 198 35000 -34 -30 55.3 236 472 311 170 324 178 336 185 37000 -37 -34 48.3 211 422 285 149 305 160 320 169 39000 - - - - - - - - - - - 41000 - - - - - - - - - - - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 38. Recommended Cruise Power - 1800 RPM - ISA +20°C (ref. Fig. 5-46) SUPPLEMENT 15 Page 84 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA +30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1000 271 260 271 260 271 260 477 954 291 260 291 260 291 260 93.9 453 906 314 260 314 260 314 260 99.0 432 864 339 260 339 260 339 260 42 93.5 390 780 352 248 353 250 355 251 -1 31 84.3 352 704 348 234 352 236 354 238 25000 -5 24 77.8 326 652 344 223 348 226 352 228 27000 -8 17 70.7 301 602 338 211 342 214 347 217 28000 -10 13 67.1 288 576 334 205 339 208 343 211 29000 -12 10 63.5 275 550 327 197 335 202 340 205 FEET °C °F % LBS/HR LBS/HR 0 45 113 81.7 500 5000 35 95 88.4 10000 25 77 15000 15 60 20000 5 23000 31000 -16 2 56.5 250 500 310 179 323 187 332 193 33000 -20 -5 50.7 229 458 291 162 309 172 322 180 35000 -24 -12 45.0 207 414 - - 289 155 308 165 37000 - - - - - - - - - - - 39000 - - - - - - - - - - - 41000 - - - - - - - - - - - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 39. Recommended Cruise Power - 1800 RPM - ISA +30°C (ref. Fig. 5-47) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 85 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA -30°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -15 5 61.9 440 239 254 59.3 433 237 252 56.7 425 235 250 -25 -13 57.9 385 243 241 56.4 381 242 240 53.7 374 240 238 10000 -35 -31 55.0 340 248 229 51.3 330 244 225 48.7 323 241 223 15000 -45 -48 52.1 300 254 218 49.3 293 251 215 45.5 282 246 210 20000 -55 -66 47.7 262 258 204 44.9 255 254 201 42.3 248 251 198 23000 -61 -77 48.3 251 266 201 44.0 239 260 196 41.0 231 255 193 25000 -65 -84 47.7 241 270 198 43.6 229 263 193 39.6 218 257 188 27000 -68 -91 46.4 230 272 193 43.2 221 268 189 39.2 210 260 184 28000 -70 -95 46.1 226 274 191 42.9 217 269 188 39.6 208 264 184 29000 -72 -98 46.2 224 276 189 42.5 213 271 186 38.8 202 264 181 31000 -76 -106 46.2 218 280 186 41.7 205 273 181 38.1 194 268 177 33000 -80 -113 45.1 211 281 180 41.4 199 276 177 37.7 188 271 173 35000 -84 -120 44.5 205 285 176 41.0 194 280 173 37.5 182 275 170 37000 -87 -124 43.5 199 287 170 40.6 189 284 169 37.1 178 279 165 39000 -87 -124 42.7 194 291 165 39.9 184 288 163 36.5 173 283 160 41000 -87 -124 42.1 190 296 160 39.0 179 292 158 36.0 169 287 155 5000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 40. Maximum Range Power - 2000 RPM - ISA -30°C (ref. Fig. 5-48) SUPPLEMENT 15 Page 86 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA -20°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -5 23 59.8 436 239 249 57.2 428 237 247 54.4 420 235 245 5000 -15 5 57.0 385 244 237 54.6 378 242 235 51.8 370 240 233 10000 -25 -13 54.5 341 250 226 51.4 332 247 223 48.7 325 244 221 15000 -35 -30 52.3 303 258 216 49.4 295 254 213 46.4 287 251 210 20000 -45 -48 48.7 267 264 204 46.1 260 260 202 43.3 252 256 198 23000 -51 -59 49.4 257 272 201 44.3 242 263 194 41.3 234 259 191 25000 -55 -66 48.8 247 276 198 44.8 235 270 193 39.8 221 261 186 27000 -58 -73 47.5 236 279 193 44.2 227 274 189 40.1 215 266 184 28000 -60 -77 47.2 233 281 191 43.1 221 273 186 40.0 211 269 183 29000 -62 -80 47.3 230 283 189 42.8 216 275 184 39.7 207 271 181 31000 -66 -88 46.6 223 285 184 42.7 211 280 181 38.4 198 272 176 33000 -70 -95 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 46.2 217 289 180 42.4 205 283 177 38.0 191 276 172 35000 -74 -102 45.7 212 292 176 42.0 200 287 173 38.4 188 282 170 37000 -77 -106 44.8 206 295 171 41.5 195 291 168 38.1 183 286 165 39000 -77 -106 44.0 201 300 165 41.0 190 296 163 37.6 179 291 160 41000 -77 -106 43.0 196 303 160 40.0 185 300 158 37.0 175 296 155 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 41. Maximum Range Power - 2000 RPM - ISA -20°C (ref. Fig. 5-49) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 87 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA -10°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 5 41 56.1 424 235 241 53.2 416 233 239 50.4 407 231 236 5000 -5 23 55.3 382 244 233 53.5 377 243 232 50.8 368 241 229 10000 -15 5 53.7 341 251 223 49.6 329 246 218 46.9 322 244 216 15000 -25 -12 51.6 304 259 213 47.9 293 254 208 44.8 285 250 205 20000 -35 -30 48.3 269 266 201 45.4 261 261 198 43.3 254 259 196 23000 -41 -41 49.6 260 276 199 44.4 245 267 193 41.4 236 263 190 25000 -45 -48 49.1 250 280 196 45.1 238 274 191 39.9 223 264 184 27000 -48 -55 47.8 240 283 191 44.5 230 278 188 40.3 217 270 182 28000 -50 -59 47.5 236 285 189 44.1 226 280 186 40.2 214 272 181 29000 -52 -62 48.1 235 289 189 43.7 221 282 184 40.6 212 277 181 31000 -56 -70 48.2 230 293 185 43.5 215 286 180 39.7 204 280 177 33000 -60 -77 47.7 224 297 181 43.5 211 290 177 39.0 197 283 172 35000 -64 -84 47.0 218 300 176 43.0 205 294 172 39.0 193 287 169 37000 -67 -88 45.9 212 303 171 42.5 200 298 168 38.9 188 293 165 39000 -67 -88 45.1 207 307 165 41.9 196 303 163 38.4 184 297 160 41000 -67 -88 - - - 190 306 157 37.8 179 302 155 LBS/HR KTS KTS - % 40.9 LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 42. Maximum Range Power - 2000 RPM - ISA -10°C (ref. Fig. 5-50) SUPPLEMENT 15 Page 88 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 15 59 52.4 414 232 233 49.5 405 229 230 46.5 394 227 228 5000 5 41 52.7 376 242 226 49.9 367 239 224 47.0 358 236 221 10000 -5 23 52.8 341 252 219 49.8 332 250 217 46.8 323 246 214 15000 -15 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 6 51.1 305 261 210 48.0 296 257 207 44.8 287 253 203 20000 -25 -12 48.5 272 269 200 45.6 264 265 196 42.5 255 260 193 23000 -31 -23 49.9 264 279 198 44.8 249 271 191 40.7 237 264 186 25000 -35 -30 49.4 254 284 194 45.2 241 277 189 40.7 228 270 184 27000 -38 -37 48.8 246 289 191 44.7 233 281 186 40.6 221 274 181 28000 -40 -41 48.7 243 291 189 44.3 229 283 184 40.8 218 277 180 29000 -42 -44 48.6 240 293 187 44.1 226 286 182 40.7 215 280 179 31000 -46 -52 49.0 236 299 184 44.0 220 290 179 40.2 208 285 176 33000 -50 -59 48.6 230 303 180 44.1 216 296 176 39.9 202 290 172 35000 -54 -66 47.4 222 304 175 43.9 210 300 172 39.6 196 292 168 37000 -57 -70 46.8 217 309 170 43.0 204 303 167 39.7 193 299 164 39000 -57 -70 46.0 212 313 165 42.7 201 309 162 39.1 188 304 159 41000 -57 -70 - - - - - 185 309 155 - - - 38.6 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 43. Maximum Range Power - 2000 RPM - ISA (ref. Fig. 5-51) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 89 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA +10°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 25 77 49.9 408 229 227 46.9 397 227 224 42.9 383 222 220 5000 15 59 50.0 370 239 220 47.3 361 236 217 44.3 351 233 214 10000 5 41 51.3 340 252 215 47.3 327 247 210 43.3 315 241 206 15000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS -5 24 51.2 309 264 208 48.0 299 260 205 43.9 287 254 200 20000 -15 6 48.6 276 272 198 45.6 267 267 195 42.5 257 263 191 23000 -21 -5 50.1 268 283 196 44.9 252 274 190 40.7 239 266 184 25000 -25 -12 50.6 261 290 194 45.4 245 280 188 40.2 229 271 181 27000 -28 -19 49.3 251 293 190 45.9 240 288 186 41.4 226 279 181 28000 -30 -23 49.0 247 295 188 45.7 236 290 185 41.3 223 282 179 29000 -32 -26 49.6 246 299 187 45.1 232 292 183 41.2 220 285 178 31000 -36 -34 50.0 242 305 184 45.2 227 298 180 40.6 212 290 174 33000 -40 -41 49.6 236 309 180 45.0 221 302 175 40.5 207 295 171 35000 -44 -48 48.7 230 312 175 44.8 216 307 172 40.6 202 300 168 37000 -47 -52 47.8 223 316 170 44.0 210 310 167 40.2 197 304 163 39000 -47 -52 - - - - 43.8 207 317 163 40.1 194 311 160 41000 - - - - - - - - - - - - - - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 44. Maximum Range Power - 2000 RPM - ISA +10°C (ref. Fig. 5-52) SUPPLEMENT 15 Page 90 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA +20°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 35 95 47.2 403 226 220 44.3 391 224 218 40.4 376 219 213 5000 25 77 47.6 366 236 213 44.6 355 233 210 41.7 345 230 208 10000 15 59 49.8 339 251 210 45.5 325 245 205 41.5 311 239 200 15000 5 42 50.4 311 264 205 46.5 298 258 200 42.3 285 252 195 20000 -5 24 48.7 280 275 196 45.1 268 268 192 41.9 259 264 188 23000 -11 13 50.7 273 287 195 45.0 256 277 188 40.7 242 269 183 25000 -15 6 50.5 264 293 192 46.0 250 285 187 40.6 233 275 180 27000 -18 -1 50.1 257 298 189 46.2 245 292 185 41.4 230 282 179 28000 -20 -5 50.3 254 302 188 45.9 240 294 183 41.8 227 286 178 29000 -22 -8 50.4 251 304 187 45.8 237 297 182 41.5 223 289 177 31000 -26 -16 50.6 247 310 183 46.0 232 304 179 41.1 216 294 173 33000 -30 -23 50.5 242 315 180 45.8 226 308 175 41.1 211 300 171 35000 -34 -30 49.6 235 318 175 45.8 222 313 172 41.5 208 306 168 37000 -37 -34 46.5 221 311 164 45.1 216 317 167 41.3 203 311 164 39000 -37 -34 - - - - - - - - 39.2 193 308 155 41000 - - - - - - - - - - - - - LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 45. Maximum Range Power - 2000 RPM - ISA +20°C (ref. Fig. 5-53) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 91 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA +30°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 45 113 46.5 405 227 217 42.5 389 222 212 38.7 374 218 208 5000 35 95 47.0 369 237 210 43.0 354 232 206 39.1 339 226 201 10000 25 77 48.9 342 251 207 43.9 324 244 201 39.9 310 238 196 15000 15 60 49.8 314 265 202 45.7 300 259 197 41.6 287 253 192 20000 5 42 48.7 285 277 194 45.3 274 272 190 41.7 262 265 186 23000 -1 31 52.0 282 294 196 45.5 262 281 187 40.6 246 271 181 25000 -5 24 52.3 275 301 194 46.6 257 289 186 40.4 237 277 178 27000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS -8 17 52.2 267 308 192 47.2 252 298 185 41.8 235 286 178 28000 -10 13 52.0 263 311 190 47.5 249 302 185 42.5 234 292 178 29000 -12 10 52.2 261 313 188 46.9 244 304 182 42.8 231 296 178 31000 -16 2 52.7 256 320 186 47.1 239 310 180 42.2 223 301 174 33000 -20 -5 48.1 236 307 171 47.5 234 317 177 42.4 218 308 172 35000 -24 -12 - - - - 43.7 217 305 164 42.8 214 315 169 37000 -27 -16 - - - - - - - - 38.0 194 294 151 39000 - - - - - - - - - - - - - - 41000 - - - - - - - - - - - - - - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 46. Maximum Range Power - 2000 RPM - ISA +30°C (ref. Fig. 5-54) SUPPLEMENT 15 Page 92 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 1800 RPM ISA -30°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -15 5 69.4 435 239 254 66.1 427 237 252 62.8 419 235 250 -25 -13 66.8 386 244 242 63.5 378 242 240 60.2 370 240 238 10000 -35 -31 62.2 338 248 229 59.1 331 246 227 56.1 323 243 224 15000 -45 -48 57.5 295 252 216 55.4 290 251 215 52.3 283 248 212 20000 -55 -66 53.2 260 258 204 50.4 253 255 202 47.5 245 251 198 23000 -61 -77 53.0 247 264 200 48.3 235 258 194 45.2 227 254 191 25000 -65 -84 52.4 237 268 196 48.1 226 262 191 43.4 214 255 186 27000 -68 -91 51.0 226 270 191 48.0 219 267 189 43.8 208 260 184 28000 -70 -95 50.3 222 270 188 47.2 213 267 186 43.5 204 262 182 29000 -72 -98 50.2 219 271 186 46.3 208 268 183 42.8 199 263 180 31000 -76 -106 49.0 210 270 178 45.8 201 270 179 41.9 191 266 176 5000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 33000 -80 -113 48.6 205 271 173 44.4 193 268 171 41.0 183 267 170 35000 -84 -120 47.7 199 270 167 43.6 187 267 165 40.1 176 266 164 37000 -87 -124 48.0 197 276 163 43.5 183 270 160 39.5 171 267 158 39000 -87 -124 48.5 197 282 160 43.8 182 276 156 39.3 168 270 152 41000 -87 -124 50.5 203 298 161 44.5 183 284 153 39.9 168 277 149 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 47. Maximum Range Power - 1800 RPM - ISA -30°C (ref. Fig. 5-55) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 93 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 1800 RPM ISA -20°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -5 23 67.1 431 239 249 63.7 422 237 247 60.3 413 235 245 5000 -15 5 64.7 383 244 237 60.4 372 240 234 57.0 363 238 231 10000 -25 -13 61.7 339 250 226 58.5 331 247 223 55.1 323 244 221 15000 -35 -30 57.8 298 256 214 55.6 293 254 213 52.4 285 251 210 20000 -45 -48 52.8 261 260 201 50.7 256 258 200 47.6 248 254 197 23000 -51 -59 54.2 252 270 199 48.5 238 261 193 45.3 229 257 190 25000 -55 -66 53.1 241 273 195 49.2 231 268 191 43.6 217 258 184 27000 -58 -73 52.4 233 277 191 48.6 223 271 188 43.8 210 263 182 28000 -60 -77 51.7 228 278 189 47.8 218 272 185 44.1 208 267 181 29000 -62 -80 50.9 224 276 185 47.7 215 275 184 43.3 203 267 178 31000 -66 -88 50.4 217 277 179 46.4 206 275 177 42.5 195 271 175 33000 -70 -95 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 49.6 211 277 173 45.6 199 274 171 41.3 187 271 169 35000 -74 -102 48.8 205 277 166 44.7 193 274 164 41.1 182 273 164 37000 -77 -106 49.2 204 282 163 44.4 189 276 159 40.7 178 274 158 39000 -77 -106 50.2 205 292 161 45.0 189 283 156 40.6 175 278 153 41000 -77 -106 51.8 210 306 161 45.9 190 293 154 40.7 173 283 148 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 48. Maximum Range Power - 1800 RPM - ISA -20°C (ref. Fig. 5-56) SUPPLEMENT 15 Page 94 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 1800 RPM ISA -10°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 5 41 61.8 416 234 239 58.3 406 231 237 53.8 393 228 233 5000 -5 23 62.9 380 244 233 59.4 371 241 230 55.8 361 239 228 10000 -15 5 60.8 340 251 223 57.5 331 248 220 53.2 320 244 216 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 15000 -25 -12 57.0 299 257 211 54.0 291 254 208 50.8 283 250 205 20000 -35 -30 53.0 264 263 200 50.8 258 261 198 47.7 250 257 195 23000 -41 -41 54.3 255 273 197 49.0 241 265 191 45.4 232 260 188 25000 -45 -48 53.7 245 277 194 49.8 235 272 190 44.5 221 264 184 27000 -48 -55 52.8 237 281 190 49.1 227 276 186 44.3 214 268 181 28000 -50 -59 52.3 233 282 187 49.1 224 279 185 44.4 211 271 180 29000 -52 -62 52.2 230 283 185 48.3 219 280 183 44.6 209 275 179 31000 -56 -70 51.0 222 282 178 47.2 211 281 177 43.6 201 278 175 33000 -60 -77 50.4 216 283 172 46.7 205 281 171 42.3 192 278 169 35000 -64 -84 50.2 212 285 167 46.1 200 282 165 41.5 186 277 162 37000 -67 -88 50.2 209 289 162 45.4 194 283 159 41.5 182 280 158 39000 -67 -88 51.2 211 298 160 45.9 194 289 155 41.3 179 284 152 41000 -67 -88 - - - 195 298 153 41.4 178 289 148 - 46.6 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 49. Maximum Range Power - 1800 RPM - ISA -10°C (ref. Fig. 5-57) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 95 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 1800 RPM ISA 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 15 59 56.9 403 228 230 53.1 391 226 227 49.7 381 224 225 5000 5 41 59.0 371 240 225 55.3 361 237 222 51.6 350 234 219 10000 -5 23 59.1 338 251 218 55.7 328 248 215 52.2 319 244 212 15000 -15 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 6 57.4 303 261 210 54.1 295 257 207 50.8 286 253 203 20000 -25 -12 53.2 267 267 198 50.0 259 262 195 47.7 253 260 193 23000 -31 -23 54.8 260 277 196 48.9 244 268 189 44.6 232 261 184 25000 -35 -30 54.3 250 281 192 49.5 237 274 187 44.4 223 266 182 27000 -38 -37 53.4 242 285 189 49.7 231 280 185 44.8 218 272 180 28000 -40 -41 53.3 239 288 187 49.4 228 283 184 44.7 215 275 178 29000 -42 -44 52.8 235 288 184 49.0 224 285 182 44.6 211 277 177 31000 -46 -52 51.7 227 287 177 47.7 215 285 175 44.0 204 282 174 33000 -50 -59 51.1 221 287 171 47.4 210 286 170 43.3 198 284 169 35000 -54 -66 51.0 217 290 166 46.6 203 286 164 42.4 191 283 162 37000 -57 -70 50.6 213 292 161 46.2 199 288 158 41.8 185 284 156 39000 -57 -70 51.7 215 302 158 46.6 199 294 154 41.8 183 288 151 41000 -57 -70 - - - - - 183 294 147 - - - 42.2 Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 50. Maximum Range Power - 1800 RPM - ISA (ref. Fig. 5-58) SUPPLEMENT 15 Page 96 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 1800 RPM ISA +10°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 25 77 54.1 396 226 223 50.3 384 223 221 45.8 369 219 217 5000 15 59 55.3 364 236 217 51.5 352 233 214 47.7 340 230 211 10000 5 41 57.3 336 250 213 53.0 324 245 209 48.3 310 239 204 15000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS -5 24 56.5 304 261 206 53.2 295 258 203 49.1 284 252 199 20000 -15 6 53.3 271 269 196 50.1 262 265 193 47.0 254 261 190 23000 -21 -5 55.3 264 281 195 49.3 248 272 188 45.1 236 265 184 25000 -25 -12 55.6 257 288 193 50.0 241 278 186 44.0 225 268 179 27000 -28 -19 54.6 248 292 189 50.1 236 285 184 45.6 223 277 179 28000 -30 -23 54.2 245 293 187 49.8 232 287 182 45.5 220 280 178 29000 -32 -26 53.5 240 293 183 49.3 228 289 180 45.2 216 282 176 31000 -36 -34 53.0 234 293 177 48.9 221 292 176 44.9 210 288 173 33000 -40 -41 52.0 227 293 170 47.8 214 290 169 43.7 202 288 167 35000 -44 -48 51.6 222 294 165 47.6 209 292 164 43.2 196 289 162 37000 -47 -52 51.9 220 300 161 47.3 205 295 158 42.7 191 290 156 39000 -47 -52 - - - - 46.5 201 296 151 43.0 189 296 151 41000 - - - - - - - - - - - - - - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 51. Maximum Range Power - 1800 RPM - ISA +10°C (ref. Fig. 5-59) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 97 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 1800 RPM ISA +20°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 35 95 50.5 388 222 215 46.7 375 219 213 43.0 361 216 210 5000 25 77 52.7 359 233 210 48.8 347 230 207 44.9 334 226 204 10000 15 59 54.7 333 247 207 50.1 319 241 202 45.7 305 236 197 15000 5 42 55.0 304 260 202 51.6 294 256 198 48.0 284 252 195 20000 -5 24 52.2 272 269 192 49.2 263 265 189 46.1 254 261 186 23000 -11 13 55.7 269 285 193 48.9 250 273 185 44.9 239 267 181 25000 -15 6 56.1 262 292 192 50.6 247 283 185 44.1 228 271 177 27000 -18 -1 55.4 254 297 188 50.7 241 289 183 45.6 226 280 177 28000 -20 -5 54.8 250 298 186 50.7 238 292 182 45.9 224 284 177 29000 -22 -8 54.3 246 297 182 50.1 233 294 180 46.2 222 288 176 31000 -26 -16 54.1 240 299 177 49.5 226 296 175 45.5 214 292 173 33000 -30 -23 53.2 233 299 170 49.0 220 297 169 44.7 207 295 168 35000 -34 -30 53.0 229 302 165 48.2 214 297 163 44.0 201 295 161 37000 -37 -34 48.3 211 285 149 48.5 211 302 159 43.7 196 297 156 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS 39000 - - - - - - - - - - - - - - 41000 - - - - - - - - - - - - - - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 52. Maximum Range Power - 1800 RPM - ISA +20°C (ref. Fig. 5-60) SUPPLEMENT 15 Page 98 of 112 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 1800 RPM ISA +30°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 45 113 49.8 391 222 212 45.0 374 217 208 41.1 358 214 205 5000 35 95 50.9 358 231 205 46.3 342 226 201 42.3 328 223 198 10000 25 77 53.8 335 247 203 48.5 318 240 197 43.7 303 234 192 15000 15 60 55.1 310 263 200 50.7 296 256 195 45.5 281 248 189 20000 5 42 52.9 279 273 192 49.5 269 268 188 45.7 258 262 184 23000 -1 31 57.0 278 291 194 49.4 256 277 184 44.2 241 268 178 25000 -5 24 57.1 270 297 191 51.1 253 287 185 43.9 232 273 175 27000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS -8 17 57.3 264 305 190 52.2 249 296 184 45.9 231 284 176 28000 -10 13 56.3 258 305 187 52.2 246 299 183 46.4 230 288 176 29000 -12 10 56.2 255 306 184 51.5 241 301 181 46.7 228 292 175 31000 -16 2 55.7 248 307 178 50.8 234 303 175 46.4 221 298 173 33000 -20 -5 50.7 229 291 162 50.5 227 305 170 45.9 214 302 168 31000 -24 -12 - - - - 46.0 210 289 155 45.5 208 303 163 37000 - - - - - - - - - - - - - - 39000 - - - - - - - - - - - - - - 41000 - - - - - - - - - - - - - - Note 1: Natural Laminar Flow Degradation is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque will decrease. In order to maintain maximum range configuration do not reset power to original setting. Fuel flow will remain about the same, but true airspeed may decrease approximately 6 knots. Figure 53. Maximum Range Power - 1800 RPM - ISA +30°C (ref. Fig. 5-61) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 99 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 54. Balked Landing Climb Torque - Flaps DOWN, Landing Gear Extended (Equivalent to Fig. 5-67 of the basic AFM) SUPPLEMENT 15 Appr. DOA EASA.21J.685 Page 100 of 112 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 55. Balked Landing Rate of Climb - Flaps DOWN, Landing Gear Extended (For lower weights refer to Fig. 5-68 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 101 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 56. Landing Distance over 50 feet without Propeller Reversing - Flaps DN (For lower weights refer to Fig. 5-69 of the basic AFM) SUPPLEMENT 15 Appr. DOA EASA.21J.685 Page 102 of 112 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 57. Landing Distance over 50 feet with Propeller Reversing - Flaps DN (For lower weights refer to Fig. 5-70 of the basic ) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 103 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 58. Balked Landing Climb Torque - Flaps MID, Landing Gear Extended (Equivalent to Fig. 5-71 of the basic AFM) SUPPLEMENT 15 Appr. DOA EASA.21J.685 Page 104 of 112 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 59. Balked Landing Rate of Climb - Flaps MID (For lower limits refer to Fig. 7-72 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 105 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 60. Landing Distance over 50 feet without Propeller Reversing - Flaps MID (For lower weights refer to Fig. 5-73 of the basic AFM) SUPPLEMENT 15 Appr. DOA EASA.21J.685 Page 106 of 112 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 61. Landing Distance over 50 feet with Propeller Reversing - Flaps MID (For lower weights refer to Fig. 5-74 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 107 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 5.5 ADDITIONAL PERFORMANCE FOR CATEGORY II OPERATIONS Category II Operations Performance data provided by Section 5 of the basic Airplane Flight Manual are integrated, for Maximum Landing Weight higher than 10945 lbs (4965 kg), by the following additional corrections that have to be considered when CAT II approaches are conducted: a. "Landing Weight in Single Engine Go Around" data, as per Figure 5-75, are integrated by Figure 62; b. "Landing Distance over 50 feet without Propeller Reversing (Flaps Down)" data, as per Figure 56 of this Supplement, must be increased by approximately 8%; c. Landing Distance in icing conditions, with Flap MID and without Propeller Reversing, as per Figure 60 of this Supplement, must be increased approximately 10%. NOTE The EASA not approved Figure 57 of this Supplement provides the "Landing Distance over 50 feet with Propeller Reversing (Flaps Down)" which has to be increased by approximately 9%. SUPPLEMENT 15 Appr. DOA EASA.21J.685 Page 108 of 112 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 62. Landing Weight - Single Engine Go Around (For lower weights refer to Fig. 5-75 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 1105-2999 PT6A-66 eng. SUPPLEMENT 15 Page 109 of 112 .A P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 INTENTIONALLY LEFT BLANK SUPPLEMENT 15 Appr. DOA EASA.21J.685 Page 110 of 112 1105-2999 PT6A-66 eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 SECTION 5 - PERFORMANCE 5.0 GENERAL List of EASA approved figures: 2, 3, 4, 5, 6, 10, 12, 13, 14, 16, 17, 21, 23, 24, 54, 56, 58, 60, 62. NOTE EASA approved figures 4, 10, 12, 14, 21, 54 and 58 are equivalent to the corresponding figures in the basic Airplane Flight Manual and are not affected by weight; these figures are included in this supplement for pilot’s convenience and in order to maintain the operative sequence. EASA approved figure 5-12 of the basic Airplane Flight Manual is no more applicable. EASA not approved figures are 5/1, 7, 8, 9, 11, 15, 18, 19, 20, 22, 25, from 26 to 53, 55, 57, 59 and 61 are included in this Supplement for pilot’s convenience and arranged in a reasonable operative sequence. Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 47 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 WEIGHT 12,100 LBS (5490 KGS) BANK ANGLE FLAPS UP FLAPS MID FLAPS DN DEG KIAS KCAS KIAS KCAS KIAS KCAS 0 114 113 106 104 99 98 10 115 114 106 105 99 99 20 118 116 109 108 102 101 30 123 121 113 112 106 105 40 130 129 120 119 113 112 50 142 141 131 130 123 122 60 161 160 149 147 139 139 ASSOCIATED CONDITIONS: IDLE POWER - FORWARD C.G. GEAR POSITION HAS NO EFFECT ON STALLING SPEEDS. MAXIMUM ALTITUDE LOSS DURING STALL IS 1,000 FT. WEIGHT 11,551 LBS (5240 KGS) BANK ANGLE FLAPS UP FLAPS MID FLAPS DN DEG KIAS KCAS KIAS KCAS KIAS KCAS 0 112 110 104 102 98 96 10 113 111 105 103 99 97 20 115 114 107 105 101 100 30 120 119 111 109 105 104 40 128 126 118 116 112 110 50 139 138 129 127 122 120 60 158 156 146 144 138 136 Figure 2. Stall Speed (For lower weights refer to Fig. 5-11 of the basic AFM) SUPPLEMENT 15 Page 48 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 3. Buffet Onset Limits (This figure supersedes Fig. 5-12 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 49 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 NOTE Torque limit of 96.4% (2150 lb.ft) is the static value to be applied for takeoff in order to obtain the normal 100% (2230 lb.ft) at takeoff speed for ram effect during the takeoff run. Figure 4. Takeoff Power Torque (Equivalent to Fig. 5-14 of the basic AFM) SUPPLEMENT 15 Page 50 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 5. Maximum Takeoff Weight to achieve One Engine Inoperative Takeoff Climb Requirements - Flaps MID, Landing Gear Retracted Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 51 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 5/1. Maximum Takeoff Weight - Flaps MID (Landing Gear DOWN) SUPPLEMENT 15 Page 52 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 6. Takeoff Ground Run and Takeoff Distance over 50 feet (For lower weights refer to Fig. 5-16 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 53 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 7. Accelerate and Go Distance over 50 feet (For lower weights refer to Fig. 5-18 of the basic AFM) SUPPLEMENT 15 Page 54 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 8. Accelerate and Stop Distance (For lower weights refer to Fig. 5-19 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 55 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 9. Brake Energy and Associated Weights for Rejected Takeoff SUPPLEMENT 15 Page 56 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 10. Twin Engine Climb Torque - Flaps MID (Equivalent to Fig. 5-21 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 57 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 11. Twin Engine Gradient of Climb - Flaps MID (For lower weights refer to Fig. 5-23 of the basic AFM) SUPPLEMENT 15 Page 58 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 NOTE This graph is also applicable for CAT II - One Engine Inoperative Go-Around, flown at 125 KIAS, for any weight from 10945 lbs (4965 kg) to 11500 lbs (5216 kg). Figure 12. One Engine Inoperative Takeoff Climb Torque (Equivalent to Fig. 5-23/1 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 59 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 13. One Engine Inoperative Takeoff Climb (For lower weights refer to Fig. 5-23/2 of the basic AFM) SUPPLEMENT 15 Page 60 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 14. Twin Engine En-Route Climb Torque (Equivalent to Fig. 5-24 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 61 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 15. Twin Engine Climb Fuel Flow - Flaps Retracted (Equivalent to Fig. 5-25 of the basic AFM) SUPPLEMENT 15 Page 62 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 16. Twin Engine En-Route Rate of Climb/Descent (For lower weights refer to Fig. 5-26 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 63 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 17. Twin Engine En-Route Gradient of Climb/Descent (For lower weights refer to Fig. 5-26/1 of the basic AFM) SUPPLEMENT 15 Page 64 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 18. Time to Climb (This graph supersedes Fig. 5-27 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 65 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 19. Fuel to Climb (This graph supersedes Fig. 5-28 of the basic AFM) SUPPLEMENT 15 Page 66 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 20. Distance to Climb (This graph supesedes Fig. 5-29 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 67 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 21. One Engine Inoperative En-Route Climb/Descent Torque (Equivalent to Fig. 5-30 of the basic AFM) SUPPLEMENT 15 Page 68 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 22. One Engine Inoperative En-Route Climb Fuel Flow (Equivalent to Fig. 5-31 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 69 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 23. One Engine Inoperative En-Route Rate of Climb/Descent (For lower weights refer to Fig. 5-32 of the basic AFM) SUPPLEMENT 15 Page 70 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 24. One Engine Inoperative En-Route Gradient of Climb/Descent (For lower weights refer to Fig. 5-32/1 of the basic AFM) Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 71 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 Figure 25. One Engine Inoperative Service Ceiling - Flaps Retracted (For lower weights refer to Fig. 5-33 of the basic AFM) SUPPLEMENT 15 Page 72 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA -30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 998 244 260 244 260 244 260 460 920 262 260 262 260 262 260 75.0 427 854 281 260 281 260 281 260 79.3 407 814 302 260 302 260 302 260 -66 83.2 385 770 325 260 325 260 325 260 -61 -77 86.7 379 758 340 260 340 260 340 260 25000 -65 -84 89.3 377 754 350 260 350 260 350 260 27000 -68 -91 92.3 382 764 361 260 361 260 361 260 29000 -72 -98 96.2 391 782 372 260 372 260 372 260 31000 -76 -106 97.7 395 790 380 257 380 257 380 257 33000 -80 -113 90.8 373 746 376 245 376 245 376 245 35000 -84 -120 84.3 351 702 372 234 372 234 372 234 37000 -87 -124 78.8 331 662 370 224 370 224 370 224 39000 -87 -124 74.2 315 630 370 213 370 213 370 213 41000 -87 -124 67.8 290 580 366 201 370 203 370 203 FEET °C °F % LBS/HR LBS/HR 0 -15 5 65.7 499 5000 -25 -13 70.4 10000 -35 -31 15000 -45 -48 20000 -55 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 26. Maximum Cruise Power - 2000 RPM - ISA -30°C Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 73 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA -20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1016 249 260 249 260 249 260 469 938 267 260 267 260 267 260 76.5 436 872 286 260 286 260 286 260 81.0 416 832 308 260 308 260 308 260 -48 85.1 394 788 332 260 332 260 332 260 -51 -59 88.7 389 778 348 260 348 260 348 260 25000 -55 -66 91.4 387 774 358 260 358 260 358 260 27000 -58 -73 94.5 393 786 370 260 370 260 370 260 29000 -62 -80 98.6 403 806 381 260 381 260 381 260 31000 -66 -88 100.0 407 814 389 257 389 257 389 257 33000 -70 -95 93.1 384 768 386 245 386 245 386 245 35000 -74 -102 86.5 360 720 382 234 382 234 382 234 37000 -77 -106 80.9 339 678 380 224 380 224 380 224 39000 -77 -106 72.1 306 612 372 208 377 212 380 213 41000 -77 -106 61.9 268 536 358 191 364 194 370 198 FEET °C °F % LBS/HR LBS/HR 0 -5 23 67.0 508 5000 -15 5 71.8 10000 -25 -13 15000 -35 -30 20000 -45 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 27. Maximum Cruise Power - 2000 RPM - ISA -20°C SUPPLEMENT 15 Page 74 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA -10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1032 253 260 253 260 253 260 478 956 272 260 272 260 272 260 FEET °C °F % LBS/HR LBS/HR 0 5 41 68.2 516 5000 -5 23 73.2 10000 -15 5 78.1 445 890 292 260 292 260 292 260 15000 -25 -12 82.7 425 850 315 260 315 260 315 260 20000 -35 -30 87.0 403 806 339 260 339 260 339 260 23000 -41 -41 90.7 399 798 355 260 355 260 355 260 25000 -45 -48 93.5 397 794 366 260 366 260 366 260 27000 -48 -55 96.7 403 806 378 260 378 260 378 260 29000 -52 -62 100.0 411 822 389 259 390 260 390 260 31000 -56 -70 99.9 410 820 395 254 399 257 399 257 33000 -60 -77 93.3 386 772 392 243 395 245 395 245 35000 -64 -84 85.8 357 714 386 231 391 234 391 234 37000 -67 -88 75.6 320 640 375 215 381 218 386 221 39000 -67 -88 63.8 277 554 360 196 366 199 372 203 41000 -67 -88 53.2 238 476 341 176 348 180 356 184 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 28. Maximum Cruise Power - 2000 RPM - ISA -10°C Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 75 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1048 258 260 258 260 258 260 974 277 260 277 260 277 260 FEET °C °F % LBS/HR LBS/HR 0 15 59 69.4 524 5000 5 41 74.5 487 10000 -5 23 79.6 454 908 298 260 298 260 298 260 15000 -15 6 84.3 434 868 321 260 321 260 321 260 20000 -25 -12 88.7 413 826 346 260 346 260 346 260 23000 -31 -23 92.6 409 818 363 260 363 260 363 260 25000 -35 -30 95.5 408 816 374 260 374 260 374 260 27000 -38 -37 98.8 414 828 386 260 386 260 386 260 29000 -42 -44 99.9 415 830 394 257 398 259 399 260 31000 -46 -52 95.2 396 792 393 247 398 250 402 253 33000 -50 -59 87.0 365 730 387 234 392 237 397 240 35000 -54 -66 79.2 336 672 381 221 386 225 391 228 37000 -57 -70 69.0 298 596 368 205 374 208 380 212 39000 -57 -70 57.8 258 516 350 185 357 189 364 193 41000 -57 -70 47.3 220 440 323 162 334 168 344 173 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 29. Maximum Cruise Power - 2000 RPM - ISA SUPPLEMENT 15 Page 76 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA +10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. FEET °C °F % 0 25 77 70.6 533 5000 15 59 75.9 496 TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1066 262 260 262 260 262 260 992 282 260 282 260 282 260 LBS/HR LBS/HR 10000 5 41 81.1 463 926 303 260 303 260 303 260 15000 -5 24 86.0 443 886 327 260 327 260 327 260 20000 -15 6 90.5 422 844 353 260 353 260 353 260 23000 -21 -5 94.5 419 838 370 260 370 260 370 260 25000 -25 -12 97.4 418 836 382 260 382 260 382 260 27000 -28 -19 99.4 420 840 393 258 395 260 395 260 29000 -32 -26 92.6 392 784 389 247 393 249 396 252 31000 -36 -34 84.4 361 722 382 234 387 237 391 240 33000 -40 -41 76.8 331 662 375 221 380 224 385 227 35000 -44 -48 69.4 303 606 367 208 373 211 378 215 37000 -47 -52 60.0 269 538 352 191 359 195 366 199 39000 -47 -52 49.4 230 460 326 167 337 174 346 179 41000 -47 -52 38.2 191 382 – – – – 308 151 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 30. Maximum Cruise Power - 2000 RPM - ISA +10°C Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 77 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA +20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1084 267 260 267 260 267 260 505 1010 287 260 287 260 287 260 82.5 472 944 309 260 309 260 309 260 87.6 452 904 333 260 333 260 333 260 24 92.2 432 864 360 260 360 260 360 260 13 96.3 427 854 377 260 377 260 377 260 FEET °C °F % LBS/HR LBS/HR 0 35 95 71.7 542 5000 25 77 77.2 10000 15 59 15000 5 42 20000 -5 23000 -11 25000 -15 6 96.6 418 836 385 257 388 259 390 260 27000 -18 -1 88.6 386 772 381 245 384 247 387 249 29000 -22 -8 80.8 355 710 375 232 379 235 382 237 31000 -26 -16 73.3 326 652 367 219 373 222 377 225 33000 -30 -23 66.1 297 594 358 206 364 209 370 213 35000 -34 -30 59.1 270 540 347 192 355 196 361 200 37000 -37 -34 50.3 238 476 325 171 336 177 345 182 39000 -37 -34 39.5 200 400 – – – – 310 155 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 31. Maximum Cruise Power - 2000 RPM - ISA +20°C SUPPLEMENT 15 Page 78 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM CRUISE POWER 2000 RPM ISA +30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1102 271 260 271 260 271 260 514 1028 291 260 291 260 291 260 83.9 480 960 314 260 314 260 314 260 89.1 461 922 339 260 339 260 339 260 42 93.9 439 878 367 260 367 260 367 260 -1 31 88.1 403 806 369 248 372 250 373 252 25000 -5 24 81.9 373 746 366 238 369 240 372 242 27000 -8 17 74.4 343 686 361 226 364 228 367 231 29000 -12 10 67.2 314 628 352 213 358 216 361 219 31000 -16 2 60.2 286 572 341 198 349 203 354 206 33000 -20 -5 53.5 259 518 326 182 336 188 345 193 35000 -24 -12 47.0 233 466 296 159 318 171 330 178 37000 -27 -16 38.0 201 402 – – – – 294 151 39000 – – – – – – – – – – – 41000 – – – – – – – – – – – FEET °C °F % LBS/HR LBS/HR 0 45 113 72.9 551 5000 35 95 78.4 10000 25 77 15000 15 60 20000 5 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 32. Maximum Cruise Power - 2000 RPM - ISA +30°C Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 79 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA -30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 972 244 260 244 260 244 260 453 906 262 260 262 260 262 260 83.9 419 838 281 260 281 260 281 260 88.1 399 798 302 260 302 260 302 260 -66 92.3 379 758 325 260 325 260 325 260 -61 -77 96.4 375 750 340 260 340 260 340 260 25000 -65 -84 99.7 375 750 350 260 350 260 350 260 27000 -68 -91 100.0 372 744 356 256 359 259 361 260 29000 -72 -98 100.0 370 740 362 252 365 255 369 257 31000 -76 -106 100.0 369 738 368 248 371 250 375 253 33000 -80 -113 100.0 369 738 374 244 376 245 376 245 35000 -84 -120 93.8 351 702 372 234 372 234 372 234 37000 -87 -124 87.3 331 662 370 224 370 224 370 224 39000 -87 -124 81.8 313 626 370 213 370 213 370 213 41000 -87 -124 72.8 283 566 362 199 367 202 370 203 FEET °C °F % LBS/HR LBS/HR 0 -15 5 73.6 486 5000 -25 -13 79.3 10000 -35 -31 15000 -45 -48 20000 -55 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 33. Recommended Cruise Power - 1800 RPM - ISA -30°C SUPPLEMENT 15 Page 80 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA -20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 990 249 260 249 260 249 260 461 922 267 260 267 260 267 260 85.7 428 856 286 260 286 260 286 260 90.0 408 816 308 260 308 260 308 260 -48 94.4 388 776 332 260 332 260 332 260 -51 -59 98.7 385 770 348 260 348 260 348 260 25000 -55 -66 99.9 380 760 356 258 358 260 358 260 27000 -58 -73 100.0 376 752 362 254 365 256 368 259 29000 -62 -80 100.0 374 748 368 250 371 252 375 255 31000 -66 -88 100.0 372 744 374 246 377 248 381 251 33000 -70 -95 100.0 373 746 381 242 384 244 386 245 35000 -74 -102 96.3 361 722 382 234 382 234 382 234 37000 -77 -106 87.1 330 660 375 221 380 224 380 224 39000 -77 -106 75.8 293 586 364 204 369 207 374 210 41000 -77 -106 64.8 256 512 351 187 357 190 363 193 FEET °C °F % LBS/HR LBS/HR 0 -5 23 75.0 495 5000 -15 5 80.9 10000 -25 -13 15000 -35 -30 20000 -45 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 34. Recommended Cruise Power - 1800 RPM - ISA -20°C Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 81 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA -10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1008 253 260 253 260 253 260 940 272 260 272 260 272 260 FEET °C °F % LBS/HR LBS/HR 0 5 41 76.4 504 5000 -5 23 82.5 470 10000 -15 5 87.4 437 874 292 260 292 260 292 260 15000 -25 -12 91.9 418 836 315 260 315 260 315 260 20000 -35 -30 96.5 398 796 339 260 339 260 339 260 23000 -41 -41 100.0 393 786 354 259 355 260 355 260 25000 -45 -48 100.0 384 768 361 256 364 258 366 260 27000 -48 -55 100.0 380 760 367 252 370 254 374 257 29000 -52 -62 100.0 378 756 374 248 377 250 380 253 31000 -56 -70 99.9 376 752 380 244 383 246 387 248 33000 -60 -77 95.8 361 722 380 235 384 238 388 240 35000 -64 -84 87.0 331 662 373 222 378 225 382 228 37000 -67 -88 77.0 298 596 364 208 369 211 374 214 39000 -67 -88 65.7 261 522 350 190 356 193 362 197 41000 -67 -88 55.4 227 454 332 171 340 176 347 179 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 35. Recommended Cruise Power - 1800 RPM - ISA -10°C SUPPLEMENT 15 Page 82 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1026 258 260 258 260 258 260 956 277 260 277 260 277 260 FEET °C °F % LBS/HR LBS/HR 0 15 59 77.8 513 5000 5 41 84.0 478 10000 -5 23 89.1 446 892 298 260 298 260 298 260 15000 -15 6 93.7 427 854 321 260 321 260 321 260 20000 -25 -12 98.5 407 814 346 260 346 260 346 260 23000 -31 -23 100.0 398 796 359 257 362 259 363 260 25000 -35 -30 100.0 389 778 366 253 369 256 372 258 27000 -38 -37 100.0 385 770 372 250 376 252 379 254 29000 -42 -44 100.0 382 764 379 246 382 248 386 251 31000 -46 -52 96.4 368 736 380 237 383 240 388 243 33000 -50 -59 87.3 337 674 373 225 377 228 381 230 35000 -54 -66 78.7 307 614 365 212 370 215 375 218 37000 -57 -70 69.3 275 550 354 197 360 200 366 203 39000 -57 -70 58.2 239 478 336 177 343 181 350 185 41000 -57 -70 47.9 205 410 – – 317 159 329 166 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 36. Recommended Cruise Power - 1800 RPM - ISA Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 83 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA +10°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1046 262 260 262 260 262 260 487 974 282 260 282 260 282 260 90.7 454 908 303 260 303 260 303 260 95.5 436 872 327 260 327 260 327 260 6 100.0 416 832 353 259 353 260 353 260 -21 -5 100.0 402 804 363 255 366 257 368 258 25000 -25 -12 100.0 393 786 371 251 374 254 377 256 27000 -28 -19 100.0 389 778 378 248 381 250 384 252 29000 -32 -26 95.7 372 744 377 239 381 242 385 244 31000 -36 -34 86.8 340 680 370 226 375 229 379 232 33000 -40 -41 78.3 311 622 362 213 367 216 372 219 35000 -44 -48 70.3 282 564 353 200 359 203 365 207 37000 -47 -52 61.2 252 504 339 183 347 188 353 191 39000 -47 -52 49.7 215 430 – – 320 164 331 170 41000 -47 -52 – – – – – – – – – FEET °C °F % LBS/HR LBS/HR 0 25 77 79.1 523 5000 15 59 85.5 10000 5 41 15000 -5 24 20000 -15 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 37. Recommended Cruise Power - 1800 RPM - ISA +10°C SUPPLEMENT 15 Page 84 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA +20°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1064 267 260 267 260 267 260 496 992 287 260 287 260 287 260 92.3 463 926 309 260 309 260 309 260 97.3 445 890 333 260 333 260 333 260 24 100.0 420 840 357 257 358 258 360 259 13 99.1 404 808 366 252 369 254 371 255 FEET °C °F % LBS/HR LBS/HR 0 35 95 80.4 532 5000 25 77 87.0 10000 15 59 15000 5 42 20000 -5 23000 -11 25000 -15 6 98.9 394 788 373 248 376 250 380 253 27000 -18 -1 91.6 367 734 369 237 373 239 377 242 29000 -22 -8 83.2 337 674 363 224 367 227 371 230 31000 -26 -16 75.2 308 616 354 211 360 214 365 217 33000 -30 -23 67.5 281 562 345 197 351 201 357 205 35000 -34 -30 60.2 254 508 332 183 341 188 348 192 37000 -37 -34 51.2 224 448 299 157 319 168 331 174 39000 -37 -34 – – – – – – – – – 41000 – – – – – – – – – – – Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 38. Recommended Cruise Power - 1800 RPM - ISA +20°C Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 85 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 RECOMMENDED CRUISE POWER 1800 RPM ISA +30°C PRESS. ALT. SAT ENG. FUEL TORQUE FLOW PER ENG. TOTAL FUEL FLOW AIRSPEED KNOTS 11500 LBS 10500 LBS 9500 LBS (5216 KG) (4763 KG) (4309 KG) TAS IAS TAS IAS TAS IAS 1080 271 260 271 260 271 260 505 1010 291 260 291 260 291 260 93.9 472 944 314 260 314 260 314 260 99.0 454 908 339 260 339 260 339 260 42 99.1 422 844 360 254 361 256 363 257 -1 31 90.1 381 762 357 240 360 242 363 244 25000 -5 24 83.9 353 706 354 230 358 232 361 235 27000 -8 17 76.1 323 646 347 217 351 220 356 223 29000 -12 10 68.5 296 592 338 204 344 208 349 211 31000 -16 2 61.3 269 538 325 189 334 194 341 198 33000 -20 -5 54.2 243 486 303 169 319 178 330 184 35000 -24 -12 47.1 218 436 – – 290 156 312 168 37000 -27 -16 – – – – – – – – – 39000 – – – – – – – – – – – 41000 – – – – – – – – – – – FEET °C °F % LBS/HR LBS/HR 0 45 113 81.7 540 5000 35 95 88.4 10000 25 77 15000 15 60 20000 5 23000 Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%, true airspeed 30 knots and fuel flow 10%, approximately. If original power is reset, fuel flow may increase approximately 30 LB/H/ ENGINE, and speed remains unchanged. Figure 39. Recommended Cruise Power - 1800 RPM - ISA +30°C SUPPLEMENT 15 Page 86 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA -30°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -15 5 53.5 461 226 240 51.0 452 224 238 48.4 443 222 236 -25 -13 52.7 409 234 232 50.1 399 231 229 47.4 390 229 227 10000 -35 -31 51.9 363 242 223 48.7 352 239 220 46.0 343 236 217 15000 -45 -48 50.6 327 251 215 47.5 317 247 211 44.4 307 243 208 20000 -55 -66 48.7 287 260 206 45.7 278 256 203 42.6 269 251 199 23000 -61 -77 48.4 270 266 201 44.6 259 261 197 41.2 249 256 193 25000 -65 -84 47.9 257 271 198 44.2 246 265 194 40.4 235 259 189 27000 -68 -91 47.2 249 275 195 43.6 238 269 190 40.0 227 263 186 29000 -72 -98 47.1 242 279 191 42.9 229 273 187 39.3 219 266 182 31000 -76 -106 47.1 236 284 188 42.6 222 277 183 38.5 210 270 178 33000 -80 -113 47.0 230 288 185 42.6 216 281 180 38.1 203 273 175 35000 -84 -120 45.7 220 289 179 41.8 208 283 175 37.9 196 277 171 37000 -87 -124 44.5 212 291 173 41.1 202 286 170 37.7 191 282 167 39000 -87 -124 43.5 207 295 167 40.6 197 291 165 37.6 187 288 163 41000 -87 -124 42.5 201 298 161 40.0 192 296 160 37.4 184 294 159 5000 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 40. Maximum Range Power - 2000 RPM - ISA -30°C Issued: January 10, 2006 Rev. 10: Mar. 04, 2019 Appr. DOA EASA.21J.685 SUPPLEMENT 15 1105-2999 PT6A-66B eng. Page 87 of 112 .B P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA -20°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 -5 23 54.5 470 230 240 51.6 460 228 237 48.7 449 225 235 5000 -15 5 53.7 417 238 232 50.8 407 235 229 47.9 396 233 226 10000 -25 -13 52.9 370 247 223 49.6 359 244 220 46.5 349 240 217 15000 -35 -30 51.7 334 256 215 48.4 324 252 211 45.2 313 248 208 20000 -45 -48 49.7 294 266 206 46.6 284 261 202 43.4 275 256 198 23000 -51 -59 49.5 276 273 201 45.6 265 267 197 42.1 254 262 193 25000 -55 -66 49.0 264 277 198 45.2 252 271 194 41.3 241 265 189 27000 -58 -73 48.3 255 281 195 44.7 244 275 190 40.9 233 269 186 29000 -62 -80 48.2 248 286 191 43.9 235 279 187 40.3 225 273 182 31000 -66 -88 48.3 242 291 188 43.7 228 284 183 39.6 216 277 178 33000 -70 -95 48.2 235 295 184 43.7 222 288 180 39.2 208 281 175 35000 -74 -102 46.8 226 297 179 42.9 214 290 175 39.0 202 284 171 37000 -77 -106 45.7 218 299 173 42.2 207 294 170 38.7 197 289 167 39000 -77 -106 44.7 212 303 167 41.7 202 299 165 38.6 192 296 163 41000 -77 -106 43.6 206 306 161 41.0 197 304 160 38.4 189 302 159 LBS/HR KTS KTS % LBS/HR KTS KTS % LBS/HR KTS KTS Note 1: Natural Laminar Flow Degradation effect is a speed reduction of 5%, maintaining torque as indicated in the Table. Note 2: During operation with Anti Icing Systems on, torque may decrease 20%. In order to maintain maximum range configuration reset power to original setting. Fuel flow will increase 3% approximately and speed remains unchanged. Figure 41. Maximum Range Power - 2000 RPM - ISA -20°C SUPPLEMENT 15 Page 88 of 112 .B Appr. DOA EASA.21J.685 1105-2999 PT6A-66B eng. Issued: January 10, 2006 Rev. 10 : Mar. 04, 2019 P.180 AVANTI II AIRPLANE FLIGHT MANUAL Rep. 180-MAN-0010-01100 MAXIMUM RANGE POWER 2000 RPM ISA -10°C 11500 LBS (5216 KG) PRESS. ALT. SAT 10500 LBS (4763 KG) 9500 LBS (4309 KG) ENG. FUEL AIRENG. FUEL AIRENG. FUEL AIRTOR FLOW SPEED TOR FLOW SPEED TOR FLOW SPEED QUE PER QUE PER QUE PER ENG. TAS IAS ENG. TAS IAS ENG. TAS IAS FEET °C °F % 0 5 41 55.5 478 234 240 52.2 466 231 237 49.0 454 229 234 5000 -5 23 54.7 425 243 231 51.5 413 239 228 48.3 402 236 225 10000 -15 5 53.9 378 252 223 50.4 366 248 220 47.1 355 244 216 15000 -25 -12 52.7 341 262 215 49.3 330 257 211 45.8 319 253 207 20000 -35 -30 50.8 300 272 206 47.5 291 267 202 44.2 281 262 198 23000 -41 -41 50.5 283 278 201 46.5 271 273 197 43.0 260 267 193 25000 -45 -48 50.0 270 283 198 46.2 258 277 194 42.2 247 271 189 27000 -48 -55 49.4 261 288 194 45.7 250 281 190 41.9 238 275 186 29000 -52 -62 49.3 254 292 191 45.0 241 286 187 41.3 230 279 182 31000 -56 -70 49.4 247 297 188 44.8 233 290 183 40.6 221 284 179 33000 -60 -77 49.3 241 302 184 44.8 227 295 180 40.3 213 288 175 35000 -64 -84 48.0 232 304 179 44.0 219 298 175 40.0 207 291 171 37000 -67 -88 46.8 224 306 173 43.3 213 301 170 39.8 201 297 167 39000 -67 -88 45.8 217 310 167 42.7 207 307 165 39.6 197

P.180 Avanti II/EVO Airplane Flight Manual

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