TCDS H11EU

1------+----+---+----+----+----+----+----+-_+----+--_f--------+----+----+-------ll I DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H11EU Revision 12 Airbus Helicopters AS355E AS355F AS355F1 AS355F2 AS355N AS355NP February 8, 2022 TYPE CERTIFICATE DATA SHEET No. H11EU This Data Sheet which is part of Type Certificate No. H11EU, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder. Airbus Helicopters Aeroport International Marseille Provence 13725 - Marignane - Cedex France TC Holder Record: Eurocopter France changed name to Airbus Helicopters on January 1, 2014. I. Model AS355E "TWINSTAR" (Normal Category), November 20, 1981. Engine. 2 ALLISON Model 250-C20F Installed Engine Limits. Torque Gas Generator Speed Exhaust Gas Temp. Output Shaft Speed Take-off (5 min) Maximum Continuous (two engines operative) (one engine inoperative) 380 mN (73%) 380 mN (73%) 521 mN (100%) 53519 rpm " " 810ºC 738ºC 810ºC 6196 rpm " " Engine gearbox Torque limit = 384 ft - lb (521 mN) = 100% Refer to Flight Manual AS355E for transients. Fuel. Refer to Flight Manual AS355E for approved fuels and additive specifications. Helicopter Limits. Maximum (one engine inoperative): Maximum (two engines operative): 100% (521 mN) 73% (380 mN) Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Rev. No. 12 6 3 6 4 10 6 10 6 10 10 10 10 10 12 11 500 2400 2200 2100 2000 1900 1850 1800 3.17 3.26 ◄ CENTRAGE (m) ► 3.47 3.5<1 3.2 0 3.30 3.40 3.50 1 -- . . I - I • ,_ • I I i I I -, 5000 t I I~ I' t t ♦ t tr S .·J '· • ! : • . I I I- ◄ t t. +-i-++-lr-+-iti'+~,~+-1-!',~;i"f'+-t-!1~~-t-lt-~ •,-,..~ ,!-t--!,""'"~ ,-+-!:-:!'-~ :,-+-+-T"1'"'"'ri- ~ 1 LIMITE AVANT !.., Llt,.1ITE ARRIERE ;:: I FORWARD LIMIT h REARWARD LIMIT ._ == <1 500 -t-,II--IIJ'-I-M-+-+-11--PI --II,..+-+ ll_t-.11--11,..-1--111,...._.1_+-+11_+-+ll_+-+1 ... 1.._+-+ 1_+-+11 ... 1.._.-! 11_+-+'-+-HI-+_, -oillJ I I I I I I I I I I I I I I I I I I I I I I I I I l <1ooo 125 124.8 130 ◄ CG (in) 135 ► 139.3 2 of 16 H11EU C.G. Range Longitudinal Datum. Longitudinal = 133.8 in. forward of main rotor hub center Lateral = Vertical plane passing longitudinally through main rotor hub center Maximum Weight. 4628 lb (2100 kg) Rotor Speed. Power-off maximum = 425 rpm minimum = 330 rpm Power-on = 390 = 375 to 394 rpm with both engine operating rpm with one engine inoperative Rotor Speed Warning. Aural at 360 rpm Airspeed Limits. Never exceed speed VNE Power-on: 0 - 73% torque. 150 kts at zero pressure altitude. Doors removed, 70 kts at zero pressure altitude. 73% - 78% torque. 55 kts at all altitudes. Never exceed speed VNE Power-off: 120 kt at zero pressure-altitude See Rotorcraft Flight Manual for decrease of these values with altitude and temperature. Minimum Crew. 1 pilot at 60.62 in. - Starboard seat Maximum Passenger. (5). 4 at 98.42 in. 1 at 60.62 in. Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in Left baggage compartment = 264 lb at 125.908 in Rear baggage compartment = 176 lb at 181.10 in Main cabin (on rear = 682 lb at 88.58 in (on LH forward = 330 lb at 61.02 in 3 of 16 H11EU Fuel Capacity. Front Tank Rear Tank Total 88.1 U.S. gallons 106.5 U.S. gallons Usable 87.2 U.S. gallons 105.7 U.S. gallons C.G. Range 127.55 in 151.55 in See NOTE 1 for data on unusable fuel. Empty Weight CG Range. None Leveling Means. Transmission support platform. Oil Capacity. Engine MGB TGB = 2 x 1.5 U.S. gallons at 140.5 in = 2.9 U.S. gallons at 145.2 in = 0.08 U.S. gallons at 379.5 in Rotor Blades and Control For rigging information, refer to the AS 355 Maintenance Manual. Movements. II. Model AS 355-F "TWINSTAR" (Normal Category), November 20, 1981. (Same as model AS355E except for maximum weight and dual hydraulic systems). Engine. 2 ALLISON Model 250-C20F. Installed Engine Limits. Torque Gas Generator Speed Exhaust Gas Temp. Output Shaft Speed Take-off (5 min) (two engines operative) Maximum Continuous (one engine operative) 380 mN (73%) 380 mN (73%) 521 mN (100%) 53519 rpm " " 810ºC 738ºC 810ºC 6196 rpm " " Engine gearbox torque limit = 384 ft=lb (521 mN) = 100% Refer to Flight Manual AS355F for transients. Fuel. Refer to Flight Manual AS355F for approved fuels and additive specification. Helicopter Limits. Maximum (one engine inoperative): 100% (521 mN) Maximum (two engines operative): 73% (380 mN) C.G. Range. Longitudinal 2600 2500 2400 ~ ~ ~ 2200 ., ~ ~ 2000 1900 ' l ·Y I ~ 1800 I . .- , I I I ◄ CENTRAGE [m] ► 0 3.5 4 3.30 3.40 T., 3.50 I I 1 LIMITE AVANT FORWARD LIMIT I I I I I do ◄ CG (in) t : I I I I I I I LIMITE ARRIERE REARWARD LIMIT I I I I I I I ·l ·:kl:: I °' :: I I I 1 I I I I I I I I I I I I I I I I I ► ~ 4000 4 of 16 H11EU Lateral - Right = 3.54 in Left = 6.30 in Datum. Longitudinal = 133.8 in. forward of main rotor hub center Lateral = Vertical plane passing longitudinally through main rotor hub center Maximum Weight. 5070 lb (2300 kg) Rotor Speed. Power-off maximum = 425 rpm minimum = 330 rpm Power-on = 390 = 375 to 394 rpm with both engines operating rpm with one engine inoperative Rotor Speed Warning. Aural at 360 rpm Airspeed Limits. Never exceed speed VNE Power-on: 150 kt at zero pressure altitude. Doors removed; 70 knots at zero pressure altitude. Never exceed speed VNE Power-off 120 kt at zero pressure-altitude See Rotorcraft Flight Manual for decrease of these values with altitude and temperature. Minimum Crew. 1 pilot at 60.62 in. - Starboard seat Maximum Passengers (5). 4 at 98.42 in. 1 at 60.62 in. Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in Left baggage compartment = 264 lb at 125.908 in Rear baggage compartment = 176 lb at 181.10 in Main cabin (on rear = 682 lb at 88.58 in (on LH forward = 330 lb at 61.02 in) 5 of 16 H11EU Fuel Capacity. Front Tank Rear Tank Total 88.1 U.S. gallons 106.5 U.S. gallons Usable 87.2 U.S. gallons 105.7 U.S. gallons C.G. Range 127.55 in 151.55 in See NOTE 1 for data on unusable fuel. Empty Weight CG Range. None Leveling Means. Transmission support platform. Oil Capacity. Engine MGB TGB = 2 x 1.5 U.S. gallons at 140.5 in = 2.9 U.S. gallons at 145.2 in = 0.08 U.S. gallons at 379.5 in Rotor Blades and Control For rigging information, refer to the AS 355 Maintenance Manual. Movements. III. Model AS 355-F1 "TWINSTAR" (Normal Category), April 11, 1984. Engine. 2 ALLISON Model 250-C20F Installed Engine Limits. Torque Gas Generator Speed Exhaust Gas Temp. Output Shaft Speed Take-off (5 min) Maximum Continuous (two engines operative) (one engine operative) 406 mN (78%) 380 mN (73%) 521 mN (100%) 53,519 rpm " " 810ºC 738ºC 810ºC 6,196 rpm " " Engine gearbox Torque limit = 384 ft=lb (521 mN) = 100% Refer to Flight Manual AS355F1 for transients. Fuel. Refer to Flight Manual AS355F1 for approved fuels and additive specifications. Helicopter Limits. Maximum (one engine inoperative): Maximum (two engines operative): 100% (521 mN) 78% (406 mN) ~ :::: ::: ; :· ~ -- : t: ♦ : · ::·.t:::J-: : : :: - . ,: ·: :t :: ► ·. -:.i::T .' ◄ CENTRAGE [m] ► ::. -:-1-. -:. :.:: ·· .1::'.I·> :::+·:-1:::: .. :::::, ,::::::f ::,:.;: ::: :i<;:;+<. ::: ::: ::::t::-t :i-:-1:-: :;-1·· ; . ·_: ::.J::-:•·:·;.:- :- t .<t•::r ::t :: -::t:::l:'.:1:::: ':, :-:~ +:: ::-1:: :::+:::(:•:•: t :: [ffi!] ::: =:=•:+•=:r·· .·,; -:·:-. 'J ·,, ,.., ::: ::.t.:-::-::f•: : -: ♦- - f~ f·.·I, .·. -::! ;:+.;.I ' :-:-:t;:;:t;::t,;:;; :::t'. •:J_:;f.;:: :,.•:-'.·'-· <·\'.:'. ::::•:;:;t: ·:: •:::;: I I • 1 I I I I ··1.:: ;.;+:::t:;.j:::~:: 2:300 2200 mill [iii] :'T: 7 I U DO ·.-! ; I I d . I I Ii I I I LIMITE AVANT 1 1 1 I I I FORWARD LIMIT 1--1,-1-1-+-+- --1-.-1 .. 1""!-..+l-, ""1 ....... .,_. , I I I I I 11 I l I I I I I I I I I I I ~ ◄ CG [in] ► I I I I I I I l I I I I I I I I I I I ' I I I I .Js.e 1JJ .... ~ SSIO .... ~ '.E suo 0 t'" [!fil] ~ •soo ~ mm •no 6 of 16 H11EU C.G. Range. Longitudinal Lateral - Right = 3.54 in - Left = 6.30 in Datum. Longitudinal Lateral = 133.8 in. forward of main rotor hub center = Vertical plane passing longitudinally through main rotor hub center. Maximum Weight. 5291 lb (2400 kg) Rotor Speed. Power-off maximum = 425 rpm minimum = 330 rpm Power-on = 390 = 375 to 394 rpm with both engines operating rpm with one engine inoperative Rotor Speed Warning. Aural at 360 rpm and 410 rpm. Airspeed Limits. Never exceed speed VNE Power-on: 150 kt at zero pressure altitude. Doors removed; 70 knots at zero pressure altitude. Never exceed speed VNE Power-off 120 kt at zero pressure-altitude See Rotorcraft Flight Manual for decrease of these values with altitude and temperature. Minimum Crew. 1 pilot at 60.62 in. - Starboard seat Maximum Passengers Standard(5). 4 at 98.42 in. 1 at 60.62 in. Maximum passengers of 6 is available when the aircraft is equipped with the optional two-place seat at 60.62 in. This optional item is to be used in accordance with the associated Flight Manual supplement. Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in Left baggage compartment = 264 lb at 125.908 in Rear baggage compartment = 176 lb at 181.10 in Main cabin (on rear = 682 lb at 88.58 in (on LH forward = 330 lb at 61.02 in 7 of 16 H11EU Fuel Capacity. Front Tank Rear Tank Total 88.1 U.S. gallons 106.5 U.S. gallons Usable 87.2 U.S. gallons 105.7 U.S. gallons C.G. Range 127.55 in 151.55 in See NOTE for data on unusable fuel. Empty Weight CG Range. None Leveling Means. Transmission support platform Oil Capacity. Engine MGB TGB = 2 x 1.5 U.S. gallons at 140.5 in = 2.9 U.S. gallons at 145.2 in = 0.08 U.S. gallons at 379.5 in Rotor Blades and Control For rigging information, refer to the AS 355 Maintenance Manual. Movements. IV. Model AS355F2 "TWINSTAR" (Normal Category), February 13, 1987. (Same as AS355F1 except for maximum weight, external load maximum weight, yaw compensation system, etc.) Engine. 2 ALLISON Model 250-C20F Installed Engine Limits. Torque Gas Generator Speed Exhaust Gas Temp. Output Shaft Speed Take-off (5 min) Maximum Continuous (two engines operative) (one engine operative) 406 mN (78%) 380 mN (73%) 521 mN (100%) 53,519 rpm " " 810ºC 738ºC 810ºC 6,196 rpm " " Engine gearbox Torque limit = 384 ft=lb (521 mN) = 100% Refer to Flight Manual AS355F2 for transients. Fuel. Refer to Flight Manual AS355F2 approved fuels and additive specification. Helicopter Limits. Maximum (one engine inoperative): Maximum (two engines operative): 100% (521 mN) 78% (406 mN) mm "" 2•oe ZlOI ~ 22H ~ ~ ~ 11!!] 190I 1191 J. 17 CENTRAGE [m) ► J.(5 l.U : •J. ·:r · ·: • ·-•p.·. _j :_. fJ::J.:· :::: .) ::: :• LIMITE AVANT FORWARD LIMIT I ~ '" ◄ I I I I I I I I I I I LIMITE ARRIERE REARWARD LIMIT I I I I I ).· ·,··"'. •·•:•···-"·• .·.,·.- .·. \.:i :f ::F ::J ::· d :::f:: I I r"l· :::f:': :;,:::::: ~xv :::i::: ::: I I\ :::1:::i,:: I I I I : I I I! I I I I I•~ ~ "' CG [in) ► 115.B .rs;, -"'' :;s C !2 @!I g "" ~ .s 400I 2501 8 of 16 H11EU C.G. Range. Longitudinal Lateral - Right - Left = 3.54 in = 6.30 in Datum. Longitudinal Lateral = 133.8 in. forward of main rotor hub center = Vertical plane passing longitudinally through main rotor hub center Maximum Weight. 5600 lb (2540 Kg) Rotor Speed. Power-off maximum = 425 rpm minimum = 330 rpm Power-on = 390 = 375 to 394 rpm with both engines operating rpm with one engine inoperative Rotor Speed Warning. Aural at 360 rpm and 410 rpm. Airspeed Limits. Never exceed speed VNE Power-on: 150 kt zero pressure altitude. Doors open or removed: 70 knots at zero pressure altitude. Never exceed speed VNE Power-off 120 kt at zero pressure-altitude See Rotorcraft Flight Manual for decrease of these values with altitude and temperature. Minimum Crew. 1 pilot at 60.62 in. - Starboard seat Maximum Passengers Standard (5). 4 at 98.42 in. 1 at 60.62 in. Maximum passengers of 6 is available when the aircraft is equipped with the optional two-place seat at 60.62 in. This optional item is to be used in accordance with the associated Flight Manual supplement. Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in Left baggage compartment = 264 lb at 125.908 in Rear baggage compartment = 176 lb at 181.10 in Main cabin (on rear = 682 lb at 88.58 in (on LH forward = 330 lb at 61.02 in 9 of 16 H11EU Fuel Capacity. Front Tank Rear Tank Total 88.1 U.S. gallons 106.5 U.S. gallons Usable 87.2 U.S. gallons 105.7 U.S. gallons C.G. Range 127.55 in 151.55 in See NOTE for data on unusable fuel. Empty Weight CG Range. None Leveling Means. Transmission support platform Oil Capacity. Engine MGB TGB = 2 x 1.5 U.S. gallons at 140.5 in = 2.9 U.S. gallons at 145.2 in = 0.08 U.S. gallons at 379.5 in Rotor Blade and Control For rigging information, refer to the AS355 Maintenance Manual. Movements. V. Model AS355N "Twinstar" (Normal Category), October 15, 1992. The major difference between the AS355N and AS355F series is the replacement of the Allison C250 engines with Turbomeca Arrius 1 A engines. Engine. 2 Turbomeca model Arrius 1 A controlled by a digital electronic control units. Installed Engine Limits. Torque Gas Generator Speed Exhaust Gas Temp. Output Shaft Speed Take-off (5 min) Maximum Continuous two engines operative Maximum continuous one engine operative 30 mn. one engine inoperative 2 mn. 30s one engine inoperative 406 mN (78%)* 380 mN (73%)* 521 mN (100%)* 599 mN (115%) * 683 mN (131%) 54,685 rpm 53,285 rpm 53,285 rpm 55,300 rpm 56,140 rpm 800ºC 765ºC 765ºC 800ºC 870ºC 6,256 rpm 6,256 rpm 6,256 rpm 6,256 rpm 6,256 rpm * Torque limits of helicopter main gearbox Engine gearbox torque limit = 521 mN (100% torque) refer to Flight Manual AS355N for transients. Fuel. Refer to Flight Manual AS355N for approved fuels and additive specifications. Helicopter Limits. One engine inoperative: Maximum continuous torque: 100% (521 mN) 30 mn. torque: 115% (599mN). 2mn 30s. torque: 131% (683 mN). Two engines operative: IAS < 55 Kts.: 78% (406 mN). IAS > 55 Kts.: 73% (380 mN). (m) l .11 l.25 3.45 3.§4 121 3.30 HO l.50 2600 Gill 2508 " / '- mm 5500 2400 oil 2180 g '" 2208 1§ 8 ~ ~ / '\.. I "' I REARWARD LIMIT ➔ ' J "' I.I ' "' I f- 'I 7 FORWARD LIMIT I :a 0 5000 ~ mm f 4500 (Eill 1'111 1800 .... 125 J]O 1l5 T2U IZ7.9 CG (in) 135.8 IU.3 CENTERING 10 of 16 H11EU C.G. Range. Longitudinal Lateral - Right - Left = 0.09 m (3.54 in) = 0.16 m (6.30 in) Datum. Longitudinal = 3.40 m (133.8 in. forward of main rotor hub center) Lateral = Vertical plane passing longitudinally through main rotor hub center. Maximum Weight. 5732 lb (2600 kg) Rotor Speed Limitations. Power-on flight - two engines in operation: 390 (+ 4, -5) rpm For IAS below 55 kt: 390 (+ 10, -5) rpm - OEI : 375 to 394 rpm Power-off flight - max. 425 rpm (aural warning at 410 rpm) - min. 330 rpm (aural warning at 360 rpm) Airspeed Limits. Never exceed speed VNE Power-on: 150 kt zero pressure altitude. Doors removed: see the flight manual (section 2.1, § 5.2.) Never exceed speed VNE Power-off: 120 kt at zero pressure-altitude. See Rotorcraft Flight Manual for decrease of these values with altitude and temperature. Minimum Crew. 1 pilot at 60.62 in. - Starboard seat. Maximum Passenger Standard (5). Maximum Baggage. 4 at 98.42 in. 1 at 60.62 in. Maximum passengers of 6 is available when the aircraft is equipped with the optional two-place seat at 60.62 in. This optional item is to be used in accordance with the associated Flight Manual supplement. Right baggage compartment = 220 lb at 125.98 in Left baggage compartment = 264 lb at 125.908 in Rear baggage compartment = 176 lb at 181.10 in Main cabin (on rear = 682 lb at 88.58 in (on LH forward = 330 lb at 61.02 in 11 of 16 H11EU Fuel Capacity. Front Tank Rear Tank Total 88.1 U.S. gallons 106.5 U.S. gallons Usable 87.2 U.S. gallons 105.7 U.S. gallons C.G. Range 127.55 in 151.55 in See NOTE 1 for data on unusable fuel. Empty Weight CG Range. None Leveling Means. Transmission support platform. Oil Capacity. Engine MGB TGN = 2 x 1.5 U.S. gallons at 140.5 in = 2.9 U.S. gallons at 145.2 in = 0.08 U.S. gallons at 379.5 in Rotor Blade and Control For rigging information, refer to the AS 355 Maintenance Manual. Movements. VI. Model AS355NP "Twinstar" (Normal Category), January 9, 2008. The major difference between the AS355NP and AS355N is the replacement of the Turbomeca Arrius 1A engines with Turbomeca Arrius 1A1 engines, addition of New engine monitoring system: VEMD (Vehicule and Engine Multifunction Display), electric oil cooling fan and upgraded main gear box. Engine. 2 Turbomeca model Arrius 1A1 controlled by a digital electronic control units. Installed Engine Limits. Torque Gas Generator Speed Exhaust Gas Temp. Output Shaft Speed Take-off (5 min) Maximum Continuous two engines operative Maximum continuous one engine operative 2 mn. 30s one engine inoperative 450 mN (86.4%)* 374 mN (71.8%)* 599 mN (115%)* 683 mN (131%) 54,375 rpm 53,285 rpm 55,452 rpm 56,347 rpm 773ºC 749ºC 812ºC 885ºC 6,016 rpm 6,016 rpm 6,016 rpm 6,016 rpm * Torque limits of helicopter main gearbox Engine gearbox torque limit = 521 mN (100% torque) refer to Flight Manual AS355NP for transients. Fuel. Refer to Flight Manual AS355NP for approved fuels and additive specifications. Helicopter Limits. One engine inoperative: Maximum continuous torque: 2mn 30s. torque: 115% (599 mN) 131% (683 mN). Two engines operative: IAS < 55 Kts.: IAS > 55 Kts.: 86.4% (450 mN). 71.8% (374 mN). 5732 1 18 0 0 ::;'t::D;;:::::=:=:::::::;:=::~;:::::;::::::~:::::::::;::::::;;:::=:::;::::::;:::::::::;:::;::::;:::::::=::::::;::::::::::;::;: - 410 0 0 I I I ~ 8 130 1~35-~ [g!]] 1128 .3 ◄ CG ( in ) ► 135.4 139.3 1 12 of 16 H11EU C.G. Range. Longitudinal Lateral - Right - Left - Left = 0.09 m (3.54 in) = 0.09 m (3.54 in) = 0.16 m (6.30 in) (hoisting operation) Datum. Longitudinal = 3.40 m (133.8 in. forward of main rotor hub center) Lateral = Vertical plane passing longitudinally through main rotor hub center. Maximum Weight. 5732 lb (2600 kg) Rotor Speed Limitations. Power-on flight - two engines in operation 375-394 rpm For IAS below 55 kt: 390 (+ 10, -5) rpm - OEI : 375 to 394 rpm Power-off flight - max. 425 rpm (aural warning at 410 rpm) - min. 330 rpm (aural warning at 360 rpm) Maximum Rotor Brake Application: 170 rpm Airspeed Limits. Never exceed speed VNE Power-on: 150 kt zero pressure altitude. Doors removed: see the flight manual (section 2, § 2.3) Never exceed speed VNE Power-off: 120 kt at zero pressure-altitude. See Rotorcraft Flight Manual for decrease of these values with altitude and temperature. Minimum Crew. 1 pilot at 60.62 in. - Starboard seat. Maximum Passenger Standard(5). 4 at 98.42 in. 1 at 60.62 in. 13 of 16 H11EU Maximum passengers of 6 is available when the aircraft is equipped with the optional two-place seat at 60.62 in. This optional item is to be used in accordance with the associated Flight Manual supplement. Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in Left baggage compartment = 264 lb at 125.908 in Rear baggage compartment = 176 lb at 181.10 in Main cabin (on rear = 682 lb at 88.58 in (on LH forward = 330 lb at 61.02 in Fuel Capacity. Front Tank Rear Tank Total 88.1 U.S. gallons 106.5 U.S. gallons Usable 87.2 U.S. gallons 105.7 U.S. gallons C.G. Range 127.55 in 151.55 in See NOTE 1 for data on unusable fuel. Empty Weight CG Range. None Leveling Means. Transmission support platform. Oil Capacity. Engine MGB TGN = 2 x 1.5 U.S. gallons at 140.5 in = 2.9 U.S. gallons at 145.2 in = 0.08 U.S. gallons at 379.5 in Rotor Blade and Control Movements. For rigging information, refer to the AS 355 Maintenance Manual. Certification Basis. AS355E AS355F, AS355F1, AS355F2 FAR 21.29 and FAR 27 effective February 1, 1965 plus Amendments 27-1 through 27-16. Type Certificate No. H11EU, issued January 19, 1981. Amended November 20, 1981 to add Model AS355F. Amended April 11, 1984 to add Model AS355F1. Amended February 13, 1987 to add Model AS355F2. Date of Application for Type Certificate: January 4, 1979. AS 355 N version: - The basic certification basis consists of FAR 21.29 and FAR 27 effective February 1, 1965, including amendments 27.1 through 27.20, plus - The following sections of amendment 27.21: 27.21, 27.45, 27.71, 27.79, 27.143, 27.151, 27.161, 27.173, 27.175, 27.177, 27.672, 27.673, 27.729, 27.735, 27.779, 27.807, 27.1329, 27.1413, 27.1519, 27.1525, 27.1555, 27.1585 and 27.1587. DGAC special conditions notified in letter DGAC No. 54408 dated October 21, 1988 are: A - Limit Pilot Forces B - Engine air intake protection against birds (2 lbs) and hail ingestion C - Engine governing system The FADEC has been HIRF tested on the Arrius 1A engine with success at 200V/m according to Cat Y DO160. In this certification basis, the following sections remain at the Amendment preceding the Amendment 27.21: 27.141, 27.610, 27.785, 27.1309, 27.1505 and 27.1559. 14 of 16 H11EU The French Direction Generale de l’Aviation Civile (DGAC) originally type certificated this rotorcraft under its type certificate TC 168. The FAA validated this product under U.S. Type Certificate Number H11EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the DGAC. AS 355 NP version: - The basic certification basis consists of FAR 21.29 and FAR 27 effective February 1, 1965, including amendments 27.1 through 27.20, plus - The following sections of amendment 27.21: 27.21, 27.45, 27.71, 27.79, 27.143, 27.151, 27.161, 27.173, 27.175, 27.177, 27.672, 27.673, 27.729, 27.735, 27.779, 27.807, 27.1329, 27.1413, 27.1519, 27.1525, 27.1555, 27.1585 and 27.1587. - The following section of amendment 27.23: 27.923 DGAC special conditions notified in letter DGAC No. 54408 dated October 21, 1988 are: A - Limit Pilot Forces B - Engine air intake protection against birds (2 lbs) and hail ingestion C - Engine governing system The FADEC HIRF approval for the Arrius 1A1 was accomplished by similarity to the testing accomplished on the Arrius 1A engine installed on the AS355N helicopter. The AS355NP also complies with the following FAR 29 paragraphs: §45(a) and (b)(2) Amdnt 24; §49(a) Amdnt 39; §51 Amdnt 39; §53 Amdnt 39; §55 Amdnt 39; §59 Amdnt 44; §60 Amdnt 39; §61 Amdnt 39; §62 Amdnt 44; §64 Amdnt 39; §65(a) Amdnt 39; §67(a) Amdnt 44; §75 Amdnt 39; §77 Amdnt 44; §79 Amdnt 39; §81 Amdnt 44; §85 Amdnt 44; §87(a) Amdnt 39; §861(a) Amdnt 30; §901(c) Amdnt 26; §903(b) (c) and (e) Amdnt 36; §908(a) Amdnt 26; §917( (c)(1) Rotor drive system: Design. Amdnt 40; §953(a) Amdnt 0; §1027(a) Amdnt 26; §1045(a)(1), (b), (c), (d), and (f) Amdnt 26; §1047(a) Amdnt 26; §1181(a) Amdnt 26; §1187(e) Amdnt 0; §1189(c) Amdnt 26; §1191(a)(1) Amdnt 3; §1193(e) Amdnt 26; §1195(a) and (d) Amdnt 17; §1197 Amdnt 13; §1199 Amdnt 13; §1201 Amdnt 0; §1305 (b) Amdnt 40; §1309(b) Amdnt 14; §1323(c)(1) Amdnt 44; §1331(b) Amdnt 24; §1587(a) Amdnt 44. FAR Part 36 Noise Standards amended by Amendments 36-1 through 36-21. DATA PERTINENT TO ALL MODELS. Serial Numbers Eligible. The French Government "Certificat de Navigabilite pour Exportation" endorsed as noted below under "Import Requirements" must be submitted for each individual aircraft for which application for FAA certification is made. Type Certificate. Type Certificate No. H11EU, issued January 19, 1981. Amended November 20, 1981 to add Model AS355F. Amended April 11, 1984 to add Model AS355F1. Amended February 13, 1987 to add Model AS355F2. Amended October 15, 1992 to add Model AS355N. Date of application for amended type certificate: February 12, 1991. Amended January 9, 2008 to add Model AS355NP. Date of application for ameded type certificate: April 6, 2007. 15 of 16 H11EU Import Requirements. The FAA can issue a U.S. airworthiness certificate based on a National AviationAuthority (NAA) Export Certificate of Airworthiness (Export C of A) signed by a representative of the French Generale de l’Aviation Civile (DGAC) on behalf of the European Community. Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement,