TCDS A16NM

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. A16NM This data sheet, which is a part of Type Certificate No. A16NM prescribes conditions and limitations under which the aircraft for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder. Gulfstream Aerospace LP C/o Israel Aircraft Industries, LTD., Department 4199 Ben Gurion International Airport 70100, Israel Type Certificate Holder Record. Israel Aircraft Industries, LTD. transferred ownership of Type Certificate A16NM to Gulfstream Aerospace LP on March 26, 2002 I. Model 1125 Westwind Astra (Transport Category), Approved August 29, 1985. Engines. Two Honeywell (formerly AlliedSignal and Garrett) TFE 731-3A-200G or TFE 731-3C- 200G per FAA Type Certificate Data Sheet E6WE Fuel. Conforming to Honeywell Specifications EMS 53111 (Jet A type), EMS 53112 (Jet A-1 & JP-8 types), EMS 53113 (Jet B & JP-4 types), and EMS 53116 (JP-5 type) as per LIMITATIONS SECTION of approved Airplane Flight Manual. Oil. Conforming to Honeywell Specification EMS 53110 type 2. Engine Limits. Static thrust at sea level, LBS - Maximum continuous 3,700 - Take-off (5 minutes) 3,700 Maximum continuous permissible engine operating speeds for the engine rotors, % RPM (RPM) - Low Pressure Rotor (N1) 101.5 (21000) - High Pressure Rotor (N2) 100.0 (29692) Maximum Interstage Turbine Temperature - Maximum Continuous (ITT), ºC -3A 885 -3C 910 - Take-Off (5 minutes) 907 910 - During Starting 907 910 Maximum Oil Inlet Temperature, ºC Up to 30,000 ft Above 30,000 ft. - Fan Gearbox 127 140 - Fan Gearbox Transient (2 minutes) 149 149 - Accessory Gearbox 149 157 Oil Pressure, PSIG - Normal Operating 38 to 46 - At Idle, Minimum 25 - Maximum 55 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Rev. No. 7 7 6 6 7 7 7 7 7 7 9 7 7 7 A16NM Revision 9 Gulfstream Aerospace LP 1125 Westwind Astra Astra SPX Gulfstream 100 Gulfstream G150 October 26, 2022 Page 2 of 14 Rev 8 A16NM Airspeed Limits: Maximum bleed and power extraction: - See Honeywell Installation Manual IM-8001 - Va (Maneuvering) 280 KCAS at 37000 ft. 280 KCAS at 37000 ft. 250 KCAS at 41000 ft. * SEE NOTE 4 II. Model Astra SPX (Transport Category) Approved January 8, 1996 The Model Astra SPX is a derivative of the Model 1125 Westwind Astra. The changes include: installation of Honeywell (formerly AlliedSignal) TFE 731-40R-200G engines; installation of winglets and minor structural modifications to the wing; installation of Collins pro-line 4 avionics; and a new Airplane Flight Manual to take credit for the aerodynamic and performance improvements. III. Model Gulfstream 100 (Transport Category) Approved August 9, 2002 The Model Gulfstream 100 type design is identical to the Model Astra SPX type design except for the model designation. The only difference is the model designation (name) used on the data plate and associated manuals. The type design of the Model Gulfst ream 100 includes all of the mandatory type design changes applied to the Astra SPX as of the date of approval. IV. Model Gulfstream G150 (Transport Category) Approved November 7, 2005 The “GULFSTREAM G150” is a derivative model of the former “GULFSTREAM G100”. The changes include: - A 5.5% increase of maximum takeoff weight - A12-inch increase in the passenger cabin width -A16 inch fuselage “Plug” aft of rear pressure bulkhead - A modified cockpit and nose section with enhanced pilot accommodation and visibility - COLLINS PROLINE 21 avionics in lieu of the COLLINS PROLINE 4 - Modification of the Engine Electronic Control (EEC) to achieve an increase of up to 6% in thrust - Systems adaptations associated with the aforementioned modifications - Vmo (Max Operating) S.L. to 25000 ft. - Mmo Above 25000 ft. - Mmo with Autopilot disengaged above 22500 ft. 1125 BASIC 360 KCAS 0.85 M 0.81 M *1125 IW - Vmo (Max Operating) S.L. to 26360 ft. - Mmo Above 26360 ft. - Mmo with Autopilot disengaged above 24130 ft. - At 23500 LBS: 350 KCAS 0.85 M 0.81 M - SL to 10000 ft 233 KCAS - At 37000 ft 280 KCAS - Va varies linearly from 233 KCAS at 10000 ft to - At 24650 LBS: - SL to 10000 ft 233 KCAS - At 37000 ft 280 KCAS - Va varies linearly from 233 KCAS at 10000 ft. to - At 18000 LBS: - SL to 20000 ft 204 KCAS 204 KCAS - At 41000 ft 250 KCAS 250 KCAS - Va varies linearly from 204 KCAS at 20000 ft to - Above 41000 ft 0.85M 0.85 M - Vfe (Flaps 12º and slats 25º) 250 KCAS 250 KCAS - Vfe (Flaps 20º and slats 25º) 225 KCAS 225 KCAS - Vfe (Flaps Landing 40º and slats 25º) 180 KCAS 180 KCAS - Vsb (Airbrakes Operation) No speed Limitation - Vle and Vlo (L/G Extension and Operating Speed) 180 KCAS 180 KCAS - Vmca (Flaps 12º and 20º) 92 KCAS 92 KCAS - Vmcg (Flaps 12º and 20º) 89 KCAS 89 KCAS - Tire Limit Ground Speed: KTS (MPH) 182 (210) 182 (210) Page 3 of 14 A16NM Data Pertinent to Models Astra SPX and Gulfstream 100 Engines. Two Honeywell Engines (formerly AlliedSignal) TFE 731-40R-200G per FAA Type Certificate Data Sheet E1NM Fuel. Conforming to Honeywell Specifications EMS 53111 (Jet A type), EMS 53112 (Jet A-1 & JP-8 types), EMS 53113 (Jet B & JP-4 types), and EMS 53116 (JP-5 type) as per LIMITATIONS SECTION of approved AFM. Oil. Conforming to Honeywell Specification EMS 53110 type 2. Engine Limits. Static thrust at sea level, LBS - Maximum continuous 4,250 - Take-off (5 minutes) 4,250 Maximum continuous permissible engine operating speeds for the engine rotors, % RPM (RPM) - Low Pressure Rotor (N1) 100.0 (21000) - High Pressure Rotor (N2) 101.0 (31485) Maximum Interstage Turbine Temperature (ITT), ºC - Maximum Continuous 991 - Take-Off (5 minutes) 991 - Take-Off (5 minutes) with APR On 1013 - During Starting 991 Maximum Oil Inlet Temperature, ºC Up to 30,000 ft Above 30,000 ft. - Fan Gearbox 127 140 - Fan Gearbox Transient (2 minutes) 149 149 - Accessory Gearbox 149 157 Oil Pressure, PSIG - Normal Operating 65 to 80 - At Idle, Minimum 50 - Maximum 100 Airspeed Limits: Maximum bleed and power extraction: - See Honeywell Installation Manual IM-8010 - Vmo (Max Operating) S.L. to 27600 ft. 350 KCAS - Mmo Above 27600 ft. 0.87 M - Mmo with Autopilot disengaged and Mach Trim inoperative above 23900 ft. 0.81 M - Va (Maneuvering) - At 24650 LBS: - S.L. to 10000 ft 233 KCAS - At 37000 ft 280 KCAS - Va varies linearly from 233 KCAS at 10000 ft to 280 KCAS at 37000 ft. - At 18000 LBS: - S.L. to 20000 ft 204 KCAS - At 41000 ft 250 KCAS - Va varies linearly from 204 KCAS at 20000 ft to 250 KCAS at 41000 ft. - Above 41000 ft 0.87M - Vfe (Flaps 12º and slats 25º) 250 KCAS - Vfe (Flaps 20º and slats 25º) 225 KCAS - Vfe (Flaps Landing 40º and slats 25º) 180 KCAS - Vsb (Airbrakes Operation) No speed Limitation - Vle and Vlo (L/G Extension and Operating Speed) 180 KCAS - Vmca (Flaps 12º and 20º) 100 KCAS - Vmcg (Flaps 12º and 20º) 100 KCAS - Tire Limit Ground Speed: KTS (MPH) 182 (210) Page 4 of 14 Rev 8 A16NM Data Pertinent to all Models except Gulfstream G150 C.G. Range. Approved center of gravity range is as shown in the following tables: (Gear extension and retraction moment is negligible). 1125 BASIC *1125 IW , Astra SPX & Gulfstream 100 12,100 LBS – 39.00 % MAC 12,100 LBS – 39.00 % MAC 12,100 LBS – 36.40 % MAC 12,100 LBS – 36.40 % MAC 12,900 LBS – 19.60 % MAC 12,900 LBS – 19.60 % MAC 16,500 LBS – 19.60 % MAC 16,500 LBS – 19.60 % MAC 21,250 LBS – 25.00 % MAC 21,250 LBS – 25.00 % MAC 23,650 LBS – 30.39 % MAC 24,800 LBS – 32.97 % MAC 23,650 LBS – 39.00 % MAC 24,800 LBS – 39.00 % MAC LINEAR VARIATION BETWEEN POINTS * SEE NOTE 4 Datum. Fuselage Station 0, is located 92.78 inches forward of airstairs opening aft frame. Mean Aerodynamic Chord 86.26 inches with leading edge at Fuselage Station 233.94. (MAC). Leveling Means. Longitudinally: Place level on either seat rail at fuselage station 200 parallel to A/C centerline. Laterally: Place level on seat rails at fuselage station 200 at 90º to A/C centerline. Maximum Weight: 1125 BASIC 1125 IW, Astra SPX, & Gulfstream 100 - Ramp Gross Weight 23650 lbs 24800 lbs - Max Takeoff Weight 23500 lbs 24650 lbs - Max Landing Weight 20700 lbs 20700 lbs - Max Zero Fuel Weight 16000 lbs 17000 lbs Minimum Crew. Two (Pilot and Copilot) Maximum Passengers. Nine Maximum Baggage. Central Tank Extension (CTE) STATUS: LBS ARM (INCHES) - CTE installed (full or empty) 370 358 - CTE not installed 1100 350 Fuel Capacity. Fuel Tanks LH WING CENTER CENTER RH WING (w/o CTE) (w/ CTE) Total/Usable Fuel (LBS) 1936/1920 4857/4852 5530/5525 1936/1920 Arm (INCHES) 256.1 278.5 285.3 256.1 Unusable Fuel (LBS) 16 5 5 16 Arm (INCHES) 236.5 228.5 228.5 236.5 Density: 6.7 LBS/U.S. Gallon See Note 1 for data on Fuel System Oil Capacity. *TOTAL (LBS) *USABLE (LBS) ARM (INCHES) -3A & -3C Engines 36 8 394 -40R Engines 32 8 394 *For Both Engines Combined Density: 8.2 LBS/U.S. Gallon See Note 1 for Data on Oil System) Page 5 of 14 A16NM Maximum Operating Altitude. 45,000 ft. Other Operating Limitations. Aircraft shall be operated according to operating limitations specified in approved airplane flight manual. (See notes 4 and 6.) Control Surface Movements. Surface Travel (at trailing edge) Tolerance Aileron Aileron Trim Up Down Up Down 15º 15º 5º 5º +0º-30' +0º-45' ± 1º Rudder Left 22º ± 30' Right 22º Rudder Trim Tab Left 11º30' + 2º-1º Right 11º30' Elevator Up 22º ± 30' Down 12º Elevator Gear Tab Up 4º30' ± 30' Down 9º30' ± 15' Stabilizer Trim Up 1º ± 15' (Leading Edge) Down 12º ± 30' Airbrakes Up 20º ± 1º Slats Down 25º + 1º-2º Flaps Max Down 40º +1º-1º30' Manufacturer's Serial Models 1125 Westwind Astra and 1125 IW - S/N 002, 004 thru 72, and 074 thru 078 Numbers Eligible. Model Astra SPX - S/N 073, 079 thru 145. Model Gulfstream 100 - S/N 146 and subsequent Import Requirements, A U.S. Airworthiness Certificate may be issued on the basis of an Israeli Certificate of Airworthiness for Export signed by a representative of the Civil Aviation Administration of Israel (CAAI) containing the following statement: "The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under FAA Type Certificate No. A16NM, and to be in condition for safe operation". Data Pertinent to Model GULFSTREAM G150 Engines 2 Honeywell (formerly Allied Signal) TFE 731-40AR-200G FAA Type Certificate E1NM Fuel Conforming to Honeywell Specifications EMS 53111 (Jet A type), EMS 53112 (Jet A-1 & JP-8 types), EMS 53116 (JP-5 type) and EMS 53113 (Jet B & JP-4 types) as per LIMITATIONS SECTION of approved AFM Oil Conforming to Honeywell Specification EMS 53110, Type 2. Engine Limits Static Thrust at Sea Level LBS Maximum Continuous 4420 Take-off (5 minute) 4420 Maximum Continuous Permissible Engine Operating Speeds for the Engine Rotors, %RPM (RPM) Low pressure rotor (N1) 100.0 (21000) High pressure rotor (N2) 100.4 (31611) Maximum Interstage Turbine Temperature (ITT), Maximum Continuous º C 990 Take-off (5 minutes) 1004 Take-off (5 minutes) with APR ON 1022 During starting 990 Page 6 of 14 Rev 8 A16NM Maximum Oil Inlet Temperature, º C Up to 30,000 ft. Above 30,000 ft Fan gearbox 127 140 Fan gearbox transient for 2 minutes maximum 149 149 Accessory gearbox 149 157 Oil Pressure Normal operating At idle, minimum PSIG 62 TO 83 50 Maximum 100 Maximum Bleed and Power Extraction: See Honeywell Installation Manual IM-8010 Airspeed Limits: -VMo (Max operating) S.L. to 8000 ft. 310KCAS and increasing linearly from 8000.ft to 29260 ft to 330KCAS - MMo Above 29260 ft. 0.85M - MMo with Autopilot disengaged and Mach Trim inoperative above 24770 ft. 0.78M - VA (Maneuvering): - VA varies linearly from 272KCAS at S.L. to 287 KCAS at 20000ft. - VA varies linearly from 287 KCAS at 20000 ft. to 330 KCAS at 29300 ft. - Above 29300 ft. 0.85 M - VFE (Flaps12º and slats 25º) 250 KCAS - VFE (Flaps 20º and slats 25º ) 225 KCAS - VFE(Flaps Landing 40º and slats 25º ) 180 KCAS - VSB (Airbrakes Operation) No speed limitation - VLE and VLO (L/G Extension & Operating Speed) 180 KCAS - VMCA(Flaps 12º and 20º) 101 KCAS - VMCG (Flaps 12º and 20º) 103 KCAS - Tire limit ground speed : KTS (MPH) 182 KTS (210) C.G. Range Approved center of gravity range is as shown in the following tables : (Gear extension and retraction moment change is negligible) 13200 LBS 37.00 % MAC 14330 LBS – 20.00 % MAC 18700 LBS – 20 00 % MAC 23700 LBS—24.50 % MAC 26250 LBS –30.60 % MAC 26250 LBS – 38.00 % MAC 22000 LBS – 38.00 % MAC 21700 LBS—37.00 % MAC LINEAR VARIATION BETWEEN POINTS Datum Fuselage station 0 is located 135.65 inches forward of alignment points 14L / 14R Points 14L / 14R are the protruding rivets heads located in FWD fuselage at STA. 135.65, BL ± 36.99, WL 35.00 Mean 86.26 inches with leading edge at fuselage station 317.087 Aerodynamic Chord (MAC) Levelling Longitudinally: Place level on either seat rail at fuselage station 298.3 (FR 30) parallel to A/C centerline. Means Laterally Place level on seat rails at fuselage station 298.3 (FR 30) at 90º to A/C centerline Page 7 of 14 A16NM Maximum Weights - Ramp Gross Weight - Max Takeoff Weight - Max Landing Weight - Max Zero Fuel Weight 26,250 LBS 26,100 LBS 21,700 LBS 17,500 LBS Minimum Crew 2 (Pilot and Copilot) Maximum Passengers: Nine See Note 7 Maximum Baggage LBS 1100 ARM (INCHES) 452 Fuel Capacity LH / RH Wing tanks Collectors CTS Fuselage Total/Usable Fuel (LBS) 3592 / 3574 116 / 105 1317 / 1315 5308 / 5306 Arm (INCHES) 342 334.8 310.6 388.2 Unusable Fuel (LBS) 18.6 11 1.6 1.8 Arm (INCHES) 342.1 348 310.7 388.4 (See NOTE 1 for data on Fuel System) Oil Capacity (Density: 8.2 LBS/US Gallon) 2 engine systems, Total, LBS (See NOTE 1 for data on Oil System) TOTAL 32 USABLE 8 ARM 496 Maximum 45000 ft. Operating Altitude Other Operating Aircraft shall be operated according to operating limitations specified in approved Airplane Flight Limitations Manual see Note 5. Control Surface Movements Surface Aileron Travel (at trailing edge) Up 15º Tolerance ± 15’ Down 15º ± 15’ Aileron Trim Up 5º +0º -1º Down 5º +0º -1º Rudder Left 22º ±30′ Right 22º ±30′ Rudder Trim Tab Left 11º30′ +2º -1º Right 11º30′ +2º -1º Rudder Gear Tab Left 7.75º ±1º Right 7.75º ±1º Elevator Nose Up 22º30’ ±30′ Nose Down 12º30’ ±15′ Elevator Gear Tab Nose Up 3º ±30′ Nose Down 18º ±30' Stabilizer Trim Up 1º ±15′ (Leading edge) Down 12º ±30′ Airbrakes Up 45º ±15′ Slats Down 25º +1-2º Flaps Max Down 40º +1 -1º30′ Page 8 of 14 Rev 8 A16NM Manufacturer’s Serial numbers Eligible Model GULFSTREAM G150 S/N 201 and subs. Import Requirements: A US Airworthiness Certificate may be used on the basis of an Israeli Certificate of Airworthiness for Export signed by a representative of the Civil Aviation Administration of Israel (CAAI) containing the following statement: “The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under FAA Type Certificate No A16NM, and to be in condition for safe operation” Certification Basis. Models 1125 Westwind Astra and 1125 IW - 14 CFR Part 21.29 - 14 CFR Part 25, effective February 1, 1965, including Amendments 25-1 through 25-54. - SFAR 27, effective February 1, 1974, including Amendments 27-1 through 27-5. - 14 CFR Part 36, effective December 1, 1969, including Amendments 36-1 through 36-12. - Special conditions for operation up to 45000 feet, per FAA S.C. No. 25-ANM-5. - Special conditions for Automatic Takeoff Thrust Control System (ATTCS) installation, per FAA S.C. No. 25-ANM-5. - Exemption No. 3692 from FAR 25.1305 (d) (3) Rotor Unbalance Indication. - Compliance with ditching structural provisions of FAR 25.801(b) through (e) and 25.807(d) has been established. - Equivalent safety: FAR 25.729 (e)(2) Landing Configuration Aural Warning. - Equivalent safety: FAR 25.813(a) and 25.813(e) Emergency Exit Access, Lavatory Door (mod 6016). - Equivalent safety: FAR 25.1305 Powerplant Instruments for APU Installation (mod 6043) Page 9 of 14 A16NM Models Astra SPX and Gulfstream 100 - 14 CFR Part 21.29 - 14 CFR Part 25, effective February 1, 1965, including Amendments 25-1 through 25-54, plus Subpart B, Flight, Sections 25.21 through 25.255, and Subpart E, Powerplant, Sections 25.901 through 25.945, and 25.1011 through 25.1207, including Amendments 25-1 through 25-80, which have been applied to the changes or the areas affected by the change per the FAA derivative aircraft policy. In addition, the following specific regulations including Amendments 25-1 through 25-80 have been applied to the changes or the areas affected by the change per the FAA derivative aircraft policy: Section Title 25.305 Strength and deformation 25.307 Proof of structure 25.571 Damage tolerance & fatigue evaluation of structure 25.625 Fitting factors 25.629 Aeroelastic stability requirements 25.961 Fuel system hot weather operation 25.994 Fuel system components 25.997 Fuel strainer or filter 25.1001 Fuel jettisoning system 25.1305 Powerplant Instruments 25.1307 Miscellaneous equipment 25.1316 System lightning protection 25.1521 Powerplant limitations 25.1551 Oil quantity indication Further, Section 25.729 Amendment 25-75 has been applied in lieu of the equivalent safety finding made for this section on the IAI Model 1125 Westwind Astra. - 14 CFR Part 34, effective September 10, 1990. - 14 CFR Part 36, effective December 1, 1969, including Amendments 36-1 through 36-20. - Special Condition No. 25-ANM-104 for High Intensity Radiated Fields (HIRF). - Special Condition No. 25 -ANM-5 for operation to 45,000 feet and for ATTCS. Note: Compliance with Section 25.904, as promulgated by Amendment 25-62, was required for the ATTCS system in lieu of the Special Condition 25-ANM-5. - An equivalent safety finding exists with respect to Section 25.1203(a) Fire detection system within the turbine tailpipe zone. In addition, the following equivalent safety findings, previously made for the IAI Model 1125 Westwind Astra under the provisions of Section 21.21(b)(1), are also applicable to the IAI Model Astra SPX: Section 25.813(a) and (e) Emergency exit access, lavatory door Section 25.1305 Powerplant instruments for APU installation - Compliance with the following optional requirements has been established: Section 25.801 Ditching Section 25.1419 Ice Protection Certification Basis. Model Gulfstream G150 1A. Airworthiness & Environmental Standards for components and areas not affected or not significantly affected by the change : The certification basis for the unchanged portion of the model G150 is the same as the Model G100 as shown in the relevant G100 section above. 1B.Airworthiness and Environmental Standards for components and areas affected by the change for the basic G150: 14 CFR part 25, effective February 1, 1965, including amendments 25-1 through 25-108, except for the following paragraphs, which are complied with at the identified amendment level. Page 10 of 14 Rev 9 A16NM FAR 25 SUB- SECTION FAR SECTION TITLE ALLPICABLE TO ZONE / SYSTEM G150 AMDT 101 PERFORMANCE - GENERAL 38 105 TAKEOFF 0 109 ACCELERATE-STOP DISTANCE 42 113 TAKEOFF DISTANCE & TAKEOFF RUN 23 115 TAKEOFF FLIGHT PATH 0 143 f CONTROL & MANEUVER - GENERAL 42 149 h MINIMUM CONTROL SPEED 72 201 c, d STALL DEMONSTRATION 42 203 STALL CHARACTERISTICS 0 253 HIGH SPEED CHARACTERISTICS 72 305 STRENGTH & DEFORMATION AFT FUSELAGE ( * ), HORIZONTAL STABILIZER, VERTICAL TAIL, LANDING GEAR 54 305 STRENGTH & DEFORMATION WING, NACELLE 77 307 PROOF OF STRUCTURE AFT FUSELAGE, HORIZONTAL STABILIZER, VERTICAL TAIL, LANDING GEAR, WING, NACELLE 54 321 FLIGHT LOADS - GENERAL AFT FUSELAGE, NACELLE, VERTICAL TAIL, WING 23 333 FLIGHT ENVELOPE AFT FUSELAGE, NACELLE, VERTICAL TAIL, WING 0 335 DESIGN AIRSPEED AFT FUSELAGE, NACELLE, VERTICAL TAIL, WING 23 341 GUST LOADS AFT FUSELAGE, NACELLE, VERTICAL TAIL, WING 0 343 DESIGN FUEL & OIL LOADS AFT FUSELAGE, NACELLE, VERTICAL TAIL, HORIZONTAL STABILIZER, WING 18 345 HIGH LIFT DEVICES 46 349 ROLLING CONDITIONS NACELLE, WING 23 351 YAWING CONDITIONS AFT FUSELAGE, NACELLE, VERTICAL TAIL, HORIZONTAL STABILIZER 46 361 ENGINE TORQUE 46 363 SIDE LOAD ON ENGINE MOUNT 23 371 GYROSCOPIC LOADS 0 373 SPEED CONTROL DEVICES 0 391 CONTROL SURFACE LOADS- GENERAL WING, VERTICAL TAIL 0 395 CONTROL SYSTEM WING, VERTICAL TAIL, FLIGHT CONTROLS SYS. 23 397 CONTROL SURFACE LOADS WING, VERTICAL TAIL, HORIZONTAL STABILIZER, FLIGHT CONTROL SYS. 38 415 GROUND GUST CONDITIONS VERTICAL TAIL, HORIZONTAL SABILIZER, FLIGHT CONTROLS SYS. 0 427 UNSYMETRICAL LOADS AFT FUSELAGE, VERTICAL TAIL 23 445 AUXILLIARY AERODYNAMIC SURFACES WINGLETS 0 459 SPECIAL DEVICES SLATS 0 473 GROUND LOADS CONDITIONS & ASSUMPTIONS LANDING GEAR, NACELLE, WING, AFT FUSELAGE, VERTICAL TAIL, HORIZONTAL SABILIZER 23 479 LEVEL LANDING CONDITIONS LANDING GEAR, NACELLE, WING, AFT FUSELAGE 23 481 TAIL DOWN LANDING CONDITIONS LANDING GEAR, NACELLE, WING, AFT FUSELAGE 0 483 ONE WHEEL LANDING CONDITIONS AFT FUSELAGE, LAND GEAR, NACELLE, WING 0 Page 11 of 14 A16NM FAR 25 SUB- SECTION FAR SECTION TITLE ALLPICABLE TO ZONE / SYSTEM G150 AMDT 485 SIDE LOAD CONDITIONS LANDING GEAR, NACELLE, WING, AFT FUSELAGE 0 491 TAKEOFF RUN LANDING GEAR, NACELLE, WING, AFT FUSELAGE 0 493 BRAKED ROLL CONDITIONS AFT FUSELAGE, LANDING GEAR 23 499 NOSE WHEEL YAW AFT FUSELAGE, LAND GEAR 46 561 EMERG. LANDING CONDITION - GENERAL AFT FUSELAGE, NACELLE 23 693 - JOINTS 0 697 - LIFT AND DRAG DEVICES CONTROLS 46 701 FLAP & SLAT INTERCONNECTION 46 723 SHOCK ABSORPTION TESTS 46 725 LIMIT DROP TESTS 23 727 RESERVE ENERGY ABSORP. DROP TESTS 23 731 WHEELS 0 733 TIRES 48 735 BRAKES 48 783 e DOORS 54 855 CARGO OR BAGGAGE COMPARTMENT AFT FUSELAGE 32 856 THERMAL ACOUSTIC INSULATION MATERIALS 111 857 CARGO COMPT. CLASSIFICATION AFT FUSELAGE 32 951 FUEL SYSTEM - GENERAL 38 979 PRESSURE FUELING SYSTEM 38 981 FUEL TANK (IGNITION PREVENTION) (**) 1351 ELECT. SYSTEMS & EQUIPT. - GENERAL 41 1416 PNEUMATIC DE-ICER BOOT SYSTEM 46 1419 ICE PROTECTION 0 1435 HYDRAULIC SYSTEMS 41 Notes: ( * ) Aft fuselage is defined Aft of Station 10824 (frame 43) ( ** ) GALP elected to comply with 25.981 at amendment 25-102 except for paragraph 25.981 (c) 2. Special Conditions: 5 –ANM-104, High Intensity Radiated Fields (HIRF) (applicability to G100 extended to G150) 25.562 (25-294-SC) Dynamic test requirements for single place side facing seats 25.773 (b) Pilot Compartment View (Hydrophobic coating) No. 25-661-SC Non-Rechargeable Lithium Battery Installations NOTE: The FAA Special Conditions referenced above may be accessed via the Dynamic Regulatory System, internet location: https://drs.faa.gov/browse Page 12 of 14 Rev 8 A16NM 3. Equivalent Level of Safety Findings: Section 25.812 (a)( 1), (c), (d), (e) Emergency Lighting Section 25.831 (g) Ventilation System Failures – Cabin Temperature and Humidity Section 25.841 (b6) Cabin Pressurization – High Altitude Take-off and Landing Operations Section 25.1203 (a) Fire Detection System within the Turbine Tailpipe Zone (applicability to G100 extended to G150) Section 25.1305 ( c3 ) Digital Display Only of Turbine Engine High Pressure Rotor Speed ( N2 ) FAR.25.APPENDIX K Adoption of Draft Harmonized Rules for APU Certification Section 25.255(a) Maneuvering stability and controllability in a mistrim condition Section 25.1121(c) Exhaust system components separated by fireproof shields NOTE: The FAA Equivalent Level of Safety Findings referenced above may be accessed via the Dynamic Regulatory System, internet location: https://drs.faa.gov/browse 4. Exemptions Section 25.785 (b) Dynamic test requirements for multiple place side facing seats Section 25.901 (c) Uncontrollable High Engine Thrust FAA has concluded that the occurrence of any uncontrollable high thrust failure condition, or any of the associated causal failures listed within the FAA-approved ‘Airworthiness Assessment and Risk