TCDS A50NM

Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Revision 17 - - 1 3 - 15 8 14 14 17 13 11 12 6 6 Page 17 18 19 20 21 22 Revision 12 9 17 16 14 14 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A50NM Revision 17 DASSAULT AVIATION FALCON 2000 FALCON 2000EX September 5, 2026 TYPE CERTIFICATE DATA SHEET No. A50NM This data sheet which is part of Type Certificate No. A50NM prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the US Federal Aviation Regulations. Type Certificate Holder Dassault Aviation 9 rond Point des Champs Elysées 75008 PARIS FRANCE The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g. third party country) is FAR 21.183(d) or 21.185(b). Notwithstanding that the FAR referenced in the above paragraph does not specifically address or require a foreign civil airworthiness authority certification, such certification is the only practical way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA -approved type design and conditions for safe operation. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States. I. Model Falcon 2000 (Transport Category) approved February 2, 1995 (a) Basic Model Definition Engines 2 engines. CFE Company, Model CFE 738-1-1B (see NOTE 3b) Engine Limits Static, Standard, Sea Level Take-off (5 min)5,725 lb(2,547 daN) Maximum Continuous5,560 lb (2,474,daN) Maximum Steady State Rotor Speeds Low pressure rotor (N1)RPM 9,400 (96.7%) High pressure rotor (N2) 5 minutesRPM 28,000 (106%) ContinuousRPM 27,709 (104.9%) A50NM Page 2 of 23 Rev 17 Engine Limits (cont’d) Turbine Interstage Temperature Limits Ground starting815 °C Air starting864 °C Maximum take-off (5 min)877 °C Maximum take-off (2 min)890 °C Maximum continuous861 °C Airstart transient (10 sec)890 °C Airstart transient (2 sec)1000 °C Oil Temperature Maximum continuous138 °C Minimum continuous30 °C Maximum transient (3 min)155 °C Fuel Pump Inlet Pressure Minimum5 psi above true vapor pressure Maximum50 psig Oil Pressure Idle30-85 psig Normal operating range60-85 psig Maximum transient (3 min)100 psig (may be exceeded for 2.5 min. in case of a cold start (temp < 0 C)) Thrust Reversers Thrust reverser use is not approved, unless Dassault Aviation change M3B has been incorporated. APU Allied Signal Model GTCP36-150 (F2M) Limitation Maximum operating starting altitude35,000 ft Maximum N1 (%)110 Exhaust gas temperature, Steady 746 °C Exhaust gas temperature, Starting 974 °C Maximum oil temperature163 °C Minimum oil pressure35 psi Operation of the APU with passengers in the cabin and without crew member monitoring is not authorized. Airspeed Limits Unless otherwise stated, speeds are indicated airspeeds VMO (Maximum Operating) 350 kt at sea level, 370 kt at 10,000 ft with straight line variation between those points. 370 kt from 10,000 to 25,000 ft MMO (Maximum Operating) M = 0.862 from 25,000 to 38,000 ft 0.862 at 38,000 ft, 0.85 at 42,000 ft with straight line variation between those points 0.85 above 42,000 ft A50NM Page 3 of 23 Rev 17 Airspeed Limits (cont’d) VA (Maneuvering)198 kt VFE (Slat and Flap Speeds) Slats + Flaps 10°200 kt Slats + Flaps 20°160 kt Slats + Flaps 40°160 kt VLO (Landing Gear Operation)190 kt MLO0.70 VLE (Landing Gear Extended)245 kt MLE0.75 VMC (Minimum Control Speed) Flight90 kt Windshield Wiper Operation215 kt Direct Vision Window215 kt CG Range (Gear Extended) a. Without Option M57 Weight (lb)Forward Limit (% MAC)Rearward Limit (% MAC) 36,00016.7 26.2 33,00014 - 28,660 or less14 32.5 b. With Option M57 Weight (lb)Forward Limit (% MAC)Rearward Limit (% MAC) 36,50017.2 25.8 33,00014 - 28,660 or less14 32.5 Straight line variation between points. Gear retraction has negligible effect on CG range. Datum Datum is 25% of mean aerodynamic chord (MAC) which coincides with fuselage station FS + 400.43 in (Fuselage station reference +0 is the fo rward end of the airplane nose cone). Mean Aerodynamic chord (MAC) Length113.69 in Zero percent MAC is at FS +372.01 in Leveling Means Standard bubble type level to be installed on the passenger seat tracks A50NM Page 4 of 23 Rev 17 Weight Limitations Without Option M57 With Option M57 Maximum ramp36,000 lb36,500 lb Maximum take-off35,800 lb36,500 lb Maximum landing33,000 lb33,000 lb Maximum zero fuel28,660 lb28,660 lb Minimum flight at 14% CG23,075 lb23,075 lb at 32.5% CG20,100 lb20,100 lb Minimum Crew 2 - Pilot and copilot Maximum Passenger Seats 19 - limited by emergency exit requirements of Federal Aviation Regulations § 25.807(c) 0 - Without passenger provision but incorporating Dassault Ferry flight configuration : M0054. Maximum Baggage Baggage compartment1,600 lb (not to exceed 61.4 lb per sq ft) Fuel Capacity Nominal - Refer to weight and balance report of each airplane for exact capacity Refer to NOTE 1(b) for data on unusable system fuel and oil Usable FuelUS GallonsPoundsArm (in) LH outboard wing348.42,334 22.64 LH inboard wing213.7 1,432-27.68 LH center wing box216.91,453-37.76 LH Feeder tank127851-16.34 RH outboard349.22,340 22.64 RH inboard wing214.11,435-27.68 RH center wing box217.41,457 -37.76 RH feeder tank127.3853-57.87 Total Usable1,814.012,155 Total Fuel1830.312,259 Fuels Fuels conforming to General Electric specification No. D50TF2, current revision See NOTE 4 for fuel additives The above mentioned fuels and additives are also suitable for the APU Pressure Fueling Maximum50 psi Oil Capacity Refer to NOTE 1(b) for data on unusable system fuel and oil (each engine) Usable0.55 US gallon Total1.25 US gallon Oils Oil conforming to General Electric Specification No. D50TR1, or Allied Signal oil Specification EMS 53110, current revision See NOTE 5 Maximum Operating Altitude 47,000 ft Control Surface Movements ElevatorDown 16°Up 20° RudderRight 29°Left 29° AileronUp 25°20´Down 24°50´ FlapsDown 40° A50NM Page 5 of 23 Rev 17 Control Surface Movements (cont’d) AirbrakesInboard up 68° Center up 50° Outboards up 37° Wing slatsDown 30° StabilizerElectrical stops AND 2°ANU 10° Mechanical stopsAND Max 2°30´ANU Max 10°30´ Structural stopsAND Min 2°40´ANU Min 11° Rigging tolerances are included in Maintenance Manual II. Model FALCON 2000EX (Transport Category Airplane) approved March 21, 2003 (a) Basic Model Definition The Falcon 2000EX is defined by Dassault modification M1802 and differs from the Falcon 2000 in the following major respects: (i) Pratt &Whitney Canada Engines PW308C replace CFE 738 -1-1B engines; (ii) New forward and aft fuel tanks are added, (iii) New main and nose landing gear, (iv) New tires and brakes Engines 2 engines. (PRATT & WHITNEY Canada) Model PW308C Turbofan (see NOTE 3b) Engine Limits Static, Standard, Sea Level Take-off (5 min)6,998 lb(3,114 daN) Maximum Continuous6,998 lb (3,114 daN) Maximum Steady State Rotor Speeds Low pressure rotor (N1)RPM 10,660 (102.5%) High pressure rotor (N2)RPM 27,316 (102%) Turbine Interstage Temperature Limits Ground start950 °C Air start950 °C Normal Takeoff (5 min.)860 °C Maximum take-off (5 min)875 °C Maximum continuous860 °C Restarting Max. (air start/ground start)500 °C/ 340 °C Transient (20 sec)885 °C Oil Temperature Maximum135 °C Minimum takeoff/ in-flight27 °C/ 16 °C Maximum transient (90 sec.)143 °C Starting (minimum)-40 °C Fuel Pump Inlet Pressure Minimum(SEE ENGINE INSTALLATON MANUAL) Maximum(SEE ENGINE INSTALLATION MANUAL) Engine Limits (cont’d) A50NM Page 6 of 23 Rev 17 Oil Pressure Operating Range36 to 100 psi Minimum at Idle20 psi Transient (20 sec.)0 to 220 psi Transient (90 sec.)10 to 220 psi Cold start: during starting240 psi Thrust Reversers Thrust reverser use is approved only on the ground. APU Allied Signal Model GTCP36-150 (F2M) Limitation Maximum operating/starting altitude35,000 ft Maximum N1 (%)110 Exhaust gas temperature, Steady 746 °C Exhaust gas temperature, Starting 974 °C Maximum oil temperature163 °C Minimum oil pressure35 psi Operation of the APU with passengers in the cabin and without crew member monitoring is not authorized. Airspeed Limits Unless otherwise stated, speeds are indicated airspeeds VMO (Maximum Operating): 350 kt at sea level, 370 kt at 10,000 ft with straight line variation between those points. 370 kt from 10,000 to 25,000 ft MMO (Maximum Operating): 0.862 from 25,000 to 38,000 ft 0.862 at 38,000 ft, 0.85 at 42,000 ft with straight line variation between those points 0.85 above 42,000 ft VA (Maneuvering)198 kt VFE (Slat and Flap Speeds) Slats + Flaps 10°200 kt Slats + Flaps 20°190 kt Slats + Flaps 40°180 kt VLO (Landing Gear Operation)190 kt MLO0.70 VLE (Landing Gear Extended)245 kt MLE0.75 Airspeed Limits (cont’d) VMC (Minimum Control Speed) Flight90 kt A50NM Page 7 of 23 Rev 17 Windshield Wiper Operation215 kt Direct Vision Window Opening215 kt CG Range (Gear Extended) Weight (lb)Forward Limit (% MAC)Rearward Limit (% MAC) 40,90015.723.4 38,30014 26.0 28,660 or less14 32.5 Straight line variation between points. Gear retraction has negligible effect on CG range. Datum Datum is 25% of mean aerodynamic chord (MAC) which coincides with fuselage station FS + 400.43 in (Fuselage station reference +0 is the forward end of the airplane nose cone). Mean Aerodynamic chord (MAC) Length113.69 in Zero percent MAC is at FS +372.01 in Leveling Means Standard bubble type level to be installed on the passenger seat tracks Weight Limitations Without M1826 (serial no.1 only) with M1826 with M1826 and M1842 (Maximums) Taxi and Ramp 40,900 lb 41,500 lb 42,400 lb Take-off 40,700 lb 41,300 lb 42,200 lb Landing 38,300 lb 39,300 lb 39,300 lb Zero fuel 29,700 lb 29,700 lb 29,700 lb Minimum flight at 14% CG23,444 lb23,444 lb at 32.5% CG21,149 lb21,149 lb Minimum Crew 2 - Pilot and copilot Maximum Passenger Seats 19 - limited by emergency exit requirements of Federal Aviation Regulations § 25.807(c) Maximum Baggage Baggage compartment1,600 lb (not to exceed 61.4 lb per sq ft) Fuel Capacity Nominal - Refer to weight and balance report of each airplane for exact capacity Refer to NOTE 1(b) for data on unusable system fuel and oil Without M1826 applied (serial no. 1 only) Usable FuelUS GallonsPounds LH wing+1/2 center wing box9116,105 RH wing+1/2 center wing box9116,105 Rear Tank2441,630 Front Tank3292,205 Total Usable2,39516,045 Total Fuel2,40716,127 Fuel Capacity (cont’d) With M1826 applied (serial no. 2 and on) Usable FuelUS GallonsPounds A50NM Page 8 of 23 Rev 17 LH wing+1/2 center wing box9096,092 RH wing+1/2 center wing box9126,112 Rear Tank2931,962 Front Tank3832,564 Total Usable2,49716,730 Total Fuel2,50916,812 Fuels Fuels and additives conforming with the specifications listed in the applicable P&WC Maintenance Manual are approved. See NOTE 4 for fuel additives. The above mentioned fuels and additives are also suitable for the APU Fuel anti-icing must be used for fuel temperature below –50 °C Pressure Fueling Maximum50 psi Oil Capacity Refer to NOTE 1(b) for data on unusable system fuel and oil (each engine) Usable0.49 US gallon Total2.4 US gallon Oils Oils conforming to the Specifications listed in the applicable P&WC Maintenance Manual (P/N 30C3882) are approved Maximum Operating Altitude 47,000 ft Control Surface Movements ElevatorDown 16°Up 20° RudderRight 29°Left 29° AileronUp 25°20´Down 24°50´ FlapsDown 40° AirbrakesInboard up 68° Center up 50° Outboards up 37° Wing slatsDown 30° StabilizerElectrical stops AND 2°ANU 10° Mechanical stopsAND Max 2°30´ANU Max 10°30´ Structural stopsAND Min 2°40´ANU Min 11° Rigging tolerances are included in Maintenance Manual (b) Falcon 2000EX EASy Definition (Approved June 21, 2004) EASy designation for Falcon 2000EX does not correspond to a model designation. This is only a commercial designation for airplanes on which Major modification numbers M1691, M1745, and M1504 have been embodied. Major Change Modification number M1691 to the Falcon 2000EX consists of the installation of an Enhanced Avionics System (EASy) based on the Honeywell “Primus EPIC” product line. This system architecture is mainly built around 2 cabinets called Modular Avionics Units (MAU), 2 Modular Radio Cabinets (MRC), 2 Audio panels, 2 reversionary panels and 4 14.1 inch Liquid Crystal Displays. The pilots have access to the system using the 2 CCDs with multipurpose knob, menu pushbutton, display switch, action pushbuttons and trackball, 2 alphanumeric keyboards and the hard controls. M1745 installs an “Oxygen system electro-pneumatic altimetric controller" M1504 installs an "All falcon Common pressurization system" M1691, M1745, and M1504 are basic on all Falcon 2000EX aircraft serial numbers 6, 28 and subsequent. A50NM Page 9 of 23 Rev 17 All parameters listed in the preceding sub-section (a) for the basic Falcon 2000EX remain valid for airplanes which incorporate M1691, M1745 and M1504. (c) Falcon 2000DX Definition (Approved October 3, 2007) The DX definition of the Falcon 2000EX does not correspond to a model designation. The Falcon 2000DX is only a commercial designation for Falcon 2000EX airplanes in the EASy configuration on which modifications M3000 and M3001 are installed at production. Modification M3000 defines the airplane and reduces the fuel tank capacity. Modification M3001 installs a new fuel quantity indication system. M3000 and M3001 are basic on all Falcon 2000EX airplanes in the EASy configuration starting with serial number 601 and subsequent. All parameters listed in the preceding sub-section (b) above for the Falcon 2000EX EASy remain valid for airplanes which incorporate M3000 and M3001, except for the following weight limits and useable fuel. Falcon 2000DX Weight (lb) Maximum landing weight Maximum takeoff weight Maximum taxi and ramp weight 39 300 41 000 41 200 Useable fuel Front Tank 189 US Gallons 1,268 lbs Rear Tank 183 US Gallons1,224 lbs (d) Falcon 2000LX Definition (Approved April 29, 2009) The LX definition of the Falcon 2000EX does not correspond to a model designation. The Falcon 2000LX is only a commercial designation for Falcon 2000EX airplanes in the EASy configuration on which modifications M2846 and M3229 are installed. Modification M2846 incorporates winglets on the airplane and M3229 installs new slats. Major All parameters listed in the preceding sub-section (c) above for the Falcon 2000EX EASy remain valid for airplanes which incorporate M2846 and M3229, except for the following weight limits. Falcon 2000LX Without M3390 With M3390 Weight (lb) Maximum landing weight Maximum takeoff weight Maximum taxi and ramp weight 39 300 42 200 42 400 39 300 42 800 43 000 (e) Falcon 2000LXS Definition (Approved March 25, 2013) The LXS definition of the Falcon 2000EX does not correspond to a model designation. The Falcon 2000LXS is only a commercial designation for Falcon 2000EX airplanes in the EASy configuration on which modifications M2846, M3229, M3254, M3390, M3453, and M5000 are installed at production. Modification M2846 installs winglets, M3254 incorporates the EASy Phase II, M3390, incorporates a weight and balance envelope increase for take-off, M3453 incorporates new FADEC software V9.03 for the PW308C engines and M5000 incorporates movable inboard leading edge slats. All parameters listed in the preceding sub-section (d) above for the Falcon 2000LX remain valid for airplanes which incorporate modification M5000, except for the following weight limits. Falcon 2000LXS Weight (lb) Maximum zero fuel weight 31 200 A50NM Page 10 of 23 Rev 17 (f) Falcon 2000S Definition (Approved March 25, 2013) The S definition of the Falcon 2000EX does not correspond to a model designation. The Falcon 2000S is only a commercial designation for Falcon 2000EX airplanes in the LXS configuration on which modifications M3000, M3001, and M5001 are installed at production. Modification M5001 incorporates movable inboard leading edge slats. All parameters listed in the preceding sub-section (c) above for the Falcon 2000DX remain valid for airplanes which incorporate modifications M3000, M3001 and M5001, except for the following weight limits. Falcon 2000S Without M5031 With M5031 Weight (lb) Maximum takeoff weight Maximum taxi and ramp weight 41 000 41 200 42 800 43 000 Data Pertinent to all Models Manufacturer Serial Number Eligible A French "Certificat de Navigabilité pour Exportation" endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for US certification is made. Serial Numbers: For FALCON 2000: Aircraft serial number 1 and up For FALCON 2000EX: Aircraft serial number 1 through 5 and 7 through 27. Serial numbers 6 and 28 through 217 include M1691, M1745, and M1504 as standard (F2000EX EASy definition). Aircraft serial numbers 601 through 700 include M3000 and M3001 as standard (F2000DX definition). Aircraft serial numbers 218 through 262 include M2846 and M3229 (F2000LX definition). Aircraft serial number 263 and subsequent includes M2846, M3229, M3254, M3390, M3453, and M5000. Aircraft serial numbers 701 and subsequent include M3000, M3001, and M5001. Import Requirements 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, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Certification Basis (a) For FALCON 2000 (basic model): 1. FAR, Part 25 as amended by Amendment 25-1 through 25-69. In addition, Dassault Aviation has elected to comply with amendments 25 -71 for § 25.365(e), 25-72 for §§ 25.783(g) and 25.177; 25-75 for § 25.729(e); 25-79 for § 25.811(e)(2) and 25-80 for § 25.1316 2. FAR Part 34, original issue (Fuel Venting and Exhaust Emissions) 3. FAA, Part 36 as amended by amendment 36-1 through 36-20 4. FAA, Special Conditions: A50NM Page 11 of 23 Rev 17 25-ANM-90 - High Altitude Operation 25-ANM-91 - High -Intensity Radiated Fields 25-ANM-94 - Automatic Takeoff Thrust Control System 25‐713‐SC - Non‐Rechargeable Lithium Batteries, effective to design changes applied for after January 18, 2018. See the applicability section of this special condition for more information on which design changes must meet it. 5. FAA Exemption No. 7104A (for side facing sofa) For precision approach and landings, the applicable technical requirements are complemented by FAA Advisory Circulars (AC) 120-29 and AC 120-28(c) For the automatic flight control system, the applicable technical requirements are complemented by AC 25.1329-1A for cruise. Equivalent safety findings exist with respect to the following requirements: •Design gust criteria, (refer to Issue Paper (IP) A-5) •Use of the 1-g stall speeds instead of minimum speed in the stall as a basis for determining compliance (refer to IP F-1) •Rejected take-off and landing performance (refer to IP F-3) •N2 Digital Indication (refer to IP P-10) •Flight Critical Thrust Reverser Certification (refer to IP P-7) Compliance has been shown to the following optional requirement: •Ditching, FAR § 25.801 •Ice Protection FAR § 25.1419 For Falcon 2000 airplanes incorporating modification M-OPT0413 (Starlink Antenna Provisions): Equivalent Level of Safety Findings according to the provisions of 14 CFR 21.21(b)(1) for the following: Section 25.251: Vibration and Buffeting (documented in ELOS memo AT20300IB-T-ESF-B25.251-01) Type Certificate A50NM issued February 2, 1995 Reference date for type certification: November 30, 1989 (b) For Falcon 2000EX (1) For parts of the airplane not changed or not affected by the modifications: Unchanged from basic Falcon 2000 (2) For those parts of the airplane that are changed or are affected by the modifications M1802, M1803, M1804, M1805: The following sections of 14 CFR 25 as amended by amendments 25 -1 through 25-98 apply per the FAA derivative aircraft process FAA Order 8110.4B to the changes and areas affected by the changes for the Falcon 2000EX: Subpart B – Flight: All the paragraphs are applicable at amendment 25-98 except the following which are applicable as modified in Equivalent Level of Safety Finding Issue A50NM Page 12 of 23 Rev 17 Paper F-4 titled “Use of 1-g Stall Speeds Instead of Minimum Speed in the Stall as a Basis for Determining Compliance” 25.103, 25.107, 25.111, 25.119, 25.121, 25.125, 25.143, 25.145, 25.147, 25.149, 25.161, 25.175, 25.177, 25.181, 25.201, 25.207, 25.231, 25.233, 25.237 Subpart C – Structure: All the paragraphs are applicable at amendment 25-98 Subpart D – Design and Construction: The following paragraphs are applicable at amendment 25-98: 25.601 to 25.703, 25.721, 25.723, 25.729, 25.801, 25.863 to 25.869 The following paragraphs are applicable as modified by Equivalent Level of Safety Issue Paper F-4 titled “Use of 1-g Stall Speeds Instead of Minimum Speed in the Stall as a Basis for Determining Compliance”: 25.735, 25.773 Subpart E – Powerplant: All the paragraphs are applicable at amendment 25-98 except the following which is applicable as modified in Equivalent Level of Safety Finding Issue Paper F-4 titled “Use of 1-g Stall Speeds Instead of Minimum Speed in the Stall as a Basis for Determining Compliance” 25.1001 Subpart F – Equipment: The following paragraphs are applicable at amendment 25-98: 25.1301, 25.1305 to 25.1322, 25.1337, 25.1431 The following paragraphs are applicable as modified by Equivalent Level of Safety Issue Paper F-4 titled “Use of 1-g Stall Speeds Instead of Minimum Speed in the Stall as a Basis for Determining Compliance”: 25.1323, 25.1325, 25.1587 Subpart G – Operating Limitations and Information: All the paragraphs are applicable at amendment 25-98 except the following: 25.1515, 25.1522, 25.1523, 25.1525, 25.1529, 25.1531, 25.1547, 25.1561 (3) FAR Part 34, original issue (Fuel Venting and Exhaust Emissions) (4) FAA, Part 36 as amended by amendment 36-1 through 36-24 (5) FAA, Special Conditions: 25-ANM-90 - High Altitude Operation 25-ANM-91 - High -Intensity Radiated Fields A50NM Page 13 of 23 Rev 17 25-ANM-94 - Automatic Takeoff Thrust Control System 25‐713‐SC - Non‐Rechargeable Lithium Batteries, effective to design changes applied for after January 18, 2018. See the applicability section of this special condition for more information on which design changes must meet it. (6) FAA Exemption No. 8007A (for side facing sofa) (7) Equivalent safety findings according to 14 CFR 21.21(b)(1) for the following subjects: •§ 25.103 & related paragraphs, 1-G Stall Speeds (documented in TAD ELOS Memo AT0021IB-T-F-4) •Section 933(a)(1)(ii): Reversing Systems (documented in TAD ELOS Memo AT0012IB-T-P-12) •§ 25.1203(a) Fire Detector System (documented in TAD ELOS Memo AT0021IB-T-P-15) •§§ 25.809(b) and 25.813(c)(2)(ii) - Emergency Exit Access (documented in TAD ELOS Memorandum AT10010IB-T-CI-101) •§ 25.813(c)(2) “Emergency Exit Access” (documented in TAD ELOS Memo SP00843IB-T) (8) Miscellaneous: For precision approach and landings, the applicable technical requirements are complemented by FAA Advisory Circulars (AC) 120-29 and AC 120- 28(c)