TCDS T00008WI

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 Rev. No. 34 26 25 15 33 30 26 15 29 33 26 21 18 Page No. 14 15 16 17 18 19 20 21 22 23 24 25 26 Rev. No. 34 30 26 21 18 28 34 25 22 25 27 31 33 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00008WI Revision 34 Learjet 45 June 8, 2026 TYPE CERTIFICATE DATA SHEET NO. T00008WI This data sheet, which is part of Type Certificate No. T00008WI, 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 Learjet Inc. One Learjet Way Wichita, Kansas 67209-2942 I. Model 45 (Learjet 45), S/N 45-002 thru 45-455 (See NOTE 6), Learjet (Transport Category), Approved September 22, 1997 Engines Two Honeywell (AlliedSignal Engine s) TFE731-20R or TFE731-20AR or TFE731- 20BR-1B turbofan engines, TC E1NM. Eligible part numbers are listed below. Each engine is controlled by a single power lever and by Digital Electronic Engine Control (DEEC) software. Left and right engines must utilize common DEEC part numbers. Engine installation configuration is defined by the Learjet Engineering Change Record (ECR) or ModSum, and as noted below. Engine Configuration Designation Model No.: TFE731-( )- 1B Engine P/N DEEC P/N ECR/ ModSum Engine Configurations* interchangeable with: A 20R 3060020-8 2118882-1004 4601 A B 20R 3060020-9 2118882-1004 8711 B C 20R 3060020-10 2118882-1005 7266 C/J D 20R 3060020-10 **2118882-1006 7821 D/ K E 20R 3060020-11 #2118882-1007 8778 E/F/G/H/L/M/N/P F 20R 3060020-12 2118882-1007 *** E/F/G/H/L/M/N/P G 20R 3060020-13 2118882-1008 **** E/F/G/H/L/M/N/P H 20R 3060020-14 2118882-1008 **** E/F/G/H/L/M/N/P J 20AR 3060082-2 2118882-1005 7323 C/J K 20AR 3060082-2 **2118882-1006 7821 D/ K L 20AR 3060082-3 2118882-1007 8756 E/F/G/H/L/M/N/P M 20AR 3060082-4 2118882-1007 7944 E/F/G/H/L/M/N/P N 20AR 3060082-6 2118882-1008 045T020412 E/F/G/H/L/M/N/P P 20AR 3060082-7 2118882-1008 **** E/F/G/H/L/M/N/P R 20BR 3060084-1 2118882-1008 7772 R/S S 20BR 3060084-2 2118882-1008 7772 R/S * Listed engine configurations in each row may be installed single or pairs. ** Installed by Service Bulletin SB 45-76-2 only for activation of Thrust Reversers to maximum reverse. *** Installed by Honeywell Engine and Systems Service Bulletin SB TFE 731-72-5149 to install Engine Fan Bypass Duct of Composite Material on fielded airplanes. Requires prior or concurrent incorporation of ECR 8778. **** Installed by Honeywell Engine and Systems Service Bulletin SB TFE 731-72-5120. Requires prior or concurrent incorporation of ECR 8778 or ECR 7599. # Installed by Service Bulletin SB 45-22-4 to incorporate Honeywell Avionics Phase III and -1007 DEEC on fielded airplanes. T00008WI 2 of 26 Rev. 34 I. Model 45 (Learjet 45) (cont’d) Fuel See NOTE 15. Engine Limits See NOTE 19. Static thrust, standard day, sea level: APR (5 min.)* 3650 lbs. Takeoff (5 min.)* 3500 lbs. *5 minutes total at takeoff or above Max. permissible engine rotor operating speed: N1 (Fan) steady state 100.1% N1 = 21,021 RPM N2 (Gas gen.) steady state 100% N2 = 31,173 RPM N2 (Gas gen.) APR 101% N2 = 31,485 RPM N1 (Fan) transient (10 sec.) 100.5% N1 = 21,105 RPM N2 (Gas gen.) transient (10 sec.) 102.5% N2 = 31,957 RPM N1 (Fan) (10 sec.) 103.0% N1 = 21,630 RPM* N2 (Gas gen.) (10 sec.) 104.0% N2 = 32,430 RPM* *Reduce power to bring wi thin steady state limits Max. Permissible Interstage Turbine Gas Temperatures Engine Model: TFE721-20R-1B TFE731-20R-1B TFE731-20BR-1B TFE731-20AR-1B Part Number: 3060020-10 3060020-8, -9 3060020-11, -12, -13, -14 3060084-1, -2 3060082-2 3060082-3, -4, -6, -7 Takeoff (5 min) 941°C 941°C 963°C (A/I On) 941°C (A/I Off) 991°C 941°C 963°C (A/I On) 941°C (A/I Off) APR (5 min) 963°C 963°C 963°C 1013°C 963°C 963°C Max. Continuous 941°C (A/I On) 916°C (A/I Off) 916°C 941°C (A/I On) 916°C (A/I Off) 991°C 916°C 941°C (A/I On) 916°C (A/I Off) Maximum Cruise 900°C 900°C 900°C 974°C 900°C 900°C Starting (below): Starter assisted 941°C 941°C 941°C 991°C 941°C 941°C Windmill 941°C 941°C 941° C 991°C 941°C 941°C APU Honeywell Engines and Systems RE100[LJ] APU (formerly AlliedSignal) APU Limits The APU is limited to ground operations only, up to field pressure altitudes of 10,000 ft., and must be shut down prior to takeoff. See Airplane Flight Manual (AFM) for additional limits. Airspeed Limits V MO (Maximum Operating) 330 KIAS Sea Level to 26,756 ft. MMO (Maximum Operating) .81 Mach above 26,756 ft. VA (Sea Level) 149 KIAS 12,500 lbs. 155 KIAS 13,500 lbs. 159 KIAS 14,000 lbs. 178 KIAS 17,000 lbs. 192 KIAS 19,200 lbs. 200 KIAS 20,500 lbs. 206 KIAS 21,500 lbs. See AFM for variations with weight, altitude, aircraft serial numbers, and modifications. VB (Speed for maximum gust intensity) 250 KIAS T00008WI 3 of 26 Rev. 34 I. Model 45 (Learjet 45) (cont’d) Airspeed Limits (cont’d) VFE (Flaps extended) Flaps 8 250 KIAS Flaps 20 200 KIAS Ldg Position - Full Flaps 150 KIAS VMCA (Minimum control speed) Air Flaps 8 103 KIAS Flaps 20 100 KIAS VMCG (Minimum control speed) Ground APR On 103 KIAS APR Off 100 KIAS VMCL (Minimum control speed) Landing Flaps 20 105 KIAS Flaps 40 97 KIAS VLO (Landing gear operating) 200 KIAS VLE (Landing gear extended) 260 KIAS Max. tire ground speeds: Nose Gear Tire 210 MPH Main Gear Tire 190 MPH C.G. Range Maximum Design C.G. Limits (Landing Gear Extended) (1) AFT Flight Limit: FS 435.57 (25.0% MAC) at 14,000 lbs. and tapers to FS 438.19 (28.0% MAC) at 15,000 lbs. and remains at FS 438.19 (28.0% MAC) up to and including 20,750 lbs. (Max Ramp Weight). For aircraft modified by SB 45-11-4, the aft C.G. Limit of FS 438.19 (28% MAC) is extended to 21,000 lbs. and then to FS 435.84 (25.3% MAC) at 21,750 lbs. (Max Ramp Weight). (2) FWD Flight Limit: FS 414.64 (1% MAC) for weights at 14,000 lbs. up to, and including, 15,000 lbs. and tapers to FS 419.87 (7% MAC) at 18,000 lbs. then to FS 427.87 (16.2% MAC) at 20,750 lbs. (Max Ramp Weight). For aircraft modified by SB 45-11-4, the forward limit extends to FS 430.77 (19.5% MAC) at 21,750 lbs. (Max Ramp Weight) (for Learjet 45, S/N 45- 368, see NOTE 18). See AFM, Section I, for additional approved limits. Datum 75.05 inches fwd of nose. Wing jack points are at STA 468.00. Fuselage jack point is at STA 158.95. MAC 87.215 (L.E. of MAC 413.769) Leveling Means Lateral and longitudinal leveling ma rks are provided at FS 613.768. See Maintenance Manual or LES 1427 for leveling instructions. A/C modified by SB 45-11-4 A/C modified by SB 45-11-5 Maximum Weight (lbs.) Ramp 20,750 lbs. 21,750 lbs. 20,750 lbs. Takeoff 20,500 lbs. 21,500 lbs. 20,500 lbs. Landing 19,200 lbs. 19,200 lbs. 19,200 lbs. Zero Fuel 16,000 lbs. 16,000 lbs. 16,500 lbs. Min. Flight Weight 14,000 lbs. 14,000 lbs. 14,000 lbs. See AFM, maximum weights vary with serial numbers and modifications. T00008WI 4 of 26 Rev. 34 I. Model 45 (Learjet 45) (cont’d) Minimum Crew For all flights: two persons (pilot and co-pilot) No. of Seats 11 (two pilots, nine passengers) Maximum Baggage Cabin 170 lbs. Arm 425 inches Tail compartment 500 lbs. Arm 544 inches Floor loading density 75 psf Fuel Capacity (Gal.) Usable 905 gals. Weight 6,062 lbs. Arm 460 inches See NOTE 1 for data on unusable fuel. Oil Capacity (Gal.) Two engine mounted tanks: Total 3.8 gal. Arm 519 inches (1.9 gal. each) (tank plus system) See NOTE 1 for data on unusable oil. Max. Operating Altitude 51,000 feet Control Surface Movements For proper rigging instructions , see the Maintenance Manual or the specific Learjet Engineering Specification - Functional Test listed below for the individual control system. Horizontal Stabilizer Ri gging Instructions: LES-FT-1981 Primary Trim -0.30° to -0.55 ° L E UP -9.25° to -9.50° L E DN Secondary Trim -0.30° to -0.55 ° L E UP -9.25° to -9.50° L E DN Elevator Rigging Instructions: LES-FT-1976 15.0° ± 0.5° Trailing Edge UP 15.5° ± 0.5° Trailing Edge DN Rudder Rigging Instructions: LES-FT-1976 30° + 2.0°/– 1.0° Trailing Edge Left 30° + 2.0°/– 1.0° Trailing Edge Right Rudder trim Rigging Instructions: LES-FT-1979 20° ± 1° Trailing Edge Left 20° ± 1° Trailing Edge Right Aileron Rigging Instructions: LES-FT-1976 From faired position 18.0° + 1.0°/– 0.0° Trailing Edge DN >18.0° Trailing Edge UP Droop position 3.1° ± 0.2° down from faired Aileron Trim Rigging In structions: LES-FT-1979 15.0° ± 1.0° Trailing Edge UP 15.0° ± 1.0° Trailing Edge DN Flaps Rigging Instructions: LES-FT-1973 Flap Position Allowable Tolerance 0° Rig Position 8° ± 1° 20° ± 1° 40° ± 2° Spoiler/Spoileron Rigging Instructions: LES-FT-1766 First partial detent: 14.5° ± 2.0° Second partial detent: 28.5° ± 2.0° EXT detent: 60.0° ± 2.0° Spoileron Mode: 60.0° ± 2.0° T00008WI 5 of 26 Rev. 34 I. Model 45 (Learjet 45) (cont’d) Serial Nos. Eligible 45-002 th ru 45-455 (See NOTES 6 and 21). Certification Basis 14 CFR Part 25, Airworthiness Standards: Transport Category Airplanes, effective February 1, 1965, including Amendments 25-1 through Amendment 77. In addition, the following regulation at the specified Amendment applies: 14 CFR 25.856 Amdt 25-111 for all changes where application is made after September 2, 2005. In addition, the following regulations at the specified Amendments apply: 14 CFR 25.899 Amdt 25-123, 25.981 Amdt 25-102, 25.1353 Amdt 25-113 for the Passenger Communication System. In addition, the following regulations at the specified Amendments apply: 14 CFR 25.981 Amdt 25-102 for the Brake System Timing Change (ModSum 045T026230). 14 CFR Part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, effective September 10, 1990, including Amendments 34-1 through 34-2. 14 CFR Part 36, Noise Standards: Aircraft Type Certification and Airworthiness Certification, effective December 1, 1969, including Amendments 36-1 through 36-28. Compliance with Section 44715(e) of Title 49 U.S.C. (Noise Control Act of 1972) Optional Design Regulations: 14 CFR 25.801 ditching not complied with. In accordance with 14 CFR Part 21, the following special conditions apply to the Model 45: No. 25-ANM-81 High Altitude Operation (See NOTE 8) No. 25-ANM-88 Lightning and High Intensity Radiated Fields No. 25-707-SC Non-Rechargeable Lithiu m Batteries, effective to design changes applied for after January 4, 2018. See applicability section of this special condition for more information on which design changes must meet it. Exemptions from 14 CFR Part 25 in accordance with 14 CFR Part 11: A. Exemption No. 6021, granted on January 26, 1995. Exemption from 14 CFR 25.571(e)(1) to use Vc at sea level or 0.85 Vc at 8000 feet, whichever is the more critical. B. Exemption No. 6468A, granted on December 29, 1997. Exemption from FAR 25.783(h) to allow the use of the upper half of the two-part cabin door as the required emergency exit. Other requirements of 14 CFR 25.783(h), which relate to emergency exit access, emergency exit lighting etc., as they pertain to Type II emergency exits still apply. C. Exemption No. 10634, granted on September 26, 2012 (see NOTE 20). Exemption from the general occupant pr otection requirements of 14 CFR 25.562(a) Amdt 25-64 and 25.785(b) Amdt 25-72 for a single occupant side-facing seat T00008WI 6 of 26 Rev. 34 I. Model 45 (Learjet 45) (cont’d) Certification Basis (cont’d) Equivalent Safety Findings according to the provisions of 14 CFR Part 21.21(b)(1) for the following subjects: ELOS Memo No. 14 CFR Part: Title N/A 25.841 (b)(6) Hi gh Altitude Airport Operation N/A 25.109 & related para., see NPRM 93-8 Accelerate Stop Distance N/A 25.103 & related para., see NPRM 93-17 1 'g' Stall Speeds N/A 25.811(d)(1)(2) Emergency Exit Sign N/A 25.813(e) Frangible Lavatory Doo r N/A 25.1549; 25.1321 (c) Di gital N2 Indication N/A 25.1549 Di gital Oil Indication N/A 25.1305(a)(1)(4)(5)(6)(c) (1)(2)(3)(6); 25.1549 APU Instruments ST4775WI-T-SE-1 25.1397(c) Wing and Tail Position Lights Chromaticity Requirements Type Certificate Application Date January 27, 1992 Production Basis S/N 45-002 thru 45-455 (See NOTE 6). Equipment The basic required equipment as prescrib ed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. II. Model 45 (Learjet 40), S/N 45-2001 through 45-2133 (see NOTE 6), Learjet (Transport Category), Approved July 11, 2003 Engines Two Honeywell (AlliedSignal Engines) TFE731-20AR or TFE731-20BR-1B turbofan engines, TC E1NM. Eligible part numbers are listed below. Each engine is controlled by a single power lever and by Digital Electronic Engine Control (DEEC) software. Left and right engines must utilize common DEEC part numbers. Engine installation configuration is defined by the Learjet Engineering Change Record (ECR) or ModSum, as noted below. Engine Configuration Designation Model No.: TFE731-( )- 1B Engine P/N DEEC P/N ECR/ ModSum Engine Configurations* interchangeable with: L 20AR 3060082-3 2118882-1007 8756 L/M/N/P M 20AR 3060082-4 2118882-1007 7944 L/M/N/P N 20AR 3060082-6 2118882-1008 045T020412 L/M/N/P P 20AR 3060082-7 2118882-1008 ** L/M/N/P R 20BR 3060084-1 2118882-1008 8266 R S 20BR 3060084-2 2118882-1008 8266 S * Listed engine configurations in each row may be installed single or pairs. ** Installed by Honeywell Engine and Systems Service Bulletin SB TFE 731-72-5120. Requires prior or concurrent incorporation of ECR 8778 or ECR 7599. Fuel See NOTE 15. Engine Limits See NOTE 19. Static thrust, standard day, sea level: APR (5 min.)* 3650 lbs. Takeoff (5 min.)* 3500 lbs. *5 Minutes total at Takeoff or above T00008WI 7 of 26 Rev. 34 II. Model 45 (Learjet 40) (cont’d) Engine Limits (cont’d) Max. permissible engine rotor operating speed: N1 (Fan) steady state 100.1% N1 = 21,021 RPM N2 (Gas gen.) steady state 100% N2 = 31,173 RPM N2 (Gas gen.) APR 101% N2 = 31,485 RPM N1 (Fan) transient (10 sec.) 100.5% N1 = 21,105 RPM N2 (Gas gen.) transient (10 sec.) 102.5% N2 = 31,957 RPM N1 (Fan) (10 sec.) 103.0% N1 = 21,630 RPM* N2 (Gas gen.) (10 sec.) 104.0% N2 = 32,430 RPM* *Reduce power to bring within steady state limits Max. Permissable Interstage Turbine Gas Tempatures Engine Model: TFE731- 20AR-1B TFE731-20BR-1B Part Number: 3060082-3, -4, -6, -7 3060084-1, -2 Takeoff (5 min) 963℃ (A/I on) 941℃ (A/I off) 991℃ APR (5 min) 963 ℃ 1013 ℃ Max. Continuous 941℃ (A/I on) 916℃ (A/I off) 991℃ Max. Cruise 900 ℃ 974 ℃ Starting (below): Starter Assisted 941 ℃ 991 ℃ Windmill 941 ℃ 991 ℃ APU None Airspeed Limits V MO (Maximum Operating) 330 KIAS Sea Level to 26,756 ft. MMO (Maximum Operating) .81 Mach above 26,756 ft. VA (Sea Level) 149 KIAS 12,500 lbs. 155 KIAS 13,500 lbs. 159 KIAS 14,000 lbs. 178 KIAS 17,000 lbs. 192 KIAS 19,200 lbs. 199 KIAS 20,350 lbs. 203 KIAS 21,000 lbs. See AFM for variations with weight, altitude, aircraft serial numbers, and modifications. VB (Speed for maximum gust intensity) 250 KIAS VFE (Flaps extended) Flaps 8 250 KIAS Flaps 20 200 KIAS Ldg Position - Full Flaps 150 KIAS VMCA (Minimum control speed) Air Flaps 8 103 KIAS Flaps 20 100 KIAS T00008WI 8 of 26 Rev. 34 II. Model 45 (Learjet 40) (cont’d) Airspeed Limits (cont’d) VMCG (Minimum control speed) Ground APR On 103 KIAS APR Off 100 KIAS VMCL (Minimum control speed) Landing Flaps 20 105 KIAS Flaps 40 97 KIAS VLO (Landing gear operating) 200 KIAS VLE (Landing gear extended) 260 KIAS Max. tire ground speeds: Nose Gear Tire 210 MPH Main Gear Tire 190 MPH C.G. Range Maximum Design C.G. Limits (Landing Gear Extended) (1) AFT Flight Limit: FS 434.27 (23.5% MAC) at 13,500 lbs. and tapers to FS 438.19 (28.0% MAC) at 15,000 lbs. and remains at FS 438.19 (28.0% MAC) up to and including 20,600 lbs. (Max Ramp Weight). For A/C modified by SB 40-11-1, the aft C.G. Limit of 438.19 (28% MAC) is extended to 21,000 lbs. It then extends to FS 437.41 (27.1% MAC) at 21,250 lbs. (Max Ramp Weight). (2) FWD Flight Limit: FS 419.88 (7% MAC) for weights at 13,500 lbs. up to and including 15,000 lbs. and tapers to FS 425.98 (14% MAC) at 18,500 lbs. then to FS 427.35 (15.57% MAC) at 19,200 lbs. then to FS 430.08 (18.7% MAC) at 20,600 lbs. (Max Ramp Weight). For A/C modified by SB 40-11-01, the forward C.G. Limit extends to FS 430.86 (19.6% MAC) at 21,000 lbs. and then to FS 431.35 (20.2% MAC) at 21,250 lbs. (Max Ramp Weight). See AFM, Section I, for additional approved limits. Datum 99.56 inches fwd of nose. Wing jack points are at STA 468.00. Fuselage jack point is at STA 183.46. MAC 87.215 (L.E. of MAC 413.769) Leveling Means Lateral and longitudinal leveling ma rks are provided at FS 613.768. See Maintenance Manual or LES 1427 for leveling instructions. A/C modified by SB 40-11-1 Maximum Weight (lbs.) Ramp 20,600 lbs. 21,250 lbs. Takeoff 20,350 lbs. 21,000 lbs. Landing 19,200 lbs. 19,200 lbs. Zero Fuel 16,000 lbs. 16,000 lbs. Minimum Flight Weight 13,500 lbs. 13,500 lbs. See AFM, maximum weights vary with serial numbers and modifications. Minimum Crew For all flights: two persons (pilot and co-pilot) No. of Seats 9 (two pilots, seven passengers) (See NOTE 13 for optional seating configuration) Maximum Baggage Cabin: 170 lbs. Arm 425 inches Tail compartment: 500 lbs. Arm 544 inches Floor loading density: 75 psf T00008WI 9 of 26 Rev. 34 II. Model 45 (Learjet 40) (cont’d) Fuel Capacity (gal.) Usable 802 gal. Weight 5375 lbs. Arm 458 inches See NOTE 1 for data on unusable fuel. See NOTE 14 for Fuel Capacity Increased Range Option Oil Capacity (gal.) Two engine mounted tanks: Total 3.8 gal. Arm 519 inches (1.9 gal. each) (tank plus system) See NOTE 1 for data on unusable oil. Max. Operating Altitude 51,000 feet Control Surface Movements For proper ri gging instructions see the Maintenance Manual or the specific Learjet Engineering Specification - Functional Test listed below for the individual control system. Horizontal Stabilizer Riggi ng Instructions: LES-FT-1981 Primary Trim -0.30° to -0.55 ° L E UP -9.25° to -9.50° L E DN Secondary Trim -0.30° to -0.55 ° L E UP -9.25° to -9.50° L E DN Elevator Rigging Instructions: LES-FT-1976 15.0° ± 0.5° Trailing Edge UP 15.5° ± 0.5° Trailing Edge DN Rudder Rigging Instructions: LES-FT-1976 30° + 2.0°/– 1.0° Trailing Edge Left 30° + 2.0°/– 1.0° Trailing Edge Right Rudder trim Rigging Instructions: LES-FT-1979 20° ± 1° Trailing Edge Left 20° ± 1° Trailing Edge Right Aileron Rigging Instructions: LES-FT-1976 from faired position 18.0° + 1.0°/– 0.0° Trailing Edge DN >18.0° Trailing Edge UP droop position 3.1° ± 0.2° down from faired Aileron Trim Rigging In structions: LES-FT-1979 15.0° ± 1.0° Trailing Edge UP 15.0° ± 1.0° Trailing Edge DN Flaps Rigging Instructions: LES-FT-1973 Flap Position Allowable Tolerance 0° Rig Position 8° ± 1° 20° ± 1° 40° ± 2° Spoiler/Spoileron Rigging Instructions: LES-FT-1766 First partial detent: 14.5° ± 2.0° Second partial detent: 28.5° ± 2.0° EXT detent: 60.0° ± 2.0° Spoileron Mode: 60.0° ± 2.0° Serial Nos. Eligible 45-2001 th ru 45-2133 (See NOTES 6 and 21). Certification Basis 14 CFR Part 25, Airworthiness Standards: Transport Category Airplanes, effective February 1, 1965, including Amendments 25-1 through Amendment 77. In addition, the following regulation at the specified Amendment applies: 14 CFR 25.856 Amdt 25-111 for all changes where application is made after September 2, 2005. T00008WI 10 of 26 Rev. 34 II. Model 45 (Learjet 40) (cont’d) Certification Basis (cont’d) In addition, the following regulations at the specified Amendments apply: 14 CFR 25.899 Amdt 25-123, 25.981 Amdt 25-102, 25.1353 Amdt 25-113, for the Passenger Communication System. In addition, the following regulations at the specified Amendments apply: 14 CFR 25.981 Amdt 25-102, for the Brake System Timing Change (ModSum 045T026230). 14 CFR Part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, effective September 10, 1990, including Amendments 34-1 through 34-2. 14 CFR Part 36, Noise Standards: Aircraft Type Certification and Airworthiness Certification, effective December 1, 1969, including Amendments 36-1 through 36-28. Compliance with Section 44715(e) of Title 49 U.S.C. (Noise Control Act of 1972) Optional Design Regulations: 14 CFR 25.801 ditching not complied with. In accordance with 14 CFR Part 21, the following special conditions apply to the Model 45: No. 25-ANM-81 High Altitude Operation (See NOTE 8) No. 25-ANM-88 Lightning and High Intensity Radiated Fields No. 25-707-SC Non-Rechargeable Lithiu m Batteries, effective to design changes applied for after January 4, 2018. See applicability section of this special condition for more information on which design changes must meet it. Exemptions from 14 CFR Part 25 in accordance with 14 CFR Part 11: A. Exemption No. 6021, granted on January 26, 1995. Exemption from 14 CFR 25.571(e)(1) to use Vc at sea level or 0.85 Vc at 8000 feet, whichever is the more critical. B. Exemption No. 6468A, granted on December 29, 1997. Exemption from FAR 25.783(h) to allow the use of the upper half of the two-part cabin door as the required emergency exit. Other requirements of 14 CFR 25.783(h) which relate to emergency exit access, emergency exit lighting etc., as they pertain to Type II emergency exits still apply. C. Exemption No. 10634, granted on September 26, 2012 (see NOTE 20). Exemption from the general occupant pr otection requirements of 14 CFR 25.562(a) Amdt 25-64 and 25.785(b) Amdt 25-72 for a single occupant side-facing seat. Equivalent Safety Findings according to the provisions of 14 CFR Part 21.21(b)(1) for the following subjects: ELOS Memo No. 14 CFR Part: Title N/A 25.841 (b)(6) Hi gh Altitude Airport Operation N/A 25.109 & related para., see NPRM 93-8 Accelerate Stop Distance N/A 25.103 & related para., see NPRM 93-17 1 'g' Stall Speeds N/A 25.811(d)(1)(2) Emergency Exit Sign N/A 25.813 (e) Fran gible Lavatory Door N/A 25.1549; 25.1321 (c) Di gital N2 Indication N/A 25.1549 Di gital Oil Indication N/A 25.1305(a)(1)(4)(5)(6)(c) (1)(2)(3)(6); 25.1549 APU Instruments ST4775WI-T-SE-1 25.1397(c) Wing and Tail Position Lights Chromaticity Requirements T00008WI 11 of 26 Rev. 34 II. Model 45 (Learjet 40) (cont’d) Production Basis 45-2001 thru 45-2133 (See NOTE 6). Equipment The basic required equipment as prescrib ed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. III. Model 45 (Learjet 75), S/N 45-456 through 45-2000 (S ee NOTE 6), Learjet (Transport Category), Approved November 13, 2013 Engines Two Honeywell (Honeywell International Inc.) TFE731-40BR-1B turbofan engines, TC E1NM. Eligible part numbers are listed below. Each engine is controlled by a single power lever and by Digital Electronic Engine Control (DEEC) software. Left and right engines must utilize common DEEC part numbers. Engine installation configuration is defined by the Learjet ModSum as noted below. Engine Configuration Designation Model No.: TFE731-( )- 1B Engine P/N DEEC P/N ECR/ ModSum Engine Configurations interchangeable with: T 40BR 3062075-1 2118882-8001 045T010267 T Fuel See NOTE 15. Engine Limits See NOTE 19. Static thrust, standard day, sea level: APR (5 min.)* 3850 lbs. Takeoff (5 min.)* 3850 lbs. *5 Minutes total at Takeoff or above: All Engines Operating *10 Minutes total at Takeoff or above: One Engine Inoperative Max. permissible engine rotor operating speed: N1 (Fan) steady state 100.1% N1 = 21,021 RPM N2 (Gas gen.) steady state 100% N2 = 31,485 RPM N2 (Gas gen.) APR 101% N2 = 31,800 RPM N1 (Fan) transient (10 sec.) 100.5% N1 = 21,105 RPM N2 (Gas gen.) transient (10 sec.) 102.5% N2= 32,277 RPM N1 (Fan) (10 sec.) 103.0% N1 = 21,630 RPM* N2 (Gas gen.) (10 sec.) 103.0% N2 = 32,430 RPM* *Reduce power to bring wi thin steady state limits Max. Permissable Interstage Turbine Gas Tempatures Engine Model: TFE731-40BR-1B Part Number: 3062075-1 Takeoff (5 min)* 1000°C APR (5 min)* 1022°C Max. Continuous 991°C Max. Cruise 974 ℃ Starting (below): Starter Assisted 991 ℃ Windmill 991 ℃