# TCDS T00008WI: Learjet Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Learjet Inc.
- Revision: 34
- Revised: June 8, 2026
- Product: Aircraft, Large Airplane
- Certification basis: Part 25
- Registered aircraft: 433, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/00/31/00317751673bb2ec3b346131ef133c115065ceb54b271341c1810ee740ae1bed
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID173477243220260610144929.0001
- Page: https://openairdocs.org/tcds/T00008WI

## Models (1)

As the data sheet lists them.

- 45

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
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 ℃ 
*5 minutes for All Engines Operating 
*10 minutes for One Engine Inoperative 
 
APU Honeywell International Inc. RE 100[LJ] APU (formerly AlliedSignal) 
 
APU Limits 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 AFM for additional limits.

T00008WI 12 of 26  Rev. 34 
III. Model 45 (Learjet 75)  (cont’d) 
 
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 
 
VFE (Flaps extended) 
Flaps 8  250 KIAS 
Flaps 20  200 KIAS 
Ldg Position - Full Flaps 150 KIAS 
 
VMCA (Minimum control speed) Air 
Flaps 8  107 KIAS 
Flaps 20  107 KIAS 
 
VMCG (Minimum control speed) Ground 
APR On/Off 105 KIAS 
 
VMCL (Minimum control speed) Landing 
Flaps 8 110 KIAS 
Flaps 40 102 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) 
 
AFT Flight Limit: FS 435.57 (25.0% MAC) at 14,000 lb s. 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 21,000 lbs. then 
to FS 435.84 (25.3% MAC) at 21,750 lbs. (Max Ramp Weight). 
 
FWD Flight Limit: FS 416.82 (3.5% MAC) for weights at  14,000 lbs. up to and including 16,250 lbs. and  
tapers to FS 419.87 (7.0% MAC) at 18,000 lbs. then to FS 430.77 (19.5% MAC) at 
21,750 lbs. (Max Ramp Weight). 
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)

T00008WI 13 of 26  Rev. 34 
III. Model 45 (Learjet 75)  (cont’d) 
 
Maximum Weight (lbs.) Ramp 21,750 lbs. 
Takeoff 21,500 lbs. 
Landing 19,200 lbs. 
Zero Fuel 16,000 lbs.* 
Minimum Flight Weight 14,000 lbs. 
*16,500 lbs. for aircraft modified with SB75-11-01 
See AFM, maximum weights vary with serial numbers and modifications. 
 
Leveling Means Lateral and longitudinal leveling ma rks are provided at FS 613.768.  See Maintenance 
Manual or LES 1427 for leveling instructions. 
 
Minimum Crew For all flights: 2 persons (pilot and co-pilot) 
 
No. of Seats 11 (2 pilots, 9 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 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

T00008WI 14 of 26  Rev. 34 
III. Model 45 (Learjet 75)  (cont’d) 
 
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 45-456 thru  45-2000 (See NOTE 6 and NOTE 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. 
 
In addition, the following regulations at the specified Amendments apply:  
14 CFR 25.981 Amdt 25-102 for the Garmin G5000 Avionics System, the Electronic 
Standby Instrument System, the DME, the Radio Altimeter, the CVR, the ELT, the 
Emergency Battery, the Cockpit Lighting System, the Winglet Installation, Passenger 
Communication System, the Interior Furnishings and Floorplan, the Passenger Cabin 
Systems & Equipment, and. the Brake System Timing Change (ModSum 045T026230). 
 
In addition, the following regulations at the specified Amendments apply:  
14 CFR 25.899 Amdt 25-123, 25.1316 Amdt 25-80, 25.1317 Amdt 25-122, 25.1353 
Amdt 25-113 for the Garmin G5000 Avionics System, the Electronic Standby Instrument 
System, the DME, the Radio Altimeter, the CVR, the FDR, the ELT, the Emergency 
Battery, the Cockpit Lighting System, the TFE731-40BR engine installation, the Winglet 
Installation, Passenger Communication System, Nose Oxygen Cylinder Assy, the Interior 
Furnishings and Floorplan, and the Passenger Cabin Systems & Equipment. 
 
In addition, the following regulations at the specified Amendments apply:  
14 CFR 25.1457 Amdt 25-124 for the Garmin G5000 Avionics System when equipped 
with ACARS and FANS 1/A+. 
 
In addition, the following regulations at the specified Amendments apply:  
14 CFR 25.101 Amdt 25-92, 25.105 Amdt 25-92, 25.109 Amdt 25-92, 25.113 Amdt 25-
92, 25.1533 Amdt 25-92, for Learjet Runway Performance Improvement (ModSum 
077T026771). 
 
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.

T00008WI 15 of 26  Rev. 34 
III. Model 45 (Learjet 75)  (cont’d) 
Certification Basis (cont’d) 
 
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 Intens ity Radiated Fields (See NOTE 17) 
No. 25-501-SC Aircraft Electronic System Security Protection from 
  Unauthorized External Access 
No. 25-502-SC Isolation or Security Protect ion of the Aircraft Control Domain  
  and the Airline Information Services Domain from the 
  Passenger Services Domain 
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 conditi on 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 protection 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) High 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) Emer gency Exit Sign 
N/A 25.813(e) Frangible Lavatory Doo r 
N/A 25.1549, 25.1321(c)  Digital N2 Indication 
N/A 25.1549 Digital 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 
ST5386WI-T-SE-5 25.1303(a)(3),  25.1327, 25.1547 Use of an Electric-Only Direction  Indicator Standby Instrumentation 
ST5386WI-T-P-1 25.901, 25.1305, 25.1309, 25.1321, 25.1322, 25.1549 Digital-Only Display of Turbine Engine High Pressure Rotor Speed (N2), Oil Pressure and Oil Temperature 
ST05908WI-T-A-1 25.811 (d)(1)(2) Emer gency Exit Marking 
 
 Additional Design Requirements and Conditions 
The following design details or information must be maintained to ensure that an unsafe 
design condition is not present:

T00008WI 16 of 26  Rev. 34 
III. Model 45 (Learjet 75)  (cont’d) 
 
In-Flight Engine Restart 
A minimum restart capability after an all-engines-out scenario must be established  
under the following conditions using procedures provided in the AFM: 
1. During the take-off and the initial climb-out portion of the flight, the airplane should 
have the capability for the flightcrew to restore engine power immediately following 
an all-engine-out scenario and when the fuel source to the engine is restored. 
2. During the high altitude portion of the fl ight at cruise speed and maximum altitude, 
the airplane should have the capability for the flightcrew to restart engines from a 
stabilized windmill speed prior to descending below an altitude of 15,000 feet, by 
showing either or both: 
a) All but one engine s hould be restarted and accelerated to produce maximum 
 continuous thrust/power, or  
b) The engine(s) should be restarted, and the necessary thrust/power achieved,  
 to enable the airplane to maintain level flight.  
3. During flight at speeds greater than the minimum flaps-up “holding speed” and at 
altitudes below 20,000 feet, the airplane should have the capability for the flightcrew 
to restart engines from a stabilized windmill speed prior to descending 5000 feet 
from the initiation of the restart procedure and prior to exceeding an airspeed of 300 
knots, by showing either or both: 
a) All but one engine s hould be restarted and accelerated to produce maximum 
 continuous thrust/power, or  
b) The engine(s) should be restarted, and the necessary thrust/power achieved,  
 to enable the airplane to maintain level flight.  
 
Production Basis  45-456 thru 45-2000 (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. 
 
IV. Model 45 (Learjet 70), S/N 45-2134 through 45-4000 (See  NOTE 6), Learjet (Transport Category), Approved  
 November 13, 2013 
 
Engines Two Honeywell (Honeywell Internationa l Inc.) TFE731-40BR 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: 
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

T00008WI 17 of 26  Rev. 34 
IV. Model 45 (Learjet 70)  (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 = 31,485 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 within 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 ℃ 
*5 minutes for All Engines Operating 
*10 minutes for One Engine Inoperative 
 
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. 
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 
  
VFF (Flaps extended) 
Flaps 8  250 KIAS  
Flaps 20  200 KIAS   
Ldg Position - Full Flaps 150 KIAS  
  
VMCA (Minimum control speed) Air 
Flaps 8  107 KIAS 
Flaps 20 107 KIAS

T00008WI 18 of 26  Rev. 34 
IV. Model 45 (Learjet 70)  (cont’d) 
Airspeed Limits (cont’d)  
 
VMCG (Minimum control speed) Ground 
APR On/Off 105 KIAS 
 
VMCL (Minimum control speed) Landing 
Flaps 8 110 KIAS 
Flaps 40 102 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 21,000 lbs. then to FS 
435.84 (25.3% MAC) at 21,750lbs. (Max Ramp Weight).  
  
(2) FWD Flight Limit: FS 419.88 (7.0% MAC) for weights at 13,500 lbs. up to and including 15,000 lbs. and 
tapers to FS 425.98 (14.0% MAC) at 18,500 lbs. then to FS 432.52 (21.5% MAC) at 
21,750 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.  
 
Maximum Weight (lbs.) Ramp 21,750 lbs. 
Takeoff 21,500 lbs. 
Landing 19,200 lbs. 
Zero Fuel 16,000 lbs. 
Minimum Flight Weight 13,500 lbs. 
 
See AFM, maximum weights vary with serial numbers and modifications. 
 
Minimum Crew For all flights: 2 persons (pilot and co-pilot)  
  
No. of Seats 9 (2 pilots, 7 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.

T00008WI 19 of 26  Rev. 34 
IV. Model 45 (Learjet 70)  (cont’d) 
 
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 45-2134 thr ough 45-4000 (See NOTE 6 and NOTE 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. 
 
In addition, the following regulations at the specified Amendments apply:  
14 CFR 25.981 Amdt 25-102 for the Garmin G5000 Avionics System, the Electronic 
Standby Instrument System, the DME, the Radio Altimeter, the CVR, the ELT, the 
Emergency Battery, the Cockpit Lighting System, the Winglet Installation, Passenger 
Communication System, the Interior Furnishings and Floorplan, the Passenger Cabin 
Systems & Equipment, and the Brake System Timing Change (ModSum 045T026230).

T00008WI 20 of 26  Rev. 34 
IV. Model 45 (Learjet 70)  (cont’d) 
Certification Basis (cont’d) 
 
In addition, the following regulations at the specified Amendments apply:  
14 CFR 25.899 Amdt 25-123,  25.1316 Amdt 25-80, 25.1317 Amdt 25-122, 25.1353 
Amdt 25-113 for the Garmin G5000 Avionics System, the Electronic Standby Instrument 
System, the DME, the Radio Altimeter, the CVR, the FDR, the ELT, the Emergency 
Battery, the Cockpit Lighting System, the TFE731-40BR engine installation, the Winglet 
Installation, Passenger Communication System, Nose Oxygen Cylinder Assy, the Interior 
Furnishings and Floorplan, and the Passenger Cabin Systems & Equipment. 
 
In addition, the following regulations at the specified Amendments apply:  
14 CFR 25.1457 Amdt 25-124 for the Garmin G5000 Avionics System when equipped 
with ACARS and FANS 1/A+. 
 
In addition, the following regulations at the specified Amendments apply:  
14 CFR 25.101 Amdt 25-92, 25.105 Amdt 25-92, 25.109 Amdt 25-92, 25.113 Amdt 25-
92, 25.1533 Amdt 25-92, for Learjet Runway Performance Improvement (ModSum 
077T026771). 
 
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 Intens ity Radiated Fields (See NOTE 17) 
No. 25-501-SC Aircraft Electronic System Security Protection from 
Unauthorized External Access 
No. 25-502-SC Isolation or Security Protect ion of the Aircraft Control Domain  
and the Airline Information Services Domain from the 
Passenger Services Domain 
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 protection 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 21 of 26  Rev. 34 
IV. Model 45 (Learjet 70)  (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 25.1305(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 
ST5386WI-T-SE-5 25.1303(a)(3),  25.1327, 25.1547 Use of an Electric-Only Direction  Indicator Standby Instrumentation 
ST5386WI-T-P-1 25.901, 25.1305, 25.1309, 25.1321, 25.1322, 25.1549 Digital-Only Display of Turbine Engine High Pressure Rotor Speed (N2), Oil Pressure and Oil Temperature 
 
Additional Design Requirements and Conditions 
The following design details or information must be maintained to ensure that an unsafe 
design condition is not present: 
 
In-Flight Engine Restart 
A minimum restart capability after an all-engines-out scenario must be established under 
the following conditions using procedures provided in the AFM: 
1. During the take-off and the initial climb-out portion of the flight, the airplane should 
have the capability for the flightcrew to restore engine power immediately following 
an all-engine-out scenario and when the fuel source to the engine is restored. 
2. During the high-altitude portion of the fli ght at cruise speed and maximum altitude, 
the airplane should have the capability for the flightcrew to restart engines from a 
stabilized windmill speed prior to descending below an altitude of 15,000 feet, by 
showing either or both: 
a) All but one engine s hould be restarted and accelerated to produce maximum 
 continuous thrust/power, or  
b) The engine(s) should be restarted, and the necessary thrust/power achieved,  
 to enable the airplane to maintain level flight.  
3. During flight at speeds greater than the minimum flaps-up “holding speed” and at 
altitudes below 20,000 feet, the airplane should have the capability for the flightcrew 
to restart engines from a stabilized windmill speed prior to descending 5000 feet 
from the initiation of the restart procedure and prior to exceeding an airspeed of 300 
knots, by showing either or both: 
a) All but one engine s hould be restarted and accelerated to produce maximum 
 continuous thrust/power, or  
b) The engine(s) should be restarted, and the necessary thrust/power achieved,  
 to enable the airplane to maintain level flight.  
 
Production Basis S/N 45-2134 thru 45-4000 (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.

T00008WI 22 of 26  Rev. 34 
NOTES 
 
NOTE 1. The current weight an d balance report, loading instructions (when necessary), and a list of equipment included 
in the certificated empty weight must be provided for each airplane at the time of original airworthiness 
certification. 
 
The certified empty weight and corresponding center of gravity location must include: 
 
 WEIGHT (lbs.) ARM (in.) 
Hydraulic Fluid 21.5 473 
Unusable Fuel  93.1 427 
Trapped Fuel 14.0 425 
Engine Trapped Oil (each) 8.8 513 
Engine Drainable Oil (each) 13.6 526 
 
NOTE 2. FAA Approved AFM: The airplane  must be operated according to the appropriate FAA Approved AFM.  The 
placards specified in the Maintenance Manual, part number MM-104 for the Learjet 45 MM-105 for the Learjet 
40, MM-106 for the Learjet 70 and MM-107 for the Learjet 75 (latest approved revision), or equivalent 
production drawings, must be displayed.  For the Learjet 45, S/N 45-368, see NOTE 18. 
 
NOTE 3. FAA approved Airworthiness Limitations for mandatory compliance retirement life or inspection are included 
in the Maintenance Manual (Instructions for Continued Airworthiness), Chapter 4. 
 
NOTE 4. Certification Maintenance Requirements (CMR) are found in:  
 
Maintenance Manual MM-104, Chapter 4, for Learjet 45 and MM-105, Chapter 4, for Learjet 40.  Engineering 
approval of the CMR is documented in Learjet Report 45-D1503. 
 
Maintenance Manual MM-106, Chapter 4, for the Learjet 70 and Maintenance Manual MM-107, Chapter 4, for 
the Learjet 75 and the Learjet 45, S/N 45-368 (see NOTE 18).  Engineering approval of the CMR is 
documented in Learjet Reports 45-D1503 and 45-D2194. 
 
NOTE 5. All replacement seats (crew an d passenger) and foam cushion construction deviations even though compliant 
with TSO C127, must be evaluated for their impact to the surrounding seat envelope (i.e. cabinet changes, 
galley changes, sidewall changes, floor plan changes, etc.) and its certification effect on 14 CFR 25.562(c)(5) 
and the applicable parts of 25.803 through 25.815.  These items must demonstrate compliance with the 
requirements of 14 CFR paragraphs 25.333, 25.561, 25.562, 25.785, and 25.853 as applicable. 
 
NOTE 6. Learjet 45 (Model 45, S/N 45-002 thru 45-455) is defined by Learjet Engineering Change Record ECR 4601. 
 
Learjet 40 (Model 45, S/N 45-2001 thru 45-2133) is defined by Learjet Engineering Configuration Statement 
RAL-045-CP223. 
 
Learjet 75 (Model 45, S/N 45-456 thru 45-2000) is defined by Learjet Engineering drawing 4500080801-
XXXX. (XXXX represents the S/N for the airplane concerned).  
 
Learjet 70 (Model 45, S/N 45-2134 thru 45-4000) is defined by Learjet Engineering drawing 4500080801-
XXXX. (XXXX represents the S/N for the airplane concerned). 
 
Model 45, S/N 45-446, when modified by ModSums 045T023813, 045T010268, 045T010241, 045T010242, 
045T010267, is in the Learjet 75 configuration. 
 
Model 45, S/N 45-2129, when modified by ModSums 045T023813, 045T010268, 045T010241, 045T010242, 
045T010267, is in the Learjet 70 configuration.

T00008WI 23 of 26  Rev. 34 
 
NOTE 7. The approved minimum aisle width below 25 inches from the floor is (9.0) inches in accordance with  
14 CFR 25.815.  Approval of the minimum aisle width is documented in Learjet Report ER-221, Rev. B, page 
31, Section 6-10.  The approved Type Design aisle width above 25 inches includes an intrusion due to the 
padding on the seatbacks as defined by Learjet Dwg. No. 4525203000, "Upholstery Assy, Passenger Seat", for 
aircraft S/N 45-002 thru 45-231.  For aircraft S/N 45-232 thru S/N 45-367, S/N 45-369 thru S/N 45-445, S/N 
45-447 thru S/N 45-455 and S/N 45-2001 thru S/N 45-2128, refer to Learjet Dwg No. M6613100.  Floorplan 
45-7 (LJ40 Configuration) refers to Learjet Engineering Report 45-D2005 approved under Modsum 
045T022329.  Floorplan FP45-3B, refers to Learjet Engineering Report 45-D2215, approved under Modsum 
045T023617.  Floorplan 45-5A, refers to Learjet Engineering report 45-D-2253, approved under Modsum 
045T023630.  The Learjet 75 Seven Passenger Floor Plan refers to Learjet Engineering Report No. 45-D6038, 
approved under Modsum 045T024322.  Any modifications to the interior that changes the seats, aisle width, or 
layout shall be coordinated with the Central Certification Branch (formerly Wichita Aircraft Certification 
Office) or substantiated with FAA approved compliance data from Learjet, Inc. 
 
NOTE 8. The Learjet Model 45 is the subject of a Special Condition related to operation at high altitude.  This special 
condition includes pressurization system requirements, as well as damage tolerance requirements on the 
pressure vessel.  Therefore, any changes to the pressurization system or modifications or repairs to the pressure 
vessel must be approved in accordance with the requirements defined in the special condition. 
 The damage tolerance requirements in the special conditi on are specified in terms of cabin altitude time history, 
which is a function of the cabin leak rate.  For Learjet Model 45 specified cabin altitude time history 
requirement can be met with a pressure vessel opening of 1.9 square inches, (assuming an emergency descent).  
The determination of an equivalent crack length will depend upon the location of the crack, the pressure vessel 
configuration in that location, and the direction of the crack, etc.  The approval of modifications and/or repairs 
must consider the requirements of the special condition and how they apply to the location and configuration 
being modified or repaired.  The resulting inspection program must also consider other applicable structural 
criteria.  Engineering Approval is documented in Learjet Report No. 45-D1185, Paragraph 3.16, for Learjet 
45/75 (Model 45, S/N 45-002 thru 45-2000) or Learjet Report No. 45-D1184, Appendix G, for Learjet 40/70 
(Model 45, S/N 45-2001 thru 45-4000). 
 
NOTE 9. Learjet Model 45 has been validated by the Joint Aviation Authorities (JAA) of Europe and has received Type 
Certificates (or equivalent) from the European National Airworthiness Authorities based on this validation. The 
Learjet 40 configuration was validated by European Aviation Safety Agency (EASA) and is therefore approved 
in all EU Member States.  Any major changes to the airplane without consultation with Learjet Inc. may result 
in the ineligibility of the airplane to be exported to one of these countries. 
 
NOTE 10. ECR 4684 is a prior or concurrent requirement for export of a Model 45 (Learjet 45 and Learjet 40) to any 
JAA/EASA member country.  In addition, Learjet 45 and Learjet 40 aircraft must be modified in accordance 
with the applicable ECR listed below to be eligible for export to a particular country. 
 
ECR No. Country Public/Private 
4685 German y Private 
4686 German y Public 
4841 Austria Private 
4903 Austria Public 
4907 Belgiu m Private 
4720 Bel gium Public 
4907 Luxembour g Private 
4723 Luxembour g Public 
7531 Ital y Private 
7530 Ital y Public 
4909 Switzerlan d Private 
4729 Switzerlan d Public 
7801 Denmar k Private 
7800 Denmar k Public 
6619 Finlan d Private 
6618 Finlan d Public 
4910 United Kin gdom Private 
4731 United Kin gdom Public 
8152 S pain Public

T00008WI 24 of 26  Rev. 34 
NOTE 10 (cont’d) 
 
Learjet 45 is eligible for export to the following non-JAA/EASA countries when modified in accordance with 
the ECRs listed below: 
 
ECR No. Country Public/Private 
4461 Ar gentina Private 
4460 Argentina Public 
4719 Australia Public 
4724 Brazil Private 
6588 Brazil Public 
7844 Canada Private 
4721 Canada Public 
4807 South Africa Private 
4869 South Africa Public 
7719 E gypt Private 
7718 E gypt Public 
6621 Phili ppines Private 
4727 Philippines Public 
7583 Cayman Islands Private 
4725 Mexico Private 
6587 Mexico Public 
6589 Sin gapore Private 
4728 Singapore Public 
 
Learjet 40 is eligible for export to the following non-JAA/EASA countries when modified in accordance with 
the ECRs listed below: 
 
ECR No. Country Public/Private 
4461 Argentina Private 
4460 Argentina Public 
7844 Canada Private 
4721 Canada Public 
4725 Mexico Private 
6587 Mexico Public 
 
Learjet 70/75 is eligible for export to the following non JAA/EASA countries when modified in accordance 
with the ModSums listed below: 
 
ModSum No. Country Public/Private 
045T024072 Canada Private 
045T024071 Canada Public 
 
NOTE 11. Learjet 45, Learjet 40, Learjet 70 , and Learjet 75 have been shown to meet the airworthiness requirements for 
operations in Reduced Vertical Separation Minimum (RVSM) airspace between 29,000 and 41,000 feet.  No 
Service Bulletin is associated with this requirement.  All serial numbers are eligible.  Airworthiness approval is 
documented in FAA approved ECR 7539 (for Learjet 40 and 45) or ModSum 045T023846 (for Learjet 70 and 
75) or ModSum 045T010296 (for the Learjet 45, S/N 45-368 (see NOTE 18) and Learjet Compliance Report 
No. 45-D1665, RVSM Compliance and Data Analysis, M45. 
 
NOTE 12. Deleted. 
 
NOTE 13. Maximum number of occupant s: 10 (two crew, eight passengers) 
The following optional seating configuration is approved:  
 
Ref. Floorplan 45-7 (Learjet 40 configuration) 
Ref. Modsums 045T022329 and 045T022874

T00008WI 25 of 26  Rev. 34 
 
NOTE 14. Fuel Capacity Increased Range Option (applicable to Learjet 40 only): 
 
Usable: 905 gals. Weight: 6062 lbs. Arm: 460 inches 
 
Ref. Modsum 045T022958 
 
NOTE 15. The following fuels are approved: 
 
United States Commercial Specifications 
ASTM D 1655 – Jet A 
ASTM D 1655 – Jet A-1 
 
United States Military Specifications 
MIL-DTL-5624 – Grade JP-5 
MIL-DTL-83133 – Grade JP-8 
MIL-DTL-83133 – Grade NATO F-35 
MIL-DTL-83133 – Grade JP-8+100 
 
Canadian Specifications 
CAN/CGSB-3.24 – Grade F-44 
CAN/CGSB-3.23 – Grade F-34 
 
NATO Designations 
NATO F-34 – (Grade JP-8 with FSII) 
NATO F-35 – (Grade JP-8 without FSII) 
NATO F-37 – (Grade JP-8+100) 
NATO F-44 – (Grade JP-5) 
 
People’s Republic of China Specifications 
GB6537 – RP-3 Jet Fuel 
GB6537 – No. 3 Jet Fuel 
 
Russian/Commonwealth of Independent States 
GOST 10227-86, or later editions, (Kerosene) TS-1 
 
United Kingdom Specifications 
Def Stan 91-86 – Grade AVCAT/FSII 
Def Stan 91-87 – Grade AVTUR/FSII 
Def Stan 97-97 – Type Jet A-1 
 
NOTE 16. Learjet 75 and Learjet 70 incorporate integrated avionics using software-based Line Replaceable Units (LRU) 
which share a digital signal transmission bus. The avionics configuration of the Learjet 75 and Learjet 70 as 
delivered from production is critical to maintain security against external and internal intrusions of the 
electronics system which enable safe operation of the aircraft.  Modification to the LRU software supplied with 
the Learjet 75 and Learjet 70, replacement of an LRU with a different LRU, addition of new LRU, or alteration 
of an LRU interface could adversely affect the airworthiness of the certified product.  Accordingly, no major 
changes to the integrated avionics may be made without coordination with the FAA Certificate Management 
Office for the Learjet 75 and Learjet 70 TC. 
 
NOTE 17. Applies only to changes that do not affect the Garmin G5000 Avionics System, the Electronic Standby 
Instrument System, the DME, the Radio Altimeter, the CVR, the FDR, the ELT, the Emergency Battery, the 
Cockpit Lighting System, the TFE731-40BR engine installation, the Winglet Installation, Passenger 
Communication System, Nose Oxygen Cylinder Assy, the Interior Furnishings and Floorplan, and the 
Passenger Cabin Systems & Equipment

T00008WI 26 of 26  Rev. 34 
 
NOTE 18. Learjet 45, S/N 45-368, has been modified to inco rporate the Learjet 75 Performance Modification Package.   
 
Learjet 45, S/N 45-368, incorporating the Learjet 75 Performance Modification Package, consisting of 
ModSums 045T023813, 045T010241, 045T010242, and 045T010268, the following applies: 
Maintenance Manual No. MM-107 and AFM No. FM-134, revisions prior to reissue A, in conjunction with 
AFMS W1649. 
 
Learjet 45, S/N 45-368, incorporating the Learjet 75 Performance Modification Package, for the C.G. Range 
(Landing Gear Extended) FWD Flight Limit, the following applies:  FS 416.82 (3.5% MAC) for weights at 
14,000 lbs., up to and including 16,250 lbs., and tapers to FS 419.87 (7.0% MAC) at 18,000 lbs., then to FS 
430.77 (19.5% MAC) at 21,750 lbs. (Max Ramp Weight). 
 
NOTE 19. All listed N1 rpm values are used for installed indica tions (%) and are higher than actual engine rpms based on 
the value of Honeywell installed indication tolerance of ± 0.15% (32 rpm). 
 
NOTE 20. Applicable only to th e following serial numbers:  
Learjet 45, S/N 45-368 and 45-446.   
Learjet 40, S/N 45-2129.   
Learjet 70, S/N 45-2134 thru 45-4000.   
Learjet 75, S/N 45-456 thru 45-2000.   
 
NOTE 21. It is acceptable to refe r to all configurations of the Model 45 aircraft serial numbers either with, or without, the 
"45-" prefix (e.g., 45-2345 and 2345 are both acceptable serial numbers). 
 
 
 
---- END ----
```

## ADs (27, in force first)

- [AD 2023-01-05](https://openairdocs.org/ad/2023-01-05): Pneumatic · Learjet 45. Effective Mar 9, 2023
- [AD 2021-23-08](https://openairdocs.org/ad/2021-23-08): Wing, Center Box · Learjet 45. Effective Jan 10, 2022
- [AD 2021-23-11](https://openairdocs.org/ad/2021-23-11): Powerplant System · Learjet 45. Effective Jan 10, 2022
- [AD 2015-12-06](https://openairdocs.org/ad/2015-12-06): Fuselage · Learjet 45. Effective Jul 21, 2015
- [AD 2014-13-06](https://openairdocs.org/ad/2014-13-06): Engine Exhaust · Learjet 45. Effective Aug 19, 2014
- [AD 2013-14-07](https://openairdocs.org/ad/2013-14-07): Equipment/Furnishings · Learjet 45. Effective Aug 26, 2013
- [AD 2012-08-08](https://openairdocs.org/ad/2012-08-08): Periodic Inspections · Learjet 45. Effective May 29, 2012
- [AD 2011-25-03](https://openairdocs.org/ad/2011-25-03): Landing Gear · Learjet 45. Effective Jan 23, 2012
- [AD 2011-13-10](https://openairdocs.org/ad/2011-13-10): Powerplant · Learjet 45. Effective Aug 1, 2011
- [AD 2011-04-08](https://openairdocs.org/ad/2011-04-08): Electrical power · Learjet 45. Effective Mar 31, 2011
- [AD 2010-21-19](https://openairdocs.org/ad/2010-21-19): Fire protection · Learjet 45. Effective Nov 18, 2010
- [AD 2010-06-13](https://openairdocs.org/ad/2010-06-13): Flight controls · Learjet 45. Effective Apr 1, 2010
- [AD 2009-24-22](https://openairdocs.org/ad/2009-24-22): Equipment/Furnishings · Learjet 45. Effective Jan 8, 2010
- [AD 2008-01-03](https://openairdocs.org/ad/2008-01-03): Principal structural elements (PSEs · Learjet 45. Effective Feb 14, 2008
- [AD 2007-17-17](https://openairdocs.org/ad/2007-17-17): Unsealed gaps on the pylon side of the engine firewall · Learjet 31, 31A, 35 and 7 more. Effective Oct 2, 2007
- [AD 2007-09-03](https://openairdocs.org/ad/2007-09-03): Auxiliary power unit (APU) · Learjet 45. Effective May 11, 2007
- [AD 2006-10-15](https://openairdocs.org/ad/2006-10-15): Inspection reference numbers (IRNs) · Learjet 45. Effective May 31, 2006
- [AD 2005-24-13](https://openairdocs.org/ad/2005-24-13): Electrical wire bundle for the alternator on the left-hand engine · Learjet 45. Effective Dec 20, 2005
- [AD 2003-17-08](https://openairdocs.org/ad/2003-17-08): Nose landing gear (NLG) squat switch camrod · Learjet 45. Effective Sep 24, 2003
- [AD 2003-16-09](https://openairdocs.org/ad/2003-16-09): Main landing gears (MLG) · Learjet 45. Effective Aug 27, 2003
- [AD 2003-16-19](https://openairdocs.org/ad/2003-16-19): Horizontal Stabilizer Actuator Assembly (HSAA) · Learjet 45. Effective Aug 13, 2003
- [AD 2003-06-51](https://openairdocs.org/ad/2003-06-51): Horizontal stabilizer actuator · Learjet 45. Effective Apr 28, 2003
- [AD 2002-17-01](https://openairdocs.org/ad/2002-17-01): Foot Warm circuit breaker · Learjet 45. Effective Sep 12, 2002
- [AD 2001-03-05](https://openairdocs.org/ad/2001-03-05): Anti-ice Manifold Assembly · Learjet 45. Effective Feb 20, 2001
- [AD 2000-08-13](https://openairdocs.org/ad/2000-08-13): Brakes · Learjet 45. Effective May 15, 2000
- [AD 2009-11-13](https://openairdocs.org/ad/2009-11-13) (historical): Hydraulic power · Learjet 45. Effective Jun 17, 2009
- [AD 2000-22-04](https://openairdocs.org/ad/2000-22-04) (historical): Nose Landing Gear · Learjet 45. Effective Dec 6, 2000

## Registered aircraft by registry model (OpenAirDocs)

- [Learjet 45](https://openairdocs.org/model/learjet-45): 433 aircraft (registry code 5170805)
- [Learjet 45 (LEARJET 40)](https://openairdocs.org/model/learjet-45-learjet-40): 0 aircraft (registry code 5170810)

## STCs approved under this data sheet (178, first 50)

- [STC ST12518IB](https://openairdocs.org/stc/ST12518IB): Flight Data Recorder (FDR) Installation Structural Provisions. Sky Service F.B.O. Inc.
- [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems
- [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc.
- [STC ST04760NY](https://openairdocs.org/stc/ST04760NY): Installation of LAI Windshields. Lee Aerospace
- [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC
- [STC ST12153AC](https://openairdocs.org/stc/ST12153AC): Installation of the Honeywell RFF-100 5G Bandpass Filter on certain Honeywell AA-300 and KRA 405B equipped aircraft. TES Parts LLC
- [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc.
- [STC ST12087CH](https://openairdocs.org/stc/ST12087CH): Installation replacement Cabin/Cockpit Handheld Fire Extinguishers. Avcon Industries Inc.
- [STC ST01119DE](https://openairdocs.org/stc/ST01119DE): Installation of a Gogo Galileo Half-Duplex (HDX) System. Peregrine
- [STC ST12142IB](https://openairdocs.org/stc/ST12142IB): Installation of of the Honeywell RDR 7000 Weather Radar System. Maga Aviation Manutenção de Aeronaves LTDA
- [STC ST03292CH](https://openairdocs.org/stc/ST03292CH): Activation of an 802.11 a/b/g/n WiFi System. Elliott Aviation Technical Products Development, Inc.
- [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc.
- [STC ST01117DE](https://openairdocs.org/stc/ST01117DE): Installation of the Gogo ATG C1.. Peregrine
- [STC ST01936WI](https://openairdocs.org/stc/ST01936WI): Installation of LED lights. AeroLED's Holdings LLC
- [STC ST04159CH](https://openairdocs.org/stc/ST04159CH): Upgrade of Honeywell Primus II Communications Units RCZ-8XX Transponders to support Certification of Automatic Dependent Surveillance -Broadcast (ADS-B) Out. CMD Flight Solutions LLC
- [STC ST03424CH](https://openairdocs.org/stc/ST03424CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC
- [STC ST01639WI](https://openairdocs.org/stc/ST01639WI): Removal of the Concorde RG-443 Emergency Battery and replacement with the Concorde RG-145-2 Emergency
Battery.. Global Aviation Tech LLC
- [STC ST01726WI](https://openairdocs.org/stc/ST01726WI): Installation of a Tailcone Cooling Axial Fan and Ducting. Global Aviation Tech LLC
- [STC ST04575AT](https://openairdocs.org/stc/ST04575AT): Installation of the Rockwell Collins ALT-1000+/ -4000+ with 5G Filtering. Chippewa Aerospace Inc.
- [STC ST01651CH](https://openairdocs.org/stc/ST01651CH): Install air ambulance conversion.. Spectrum Aeromed LLC dba Spectrum Aeromed
- [STC ST01070DE](https://openairdocs.org/stc/ST01070DE): Installation of the Curtiss-Wright Fortress Flight Data Recorder (with Cockpit Voice Recorder). Peregrine
- [STC ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited
- [STC ST01976WI](https://openairdocs.org/stc/ST01976WI): Add Honeywell Synthetic Vision Capability to the DU-875 Display Units, Primus Elite Advanced Features (PEAF). TurboJet Engineering Pty Ltd
- [STC ST04522CH](https://openairdocs.org/stc/ST04522CH): INSTALL UNIVERSAL AVIONICS SYSTEMS CORP (UASC) FMS SOFTWARE VERSION 1002.X INTO EXISTING UASC FMS's. FLIGHTSTAR CORPORATION
- [STC ST01704WI](https://openairdocs.org/stc/ST01704WI): Installation of Crane Aerospace & Electronics SmartStem Wireless Tire Pressure Sensing System.. ELDEC Corporation
- [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc.
- [STC ST04479CH](https://openairdocs.org/stc/ST04479CH): INSTALL GOGO AVANCE L5 SYSTEM PROVISIONS. FLIGHTSTAR CORPORATION
- [STC ST01270WI-D](https://openairdocs.org/stc/ST01270WI-D): Installation of Honeywell MK V and MK VII EGPWS Runway Awareness and Advisory System (RAAS).  This approval is limited to specifically idenitfied aircraft.. Duncan Aviation Inc
- [STC ST02635LA](https://openairdocs.org/stc/ST02635LA): Modification to replace the existing Mode S Transponder system with the ACSS NXT-600 Mode S Transponder with ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC SA01452CH](https://openairdocs.org/stc/SA01452CH): Installation of an air ambulance conversion kit.. Med-Pac Inc.
- [STC ST04439CH](https://openairdocs.org/stc/ST04439CH): The certification for Transmitting Portable Electronic Device (TPED) on Learjet Inc. Model 45 aircraft in accordance with Flightstar Corporation Master Data List 45-001-028, Revision C, dated November 21, 2019, or later FAA approved revision.. Flightstar Corporation
- [STC ST01927WI](https://openairdocs.org/stc/ST01927WI): Installation of Mid-Continent MD-302 Standby Attitude Module. Jet City Engineering Pty Ltd
- [STC ST04421CH](https://openairdocs.org/stc/ST04421CH): Installation of a Data link communication system supporting FANS 1/A+ capability. Flightstar Corporation
- [STC ST00934DE](https://openairdocs.org/stc/ST00934DE): Installation of Becker Avionics BXT6553 transponder. Peregrine
- [STC ST01558WI](https://openairdocs.org/stc/ST01558WI): Installation of a Nav Light Switch Modification for Flight Deck Annunciator Dimming. Diamond W. Inc.
- [STC ST00909SE](https://openairdocs.org/stc/ST00909SE): Installation of emergency medical stretchers and bases, oxygen and electrical systems. LifePort LLC
- [STC ST10526SC](https://openairdocs.org/stc/ST10526SC): Replacement of Thrust Reverser Control Units. The NORDAM Group LLC
- [STC ST04298NY](https://openairdocs.org/stc/ST04298NY): Installation of the Universal Avionics System Corporation (UASC) UL-801 UNILINK Airborne Data Link. Sky Service F.B.O. Inc
- [STC ST00942DE](https://openairdocs.org/stc/ST00942DE): Demonstration of Aircraft Compatibility to Wireless Fidelity (WiFi) Data Transmissions (Ground & Flight). West Star Aviation, LLC
- [STC ST00790DE](https://openairdocs.org/stc/ST00790DE): Installation of BendixKing CAS 67B Traffic Alert and Collision Avoidance System (TCAS) II Version 7.1. Peregrine
- [STC ST02636LA](https://openairdocs.org/stc/ST02636LA): Modification to upgrade the existing XS-950 Mode S Transponder system to add ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC ST00347BO](https://openairdocs.org/stc/ST00347BO): Modification to upgrade a BendixKing CAS 67A TCAS II system to CAS 67B TCAS II Change 7.1. Pro Star Aviation, LLC
- [STC ST00361BO](https://openairdocs.org/stc/ST00361BO): Installation of a Honeywell Primus II (XS-852) ADS-B Out System. Pro Star Aviation, LLC
- [STC ST00373BO](https://openairdocs.org/stc/ST00373BO): Installation of Rockwell Collins TDR-94D Transponders with ADS-B Out. Pro Star Aviation, LLC
- [STC ST01878WI](https://openairdocs.org/stc/ST01878WI): Installation of replacement components for the cabin management/in-flight entertainment systems on the Learjet Model 45 aircraft (Learjet 70/75 configurations). Learjet Inc.
- [STC ST11071SC](https://openairdocs.org/stc/ST11071SC): Demonstration of aircraft critical equipment and antenna systems tolerance of radio frequency interference (RFI) from intentional or spurious transmissions from certain Portable Electronic Devices (PEDs). Liberty Partners Inc
- [STC ST01842WI](https://openairdocs.org/stc/ST01842WI): Installation of Honeywell DU-875 Primus Elite cockpit display units. Learjet Inc
- [STC ST04194CH](https://openairdocs.org/stc/ST04194CH): Install Honeywell Liquid Crystal Display (LCD) Flight Displays. Pentastar Aviation LLC
- [STC ST04030CH](https://openairdocs.org/stc/ST04030CH): Installation of Aircell ATG-2000/4000/5000 High Speed Internet with Wireless Local Area Network (WLAN). Nextant Aerospace
- [STC ST03873NY](https://openairdocs.org/stc/ST03873NY): Installation of Honeywell DU-875 MFD. Aviation Traders Limited (Trading as ATL)

All 178: https://openairdocs.org/tcds/T00008WI/stcs.md

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