# TCDS A-723: Lockheed Martin Aeronautics Company

- Type: Type certificate data sheet
- Status: Current
- Holder: Lockheed Martin Aeronautics Company
- Revision: 23
- Revised: July 23, 2012
- Product: Aircraft, Large Airplane
- Certification basis: CAR 4a
- Registered aircraft: 2, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/af/70/af704843d004eeec5cf60c6cb5cfb1c40917830b84d9f2b8b65db49b5b4e321f
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C536FBA036B7185186257A45004A0D65.0001
- Page: https://openairdocs.org/tcds/A-723

## Models (1)

As the data sheet lists them.

- 18

## 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 
Rev. No. 23 22 22 22 22 22 22 22 22 22 22 
Reformatted 5/95. 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
A-723 
Revision 23 
LOCKHEED 
18 
 
July 23, 2012 
AIRCRAFT SPECIFICATION NO. A-723 
 
 
This aircraft specification  which is part of Type Certificate No. 723 prescribes conditions and limitations under which the 
product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. 
 
Type Certificate Holder Lockheed Martin Aeronautics Company 
 86 South Cobb Drive 
 Marietta, GA 30063 
 
Type Certificate Holder Record Lockheed Aircraft Corporation 
  Burbank, California 
 
I - Model 18 (See NOTE 11 for original civil and military designations and dates of approval and  NOTE 12 for "Learstar" 
modification) Engines 
    (1)    2 P&W Hornets S1E2-G, with 3:2 reduction gearing and two 4 1/2N dampers. 
    (2) 2 P&W Hornets S1E3-G, with 3:2 reduction gearing and two 4 1/2N dampers. 
    (3) 2 P&W Twin Wasps SC3-G, with 3:2 reduction gearing and one 3 1/2N damper. 
    (4) 2 P&W Twin Wasps S1C3-G, with 3:2 reduction gearing or 16.9 spline  
     coupled reduction gearing and one 3 1/2N damper. 
    (5) 2 P&W Military R-1830-75 or -94, with 16:9 spline coupled reduction gearing and  
     one 3 1/2N damper. 
    (6) 2 P&W Twin Wasps S4C4-G, with 3:2 reduction gearing and one 3 1/2N damper. 
    (7) 2 Wright Cyclones GR1820G-102A, with 16:11 reduction gearing and two  
     4 1/2N dampers. 
     (8) 2 Wright Cyclones GR1820-G202A, 702C9GC1 or 2, with 3:2 reduction gearing  
     and two 4 1/2N dampers. 
    (9) 2 Wright Military R1820-56, -66, -72 or -72A with 3:2 reduction gearing and two  
     4 1/2N dampers.  (Mixed engines permissible) 
    (10) 2 Wright Cyclones 730C9GD1, 2, 3 or 4, with 3:2 reduction gearing and  
     two 4 1/2N dampers. 
    (11) 2 Wright Cyclones 704C9GC1, 2, 3 or 4, with 3:2 reduction gearing and  
     two 4 1/2N dampers. 
    (12) 2 Wright Military R1820-40, -60, -87 or -95, with 3:2 reduction gearing and  
     two 4 1/2N dampers. 
 Engine limits  
  Engines (1) & (2) Fuel 87 Min. Grade  Engine (3) Fuel 87 Min. grade 
 Takeoff Maximum Continuous    Takeoff Maximum Continuous  
 (1 Min.) S.L. 5500 ft.   (1 Min.) S.L. 12000 ft. 
In. Hg. 41.0/39.5 36.5 34.5  In.Hg. 42.0 36.0 34.0 
RPM 2300/2500 2250 2250  RPM 2700 2550 2550 
HP   900/885 800 800  HP 1050 900 900 
 
  Engines (4) Fuel 91 Min. Grade   Engine (5) Fuel 100 Min. grade 
 Takeoff Maximum Continuous    Takeoff Maximum Continuous  
 (1 Min.) S.L. 5500 ft.   (1 Min.) S.L. 12000 ft. 
In. Hg. 48.0 41.5 39.5  In.Hg. 52.0 41.5 41.0 
RPM 2700 2550 2550  RPM 2800 2550 2550 
HP 1200 1050 1050  HP 1350* 1050 1050 
  *Ref NOTE 9(b) for requirements for aircraft w ith engine takeoff ratings in excess of 1200 R.H.P. 
 
  Engine (6)  Fuel 91 Min. grade 
 Low Ratio Supercharger High Ratio Supercharger

A-723  2 
 Takeoff Maximum Continuous  Maximum Continuous  
 (1 Min.) S.L. 7500 ft. 15,400 ft. 
In. Hg. 48.0 41.5 39.0 35.5 
RPM 2700 2550 2550 2550 
HP 1200 1050 1050 900 
  Engines (7)  Fuel 91 Min. Grade   Engine (8) Fuel 91 Min. grade 
 Takeoff Maximum Continuous    Takeoff Maximum Continuous  
 (1 Min.) S.L. 5500 ft.   (1 Min.) S.L. 6900 ft. 
In. Hg. 43.5 37.5 35.4  In.Hg. 45.5 39.5 37.2 
RPM 2300 2300 2300  RPM 2500 2300 2300 
HP 1100 900 900  HP 1200 1000 1000 
 
  Engine (9)  *Fuel 91 & 100 Min. grade 
 Low Ratio Supercharger High Ratio Supercharger 
 Takeoff Maximum Continuous  Maximum Continuous  
 (1 Min.) S.L. 7500 ft. 11,100 ft. 17,000 ft. 
In. Hg. 44.0 (S.L.) 39.0 38.50 42.0 40.0 
RPM 2500 2400 2400 2500 2500 
HP 1200 1050 1050 900 900 
  *The above limits are applicable for both 91 and 100 mi n. grade fuel with appropriate carburetor adjustments 
  in accordance with Wright Aeronautical Company instructions. 
 
  Engine (10)  Fuel 91 Min. Grade   Engine (11)  Fuel 91 Min. Grade 
     Low Ratio High Ratio 
     Supercharger Supercharger 
 Takeoff  Maximum Continuous    Takeoff  Maximum Continuous  Max Cont 
 (1 min.) S.L. 6900 Ft.   (1 min.) S.L. 6900 ft. 15,200 ft. 
In. Hg. 45.0 39.0 36.7  In. Hg. 45.5 39.5 37.2 40.0 
RPM 2500 2300 2300  RPM 2500 2300 2300 2300 
HP 1200 1000 1000  HP 1200 1000 1000 900 
 
  Engine (12)       *Fuel 91 & 100 Min. grade    
 Low Ratio Supercharger High Ratio Supercharger 
 Takeoff Maximum Continuous  Maximum Continuous  
 (1 Min.) S.L. 6900 ft. 15,200 ft. 
In. Hg. 45.5 39.5 37.2 40.0 
RPM 2500 2300 2300 2300 
HP 1200 1000 1000 900 
   *The above limits are applicable for both 91 and 100 min. grade fuel with appropriate  carburetor adjustments in  
    accordance with Wright Aeronautical Company instructions. 
 
Airspeed limits 
     Vl  (Level flight or climb) 238 mph (207 knots) True Ind. 
     Vne (Never exceed) 279 mph (243 knots) True Ind. 
     Vf  (Flaps extended) 115 mph (100 knots) True Ind. 
 
Usable ceilings Engines (1) & (2) 
Ceiling Weight TIAS Propeller Deicers 
(Ft.) (lbs.) MPH (Knots) (Item) Prop Wing 
6400 17500 122 (106) 1(c) No No 
4800 17500 122 (106) 1(c) No Yes 
 
  Engines (3) & (4) 
Ceiling Weight TIAS Prop. (Items) Fuel De-Icers 
(Ft.) (Lbs.) MPH (Knots) Eng (3) Eng (4) Grade Prop Wing 
11800 17500 127 (110) 1(c) 1(c) 87 or 91 No Yes 
9600 18500 128 (111) 1(c) 1(c) 91 No Yes 
9100 18500 126 (110) 1(c) 1(c) 91 Yes (See  
Note 11) 
Yes 
8300 18500 128 (111) - 1(a) 91 No Yes

3 A-723 
6900 18500 127 (110) 1(c) 1(c) 87 No Yes 
  Engine (5) 
Ceiling Weight TIAS Propeller Deicers 
(Ft.) (lbs.) MPH (Knots) (Item) Prop Wing 
11300 17500 127 1(b) No No 
10300 18500 127 1(b) No Yes 
 
  Engine (6) 
Ceiling Weight TIAS Propelle r Deicers Supercharger 
(Ft.) (lbs.) MPH (Knots) (Item) Prop Wing Ratio 
13750 17500 123 (107) 1(c) No No High 
11800 18500 123 (107) 1(c) No No Low 
 
  Engine (7) 
Ceiling Weight TIAS Propeller Deicers 
(Ft.) (lbs.) MPH (Knots) (Item) Prop Wing 
10000 17500 123 (107) 1(c) No Yes 
8900 18500 124 (108) 1(c) No No 
 
  Engines (8) & (10) 
Ceiling Weight TIAS Propeller Deicers 
(Ft.) (lbs.) MPH (Knots) (Item) Prop Wing 
12700 17500 121 (105) 1(c) or (d) No No 
12200 17500 124 (105) 1(c) Yes (See 
Note 11) 
No 
10800 18500 124 (108) 1(c) or (d) No No 
10300 18500 124 (108) 1(c) Yes (See 
Note 11) 
No 
 
  Engines (9), (11), & (12) 
    (Supercharger Ratio High)   
Ceiling Weight TIAS Propeller Fuel Grade De-icers 
(Ft.) (lbs.) MPH (Knots) (Item) Eng. (9), 
(11), (12) 
Eng. (9) 
(12) 
Prop Wing 
15100 17500 120 (104) 1(c) or (d) 91 100 No Yes 
14600 17500 120 (104) 1(c) 91 100 Yes 
(See  
Note 11) 
Yes 
13350 18500 120 (104) 1(c) or (d) 91 100 No Yes 
12850 18500 120 (104) 1(c) 91 100 Yes 
(See  
Note 11) 
Yes 
 
 Conditions for Usable Ceilings: (1) Standard Air 
  (2) Either engine inoperative 
  (3) Inoperative propeller fully feathered 
  (4) Carburetor air intake on "cold air"  and carburetor air filter in "off" position. 
  (5) Operative engine at maximum conti nuous power at altitudes below the engine  
   critical altitude and at rated rpm and full throttle at altitudes above the 
   engine critical altitude. 
 
 C.G. range Forward limit  (28.1% MAC) (+0.3) 
 (Gear down) Aft limit (37.2% MAC) (+10.8) 
    Moment change due to landing gear retraction +30050 in.lbs.

A-723  4 
 Maximum weights (Airplanes incor porating engines (1) or (2) and which have not been modified in  
    accordance with NOTE 5 are limited to a landing and takeoff weight of 17,500 lbs.) 
    Landing 17,500 lbs. 
    Landing as cargo carrier 18,500 lbs. 
    Takeoff 18,500 lbs. 
    (See NOTE 3 for dump valve requireme nts, NOTE 4 for weight increase when  
    de-icers are installed, NOTE 5 for modifi cations required for 18,500 lb. takeoff weight,  
    NOTE 7 for modifications for 18,500 lb. landing weight and NOTE 9 for requirements  
    for certification at or in excess of 19, 500 lbs. takeoff and 18,500 lbs. landing weights.) 
 
 Number of seats 17 (Crew 2, 3 or 4 including 2 p ilots (-52.5), stewardess (+242.5) and radio operator  
    (-21.5)). 
 Maximum baggage Maximum capacity of compartments: 
    No. 1 (nose) 1500 lbs. (- 133.5) 
    No. 2 (fwd. belly) 800 lbs. (-   68.5) 
    No. 3 (mid belly) 400 lbs. (-   20.5) 
    No. 4 (rear belly) 700 lbs. (+  30.5) 
    Buffet 50 lbs. (+184.5) 
 
 Fuel capacity 644 gals. (4 tanks in center section wing: 
     2 front tanks 150 gals. each (- 20.5) 
     2 rear tanks 172 gals. each (+22.5)) 
 
 Oil capacity 40 gals.  (1 tank in each nacelle 20 gals. each (-15)) 
    or 44 gals.  (1 tank in each nacelle 22 gals. each (-52.5)) 
 
 Control surface movements Elevators 34° up 23.5° down 
    Elevator trim tab 25° up and down 
    Elevator anti-servo tab 12°  elev. up 6.5°  elev. down 
    Ailerons 25° up 9° down 
    Aileron trim tab 20° up 26° down 
     (L.H. tab only) 
    Aileron servo tab 3° up 14.5° down 
    Rudders 31° right and left 
    Rudder trim tabs 25° right and left 
     Rudder servo tabs 6° right and left 
 
 Serial Nos. eligible 2001 and up 
    2626, 6124, 6333, 6378, 6608, 7419, manufact ured by Gordon S. Hamilton Co. as  
    Lockheed licensee. 
 
 Required equipment In addition to the pertinent require d basic equipment specified in CAR 4a, the following  
    items of equipment must be installed: 
    Items 1(a), (b), (c), or (d), 101(a)  or (b), 201(a), 202(a), 203(a), 204(a), 205(a),  
    206(a), 207(a) or (b), 601, 602(a) and (b). 
 
Specifications Pertinent to All Models 
 Datum  Spar centerline on underside of wing (fuse. sta. 188) 
 MAC  115.84 in. L.E. MAC fuse. sta. 155.75 
 Leveling means Cabin window base line 
 Certification basis Type Certificate No. 723 (CAR 4a) 
 Production basis None.  After February 1, 1944, prio r to original certification,  a CAA agent must  
    perform a detailed inspection for workmans hip, materials, and conformity with the  
    approved technical data, and a check of the flight characteristics. 
 
 Export eligibility Eligible for export to all countries  subject to the provisions of MOP 2-4 except as  
    follows: 
    Canada: Landplane -eligible 
               Skiplane   - not eligible

5 A-723 
Equipment: Approval for the installation of all items of equi pment listed herein has been obtained by the aircraft  
   manufacturer except those items preceded by an asterisk  (*).  The asterisk denotes that approval has been  
   obtained by other than the aircraft manufacturer.  An item marked with an asterisk may not have been  
   manufactured under a CAA monitored or approved quality  control system, and therefore attention should be  
   paid to workmanship and conformity with pertinent data called for in this specification. 
 
Propellers and Propeller Accessories 
 1. (a) (1) 2 propellers - Ham. Std., hubs 23E50, blades 6179A-0. 706 lbs. (-110) 
    For interchangeable blade mode ls see Prop. Spec. No. 603 (NOTE 6). 
    Dia.:  Max. 10' 6-3/8", min.  allowable for repairs 10' 3-5/8". 
      No further reduction permitted. 
    Low pitch setting 24° at 42 in. sta. 
    (Eligible only with S1C3G engi nes having 16:9 spline-coupled reduction  
     gearing and one 3 1/2N damper.) 
    Placarded required:  "Avoid continuous operation between 1200 and  
      1400 RPM and between 1940 and 2050 RPM." 
  (b) (2) 2 propellers - Ham. Std., hubs 23E50, blades 6353-30. 790 lbs. (-105) 
    For interchangeable blade mode ls see Prop. Spec. No. 603 (NOTE 6). 
    Round or square tipped blades eligible. 
    Dia.:  Max. 10' 6-3/8", min.  allowable for repairs 10' 3-5/8". 
      No further reduction permitted. 
    Low pitch setting 21° at 42 in. sta. for 1200 hp T.O. rating 
      and 17° at 42 in. sta. for 1350 hp T.O. rating. 
    (Eligible with "(5)" engines ha ving spline-coupled 16:9 reduction gears.) 
  (c)(101) 2 propellers - Ham. Std., hubs 23E50, blades 6139-12. 758 lbs. (-110) 
    For interchangeable blade mode ls see Prop. Spec. No. 603 (NOTE 6). 
    Dia.:  Max. 10' 6-3/8", min.  allowable for repairs 10' 3-5/8". 
      No further reduction permitted. 
    Low pitch setting at 42 in. sta.:  17° for engines "(3), (4) and (7)"; 
      18° for engines "(1), (2), (8),  (11) and (12)"; 20° for engine "(6)". 
      21° for engines "(9) and (10)". 
    (Eligible for all engines except those having 16:9  
    reduction gearing). 
 
  (d)(203) 2 propellers - Ham. Std., hubs 33D50, blades 6259-12, 6459-12, 610 lbs. (-106) 
      6505-12, 6511-12 or 6529-12. 
    Dia.:  Max. 10' 7", min. allowable for repairs 10' 4-1/4". 
      No further reduction permitted. 
    Low pitch setting at 42 in. sta.:  20° for engines "(8), (11) and (12"; 
    21° for engines "(9) and (10)". 
    With blades model 6511-12 or 6529-12, following placard required: 
      "Avoid continuous operation in flight below 1450 RPM and between 
      1650 and 1850 RPM." 
  *(e)  2 propellers - Ham. Std., hubs 33D 50, blades 6511-12S or 6529-12S. 630 lbs. (-106) 
    Dia.:  Max. 10' 7", min. allowable for repairs 10' 4-1/4". 
      No further reduction permitted. 
    Low pitch setting at 42 in. sta.:  21.5° 
    Feathered pitch setting at 42 in. sta.:  88.5°. 
    (For engines listed in "Learstar" Modification in NOTE 12.) 
    Placard required:  "Avoid c ontinuous operation in flight below 
      1450 RPM and between 1650 and 1850 RPM." 
 
Engine and Engine Accessories - Fuel and Oil System 
 101. (a) (102 a) Residual fuel and oil for m odels with single row engines 35 lbs. (-79) 
  (b) (102 b) Residual fuel and oil for models  with P&W Twin Wasp engines 45 lbs. (-79.5) 
  *(c)  System fuel and oil ("Learstar" modification) 48 lbs. (-79) 
 102. (a)(201) Fuel dump valve installati on (Lockheed Dwg. No. 54418) 53 lbs. (+8) 
    (See NOTE 3 for restrictions) 
  *(b)  2 fuel dump valves, General Controls AV16B1165 6 lbs. (+5)

A-723  6 
Landing Gear 
 201. Main Wheel and Brake Assemblies  
  (a) (15.00-16) 
   2 Goodyear wheels (No. 530161) 161 lbs. (-29)  
   2 Goodyear brakes (No. 510967-2) 
  *(b) (12.50-16) 
   2 Goodyear wheels (No. 9540512) 196 lbs. (-29)  
   2 Goodyear brakes (No. 9540622) 
   (Eligible for use on Model 18 when modified in accordance with  
   Lear Dwg. 6048190.  Eligible for use on "Learstar" when modified  
   in accordance with Lear Dwg. 6048179.) 
  (c) (15.00-16) 
   Goodrich wheel-brake assembly (Dwg. No. H-14-957) 
   2 Goodrich wheels (No. H-3-857) 
   2 Goodrich brakes (No. G-2-626) 
 
 202. Main gear Tires and Tubes  
  (a) 2 Firestone 10-ply HD, 15.00-16, with regular tubes 225 lbs. (-29)  
  *(b) 2 Goodyear 10-ply type III, 15.00-16, with regular tubes 240 lbs. (-29)  
 
 203. Tail Wheel Assembly  
  (a) 18 in. Hayes (Lockheed Dwg. 660058) (swiveling) 5 lbs. (+395) 
  *(b) 17 in. Hayes D254A (swiveling) 5 lbs. (+395) 
 
 204. Tail Wheel Tire and Tube  
  (a) 18 in. Firestone 6-ply with cactus-proof tube 19 lbs. (+395) 
  *(b) 17 in. Goodyear 8-ply with regular tube 14 lbs. (+395) 
 
 205. Main Gear Shock Struts  
  (a) 2 Aerol XY-450 LB 454 lbs. (-29)  
  *(b) 2 Aerol XY-450 LB (Eligible for use on M odel 18 with Item 201(b) when 454 lbs. (-29)  
   modified in accordance with Lear Dwg . 6048190.  Eligible for use on "Learstar"  
   with Item 201(b) when modified in accordance with Lear Dwgs. 6048179 and 6048201). 
 
 206. Tail Gear Shock Strut  
  (a) Aerol 7976 27 lbs. (+382) 
  *(b) Aerol 7976 per Lear Dwg. 6048189 27 lbs. (+382) 
  (c) Aerol B-250 LA 27 lbs. (+382) 
 
 207. Main Gear Emergency Extension System  
  (a) Independent oil-draulic system , manually operated 8 lbs. (0)    
  (b) Nitrogen (Lockheed Dwg. 75346) 15 lbs. (-58)  
  *(c) Nitrogen (Lear Dwg. 603625) 15 lbs. (-95)  
 
Interior Equipment 
 401. CAA Approved Airplane Flight  Manual (Learstar modification) 
  (The manual may be carried as part of, or bound with, the  
  operator's "Operations Manual", but must  remain in the airplane  
  and must  retain its identity as an individual manual.) 
 
 402. (401) Automatic pilot 
  *(a) Lear Model L-5 (3 servos Model 118, 1 elevator tab servo  
    Model 866 or 2204, and 1 rudder servo (optional) Model 2204B). 
   Installation per Lear Dwg. 82525 (with installation of rudder  
    tab servo per Lear Dwg. 700211) 77 lbs. (+23)   
    (without installation of r udder tab servo) 75 lbs. (+13.5) 
   Installation per Lear Dwg. 82825F with servo in wing 93 lbs. (+67)   
   Main servo slip clutch torques:  175 (+  10) in. lbs.

7 A-723 
 402. (401) Automatic pilot (cont'd) 
  (a) Lear L-5 autopilot for installation Learstar modification of NOTE 12  
    this specification, with following servo stall torques in inch  
    pounds measured at servos:  rudder 70-90, aileron 135-165,  
    elevator 80-100.  Satisfactory for automatic approach with  
    above values.  Servos are:  118 AB, main , and 2218C-1, rudder  
    and elevator tabs. 
     Placards required in full view of automatic pilot controller: 
     "Caution - when approach c oupler is engaged, elevator trim  
    must be checked by momentarily disengaging the auto-pilot by  
    means of the quick-disconnect button." 
    (Note:  This placard may be deleted if trim indicators for both  
    pitch and yaw axes are installed.) 
    "When using autopilot in crui se configuration, minimum terrain  
    clearance is 250 ft.  When using autopilot during approach,  
    minimum altitude is 200 ft." 
    (Minimum altitude for each case does not override any  
    higher minimum operational altitude.) 
  *(b)  Lear Model L-2C installation in  accordance with Lear Dwg. 91350A 60 lbs. (+103) 
     Main servo Model 118K and trim tab servo Model 868G. 
     Main servo slip clutch torques:  175 in. lbs. 
     Placards required in full view of automatic pilot controller: 
     "When using autopilot for cruising operations the minimum  
    terrain clearance is 250 ft.  When using autopilot during  
    approach, minimum altitude is 200 ft., pilot's seat belt  
    fastened and hand on control wheel." 
    (Minimum altitude for each case does not override any higher  
    minimum operational altitude.) 
    "Do not override autopilot to increase angle of bank." 
  *(c)  Pioneer PB-10, 3 main servos 15601-1A, elevator tab servo  207 lbs. (-23)  
    15602-1B, throttle servo 15620-2A.  Installation per  
    Grand Central Aircraft, Glendale, California Dwgs. 20493,  
    20495, 20497, 20499, 20536, 20537 and photos 1 through 6.   
    Airplane Flight Manual Revision dated 4-11-55 required. 
 
    Servo stall torque inch pounds measured @ servos are satisfactory  
    for FPC:  Aileron 372 - 480, Elevator 325 - 400, Rudder 272 - 413. 
 
Miscellaneous 
 601. (103) Fixed wing slot in stallation   25 lbs. (-7)  
 602. (a)(104a) Wing trailing edge extensi on (Lockheed Dwg. 74349 or 79310) 35 lbs. (+94) 
  (b)(104b) Elevator control system damping unit (Lockheed Dwg.  12 lbs. (-16) 
     No. 73975) (When complete automatic pilot is installed, or  
     when changes described in Lockheed Service Bulletin Bo. 18-44 
     are incorporated, this item may be omitted.) 
 
NOTE 1. (a) An approved Lockheed weight and balance report including list of equipment included in certificated weight  
   empty, and loading instructions when necessary, must be  in each aircraft at the time of original certification and  
   at all times thereafter, except in the case of air ca rrier operators having an approved weight control system. 
  (b) Lear Report No. 17 "Weight and Balance and Equipmen t List" showing interior arrangement and locations and  
   capacities of cargo and luggage compartments shall be in each "Learstar" modification of the Lockheed Model  
   18 at the time of original approval and at all times thereafter. 
 
NOTE 2. (a) Placard lavatory door as follows:  "This room  not to be occupied during takeoff and landing."   
  (b) A placard which states the order in which the fuel tanks are to be used must be installed at the fuel selector  
   valve.  The order of using fuel shall be the same as i ndicated in the loading instructions.  (In lieu of posting such  
   a placard in air carrier airplanes, and subject to the a pproval of the Chief, Air Carrier Safety Division, definite  
   instructions must be issued by the operator to the e ffect that fuel tanks should be filled and used in order  
   indicated in their approved loading instructions.)

A-723  8 
NOTE 2.  (cont'd) 
  (c) For those airplanes requiring an "Airplane Flight Manual", the following placard shall be placed on the  
   instrument panel in full view of the pilot, and wh en appropriate, the instruments should be properly marked: 
   "This airplane shall be operated in compliance with  the operating limitations specified in the CAA Approved  
   Airplane Flight Manual." 
  (d) The following propeller placards shall be placed on the instrument panel in full view of the pilot and the  
   tachometer appropriately marked for those airplane s on which the propellers listed below are installed.   
   (1) Item 1(a):  "Avoid continuous operation be tween 1200 and 1400 RPM and between 1944 and 2050 RPM.   
   (2) Item 1(d) with blades Model 6511-12 or 6529-12 a nd Item 1(e):  "Avoid continuous operation in flight  
    below 1450 RPM and between 1650 and 1850 RPM." 
 
NOTE 3. Fuel jettisoning provisions are not required for aircraft  having not more than 1000 lbs. spread between maximum  
  takeoff and maximum landing weight.  If dump valves other than Item 102(a) are installed, the former shall be  
  removed or made positively inoperative. 
 
NOTE 4. Maximum landing or takeoff weight may be increased 105 lbs. when complete de-icer system is installed.  Applicable  
  to aircraft up to 19,500 lbs. takeoff weight only. 
 
NOTE 5. For certification at 18,500 lbs. take off weight (or landing weight as cargo carrier) Model 18 airplanes of Serial Nos. 
  2001 to 2024, inclusive, must be modified structurally to  conform with drawing changes and new drawings listed on  
  Lockheed Service Project Drawing No. 1037.  Airplanes of Serial Nos. 2025 and up have had the structural revisions  
  necessary for eligibility at 18,500 lbs. takeoff weight (or landing weight as cargo carrier) incorporated in the  
  airplanes at the factory. 
 
NOTE 6. Replacement surfaces which incorporate flush type riveti ng may be substituted for surfaces having external head type  
  rivets except that in the event that an outer wing panel or  wing tip (with external head rivet) is being replaced by a  
  flush type rivet panel, both left and right surfaces must be replaced. 
 
NOTE 7. All Model 18 aircraft which have been modified in accordance with NOTE 5 are eligible as cargo carriers with a  
  maximum landing weight of 18,500 lbs. when the passenger seats are removed and the cabin is revised in accordance  
  with Lockheed Service Project Dwgs. 1221A and 1222.  Wh en airplanes of these models are certificated as cargo  
  carriers, no passengers may be carried and satis factory loading instructions must be provided. 
 
NOTE 8. The various Air Force and Navy models were originally  built as commercial aircraft but the cabins were converted  
  for Military use by removal of seats and the installati on of troop benches or cargo provisions.  Also, the military  
  models differed from the Model 18 for certain powerplant in stallation details, minor structural differences and were  
  equipped with a 12-volt electrical system.  Prior to cer tification as a civil aircraft, the following must be  
  accomplished in addition to compliance with Lockh eed Service Technical Report No. 1 and applicable  
  AIRWORTHINESS DIRECTIVES: 
  (a) Each airplane must satisfactorily pass an insp ection for conformity, possible hidden damage, and for  
   workmanship and materials used in making any repairs and/or alternations.  Particular attention should be paid  
   to placards, instrument markings and windshield equipment. 
  (b) The following military equipment should be removed:  Propane priming, auxiliary fuel tanks and supporting  
   structure.  Such brackets and supporting structure as w ill not interfere with the safe operation of the aircraft  
   may, at the operator's discretion, be left in the airc raft as long as the equipment has been rendered inoperative.  
   Operators may retain the oil dilution system and hopper type oil tank upon compliance with paragraph 1 of  
   Airworthiness Directive 46-13-3.  Otherwise the inst allation of a conventional oil tank and rework of the  
   standpipe will be required in accordance with paragr aphs 2 and 3 of Airworthiness Directive 46-13-3.   
  (c) If the Jack & Heintz automatic pilot directional gyro  control unit, Part No. JH5000 and climb and turn control  
   unit, Part No. JH6000, are installed, they should be of  the modified version identified by a yellow "M" adjacent  
   to name plate, as covered in Jack & Heintz Service Bu lletin No. P-1.  If the Jack & Heintz A-3A autopilot servo  
   units are installed, they should be  of the modified version in which the over-power differential pressure is  
   limited to 175+ 15 psi, as covered in Jack & Heintz Service Bulletin No. P-4.  The modified unit is identified by  
   a new name plate (JH11609) on which CAA approval is  indicated.  CAA approved model numbers will be one  
   of the following:  M11-D3-A, M8-D3-A, M6-D3-A or M6-D3-B.  Also, the JH6000 bank and climb gyro  
   control head incorporated as a co mponent of the A-3A autopilot must be the modified version incorporating a  
   placard warning that "the bank-climb gyro limit as an altitude reference is forty-five degrees (45°) in bank,  
   climb or dive", as covered in Jack & Heintz Service Bulletin No. P-5. 
  (d) If the airplane is to be used in scheduled air-carrier  operation, the oil inlet line installed forward of the firewall  
   shall be of fire-resistant material.

9 A-723 
  (e) Each airplane must be weighed to determine its we ight and balance and an approved loading chart or device  
   must be installed.  The loading chart or device should be prepared in accordance with Lockheed Service  
   Information Letter No. 18-33.  An equipment list must be prepared.  This list, the approved loading chart or  
   device, and the weight and balance data will constitu te the Weight and Balance Report for the particular  
   airplane.  If any changes have been made which would adversely affect the flight characteristics, the airplane  
   must be flight tested. 
   In compiling the equipment list for an airplane, refere nce should be made to the Lockheed Master Equipment  
   List to determine that all Class 100 items or satisfactor y alternates are installed.  Certain Class 200 items on the  
   Master List may also be required by the type of opera tion which is to be authorized.  If any of the equipment  
   items installed bear Air Force designations, their accepta bility for civil use should be determined or they should  
   be replaced. 
  (f) All Aero Supply PK-3 type fuel selector valves manuf actured prior to 1943 must be reworked to incorporate the  
   new metal retainer washer (cup type) and the new Hycar seals.  The year of manufacture can be determined  
   from the prefix of the number stamped on the moun ting bolt hole boss, i.e., 2-567 means 1942 and 3-567 means  
   1943. Stamp the reworked valves with the designation letters CPRW-H (cup plate - Hycar) to show the rework  
   has been accomplished.  (Lockheed Service Telegram  dated November 17, 1943, covers this same subject.) 
  (g) (Applies only to serial numbers 1954, 1956, 1957 and 2001 through 2075.)  The Vickers AA-14000 accumulator  
   must be removed and Bendix 401531 7-1/2 inch accumu lator and AN 6234-3 filter installed.  Also the 55285  
   hydraulic reservoir must be reworked to increase its  capacity to 2.3 gallons.  (Lockheed Service Bulletin 18/SN- 
   120 dated April 21, 1945, covers this same subject.) 
  (h) On airplanes with low pressure brakes equipped with  deboosters, it may be necessary to install a longer hose in  
   the inboard end of each debooster to eliminate interfere nce with the drag strut knee bolt.  (Lockheed Service  
   Information Letter dated August 1, 1945, revise d December 10, 1945, covers this same subject.) 
  (i) On all Wright C9GC (G-200 Series) engines, re move the upper valve washers, Part Nos. 69271 and 113171.   
   Engines equipped with the two spring combination are satisfactory without change.  For engines equipped with  
   the three spring combination, it will be satisfactor y to use Part Nos. 118815, 113171 or No. 113171J.  If either  
   of the latter two is used, it should be of the high dime nsion type (0.60) inch total height.) (Wright Service  
   Bulletin no. C912A covers this same subject.) 
 
NOTE 9. (a) Model 18 aircraft are authorized to be operated at a takeoff weight of 19,500 lbs. and a landing weight of  
   18,500 lbs. provided NOTE 5 has been complied with a nd, provided compliance is shown with the requirements  
   of CAR No. SR-407.  For certificated weights in ex cess of the above, compliance is also required with CAR  
   No. SR-407. 
  (b) Model 18 aircraft incorporating engines of more than  1830 cu.in. displacement or with takeoff power ratings in  
   excess of 1200 BHP shall comply with the requirements of CAR No. SR-407. 
 
NOTE 10. Goodrich propeller de-icer fluid feed strips, Part No . 37572, eligible on propellers (Items 1(d) and 1(e) when  
   installed not to extend beyond the 48 1/2 inch blade sta tion. Install in accordance with B.F. Goodrich Installation  
   Manual 4-7195-NS.  Weight change is negligible. 
 
NOTE 11. The various model dash numbers appearing in previous specifications are actually versions of the basic Model  
   18 series aircraft, the certification basis for which is  Type Certificate No. 723.  These dash numbers were  
   selected by Lockheed primarily for engine designati on and clerical purposes, and should not be considered to  
   define different models of airplane s.  Any one version may be converted to another by incorporation of pertinent  
   required equipment and complete conf ormity with corresponding approved drawings. 
   In the future, all aircraft may be considered as basi c Model 18 airplanes and all references to the dash numbers  
   in the model designation, including the identification plat es in the cockpit, may be disregarded.  The original  
   model designation and dates of approval are listed below for reference purposes only. 
 
MODEL DATE APPROVED 
Civil Air Force Navy  
18-07 C-59 R50-2 March 30, 1940 
18-08 C-57 R50-3 August 17, 1940 
 C-57B   
18-14 ---- ---- August 17, 1940 
18-40 ---- R50-1 August 17, 1940 
18-50 ---- ---- Dec 20, 1940 
18-56 C-60 R50-5 May 30, 1942 
 C-60A R50-6

A-723  10 
NOTE 12. "Learstar" Modification.  
   Basic configuration approved January 21, 1955 for Lear , Inc., Aircraft Engineering Division, Santa Monica  
   Airport, California.  Aircraft conforming to any "Learstar" modification version described in Lear Report  
   No. 18 "Lockheed Model 18 - Lodestar - Learstar Modification - Specification and Drawing List" dated  
   December 29, 1954, and complying with this  specification are eligible for certification. 
 
Engines  (1) 2 Wright R1820-76A 
   (2) 2 Wright R1820-76B 
   (3) 2 Wright 987C9HD1 
 
 Engine limits Engine (1) and (2) Fuel 100/130 grade 
 MAXIMUM CONTINUOUS 
 Low Ratio Supercharger High Ratio Supercharger 
 TAKEOFF  Altitude Alt.  (Min.) Alt. (Max.) 
 (4 Min.) Sea Level (3500 ft.) (12000 ft.) (18300 ft.) 
In. Hg. 51.5 (S.L.) 46.5 45.2 43.5 42.0 
RPM 2700 2500 2500 2500 2500 
HP 1425 1275 1275 975 975 
 
    Engine (3) Fuel 100/130 Grade 
 MAXIMUM CONTINUOUS 
 Low Ratio Supercharger High Ratio Supercharger 
 TAKEOFF  Altitude Alt.  (Min.) Alt. (Max.) 
 (4 Min.) Sea Level (3300 ft.) (12000 ft.) (18300 ft.) 
In. Hg. 52.5 (S.L.) 47.5 46 43 42.0 
RPM 2700 2500 2500 2500 2500 
HP 1425 1275 1275 975 975 
 
 Airspeed limit Vno (Normal Opera tion) 260 mph (226 knots) True Ind. 
     (Above 17000 ft. reduce speed      6 mph (5 knots) per 1000 ft.) 
    Vne (Never Exceed 289 mph (251 knots) True Ind. 
     (Above 17000 ft. reduce speed     5 mph (5 knots) per 1000 ft.) 
    Va (Maneuvering) 168 mph (146 knots) True Ind. 
    Vf (Approach position - 20%) 215 mph (187 knots) True Ind. 
    Vf (Landing position - 100%) 158 mph (137 knots) True Ind. 
    Vlo (Landing gear operation) 167 mph (145 knots) True Ind. 
    Vle (Landing gear extended) 200 mph (174 knots) True Ind. 
 
 C.G. range (Gear Down) Forward limit (27.8% MAC) (+0) 
      Aft limit (37.2% MAC) (+10.8) 
     Moment change due to main gear retraction   +34,100 in.lb. 
     Moment change due to tail gear retraction negligible. 
 
 Maximum weights Landing 20, 400 lbs.; Takeoff 22,500 lbs. 
    Note:  Maximum landing and takeoff we ights may be increased to 21,500 lbs. and  
    24,000 lbs. respectively when provisions  of Lear Dwg. No. 600030A are incorporated  
    and appropriate Airplane  Flight Manual is provided. 
 
 Minimum crew Pilot and copilot at (-53.0) 
 
 Passengers (See Lear Report No. 17, Weight a nd Balance and Equipment List for number and  
    location.) 
 
 Maximum baggage Maximum capacity of compartments:   
      No. 2 (Fwd. belly) 800 lbs. (-65.5) 
      No. 3 (Mid belly) 400 lbs. (-20.5) 
      No. 4 (Rear belly) 700 lbs. (+30.5) 
      Galley 100 lbs. (-22.0) 
      Cloakroom 100 lbs. (+236.0)

11 A-723 
 Fuel capacity 1114 gals. (4 tanks in cente r section wing, 2 tanks in outer wing) 
    2 front center section tanks 150 gals. ea. (-20.5) 
    2 rear center section tanks 172 gals. ea. (+22.5) 
    2 outer wing tanks 235 gals. ea. (-13.0) 
 
 Oil capacity 40 gals. (1 tank in each nacelle)   20 gals. ea. (-15.0) 
 
 Alcohol capacity 30 gals. (1 tank in each nacelle)   15 gals. ea. (-18.0) 
 
 Control surface movements Elevators 34° up 23.5° down 
    Elevator trim tab 21.5° up 18.5° down 
    Elevator spring tab 3° up 3° down 
    Ailerons 25° up 8.5° down 
    Aileron trim tab (L.H. tab only) 22.5° up 26.5° down 
    Aileron servo tab (both tabs) 3° up 13.5° down 
    Rudders                                           20° inboard              30° outboard (quadrant travel) 
    Rudder trim tab                               25°right                24 .5° left 
    Rudder servo tab                             5.5° right and left 
    Rudder spring tab                             20° right and left 
 
 Serial Nos. eligible 2001 to 2024, inclusive, when  modified in accordance with NOTE 5 and 2025 and up. 
 
 Required equipment In addition to the pertinent required basic equipment specified in CAR 4(a) and 4(b) the  
    following items of equipment must be installed: 
    1(e), 101(c), 102(b), 201(b), 202(b), 203(b), 204(b), 205(b), 206(b), 207(c), 401(a). 
 
 Certification basis Type Certificate No. 723 (CAR 4a  as revised by CAR No. SR 407, effective date  
    Sept. 10, 1954) whereby structural require ments of CAR 4a, as amended to April 7,  
    1950, were complied with, and flight and powerplant requirements of CAR 4b, as  
    amended to December 31, 1953, were complied with. 
 
NOTE 13. In the revision dated November 15, 1955, to this sp ecification the equipment items were renumbered.  The old  
   item numbers are also included in th e Equipment Section of the specification and appear in brackets to the right  
   of the new numbers.  Elsewhere in the specification, only the new numbers are used. 
 
 
.-END-
```

## ADs (24, in force first)

- [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026
- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 99-19-08](https://openairdocs.org/ad/99-19-08): AFM - Deicing · Lockheed 14-H, 14-H2, 14-N and 3 more. Effective Dec 27, 1999
- [AD 98-04-32](https://openairdocs.org/ad/98-04-32): AFM - Limitations Section - Icing · Lockheed 14-H, 14-H2, 14-N and 3 more. Effective Mar 25, 1998
- [AD 93-14-12](https://openairdocs.org/ad/93-14-12): Crewmember Protective Breathing Equipment Units · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 201 more. Effective Sep 2, 1993
- [AD 77-10-03](https://openairdocs.org/ad/77-10-03): Fire Resistant Prop Feathering System · Lockheed 18. Effective Jun 16, 1977
- [AD 66-02-01](https://openairdocs.org/ad/66-02-01): Air Conditioners · Beechcraft 56TC, 58, 58A and 39 more. Effective Feb 10, 1966
- [AD 63-21-04](https://openairdocs.org/ad/63-21-04): Elevator Trim Tabs · Air Trading Navy PV-1 and 18. Effective Jan 10, 1964
- [AD 63-03-03](https://openairdocs.org/ad/63-03-03): Main Landing Gear Drag Strut · Lockheed 18. Effective Mar 5, 1963
- [AD 61-22-06](https://openairdocs.org/ad/61-22-06): Elevator Control Mast Castings · Air Trading Army B-34, Navy PV-1 and 18. Effective Nov 21, 1961
- [AD 46-13-01](https://openairdocs.org/ad/46-13-01): Landing Gear Hose Ferrules · Lockheed 18
- [AD 46-13-02](https://openairdocs.org/ad/46-13-02): Dual Fuel System · Lockheed 18
- [AD 46-13-03](https://openairdocs.org/ad/46-13-03): Hopper Oil Tanks · Lockheed 18
- [AD 47-43-10](https://openairdocs.org/ad/47-43-10): Fire Extinguisher Bottle Rework · Lockheed 18
- [AD 47-43-11](https://openairdocs.org/ad/47-43-11): Elevator Push-Pull Rod Bolts · Lockheed 18
- [AD 48-42-02](https://openairdocs.org/ad/48-42-02): Fire Prevention Modification · Lockheed 18
- [AD 52-08-01](https://openairdocs.org/ad/52-08-01): Fuel Tank Seal · Lockheed 18
- [AD 57-23-01](https://openairdocs.org/ad/57-23-01): Vacuum System Fusible Plug · Lockheed 18
- [AD 58-08-03](https://openairdocs.org/ad/58-08-03): CB Fire Extinguisher System · Air Trading Navy PV-1, DC3-G102, DC3-G102A and 13 more
- [AD 58-11-02](https://openairdocs.org/ad/58-11-02): Landing Gear Drag Strut Yoke · Lockheed 18
- [AD 58-11-03](https://openairdocs.org/ad/58-11-03): Rudder Cable Attachment · Air Trading Navy PV-1 and 18
- [AD 59-16-02](https://openairdocs.org/ad/59-16-02): Stabilizer Spar · Air Trading Army B-34, Navy PV-1 and 18
- [AD 60-21-02](https://openairdocs.org/ad/60-21-02): Carburetor Preheat Modification · Lockheed 18

## Registered aircraft by registry model (OpenAirDocs)

- [Lockheed 18](https://openairdocs.org/model/lockheed-18): 2 aircraft (registry code 5261602)
- [Lockheed AT 18](https://openairdocs.org/model/lockheed-at-18): 0 aircraft (registry code 5261558)

## STCs approved under this data sheet (281, first 50)

- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA1686WE](https://openairdocs.org/stc/SA1686WE): Installation of Vibration Isolation Products (VIP) engine mount P/Ns VIP 50525-1 and VIP 50545-1 on various aircraft as shown on FAA Approved Model List (AML) No. SA1686WE.. FTG, Inc.
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA2-565](https://openairdocs.org/stc/SA2-565): Installation of electronics rack. Associated Air Center, Inc. - c/o CT Corporation System
- [STC SA2-885](https://openairdocs.org/stc/SA2-885): Installation of McMillan Radome nose P/N 7311. Associated Air Center, Inc. - c/o CT Corporation System
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation
- [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation
- [STC SA01229SE PAGE 1](https://openairdocs.org/stc/SA01229SE%20PAGE%201): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc
- [STC SA01933LA-D PAGE 1](https://openairdocs.org/stc/SA01933LA-D%20PAGE%201): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation
System. Garmin International Inc
- [STC SA3-41](https://openairdocs.org/stc/SA3-41): Short stack installation - Pratt & Whitney R-1830 or Wright R-1820 engines.. Sabreliner Aviation LLC
- [STC SA3-42](https://openairdocs.org/stc/SA3-42): Modification to Janitrol heater air inlet scoop. Installation of Janitrol heater overheat warning system.. Sabreliner Aviation LLC
- [STC SA3-46](https://openairdocs.org/stc/SA3-46): Nose heater installation, Stewart-Warner Model 940-B24.. Sabreliner Aviation LLC
- [STC SA3-466](https://openairdocs.org/stc/SA3-466): DC-3 exhaust collector ring and short stack installation.. Sabreliner Aviation LLC
- [STC SA01692SE](https://openairdocs.org/stc/SA01692SE): Installation of a Garmin GMX 200 Multi-Function Display. Garmin International Inc
- [STC SA02016SE-D](https://openairdocs.org/stc/SA02016SE-D): Installation of Garmin GTS 800, GTS 820 or GTS 850 Traffic System. Garmin International Inc
- [STC SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc
- [STC SA100CE](https://openairdocs.org/stc/SA100CE): Installation of Hoskins Supplemental Model A or B High Intensity Wing Tip Lights, Model C Tail Light, with or without Model 1 or 2 High Intensity Fuselage Lights.. BF Goodrich Aerospace
- [STC SA451CE](https://openairdocs.org/stc/SA451CE): Install Hoskins Twilighter MK III Supplementary lighting system with Model E, F or P wing tip and Model C tail lights.. BF Goodrich Aerospace
- [STC SA2-1582](https://openairdocs.org/stc/SA2-1582): Flap modification removal.. Airline Fueling Inc.
- [STC SA01473SE](https://openairdocs.org/stc/SA01473SE): Installation of a GTX 32 (mode C), GTX 33 (mode S), or GTX 33D (mode S with diversity) Remote Transponde. Garmin AT Inc.
- [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc.
- [STC SA01487SE](https://openairdocs.org/stc/SA01487SE): Installation of a GDL 69 or GDL 69A XM Satellite Receiver in accordance with Garmin Supplemental Type Certificate Master Data List, P/N 005-C0217-00, Revision A, dated December 20, 2004, or later FAA approved revision.. Garmin AT Inc.
- [STC SA1-66](https://openairdocs.org/stc/SA1-66): 1003-X radome.. Saint-Gobain Performance Plastics Corp
- [STC SA02217AK](https://openairdocs.org/stc/SA02217AK): Installation of Garmin AT Model GDL90 UAT Data Link System, in accordance with Garmin AT, Inc., GDL 90 UAT Master Data List, P/N 560-0278-01, Revision A, dated November 12, 2004, or later FAA approved revision.. Garmin AT Inc.
- [STC SA105SW](https://openairdocs.org/stc/SA105SW): Installation of landing gear doors.. Signature Flight Support Corporation
- [STC SA106SW](https://openairdocs.org/stc/SA106SW): Installation of Model M-4 autopilot.. Signature Flight Support Corporation
- [STC SA107SW](https://openairdocs.org/stc/SA107SW): Installation of alcohol deicing system.. Signature Flight Support Corporation
- [STC SA129SW](https://openairdocs.org/stc/SA129SW): Installation of empennage saddle-back fairing.. Signature Flight Support Corporation
- [STC SA146SW](https://openairdocs.org/stc/SA146SW): Installation of Lear L5 autopilot.. Signature Flight Support Corporation
- [STC SA177SW](https://openairdocs.org/stc/SA177SW): Installation of tail cone.. Signature Flight Support Corporation
- [STC SA17SW](https://openairdocs.org/stc/SA17SW): Installation of electric trim tab servo.. Signature Flight Support Corporation
- [STC SA181SW](https://openairdocs.org/stc/SA181SW): Installation of oxygen system.. Signature Flight Support Corporation
- [STC SA183SW](https://openairdocs.org/stc/SA183SW): Installation of air conditioner.. Signature Flight Support Corporation
- [STC SA187SW](https://openairdocs.org/stc/SA187SW): Firewall fluid shutoff valve installation. Signature Flight Support Corporation
- [STC SA188SW](https://openairdocs.org/stc/SA188SW): Installation of Scene-A-Ramic cabin windows.. Signature Flight Support Corporation
- [STC SA192SW](https://openairdocs.org/stc/SA192SW): Installation of Mighty Midget hydraulic selector (flap and gear).. Signature Flight Support Corporation
- [STC SA194SW](https://openairdocs.org/stc/SA194SW): Installation of cockpit side windows.. Signature Flight Support Corporation
- [STC SA2-100](https://openairdocs.org/stc/SA2-100): Installation of electric trim actuator.. Signature Flight Support Corporation
- [STC SA2-102](https://openairdocs.org/stc/SA2-102): Installation of Emergency Fluid Shut-Off Valves.. Signature Flight Support Corporation
- [STC SA2-103](https://openairdocs.org/stc/SA2-103): Installation of anti-collision lights.. Signature Flight Support Corporation
- [STC SA2-105](https://openairdocs.org/stc/SA2-105): Installation of 36-inch length picture windows between Stations 279 and 392.. Signature Flight Support Corporation
- [STC SA2-1078](https://openairdocs.org/stc/SA2-1078): Installation of flight line nose heater.. Signature Flight Support Corporation
- [STC SA2-109](https://openairdocs.org/stc/SA2-109): Installation of instrument panel.. Signature Flight Support Corporation
- [STC SA2-1126](https://openairdocs.org/stc/SA2-1126): Rudder anti-overbalance springs.. Signature Flight Support Corporation

All 281: https://openairdocs.org/tcds/A-723/stcs.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.