# TCDS A1SO: Lockheed Martin Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Lockheed Martin Corporation
- Revision: 17
- Revised: November 15, 2019
- Product: Aircraft, Large Airplane
- Certification basis: Part 1, Part 21, Part 25, Part 26, Part 36
- Registered aircraft: 11, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/20/e9/20e9a4685c983ad13c4ce08b8ee2419ab6f8363f4ebbf125e20017b3479bae5a
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/6B8971BD3E1EBB4F862584C5006C541A.0001
- Page: https://openairdocs.org/tcds/A1SO

## Models (6)

As the data sheet lists them.

- 382F
- 382
- 382E
- 382B
- 382J
- 382G

## 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 14 15 16 17 
Rev. No. 17 10 9 11 9 10 11 10 11 10 10 11 13 13 17 17 16 
Page No. 18 19 20 21 22 23 
Rev. No. 17 17 14 17 17 17 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A1SO 
Revision 17 
LOCKHEED 
 
382 
382B 
382E 
382F 
382G 
382J  
 
November 15, 2019 
 
TYPE CERTIFICATE DATA SHEET NO. A1SO 
 
This data sheet, which is a part of Type Certificate No. A1SO, 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: Lockheed Martin Corporation 
 Lockheed Martin Aeronautis Company 
 86 South Cobb Drive 
 Marietta, Georgia  30063-0655 
 
I.  - Model 382  (Hercules)  Transport Category Aircraft),  Approved 16 February 1965  (See NOTE 5.) 
Engines 4 Allison Turbo-prop 501-D22A 
` Engine Type Certificate No. E-282 
 
Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D1655-59T, 
types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4 or 
JP-5. 
 
Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002 
 
Engine Limits Static, standard day, sea level: 
 
 Turbine Inlet Temp.  Torque   Oil Temp 
 Take-off (5 minutes)  19,600 in. lb.  40°C - 100°C 
 1077°C 
 
 Maximum continuous 
 1010°C     19,600 in.lb.  60°C - 85°C 
 
 Rated Speed:   100% - 13,820 erpm 
 
Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers 
 Hub 54H60-91/54H60-117 Blade A7111D-2 
 Propeller Type Certificate No. P-906 
 Diameter: 13 ft. 6 in. 
 2% reduction allowable for repair 
 Single rotation, four blade assembly with governing speed setting 1020 prpm 
(13,820 erpm).  Propeller assembly is complete with spinner, feathering and reversing 
provision, constant speed control, negative torque control, synchrophaser, and electrical 
ice control.

A1SO 2 of 23 
 
 Blade angles  See NOTE 3 
    
 Feather 92.5°   ±   0.20° (a)  (b) 
 Low pitch stop 
   (min. flt. Idle) 
23.25° ±   0.50° (a) 
 Ground start   4.75° ±   0.75° (b) 
 Ground idle   1.0°   ±  (c) 
 Reverse  -7.0     ±  1.0° (b) 
 
Propeller Oil MIL-H-5606B 
 
Airspeed Limits VMO Maximum operating) See Fig. 1-2 
 VA (Maneuvering) of approved 
 VB (Turbulent air penetration) Airplane Flight Manual 
 VFE (Take-off & approach, 50%) 183K 
 VFE (Landing, 100%) 145K 
 VLO (Landing gear operation) 168K 
 VLE (Landing gear extended) 168K 
 VLL (Landing light extended) 168K 
    
Heated Windshield 
       Limitations If electric windshield heat is operative, it must be used for all flight operations.  
Operation without electric windshield heat, on any or all portions of the windshield, is 
permissible provided (1) the airplane is not flown in known icing conditions, and (2) the 
maximum speed limit below 10,000 ft. is 187 KCAS. 
 
Weight & C.G. Limits   Most Fwd. C.G. Most Aft C.G. 
   (gear up or down) Condition Wt./lbs. %MAC F.S. %MAC F.S. 
 Ramp 155,800 23.3 525.7 30 536.8 
 Take-off 155,000 23.2 525.5 30 536.8 
 Landing 130,000 20.2 520.6 30 536.8 
 Zero fuel 120,000 18.8 518.3 30 536.8 
 
Datum Trim Station -493.0 (F.S. 94.0), W.L. 142.98, B. L. O.O. (NAS 221 screw head on 
bottom of forward fuselage, 71.0" forward of center of line of nose gear strut.) 
 
M.A.C. 164.5"; leading edge M.A.C. Trim Station  
 -39.6 (F.S. 487.4) 
 
Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left 
side at approximately Trim Station +110 (F.S. 637).  A plumb line support bracket is 
located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling 
plate is located on top of the cargo floor curb at approximately W.L. 150 B.L.  64L. 
 
Minimum Crew Three (3) - Pilot, Co-pilot, and Flight Engineer 
 
Passengers None.  Approved for cargo only. 
 
Cargo Compartment Length 48.3 
 Width 9 ft/. 11½ in. 
 Height 9 ft. 
 Usable volume 4,536 cu. ft. 
 Maximum cargo See SMP 521-2.

3 of 23 A1SO 
 Loading data for approved loading schedule are contained in Lockheed Report ER-9511.  
Individual aircraft weight and balance data are contained in Lockheed Report 
SMP 521-2. 
 Class E cargo compartment.  Cargo must be loaded in compliance with loading placard, 
Lockheed Drawing 398251-1.  When cargo restraining (barrier) net is installed, the 
393487-15 placard is a required part of the installation. 
 
Maximum Fuel Quantity  Tank Usable Fuel Total Fuel F.S. Arm (full) (T.S.) 
 1 (outboard) 9,238 lbs. 9,331 lbs. 545.2 +18.2 
 2 (inboard) 8,437 lbs. 8,578 lbs. 555.0 +28.0 
 3 (inboard) 8,437 lbs. 8,578 lbs. 555.0 +28.0 
 4 (outboard) 9,238 lbs. 9,331 lbs. 545.2 +18.2 
 **  Left Aux. 6,269 lbs. 6,329 lbs. 556.7 +29.7 
 ** Right Aux. 6,269 lbs. 6,329 lbs. 556.7 +29.7 
 *** Left External 9,355 lbs. 9,465 lbs. 551.2 +24.2 
 *** Right External   9,355 lbs.   9,465 lbs. 551.2 +24.2 
 ***  66,598 lbs. *67,406 lbs. (549.9)  
       
 **** Left External 9,355 lbs. 9,499 lbs. 551.2 +24.2 
 **** Right External   9,355 lbs.   9,499 lbs. 551.2 +24.2 
 ****  66,598 lbs. *67,474 lbs. (549.9)  
 
 * Does not include line fuel.   (See NOTE 1(c)). 
 ** Optional tank installations. 
 *** Optional external tank installation (Lockheed P/N 388236) 
 **** Optional external tank installation (Lear Siegler P/N 305J001) 
 
Maximum fuel quantity These fuel weights are not to be exceeded. 
 (Tank volume may be calculated using fuel density of 6.9 lbs./gal.) 
 
 Arm varies with fuel loading.  Reference loading data, Lockheed Report SMP 521-2, for 
approved fuel loading information.  See NOTE 1 for unusable fuel. 
 
Oil Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0, Trim 
Station -85.0).  Capacity for each, 8 gallons usable, total 12 gallons.  Capacity for all, 32 
gallons usable, total 48 gallons.  See NOTE 1 for system oil. 
 
Maximum operating altitude 32,600 feet 
 
Other operating limitations Aircraft shall be operated in compliance with the operating limitations specified in the 
FAA approved Airplane Flight Manual. 
 
Manufacturer's Serial 3946 is a Model 382 and is only aircraft numbers eligible by incorporation of STC 
ST396SO.  (See NOTE 5). 
 
II. Model 382B  (Hercules)  (transport aircraft), approved 5 October 1965  (See NOTE 5)  
Engines 4 Allison turbo-prop 501-D22 
 Engine Type Certificate No. E-282 
 
Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D1655-59T, 
types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4, or 
JP-5. 
 
Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002

A1SO 4 of 23 
Engine limits Static, Standard day, sea level: 
  
 Turbine Inlet Temp.  Torque   Oil Temp 
 Take-off (5 minutes) 
 Model 382B 977°C  19,600 in. lb.  40°C - 100°C 
 
 Maximum continuous 
    932°C  18,000 in.lb.  60°C - 85°C 
 
 Rated Speed:  100% - 13,820 erpm 
 
Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers 
 Hub 54H60-91/54H60-117 Blade A7111C-2/A7111D-2 
 Propeller Type Certificate No. P-906 
 Diameter: 13 ft. 6 in. 
 2% reduction allowable for repair 
 
 Single rotation, four blade assembly with governing speed setting 1020 prpm 
(13,820 erpm).  Propeller assembly is complete with spinner, feathering and reversing 
provision, constant speed control, negative torque control, synchrophaser, and electrical 
ice control. 
 
 Blade angles  See NOTE 3 
    
 Feather 92.5°    ± 0.20° (a)  (b) 
 Low pitch stop 
   (min. flt. idle) 
23.25°  ± 0.50° (a) 
 Ground start   4.75°  ± 0.75° (b) 
 Ground idle   1.0° (c) 
 Reverse  -7.0°    ± 1.0° (b) 
 
Propeller Oil MIL-H-5606B 
 
Airspeed Limits VMO (Maximum operating) See Fig. 1-2 
 VA (Maneuvering) of approved 
 VB (Turbulent air penetration) Airplane Flight Manual 
 VFE (Take-off & approach, 50%) 183K 
 VFE (Landing, 100%) 145K 
 VLO (Landing gear operation) 168K 
 VLE (Landing gear extended) 168K 
 VLL (Landing light extended) 168K 
 
Heated windshield limitations If electric windshield heat is operative, it must be used for all flight operations.  
Operation without electric windshield heat, on any or all portions of the windshield, is 
permissible provided (1) the airplane is not flown in known icing conditions, and (2) the 
maximum speed limit below 10,000 ft. is 187 KCAS. 
 
Weight & C.G. Limits Condition Wt./lbs. Most Fwd. C.G. Most Aft C.G. 
   (gear up or down)   %MAC F.S. %MAC F.S. 
 Ramp 155,800 23.3 525.7 30 536.8 
 Take-off 155,000 23.2 525.5 30 536.8 
 Landing 130,000 20.2 520.6 30 536.8 
 Zero fuel 117,943 18.4 517.6 30 536.8 
 
 The above weights pertain to an aircraft configuration which does not have 
 pylon tanks installed.  Consult the FAA approved Airplane Flight Manual 
 for proper weight and center-of-gravity restrictions.

5 of 23 A1SO 
 
Datum Trim Station - 493.0 (F.S. 94.0), W.L. 142.98, B.L. 0.0 (NAS 221 screw head on bottom 
of forward fuselage, 71.0" forward of center line of nose gear strut.) 
 
M.A.C. 164.5"; leading edge M.A.C. Trim Station -39.6 (F.S. 487.4) 
 
Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left 
side at approximately Trim Station +110 (F.S. 637).  A plumb line support bracket is 
located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling 
plate is located on top of the cargo floor curb at approximately W.L. 150, B.L. 64L. 
 
Minimum Crew Three (3) - Pilot, Co-pilot, and Flight Engineer.  See AFM for fourth member of some 
versions. 
 
Passengers None.  Approved for cargo only. 
 
Cargo compartment Length    40 ft. 
 Width    9 ft. 11½ in. 
 Height    9 ft. 
 Usable Volume  3,780 cu. ft. 
 Maximum cargo  See SMP 521. 
 
 Loading data for approved loading schedules are contained in Lockheed Report 
ER-8083.  Individual aircraft weight and balance data are contained in Lockheed Report 
SMP 521. 
 
 Class E cargo compartment.  Cargo must be loaded in compliance with loading placard, 
Lockheed Drawing 393487-11.  When cargo restraining (barrier) net is installed, the 
393487-11 placard is a required part of the installation. 
 
Maximum fuel quantity Aircraft S/N 4101 through 4581.  See NOTE 9 for aircraft S/N 4582 and up. 
 
  Tank Usable Fuel Total Fuel F.S. Arm (Full)  T.S. 
 1 (outboard) 9,238 lbs. 9,331 lbs. 545.2 +18.2 
 2 (inboard) 8,437 lbs. 8,578 lbs. 555.0 +28.0 
 3 (inboard) 8,437 lbs. 8,578 lbs. 555.0 +28.0 
 4 (outboard) 9,238 lbs. 8,331 lbs. 545.2 +18.2 
 **  Left Aux. 6,269 lbs. 6,329 lbs. 556.7 +29.7 
 ** Right Aux. 6,269 lbs. 6,329 lbs. 556.7 +29.7 
 *** Left External 9,355 lbs. 9,465 lbs. 551.2 +24.2 
 *** Right External   9,355 lbs.   9,465 lbs. 551.2 +24.2 
   66,598 lbs. *67,406 lbs. (549.9)  
       
 **** Left External 9,355 lbs. 9,499 lbs. 551.2 +24.2 
 **** Right External   9,355 lbs.   9,499 lbs. 551.2 +24.2 
 ****  66,598 lbs. *67,474 lbs. (549.9)  
 
 * Does not include line fuel (See NOTE 1 (c)). 
 ** Optional tank installations. 
 *** Optional external tank installation (Lockheed P/N 388236) 
 **** Optional external tank installation (Lear Siegler P/N 305J001) 
 
 The above fuel weights are not to be exceeded (Tank volume may be calculated using 
fuel density of 6.9 lbs./gal.) 
 
 Arm varies with fuel loading.  Reference Weight and Balance data, Lockheed Report 
SMP 521, for approved fuel loading information. 
 
 See NOTE 1 for unusable fuel.

A1SO 6 of 23 
Oil Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0).  Capacity 
for each, 8 gallons usable, total 12 gallons.  Capacity for all, 32 gallons usable, total 48 
gallons. 
 See NOTE 1 for system oil. 
 
Maximum operating altitude 32,600 feet 
 
Other operating limitations Aircraft shall be operated in compliance with the operating limitations specified in the 
FAA approved Airplane Flight Manual. 
 
Manufacturer's Serial Number 4101 and up. 
 
 
III. - Model 382E  (Hercules)  (transport aircraft), approved 4 October 1968   (See NOTE 5) 
Engines 4 Allison turbo-prop 501-D22A 
 Engine Type Certificate No. E-282 
 
Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D 1655-59T, 
types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4 or 
JP-5. 
 
Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002. 
 
Engine Limits Static, standard day, sea level: 
 Turbine inlet Temp    Torque   Oil Temp 
 Take-off (5 minutes) 
 1077°C      19,600 in-lbs.  40°C - 100°C 
 
 Maximum continuous 
 1010°      19,600 in-lbs.   60°C - 85°C 
 
 Rated Speed:  100% - 13,820 erpm 
 
Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers  
 Hub 54H60-91/54H-60117  Blade A7111C-2/A7111D-2 
 Propeller Type Certificate No. P-906 
 Diameter:  13 ft. 6 in. 
 2% reduction allowable for repair 
 
 Single rotation, four blade assembly with governing speed setting 1020 prpm 
(13,820 erpm).  Propeller assembly is complete with spinner, feathering and reversing 
provisions, constant speed control, negative torque control, synchrophaser, and electrical 
ice control. 
 
 Blade angles  See NOTE 3 
    
 Feather 92.5°   ± 0.20° (a)  (b) 
 Low pitch stop 
   (min. flt. idle) 
23.25° ± 0.50° (a) 
 Ground start   4.75° ±  0.75° (b) 
 Ground idle   1.0° (c) 
 Reverse  -7.0°  ±  1.0° (b) 
 
 
Propeller Oil MIL-H-5606B

7 of 23 A1SO 
 
Airspeed Limits VMO (Maximum operating) See Fig. 1-2 
 VA (Maneuvering) of approved 
 VB (Turbulent air penetration) Airplane Flight Manual 
 VFE (Take-off & approach, 50%) 183K 
 VFE (Landing, 100%) 145K 
 VLO (Landing gear operation) 168K 
 VLE (Landing gear extended) 168K 
 VLL (Landing light extended) 168K 
 
 
Heated Windshield If electric windshield heat is operative, it must be used for all flight operations.  
       Limitations Operation without electric windshield heat, on any or all portions of the windshield, is 
permissible provided (1) the airplane is not flown in known icing conditions, and (2) the 
maximum speed limit below 10,000 ft. is 187 KCAS. 
 
Weight & C.G. Limits Condition Wt./lbs. Most Fwd. C.G. Most Aft C.G. 
   (gear up or down)   %MAC F.S. %MAC F.S. 
 Ramp 155,800 23.3 525.7 30 536.8 
 Take-off 155,000 23.2 525.5 30 536.8 
 Landing 130,000 20.2 520.6 30 536.8 
 Zero fuel 120,000 18.8 518.3 30 536.8 
 
 The above weights pertain to an aircraft configuration which includes a 
 structurally heavier wng (S/N 4299 and up) and does not have pylon tanks 
 installed.  Consult the FAA approved Airplane Flight Manual for proper weight 
 and center gravity restrictions. 
 
Datum Trim Station - 493.0 (F.S. 94.0), W.L. 142.98, B.L.  O.O (NAS 221 screw head on 
bottom of forward fuselage, 71.0" forward of center line of nose gear strut.) 
 
M.A.C. 164.5"; leading edge M.A.C. Trim Station -39.6 (F.S. 487.4) 
 
Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left 
side at approximately Trim Station +110 (F.S. 637).  A plumb line support bracket is 
located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling 
plate is located on top of the cargo floor curb at approximately W.L. 150, B.L. 64L. 
 
Minimum Crew Three (3) - Pilot, Co-pilot, and Flight Engineer. 
 
Passengers None, approved for cargo only. 
 
Cargo compartment Length    48.3 ft. 
 Width    9 ft. 11½ in. 
 Height    9 ft. 
 Usable Volume  4,536 cu. ft. 
 Maximum cargo  See SMP 521-2. 
 
 Loading data for approved loading schedules are contained in Lockheed Report ER-9511.  
Individual aircraft weight and balance data are contained in Lockheed Report SMP 521-2. 
 
 Class E cargo compartment.  Cargo must be loaded in compliance with loading placard, 
Lockheed Drawing 398251-1.  When cargo restraining (barrier) net is installed, the 
393487-15 placard is a required part of the installation.

A1SO 8 of 23 
Maximum fuel quantity Aircraft S/N 4101 through 4581.  See NOTE 9 for aircraft S/N 4582 and up. 
 
  Tank Usable Fuel Total Fuel F.S. Arm (Full)  T.S. 
 1 (outboard) 9239 lbs. 9331 lbs. 545.2 +18.2 
 2 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 
 3 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 
 4 (outboard) 9238 lbs. 9331 lbs. 545.2 +18.2 
 **  Left Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 
 ** Right Aux. 6269 lbs. 6329 556.7 +29.7 
 *** Left External 9355 lbs. 9465 lbs. 551.2 +24.2 
 *** Right External   9355 lbs.   9465 lbs. 551.2 +24.2 
   66,598 lbs. *67,406 lbs. (549.9)  
       
 **** Left External 9355 lbs. 9499 lbs. 551.2 +24.2 
 **** Right External     9355 lbs.     9499 lbs. 551.2 +24.2 
 ****  66,598 lbs. *67,474 lbs. (549.9)  
 * Does not include line fuel (See NOTE 1 (c)). 
 ** Optional tank installations. 
 *** Optional external tank installation (Lockheed P/N 388236) 
 **** Optional external tank installation (Lear Siegler P/N 305J001) 
 
 The above fuel weight are not to be exceeded.  (Tank volume may be calculated using 
fuel density of 6.9 lbs./gal.). 
 
 Arm varies with fuel loading.  Reference loading data, Lock heed Report SMP 521-2, for 
approved fuel loading information. 
 See NOTE 1 for unusable fuel. 
 
Oil Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0, Trim 
Station -85.0).  Capacity for each, 8 gallons usable, total 12 gallons.  Capacity for all, 32 
gallons usable, total 48 gallons.  See NOTE 1 for system oil. 
 
Maximum operating altitude 32,600 feet 
 
Other operating limitations Aircraft shall be operated in compliance with the operating limitations specified in the 
FAA approved Airplane Flight Manual. 
 
Manufacturer's Serial Numbers 4299 and up, 4101 through 4298 by incorporation of STC STC395SO  (See NOTE 5) . 
 
 
IV. - Model 382 F  (Hercules)  (transport aircraft),  approved 3 December 1969  (See NOTE 5) 
Engines 4 Allison turbo-prop 501-D22 
 Engine Type Certificate No. E-282 
 
Fuel Commercial aviation turbine fuel conforming to ASTM Specification No. D 1655-59T, 
types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4, or 
JP-5. 
 
Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002 
 
Engine Limits Static, standard day, sea level: 
 
 Turbine Inlet Temp.   Torque    Oil Temp. 
 Take-off (5 minutes) 
 Model 382F  977°C   19,600 in-lb.   40°C - 100°C 
 
 Maximum continuous 
    932°C   18,000 in-lb.  60°C - 85°C 
 
 Rated Speed: 100% - 13,820 erpm

9 of 23 A1SO 
Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers 
 Hub 54H60-91/54H60-117   Blade A7111C-2/A7111D-2 
 Propeller Type Certificate No. P-906 
 Diameter:  13 ft. 6 in. 
 2% reduction allowable for repair 
 
Single rotation four blade assembly with governing speed setting 1020 prpm  
 (13,820 erpm).  Propeller assembly is complete with spinner, feathering and reversing  
 provisions, constant speed control, negative torque control, synchrophaser, and electrical  
 ice control. 
 
 Blade angles  See NOTE 3 
    
 Feather 92.5° ± 0.20° (a)  (b) 
 Low pitch stop 
   (min. flt. idle) 
23.25° ± 0.50° (a) 
 Ground start 4.75° ± 0.75° (b) 
 Ground idle 1.0° ±  (c) 
 Reverse -7.0 ± 1.0° (b) 
 
Propeller Oil MIL-H-5606B 
 
Airspeed Limits VMO Maximum operating) See Fig. 1-2 
 VA (Maneuvering) of approved 
 VB (Turbulent air penetration) Airplane Flight Manual 
 VFE (Take-off & approach, 50%) 183K 
 VFE (Landing, 100%) 145K 
 VLO (Landing gear operation) 168K 
 VLE (Landing gear extended) 168K 
 VLL (Landing light extended) 168K 
    
 
Heated Windshield If electric windshield heat is operative, it must be used for all flight operations.  
Operation without electric windshield heat, on any or all portions of the windshield, is 
permissible provided (1) the airplane is not flown in known icing conditions, and (2) the 
maximum speed limit below 10,000 ft. is 187 KCAS. 
 
Weight & C.G. Limits Condition Wt./lbs. Most Fwd. C.G. Most Aft C.G. 
   (gear up or down)   %MAC F.S. %MAC F.S. 
 Ramp 155,800 23.3 525.7 30 536.8 
 Take-off 155,000 23.2 525.5 30 536.8 
 Landing 130,000 20.2 520.6 30 536.8 
 Zero fuel 120,000 18.8 518.3 30 536.8 
 
 The above weights pertain to an aircraft configuration which includes a structurally 
heavier wing (S/N 4299 and up)  and does not have pylon tanks installed.  Consult the 
FAA approved Airplane Flight Manual for proper weight and center-of-gravity 
restrictions. 
 
Datum Trim Station -493.0 (F.S. 94.0), W.L. 142.98, B.L.  0.0 (NAS 221 screw head on bottom 
of forward fuselage, 71.0" forward of center line of nose gear strut.) 
 
M.A.C. 164.5"; leading edge M.A.C., Trim Station -39.6 (F.S. 487.4) 
 
Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left 
side at approximately Trim Station +110 (F.S. 637).  A plumb line support bracket is 
located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling 
plate is located on top of the cargo floor curb at approximately W.L. 150, B.L. 64L.

A1SO 10 of 23 
 
Minimum Crew Three (3) - Pilot, Co-Pilot, and Flight Engineer 
 
Passengers None.  Approved for cargo only. 
 
Cargo Compartment Length   48.3 
 Width   9 ft. 11½ in. 
 Height   9 ft. 
 Unusable volume 4,536 cu. ft. 
 Maximum cargo See SMP 521-2. 
 
 Loading data for approved loading schedule are contained in Lockheed Report ER-9511.  
Individual aircraft weight and balance data are contained in Lockheed Report 
SMP 521-2. 
 
 Class E cargo compartment.  Cargo must be loaded in compliance with loading placard, 
Lockheed Drawing 398251-1.  When cargo restraining (barrier) net is installed, the 
393487-15 placard is a required part of the installation. 
 
Maximum fuel quantity Aircraft S/N 4101 through 4581.  See NOTE 9 for aircraft S/N 4582 and up. 
 
  Tank Usable Fuel Total Fuel F.S. Arm (Full)  T.S. 
 1 (outboard) 9238 lbs. 9331 lbs. 545.2 +18.2 
 2 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 
 3 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 
 4 (outboard) 9238 lbs. 8331 lbs. 545.2 +18.2 
 **  Left Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 
 ** Right Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 
 *** Left External 9355 lbs. 9465 lbs. 551.2 +24.2 
 *** Right External     9355 lbs.     9465 lbs. 551.2 +24.2 
   66,598 lbs. *67,406 lbs. (549.9)  
       
 **** Left External 9355 lbs. 9499 lbs. 551.2 +24.2 
 **** Right External     9355 lbs.     9499 lbs. 551.2 +24.2 
 ****  66,598 lbs. *67,474 lbs. (549.9)  
 
 * Does not include line fuel (See NOTE 1 (c)). 
 ** Optional tank installations. 
 *** Optional external tank installation (Lockheed P/N 388236) 
 **** Optional external tank installation (Lear Siegler P/N 305J001) 
 
 The above fuel weights are not to be exceeded.  (Tank volume may be calculated 
 using fuel density of 6.9 lbs./gal.) 
 
 Arm varies with fuel loading.  Reference loading data, Lockheed Report 521-2, for 
approved fuel loading information. 
 
 See NOTE 1 for system oil. 
 
Oil Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0, Trim 
 Sta. - 85.0).  Capacity for each, 8 gallons usable, total 12 gallons.  Capacity for all, 
 32 gallons usable, total 48 gallons. 
 
Maximum operating altitude 32,600 feet 
 
Other operating limitations Aircraft shall be operated in compliance with the operating limitation specified in the 
FAA approved Airplane Flight Manual. 
 
Manufacturer's Serial Numbers 4299 and up, 4101 through 4298 by incorporation of STC serial numbers ST425SO  (See 
NOTE 5).

11 of 23 A1SO 
V. - Model 382G  (Hercules)  (Transport Aircraft),  approved October 7, 1970,  See NOTE 5) 
Engines 4 Allison turbo-prop 510-D22A 
 Engine Type Certificate No. E-282 
 
Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D 1655-59T, 
types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4 or 
JP-5. 
 
Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002. 
 
Engine Limits Static, standard day, sea level: 
 Turbine Inlet Temp.    Torque   Oil Temp. 
 Take-off (5 minutes) 
 1077°C       19,600 in lbs.  40°C - 100°C 
 Maximum continuous 
 1010°C       19,600 in. lbs.  60°C - 85°C 
 Rated Speed: 100% - 13,820 erpm 
 
Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers 
 Hub 54H60-91/54H60-117  Blade A7111C-2/A7111D-2 
 Propeller Type Certificate No. P-906 
 Diameter: 13 ft. 6 in. 
 2% reduction allowable for repair 
 
 Single rotation, four blade assembly with governing speed setting 1020 prpm  
 (13,820 erpm).  Propeller assembly is complete with spinner, feathering and reversing  
 provisions, constant speed control, negative torque control, synchrophaser, and  
 electrical ice control. 
 
 Blade angles  See NOTE 3 
    
 Feather 92.5°   ± 0.20° (a)  (b) 
 Low pitch stop 
   (min. flt. idle) 
23.25° ± 0.50° (a) 
 Ground start 4.75°   ± 0.75° (b) 
 Ground idle 1.0°   (c) 
 Reverse -7.0     ± 1.0° (b) 
 
Propeller Oil MIL-H-5606B 
 
Airspeed Limits VMO Maximum operating) See Fig. 1-2 
 VA (Maneuvering) of approved 
 VB (Turbulent air penetration) Airplane Flight Manual 
 VFE (Take-off & approach, 50%) 183K 
 VFE (Landing, 100%) 150K 
 VLO (Landing gear operation) 171K 
 VLE (Landing gear extended) 171K 
 VLL (Landing light extended) 171K 
    
Heated windshield limitations If electric windshield heat is operative, it must be used for all flight operations.  
Operation without electric windshield heat, on any or all portions of the windshield, is 
permissible provided (1) the airplane is not flown in known icing conditions, and (2) the 
maximum speed limit below 10,000 ft. is 187 KCAS. 
 
Weight & C.G. Limits Condition Wt./lbs. Most Fwd. C.G. Most Aft C.G. 
   (gear up or down)   %MAC F.S. %MAC F.S. 
 Ramp 155,800 21.2 522.2 30 536.8 
 Take-off 155,000 21.1 522.1 30 536.8 
 Landing 135,000 18.6 518.0 30 536.8 
 Zero fuel 125,000 17.0 515.5 30 536.8

A1SO 12 of 23 
 
 The above weights pertain to an aircraft configuration which includes a structurally 
heavier wing (S/N 4383 and up) and does not have pylon tanks installed.  Consult the 
FAA approved Airplane Flight Manual for proper weight and center-of-gravity 
restrictions. 
 
Datum Trim Station -533.0 (F.S. 94.0), W.L. 142.98, B.L.  0.0  (NAS 221 screw head on bottom 
of forward fuselage, 71.0" forward of center line of nose gear strut). 
 
M.A.C. 164.5"; leading edge M.A.C. Trim Station -39.6 (F.S. 487.4) 
 
Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left 
side at approximately Trim Station +110 (F.S. 637).  A plumb line support bracket is 
located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling 
plate is located on top of the cargo floor curb at approximately W.L. 150, B.L. 64L. 
 
Minimum Crew Three (3) - Pilot, Co-Pilot, and Flight Engineer 
 
Passengers None.  Approved for cargo only. 
 
Cargo compartment Length   54.9 
 Width   9 ft. 11½ in. 
 Height   9 ft. 
 Usable volume 5,140 cu. ft. 
 Maximum cargo See SMP 521-4 
 
 Loading data for approved loading schedules are contained in Lockheed Report 
ER-10761.  Individual aircraft weight and balance data are contained in Lockheed Report 
SMP 521-4. 
 
 Class E cargo compartment.  Cargo must be loaded in compliance with loading placard, 
Lockheed Drawing 398251-1.  When cargo restraining (barrier) net is installed, the 
393487-15 placard is a required part of the installation. 
 
Maximum fuel quantity Aircraft S/N 4101 through 4581.  See NOTE 9 for aircraft S/N 4582 and up. 
 
  Tank Usable Fuel Total Fuel F.S. Arm (Full)  T.S. 
 1 (outboard) 9238 lbs. 9331 lbs. 545.2 +18.2 
 2 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 
 3 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 
 4 (outboard) 9238 lbs. 9331 lbs. 545.2 +18.2 
 **  Left Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 
 ** Right Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 
 *** Left External 9355 lbs. 9465 lbs. 551.2 +24.2 
 *** Right External   9355 lbs.   9465 lbs. 551.2 +24.2 
   66,598 lbs. *67,406 lbs. (549.9)  
       
 **** Left External 9355 lbs. 9499 lbs. 551.2 +24.2 
 **** Right External   9355 lbs.   9499 lbs. 551.2 +24.2 
 ****  66,598 lbs. *67,474 lbs. (549.9)  
 
 * Does not include line fuel (See NOTE 1 (c)). 
 ** Optional tank installations. 
 *** Optional external tank installation (Lockheed P/N 388236) 
 **** Optional external tank installation (Lear Siegler P/N 305J001) 
 
 The above fuel weights are not to be exceeded.  (Tank volume may be calculated using 
fuel density of 6.9 lbs./gal.).

13 of 23 A1SO 
 
 Arm varies with fuel loading.  Reference loading data, Lockheed Report SMP 521-4, for 
approved fuel loading information. 
 
 See NOTE 1 for unusable fuel. 
 
Oil  Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0, Trim 
Station -85.0).  Capacity for each, 8 gallons usable, total 12 gallons.  Capacity for all, 32 
gallons usable, total 48 gallons. 
 
 See NOTE 1 for system oil. 
 
Maximum operating altitude 32,600 feet 
 
Other operating limitations Aircraft shall be operated in compliance with the operating limitations specified in the 
FAA approved Airplane Flight Manual. 
 
Manufacturer's Serial Numbers 4388 and up, 4299 through 4387 which have been modified in accordance with STC 
ST446SO.  (See NOTE 5.) 
 
 
VI. - Model 382J S/N 5408 (Hercules II)  (Transport Aircraft),  approved September 9, 1998,  See NOTE 5) 
Engines 4 Allison turbo-prop AE2100D3 
 Engine Type Certificate No. TE1CH 
  
Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D 1655-59T, 
types Jet A, Jet A-1 or Jet B, or commercial equivalents of MIL-J-5624, grade JP-4, 
 JP-5, or JP-8. 
  
Lubricating Oil Exxon Turbo Oil 2380 (-40 deg. C) or Mobil Jet II (-40 deg. C) 
  
 Engine Limits 
  
    Oil Pressure - PSIG  
Condition MGT C NG % Prop % 
RPM 
Prop Gear 
Box 
Engine Oil Temp C 
Start  (Note 8) < 807 
(Note 1) 
 72 N/A (Note 2) (Note 3) (Note 4) 
(Note 13) 
Ground 
Operations 
Feathered LSGI 
Unfeathered LSGI 
 
Unfeathered HSGI 
 
< 600 
<600 
 
<600 
(Note 5) 
 
 72 
 72 
 
 72 
 
20 – 30 
71 – 75 
(Note 6) 
99 
 
 15 
110 – 210 
 
170 - 210 
 
40 – 80 
 
60 – 86 
(Note 7) 
Maximum 
Reverse 
< 833 < 102 101 170 - 210 40 - 80 60 - 86 
  
 852 
(Note 9) 
 
< 102 
 
99 – 101 
 
170 – 210 
 
40 – 80 
 
60 – 86 
(Note 10) 
Flight 
Max Continuous 
Idle 
 
< 833 
< 833 
 
< 102 
 
99 – 101 
(Note 11) 
 
170 - 210 
 
40 - 80 
 
60 – 86 
(Note 12) 
 Note 
1. Starting (start sequence, below 65% NG) MGT of 807C for a maximum of three seconds is permitted. 
2. An indication of increasing oil pressure must be noted within 15 seconds of propeller rotation. 
3. An indication of increasing oil pressure must be noted within 15 seconds of gas generator rotation.

A1SO 14 of 23 
4. Engine starts are prohibited when oil temperatures are -40C or below with MIL-L-23699 oil or its commercial equivalent 
(Exxon Turbo Oil 2380, Mobil Jet II) 
5. Ground Operation MGT reference temperature. 
6. Avoid stabilized operation between 52-68 percent and 76 to 85 percent propeller RPM (turbine shaft and propeller 
critical speed range). 
7. During ground operation engine power is limited to idle when oil temperature is less than 0C, and to 1,000 HP when 
engine oil temperature is less than 45C. 
8. Engine life cycle is counted each time the engine is started. 
9. If MGT exceeds 852C, accomplish the EMERGENCE ENGINE SHUTDOWN procedure contained in the FAA 
Approved Airplane Flight Manual. 
10. Take-off is permitted with an oil temperature of 45C. 
11. Transient operation up to 112 percent during transition from flight idle to ground idle is acceptable.  
12. If oil temperature exceeds 93C, engine shutdown is recommended and maintenance is required. 
13. Blade angle changes when the engine is not operating should not be accomplished when oil temperature is less than -
40C. 
 
Propeller and Propeller Limits 4 Dowty Aerospace (c)R391/6-132-F/3 propellers (constant speed, hydraulic) 
 Propeller Type Certificate No. P15BO 
 Diameter: 13 ft. 6 in. 
 Single rotation, six blade assembly with governing speed setting 1020 prpm.  
 Propeller assembly is complete with spinner, feathering and reversing  
 provisions, constant speed control, synchrophaser, and electrical ice control. 
  
 Blade angles  See NOTE 3 
 Feather 84.5°  ± 0.3° (d) 
 Low pitch stop 
   (min. flt. idle) 
13.0° ± 2.0° (d) 
 Ground idle 1.0° ± 0.3°   (d) 
 Reverse -17.0 ± 0.3° (d) 
 
Airspeed Limits VMO Maximum operating) See Fig. 1-3 
 VA (Maneuvering) of approved 
 VB (Turbulent air penetration) Airplane Flight Manual 
 VFE (Take-off & approach, 50%) 182K 
 VFE (Landing, 100%) 149K 
 VLO (Landing gear operation) 170K 
 VLE (Landing gear extended) 170K 
 VLL (Landing light extended) 250K 
     
  
Heated windshield limitations If electric windshield heat is operative, it must be used for all flight operations.  
Operation without electric windshield heat, on any or all portions of the windshield, is 
permissible provided (1) the airplane is not flown in known icing conditions, and (2) the 
maximum speed limit below 10,000 ft. is 187 KCAS. 
  
Weight & C.G. Limits Condition Wt./lbs. Most Fwd. C.G. Most Aft C.G. 
   (gear up or down)   %MAC F.S. %MAC F.S. 
 Ramp 155,800 21.2 522.3 30 536.8 
 Take-off 155,000 21.1 522.1 30 536.8 
 Landing 130,000 17.8 516.7 30 536.8 
 Zero fuel 124,000 16.8 515.0 30 536.8 
   
Datum Trim Station -533.0 (F.S. 94.0), W.L. 142.98, B.L.  0.0  (NAS 221 screw head on bottom 
of forward fuselage, 71.0" forward of center line of nose gear strut). 
  
M.A.C. 164.5"; leading edge M.A.C. Trim Station -39.6 (F.S. 487.4)

15 of 23 A1SO 
 
Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left 
side at approximately Trim Station +110 (F.S. 637).  A plumb line support bracket is 
located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling 
plate is located on top of the cargo floor curb at approximately W.L. 150, B.L. 64L. 
  
Minimum Crew Two (2) - Pilot and Co-Pilot 
  
Passengers None.  Approved for cargo only. 
  
Cargo compartment Length   54.9 
 Width   9 ft. 11½ in. 
 Height   9 ft. 
 Usable volume 5,140 cu. ft. 
 Maximum cargo See SMP 521-5 
  
 Loading data for approved loading schedules are contained in Lockheed Report 
LG95ER0192 for aircraft S/N 5408.  Individual aircraft weight and balance data are 
contained in Lockheed Report SMP 521-5. 
  
 Class E cargo compartment.  For all models except the Model 382J, cargo must be loaded 
in compliance with loading placard, Lockheed Drawing 398251-1.  For all models except 
the Model 382J, when cargo restraining (barrier) net is installed, the 393487 -15 placard 
is a required part of the installation.  For the Model 382J, cargo must be loaded in 
compliance with loading placard, Lockheed Drawing 3305068-5.  For the Model 382J, 
when cargo restraining (barrier) net is installed, the 3305073-1 placard is a required part 
of this installation. 
 
Maximum fuel quantity  
  Tank Usable Fuel Total Fuel F.S. Arm (Full)  T.S. 
 1 (outboard) 8,784 lbs. 8,970 lbs. 545.2 +18.2 
 2 (inboard) 8,183 lbs. 8,280 lbs. 555.0 +28.0 
 3 (inboard) 8,183 lbs. 8,280 lbs. 555.0 +28.0 
 4 (outboard) 8,784 lbs. 8,970 lbs. 545.2 +18.2 
  Left Aux. 6,217 lbs. 6,279 lbs. 556.7 +29.7 
  Right Aux. 6,217 lbs. 6,279 lbs. 556.7 +29.7 
  Total 46,368 lbs. *47,058 lbs. (551.8) (+24.8) 
  
 * Does not include line fuel (See NOTE 1 (c)). 
  
 The above fuel weights are not to be exceeded.  (Tank volume may be calculated using 
fuel density of 6.9 lbs./gal.). 
  
 Arm varies with fuel loading.  Reference loading data, Lockheed Report SMP 521-5, for 
approved fuel loading information. 
  
 See NOTE 1 for unusable fuel. 
  
Oil  Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0, Trim 
Station -85.0).  Capacity for each, 12 gallons usable, total 12 gallons.  Capacity for all, 48 
gallons usable, total 48 gallons. 
  
 See NOTE 1 for system oil. 
  
Maximum operating altitude 32,200 feet 
  
Other operating limitations Aircraft shall be operated in compliance with the operating limitations specified in the 
FAA approved Airplane Flight Manual. 
  
Manufacturer's Serial Numbers 5408

A1SO 16 of 23 
VII. - Model 382J (LM-100J) Type Design Upgrade approved November 15, 2019 (See NOTE 5) 
 
A 382J (LM100) is a 382J cargo airplane that has been modified with significant upgrades. These aircraft remain 382J aircraft for 
documentation purposes on this TCDS and with regard to the applicability of airworthiness directives. Because of the magnitude 
of thses changes, the certification basis for the changed aspects was required to established and documented in accordance with 
section 21.101 (Changed Product Rule). 
 
Certification Basis: The certification basis is advanced for the following regulations for the areas listed below: 
 
For new systems, and those systems which have been significantly modified to alter its basic function or capability, 
compliance was shown to FAR 25, dated 21 February 2014, as modified by Amendment 25-1 through 25-137, and FAR 26, 
dated 10 December 2007, as modified by amendments 26-1 thru 26-6 except that: 
 
 Paragraph  Amendment  Paragraph Amendment  
 25.21   25-72   25.171   25-7 
 25.103   25-108   25.177   25-108 
 25.105   25-92   25.207   25-108 
 25.107   25-108   25.237(a)   25-108 
 25.111   25-115   25.253   25-84 
 25.119   25-108   25.305   25-0 
 25.121   25-108   25.333   25-0  
 25.123   25-0    25.335(a-d) e(1-2) 25-23 
 25.125   25-108   25.335(e)(3)  25-23 
 25.143   25-108   25.341   25-0 
 25.149(e)   25-137-SC  25.343   25-0 
 25.161(d)   CAR 4b.143  25.345   25-0 
 25.345   25-0    25.904   25-137-SC 
 25.349   25-0    25.905   25-72 
 25.351   25-23   25.907   25-0 
 25.363   25-23   25.961   25-0 
 25.365   25-0    25.963   25-0 
 25.371   25-0    25.965   25-0 
 25.391   25-0    25.969   25-0 
 25.415   25-0    25.977   25-0 
 25.427   25-23   25.979   25-0 
 25.479(a-c)(e)  25-23   25.981(a-2) (b) 25-102 
 25.485   25-0    25.981(a)(3)  25-102 
 25.491   25-91   25.981(c)   25-102 
 25.499   25-23   25.993   25-0 
 25.561(a-c)  25-23   25.1013   25-0 
 25.571(a-d)  25-54   25.1091   25-0/25-57 
 25.571(e)   25-54   25.1103   25-0 
 25.573   25-0    25.1121   25-0 
 25.629   25-72   25.1141   25-72 
 25.657   25-0    25.1163   25-0 
 25.671   25-0    25.1181   25-0/25-72 
 25.683   25-0    25.1183   25-57 
 25.685   25-0    25.1189   25-0 
 25.693   25-0    25.1199   25-0 
 25.695   25-0    25.1203   25-26 
 25.697   25-0    25.1205   25-0 
 25.701   25-0    25.1301   ARAC RECOMMENDED 
 25.721   25-0    25.1303   SC NO. 25-ANM-124 
 25.729   25-0    25.1309   ARAC RECOMMENDED 
 25.775   25-0    25.1317   SC NO. 25-ANM-125 
 25.783   25-0    25.1321   SC NO. 25-ANM-124  
 25.785   25-0    25.1322   25-38  
 25.789   25-46   25.1329   25-46 
 25.809   25-9    25.1335   25-41 
 25.801(a)(2)  25-72   25.1359   25-0 
 25.811(a)(e-g)  25-0    25.1411   25-0

17 of 23 A1SO 
 25.811(b-d)  25-0    25.1415   25-0 
 25.812(a)(1)(e)(h-j) 25-15   25.1419   25-72 
 25.813   25-0    25.1435   25-0 
 25.831   25-41   25.1557   25-0 
 25.841   25-38   C25.1   25-0 
 25.851   25-0    F25.2   25-72 
 25.853   25-72    I25.1 thru .6  25-137-SC 
 25.855   25-123    I25.1   SC No. 25-AMN-125 
 25.863   25-0    36.1    36-30 
 25.901   25-0/25-46    
 25.903   25-94    
 
Weight & C.G. Limits Condition Wt./lbs. Most Fwd. C.G. Most Aft C.G. 
   (gear up or down)   %MAC F.S. %MAC 
 Ramp 164,00 21.2 522.3 30 
 Take-off 164000 22.1 523.8 30 
 Landing 143,000 19.7 519.7 30 
 Zero fuel 129,000 17.6 516.4 30 
 
Cargo compartment Length   55.0 ft 
 Width   9 ft. 11½ in. 
 Height   9 ft. 
 Usable volume approx. 5,836 cu. ft. 
 Maximum cargo See SMP 3518 
  
 Loading data for approved loading schedules are contained in Lockheed Cargo 
Compartment Loads Document No.  LM01-800002-626A.  Individual aircraft weight and 
balance data are contained in Lockheed Weight and Balance Manual SMP 3518. 
 
 
Manufacturer's Serial Numbers 5818 and up. 
 
 
 
DATA PERTINENT TO ALL MODELS: 
Certification Basis CAR 1 dated October 1, 1955, and Amendments 1-1 through 1-9. 
 
 CAR 9a effective 10 January 1964, which references CAR 4b amended to 31 December 
1953, including Amendments 4b-1 through 4b-11, together with SR-422B, SR-450A and 
amendment 4b-12 as related to CAR 4b.307(a). 
 
                                                       Based on 14 CFR § 21.17(a) for new type certificates (TCs), (or 14 CFR § 21.101(g) for 
changes to TCs), applicable provisions of 14 CFR part 26 are included in the 
certifaication basis.  For any future 14 CFR part 26 amendments, the holder of this TC 
must demonstrate compliance with the applicable sections. 
 
 The Lockheed Model 382J (S/N 5408) was certified as a derivative aircraft and its 
certification basis was established in accordance with FAA Order 8110.23.  For 
unmodified systems and airframe components, which do not alter the basic system 
function or capability, the certification basis is FAR Part 25, dated February 1, 1965.  For 
new systems, and those systems which have been significantly modified to alter its basic 
function or capability, compliance was shown to FAR 25, dated 1 February 1965, as 
modified by Amendment 25-1 through 25-76, except that: 
 
 Compliance with the amendment levels of the following paragraphs was shown: 
 Paragraph  Amendment 
 25.143   25-0 
 25.147   25-0 
 25.149   25-0 
 25.361   25-46

A1SO 18 of 23 
 25.629   25-72 
 25.1001   25-18 
 25.1316   25-81 
 25.1505   25-22 
  
 Compliance was shown to the equivalent CAR 4b requirement for the following FAR 25 
requirements: 
  
 FAR 25   CAR 4b 
 25.161   4b.143 
 25.365   4b.216 
 25.457   4b.221 
  
 Special conditions applicable to the Model 382J (S/N 5408) are shown in the attachments 
to the following FAA letters to Lockheed Martin:  April 16, 1997, May 19, 1997, and 
February 6, 1998. 
 
 FAR 91 effective September 30, 1963. 
 
 Application for Type Certificate dated April 23, 1964. 
 
 Type Certificate A1SO issued February 16, 1965. 
 
 Compliance with CAR 4b.361, Ditching Provisions, has been established. 
 
 Compliance with CAR 4b.640, Ice Protection, has been established.  Compliance with 
FAR 25.1419 has been established for the Model 382J S/N 5408. 
 
 Compliance with Amendments 4b-11 (CAR 4b.334), Wing Flap Aural Warning, has 
been established. 
 
 Compliance with FAR 25.1001 as amended by 25-18 effective September 28, 1968, has 
been established. 
 
 For the Model 382G, compliance has been shown with FAR 21.93(b), effective 
December 1, 1969, in that noise levels have not been increased. 
 
 For Models 382E, 382G, and 382J compliance with FAR 36.1(d)(1), noise standards, has 
been established.  The Models 382E, 382G, and 382J (S/N 5408)also meet FAR 36, 
Stage 3 noise requirements. The Model 382J (LM-100J) meets 14 CFR Part 36, Stage 5 
noise requirements. 
 
                                                        Compliance has been found for the following regulations: 14 CFR § 26.11, 26.43 and 
26.45, (Amdt. No. 26-0 through 26-3).  
 
Production Basis Production Certificate No. 205 
 
Equipment The basic required equipment, as prescribed in the applicable airworthiness regulations 
(see certification basis), must be installed in the aircraft for certification.  Approved 
Equipment for Model 382 is shown on Master Equipment List ER-9798.  Approved 
equipment for the Models 382B, 382E, and 382F, S/N 4101 through 4933 is shown in 
the Master Equipment List, Lockheed Report ER-9710, revised October 4, 1968, or later 
FAA approved revision.  Approved equipment for Lockheed Models 382B, 382E, and 
382F, S/N 4350 and up is shown on Lockheed Drawing 3303609, Type Design 
Equipment List, latest FAA approved revision.  Approved equipment for the Lockheed 
Model 382G is shown on Lockheed Drawings 3331262-1 and 393201-3.  Approved 
equipment for the Model 382J (S/N 5408) is shown on Lockheed Drawings 3331262-
1and 3350139-1/3/7. 
 
Control Surface Movements Rudder 35° right 35° left 
 Elevator 40° up 15° down

19 of 23 A1SO 
 Ailerons 25° up 15° down 
 Rudder Tab 25° right 25° left 
 Elevator Tab 6° up 25° down 
 Aileron Tab 20° up 20° down 
 Wing flap 36° down     (100%)  
 
Service information Lockheed operations and maintenance instructions, service bulletins and other service 
information, when FAA approved, will carry a statement to that effect. 
 
NOTE 1. a. Current weight and balance report, including a list of equipment in certificated empty weight, and 
loading instructions when necessary, must be in each airplane at the time of original certification and at 
all times thereafter except in the case of operators having an approved weight control system.  Approved 
weight and balance data for the Model 382 is contained in Lockheed Report ER-9511.  Approved 
weight and balance data for the Model 382B is contained in Lockheed Report ER-8083.  Approved 
weight and balance data for Model 382E airplanes, ship serials 4222 and 4225, is contained in ER -
10285.  Approved weight and balance data for the remaining Model 382E airplanes and all Model 382F 
airplanes is contained in Lockheed Report ER-9511. 
 
  Approved weight and balance data for the Model 382G is contained in Lockheed Report ER-10761.  
Individual aircraft weight and balance data are contained in Lockheed Report SMP 521 (Model 382B), 
SMP 521-2 (382, 382E and 382F), SMP 521 -3 (ship serials 4222 and 4225), and SMP 521 -4  
  (Model 382G). 
 
  Approved weight and balance data for the Model 382J (S/N 5408) is contained in Lockheed report 
LG95ER0192.  Individual aircraft weight and balance data are contained in Lockheed Report SMP 521 -
5. Approved weight and balance data for Model 382J (LM-100J), are contained in Lockheed report 
LM01-800002-626A. Individual aircraft weight and balance data are contained in Lockheed Report 
SMP 3518. 
 
 b. The airplane must be loaded so that the C.G. is within the specified limits at all times.  Moment change 
due to gear retraction is negligible. 
 
 c. The weight of the system fuel and oil as defined below, and hydraulic fluid, must be included in the 
airplane empty weight. 
 
 System fuel:  The weight of all fuel required to fill all lines and tanks up to the zero point on the fuel 
 gauges in the level flight attitude.  Unusable (includes drainable and trapped fuel):

A1SO 20 of 23 
 Unusable fuel aircraft serial 4101 through 4581. 
 
 Tank Wt./lbs. Arm (F.S.) Arm (T.S.) 
 1 (outboard) 93 555.3 +28.3 
 2 (inboard) 141 565.4 +38.4 
 3 (inboard) 141 565.4 +38.4 
 4 (outboard) 93 555.3 +28.3 
 Left Aux. *60 564.0 +37.0 
 Right Aux. *60 564.0 +37.0 
 Left Ext. (Lockheed P/N 388236) **110 552.0 25.0 
 Right Ext. (Lockheed P/N 388236) **110 552.0 +25.0 
 Lines .....44   
  852   
     
 Left Ex.  (Lear Siegler P/N 305J001) **144 552.0 +25.0 
 Right Ext.  (Lear Siegler P/N 305J001) **144 552.0 +25.0 
  920   
 
  Unusable fuel aircraft serial 4582 and up (except Model 382J). 
 
 Tank Wt./lbs. Arm (F.S.) Arm (T.S.) 
 1 (outboard) 84 555.3 +28.3 
 2 (inboard) 97 565.4 +38.4 
 3 (inboard) 97 565.4 +38.4 
 4 (outboard) 84 555.3 +28.3 
 Left Aux. *60 564.0 +37.0 
 Right Aux. *60 564.0 +37.0 
 Left Ext. (Lockheed P/N 388236) Lines **110 552.0 25.0 
 Right Ext. (Lockheed 
P/N 388236)  
**110 552.0 +25.0 
 
 Lines   44   
  746   
     
 Left Ex.  (Lear Siegler P/N 305J001) **144 552.0 +25.0 
 Right Ext.  (Lear Siegler P/N 305J001) **144 552.0 +25.0 
  814   
     
   *  See NOTE 4    
 **  See NOTE 8    
 
  Unusable fuel aircraft Model 382J, serial 5408. 
  
 Tank Wt./lbs. Arm (F.S.) Arm (T.S.) 
 1 (outboard) 186 552.2 +25.2 
 2 (inboard) 97 565.1 +38.1 
 3 (inboard) 97 565.1 +38.1 
 4 (outboard) 186 552.2 +25.2 
 Left Aux. *62 565.9 +38.9 
 Right Aux. *62 565.9 +38.9 
 Lines   44   
   690   
   *  See NOTE 4    
 
 A density of 6.9 lbs./gal. was used in calculating unusable fuel weights. 
 
 System oil:  The weight of oil remaining in the engine lines and tanks after subtracting the usable oil from the 
total capacity.

21 of 23 A1SO 
 
 Total:  221 lbs., Arm 442.0 (Model 382 and 382B), 
 Trim Station - 85.0  (Model 382E and 382G). 
  
 Total:     108 lbs.      (Model 382J) 
 Trim Station:  -77.0 
 
 Fuel loading and usage: 
  1. Fuel must be loaded and used to provide compliance with the "Fuel Unbalance" limitations  
   contained in the approved Airplane Flight Manual. 
 
  2. Refer to the approved Airplane Flight Manual for normal fuel management procedures. 
 
  3. Phillips fuel additive PFA-55MB may be used in concentrations not to exceed 0.15% by volume.  
 No fuel system anti-icing credit is allowed. 
 
NOTE 2. The following Airplane Flight Manuals are required:  For the Model 382B, AFM Lockheed Publication SMP 
514, dated October 5, 1965 (with appropriate revisions), for the Model 382F, AFM Lockheed 
Publication SMP 760, dated December 3, 1969 (with appropriate revisions), and for the Models 382, 
382E, and 382G, AFM 382/E/G, dated August 30, 1978 (with appropriate revisions).  For the Model 
382J (S/N 5408), Lockheed publication AFM 382J, dated September 9, 1998 is required.  For Model 
382J (LM-100J)), Lockheed publication AFM 382J (SMP 3510), dated November 15, 2019 is required. 
 
NOTE 3. a. Propeller blade angles are measured at the blade 42 inch stations with the propeller on a test post under 
conditions established by the applicable Hamilton Standard Maintenance Manual. 
 
 b. Propeller blade angles are indicated on the back-up valve housing under conditions established in the 
applicable Lockheed Model 382 Maintenance Manual. 
 
 c. 1° blade angle is a running blade angle and corresponds to a static coordinator pointer position of 10° ± 
1°.  This position is obtained with the throttle lever in the ground idle aft detent.  
 
 d.     For the Model 382J, propeller blade angles are measured at seventy percent of blade radius. 
 
NOTE 4. Auxiliary fuel tanks are eligible for installation in the Model 382B and 382E and 382F when installed  
 according to Lockheed Drawing 393830 and PS 101 for 382B up to S/N 4299, and Drawing 399301 for  
 aircraft with S/n 4299 and up. 
 
NOTE 5. The basic model numbers of the aircraft are 382, 382B, 382E, 382F, 382G, and 382J.  The nameplate  
 contains two sets of additional numbers; the first set represents the engine and the second set represents  
 the type of fuselage on initial issue of the standard airworthiness certificate. 
 
 EXAMPLES: 
 
 1. 382B-44B-17 contains 501-D22 engines and short fuselage. 
 
 2. 382E-44K-20 contains 501-D22A engines and has the 100 inch fuselage stretch. 
 
 3. 382F-44B-20 contains 501-D22 engines and has the 100 inch fuselage stretch. 
 
 4. 382G-44K-30 contains 501-D22A engines and has the 180 inch fuselage stretch 
 
  The Model numbers are specified in ER-206M, Addendum A. Incorporation of Supplemental Type 
Certificate ST395SO modifies a 382B to 382E configuration and is noted with the installation of a 
modification data plate.  The basic model remains 382B on the registration and airworthiness 
certificates.  The modified airplane is operated in accordance with the Model 382E data contained in the 
data sheet and in the Airplane Flight Manual, Lockheed Publication AFM 382/E/G dated

A1SO 22 of 23 
 
  August 30, 1978.  Incorporation of Supplemental Type Certificate ST425SO modifies a 382B to a 382F 
configuration and is noted with the installation of a modification data plate.  The basic model remains 
382B on the registration and airworthiness certificates.  The modified airplane is operated in accordance 
with the Model 382F data contained in the data sheet and in the Airplane Flight Manual, Lockheed 
Publication SMP 760, dated 3 December 1969.  Incorporation of Supp lemental Type Certificate 
ST446SO modifies a Model 382B to a 382G configuration and is noted with the installation of a 
modification data plate.  The basic model remains 382B on the registration and airworthiness 
certificates.  The modified airplane is operated in accordance with the Model 382G data contained in the 
data sheet and in the Airplane Flight Manual, AFM 382/E/G, dated August 30, 1978.  
 
 The suffix -1C, -2C, etc., appearing on the aircraft data plate designates a customer peculiar configuration, 
which includes variations in equipment installations from the basic model airplane. 
 
NOTE 6. FAA Exemption No. 319 is pertinent to the civil certification of this model aircraft and will be noted on all  
 Certificates of Airworthiness. 
 
NOTE 7. For all Model 382 aircraft, except the Model 382J:  The 373118 beam at W.L. 195, F.S. 93 to 172, must be  
replaced after every 40,000 flight hours.  For the Model 382J (S/N 5408), mandatory inspections and life 
limited components are listed in Lockheed Report J61C05A626, “Maintenance Program for Lockheed 
Model382J (S/N 5408),” dated 26 August 1998, or later FAA approved revision. For Model 382J (LM-
100J), mandatory inspections and life limited components are listed in Lockheed Report PMC-L382-98897-
MI000-00, “Aircraft Scheduled Inspections and Maintenance Requirements Manual Work Cards”. 
 
NOTE 8.  External fuel tanks are eligible for removal in accordance with the maintenance manuals for the Models 
 382, 382B, 382E, 382F, and 382G airplanes.  For Model 382J series External tanks are not part of 
the certification basis. 
 
NOTE 9. Maximum Fuel Quantity for aircraft S/N 4582 and up (except the Model 382J). 
 
Maximum fuel quantity Aircraft S/N 4101 through 4581.  See NOTE 9 for aircraft S/N 4582 and up. 
 
  Tank Usable Fuel Total Fuel F.S. Arm (Full)  T.S. 
 1 (outboard) 9247 lbs. 9331 lbs. 545.2 +18.2 
 2 (inboard) 8481 lbs. 8578 lbs. 555.0 +28.0 
 3 (inboard) 8481 lbs. 8578 lbs. 555.0 +28.0 
 4 (outboard) 9247 lbs. 9331 lbs. 545.2 +18.2 
 **  Left Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 
 ** Right Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 
 *** Left External 9355 lbs. 9465 lbs. 551.2 +24.2 
 *** Right External     9355 lbs.     9465 lbs. 551.2 +24.2 
   66,704 lbs. *67,406 lbs. (549.9)  
       
 **** Left External 9355 lbs. 9499 lbs. 551.2 +24.2 
 **** Right External     9355 lbs.     9499 lbs. 551.2 +24.2 
 ****  66,704 lbs. *67,474 lbs. (549.9)  
 
 * Does not include line fuel (See NOTE 1 (c)). 
 ** Optional tank installations. 
 *** Optional external tank installation (Lockheed P/N 388263) 
 **** Optional external tank installation (Lear Siegler P/N 305J001) 
 
     See NOTE 1 for unusable fuel. 
 
NOTE 10. For the Model 382J (S/N 5408), no issuance of a standard certificate of airworthiness is permissable without 
FAA approval of a maintenance review board (MRB) report and a maintenance program per the requirements 
of Advisory Circular 121.22A.

23 of 23 A1SO 
 
Note 11.   For Model 382J (LM-100J), the following Exemptions, Equivalent Levels of Safety (ELOSs), Special 
Conditions apply: 
  
 Exemptions:  
 Exemption No. 17185 for 25.335(e)(3) and 25.473(a)(2)  
 Exemption No. 17702 for 25.981(a)(3) 
    
 Equivalent Level of Safety (ELOS) for 25.1301 and 25.1309 ARAC Recommend 
 
 Special Conditions for; 25.1317, SC NO. 25-ANM-125 
           25.1321 and 25.1303, SC NO. 25-ANM-124 
           Appendices I25.1 thru .6, 25-137-SC 
           Appendices L25.1, SC No. 25-AMN-125 
  
Note 12.   For Model 382J (LM-100J) Fire Containment Covers (FCCs) must be used in accordance with SMP 3520 
(382J Cargo Loading Manual) and must meet the qualification test requirements on Lockheed Martin 
Source Control Drawing (SCD) 698490. 
...END...
```

## ADs (59, first 50, 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 2024-01-02](https://openairdocs.org/ad/2024-01-02): Fuselage · Lockheed 382, 382B, 382E and 9 more. Effective Jan 24, 2024
- [AD 2023-22-06](https://openairdocs.org/ad/2023-22-06): Powerplant · Lockheed Martin 382, 382B, 382E and 8 more. Effective Nov 21, 2023
- [AD 2023-11-10](https://openairdocs.org/ad/2023-11-10): Fuselage · Lockheed Martin 382, 382B, 382E and 9 more. Effective Jul 11, 2023
- [AD 2023-09-13](https://openairdocs.org/ad/2023-09-13): Wings · Lockheed Martin 382, 382B, 382E and 7 more. Effective May 31, 2023
- [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 2021-09-15](https://openairdocs.org/ad/2021-09-15): Wings · Coulson EC-130Q, C-130A, C-130A and 11 more. Effective Jun 1, 2021
- [AD 2019-25-20](https://openairdocs.org/ad/2019-25-20): Flight controls · Coulson EC-130Q, C-130A, C-130A and 11 more. Effective Feb 28, 2020
- [AD 2015-22-11](https://openairdocs.org/ad/2015-22-11): Wings · Lockheed Martin 382, 382B, 382E and 2 more. Effective Dec 28, 2015
- [AD 2015-18-02](https://openairdocs.org/ad/2015-18-02): Wings · Lockheed Martin 382, 382B, 382E and 2 more. Effective Sep 17, 2015
- [AD 2015-06-08](https://openairdocs.org/ad/2015-06-08): Wings · Lockheed Martin 382, 382B, 382E and 2 more. Effective May 14, 2015
- [AD 2015-05-08](https://openairdocs.org/ad/2015-05-08): Wings · Lockheed Martin 382, 382B, 382E and 2 more. Effective Apr 24, 2015
- [AD 2014-17-02](https://openairdocs.org/ad/2014-17-02): Communications · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 137 more. Effective Sep 9, 2014
- [AD 2012-06-09](https://openairdocs.org/ad/2012-06-09): Standard practices/structures · Lockheed Martin 382, 382B, 382E and 2 more. Effective May 15, 2012
- [AD 2011-15-02](https://openairdocs.org/ad/2011-15-02): Fuel · Lockheed Martin 382, 382B, 382E and 2 more. Effective Aug 19, 2011
- [AD 2009-11-03](https://openairdocs.org/ad/2009-11-03): Wings · Lockheed Martin 382, 382B, 382E and 2 more. Effective Jun 4, 2009
- [AD 2009-08-01](https://openairdocs.org/ad/2009-08-01): Honeywell FMSs · Bombardier CL-600-2B16 (CL-601-3A), CL-600-2B16 (CL-601-3R), CL-600-2B16 (CL-604) and 11 more. Effective May 14, 2009
- [AD 2008-14-10](https://openairdocs.org/ad/2008-14-10): Upper engine mount bolts · Lockheed Martin 382, 382B, 382E and 3 more. Effective Jul 22, 2008
- [AD 2006-19-04](https://openairdocs.org/ad/2006-19-04): Honeywell COM unit and Mode S transponder · Bombardier BD-700-1A10, BD-700-1A11, 550 and 26 more. Effective Oct 17, 2006
- [AD 2003-14-16](https://openairdocs.org/ad/2003-14-16): Latch mechanism · Lockheed Martin 382G. Effective Aug 25, 2003
- [AD 2001-22-14](https://openairdocs.org/ad/2001-22-14): Fire Extinguishing System Bottle Cartridges · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 105 more. Effective Dec 10, 2001
- [AD 99-25-04](https://openairdocs.org/ad/99-25-04): Floor to Ring Fittings · Lockheed Martin 382, 382B, 382E and 3 more. Effective Jan 7, 2000
- [AD 97-21-13](https://openairdocs.org/ad/97-21-13): AFM - Power Levers · Lockheed Martin 382, 382B, 382E and 2 more. Effective Nov 24, 1997
- [AD 97-05-07](https://openairdocs.org/ad/97-05-07): AFM Supplement 382-16 · Lockheed Martin 382, 382E and 382G. Effective Apr 4, 1997
- [AD 97-04-15](https://openairdocs.org/ad/97-04-15): Fire Extinguisher Bottle Cartridges · Bombardier DHC-8-101, DHC-8-102, DHC-8-103 and 24 more. Effective Mar 7, 1997
- [AD 96-24-14](https://openairdocs.org/ad/96-24-14): Main Landing Gear Brakes Inspection · Lockheed Martin 382, 382B, 382E and 2 more. Effective Jan 27, 1997
- [AD 95-07-03](https://openairdocs.org/ad/95-07-03): Auxiliary Power Units · Allliedsignal Aerospace Auxiliary Power Units, 707-100 Long Body, 707-100B Long Body and 46 more. Effective May 3, 1995
- [AD 94-26-15](https://openairdocs.org/ad/94-26-15): Outer Wing Assembly · Lockheed Martin 382, 382B, 382E and 2 more. Effective Feb 3, 1995
- [AD 92-10-14](https://openairdocs.org/ad/92-10-14): AFM Changes - Cabin Pressure · Lockheed Martin 382, 382B, 382E and 2 more. Effective Jun 29, 1992
- [AD 90-04-02](https://openairdocs.org/ad/90-04-02): Fire Extinguisher Squibs · Lockheed Martin 382G. Effective Feb 26, 1990
- [AD 89-16-09](https://openairdocs.org/ad/89-16-09): Nose Landing Gear Strut Assembly · Lockheed Martin 382, 382B, 382E and 2 more. Effective Sep 7, 1989
- [AD 88-09-03](https://openairdocs.org/ad/88-09-03): Control Column Base · Lockheed Martin 382, 382B, 382E and 2 more. Effective Jun 7, 1988
- [AD 88-10-05](https://openairdocs.org/ad/88-10-05): Wing Panel Doublers · Lockheed Martin 382, 382B, 382E and 2 more. Effective May 25, 1988
- [AD 88-10-06](https://openairdocs.org/ad/88-10-06): Wing Panel Risers · Lockheed Martin 382, 382B, 382E and 2 more. Effective May 25, 1988
- [AD 87-18-04](https://openairdocs.org/ad/87-18-04): Circuit Breaker Panels · Lockheed Martin 382, 382B, 382E and 2 more. Effective Sep 17, 1987
- [AD 85-23-03](https://openairdocs.org/ad/85-23-03): Fire Estinguisher Squib Insp. · Lockheed Martin 382, 382B, 382E and 2 more. Effective Nov 24, 1985
- [AD 81-12-02](https://openairdocs.org/ad/81-12-02): Longerons · Lockheed Martin 382, 382B, 382E and 2 more. Effective Jun 5, 1981
- [AD 79-05-05](https://openairdocs.org/ad/79-05-05): Throttle Cables · Lockheed Martin 382, 382B, 382E and 2 more. Effective Jan 2, 1980
- [AD 79-25-06](https://openairdocs.org/ad/79-25-06): Window Latch Catches · Lockheed Martin 382, 382B, 382E and 2 more. Effective Dec 19, 1979
- [AD 79-18-12](https://openairdocs.org/ad/79-18-12): Auxiliary Power Units · Airbus BAC 1-11 200 Series, BAC 1-11 400 Series, Manufacturing Company Auxiliary Power Units and 46 more. Effective Oct 8, 1979
- [AD 79-03-04](https://openairdocs.org/ad/79-03-04): Ballscrew Assembly in MLG · Lockheed Martin 382, 382B, 382E and 2 more. Effective Feb 5, 1979
- [AD 74-12-06](https://openairdocs.org/ad/74-12-06): Outer Wing Beam Cap · Lockheed Martin 382, 382B, 382E and 2 more. Effective Dec 8, 1978
- [AD 75-17-04](https://openairdocs.org/ad/75-17-04): Main Frames · Lockheed Martin 382, 382B, 382E and 2 more. Effective Apr 21, 1978
- [AD 75-18-03](https://openairdocs.org/ad/75-18-03): Outer Wing Spar Cap · Lockheed Martin 382, 382B, 382E and 2 more. Effective Mar 20, 1978
- [AD 75-18-04](https://openairdocs.org/ad/75-18-04): Outer Wing Lower Panels · Lockheed Martin 382, 382B, 382E and 2 more. Effective Mar 20, 1978
- [AD 75-19-02](https://openairdocs.org/ad/75-19-02): Wing Beam Caps · Lockheed Martin 382, 382B, 382E and 2 more. Effective Mar 20, 1978
- [AD 76-09-11](https://openairdocs.org/ad/76-09-11): Crank Arm or Servo Valve Assembly · Lockheed Martin 382, 382B, 382E and 2 more. Effective May 14, 1976
- [AD 75-17-35](https://openairdocs.org/ad/75-17-35): Propeller Torque Check · Lockheed Martin 382, 382B, 382E and 2 more. Effective Aug 13, 1975
- [AD 74-24-08](https://openairdocs.org/ad/74-24-08): Engine Throttle Cables · Lockheed Martin 382, 382B, 382E and 2 more. Effective Nov 27, 1974
- [AD 74-24-04](https://openairdocs.org/ad/74-24-04): Lower Center Wing · Lockheed Martin 382, 382B, 382E and 2 more. Effective Nov 20, 1974

All 59: https://openairdocs.org/tcds/A1SO/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Lockheed 382G](https://openairdocs.org/model/lockheed-382g): 5 aircraft (registry code 526414U)
- [Lockheed Martin 382J](https://openairdocs.org/model/lockheed-martin-382j): 5 aircraft (registry code 5264153)
- [Lockheed 382 44C (C130K)](https://openairdocs.org/model/lockheed-382-44c-c130k): 1 aircraft (registry code 526021A)
- [Lockheed 382](https://openairdocs.org/model/lockheed-382): 0 aircraft (registry code 5264102)
- [Lockheed 382B](https://openairdocs.org/model/lockheed-382b): 0 aircraft (registry code 5264104)
- [Lockheed 382E](https://openairdocs.org/model/lockheed-382e): 0 aircraft (registry code 526413U)

## STCs approved under this data sheet (102, first 50)

- [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center
- [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 SA7757SW](https://openairdocs.org/stc/SA7757SW): Interior installation for 97 passengers. Lynden Air Cargo LLC
- [STC ST02537LA](https://openairdocs.org/stc/ST02537LA): Installation of below the floor retardant tank. Coulson Aviation (USA) Inc.
- [STC ST02584LA](https://openairdocs.org/stc/ST02584LA): Installation of Retardant Aerial Delivery System (RADS) XXL. Coulson Aviation (USA) Inc.
- [STC ST02254CH](https://openairdocs.org/stc/ST02254CH): Installation of Honeywell Enhanced Ground Proximity Warning System and Honeywell Multi Function Radar Display. Amphenol Cable and Interconnect Technologies Inc.
- [STC ST02583AK](https://openairdocs.org/stc/ST02583AK): Installation of Pallet Retention Aerial Delivery System (PRADS). Lynden Air Cargo LLC
- [STC ST02771AT](https://openairdocs.org/stc/ST02771AT): Installation of an Enhanced Ground Proximity Warning System (EGPWS). Woven Electronics, LLC
- [STC ST02773AT](https://openairdocs.org/stc/ST02773AT): Installation of an Global Positioning System (GPS). Woven Electronics, LLC
- [STC ST02772AT](https://openairdocs.org/stc/ST02772AT): Installation of a Honeywell CAS-81 Traffic Alert and Collision Avoidance System (TCAS) and a single TRA-67 Mode-S Transmitter System. Woven Electronics, LLC
- [STC ST02571AK](https://openairdocs.org/stc/ST02571AK): Installation of the Propeller Pre-Heat System. Lynden Air Cargo, LLC
- [STC ST02109CH](https://openairdocs.org/stc/ST02109CH): Installation of a Honeywell RESCU 406AF/AFN Emergency Locator Transmitter (ELT) System. Honeywell International Inc.
- [STC ST02550AK](https://openairdocs.org/stc/ST02550AK): Installation of a Digital Fuel Quantity Indication System. Lynden Air Cargo LLC
- [STC ST03679NY](https://openairdocs.org/stc/ST03679NY): Installation of the Propeller Pre-Heat System. Lynden Air Cargo LLC
- [STC ST03680NY](https://openairdocs.org/stc/ST03680NY): Installation of the Propeller Pre-Heat System. Lynden Air Cargo LLC
- [STC ST02511AK](https://openairdocs.org/stc/ST02511AK): Installation of aft fuselage microvanes. Lynden Air Cargo LLC
- [STC ST02495LA](https://openairdocs.org/stc/ST02495LA): Installation of a multipurpose hatch system. R4 Integration Inc
- [STC ST01162LA](https://openairdocs.org/stc/ST01162LA): Activation of the Enhanced Mode S Transponder function and installation of the Avionics Upgrade on the Lockheed 382G airplane. Honeywell International Inc
- [STC ST00221BO](https://openairdocs.org/stc/ST00221BO): Installation of a BAE Systems IRCM.. BAE SYSTEMS Information and Electronic Systems Integration Inc.
- [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 SA3589SW](https://openairdocs.org/stc/SA3589SW): Installation of an auxiliary power unit and freon air conditioning system in each of two wing pods.. Aircraft Technical Development Inc. dba Aerocon Engineering Company
- [STC ST00113AT](https://openairdocs.org/stc/ST00113AT): Installation of a replacement coalescer filter, P/N 21BC107.. Purolator Facet, Inc
- [STC ST04367AT](https://openairdocs.org/stc/ST04367AT): Removal of the Existing Honeywell DL-900 or DL-950 Data Loader and Installation of the Honeywell DL-1000 Data Loader. Chippewa Aerospace Inc
- [STC ST00881WI-D](https://openairdocs.org/stc/ST00881WI-D): Modification of a TCAS II system installation to Change 7.0 or Change 7.1. Rockwell Collins Inc
- [STC SA2929WE](https://openairdocs.org/stc/SA2929WE): Installation of palletized dual LTN-51 or dual LTN-72 INS or combination of either.. Northrop Grumman Systems Corporation
- [STC ST03644NY](https://openairdocs.org/stc/ST03644NY): See STC: Attachment - ST03644NY.pdf.. First Air
- [STC SA3934NM](https://openairdocs.org/stc/SA3934NM): Fabrication of Biegert Airborne dispersant delivery system (ADDS).. Oil Spill Response (Americas) Limited
- [STC SA733CE](https://openairdocs.org/stc/SA733CE): Installation of cargo pallets.. Telair US LLC
- [STC ST00772CH](https://openairdocs.org/stc/ST00772CH): Install Cargo Handling System. Telair US LLC
- [STC ST427SO](https://openairdocs.org/stc/ST427SO): Installation of cargo rail system. Telair US LLC
- [STC ST03595AT](https://openairdocs.org/stc/ST03595AT): Installation of a LED Anticollision Lights. B/E Aerospace Inc
- [STC ST03595T](https://openairdocs.org/stc/ST03595T): Installation of a LED Anticollision Lights. Woven Electronics, LLC
- [STC ST02524LA](https://openairdocs.org/stc/ST02524LA): Installation of TCAS version 7.0. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC ST02437AK](https://openairdocs.org/stc/ST02437AK): Installation of Software Version 6.1 on Honeywell FMZ-2000, ADS-B Out and WAAS/LPV capabilities. Lynden Air Cargo LLC
- [STC ST01635WI-D](https://openairdocs.org/stc/ST01635WI-D): Modification of Rockwell Collins, Inc. VHF-4000 and VHF-4000E installations. Rockwell Collins Inc
- [STC SA3132NM](https://openairdocs.org/stc/SA3132NM): Installation of a de-icing system on the Hamilton Standard P/N 554654 propeller spinner.. ROBERT W. MURRAY
- [STC SA3407NM](https://openairdocs.org/stc/SA3407NM): Installation of a de-icing system on the Hamilton Standard P/N 560501 propeller spinner afterbody.. ROBERT W. MURRAY
- [STC ST02369LA](https://openairdocs.org/stc/ST02369LA): :    Installation of provisions for Mission System Equipment (MSE), in accordance with FAA approved BAE Master Data List, 0139A1003, Revision A, dated August 26, 2011, or later FAA approved revisions.. BAE Systems
- [STC ST01202WI-D](https://openairdocs.org/stc/ST01202WI-D): Modification of an existing FAA approved Collins TPR-720, TPR-900 or TPR-901 Mode S transponder installation in Part 25 Aircraft using Collins Drawing Index as listed on AML No. ST01202WI-D, latest FAA approved revision.. Rockwell Collins Inc
- [STC ST03600AT](https://openairdocs.org/stc/ST03600AT): Installation of a Wingspeed Iridium Communication Management System and Dual DAC International Electronic Flights Bags (EFBs).. Avionics Support Group Inc.
- [STC ST02282LA](https://openairdocs.org/stc/ST02282LA): ONE ONLY STC, SN 4954: Installation of Potable Water and Waste System.. Dynamo Aviation Inc.
- [STC ST01256WI-D](https://openairdocs.org/stc/ST01256WI-D): Modification of a Collins TPR-720, TPR-900 or TPR-901 Mode S Transponder System installation with an ATC/TCAS Control Panel to an Elementary Surveillance Compliant Collins TPR-901 Mode S Transponder System installation with a Flight ID/ATC/TCAS Control Panel in accordance with Collins Drawing Index as listed on AML No. ST01256WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc
- [STC ST00435CH-D](https://openairdocs.org/stc/ST00435CH-D): Installation of a Collins TCAS-94 Traffic Alert and Collision Avoidance System (TCAS-II) system.. Duncan Aviation Inc
- [STC ST434CH-D](https://openairdocs.org/stc/ST434CH-D): Installation of Dual Trimble TNL8100 GPS Navigation Systems.. Duncan Aviation Inc
- [STC SA1625WE](https://openairdocs.org/stc/SA1625WE): Pallet assembly provisions.. Lockheed Martin Aeronautics Company
- [STC ST00224AT](https://openairdocs.org/stc/ST00224AT): Installation of an Expanded Parameters Digital Flight Data Recorder.. ASB Avionics
- [STC ST02020NY](https://openairdocs.org/stc/ST02020NY): Installation of Ayles Fernie International (AFI) NIMBUS Oil Dispersant Spraying System.. Amtech Aeronautical Limited
- [STC SA02365CH](https://openairdocs.org/stc/SA02365CH): Installation of NASI Supplemental Air-Conditioning System. National Aircraft Service Inc
- [STC ST02274AK](https://openairdocs.org/stc/ST02274AK): Manufacture and  install bulk fuel tank system.. Lynden Air Cargo LLC
- [STC ST01307WI-D](https://openairdocs.org/stc/ST01307WI-D): Modification of a Collins TVI-920/TVI-920D Vertical Speed/TCAS Indicator installation. Rockwell Collins Inc

All 102: https://openairdocs.org/tcds/A1SO/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.