# TCDS 4A22: Lockheed Martin Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Lockheed Martin Corporation
- Revision: 14
- Revised: January 11, 2010
- Product: Aircraft, Large Airplane
- Certification basis: CAR 4b
- Registered aircraft: 4, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/4a/0f/4a0f6e58d12854edc1dc24f26df8e101b1e5ede8e8f0dd669cdde01d503aa9bc
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BB0ABA041A44E220862576AC0056B343.0001
- Page: https://openairdocs.org/tcds/4A22

## Models (2)

As the data sheet lists them.

- 188A
- 188C

## What the data sheet says

This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers.

```text
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
4A22
Revision 14
LOÇKHEED
188A
188C
January 11, 2010
TYPE CERTIFICATE DATA SHEET NO. 4A22
This data sheet which is a part of type certificate No. 4A22 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 Corporation
Lockheed Martin Aeronautis Company
86 South Cobb Drive
Marietta, Georgia 30063-0655
I. - Model 188A (Transport Category), Approved August 22, 1958 (See NOTE 6)
Engines  4 Allison 501-D13 or 501-D13A (used with Ham. Std. prop)
Turboprop with 13.54:1 reduction gear ratio (See NOTE 6.)
Fuel  Kerosene (Allison Spec EMS 64C) or JP4 (MIL-F-5624C) See NOTE 1(e)(4).
Lubricating Oil  Allison Spec EMS-35E or EMS-53
Engine Limits  Takeoff (5 minutes) at Sea Level, Equivalent shaft hp, shaft hp., jet thrust,
rpm: 3750-3460-726-13820
Maximum continuous at Sea Level, Equivalent Shaft hp, shaft hp., jet thrust,
rpm: 3420-3138-705-13820
The above ratings are based on static Sea Level conditions, compressor inlet
air (dry) 59°F, 29.92 in. Hg., no external accessory loads and no air bleed.
Maximum permissible temperatures:
Turbine Inlet Gas Temperature, Takeoff:  1780°F (971°C)
Max. Cont: 1710°F (932°C)
Maximum Transient (not to exceed 2 sec.)  2040°F (1116°C)
Oil Inlet Temperature, minus 25°F (-32° C) minimum, 185°F (85°C) maximum except
for 212°F (100°C) maximum at Flight Idle and below and for 5 minutes above
Flight Idle.
The maximum allowable power as measured by the torquemeter for below standard inlet
air temperature and/or ram conditions is 4000 hp for takeoff and 3400 hp for maximum
continuous.
Propeller and Propeller Limits  (1) 4 Aero Products A6441 FN-606 Hydromechanical
Diameter: 13 feet 6 inches. No reduction in diameter permitted.
Single rotation four blade assembly with gov. speed setting of 1020 p.r.p.m.
(13,820 e.r.p.m.) Propeller assembly is complete with spinner, feathering and
reversing provisions, selective pitch control, negative torque control,
synchronizer, blade phase control and electrical ice control.
Hyd. low pitch stop (min. Flight Idle) +20.0°, start +7.0°, reverse -4.0°, feather
+94.9° +0.1° -0.2°, beta follow-up +32.0°, mech. low pitch stop +18.25°, ground
Blade station at which angles are measured is 42"R.
Ground Limitation:
'Avoid continuous operation of propellers on the ground below 9,900 engine
RPM for low RPM idle and above 14,530 engine RPM for overspeed fuel governor
checks."
(2) 4 Hamilton Standard, hubs 54H60, blades A-7109B-2 or A-7121B-2,
electro-hydromatic
Page No.
Rev. No.  13  12  12  12  14  12

4A22  Page 2 of 9
Diameter: 13 feet 6 inches
Single rotation four blade assembly with gov. speed setting of 1020 p.r.p.m.
(13,820 e.r.p.m.)
Propeller assembly is complete with spinner, feathering and reversing
provisions, selective pitch control and negative torque control, synchronizer and
olade phase control, and electrical ice control.
Hyd. low pitch stop (min. Flight Idle) +11.0°, start 0°, reverse 15.0°,
feather 86.65° + .10°, beta follow-up 22.5°, mechanical low pitch stop 12.0°
ground idle -6.0°.
Blade station at which angles are measured is 54"R.
Propeller Hydraulic Oil  (1) Aeroproducts Propeller  -AMS/1-40002
(2) Hamilton Standard, Propeller -HIL-H-6083B
Type 1 Hyd. Fluid
Airspeed Limits  (normal operation)  373 mph  (324 knots)
(Calibrated)  S.L. to 12000 ft. Above 12,000 ft. M = .615
(never exceed)  418 mph (364 knots)
S.L. to 8000 ft.  Above 8000 ft. M = .640
(maneuvering)  234 mph (203 knots)
Vf  (takeoff position 78%)  218 mph/  (190 knots)
(landing position 100%)  196 mph  (170 knots)
VIo  (landing gear operation)  218 mph  (190 knots)
VIe  (landing gear extended)  250 mph  (217 knots)
Vmc (minimum control)  127 mph/  (110 knots)
Landing light extension  300 mph  (261 knots)
Mach no. - never exceed, M = ,64
C. G. Range  See NOTE 1(b) for required loading and gear retraction moment.
Landing  Limit  Limit
Condition  Weight Ib.  % MAC  Aft. Sta.  % MAC
Takeoff  113,000*  22.1  599.9  32.0
77,410*  15.0  599.9  32.0
or less
Landing  95,650*  Down  577.3  18.6  599.9  32.0
77,410*  Down  571.2  15.0  599.9  32.0
or less
Cruising  113,000*  Up  579.0  19.6  601.6  33.0
Flight  77,410*  Up  566.1  12.0  601.6  33.0
or less
* Straight line variation between these values
Weight Limits  Landing:  95,650 lb.
Takeoff:  113,000 lb.  (dump valves are required)
Maximum zero fuel weight:
Serial Nos. 1001 through 1034  82,500 1b.
Serial Nos. 1035 and up  86,000 lb.
See NOTE 1(e) for fuel loading.
3 engine ferry weight 95,000 lb.
Minimum Crew  3: Pilot, Copilot and Flight Engineer.
Maximum Passengers  99 (CAR 4b.362 as amended to 12-31-53 and supplemented by CAA letter dated January
22, 1957.) See Approved Weight and Balance Report for actual number and location.
Maximum Baggage  Maximum capacity of internal baggage and storage compartments:
Capacity  Compt.
Loading psf  (Ib.)  C.G.
(A) Fwd. Cargo Compt. F.S., 201 to 417  3810  313
(B) Aft. Cargo Compt. F.S., 768 to 1005  4050  885
Carry-on baggage L.H. (entrance)  386
Carry-on baggage R.H. (entrance)  352

Page 3 of 9  4A22
Wash water  375.0  569.9
Galley area between Stations 805.5 and 908.5 and 10" from airplane centerline R.H. side
is structurally satisfactory for a maximum total load of 1600 pounds, with a maximum
unit floor loading of 45 pounds per square foot.
Maximum Fuel Quantity  See NOTE 1(c) regarding "Unusable fuel and system oil" and fuel density accounting.
Usable Fuel  Total Fuel
Tanks 2 & 3  7370 lb. ea.  (1100 gal. ea.)  (1105 gal. ea.)
11122 Ib. ea.  (1660 gal. ea.)  (1662 gal. ea.)  (+605.7)
For aircraft with extended inboard tank capacity (optional)
Usable Fuel  Total Fuel
Quantity  Quantity
Tanks 2 & 3  (Inb'd)  10720 Ib. ea.  (1600 gal. ea.)  10754 1b.  (1605 gal. ea.)  (+625.1)
Tanks 1 & 4 (Outb'd)  11122 lb. ca.  (1660 gal. ea.)  11135 lb.  (1662 gal. ea.)  (+605.7)
Total  43684  43778  6534
Oil Capacity  See NOTE 1(c) regarding "Unusable fuel and system oil."
Usable Oil
2 Inboard tanks  7.6 gal. ea.  60.8 1b. (+477.0)
2 Outboard tanks  7.6 gal. ea.  60.8 1b. (+486.0)
Totals  30.4  243.2
Maximum Operating Altitude  30,000 ft. and 25,000 ft.
See NOTE 5 for requirement relative to operation above 25,000 ft.
Other Operating Limitations  Aircraft shall be operated in compliance with the operating limitation specified in the
FAA approved Airplane Flight Manual.
Control Surface Movements  Main surfaces (boost on)
Tabs (Main surfaces in neutral)  Down
Flaps 40° total angular travel
Serial Nos. Eligible  188A/1001, 188A/1002, 188A/1004 through 188A/1070,
188A/1072 through 188A/1074, 188A/1076, 188A/1079,
188A/1081, 188A/1083, 188A/1084, 188A/1086, 188A/1087,
188A/1089, 188A/1090, 188A/1092 through 188A/1097,
188A/1099, 188A/1100, 188A/1102, 188A/1104, 188A/1106,
188A/1107, 188A/1114 through 188A/1129, 188A/1140,
188A/1143, 188A/1145, 188A/1146, 188A/1148

4A22  Page 4 of 9
II. - Model 188C (Transport Category), approved July 10, 1959. (Same as Model 188A except that wings, fuselage and nose
landing. gear have been reinforced to provide for a takeoff weight increase from 113,000 to 116,000 1b.)
(See NOTE 6.)
Engines  4 Allison 501-D13 or 501-D13A (used with Ham. Std. prop)
Turboprop with 13.54:1 reduction gear ratio (See NOTE 6).
Fuel  Kerosene  (Allison Spec EMS 64C) or JP4 (MIL-F-5624C)
See NOTE 1e)(4).
Lubricating Oil  Allison Spec EMS-35E or EMS-53
Engine Limits  Takeoff (5 minutes) at Sea Level, Equivalent shaft hp. shaft hp., jet thrust,
rpm 3750-3460-726-13820
Maximum continuous at Sea Level, Equivalent shaft hp., shalt hp., jet thrust,
rpm 3420-3138-705-13820
The above ratings are based on static Sea Level conditions, compressor inlet air
(dry) 59°F, 29.92 in.Hg., no external accessory loads and no air bleed.
Maximum permissible temperatures:
Turbine inlet Gas Temperature,  1780°F (971°C)
Maximum Transient (not to exceed 2 sec.)  2040°f (1116°C)
Oil Inlet Temperature, minus 25°F (-32°C) minimum, 185°F (85°C) maximum
except for 212°F (100°C) maximum at Flight Idle and below and for 5 minutes
above Flight Idle.
The maximum allowable power as measured by the torquemeter for below standard
inlet air temperature and/or ram conditions is 4000 hp for takeoff and 3400 hp for
Propeller and Propeller Limits  (1) 4 Aero Products A6441 FN-606 Hydromechanical
Diameter: 13 feet 6 inches. No reduction in diameter permitted.
Single rotation four blade assembly with gov. speed setting of 1020 p.r.p.m.
(13,820 e.r.p.m.) Propeller assembly is complete with spinner, feathering and
reversing provisions, selective pitch control and negative torque control,
synchronizer and blade phase control, and electrical ice control.
Hyd. low pitch stop (min Flight Idle) +20.0°, start + 7.0°, reverse -4.0°, feather
+ 94.9° -0.1°, -0.2°, beta follow-up +32.0°, mech. low pitch stop +18.25°, ground
Blade station at which angles are measured in 42"R.
Ground limitation:
"Avoid continuous operation of propellers on the ground below 9,900 engine RPM
for low RPM idle and above 14,530 engine RPM for overspeed fuel governor
checks."
(2) 4 Hamilton Standard, hubs 54H60, blades A-7109B-2 or A-7121B-2,
electrohydromatic
Diameter: 13 feet 6 inches
Single rotation four blade assembly with gov. speed setting of 1020 p.r.p.m.
(13,820 e.r. p.m.)
Propeller assembly is complete with spinner, feathering and reversing provisions,
selective pitch control and negative torque control, synchronizer and blade phase
control, and electrical ice control.
Hyd. low pitch stop (min. Flight Idle) +11.0°, start 0°, reverse -13.0°, feather
86.65° + .10°, beta follow-up 22.5°, mechanical low pitch stop 12.0° ground
Blade station at which angles are measured is 54"R.
Propeller Hydraulic Oil  (1) Aeroproducts Propeller  -AMS/1-40002
(2) Hamilton Standard, Propeller-MIL-H-6083B
Type 1 Hyd. Fluid

Page 5 of 9  4A22
Airspeed Limits  Vno  (normal operation)  373 mph (324 knots)
(Calibrated)  S.L. to 12000 ft. Above 12,000 ft. M = .615
Vne  (never exceed)  418 mph  (364 knots)
S.L. to 8000 ft.  Above 8000 ft. M = .640
237 mph  (206 knots)
(takeoff position 78%)  218 mph  (190 knots)
((landing position 100%)  196 mph  (170 knots)
(landing gear operation)  218 mph/  (190 knots)
(landing gear extended)  250 mph  (217 knots)
Vmc (minimum control)  127 mph  (110 knots)
Landing light extension  300 mph  (261 knots)
Mach no. - never exceed, M = .64
C. G. Range  (See NOTE 1(b) for required loading and gear retraction moment.
Landing  Fwd  Limit
Condition  Weight Ib  Gear  Sta.  % MAC  Aft. Sta.  % MAC
Takeoff  116,000*  Down  584.2  22.7  598.2  31.0
115,500*  Down  599.9  32.0
77,410*  Down  571.2  15.0  599.9  32.0
or less
Landing  95,650*  Down  577.3  18.6  599.9  32.0
77,410*  Down  571.2  15.0  599.9  32.0
or less
Cruising  116,000*  Up  580.0  20.2  601.6  33.0
Flight  77,410*  Up  566.1  12.0  601.6  33.0
or less
* Straight line variation between these values
Weight Limits  Landing  95,650 lb.
Takeoff 116,000 lb. (Dump valves are required)
Maximum zero fuel weight 86,000 Ib. See NOTE 1(e) for fuel loading. 3 engine ferry
weight 95,000 lb.
Minimum Crew  3. Pilot, Copilot and Flight Engincer.
Maximum Passengers  99 (CAR 4b.362 as amended to 12-31-53 and supplemented by CAA letter dated
January 22, 1957.) See Approved Weight and Balance Report for actual number and
location.
Maximum Baggage  Maximum capacity of internal baggage and storage compartments:
Vol.  Max. floor  Capacity  Compt.
(cu. ft.)  Loading psf  (Ib.)  C.G.
(A) Fwd. Cargo Compt. F.S., 201 to 417  45  3810  313
(B) Aft. Cargo Compt. F.S., 788 to 1005  45  4050  885
Carry-on baggage L.H. (entrance)  30  386
Carry-on baggage R.H. (entrance)  30  352
Wash water  375.0  569.9
Galley area between Stations 805.5 and 908.5 and 10" from airplane centerline
R.H. side is structurally satisfactory for a maximum total load of 1600 pounds, with a
maximum unit floor loading of 45 pounds per square foot.

4A22  Page 6 of 9
Maximum Fuel Quantity  See NOTE 1(c) regarding "Unusable fuel and system oil" and fuel density accounting.
Usable Fuel  Total Fuel
Quantity  Quantity
Tanks 2 & 3  (Inb'd)  7370 lb. ea.  (1100 gal. ea.)  7404 1b.  (1105 gal. ca.)  (+628.4)
Tanks 1 & 4  (Outb'd)  11122 Ib. ea.  (1660 gal. ea.)  11135 1b.  (1662 gal. ea.)  (+605.7)
Total  36984  5520  37078  5534
For aircraft with extended inboard tank capacity (optional)
Oil Capacity  See NOTE 1(c) regarding "Unusable fuel and system oil."
Usable Oil
2 Inboard tanks  7.6 gal. ea.  60.8 1b.  (+477.0)
2 Outboard tanks  7.6 gal. ea.  60.8 1b. (+486.0)
Totals  30,4  243.2
Maximum Operating Altitude  30,000 ft. and 25,000 ft.
See NOTE 5 for requirement relative to operation above 25,000 ft.
Other Operating Limitations  Aircraft shall be operated in compliance with the operating limitation specified in the
FAA approved Airplane Flight Manual.
Serial Nos. Eligible  188C/1071,  188C/1075, 188C/1077, 188C/1078, 188C/1080
188C/1082,  188C/1103, 188/105, 188C/1103 through 188C/13
188C/1130  188C/1139, 188C/1141, 188C/1142,
188C/1144, 188C/1147, 188C/2001 and up
Data Pertinent to All Models
Datum  571.89 in. forward of jig point. (Screwhead on bottom surface of wing at
W.S. 59 L. and R.)
MAC  168.7 in. leading edge of MAC at Sta, 545.9
Leveling Means  Leveling plate under fuselage floor at ref. Sta. 832.0
Control Surface Movements  Main surfaces (boost on)
Down
Tabs (Main surfaces in neutral)
Flaps 40° total angular travel
Certification Basis  CAR 4b dated December, 1953, Amendments 4b-1 and 4b-2 thereto; the special
conditions and provisions of Amendments 4b-3, 4b-4 and 4b-6 listed in Attachment A to
CAA letter of October 21, 1957, and the provisions of Item 2 of Special Civil Air
Regulation No. SR-422. CA letters to Lockheed Aircraft Corporation dated January 22,
1957 and January 22, 1958, relative to emergency exits and oxygen requirements
respectively provide the basis in regard to these items.
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 certitication
basis. For any future 14 CFR part 26 amendments, the holder of the TC must
demonstrate compliance with the applicable sections.

Page 7 of 9  4A22
Type Certificate No. 4A22 issued August 22, 1958.
Application for Type Certificate dated November 11, 1955..
Compliance with the ditching requirements has been demonstrated.
Compliance has been found for the following regulations: 14 CFR § 26.43 and 26.45,
(Amdt. No. 26-0 through 26-3).
Production Basis  Production Certificate No. 600
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 is shown in the Master Equipment list, Lockheed Report No. 12897.
Service information  Lockheed "Electra" Structural Repair Manual, is FAA approved. Service Bulletins and
other service information, when FAA approved, will carry a statement to that effect.
NOTE 1.  Current weight and balance report including list of equipment included in certificated empty weight,
and loading instructions, must be provided for each aircraft at the time of original certification. See
Approved "Weight and Balance Data" (Lockheed Report No. 12944) for list of approved items of
(b) The airplane must be loaded so that the C.G. is within the specified limits at all times, with the effects
of fuel use, gear retraction, and movement of crew and passengers from their assigned positions being
considered (retraction of the main and nose gears causes the C. G. to move forward; a value of 175,000
in. Ib. is a satisfactory approximation of the change in moment for all approved wheel items). At
takeoff, the airplane shall be loaded so that, due to fuel use, the C.G. cannot move forward of 15%
MAC. A 33% aft C.G. limit (gear retracted) for cruising flight may be used when the effect of
passenger and crew movements from their assigned positions has been taken into account.
(c)  "Unusable Fuel and System Oil" and all-hydraulic fluid must be included in the certificated empty weight.
Unusable Fuel is that quantity of fuel in the system and in the tanks which is unavailable to the
engines under critical flight conditions as defined in CAR 4b.416. This unusable fuel includes the
"system fuel" which is defined as the quantity required to fill the system and tanks to the tank outlet
level when the airplane is in the ground level attitude. The total amount of fuel is as follows:
Model No.  *Usable Fuel  Unusable Fuel (Ib.)
188A or 188C  36,985 1b. (5520 gal.)  266
188A or 188C
with extended inner tank  43,684 Ib. (6520 gal.)  266
The volume (gallons) of the fuel tank is the size required to contain the weight of fuel shown only when the fuel
density is 6.7 #/gallon. Variations of the fuel density must be accounted for when loading fuel so that the
minimum fuel weight versus takeoff weight is properly provided. Also, the maximum permissible quantity of
fuel for full tank takeoff is the weight of fuel shown in the "maximum fuel quantity" tables of this Data Shect.
System Oil is that amount of oil required to fill the oil system and tanks to the tank outlets to the engines. The
oil tank capacities shown in this specification include only the usable oil for which the tanks are placarded.
Dipstick readings indicate the amount of usable oil.
Model No.  Usable Oil (Ib.)  System Oil (Ib.)
188A or 188C  243.2  97.4
(d) Fuel dumping. When fuel dump valaves are installed per NOTE 3, the amount of usable fuel, over and
above the unusable fuel remaining after dumping, is as follows:
Gallons Remaining in Tanks
Model  1&4  2&3  Total
188A or 188C  135 each  112 each  494 gallons
(e)  Fuel loading and usage.
(1) Fuel must be distributed and used in a manner that will permit compliance with the lateral
balance limitations in the FAA Approved Airplane Flight Manual.

4A22  Page 8 of 8
(2) For minimum fuel at any takeoff weight, refer to the minimum fuel required chart in the pertinent
FAA Approved Airplane Flight Manual.
(3) For landing, the fuel quantities must not exceed the following:
Tanks 1 and 4:  6,700 lb. each
Total fuel in tanks 1 and 2:  13,400 lb.
Total fuel in tanks 3 and 4:  13.400 lb.
(4)  Phillips PFA-55MB or anti-icing additive to Specification MIL-1-27686E may be used if concen-
tration to airplane does not exceed 0.1% by volume. No fuel system anti-icing credit is allowed.
NOTE 2.  Deleted.
NOTE 3.  Fuel dump valves must be installed for operation of the airplane at weights in excess of maximum landing
weight. Refer to FAA Approved Airplane Flight Manual for limitations and cautionary procedure to be
observed during the dumping of fuel.
NOTE 4.  Radio Restriction:
Due to coupling effects between the VHF navigation system and the No. 1 VHF communications system,
resulting interference may adversely affect the VHF navigation system whenever transmitting on so called
spurious response frequencies. * VHF navigation information is satisfactory only when the No. 1 VHF
communications transmissions do not adversely interfere with the VHF navigation output to indicating
instruments and coupled autopilot.
Any superheterodyne type receiver will have some spurious response frequencies. In the Wilcox type 706A
VHF navigation receiver an offending response appears at seven (7) megacycles above the selected
frequency. This means, for example, that when 111.0 mc has been selected on the NAV receiver,
transmissions on 118 mc with VHF No. 1 will result in interference. Any model receiver with less than
approximately 90 decibels spurious response rejection characteristic may be similarly affected if a response
frequency appears within the navigation band (108-118 mc).
NOTE 5.  For Air Carrier operations above 25,000 ft. the aircraft must be equipped with the following:
(1) Approved oxygen masks and installation. The stowage of the masks must be such that
a mask is immediately available to each occupant and the stowage location is to be indicated by a
placard. (Lockheed Drawing No. 8933121 shows a typical approved installation.)
(2) Deleted.
NOTE 6.  Issuance of Airworthiness Directive Note 60-9-3 on March 25, 1960, imposed speed restrictions and
other limitations on all 188 aircraft. These limitations are removed with the incorporation of changes to the
airplane per Lockheed Service Bulletins Nos. 88/SB-500 and 88/SB-453 and Airworthiness Directive Note
60-21-1 as indicated in revision to Airworthiness Directive Note 60-9-3 made effective
December 31, 1960. Engines modified to incorporate the six mount installations per NOTE 15c of Engine
Specification No. E-282 are required by Service Bulletin No. 88/SB-500.
NOTE 7.  The approved manufacturer's model number is 188A. In Revision 10 of this data sheet, all reference to
Model 188A-08 has been revised to read 188A.
NOTE 8.  The following serial numbers are eligible for conversion from Model 188A to Model 188C when Lockheed
Service Bulletin No. 88/SB-687A is incorporated:
188A/1070, 1072, 1073, 1074, 1076, 1079, 1081, 1083, 1084, 1086, 1087, 1089, 1092 through 1097, 1100,
1102, 1104, 1107, 1114 through 1116, 1118 through 1129, 1140, 1143, 1145, 1146 and 1148.
..END.....
```

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- [AD 80-10-05](https://openairdocs.org/ad/80-10-05): Wing Front Spar Caps · Lockheed Martin 188A and 188C. Effective Jun 23, 1980
- [AD 80-12-01](https://openairdocs.org/ad/80-12-01): Cargo Door Modifications · Lockheed Martin 188A and 188C with STC SA1754WE or SA2536WE. Effective Jun 9, 1980
- [AD 77-21-09](https://openairdocs.org/ad/77-21-09): Aileron Rudder Balance Interconnect Mechanism · Lockheed Martin 188A and 188C. Effective Nov 25, 1977
- [AD 76-05-02](https://openairdocs.org/ad/76-05-02): Side-Facing Seats · Boeing 707-300B Series, 727-100 Series, 188A and 1 more. Effective Apr 1, 1976
- [AD 74-25-04](https://openairdocs.org/ad/74-25-04): Horizontal Stabilizer · Lockheed Martin 188A and 188C. Effective Jan 3, 1975
- [AD 74-17-01](https://openairdocs.org/ad/74-17-01): Regulator · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 78 more. Effective Sep 16, 1974
- [AD 69-26-08](https://openairdocs.org/ad/69-26-08): Takeoff Warning System · Lockheed Martin 188A and 188C. Effective Jan 10, 1970
- [AD 69-08-07](https://openairdocs.org/ad/69-08-07): Lower Wing Surface · Lockheed Martin 188A and 188C. Effective Apr 17, 1969
- [AD 68-11-02](https://openairdocs.org/ad/68-11-02): Upper & Lower Wing Planks · Lockheed Martin 188A and 188C. Effective Jan 4, 1969
- [AD 68-23-05](https://openairdocs.org/ad/68-23-05): Upper Wing Plank · Lockheed Martin 188A and 188C. Effective Dec 6, 1968
- [AD 67-11-04](https://openairdocs.org/ad/67-11-04): Fuselage Main Frames Forging · Lockheed Martin 188A and 188C. Effective Jun 9, 1967
- [AD 66-04-02](https://openairdocs.org/ad/66-04-02): Wing Plank Splice Areas · Lockheed Martin 188A and 188C. Effective Feb 18, 1967
- [AD 67-03-06](https://openairdocs.org/ad/67-03-06): Landing Gear Door Cylinders · Lockheed Martin 188A and 188C. Effective Jan 20, 1967
- [AD 66-28-04](https://openairdocs.org/ad/66-28-04): Nose Landing Gear Steering Housing · Lockheed Martin 188A and 188C. Effective Nov 25, 1966
- [AD 66-11-02](https://openairdocs.org/ad/66-11-02): Lower Wing Plank Splice Areas · Lockheed Martin 188A and 188C. Effective Sep 23, 1966
- [AD 66-05-03](https://openairdocs.org/ad/66-05-03): Outer Wing Cap Fittings · Lockheed Martin 188A and 188C. Effective Feb 19, 1966
- [AD 65-15-04](https://openairdocs.org/ad/65-15-04): No. 4 Wing Plank Drain Holes · Lockheed Martin 188A and 188C. Effective Dec 9, 1965
- [AD 65-21-05](https://openairdocs.org/ad/65-21-05): Vertical Stabilizer Attach Channel · Lockheed Martin 188A and 188C. Effective Oct 11, 1965
- [AD 64-12-05](https://openairdocs.org/ad/64-12-05): Landing Gear Cam Follower · Lockheed Martin 188A and 188C. Effective Sep 28, 1965
- [AD 65-16-01](https://openairdocs.org/ad/65-16-01): Nose Landing Gear Support Link · Lockheed Martin 188A and 188C. Effective Jul 30, 1965
- [AD 65-09-04](https://openairdocs.org/ad/65-09-04): Upper Wing Planks · Lockheed Martin 188A and 188C. Effective Apr 28, 1965
- [AD 64-16-04](https://openairdocs.org/ad/64-16-04): Aileron Push-Pull Tubes · Lockheed Martin 188A and 188C. Effective Mar 2, 1965
- [AD 64-14-05](https://openairdocs.org/ad/64-14-05): Main Landing Gear Support Fitting · Lockheed Martin 188A and 188C. Effective Jun 26, 1964
- [AD 64-11-03](https://openairdocs.org/ad/64-11-03): Upper Wing Planks · Lockheed Martin 188A and 188C. Effective Jun 15, 1964
- [AD 63-17-03](https://openairdocs.org/ad/63-17-03): Horizontal Stabilizer Spar Web · Lockheed Martin 188A and 188C. Effective Nov 21, 1963
- [AD 63-18-03](https://openairdocs.org/ad/63-18-03): Fuselage Stringers · Lockheed Martin 188A and 188C. Effective Sep 17, 1963
- [AD 63-08-03](https://openairdocs.org/ad/63-08-03): Deboost Control System · Lockheed Martin 188A and 188C. Effective May 9, 1963
- [AD 62-26-04](https://openairdocs.org/ad/62-26-04): Elevator Balance Weight Arms · Lockheed Martin 188A and 188C. Effective Dec 4, 1962
- [AD 61-21-05](https://openairdocs.org/ad/61-21-05): Compass Circuit Breakers · Lockheed Martin 188A and 188C. Effective Nov 2, 1961
- [AD 61-15-04](https://openairdocs.org/ad/61-15-04): Safety Belt Grommets · Lockheed Martin 188A and 188C. Effective Aug 2, 1961
- [AD 61-09-01](https://openairdocs.org/ad/61-09-01): Elevator Hydraulic Damper Housing · Lockheed Martin 188A and 188C. Effective Apr 7, 1961
- [AD 60-26-05](https://openairdocs.org/ad/60-26-05): Elevator and Boost Control Valve · Lockheed Martin 188A and 188C. Effective Dec 22, 1960
- [AD 60-26-04](https://openairdocs.org/ad/60-26-04): Swirl Straightener Scoop · Lockheed Martin 188A and 188C. Effective Dec 14, 1960
- [AD 60-24-01](https://openairdocs.org/ad/60-24-01): Fuel Pressure Relief Valve · Lockheed Martin 188A and 188C. Effective Dec 13, 1960

All 64: https://openairdocs.org/tcds/4A22/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Lockheed 188C](https://openairdocs.org/model/lockheed-188c): 3 aircraft (registry code 5262604)
- [Lockheed 188A](https://openairdocs.org/model/lockheed-188a): 1 aircraft (registry code 5262602)

## STCs approved under this data sheet (113, 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 ST00353LA](https://openairdocs.org/stc/ST00353LA): Installation of a 3000 gallon retardant tank system.. Air Spray USA 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 SA8009NM](https://openairdocs.org/stc/SA8009NM): Installation of a 3000 gallon fire retardant tank system. United Aeronautical Corporation
- [STC SA2197WE](https://openairdocs.org/stc/SA2197WE): Installation of Brownline modified cargo restraint system.. Telair US LLC
- [STC SA3675WE](https://openairdocs.org/stc/SA3675WE): Installation of Brownline cargo system P/N 46234-101.. Telair US LLC
- [STC ST02524LA](https://openairdocs.org/stc/ST02524LA): Installation of TCAS version 7.0. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC SA2324WE](https://openairdocs.org/stc/SA2324WE): Installation of spraymat ice protection system on L-188 propeller spinner, Hamilton Standard P/N 553546, replacing Hamilton Standard heater blanket.. ROBERT W. MURRAY
- [STC ST00986LA-D](https://openairdocs.org/stc/ST00986LA-D): Installation of lower cargo compartment smoke detection system provisions.. Ontic Engineering and Manufacturing Inc.
- [STC SA1064SO](https://openairdocs.org/stc/SA1064SO): Increase in zero fuel weight from 82,500 lbs. to 90,800 lbs.. Aeronautical Engineers, Inc
- [STC SA1071SO](https://openairdocs.org/stc/SA1071SO): Increase in zero fuel weight from 86,000 pounds to 92,340 pounds.. Aeronautical Engineers, Inc
- [STC SA1081SO](https://openairdocs.org/stc/SA1081SO): Increase in fuel weight from86,000 pounds to 92,340 pounds.. Aeronautical Engineers Inc
- [STC ST508SO](https://openairdocs.org/stc/ST508SO): Installation of lap/shoulder belts.. Aeronautical Engineers Inc
- [STC ST885SO](https://openairdocs.org/stc/ST885SO): Modification to a cargo configuration.. Aeronautical Engineers Inc
- [STC SA2536WE](https://openairdocs.org/stc/SA2536WE): Modification and installation of aft cargo door; cargo loading and retention system; strengthened floor support structure; increased zero fuel weight to 90,000 pounds; improved avionics and instrumentation. (Model 188A serial number 1035 and up). Lockheed Martin Aeronautics Company
- [STC SA7772SW](https://openairdocs.org/stc/SA7772SW): Replacement of existing torquemeters.. AVMAR a Michigan Corporation
- [STC SA1637WE](https://openairdocs.org/stc/SA1637WE): Installation of cargo door approximately 80 inches high by 144 inches long in left side of fuselage forebody.. Lockheed Martin Aeronautics Company
- [STC SA1754WE](https://openairdocs.org/stc/SA1754WE): Installation of cargo doors, cargo floor and other changes. (188A, 188C Aircraft SN 1070 and higher are eligible.). Lockheed Martin Aeronautics Company
- [STC SA4-1403](https://openairdocs.org/stc/SA4-1403): Installation of a Lockheed Aircraft Service model 109C flight data recorder.. Lockheed Martin Aeronautics Company
- [STC SA707EA](https://openairdocs.org/stc/SA707EA): Relocation of cabin window right-side from fuselage station 217-236 to fuselage station 333-352.. Lockheed Martin Aeronautics Company
- [STC SA708EA](https://openairdocs.org/stc/SA708EA): Installation of opening in fuselage right hand for emergency exit between fuselage station 226 and fuselage station 253.4. Is approved only for its structural, electrical and mechanical provisions and can be incorporated with STC SA707EA and STC SA709EA.. Lockheed Martin Aeronautics Company
- [STC SA709EA](https://openairdocs.org/stc/SA709EA): Installation of floor structure and miscellaneous modifications. Is approved only for its structural and electrical provisions and can be incorporated with STC SA707EA and SA708EA.. Lockheed Martin Aeronautics Company
- [STC ST01836NY](https://openairdocs.org/stc/ST01836NY): Three Man to Two Man Crew Conversion.. Cascade Aerospace Inc.
- [STC ST01004NY](https://openairdocs.org/stc/ST01004NY): Installation of cargo restraint straps.. Airline Container Manufacturing Co Inc
- [STC ST02035AK](https://openairdocs.org/stc/ST02035AK): Installation of Honeywell TCAS II.. ACSS (Aviation Communication and Surveillance Syst
- [STC SA2405WE](https://openairdocs.org/stc/SA2405WE): Installation of PICO Division pressure regulator P/N 3001 on automatically inflatable emergency evacuation slides in lieu of International Inflatables pressure regulator P/N 68240 and 70003.. Goodrich Corporation
- [STC SA1060GL](https://openairdocs.org/stc/SA1060GL): Installation of Norton Radome Kit4306CX.. Saint-Gobain Performance Plastics Corp
- [STC SA1149SW](https://openairdocs.org/stc/SA1149SW): Installation of a hot water heater.. Signature Flight Support Corporation
- [STC SA1150SW](https://openairdocs.org/stc/SA1150SW): Installation of Litton LTN 51 inertial navigation system.. Signature Flight Support Corporation
- [STC SA2301WE](https://openairdocs.org/stc/SA2301WE): Installation of emblem light.. DeVore Aviation Corporation of America, a New Mexico Corporation
- [STC SA2974WE](https://openairdocs.org/stc/SA2974WE): Modification for installation of aft galley and forward galley rework.. DeVore Aviation Corporation of America, a New Mexico Corporation
- [STC ST01136AT](https://openairdocs.org/stc/ST01136AT): Modification of Lockheed Electra, Foote-Brothers Mfg. two-speed gear box P/N 50701-1, -2, -3, or -4.. Zantop Intl Airlines Inc
- [STC ST02004AK](https://openairdocs.org/stc/ST02004AK): Installation of a Dual Bendix/King MLS-21 microwave landing system.. Reeve Aleutian Airways, Inc
- [STC SA218WE](https://openairdocs.org/stc/SA218WE): Turbine installation GTC 85-90E or GTCP 85-291E.. AlliedSignal Aviation Services
- [STC SA2754WE](https://openairdocs.org/stc/SA2754WE): Installation of an auxiliary power unit connector.. Steward-Davis Intn'l, Inc
- [STC SA3120WE](https://openairdocs.org/stc/SA3120WE): Modification consisting of installation of cargo pallet restraint system. (188A s/n 1035 and up). Pemco Engineers Inc
- [STC SA5502NM](https://openairdocs.org/stc/SA5502NM): Modification of Lockheed model L-188A/L-188C airplanes.. Channel Express(Air Serviced) Ltd
- [STC SA3117SO](https://openairdocs.org/stc/SA3117SO): Installation of an engine reduction gearbox electrical/magnetic chip detector system.. Zantop Intl Airlines Inc
- [STC SA3118SO](https://openairdocs.org/stc/SA3118SO): Installation of fuel flowmeters and a fuel management system.. Zantop Intl Airlines Inc
- [STC SA1833SO](https://openairdocs.org/stc/SA1833SO): Installation of an aft cargo door and cargo compartment interior.. Universal Cargo Doors & Serv, Inc
- [STC SA1834SO](https://openairdocs.org/stc/SA1834SO): Installation of a forward cargo door and cargo compartment interior.. Universal Cargo Doors & Serv, Inc
- [STC SA1506GL](https://openairdocs.org/stc/SA1506GL): Rebuilt alternate flap drive torque tube assembly P/N 807723-R, rebuilt Lockheed P/N 807723 with 4130 tubing and type design end fittings.. Zantop Intn'l Airlines Inc
- [STC SA1506GL;](https://openairdocs.org/stc/SA1506GL%3B): Rebuilt alternate flap drive torque tube assembly P/N 807723-R, rebuilt Lockheed P/N 807723 with 4130 tubing and type design end fittings.. Zantop Intn'l Airlines, Inc
- [STC SA4925NM](https://openairdocs.org/stc/SA4925NM): Installation of horse containers.. Instone Airline Ltd
- [STC SA3148WE](https://openairdocs.org/stc/SA3148WE): Installation of Collins FPC-75 ground proximity warning system.. US Airways, Inc
- [STC SA2043SO](https://openairdocs.org/stc/SA2043SO): Installation of dual Sperry SPI-402, flight director system.. Zantop Intl Airlines Inc
- [STC SA2012SO](https://openairdocs.org/stc/SA2012SO): Installation of a divider and a courier seat.. Spirit America Airlines
- [STC SA835GL](https://openairdocs.org/stc/SA835GL): Modification of underwing fuel quantity gages, Accessory Prod. Co. P/N 727100 (Lockheed P/N LAC 634063) by removing spring and poppet valve and installing a petcock P/N CCA-1550 (TSO-C76).. Zantop Intn'l Airlines, Inc
- [STC SA1495SO](https://openairdocs.org/stc/SA1495SO): Modification of Flight Equip. and Engrg. double passenger seat model650L to attach a double shoulder harness/lap belt assembly.. Survival Products Inc

All 113: https://openairdocs.org/tcds/4A22/stcs.md

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