TCDS 4A22

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.....