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DEPARTMENT OF TRANSPORTATION 

FEDERAL AVIATION ADMINISTRATION 

A20WE 

BOEING 

Revision 49 

 747-100 Series 

 747-200B Series 

 747-200F Series 

 747-200C Series 

 747SR Series 

 747SP Series 

 747-100B Series 

 747-300 Series 

 747-100B SUD Series 

 747-400 Series 

 747-400D Series 

747-400F Series 

747-8F Series 

747-8 Series 

February 29, 2012

TYPE CERTIFICATE DATA SHEET NO. A20WE

This data sheet, which is a part of Type Certificate No. A20WE, 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: The Boeing Company 

PO Box 3707 

Seattle, WA 98124 

I - 747-100 (Approved December 30, 1969) Transport Aircraft

Engines: 4 Pratt and Whitney JT9D-3, JT9D-3A, or JT9D-7, JT9D-7A, JT9D-7F, JT9D-7J. 

See NOTE 5 regarding intermixing of engines. 

Fuel: See NOTE 3. 

Engine Limits: See data pertinent to all models. 

Airspeed Limits: VMO/MMO 375/0.92 (KEAS) For other airspeed limits see the appropriate FAA Approved 

 Airplane Flight Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

 FAA Approved Weight and Balance Control and Loading Manual: D6-13700 

 FAA Approved Airplane Flight Manual: D6-13703 
A20WE 2 

 

I. 747-100 (cont’d)

Model Eligible Serial Numbers

747-1D1 20208 

747-121 19637-19661, 20235, 20347-20354 

747-122 19753-19757, 19875-19883, 19925-19928 

747-123 20100-20109, 20323-20326, 20390, 20391 

747-124 19733-19735, 20305 

747-127 20207 

747-128 19749-19752, 20355, 20376-20378, 20541-20543, 20798-20800, 20954, 21141 

747-129 20401, 20402 

747-130 19746-19748 

747-131 19667-19678, 20080-20083, 20320-20322 

747-132 19896-19898, 20246, 20247 

747-133 20013-20015, 20767, 20881 

747-135 19918, 19919 

747-136 19761-19766, 20269-20273, 20284, 20708, 20809, 20810, 20952, 20953, 21213 

747-143 19729, 19730 

747-146 19725-19727, 20332, 20528, 20531, 20532, 21029 

747-148 19744, 19745 

747-151 19778-19787 

747-156 19957, 19958 

II - 747-200B (Approved December 23, 1970) Transport Aircraft

The 747-200B is an extended-range passenger version of the basic 747-100 series aircraft. The exterior geometry of the 747-200B is 

identical to the 747-100 and aircraft systems are essentially unchanged except for differences resulting from changes outlined below. The 

principal differences involve the following: 

Increased strength wing structure, local body and empennage changes for increased strength, increased center wing tank fuel capacity, 

increased strength landing gear, modified nacelle and engine acoustic treatment, increased gross weight, and modified balance limits. 

Engines: 4 Pratt and Whitney JT9D-3A, JT9D-7, JT9D-7A, JT9D-7F, JT9D-7J, JT9D-70A, JT9D-7Q, JT9D-7Q3, 

JT9D-7R4G2 

 4 General Electric CF6-50E, CF6-50E1, CF6-50E2, CF6-80C2B1 

 4 Rolls Royce RB211-524B2-19, RB211-524C2-19, RB211-524D4-19, RB211-524D4-39. 

See NOTE 5 regarding intermixing of engines. 

Fuel: See NOTE 3. 

Engine Limits: See data pertinent to all models. 

Airspeed Limits: VMO/MMO 375/0.92 (KEAS) For other airspeed limits see the appropriate FAA approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

FAA Approved Weight and Balance Control and Loading Manual: D6-13700, 1E-4A-5, 1E-4B-5 

FAA Approved Airplane Flight Manuals: D6-13703, D6-33747, D6-34747, D6-35747 
3 A20WE 

II. 747-200B (cont’d)

Model Eligible Serial Numbers

747-206B 19922-19924, 20398-20400, 20427, 21110, 21111, 21549, 21550, 21659, 21660, 21848, 22376, 22379, 

22380 

747-209B 21454, 21843, 22446, 22447 

747-211B 21516, 21517 

747-212B 20712, 20713, 20888, 21048, 21162, 21316, 21439, 21683, 21684, 21935-21944 

747-217B 20801, 20802, 20927, 20929 

747-219B 22722-22725, 22791 

747-222B 23736, 23737 

747-227B 21682, 21991, 22234 

747-228B 21326, 21429, 21537, 21731, 21745, 21982, 22272, 22427, 22428, 22794, 23611, 23676, 24067 

747-230B 20372, 20527, 21220, 21221, 21380, 21588-21591, 21643, 21644, 22363, 22669-22671, 23286, 23287, 

23393, 23407, 23509, 23622 

747-233B 20977, 21627 

747-236B 21238-21241, 21350, 21351, 21536, 21635, 21830, 21831, 22303-22305, 22442, 23711, 23735, 23799, 

24088 

747-237B 19959, 19960, 20459, 20558, 21182, 21446, 21473, 21829, 21993-21995 

747-238B 20009-20012, 20534, 20535, 20841, 20842, 20921, 21054, 21140, 21237, 21352-21354, 21657, 21658, 

21977, 22145, 22614-22616 

747-240B 21825, 22077 

747-243B 19731, 19732, 20520, 22506-22508, 22510-22513, 22969, 23300, 23301, 23476 

747-244B 20237-20239, 20556, 20557, 22170, 22171 

747-246B 19823-19825, 20333, 20503-20505, 20529, 20530, 20924, 21030, 21031, 21678-21680, 22064, 22065, 

22478, 22479, 22745, 22746, 22990, 22991, 23389 

747-247B 22378 

747-251B 20356-20360, 21704-21709, 22389, 23111, 23112, 23547-23549 

747-256B 20137, 22238, 22239, 22454, 22455, 22764, 24071 

747-257B 20116, 20117 

747-258B 20135, 20274, 20704, 22254 

747-259B 21730 

747-267B 21746, 21966, 22149, 22429, 22530, 22872, 23048, 23120 

747-269B 21541-21543, 22740 

747-281B 23501, 23502, 23698, 23813, 24399 

747-282B 20501, 20502, 20928, 21035 

747-283B 20120, 20121, 21381, 21575, 22381, 22496 

747-284B 20742, 20825 

747-286B 21217, 21218 

747-287B 21189, 21725-21727, 22297, 22592, 22593 

747-2B2B 21614 

747-2B3B 22514, 22515 

747-2B4B 21097-21099 

747-2B5B 20770, 20771, 21772, 21773, 22482, 22485 

747-2B6B 21615 

747-2D3B 21251, 21252, 22579 

747-2D7B 21782-21784, 22337, 22471, 22472 

747-2F4B 20493, 20559 

747-2F6B 21832-21834, 22382 

747-2G4B 23824, 23825 

747-2J6B 23071, 23461, 23746 

747-2L5B 22105-22107 

747-2Q2B 21468 

747-2U3B 22246-22249, 22768, 22769 

747-E4A 20682-20684 

747-E4B 20949 
A20WE 4 

 

III - 747-200F (Approved March 7, 1972) Transport Aircraft

The 747-200F is a freighter version of the basic 747-200B series aircraft. The exterior geometry of the 747-200F is identical to the 

747-200B and aircraft systems are essentially unchanged except for differences resulting from the changes outlined below. The principal 

differences involve the following: 

 Upward opening nose cargo door. 

 Redesigned interior for freight handling. 

 Revised upper deck layout for additional crew members. 

 Increased strength of main deck floor and keel beam. 

 Increased strength of center wing section. 

 Deletion of main deck windows and passenger doors 1 through 5 right side and 2 through 4 left side. 

 T.E. flap two position load relief system. 

 Revised air conditioning system to suit freight requirements. 

 Main deck smoke detection system. 

 Optional main deck smoke detection system. 

 Optional side cargo door. 

Engines: 4 Pratt and Whitney JT9D-3A, JT9D-7, JT9D-7A, JT9D-7F, JT9D-7J, JT9D-70A, JT9D-7Q, 

 JT9D-7Q3, JT9D-7R4G2 

 4 General Electric CF6-50E, CF6-50E1, CF6-50E2 

 4 Rolls Royce RB211-524B2-19, RB211-524C2-19, RB211-524D4-19, RB211-524D4-39. 

See NOTE 5 regarding intermixing of engines. 

Fuel: See NOTE 3. 

Engine Limits: See data pertinent to all models. 

Airspeed Limits: VMO/MMO 375/0.92 (KEAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

 FAA Approved Weight and Balance Control and Loading Manual: D6-13700 

 FAA Approved Airplane Flight Manuals: D6-13703, D6-33747, D6-35747, D6-34747 

Model Eligible Serial Numbers

747-209F 22299, 24308 

747-212F 24177 

747-221F 21743, 21744 

747-228F 20887, 21255, 21576, 21787, 22678, 22939, 24158, 24735, 24879, 25266 

747-230F 20373, 21592, 22668, 23348, 23621, 24138 

747-236F 22306 

747-243F 22545 

747-245F 20826, 20827, 21764, 21841, 22150, 22151 

747-246F 21034, 21681, 22063, 22477, 22989, 23391, 23641 

747-249F 21827, 21828, 22237, 22245 

747-251F 21120-21122, 21321, 22388, 23887, 23888 

747-258F 21737 

747-267F 23864, 24568 

747-268F 24359 

747-281F 23138, 23139, 23350, 23919, 24576, 25171 

747-2B3F 21515, 21835 

747-2B5F 22480, 22481, 22486, 24195, 24196 

747-2J6F 24960 

747-2J9F 21486, 21487, 21507, 21514, 21668 

747-2R7F 21650, 22390 

747-2S4F 22169 
5 A20WE 

IV - 747-200C (Approved April 17, 1973) Transport Aircraft

The 747-200C is a convertible version of the basic 747-200B series aircraft. The exterior geometry of the 747-200C is identical to the 

747-200B and aircraft systems are essentially unchanged except for differences resulting from the changes outlined below. The principal 

differences involve the following: 

 Upward opening nose cargo door. 

 Redesigned interior permitting all passenger, all cargo, or mixed passenger/cargo configurations. 

 Increased strength of main deck floor and keel beam. 

 Increased strength of center wing section. 

 T.E. flap two position load relief system. 

 Main deck smoke detection system. 

 Optional side cargo door. 

Engines: 4 Pratt and Whitney JT9D-3A, JT9D-7, JT9D-7A, JT9D-7F, JT9D-7J, JT9D-70A,JT9D-7Q, JT9D-7Q3, 

JT9D-7R4G2 

 4 General Electric CF6-50E, CF6-50E1,CF6-50E2 

 4 Rolls Royce RB211-524B2-19, RB211-524C2, RB211-524D4. 

See NOTE 5 regarding intermixing of engines. 

Fuel: See NOTE 3. 

Engine Limits: See data pertinent to all models. 

Airspeed Limits: VMO/MMO 375/0.92 (KEAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/ 

Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

 FAA Approved Weight and Balance Control and Loading Manual: D6-13700 

 FAA Approved Airplane Flight Manuals: D6-13703, D6-33747 

Model Eligible Serial Numbers

747-21AC 23652, 24134 

747-258C 21190, 21594 

747-270C 21180, 21181, 22366 

747-271C 21964, 21965, 22403 

747-273C 20651-20653 

V - 747SR (Approved September 26, 1973) Transport Aircraft

The 747SR is basically a 747-100 series airplane with certain modifications to improve the fatigue life. 

Engines: 4 General Electric CF6-45A, CF6-45A2, CF6-50E2 

 4 Pratt and Whitney JT9D-7, JT9D-7A. 

See NOTE 5 regarding intermixing of engines. 

Fuel: See NOTE 3. 

Engine Limits: See data pertinent to all models. 

Airspeed Limits: VMO/MMO 375/0.92 (KEAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 
A20WE 6 

 

V. 747SR (cont’d)

MaximumBaggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

 FAA Approved Weight and Balance Control and Loading Manual: D6-13700 

 FAA Approved Airplane Flight Manuals: D6-13703, D6-33747 

Model Eligible Serial Numbers

747SR-46 20781-20784, 20923, 21032, 21033 

747SR-81 21604-21606, 21922-21925, 22291-22294, 22594, 22595, 22709-22712 

VI - 747SP (Approved February 4, 1976) Transport Aircraft

The 747SP (Special Performance) is basically a long-range derivative of the 747-100. The exterior geometry of the 747SP has been 

changed from the 747-100. Aircraft systems are essentially unchanged except for differences resulting from changes outlined below. 

The principal differences involve the following: 

 Overall airplane length is 47'1" shorter. 

 Body is 48'5" shorter. 

 Overall airplane height is approximately 2'11" higher. 

 Vertical tail has been extended 5 feet. 

 Horizontal tail has been extended on each end. 

 Flaps have been modified to a single variable pivot flap. 

 Main deck doors are reduced to 4 on each side. 

Engines: 4 Pratt and Whitney JT9D-3, JT9D-3A, JT9D-7, JT9D-7A, JT9D-7F, JT9D-7J 

 4 Rolls Royce RB211-524B2-19, RB211-524C2-19, RB211-524D4-19, RB211-524D4-39. 

See NOTE 5 regarding intermixing of engines. 

Fuel: See NOTE 3. 

Engine Limits: See data pertinent to all models. 

Airspeed Limits: VMO/MMO 375/0.92 (KEAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

 

 FAA Approved Weight and Balance Control and Loading Manual: D6-33800 

 FAA Approved Airplane Flight Manuals: D6-34047, D6-36747 

Model Eligible Serial Numbers

747SP-09 21300, 22298, 22547, 22805 

747SP-21 21022-21026, 21441, 21547, 21548, 21648, 21649 

747SP-27 21785, 21786, 21992, 22302 

747SP-31 21961-21963 

747SP-38 22495, 22672 

747SP-44 21132-21134, 21253, 21254, 21263 

747SP-68 21652, 22503, 22750 

747SP-70 22858 

747SP-86 20998, 20999, 21093, 21758 

747SP-94 21174, 21175 

747SP-B5 22483, 22484 

747SP-J6 21932-21934 

747SP-Z5 23610 
7 A20WE 

VII - 747-100B (Approved August 1, 1979) Transport Aircraft

The 747-100B is basically a 747SR series airplane with certain modifications to permit increases in maximum permissible operating 

weights. 

Engines: 4 Pratt and Whitney JT9D-7A, JT9D-7F 

 4 Rolls Royce RB2ll-524B2-19, RB211-524C2-19, RB211-524D4-19, RB211-524D4-39. 

 See NOTE 5 regarding intermixing of engines. 

Fuel: See NOTE 3. 

Engine Limits: See data pertinent to all models. 

Airspeed Limits: VMO/MMO 375/0.92 (KEAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

 FAA Approved Weight and Balance Control and Loading Manual: D6-13700 

 FAA Approved Airplane Flight Manuals: D6-13703, D6-35747 

Model Eligible Serial Numbers

747-146B 22066, 22067, 23150 

747-168B 22498-22502, 22747-22749 

747-186B 21759 

See NOTE 7. 

VIII - 747-300 (Approved March 1, 1983) Transport Aircraft

The 747-300 is basically a 747-200 series airplane with a stretched upper deck. 

Engines: 4 Pratt and Whitney JT9D-7R4G2 

 4 General Electric CF6-50E2, CF6-80C2B1 

 4 Rolls Royce RB211-524B2-19, RB211-524C2-19, or RB211-524D4-19, RB211-524D4-39. 

See NOTE 5 regarding intermixing of engines. 

Fuel: See NOTE 3. 

Engine Limits: See data pertinent to all models. 

Airspeed Limits: VMO/MMO 375/0.92 (KEAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

FAA Approved Weight and Balance Control and Loading Manual: D6-13700 

FAA Approved Airplane Flight Manuals: D6-13703, D6-33747, D6-35747 
A20WE 8 

 

VIII – 747-300 (cont’d):

Model Eligible Serial Numbers

747-306 23056, 23137, 23508 

747-312 23026-23033, 23243-23245, 23409, 23410, 23769 

747-329 23439, 24837 

747-337 24159, 24160 

747-338 23222-23224, 23408, 23688, 23823 

747-341 23394, 23395, 24106-24108 

747-344 22970, 22971 

747-346 23067, 23068, 23149, 23151, 23482, 23638-23640, 23967-23969, 24018, 24019, 24156 

747-357 22704, 22705, 22995, 22996, 23751 

747-366 24161, 24162 

747-367 23221, 23392, 23534, 23709, 23920, 24215 

747-368 23262-23271 

747-3B3 22870, 23413, 23480 

747-3B5 22487, 22489, 24194 

747-3D7 23721, 23722 

747-3G1 23070 

747-3H6 23600 

IX - 747-100B SUD (Approved March 24, 1986) Transport Aircraft

The 747-100B SUD is basically a 747-100B series airplane with a stretched upper deck. 

Engines: 4 Pratt and Whitney JT9D-7A 

 See NOTE 5 regarding intermixing of engines. 

Fuel: See NOTE 3. 

Engine Limits: See data pertinent to all models. 

Airspeed Limits: VMO/MMO 375/0.92 (KEAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

 FAA Approved Weight and Balance Control and Loading Manual: D6-13700 

 FAA Approved Airplane Flight Manual: D6-13703 

Model Eligible Serial Numbers

747-146B SUD 23390, 23637 

DATA PERTINENT TO ALL MODELS, EXCEPT MODEL 747-400 AND 747-8F SERIES

Engine Limits: 

(Pratt & Whitney) JT9D-3 JT9D-3A JT9D-7 JT9D-7A JT9D-7F JT9D-7J

Takeoff static thrust 43,500 43,500 45,500 46,150 46,750 48,650 

standard day, lbs. lbs. lbs. lbs. lbs. lbs. 

seal level conditions 

(in pounds); 

Dry (5 min) (Ideal) 

With water injection 43,500 45,000 47,000 47,670 48,650 

(2 1/2 min.) lbs. lbs. lbs. lbs. lbs. 

 
9 A20WE 

DATA PERTINENT TO ALL MODELS, EXCEPT MODEL 747-400 AND 747-8F SERIES (cont’d):

Maximum continuous JT9D-3 JT9D-3A JT9D-7 JT9D-7A JT9D-7F JT9D-7J

static thrust, 

standard day, sea 36,400 36,400 39,650 40,080 39,200 40,200 

level condition: lbs. lbs. lbs. lbs. lbs. lbs. 

(Ideal) 

Engine Limits: 

(Pratt & Whitney) JT9D-70A JT9D-7Q JT9D-7Q3 JT9D-7R4G2

Takeoff static thrust 

standard day, 51,140 51,100 51,100 54,750 

sea level conditions lbs. lbs. lbs. lbs. 

(in pounds) Dry (5 min) 

(Ideal) 

Maximum continuous 

static thrust: 44,290 44,290 44,290 50,200 

standard day, sea level lbs. lbs. lbs. lbs. 

condition: (Ideal) 

Engine Limits 

(General Electric) CF6-50E 

 CF6-50E1 CF6-45A 

 CF6-50E2 CF6-45A2 CF6-80C2B1

Engine thrust ratings: 

(Ideal) 

Takeoff (5 min) 51,800 lbs. 45,600 lbs. 55,980 lbs. 

Maximum continuous 46,300 lbs. 43,250 lbs. 

Engine Limits: 

(Rolls Royce) RB211-524B2-19

Rated takeoff thrust 

(5 min.) 49,120 lbs. 

Sea level static 

conditions (Ideal) 

Rated Maximum 

continuous thrust 44,780 lbs. 

Engine Limits: RB211-524D4-19 

(Rolls Royce) RB211-524C2-19 RB211-524D4-39

Rated takeoff thrust 

(5 min.) 50,600 lbs. 51,980 lbs. 

Sea level static 

conditions (Ideal) 

Rated Maximum 

continuous thrust 46,120 lbs. 47,230 lbs. 

For engine operating limits see the FAA Approved Airplane Flight Manual under the serial numbers section of this data sheet or the 

appropriate engine type certificate data sheet: 

 Pratt & Whitney E3NE and E20EA 

 General Electric E23EA and E13NE 

 Rolls Royce E12EU 

Thrust Setting: The appropriate EPR or N1 thrust setting curve in Section 4 of the Airplane Flight Manual must be used for 

control of engine thrust. 

Maximum Operating 

Altitude: The maximum operating altitude is 45,100 feet. 
A20WE 10 

 

DATA PERTINENT TO ALL MODELS, EXCEPT MODEL 747-400 AND 747-8F SERIES (cont’d):

Minimum Crew: For all flights, 3 persons (pilot, copilot, flight engineer). When passengers are being carried, one attendant is 

required at each No. 3 over-wing exit. At least one flight attendant is required on the upper deck during taxi, 

takeoff and landing when passengers occupy the upper deck. 

Maximum Passengers: For 747SR and 747-100, -100B, -200B, -200C airplanes the total passenger capacity is limited to: 

 550 with 5 pair of Type "A" exits on main deck 

 440 with 4 pair of Type "A" exits on main deck 

 Upper deck passenger capacity is limited to: 

 8 with one exit on the upper deck 16 with one exit, improved slide and smoke barrier 

 24 with one exit, straight stairway, smoke barrier, and escape slide capable of operation in 25 kt. wind 

 32 if in compliance with the requirements of Special Condition No. 25-61-NW-1 

 45 if in compliance with the requirements of Special Condition No. 25-71-NW-3 

 5 persons on upper deck per Exemption 1870D. 

 (747-100 and 747-200) 

 For 747SP the total passenger capacity is limited to: 

 400 passengers with the same upper deck limits as listed above. 

 For 747-200F the total passenger capacity is limited to: 

 19 passengers on upper deck with 2 doors, 25 knot slides, C.G. Limitation, and compliance shown 

with AD 93-07-15; or 19 persons on upper deck equipped with emergency descent reels and 

harnesses, 2 doors and 25 knot slides. 

 5 persons on upper deck per Exemption 1870D. 

 For 747-300 and 747-100B SUD the total passenger capacity is limited to: 

 660 passengers with 5 pair of Type "A" exits on the main deck plus one pair of Type "A"exits on 

the upper deck. Main deck limited to 550 and upper deck limited to 110 if in compliance with the 

requirements of modified Special Condition No. 25-71-NW-3, transmitted to Boeing by FAA letter 

dated August 3, 1981.) See NOTE 9. 

 550 passengers with 4 pair of Type "A" exits on the main deck limited to 440 and upper deck 

limited to 110 if in compliance with the requirements of modified Special Condition No. 

25-71-NW-3, transmitted to Boeing by FAA letter dated August 3, 1981. 

Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification 

Basis) must be installed in the aircraft for certification. The required equipment is noted in the Type Design 

Data. 

Datum: Balance Arm Datum corresponds to Body Station 0 and is 90 inches (290 inches on SP) forward of nose. All 

productions stations coincide numerically with arms except on 747SP. 

 Horizontal distance of datum to nose gear jack points in 384.7 inches. (584.7 inches on 747SP) 

Mean Aerodynamic 

Chord (MAC): MAC length is 327.8 inches. Leading edge of MAC is 1258 inches aft of datum. 

Level Means: A plumb-bob attachment and leveling provision scale are provided in the R.H. body wheel well at BS 

1444.0. They are referred to as ARM on the 747SP and are a true measure in inches aft of a forward 

reference datum which is located 290 inches ahead of the airplane nose. 

 Balance ARMS have the following relationship with Body Stations on the 747SP: 

 BODY STATION ADJUSTMENT ARM 

 INCHES INCHES INCHES 

 

 90 to 800 +200 290 to 1,000 

 (800 to 1,000 Section removed) 

 

 1,000 to 1,480 0 1,000 to 1,480 

 (1,480 to 1,640 Section removed) 

 1,640 to 2,140 -160 1,480 to 1,980 

 (2,140 to 2,360 Section removed) 

 

 2,360 to 2,792 -380 1,980 to 2,412 
11 A20WE 

DATA PERTINENT TO ALL MODELS, EXCEPT MODEL 747-400 AND 747-8F SERIES (cont’d):

Control Surface 

Movements: To insure proper operation of the airplane, the movement of the various control surfaces must be carefully 

controlled by proper rigging of the flight control systems. The airplane must, therefore, be rigged according 

to the following FAA-approved data: 

 Boeing Drawing Numbers 

 65B04001 Control Installation Aileron and Spoiler 

 65B04002 Control Installation Elevator 

 65B04003 Control Installation Rudder 

 65B04004 Control Installation Stabilizer Trim 

 65B04006 Control Installation Rudder Trim 

 65B04007 Control Installation Wing Flap 

 65B04016 Control Installation Speed Brakes 

 

Service Information: Boeing Reports D6-13592, "Structural Repair Manual", (except for 747SP) is FAA-Approved. 

 Boeing Reports D6-34024, "Structural Repair Manual", is FAA-Approved for the 747SP. Service 

 Bulletins and other service information, when FAA-Approved, will carry a statement to the effect. 

Certification Basis: FAR Part 1, FAR Part 21, FAR Part 36, FAR Part 25 effective February 1, 1965, Amendments 25-1 through 

25-8 plus 25-15, 25-17, 25-18, 25-20, and Amendment 25-39 transmitted by FAA letter dated February 4, 

1977, and special conditions summarized for record purposes as enclosed with FAA letter to The Boeing 

Company dated February 20, 1970. Special Condition 4A, revised to apply to airplanes with the landing gear 

load evener system deleted, was recorded as attachment to an FAA letter to The Boeing Company dated May 

12, 1971. 

 

Based on 14 CFR § 21.101(g) for changes to TC’s, applicable provisions of 14 CFR part 26 are included in 

the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate 

compliance with the applicable sections. 

 

 Amendment 25-46, Section 25.803(d) transmitted by FAA letter to The Boeing Company dated September 2, 

1983. This is limited to all passenger configurations and 6/7 pallet combi configurations for Model 747-100, 

-200, and -300 series airplanes. 

 Exemptions from 14 CFR part 25: 

 1. Exemption from 14 CFR 25.807(c)(1), 25.807(c)(5), 25.809(f)(1), 25.813(b), Allowance of non crew 

members on the upper deck of 747-200F, 747-200C and certain 747-100 airplanes when in the main deck 

cargo configuration. (Exemption No. 1870 dated September 14, 1973, No. 1870A dated March 10, 1977, No. 

1870B dated October 26, 1981, No. 1870C dated June 2, 1986, and No. 1870D dated April 3, 1991) 

 

 Special Condition No. 25-61-NW-1 for occupancy not to exceed 32 passengers on the upper deck of 

airplanes with spiral staircase was transmitted to The Boeing Company by FAA letter dated February 26, 

1975. 

 Special Condition No. 25-71-NW-3 for occupancy not to exceed 45 passengers on the upper deck of 

airplanes with straight segmented stairway was transmitted to The Boeing Company by FAA letter dated 

September 8, 1976. 

 Modification of Special Condition No. 25-71-NW-3 for occupancy not to exceed 110 passengers on the 

upper deck of airplanes with straight segmented stairway was transmitted to The Boeing Company by FAA 

letter dated August 3, 1981. 

 RB211 engine oil filter system complies with FAR 25.1019 and 25.1305(c)(7) of Amendment 25-36. 

 Special Condition No. 25-77-NW-4 (modification of the autopilot system to approve the airplane for use of 

the system under category IIIb landing conditions) was transmitted to The Boeing Company by FAA letter 

dated July 8, 1977. 

 

 Special Condition No. 25-ANM-16 for installation of an overhead crew rest area, occupancy not to exceed 

10 crewmembers. FAA approved procedures required for compliance with paragraph 3 of the Special 

Condition are located in Boeing Document D926U303, Appendix D. 
A20WE 12 

 

DATA PERTINENT TO ALL MODELS, EXCEPT MODEL 747-400 AND 747-8F SERIES (cont’d):

Special Condition No. 25-ANM-16A for installation of an overhead crew rest area with hard partitions and a 

curtain, occupancy not to exceed 10 crewmembers. FAA approved procedures required for compliance with 

paragraph 2 and 13(e) of the Special Condition are located in Boeing Document D926U303, Appendix D and 

E.

 

 Compliance with the following optional requirements has been established: 

 Ditching Provisions FAR 25.801 

 Ice Protection Provisions FAR 25.1419 

 Equivalent Safety Findings exist with respect to the following Regulations: 

 For Model 747-100, -200B, -200F, -200C, 747SR, 747SP, -100B, -300, -100B SUD: 

 25.1415(d) Emergency Locator Transmitter (ELT) 

 25.561(b)(3)(ii) Passenger (and non-crewmember) seat track bending calculations only per FAA 

Memorandum TD6633SE-T-C-1, dated January 26, 2004. 

 For 747-300 only: 

 25.812(k)(2) 

 25.815 

 For Model 747-100, -200, -300 Series: 

 25.773(b)(2)(i), Amendments 25-1 through 25-67 

 25.811(f) Emergency Exit Marking 

Production Basis: Production Certificate No. 700. 

Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification 

Basis) must be installed. 

X - 747-400 (Approved January 10, 1989) Transport Aircraft

The 747-400 is basically 747-300 series airplane with wing extension and winglets, additional fuel tank in the horizontal stabilizer, 

additional auxiliary fuel tank in the forward section of the cargo bay and reconfigured cockpit for two man crew and associated automation 

and advanced avionics. 

Engines: 4 Pratt and Whitney PW4000 Series 

 General Electric CF6-80C2B1F, CF6-80C2B5F 

 Rolls Royce RB211-524G2-19, RB211-524G3-19, RB211-524H2-19, RB211-524G2-T-19, RB211-524G3-

T-19, RB211-524H2-T-19. 

 WARNING: To prevent unsafe airplane handling characteristics, PW4000 series engines with electronic 

Engine control (EEC) part number 791100-14-102 (Pratt & Whitney part number 54D043) must not be 

installed on the same airplane as PW4000 series engines that have the ring case compressor configuration. 

This combination of engine configurations is not approved because of a significant difference in engine 

acceleration rates and the effect of that difference on airplane handling characteristics. Ring case compressor 

equipped engines were approved with the same engine model number as previously approved PW4000 

configurations, and must be identified by the presence of a “/A5” marked at the end of the “INSTL ARR” 

block on the engine data plate. 

 SEE NOTE 5 for further information regarding intermixing engines 

Engine Thrust Limits: See data pertinent to all Model 747-400's 

Fuel: See NOTE 3. 

Airspeed Limits: VMO/MMO 365/0.92 (KCAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 
13 A20WE 

X. 747-400 (cont’d):

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel/Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

FAA Approved Weight and Balance Control and Loading Manual: D043U400 

FAA Approved Airplane Flight Manuals: D6-U10001, D6-U10002, and D6-U10003 

Model Eligible Serial Numbers

747-406 23982, 23999-24001, 24201, 24202, 24517, 24518, 25086, 25087, 25356, 25413, 26372-26374, 27202, 

28195, 28196, 28459, 28460, 30454, 30455 

747-409 24309-24313, 27965, 28709-28712, 29030, 29031, 29219, 29906, 33734-33737 

747-412 24061-24066, 24226, 24227, 24975, 25068, 25127, 25128, 26547-26552, 26554-26557, 26562, 27066-

27071, 27132-27134, 27137, 27178, 27217, 28022, 28023, 28025, 28028, 28029, 28031, 29950 

747-419 24386, 24855, 25605, 26910, 29375 

747-422 24322, 24363, 24380-24385, 25158, 25224, 25278, 25279, 25379, 25380, 25395, 26875-26881, 26890, 

26892, 26899-26903, 26906, 26908, 28715-28717, 28810-28813, 29166-29168, 30023 

747-428 24969, 24990, 25238, 25302, 25344, 25599-25602, 25628-25630, 32868, 32869, 32871 

747-430 23816, 23817, 24285-24288, 24715, 24740, 24741, 24761, 24966, 24967, 25045-25047, 26425-26427, 

28086, 28284-28287, 29101, 29492, 29493, 29868-29872, 32445 

747-433 24998, 25074, 25075 

747-436 23908-23911, 24047-24058, 24447, 24629, 24630, 25406, 25427, 25432, 25434, 25435, 25809, 25810-

25814, 25817-25824, 27090-27092, 27349, 27350, 27478, 28700, 28848-28859, 

747-437 27078, 27164, 27165, 27214, 28094, 28095 

747-438 24354, 24373, 24406, 24481-24483, 24779, 24806, 24887, 24974, 25067, 25151, 25245, 25315, 25544-

25547, 25564-25566, 32909-32914 

747-441 24956, 24957 

747-443 30885, 32337-32340 

747-444 24976, 25152, 26637, 26638, 28468, 29119 

747-446 24423-24427, 24777, 24784, 24870, 24885, 24886, 25064, 25212, 25260, 25308, 26341-26344, 26346, 

26350, 26353, 26355, 26356, 26359-26362, 27099, 27100, 27645, 27646, 27648, 27650, 29899 

747-451 23719, 23720, 23818-23821, 24222-24225, 26473, 26474, 26477, 30267-30269, 33001, 33002 

747-458 26055, 26056, 27915, 29328 

747-467 23814, 23815, 24631, 24850, 24851, 24925, 24955, 25082, 25211, 25351, 25869-25874, 27117, 27230, 

27595 

747-468 28339-28343

747-469 27338, 27663 

747-475 24883, 24895, 24896, 25422 

747-481 24801, 24833, 24920, 25135, 25207, 25641, 25645, 28282, 28283, 29262, 29263, 30322 

747-41R 29406, 32745, 32746 

747-45E 26062, 27062, 27063, 27141, 27142, 27154, 27173, 27174, 27898, 27899, 28092, 28093, 29061, 29111, 

29112 

747-47C 24730, 24731 

747-48E 25405, 25452, 25777-25780, 25782, 25784, 28551, 28552 

747-4B3 24154, 24155 

747-4B5 24198-24200, 24619, 24621, 25205, 25275, 26392-26398, 26400, 26402-26405, 26407, 26409, 26412, 

27072, 27177, 27341, 27662, 28096, 28335 

747-4D7 24458, 24459, 24993, 25366, 26609, 26610, 26615, 26616, 27093, 27723- 27725, 28705, 28706, 32369-

32370 , 33770, 33771 

747-4F6 27261, 27262, 27602, 27827, 27828, 28959-28961 

747-4H6 24315, 24405, 24836, 25126, 25699-25703, 27042-27044, 27672, 28426-28428, 28432, 28433, 28435, 

29900, 29901, 30158 

747-4J6 24346-24348, 25879-25883, 28754-28756, 29070, 29071, 30158 

747-4P8 33684 

747-4Q3 29486 

747-4Q8 24958, 26255, 26326, 28194, 28757 

747-4U3 25704, 25705 
A20WE 14 

 

X. 747-400 (cont’d):

For engine operating limits see the FAA Approved Airplane Flight Manual referenced under Section X of this data sheet or the appropriate 

engine type certificate data sheet: 

 Pratt and Whitney: E24NE 

 General Electric: E13NE 

 Rolls Royce: E30NE 

Thrust Setting: The appropriate EPR or N1 thrust setting curves in Section 4 of the Airplane Flight Manual (AFM) must be 

used for control of engine thrust. 

Maximum Operating 

Altitude: 45,100 feet 

Minimum Crew: For all flights, 2 persons (pilot, copilot). When passengers are being carried, one attendant is required at 

each No. 3 over-wing exit. At least one flight attendant is required on the upper deck during taxi, takeoff, 

and landing when passengers occupy the upper deck. 

Maximum Passengers: For 747-400 the total passenger capacity is limited to: 

 660 passengers with 5 pair of Type "A" exits on main deck plus one pair of Type "A" exits on the upper 

deck. (Main deck limited to 550 and upper deck limited to 110 if in compliance with the requirements of 

modified Special Condition Number 25-71-NW-3, transmitted to Boeing by FAA letter dated August 3, 

1981.) See NOTE 9. 

Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification 

Basis) must be installed in the aircraft for certification. The required equipment is noted in the Type Design 

Data. 

 

Datum: Balance Arm Datum corresponds to Body Station 0 and is 90 inches forward of nose. All productions 

stations coincide numerically with arms. Horizontal distance of datum to nose gear jack points is 384.7 

inches. 

MAC: MAC length is 327.8 inches. Leading edge of MAC is 1258 inches aft of datum. 

Level Means: A plumb-bob attachment and leveling provision scale are provided in the R.H. body wheel well at BS 

1444.0. 

Control Surface 

Movements: To insure proper operation of the airplane, the movement of the various control surfaces must be carefully 

controlled by proper rigging of the flight control systems. The airplane must, therefore, be rigged according 

to the following FAA-approved data: 

 Boeing Drawing Numbers: 

 251U1001 Rigging Procedures Aileron and Spoiler 

 251U2001 Rigging Procedures Elevator 

 251U3002 Rigging Procedures Rudder 

 251U4001 Rigging Procedures Stabilizer Trim 

 253U5001 Rigging Procedure - Control Stand (Includes flap control assembly) 

 256U2001 Rigging Procedures Leading Edge Flaps 

 256U3001 Rigging Procedures Trailing Edge Flaps 

 251U1003 Rigging Procedures Speed Brakes 

Service Information: Boeing Report D634U102, "Structural Repair Manual," is FAA-approved. Service Bulletins and other 

Service information, when FAA-approved, will carry a statement to that effect. 

Certification Basis: Part 25 of the FAR, effective February 1, 1965, as amended by Amendments 25-1 through 25-59 with the 

following exceptions: 

 SECTION NO. TITLE THRU AMDT.25-

 25.107 Takeoff speeds 41 

 25.109 Accelerate-stop distance 41 

 25.149 Minimum control speed 41 
15 A20WE 

X. 747-400 (cont’d):

 25.251 Vibration and buffeting 22 

 25.305 Strength and deformation 22 

 25.331 General 45 

 25.351 Yawing conditions 45 

 25.365 Pressurized cabin loads 53 

 25.571 Damage-tolerance and fatigue 

 evaluation of structure 9 

 25.607 Fasteners 22 

 25.631 Bird Strike damage (NA)** 

 25.657 Hinges 22 

 25.675 Stops 37 

 25.683 Operation tests 22 

 25.772 Pilot compartment doors 46 

 25.773(b)(2)(ii) Pilot Compartment View 72 

 25.783 Doors 53 

 25.785 Seats, berths, safety belts, harnesses 50 

 25.787 Stowage Compartments 31 

 25.789 Retention of items of mass in passenger 

 and crew compartments 45 

 25.809 Emergency exit arrangement 45 

 25.812 Emergency lighting 31 

 25.832 Cabin ozone concentration (NA)**

 25.858 Cargo compartment fire detections systems (NA)** 

 25.1103 Induction system ducts and air duct systems 45 

 25.1401 Anticollision light system 26 

 25.1438 Pressurization and pneumatic systems (NA)**

 25.1529 Instructions for continued airworthiness (NA)**

 **Not applicable - The requirements of this section do not apply to this type design because the original 

certification basis, which did not include this section, has been determined to be adequate. 

 

 Based on 14 CFR § 21.101(g) for changes to TC’s, applicable provisions of 14 CFR part 26 are included in 

the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate 

compliance with the applicable sections. 

 

Compliance has been found for the following regulations at Amendment 26-0: 26.11 

 Compliance has been found for the following regulations at Amendment 26-1: 26.43, 26.45, 26.47, and 26.49

 

 Part 36 of the FAR as amended by Amendments 36-1 through 36-15, and any later amendments in existence 

at the time of certification. 

 Special Federal Aviation Regulation (SFAR) 27, as amended by Amendments 27-1 through 27-6 and any 

later amendments in existence at the time of type certification. 

 

 The following special conditions, exemptions; and equivalent safety findings, which are part of the Model 

747-300 certification basis, are also part of the certification basis for the Model 747-400. The special 

conditions include those enclosed with FAA letter to The Boeing Company dated February 20, 1970, and the 

following: 

 1. Special Condition 4A, revised to apply to airplanes with the landing gear load evener system deleted, 

was recorded as an enclosure to an FAA letter to The Boeing Company dated May 12, 1971. 

 2. Special Condition No. 25-61-NW-1 for occupancy not to exceed 32 passengers on the upper deck of 

airplanes with spiral staircase was transmitted to The Boeing Company by FAA letter dated February 

26, 1975. 

 

 3. Special Condition No. 25-71-NW-3 for occupancy not to exceed 45 passengers on the upper deck of 

airplanes with straight segmented stairway was transmitted to The Boeing Company by FAA 

letter dated September 8, 1976. 
A20WE 16 

 

X. 747-400 (cont’d):

 4. Modification of Special Condition No. 25-71-NW-3 for occupancy not to exceed 110 passengers on 

the upper deck of airplanes with straight segmented stairway was transmitted to The Boeing Company 

by FAA letter dated August 3, 1981. 

 

 5. Special Condition No. 25-77-NW-4 (modification of the auto pilot system to approve the airplane for 

use of the system under Category IlIb landing conditions) was transmitted to The Boeing Company by 

FAA letter dated July 8, 1977. 

 6. Special Condition No. 25-ANM-16 for use of an overhead crew rest area, occupancy not to exceed ten 

crewmembers was transmitted to The Boeing Company by FAA letter dated November 19, 1987. FAA 

approved procedures required for compliance with paragraph 13 of the Special Condition are located in 

Boeing Document D926U303, Appendix D. 

 

 7. Special Condition No. 25-ANM-24 applicable to flight deck displays and propulsion control system was 

provided to Boeing on December 22, 1988. 

 8. Special Condition No. 25-ANM-25 which established lightning and radio frequency (RF) energy 

protection requirements was provided to Boeing on December 22, 1988. 

9. Special Condition No. 25-ANM-16A for installation of an overhead crew rest area with hard partitions 

and a curtain, occupancy not to exceed 10 crewmembers. FAA approved procedures required for 

compliance with paragraph 2 and 13(e) of the Special Condition are located in Boeing Document 

D926U303, Appendix D and E. 

 The following optional requirements, which are part of the Model 747-300 certification basis, apply also to 

the 747-400: 

 Ditching Provisions Section 25.801 

 Ice Protection Provisions Section 25.1419 

 The following equivalent safety findings, previously made for earlier models under the provisions of Section 

21.21(b)(1), are also applicable to the Model 747-400: 

 Width of Aisle Section 25.815 

 Pilot Compartment View Section 25.773 

 Use of 1-g Stall Speed 

 (nonstructural items) Several (747-400 only) 

 Use of 1-g Stall Speed 

 (structural items) Several (747-400 only) 

 Position Light Distribution 

 and Intensities Section 25.1389(b)(3) 

 (747-400 only) 

 Fire-detection System Section 25.1203 

 See Note 1. 

 Pressure Relief Section 25.1103(d) 

 See Note 1. 

 Emergency Locator 

 Transmitter (ELT) Section 25.1415(d) 

Emergency Exit 

 Marking Section 25.811(f) 

Note 1: Applies to RB211-524G/H series engine installations only. 

 

 Equivalent Safety Findings exist with respect to the following Regulation: 25.773(b)(2)(i), Amendments 25-1 

throught 25-67 (Boeing 747-400 Series) 

 Part 25 of the FAR, effective February 1, 1965, as amended by Amendment 25-1 through 25-59 With the 

following exceptions: (See Note 15).
17 A20WE 

X. 747-400 (cont’d):

Exemptions from FAR Part 25: 

Exemption from 14 CFR 25.779(b)(1), 25.1301(d), and 25.1309(a), 747-400F with Rolls Royce RB211-524G/H engines 

installed with Full Authority Fuel Control Software “Issue 17” software (Exemption 10069, dated May 25, 2010) 

Certification Maintenance Requirements (CMR's): 

 The CMR's are listed in either the FAA-approved Section 9 of Boeing Maintenance Planning Data Document 

D621U400 or the applicable engine Type Certificate Data Sheet. The more restrictive requirement from 

these two documents shall be in force. 

Production Basis: Production Certificate No. 700 has been issued to The Boeing Company. 

Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification 

Basis) must be installed in the aircraft. 

XI - 747-400D (Approved October 10, 1991) Transport Aircraft

The 747-400D is basically the 747-400 series airplane with strengthened wings and without the 6-foot wing tip extension and 6-foot 

winglet. It is delivered with a wing tip equivalent in planform to the 747-300 airplane and has provisions for a "one-time" conversion from 

the Domestic configuration to the International configuration by adding the 747-400 wing extension and winglet. 

Engines: 4 General Electric CF6-80C2B1F 

Engine Thrust Limits: See data pertinent to all Model 747-400's 

Fuel: See NOTE 3. 

Airspeed Limits: VMO/MMO 365/0.92 (KCAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

FAA Approved Weight and Balance Control and Loading Manual: D043U400 

FAA Approved Airplane Flight Manual: D6U10002 

Model Eligible Serial Numbers

747-446D 25213, 25214, 26345, 26347-26349, 26351, 26352 

747-481D 25292, 25639, 25640, 25642-25644, 25646, 25647, 27163, 27436, 27442 

For engine operating limits see the FAA Approved Airplane Flight Manual referenced under Section XI of this data sheet or the 

appropriate engine type certificate data sheet: 

 General Electric: E13NE 

Thrust Setting: The appropriate EPR or N1 thrust setting curves in Section 4 of the Airplane Flight Manual (AFM) must be 

used for control of engine thrust. 

Maximum Operating 

Altitude: 45,100 feet 

Minimum Crew: For all flights, 2 persons (pilot, copilot). When passengers are being carried, one attendant is required at 

each No. 3 over-wing exit. At least one flight attendant is required on the upper deck during taxi, takeoff, 

and landing when passengers occupy the upper deck. 

Maximum Passengers: For 747-400D airplanes the total passenger capacity is Limited to: 

 660 passengers with 5 pair of Type "A" exits on main deck plus one pair of Type "A" exits on the upper 

deck. (Main deck limited to 550 and upper deck limited to 110 if in compliance with the requirements of 

modified Special Condition Number 25-71-NW-3, transmitted to Boeing by FAA letter dated August 3, 

1981). 
A20WE 18 

 

XI. 747-400D (cont’d):

Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See 

 Certification Basis) must be installed in the aircraft for certification. The required equipment is 

 noted in the Type Design Data. 

Datum: Balance Arm Datum corresponds to Body Station 0 and is 90 inches forward of nose. All 

 productions stations coincide numerically with arms. Horizontal distance of datum to nose gear 

 jack points is 384.7 inches. 

MAC: MAC length is 327.8 inches. Leading edge of MAC is 1258 inches aft of datum. 

Level Means: A plumb-bob attachment and leveling provision scale are provided in the R.H. body wheel well at 

 BS 1444.0. 

Control Surface 

Movements: To insure proper operation of the airplane, the movement of the various control surfaces must be carefully 

controlled by proper rigging of the flight control systems. The airplane must, therefore, be rigged according 

to the following FAA-approved data: 

 Boeing Drawing Numbers: 

 251U1001 Rigging Procedures Aileron and Spoiler 

 251U2001 Rigging Procedures Elevator 

 251U3002 Rigging Procedures Rudder 

 251U4001 Rigging Procedures Stabilizer Trim 

 253U5001 Rigging Procedures Control Stand (includes flap control assembly) 

 256U2001 Rigging Procedures Leading Edge Flaps 

 256U3001 Rigging Procedures Trailing Edge Flaps 

 251U1003 Rigging Procedures Speed Brakes 

Service Information: Boeing Report D634U102, "Structural Repair Manual," is FAA-approved. Service Bulletins and other 

Service information, when FAA-approved, will carry a statement to that effect. 

Certification Basis: Part 25 of the FAR, effective February 1, 1965, as amended by Amendments 25-1 through 25-70 

 with the following exceptions: 

 THRU 

 SECTION NO. TITLE AMDT.25-

 25.107 Takeoff speeds 41 

 25.109 Accelerate-stop distance 41 

 25.149 Minimum control speed 41 

 25.251 Vibration and buffeting 22 

 25.305 Strength and deformation 22 

 25.331 General 45 

 25.351 Yawing conditions 45 

 25.365 Pressurized cabin loads 53 

 25.561 General 63 

 25.562 Emergency landing dynamic conditions 63** 

25.571 Damage-tolerance and fatigue evaluation of structure 9 

 25.607 Fasteners 22 

 25.631 Bird strike damage (NA)** 

 25.657 Hinges 22 

 25.675 Stops 37 

 25.683 Operation tests 22 

 25.772 Pilot compartment doors 46 

 25.783 Doors 53 

 25.785 Seats, berths, safety belts, harnesses 50 

 25.809 Emergency exit arrangement 45 

 25.812 Emergency lighting 31 

 25.855 Cargo or baggage compartments 59 

 25.858 Cargo Compartment Fire Detection Systems (NA)**

 25.1103 Induction system ducts and air duct systems 45 

 25.1401 Anticollision light system 26 

 25.1438 Pressurization and pneumatic systems (NA)**

 
19 A20WE 

XI. 747-400D (cont’d):

25.1529 Instructions for continued airworthiness (NA)**

** Not applicable - The requirements of this section do not apply to this type design because the original 

certification basis, which did not include this section, has been determined to be adequate. 

Based on 14 CFR § 21.101(g) for changes to TC’s, applicable provisions of 14 CFR part 26 are included in the certification basis. For any 

future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. 

Compliance has been found for the following regulations at Amendment 26-0: 26.11 

Compliance has been found for the following regulations at Amendment 26-1: 26.43, 26.45, 26.47, and 26.49

Part 36 of the FAR as amended by Amendments 36-1 through 36-18. 

Special Federal Aviation Regulation (SFAR) 27, as amended by Amendments 27-1 through 27-6, and any later amendments in existence, 

at the time of certification 

The following special conditions, exemptions, and equivalent safety findings, which are part of the Model 747-300 certification basis, are 

also part of the certification basis for the Model 747-400D: 

The special conditions include those enclosed with FAA letter to The Boeing Company dated February 20, 1970, and the following:

 1. Special Condition 4A, revised to apply to airplanes with the landing gear load evener system deleted, 

was recorded as an enclosure to an FAA letter to The Boeing Company dated May 12, 1971. 

 

 2. Special Condition No. 25-61-NW-1 for occupancy not to exceed 32 passengers on the upper deck of 

airplanes with spiral staircase was transmitted to The Boeing Company by FAA letter dated February 

26, 1975. 

 

 3. Special Condition No. 25-71-NW-3 for occupancy not to exceed 45 passengers on the upper deck of 

airplanes with straight segmented stairway was transmitted to The Boeing Company by FAA 

letter dated September 8, 1976. 

 4. Modification of Special Condition No. 25-71-NW-3 for occupancy not to exceed 110 passengers on the 

upper deck of airplanes with straight segmented stairway was transmitted to The Boeing Company by 

FAA letter dated August 3, 1981. 

 

 5. Special Condition No. 25-77-NW-4 (modification of the auto pilot system to approve the airplane for 

use of the system under Category IIIb landing conditions) was transmitted to The Boeing Company by 

FAA letter dated July 8, 1977. 

 

 6. Special Condition No. 25-ANM-16 for use of an overhead crew rest area, occupancy not to exceed ten 

crewmembers was transmitted to The Boeing Company by FAA letter dated November 19, 1987. 

 7. Special Condition No. 25-ANM-24 applicable to flight deck displays and propulsion control system was 

provided to Boeing on December 22, 1988. FAA approved procedures required for compliance with 

paragraph 13 of the Special Condition are located in Boeing Document D926U303, Appendix D. 

 8. Special Condition No. 25-ANM-25 which established lightning and radio frequency (RF) energy 

protection requirements was provided to Boeing on December 22, 1988. 

9. Special Condition No. 25-ANM-16A for installation of an overhead crew rest area with hard partitions 

and a curtain, occupancy not to exceed 10 crewmembers. FAA approved procedures required for 

compliance with paragraph 2 and 13(e) of the Special Condition are located in Boeing Document 

D926U303, Appendix D and E.

The following Optional requirements, which are part of the Model 747-300 certification basis, apply also to 

the 747-400D: 

 Ditching Provisions Section 25.801 

 Ice Protection Provisions Section 25.773 
A20WE 20 

 

XI. 747-400D (cont’d):

The following equivalent safety findings, previously made for earlier models under the provisions of Section 21.21(b)(1), are also 

applicable to the Model 747-400D: 

 Width of Aisle Section 25.815 

 

 Use of 1-g Stall Speed 

 (nonstructural items) Several 

 

 Use of 1-g Stall Speed 

 (structural items) Several 

 Position Light Distribution 

 and Intensities Section 25.1389(b)(3) 

 Emergency Locator 

 Transmitter (ELT) Section 25.1415(d) 

 Emergency Exit Markings Section 25.811(f) 

 Part 25 of the FAR, effective February 1, 1965, as amended by Amendment 25-1 through 

 25-59 with the following exceptions: (See Note 15)

Certification Maintenance Requirements (CMR's): 

 The CMR's are listed in the FAA-approved Section 9 of Boeing Maintenance Planning Data Document 

D621U400 or the applicable engine Type Certificate Data Sheet. The more restrictive requirements from 

these two documents shall be in force. 

Production Basis: Production Certificate No. 700. 

Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification 

Basis) must be installed in the aircraft. 

Note: The Boeing Company has offered and the FAA has agreed, to upgrade the certification basis for the Model 

747-400D in relation to FAR Part 25.365 (Amendment 25-54), Pressurized Cabin Loads on the condition that 

initial deliveries need not comply at the time of delivery, but shall be retrofitted later. 

 By March 31, 1993, Model 747-400D production airplanes must include an FAA-approved production 

change which demonstrates compliance with the Certification Basis. Retrofit modification kits will also be 

available (beginning June 30, 1993) for installation in airplanes delivered without the production change 

(S/N's 25213, 25214, 25292, 25639, 25640, 25642 & 26347). 

XII - 747-400F (Approved October 27, 1993) Transport Aircraft

The new 747-400F (Freighter) is basically the 747-400 series airplane with strengthened wings and the 747-200F fuselage. 

Engines: 4 Pratt & Whitney PW4000 Series 

 4 General Electric CF6-80C2B1F, CF6-80C2B5F 

 Rolls-Royce RB211-524-G2-19, RB211-524G3-19, RB211-524H2-19, RB211-524G2-T-19, 

 RB211-524G3-T-19, RB211-524H2-T-19 

 

 WARNING: To prevent unsafe airplane handling characteristics, PW4000 series engines with electronic 

engine control (EEC) part number 791100-14-102 (Pratt & Whitney part number 54D043) must not be 

installed on the same airplane as PW4000 series engines that have the ring case compressor configuration. 

This combination of engine configurations is not approved because of a significant difference in engine 

acceleration rates and the effect of that difference on airplane handling characteristics. Ring case compressor 

equipped engines were approved with the same engine model number as previously approved PW4000 

configurations, and must be identified by the presence of a “/A5” marked at the end of the “INSTL ARR” 

block on the engine data plate. 

SEE NOTE 5 for additional information regarding intermixing engines. 
21 A20WE 

XII. 747-400F (cont’d):

Engine Thrust Limits: See data pertinent to all Model 747-400's 

Fuel: See NOTE 3. 

Airspeed Limits: VMO/MMO 365/0.92 (KCAS) For other airspeed limits see the appropriate FAA Approved Airplane Flight 

Manual. 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Weights: See the appropriate FAA Approved Airplane Flight Manual. 

Maximum Baggage/Cargo: See the appropriate Weight and Balance Control and Loading Manual. 

Fuel and Oil Capacity: See the appropriate Weight and Balance Control and Loading Manual. 

FAA Approved Weight and Balance Control and Loading Manual: D043U550 

FAA Approved Airplane Flight Manual: D6U10001, D6U10002 and D6U10003 

Model Eligible Serial Numbers

747-406F 33694-33696, 35233 

747-409F 30759-30771, 33729, 33731-33733, 33738, 33739, 34265, 34266 

747-412F 26553, 26558-26561, 26563, 28026, 28027, 28030, 28032, 28263, 32897-32902 

747-428F 25632, 32866, 32867, 32870, 33096, 33097 

747-446F 33748, 33749 

747-467F 27175, 27503, 30804, 30805, 32571, 34150, 36867-36871, 37299 

747-481F 34016-34018, 34283 

747-4B5F 26401, 26406, 26408, 26411, 26413, 26414, 26416, 27073, 32808, 32809, 33515-33517, 33945, 33946, 

34302, 35526 

747-4G4F 30201 

747-4H6F 28434, 29902 

747-4R7F 25866-25868, 29053, 29729-29733, 30400, 30401, 33827, 34235, 35804, 35805 

747-40BF 35207, 35208 

747-41BF 32803, 32804 

747-44AF 35662-35669 

747-45EF 30607-30609 

747-46NF 30808-30812, 35420, 35421 

747-47UF 29252-29261, 30558, 30559, 32837, 32838, 32840 

747-48EF 25781, 25783, 27603, 28367, 29170, 29907 

747-4EVF 35169-35174 

747-4FTF 34235, 34239, 34240 

747-4HAF 35232-35237 

747-4HQF 37303, 37304 

747-4KZF 36132-36135, 36784, 36785 

For engine operating limits see the FAA Approved Airplane Flight Manual referenced under Section XII of this data sheet or the 

appropriate engine type certificate data sheet: 

 Pratt & Whitney E24NE 

 General Electric: E13NE 

 Rolls-Royce E30NE 

Thrust Setting: The appropriate EPR or N1 thrust setting curves in Section 4 of the Airplane Flight Manual (AFM) must be 

used for control of engine thrust. 

Maximum Operating 

Altitude: 45,100 feet 

Minimum Crew: For all flights, 2 persons (pilot, copilot). 

Maximum Persons: For 747-400F airplanes the total persons capacity is Limited to: 

 Six (6) persons on the upper deck per Exemption 1870E 
A20WE 22 

 

XII. 747-400F (cont’d):

Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification 

Basis) must be installed in the aircraft for certification. The required equipment is noted in the Type Design 

Data. 

Datum: Balance Arm Datum corresponds to Body Station 0 and is 90 inches forward of nose. All production stations 

coincide numerically with arms. Horizontal distance of datum to nose gear jack points is 384.7 inches. 

MAC: MAC length is 327.8 inches. Leading edge of MAC is 1258 inches aft of datum. 

Level Means: A plumb-bob attachment and leveling provision scale are provided in the R.H. body wheel well at BS 

1444.0. 

Control Surface Movements: To insure proper operation of the airplane, the movement of the various control surfaces must be carefully 

controlled by proper rigging of the flight control systems. The airplane must, therefore, be rigged according 

to the following FAA-approved data: 

 Boeing Drawing Numbers: 

 251U1001 Rigging Procedures Aileron and Spoiler 

 251U2001 Rigging Procedures Elevator 

 251U3002 Rigging Procedures Rudder 

 251U4001 Rigging Procedures Stabilizer Trim 

 253U5001 Rigging Procedures - Control Stand (includes flap control assembly) 

 256U2001 Rigging Procedures Leading Edge Flaps 

 256U3001 Rigging Procedures Trailing Edge Flaps 

 251U1003 Rigging Procedures Speed Brakes 

Service Information: Boeing Report D634U102, "Structural Repair Manual," is FAA-approved. Service Bulletins and other 

Service Information, when FAA-approved, will carry a statement to that effect. 

Certification Basis: Part 25 of the FAR, effective February 1, 1965, as amended by Amendments 25-1 through 25-67 with the 

following exceptions: 

 (See Note 14 for cargo compartment liner requirements) 

 SECTION NO. TITLE THRU AMDT.25-

 25.107 Takeoff speeds 41 

 25.109 Accelerate-stop distance 41 

 25.149 Minimum control speed 41 

 25.251 Vibration and buffeting 22 

 25.305 Strength and deformation 22 

 25.331 General 45 

 25.351 Yawing conditions 45 

 25.365 Pressurized Compartment Loads 53 

25.562 Emergency landing dynamic conditions 63** 

 25.571 Damage-tolerance and fatigue evaluation of structure 9 

 25.607 Fasteners 22 

 25.631 Bird strike damage 22 

 25.657 Hinges 22 

 25.675 Stops 37 

 25.683 Operation tests 22 

 25.772 Pilot compartment doors 46 

 25.773(b)(2)(ii) Pilot Compartment View 72 

 25.783 Doors 53 

 25.809(f)(1)(v) Emergency exit arrangement 45 

 25.812 Emergency lighting 31 

 25.858 Cargo Compartment Fire Detection Systems (NA)**

 25.1103 Induction system ducts and air duct systems 45 

 25.1401 Anticollision light system 26 

 25.1438 Pressurization and pneumatic systems (NA)** 
23 A20WE 

XII. 747-400F (cont’d):

 25.1529 Instructions for continued airworthiness (NA)**

**Not Applicable - The requirements of this section do not apply to this type design because the original 

certification basis, which did not include this section, has been determined to be adequate. 

Based on 14 CFR § 21.101(g) for changes to TC’s, applicable provisions of 14 CFR part 26 are included in the certification basis. For any 

future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. 

Compliance has been found for the following regulations at Amendment 26-0: 26.11 

Compliance has been found for the following regulations at Amendment 26-1: 26.43, 26.45, 26.47, and 26.49

Part 36 of the FAR as amended by Amendments 36-1 through 36-20. 

Special Federal Aviation Regulation (SFAR) 27, as amended by Amendments 27-1 through 27-7. (Same as FAR Part 34, October 14, 

1993) 

The following special conditions, exemptions, and equivalent safety findings, which are part of the Model 747-200F and 747-400 

certification basis, are also part of the certification basis for the Model 747-400F: 

The special conditions include those enclosed with FAA letter to The Boeing Company dated February 20, 1970, and the following:

 1. Special Condition 4A, revised to apply to airplanes with the landing gear load evener system deleted, 

was recorded as an enclosure to an FAA letter to The Boeing Company dated May 12, 1971. 

 2, 3, and 4 were removed in this Revision 27, dated August 1, 1996 

 5. Special Condition No. 25-77-NW-4 (modification of the auto pilot system to approve the airplane for 

use of the system under Category IIIb landing conditions) was transmitted to The Boeing Company by 

FAA letter dated July 8, 1977. 

 

 6. was removed in this Revision 27, dated August 1, 1996 

 

 7. Special Condition No. 25-ANM-24 applicable to flight deck displays and propulsion control system was 

provided to Boeing on December 22, 1988. 

8. Special Condition No. 25-ANM-25 which established lightning and radio frequency (RF) energy 

protection requirements was provided to Boeing on December 22, 1988. 

Exemptions from FAR Part 25: 

1. Exemption from 14 CFR 25.807(c)(1), 25.807(c)(5), 25.809(f)(1), 25.813(b), Allowance of non crew members on the upper 

deck of 747-200F, 747-200C, certain 747-100 airplanes when in the main deck cargo configuration, and 747-400F. (Exemption 

No. 1870E dated September 8, 1993) 

 2. Partial Exemption from 14 CFR 25.855(c), Latches used on decompression vent doors only (Exemption No. 5649, dated April 

27, 1993) 

 3. Exemption from 14 CFR 25.779(b)(1), 25.1301(d), and 25.1309(a) , 747-400F with Rolls Royce RB211-524G/H engines 

installed with Full Authority Fuel Control Software “Issue 17” software (Exemption 10069, dated May 25, 2010) 

The following optional requirements, which are part of the Model 747-400 certification basis, apply also to the 747-400F: 

 Ditching Provisions Section 25.801 

 Ice Protection Provisions Section 25.773 

The following equivalent safety findings (ESF), previously made for earlier models under the provisions of Section 21.21(b)(1), are also 

applicable to the Model 747-400F: 

 Width of Aisle Section 25.815 

 

 Use of 1-g Stall Speed 

 (nonstructural items) Several 

 

 Use of 1-g Stall Speed 

 (structural items) Several 
A20WE 24 

 

XII. 747-400F (cont’d):

 Position Light Distribution 

 and Intensities Section 25.1389(b)(3) 

 Emergency Locator Transmitter (ELT) Section 25.1415(d) 

 Emergency Exit Marking Section 25.811(f) 

New ESF for 747-400F: 

 Doors Section 25.783(e) 

 Part 25 of the FAR, effective February 1, 1965, as amended by Amendment 25-1 through 25-59 with the 

following exceptions: (See Note 15).

Certification Maintenance Requirements (CMR's): 

 The CMR's are listed in the FAA-approved Section 9 of Boeing Maintenance Planning Data Document 

D621U400 or the applicable engine Type Certificate Data Sheet. The more restrictive requirement from 

these two documents shall be in force. 

Production Basis: Production Certificate No. 700 has been issued to The Boeing Company 

Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification 

Basis) must be installed in the aircraft for certification. 

XIII. 747-400SF Major Design Change

A 747-400 SF (Special Freighter), or optionally known as a 747-400 BCF (Boeing Converted Freighter), is a 747-400 Series passenger 

airplane that has been modified in accordance with FAA-approved Boeing Service Bulletin 747-00-2004 to operate in a freighter 

configuration. These aircraft remain as 747-400 Series aircraft for documentation purposes on this TCDS and with regard to the 

applicability of airworthiness directives. Because of the magnitude of this design change, the certification basis for the changed aspects 

was required to be established and documented in accordance with section 21.101 (Changed Product Rule). 

All general information in TCDS A20WE for the 747-400 Series remains applicable to an airplane operating in the 747-400SF 

configuration, with the following exceptions: 

Maximum Passengers: There are no provisions for the carriage of passengers. A maximum of 20 supernumeraries can occupy the 

aft cabin of the upper deck as given in Exemption 8590. 

Minimum Crew: There is no requirement for a flight attendant, as given in Exemption 8590. 

FAA Approved Weight and Balance Control and Loading Manual: D043U544 

FAA Approved Airplane Flight Manual: D6U10001, D6U10002, and D6U10003 

Service Information: Boeing Report D634U104, "Structural Repair Manual," is FAA-approved. Service Bulletins and other 

Service Information, when FAA-approved, will carry a statement to that effect. 

Certification Maintenance Requirements (CMR's): 

 The CMR's are listed in the FAA-approved Section 9 of Boeing Maintenance Planning Data Document 

D621U400 or the applicable engine Type Certificate Data Sheet. The more restrictive requirement from 

these two documents shall be in force. 

The 747-400 SF certification basis was established according to the requirements given in § 21.101 and AC 21.101-1, and was determined 

in accordance with FAA Order 8110.48. The conversion to the 747-400 SF configuration entails the following product level changes: 

 1. Passenger to Freighter change (significant product level change, per AC 21.101-1) and, 

 2. Upper Deck Interior Rearrangement (not a significant change, per AC 21.101-1) 
25 A20WE 

XIII. 747-400SF Major Design Change (cont’d)

1. Significant Product Level Change - Passenger to Freighter Conversion: 

Certification basis: Part 36: unchanged from 747-400 Series 

 

 SFAR 27: unchanged from 747-400 Series 

 

Part 25 of the FAR, effective February 1, 1965, as amended by Amendments 25-1 through 25-112 with the following exceptions per 

section 21.101(b): 

SECTION NO. TITLE THRU AMDT.25-

25.305 (a)(b) Strength and Deformation 25-22 

 25.365 Pressurized Compartment 25-53, except as follows: Areas that comply with 

25-54: Lower Lobe – Nose area, STA 140 to 460, 

all below WL 200. Wing – Wheel Well Floor Beam 

area 

 Areas that comply with Amendment 25-72: Ceiling 

compartment above Main Deck Cargo 

Compartment. Main Deck Cargo Compartment. 

Lower Lobe – Forward, Aft, and Aft Bulk Cargo 

Compartments. 

 25.561 Emergency Landing Conditions 25-91 except the requirements of 25.561(c)(1)(ii) 

are not included in the certification basis. 

25.571 Damage Tolerance and Fatigue 25-22 

 Evaluation of Structure 

 25.831(a) Ventilation 25-41 

 25.841(a) Pressurized Cabins 25-38

Changed Areas: The following is a listing of the changes incorporated as part of the passenger to freighter conversion: 

▪ Increased maximum zero fuel weight 

▪ Strengthened wing-to-body joint, main deck floor, fuselage frames and fuselage stub beams 

▪ Replaced aft upper deck floor beams with tension ties 

▪ Added a main deck side cargo door, door surround structure, and related control wiring 

▪ Installed provisions (structural, electrical & drainage) to support installation of cargo handling 

systems 

▪ Modified upper deck floor beams to allow installation of a folding ladder 

▪ Installed new main deck sidewall & ceiling cargo liners 

▪ Deactivated horizontal stabilizer tail fuel tanks (if previously installed) 

▪ Reconfigured air conditioning, air distribution, equipment cooling, cabin pressurization, and 

lavatory/galley ventilation systems to freighter configurations 

▪ Changed decompression venting 

▪ Added main deck smoke detection and class E depressurization capability 

▪ Replaced smoke detectors with area detectors in the lower cargo compartments 

▪ Replaced cabin pressure controller for compatibility with cargo fire mode 

▪ Added additional Halon bottle and air conditioning for the lower cargo compartments 

▪ Added a main deck rigid cargo barrier forward of STA 140 and a 9-G cargo net aft of the aft bulkhead 

of the upper deck 

 All other changes resulting from the Passenger to Freighter Product Level Change are either Secondary or 

Not Affected in accordance with § 21.101 and AC 21.101-1. Amendment levels for sections of 14CFR Part 

25 that apply to Secondary Changes or Not Affected Areas remain at the 747-400 Series amendment levels. 

2. Product Level Change - Upper Deck Interior Reconfiguration: 
A20WE 26 

 

XIII. 747-400SF Major Design Change (cont’d)

Certification basis: The certification basis for the changed aspects associated with the upper deck interior configuration 

rearrangement is unchanged from the 747-400 Series in accordance with section 21.101(b)(1). 

 

 Based on 14 CFR § 21.101(g) for changes to TC’s, applicable provisions of 14 CFR part 26 are included in 

the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate 

compliance with the applicable sections. 

Compliance has been found for the following regulations at Amendment 26-0: 26.11 

 Compliance has been found for the following regulations at Amendment 26-1: 26.43, 26.45, 26.47, and 26.49

Special Conditions: Special conditions that are part of the certification basis for the 747-400 Series apply to the airplane 

operating in the 747-400 SF configuration, unless otherwise noted below: 

Special Condition 25-ANM-16 (use of an overhead crew rest area, occupancy not to exceed ten 

crewmembers) does not apply to aircraft operated in the 747-400SF configuration. 

 Special Conditions 25-61-NW-1 (occupancy not to exceed 32 passengers on the upper deck – spiral 

staircase) and 25-71-NW-3 (occupancy not to exceed 45 (or later, 110) passengers on the upper deck of 

airplanes with a straight segmented stairway): 

 

 The 747-400 SF conversion removes the stairway between the main and upper deck, which 

eliminates some aspects of Special Conditions 25-61-NW-1 and 25-71-NW-3 as described below. 

For Special Condition 25-61-NW-1, all aspects related to occupant egress and escape provisions 

noted in this special condition are also addressed in Special Condition 25-71-NW-3. Special 

Condition 25-71-NW-3 remains part of the certification basis for the 747-400 Series operating in 

the 747-400 SF configuration, with the following noted exceptions: 

 1. The requirements of Special Condition numbered 25-71-NW-3, 3(a)(1) through 3(a)(7) do 

not apply to airplanes in the 747-400 SF configuration. 

 

 2. The requirements of Special Condition numbered 25-71-NW-3, 4(a) and 4(b) do not apply to 

airplanes in the 747-400 SF configuration. 

Exemptions From 14 CFR Part 25: 

 

 All exemptions from 14 CFR Part 25 listed in TCDS A20WE for the 747-400 Series apply to the 747-400 SF configuration. 

 

 Partial Exemption from 14 CFR 25.785(j), 25.807(c), 25.857(e), 25.1447(c) – Allowance for up to 20 persons to occupy the 

upper deck cabin and in-flight access to Class E Cargo compartments with limitations listed in the exemption of the 747-400 SF 

without a flight attendant. (Exemption No. 8590, dated July, 25 2005, No. 8590A, dated May 1, 2008, and No. 8590B, dated 

December 1, 2008) 

Equivalent Safety Findings: All existing Equivalent Safety Findings listed in TCDS A20WE for the 747-400 Series apply to the 747-

400 operated in the 747-400 SF configuration. 

ELOS AT8167SE-T-ES-1, section 25.857(c)(1), was granted on 12/06/2005, Inadvertent Smoke 

Detection in the Forward and Aft Lower Lobe Class C Cargo Compartments from a Smoke Source in a 

Main Deck Class E Compartment. 

TCDS Notes: All Notes in TCDS A20WE that apply to the 747-400 Series also apply to an airplane operated in the 

747-400 SF configuration. 

 Note 14, as applicable to the 747-400F Series, is also applicable to the 747-400 Series operated in the 

747-400 SF configuration. 

Optional Requirements: All optional requirements in TCDS A20WE that apply to the 747-400 Series also apply to an airplane 

operated in the 747-400 SF configuration. 
27 A20WE 

XIV. 747-400 Large Cargo Freighter (LCF) Major Design Change

A 747-400 LCF is a 747-400 Series passenger airplane that has been modified in accordance with FAA-approved Boeing Service Bulletin 

747-00-2084 to operate in a freighter configuration. These aircraft remain 747-400 Series aircraft for documentation purposes on this 

TCDS and with regard to the applicability of airworthiness directives. Because of the magnitude of this design change, the certification 

basis for the changed aspects was required to be established and documented in accordance with section 21.101 (Changed Product Rule). 

All general information in TCDS A20WE for the 747-400 Series remains applicable to an airplane operating in the 747-400 LCF 

configuration, with the following exceptions: 

Maximum Passengers: There are no provisions for the carriage of passengers 

Minimum Crew: There is no requirement for a flight attendant to occupy the upper deck 

FAA Approved Weight and Balance Control and Loading Manual: D043U545-BHC1 

FAA Approved Airplane Flight Manual: D6U10001.4J61 

Maximum Operating Altitude: 43,100 feet 

Service Information: Boeing Report D634U105, "Structural Repair Manual," is FAA-approved. Service Bulletins and other 

Service Information, when FAA-approved, will carry a statement to that effect. 

Certification Maintenance Requirements (CMR's): 

 The CMR's are listed in the FAA-approved Section 9 of Boeing Maintenance Planning Data Document 

D621U400-9 or the applicable engine Type Certificate Data Sheet. The more restrictive requirement from 

these two documents shall be in force. 

Allowable Cargo: These airplanes are not approved for commercial freight hauling operations of material other than that 

approved per Exemptions 8769 and 8769A. Only cargo that supports Boeing corporate lines of business is 

allowed for carriage. The lower lobe cargo compartments are decommissioned and may not be used to carry 

cargo. All items intended for carriage must conform to the standards found in Document D926U013-44, 

“747-400 LCF Flammability Acceptance Criteria for Cargo Carriage,” or be accepted by the FAA once a 

safe method of transport has been established. A summary of all items allowed for carriage is identified in 

Document D451U742-01, “Allowable Cargo – 747-400 Large Cargo Freighter.” Document D451U742-01 is 

considered part of the Weight and Balance Manual/Airplane Flight Manual. In addition, a listing of the 

FAA-approved shipping mechanical equipment (SME) fixtures that are approved for installation on the 747-

400 LCF aircraft are contained in the Weight and Balance Control and Loading Manual (Document 

D043U545-BHC1). 

Model Eligible Serial Numbers

747-409 24309 (RT631) 

 24310 (RT632) 

747-4H6 27042 (RT743) 

747-4J6 25879 (RT876) 

The conversion to the 747-400 LCF configuration entails the following product level changes: 

 1. Passenger to Freighter change (significant product level change, per AC 21.101-1) and, 

 2. Reconfiguration of the interior commodities within the pressurized portion of the aircraft (not a significant 

change, per AC 21.101-1) 

1. Significant Product Level Change - Passenger to Freighter Conversion: 

Certification basis: Part 36: unchanged from 747-400 Series 

 SFAR 27: unchanged from 747-400 Series 

 
A20WE 28 

 

XIV. 747-400 LCF Major Design Change (cont’d)

Part 25 of the FAR, effective February 1, 1965, as amended by Amendments 25-1 through 25-112 and 

25.783 as amended by 25-114 (for the swing tail only) with the following exceptions per section 21.101(b): 

Section No. Title At Amdt 25-

 25.103 Performance- Stalling Speed 0 

 25.107(b)-(f) Takeoff Speeds 38 

 25.121 Climb (One Engine Inoperative) 84 

 25.125 Landing 84 

 25.143(f) Controllability and Maneuverability: General 42 (i.e. not part of certification basis) 

 25.201(d) Stall Demonstration 42 

 25.251(e) Vibraton and Buffeting 22 (i.e. not part of certification basis) 

 25.305 Strength & Deformation 22 

 25.335 Design Airspeeds 23 

 25.365 Pressurized Compartment Loads 53 

 25.427 Unsymmetrical Loads 23 

 25.473 Ground Load Conditions and Assumptions 23 

 25.479 Level Landing Conditions 23 

 25.481 Tail-down Landing Conditions 0 

 25.483 One-wheel Landing Conditions 0 

 25.485 Side Load Conditions 0 

 25.491 Takeoff Run 0 

 25.493 Braked Roll Conditions 23 

 25.499 Nose-wheel Yaw 46 

 25.519 Jacking and Tie-Down Provisions 0 (i.e. not part of certification basis) 

 25.571 Damage-tolerance and Fatigue Evaluation 0 (except as modified by Note 15) 

 Of Structure 

 25.629 Aeroelastic Stability Requirements 46 

 25.831 Ventilation 41 

 25.841 Pressurized Cabin 38 

 25.1587 Performance Information 105 

Voluntary compliance with later requirements has been demonstrated as follows: 

 Section No. Title At Amdt 25-

 25.733(e) Tires 78 

 25.773(b),(c) Pilot Compartment View (ECS System) 72 

 25.820 Lavatory Doors 114 

 25.1438 Pressurization and pneumatic systems 41 

 (new ducting) 

Changed Areas: The following is a high level description of changes incorporated as part of the passenger to LCF conversion: 

 Installed new crown structure to increase the fuselage cross section, 

 Installed a new pressure bulkhead immediately aft of the flight deck, 

 Installed a swing tail cargo door in conjunction with a 10 foot fuselage extension, 

 Installed a 5 foot vertical stabilizer extension, 

 Installed strengthened floor beams, 

 Installed an electronic flight bag (EFB) based system to interface with a cargo camera monitoring 

system, 

 Revised cargo ventilation system, 

 Winglets removed. 

The certification basis for areas not affected by the change and for secondary changes is the original certification basis for the Model 747-

400 shown on TCDS A20WE 

2. Product Level Change - Reconfiguration of the interior commodities within the pressurized portion of the aircraft: 

Certification basis: The certification basis for the changed aspects associated with the reconfiguration of the interior 

commodities within the pressurized portion of the aircraft is unchanged from the 747-400 Series. 
29 A20WE 

XIV. 747-400 LCF Major Design Change (cont’d)

Special Conditions: Special conditions that are part of the certification basis for the 747-400 Series apply to the airplane 

operating in the 747-400 LCF configuration, unless otherwise noted below: 

 Special Condition 25-ANM-16 (use of an overhead crew rest area, occupancy not to exceed ten 

crewmembers) does not apply to aircraft operated in the 747-400 LCF configuration. 

 Special Conditions 25-61-NW-1 (occupancy not to exceed 32 passengers on the upper deck – spiral 

staircase) and 25-71-NW-3 (occupancy not to exceed 45 (or later, 110) passengers on the upper deck of 

airplanes with a straight segmented stairway) do not apply to aircraft operated in the 747-400 LCF 

configuration 

Exemptions from 14 CFR Part 25: 

 

 All exemptions from 747-400 series aircraft apply to the 747-400 LCF configuration 

 Exemption from 14 CFR 25.885(b), 25.855(h)(2), 25.857(e)(2), 25.857(e)(3), 121.221(f)(1), 121.221(f)(2), 121.221(f)(3), 

121.223 - provide relief from the requirements to provide a complete cargo compartment liner, conduct flight tests to show 

compliance to smoke penetration requirements, provide a smoke detection system within the main deck cargo compartment, and 

provide a means to shut off the ventilating airflow to, or within, the main deck cargo compartment. (Exemption No. 8769, dated 

8/18/2006, No. 8769A, dated 1/29/2007) 

Equivalent Safety Findings: All existing Equivalent Safety Findings listed in TCDS A20WE for the 747-400 Series apply to the 747-400 

operated in the 747-400 LCF configuration, except those listed below: 

 Section 25.815, Width of Aisle, does not apply 

 Section 25.1203, Fire-Detection System, does not apply 

 Section 25.1103(d), Pressure Relief, does not apply 

 The following Equivalent Safety Findings are specific to the 747-400 LCF and documented in the following 

memorandums: 

 Section 25.1435(b)(1), Hydraulic system test pressure, granted 10/11/2006 (Documented in Transport 

Airplane Directorate ELOS memo AT8613SE-T-S-1) 

 Section 25.783(f), Visual Indication of Swing Tail Door Closed, Latched and Locked Condition, granted 

05/24/2007 (Documented in Transport Airplane Directorate ELOS memo PS05-0023-C-1) 

 Section 25.783(f), Visual Inspection Camera System, granted 05/24/2007 (Documented in Transport 

Airplane Directorate ELOS memo PS05-0023-C-2) 

 Section 25.729(e), Landing Gear Configuration Warning System, granted 05/29/2007 (Documented in 

Transport Airplane Directorate ELOS memo PS05-0023-S-2) 

TCDS Notes: All Notes in TCDS A20WE that apply to the 747-400 Series also apply to an airplane operated in the 747-

400 LCF configuration.

Optional Requirements: All optional requirements in TCDS A20WE that apply to the 747-400 Series also 

apply to an airplane operated in the 747-400 LCF configuration. 

Data pertinent for Fuel Tank Flammability Reduction System Installed on Model 747-400, -400D, and -400F SERIES 

A flammability reduction system (FRS) may be installed as an option in new airplane production, or as a modification in accordance with 

an FAA-approved Boeing service bulletin. Airworthiness limitations for the FRS are contained in section 9 of the applicable Maintenance 

Planning Data document for each airplane model incorporating the FRS. 

Certification Basis: Amendment 25-102, section 25.981 transmitted to The Boeing Company dated 

August 24, 2005. 

 Special Conditions No. 25.285-SC for the certification and operation requirements of the flammability 

reduction means (fuel tank inerting). 
A20WE 30 

 

DATA PERTINENT TO ALL MODEL 747-400 SERIES:

Engine Models PW4056 PW4062A CF6-80C2B1F RB211-524G, RB211-524H, 

 RB211-524G2, RB211-524H2 

 RB211-524G3 

Thrust Limits: 

Takeoff, Sea 56,750 lbs. 62,000 lbs. 57,160 lbs. 56,870 lbs. 59,450 lbs 

Level, Standard 

Day (5 minutes) 

Maximum 47,970 lbs. 47,970 lbs. 49,800 lbs. 47,230 lbs. 47,230 lbs. 

Continuous 

THE FOLLOWING INFORMATION AND NOTES APPLY TO ALL MODELS PRIOR TO MODEL 747-8F 

UNLESS OTHERWISE NOTED:

Exemptions to 14 CFR part 25: 

1. Exemption from 14 CFR 25.1301(a), 25.1303(b), and 21.601 (formerly 37.120(a)) - To permit the type certification of Boeing Model 

747 aircraft with: (1) location of the flap position indicator in the lower left-hand corner of the pilot's center instrument panel and (2) 

servo altimeters configured with dial markings at 50-foot increments. This exemption is subject to the following conditions: (1) It is 

valid only for foreign air carriers only. (2) Boeing must provide a list of all operators and aircraft operated under this exemption to be 

maintained in the public docekt for this exemption. Boeing must update the list whenever a change is made. (Exemption No. 3035, 

September 9, 1980, No. 3035A, September 7, 1983, No 3035B, August 6, 1986, No. 3035C, January 23, 1987, No. 3035D, June 2, 

1987, No. 3035E, September 4, 1987, No. 3035F, April 19, 1988.) 

2. Exemption from 14 CFR 25.471(b) - Allowance for lateral displacement of the C.G. from the airplane certerline (Exemption No. 1013A 

dated December 24, 1969) 

3. Partial Time-Limited Exemption from 14 CFR §25.853(a), appendix F, paragraph (a)(1)(i), Testing on Large Interior Panels, granted 

through November 28, 2011. (Exemption No. 9791, November 28, 2008, Exemption No. 9791B, March 1, 2010 , Exemption No. 9791C, 

February 4, 2011) 

NOTES APPLY TO ALL MODELS PRIOR TO MODEL 747-8F UNLESS OTHERWISE SPECIFIED

NOTE 1. A current Weight and Balance Manual including a list of equipment included in the certificated empty weight and 

loading instructions must be in each aircraft at the time of original airworthiness certification and at all times thereafter 

except in the case of an operator having an approved weight control system. 

NOTE 2. Airplane operation must be in accordance with the FAA Approved Airplane Flight Manual. All placards required by 

either the FAA Approved Airplane Flight Manual, the applicable operating rules or the certification basis must be 

installed in the airplane. 

NOTE 3. The following fuels are eligible for Pratt and Whitney engines: JP-1, JP-4, and JP-5 fuels conforming to the P&WA 

Specification No. 522E or later revision may be used separately or mixed in any proportion without adversely affecting 

the engine operation or power output. No fuel control adjustment is required when switching fuel types. 

 G.E. engines use fuels conforming to G.E. Spec. D50TF2. MIL-T-5624, Grades JP-4 or JP-5, and ASTM D1655, Jet 

A, Jet A1, and Jet 8 are consistent with G.E. Specifications. [JP-8 is also approved for use in CF6-80C2 Series 

engines.] CF6-80C2 series engines incorporating Dribble Flow Fuel Nozzles PN 9331M72P33, P34 and P41 are 

prohibited from the use of JP-4 and Jet B (wide cut) fuel. 

 The following fuels are eligible for Rolls Royce RB211-524 Series engines: 

 Grade (Type) Specification 

 Kerosene,(Type) D. Eng. R.D. 2453 

 (AVTUR:JP-1) D. Eng. R.E. 2494 

 A.S.T.M. D1655 Jet A 

 A.S.T.M. D1655 Jet A-1 

 3-GP-23 

 I.A.T.A. Kerosene Type 

 Wide Cut Fuels D. Eng. R.D. 2454 

 (AVTAG:JP-4) D. Eng. R.D. 2486 

 A.S.T.M. D1655 Jet B Type 

 3-GP-22 
31 A20WE 

NOTES APPLY TO ALL MODELS PRIOR TO MODEL 747-8F UNLESS OTHERWISE SPECIFIED

(cont’d):

 MIL-T-5624 JP-4 Grade 

 I.A.T.A. Wide Cut 

 RB211-524G/H-T series engines are prohibited from the use 

 Of JP-4 and Jet B (wide cut) fuel 

 High Flash Point D.Eng. R.D. 2498 

 (AVCAT:JP-5) 3-GP-24 

 MIL-T-5624 JP-5 Grade 13 

 

 Optional Additives (Applies to all engines)

 

 The only optional additives that may be used in approved fuel are as follows: 

 

 (1) Anti-static additive - Shell ASA3 in concentrations not exceeding 1.0 parts per million (grams per cubic meter). 

 (2) Anti-icing additive - Specification D. Eng. R.D. 2451 (Issue 2) or MIL/1/27686E in concentrations not exceeding 0.15 

percent by volume. 

 (3) Anti-Corrosion/lubricity additive - HITEC E515 may be used (formerly Santolene C) at a concentration range up to 5 

lb. per 35,000 Imperial gallons, which gives a phosphorus content in the order of 0.07 parts per million. 

 (4) Anti-microbiological additive - Biobor JF may be used on an intermittent or not-continuous basis at a 

 concentration level not exceeding 270 parts per million (20 ppm Boron). It is permitted to burn off the 

 treated fuel provided the concentration does not exceed 270 ppm, and the fuel is not contaminated by 

 microbial debris. 

 (5) Corrosion inhibitor additive: 

 (a) TOLAD 245 - in concentrations not exceeding 12 lb. per 35,000 Imperial gallons (approximately 35 mg/L). 

 (b) APOLLO PRI 19 - in concentrations not exceeding 8 lb. per 35,000 Imperial gallons (approximately 23 

mg/L). 

 (c) EMERY 9855 - in concentrations not exceeding 12 lb. per 35,000 Imperial gallons (approximately 35 mg/L). 

 Fuel load and usage limitations are contained in the FAA Approved Airplane Flight Manual applicable to each operator. 

 

 The following oils are eligible for the engines: 

 

 Pratt & Whitney: Synthetic type conforming to P&WA 521 as revised. 

 P&WA Turbojet Engine 

 Service Bulletin No. 238 lists approved brand oils. 

 

 General Electric: G.E. engines use synthetic type oil conforming to G.E. Spec. D50TF1, classes A and B. G.E. 

 Service Bulletin 79-1 lists approved oil brands. 

 

 

 Rolls Royce: RB211 engines use ESSO Turbo Oil 25 or Aero Shell Turbine Oil 555. Castrol 580 gas turbine 

 oil II and these oils reclaimed to Rolls Royce standards. 

NOTE 4. LIFE LIMITED PARTS AND INSPECTION REQUIREMENTS: 

 

 Nose Landing Gear: 

 The nose landing gear is life-limited to 50,430 landings. This service life may be corrected to flight hours based on 

service route segments average times and must be approved by the FAA. 

 Refueling Spoiler: 

 Inflight refueling spoiler P/N 65B20238 is limited to 20,000 inflight operations. 

 Escape System: 

 Escape system cool gas generator cartridges manufactured by Olin Corporation and stored either in their original 

(unopened) shipping canisters or in a cool gas generator between +10F and +90F for up to 6 years from date of 

manufacture are considered serviceable. Cartridges stored for more than 6 years must not be put into service. 

Inservice cartridge life is limited to 3 years. 

 Escape system cool gas generator cartridges manufactured by Talley Industries (Ref. Boeing Service Bulletin 

747-25-2448) have a storage limit of 7 years from the date of manufacture. Cartridges stored for more than 7 years 

must not be put in service. Inservice cartridge life is limited to 3 years. 

 
A20WE 32 

 

NOTES APPLY TO ALL MODELS PRIOR TO MODEL 747-8F UNLESS OTHERWISE SPECIFIED

 (cont’d):

 Escape system off-wing slide door and latch thruster (six each per airplane) must be replaced after 15 firings. In 

addition, the housing bore must be replaced if the bore is 0.002 inches more than the maximum drawing tolerance. 

Thruster cartridges must be replaced before 5 years calendar time after date of manufacture. 

 Number 3 and 4 Flap Track Fairings: 

The following parts on numbers 3 and 4 flap track fairings are life limited when operated with an RB211 engine in the 

spare engine position. 

 152-Hour Life Limit 

 Outboard Vertical Rod - Rod Ends - 69B14163 

 Drive Rod Attach Fittings to the Mid-Flap - 65B39035-1 

 Box Links - 65B15598, 65B15599, 65B15598-1-3 and 65B15599-1-3-5 

 Seal Support Channels - 65B15544 and 65B15666 

 Drive Rod Tubes - 65B15929, 65B15929-3 and 65B15929-8 

 Outboard Vertical Rod Tubes - 69B13761-2 

 Inboard Vertical Rod Tubes - 69B13762-2 

 300-Hour Life Limit 

 Inboard Vertical Rod - Rod Ends - 69B14163-1 

 Drive Truss Fittings - 65B17002-1 and 65B17003-1 

 600-Hour Life Limit 

 Lateral Rod Tubes - 69B13750-5 and 69B13750-6 

 1200-Hour Life Limit 

 Outboard Vertical Rod Brackets - 69B13755-2 and 69B13758-1 

 Lateral Rod Brackets - 69B13758-2 and 69B13759-2 

 747-400F Nacelle Strut Spring Beam Assemblies: 

 The following spring beam assemblies are life limited to 50,000 landings. 

 Engine Installation Engine Position Part Number

 GE CF6-80C2 Series 1 311U0050-46 and -48 

 4 311U0050-42 and -44 

 

 RR RB211-524G/H Series 1 321U0496-11 and -12 

 4 65B89727-27 and -28 

 PW 4000 Series 1 311U0050-46 and -48 

 4 311U0050-50 and -52 

 Engine Pylon - Required Inspections:

 

 All outboard engine pylons incorporating the strut beams with spherical bearings must be inspected for bearing seizure 

every 6,000 flight hours on all models except for the 747-400 airplane. The inspection interval shall not exceed 12,500 

hours for the 747-400 airplane. Inspection procedures specified in Boeing Maintenance Planning Document 

D6-13747, or D621U400 for the 747-400 airplane, or equivalent are acceptable. 

NOTE 5. The Pratt and Whitney JT9D-3 and JT9D-3A engines and the JT9D-3A, JT9D-7, JT9D-7A, JT9D-7F, JT9D-7Q, 

JT9D-7Q3, JT9D-7R4G2, and JT9D-7J engines may be intermixed in the combinations and with the appropriate 

limitations noted in the FAA Approved Airplane Flight Manual. 

 

 The Pratt and Whitney JT9D-7H engines may be intermixed with all JT9D-7 engines with appropriate limitations 

noted in the FAA Approved Airplane Flight Manual. 

 The Pratt and Whitney JT9D-7AH engines may be intermixed will all JT9D-7A engines with appropriate limitations 

noted in the FAA Approved Airplane Flight Manual. 

 

 The General Electric CF6-50C engines may be intermixed with CF6-50E engines with appropriate limitations noted in 

the FAA Approved Airplane Flight Manual. 

The Rolls Royce RB211-524B2-19, RB211-524C2-19, and RB211-524D4-19, and RB211-524D4-39 engines may be 

intermixed with the appropriate limitations noted in the FAA Approved Airplane Flight Manual. 
33 A20WE 

NOTES APPLY TO ALL MODELS PRIOR TO MODEL 747-8F UNLESS OTHERWISE SPECIFIED (cont’d):

 

 The Rolls Royce RB211-524D4X-19 and RB211-524D4X-B-19 engines may be intermixed with RB211-524D4-19 

and RB211-524D4-39 engines with the appropriate limitations noted in the FAA Approved Airplane Flight Manual. 

 The Rolls Royce RB211-524D4-B-19 and RB211-524D4-B-39 engines may be intermixed with RB211-524D4-19 and 

RB211-524D4-B-39 engines with the appropriate limitations noted in the FAA Approved Airplane Flight Manual. 

The Rolls-Royce RB211-524B2-B-19 engines may be intermixed with RB211-524B2-19 engines, and RB211-524C2-

B-19 engines may be intermixed with RB211-524C2-19 engines with the appropriate limitations noted in the FAA 

Approved Airplane Flight Manual. 

The Rolls-Royce RB211-524G2-19, RB211-524G3-19, and RB211-524H2-19 engines may be intermixed in the 

combinations and with the appropriate limitations noted in the FAA Approved Airplane Flight Manual. 

 

 The Rolls-Royce RB211-524G2-T-19, RB211-524G3-T-19, and RB211-524H2-T-19 engines may be 

 Intermixed in the combinations and with the appropriate limitations noted in the FAA-Approved 

 Airplane Flight Manual. 

 The Rolls-Royce RB211-524G2-T-19, RB211-524G3-T-19, and RB311-524H2-T-19 engines may be 

 Intermixed with RB524G2-19, RB211-534G3-19 and RB211-524H2-19 in the combinations and with the 

 Appropriate limitations noted in the FAA-Approved Airplane Flight Manual. 

NOTE 6 Blow-in door and fixed lip nacelles may be intermixed in the combinations and the appropriate limitations 

 noted in the FAA Approved Airplane Flight Manual and in the appropriate Appendix of the Airplane Flight 

 Manual. 

NOTE 7. The 747-100B series airplanes are basically 747SR series airplanes. 

NOTE 8. There are service bulletins which call for modifications which do not comply with the Type Certification Basis. These

service bulletins are listed in Boeing Document D6-30300 titled "Service Bulletin 747". The records of airplanes 

imported into the USA should be reviewed to be sure that further modifications are accomplished to ensure 

compliance, if the non FAA-approved service bulletins modifications have been installed. 

NOTE 9. On certain 747-300 and 747-400 airplanes, the Upper deck exits are rated as a Type "I" due only to the interior 

arrangement. Requirements for the rerating of the exit are located in FAA Letter ANM-120S:RSY, dated August 1, 

1989. The passenger capacity of these airplanes is the same as for the 747-200B (550 total passengers with up to 45 on 

the upper deck.) 

 Also on certain 747-400 airplanes, Door No. 3 is rated as a Type "I" due only to the interior arrangement. 

Requirements for the rerating of the exit are located in FAA Letter ANM-120S:JG dated December 21, 1988. The 

passenger capacity is limited to 485 total with up to 45 on the upper deck when the upper deck is also rated as Type 

"I". With the upper deck rated as a Type "A" the passenger capacity is 595 total (485 main deck plus 110 on the upper 

deck). 

NOTE 10. Airplanes line number 679, 685, 696, 700, 705, 708, 710, and on were manufactured after August 20, 1988, 

 and Airplane line numbers 804 and subsequent were manufactured after August 20, 1990, (Reference FAR 

 121.312(a)(1) Amendment 121-198). Airplane line numbers 805 through 814 are exempt (Exemption No. 

 5176A). See Boeing Document D6-30300 titled "Service Bulletin 747" for cross reference of line number 

 to serial number to block number. 

NOTE 11. Message Category Definitions

 1. Warning: Defined as an operational or aircraft system condition which may require immediate 

 corrective or compensatory action by the crew. 

 2. Cautions: An operational or aircraft system condition which requires immediate crew awareness and 

 prompt compensatory action. 

 

 3. Advisories: An operational or aircraft system condition which requires crew awareness for possible 

 future compensatory action. 

 4. Memo: Crew reminders of the current state of selected normal conditions. 

 5. Status: Indications of airplane's condition for dispatch. 

 6. FMC Alerts: Associated with advisories - FMC related operational conditions which require crew 

 awareness for possible future compensatory action. 
A20WE 34 

 

NOTES APPLY TO ALL MODELS PRIOR TO MODEL 747-8F UNLESS OTHERWISE SPECIFIED

(cont’d)

 7. CMC Messages: Detailed (maintenance level) messages related to airplane faults. 

NOTE 12. MESSAGE, OPERATION, ACTION AND RESPONSIBILITY:

Message Responsibility Phase of How Quickly is: How Quickly is: 

 Operation Awareness Req'd Action Req'd

WARNING PILOTS ALL IMMEDIATE IMMEDIATE 

CAUTIONS PILOTS ALL IMMEDIATE PROMPT 

ADVISORIES PILOTS ALL TIMELY TIMELY* 

STATUS GROUND CREW DISPATCH DISPATCH BEFORE DISPATCH, 

 AND PILOTS DEPENDS ON MMEL 

FMC ALERTS PILOTS ALL WHEN TIMELY TIMELY 

 USING FMCs (if required) 

FMC PILOTS ALL WHEN TIMELY TIMELY 

ADVISORIES USING FMCs (if required) 

CMC GROUND CREW DISPATCH WHEN REQ'D BY CMR OR 

 & MAINTENANCE PREPARATION & CMR OR SCHEDULE A 

 CHECKS MAINTENANCE MAINTENANCE 

*Depends on other failures, phase of flight or context of operation of airplane. 

NOTE 13. The Boeing 747 Supplemental Structural Inspection Document D6-35022 (See AD 84-21-02, Amendment 39-4936) is 

applicable. 

NOTE 14. The class E cargo compartment on the 747-400F is required to be fitted with a full fire resistant liner which meets the 

 requirement of Part 25 Appendix F, Part III at Amendment 25-60. This requirement is documented in Issue Paper 

 SE-1, Stage 4, dated October 14, 1993, titled Protection of Critical Systems and Equipment within Class E Cargo 

 Compartments. 

NOTE 15. Boeing production line numbers 1047 and on have incorporated the 747 strut modification program in the production 

 sequence. The certification basis for the strut-to-wing attachment structure complies with the following FAR’s at the 

upgraded amendment levels listed below: 

 FAR(s) Subject Amendment Level 

 25.301, 25.303, 25.307 General Structure 78 

 25.305 Strength and Deformation 54 

 25.321 through 25.563 Load Conditions 78 

 25.571 Damage Tolerance 45 

 25.581 through 25.625 Design and Construction 78 

 25.629 Aerodynamic Stability 78 

 Boeing Production Line Numbers 1 through 1046 have incorporated the 747 strut modification program by 

 means of Airworthiness Directive (AD) compliance. The certification basis of this modification is as listed 

 above. The AD’s are as follows: 95-13-07 (CF6-45/-50 & JT9D-70; AD 95-13-06 (PW4000 & CF6-80C2); 

 AD 95-13-05 (RB211); and AD 95-10-16 (JT9D-3, -7). 

NOTE 16. The Rolls-Royce Model RB211-524B-19 is removed as an eligible engine because it is removed from the 

 Engine Type Certificate Data Sheet E12EU. 

NOTE 17: For Model 747-100, -200B, -200F, -200C, SR, SP, -100B, -300, and -100B SUD series airplanes: Mandatory 

replacement times, inspection intervals, related inspection procedures and all critical design configuration control 

limitation for the fuel tank system determined during the Special Federal Aviation Regulation No. 88 program and for 

compliance with 14 CFR 25.981 are listed in the FAA-approved Airworthiness Limitations document, Boeing 747-

100/200/300/SP Airworthiness Limitations and Certification Maintenance Requirements, Document D6-13747-CMR, 

Revision March 2006 or later FAA-approved revision. The FAA has issued an airworthiness directive 2008-10-06 

mandating compliance with Revision March 2006, or a later FAA-approved revision, applicable to all Model 747-100, 

-200B, -200F, -200C, SR, SP, -100B, -300, and -100B SUD series airplanes. 
35 A20WE 

NOTES APPLY TO ALL MODELS PRIOR TO MODEL 747-8F UNLESS OTHERWISE SPECIFIED

(cont’d)

NOTE 18: For Model 747-400, -400D, and -400F series airplanes: Mandatory replacement times, inspection intervals, related 

inspection procedures and all critical design configuration control limitation for the fuel tank system determined during 

the Special Federal Aviation Regulation No. 88 program and for compliance with 14 CFR 25.981 and Special 

Conditions No. 25.285-SC are listed in the FAA-approved Airworthiness Limitations and Certification Maintenance 

Requirement, Section 9, of Boeing 747-400 Maintenance Planning Data Document D621U400-9, Revision August 

2005 or later FAA-approved revision. All Model 747-400, -400D, and -400F series airplanes, production line number 

1377 and on, must comply with Revision March 2006, or a later FAA-approved revision. The FAA is planning to 

issue an airworthiness directive mandating compliance with Revision March 2006, or a later FAA-approved revision, 

applicable to all Model 747-400, -400D, and -400F series airplanes with production numbers lower than 1377 

XV. Model 747-8F (Approved August 19, 2011) Transport Category 

The 747-8F series is based on the model 747-400F series aircraft with design changes to the empennage, fuselage, landing gear, wings, 

engines, fuel systems, and other aircraft systems as defined in the certification basis within this section. The certification basis for areas 

unaffected by this change from the 747-400F series aircraft will remain certified at the 14 CFR Part 25 Amendment level of their original 

certification date. 

Engines: 4 General Electric Turbofan Engines Model: GEnx-2B67, GEnx-2B67B (Engine Type Certificate No. E00078NE) 

Fuel: General Electric Turbofan Engines 

 Fuels conforming to: 

 ASTM D-1655 grades Jet-A and Jet A-1 

 MIL-T-5624 grade JP-5 

 MIL-T-83133 grade JP-8 

 are acceptable 

 Fuels produced to other specifications and having properties meeting the requirements of the above specifications are acceptable. 

The fuel and any fuel additives must conform to the relevant Engine Operating Instructions. 

Engine Limits: General Electric Turbofan Engines 

See the FAA approved Airplane Flight Manual for engine ratings. 

Airspeed Limits: VMO/MMO = 365/0.9 (KCAS) See the appropriate FAA Approved Airplane Flight Manual for other 

airspeed limits 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual 

Empty Weight C.G.: See the appropriate FAA Approved Airplane Flight Manual 

Datum: See Weights and Balance Manual 

Leveling Means: See FAA Approve Airplane Flight Manual 

Maximum Weights: See the appropriate FAA approved Airplane Flight Manual 

Minimum Crew: Two (2) persons: pilot and copilot 

Number of Seats: Maximum of eight (8) persons including the flight crew per exemption 9793C and limitations outlined in the 

FAA approved Airplane Flight Manual 

Maximum Compartment: See the appropriate Weight and Balance Control Manual 

Weights 

Fuel Capacity: See the appropriate Weight and Balance Control Manual 

Oil Capacity: See the appropriate Weight and Balance Control Manual 

Maximum Operating: 42,100 

Altitude 
A20WE 36 

 

XV. Model 747-8F (cont’d)

Control Surface: To insure proper operation of the airplane, the movement of the various control surfaces must be carefully 

Movements controlled by proper rigging of the flight control systems. The airplane must, therefore, be rigged according 

to the following FAA-approved data: 

 Boeing Drawing Numbers: 

 251U1001 Rigging Instructions Lateral Controls 

251U1003 Rigging Instructions Speed Brakes 

 251U2001 Rigging Instructions Elevator Controls 

251U3002 Rigging Instructions Rudder Controls 

 251U4001 Rigging Instructions Stablizer Trim Controls 

 114U0001 Rigging Instructions Leading Edge Slats Controls 

 253U5001 Rigging Instructions Control Stand 

 256U5001 Rigging Instructions Trailing Edge Flap Controls 

Model Eligible Serial Numbers

747-867F 39238, 39239, 39242-39244, 

747-87UF 37561, 37568, 37569 

747-8R7F 35806, 35807, 35809 

747-8HTF 37132 

747-8NVF 37581 

Certification Basis: 

 A. The certification basis of the 747-8F is 14 CFR part 25, as amended by Amendment 25-1 through Amendment 25-120 with 

exceptions permitted by 14 CFR 21.101. Table A documents the changed/affected areas of the aircraft. Table B documents all 

regulations for which there are exceptions from Amendment 25-120 for the changed/affected areas. Table C documents 

unchanged/unaffected areas for which compliance has been shown at an Amendment level higher than the 747-400F Amendment 

level. 

 

Section A 

The following section contains a listing of all areas that are changed/affected as part of the 747-8F minor model.

Airplane Area Changed/Affected Areas 

Static Loads; Dynamic Flight Loads; Dynamic Ground Loads; Flutter 

Flotation and ditching 

Weight and balance; Onboard weight and balance system 

Airplane Level 

Aerodynamic Stability & Control; Aerodynamic Performace; Aerodynamic Configurations 

Airframe – 

Empennage 

All empennage (includes the outboard elevator balance weight towers) except: 

 Inboard elevator; Remainder of outboard elevator 

Airframe – 

Fuselage 

All fuselage (includes all fuselage, floors, doors, and windows) except: 

 nose cargo door cutout including latches and hinges 

 upper deck structure from S-0 to S-13, BS 220 to BS 300 

 crown skin/stringer from S-0 to S-6, BS 300-520 

 upper deck side of body shear trusses 

 flight deck floor beams from BS 220-300 

 structural support for flight deck windshields 

 all upper deck seat tracks, floor panels, decompression trusses, and side of body shear panels from BS 520-

700 

 BS 2360 aft pressure dome and APU tail cone 

 Nose radome and nose landing gear doors 

 Nose cargo door, main entry door, crew door (and integrated window) 

 flight deck overhead exit door, and forward and center electrical equipment access doors. 
37 A20WE 

XV. Model 747-8F (cont’d)

Section A (continued) 

The following section contains a listing of all areas that are changed/affected as part of the 747-8F minor model.

Airplane Area Changed/Affected Areas 

Pitot static line plumbing 

Integrated Display System (IDS) 

Modularized Avionics and Warning Electronics Assembly (MAWEA) 

Flight Management Computer (FMC) 

Communication Management Unit (CMU) 

Enhanced Ground Proximity Warning System (EGPWS) 

Central Maintenance Computer System (CMCS) 

Airplane Condition and Monitoring System (Data Management Unit (DMU) and Quick Access Recorder (QAR)) 

Low Range Radio Altimeter (LRRA) 

Multi-Mode Receiver (MMR) 

Distance Measuring Equipment (DME) 

Automatic Direction Finder (ADF) 

VHF Omnidirectional Range/Marker Beacon (VOR/MB) 

Air Data Inertial Reference System (ADIRS) software 

SATCOM 

Cockpit Voice Recorder (CVR) 

Flight Deck (FD) Printer 

Flight Data Recorder Systems (FDRS) 

Onboard Network System (ONS) 

Terminal Wireless Lan Unit (TWLU) 

Emergency Locator Transmitter (ELT) 

HF/VHF Radio Communication Panel 

Main Deck Alerting System (MDAS) 

Traffic Alert and Collision Avoidance System (TCAS) and Air Traffic Control (ATC) Systems 

Avionics 

Flight Deck Audio System (Audio Management Unit (AMU) and Audio Control Panels (ACP)) 

Provisions including structural, electrical & drain for Cargo Handling System for Main Deck and Lower Lobe 

Compartments 

Cargo 

Cargo Furnishings, Linings and Placards 

Duct Leak Detection System (DLDS) 

Integrated Wingtip Light Assembly (IWLA) 

Integrated Drive Generator (IDG) 

Main and APU battery 

Weight and Balance Computer of the On-Board Weight and Balance System 

Dimmer control unit (DCU) 

Electrical Power Generation System 

Cargo Powered Outlets 

Window Heat Control Unit (WHCU) and flight deck window sensors 

Electrical 

Sub-systems 

Service and maintenance lights in the wheel wells, AC pack bay, Tailcone/APU compartment and forward EE bay 

Fuselage, Wing, Strut, Wheel Well, E/E Cooling, Cargo Handling, FQIS, and Engine Wiring 

Wing Fuel Tank Stringer clip 

Electrical 

Wiring and 

Installation 

Integration panels 
A20WE 38 

 

XV. Model 747-8F (cont’d)

Section A (continued) 

The following section contains a listing of all areas that are changed/affected as part of the 747-8F minor model.

Airplane Area Changed/Affected Areas 

Main Deck and Lower Lobe Cargo Fire Protection System 

Forward Cargo Air Conditioning (FCAC) System flow rate and ducting 

Aft Cargo Air Conditioning (ACAC) System flow rate and ducting 

APU air supply ducting 

Air conditioning and trim ducting. 

E6/E9 equipment cooling supply line 

Forward cargo heat ducting 

Aft/bulk cargo heat ducting 

Recirculation fans 

Lower recirculation filters 

Lav/Galley Vent System (LGVS) ducting 

Cabin Pressure Control System (CPCS) 

Alternate Ventilation System (AVS) 

Engine Anti-Ice Valves 

Air Supply Control System (ASCS) 

Wing Anti-Ice (WAI) System 

Hydraulic Air Drive Unit (ADU) air ducting in outboard engine struts 

Cabin Air Conditioning Temperature Control System (CACTCS) 

Environmental 

Systems 

Forward and aft electrical equipment (EE) cooling systems 

Fly-by-Wire (FBW) spoiler and outboard aileron control system 

Inboard and outboard aileron droop 

Flight control mechanical component installations and flight control cables 

Upper and lower rudder actuator 

Autoflight software 

Integrated Standby Flight Display (ISFD) 

Rudder ratio changer 

Elevator feel computer 

Yaw damper control laws 

Yaw damper stabilizer trim modules (YSM) 

Pitch Augmentation Control System (PACS) 

Yaw Damper Modal Suppression System (MSS) 

Outboard Aileron Modal Suppression (OAMS) 

Roller brake assembly 

Lateral Augmented Pitch Function (LAPS) 

Landing Attitude Modifier (LAM) 

Elevator Feel Shift (EFS) 

Rudder Input Linkages 

Flight Controls Stabilizer Trim Indication 

Flight Controls 

High Lift Systems 

Flight Crew 

Oxygen 

System 

Fourth 115 cu. ft. crew oxygen cylinder provisions 
39 A20WE 

XV. Model 747-8F (cont’d)

Section A (continued) 

The following section contains a listing of all areas that are changed/affected as part of the 747-8F minor model.

 Airplane Area Changed/Affected Areas 

Forward instrument panel (FIP) structure 

Flight deck display interface 

Glareshield 

Pilot Compartment Viewing 

Flight Deck 

Ram Air Turbine (RAT) manual deploy switch 

Emergency equipment stowage, equipment and placarding 

Flight manual stowage retention straps 

Flight deck stowage door latches 

Portable oxygen bottle stowage provisions 

PC power outlets for Captain and First Officer 

Hand microphones at all 4 crew positions 

Provisions to support EFB installation 

Crew oxygen mask stowage boxes 

Crew oxygen masks 

Pencil holders 

Overhead light 

Carpet periphery 

Flight Deck 

Crew 

Accommodations 

Boom microphone jack panels at all 4 crew positions 

Thermal acoustic blankets. 

Fuselage mounted emergency light for inertia reel use at crew door. 

Interiors 

Customer specific exterior markings including door bands at the crew door. 

Nose Landing Gear 

Body Landing Gear 

Landing Gear 

Structures 

Wing Landing Gear 

Landing gear alternate extend cables and brake cables 

Wheels, brakes, and tires. 

Brake system control unit 

Body and wing gear retract actuators 

Body and wing gear door actuators 

Ram Air Turbine (RAT) and associated equipment and engine driven pumps (EDPs), EDP hoses and EDP check 

valves 

Hydraulic system (except RAT and associated equipment and EDPs, EDP hoses, and EDP check valves) 

Tire Pressure Indication System and Brake Monitor System 

Ground Fault Interrupt 

Mechanical and 

Hydraulic 

Systems 

Landing Gear Selection System 

GEnx-2B67 engines 

Engine Driven Hydraulic Pumps (EDP) 

Hydraulic tubing, hoses, and component installations on the engine 

Hydraulic tubing, hoses, and component installations in the aft engine strut 

Propulsion 

APU fire extinguishing system extinguisher bottle, safety relief/filler port assembly, discharge head assembly, and 

discharge outlet/distribution plumbing 
A20WE 40 

 

XV. Model 747-8F (cont’d)

Section A (continued) 

The following section contains a listing of all areas that are changed/affected as part of the 747-8F minor model.

 Airplane Area Changed/Affected Areas 

APU, APU Controls and APU Installation 

Engine Controls 

Thrust Reverser Systems 

Propulsion – 

 Electrical 

 Sub-systems 

APU power feeder 

Jettison System 

Auxiliary Power Unit (APU) Feed System line, pumps and plumbing 

Reserve Tank Transfer System 

Fuel System Scavenge 

Fuel tank structure 

Fuel Feed System 

Fuel Vent System 

Fuel Management System 

Refuel/Defuel System 

Fuel Quantity Indicating System (FQIS) and fuel level sensing 

Fuel sump system drain valves 

Propulsion -Fuels 

Nitrogen Generation System (NGS) 

Propulsion – 

Structures 

Strut, nacelle, thrust reverser, inlet, exhaust, and systems 

Emergency Evacuation Harnesses 

Ceilings 

Closet 

Seats 

PSUs and general lighting 

Sidewall linings 

Partition between closet and RH sidewall 

Placarding 

Floor coverings 

Crew bunk mattresses 

Crew bunk area smoke penetration seals 

Ladder Enclosure to Upper Deck Supernumerary Area Smoke Penetration Seals 

Lavatory 

Galley 

Portable oxygen cylinders and full face masks for main deck cargo access 

Placarding in supernumerary area for main deck cargo access 

Emergency equipment stowage, equipment and placarding 

Supernumerary 

Area 

Lighted Signs and Overhead emergency exit signs 

Oxygen boxes 

Portable oxygen bottles 

Supernumerary 

Oxygen System 

Composite Cylinders 
41 A20WE 

XV. Model 747-8F (cont’d)

Section A (continued) 

The following section contains a listing of all areas that are changed/affected as part of the 747-8F minor model.

Airplane Area Changed/Affected Areas 

Potable water pressurization system 

Potable water tank attachment flanges 

Potable water distribution lines 

Vacuum lavatory system 

Waste/Water 

Gray waste water drain system and service panel 

Wing Wing pylon structure 

All wing structure 

Section B 

The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.305 Strength and 

deformation. 

25-0 for 25.305(b) for Airframe - Empennage 

(Outboard Elevator Balance Weight Tower) 

25-0 for 25.305(b) for Systems Stress related to: 

Landing Gear (Landing gear alternate extend cables 

and brake cables, Body gear truck positioner 

mounting features), Hydraulics (Hydraulic reservoirs, 

hydraulic line, Rudder PCA tubing, LG retract 

actuators, aileron and spoiler PCUs, Hydraulic 

Systems 1 and 4 electric pump , PACS actuator and 

elevator feel shift module hydraulic tubing, Aft strut 

hydraulic installations), Flight Controls Rudder 

Control (Cables, mech components installations, 

upper/lower actuator installation, rudder input 

linkage), Flight Controls Elevator Control (Cables, 

mech components installations, Elevator Feel 

computer. Horizontal stabilizer trim actuator - trim 

arm switch and control wire) and Flight Controls 

High Lift (Flap Detents vs Dspeed, LE/TE 

components, flap drive stroke, flap skew detection). 

25.365 Pressurized 

compartment 

loads. 

25-0 for 25.365(e), (f), and (g) for Systems Stress 

related to: Flight Deck (Linings, stowages, and 

latches, oxygen mask stowage box) and Interiors - 

Supernumerary Area (Galley and Lavatory) 

25-54 for 25.365(e)(2) for Fuselage (Section 41 main 

deck floor side of body shear trusses and side of body 

shear webs; Section 41 lower lobe skin panels and 

flight deck skin panels - pressurized area only, below 

WL 200, between STA 140 and 460; Pressurized skin 

panels) and Empennage (Forward fin box of vertical 

stab - unpressurized area) 

25.395 Control 

system. 

25-23 for 25.395(a), (b), and (c) for Systems Stress 

related to: Flight Controls Rudder Control (Cables, 

mech components installations, upper/lower actuator 

installation, rudder input linkage), Flight Controls 

Elevator Control (Cables, mech components 

installations, Elevator Feel computer. Horizontal 

stabilizer trim actuator - trim arm switch and control 

wire) and Flight Controls High Lift (Flap Detents vs 

Dspeed, LE/TE components, flap drive stroke, flap 

skew detection). 
A20WE 42 

 

XV. Model 747-8F (cont’d)

Section B (continued) 

The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.397 Control 

system 

loads. 

25-38 for 25.397 for Systems Stress related to: Flight 

Controls Rudder Control (Cables, mech components 

installations, upper/lower actuator installation, rudder 

input linkage), Flight Controls Elevator Control 

(Cables, mech components installations, Elevator 

Feel computer. Horizontal stabilizer trim actuator - 

trim arm switch and control wire) and Flight Controls 

High Lift (Flap Detents vs Dspeed, LE/TE 

components, flap drive stroke, flap skew detection). 

25.415 Ground gust 

conditions. 

25-0 for 25.415 for Systems Stress related to: Flight 

Controls Rudder Control (Cables, mech components 

installations, upper/lower actuator installation, rudder 

input linkage), Flight Controls Elevator Control 

(Cables, mech components installations, Elevator 

Feel computer. Horizontal stabilizer trim actuator - 

trim arm switch and control wire) and Flight Controls 

High Lift (Flap Detents vs Dspeed, LE/TE 

components, flap drive stroke, flap skew detection). 

25.561 General. N/A for 25.561(c)(1)(ii) for Airframe – 

Fuselage/Floor Structures (Section 46 floor beams 

and frames) 

25.562 Emergency 

landing 

dynamic 

conditions. 

N/A for 25.562 for Flight Deck - Flight Deck Seats 

and Interiors – Supernumerary Area 

25.571 Damagetolerance 

and fatigue 

evaluation of 

structure. 

25-0 for 25.571(a) and (c) for Systems Stress related 

to: Flight Controls Rudder Control (Cables, mech 

components installations, upper/lower actuator 

installation, rudder input linkage), Flight Controls 

Elevator Control (Cables, mech components 

installations, Elevator Feel computer. Horizontal 

stabilizer trim actuator - trim arm switch and control 

wire) and Flight Controls High Lift (Flap Detents vs 

Dspeed, LE/TE components, flap drive stroke, flap 

skew detection). 

25-86 for 25.571(a) and (b) for Systems Stress related 

to Flight Controls – Lower Rudder Tab Push Rod 

25-86 for 25.571(a) and (b) for Fuselage (Section 41 

upper deck floor beams BS 320-520; main deck floor 

side of body shear trusses and side of body shear 

webs; Section 42 skins BS 520-740 except window 

belt skin panels; stringers S-0 to S-5 L/R, S-11 to S17, S-28 to S-33; frames at upper deck floor joint 

(except new plug frames); crown splice fittings at BS 

520 & BS740; upper deck emergency door surround 

structure; lower lobe cargo door surround structure; 

upper deck floor stabilization system, lavatory and 

galley supports, and floor beam to frame connections; 

main deck floor side of body shear trusses and side of 

body shear webs; bulk cargo door; Main Deck Side 

Cargo Door; forward and aft lower lobe cargo doors), 

Wing, and Empennage (Stabilizer forward torque box 

and leading edge; fin forward torque box; Outboard 

Elevator Balance Weight Tower) 

N/A for 25.571 for Landing Gear (Main Gear) 

Compliance to be shown to CFR25.573(a) and 

(c) Amdt 25-0 in lieu of CFR25.571 Amdt 120 

for Landing Gear (Main Gear).
43 A20WE 

XV. Model 747-8F (cont’d)

Section (continued) 

The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.573 Fatigue 

evaluation of 

landing gear. 

 25-0 for 25.573(a) and (c) for Landing Gear (Main 

Gear) 

25.607 Fasteners. 25-0 for 25.607 for Airframe – Empennage 

(Outboard Elevator Balance Weight Tower) 

25-0 for 25.607 for Flight Controls Elevator and 

Lateral Control (Control Wheels, Left and Right 

Forward Cable Quadrants, Forward Load Limiter 

Device, Right and Left Cable Systems, Aileron Feel 

and Centering Unit, Aileron Trim System, Lateral 

Central Control Actuator, Third Autopilot Servo, 

Aileron Programmer, Wing Cable System to Inboard 

Aileron PCU, No-back Brake assembly, Elevator 

Feel Computer and Autospeedbrake system to drive 

speedbrake lever) and High Lift Systems 

25-0 for 25.607 for Hydraulics (except RAT and 

hydraulics associated with engine installations) 

25-0 for 25.607 for Systems Stress related to: 

Landing Gear (Landing gear alternate extend cables 

and brake cables, Body gear truck positioner 

mounting features), Hydraulics (Hydraulic reservoirs, 

hydraulic line, Rudder PCA tubing, LG retract 

actuators, aileron and spoiler PCUs, Hydraulic 

Systems 1 and 4 electric pump , PACS actuator and 

elevator feel shift module hydraulic tubing, Aft strut 

hydraulic installations), Flight Controls Rudder 

Control (Cables, mech components installations, 

upper/lower actuator installation, rudder input 

linkage), Flight Controls Elevator Control (Cables, 

mech components installations, Elevator Feel 

computer. Horizontal stabilizer trim actuator - trim 

arm switch and control wire) and Flight Controls 

High Lift (Flap Detents vs Dspeed, LE/TE 

components, flap drive stroke, flap skew detection). 

25.613 Material 

strength 

properties 

and design 

values. 

25-46 for 25.613 for Airframe – Empennage 

(Outboard Elevator Balance Weight Tower) 

25.615 Design 

properties. 

25-23 for 25.615 for Airframe – Empennage 

(Outboard Elevator Balance Weight Tower) 
A20WE 44 

 

XV. Model 747-8F (cont’d)

Section B (continued) 

The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.625 Fitting 

factors. 

25.23 for 25.625(a), (b) and (c) for System Stress 

related to: Hydraulics (Hydraulic reservoirs, 

hydraulic line, Rudder PCA tubing, LG retract 

actuators, aileron and spoiler PCUs, Hydraulic 

Systems 1 and 4 electric pump , PACS actuator and 

elevator feel shift module hydraulic tubing, Aft strut 

hydraulic installations), Landing Gear (Landing gear 

alternate extend cables and brake cables, Body gear 

truck positioner mounting features), Flight Controls 

Rudder Control (Cables, mech components 

installations, upper/lower actuator installation, rudder 

input linkage), Flight Controls Elevator Control 

(Cables, mech components installations, Elevator 

Feel computer. Horizontal stabilizer trim actuator - 

trim arm switch and control wire) and Flight Controls 

High Lift (Flap Detents vs Dspeed, LE/TE 

components, flap drive stroke, flap skew detection). 

25.675 Stops. 25-0 for 25.675(a), (b), and (c) for Flight Controls - 

Elevator and Lateral Control (Control Wheels, Left 

and Right Forward Cable Quadrants, Forward Load 

Limiter Device, Right and Left Cable Systems, 

Aileron Feel and Centering Unit, Aileron Trim 

System, Lateral Central Control Actuator, Third 

Autopilot Servo, Aileron Programmer, Wing Cable 

System to Inboard Aileron PCU, No-back Brake 

assembly, Elevator Feel Computer and 

Autospeedbrake system to drive speedbrake lever), 

Rudder (Rudder cables, Rudder PCMs, Rudder 

PCAs, Press-to-Center function, Remote 

compensators, Rudder Anti-cav/relief valves; 

Primary control linkage aft of aft quadrant, secondary 

linkage (buss linkage), rudder input linkage) and 

Stabilizer (Trim arm and control wires) 

25-0 for 25.675(a) and (b) for Flight Controls High 

Lift System 

25-0 for 25.675(c) for System Stress related to: Flight 

Controls Rudder Control (Cables, mech components 

installations, upper/lower actuator installation), Flight 

Controls Elevator Control (Cables, mech components 

installations, Elevator Feel computer. Horizontal 

stabilizer trim actuator - trim arm switch and control 

wire) and Flight Controls High Lift (Flap Detents vs 

Dspeed, LE/TE components, flap drive stroke, flap 

skew detection). 
45 A20WE 

XV. Model 747-8F (cont’d)

Section B (continued) 

The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.677 Trim systems. 25-23 for 25.677(a), (b), (c), and (d) for Flight 

Controls Elevator and Lateral Control System 

(Control Wheels, Left and Right Forward Cable 

Quadrants, Forward Load Limiter Device, Right and 

Left Cable Systems, Aileron Feel and Centering 

Unit, Aileron Trim System, Lateral Central Control 

Actuator, Third Autopilot Servo, Aileron 

Programmer, Wing Cable System to Inboard 

Aileron PCU, No-back Brake assembly, Elevator 

Feel Computer and Autospeedbrake system to drive 

speedbrake lever) 

25-23 for 25.677(a), (b), and (c) for Flight Controls 

Rudder (Rudder cables, Rudder PCMs, Rudder 

PCAs, Press-to-Center function, Remote 

compensators, Rudder Anti-cav/relief valves) and 

Stabilizer (Trim arm and control wires) 

25-23 for 25.677(b) for Flight Controls Stabilizer 

trim indicator and greenband on flight deck 

25.683 Operation tests. 25-0 for 25.683 for Systems Stress related to: Flight 

Controls Rudder Control (Cables, mech components 

installations, upper/lower actuator installation, 

rudder input linkage), Flight Controls Elevator 

Control (Cables, mech components installations, 

Elevator Feel computer. Horizontal stabilizer trim 

actuator - trim arm switch and control wire) and 

Flight Controls High Lift (Flap Detents vs Dspeed, 

LE/TE components, flap drive stroke, flap skew 

detection). 

25.685 Control system 

details. 

25-0 for 25.685(a), (b), and (c) for Flight Controls 

Elevator and Lateral Control System (Control 

Wheels, Left and Right Forward Cable Quadrants, 

Forward Load Limiter Device, Right and Left Cable 

Systems, Aileron Feel and Centering Unit, Aileron 

Trim System, Lateral Central Control Actuator, 

Third Autopilot Servo, Aileron Programmer, Wing 

Cable System to Inboard Aileron PCU, No-back 

Brake assembly, Elevator Feel Computer and 

Autospeedbrake system to drive speedbrake lever) 

25.693 Joints. 25-0 for 25.693 for Systems Stress related to: Flight 

Controls Rudder Control (Cables, mech components 

installations, upper/lower actuator installation, 

rudder input linkage), Flight Controls Elevator 

Control (Cables, mech components installations, 

Elevator Feel computer. Horizontal stabilizer trim 

actuator - trim arm switch and control wire) and 

Flight Controls High Lift (Flap Detents vs Dspeed, 

LE/TE components, flap drive stroke, flap skew 

detection). 

25.701 Flap 

interconnection

. 

 25-23 for 25.701(a) for Flight Controls High Lift 

System 

25.783 Doors. 25-88 for 25.783 for Main Deck Side Cargo Door; 

Forward and Aft Lower Lobe Cargo Doors 

25-23 for 25.783 for Airframe – Fuselage (Bulk 

Cargo Door; ECS pack bay access panels) 
A20WE 46 

 

XV. Model 747-8F (cont’d)

Section B (continued) 

The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.785 Seats, berths, 

safety belts, 

and harnesses. 

25-64 for 25.785(a), (b), (c), (d), (e) and (i) for 

Interiors – Supernumerary Area 

25-64 for 25.785(a) for Flight Deck - Flight Deck 

Seats 

25.795 Security 

considerations

. 

25-127 for 25.795(b)(2) for Environmental Systems 

– Air Distribution System 

25.807 Emergency 

exits. 

25-67 for 25.807(b) and (c) for Interiors – 

Supernumerary Area 

25-67 for 25.807(a) for Escape Systems (escape 

slide at crew door) 

25.809 Emergency 

exit 

arrangement. 

25-114 for 25.809(a) for Escape Systems (Flight 

Deck Overhead Exit Door; Crew Service Door) 

25-47 for 25.809(f)(1)(ii), f(1)(iv) and (f)(2) for 

Escape Systems (Crew Door Escape Slide) 

25-34 for 25.809(f)(1)(v) for Escape Systems (Crew 

Door Escape Slide) 

25.811 Emergency 

exit marking. 

25-46 for 25.811(a), (b), (d), (e) and (g) for Interiors 

– Supernumerary Area and Supernumary Area 

Emergency Lighting 

25.812 Emergency 

lighting. 

25-28 for 25.812 for Interiors – Supernumerary Area 

and Supernumary Area Emergency Lighting 

25.813 Emergency 

exit access. 

25-46 for 25.813(a), (b), (c) and (d) for Interiors – 

Supernumerary Area 

25.863 Flammable 

fluid fire 

protection. 

25-0 for 25.863(a) and (b) for Flight Controls 

Elevator and Lateral Control System (Control 

Wheels, Left and Right Forward Cable Quadrants, 

Forward Load Limiter Device, Right and Left Cable 

Systems, Aileron Feel and Centering Unit, Aileron 

Trim System, Lateral Central Control Actuator, 

Third Autopilot Servo, Aileron Programmer, Wing 

Cable System to Inboard Aileron PCU, No-back 

Brake assembly, Elevator Feel Computer and 

Autospeedbrake system to drive speedbrake lever) 

25.869 Fire 

protection: 

Systems 

N/A for 25.869(a)(1) for Hydraulics Electrical 

(Hydraulics system fire shutoff valve and flight 

control shutoff valve; Hydraulic fluid quantity probe 

in each reservoir) 

25.1359(d) at Amdt 25-32 for 25.869(a)(4) for 

Hydraulics Electrical (Hydraulics system fire shutoff 

valve and flight control shutoff valve; Hydraulic 

fluid quantity probe in each reservoir; Ground Fault 

Interrupt) and Flight Controls High Lift 

Compliance to be shown to CFR25.1359(d) 

Amdt 25-32 in lieu of CFR25.869(a)(4) Amdt 

120 for Hydraulics Electrical. 

25.899 Electrical 

bonding and 

protection 

against static 

electricity. 

25-123 

25.903 Engines. 25-57 for 25.903(a) and (c) for Propulsion - APU 
47 A20WE 

XV. Model 747-8F (cont’d)

Section B (continued) 

The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25-11 for 25.981(a)(3) and (b) for Propulsion – Fuels 

(APU fuel feed system line, pumps and plumbing, 

and fuel system scavenge) 

25.981 Fuel tank 

ignition 

prevention. 

25-125 for 25.981(c) Nitrogen Generation System 

(NGS) 

25.1013 Oil tanks. 25-57 for 25.1013(a) and (c) for Propulsion - APU 

25.1093 Induction 

system deicing 

and anti-icing 

provisions. 

25-57 for 25.1093(b) for Propulsion - APU 

25.1103 Induction 

system ducts. 

25-23 for 25.1103(b)(2) for Propulsion - APU 

25.1141 Powerplant 

controls: 

General. 

25-40 for 25.1141(f)(2) for Propulsion - APU 

25.1181 Designated 

fire zones: 

Regions 

included. 

25-23 for 25.1181(b) for Propulsion - APU 

25.1183 Lines and 

fittings. 

25-57 for 25.1183 for Propulsion - APU 

25.1305 Powerplant 

instruments. 

25-54 for 25.1305(a)(7) for Propulsion - APU 

25.1309 Equipment 

systems and 

installations. 

25-0 for 25.1309(a), (b), (c), and (d) for Flight 

Controls Elevator and Lateral Control System 

(Control Wheels, Left and Right Forward Cable 

Quadrants, Forward Load Limiter Device, Right and 

Left Cable Systems, Aileron Feel and Centering 

Unit, Aileron Trim System, Lateral Central Control 

Actuator, Third Autopilot Servo, Aileron 

Programmer, Wing Cable System to Inboard Aileron 

PCU, No-back Brake assembly, Elevator Feel 

Computer and Autospeedbrake system to drive 

speedbrake lever) 

25.1317 High-intensity 

radiated fields 

(HIRF) 

protection. 

 25-122 

25.1323 Airspeed 

indicating 

system. 

25-108 for 25.1323(a), (b), and (c) for Flight 

Controls – Integrated Standby Flight Display 

25-108 for 25.1323(b), (c), (d), (e), and (f) for 

Avionics – ADIRS 

25-108 for 25.1323(b) and (c) for Aerodynamic 

Configurations 
A20WE 48 

 

XV. Model 747-8F (cont’d)

Seciton B (continued) 

The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.1325 Static air vent 

and pressure 

altimeter 

systems. 

25-108 for 25.1325(d) and (e) for Flight Controls – 

Integrated Standby Flight Display 

25-108 for 25.1325(a), (b), (c), (d), and (e) for 

Avionics – ADIRS 

25-108 for 25.1325(b) and (e) for Aerodynamic 

Configurations 

25.1329 Flight 

guidance 

system. 

25-46 for Avionics – Flight Management Computer 

System 

25-46 for Flight Controls - Autopilot Flight Director 

System 

25-46 for 25.1329(f) for Flight Controls Elevator 

and Lateral Control System (Control Wheels, Left 

and Right Forward Cable Quadrants, Forward Load 

Limiter Device, Right and Left Cable Systems, 

Aileron Feel and Centering Unit, Aileron Trim 

System, Lateral Central Control Actuator, Third 

Autopilot Servo, Aileron Programmer, Wing Cable 

System to Inboard Aileron PCU, No-back Brake 

assembly, Elevator Feel Computer and 

Autospeedbrake system to drive speedbrake lever) 

25.1335 Flight director 

systems. 

 25-41 for Flight Controls - Autopilot Flight Director 

 System 

25.1353 Electrical 

equipment and 

installations. 

25-42 for 25.1353(a) for Hydraulics (Hydraulics 

system fire shutoff valve and flight control shutoff 

valve) 

25-42 for 25.1353(a) for Electircal Subsystems - 

APU 

25-42 for 25.1353(a) and (b) for Flight Controls 

High Lift System 

25.1413 Safety belts. 25-51 for Interiors – Supernumary Area 

25.1431 Electronic 

equipment. 

N/A for 25.1431(d) for Hydraulics )Hydraulic fluid 

quantity probe in each reservoir) 

N/A for 25.1431(d) for Electrical Subsystems - APU 

25.1435 Hydraulic 

systems. 

25-0 for 25.1435(a) and (b) for Flight Controls 

Elevator and Lateral Control (Control Wheels, Left 

and Right Forward Cable Quadrants, Forward Load 

Limiter Device, Right and Left Cable Systems, 

Aileron Feel and Centering Unit, Aileron Trim 

System, Lateral Central Control Actuator, Third 

Autopilot Servo, Aileron Programmer, Wing Cable 

System to Inboard Aileron PCU, No-back Brake 

assembly, Elevator Feel Computer and 

Autospeedbrake system to drive speedbrake lever), 

Rudder (Rudder cables, Rudder PCMs, Rudder 

PCAs, Press-to-Center function, Remote 

compensators, Rudder Anti-cav/relief valves; 

Primary control linkage aft of aft quadrant, 

secondary linkage (buss linkage)) and Stabilizer 

(Trim arm and control wires) 

25-41 for 25.1435(a)(1), (a)(5), (a)(6), (a)(7), and 

(b)(2) for Flight Controls High Lift System 

25-41 for 25.1435(a)(1), (a)(2), (a)(4), (a)(5), (a)(6), 

(a)(7), (a)(8), (b)(1), (b)(2), and (c) for Hydraulics 

(except RAT and hydraulics associated with engine 

installations) 
49 A20WE 

XV. Model 747-8F (cont’d)

Section B (continued) 

The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.1439 Protective 

breathing 

equipment. 

25-38 for Interiors – Supernumerary Area 

25.1447 Equipment 

stands for 

oxygen 

dispensing 

units. 

25-41 for 25.1447(a), (c)(1), (c)(3)(i) and (c)(3)(ii) 

for Interiors – Supernumerary Area 

25.1457 Cockpit voice 

recorders. 

25-124 for 25.1457(a)(6), (d)(1), (d)(4), (d)(5)(i), 

(d)(5)(ii), (d)(5)(iii), (6)(e)(1) for Avionics - Cockpit 

Voice Recorder 

25.1459 Flight 

recorders. 

25-124 for 25.1459(a)(3), (a)(7) and (a)(8) for 

Avionics – Flight Data Recorder System 

25.1522 APU 

Limitations. 

 25-46 for 25.1522 for Propulsion - APU 

25.1551 Oil quantity 

indicator. 

25-0 for 25.1551 for Propulsion - APU 

Section C 

The following section contains a listing of all regulations for which unchanged/unaffected areas of the aircraft comply with 14 CFR §25 

at an Amendment level greater than the 747-400F Amendment level.

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.303 Factor of 

safety. 

 25-120 for 25.303 for Airframe – Fuselage - #2 and 

#3 flight deck windshield 

25.305 Strength and 

deformation. 

 25-120 for 25.305(a), (b) and (c) for Airframe - 

Fuselage 

25.307 Proof of 

structure. 

 25-120 for 25.307(a) and (d) for Airframe – Fuselage 

- #2 and #3 flight deck windshield 

25.365 Pressurized 

cabin loads. 

 25-54 for 25.365(e) for Airframe – Fuselage - Flight 

deck floor beams/frames (not 

 affected from decompression standpoint) 

 25-120 for 25.365(a), (b), and (d) for Airframe – 

Fuselage - #2 and #3 flight deck 

 windshield 

25.571 Damagetolerance and 

fatigue 

evaluation of 

structure. 

 25-86 for 25.571(a) and (b) for Airframe – 

Empennage and Fuselage 

 25-120 for 25.571(d) and (e) for Airframe – 

Empennage and Fuselage 

 25-120 for 25.571(b)(5)(ii) for Airframe – Fuselage - 

#2 and #3 flight deck windshield 

25.601 Design & 

Construction - 

General. 

 25-120 for 25.601 for Airframe – Fuselage - #2 and 

#3 flight deck windshield 

25.603 Materials. 25-120 for 25.603 for Airframe – Fuselage - #2 and 

#3 flight deck windshield 

25.605 Fabrication 

methods. 

 25-120 for 25.605 for Airframe – Fuselage - #2 and 

#3 flight deck windshield 

25.609 Protection of 

structure. 

 25-120 for 25.609 for Airframe – Fuselage - #2 and 

#3 flight deck windshield 

25.611 Inspection 

provisions. 

 25-120 for 25.611 for Airframe – Fuselage - #2 and 

#3 flight deck windshield 

25.775 Windshields 

and windows. 

 25-120 for 25.775 for Airframe – Fuselage - #2 and 

#3 flight deck windshield 

25.807 Emergency 

Exits. 

 25-120 for 25.2807(g)(1) for Interiors – Escape 

Systems Exits 
A20WE 50 

 

XV. Model 747-8F (cont’d)

Additional Certification Basis Information: 

Based on 14 CFR §21.101(g) for changes made to TCs applicable provisions of 14 CFR part 26 are included in the certification basis. For 

any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections 

14 CFR §26 of the FAR as amended by Amendments 26-1 through 26-3, and any later amendments in existence at the time of certification. 

 

14 CFR §34 of the FAR as amended by Amendments 34-1 through 34-4, and any later amendments in existence at the time of certification 

14 CFR §36 of the FAR as amended by Amendments 36-1 through 36-28, and any later amendments in existence at the time of 

certification 

Exemptions from 14 CFR §25: 

Applicable 

Part 25 

Section 

Amndt 

Level 

Subject Exemption 

Number 

Date 

Issued 

Expiration 

Date 

(if applicable) 

25.841(a) (2) 

and (a)(3) 

87 Pressurized Cabins – Uncontained Engine Failure 9943 

9943A 

10/29/2009 

7/12/2011 

None 

25.901(c) 40 Installation-No Single Engine Failure Criteria 8518 03/23/2005 None 

25.981(a) (3) 102 Fuel Tank Ignition Prevention-Fuel Tank Structural 

Fastener Penetrations 

10174 12/14/2010 None 

25.783(g) 

25.785(d) 

25.807(a)(1) 

25.807(g)(1) 

25.807(i)(1) 

25.810(a)(1)(i) 

25.810(a)(1)(iii) 

25.812(g)(1)(ii) 

25.813(a) 

25.813(b) 

25.857(e) 

25.1447(c)(1) 

23 

64 

67 

114 

114 

114 

114 

28 

46 

46 

93 

41 

Partial Exemption from, Carriage of supernumeraries 

on an airplane with a class E cargo compartment 

(with access to the class E compartment) and escape 

systems 

9793 

9793A 

9793B 

9793C 

11/26/2008 

10/02/2009 

10/22/2010 

6/16/2011 

None 

25.1305(c) 

25.1309(c) 

 Fuel System Contamination 10267 

10267A 

05/19/2011 

08/05/2011 

12/31/2016 

The following regulations have been complied with by findings of an Equivalent Level of Safety: 

Applicable 

Part 25 

Section

Amndt 

Level

Subject ELOS 

Number

25.107(e)(1)(iv) Minimum Unstick Speed (VMU) TC6918SE-T-F-6 

25.689(a)(1) Control Cable Diameter PS05-0212-SF-2 

25.777(e) 46 Wing Flap Control Lever PS05-0212-SF-1 

25.783(e) 88 Visual Indication of Forward and Aft Lower Lobe 

Cargo Door Locked Condition 

PS05-0212-C-1 

25.783(e) 88 Visual Indication of Main Deck Side Cargo Door 

Closed, Latched, and Locked Condition. 

PS05-0212-C-2 

25.811 Door Sill Reflectance and Exterior Exit Markings TC6918SE-T-CS-2 

25.831(g) Acceptable High Temperature Physiological 

Environment During Failure Conditions 

25.857(c)(1) Cargo Compartment Classification Inadvertent Smoke 

Detection in Lower Lobe Class C Cargo 

Compartments 

AT8167-T-ES-1 

25.863 

25.1182(a) 

25.1183(a) 

 Engine Nacelle Power Door Opening System (PDOS) 

Fire Testing 

PS05-0211-P-6 
51 A20WE 

XV. Model 747-8F (cont’d)

Equivalent Level of Safety findings (continued): 

Applicable 

Part 25 

Section

Amndt 

Level

Subject ELOS 

Number

25.863 

25.1182(a) 

25.1183(a) 

 Nacelle Areas Behind Firewalls for Thrust Reverser 

Directional Control Valve (DCV) 

PS05-0212-P-18 

25.933 Flight Critical Thrust Reverser TC6918SE-T-P-2 

25.934 Engine and Thrust Reverser System Testing TC6918SE-T-P-17 

25.981(a)(3) Means of Compliance for the Installation of GFI 

Relays on Boeing Model 707, 727, 737CL, 737NG, 

747 CL, 747-400, 757, 767, & 777 Airplanes and 

Equivalent Safety Finding for Ground Fault 

Interrupter Circuit Protection for Fuel Override and 

Jettison Pumps 

PS05-0123-P-1 Rev 1 

25.981(b) 125 Fuel Tank Flammability Reduction Rule PS05-0177-P-2 

25.997(d) 

25.1305(c)(6) 

 Warning Means for Engine Fuel Filter Contamination PS05-0212-P-4 

25.1145(a) and 

(b) 

 Ignition Switches PS05-0212-P-5 

25.1181(a)(6) 

25.1182(a) 

 Fire Safety Requirements for the GEnx-2B Engine 

Fan Case 

PS05-0211-P-23 

25.1182 

25.1183 

 Fire Safety Requirements for the Aft Strut Fairing 

Compartment 

PS05-0212-P-21 

25.1193 Cowling and Nacelle Skin Fireproof Regions PS05-0212-P-16 

25.1301(a), and 

(d) 

25.1309(a), and 

(c) 

 Transition Speed of Enhanced Ground Proximity 

Warning System (EGPWS) Mode 4 Alerts; Too Low 

Flaps/Too Low Terrain 

PS05-0212-S-3 

25.1303(c)(1) Overspeed Aural Warning TC6918SE-T-SA-11 

25.1435(b)(1) 104 Request for an Equivalent Level of Safety Finding for 

the Hydraulic System Pressure Test 

PS05-0212-SF-4 

25.1517 Rough Air Speed (VRA) TC6918SE-T-F-4 

25.1529 

Appendix H 

 Maintenance Planning Document Section 9 

(Instructions for Continued Airworthiness) 

PS05-0212-P-G-8 

25.1325(e) Standby Air Data System PS05-0212-F-3 

25.161(a), and 

(c)(3), 

25.1301(a), 

25.1309(a) 

 Longitudinal Trim PS05-0212-F-4 

Special Conditions with respect to the following subjects apply to the 747-8F: 

Special 

Condition 

Number 

Effective 

Date 

Subject 

25-385-SC 11/09/2009 Structural Design Requirements for Four-Post Main Landing Gear 

System 

25-387-SC 09/11/2009 Additional Airframe Structural Design Requirements Related to 

Sudden Engine Stoppage Due to Fan Blade Failures 

25-388A-SC 06/27/2011 Interaction of Systems and Structures 

25-401-SC 02/16/2010 Systems and Data Networks Security--Protection of Airplane 

Systems and Data Networks From Unauthorized External Access 

25-402-SC 02/16/2010 Design Roll Maneuver Requirement 
A20WE 52 

 

XV. Model 747-8F (cont’d)

Additional Design Requirements and Conditions: 

 The following design details or information must be maintained to ensure that an unsafe design condition is not present: 

14 CFR 25.1329 – Flight Guidance System 

The following design features must be incorporated in the type design (reference § 25.1329, Amendment 25-46). In lieu of the following, 

compliance to 25.1329, Amendment 25-119, may be shown. 

1. Quick autopilot disconnect switches for each pilot on the outboard arm of each control wheel and quick autothrust disconnect 

switches for each pilot on the underside of the thrust control levers for engines 1 and 4. 

 2. Positive disconnect function for the autopilot is provided by the disconnect bar located at the glare shield on the autopilot mode 

control panel (MCP). 

 3. Positive disconnect function for the autothrottle is provided by the autothrottle arm switch, also located on the MCP. 

 4. Automatic synchronization of the autopilot and autothrust functions is provided in order to ensure transient free engagement and 

mode switching. 

 5. Automatic stabilizer trim is used to offload the elevator in order to ensure transient free disengagement of the autopilot pitch axis. 

 6. The wheel position provides a visual and tactile indication of any wheel input which may be required at disengagement of the 

autopilot roll axis. 

 7. When multiple autopilot channels are engaged, disengagement of an individual autopilot does not result in a transient any greater 

than a minor transient. 

 8. The throttle levers remain in the current position when the autothrust function is disengaged. 

 9. Failures of the automatic stabilizer trim function, and other detected failures which degrade autopilot operation but do not pose an 

immediate hazard to the airplane, result in activation of the master caution light and aural, as well as the display of an AUTOPILOT 

caution message. 

 10. Detected failures which do pose an immediate hazard to the airplane, result in an autopilot disconnect with associated autopilot 

disconnect warning level annunciation that includes activation of the master warning light and aural as well as the display of an 

AUTOPILOT warning message. 

 11. Transition from multiple autopilot operation to single autopilot operation (with associated yaw axis autopilot servo disconnect), 

during engine inoperative go-around, does not require exceptional piloting skill, alertness, or strength. 

 12. The AFDS provides low speed protection via the following features: 

 a. The AFDS controls to an angle-of-attack which corresponds to one degree below the stick shaker angle-of-attack. 

 b. The AFDS take-off mode provides windshear recovery guidance which meets the criteria of AC 25-12 and AC 120-41. 

 c. An indication to the flight crew of a low speed condition includes the display of the stick shaker angle-of-attack via a 

pitch limit indicator (PLI). 

 d. The thrust management function (TMF), when engaged in SPD mode, provides low speed protection when the AFDS 

vertical speed (V/S) mode is engaged and commanding a climb. In addition, if the angle-of-attack rises above a fixed 

reference point, the AFDS issues a V/S mode failure by removing the pitch flight director bars if the flight director is turned

on. 

 e. If the autopilot is engaged, a V/S mode failure will result in an amber line being drawn through the V/S mode 

annunciation on the primary flight display (PFD), illumination of the master caution light, activation of the master caution 

aural, and display of an AUTOPILOT caution message. 

 f. An indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message when the airspeed 

drops below the top of the lower amber band of the airspeed indicator. 

 g. The AFDS provides low speed protection by controlling to a reference angle-of-attack when in Flight Level Change 

(FLCH) mode. An additional indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message 

when the airspeed drops below the top of the lower amber band. 

 h. When the AFDS altitude capture (ALT CAP) mode is engaged, the TMF, if engaged in SPD mode, provides low speed 

protection. In addition, under certain conditions the AFDS will provide altitude capture speed floor protection by 

controlling to a speed no lower than 5 knots below the MCP selected speed. 
53 A20WE 

XV. Model 747-8F (cont’d)

 i. If the AFDS altitude capture mode is engaged, and the angle-of-attack rises above a fixed reference point the AFDS will 

issue an ALT CAP mode failure by removing the pitch flight director bars if the flight director is turned on. If the 

autopilot is engaged, the ALT CAP mode failure will result in a mode annunciation on the Primary Flight Display (PFD), 

illumination of the master caution light, activation of the master caution aural, and display of an AUTOPILOT caution 

message. An additional indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message 

when the airspeed drops below the top of the lower amber band. 

 j. When the AFDS Altitude Hold (ALT HLD) mode is engaged, the TMF, if engaged in SPD mode, provides low speed 

protection. An additional indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message 

when the airspeed drops below the top of the lower amber band. 

 k. When the AFDS Vertical Navigation (VNAV) mode is engaged, the TMF, if engaged in SPD mode, provides low speed 

protection. Otherwise, when engaged in VNAV SPD, the FMF provides low speed protection. An additional indication 

to the flight crew of a low speed condition is an AIRSPEED LOW caution message when the airspeed drops below the 

top of the lower amber band. 

 l. When the AFDS glideslope (G/S) mode is engaged, the TMF, if engaged in SPD mode, provides low speed protection. 

An additional indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message when the 

airspeed drops below the top of the lower amber band. 

 m. When the AFDS go-around mode is engaged, the AFDS provides low speed protection by controlling to an angle-ofattack which corresponds to one degree below the stick shaker angle-of-attack. The AFDS go-around mode provides 

windshear recovery guidance and meets the criteria of AC 25-12 and AC 120-41. An additional indication to the flight 

crew of a low speed condition includes the display of the stick shaker angle-of-attack (via a pitch limit indicator (PLI)). 

 n. Autothrottle wake-up requires that the autothrottle arm switch, located on the MCP, be in the ARM position. When the 

AFDS in not in takeoff, go-around, FLCH, or VNAV SPD modes, the autothrottle will automatically engage into SPD 

mode and provide speed protection when the airspeed drops approximately 5 to 10 knots below the top of the lower 

amber band. 

 13. The AFDS provides high speed protection via the following features: 

 o. Indication to the flight crew of a high speed condition is an OVERSPEED warning message when the airspeed/Mach 

number exceeds VMO/MMO 

 p. When the AFDS takeoff mode is engaged, the AFDS provides high speed protection by controlling to the flap placard 

(flaps down) or VMO/MMO (flaps up). 

 q. When the AFDS V/S mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

 r. When the AFDS FLCH mode in engaged, the AFDS provides high speed protection by controlling to the flap placard 

(flaps down) or VMO/MMO (flaps up). 

 s. When the AFDS ALT CAP mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

 t. When the AFDS ALT HLD mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

 u. When the AFDS VNAV mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

Otherwise, when engaged in VNAV SPD, the FMF provides high speed protection. 

 v. When the AFDS G/S mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

 w. When the AFDS go-Around mode is engaged, the AFDS provides high speed protection by controlling to the flap 

placard (flaps down) or VMO/MMO (flaps up). 

 14. For the flight guidance system functions, controls, indications, and alerts, means are provided to indicate the current mode of 

operation as well as any armed modes. Mode transitions are indicated on the Primary Flight Display (PFD) and highlighted with 

boxes that are displayed around the changed mode for ten seconds following the mode change. The indications are visible to each 

pilot under all expected lighting conditions during the flight deck lighting evaluation. 

 15. Autopilot disengagement is annunciated via illumination of the master warning light, activation of the master warning aural, and 

via the display of an AUTOPILOT warning message. A dedicated autopilot warning provides for an aural warning which is 

unique from all of the other aural warnings. 

 16. Override of the Autothrust by the flight crew using the throttles does not require excessive force, and does not create a potential 

hazard to the airplane. 
A20WE 54 

 

XV. Model 747-8F (cont’d)

14 CFR 25.365(e)(2) – Section 41 Lower Lobe (BS 140-460) 

The following design features must be incorporated in the type design (reference § 25.365, Amendment 25-54). In lieu of incorporating 

the following design features, compliance to § 25.365, Amendment 25-120, may be shown. 

Section 41 Lower Lobe (BS 140-460): 

When evaluating this compartment for compliance to § 25.365, the compartment must be analyzed using the following two conditions: 

 

 (1) A 3.7 square foot opening (forward EE Bay access door) with the BS 464 cargo liner intact (3.7 sf), and 

 (2) A 20.0 square foot opening with the BS 464 cargo liner blown down. This essentially combines the Section 41 Lower Lobe and

the forward cargo compartment into one compartment in the analysis. 

 

14 CFR 25.561(c)(1)(ii) – Auxiliary Power Unit Fuel Line in Section 46 

The following design features must be incorporated in the type design. In lieu of incorporating the following design features, compliance 

to § 25.561(c)(1)(ii), Amendment 25-120, may be shown. 

 (1) The Section 46 floor beams must be designed to protect the auxiliary power unit (APU) fuel lines from an emergency landing load 

event of a minimum of 5.2 g's down and 1.5 g’s up. 

 (2) The APU fuel line must be routed through the main deck floor beams just outboard of BL 0 to minimize potential for all types of 

penetration (including rotor burst, wheels up landing impact, etc). 

 (3) Occupants must be located no less than 72 feet forward of the forward-most potential penetration location in the APU fuel hose. 

 

Damage Tolerance and Fatigue Evaluation of Structure 

14 CFR 25.571(a) and (b) – Wing, Empennage, Fuselage, Floors and Doors 

The following design features must be incorporated in the type design (reference § 25.571(a) and (b), Amendment 25-86). In lieu of 

incorporating the following design features, compliance to § 25.571(a) and (b), Amendment 25-120, may be shown. 

(1) For the 747-8F structure, an evaluation of the existing damage tolerance analysis (DTA) inspection program identified in the 

Supplemental Structural Inspection Document (SSID) must be performed for any required changes due to loads, geometry changes, 

material changes, etc. The resulting inspection requirements for the 747-8F must be included in Section 9 (Airworthiness 

Limitations) of the Boeing Maintenance Planning Document (MPD) D621U400 in accordance with § 25.571(a)(3) at Amendment 

25-120. 

 (2) The above evaluation must include loading magnitudes and loading spectra which are developed in accordance with § 25.571 at 

Amendment 25-120. This includes usage of the 1.15 factor for pressure acting alone in accordance with § 25.571(b)(5) at 

Amendment 25-120. 

 (3) Maintenance instructions must be based on in-service data and fatigue testing to ensure freedom from widespread fatigue damage. 

14 CFR 25.809(a) – Outside Viewing means for Flight Deck Overhead Exit 

The following design features must be incorporated in the type design (reference § 25.809(a), Amendment 25-47). In lieu of incorporating 

the following design features, compliance to § 25.809(a), Amendment 25-120, may be shown. 

 (1) Large windows installed adjacent to the overhead flight deck exit door that provide a means for outside viewing to determine if 

there is a hazard (such as a fire) that would pose an immediate threat to the occupants of the airplane if the emergency exit were to be 

opened. 

 (2) 8 inertia reels (with harnesses) installed for egress out flight deck overhead exit door. 
55 A20WE 

XV. Model 747-8F (cont’d)

The following design details must be maintained to ensure that an unsafe design feature is not present: 

 

 Following fire/smoke detection, the crew will follow the AFM procedure to depressurize the cabin and ascend or descend the airplane 

to an altitude of 25,000 feet until final descent to a suitable airport is possible. 

 Class E cargo compartment liners will be tested to meet requirements of 14 CFR part 25, appendix F part III (Amdt. 25.83). Except at 

the following locations: 

 1. The linings above the cargo compartment ceiling in the stairwell to the upper deck; 

 2. Equipment/features mounted in the sidewall liners (and any sidewall liner joints to the equipment) such as the nose door 

control panel; 

 3. Liner joints at door edge frames (door 1, side cargo door, nose door); 

 4. Soft liner and joints above side cargo door where the hinges penetrate; 

 5. The aluminum and fiberglass dado panels (and associated joints) installed along the cargo compartment sidewalls from the 

cargo floor to approximately 10” to 15” above the floor. 

 

 Air grills in the ceiling panels between station 520 and 620 that are painted with intumescent paint which expand and close off the 

grill when exposed to a fire. 

 

 Protection of wires required for continued safe flight and landing inside the Class E compartment will be accomplished by any one, 

or combination of the following: 

 1. Routing behind fire resistant liners; 

 2. Routing of redundant wires on opposite sides of the main deck floor and/or opposite sides of the crown area, and/or with a 

minimum separation of 6’; 

 3. Placement of air dams or fire stops behind cargo liners as required to prevent propagation of fire behind the liner; 

 4. Use of fire resistant wire or insulation where required to protect wire in locations subject to potential high temperatures on the 

backside of cargo liners and above ceiling panels (below the flight deck for example); and 

 5. Placement of special fire resistant covers behind air return grilles/decompression vents as required. 

 At least one critical oxygen line, which provides oxygen to the flight deck, will also be protected by fire resistant sidewall liner 

material and a protective fiberglass cover on the associated air return grille/decompression vent. 

 

 Additional information is listed in Section 9 of Boeing Maintenance Planning Data Document D011U721-02 or the applicable engine 

Type Certificate Data Sheet. The more restrictive requirement from these two documents shall be in force. 

Production Basis: Production Certificate No. 700 has been issued to The Boeing Company. 

Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be 

installed in the aircraft for certification. 

XVI. Model 747-8 (Approved December 14, 2011) Transport Category 

The 747-8 series is based on the model 747-400 series aircraft with design changes to the empennage, fuselage, landing gear, wings, 

engines, fuel systems, and other aircraft systems as defined in the certification basis within this section. The certification basis for areas 

unaffected by this change from the 747-400 series aircraft will remain certified at the 14 CFR Part 25 Amendment level of their original 

certification date. 

Engines: 4 General Electric Turbofan Engines Model: GEnx-2B67B (Engine Type Certificate No. E00078NE) 

Fuel: General Electric Turbofan Engines 

 Fuels conforming to: 

 ASTM D-1655 grades Jet-A and Jet A-1 

 MIL-T-5624 grade JP-5 

 MIL-T-83133 grade JP-8 

 are acceptable 

 Fuels produced to other specifications and having properties meeting the requirements of the above specifications are acceptable. 

The fuel and any fuel additives must conform to the relevant Engine Operating Instructions. 

Engine Limits: General Electric Turbofan Engines 

See the appropriate FAA approved Airplane Flight Manual for engine ratings. 

Airspeed Limits: VMO/MMO = 365/0.9 (KCAS) See the appropriate FAA Approved Airplane Flight Manual for other 

airspeed limits 

C.G. Range: See the appropriate FAA Approved Airplane Flight Manual 
A20WE 56 

 

Empty Weight C.G.: See the appropriate FAA Approved Airplane Flight Manual 

Datum: See the appropriate Weight and Balance Control Manual 

Leveling Means: See the appropriate FAA Approved Airplane Flight Manual 

Maximum Weights: See the appropriate FAA approved Airplane Flight Manual 

Minimum Crew: For all flights, 2 persons (pilot, copilot). 

Maximum Number of : 0 

Seats 

Maximum Compartment: See the appropriate Weight and Balance Control Manual 

Weights 

Fuel Capacity: See the appropriate Weight and Balance Control Manual 

Oil Capacity: See the appropriate Weight and Balance Control Manual 

Maximum Operating: 43,100 

Altitude 

Control Surface: To insure proper operation of the airplane, the movement of the various control surfaces must be carefully 

Movements controlled by proper rigging of the flight control systems. The airplane must, therefore, be rigged according 

to the following FAA-approved data: 

 Boeing Drawing Numbers: 

 251U1001 Rigging Instructions Lateral Controls 

251U1003 Rigging Instructions Speed Brakes 

 251U2001 Rigging Instructions Elevator Controls 

251U3002 Rigging Instructions Rudder Controls 

 251U4001 Rigging Instructions Stablizer Trim Controls 

 114U0001 Rigging Instructions Leading Edge Slats Controls 

 253U5001 Rigging Instructions Control Stand 

 256U5001 Rigging Instructions Trailing Edge Flap Controls 

Model Eligible Serial Numbers

747-8KB 37544 

Certification Basis: 

The 747-8 series is based on the model 747-400 series aircraft with design changes to the empennage, fuselage, landing gear, wings, 

engines, fuel systems, and other aircraft systems as defined in the certification basis within this section. The certification basis for areas 

unaffected by this change from the 747-400 series aircraft will remain certified at the 14 CFR Part 25 Amendment level of their original 

certification date. The certification basis for areas changed or affected by the 747-8 minor model is 14 CFR part 25, as amended by 

Amendment 25-1 through Amendment 25-120 with exceptions permitted by 14 CFR 21.101. Section A documents the changed/affected 

areas of the aircraft. Section B documents all regulations for which there are exceptions from Amendment 25-120 for the changed/affected 

areas. Section C documents unchanged/unaffected areas for which compliance has been shown at an Amendment level higher than the 

747-400 Amendment level. 

 

A. The following section contains a listing of all areas that are changed/affected as part of the 747-8 minor model. 

 

Airplane Area Changed/Affected Areas 

Static Loads; Dynamic Flight Loads; Dynamic Ground Loads; Flutter 

Flotation and ditching 

Weight and balance 

Airplane Level 

Aerodynamic Stability & Control; Aerodynamic Performace; Aerodynamic Configurations 
57 A20WE 

XVI. Model 747-8 (cont’d)

Airplane Area Changed/Affected Areas 

Airframe - 

Empennage 

All empennage (including the outboard elevator balance weight towers) except: 

 Inboard elevator, remainder of outboard elevator. 

Airframe - 

Fuselage 

All fuselage (includes all fuselage, floors, doors, and window structure) except: 

 BS 140 pressure bulkhead; frames, S-0 to S-13, BS 160 to BS 320; 

 flight deck surround skins/stringers from S-0 to S-13, BS 220-300; 

 flight deck floor beams from BS 220-300; 

 structural supports and sills for flight deck windshields; 

 crown skin from S-0 to S-6 from BS 280 to 520; 

 upper deck side of body shear trusses; 

 9G intercostals for upper deck galleys, 

 upper deck floor decompression trusses, 

 side of body shear panels; 

 BS 2360 aft pressure dome and APU tail cone; 

 Nose radome and nose landing gear doors; 

 Upper deck emergency exit doors , flight deck overhead emergency exit door, and forward and center 

electrical equipment access doors 

Pitot static line plumbing 

Integrated Display System (IDS) 

Modularized Avionics and Warning Electronics Assembly (MAWEA) 

Flight Management Computer (FMC) 

Communication Management Unit (CMU) 

Enhanced Ground Proximity Warning System (EGPWS) 

Central Maintenance Computer System (CMCS) 

Airplane Condition and Monitoring System (Data Management Unit (DMU) and Quick Access Recorder (QAR)) 

Low Range Radio Altimeter (LRRA) 

Multi-Mode Receiver (MMR) 

Distance Measuring Equipment (DME) 

Automatic Direction Finder (ADF) 

VHF Omnidirectional Range/Marker Beacon (VOR/MB) 

Air Data Inertial Reference System (ADIRS) software 

SATCOM 

Cockpit Voice Recorder (CVR) 

Flight Deck (FD) Printer 

Flight Data Recorder Systems (FDRS) 

Onboard Network System (ONS) 

Terminal Wireless LAN Unit (TWLU) 

Automatic Fixed Emergency Locator Transmitter (ELT) 

HF/VHF Radio Communication Panel 

Traffic Alert and Collision Avoidance System (TCAS) and Air Traffic Control (ATC) Systems 

Avionics 

Flight Deck Audio System (Audio Management Unit (AMU) and Audio Control Panels (ACP)) 

Cargo Provisions including structural and electrical for Cargo Handling System for Lower Lobe Compartments 

Cargo Furnishings, Linings and Placards 

Duct Leak Detection System (DLDS) 

Integrated Wingtip Light Assembly (IWLA) 

Integrated Drive Generator (IDG) 

Main and APU battery 

Cabin Services System (CSS) 

Weight and Balance Computer of the On-Board Weight and Balance System 

Electrical Power Generation System 

Electrical Subsystems 

Service and maintenance lights in the wheel wells, AC pack bay, Tailcone/APU compartment and forward EE bay 
A20WE 58 

 

XVI. Model 747-8 (cont’d)

Window Heat Control Unit (WHCU) and flight deck window sensors 

Dimmer control unit (DCU) 

Fuselage, Wing, Strut, Wheel Well, E/E Cooling, Cargo Handling, FQIS, Galley Systems, Door 2 Entry and Stairs, 

Door 5 Crew Rest, Lavatory, Water System, Waste System, Oxygen Systems, Cabin Services System and Engine 

Wiring 

Wing Fuel Tank Stringer clip 

Electrical Wiring 

and Installation 

Integration panels 

Lower Lobe Cargo Fire Protection System 

Aft Cargo Air Conditioning (ACAC) System flow rate and ducting 

APU air supply ducting 

Air conditioning and trim ducting. 

E6/E9 equipment cooling supply line 

Forward cargo heat ducting 

Aft/bulk cargo heat ducting 

Recirculation fans 

Upper and lower recirculation filters 

Air distribution riser ducts. 

Lav/Galley Vent System (LGVS) ducting 

Air Supply Control System (ASCS) 

Wing Anti-Ice (WAI) System 

Cabin Air Conditioning Temperature Control System (CACTCS) 

Forward and aft electrical equipment (EE) cooling systems 

In-flight entertainment (IFE) cooling system 

Flight Deck Air Distribution System 

Environmental 

Systems 

Alternate Ventilation System (AVS) 

Door 1 slide/raft with integral exterior emergency lighting 

Upper deck escape slide with integral exterior emergency lighting 

Escape Slide latch to pack board (all doors) 

Escape Systems 

Door 3 escape slide interface with wing flap 

Fly-by-Wire (FBW) spoiler and outboard aileron control system. 

Inboard and outboard aileron droop. 

Flight control mechanical component installations and flight control cables 

Upper and lower rudder actuator 

Autoflight software 

Integrated Standby Flight Display (ISFD) 

Rudder ratio changer 

Elevator feel computer 

Yaw damper control laws. 

Yaw damper stabilizer trim modules (YSM) 

Pitch Augmentation Control System (PACS) 

Lateral Modal Suppression control laws. 

Outboard Aileron Modal Suppression (OAMS) 

Flap control unit software 

Elevator Feel Shift (EFS) 

Roller brake assembly 

Lateral Augmented Pitch Function (LAPS) 

Landing Attitude Modifier (LAM) 

Inboard Spoiler Function (Spudders) Pedal 

Emergency Decent Spoilers (EDS) 

Flight Controls 

Rudder Input Linkages 
59 A20WE 

XVI. Model 747-8 (cont’d)

Stabalizer Trim Indication 

Maneuver Load Alleviation (MLA) augmentation function 

Forward instrument panel (FIP) structure 

Flight deck display interface 

Glareshield 

Pilot Compartment Viewing 

Flight Deck 

Flight deck lighting dimmer 

Emergency equipment stowage, equipment and placarding 

Flight manual stowage retention straps 

Flight deck stowage door latches 

Portable oxygen bottle stowage provisions 

PC power outlets for Captain and First Officer 

Hand microphones at all 4 crew positions 

Provisions to support EFB installation 

Crew oxygen mask stowage boxes 

Crew oxygen masks 

Overhead light 

Carpet periphery 

Flight Deck Crew 

Accommodations 

Boom microphone jack panels at all 4 crew positions 

Flight Deck Crew 

Rest 

Wall mounted seat 

Jettison System 

Auxiliary Power Unit (APU) Feed System line, pumps and plumbing 

Reserve Tank Transfer System 

Fuel System Scavenge 

Fuel tank structure 

Fuel Feed System 

Fuel Vent System 

Fuel Management System 

Refuel/Defuel System 

Fuel Quantity Indicating System (FQIS) and fuel level sensing 

Fuel sump system drain valves 

Flammability Reduction System (FRS) 

Fuels 

Horizontal Stabilizer Tank 

Ceilings 

Stowage bins 

ceiling and bin secondary supports 

PSUs (including reading lights and gasper air) 

Sidewalls 

Window reveals 

Door and doorway linings 

Door 5 overhead attendant rest and entrance enclosure 

Closets/stowage units 

Partitions/class dividers 

Curtains 

Floor mounted stowages 

Emergency equipment stowages, equipment and related placarding 

Video control/Purser Work stations 

All main deck Lavatories 

Interior 

Upper deck lavatories 6U and 8U 
A20WE 60 

 

XVI. Model 747-8 (cont’d)

All Galleys 

Door 2 stairs 

Cart Lift electronics, drive mechanism, frame guide mechanism, and control panel. 

Floor coverings 

Placarding throughout cabin 

LED interior general lighting. 

Interior emergency lighting 

Passenger & attendant seat installations 

Assist spaces and assist handles 

Paint schemes including door markings and placards 

Thermal acoustic blankets 

Nose Landing Gear 

Body Landing Gear 

Landing Gear 

Structures 

Wing Landing Gear 

Landing gear alternate extend cables and brake cables 

Wheels, brakes, and tires. 

Brake system control unit software 

Body and wing gear retract actuators 

Body and wing gear door actuators 

Ram Air Turbine (RAT) and associated equipment and engine driven pumps (EDPs), EDP hoses and EDP check 

valves 

Hydraulic system (except RAT and associated equipment and EDPs, EDP hoses, and EDP check valves) 

Tire Pressure Indication System and Brake Monitor System 

Landing Gear Selection System 

Mechanical and 

Hydraulic 

Systems 

System 2 & 3 Alternating Current Motor Pump (ACMP) Demand Pumps 

Passenger oxygen system distribution lines 

Door 5 crew rest oxygen system 

Second 115 cu. ft. crew oxygen cylinder provisions 

Oxygen System 

Composite oxygen cylinders. 

GEnx-2B67 engines 

Engine Driven Hydraulic Pumps (EDP) 

Hydraulic tubing, hoses, and component installations on the engine. 

Hydraulic tubing, hoses, and component installations in the aft engine strut. 

APU fire extinguishing system extinguisher bottle, safety relief/filler port assembly, discharge head assembly, and 

discharge outlet/distribution plumbing. 

APU, APU Controls and APU Installation 

Engine Controls 

Propulsion 

Thrust Reverser Systems 

Propulsion - 

Structures 

Strut, nacelle, thrust reverser, inlet, exhaust, and systems 

Propulsion - 

Electrical Subsystems 

APU power feeder 

Potable water tanks 

Waste water drain system 

Waste and Water lines 

Waste tanks 

Water/Waste 

Waste water service panel components 

All wing structure 

Wing pylon structure 

Wing 

Aft wall extension 
61 A20WE 

XVI. Model 747-8 (cont’d)

B. The following section contains a listing of all regulations for which changed/affected areas of the aircraft comply with 14 CFR §25 at an 

Amendment level other than 25-120. 

14 CFR § Title Amdt Level 

For Changed/Affected Areas 

Comments 

25.305 Strength and 

deformation. 

25-0 for 25.305(b) for Airframe - Empennage (Outboard 

Elevator Balance Weight Tower) 

25-0 for 25.305(b) for Systems Stress related to: Landing Gear 

(Landing gear alternate extend cables and brake cables, Body 

gear truck positioner mounting features), Hydraulics (Hydraulic 

reservoirs, hydraulic line, Rudder PCA tubing, LG retract 

actuators, aileron and spoiler PCUs, Hydraulic Systems 1 and 4 

electric pump , PACS actuator and elevator feel shift module 

hydraulic tubing, Aft strut hydraulic installations), Flight 

Controls Rudder Control (Cables, mech components 

installations, upper/lower actuator installation, rudder input 

linkage), Flight Controls Elevator Control (Cables, mech 

components installations, Elevator Feel computer. Horizontal 

stabilizer trim actuator - trim arm switch and control wire) and 

Flight Controls High Lift (Flap Detents vs Dspeed, LE/TE 

components, flap drive stroke, flap skew detection). 

25.365 Pressurized 

compartment 

loads. 

25-0 for 25.365(e), (f), and (g) for Systems Stress related to: 

Flight Deck (Linings, stowages, and latches, oxygen mask 

stowage box) 

25-54 for 25.365(e)(2) for Fuselage (Section 41 main deck floor 

side of body shear trusses and side of body shear webs; Section 

41 lower lobe skin panels and flight deck skin panels - 

pressurized area only, below WL 200, between STA 140 and 

460; Pressurized skin panels) and Empennage (Forward fin box 

of vertical stab - unpressurized area) 

25.395 Control system. 25-23 for 25.395(a), (b), and (c) for Systems Stress related to: 

Flight Controls Rudder Control (Cables, mech components 

installations, upper/lower actuator installation, rudder input 

linkage), Flight Controls Elevator Control (Cables, mech 

components installations, Elevator Feel computer. Horizontal 

stabilizer trim actuator - trim arm switch and control wire) and 

Flight Controls High Lift (Flap Detents vs Dspeed, LE/TE 

components, flap drive stroke, flap skew detection). 

25.397 Control system 

loads. 

25-38 for 25.397 for Systems Stress related to: Flight Controls 

Rudder Control (Cables, mech components installations, 

upper/lower actuator installation, rudder input linkage), Flight 

Controls Elevator Control (Cables, mech components 

installations, Elevator Feel computer. Horizontal stabilizer trim 

actuator - trim arm switch and control wire) and Flight Controls 

High Lift (Flap Detents vs Dspeed, LE/TE components, flap 

drive stroke, flap skew detection). 

25.415 Ground gust 

conditions. 

25-0 for 25.415 for Systems Stress related to: Flight Controls 

Rudder Control (Cables, mech components installations, 

upper/lower actuator installation, rudder input linkage), Flight 

Controls Elevator Control (Cables, mech components 

installations, Elevator Feel computer. Horizontal stabilizer trim 

actuator - trim arm switch and control wire) and Flight Controls 

High Lift (Flap Detents vs Dspeed, LE/TE components, flap 

drive stroke, flap skew detection). 
A20WE 62 

 

XVI. Model 747-8 (cont’d)

25.561 General. 25-23 for Flight Deck - Wall Mounted Flight Deck Crew Rest 

Seat 

25.562 Emergency 

landing dynamic 

conditions. 

N/A for 25.562 for Flight Deck - Flight Deck Seats and Wall 

Mounted Flight Deck Crew Rest Seat 

25.571 Damage-tolerance 

and fatigue 

evaluation of 

structure. 

25-0 for 25.571(a) and (c) for Systems Stress related to: Flight 

Controls Rudder Control (Cables, mech components 

installations, upper/lower actuator installation, rudder input 

linkage), Flight Controls Elevator Control (Cables, mech 

components installations, Elevator Feel computer. Horizontal 

stabilizer trim actuator - trim arm switch and control wire) and 

Flight Controls High Lift (Flap Detents vs Dspeed, LE/TE 

components, flap drive stroke, flap skew detection). 

25-86 for 25.571(a) and (b) for Systems Stress related to Flight 

Controls – Lower Rudder Tab Push Rod 

25-86 for 25.571(a) and (b) for Fuselage (Section 41 upper deck 

floor beams BS 320-520; main deck floor side of body shear 

trusses and side of body shear webs; Section 42 skins BS 520-

740 except window belt skin panels; stringers S-0 to S-5 L/R, S11 to S-17, S-28 to S-33; frames at upper deck floor joint 

(except new plug frames); crown splice fittings at BS 520 & 

BS740; upper deck emergency door surround structure; lower 

lobe cargo door surround structure; upper deck floor 

stabilization system, lavatory and galley supports, and floor 

beam to frame connections; main deck floor side of body shear 

trusses and side of body shear webs; bulk cargo door; forward 

and aft lower lobe cargo doors; passenger entry doors 1-5), 

Wing, and Empennage (Stabilizer forward torque box and 

leading edge; fin forward torque box; Outboard Elevator 

Balance Weight Tower) 

N/A for 25.571(a) and (c) for Landing Gear (Main Gear) 
63 A20WE 

XVI. Model 747-8 (cont’d)

25.573 Fatigue evaluation 

of landing gear. 

 25-0 for 25.573(a) and (c) for Landing Gear (Main Gear) 

25.607 Fasteners. 25-0 for 25.607 for Airframe – Empennage (Outboard Elevator 

Balance Weight Tower) 

25-0 for 25.607 for Flight Controls Elevator and Lateral Control 

(Control Wheels, Left and Right Forward Cable Quadrants, 

Forward Load Limiter Device, Right and Left Cable Systems, 

Aileron Feel and Centering Unit, Aileron Trim System, Lateral 

Central Control Actuator, Third Autopilot Servo, Aileron 

Programmer, Wing Cable System to Inboard Aileron PCU, Noback Brake assembly, Elevator Feel Computer and 

Autospeedbrake system to drive speedbrake lever) and High Lift 

Systems 

25-0 for 25.607 for Hydraulics (except RAT and hydraulics 

associated with engine installations) 

25-0 for 25.607 for Systems Stress related to: Landing Gear 

(Landing gear alternate extend cables and brake cables, Body 

gear truck positioner mounting features), Hydraulics (Hydraulic 

reservoirs, hydraulic line, Rudder PCA tubing, LG retract 

actuators, aileron and spoiler PCUs, Hydraulic Systems 1 and 4 

electric pump , PACS actuator and elevator feel shift module 

hydraulic tubing, Aft strut hydraulic installations), Flight 

Controls Rudder Control (Cables, mech components 

installations, upper/lower actuator installation, rudder input 

linkage), Flight Controls Elevator Control (Cables, mech 

components installations, Elevator Feel computer. Horizontal 

stabilizer trim actuator - trim arm switch and control wire) and 

Flight Controls High Lift (Flap Detents vs Dspeed, LE/TE 

components, flap drive stroke, flap skew detection). 

25.613 Material strength 

properties and 

design values. 

25-46 for 25.613 for Airframe – Empennage (Outboard Elevator 

Balance Weight Tower) 

25.615 Design properties. 25-23 for 25.615 for Airframe – Empennage (Outboard Elevator 

Balance Weight Tower) 
A20WE 64 

 

XVI. Model 747-8 (cont’d)

25.625 Fitting factors. 25.23 for 25.625(a), (b) and (c) for System Stress related to: 

Hydraulics (Hydraulic reservoirs, hydraulic line, Rudder PCA 

tubing, LG retract actuators, aileron and spoiler PCUs, 

Hydraulic Systems 1 and 4 electric pump , PACS actuator and 

elevator feel shift module hydraulic tubing, Aft strut hydraulic 

installations), Landing Gear (Landing gear alternate extend 

cables and brake cables, Body gear truck positioner mounting 

features), Flight Controls Rudder Control (Cables, mech 

components installations, upper/lower actuator installation, 

rudder input linkage), Flight Controls Elevator Control (Cables, 

mech components installations, Elevator Feel computer. 

Horizontal stabilizer trim actuator - trim arm switch and control 

wire) and Flight Controls High Lift (Flap Detents vs Dspeed, 

LE/TE components, flap drive stroke, flap skew detection). 

25.675 Stops. 25-0 for 25.675(a), (b), and (c) for Flight Controls - Elevator and 

Lateral Control (Control Wheels, Left and Right Forward Cable 

Quadrants, Forward Load Limiter Device, Right and Left Cable 

Systems, Aileron Feel and Centering Unit, Aileron Trim 

System, Lateral Central Control Actuator, Third Autopilot 

Servo, Aileron Programmer, Wing Cable System to Inboard 

Aileron PCU, No-back Brake assembly, Elevator Feel Computer 

and Autospeedbrake system to drive speedbrake lever), Rudder 

(Rudder cables, Rudder PCMs, Rudder PCAs, Press-to-Center 

function, Remote compensators, Rudder Anti-cav/relief valves; 

Primary control linkage aft of aft quadrant, secondary linkage 

(buss linkage), rudder input linkage) and Stabilizer (Trim arm 

and control wires) 

25-0 for 25.675(a) and (b) for Flight Controls High Lift System 

25-0 for 25.675(c) for System Stress related to: Flight Controls 

Rudder Control (Cables, mech components installations, 

upper/lower actuator installation), Flight Controls Elevator 

Control (Cables, mech components installations, Elevator Feel 

computer. Horizontal stabilizer trim actuator - trim arm switch 

and control wire) and Flight Controls High Lift (Flap Detents vs 

Dspeed, LE/TE components, flap drive stroke, flap skew 

detection). 
65 A20WE 

XVI. Model 747-8 (cont’d)

25.677 Trim systems. 25-23 for 25.677(a), (b), (c), and (d) for Flight Controls Elevator 

and Lateral Control System (Control Wheels, Left and Right 

Forward Cable Quadrants, Forward Load Limiter Device, Right 

and Left Cable Systems, Aileron Feel and Centering Unit, 

Aileron Trim System, Lateral Central Control Actuator, Third 

Autopilot Servo, Aileron Programmer, Wing Cable System to 

Inboard Aileron PCU, No-back Brake assembly, Elevator Feel 

Computer and Autospeedbrake system to drive speedbrake 

lever) 

25-23 for 25.677(a), (b), and (c) for Flight Controls Rudder 

(Rudder cables, Rudder PCMs, Rudder PCAs, Press-to-Center 

function, Remote compensators, Rudder Anti-cav/relief valves) 

and Stabilizer (Trim arm and control wires) 

25-23 for 25.677(b) for Flight Controls Stabilizer trim indicator 

and greenband on flight deck 

25.683 Operation tests. 25-0 for 25.683 for Systems Stress related to: Flight Controls 

Rudder Control (Cables, mech components installations, 

upper/lower actuator installation, rudder input linkage), Flight 

Controls Elevator Control (Cables, mech components 

installations, Elevator Feel computer. Horizontal stabilizer trim 

actuator - trim arm switch and control wire) and Flight Controls 

High Lift (Flap Detents vs Dspeed, LE/TE components, flap 

drive stroke, flap skew detection). 

25.685 Control system 

details. 

25-0 for 25.685(a), (b), and (c) for Flight Controls Elevator and 

Lateral Control System (Control Wheels, Left and Right 

Forward Cable Quadrants, Forward Load Limiter Device, Right 

and Left Cable Systems, Aileron Feel and Centering Unit, 

Aileron Trim System, Lateral Central Control Actuator, Third 

Autopilot Servo, Aileron Programmer, Wing Cable System to 

Inboard Aileron PCU, No-back Brake assembly, Elevator Feel 

Computer and Autospeedbrake system to drive speedbrake 

lever) 

25.693 Joints. 25-0 for 25.693 for Systems Stress related to: Flight Controls 

Rudder Control (Cables, mech components installations, 

upper/lower actuator installation, rudder input linkage), Flight 

Controls Elevator Control (Cables, mech components 

installations, Elevator Feel computer. Horizontal stabilizer trim 

actuator - trim arm switch and control wire) and Flight Controls 

High Lift (Flap Detents vs Dspeed, LE/TE components, flap 

drive stroke, flap skew detection). 

25.701 Flap 

interconnection. 

 25-23 for 25.701(a) for Flight Controls High Lift System 

25.783 Doors. 25-88 for 25.783 for Forward and Aft Lower Lobe Cargo Doors 

25-23 for 25.783 for Airframe - Bulk Cargo Door, Passenger 

Entry Doors 1-5 and ECS pack bay access panels. 

25.785 Seats, berths, 

safety belts, and 

harnesses. 

25-32 for 25.785(h)(2) for Interiors - Zone A (Cabin Attendant 

Direct View) 

25.785(a) at Amdt 25-32 for 25.785(b) for Flight Deck Seats 

25-32 for 25.785 for Wall Mounted Flight Deck Crew Rest Seat 

Compliance to be shown to 

CFR25.785(a) Amdt 25-32 in 

lieu of CFR25.785(b) Amdt 120 

for Flight Deck Seats.

25.795 Security 

considerations. 

25-127 for 25.795(b)(2) for Environmental Systems – Air 

Distribution System 
A20WE 66 

 

XVI. Model 747-8 (cont’d)

25.809 Emergency exit 

arrangement. 

25-114 for 25.809(a) for Escape Systems – Flight deck over 

head exit and passenger door 3. 

25.812 Emergency 

lighting. 

25-128 for 25.812 for Exterior Lights for Flight Deck Exits 

25.863 Flammable fluid 

fire protection. 

25-0 for 25.863(a) and (b) for Flight Controls Elevator and 

Lateral Control System (Control Wheels, Left and Right 

Forward Cable Quadrants, Forward Load Limiter Device, Right 

and Left Cable Systems, Aileron Feel and Centering Unit, 

Aileron Trim System, Lateral Central Control Actuator, Third 

Autopilot Servo, Aileron Programmer, Wing Cable System to 

Inboard Aileron PCU, No-back Brake assembly, Elevator Feel 

Computer and Autospeedbrake system to drive speedbrake 

lever) 

25.869 Fire protection: 

Systems 

N/A for 25.869(a)(1) for Hydraulics Electrical (Hydraulics 

system fire shutoff valve and flight control shutoff valve; 

Hydraulic fluid quantity probe in each reservoir) 

25.1359(d) at Amdt 25-32 for 25.869(a)(4) for Hydraulics 

Electrical (Hydraulics system fire shutoff valve and flight 

control shutoff valve; Hydraulic fluid quantity probe in each 

reservoir; Ground Fault Interrupt) and Flight Controls High Lift 

Compliance to be shown to 

CFR25.1359(d) Amdt 25-32 in 

lieu of CFR25.869(a)(4) Amdt 

120 for Hydraulics Electrical. 

25.899 Electrical bonding 

and protection 

against static 

electricity. 

25-123 

25.903 Engines. 25-57 for 25.903(a) and (c) for Propulsion - APU 

25.981 Fuel tank ignition 

prevention. 

25-125 for 25.981(a), (b), and (c) for Propulsion - Nitrogen 

Generation System (NGS) 

25.1013 Oil tanks. 25-57 for 25.1013(a) and (c) for Propulsion - APU 

25.1093 Induction system 

deicing and antiicing provisions. 

25-57 for 25.1093(b) for Propulsion - APU 

25.1103 Induction system 

ducts. 

25-23 for 25.1103(b)(2) for Propulsion - APU 

25.1141 Powerplant 

controls: General. 

25-40 for 25.1141(f)(2) for Propulsion - APU 

25.1181 Designated fire 

zones: Regions 

included. 

25-23 for 25.1181(b) for Propulsion - APU 

25.1183 Lines and fittings. 25-57 for 25.1183 for Propulsion - APU 

25.1305 Powerplant 

instruments. 

25-54 for 25.1305(a)(7) for Propulsion - APU 
67 A20WE 

XVI. Model 747-8 (cont’d)

25.1309 Equipment systems 

and installations. 

25-0 for 25.1309(a), (b), (c), and (d) for Flight Controls Elevator 

and Lateral Control System (Control Wheels, Left and Right 

Forward Cable Quadrants, Forward Load Limiter Device, Right 

and Left Cable Systems, Aileron Feel and Centering Unit, 

Aileron Trim System, Lateral Central Control Actuator, Third 

Autopilot Servo, Aileron Programmer, Wing Cable System to 

Inboard Aileron PCU, No-back Brake assembly, Elevator Feel 

Computer and Autospeedbrake system to drive speedbrake 

lever) 

25.1317 High-intensity 

radiated fields 

(HIRF) protection. 

 25-122 

25.1323 Airspeed 

indicating system. 

25-108 for 25.1323(a), (b), and (c) for Flight Controls – 

Integrated Standby Flight Display 

25-108 for 25.1323(b), (c), (d), (e), and (f) for Avionics – 

ADIRS 

25-108 for 25.1323(b) and (c) for Aerodynamic Configurations 

25.1325 Static air vent and 

pressure altimeter 

systems. 

25-108 for 25.1325(d) and (e) for Flight Controls – Integrated 

Standby Flight Display 

25-108 for 25.1325(a), (b), (c), (d), and (e) for Avionics – 

ADIRS 

25-108 for 25.1325(b) and (e) for Aerodynamic Configurations 

25.1329 Flight guidance 

system. 

25-46 for Avionics – Flight Management Computer System 

25-46 for Flight Controls - Autopilot Flight Director System 

25-46 for 25.1329(f) for Flight Controls Elevator and Lateral 

Control System (Control Wheels, Left and Right Forward Cable 

Quadrants, Forward Load Limiter Device, Right and Left Cable 

Systems, Aileron Feel and Centering Unit, Aileron Trim 

System, Lateral Central Control Actuator, Third Autopilot 

Servo, Aileron Programmer, Wing Cable System to Inboard 

Aileron PCU, No-back Brake assembly, Elevator Feel Computer 

and Autospeedbrake system to drive speedbrake lever) 

25.1335 Flight director 

systems. 

 25-41 for Flight Controls - Autopilot Flight Director System 

25.1353 Electrical 

equipment and 

installations. 

25-42 for 25.1353(a) for Hydraulics (Hydraulics system fire 

shutoff valve and flight control shutoff valve) 

25-42 for 25.1353(a) for Electircal Subsystems - APU 

25-42 for 25.1353(a) and (b) for Flight Controls High Lift 

System 
A20WE 68 

 

XVI. Model 747-8 (cont’d)

25.1431 Electronic 

equipment. 

N/A for 25.1431(d) for Hydraulics )Hydraulic fluid quantity 

probe in each reservoir) 

N/A for 25.1431(d) for Electrical Subsystems - APU 

25.1435 Hydraulic systems. 25-0 for 25.1435(a) and (b) for Flight Controls Elevator and 

Lateral Control (Control Wheels, Left and Right Forward Cable 

Quadrants, Forward Load Limiter Device, Right and Left Cable 

Systems, Aileron Feel and Centering Unit, Aileron Trim 

System, Lateral Central Control Actuator, Third Autopilot 

Servo, Aileron Programmer, Wing Cable System to Inboard 

Aileron PCU, No-back Brake assembly, Elevator Feel Computer 

and Autospeedbrake system to drive speedbrake lever), Rudder 

(Rudder cables, Rudder PCMs, Rudder PCAs, Press-to-Center 

function, Remote compensators, Rudder Anti-cav/relief valves; 

Primary control linkage aft of aft quadrant, secondary linkage 

(buss linkage)) and Stabilizer (Trim arm and control wires) 

25-41 for 25.1435(a)(1), (a)(5), (a)(6), (a)(7), and (b)(2) for 

Flight Controls High Lift System 

25-41 for 25.1435(a)(1), (a)(2), (a)(4), (a)(5), (a)(6), (a)(7), 

(a)(8), (b)(1), (b)(2), and (c) for Hydraulics (except RAT and 

hydraulics associated with engine installations) 

25.1457 Cockpit voice 

recorders. 

25-124 for 25.1457(a)(6), (d)(1), (d)(4), (d)(5)(i), (d)(5)(ii), 

(d)(5)(iii), (6)(e)(1) for Avionics - Cockpit Voice Recorder 

 

25.1459 Flight recorders. 25-124 for 25.1459(a)(3), (a)(7) and (a)(8) for Avionics – Flight 

Data Recorder System 

 

25.1522 APU Limitations. 25-46 for 25.1522 for Propulsion - APU 

25.1551 Oil quantity 

indicator. 

25-0 for 25.1551 for Propulsion - APU 

C. The following section contains a listing of all regulations for which unchanged/unaffected areas of the aircraft comply with 14 CFR §25 

at an Amendment level greater than the 747-400 Amendment level. 

14 CFR § Title Amdt Level 

For Unchanged/Unaffected Areas 

25.303 Factor of safety. 25-120 for 25.303 for Airframe – Fuselage - #2 and #3 flight deck windshield 

25.305 Strength and deformation. 25-120 for 25.305(a), (b) and (c) for Airframe - Fuselage 

25.307 Proof of structure. 25-120 for 25.307(a) and (d) for Airframe – Fuselage - #2 and #3 flight deck windshield

25.365 Pressurized cabin loads. 25-54 for 25.365(e) for Airframe – Fuselage - Flight deck floor beams/frames (not 

 affected from decompression standpoint) 

 25-120 for 25.365(a), (b), and (d) for Airframe – Fuselage - #2 and #3 flight deck 

 windshield 
69 A20WE 

XVI. Model 747-8 (cont’d)

25.571 Damage-tolerance and fatigue 

evaluation of structure. 

 25-86 for 25.571(a) and (b) for Airframe – Empennage and Fuselage 

 25-120 for 25.571(d) and (e) for Airframe – Empennage and Fuselage 

 25-120 for 25.571(b)(5)(ii) for Airframe – Fuselage - #2 and #3 flight deck windshield 

25.601 Design & Construction - 

General. 

 25-120 for 25.601 for Airframe – Fuselage - #2 and #3 flight deck windshield 

25.603 Materials. 25-120 for 25.603 for Airframe – Fuselage - #2 and #3 flight deck windshield 

25.605 Fabrication methods. 25-120 for 25.605 for Airframe – Fuselage - #2 and #3 flight deck windshield 

25.609 Protection of structure. 25-120 for 25.609 for Airframe – Fuselage - #2 and #3 flight deck windshield 

25.611 Inspection provisions. 25-120 for 25.611 for Airframe – Fuselage - #2 and #3 flight deck windshield 

25.775 Windshields and windows. 25-120 for 25.775 for Airframe – Fuselage - #2 and #3 flight deck windshield 

25.795(a) Security considerations. 25-127 for 25.795(a) for Vertical portions of the flight deck boundary 

 common to passenger compartment 

Additional Certification Basis Information: 

Based on 14 CFR §21.17(a) and §21.101(g) for changes made to TCs applicable provisions of 14 CFR part 26 are included in the 

certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable 

sections 

14 CFR §26 of the FAR as amended by Amendments 26-1 through 26-3, and any later amendments in existence at the time of certification. 

 

14 CFR §34 of the FAR as amended by Amendments 34-1 through 34-4, and any later amendments in existence at the time of certification. 

14 CFR §36 of the FAR as amended by Amendments 36-1 through 36-28, and any later amendments in existence at the time of 

certification. 

Exemptions from 14 CFR §25: 

Applicable 

Part 25 

Section 

Amndt 

Level 

Subject Exemption 

Number 

Date 

Issued 

Expiration 

Date 

(if applicable) 

25.809(a) 116 Exterior Outside Viewing Means 10367 10/20/2011 8/1/2014 

25.841(a) (2) 

and (a)(3) 

25-87 Pressurized Cabins – Uncontained Engine Failure 9943 

9943A 

10/29/2009 

7/12/2011 

None 

25.901(c) 25-46 Installation - No Single Failure Criteria Partial 

Exemption 

8518 03/23/2005 None 

25.981(a)(3) 25-102 Fuel Tank Ignition Prevention - Fuel Tank Structural 

Fastener Penetrations 

10174 12/14/2010 None 

25.1305(c)(6) 

25.1309(c) 

25-120 Fuel System Contamination 10267 

10267A 

05/19/2011 

08/05/2011 

12/31/2016 

06/30/2014 
A20WE 70 

 

XVI. Model 747-8 (cont’d)

The following regulations have been complied with by findings of an Equivalent Level of Safety: 

Applicable 

Part 25 

Section

Amndt 

Level

Subject ELOS 

Number

25.107(e)(1)(iv) Minimum Unstick Speed (VMU) TC6918SE-T-F-6 

Rev 1 

25.161(a) and (c)(3) 

25.1301(a) 

25.1309(a) 

 Longitudinal Trim PS05-0212-F-4 

25.689(a)(1) Control Cable Diameter PS05-0212-SF-2 

25.777(e) 46 Wing Flap Control Lever PS05-0212-SF-1 

25.783(e) 88 Visual Indication of Forward and Aft Lower Lobe 

Cargo Door Locked Condition 

PS05-0212-C-1 

25.807 

25.813(a) and (b) 

 Upper Deck 22” Passageway PS05-0211-C-16 

25.809(a) Outside Viewing Means for Upper Deck Emergency 

Exits 

PS05-0211-C-15 

25.810(a)(1)(ii) 10 Second Inflation (in Lieu of 6 Seconds) for Type 

A U/D Exits. 

PS05-0211-C-5 

25.811 Door Sill Reflectance TC6918SE-T-CS-2 

Rev 1 

25.811 Exterior Exit Markings TC6918SE-T-CS-2 

Rev 1 

25.815 Width of Aisle ANM-100S-0120-CI-1 

Rev 1 

25.831(g) Acceptable High Temperature Physiological 

Environment During Failure Conditions 

PS05-0020-ES-3 

Rev 1 

25.863 

25.1182(a) 

25.1183(a) 

 Engine Nacelle Power Door Opening System 

(PDOS) Fire Testing 

PS05-0211-P-6 

25.863 

25.1182(a) 

25.1183(a) 

 Nacelle Areas Behind Firewalls for Thrust Reverser 

Directional Control Valve (DCV) 

PS05-0212-P-18 

25.899(a)(2) 

25.901(c) 

25.954 

25.981(a)(3) and (b) 

25.1309(a) and (b) 

 Equivalent Safety Finding for Zero Fuel Horizontal 

Stabilizer Fuel Tank (HST) 

PS05-0211-P-25 

25.933 Flight Critical Thrust Reverser TC6918SE-T-P-2 

Rev 1 

25.934 Engine and Thrust Reverser System Testing TC6918SE-T-P-17 

Rev 1 

25.981(a)(3) Means of Compliance for the Installation of GFI 

Relays on Boeing Model 707, 727, 737CL, 737NG, 

747 CL, 747-400, 757, 767, & 777 Airplanes 

PS05-0123-P-1 Rev 1 

25.981(b) 125 Fuel Tank Flammability Reduction Rule PS05-0177-P-2 

25.981(a)(3) Equivalent Safety Finding for Ground Fault 

Interrupter Circuit Protection for Fuel Override and 

Jettison Pumps 

PS05-0212-P-24 

25.997(d) 

25.1305(c)(6) 

 Warning Means for Engine Fuel Filter 

Contamination 

PS05-0212-P-4 

25.1145(a) and (b) Ignition Switches PS05-0212-P-5 

25.1181(a)(6) 

25.1182(a) 

 Fire Safety Requirements for the GEnx-2B Engine 

Fan Case 

PS05-0211-P-23 

25.1182 

25.1183 

 Fire Safety Requirements for the Aft Strut Fairing 

Compartment 

PS05-0212-P-21 

25.1193 Cowling and Nacelle Skin Fireproof Regions PS05-0212-P-16 

25.1301(a), and (d) 

25.1309(a), and (c) 

 Transition Speed of Enhanced Ground Proximity 

Warning System (EGPWS) Mode 4 Alerts; Too Low 

Flaps/Too Low Terrain 

PS05-0212-S-3 

25.1303(c)(1) Overspeed Aural Warning TC6918SE-T-SA-11 

Rev 1 
71 A20WE 

XVI. Model 747-8 (cont’d)

25.1325(e) Standby Air Data System PS05-0212-F-3 

25.1415(c) Remote Stowage of Door 1 Slide/Raft Survival Kits PS05-0211-C-9 

25.1435(b)(1) 104 Request for an Equivalent Level of Safety Finding 

for the Hydraulic System Pressure Test 

PS05-0212-SF-4 

25.1517 Rough Air Speed (VRA) TC6918SE-T-F-4 

Rev 1 

25.1529 

Appendix H 

 Maintenance Planning Document Section 9 

(Instructions for Continued Airworthiness) 

PS05-0212-P-G-8 

Note: The 777F issue paper ES-3, stage 4, “Acceptable High Temperature Physiological Environment During Failure Conditions,” signed January 18, 2008 

references the July 31, 2003 version of the Mechanical Systems Harmonization Working Group (MSHWG) final report on § 25.831(g). The Actual version 

of the MSHWG final report approved unanimously by the Transport Airplane Engine Issues Group (TAEIG) was dated July 24, 2003. The draft rule, 

transient heat analysis, and body core limits are the same in the July 24, 2003 and July 31, 2003 versions of the MSHWG final report. Compliance findings 

should reference the July 24, 2003 version of the MSHWG final report on § 25.831(g). 

Special Conditions with respect to the following subjects apply to the 747-8: 

Special 

Condition 

Number 

Effective 

Date 

Subject 

25-ANM-24 12/21/1988 Flight Deck Displays and Propulsion Control Systems 

25-368-SC 03/17/2008 Seats with Non-Traditional, Large, Non-Metallic Panels 

25-385-SC 11/09/2009 Structural Design Requirements for Four-Post Main Landing Gear 

System 

25-387-SC 09/11/2009 Additional Airframe Structural Design Requirements Related to 

Sudden Engine Stoppage Due to Fan Blade Failures 

25-388A-SC 06/27/2011 Interaction of Systems and Structures 

25-401-SC 02/16/2010 Systems and Data Networks Security--Protection of Airplane 

Systems and Data Networks From Unauthorized External Access 

25-402-SC 02/16/2010 Design Roll Maneuver Requirement 

25-421-SC 03/09/2011 Security Protection of Aircraft Control Domain and Airline 

Information Domain from the Passenger Entertainment Domain 

25-430-SC 07/01/2011 Stairwell Between the Main and Upper Decks 

25-438-SC 08/01/2011 Door 1 Extendable Length Escape Slide 

25-442-SC 08/24/2011 Overhead Flight Attendant Rest Compartment 

25-446-SC 09/28/2011 Upper Deck Occupancy 

Additional Design Requirements and Conditions:

 The following design details or information must be maintained to ensure that an unsafe design condition is not present: 

14 CFR 25.1329 – Flight Guidance System 

The following design features must be incorporated in the type design (reference § 25.1329, Amendment 25-46). In lieu of the following, 

compliance to 25.1329, Amendment 25-119, may be shown. 

1. Quick autopilot disconnect switches for each pilot on the outboard arm of each control wheel and quick autothrust disconnect 

switches for each pilot on the underside of the thrust control levers for engines 1 and 4. 

 2. Positive disconnect function for the autopilot is provided by the disconnect bar located at the glare shield on the autopilot mode 

control panel (MCP). 

 3. Positive disconnect function for the autothrottle is provided by the autothrottle arm switch, also located on the MCP. 

 4. Automatic synchronization of the autopilot and autothrust functions is provided in order to ensure transient free engagement and 

mode switching. 

 5. Automatic stabilizer trim is used to offload the elevator in order to ensure transient free disengagement of the autopilot pitch axis. 

 6. The wheel position provides a visual and tactile indication of any wheel input which may be required at disengagement of the 

autopilot roll axis. 

 7. When multiple autopilot channels are engaged, disengagement of an individual autopilot does not result in a transient any greater 

than a minor transient. 

 8. The throttle levers remain in the current position when the autothrust function is disengaged. 
A20WE 72 

 

XVI. Model 747-8 (cont’d)

 9. Failures of the automatic stabilizer trim function, and other detected failures which degrade autopilot operation but do not pose an 

immediate hazard to the airplane, result in activation of the master caution light and aural, as well as the display of an AUTOPILOT 

caution message. 

 10. Detected failures which do pose an immediate hazard to the airplane, result in an autopilot disconnect with associated autopilot 

disconnect warning level annunciation that includes activation of the master warning light and aural as well as the display of an 

AUTOPILOT warning message. 

 11. Transition from multiple autopilot operation to single autopilot operation (with associated yaw axis autopilot servo disconnect), 

during engine inoperative go-around, does not require exceptional piloting skill, alertness, or strength. 

 12. The AFDS provides low speed protection via the following features: 

 a. The AFDS controls to an angle-of-attack which corresponds to one degree below the stick shaker angle-of-attack. 

 b. The AFDS take-off mode provides windshear recovery guidance which meets the criteria of AC 25-12 and AC 120-41. 

 c. An indication to the flight crew of a low speed condition includes the display of the stick shaker angle-of-attack via a 

pitch limit indicator (PLI). 

 d. The thrust management function (TMF), when engaged in SPD mode, provides low speed protection when the AFDS 

vertical speed (V/S) mode is engaged and commanding a climb. In addition, if the angle-of-attack rises above a fixed 

reference point, the AFDS issues a V/S mode failure by removing the pitch flight director bars if the flight director is turned

on. 

 e. If the autopilot is engaged, a V/S mode failure will result in an amber line being drawn through the V/S mode 

annunciation on the primary flight display (PFD), illumination of the master caution light, activation of the master caution 

aural, and display of an AUTOPILOT caution message. 

 f. An indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message when the airspeed 

drops below the top of the lower amber band of the airspeed indicator. 

 g. The AFDS provides low speed protection by controlling to a reference angle-of-attack when in Flight Level Change 

(FLCH) mode. An additional indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message 

when the airspeed drops below the top of the lower amber band. 

 h. When the AFDS altitude capture (ALT CAP) mode is engaged, the TMF, if engaged in SPD mode, provides low speed 

protection. In addition, under certain conditions the AFDS will provide altitude capture speed floor protection by 

controlling to a speed no lower than 5 knots below the MCP selected speed.

 i. If the AFDS altitude capture mode is engaged, and the angle-of-attack rises above a fixed reference point the AFDS will 

issue an ALT CAP mode failure by removing the pitch flight director bars if the flight director is turned on. If the 

autopilot is engaged, the ALT CAP mode failure will result in a mode annunciation on the Primary Flight Display (PFD), 

illumination of the master caution light, activation of the master caution aural, and display of an AUTOPILOT caution 

message. An additional indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message 

when the airspeed drops below the top of the lower amber band. 

 j. When the AFDS Altitude Hold (ALT HLD) mode is engaged, the TMF, if engaged in SPD mode, provides low speed 

protection. An additional indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message 

when the airspeed drops below the top of the lower amber band. 

 k. When the AFDS Vertical Navigation (VNAV) mode is engaged, the TMF, if engaged in SPD mode, provides low speed 

protection. Otherwise, when engaged in VNAV SPD, the FMF provides low speed protection. An additional indication 

to the flight crew of a low speed condition is an AIRSPEED LOW caution message when the airspeed drops below the 

top of the lower amber band. 

 l. When the AFDS glideslope (G/S) mode is engaged, the TMF, if engaged in SPD mode, provides low speed protection. 

An additional indication to the flight crew of a low speed condition is an AIRSPEED LOW caution message when the 

airspeed drops below the top of the lower amber band. 

 m. When the AFDS go-around mode is engaged, the AFDS provides low speed protection by controlling to an angle-ofattack which corresponds to one degree below the stick shaker angle-of-attack. The AFDS go-around mode provides 

windshear recovery guidance and meets the criteria of AC 25-12 and AC 120-41. An additional indication to the flight 

crew of a low speed condition includes the display of the stick shaker angle-of-attack (via a pitch limit indicator (PLI)). 

 n. Autothrottle wake-up requires that the autothrottle arm switch, located on the MCP, be in the ARM position. When the 

AFDS in not in takeoff, go-around, FLCH, or VNAV SPD modes, the autothrottle will automatically engage into SPD 

mode and provide speed protection when the airspeed drops approximately 5 to 10 knots below the top of the lower 

amber band. 
73 A20WE 

XVI. Model 747-8 (cont’d)

 13. The AFDS provides high speed protection via the following features: 

 a. Indication to the flight crew of a high speed condition is an OVERSPEED warning message when the airspeed/Mach 

number exceeds VMO/MMO 

 b. When the AFDS takeoff mode is engaged, the AFDS provides high speed protection by controlling to the flap placard 

(flaps down) or VMO/MMO (flaps up). 

 c. When the AFDS V/S mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

 d. When the AFDS FLCH mode in engaged, the AFDS provides high speed protection by controlling to the flap placard 

(flaps down) or VMO/MMO (flaps up). 

 e. When the AFDS ALT CAP mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

 f. When the AFDS ALT HLD mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

 g. When the AFDS VNAV mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

Otherwise, when engaged in VNAV SPD, the FMF provides high speed protection. 

 h. When the AFDS G/S mode is engaged, the TMF, if engaged in SPD mode, provides high speed protection. 

 i. When the AFDS go-Around mode is engaged, the AFDS provides high speed protection by controlling to the flap placard 

(flaps down) or VMO/MMO (flaps up). 

 14. For the flight guidance system functions, controls, indications, and alerts, means are provided to indicate the current mode of 

operation as well as any armed modes. Mode transitions are indicated on the Primary Flight Display (PFD) and highlighted with 

boxes that are displayed around the changed mode for ten seconds following the mode change. The indications are visible to each 

pilot under all expected lighting conditions during the flight deck lighting evaluation. 

 15. Autopilot disengagement is annunciated via illumination of the master warning light, activation of the master warning aural, and 

via the display of an AUTOPILOT warning message. A dedicated autopilot warning provides for an aural warning which is 

unique from all of the other aural warnings. 

 16. Override of the Autothrust by the flight crew using the throttles does not require excessive force, and does not create a potential 

hazard to the airplane. 

 Unrelated to the necessary design features itemized above, the FAA wishes to make the following clarifying statement. The FAA has 

 determined the equivalent safety finding associated with Longitudinal Trim (IP F-4) does not affect the exception granted for § 25.1329. 

14 CFR 25.365(e)(2) – Section 41 Lower Lobe (BS 140-460) 

The following design features must be incorporated in the type design (reference § 25.365, Amendment 25-54). In lieu of incorporating 

the following design features, compliance to § 25.365, Amendment 25-120, may be shown. 

Section 41 Lower Lobe (BS 140-460): 

When evaluating this compartment for compliance to § 25.365, the compartment must be analyzed using the following two conditions: 

 

 (1) A 3.7 square foot opening (forward EE Bay access door) with the BS 464 cargo liner intact (3.7 sf), and 

 (2) A 20.0 square foot opening with the BS 464 cargo liner blown down. This essentially combines the Section 41 Lower Lobe and

the forward cargo compartment into one compartment in the analysis. 

 

14 CFR 25.561(c)(1)(ii) – Auxiliary Power Unit Fuel Line in Section 46 

The following design features must be incorporated in the type design. In lieu of incorporating the following design features, compliance 

to § 25.561(c)(1)(ii), Amendment 25-120, may be shown. 

 (1) The Section 46 floor beams must be designed to protect the auxiliary power unit (APU) fuel lines from an emergency landing load 

event of a minimum of 5.2 g's down and 1.5 g’s up. 

 (2) The APU fuel line must be routed through the main deck floor beams just outboard of BL 0 to minimize potential for all types of 

penetration (including rotor burst, wheels up landing impact, etc). 

 (3) Occupants must be located no less than 72 feet forward of the forward-most potential penetration location in the APU fuel hose. 

 

Damage Tolerance and Fatigue Evaluation of Structure 

14 CFR 25.571(a) and (b) – Wing, Empennage, Fuselage, Floors and Doors

The following design features must be incorporated in the type design (reference § 25.571(a) and (b), Amendment 25-86). In lieu of 

incorporating the following design features, compliance to § 25.571(a) and (b), Amendment 25-120, may be shown. 
A20WE 74 

 

XVI. Model 747-8 (cont’d)

(1) For the 747-8 structure, an evaluation of the existing damage tolerance analysis (DTA) inspection program identified in the

Supplemental Structural Inspection Document (SSID) must be performed for any required changes due to loads, geometry changes, 

material changes, etc. The resulting inspection requirements for the 747-8 must be included in Section 9 (Airworthiness Limitations) 

of the Boeing Maintenance Planning Document (MPD) D621U400 in accordance with § 25.571(a)(3) at Amendment 25-120. 

 (2) The above evaluation must include loading magnitudes and loading spectra which are developed in accordance with § 25.571 at 

Amendment 25-120. This includes usage of the 1.15 factor for pressure acting alone in accordance with § 25.571(b)(5) at 

Amendment 25-120. 

 (3) Maintenance instructions must be based on in-service data and fatigue testing to ensure freedom from widespread fatigue damage. 

Production Basis: Production Certificate No. 700 has been issued to The Boeing Company. 

Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be 

 installed in the aircraft for certification. 

NOTES APPLICABLE TO SECTION XV MODEL 747-8F and SECTION XVI MODEL 747-8 ONLY: 

NOTE 1. A current Weight and Balance Manual including a list of equipment included in the certificated empty weight and loading

instructions must be in each aircraft at the time of original airworthiness certification and at all times thereafter except in the 

case of an operator having an approved weight control system. 

NOTE 2. Airplane operation must be in accordance with the FAA Approved Airplane Flight Manual. All placards required by either

the FAA Approved Airplane Flight Manual, the applicable operating rules or the certification basis must be installed in the 

airplane. 

NOTE 3 The FAA approved Airworthiness Limitations Section of the Instructions for Continued Airworthiness are referenced in 

Maintenance Planning Data Document (MPD) Section 9 - Airworthiness Limitations and Certification Maintenance 

Requirements; Boeing Document D011U721-02. The Airworthiness Limitations section is FAA-approved and specifies 

maintenance required under 14 CFR 43.16 and 91.403 of the Federal Aviation Regulations, unless an alternative program 

has been FAA approved. The following documents are the FAA approved requirements to comply with 14 CFR 25.1529, 

43.16 and 91.403: 

 

 D011U721-02-01, 747-8/8F Airworthiness Limitations (AWLs) 

 D011U721-02-02, 747-8/8F Airworthiness Limitations (AWLs) - Line No. Specific 

 D011U721-02-03, 747-8/8F Certification Maintenance Requirements (CMRs) 

 D011U721-02-04, 747-8/8F Special Compliance Items (SCls)/Airworthiness Limitations 

...-END-.....