# TCDS 4A26: The Boeing Company

- Type: Type certificate data sheet
- Status: Current
- Holder: The Boeing Company
- Revision: 11
- Revised: July 30, 1984
- Product: Aircraft, Large Airplane
- Certification basis: CAR 4b
- Registered aircraft: 8, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/ce/5e/ce5e0733bf9faff2645fab3417b4136512b858999103150769a9a2d31f0138ff
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/1BA4297B003B30A88525672400607E05.0001
- Page: https://openairdocs.org/tcds/4A26

## Models (4)

As the data sheet lists them.

- 707-300B Series
- 707-400 Series
- 707-300 Series
- 707-300C Series

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21
Rev No. 11 10 11 10 10 10 10 11 11 11 11 10 10 10 10 10 10 11 11 11 11
Reformatted 12/93.
DEPARTMENT OF TRANSPORATION
FEDERAL AVIATION ADMINISTRATION
4A26
Revision 11
 BOEING
707-300    Series
707-400    Series
707-300B   Series
707-300C   Series
July 30, 1984
TYPE CERTIFICATE DATA SHEET NO. 4A26
This data sheet which is a part of type certificate No. 4A26 prescribes conditions and limitations under which the product for which
the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations.
Type Certificate Holder THE BOEING COMPANY
Renton, Washington
I - Model 707-300 Series (Transport aircraft), Approved July 15, 1959
 Model Serial Nos. Eligible
 707-321 17592 thru 17608, 18083 thru 18085
 707-328 17613 thru 17622, 17918 thru 17924, 18245 thru 18247, 18375
 707-329 17623 thru 17627, 18374, 18460
 707-331 17673 thru 17690
 707-344 17928, 17929, 17930
Engines 4 Pratt and Whitney Turbojet JT4A-9, -1, -11, -12
(See NOTE 9 for interchangeable engine combinations.)
Fuel See NOTE 10.
Engine limits JT4A-9, -10 JT4A-11, -12
Takeoff static thrust, standard day,
  sea level conditions (5 min.) lb. 16,800 17,500
Maximum continuous static thrust, standard
  day, sea level conditions, lb. 13,500 14,900
Maximum permissible engine rotors operating speeds:
  Low pressure compressor  (N1), r.p.m.  7,060  7,160
  High pressure compressor (N2), r.p.m.  9,135  9,355
Maximum permissible turbine outlet gas temperatures:
  Takeoff (5 min.) (635°C) 1175°F (655°C) 1211°F
  Maximum continuous (516°C)   960°F (560°C) 1040°F
  Maximum for acceleration (2 min.) (635°C) 1175°F (655°C) 1211°F
  Starting maximum gas temperature
Ground (450°C)   842°F (450°C)   842°F
In Flight (475°C)   887°F (475°C)   887°F
Maximum permissible oil inlet temperature (121°C) 250°F (121°C) 250°F

4A26
Page 2
Maximum permissible air bleed extractions of total JT4A-9, -10 JT4A-11, -12
  engine air flow:
  High pressure compressor
    From idle to maximum continuous 5.5% 5.5%
    Takeoff 1.5% 1.5%
  Low pressure compressor
    From idle to maximum continuous 2.00% 2.00%
    Takeoff 1.65% 1.65%
Maximum permissible mechanical extraction 150 hp. 150 hp.
Thrust Setting:
  The appropriate thrust setting curve, (EPR or Pt7), in the Airplane Flight Manual must be used for control
  of engine thrust.
Airspeed limits (AIS) Vmo (Maximum Operating) MPH KTS
  at Sea Level 390 339
  at 5,000 ft. 396 344
  at 10,000 ft. 404 351
  at 15,000 ft. 413 359
  at 20,000 ft. 425 369
  at 24,900 ft. 435 378
Mmo (Maximum Operating)
 at 25,000 ft. and above (M = 0.887)
Va  (Maneuvering) MPH KTS
at sea level 287 249
at 20,000 ft. 299 260
at 37,700 ft. 331 287
Straight line variation between points shown.
Ma  (Maneuvering)
at 37,700 ft. and above (M - 0.887)
Vfe (Flaps Extended) Maximum Flap Defection    MPH KTS
    (Flaps not to be 10° 265 230
  extended above 20° 252 218
  20,000 ft.) 30° 238 207
50° 209 181
Vlo (Landing Gear Operating)
at sea level to 30,000 ft. 310 269
at 30,000 ft. to 35,000 ft. 322 280
Mlo (Landing Gear Operating
  at 35,000 ft. and above (M = 0.825)
Vle (Landing Gear Extended)
at sea level to 30,000 ft. 367 319
Mle (Landing Gear Extended)
at 30,000 ft. and above (M = 0.825)
Vdco (Dump Chute Operation)
at sea level to 42,000 ft. 275 239
Vdce (Dump Chute Extended)
at sea level to 36,000 316 274
Mdce (Dump Chute Extended)
at 36,000 ft. and above (M = 0.825)

4A26
Page 3
Vmca (Air Minimum Control Speed)
(Sea Level + 15°C) MPH KTS
JT4A-11, -12 T.O. Thrust 135 117
JT4A-9, -10 T.O.  Thrust 132 115
JT4A-11, -12 Limited Thrust 132 115
Mmcg (Ground Minimum Control Speed)
(Sea Level + 15°C) MPH KTS
JT4A-11, -12 T.O. Thrust 131 114
JT4A-9, -10 T.O.  Thrust 128 111
JT4A-11, -12 Limited Thrust 128 111
C.G. range The nose gear retraction moment is 22,500 in.lb. and moves C.G. forward.  The main gear
 (Landing Gear Extended) retracts parallel to the wing reference axis; hence, has no effect on the airplane
longitudinal C.G.
3 1 0
2 9 0
2 7 0
2 5 0
2 3 0
2 1 0
1 9 0
1 7 0
1 5 0
1 6 . 0 1 7 . 5 1 9 .0 2 1 .0 2 3 .0 3 5 . 03 3 . 03 1 .02 9 .02 7 .02 5 .0
C . G. % M A C
7 0 7 -3 0 0 and 7 0 7 -4 0 0 C . G . D iagram
T ak eo f f Lim it O n ly
En v elo p e Ex t en s io n f o r 7 0 7 -4 0 0 an d 7 0 7 -3 0 0 Series
airc raf t eq u ip p ed w it h s t ren g t h lan d in g g ear (See N o t e 8 ).
Maximum weights -300 Series with -300 & -400
Restricted Landing  -300 & -400 Series  with Heavy Gear &
Gear (See NOTE 8)   with Heavy Gear   7 Cell Center Tank
Maximum ramp weight 302,000 lb. 316,000 lb. 316,000 lb.
Maximum flight weight
  with 30° flaps 301,000 lb. 311,000 lb.* 316,000 lb.**
 Maximum flight weight
  flaps up 300,000 lb. 310,000 lb. 310,000 lb.*
316,000 lb.**
Maximum flight weight at
  which the outboard
  auxiliary fuel
  tanks can be empty 275,000 lb. 275,000 lb. 275,000 lb.
Maximum landing weight 198,500 lb. 207,500 lb. 207,500 lb.
Maximum zero fuel weight 190,000 lb. 190,000 lb. 190,000 lb.
*   Basic fuel management
** Alternate fuel management

4A26
Page 4
Minimum crew For any flight, 3 persons (Pilot, Copilot, Flight Engineer).  When in the
mixed passenger/cargo configuration one flight attendant is required in the
passenger compartment.
Maximum passengers 179 limited by emergency exit requirements.  Approved for 189 passengers if
equipped with four (4) inflatable escape chutes installed in accordance with FAA
approved type design data.  (Review case no. 5 dated July 17, 1963.)
Maximum baggage Maximum Maximum Moment
Body Load Concentration Capacity Arm
Compt. Station lb./in. p.s.f. lb. inches
Fwd. Belly 400-600B + 18 48 150 14300 + 389
Aft Belly 960-1060 50 150 7000 +1030
Aft Belly 1060-1200 35 150 4900 +1170
Aft Belly   1200-1300        20 150 2000 +1290
Fuel capacity (See NOTE 1(c) for information relative to unusable fuel; NOTE 1(e) for required
fuel usage procedure; NOTE 1(f) for undumpable fuel.)
The maximum fuel capacity listed below must not be exceeded.  For numbers
in parentheses, see NOTE 16.  For other fuel C.G. locations with partially filled tanks,
see appropriate Boeing Weight and Balance Manuals listed under NOTE 14.
Nominal Capacity Maximum Capacity
               Usable fuel in tank (See NOTE 17) Moment Arm
Tank U.S. Gal. per Tank Pounds/Tank Inches
No. 1 & No. 4 Reserve   439   3,029 1101.7
No. 1 & No. 4 Main 2,307 15,918 933.4
(2,323) (16,029) (934.6)
No. 2 or No. 3 Main 4,065 28,049 788.4
(4,069) (28,076) (788.4)
7-Cell Center 10,193 70,332 706.9
4-Cell Center (707-300
  Series and 707-437 only;
                          See NOTE 13) 7,640 52,716 728.6
TOTAL    7-Cell center 23,815 164,324
(23,855) (164,600)
TOTAL    4-Cell center 21,262 146,984
Whenever fuel is loaded into the center section fuel tank, drain the sump of water prior to flight.

4A26
Page 5
Oil capacity   Tank Total Total Moment Arm
                                Gal.               Lb.                  In.
                  No. 1 tank 8.3 64.0 886 * (a)  The oil tank capacity
                  Oil Cooler .4 3.2 862 (8.3 gal.) as required per
               Engine 1.5 11.0 898 CAR 4b.440(b) is based on a
               Oil lines 1.4 10.0 871 maximum engine oil consumption
of 0.4 gal. per hr.  Any increase
                  No. 2 tank 8.3 64.0 702    in engine oil consumption above
               Oil cooler .4 3.2         678    this rate will reduce the operating
               Engine 1.5 11.0         714    range of the airplane.
               Oil lines 1.4 10.0         688
No. 3 tank 8.3 64.0         702 * (b)  Using the bullseye or sight
Oil cooler .4 3.2         678 glass as a level for servicing
Engine 1.5 11.0 714 the oil tank will result in a
Oil lines 1.4 10.0 688 lesser oil quantity and will
reduce the operating range of the
No. 4 tank 8.3 64.0 886 airplane.
Oil cooler  .4  3.2 862
                  Engine 1.5 11.0 898
Oil lines 1.4 10.0 871
Total 46.4 352.8
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 appropriate Weight and Balance Manuals in NOTE 14 contain lists of equipment
as well as optional equipment installations approved by the FAA.
II - Model 707-400 Series (Transport Aircraft), approved February 12, 1960
Model Serial Nos. Eligible
707-430 17718, 17719, 17720, 17721, 18056
707-436 17703-17717, 18411-18413
707-437 17722-17724, 18055, 18414, 18415
707-441 17905, 17906, 18694
707-458 18070, 18071, 18357
707-465 18372, 18373
Engines 4 Rolls Royce Turbojet Conway Mark 508 (R.CO-12)
Fuel Fuel designation: British DERD 2482, 2486, 2494
American JP-1 (U.S. MIL-F-5616)
JP-4 (U.S. MIL-F-5624C)
Canadian 3-CP-23D, 3-CP-228
Engine limits Takeoff static thrust, standard day, sea level
conditions (5 min.), lb. 17,500
Maximum continuous static thrust, standard day, sea
level conditions lb. 14,625
Maximum permissible engine rotors operating speeds:
  Low pressure compressor  (N1), r.p.m.                        7,560
  High pressure compressor (N1), r.p.m. 10,500

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Page 6
Maximum permissible turbine outlet gas temperatures:
  Takeoff (5 min.)                    (675°C) 1247°F
  Maximum continuous                  (600°C) 1112°F
  Starting maximum gas temperature (675°C) 1247°F
  Maximum with reverse thrust selection (675°C) 1247°F
Maximum permissible oil inlet temperature (105°C)  221°F
Maximum permissible air bleed delivery for engine and
  aircraft services at sea level conditions
  as percent of no bleed low pressure compressor
  mass flow:
Takeoff rpm
  High pressure compressor bleed                        5.6%
  Low pressure compressor bleed                         1.1%
Maximum continuous rpm
  High pressure compressor bleed                        5.8%
Airspeed limits 707-400 series aircraft Vmo Airspeed Limits are identical to those listed in the
applicable section Part I of this Data Sheet except the 707-436 and 707-465 Vmo limit
at 23,300 feet is 430 mph (375 kts) and the Mmo limit is .852 at 23,300 feet and above.
707-400 series aircraft, Va, Ma, Vfe, Vlo, Mlo, Vle, Mle, Dump Chute Extended and
Dump Chute Operation Airspeed Limits are identical to those listed in the applicable
section, PART 1, of this Data Sheet.
Vmca (Air Minimum Control Speed) MPH KTS
     (Sea Level and 15°C) 139 121
Vmcg (Ground Minimum Control Speed) 145 126
C.G. range The 707-400 series aircraft C.G. Range and Landing gear retraction moment are
  (Landing gear extended) shown in applicable Section, PART I, of this Data Sheet.
Maximum weights 707-400 series aircraft Maximum Weights are shown in the applicable section, PART I,
of this Data Sheet.
Minimum crew For any flight, 3 persons (pilot, copilot, flight engineer)
Maximum passengers 179 limited by emergency exit requirements.  Approved 189 passengers if equipped
with four (4) inflatable escape chutes installed in accordance with FAA approved
type design data.
Maximum baggage 707-400 series aircraft Maximum Baggage is identical to that shown in the applicable
section, PART I, of this Data Sheet. 
Fuel capacity 707-400 series aircraft Fuel Capacity is shown in the applicable Section, PART I, of this
Data Sheet.

4A26
Page 7
Oil capacity Moment Arms
       Tank gal.              lb.               inches
No. 1
  Oil in engine tank 3.79 29.15 853.6
  Oil in C.S.D. tank       1.43 11.00 853.6
 *Oil in system 1.44 11.07 896.4   *Oil in system includes oil in
engine, oil cooler, constant
No. 2 speed drive and lines.  The
  Oil in engine tank 3.79 29.15 670.4   oil tank capacity (14.45 imp.
  Oil in C.S.D. tank       1.43 11.00 670.4 pints) as required per CAR
4b.440(b) is based on a maximum
  Oil in system 1.44 11.07 712.6 engine oil consumption of 0.9
pint per hour.  Any increase in
No. 3 engine oil consumption above
  Oil in engine tank 3.71 28.53 670.4   this rate will reduce the
  Oil in C.S.D. tank       1.48 11.38 670.4 operating range of the airplane.
  Oil in system 1.44 11.07 712.6
No. 4
  Oil in engine tank 3.71 28.53 853.6
  Oil in C.S.D. tank       1.48 11.38 853.6
  Oil in system 1.44 11.07 896.4
TOTAL                     26.58   204.40
Required equipment The basic required equipment as prescribed in the applicable Airworthiness Regulations
(See Certification Basis) must be installed in the aircraft for certification.  Appropriate
Weight and Balance Manuals in NOTE 14 contain lists of equipment as well as optional
equipment installations approved by the FAA.
III  707-300B Series (Transport Aircraft) approved May 31, 1962
Model
707-312B 19737-19739
707-321B 18335-18339, 18838-18842, 18956-18960, 19264-19266, 19275-19278,
19361-19366, 19374, 19376, 19378, 19693-19699, 20019-20034
707-323B 20170-20179
707-328B 18456-18459, 18685-18686, 18941, 19291
707-330B 18462, 18463, 18819, 18923, 18826-18831, 19315-19316
707-331B 18405-18409, 18764, 18913-18918, 18978-18985, 19224-19227,
19570-19573, 20058-20067
707-336B 20456, 20457
707-337B 18708, 18873, 19247
707-344B 18891, 19133
707-351B 18584-18586, 18693, 18710, 19633-19636
707-353B 18461, 20630
707-358B 19004, 19502, 20097
707-359B 19741, 20340
707-382B 18961, 18962, 19740, 19969, 20136, 20297, 20298
707-384B 20035, 20036
707-387B 19238-19241
707-3J6B 20714-20716
707-3L6B 21049
Engines 4 Pratt & Whitney Turbofan JT3D-3, -3B, -7, * or JT3D-1, -1MC6 and
-1MC7 (See NOTE 9 for Interchangeable engine combinations.)
* (300C only)
Fuel See NOTE 10

4A26
Page 8
Engine limits JT3D-1;
Takeoff static net thrust (Std. day),   -1MC6: -1MC7 JT3D-3  JT3D-3B JT3D-7
  lb., at sea level, dry (5 minutes) 17,000 18,000 18,000 19,000
  Take off wet (2 1/2 minutes) 17,000 18,000 18,000 19,000
Maximum continuous static thrust
(Std. day), lb., at sea level              14,500 16,400 16,400 17,200
Maximum permissible engine rotors
  operating speeds:
  Low pressure compressor  (N1), r.p.m. 6,800 6,800 6,850 6,850
   High pressure compressor (N2), r.p.m. 10,200 10,250 10,250 10,250
  Maximum EPR values shown in the airplane flight manual shall not be exceeded.
Maximum permissible turbine outlet gas temperatures:
JT3D-1;
-1MC6; -1MC7 JT3D-3; -3B   JT3D-7
Takeoff (5 minutes) (530°C) 986°F (555°C) 1031°F) (575°C) 1067°F
Maximum continuous (460°C) 860°F (490°C)  914°F) (510°C)  950°F
Maximum for acceleration
  (2 minutes) (530°C) 986°F (555°C) 1031°F) (575°C) 1067°F
Starting (450°C) 842°F (450°C)  842°F) (450°C)  842°F
 Maximum permissible air bleed extractions of total
  engine air flow:  Typical
  High pressure compressor
     From idle to maximum continuous 5.5%
    At takeoff 2.0%
  Low pressure compressor
    From idle to maximum continuous 2.0%
    At takeoff 2.2%
Maximum permissible oil inlet temperature:  Typical
  Continuous operation (132°C) 270°F
  Ten minutes operation (143°C) 290°F
Airspeed limits (IAS) Vmo (Maximum Operating) MPH KTS
  at sea level 432 375
  at 10,000 ft. 439 381
  at 15,000 ft. 443 385
  at 20,000 ft. 449 390
  at 23,000 ft. 454 394
Mmo (Maximum Operating)
  at 23,000 ft. and above     (M = 0.887)
Va  (Maneuvering) MPH KTS
  at sea level 311 270
  at 10,000 ft. 319 277
  at 20,000 ft. 329 286
  at 30,000 ft. 346 300
  at 35,000 ft. 356 309
Straight line variation between points shown
Ma  (Maneuvering)
  at 35,000 ft. and above     (M = 0.887)

4A26
Page 9
Vfe (Flaps Extended)  Maximum Flap Deflection  MPH   KT   MPH*   KT
  (Flaps not to be 14° 260 226 242 210
  extended above 17° 257 223 242 210
  20,000 ft.) 25° 248 215 242 210
50° 225 195 225 195
*Aircraft without Boeing Service Bulletin No. 1826 installed
Vlo (Landing Gear Operation)  MPH KTS
  at sea level to 30,000 ft. 311 270
  at 30,000 ft. and above 322 280
Mlo at 34,400 ft. and above             (M - 0.830)
Vle (Landing Gear Extended) 369 320
Mle (Landing Gear Extended)              (M - 0.830)
Vdco (Dump Chute Operation) 276 240
Mdco (Dump Chute Operation)              (M = 0.830)
Vdce (Dump Chute Extended) 317 275
Mdce (Dump Chute Extended)              (M = 0.830)
Landing Light Extended
  at sea level to 25,000 ft. 441 383
  at 25,000 ft. and above              (M = 0.887)
Vmca (Air Minimum Control Speed)
(Sea level + 15°C)
JT3D-3, -3B AND -3B extended temperature            133 116
JT3D-38 Extended temperature and improved cowls     135 117.5
JT3D-7                                              139 121
Vmcg (Ground Minimum Control Speed)
(Sea level = 15°C)
JT3D-3 133 116
JT3D-3B, -3B extended temperature and -7 139 121
JT3D-3B Extended temperature and improved cowls     143 124

4A26
Page 10
C.G. range The nose gear retraction moment is 22,500 in.lb. and moves C.G. forward.  The main gear retracts parallel
to the wing reference axis; hence, has no effect on the airplane longitudinal C.G.
1 4 0
3 4 0
3 2 0
3 0 0
2 8 0
2 6 0
2 4 0
2 2 0
2 0 0
1 8 0
1 6 0
1 6 . 0 1 7 . 5 1 9 .0 2 1 .0 2 3 .0 3 5 . 03 3 . 03 1 .02 9 .02 7 .02 5 .0
7 0 7 -3 0 0 B In c reased Gro ss W eig h t an d 7 0 7 -3 5 1 B o n ly .
Lan d in g W eig h t En v elo p e 7 0 7 -3 0 0 B In c reased G ro ss W eig h t
w it h 7 0 7 -3 0 0 C M ain Lan d in g G ear In st alled . See N O T E 1 2 .
C . G. % M A C
7 0 7 -3 5 1 B
7 0 7 -3 0 0 B In c reased Gro ss W eig h t w it h 7 0 7 -3 0 0 C
M ain Lan d in g Gear in st alled . See N o t e 1 2 .
7 0 7 -3 0 0 B C . G. D iagram
Maximum weights (For spare engine carry, see NOTE 18)
Basic Increased Gross Increased Gross Weight
Aircraft Weight Aircraft Aircraft (See NOTE 12)
Maximum Taxi (Ramp) weight (lb) 328,000 328,000 336,000
*Maximum flight weight (lb)
Flaps Down 327,000 328,000 335,000
Flaps Up 318,000 326,000 326,000
(322,000) (328,000) (331,000)
With outboard reserve tanks
  empty 280,000 285,000 285,000
Maximum landing weight (lb.) 207,000 207,000 247,000
Structural design zero fuel 190,000 195,000 195,000
See NOTE 1(e) for necessary fuel management for flaps up flight at weights shown in parenthesis.
*At sea level to 11,500 ft., maximum flight weight must be reduced at altitudes above 11,500 ft.
  at the rate of 1000 lb. per 3500 ft.
Minimum crew For any flight, 3 persons (Pilot, Copilot, Flight Engineer)
Maximum passengers 179 limited by emergency exit requirements.  Approved for 189 if equipped with four (4)
inflatable escape chutes installed in accordance with FAA approved type design data.
Maximum baggage 707-300B Series aircraft maximum baggage is identical to that shown in the applicable
section Part I of this Data Sheet.
For Model 707-351B Main Deck Cargo Compartment Limitations, see Weight and Balance
Document D6-10949.1.
Fuel capacity See NOTE 1(c) for information relative to unusable fuel; NOTE 1(e) for required fuel usage
procedure; NOTE 1(f) for undumpable fuel.
The maximum fuel capacity listed below must not be exceeded.  For other fuel C.G.
locations with partially filled tanks, see appropriate Boeing Weight and Balance Manuals
listed under NOTE 14.

4A26
Page 11
NOMINAL CAPACITY MAX. CAPACITY MOMENT
Usable fuel in tank (7.1 lb/gal) ARM
TANK U.S. Gallons Pounds
Per Tank Per Tank Inches
No. 1 or No. 4 Reserve 439 3,117 1,101.7
No. 1 or No. 4 Main 2,323 16,493 934.6
No. 2 or No. 3 Main 4,069 28,890 788.4
7-Cell Center 10,193 72,370 728.6
Total 23,855 169,370
Whenever fuel is loaded into the center section fuel tank, drain the sump of water prior to
flight.
Oil Tank capacity The system oil capacities are given in the appropriate Weight and Balance Control Manuals
listed under NOTE 14.
Engine Oil Volume Moment Arm
  Tank No. Location   Gal.    (In.)
1 Outboard Port 6.0 gal. 866.9
2 Inboard Port 6.0 gal. 684.1
3 Inboard Starboard 6.1 gal. 684.1
4 Outboard Starboard 6.1 gal. 866.9
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 appropriate
Weight and Balance Manuals in NOTE 14 contain lists of all required equipment as well as
optional equipment installations approved by the FAA.
IV - Model 707-100C Series (Transport Aircraft), approved April 30, 1963
Model Serial Nos.
707-307C 19997-20000
707-309C 20261, 20262
707-311C 19789
707-320C 20008, 20275, 20487, 20488
707-321C 18579, 18580, 18591, 18714-18718, 18765-18767, 18790, 18824-18826,
  19267-19274, 19367-19373, 19375, 19377, 19379, 20016-20018
707-323C 18689-18692, 18938-18940, 19235-19237, 19380-19384, 19515-19519,
  19581-19589, 19574-19577, 20087-20089
707-324C 18886-18887, 19177, 19178, 19350-19353, 19869-19871
707-327C 19104-19108, 19440, 19529-19531
707-328C 18881, 19292, 19521, 19522-19524, 19916, 19917
707-329C 18890, 19162, 19211, 19990, 20198-20200
707-330C 18932, 18937, 19317, 20123, 20124, 20395
707-331C 18711-18713, 18756, 18757, 19213-19214, 19435, 19566, 19567, 20068, 20069
707-336C 18924, 18925, 19498, 19843, 20474, 20475, 20517
707-337C 19248, 19988
707-338C 18808-18810, 18953-18955, 19293-19297, 19621-19630
707-340C 19284-19286, 19866
707-341C 19320, 19321-19322
707-344C 19705, 19706, 20110, 20230, 20283
707-345C 19840-19842
707-347C 19963-19967, 20315-20319
707-348C 18737, 18880, 19001, 19410
707-349C 18975, 18976, 19354, 19355
707-351C 18746-18748, 18888, 18889, 18921, 18922, 18964, 19034, 19163, 19164, 19168,
  19209-19211, 19263, 19412, 19434, 19443, 19631, 19632, 19773 - 19777
707-355C 19417, 19664, 19986
707-358C 20127, 20301

4A26
Page 12
707-360C 19736, 19820
707-365C 19416, 19590
707-366C 19844, 19845, 20341, 20342, 20760-20763, 20919, 20920
707-368C 19809, 19810, 21081, 21103, 21104, 21261, 21367, 21368
707-369C 20084-20086, 20546, 20547
707-370C 20889-20891
707-372C 20076, 20077
707-373C 18582, 18583, 18707, 18709, 18738, 18991, 19179, 19 441, 19442, 19715, 19716
707-379C 19821, 19822
707-384C 18948-18950, 19760
707-385C 19000, 19433, 20522
707-386C 20287, 20288, 20741, 21396
707-387C 19961, 19962
707-396C 20043
707-399C 19415, 19767
707-3B4C 20224, 20225, 20259, 20260
707-3D3C 20494, 20495
707-3F5C 20514, 20515
707-3F9C 20474, 20669, 21428
707-3H7C 20629
707-3J6C 20718-20723
707-3J8C 20897, 20898
707-3J9C 20830-20835, 21123-21129, 21475
707-3K1C 20803-20805, 21651
707-3L5C 21228
707-3L6C 21096
707-3M1C 21092
707-3P1C 21334
Engines: See Applicable Section in Part III of This Data Sheet.
Fuel: See Applicable Section in Part III of This Data Sheet.
Engine limits See Applicable Section in Part III of This Data Sheet.
Airspeed limits See Applicable Section in Part III of This Data Sheet.
C.G. range The nose gear retraction moment is 23,800 in./lb. and moves the C.G. forward.  The main
 (Landing gear extended) gear retracts parallel to the wing reference axis and has no effect on the
airplane longitudinal C.G.
3 4 0
3 2 0
3 0 0
2 8 0
2 6 0
2 4 0
2 2 0
2 0 0
1 8 0
1 6 . 0 1 7 .0 1 9 .0 2 1 .0 2 3 .0 3 5 . 03 3 . 03 1 .02 9 . 02 7 .02 5 .0
C . G. % M A C
7 0 7 -3 0 0 C C . G. D iagram
T his f orw ard C. G. env elope m ay be used
w hen c arg o is f orw ard o f St at io n 9 6 6 .
Inc reased Gross W eig ht A irc raf t

4A26
Page 13
Cargo loaded on the main cargo deck may result in an asymmetrically loaded airplane;
that is, more weight may be on the right hand side than on the left hand side of the airplane
or vice versa.  The asymmetrical moment (resulting from an off-loaded airplane) must not
exceed 864,000 inch lbs.
Maximum weights See NOTE 1(e) for necessary fuel management for flight with flaps up at weights shown
in parentheses.  For spare engine carry, see NOTE 18.
Basic Increased Gross Model 707-338C
Aircraft Weight Aircraft (See NOTE 15)
Maximum Taxi Weight (lb)
  Passenger Configuration 328,000 336,000 336,000
  Other Configurations 328,000 332,000 334,000
  *Maximum flight weight (lb)
    Flaps Down 327,000 332,000 334,000
335,000
(Pax Config)
    Flaps Up
      Passenger Configuration 322,000 326,000 325,000
   (331,600) (331,000)
       Other Configurations 322,000 325,000 325,000
(330,000) (331,000)
Maximum Weight at which Outboard
  Auxiliary tank can be empty (lb.) 280,000 285,000 285,000
Maximum Landing Weight (lb.) 247,500 247,500 247,500
Zero Fuel Weight (lb.) 230,000 230,000 230,000
220,000 220,000
(Pax Config) (Pax Config)
*At sea level to 11,500 ft., maximum flight weight must be reduced at altitudes above 11,500 ft. at the rate
of 1000 lb. per 5000 ft.
Minimum crew For any flight, three persons (Pilot, Copilot, Flight Engineer).
Maximum passengers 195 limited by emergency exit requirements.  219 if compliance with FAR 25.2 is
shown.  See Note 19.

4A26
Page 14
Maximum baggage For all passenger configuration:  See applicable section in Part I of this Data Sheet.
For cargo or split passenger/cargo configurations:  See the appropriate Weight and
Balance Manuals listed under NOTE 14.
Maximum cargo For cargo restrictions, see the appropriate Weight and Balance Control Manuals,
listed under NOTE 14.
Fuel capacity For maximum capacity fuel weights and other fuel data, see applicable section in Part III
of this Data Sheet.
For fuel C.G. locations with partially filled tanks, see the appropriate Weight and Balance
Manuals listed under NOTE 14.
Oil capacity For oil capacities and related moment arms, see the applicable section in Part III of this
Data Sheet.
The system oil capacities are given in the appropriate Weight and Balance Control
Documents listed under NOTE 14.
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 appropriate
Weight and Balance Manuals listed under NOTE 14 contain a list of all the required
equipment as well as optional equipment installations approved by the FAA.
Data Pertinent to All Models
Datum All stations noted in the data sheet are Body Stations unless identified specifically as
moment arms.  Drawing 69-10819, defines Body Stations and moment arms.  For weight
and balance purposes, datum is 30 in. aft of nose (moment arm 0).
Horizontal distance of datum to average wing jack point is 799.05 in.
MAC 272.3 (L.E. of MAC is Body Station 763.0).
Leveling means A plumb-bob attachment and leveling provision scale are provided in left wheel well.
Maximum operating altitude 42,000 ft.
Other operating The aircraft must be operated in accordance with the FAA approved Airplane
  limitations Flight Manual.
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 in accordance with the following FAA
approved data:
Surfaces Installation Dwg.
Aileron and Spoiler 50-8701
Aileron Trim 50-8705
  Inboard Aileron Balance Panel Tolerances 50-73133
  Outboard Aileron Balance Panel Tolerances 50-73134
Speed Brakes (Spoilers) 50-8716
Elevator 50-8702
Elevator Balance Panel Tolerances 65-6088
Stabilizer Trim 50-8704
Rudder 50-8703
Rudder Trim 50-8706
Rudder Balance Panel Tolerances   65-14035
Wing Flap 50-8707

4A26
Page 15
Service information Boeing Report D6-2962, "Structural Repair Manual," is FAA approved. Service
Bulletins and other service information, when FAA approved, will carry a statement
to that effect.
Certification basis CAR 4b dated December 1953, Amendments 4b-1, 4b-2 and 4b-3 thereto;the
Special Conditions and the provisions amendments listed in Attachment A of CAA
letter to Boeing dated October 30, 1957; and the provisions of Item 2 of Special Civil
Air Regulation No. SR-422B.
Type Certificate No. 4A26 issued July 15, 1959.
Date of Application for Type Certificate May 15, 1956.
Compliance with the following optional requirements has been established:
Exemptions: Model No. Exemption No.
707-300C 246
707-300C 269
All Models 279
707-300C 420
707-354C 584
Ditching Provisions -  4b.361 (See NOTE 11)
Ice Protection Provisions -  4b.640
Production basis Production Certificate No. 700
NOTE 1. Weight, Balance, Fuel Loading and Usage Data
(a) A current weight and balance report, including list of equipment considered as part of the certificated empty
weight, and loading instructions must be in each aircraft at the time of original certification and at all times
thereafter except in the case of operators having an approved weight control system.
(b) The airplane must be loaded so the C.G. is within the specified limits at all times with the effects of fuel use
and movement of crew and passengers from their assigned positions being considered.
(c) The "drainable unusable fuel" is that amount of fuel in the tanks which is unavailable to the engines under
critical flight conditions as defined in CAR 4b.416. This drainable unusable fuel does not include the "tank
trapped fuel" or "line unusable fuel", which is the unusable fuel retrained in the fuel feed and fuel dump lines.
The "total unusable fuel" and line unusable fuel must be included in the airplane empty weight or be suitably
accounted for in the airplane weight and balance report.  The total amount of unusable fuel (in gallons) is as
follows:
No. 1 & 4 No. 1 & 4 No. 2 & 3  Center Wing Fuel Airplane Total
                       Res. Tank Main Tank Main Tank 4-cell 7-cell Line 4-cell 7-cell
Tank Trapped Fuel 1.31 1.77 2.84 6.67 10.50 -- 12.59 16.42
Drainable Unusable 0.16 10.14  9.26 17.49 17.49  -- 37.05 37.05
  Fuel
Total Unusable 1.47 11.91 12.10 24.16 27.99 10.72 60.36 64.19
  Fuel
(d) "System oil" is defined as that amount of oil required to fill the oil system and tanks to the tank outlets to
the engines.  System oil and all hydraulic fluid must be included in the airplane empty weight or be suitably
accounted for in the airplane weight and balance report.  See appropriate Being document listed under NOTE 14.
(e) Fuel capacity and usage procedures are dictated by structural design.  To preserve favorable wing bending
moments, the following shall apply:

4A26
Page 16
FUEL LOADING LIMITATIONS
  For 707-300/-400 Series
  1. Load main tanks 1, 2, 3, and 4 equally.
  2. If main tanks 1 and 4 are full and additional fuel is required, continue to load main tanks 2 and 3 to
required fuel quantity.
  3. If main tanks 1, 2, 3, and 4 are full and additional fuel is required, load outboard reserve tanks.
NOTE: For fuel loading flexibility, outboard reserve fuel may be carried when main tanks are less than
full; however, outboard reserve tanks and main tanks must always be full when center wing fuel
is loaded in excess of any included in maximum zero fuel weight.
  4. If all main and outboard reserve tanks are full and additional fuel is required, load center wing tank to
required fuel quantity.
NOTE: Center wing tank fuel may be substituted for payload in any quantity up to the maximum allowable
payload or to the center wing tank capacity, whichever is lower.
NOTE: Tanks selected for flight may be loaded simultaneously.
NOTE: For 707-321 aircraft
If partial loading of the reserve tanks is not desired, reserve tanks may be full and main tanks 2
and 3 off-loaded by no more than 4,800 lb. total.
For 707-300B and 707-300C Series
Load inboard main, outboard main and reserve tanks so that the resulting fuel load is symmetrical.
Interpolate between steps for intermediate fuel loads.
TOTAL MAIN MAIN RESERVE CENTER
FUEL LOAD TANKS 1 & 4 TANKS 2 & 3 TANKS 1 & 4 TANK
STEP      GALLONS       TOTAL GALLONS        TOTAL GALLONS        TOTAL GALLONS           GALLONS  
1  6,090 3,045 3,045
2  7,846 3,045 3,923 878
3 13,662 4,646 8,138 878
4 23,855 4,646 8,138 878 10,193
NOTE: Center tank fuel may be substituted for payload in any quantity up to the maximum allowable
payload (maximum zero fuel weight less airplane basic operating weight) providing the difference
in effect on balance is also accounted for.
NOTE: Tanks selected for flight may be loaded simultaneously.
FUEL USABLE LIMITATIONS
For 707-300/-400 Series
1. All center section fuel in excess of any included in the zero fuel weight must be used before the transfer
of outboard reserve fuel.
2. Airplane gross weight must not exceed 275,000 pounds if the outboard reserve tanks are empty.
3. Outboard reserve fuel must be transferred before landing.
4. Use tank-to-engine combination during all takeoffs and landings except as noted under Minimum Fuel
Go-Around Procedure.  (See Airplane Flight Manual)

4A26
Page 17
5. When center tank fuel is required for flight, it must be used after a minimum of 12,000 lbs. and before
a maximum of 17,000 lbs. (total) of main tank fuel has been expended for takeoff and climb to altitude.
6. When taxiing is conducted at gross weights in excess of 312,000 lbs., fuel must be drawn from the center
section tanks only.
7. Fuel Reserve must be retained in main tanks only.
For 707-300B Series (Excluding Increased G.W.Aircraft)
1. Airplane Gross Weight must be below 283,000 pounds before the transfer of outboard reserve fuel
can be initiated.
2. Airplane Gross Weight must not exceed 280,000 pounds with outboard reserve tanks empty.
3. Basic Fuel Management
(a) Use main tanks to respective engines for taxi, takeoff and landing, except for a minimum fuel
go-around in which case all boost pumps should be on and all manifold valves open.
(b) Center tank fuel in excess of any included in the zero fuel weight must be used after a
minimum of 12,000 lbs. up to a maximum of 17,000 lbs. (total) of main tank fuel has been
expended for takeoff and climb to altitude.
4. Alternate Fuel Management (Must be used at Flaps Up Flight Wt. above 318,000 lbs.)
(a) Use fuel from inboard main tanks and center section tank for taxi, takeoff and flight until a
minimum of 12,000 lbs. to a maximum of 16,000 lbs. of fuel is burned off.
(b) Revert to main tank to respective engine fuel usage until a minimum of 12,000 lbs. up to a
maximum of 17,000 lbs. (total) of equal main tank fuel is used before center tank fuel is to be
used to feed all four engines.
For 707-300C Series (Excluding Increased G.W. Aircraft)
1. Airplane Gross weight must be below 283,000 lbs. before transfer of outboard reserve tank fuel can be
initiated.
2. Airplane Gross weight must not exceed 280,000 lbs. when outboard reserve tanks are empty.  Also, the
fuel quantity in each outboard reserve tank plus the adjacent main tank must not be less than 12,500 lbs.
at flight gross weights above 280,000 lbs.
3. When center tank fuel is required for flight, it must be used after a maximum of 17,000 lbs. (total) of main
tank fuel has been expended for takeoff, climb an cruise.
4. Do not initiate transfer of reserve tank fuel until the fuel quantity in each outboard main tank is less than
12,000 lbs., and the airplane flight gross weight is less than 283,000 lbs.
5. Use tank-to-engine combinations during all takeoffs and landings except as noted under minimum fuel
go-around procedure (See Airplane Flight Manual).
For 707-300B and 707-300C Increased Gross Weight Series
1. Airplane gross weight must be below 288,000 lbs. before transfer of outboard reserve tank fuel can be initiated.
2. Airplane gross weight must not exceed 285,000 lbs. when outboard reserve tanks are empty.  Also, the fuel
quantity in each outboard reserve tank plus the adjacent main tank must not be less than 12,500 lbs. at flight
gross weights above 285,000 lbs.
3. Do not initiate transfer of reserve tank fuel until the fuel quantity in each outboard main tank is less than
12,000 lbs., and the airplane flight gross weight is less than 288,000 lbs.
4. When center tank fuel is less than 20,000 pounds and is required for flight, it must be used after a maximum
of 17,000 lbs. (total) of main tank fuel has been expended for takeoff, climb, and cruise.

4A26
Page 18
5. Basic Fuel Management
(a) Taxi, takeoff, climb, and cruise using fuel from main tanks to respective engines.
(b) Center tank fuel in excess of any included in Zero fuel weight must be used after a minimum of
12,000 lbs. up to a maximum of 17,000 lbs. of main tank fuel has been consumed.
6. Alternate Fuel Management (Must be used at Flaps up Flight Weights above 326,000 lbs.
for passenger configurations and at weights above 325,000 lbs. for other configurations.
(a) Taxi, takeoff, climb, and cruise using fuel from inboard tanks and center section tank.
(b) After a minimum of 12,000 lbs. of inboard tank and center section tank fuel has been consumed,
set up direct tank to engine feed or center tank to all four engines.  If main tank fuel is used, consume
a maximum of 17,000 lbs. of main tank fuel, then use center section tank fuel to feed all four engines.
(f) FUEL DUMPING
Tanks Undumpable Fuel
2 outboard main tanks 1234 Gal.
2 inboard main tanks 1120 Gal.
Center wing tank   250 Gal.
TOTAL 2604 Gal.
NOTE 2. The following placards must be installed in view of the flight crew:
(a)  Main Panel
Landing Gear
(Limit Speed - IAS)
707-300 and -400 Series 707-300B and -300C Series
Operating 269 knots - .83M 270 knots - .83M
Extended 319 knots  - .83M 320 knots - .83M
Flaps
(Limit Speed - IAS)
                           707-300B Series
707-300 and -400 Series 707-300B Series 707-300C Series Without S.B. 1826
10° - 230 knots 14° - 226 knots 14° - 226 knots  14° - 210 knots
20° - 218 knots 17° - 223 knots 25° - 215 knots  17° - 210 knots
30° - 207 knots 25° - 215 knots  50° - 195 knots  25° - 210 knots
50° - 181 knots 50° - 195 knots  50° - 195 knots
(b) Engineer's Panel
Fuel Dump Switches
Indicated Airspeed and Position Limits
1. 707-300 or 707-400 Series
Extending or Retracting Chutes * Dumping Fuel  *
  239 knots maximum (Flaps Up) 274 knots maximum (Flaps 0 - 30°)

4A26
Page 19
2. 707-300B and 707-300C Series
Extending or Retracting Chutes  *          Dumping Fuel  *
  240 knots maximum (Flaps up)       275 knots maximum (Flaps up)
* Refer to Section I of Flight Manual for Special Operating Procedures.
NOTE 3. Life-Limited Parts
The following parts are life-limited as shown below:
Part No. Part Allowable No. of Flights
5-86047 or 65-38056 Horizontal Stabilizer Pivot Fitting 200,000
5-89537  Elev. Aft Quadrant Assy. 200,000
5-98343 Quadrant support 200,000
NOTE 4. (707-300B/300C Series Aircraft) (Establish a procedure to insure that the engines will accelerate from idle to
takeoff thrust within eight seconds.)
NOTE 5. Replacement brake lining for 707-300C Series must meet Boeing Specification No. D10-60818, and for
707-300/-400/-300B Series, Boeing Specification No. D10-3379.
NOTE 6. Whenever fuel is loaded into the center section fuel tanks, drain the sump of water prior to flight.
NOTE 7. The airplane design vertical load factors exceed the minimum requirements of TSO C-39 for certain passenger
seat locations.  Replacement passenger seats must be evaluated for compliance with CAR 4b.358(c).
NOTE 8. (707-300 Series Aircraft only).  For operation at gross weights in excess of 302,000 pounds, the heavier gear
described by Boeing Company Drawing No. 67-71080, sheets 1 and 2 (DCN "A"), "Kit Main Landing
Gear Installation, Section 61," must be installed.  Boeing Service Bulletin No. 136(R-1) describes the installation
of this gear.
NOTE 9. (a) For 707-300 Series Aircraft:
This series aircraft may intermix the following engines in the combinations and with the appropriate
limitations noted in the FAA Approved Airplane Flight Manual:
Pratt and Whitney JT4A-9, -10, -11, and -12.
(b) For 707-300B and -300C Series Aircraft:
These series may intermix the following engines in the combinations and with appropriate limitations
noted in the FAA Approved Airplane Flight Manual:
Pratt and Whitney JT3D-1, -1MC6, -MC7, -3, -3B, and -7
NOTE 10. (a) JP-1, JP-4 and JP-5 fuels conforming to P&WA Specification No. 522 and later revisions may be used
separately or mixed in any proportions without adversely affecting the engine operation or power output.
No fuel control adjustment is required when switching fuel types.
(b) Phillips anti-icing fuel additive PFA-55MB may be used if concentration delivered to airplane does
not exceed 0.1% by volume.  No fuel system anti-icing credit is allowed.
NOTE 11. All 707-300C Aircraft in Cargo-passenger configurations of:
4 Cargo Pallets and more than 140 passengers
5 Cargo Pallets and more than 70 passengers
6 or more Cargo Pallets and more than 0 passengers
must have the provisions of Boeing Service Bulletin 2045A installed in order to be in accordance with approved
type design data.
NOTE 12. 707-300B and 707-300C Series Aircraft delivered after February 1964, have the structural capability of being

4A26
Page 20
operated at the increased gross weights noted in their respective sections of this Data Sheet.  The following
707-300B aircraft had 707-300C Main Landing Gears installed at the factory and are limited at the higher values:
707-312B S/N 19737 and Subsequent 707-351B S/N 19633 and Subsequent
707-321B S/N 18832 and Subsequent 707-359B S/N 19741 and Subsequent
707-330B S/N 18923 and Subsequent 707-382B S/N 18961 and Subsequent
707-331B S/N 19224 and Subsequent 707-384B S/N 20035 and Subsequent
707-337B S/N 18873 and Subsequent 707-387B S/N 19238 and Subsequent
The following 707-300B aircraft are eligible for increased gross weight operation subsequent to accomplishment
of Service Bulletin 2185 "Replacement of 707-300B Main Landing Gear with 707-300C Main Landing Gear," or
modification per Service Bulletin 3065.
707-300B    S/N 18462, 18463, and 18819
707-323B    S/N 20170-20179
707-337B    S/N 18708
707-344B    S/N 18891, 19133
707-353B    S/N 18461
707-351B    S/N 18584, 18585, 18693
NOTE 13. Installation of three additional center fuel tank cells per Boeing Service Bulletins 138, 1605, 1880, and 2874
will increase the fuel capacity as follows:
Tank Total Fuel
Applicable 7 Cell Center Tank Usable Capacity Capacity
  Model     Fuel in U.S. Gallons      lb.       lb.
707-321             10,023 69,159 163,151
707-328            10,023 69,159 163,151
707-329             10,193 70,332 164,324
707-331             10,193 70,332 164,324
707-437             10,023 69,159 163,151
NOTE 14. Information regarding Baggage and Cargo Loading, Fuel C.G. locations with partially filled tanks, system
oil capacities, and the required equipment list, are contained in each Model Weight and Balance Manual.
The Manuals for each Model are Boeing Document Numbers as follows:
707-300/-400 707-300B 707-300C
Series Aircraft Series Aircraft Series Aircraft
Model Document Model Document Model Document
707-321 D6-1852 707-321B D6-10949.6 707-3110 D6-14083.35
707-328 D6-3598 707-328B D6-10949.4 707-321C D6-14083.6
707-329 D6-3912 707-330B D6-10949.3 707-321C D6-14083.6
707-331 D6-3590 707-331B D6-10949.5 707-323C D6-14083.1
707-344 D6-5399 707-337B D6-10949.2 707-324C D6-14083.8
707-430 D6-5059 707-344B D6-10949.7 707-327C D6-14083.16
707-436 D6-3689 707-351B D6-10949.1 707-328C D6-14083.11
707-437 D6-5060 707-353B D6-10949.13 707-329C D6-14083.10
707-441 D6-5219 707-358B D6-10949.8 707-330C D6-14083.13
707-458 D6-7238 707-359B D6-10949.12 707-331C D6-14083.4
707-465 D6-8072 707-382B D6-10949.9 707-336C D6-14083.14
707-387B D6-10949.10 707-337C D6-14083.25
707-338C D6-14083.9
707-340C D6-14083.19
707-341C D6-14083.20
707-344C D6-14083.31
707-345C D6-14083.33
707-347C D6-14083.21
707-348C D6-14083.2
707-349C D6-14083.15

4A26
Page 21
707-300C
Series Aircraft
Model Document
707-351C D6-14083.3
707-355C D6-14083.27
707-360C D6-14083.28
707-365C D6-14083.29
707-365C D6-14083.23
707-366C D6-14083.26
707-368C D6-14083.32
707-378C D6-14083.5
707-373C D6-14083.7
707-379C D6-14083.34
707-384C D6-14083.17
707-385C D6-14083.24
707-385C D6-14083.18
707-399C D6-14083.22
NOTE 15. The maximum weights for the Model 707-338C differ from the other 707-300C increased gross weight models
due to the upper deck cargo compartment, which is limited to the left hand forward side only.
NOTE 16. Number in parentheses are applicable only after Boeing Service Bulletins 1732 (R-1) dated May 3, 1963, have
been incorporated.
NOTE 17. Use 6.9 lb./gal. for -300 only.  For the rest of the series -300, use 7.1 lb./gal.
NOTE 18. 707-300, -400, -300 B/C, AND -300 B/C Advanced:  For Engine Ferry Design Gross Weights, add 500 lbs. to
landing weights.
NOTE 19. (707-300C Series Aircraft only) The passenger capacity of airplanes not in compliance with FAR 25.2 may be
limited to 189 by FAR 121.310 if automatically deployed and erected escape slides are not installed at the
station 990 exit.
---END---
```

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- [AD 2011-12-01](https://openairdocs.org/ad/2011-12-01): Equipment/Furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 268 more. Effective Aug 1, 2011
- [AD 2011-01-09](https://openairdocs.org/ad/2011-01-09): Oxygen · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 290 more. Effective Feb 9, 2011
- [AD 2009-21-10 R1](https://openairdocs.org/ad/2009-21-10-R1): Oxygen · Airbus A300 B4-605R, A300 B4-620, A300 B4-622 and 138 more. Effective Feb 4, 2010
- [AD 2008-04-11 R1](https://openairdocs.org/ad/2008-04-11-R1): Fuel tank systems · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jan 12, 2010
- [AD 2009-18-10](https://openairdocs.org/ad/2009-18-10): Wings · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Oct 14, 2009
- [AD 2009-15-06](https://openairdocs.org/ad/2009-15-06): Fuel System · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Aug 25, 2009
- [AD 2008-12-03](https://openairdocs.org/ad/2008-12-03): Auxiliary fuel tanks · Airbus BAC 1-11 400 Series, 707-100 Long Body, 707-100B Long Body and 15 more. Effective Jul 9, 2008
- [AD 2008-04-06](https://openairdocs.org/ad/2008-04-06): Left side and right side flight deck · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Mar 28, 2008
- [AD 2007-23-12](https://openairdocs.org/ad/2007-23-12): Fuel quantity indication system (FQIS) · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Dec 18, 2007
- [AD 2007-21-15](https://openairdocs.org/ad/2007-21-15): Elevator hinge support fittings · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Nov 20, 2007
- [AD 2006-26-13](https://openairdocs.org/ad/2006-26-13): Attachment of the shoulder restraint harness · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 23 more. Effective Feb 12, 2007
- [AD 2005-20-02](https://openairdocs.org/ad/2005-20-02): Airplane flight manual (AFM) · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Nov 1, 2005
- [AD 2005-14-06](https://openairdocs.org/ad/2005-14-06): Inboard leading edge slats · Boeing 707-300B Series, 707-300C Series and 707-400 Series. Effective Aug 16, 2005
- [AD 2005-08-15](https://openairdocs.org/ad/2005-08-15): Outboard engine nacelle · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective May 31, 2005
- [AD 2005-04-01](https://openairdocs.org/ad/2005-04-01): Overwing Fuel Fill Ports · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 23 more. Effective Mar 23, 2005
- [AD 2004-25-09](https://openairdocs.org/ad/2004-25-09): Main landing gear (MLG) trunnion · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jan 13, 2005
- [AD 2004-22-24](https://openairdocs.org/ad/2004-22-24): High frequency eddy current (HFEC) inspections for corrosion and cracking · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Dec 14, 2004
- [AD 2004-20-02](https://openairdocs.org/ad/2004-20-02): Wing fillet flap support link · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Nov 4, 2004
- [AD 2004-07-06](https://openairdocs.org/ad/2004-07-06): Aft trunnion support fitting of each main landing gear · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective May 11, 2004
- [AD 2004-05-14](https://openairdocs.org/ad/2004-05-14): Wing front spar upper chord · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Apr 14, 2004
- [AD 2003-03-15 R1](https://openairdocs.org/ad/2003-03-15-R1): Airplane Flight Manual (AFM) - oxygen masks · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 90 more. Effective Dec 22, 2003
- [AD 2002-22-12](https://openairdocs.org/ad/2002-22-12): Titeflex hoses · BAE Systems ATP, Avro 146-RJ100A, Avro 146-RJ70A and 122 more. Effective Dec 13, 2002
- [AD 2002-02-02](https://openairdocs.org/ad/2002-02-02): Support Structure for the Main Landing Gear (MLG) Uplock Mechanism · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Mar 11, 2002
- [AD 2001-22-14](https://openairdocs.org/ad/2001-22-14): Fire Extinguishing System Bottle Cartridges · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 105 more. Effective Dec 10, 2001
- [AD 2001-03-13](https://openairdocs.org/ad/2001-03-13): Wing - Upper Skin Cracking · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 5 more. Effective Mar 22, 2001
- [AD 2000-24-06](https://openairdocs.org/ad/2000-24-06): Main Cargo Door Skin and Frame · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jan 8, 2001
- [AD 2000-24-20](https://openairdocs.org/ad/2000-24-20): Lower Skin Wings · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jan 8, 2001
- [AD 99-23-22 R2](https://openairdocs.org/ad/99-23-22-R2): Transponders · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 74 more. Effective Apr 20, 2000
- [AD 99-04-10](https://openairdocs.org/ad/99-04-10): Fluorescent Light Ballasts · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 49 more. Effective Mar 18, 1999
- [AD 97-04-04](https://openairdocs.org/ad/97-04-04): Auxiliary Power Units · Airbus BAC 1-11 200 Series, BAC 1-11 400 Series, Auxiliary Power Units and 54 more. Effective Mar 24, 1997
- [AD 96-25-12](https://openairdocs.org/ad/96-25-12): Auxiliary Power Units · BAE Systems HS 748 Series 2A, HS 748 Series 2B, 707-100 Long Body and 74 more. Effective Jan 13, 1997

All 197: https://openairdocs.org/tcds/4A26/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Boeing 707-338C](https://openairdocs.org/model/boeing-707-338c): 2 aircraft (registry code 138367N)
- [Boeing 707-321B](https://openairdocs.org/model/boeing-707-321b): 1 aircraft (registry code 138366B)
- [Boeing 707-323B](https://openairdocs.org/model/boeing-707-323b): 1 aircraft (registry code 138366C)
- [Boeing 707-351B](https://openairdocs.org/model/boeing-707-351b): 1 aircraft (registry code 138366M)
- [Boeing 707-368C](https://openairdocs.org/model/boeing-707-368c): 1 aircraft (registry code 1383601)
- [Boeing 707-3K1C](https://openairdocs.org/model/boeing-707-3k1c): 1 aircraft (registry code 1383610)
- [Boeing 707-3L6B](https://openairdocs.org/model/boeing-707-3l6b): 1 aircraft (registry code 1383706)
- [Boeing 707-300](https://openairdocs.org/model/boeing-707-300): 0 aircraft (registry code 1383612)
- [Boeing 707-307C](https://openairdocs.org/model/boeing-707-307c): 0 aircraft (registry code 1383616)
- [Boeing 707-311C](https://openairdocs.org/model/boeing-707-311c): 0 aircraft (registry code 1383645)
- [Boeing 707-320B](https://openairdocs.org/model/boeing-707-320b): 0 aircraft (registry code 138366E)
- [Boeing 707-320C](https://openairdocs.org/model/boeing-707-320c): 0 aircraft (registry code 1383668)
- [Boeing 707-321](https://openairdocs.org/model/boeing-707-321): 0 aircraft (registry code 138365B)
- [Boeing 707-321C](https://openairdocs.org/model/boeing-707-321c): 0 aircraft (registry code 138367B)
- [Boeing 707-323C](https://openairdocs.org/model/boeing-707-323c): 0 aircraft (registry code 138367D)
- [Boeing 707-324C](https://openairdocs.org/model/boeing-707-324c): 0 aircraft (registry code 138367A)
- [Boeing 707-327C](https://openairdocs.org/model/boeing-707-327c): 0 aircraft (registry code 138367E)
- [Boeing 707-328](https://openairdocs.org/model/boeing-707-328): 0 aircraft (registry code 138365D)
- [Boeing 707-328B](https://openairdocs.org/model/boeing-707-328b): 0 aircraft (registry code 138366D)
- [Boeing 707-328C](https://openairdocs.org/model/boeing-707-328c): 0 aircraft (registry code 1383617)
- [Boeing 707-329C](https://openairdocs.org/model/boeing-707-329c): 0 aircraft (registry code 138367C)
- [Boeing 707-330B](https://openairdocs.org/model/boeing-707-330b): 0 aircraft (registry code 138366F)
- [Boeing 707-330C](https://openairdocs.org/model/boeing-707-330c): 0 aircraft (registry code 138367G)
- [Boeing 707-331](https://openairdocs.org/model/boeing-707-331): 0 aircraft (registry code 138365H)
- [Boeing 707-331B](https://openairdocs.org/model/boeing-707-331b): 0 aircraft (registry code 138366H)
- [Boeing 707-331C](https://openairdocs.org/model/boeing-707-331c): 0 aircraft (registry code 138367F)
- [Boeing 707-336C](https://openairdocs.org/model/boeing-707-336c): 0 aircraft (registry code 138367J)
- [Boeing 707-337B](https://openairdocs.org/model/boeing-707-337b): 0 aircraft (registry code 138368Z)
- [Boeing 707-337C](https://openairdocs.org/model/boeing-707-337c): 0 aircraft (registry code 1383618)
- [Boeing 707-340C](https://openairdocs.org/model/boeing-707-340c): 0 aircraft (registry code 1383619)
- [Boeing 707-341C](https://openairdocs.org/model/boeing-707-341c): 0 aircraft (registry code 138368N)
- [Boeing 707-344B](https://openairdocs.org/model/boeing-707-344b): 0 aircraft (registry code 138365L)
- [Boeing 707-344C](https://openairdocs.org/model/boeing-707-344c): 0 aircraft (registry code 1383620)
- [Boeing 707-345C](https://openairdocs.org/model/boeing-707-345c): 0 aircraft (registry code 1383671)
- [Boeing 707-347C](https://openairdocs.org/model/boeing-707-347c): 0 aircraft (registry code 138367V)
- [Boeing 707-348C](https://openairdocs.org/model/boeing-707-348c): 0 aircraft (registry code 138367H)
- [Boeing 707-349C](https://openairdocs.org/model/boeing-707-349c): 0 aircraft (registry code 138367L)
- [Boeing 707-351C](https://openairdocs.org/model/boeing-707-351c): 0 aircraft (registry code 138367K)
- [Boeing 707-355C](https://openairdocs.org/model/boeing-707-355c): 0 aircraft (registry code 138367S)
- [Boeing 707-358B](https://openairdocs.org/model/boeing-707-358b): 0 aircraft (registry code 138367U)
- [Boeing 707-359B](https://openairdocs.org/model/boeing-707-359b): 0 aircraft (registry code 1383664)
- [Boeing 707-360C](https://openairdocs.org/model/boeing-707-360c): 0 aircraft (registry code 1383621)
- [Boeing 707-365C](https://openairdocs.org/model/boeing-707-365c): 0 aircraft (registry code 138367I)
- [Boeing 707-366C](https://openairdocs.org/model/boeing-707-366c): 0 aircraft (registry code 138367T)
- [Boeing 707-369C](https://openairdocs.org/model/boeing-707-369c): 0 aircraft (registry code 1383661)
- [Boeing 707-370C](https://openairdocs.org/model/boeing-707-370c): 0 aircraft (registry code 1383622)
- [Boeing 707-372C](https://openairdocs.org/model/boeing-707-372c): 0 aircraft (registry code 1383679)
- [Boeing 707-373C](https://openairdocs.org/model/boeing-707-373c): 0 aircraft (registry code 138367M)
- [Boeing 707-379C](https://openairdocs.org/model/boeing-707-379c): 0 aircraft (registry code 1383623)
- [Boeing 707-382B](https://openairdocs.org/model/boeing-707-382b): 0 aircraft (registry code 1383663)

All 69: https://openairdocs.org/tcds/4A26/aircraft.md

## STCs approved under this data sheet (464, first 50)

- [STC ST01305WI-D](https://openairdocs.org/stc/ST01305WI-D): Modification of a Collins ALT-50A or ALT-55B Radio Altimeter system installation to a Collins ALT-1000 or ALT-4000 Radio Altimeter system installation in accordance with Collins Drawing Index as listed on AML No. ST01305WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc
- [STC ST02612AT-D](https://openairdocs.org/stc/ST02612AT-D): Installation of an Interior Reconfiguration Cabin Conversion. AIRCRAFT RECONFIG TECHNOLOGIES, LLC
- [STC SA7497SW](https://openairdocs.org/stc/SA7497SW): Installation of dual Honeywell/Sperry EDZ-805 (5) tube flight instrument system (EFIS), dual Sperry FZ-500 flight directors, dual AZ-800 air data systems, dual FMZ-800 flight management systems and triple Honeywell laseref inertial reference system.. Omega Air Inc.
- [STC ST00888LA](https://openairdocs.org/stc/ST00888LA): Installation of airplane modifications.. Omega Air Inc.
- [STC ST02287LA](https://openairdocs.org/stc/ST02287LA): Replacement of Pratt & Whitney JT3D series engine with Pratt & Whitney JT8D-219 engine and associated systems in all positions. Omega Air, Inc.
- [STC ST04222AT](https://openairdocs.org/stc/ST04222AT): Installation of a Fuel System Modification. Omega Air Inc.
- [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc.
- [STC SA2579WE](https://openairdocs.org/stc/SA2579WE): Modify installation of wing tip mounted emblem light. The Boeing Company
- [STC SA2594WE](https://openairdocs.org/stc/SA2594WE): Modify the installation of wing tip mounted emblem light.. The Boeing Company
- [STC SA817NW](https://openairdocs.org/stc/SA817NW): Installation of Mark I interior modification kit.. Safran Cabin Inc.
- [STC ST00190SE](https://openairdocs.org/stc/ST00190SE): Installation of the Mark IV Interior retrofit kit.. Safran Cabin Inc.
- [STC SA3927NM](https://openairdocs.org/stc/SA3927NM): Installation of floor proximity emergency escape path marking system.. Bruce Aerospace Inc.
- [STC ST01936AT](https://openairdocs.org/stc/ST01936AT): Installation of Rockwell Collins CDU-4500 Control Display Unit (CDU). JanzAir Consulting Services Inc.
- [STC ST01186SE](https://openairdocs.org/stc/ST01186SE): Group Reduced Vertical Separation Minimum (RVSM) airworthiness approval. AeroMech Incorporated
- [STC SA2534SW-D](https://openairdocs.org/stc/SA2534SW-D): Replacement of Switch assembly Int'l Inflatables Co. P/N 68748, with DME Corp. P/N L-140 in emergency evacuation slide lighting system.. Astronics Luminescent Systems Inc
- [STC SA2539SW-D](https://openairdocs.org/stc/SA2539SW-D): Replacement of light assembly, International Inflatables Co. P/N68555-1 with DME Corp. EL-104, EL-104A, and EL-104B in emergency slide lighting system.. Astronics Luminescent Systems Inc
- [STC SA863EA](https://openairdocs.org/stc/SA863EA): Incorporation of DME Corporation emergency evacuation slide lighting system. Astronics Luminescent Systems Inc
- [STC ST02580AT](https://openairdocs.org/stc/ST02580AT): Lithium cell battery pack to replace currently approved alkaline battery pack used in escape slide emergency light system.. Astronics Luminescent Systems Inc
- [STC ST02929AT](https://openairdocs.org/stc/ST02929AT): Installation of an Artex Model C406-1 Emergency Locator Transmitter (ELT).. Woven Electronics LLC
- [STC SA739EA](https://openairdocs.org/stc/SA739EA): Installation of Inflight Motion Picture System. (707-327C). Burrana Inc.
- [STC SA808EA](https://openairdocs.org/stc/SA808EA): Installation of inflight motion picture system. Approved for models 720-047B, 707-347C, 707-351C (serial numbers 19773 and 19774 only). Burrana Inc.
- [STC SA2610WE](https://openairdocs.org/stc/SA2610WE): Installation of Bell & Howell movie projection system Nos. 478441 and478440.. Burrana Inc.
- [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc.
- [STC SA1-593](https://openairdocs.org/stc/SA1-593): Inflight Motion Picture Pallet Assembly. Burrana Inc.
- [STC SA1442WE](https://openairdocs.org/stc/SA1442WE): Installation of an inflight motion picture projection system. (707-331). Burrana Inc.
- [STC ST09019SC](https://openairdocs.org/stc/ST09019SC): Installation of a C & X band fuselage nose radome shell.. The NORDAM Group LLC
- [STC SA208NW](https://openairdocs.org/stc/SA208NW): Installation of Fairchild Stan(R) Weight and balance system.. Aviation Technical Services
- [STC ST04229NY](https://openairdocs.org/stc/ST04229NY): Introduction of a 16G New Generation Stretcher XL P/N 1120030-Series. Bucher Leichtbau AG
- [STC SA5784SW](https://openairdocs.org/stc/SA5784SW): Deactivation of Station 990 emergency exits and installation of 132 passenger interior arrangement. Associated Air Center, Inc. - c/o CT Corporation System
- [STC SA8644SW](https://openairdocs.org/stc/SA8644SW): Installation of Bendix/King CAS-81 TCAS II system and dual Bendix/King TRA-67A Mode S transponder. (707-320). Associated Air Center
- [STC SA3486WE](https://openairdocs.org/stc/SA3486WE): Installation of dual Litton LTN-51, or dual Litton LTN-72, or one Litton LTN-51 and one Litton LTN-72 Inertial Navigation Systems. Northrop Grumman Systems Corporation
- [STC SA3539WE](https://openairdocs.org/stc/SA3539WE): Installation of single, palletized Litton LTN-51 or LTN-72 Inertial Navigation System (707-320C Series). Northrop Grumman Systems Corporation
- [STC ST00115LA](https://openairdocs.org/stc/ST00115LA): Installation of Triple LTN-92 inertial navigation systems and dual LTN-2001 gloal positioning sensors.. Northrop Grumman Systems Corporation
- [STC SA7076NM](https://openairdocs.org/stc/SA7076NM): Installation of Stretcher Carrier.. Air Medic LLC
- [STC SA2808WE](https://openairdocs.org/stc/SA2808WE): Installation of dual Litton LTN-72 inertial navigation system. Northrop Grumman Systems Corporation
- [STC ST01329AT](https://openairdocs.org/stc/ST01329AT): Installation of AlliedSignal RDR-4B Forward-Looking Windshear/Radar System.. B/E Aerospace Inc
- [STC ST01330AT](https://openairdocs.org/stc/ST01330AT): Installation of 11 Channel Digital Flight Data Recorder.. B/E Aerospace Inc
- [STC SA2401WE](https://openairdocs.org/stc/SA2401WE): Alter Type Design by installation of Transequip Structural Igloo Assembly, P/N 245084 in conjunction with loading systems 65-42625, 65-42630, 65-44166, and 65-34899. Telair International LLC
- [STC SA2453WE](https://openairdocs.org/stc/SA2453WE): Installation of Structural Containers in Position I13 (Container 235111) and Position I14 (Container 235112). Telair International LLC
- [STC SA2773WE](https://openairdocs.org/stc/SA2773WE): Installation of Tridair Industries 3G Net Assy. Part No. 43568-1201 used in conjunction with unit load devices NAS3610-2A4P or Satco Pallet Assy. Part No. 31095-505. Telair International LLC
- [STC ST09227SC](https://openairdocs.org/stc/ST09227SC): Installation of structural provisions for a CMA-2102 High Gain Satellite Communications System antenna.. LB Aircraft Engineering Inc
- [STC ST09234SC](https://openairdocs.org/stc/ST09234SC): Installation of dual Universal UNS-1C Flight Management System with Global Positioning, dual Honeywell Attitude Heading Reference System and dual Collins DME-42 Distance Measuring Equipment.. LB Aircraft Engineering Inc
- [STC ST09446SC](https://openairdocs.org/stc/ST09446SC): Installation of a Collins SAT-906 Satellite Communications System with a top mounted Canadian Marconi CMA-2102 Antenna.. LB Aircraft Engineering Inc
- [STC SA2125WE](https://openairdocs.org/stc/SA2125WE): Modify type design by installation of Ancra Cargo Net Assembly 40234-10 used in conjunction with either Brownline pallet assembly 22630-51 or Heath Tecna pallet assembly AC 10065-1. (707-321C). Ancra International LLC
- [STC SA2290WE](https://openairdocs.org/stc/SA2290WE): Modify type design by installation of Ancra pallet net assembly P/N 40452-10 used in conjunction with Boeing 9g pallet assemblies(88 inch x 125 inch) numbers 10-60935-1, 10-60935-11, 10-60935-17, 10-60935-21, 10-60935-27 and10-60935-37. (727C SERIES -31C, -180C) (707-331C, -373C). Ancra International LLC
- [STC SA359NW](https://openairdocs.org/stc/SA359NW): Installation of carry-on baggage units.. AIM Aviation Inc
- [STC SA3838NM](https://openairdocs.org/stc/SA3838NM): Installation of a Forward Coat Closet.. Aim Aerospace Inc
- [STC SA3839NM](https://openairdocs.org/stc/SA3839NM): Installation of 'Stow-All VII' Interior.. AIM Aviation Inc
- [STC ST01202WI-D](https://openairdocs.org/stc/ST01202WI-D): Modification of an existing FAA approved Collins TPR-720, TPR-900 or TPR-901 Mode S transponder installation in Part 25 Aircraft using Collins Drawing Index as listed on AML No. ST01202WI-D, latest FAA approved revision.. Rockwell Collins Inc
- [STC ST00702LA](https://openairdocs.org/stc/ST00702LA): Installation of noise reduction nacelles.. Quiet Skies Inc

All 464: https://openairdocs.org/tcds/4A26/stcs.md

---
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