# TCDS 4A28: The Boeing Company

- Type: Type certificate data sheet
- Status: Current
- Holder: The Boeing Company
- Revision: 8
- Revised: May 1, 1973
- Product: Aircraft, Large Airplane
- Data sheet PDF: https://openairdocs.org/files/sha256/97/ca/97ca0a1f35889442f19d8d077c53d7c15e831cb6b1f007bf40eae16ccd19e582
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/B72DF74D3B1847AD852567240060A02D.0001
- Page: https://openairdocs.org/tcds/4A28

## Models (2)

As the data sheet lists them.

- 720B Series
- 720 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
Rev No. 8 8 - - - - - - - 8 - 8 8 8
Reformatted 1/94.
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
4A28
Revision 8
BOEING
720
720B
May 1, 1973
TYPE CERTIFICATE DATA SHEET NO.4A28
This data sheet which is a part of type certificate No. 4A28 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
P.O. Box 3707
Seattle, Washington  98124
I - 720 Series (Transport Aircraft), approved June 30, 1960
The 720 Series airplane has several different models due to different installations of equipment, interiors, airplane flight manuals, etc.
These models are as follows:
Model Serial numbers Eligible
720-022 17907 thru 17917; 18044 thru 18050; 18072 thru 18082
720-025 18155 thru 18164; 18240 thru 18244
720-027 18064 thru 18066; 18154; 18423 and 18581
720-048 18041 thru 18043
720-062 18376 and 18377
Engines 4 Pratt and Whitney Turbojet JT3C-7, except Model 720-025, which has 4 Pratt
and Whitney JT3C-12 engines.
Fuel See NOTE 10
Engine limits CERTIFICATION LIMITS
Thrust Ratings (pounds) JT3C-7  JT3C-12
Takeoff (standard day) static
  Sea Level (5 minutes)                      12,000        13,000
  Below 43.5°F.  Compressor inlet
    temperature (5 minutes)                  12,500            ---
Maximum continuous, static, sea level        10,000        11,500
  At 4°F. ambient temperature and below      12,000             ---
  At 25°F. ambient temperature and below          ---         13,000
Maximum permissible engine rotor
operating speeds:
  Low pressure compressor  (N1) rpm 6850  (110.7%  6850  (110.7%)
  High pressure compressor (N2) rpm     9950  ( 99.7%) 10150 (101.7%)
Thrust setting -- Appropriate thrust setting curve (EPR), in the Airplane Flight
Manual must be used for control of engine thrust.

4A28 2
Maximum permissible turbine outlet gas temperatures:
  Takeoff (5 minutes) (620°C)  1148°F (665°C)  1229°F
  Maximum continuous (540°C)  1004°F (600°C)  1112°F
  Maximum for acceleration (650°C)  1202°F (695°C)  1283°F
    (2 minutes)
Starting (Ground) (450°C)  842°F (450°C)  842°F
               (Air)                     (500°C)  932°F   (500°C)  932°F
Maximum oil inlet temperature
  Continuous Operation               (121°C)  250°F (121°C)  250°F
  10 minutes ground operation only     ---        ---     (143°C)  290°F
Airspeed limits Vmo (Normal Operating) (Basic)
  (IAS)   At Sea Level 436 mph    (378 knots)
  At 6,000 feet 439 mph (381 knots)
  At 10,000 feet 442 mph (384 knots)
  At 23,400 feet 460 mph (399 knots)
Mmo = 0.906 at 23,400 feet and above
Vmo (Normal Operating) (Alternate) (See NOTE 5)
  At Sea Level 394 mph (342 knots)
  At 5,000 feet 397 mph (344 knots)
  At 10,000 feet 400 mph (347 knots)
  At 15,000 feet 404 mph (350 knots)
  At 20,000 feet 407 mph (354 knots)
  At 25,000 feet 414 mph (359 knots)
Mmo (Alternate = 0.906 at 27,900 feet and above)
Va  (Maneuvering)
  At Sea Level 278 mph (241 knots)
  At 5,000 feet 279 mph (242 knots)
  At 10,000 feet 280 mph (243 knots)
  At 15,000 feet 283 mph (245 knots)
  At 20,000 feet 284 mph (246 knots)
  At 25,000 feet 289 mph (251 knots)
  At 30,000 feet 296 mph (257 knots)
  At 35,000 feet 304 mph (264 knots)
  At 40,750 feet 316 mph (274 knots)
Ma = 0.906 at 40,750 feet and above
Vfe (Flap Speeds) (Flaps not to be extended above 20,000 feet)
Maximum
Flap Deflection MPH KTS
20° 254 220
30° 242 210
50° 213 185
Vlo (Landing Gear Operation)
  Sea Level to 30,000 feet 311 mph (270 knots)
  30,000 to 36,000 feet 323 mph (280 knots)
Mlo = 0.83 at 36,000 feet and above
Vle (Landing Gear Extended)
  Sea Level to 29,800 feet 328 mph (285 knots)
Mle = 0.83 at 29,800 feet and above

3 4A28
For Emergency Descent Only
  Vlo = 369 mph (320 knots)
  Mlo = 0.90
  Vle = 292 mph (340 knots)
  Vle = 0.90
Dump CHute Operation
  At Sea Level to 42,000 feet 277 mph (240 knots)
Dump Chute Extended
  At Sea Level to 36,600 feet 317 mph (275 knots)
M = 0.83 at 36,600 feet and above
Vmc (Minimum Control Speed)
  Vmca (Minimum Control Speed)(Air) 115 mph (100 knots)
      Maximum takeoff thrust
  Vmcg (Minimum Control Speed)(Ground) 115 mph (100 knots)
      Maximum takeoff thrust
C.G. range and Datum The nose gear retraction moment is 18,600 in/lb. for Model 720-025;
and 14,500 in./lb. for the other 720 Models, and causes the C.G. to move
forward.  The main gear retracts parallel to the wing reference axis; hence,
has no effect on the airplane C.G.
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 70 in. forward
of nose (Moment Arm 0).  Horizontal distance of datum to average wing
jack point is 810.5 in.
Gross Weight    Forward Limit    Aft Limit
Model 720-022
213,000 lb. 18.0% MAC (Sta. 829.7) 29.5% MAC (Sta. 857.6)
203,000 lb. 16.6% MAC (Sta. 826.4) 31.0% MAC (Sta. 861.2)
190,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
     Model 720-025
230,000 lb. 18.4% MAC (Sta. 830.8) 26.0% MAC (Sta. 843.1)
225,000 lb. 17.8% MAC (Sta. 829.3) 31.0% MAC (Sta. 861.2)
200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
150,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
130,000 lb. 15.0% MAC (Sta. 822.5) 30.0% MAC (Sta. 858.8)
Model 720-027  (Serial No. 18066 only)
203,000 lb. 17.0% MAC (Sta. 827.3) 31.0% MAC (Sta. 861.2)
190,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
Model 720-027
218,500 lb. 17.1% MAC (Sta. 827.5) 27.3% MAC (Sta. 852.2)
215,000 lb. 16.7% MAC (Sta. 826.6) 31.0% MAC (Sta. 861.2)
200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
Model 720-048
230,000 lb. 18.4% MAC (Sta. 830.8) 26.0% MAC (Sta. 849.1)
225,000 lb. 17.8% MAC (Sta. 829.3) 31.0% MAC (Sta. 861.2)
200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)

4A28 4
Model 720-062
214,000 lb. 16.6% MAC (Sta. 826.4) 31.0% MAC (Sta. 861.2)
213,000 lb. 16.5% MAC (Sta. 826.1) 31.0% MAC (Sta. 861.2)
199,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
175,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
Straight line variation between values shown.
Maximum weights 720-022
720-062 720-027 * 720-048 720-025
Maximum ramp weight 213,000 218,500 230,000 230,000
Maximum inflight weight 213,000 218,500 229,000 229,000
Maximum flight weight at
  start of outboard
  reserve fuel transfer
  with zero fuel weight
  of 139,000 lbs. 190,000 190,000 190,000 190,000
Maximum flight weight at
  start of outboard reserve
  fuel transfer with zero
  fuel weight of 149,000
  lbs.  (See NOTE 13) 185,000 185,000 185,000 185,000
Maximum flight weight at
  which the outboard reserve
  tanks can be empty with
  zero fuel weight of
  139,000 lbs. 185,000 185,000 185,000 185,000
Maximum flight weight at
  which the outboard reserve
  tanks can be empty with zero
  fuel weight of 149,000 lbs.
  (See NOTE 13) 180,000 180,000 180,000 180,000
Maximum landing weight 175,000 175,000 175,000 175,000
Maximum Zero Fuel Weight
  (See NOTE 13) 149,000 149,000 149,000 149,000
Alternate Zero Fuel Weight
  (See NOTE 5) 142,000    ---    ---    ---
* (See NOTE 15)
   Maximum baggage
Maximum Maximum Moment
Compartment Body Sta Load Concentration Capacity Arms
Fwd. Belly  400-600H+6 47 lb/in. 150 lb/ft2 11,560 lb. 463 in.
Aft Belly  960-1060 50 lb/in. 150 lb/ft2 3,000 lb. 990 in.
Aft Belly 1060-1200 35 lb/in. 150 lb/ft2 4,900 lb. 1090 in.
Aft Belly 1200-1300 20 lb/in. 150 lb/ft2 2,000 lb. 1210 in.

5 4A28
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 following data is given for full fuel tanks.  See Boeing Documents
indicated below for other fuel C.G. locations with partially filled tanks.
Model Document
720-022 D6-5218
720-025 D6-7441
720-027 D6-5989
720-048 D6-5612
720-062 D6-8075
TANK NOMINAL CAPACITY
(Usable fuel in tank)
MAXIMUM CAPACITY
U.S. Gallons per Tank
Overwing Underwing
Tanks Loaded Fueling Fueling Pounds Moment Arm
Model 720-022
No. 1 and No. 4 Reserve 444 430 3,081 1083.6
No. 1 and No. 4 Main 2,342 2,318 16,592 916.8
No. 2 and No. 3 Main 2,269 2,265 16,152 791.3
Center 3,450 3,464 24,490 739.5
    Total 13,560 13,490 96,140
Model 720-027
No. 1 and No. 4 Reserve 444 444 2,995 1083.6
No. 1 and No. 4 Main 2,342 2,342 16,132 916.1
No. 2 and No. 3 Main 2,269 2,269 15,704 791.3
Center 1,740 1,749 12,006 737.1
    Total 11,850 11,859 81,668
Model 720-025, 720-048 and 720-062
No. 1 and No. 4 Reserve 444 444 3,081 1083.6
No. 1 and No. 4 Main 2,342 2,342 16,592 916.8
No. 2 and No. 3 Main 2,269 2,269 16,152 791.3
Center 3,450 3,464 24,490 739.5
    Total 13,560 13,574 96,140
Oil capacity
Engine Oil
Tank No. Location Volume Capacity Moment Arm
1 Outboard Port 6.5 gallons 868.8
2 Inboard Port 6.5 gallons 686.1
3 Inboard Starboard 6.1 gallons 686.1
4 Outboard Starboard 6.1 gallons 868.9
The system oil capacities are given in Weight and Balance Control Manuals as
noted under "Fuel Capacity."

4A28 6
II - 720B Series (Transport Aircraft), Approved March 3, 1961
(Same as 720 Series, except for engines and other associated changes and limitations.)
The 720B Series airplane has several different models due to different installations of equipment, interiors, airplane flight manuals,
etc.  These models are as follows:
Model Serial numbers Eligible
720-023B 18013 thru 18037
720-024B 18416 thru 18419, 18587; 18763; 19002 AND 19003
720-030B 18248 thru 18251; 18057 thru 18060
720-040B 18378 thru 18380 and 18745
720-047B 18061 thru 18063; 18167; 18451 thru 18453; 18588 thru 18590; 18749;
18818; 18820, 18827 thru 18830; 18963; 19160, 19161; 19207; 19208;
19413; 19414; 19438; 19439 and 19523
720-051B 18381 thru 18384; 18420 thru 18422; 18687 and 18688; 18351 thru 18356;
18792 and 18793
720-058B 18424 and 18425
720-059B 18086; 18087; and 18831
720-060B 18454; 18455; and 18977
720-068B 18165 and 18166
Engines 4 Pratt and Whitney JT3D-1, JT3D-1-MC6 or JT3D-1-MC7.  See NOTE 11
for intermixing of engines.
Fuel See NOTE 10.
Engine limits CERTIFICATION LIMITS
Thrust Ratings (pounds) JT3D-1 JT3D-3
Takeoff (standard day) static
  Sea Level (5 minutes)                      17,000 18,000
Maximum continuous, standard day, static,
  Sea Level                                  14,500 16,400
Thrust setting -- appropriate thrust setting curve (EPR), in the
Airplane Flight Manual must be used for control of engine thrust.
Maximum permissible rotor operating speeds:
  Low pressure compressor (N1) rpm 6800 (109.9%) 6800 (109.9%)
  High pressure compressor (N2) rpm    10200 (105.6%) 10250 (106.2%)
Maximum permissible turbine outlet gas temperatures:
  Takeoff (5 minutes) (530°C) 985°F (555°C) 1031°F
  Maximum continuous (460°C) 860°F (490°C) 914°F
  Maximum for acceleration (530°C) 985°F (555°C) 1031°F
    (2 minutes)
  Starting (450°C) 842°F (450°C) 842°F
Maximum permissible oil inlet temperatures:
  Continuous Operation (132°C) 270°F (132°C) 270°F
  10 minutes operation (143°C) 290°F (143°C) 290°F

7 4A28
Airspeed limits Vmo (Normal Operating)
  (IAS)   At Sea Level 436 mph (378 knots)
  At 6,000 feet 439 mph (381 knots)
  At 10,200 feet 442 mph (384 knots)
  At 23,300 feet 459 mph (399 knots)
Mmo = 0.90 at 23,300 feet and above
Va  (Maneuvering)
  At Sea Level 277 mph (241 knots)
  At 5,000 feet 279 mph (242 knots)
  At 10,000 feet 280 mph (243 knots)
  At 15,000 feet 281 mph (244 knots)
  At 20,000 feet 283 mph (246 knots)
  At 25,000 feet 289 mph (251 knots)
  At 30,000 feet 296 mph (257 knots)
  At 35,000 feet 305 mph (265 knots)
  At 40,600 feet 316 mph (274 knots)
Ma = 0.90 at 40,600 feet and above
Vfe (Flap Speeds) (Flaps not to be extended above 20,000 feet)
Maximum
Flap Deflection MPH KTS
20° 253 220
30° 242 210
50° 213 185
Vlo (Landing Gear Operation)
  Sea Level to 30,000 feet 311 mph (270 knots)
  30,000 to 35,900 feet 322 mph (280 knots)
Mlo = 0.83 at 35,900 feet and above
Vle (Landing Gear Extended)
  Sea Level to 29,900 feet 369 mph (320 knots)
Mle = 0.83 at 29,900 feet and above
For Emergency Descent Only
  Vlo = 369 mph (320 knots)
  Mlo = 0.90
  Vle = 392 mph (340 knots)
  Mle = 0.90
Dump Chute Operation
  At Sea Level to 42,000 feet 276 mph (240 knots)
Dump Chute Extended
  At Sea Level to 36,700 feet 317 mph (275 knots)
M = 0.83 at 36,700 feet and above
Vmc (Minimum Control Speed)
  Vmca (Minimum Control Speed)(Air) 134 mph (116 knots)
(For Model 720-058B only):        136 mph (117.8 knots)
Maximum takeoff thrust
  Vmcg (Minimum Control Speed)(Ground) 128 mph (111 knots)
(For Model 720-058B only): 130 mph (112.5 knots)

4A28 8
C.G. range and Datum The nose gear retraction moment is 14,500 in/lb. and moves C.G. forward.  The
main gear retracts parallel to the wing reference axis; hence, has no effect on the
airplane C.G.
All stations noted in the Data Sheet are Body Stations unless identified specifically
as moment arms.  For weight and balance purposes, datum is 70 inches forward of
nose (Moment Arm 0). Horizontal distance of datum to average wing jack point
is 810.5 inches.
Gross Weight Forward Limit Aft Limit
Model 720-023B (See Note 14)
222,000 lb. 17.5% MAC (Sta. 828.5) 26.0% MAC (Sta. 849.1)
217,000 lb. 16.9% MAC (Sta. 827.1) 31.0% MAC (Sta. 861.2)
200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
Model 720-030B, 720-047B, 720-024B, and 720-023B
230,000 lb. 17.5% MAC (Sta. 828.5) 26.0% MAC (Sta. 849.1)
225,000 lb. 16.5% MAC (Sta. 825.1) 31.0% MAC (Sta. 861.2)
217,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
Model 720-060B, 720-058B, 720-051B, 720-059B, 720-040B, 720-068B, 720-030B
  (See Note 12)
235,000 lb. 17.5% MAC (Sta. 828.5) 23.0% MAC (Sta. 841.8)
225,000 lb. 16.1% MAC (Sta. 825.1) 31.0% MAC (Sta. 861.2)
217,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
At lightweight aft C.G. locations, pitch up tendency after brake release could result in
aircraft rotating onto tail.  To prevent this, the noted aft C.G. locations should be observed
when taking off at weights equal to or less than those noted below.
Gross Weight Forward Limit Aft Limit
Model 720-023B (See Note 14
Models 720-030B, 720-047B, 720-051B, 720-059B, 720-040B,
and 720-068B)
179,000 lb. 17.5% MAC (Sta. 828.5) 26.0% MAC (Sta. 849.1)
135,000 lb. 16.9% MAC (Sta. 827.1) 31.0% MAC (Sta. 861.2)
200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
Model 720-030B, 720-047B, 720-024B, and 720-023B
230,000 lb. 17.5% MAC (Sta. 828.5) 26.0% MAC (Sta. 849.1)
225,000 lb. 16.5% MAC (Sta. 825.1) 31.0% MAC (Sta. 861.2)
217,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
Model 720-060B, 720-058B, 720-051B, 720-059B, 720-040B, 720-068B, 720-030B
  (See Note 12)
235,000 lb. 17.5% MAC (Sta. 828.5) 23.0% MAC (Sta. 841.8)
225,000 lb. 16.1% MAC (Sta. 825.1) 31.0% MAC (Sta. 861.2)
217,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2)
Straight line variation between values shown.

9 4A28
Maximum weights
720-0308***
720-040B, 720-047B****
720-051B, 720-058B
720-023B, 720-024B, 720-059B, 720-060B,
720,023B* 720-030B, 720-047B** 720-068B
Maximum ramp weight 222,000 lb. 230,000 lb. 235,000 lb.
Maximum flight weight,
  30° Flaps 222,000 lb. 229,000 lb. 234,000 lb.
Maximum flight weight
  Zero Flaps 221,000 lb. 228,000 lb. 233,000 lb.
Maximum flight weight at
  start of outboard reserve
  fuel transfer 190,000 lb. 190,000 lb. 190,000 lb.
Maximum flight weight at
  which the outboard reserve
  tanks can be empty 185,000 lb. 185,000 lb. 185,000 lb.
Maximum landing weight 175,000 lb. 175,000 lb. 175,000 lb.
Maximum zero fuel weight 147,000 lb. 149,000 lb. 156,000 lb.
*       See Note 14.
**     See Note 6.
***   See Note 12.
****See Note 16 and 17.
Maximum baggage
Maximum Maximum Moment
Compartment Body Sta. Load Concentration Capacity Arms
Fwd. Belly  400-600H+6 47 lb/in. 150 lb/ft2 11,560 lb. 463 in.
Aft Belly  960-1060 50 lb/in. 150 lb/ft2 3,000 lb. 990 in.
Aft Belly 1060-1200 35 lb/in. 150 lb/ft2 4,900 lb. 1090 in.
Aft Belly 1200-1300 20 lb/in. 150 lb/ft2 2,000 lb. 1210 in.
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 following data are given for full fuel tanks.  See Boeing Documents indicated
below for other fuel C.G. locations with partially filled tanks.
Model Document
720-023B D6-5400 (Sec. 2b.)
720-024B D6-8074
720-030B D6-5857
720-040B D6-7835
720-047B D6-5858
720-051B D6-7367
720-058B D6-8073
720-059B D6-7239
720-060B D6-7237
720-068B D6-7834

4A28 10
TANK NOMINAL CAPACITY
(Usable fuel in tank)
MAXIMUM CAPACITY
U.S. Gallons per Tank
Overwing Underwing
Tanks Loaded Fueling Fueling Pounds Moment Arm
Model 720-023B
No. 1 and No. 4 Reserve 444 430 3,081 1082.6
No. 1 and No. 4 Main 2,322 2,348 6,592 916.1
No. 2 and No. 3 Main 2,269 2,265 16,152 791.3
Center 3,450 3,464 24,490 739.5
    Total 13,620 13,550 96,140
Model 720-024B, 720-030B, 720-047B, 720-051B, 720-058B, 720-060B and 720-068B
No. 1 and No. 4 Reserve 444 444 3,081 1083.6
No. 1 and No. 4 Main 2,342 2,342 16,592 916.1
No. 2 and No. 3 Main 2,269 2,269 16,152 791.3
Center 4,720 4,741 33,412 750.6
    Total 14,830 14,851 105,062
Model 720-040B and 720-059B
No. 1 and No. 4 Reserve 444 444 3,081 1083.6
No. 1 and No. 4 Main 2,342 2,342 16,592 916.8
No. 2 and No. 3 Main 2,269 2,269 16,152 791.3
Center 5,945 5,967 42,314 731.7
    Total 16,055 16,077 113,966
Engine Oil
Tank No. Location Volume Capacity Moment Arm
1 Outboard Port 6.2 gallons 866.9
2 Inboard Port 6.2 gallons 684.1
3 Inboard Starboard 6.4 gallons 684.1
4 Outboard Starboard 6.4 gallons 866.9
The system oil capacities are given in Weight and Balance Control Manuals as
noted under "Fuel Capacity."
Specifications Pertinent to Both Series
MAC 241.9 inches.  (L.E. of MAC is Body Station 786.2)
Leveling means A plumb-bob attachment and leveling provision scale are provided in left wheel well.
Minimum crew For all flights:  3 persons:  Pilot, Copilot, Flight Engineer.
Maximum passengers 139.  When inflatable escape chutes are installed per FAA approved type design
data, airplane is limited to 140 passengers by emergency exit requirement of
4b.362(d).  All 720 and 720B Series aircraft certificated to carry 141 - 149
passengers, except Model 720-025, must have the provisions of Boeing Service
Bulletin 2045A installed to be in accordance with approved type design data.
For Model 720-025, maximum passengers limited to 165.  The installation of
interior per Boeing Drawing 65-77197 allows a maximum passenger
capacity of 170 for Model 720-025.

11 4A28
Maximum operating altitude The maximum operating altitude for all Models is 42,000 feet:
Other operating See FAA Approved Flight Manuals.
  Limitations
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 Drawing
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 50-8424
Stabilizer Trim 50-8704
Rudder 50-8703
Rudder Trim 50-8706
Rudder Balance Panel Tolerances 50-14035
Wing Flap 50-8707
Service information Boeing Report D6-1891, Structural Repair Manual, is FAA approved. Service
Bulletins, D6-1647, and other service information, when FAA approved,
will carry a statement to that effect.
Certification basis CAR 4b, dated December 1953; Amendments 4b-1 thru 4b-6 thereto; Item 2
of Special Civil Regulation No. SR-422B; the special condition and the
provisions of amendments listed in Attachment A of FAA letter to Boeing
dated October 12, 1959.
Type Certificate No. 4A28 issued June 30, 1960.
Date of Application for Type Certificate - April 12, 1957.
Compliance with the following optional requirements has been established:
Ditching Provisions of 4b.361
Ice Protection Provisions of 4b.640
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 for certification.
The following Boeing Documents list all required equipment that must be installed
as well as optional equipment approved by FAA.
720 Series
Model Document
720-022 D6-5218
720-025 D6-7441
720-027 D6-5989, D6-7014
720-048 D6-5612
720-062 D6-8075

4A28 12
720B Series
Model Document
720-023B D6-5400 (Sec. 2b)
720-024B D6-8074
720-030B D6-5857
720-040B D6-7835
720-047B D6-5858
720-051B D6-7367
720-058B D6-8073
720-059B D6-7239
720-060B D6-7237
720-068B D6-7834
NOTE 1. (a) Current weight and balance report including list of equipment included in 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 that the C.G. is within the specified limits (See C.G.
Range) 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 and 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 retained in the fuel lines.  The "total unusable fuel," which includes the drainable unusable
fuel, tank trapped 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 for all 720 and 720B Series aircraft is as follows:
(d) "System oil" is defined as that amount of oil required to fill the oil system and 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 Boeing
document listed under "Equipment."
(e) To preserve favorable wing bending moments, the following limitations shall apply:
All center tank fuel in excess of any included in the zero fuel weight must be used before the
transfer of reserve tank fuel.  For 720 Series aircraft with 149,000 lbs. zero fuel weight, the
outboard reserve tanks must be filled when the airplane gross weight exceeds 180,000 lb. and
transfer of reserve tank fuel must not be initiated above gross weights of 185,000 lb.   In all
other cases for 720 Series aircraft and for 720B Series aircraft, the outboard reserve tanks
must be filled when the gross weight exceeds 185,000 lbs. and transfer of reserve fuel
must not be initiated above gross weights of 190,000 lbs.
(1) Fuel Loading Limitations
a. Load fuel equally in main tanks 1, 2, 3 and 4 up to a total capacity of 36,000 lbs.
(for 720B Series and for 720 Series aircraft utilizing a zero fuel weight of
149,000 lbs.); 43,000 lbs. (for 720 Series aircraft utilizing 139,000 lbs. for zero
fuel weight); 29,000 lbs. for 720B Series aircraft utilizing the 156,000 lbs. zero fuel weight).
b. If additional fuel is desired, load reserve tank.
c. If the reserve tanks are full and additional fuel is required, continue loading fuel
equally in main tanks 1, 2, 3, and 4.

13 4A28
d. If main tanks 2 and 3 are full and additional fuel is required, continue to load main
tanks 1 and 4 to required fuel quantity.
e. If all main and reserve tanks are full and additional fuel is required, load center tank fuel.
OPTION: Fuel must be loaded equally in the main tanks only up to a gross
weight of 185,000 lbs. or 180,000 lbs. for 720 series aircraft
utilizing the 149,000 lbs. zero fuel weight.  Additional required
fuel must be added first to the reserve tanks and when full, then
equally to the main tanks and when full, then to the center tank.
NOTE: Observing limitations above, center tank fuel may be substituted for
payload in any quantity up to the maximum allowable payload * or to
the center tank capacity, whichever is lower, provided the
difference in effect on balance is also accounted for.
       * Maximum zero fuel weight less operating weight empty.
NOTE: Tanks selected for flight may be loaded simultaneously.
(2) Fuel Usage Limitations
Use tank-to-engine combination during all takeoffs and landing except as noted under
Minimum Fuel Go-Around.  (See Airplane Flight Manual.)
The fuel in main tanks 1, 2, 3, and 4 must be used equally at airplane gross weights above
211,000 lbs. (Model 720B); 207,000 lbs. (Model 720).
Fuel reserves must be retained in main tanks only.
For 720B Series Only
Expend a minimum of 15,000 lbs. up to a maximum of 20,000 lbs. (total) of main
tank fuel for initial takeoff and climb to altitude.  (Not applicable to takeoff gross
weights below 190,000 lbs.)
(f) Fuel Dumping -
All 720 and 720B Series
Undumpable Fuel
Two Outboard Main Tanks 993.4 gallons
Two Inboard Main Tanks 622.8 gallons
NOTE 2. Reserved.
NOTE 3. Replacement brake lining must meet Boeing specification D10-60228, Revision C, "Specification
for Wheel and Brake Assembly."
NOTE 4. Aft of Fuselage Station 980 the airplane design vertical load factors exceed TSO-C39 specifications;
therefore, replacement passenger seats aft of Fuselage Station 980 must be evaluated for compliance
with CAR 4b.358(c).
NOTE 5. Not applicable to Model 720-025.  The alternate design condition (for the 720 Series only) differs
from the basic condition in that a higher zero fuel weight was selected (142,000 lbs. maximum).
Consequently, structure was substantiated at a reduced Vc speed (Vmo).
Therefore, it is necessary to reduce the Mmo speeds to the alternate Vmo speeds whenever the zero
fuel weight is greater than 139,000 lbs., and outboard reserve tanks are less than full.

4A28 14
NOTE 6. For 720-047B, Serial Nos. 18061, 18451 and higher.  The zero fuel weight is increased to 156,000 pounds.
NOTE 7. Special fatigue or retirement considerations applicable to the 720B Series aircraft:
(a) The turbo compressor duct must be inspected, maintained, and/or retired in accordance with
Boeing Service Bulletin No. 1221 dated February 23, 1962, or later FAA approved revisions.
(b) The engine nose cowling must be inspected, maintained, and/or retired in accordance with
Boeing Service Bulletin No. 1219 dated February 22, 1961, or later FAA approved revisions.
NOTE 8. For Model 720-059B only.
If an airplane enters U.S. Registry with an Interior Arrangement installed in accordance with Boeing
Service Bulletin No. 208Q, this Interior Arrangement must be inspected to determine compliance with
the applicable regulations.
NOTE 9. Reserved.
NOTE 10. 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.
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.
Anti-static fuel additive (Shell ASA-3) may be mixed with the fuel (recommended quantity 0.5 to 1.0 ppm
by weight) provided the effective conductivity of the mixture does not exceed 300 picomhos per meter.
NOTE 11. (a) For 720B Series Airplanes
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 JT3D-1, JT3D-1MC6, JT3D-1MC7, JT3D-3, AND JT3D-3B engines
(b) For 720-025 Series Airplanes
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 JT3C-7 and JT3C-12
NOTE 12. For Model 720-030B only.  Airplane Serial Nos. 18051, 18058, 18059 and 18060 are limited to a
maximum gross weight of 230,000 pounds and must not exceed the limits noted for aircraft of that weight.
Airplane Serial Nos. 18248, 18249, 18250 and 18251 are limited to a maximum gross weight of 235,000
pounds and must not exceed the limits noted for aircraft of this weight.
NOTE 13. All 720 Series aircraft can utilize the 149,000 pounds zero fuel weight except Model 720- 022, serial
Nos. 17907 through 17917, which are limited to a zero fuel weight of 139,000 pounds or an alternate
of 142,000 pounds.
NOTE 14. For Model 720-023B, Serial Nos. 18013 through 18026 only.  These aircraft are restricted to 222,000
pounds maximum ramp weight and all related weights.  (Inboard wing structural reasons.)
NOTE 15. For Model 720-027, Serial No. 18066 only.  This aircraft is restricted to 203,000 pounds maximum ramp
weight an 202,000 pounds maximum inflight weight.

15 4A28
NOTE 16. For Model 720-047B, Serial Numbers 18061, 19207, 19208, 19413, 19414, 19438, 19439 & 19523 only.
These aircraft are limited to a maximum gross weight of 235,000 pounds and must not exceed the
C.G. limit noted for aircraft of that weight.
NOTE 17. Except for NOTE 14 aircraft, Model 720/720B aircraft are approved for 185,000 pounds maximum
landing weight with appropriate airspeed placard changes.
---END---
```

## ADs (152, first 50, in force first)

- [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026
- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2020-03-11](https://openairdocs.org/ad/2020-03-11): Fuel · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Mar 18, 2020
- [AD 2018-23-12](https://openairdocs.org/ad/2018-23-12): Equipment/furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 180 more. Effective Dec 28, 2018
- [AD 2018-19-32](https://openairdocs.org/ad/2018-19-32): Nacelles/pylons · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Nov 2, 2018
- [AD 2018-19-21](https://openairdocs.org/ad/2018-19-21): Fuel · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Nov 1, 2018
- [AD 2017-09-04](https://openairdocs.org/ad/2017-09-04): Fuselage · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jun 8, 2017
- [AD 2016-08-11](https://openairdocs.org/ad/2016-08-11): Stabilizers · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective May 27, 2016
- [AD 2015-11-04](https://openairdocs.org/ad/2015-11-04): Nacelles/Pylons · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jul 6, 2015
- [AD 2014-16-09](https://openairdocs.org/ad/2014-16-09): Oxygen · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 16 more. Effective Sep 23, 2014
- [AD 2014-13-11](https://openairdocs.org/ad/2014-13-11): Fuselage · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Aug 19, 2014
- [AD 2013-24-07](https://openairdocs.org/ad/2013-24-07): Fuel · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jan 7, 2014
- [AD 2013-03-19](https://openairdocs.org/ad/2013-03-19): Electrical Power · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Mar 21, 2013
- [AD 2012-16-12](https://openairdocs.org/ad/2012-16-12): Nacelles/Pylons · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Sep 21, 2012
- [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 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 2008-04-06](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 2006-06-05](https://openairdocs.org/ad/2006-06-05): Front spar upper chords · Boeing 720 Series and 720B Series. Effective Apr 3, 2006
- [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 2005-08-15](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 2002-02-02](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 2001-18-05](https://openairdocs.org/ad/2001-18-05): Flight Eagle Tires · Boeing 720 Series, 720B Series, 111 and 6 more. Effective Sep 24, 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 95-17-01](https://openairdocs.org/ad/95-17-01): Upper Center Section Cracks · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Sep 13, 1995
- [AD 94-10-06](https://openairdocs.org/ad/94-10-06): Aging Airplane Inspections · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jun 20, 1994
- [AD 93-14-12](https://openairdocs.org/ad/93-14-12): Crewmember Protective Breathing Equipment Units · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 201 more. Effective Sep 2, 1993
- [AD 93-11-02](https://openairdocs.org/ad/93-11-02): Midspar Fittings Inspection · Modification of the Boeing Model 707-300B (Omega Aviation Services STC SA2699NM or 2 others). Effective Jul 6, 1993
- [AD 93-05-17](https://openairdocs.org/ad/93-05-17): Cabin Window Inspection · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 22 more. Effective May 5, 1993
- [AD 92-10-10](https://openairdocs.org/ad/92-10-10): Main Landing Gear Brakes · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jul 2, 1992
- [AD 91-22-04](https://openairdocs.org/ad/91-22-04): Main Cargo Door · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 9 more. Effective Nov 29, 1991
- [AD 91-07-19](https://openairdocs.org/ad/91-07-19): Structural Modifications · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Apr 29, 1991
- [AD 90-25-07](https://openairdocs.org/ad/90-25-07): Corrosion Control Program · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Dec 31, 1990
- [AD 85-12-01 R1](https://openairdocs.org/ad/85-12-01-R1): Significant Structural Detail Inspection · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Nov 14, 1986
- [AD 83-24-03](https://openairdocs.org/ad/83-24-03): Tab Control Rod Assys · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jan 3, 1984
- [AD 80-22-12 R2](https://openairdocs.org/ad/80-22-12-R2): Leading Edge Devices · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 22 more. Effective Jun 21, 1983
- [AD 79-24-04 R1](https://openairdocs.org/ad/79-24-04-R1): Horizontal Stabilizer · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 3 more. Effective Apr 4, 1983
- [AD 82-24-03](https://openairdocs.org/ad/82-24-03): Nacelle Strut Diagonal Braces · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Nov 23, 1982

All 152: https://openairdocs.org/tcds/4A28/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Boeing 720](https://openairdocs.org/model/boeing-720): 0 aircraft (registry code 1383802)
- [Boeing 720-B](https://openairdocs.org/model/boeing-720-b): 0 aircraft (registry code 1383804)

## STCs approved under this data sheet (139, first 50)

- [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 ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited
- [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 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 SA278EA](https://openairdocs.org/stc/SA278EA): See Document No. Report No. 3187, dated April 18, 1967, Revised January 30, 1969, concerning Inflight Motion Picture System.. Burrana Inc.
- [STC SA1-593](https://openairdocs.org/stc/SA1-593): Inflight Motion Picture Pallet Assembly. Burrana Inc.
- [STC SA7076NM](https://openairdocs.org/stc/SA7076NM): Installation of Stretcher Carrier.. Air Medic LLC
- [STC SA1079WE](https://openairdocs.org/stc/SA1079WE): Revision of Passenger Interior by addition of fabric cargo bins, per FAA Approved United Airlines Drawing List No. COA 4-1222, or later FAA approved revision.. United Airlines Inc
- [STC SA1169WE](https://openairdocs.org/stc/SA1169WE): Installation of Cockpit Voice Recorder in accordance with United Airlines Engineering Report No. F-1021, dated June 9, 1965, revised November 9, 1965.. United Airlines Inc
- [STC SA1222WE](https://openairdocs.org/stc/SA1222WE): Replace standard Boeing engine thrust reverser forward pressure seal with improved type shown in United Air Lines drawing 3F-10888 and described in United Air Lines Report F-1010.. United Airlines Inc
- [STC SA1245WE](https://openairdocs.org/stc/SA1245WE): Installation of either single or dual Collins AL-101 Radio Altimeter Systems in accordance with FAA Approved United Air Lines Report F-1101.. United Airlines Inc
- [STC SA1291WE](https://openairdocs.org/stc/SA1291WE): Installation of Boeing 720 Forward Lounge Revision (divider). United Airlines Inc
- [STC SA1396WE](https://openairdocs.org/stc/SA1396WE): Installation of McMillan Radome P/N 2406 as a replacement for Boeing Radome P/N 65-2040. United Airlines Inc
- [STC SA1447WE](https://openairdocs.org/stc/SA1447WE): Boeing 720-22 Alternate Seating Configuration (UAL Change Order Authorization COA 4-1477) per United Air Lines Drawing List No. COA 4-1477 dated July 3, 1967.. United Airlines Inc
- [STC SA1553WE](https://openairdocs.org/stc/SA1553WE): Installation of Fairchild P/N 13920-301 or 15630-601 Flight Data Recorder and Honeywell P/N 180 VI Central Data Computer in accordance with United Air Lines Report F-1171 dated March 21, 1967 and revised December 4, 1967 or later FAA approved revision.. United Airlines Inc
- [STC SA1619WE](https://openairdocs.org/stc/SA1619WE): Installation of passenger seats in forward cabin area. United Airlines Inc
- [STC SA1628WE](https://openairdocs.org/stc/SA1628WE): Installation of passenger seats in cabin area. United Airlines Inc
- [STC SA2051WE](https://openairdocs.org/stc/SA2051WE): Alternate seating configuration in accordance with FAA Approved United Airlines Drawing List COA 4-1605, or later FAA approved revisions. United Airlines Inc
- [STC SA2095WE](https://openairdocs.org/stc/SA2095WE): Installation of McMillan Radome P/N 2593 as a replacement for Boeing Radome P/N 65-2040, in accordance with FAA Approved United Air Lines Report No. F-1390 dated July 1, 1969.. United Airlines Inc
- [STC SA2206WE](https://openairdocs.org/stc/SA2206WE): Installation of Bendix Third Attitude Indicator to meet the requirements of 14 CFR § 121.305(j). United Airlines Inc
- [STC SA2347WE](https://openairdocs.org/stc/SA2347WE): Installation of Door Mounted Inflatable Evacuation Slide; Sargent Industries P/N 6176700 in accordance with FAA Approved United Airlines Drawing 9F9324 "Slide Installation - Aft Entry/Galley Door.". United Airlines Inc
- [STC SA260WE](https://openairdocs.org/stc/SA260WE): Applicable aircraft may be modified to have alternate interior arrangements consisting of 28 four abreast seats or 35 five abreast seats forward of a class divider and 78 six abreast seats aft of a class divider.. United Airlines Inc
- [STC SA2744WE-D](https://openairdocs.org/stc/SA2744WE-D): Alternate 143 passenger seating configuration. (720-022). United Airlines Inc
- [STC SA2746WE-D](https://openairdocs.org/stc/SA2746WE-D): Alternate 149 passenger seating configuration. (720-022). United Airlines Inc
- [STC SA2831WE-D](https://openairdocs.org/stc/SA2831WE-D): Couple EDO Loran System to ADF Sense Antenna instead of Fin Cap (No Fin Cap on UAL B720) in accordance with COA-4-1724 Master Drawing List, ER 2, or later FAA approved revisions.  Airplane to be test flown.. United Airlines Inc
- [STC SA2833WE-D](https://openairdocs.org/stc/SA2833WE-D): Installs two HF communications systems per United Air Lines drawing COA 4-1723.  The system design is as much like Boeing installation on W. A. L. airplanes as possible but using Aeronautical Engineers Inc. design dual wire antenna systems per drawings AE2257 and AE2264 and South Eastern Region  STC No. ST564SO. (720-022). United Airlines Inc
- [STC SA2834WE-D](https://openairdocs.org/stc/SA2834WE-D): :    Alternate 101 passenger seating configuration in accordance with United Air Lines Drawing List No. COA-4-1744 or later FAA approved revisions.. United Airlines Inc
- [STC SA302EA](https://openairdocs.org/stc/SA302EA): Inflight motion picture system.. United Airlines Inc
- [STC SA353WE](https://openairdocs.org/stc/SA353WE): United Air Lines B-720-022 Cabin Interior Arrangement (one class) five abreast seating. United Airlines Inc
- [STC SA4-1570](https://openairdocs.org/stc/SA4-1570): The interior arrangements in the applicable aircraft have been revised as indicated by the following United Air Lines documents:

1.  7 rows of First Class seats and 12 rows of Tourist Seats per United Air Lines Drawing 6F-8042 "no change" or (continued on page 3 ). United Airlines Inc
- [STC SA458WE](https://openairdocs.org/stc/SA458WE): Installs Crimsco Jet Cargo Container, Part No. 04-005-01, including jet cargo container seat track latch assembly, Part No. 04-005-03 in main passenger compartment as shown on and per the schedules noted on United Air Lines Drawing 15F-2228, Change "B".. United Airlines Inc
- [STC SA846WE](https://openairdocs.org/stc/SA846WE): Modify cabin interior arrangement to a three-class configuration. United Airlines Inc
- [STC SA890WE](https://openairdocs.org/stc/SA890WE): Installation of a Passenger Entertainment System per United Air Lines Report No. F-991 dated January 28, 1965, revision February 23, 1965.. United Airlines Inc
- [STC SA112NW](https://openairdocs.org/stc/SA112NW): Installation of cabin interior arrangement. (720 -22). Alaska Airlines Inc
- [STC SA3431NM](https://openairdocs.org/stc/SA3431NM): Installation of a Garrett GTCP-85-98CK auxiliary power unit in the forward baggage compartment. (720-023B). Airweld Inc.
- [STC ST10209SC](https://openairdocs.org/stc/ST10209SC): Installation of Dual Innovative Solutions & Support (IS&S) air data display system units.. AeroMech Incorporated
- [STC SA194NW](https://openairdocs.org/stc/SA194NW): Installation of new look interior arrangement. (720-047B). Heath Tecna Inc.
- [STC SA5971NM](https://openairdocs.org/stc/SA5971NM): Installation of flame reistant cargo covers.. Air Transport International LLC.
- [STC ST657SO](https://openairdocs.org/stc/ST657SO): Installation of Mace Galley Model No. 101 in aft passenger compartment and Mace Galley Model No. 102 in forward passenger compartment. (720-023B and 720-030B). B/E Aerospace
- [STC SA2405WE](https://openairdocs.org/stc/SA2405WE): Installation of PICO Division pressure regulator P/N 3001 on automatically inflatable emergency evacuation slides in lieu of International Inflatables pressure regulator P/N 68240 and 70003.. Goodrich Corporation
- [STC SA2557WE](https://openairdocs.org/stc/SA2557WE): Replacement of existing girt on Air Cruiser evacuation slide P/Ns15D22093-7, 15D22093-11, 15D22094-10 and 15D22454-2 with Sargent Industries/PICO Division girt P/N 6176105-103. (707-347) (720-047). Goodrich Corporation
- [STC SA1241EA](https://openairdocs.org/stc/SA1241EA): Installation of rear and forward folding stairs.. Patrick Aircraft Products Inc.
- [STC ST662SO](https://openairdocs.org/stc/ST662SO): Installation of Radome.. Saint-Gobain Performance Plastics Corp
- [STC SA2795SW](https://openairdocs.org/stc/SA2795SW): Installation of removable airstair.. Sierra Industries, Inc
- [STC SA2803SW](https://openairdocs.org/stc/SA2803SW): Installation of seat support subfloor beams and tracks.. Sierra Industries, Inc
- [STC SA2805SW](https://openairdocs.org/stc/SA2805SW): Installation of Dual Delco Carousel IVA Inertial Navigation Systems.. Sierra Industries, Inc
- [STC SA4326SW](https://openairdocs.org/stc/SA4326SW): Structural provisions for mid-lavatory service panel.. Sierra Industries, Inc
- [STC SA4015NM](https://openairdocs.org/stc/SA4015NM): Modification of the Boeing Model720B airplanes.. Omega Aviation Services Ltd

All 139: https://openairdocs.org/tcds/4A28/stcs.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.