# TCDS A2WE: Sabreliner Aviation LLC

- Type: Type certificate data sheet
- Status: Current
- Holder: Sabreliner Aviation LLC
- Revision: 28
- Revised: April 29, 2014
- Product: Aircraft, Large Airplane
- Certification basis: Part 21, Part 25, Part 27, Part 36, CAR 4b
- Registered aircraft: 44, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/6a/21/6a21656aa13b5f7be5a86abd6ac54a7277dfe2d868e77fea141047abcee8c731
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/CC0A4D2ECB04303E86257CDD00494678.0001
- Page: https://openairdocs.org/tcds/A2WE

## Models (8)

As the data sheet lists them.

- NA-265-40
- NA-265-80
- NA-265-60
- NA-265-70
- NA-265-30 (Military T-39D)
- NA-265-65
- NA-265-20 (Military T-39B)
- NA-265 (Military T-39A)

## What the data sheet says

Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers.

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 
Rev. No. 28 19 19 19 19 19 19 19 21 19 23 19 19 19 19 
 
Page No. 16 17 18 19 20 21 22 23 24 25 26 27 28 
Rev. No. 19 19 19 19 27 19 19 19 19 24 26 19 27 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A2WE 
Rev. 28 
SABRELINER  
NA-265 
NA-265-20 
NA-265-30 
NA-265-40 
NA-265-60 
NA-265-65 
NA-265-70 
NA-265-80 
April 29, 2014 
 
| 
 
 
 
 
 
 
 
 
 
| 
 
 
TYPE CERTIFICATE DATA SHEET NO. A2WE 
 
This data sheet, which is a part of Type Certificate No. A2WE, 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 Sabreliner Aviation LLC 
  Perryville Municipal Airport 
  1390 Highway H  
  Perryville, Missouri  63775 
 
Type Certificate Holder Record North America Rockwell Corporation transferred to 
  Rockwell International Corporation on April 19, 1968  
 
  Rockwell International Corporation transferred to  
  Sabreliner Corporation on June 30, 1983 
 
  Sabreliner Corporation transferred to  
  Sabreliner Aviation LLC on April 29, 2014 
 
I.  Model NA-265 (Transport Aircraft), Approved March 23, 1962 Military Model T-39A 
 Model NA-265-20 (Transport Aircraft), Approved August 31, 1962 Military Model T-39B 
 Model NA-265-30 (Transport Aircraft), Approved December 20, 1962 Military Model T-39D 
 
 Engines 2 Pratt and Whitney Turbo Wasp JT12A-6A 
 
 Fuel Commercial Aircraft Turbine Engine Fuel conforming to PWA Specification PWA 522 
as revised. 
 
 Fuel Controls 2 Holley P/N 31501 hydro-mechanical controls.  Minimum flow schedule must be 
adjusted between 308-325 p.p.h. per PWA components calibration schedule (CCS) 
requirements. 
 
 Engine Limits Engine Model  JT12A-6A 
 
 Static thrust (see Engine Data Sheet 1E9, NOTE 5) 
  Takeoff (5 min) 3,000 lbs. 
  Maximum continuous 2,570 lbs. 
  Maximum permissible engine rotor operating speed 16,700 r.p.m.

A2WE 
 -2- Rev. 28 
I. Model NA-265, Model NA-265-20, Model NA-265-30   (cont’d) 
 Engine Limits (cont’d) Maximum permissible gas temperature at the turbine outlet 
  Takeoff 677°C 1,250°F 
  Maximum continuous 577°C 1,070°F 
  Maximum acceleration (2 min) 677°C 1,250°F 
  Starting  (momentary) 525°C    977°F 
 
  Oil inlet temperature 121°C    250°F 
 
 Maximum permissible air bleed extraction of total engine airflow 
  Two engine operation (each engine) 
   Idle to maximum continuous 4.0% 
   Maximum continuous through takeoff 3.0% 
  One engine operation 
   Idle to maximum continuous 4.4% 
   Maximum continuous through takeoff 3.7% 
 
  NOTE: Thrust setting:  Appropriate thrust setting curves (EPR) in FAA Approved 
Airplane Flight Manual must be used for control of the engine thrust. 
 
  Engines installed must meet the minimum thrust coefficient (Cg) as shown in the 
following table.  Engines are to be equipped with 443 series tapered PT5 probes. 
 
PT5/PO 1.2 1.4 1.6 1.8 2.0 2.2 2.4 2.6 
Cg - P and WA 
Acceptance Test* 
.850 .870 .890 .905 .918 .925 .934 .938 
Cg - installed in  
NA-265** 
.897 .908 .915 .920 .923 .926 .927 .928 
 
    *With jet nozzle and exhaust pipe per PWA Drawing No. 403201 
  **With tail pipe per NR Drawing No. 265-420023-11 
 
 Oil Aircraft Turbine Engine Lubricant conforming to P&W Specification PWA 521, as 
revised. 
 
 Airspeed Limits (CAS)  
  
NA-265 
NA-265-20 
NA-265-30 
VMO (Max. operating at S.L.)  333K  333K 
VMO (Max. operating - 21,340 ft.)  346K  346K 
VMO (Max. Operating above 21,340 ft.) .765M .765M 
VA (Maneuvering at S.L.)  218K  205K 
VA (Maneuvering  -  39,000 ft.  236K   - - 
MA (Maneuvering above 39,000 ft. .765M   - - 
VA (Maneuvering  -  40,500 ft.)   - -  228K 
MA (Maneuvering above 40,500 ft.)   - - .765M 
VFE (Flaps down 23.5° (100%) indicated)  183K  183K 
VLO (Landing gear operating)  183K  183K 
VLE (Landing gear extended)  183K  183K 
VSB (Speed brake extension) Any speed Any speed 
 (Speed brake retraction) Any speed Any speed 
V (Fuel jettisoning) Any speed Any speed 
 
  NOTE: For variation between values shown and corresponding IAS Limits, for the 
airspeed system installed, refer to FAA Approved Airplane Flight Manual. 
 
   For Buffet Envelope and Limit Maneuvering Load Factor variation with 
airspeed, weight, fuel loading and altitude, refer to FAA Approved Airplane 
Flight Manual.

A2WE
Rev. 28
Model NA-265, Model NA  A-265-30  (cont'd)
C.G. Range
NA 265, -20. -30 C. G. Digrem
жі АпІ
NA 285 C. G. Diogram 111
NA 75570 C. G  ram 12)
Aleplane Graza Maighe lIbe, X 107)  (9)  Modified per NOTE 71al
121 Modified per NOTE 7ibl
13
12
Zere Fuel Weight
10
20  27
Camer of Gravity (Percens of MACI
The landing gear retraction moment is -380 in.-lb. and results in a negligible forward
movement of the C.G. When the airplane is loaded within the above C.G. envelope
limits as applicable at both the start of takeoff and zero fuel weights, and the restrictions
concerning crew and passenger movement specified in the FAA Approved Load and
Balance Schedule are complied with, the airplane will remain within the approved C.G.
limits.

A2WE 
 -4- Rev. 28 
I. Model NA-265, Model NA-265-20, Model NA-265-30   (cont’d) 
 Maximum Weight (in Pounds) 
 
Airplane Model 
NA-265, 
-20,  -30 
NA-265 Modified per Note 7(a) 
NA-265-30 Modified per Note 7(b) 
Equipped with brake P/N 9541544 9543102 9543102 9550338 
Anti-skid installed and 
  operational 
 
No 
 
No 
 
Yes 
 
Yes 
Ramp and taxi 17,760 17,760 18,650 18,650 
Start of takeoff 17,450 17,450 18,340 18,340 
Airborne 17,375 17,375 18,265 18,265 
Airborne (no fuselage fuel) 16,527 -- -- -- 
Zero fuel 10,984 10,984 12,250 12,250 
Landing 13,000 14,000 17,500 17,500 
 
  NOTE: Fuel jettison valves required for operation in excess of 105 percent of the 
maximum landing weight.  Refer to the FAA Approved Airplane Flight Manual 
for fuel jettisoning procedures.  See NOTE 1 
 
 Minimum Crew 2 pilots 
 
 Maximum Passengers 4 - NA-265, -20, -30 
  7 - NA-265 when modified per NOTE 7(a) 
  NOTE: See NOTE 1(a) and (b) 
 
 Maximum Baggage 
 
 
 
Airplane Model 
 
 
Airplane Serial 
Numbers 
 
 
 
Location 
 
Inches 
from 
Datum 
 
 
Capacity 
(pounds) 
 
Max. 
Load 
(p.s.f.) 
C.G. 
Inches 
from 
Datum 
NA-265 
NA-265-20 
NA-265-30 
265-1 thru 265-88 
270-1 thru 270-6 
277-1 thru 277-10 
285-1 thru 285-32 
Forward 145-206 250 100 180 
NA-265 276-1 thru 276-55 Forward 
Aft 
145-206 
298-320 
250 
170 
100 
50 
180 
315 
NA-265 
Modified per 
NOTE 7(a) 
265-1 thru 265-88 
276-1 thru 276-55 
Forward 
Aft 
145-206 
298-320 
270 
340 
100 
50 
180 
309 
 
 Fuel Capacity 
 Pressure Refueling 
(lbs.) 
Gravity Refueling 
(lbs.) 
C.G. Inches 
from Datum 
Fuel at 6.50 lb/gal. Total Usable Total Usable  
2 wing tanks 6,021 5,867 5,951 5,797 256 
1 fuselage tank 1,046 1,043 1,065 1,063 345 
  See NOTE 1(c) for system fuel 
 
 Oil Capacity 1.6 gal./engine, 12 pounds each.  C.G. is 324 inches from datum. 
  This weight must be included in the aircraft empty weight. 
 
 Maximum Operating 45,000 feet 
   Altitude 
  NOTE: Pressure cabin service life is based on the following pressurization limits which 
must not be exceeded. 
 
Airplane Model Airplane Altitude (feet) Cabin Altitude (feet) 
NA-265, NA-265-20, 
and NA-265-30 
Sea Level to 8,000 
8,000 to 45,000 
Ambient Pressure 
8,000

A2WE 
 -5- Rev. 28 
I. Model NA-265, Model NA-265-20, Model NA-265-30   (cont’d) 
 Serial Numbers Eligible 
 
 
Civil Model 
Rockwell 
International 
Serial No. 
 
Military 
Model 
Military Model 
Deviation 
NR Report No. 
NA-265 
 
265-1 thru 265-88 
276-1 thru 276-55 
USAF T-39A NA-62-399 
NA-265-20 270-1 thru 270-6 USAF T-39B NA-62-636 
NA-265-30 277-1 thru 277-10 
285-1 thru 285-32 
USAF T-39B NA-62-637 
 
  NOTE: Military Aircraft bearing the above serial numbers and having been issued 
Form ACA-970, Conformity Certificate - Military Aircraft, are eligible for 
FAA Certificate of Airworthiness when brought into the type design 
configuration as referenced in the deviation report.  In addition, a supplemental 
name plate must be installed adjacent to the original name plate, listing the 
name of the modifier, the date of modification, and the civil model designation. 
The original name plate, however, must not be removed.  See NOTE 5. 
 
 Fatigue Life Limits See NOTE 3(b). 
 
II. Model NA-265-40 (Transport Aircraft), Approved April 17, 1963 
 
 Engines 2 Pratt & Whitney Turbo Wasp JT12A-6A  
  or 2 Pratt  & Whitney Turbo Wasp JT12A-8 
 
  NOTE: Engines may be intermixed on airplane S/N 282-1 through 282-97.  See FAA 
Approved Airplane Flight Manual for Operating Limitations.   
   Airplane S/N 282-98 and subsequent require two JT12A-8 engines. 
 
 Fuel Commercial Aircraft Turbine Engine Fuel conforming to PWA Specification PWA 522 
as revised. 
 
 Fuel Controls Hamilton Standard JFC-46-8 Hydro-Mechanical Controls (JT12A-8 engine) 
 
  Hamilton Standard JFC-46-4 Hydro-Mechanical Controls (JT12A-6A engine) 
 
 Engine Limits See Section I for Engine Model JT12A-6A, Engine Limits 
  Engine Model (See Fatigue Life Limits Data for All Models and NOTE 7(d))     JT12A-8 
 
  Static thrust (See Engine Data Sheet 1E9, NOTE 5). 
   Takeoff (5 min.)  3,300 lbs. 
   Maximum continuous  3,000 lbs. 
   Maximum permissible engine rotor  operating speed 16,700 r.p.m. 
 
  Maximum permissible gas temperature at the turbine outlet 
   Takeoff 718°C 1,325°F 
   Maximum continuous 655°C 1,211°F 
   Maximum acceleration (2 min.) 718°C 1,325°F 
   Starting (momentary) 525°C    977°F 
 
  Oil inlet temperature 121°C    250°F 
 
  Maximum permissible air bleed extraction of total engine airflow 
   Two engine operation (each engine) 
   Idle to maximum continuous 4.0% 
   Maximum continuous through takeoff 3.0%

A2WE 
 -6- Rev. 28 
II. Model NA-265-40     (cont’d) 
 Engine Limits  (cont’d) One engine operation 
   Idle to maximum continuous 4.4% 
   Maximum continuous through takeoff 3.7% 
 
  NOTE: Thrust setting:  Appropriate thrust setting curves (EPR) in FAA Approved 
Airplane Flight Manual must be used for control of the engine thrust. 
 
 Oil Aircraft Turbine Engine Lubricant conforming to P&W Specification PWA 521, as 
revised. 
 
 Airspeed Limits  (CAS) 
 S/N 282-1 thru 
282-62 not 
modified 
per Note 6 
S/N 282-1 thru 
282-62 
modified per 
Note 6 
SN 282-63 
& subsequent 
VMO (Max. operating) (at S.L.) 333K 350K 
VMO (at 21,340 ft.) 346K - - 
MMO (above 21,340 ft.) .765M - - 
VMO (at 21,130 ft.) - - 365K 
MMO (above 21,130 ft. - - .800M 
VA (Maneuvering) (at S.L.) 195K 197K 
VA  (at 42,500 ft.) 218K - - 
VA  (at 44,180 ft.) - - 220K 
MA  (above 42,500 ft. .765M - - 
MA  (above 44,180 ft.) - - .800M 
VFE (Flaps down 15.7°) (66% indicated) 225K 225K 
VFE (Flaps down 23.5°) (100% indicated) 179K 179K 
VLO (Landing gear operating) 179K 179K 
VLE (Landing gear extended) 179K 179K 
VSB (Speed brake extension) Any speed Any speed 
 (Speed brake retraction) Any speed Any speed 
V (Fuel jettisoning) Any speed Any speed 
VTR (Minimum operating, max. reverse thrust) 60K 60K 
 
  NOTE: For variation between values shown and corresponding IAS limits, for the 
airspeed system installed, refer to FAA Approved Airplane Flight Manual. 
 
   For Buffet Envelope and Limit Maneuvering Load Factor variation with 
airspeed, weight, fuel, loading and altitude, refer to FAA Approved Airplane 
Flight Manual.

A2WE 
 -7- Rev. 28 
II. Model NA-265-40     (cont’d) 
 C.G. Range Model NA-265-40 (Transport Aircraft) 
  (S/N 282-1 thru 282-85 & S/N 282-90 thru 282-199) 
  Gross weight vs. Center of Gravity 
   (Approved Limits) 
 
 
 
  The landing gear retraction moment is -500 in.-lbs. and results in a negligible 
  movement of the C.G.  When the airplane is loaded within the above C.G. envelope 
  limits as applicable at both start of takeoff and zero fuel weights, and the 
  restrictions  concerning crew and passenger movement specified in the FAA 
  Approved Load and Balance Schedule are complied with, the airplane will remain 
  within the approved C .G. limits.

A2WE 
 -8- Rev. 28 
II. Model NA-265-40     (cont’d) 
 
 
  The landing gear retraction moment is -500 in.-lbs. and results in a negligible 
  movement of the C.G.  When the airplane is loaded within the above C.G. envelope 
  limits as applicable at both start of takeoff and zero fuel weights, and the 
  restrictions  concerning crew and passenger movement specified in the FAA 
  Approved Load and Balance Schedule are complied with, the airplane will remain 
  within the approved C .G. limits.

A2WE 
 -9- Rev. 28 
II. Model NA-265-40     (cont’d) 
 Maximum Weight (in Pounds) 
 
 
 Minimum Crew 2 pilots 
 
  NOTE: The delivery configuration minimum flight crew is one pilot and one flight 
crew assistant.  No persons other than the flight crew may be carried.  See FAA 
Approved Airplane Flight Manual (Addendum A) for additional limitations. 
 
 Maximum Passengers 7 
 
 Maximum Baggage 
 
Location 
In. from 
Datum 
Capacity 
(pounds) 
Capacity* 
(pounds) 
Max. load 
(p.s.f.) 
In. from 
Datum 
Forward 145-206 200 270 100 170 
Aft 298-320 340 510   50 311 
  *When airplane is modified per NOTE 7(e). 
 
 Fuel Capacity Fuel at 6.70 lbs./gal.: 
 Pressure Refueling 
(lbs.) 
Gravity Refueling 
(lbs.) 
 
C.G. Inches 
 Total Usable Total Usable from Datum 
2 wing tanks 6,206 6,047 6,134 5,975 256 
1 fuselage tank 1,078 1,075 1,098 1,096 345 
 
  See NOTE 1(c) for system fuel. 
 
 Oil Capacity 1.6 gal./engine, 12 pounds each.  C.G. is 324 inches from Datum. 
  This weight must be included in the aircraft empty weight. 
 
 Maximum Operating Altitude 45,000 feet 
  NOTE: Pressure cabin service life is based on the following pressurization limits which 
must not be exceeded: 
  Airplane Altitude Cabin Altitude 
  Sea Level to 21,000 ft. Sea Level 
  21,000 ft. to 40,000 ft. 8.2 p.s.i. differential 
  40,000 ft. to 45,000 ft. 8,000 ft. altitude 
 
 Serial Nos. Eligible 282-1 through 282-199 
 
 Fatigue Life Limits See NOTE 3(b) 
Airplane Model NA-265-40 NA-265-40 Modified Per: NA-265-40 
  
 
S/N 282-1 thru S/N 
282-97 
 
S/N 282-98 
and sub-
sequent 
 
 
S/N 282-1 thru 282-97 only  
NOTE 7(c)                          NOTE 7(f) 
 
 
NOTE 
7(e) 
S/N 282-86 
thru -89 
(FAA) Note 
7(e) 
Equipped with  
Brake P/N 
9542384 9542384 9550338 9543102 9543102 9550338 9550338 9550338 9550338 
Anti-Skid Installed 
and Operational 
no yes no no yes no no no yes 
Ramp and Taxi 17,760 18,650 19,035 17,760 18,650 18,650 19,035 19,922 20,372 
With JT12A-8 
Start of Takeoff 
Airborne 
 
17,450 
17,375 
 
18,650 
18,650 
 
18,650 
18,650 
 
17,450 
17,375 
 
18,650 
18,650 
 
18,650 
18,650 
 
18,650 
18,650 
 
19,612 
19,537 
 
20,172 
20,172 
With JT12A-6A 
Start of Takeoff 
Airborne 
17,450 
17,375 
18,340 
18,340 
N/A 
N/A 
17,450 
17,450 
18,650 
18,265 
18,650 
18,265 
18,650 
18,650 
N/A 
N/A 
N/A 
N/A 
Zero Fuel 
Landing 
12,800 
14,000 
12,800 
15,000 
12,800 
17,500 
12,800 
14,000 
12,800 
17,500 
12,800 
17,500 
12,800 
17,500 
12,800 
17,500 
13,300 
17,500

A2WE 
 -10- Rev. 28 
III. Model NA-265-60 (Transport Aircraft), Approved April 28, 1967 
 
 Engines 2 Pratt and Whitney Turbo Wasp JT12A-8 
 
 Fuel Commercial Aircraft Turbine Engine Fuel conforming to PWA Specification 
  PWA 522 as revised. 
 
 Fuel Controls Hamilton Standard JFC-46-8 Hydro-Mechanical Controls 
 
 Engine Limits See Section II for Engine Model JT12A-8, Engine Limits. 
 
 Oil Aircraft Turbine Engine Lubricant conforming to PWA Specification PWA 521, as  
  revised. 
 
 Airspeed Limits VMO (Max. operating) (at S.L.) 350K 
  VMO  (at 21,130 ft.) 365K 
  VMO  (above 21,130 ft.) .800M 
  VA  (at S.L.) 195K 
  VA  (at 44,300 ft.) 220K 
  MA  (above 44,300 ft.) .800M 
  VFE (Flaps Down 16.7 deg.) (66% ind.) 225K 
  VFE (Flaps Down 25 deg.) (100% ind.) 180K 
  VLO (Landing Gear Operating)  180K 
  VLE (Landing Gear Extended)  180K 
  VSB (Speed Brake Extension)  Any Speed 
   (Speed Brake Retraction)  Any Speed 
  V (Fuel Jettisoning)  Any Speed 
  VTR (Minimum operating, Full reverse thrust) 60K 
 
  NOTE: For variation between values shown and corresponding IAS limits, for the 
airspeed system installed, refer to FAA Approved Airplane Flight Manual. 
 
   For Buffet Envelope and Limit Maneuvering Load Factor variation with 
airspeed, weight, fuel loading, and altitude, refer to FAA Approved Airplane 
Flight Manual.

A2WE
-11-  Rev. 28
III. Model NA-265-60  (cont'd)
C.G. Range  Model NA-265-60 (Transport Aircraft)
Serial Numbers 306-1 Thru 306-63 (See NOTE 8)
Gross Weight Vs. Center of Gravity
(Approved Limits)
21  LANCING SEAR  PATENCH
20
AIRPLANE GROSS WEIGHT -- THOUSANDS OF POUNDS  19
18
17
16
- FORWARD FUGHT LIMIT-
20  28  32  36
AIRPLANE CENTER OF GRAVITY -- % MAC

A2WE 
 -12- Rev. 28 
III. Model NA-265-60   (cont’d) 
 
 
  The landing gear retraction moment is -475 in.-lb. and results in a  negligible movement 
of the C.G.  When the airplane is loaded within the above C.G. envelope limits as 
applicable at both start of takeoff and zero fuel weights and the restrictions concerning 
crew and passenger movement specified in the FAA Approved Load and Balance 
Schedule are complied with, the airplane will remain within the approved C.G. limits. 
 
 Maximum Weights (In pounds - With or without anti-skid equipment) 
 
  Ramp and taxi 20,372 
  Start of takeoff 20,172 
  Airborne  20,172 
  Zero fuel  13,250 (S/N 306-1 throught 306-63) (See NOTE 8) 
  Zero fuel  13,800 (S/N 306-64 and subsequent) (See NOTE 8) 
  Landing  17,500 
 
 Minimum Crew 2 pilots 
 
  NOTE: Delivery configuration minimum flight crew is one pilot and one flight crew 
assistant.  No persons other than the flight crew may be carried.  See FAA 
Approved Airplane Flight Manual (Addendum A) for additional limitations. 
 
 Maximum Passengers 10

A2WE 
 -13- Rev. 28 
III. Model NA-265-60   (cont’d) 
 Maximum Baggage  
 
Location 
Inches from 
Datum 
Capacity 
(Pounds) 
Max. Load 
(p.s.f.) 
Inches from 
Datum 
Forward 143-206 300 100 170 
Aft 336-371 510 80 342 
 
 Fuel Capacity Fuel at 6.70 lbs./gal. 
 
 Pressure Refueling 
(lbs.) 
Gravity Refueling 
(lbs.) 
 
C.G. Inches 
 Total Usable Total Usable from Datum 
2 wing tanks 6,206 6,047 6,134 5,975 273 
1 fuselage tank 1,078 1,075 1,098 1,096 383 
 
  See NOTE 1(c) for system fuel 
 
 Oil Capacity 1.6 gal./engine, 12 pounds each.  C.G. is 362 inches from Datum. 
  This weight must be included in the aircraft empty weight. 
 
 Maximum Operating Altitude 45,000 feet 
  NOTE: Pressure cabin service life is based on the following pressurization limits which 
must not be exceeded: 
 
   Airplane Altitude Cabin Altitude 
   Sea Level to 21,000 ft. Sea level 
   21,000 ft. to 40,000 ft. 8.2 p.s.i. differential 
   40,000 ft. to 45,000 ft. 8,000 ft. altitude 
 
 Serial Nos. Eligible 306-1 through 306-199 
 
 Fatigue Life Limits See NOTE 3(b) 
 
IV. Model NA-265-70 (Transport Aircraft), Approved June 17, 1970 
 
 Engines 2 Pratt and Whitney Turbo Wasp JT12A-8 
 
 Fuel Commericial Aircraft Turbine Engine Fuel conforming to PWA Specification PWA 522, 
as revised. 
 
 Fuel Controls Hamilton Standard JFC-46-8 Hydro-Mechanical Controls 
 
 Engine Limits See Section II for Engine Model JT12A-8, Engine Limits 
 
 Oil Aircraft Turbine Engine Lubricant conforming to PWA Specification PWA 521, as revised. 
 
 Airspeed Limits VMO (Max. operating) (at S.L.) 350K 
  (CAS) VMO  (at 21,130 ft.) 365K 
   MMO  (above 21,130 ft.) .800M 
 
  VA (Maneuvering) (at S.L.) 221K 
  VA  (at 40,000 ft.) 243K 
  MA  (above 40,000 ft.) .800M 
 
  VFE (Flaps Down 16.7°) (66% indicated) 225K 
  VFE (Flaps Down 25°) (100% indicated) 180K 
  VLO (Landing Gear Operating)  180K 
  VLE (Landing Gear Extended)  180K

A2WE 
 -14- Rev. 28 
IV. Model NA-265-70    (cont’d) 
 Airspeed Limits (cont’d) VSB (Speed Brake Extension)  Any Speed 
   (Speed Brake Retraction)  Any Speed 
  V (Fuel Jettisoning)  Any Speed 
  VTR (Minimum operating, Full reverse thrust) 60K 
 
  NOTE: For variation between values shown and corresponding IAS limits, for the 
airspeed system installed, refer to FAA Approved Airplane Flight Manual. 
 
   For Buffet Envelope and Limit Maneuvering Load Factor variation with 
airspeed, weight, fuel loading, and altitude, refer to FAA Approved Airplane 
Flight Manual. 
 
 C.G. Range Model NA-265-70  (Transport Aircraft) 
  Gross Weight vs. Center of Gravity 
   (Approved Limits) 
 
 
 
  The landing gear retraction moment is +591 in.-lb. and results in a negligible movement 
of the C.G.  When the airplane is loaded within the above C.G. envelope limits as 
applicable at both start of takeoff and zero fuel weights and the restrictions concerning 
crew and passenger movement specified in the FAA Approved Load and Balance 
Schedule are complied with, the airplane will remain within the approved C.G. limits.

A2WE 
 -15- Rev. 28 
IV. Model NA-265-70    (cont’d) 
 Maximum Weights (In pounds - With or without anti-skid equipment) 
  Ramp and taxi 21,200 
  Start of takeoff 21,000 
  Airborne  21,000 
  Zero fuel  14,300 
  Landing  18,500 
 
  NOTE: Fuel jettison valves are required for operation in excess of 105 percent of the 
maximum landing weight.  Refer to the FAA Approved Airplane Flight Manual 
for fuel jettisoning procedures.  See NOTE 1. 
 
 Minimum Crew 2 pilots 
 
  NOTE: Delivery configuration minimum flight crew is one pilot and one flight crew 
assistant.  No persons other than the flight crew may be carried.  See FAA 
Approved Airplane Flight Manual (Addendum A) for additional limitations. 
 
 Maximum Passengers 10 
 
 Maximum Baggage 
 
Location 
Inches from 
Datum 
Capacity 
(Pounds) 
Max. Load 
(p.s.f.) 
Inches from 
Datum 
Forward 143-206 300 100 170 
Aft 336-371 510 80 342 
 
 Fuel Capacity Fuel at 6.70 lbs./gal. 
 
 Pressure Refueling 
(lbs.) 
Gravity Refueling 
(lbs.) 
 
C.G. Inches 
 Total Usable Total Usable from Datum 
2 wing tanks 6,206 6,047 6,134 5,975 273 
1 fuselage tank 1,338 1,333 1,369 1,365 383 
 
  See NOTE 1(c) for system fuel 
 
 Oil Capacity 1.6 gal./engine, 12 pounds each.  C.G. is 362 inches from Datum. 
  This weight must be included in the aircraft empty weight. 
 
 Maximum Operating 45,000 feet 
   Altitude 
  NOTE: Pressure cabin service life is based on the following pressurization limits which 
must not be exceeded: 
 
   Airplane Altitude Cabin Altitude 
   Sea Level to 21,000 ft. Sea Level 
   21,000 ft. to 40,000 ft. 8.2 p.s.i. differential 
   40,000 ft. to 45,000 ft. 8,000 ft. altitude 
 
 Serial Nos. Eligible NA-370-1 through 370-199 
 
 Fatigue Life Limits See NOTE 3(b) 
 
V. Model NA-265-80 (Transport Aircraft), Approved November 30, 1973  (FAA Flight Inspection Aircraft),
 Approved April 15, 1975     NOTE:  See Serial Numbers Eligible, page 20 
 
 Engines 2 General Electric Aft Turbofan CF700-2D-2 
  "B" Suffix Serial Number

A2WE 
 -16- Rev. 28 
V - Model NA-265-80    (cont’d) 
 Fuel Aviation Turbine Fuels conforming to General Electric Specification D50TF2, Current 
Revision 
 
 Fuel Controls General Electric MFC-2 
 
 Engine Limits Engine Model CF700-2D-2 
 
  Static Thrust (see Engine Data Sheet E7EA, as revised) 
   Takeoff 4,500 lbs. 
   Maximum Continuous 4,120 lbs. 
   Maximum Permissible Engine Rotor Speed 16,700 r.p.m. (101.2%) 
   Maximum Permissible Fan Rotor Speed   9,000 r.p.m. (105.0%) 
 
  Maximum Permissible Exhaust Gas Temperatures 
   Takeoff (5 min.) 1365°F (741°C) 
   Maximum Continuous 1335°F (724°C) 
   Starting (2 sec.) 1670°F (910°C) 
 
  Oil Reservoir Temperature 
   Steady State 365°F (185°C) 
 
  Maximum Permissible Bleed Air 
   Extraction of Compressor Inlet Airflow 6.0% 
 
  NOTE: Thrust Setting:  Appropriate Thrust Setting Curves (EPR) in FAA Approved 
Airplane Flight Manual must be used for Control of Engine Thrust. 
 
  If the EGT obtained, when using the chart MAXIMUM CONTINUOUS THRUST EPR 
SETTING, is less than 670° C. below 20,000 feet or 695° at or above 20,000 feet 
pressure altitude, increased performance may be obtained by increasing the EGT to 
670°/695° C.  If the EGT obtained when setting the chart EPR exceeds 670°/695° C., 
then maintain chart EPR setting and observe the 724° C. EGT limit. 
 
 Oil Aircraft Gas Turbine Lubricating Oil conforming to General Electric Specification 
D50TFI, current revision. 
 
 Airspeed Limits VMO (Max. operating) (at S.L.) 350K 
  (CAS) VMO  (at 21,200 ft.) 365K 
   MMO  (above 21,200 ft.) .800M 
 
   VA (Maneuvering) (at S.L.) 221K 
   VA  (at 40,000 ft.) 243K 
   MA  (above 40,000 ft.) .800M 
 
   VFE (Flaps Down 16.7º) (66% indicated) 225K 
   VFE (Flaps Down 25º) (100% indicated) 180K 
   VLO (Landing Gear Operating)  180K 
   VLE (Landing Gear Extended)  180K 
    (Landing-Taxi Lights Extended Speed) 250K 
   VSB (Speed Brake Extension)  Any Speed 
    (Speed Brake Retraction)  Any Speed 
 
  NOTE: For variation between values shown and corresponding IAS limits, for the 
airspeed system installed, refer to FAA Approved Airplane Flight Manual. 
 
   For Buffet and Stall Warning Envelope and Limit Maneuvering Load Factor 
variation with airspeed, weight, fuel loading, and altitude, refer to FAA 
Approved Airplane Flight Manual.

A2WE 
 -17- Rev. 28 
V. Model NA-265-80    (cont’d) 
 C.G. Range Model NA-265-80  (Transport Aircraft) 
  Gross Weight vs. Center of Gravity 
   (Approved Limits) 
 
 
 
  The landing gear retraction moment is +591 in.-lb. and results in a negligible movement 
of the C.G.  When the airplane is loaded within the above C.G. envelope limits as 
applicable at both start of takeoff and zero fuel weights and the restriction concerning 
crew and passenger movement specified in the FAA Approved Load and Balance 
Schedule are complied with, the airplane will remain within the approved C.G. limits.

A2WE 
 -18- Rev. 28 
V. Model NA-265-80    (cont’d) 
 
 
  *NOTE: The FAA Flight Inspection Aircraft Serial Nos. are 380-5, -10, -14, -16, -18,  
   -20, -22, -24, -26, -28, -29, -31, -33, -35, and -37 
 
 Maximum Weights (In pounds) 
 Ramp and Taxi 23,500 
 Start of Takeoff 23,300 
 Airborne 23,300 
 Zero Fuel 15,620 
 Landing 22,000 
 
 Minimum Crew 2 pilots 
 
  NOTE: Delivery configuration minimum flight crew is one pilot and one flight crew 
assistant.  No persons other than the flight crew may be carried.  See FAA 
Approved Airplane Flight Manual (Addendum A) for additional limitations. 
 
 Maximum Passengers 10 (4 cabin occupants - FFIA) 
 
 Maximum Baggage 
 
Location 
Inches from 
Datum 
Capacity 
(Pounds) 
Max. Load 
(p.s.f.) 
Inches from 
Datum 
FFIA Cabin 215-241 180 100 237 
Forward 143-206 300 100 170 
Aft 336-371 510 80 342

A2WE 
 -19- Rev. 28 
V. Model NA-265-80    (cont’d) 
 Fuel Capacity Fuel at 6.70 lbs./gal. 
 
 Pressure Refueling 
(lbs.) 
Gravity Refueling 
(lbs.) 
 
C.G. Inches 
 Total Usable Total Usable from Datum 
2 wing tanks 6,206 6,047 6,134 5,975 273 
1 fuselage tank 1,078 1,333 1,369 1,365 383 
  Total Fuel 7,544 7,380    
 
  See NOTE 1(c) for System Fuel. 
 
 Oil Capacity 4 qt./tank/engine, 15 pounds total.  C.G. is 364 inches from Datum. 
  This weight must be included in the aircraft empty weight. 
 
 Maximum Operating 45,000 feet 
   Altitude 
  NOTE: Pressure cabin service life is based on the following pressurization limits which 
must not be exceeded. 
 
   Airplane Altitude Cabin Altitude 
   Sea Level to 21,000 ft. Sea Level 
   21,000 ft. to 40,000 ft. 8.2 p.s.i. differential 
   40,000 ft. to 45,000 ft. 8,000 ft. altitude 
 
 Serial Nos. Eligible 380-1 through 380-199 (380-5, -10, -14, -16, -18, -20, -22, -24, -26, -28, -29, 
  -31, -33, -35, -37 for FFIA).  Modification in accordance with Sabreliner Corporation 
Top Drawing RSC380016 is required to change an FAA Flight Inspection Aircraft 
(FFIA) to Transport configuration. 
 
 Fatigue Life Limits See NOTE 3(b) 
 
VI. Model NA-265-65 (Transport Aircraft), Approved November 28, 1979 
 
 Engines 2 AiResearch Mfg. Co. TFE731-3R-1D Turbofan 
 
 Fuel Turbine Engine Commercial Aircraft Fuel Conforming to AiResearch 
  Mfg. Co. Specifications EMS53111, EMS53112, and EMS53116 
 
 Fuel Controls AiResearch Mfg. Co. P/N 3070800-7 (Hydromechanical) 
  AiResearch Mfg. Co. P/N 2101144-2 (Electronic Computer) 
 
 Engine Limits Static Thrust (see Engine Data Sheet E6WE-5) 
   Non-APR APR 
  Takeoff (5 min.) 3700 lbs. 3880 lbs. 
 
  Maximum Continuous 3700 lbs. 
 
  Low Pressure Compressor 21,000 r.p.m. 
  (LPC), Rotor Speed N1 (101.5%) 
 
  High Pressure Compressor 29,692 r.p.m. 29,989 r.p.m. 
  (HPC), Rotor Speed N2 (100%) (101%) 
 
  Interstage Turbine Temp. (ITT) 
  Takeoff (5 min.) 1665°F (907°C) 1705°F 
(929°C) 
  Maximum Continuous 1625°F (885°C) 
  Starting 1665°F (907°C)

A2WE 
 -20- Rev. 28 
VI. Model NA-265-65   (cont’d) 
 Engine Limits (cont’d) Fan Gearbox Oil Temperature 
  Up to 30,000 Feet 260°F (127°C) 
  Above 30,000 Feet 284°F (140°C) 
  Maximum Transient (2 min).) 300°F (149°C) 
 
  Bleed Air Extraction Of Compressor (Core) Airflow 
  Total 8% 
  Low Pressure Compressor Bleed 5% 
  High Pressure Compressor Bleed 
   Above 30% Max. Continuous 3% 
   Below 30% Max. Continuous 5% 
 
  NOTE: Thrust Setting:  Appropriate thrust setting curves (NI) in FAA Approved 
Airplane Flight Manual shall be used for setting engine thrust. 
 
 Oil Synthetic Commercial Turbine Engine Lubricating Oil Conforming to  
  AiResearch Mfg. Co. Specification EMS53110, Type 2 
 
 Airspeed Limits VMO (Max. Operating) (at S.L.) 347K 
   (CAS) VMO  (at 25,000 ft.) 347K 
  MMO  (above 25,000 ft.) .825M 
 
  VA (Maneuvering) (S.L. to 45,000 ft.) 209K 
 
  VFE (Flaps Down 10°)  250K 
  VFE (Flaps Down 20°)  225K 
  VFE (Flaps Down 36°)  180K 
  VLO (Landing Gear Operating)  180K 
  VLE (Landing Gear Extended)  180K 
 
  VSP (Spoiler Extension)  Any Speed 
   (Spoiler Retraction)  Any Speed 
  VTR (Minimum Operating, Full Reverse Thrust) 60K 
   
  When equipped with optional speed brake: 
   
  VSB  (Speed Brake Extension)                              Any Speed 
        (Speed Brake Retraction)                              Any Speed

A2WE 
 -21- Rev. 28 
VI. Model NA-265-65   (cont’d) 
 C.G. Range 
 
 
  The landing gear retraction moment is -250 in.-lb. and results in a negligible movement 
of the C.G.  When the airplane is loaded within the above C.G. envelope limits as 
applicable at both start of takeoff and zero fuel weights and the restrictions concerning 
crew and passenger movement specified in the FAA Approved Load and Balance 
Schedule are complied with, the airplane will remain within the approved C.G. limits. 
 
 Maximum Weights (In pounds - with or without anti-skid equipment) 
 
  Ramp and Taxi 24,000 
  Start of Takeoff 24,000 
  Airborne 24,000 
  Zero Fuel 16,250 
  Minimum Flight 13,730 
  Landing 21,755 
 
 Minimum Crew 2 Pilots 
 
  NOTE: Delivery configuration minimum flight crew is one pilot and one flight crew 
assistant.  No persons other than the flight crew may be carried.  See FAA 
Approved Airplane Flight Manual (Addendum B) for additional limitations.

A2WE 
 -22- Rev. 28 
VI. Model NA-265-65   (cont’d) 
 Maximum Passengers 10 
 
 Maximum Baggage  
 
Location 
Inches from 
Datum 
Capacity 
(Pounds) 
Max. Load 
(p.s.f.) 
Inches from 
Datum 
Forward 143-206 300 100 170 
Aft 336-371 510 80 342 
 
 Fuel Capacity Fuel at 6.70 lbs./gal. 
 
 Pressure Refueling 
(lbs.) 
Gravity Refueling 
(lbs.) 
 
C.G. Inches 
 Total Usable Total Usable from Datum 
465-Series: 
465-1 thru -14 
     
2 wing tanks 7,162 7,040 6,914 6,793 272 
1 fuselage tank (aft) 1,078 1,075 1,098 1,095 383 
1 fuselage tank (fwd) 393 377 393 377 206 
465-Series: 
465-15 thru -999 
     
2 wing tanks 7,313 7,192 6,914 6,793 272 
1 fuselage tank (aft) 1,078 1,075 1,098 1,095 383 
1 fuselage tank (fwd) 393 377 393 377 206 
306 Series: 
306-1 thru -135, & 
-137 thru -146 
     
2 wing tanks 7,313 7,192 6,914 6,793 272 
1 fuselage tank (aft) 1,078 1,075 1,098 1,095 383 
 
  See NOTE 1(c) for System Fuel. 
 
 Oil Capacity 1.5 gal./engine, 12 pounds each.  C.G. is 362 inches from datum. 
  This weight must be included in the aircraft empty weight. 
 
 Maximum Operating 45,000 feet 
   Altitude 
  NOTE: Pressure cabin service life is based on the following pressurization limits which 
must not be exceeded: 
 
   Airplane Altitude Cabin Altitude 
   (465 Series) 
   Sea Level to 23,000 ft. Sea Level 
   23,000 ft. to 45,000 ft. Sea Level to 8,000 ft. 
 
   (306 Series) 
   Sea Level to 21,000 ft. Sea Level 
   21,000 ft. to 40,000 ft. 8.2 p.s.i. differential 
   40,000 ft to 45,000 ft. 8,000 ft. altitude 
 
  NOTE: Passengers are required to wear oxygen masks above 41,000 feet unless the 
airplane is inspected in accordance with the Annual Pressurization Control 
System Leakage & Structural Integrity Check-Out Procedure in Chapter 5 of 
the Model NA-265-65 Maintenance Manual, Report No. SR-78-030.

A2WE 
 -23- Rev. 28 
VI. Model NA-265-65   (cont’d) 
 Serial Nos. Eligible (465-Series) 
  465-1 through 465-999 
 
  NOTE: Model NA-265-60, S/N 306-136 has been modified in accordance with 
Rockwell International Drawing 60S-136-0011 and reidentified as Model NA-
265-65, S/N 465-1. 
 
  (306-Series) 
  306-1 through 306-135 and 306-137 through 306-146 
 
  NOTE: Model NA-265-60 serial number aircraft noted are eligible for modification and 
reidentification to Model NA-265-65, 306-Series aircraft in accordance with 
Rockwell International Drawing 60S-001-0012. 
 
 Fatigue Life Limits See NOTE 3(b) 
 
 
Data Pertinent to All Models (except as listed) 
 
 Other Operating Limitations Required FAA Approved Airplane Flight Manual 
  NA-265 NAR Report No. NA-61-3 
  NA-265-20 NAR Report No. NA-61-3 
  NA-265-30 NAR Report No. NA-61-3 
  NA-265-40 (S/N 282-1 through 282-97)  NAR Report No. NA-62-1300 
  NA-265-40 (S/N 282-98 & Subsequent)  NAR Report No. NA-72-25 
  NA-265-60 NAR Report No. NA-66-1030 
  NA-265-65 Rockwell Report No. SR-77-006 
  NA-265-70 NAR Report No. NA-69-422 
  NA-265-80 Rockwell Report No. NA-72-928 (and Appendix II for FFIA)   
   FFIA aircraft modified by Sabreliner Corporation Top Drawing RSC380016 
require AFM NA-72-928 with AFMS 80-52, 80-53, and 80-54 
 
 Datum Fuselage Station zero is the reference datum point for horizontal C.G.'s 
  and it is located at the most forward point of the radome. 
 
 MAC 100.60 in. (L.E. of MAC at 225.1 inches from datum) 
   NA-265, NA-265-20, NA-265-30, and NA-265-40 
  100.60 in. (L.E. of MAC at 242.1 inches from datum) 
   NA-265-60, NA-265-70, and NA-265-80 only 
  103.27 in. (L.E. of MAC at 243.9 inches from datum) 
   NA-265-65 
 
 Leveling Means Longitudinal: Lugs mounted on LH side of nose wheel well beams 
  Lateral: Lugs mounted on LH and RH nose wheel well beams 
 
 Control Surface Movements Horizontal Stabilizer* -  9.0° to   -1.0° 
  Horizontal Stabilizer 
    (NA-265-65- only) -12° 30’ to    0° 0’ 
  Horizontal Stabilizer 
    (NA-265-60 S/N’s 306-78, 
    -81, -86 thru -146***, 
    NA-265-70 & -80) -  8.0° to     0.0° 
  Elevator -22.0° to +11.0° 
  Aileron* -16.0° to +15.0° Neutral  -0.5° 
  Aileron (NA-265-60, -70 & 
    -80 only) -15.5° to +15.5° Neutral  0.0° 
  Aileron (NA-265-65 only) -15° to +15°    Neutral  0.0° 
  Aileron tab -12.0° to +12.0° 
  Rudder -25.0° to +25.0° 
  Rudder tab -15.0° to +15.0°

A2WE 
 -24- Rev. 28 
 Control Surface Movements Wing flap -  1.5° to +23.5° Retracted -1.5° 
 (con’t) Wing flap (NA-265-60, -70, 
    & -80 only) -  0.0° to +25.0° Retracted -0.0° 
  Wing flap (NA-265-65 only)        0° to   36°    Retracted  0.0° 
  Speed brake** +47.0° (from the Closed Position) 
  Wing spoilers (NA-265-65 only)        0° to 45° 
 
   * All Models Except as Noted 
   ** All Models Except NA-265-65 
   *** NA-265-60 S/N's 306-1 through -77, -79, -80, and -82 through -85 when modified 
by Sabreliner Drawings 306-520032, 306-510104, 306-540210, 306-931003, and 
306-522103 to the latest revisions. 
 
 Certification Basis CAR 4b, dated December 31, 1953, Amendment 4b-1 through 4b-9 thereto, Special Civil 
Air Regulation No. SR 422B Item 2 and the Special Conditions set forth in Attachment 
"A" of FAA letter to NAA dated October 8, 1959, FAA letter to NAA dated January 30, 
1962, Special Conditions No. 25-11-WE-4 dated August 29, 1969 (as applicable to NA-
265-65, NA-265-70, and NA-265-80 only), Special Conditions No. 25-92-WE-26 dated 
January 28, 1980 (NA-265-65 only), and FAR 36.1(c) and 36.2, dated December 1, 1969 
(as applicable to NA-265-70 and NA-265-80 only). 
 
  The certification basis for the NA-265-65 is the same as above except the NA-265-65 has 
complied with the following requirements: 
 
   FAR Part 36, effective December 1, 1969, and Amendments 36-1 through 36-9, 
inclusive. 
 
   Even though not included in the type certification basis defined by FAR 21.101, the 
NA-265-65 has complied with the air pollution requirements of EPA Regulations, 
Part 87, as implemented by SFAR 27, effective February 1, 1974, and Amendments 
27-1 and 27-2, as applicable to Class TI engines. 
 
   FAR Part 25 effective February 1, 1965:  FAR Parts 25.177, 25.181, 25.934, and 
25.1091(d)(2). 
 
   FAR Part 25, Amendment 25-7 effective November 4, 1965:  FAR Parts 25.171, 
25.173, and 25.175. 
 
   FAR Part 25, Amendment 25-23 effective May 8, 1970:  FAR Parts 25.251 and 
25.253. 
 
   FAR Part 25, Amendment 25-40 effective May 2, 1977:  FAR Parts 25.933 and 
25.943. 
 
   FAR Part 25, Amendment 25-42 effective March 1, 1978:  FAR Part 25.255. 
 
  A fuel jettison system is not required for the Model NA-265-40 (when two JT12A-8 
engines are installed), nor the Models NA-265-60, NA-265-65, NA-265-70, and NA-265-
80 since these aircraft comply with FAR 25.1001(d) climb requirements, when operated 
at the maximum takeoff weights permitted by the respective FAA Approved Airplane 
Flight Manuals. 
 
  Model NA-265-65:  Width of main aisle.  An equivalent safety finding permits the main 
cabin aisle width to be 9" up to 25" above floor and 12" to 25" and more above the floor 
in lieu of the requirements of CAR 4b.362(h). 
 
  Models NA-265-40, NA-265-60, NA-265-65, NA-265-70, and NA-265-80:  These 
  airplanes have been shown to comply with the optional ditching requirements of CAR 
4b.361.  Overwater operation can be conducted when the airplane has been equipped and 
installation has been approved according to CAR 4b.361.  Model NA-265-40 aircraft 
which do not incorporate two overwing exits are not certified for ditching. 
 
  Model NA-265-65:  Ice protection.  Compliance has been demonstrated in accordance 
with CAR 4b.640 when ice protection equipment is installed per Airplane Master 
Equipment List SR-78-036 for 465 Series and SR-81-006 for 306 Series.

A2WE 
 -25- Rev. 28 
 Certification basis  (cont’d) FAA Exemption No. 26:  Issued August 13, 1959, grants exemption from 4b.350(e) and 
(f) for executive transport operation and from that portion of 4b.353(e)(1) which requires 
the wing flap control to be located on the top of the pedestal. 
 
  FAA Exemption No. 270:  Issued July 10, 1963, and clarified in FAA letter to NAA 
dated July 17, 1964, grants an exemption from CAR 4b.362(h) to permit a main 
passenger aisle width of 15 inches measured 25 inches or more from the floor for a 
passenger seating capacity of six with certain provisions. 
 
  FAA Exemption No. 588:  Issued October 7, 1966, grants an exemption from CAR 
4b.362(h) to permit a main aisle width of not less than 15 inches between the two 
aftermost seats on the aisle, measured 25 inches or more from the floor. 
 
  FAA Exemption No. 709:  Issued August 15, 1967, grants an exemption from CAR 
4b.362(h) to the extent necessary to permit type certification of the Model NA-265-60 
airplane with a main aisle width of 15 inches, in the aisle space of 25 inches and more 
from the floor, for a maximum passenger seating capacity of 10. 
 
  FAA Exemption No. 709A:  Issued March 28, 1970, amends Exemption 709 to 
  read:  "North American Rockwell Corporation" and extends it to cover 
  Model NA-265-70 and NA-265-80 airplanes, provided that their seating 
  capacities are no greater than the NA-265-60, and their seating arrange- 
  ment and exit accessibility are identical to those of the NA-265-60. 
 
 Production Basis Production Certificate No. 602: 
   All NA-265 Series aircraft except as noted below. 
 
  Production Certificate No. 323CE: 
   NA-265-60, S/N 306-139 and subsequent aircraft 
   NA-265-65, S/N 465-1 and subsequent aircraft (465-Series) (excepting S/N 465-4, 
465-11, and 465-12) 
   NA-265-65, S/N 306-1 through 306-135 and 306-137 through 306-146 aircraft (306-
Series) 
   NA-265-80, S/N 380-66 and subsequent aircraft 
 
  The following airplanes were certificated under the provisions of the Type Certificate in  
  lieu of a Production Certificate: 
   NA-265-60, S/N 306-137 and 306-138 
   NA-265-65, S/N 465-4, 465-11, and 465-12 
   NA-265-80, S/N 380-59 through 380-65 
 
 Required Equipment   The basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification.  All of the 
required equipment that must be installed, as well as optional equipment installation 
approved by the FAA are contained in the following: 
 
   NA-265     NAR Reports No. NA-59-759 or NA-61-646, as applicable; 
   NA-265-20  NAR Reports No. NA-59-759 or NA-61-646, as applicable; 
   NA-265-30  NAR Reports No. NA-59-759 or NA-61-646, as applicable; 
   NA-265-40  NAR Report No. NA-62-1271 (S/N 282-1 through 282-97); 
   NA-265-40  NAR Report No. NA-71-1162 (S/N 282-98 and subsequent aircraft); 
   NA-265-60  NAR Report No. NA-66-1071; 
   NA-265-65  (465-Series) Rockwell International Report No. SR-78-036; 
   NA-265-65  (306-Series) Rockwell International Report No. SR-81-006; 
   NA-265-70  NAR Report No. NA-68-865; 
   NA-265-80  Rockwell International Report No. NA-72-929.

A2WE 
 -26- Rev. 28 
 
NOTE 1. (a) The current load and balance schedule and the list of equipment included in the certificated empty weight 
and loading restrictions must be provided for each aircraft at the time of original certification.  The load 
and balance schedule contains information for aircraft and interior arrangement as delivered.  It also 
contains information relative to the location of crew and passengers, location and capacity of baggage area 
and fuel using tables. 
 
  (b) The aircraft must be loaded so that the C.G. is within the approved limits at all times considering fuel 
loading and usage, gear retraction, and movement of crew and passengers from their assigned positions. 
 
  (c) The weight of the system fuel, total oil and hydraulic fluid, all of which must be included in the aircraft 
empty weight, is listed in the applicable Rockwell International Master Equipment List. 
 
   System Fuel:  The weight of all fuel required to fill the lines and tanks up to the zero fuel point on the fuel 
gauges in the most critical flight attitude.  This consists of trapped fuel and includes the unusable tank fuel 
as defined by CAR 4b.416. 
 
NOTE 2. This aircraft must be operated according to the FAA Approved Airplane Flight Manual. 
 
 
NOTE 3. (a) Information essential to the proper servicing and maintenance of the appropriate model aircraft is 
contained in the following list of the manufacturer's Maintenance Manuals. 
 
   NA-265, NA-265-20, NA-265-30 The applicability of the Military Maintenance Manual 
     for these models must be established for civil operations. 
   NA-265-40  NAR Report No. NA-62-1224 
   NA-265-60  NAR Report No. NA-62-1224 
   NA-265-65  (465-Series) Rockwell International Report No. SR-78-030 
   NA-265-65  (306-Series) Rockwell International Report No. SR-81-014 
   NA-265-70  NAR Report No. NA-69-420 
   NA-265-80  Rockwell International Report No. NA-69-420 
 
  (b) Components which are life limited are listed in Rockwell International Report No. SR-81-013 and must be 
replaced as indicated therein.  Report No. SR-81-013, Rev. H, or later FAA approved revision, is part of 
Data Sheet A2WE, by reference.  Copies of this report may be obtained from the manufacturer. 
 
NOTE 4. Applies to Models NA-265, NA-265-20, and NA-265-30. 
 
  When these models are operated as military aircraft, they will be operated to military operating requirements and 
limitations concerning night, IFR, and weather operations.  Due to the military instruments, communication and 
navigation equipment installed, these models have been substantiated for VFR operations only in civil use. 
 
NOTE 5. Applies to NA-265, -20 and -30, all serial numbers except as otherwise indicated below: 
 
  Prior to issuance of Certificate of Airworthiness, FAA Form 8100-2, for converted military models it must be 
determined that the aircraft complies with the requirements listed in Sabreliner Corporation Report No. TFD-68-
282, dated July 31, 1990, or later FAA approved revision.  This is in addition to requirements listed under "Serial 
Numbers Eligible" heading of Section I of this data sheet. 
 
NOTE 6. Applies to Model NA-265-40. 
 
  (a) Aircraft Serial Number 282-1 through 282-25 must have the following installed to operate at 0.8 mach 
number: 
   (1) 282-890014 Kit, Mach Warning Switch, 
   (2) Kollsman A33907-10-011 Airspeed Indicator, 
   (3) Red line on Machmeter at 0.808. 
 
  (b) Aircraft Serial Number 282-26 through 282-62 must have the following installed to operate at 0.8 mach 
number: 
   (1) Astek 8070410011 Mach Airspeed Switch, 
   (2) Kollsman A33907-10-011 Airspeed Indicator, 
   (3) Red line on Machmeter at 0.808.

A2WE 
 -27- Rev. 28 
 
NOTE 7. Applies as indicated. 
  (a) Model NA-265 
   Seven (7) passengers may be carried when the cabin interior configuration is modified in accordance with 
North American Rockwell Drawing No. 265-890356. 
 
  (b) Model NA-265-30 
   When the landing gear is modified in accordance with North American Rockwell Drawing No. 277-
890210, the airplane gross weight may be increased to 18,650 pounds. 
 
  (c) Model NA-265-40 
   Seven (7) passengers may be carried when the cabin interior configuration is modified in accordance with 
North American Rockwell Drawing No. 282-000006. 
 
  (d) Model NA-265-40 
   Installation of two (2) Pratt and Whitney Turbo Wasp JT12A-8 engines in lieu of two (2) Pratt and 
Whitney Turbo Wasp JT12A-6A engines may be accomplished in accordance with North American 
Rockwell Drawings No. 265-400001, 282-410001, 282-420001, 282-510104, and 282-530075.  (See 
Fatigue Life Limit All Models.) 
 
  (e) Model NA-265-40 
   When modified in accordance with instructions contained in North American Rockwell Corporation 
Sabreliner Field Service Bulletin No. 68-12, dated November 11, 1969, Sabreliner Corporation Optional 
Kit No. 83-5, dated February 29, 1984, or  later FAA approved revision, and NOTE 7(d) above, the 
airplane is eligible for 19,922 pound-maximum ramp and 19,537 pound-maximum airborne weights. 
 
  (f) Model NA-265-40 (S/N 282-1 through 282-97) 
   When modified in accordance with instructions contained in North American Rockwell Corporation 
Sabreliner Field Service Bulletin No. 69-23, dated February 18, 1971, or later FAA approved revision, the 
airplane is eligible for 19,035 pound-maximum ramp and 18,650 pound maximum airborne weights. 
 
  (g) Models NA-265-40 and -60 
   Allowable fuselage inertia distributions are contained in FAA Approved North American Rockwell Report 
No. TFD-67-817, revision dated July 23, 1968, or later FAA approved  revision. 
 
  (h) Deleted - See Fatigue Life Limits, NOTE 3(b). 
 
  (i) Deleted - See Fatigue Life Limits, NOTE 3(b). 
 
  (j) Models NA-265-40 and -60 
   Thrust reversers may be installed on all Pratt and Whitney Turbo Wasp JT12A-6A and -8 engines.  
Modifications must be made in accordance with all applicable instructions and kits listed in North 
American Rockwell Sabreliner Field Service Bulletin No. 68-3, dated April 4, 1968, or later FAA 
approved revision. 
 
  (k) Model NA-265-70 
   Allowable fuselage inertia distributions are contained in FAA Approved North American Rockwell Report 
No. TFD-70-215, dated April 6, 1970, or later FAA approved revision. 
 
  (l) Model NA-265-70, NA-265-40 (S/N 282-98 & subsequent), NA-265-80 
   Cabin interiors installed with passenger seats and oxygen system must be evaluated for compatibility 
 
  (m) Deleted - See Fatigue Life Limits, NOTE 3(b). 
 
  (n) Model NA-265-80 
   Allowable fuselage inertia distributions are contained in FAA Approved Rockwell Report No. SR 73-045, 
dated November 21, 1973, or later FAA approved revision. 
 
  (o) Model NA-265-80 (FFIA) 
   Modification is accomplished as described by Rockwell International Drawing No. 369-000002 (Sabreliner 
Service Bulletin 74-1).

A2WE 
 -28- Rev. 28 
NOTE 7. (cont’d) 
  (p) Compliance with fuel venting emissions requirements of Special Federal Aviation Regulation 27.  Model 
NA-265-70, Serial Numbers 370-1 and 370-7, and Model NA-265-80, Serial Numbers 380-24, -26, -28, -
29, and 380-31 and subsequent aircraft have complied with SFAR 27 at  production.  For other Model 265-
80 serial numbers see Rockwell International, Sabreliner Division, Service Bulletin 75-2. 
 
  (q) Model NA-265-65 - Installation of Solar T-62T-40C Auxiliary Power Unit. 
 
  (r) Model NA-265-65 - Installation of Garrett/AiResearch TFE-731-3R-1D Automatic Performance Reserve 
(APR). 
 
NOTE 8. Applies to Model NA-265-60 
 
  Airplane Serial Numbers 306-54 and 306-59 through 306-63 are approved for operation at the weight and center 
of gravity limits for airplanes 306-64 and subsequent as defined by Flight Manual Supplement No. 60-76. 
 
 
NOTE 9.         Applies to Model NA-265-65 
   
  When modified in accordance with Sabreliner Service Bulletin 00-02, titled "NA265-65 RVSM Aircraft 
Modification/Certification" the aircraft will qualify for flight in RVSM Altitude Airspace.  Note:  The approval is 
for the aircraft altimetry equipment installation only.  It is the responsibility of the owner/operator to obtain the 
proper training and approval for the flight crew and the approval for operating the aircraft in the RVSM Altitude 
Airspace through their local FAA Flight Standards Office. 
 
NOTE 10.   When modified in accordance with Sabreliner Certification Drawing List No. 65S-060-0012, titled “Speed Brake 
Reactivation 65 Model”, the aircraft has fully operational speed brake.  Limitations and operations procedure are 
defined by Airplane Flight Manual Supplement No. 65-91. 
 
 
.....END.....
```

## ADs (49, in force first)

- [AD 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008
- [AD 2005-25-18](https://openairdocs.org/ad/2005-25-18): Wing center section · Sabreliner NA-265, NA-265-20, NA-265-30 and 5 more. Effective Jan 18, 2006
- [AD 2004-08-15](https://openairdocs.org/ad/2004-08-15): TAWS8000 terrain awareness warning systems (TAWS) · Cessna 421, 500, 501 and 18 more. Effective Jun 7, 2004
- [AD 2002-15-02](https://openairdocs.org/ad/2002-15-02): Compressor Wheels · British Aerospace Regional Jetstream Series 3101, 234, Mystere-Falcon 20 - C5 and 22 more. Effective Aug 28, 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 99-19-03](https://openairdocs.org/ad/99-19-03): AFM - Limitations Section - Ice Protection System · Sabreliner NA-265-40, NA-265-60, NA-265-70 and 1 more. Effective Dec 27, 1999
- [AD 97-05-03 R1](https://openairdocs.org/ad/97-05-03-R1): Global Positioning Systems · BAE Systems Avro 146-RJ100A, BAe 146-200A, Jetstream Model 4101 and 27 more. Effective Apr 20, 1999
- [AD 98-04-37](https://openairdocs.org/ad/98-04-37): AFM - Limitations Section - Icing · Sabreliner NA-265-40, NA-265-60, NA-265-70 and 1 more. Effective Mar 25, 1998
- [AD 97-04-15](https://openairdocs.org/ad/97-04-15): Fire Extinguisher Bottle Cartridges · Bombardier DHC-8-101, DHC-8-102, DHC-8-103 and 24 more. Effective Mar 7, 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
- [AD 95-26-15 R1](https://openairdocs.org/ad/95-26-15-R1): Traffic Alert and Collision Avoidance Systems · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 159 more. Effective Dec 26, 1996
- [AD 94-01-05](https://openairdocs.org/ad/94-01-05): Traffic Alert and Collision Avoidance System II Processors · Airbus A340-211, A340-212, A340-213 and 85 more. Effective Feb 4, 1994
- [AD 94-01-06](https://openairdocs.org/ad/94-01-06): Traffic Alert and Collision Avoidance System II Processors · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 176 more. Effective Feb 4, 1994
- [AD 92-27-16](https://openairdocs.org/ad/92-27-16): Hydraulic Pump · Sabreliner NA-265, NA-265-20, NA-265-30 and 5 more. Effective Jan 13, 1993
- [AD 80-04-11 R2](https://openairdocs.org/ad/80-04-11-R2): Wing Leading Edge · Sabreliner NA-265-60 and NA-265-80 with STC SA687NW or SA847NW. Effective Apr 13, 1983
- [AD 82-26-02](https://openairdocs.org/ad/82-26-02): Vertical Floor Panel Inspection · Sabreliner NA-265-60 and NA-265-65. Effective Apr 13, 1983
- [AD 82-27-10](https://openairdocs.org/ad/82-27-10): Horizontal Stabilizer Trim Actuator · Sabreliner NA-265-65. Effective Jan 19, 1983
- [AD 82-10-02 R1](https://openairdocs.org/ad/82-10-02-R1): Flap Screwjack Inspection · Sabreliner NA-265-60 and NA-265-65 with STC SA687NW. Effective Sep 13, 1982
- [AD 81-15-51 R1](https://openairdocs.org/ad/81-15-51-R1): Flap Actuation System · Sabreliner NA-265-60 and NA-265-80 with STC SA687NW or SA847NW. Effective May 18, 1982
- [AD 81-13-04](https://openairdocs.org/ad/81-13-04): MLG Shock Strut Trunnion · Sabreliner NA-265-60, NA-265-70 and NA-265-80. Effective Jul 30, 1981
- [AD 81-14-09](https://openairdocs.org/ad/81-14-09): Cabin Depressurization · Sabreliner NA-265-40 and NA-265-60. Effective Jul 13, 1981
- [AD 80-26-01](https://openairdocs.org/ad/80-26-01): Fuselage Structure Inspection · Sabreliner NA-265-40 and NA-265-60. Effective Jan 19, 1981
- [AD 80-22-54](https://openairdocs.org/ad/80-22-54): Aileron Control System · Sabreliner NA-265-60 and NA-265-80 with STC SA687NW or SA847NW. Effective Dec 24, 1980
- [AD 80-01-07 R1](https://openairdocs.org/ad/80-01-07-R1): Raisbeck Modification · Sabreliner NA-265-60 and NA-265-80 with STC SA687NW or SA847NW. Effective Jun 3, 1980
- [AD 80-03-05 R1](https://openairdocs.org/ad/80-03-05-R1): Elevator Trailing Edge · Sabreliner NA-265-70 and NA-265-80. Effective May 29, 1980
- [AD 80-08-07](https://openairdocs.org/ad/80-08-07): Elevator Trailing Edge · Sabreliner NA-265-40, NA-265-60 and NA-265-70. Effective Apr 21, 1980
- [AD 80-05-02](https://openairdocs.org/ad/80-05-02): Safety Belt Assemblies · Gulfstream Aerospace G-1159, G-1159A, G-1159B and 17 more. Effective Feb 27, 1980
- [AD 79-13-02](https://openairdocs.org/ad/79-13-02): Aileron System · Sabreliner NA-265-60 with STC SA687NW. Effective Sep 4, 1979
- [AD 79-17-01](https://openairdocs.org/ad/79-17-01): Elevators · Sabreliner NA-265-60 with STC SA687NW. Effective Aug 15, 1979
- [AD 77-25-02](https://openairdocs.org/ad/77-25-02): Engine Fire Detection System · Sabreliner NA-265-70 and NA-265-80. Effective Dec 12, 1977
- [AD 77-10-10](https://openairdocs.org/ad/77-10-10): Electrical System · Sabreliner NA-265-80. Effective May 23, 1977
- [AD 75-08-11](https://openairdocs.org/ad/75-08-11): Electrical Power in Flight · Sabreliner NA-265, NA-265-20, NA-265-30 and 3 more. Effective Aug 5, 1976
- [AD 76-12-09](https://openairdocs.org/ad/76-12-09): Inflight Flutter · Sabreliner NA-265-70 and NA-265-80. Effective Jun 23, 1976
- [AD 73-12-09](https://openairdocs.org/ad/73-12-09): Thrust Reverser Deployment · Sabreliner NA-265-40, NA-265-60 and NA-265-70. Effective Jul 29, 1975
- [AD 75-12-04](https://openairdocs.org/ad/75-12-04): Engine Supports · Sabreliner NA-265-40 and NA-265-60. Effective Jun 9, 1975
- [AD 75-04-05](https://openairdocs.org/ad/75-04-05): Engine Fuel Pressure Switches · Sabreliner NA-265, NA-265-20, NA-265-30 and 5 more. Effective Feb 18, 1975
- [AD 75-01-03](https://openairdocs.org/ad/75-01-03): Landing Gear Warning System · Sabreliner NA-265, NA-265-20, NA-265-30 and 4 more. Effective Jan 6, 1975
- [AD 74-26-08](https://openairdocs.org/ad/74-26-08): Engine Oil Low Pressure Switch · Sabreliner NA-265-40, NA-265-60 and NA-265-70. Effective Dec 24, 1974
- [AD 72-23-04](https://openairdocs.org/ad/72-23-04): Main Gear Strut Cylinder · Sabreliner NA-265-40 and NA-265-60. Effective Nov 11, 1972
- [AD 72-19-03](https://openairdocs.org/ad/72-19-03): Landing Gear Side Brace · Sabreliner NA-265, NA-265-20, NA-265-30 and 2 more. Effective Sep 15, 1972
- [AD 72-14-04](https://openairdocs.org/ad/72-14-04): Main Gear Door Torque Tube · Sabreliner NA-265, NA-265-20, NA-265-30 and 2 more. Effective Jul 7, 1972
- [AD 71-25-04](https://openairdocs.org/ad/71-25-04): Aileron Control Cables · Sabreliner NA-265, NA-265-20, NA-265-30 and 3 more. Effective Dec 4, 1971
- [AD 71-03-03](https://openairdocs.org/ad/71-03-03): Flap Track Attachment Lug · Sabreliner NA-265, NA-265-20, NA-265-30 and 2 more. Effective Feb 6, 1971
- [AD 70-24-03](https://openairdocs.org/ad/70-24-03): Engine Fire Control Handle · Sabreliner NA-265, NA-265-20, NA-265-30 and 5 more. Effective Nov 28, 1970
- [AD 70-12-06](https://openairdocs.org/ad/70-12-06): Nose Gear Shimmy · Sabreliner NA-265, NA-265-20, NA-265-30 and 2 more. Effective Jun 16, 1970
- [AD 70-02-09](https://openairdocs.org/ad/70-02-09): Engine Thrust Reverser · Sabreliner NA-265-40 and NA-265-60. Effective Dec 19, 1969
- [AD 69-10-01](https://openairdocs.org/ad/69-10-01): Main Landing Gear Pistons · Sabreliner NA-265, NA-265-20, NA-265-30 and 5 more. Effective May 9, 1969
- [AD 68-20-01](https://openairdocs.org/ad/68-20-01): Horizontal Stabilizer Support · Sabreliner NA-265, NA-265-20, NA-265-30 and 2 more. Effective Oct 28, 1968
- [AD 73-18-03](https://openairdocs.org/ad/73-18-03) (historical): Front and Rear Wing Spars · Sabreliner NA-265-40, NA-265-60 and NA-265-70. Effective May 5, 1978

## Registered aircraft by registry model (OpenAirDocs)

- [Rockwell International NA-265-65](https://openairdocs.org/model/rockwell-international-na-265-65): 26 aircraft (registry code 7630107)
- [North American NA-265-40](https://openairdocs.org/model/north-american-na-265-40): 6 aircraft (registry code 6402608)
- [Rockwell International NA-265-60](https://openairdocs.org/model/rockwell-international-na-265-60): 4 aircraft (registry code 7630106)
- [North American NA-265-60](https://openairdocs.org/model/north-american-na-265-60): 3 aircraft (registry code 6402612)
- [Rockwell International NA-265](https://openairdocs.org/model/rockwell-international-na-265): 2 aircraft (registry code 7630101)
- [North American NA-265-80](https://openairdocs.org/model/north-american-na-265-80): 1 aircraft (registry code 6402618)
- [Rockwell International NA-265-40](https://openairdocs.org/model/rockwell-international-na-265-40): 1 aircraft (registry code 7630104)
- [Rockwell International NA-265-80](https://openairdocs.org/model/rockwell-international-na-265-80): 1 aircraft (registry code 7630108)
- [North American NA-265](https://openairdocs.org/model/north-american-na-265): 0 aircraft (registry code 6402602)
- [North American NA-265-20](https://openairdocs.org/model/north-american-na-265-20): 0 aircraft (registry code 6402604)
- [North American NA-265-30](https://openairdocs.org/model/north-american-na-265-30): 0 aircraft (registry code 6402606)
- [North American NA-265-70](https://openairdocs.org/model/north-american-na-265-70): 0 aircraft (registry code 6402614)
- [North American Rockwell NA-265-40](https://openairdocs.org/model/north-american-rockwell-na-265-40): 0 aircraft (registry code 6402609)
- [Sabreliner NA-265-40](https://openairdocs.org/model/sabreliner-na-265-40): 0 aircraft (registry code 6403000)
- [Sabreliner NA-265-80](https://openairdocs.org/model/sabreliner-na-265-80): 0 aircraft (registry code 6403001)

## STCs approved under this data sheet (346, 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 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 ST11216DS](https://openairdocs.org/stc/ST11216DS): Installation of automatic dependent surveillance-broadcast (ADS-B) out on Part 25 aircraft. BHE & Associates Ltd.
- [STC ST00106WI](https://openairdocs.org/stc/ST00106WI): Installation of a BFGoodrich model TCAS791 traffic alert and collision avoidance system (TCAS) I.. Acron Aviation Inc.
- [STC ST03424CH](https://openairdocs.org/stc/ST03424CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC
- [STC ST04183AT](https://openairdocs.org/stc/ST04183AT): Installation of the Honeywell CAS-100 Traffic Alert and Collision Avoidance System (TCAS), Version 7.1, and the ACSS NXT-800 Mode S Transponder with associated hardware. Woven Electronics LLC
- [STC SA2698SO](https://openairdocs.org/stc/SA2698SO): Installation of provisions for a CAS-81 TCAS. Honeywell International Inc
- [STC SA2734SO](https://openairdocs.org/stc/SA2734SO): Installation of a CAS-81 TCAS II. Honeywell International Inc
- [STC ST01930LA](https://openairdocs.org/stc/ST01930LA): Installation of Sandel Avionics SN4500 Electronic Horizontal Situation Indicator (EHSI). Sandel Avionics LLC
- [STC ST00445WI-D](https://openairdocs.org/stc/ST00445WI-D): Installation of Honeywell Enhanced Ground Proximity Warning System.  Limited to installation on NA-265-65, serial number 465-58 ONLY.. Honeywell International Inc
- [STC ST00715WI-D](https://openairdocs.org/stc/ST00715WI-D): Installation of provisions for AlliedSignal AIRSAT 1 IRIDIUM Aeronautical Satelite Communication System.. Honeywell International Inc
- [STC ST00093WI-D](https://openairdocs.org/stc/ST00093WI-D): ONE-ONLY STC, S/N 465-58: Installation of hte Bendix/King CAS 66A TCAS I System.. Honeywell International Inc
- [STC ST01343CH-D](https://openairdocs.org/stc/ST01343CH-D): Installation of AlliedSignal CAS-67A Traffic Alert and Collision Avoidance System (TCAS II) incorporating MOPS Change 7. Airplane must be previously equipped with STC ST333CH-D.. Honeywell International Inc
- [STC ST01344CH-D](https://openairdocs.org/stc/ST01344CH-D): Installation of dual Honeywell enhanced GNS-XLS Flight Management System. Aircraft must have STC ST335CH-D installed.. Honeywell International Inc
- [STC SA2073CE-D](https://openairdocs.org/stc/SA2073CE-D): Installation of Bendix/King EFS-10 electronic flight instrument sys (5 tube) dual KFC-400 automatic flight control sys, dual KAD-480 air data sys, dual KNS-660 flight mgmt sys, KHF-950HF Comm System and MLS-21 microwave landing system.. Honeywell International Inc
- [STC SA2311CE-D](https://openairdocs.org/stc/SA2311CE-D): ONE-ONLY STC, SN 465-058: Installation of Bendix/King CAS 80A Traffic Alert and Collision Avoidance System.. Honeywell International Inc
- [STC ST00791WI](https://openairdocs.org/stc/ST00791WI): Installation of AlliedSignal Avionics, Inc., KAD-481 adaptor module, part number 065-05041-28E1 (software part number 125-00981-00E1). Approved for installation on NA-265-65, serial number 465-58 ONLY.. Honeywell International Inc
- [STC ST333CH-D](https://openairdocs.org/stc/ST333CH-D): Installation of a Bendix/King CAS67A TCAS II System with dual MST-67 Mode S Transponders installed per Garrett Aviation Services.. Honeywell International Inc
- [STC ST335CH-D](https://openairdocs.org/stc/ST335CH-D): Installation of Dual AlliedSignal Aerospace, Global Wulfsberg GNS-XLS Flight Management. Honeywell International Inc
- [STC ST01553WI](https://openairdocs.org/stc/ST01553WI): Installation of the Honeywell MKV EGPWS with RAAS and Monitor Functions or the Honeywell MKV-A EGPWS with RAAS and Monitor Functions. Honeywell International Inc
- [STC ST02635LA](https://openairdocs.org/stc/ST02635LA): Modification to replace the existing Mode S Transponder system with the ACSS NXT-600 Mode S Transponder with ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC SA4991SW](https://openairdocs.org/stc/SA4991SW): Installation of freon air conditioning.. Air Comm Corporation
- [STC ST00790DE](https://openairdocs.org/stc/ST00790DE): Installation of BendixKing CAS 67B Traffic Alert and Collision Avoidance System (TCAS) II Version 7.1. Peregrine
- [STC ST02636LA](https://openairdocs.org/stc/ST02636LA): Modification to upgrade the existing XS-950 Mode S Transponder system to add ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC ST00347BO](https://openairdocs.org/stc/ST00347BO): Modification to upgrade a BendixKing CAS 67A TCAS II system to CAS 67B TCAS II Change 7.1. Pro Star Aviation, LLC
- [STC ST00373BO](https://openairdocs.org/stc/ST00373BO): Installation of Rockwell Collins TDR-94D Transponders with ADS-B Out. Pro Star Aviation, LLC
- [STC SA1963SW](https://openairdocs.org/stc/SA1963SW): Installation of Monogram Toilet. Associated Air Center, Inc. - c/o CT Corporation System
- [STC SA2901SW](https://openairdocs.org/stc/SA2901SW): Installation of Global GNS-500A Omega/VLF Navigation System. Associated Air Center, Inc. - c/o CT Corporation System
- [STC ST00105AT](https://openairdocs.org/stc/ST00105AT): Installation of a replacement coalescer filter.. Purolator Facet, Inc
- [STC ST00304WI](https://openairdocs.org/stc/ST00304WI): Installation of Keddeg Company 21BC113 coaleser assembly.. Purolator Facet, Inc
- [STC ST02632LA](https://openairdocs.org/stc/ST02632LA): Modification to replace the existing Mode S Transponder system with ACSS NXT-700 Mode S Transponder with ADS-B Out and optionally install ACSS NXG-900 GPS as a position source for ADS-B Out. Aviation Communications and Surveillance Systems
- [STC ST02609LA](https://openairdocs.org/stc/ST02609LA): Modification to replace the existing Mode S Transponder system with ACSS NXT-700 Mode S Transponder with ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC SA4407SW](https://openairdocs.org/stc/SA4407SW): Installation of emergency brake pressure indication system.. Centurion Investments
- [STC SA1357GL](https://openairdocs.org/stc/SA1357GL): Install air ambulance stretcher P/N 125 using installation kit P/N 805.. Paul/ Lanna Egan LLC
- [STC ST00881WI-D](https://openairdocs.org/stc/ST00881WI-D): Modification of a TCAS II system installation to Change 7.0 or Change 7.1. Rockwell Collins Inc
- [STC SA1725SW](https://openairdocs.org/stc/SA1725SW): Installation of Foxtronics/TRAMM BTI-600 nickel cadmium battery temperature indicator and optional TRAMM R-600 voltage control.. FoxCart GSE, LLC
- [STC ST02300NY](https://openairdocs.org/stc/ST02300NY): Certification of Sabreliner Model NA-265-80 to Stage 3 Noise Levels Utilizing Reduced Landing Weight.. Flight Test Aerospace, Inc
- [STC ST04238AT](https://openairdocs.org/stc/ST04238AT): Upgrade of Honeywell Traffic Collision Avoidance Systems II (TCAS II) Processor Software from TCAS II Version 7.0 to TCAS II Version 7.1. Aviation Partners Group Inc
- [STC SA244CE](https://openairdocs.org/stc/SA244CE): Electronics components package version F.. Sabreliner Aviation LLC
- [STC SA00120WI](https://openairdocs.org/stc/SA00120WI): Modification of existing Sabreliner Model 80 thrust reverser 232-20262-503 flexure plate to provide improved fatigue life.. Sabreliner Aviation LLC
- [STC SA1012CE](https://openairdocs.org/stc/SA1012CE): Install interior, version No. 8.. Sabreliner Aviation LLC
- [STC SA1014CE](https://openairdocs.org/stc/SA1014CE): Cockpit voice and flight data recorder, altitude alerting system, encoding, and radio altimeters and weather radar installation.. Sabreliner Aviation LLC
- [STC SA1015CE](https://openairdocs.org/stc/SA1015CE): Installation of electronic components package Version C.. Sabreliner Aviation LLC
- [STC SA1026CE](https://openairdocs.org/stc/SA1026CE): Install interior, version No. 3.. Sabreliner Aviation LLC
- [STC SA1028CE](https://openairdocs.org/stc/SA1028CE): Installation of electronic components package, version B.. Sabreliner Aviation LLC
- [STC SA1043CE](https://openairdocs.org/stc/SA1043CE): Installation of electronic components package, version D.. Sabreliner Aviation LLC
- [STC SA1057CE](https://openairdocs.org/stc/SA1057CE): Installation of electronic components package, version Z.. Sabreliner Aviation LLC
- [STC SA1065CE](https://openairdocs.org/stc/SA1065CE): Installation of electronic components package, version E.. Sabreliner Aviation LLC
- [STC SA1066CE](https://openairdocs.org/stc/SA1066CE): Installation of Teledyne angle of attack indicating system SL112B1400. Sabreliner Aviation LLC
- [STC SA1067CE](https://openairdocs.org/stc/SA1067CE): Auxiliary seat installation - aft lavatory.. Sabreliner Aviation LLC

All 346: https://openairdocs.org/tcds/A2WE/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.