# TCDS A21EU: British Aerospace Regional Aircraft

- Type: Type certificate data sheet
- Status: Current
- Holder: British Aerospace Regional Aircraft
- Revision: 21
- Revised: October 13, 2021
- Product: Aircraft, Small/Large Airplane
- Certification basis: Part 21, Part 23, Part 25
- Data sheet PDF: https://openairdocs.org/files/sha256/5a/79/5a79d205f38e095a5c79fd90b3f0fb5761a6ee7a80cbf3cd10ec7978a41225e5
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D44DFDF938A1817A8625876D0059E37B.0001
- Page: https://openairdocs.org/tcds/A21EU

## Models (3)

As the data sheet lists them.

- Jetstream Series 200
- H.P. 137 Jetstream Mk. 1
- Jetstream Series 3101

## What the data sheet says

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

```text
A21EU Page 1 of 12 
 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 
Rev. No. 21 8 9 13 13 12 15 20 18 18 16 17 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A21EU 
Revision 21 
British Aerospace (Operations) Limited 
HP.137 Jetstream Mk.1 
Jetstream Series 200 
Jetstream Series 3101 
 
October 13, 2021 
 
TYPE CERTIFICATE DATA SHEET No. A21EU 
 
This data sheet, which is a part of Type Certificate No. A21EU prescribes conditions and limitations under which the product for 
which the type certificate was issued, meets the airworthiness requirements of the Federal Aviation Regulations.  
 
Type Certificate Holder.  British Aerospace (Operations) Limited  
(trading as) British Aerospace Regional Aircraft 
    Prestwick International Airport 
    Ayrshire KA9 2RW 
    Scotland 
 
 
I.   Model HP.137 Jetstream Mk.1 (Normal Category), approved April 25, 1969. (See NOTE 7). 
 
Type Certificate Ownership Record 
 
  (1)   The EASA TC for this model was surrendered to the state of design on January 24, 2008 and is no 
longer valid.  Only standard airworthiness certificates issued prior to January 1, 2014 are valid. 
 
(2)   Future unsafe conditions existing in the aircraft may result in the revocation of the airworthiness 
certificates of the aircraft if there is no entity to comply with 14 CFR § 21.99(a), “Required design 
changes.” 
(3)   Replacement parts may not be available in the future. 
 
Engine.    2 Turbomeca Astazou XIVC or XIVC1 (Propeller Turbine) or 2 Turbomeca Astazou  
    XVIF1 (Propeller Turbine) (ADA MOD. 040/137)  (See NOTE 5). 
 
Fuel.   American  British    French  NATO 
  ASTM Jet A or A1  or D.Eng.RD 2453 or 2494  or AIR 3405 or F34 or F35 
  *ASTM Jet B or JP-4 *or D.Eng.RD 2454 or 2486  or AIR 3407 *or F40 or F45 
   (MIL-T-5624) 
  JP-5        (MIL-T-5624) or D.Eng.RD.2498   or AIR 3404 or F42 or F44 
 
  * Not usable for airplanes with MOD.NO.5168 
     (Specifications as revised) 
 
Oil.   American  British    French  NATO 
(Engine & Gearbox) MIL-L-7808    -    or AIR 3513 or 
                     3514 or 0-148 or 0-150 
         -  D.Eng.RD 2487   or AIR 3517 or 0-149 or 0-159 
         -  D.Eng.RD 2490   or AIR 3515 or 0-135 
   MIL-L-23699    -            -  or 0-156 
     Specifications as revised) 
 
Engine Limits.   Static Ratings 
    The static ratings for the Astazou engines are specified under the following test  
    conditions.

A21EU Page 2 of 12 
 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 
Rev. No. 21 8 9 13 13 12 15 20 18 18 16 17 
 
   International Standard Atmospheric Conditions at Sea Level. 
 
    Calibrated slave air intake duct (TURBOMECA 6 103 43 905 0) 
    Short and straight slave exhaust diffuser, outlet diameter 8.98 in. (228 mm) 
     
    All optional air bleeds closed. 
    Aircraft Service accessory drive unloaded. 
    43089 engine RPM. 
 
    Astazou XIVC and XIVCI 
 
  
Shaft Horse 
Power 
 
Jet 
Thrust (lb) 
 
Torquemeter 
Reading (%) 
 
Indicated 
RPM (%) 
Specific Fuel 
Consumption 
(lb/shp/hr) 
Jet Pipe 
Temp.(EGT) 
°C 
Conditions 
Takeoff 
Max. Cont. 
 
776 
699 
 
123.5 
121.0 
 
98.5 
88.5 
 
98.7 
98.7 
 
0.562 
0.582 
 
500 
480 
 
    Astazou XIVC and XIVCI 
 
  
Shaft Horse 
Power 
 
Jet 
Thrust (lb) 
 
Torquemeter 
Reading (%) 
 
Indicated 
RPM (%) 
Specific Fule 
Consumption 
(lb/shp/hr) 
Jet Pipe 
Temp.(EGT) 
°C 
Conditions 
Takeoff 
Max. Cont. 
 
839 
786 
 
137.5 
136.5 
 
103.6 
97.0 
 
98.7 
98.7 
 
0.558 
0.569 
 
585 
540 
 
Engine Limits.   All new and overhauled engines must meet the above acceptance limits.  See ARB  
    Approved Flight Manual, DOC. HP.4.3 for additional engine operating Limitations.   
    (See NOTE 5). 
 
Propeller and Propeller Limits. 2 Hamilton Standard reversible propellers Type 23LF-335, 23LF-373, or 23LF-371 for 
    ADA MOD 040/137 only. 
 
    Blades : 3 Type 1017 
    Diameter : 8 ft. 6 in. (No reduction permitted) 
    Pitch settings at 42 in. station: 
     Ground  - 5.5 
     Flight Fine + 7 ± ½ 
     Feathered  + 80 
     Full Reverse - 14 (with Modification 1331 embodied -10) 
 
Airspeed Limits.  (Maximum Operating Speed) W/O MOD.NO.5168   With MOD.NO.5168 embodied 
      See NOTE 7 
   VMO   up  to 18000 ft. 215 knots up to 19000 ft 220 knots 
    at 20000 ft. 205 knots  
    at 25000 ft. 180 knots        at 25000 ft  190 knots 
   VA  (Maneuvering Speed) 170 knots    174 knots 
   VFE  (Flaps Extended Speed) 
    Takeoff 156 knots  162 knots 
    Landing 50° Down 120 knots  120 knots 
   VLE  (Landing Gear Extended Speed) 156 knots  162 knots 
   VLO (Landing Gear Operating Speed) 156 knots 162 knots 
   VMC (Minimum Control Speed)    88 knots   88 knots 
 
C.G. Limits.   (+ 213.5 in.) to (+ 228 in.) at 11,000 lb, or less 
(Landing Gear Extended)  (+ 215.0 in.) to (+ 228 in.) at 12,500 lb. 
    (+ 215.0 in.) to (+ 228.0 in.) at 13,230 lbs. 
 
    Straight line variation between points given. 
    Moment change (Landing Gear Retraction) -4550 lb. in. (moves C of G forward)

A21EU Page 3 of 12 
 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 
Rev. No. 21 8 9 13 13 12 15 20 18 18 16 17 
 
Datum.    Fuselage station “0” (140 inches fwd of marked “cowling type” screw on fuselage  
    bottom). 
 
Leveling Means.   Leveling Marks provided on fuselage seat rails. 
    At station 225.5 left and right 
    At station 252.5 right only. 
 
Maximum Weight.      W/O MOD. NO. 5168 WITH MOD.NO.5168 
    Takeoff   12,500 lb.  13,230 lbs. 
    Zero Fuel   12,500 lb.  12,500 lbs. 
 
Minimum Crew.   1 pilot      1 pilot 
 
Maximum Passengers.  18      19 
 
Maximum Baggage.  550 lb. (+ 391.3 in.) 
 
Fuel Capacity.   461 U.S. Gals. in 2 tanks (+ 226.2 in.) 
    459 U.S. Gals. usable. 
    (See NOTE 1 for data on system fuel). 
 
Oil Capacity.   2.1 U.S. Gals./tank on each engine (+ 167 in.) 
    1.3 U.S. Gals./tank usable. 
    (See NOTE 1 for data on system oil). 
 
Max. Operating Altitude.  25,000 ft. 
 
Control Surface Movements.  Elevator   28°   Up  22°   Down 
    Elevator Trim Tab    5°   Up  13°   Down 
 
    Rudder   25°   Right 25°   Left) Measure relative 
    Rudder Trim Tab  20°   Right 20°   Left) to aircraft datum 
 
    Aileron   25°   Up  15°    Down 
    Aileron Trim Tab  8.5°  Up  8.5°   Left side only 
 
    Flaps Landing  50°   Down 
     Takeoff  20°   Down 
                Lift Dump  70°   Down 
 
II.   Jetstream Series 200 (Normal Category), approved May 17, 1977. 
 
Engine.    2 Turbomeca Astazou XVICI or XVIF (Propeller turbine). 
 
    These engines are not interchangeable. 
 
Fuel.   American  British    French  NATO 
  ASTM Jet A or A1  or D.Eng.RD 2453 or 2494  or AIR 3405 or F34 or F35 
  ASTM Jet B or JP-4 or D.Eng.RD 2454 or 2486  or AIR 3407 *or F40 or F45 
   (MIL-T-5624) 
  JP-5        (MIL-T-5624) or D.Eng.RD.2498   or AIR 3404 or F42 or F44 
 
    (Specifications as revised) 
 
Oil.   American  British   French   NATO 
(Engine & Gearbox) MIL-L-7808    -   or AIR 3513 or 3514 or 0-148 or 0-150 
         -  D.Eng.RD 2487  or AIR 3517  or 0-149 or 0-159 
         -  D.Eng.RD 2490  or AIR 3515  or 0-135 
   MIL-L-23699    -           -   or 0-136 
      
    (Specifications as revised)

Page 4 of 12 A21EU 
 
Engine Limits.    Static Ratings 
    The static ratings for the Astazou engines are specified under the following test 
    conditions. 
 
    International Standard Atmospheric Conditions at Sea Level. 
 
    Calibrated slave air intake duct (TURBOMECA 6 103 43 905 0) 
    Short and straight slave exhaust diffuser, outlet diameter 8.98 in. (228mm) 
 
    All optional air bleeds closed. 
    Aircraft service accessory drives unloaded. 
    43089 engine RPM. 
 
Engine Limits.   Astazou XVIC1C and XVIF 
(Continued) 
  
Shaft Horse 
Power 
 
Jet 
Thrust (lb) 
 
Torquemeter 
Reading (%) 
 
Indicated 
RPM (%) 
Specific Fuel 
Consumption 
(lb/shp/hr) 
Jet Pipe 
Temp.(EGT) 
°C 
Conditions 
Takeoff 
Max. Cont. 
 
912 
785 
 
141.6 
139.4 
 
97.3 
83.7 
 
98.7 
98.7 
 
0.558 
0.579 
 
585 
540 
 
    All new and overhauled engines must meet the above acceptance limits. 
    See CAA Approved Flight Manual, Doc. HP.4.8 for additional engine Operating 
    Limitations. 
 
Propeller and Propeller Limits. 2 Hamilton Standard Type 23LF-371 reversible propellers. 
 
(Clarification)   Blades :     3 Type 1017 
    Diameter :     8 ft. 6 in. (No reduction permitted) 
    Pitch settings at 42 in. station: 
     Ground  - 5.5° 
     Flight Fine + 7° ± 0.5° 
     Feathered  + 80° 
     Full Reverse - 14° 
 
Airspeed Limits.   (Maximum Operating Speed)         
    VMO   up  to 18,000 ft.   215 knots  
     at 25,000 ft.   180 knots  
    VA  (Maneuvering Speed)   170 knots  
    VFE  (Flaps Extended Speed) 
     Takeoff    156 knots  
     Landing 50° Down   120 knots  
    VLE  (Landing Gear Extended Speed)  156 knots  
    VLO (Landing Gear Operating Speed)  156 knots  
    VMC (Minimum Control Speed)     89.5 knots 
 
C.G. Limits.   (+ 213.5 in.) to (+ 228 in.) at 11,000 lb, or less 
(Landing Gear Extended)  (+ 215.0 in.) to (+ 228 in.) at 12,500 lb. 
 
    Straight line variation between points given. 
    Moment change (Landing Gear Retraction) -4550 lb. in. (moves C of G forward) 
 
Datum.    Fuselage station “0” (140 inches fwd of marked “cowling type” screw on fuselage  
    bottom).

Page 5 of 12 A21EU 
 
Leveling Means.   Leveling Marks provided on fuselage seat rails. 
    At station 225.5 left and right 
    At station 252.5 right only. 
 
Maximum Weight.   Takeoff   12,500 lb. 
    Zero Fuel   12,250 lb. 
 
Minimum Crew.   1 pilot 
 
Maximum Passengers.  18 
 
Maximum Baggage.  550 lb. (+ 391.3 in.) 
 
Fuel Capacity.   461 U.S. Gals. in 2 tanks (+ 226.2 in.) 
    459 U.S. Gals. usable. 
    (See NOTE 1 for data on system fuel). 
 
Oil Capacity.   2.1 U.S. Gals./tank on each engine (+ 167 in.) 
    1.3 U.S. Gals./tank usable. 
    (See NOTE 1 for data on system oil). 
 
Max. Operating Altitude.  25,000 ft. 
 
Control Surface Movements.  Elevator   28°   Up  22°   Down 
    Elevator Trim Tab    5°   Up  12°   Down 
 
    Rudder   25°   Right 25°   Left (Measure relative) 
    Rudder Trim Tab  25°   Right 25°   Left (to aircraft datum) 
 
    Aileron   24°   Up  15°    Down 
    Aileron Trim Tab  8.5°  Up  8.5°   Down (Both sides) 
 
    Flaps Landing  50°   Down 
     Takeoff  20°   Down 
                Lift Dump  70°   Down 
 
III.   Jetstream Model 3101 (Normal Category), approved November 30, 1982. 
    The Jetstream Model 3101 is same as Jetstream Series 200 except for: 
    1) turbopropeller engines; 
    2) propeller; 
    3) powerplant control and indications; 
    4) electrical generation and distribution; 
    5) air conditioning; 
    6) passenger cabin; 
    7) increased overall structural strength; 
    8) increased design weights and speeds; 
    9) certification basis 
 
Engine.    2 Airesearch TPE 331-10UF-501H turbopropeller 
     or  TPE 331-10UF-511H (BAe Mod 7300) 
     or  TPE 331-10UF-512H (BAe Mod 7356) 
     or  TPE 331-10UF-513H (BAe Mod 7357) 
     or  TPE 331-10UR-513H (BAe Mod 7379) 
     or  TPE 331-10UG-513H (BAe Mod 7432) (See Note 9) 
     or  TPE 331-10UGR-513H (BAe Mod 7434) (See Note 9) 
     or  TPE 331-10UGR-514H (BAe Mod 7547) (See Note 9) 
     or  TPE 331-10UG-514H (BAe Mod 7548) (See Note 9) 
    Both engines must have same model number (See Note 10)

Page 6 of 12 A21EU 
 
Fuel.    American   British   NATO 
    ASTM Jet A     -       - 
    ASTM Jet A1  or D.Eng.RD 2494  or F35 
    MIL-T-83133,JP8*  or D.Eng.RD 2453* or F34* 
    Fuel marked thus * contain fuel system icing inhibitor (FSII) and no further additions  
    shall be made. 
 
    (Specifications as revised) 
 
Oil.    MIL-L-23699B 
(Engine and Gearbox)  (Specifications as revised) 
 
Engine Limits.    Static Ratings 
    The static ratings for the Airesearch engines are based on the conditions specified on 
    TCDS E4WE. 
 
Engine Limits.   Shaft Horse Prop Shaft Exhaust Gas 
    Power (SHP) Speed (RPM) Temp. (EGT) Single 
      Red Line (°C) 
  Conditions 
  Takeoff  940* 1591 650 
  Maximum Cont. 900 1591 650 
  Starting  - - 770 
    * For airplane incorporating BAe MOD 7340, otherwise 900 SHP. 
 
    All new and overhauled engines must meet the above acceptable limits. 
    See CAA Approved Flight Manual, Doc. HP.4.10 for additional engine Operating 
    Limitations. 
 
Propeller and Propeller Limits. 2 Dowty Rotol (c) R.333/4-82-F/12 
 
    Blades :     4   
    Diameter :     106 inches (No reduction permitted) 
    Pitch angles at Section J-J setting line: 
     
     Start Locks  - 1° 45’  + 0° 30’ 
     Flight Idle  + 9°  + 0° 30’ 
     Feathered   + 82° 20’  ± 0° 20’ 
     Reverse   - 13°  + 0° 30’ 
 
Airspeed Limits.  VMO  (Maximum Operating Speed) Without MOD 7380 With MOD 7380 
    up  to 16,750 ft.          230 knots    
    up  to 18,300 ft.             223 knots    
    at 25,000 ft.          194 knots  194 knots    
   VA  (Maneuvering Speed)          180 knots  176 knots 
   VFE  (Flaps Extended Speed) 
         Takeoff     10° Down          177 knots  172 knots   
         Approach  20° Down          168 knots  164 knots   
         Landing (pre Mod 7760)  50° Down       130 knots  130 knots   
         Landing (post Mod 7760) 35° Down       149 knots  153 knots   
         Lift Dump 70° Down          100 knots  100 knots   
   VLE  (Landing Gear Extended Speed)          168 knots  164 knots   
   VLO (Landing Gear Operating Speed)         168 knots  164 knots   
   VMC (Minimum Control Speed) 
        Takeoff (Flaps 10°)            92 knots    92 knots   
        Approach (Flaps 20°)            90 knots    90 knots   
   For airplane with Mod 7340: 
        Approach (Flaps 20°)            94 knots    94 knots

Page 7 of 12 A21EU 
C.G. Limits.   (+ 213.5 in.) to (+ 226 in.) at 11,000 lb, or less 
(Landing Gear Extended)  (+ 217.2 in.) to (+ 226 in.) at 14,550 lb. for airplanes without BAe MOD 7380 
    (+ 217.8 in.) to (+ 226 in.) at 15,212 lb. for airplanes with BAe MOD 7380 
    Aft C.G. limit is 227.5 in. at all weights for airplanes with BAe MOD 7362. 
    Straight line variation between points given. 
    Moment change (Landing Gear Retraction) -4450 lb. in. (moves C of G forward) 
 
Datum.    Fuselage station “0” (140 inches fwd of marked “cowling type” screw on the bottom 
    surface of fuselage). 
 
Leveling Means.   Leveling marks provided on fuselage seat rails. 
    At station 225.5 left and right 
    At station 252.5 right only. 
 
Maximum Weight.     Without MOD 7380 With MOD 7380   
    Ramp  14,660 lb. (6650 Kg) 15,322 lb. (6950 kg) 
    Takeoff  14,550 lb. (6600 Kg) 15,212 lb. (6900 kg) 
    Zero Fuel  13,228 lb. (6000 Kg) 13,668 lb. (6200 kg) (Pre-Mod 7456) 
    Zero Fuel   -  13,889 lb. (6300 kg) (Pre-Mod 7456) 
    Zero Fuel   -  14,300 lb. (6486 kg) (Post-Mod 7846) 
    Landing  14,550 lb. (6600 Kg) 14,550 lb. (6600 kg) (Pre-Mod 7713) 
    Landing   -  14,900 lb. (6759 kg) (Pre-Mod 7713) 
 
Minimum Crew.   2 pilots 
 
Maximum Crew.   2 (See NOTE 4) 
 
Maximum Passengers.  19 (See NOTE 4) 
 
Maximum Baggage.  661 lb. (+ 380.0 in.) 
 
Fuel Capacity.   461 U.S. Gals. in 2 tanks (+ 226.2 in.) 
    451 U.S. Gals. usable. 
    (See NOTE 1 for data on system fuel). 
 
Oil Capacity.   1.56 U.S. Gals./tank in each engine compartment (+ 179.8 in.) 
    1.50 U.S. Gals./tank usable. 
    (See NOTE 1 for data on system oil). 
 
Max. Operating Altitude.  25,000 ft. 
 
Control Surface Movements.  Elevator 28° Up 22° Down 
    Elevator Trim Tab   5° Up   7.5° Down (For airplane without BAe MOD 7362) 
         8.5° Down (For airplane wit BAe MOD 7362) 
 
    Rudder 25° Right 25° Left   
    Rudder Trim Tab 25° Right 25° Left   
 
    Aileron 25° Up 15° Down 
    Aileron Trim Tab   8.5° Up   8.5° Down 
 
    Flaps Takeoff 10° Down 
     Approach 20° Down 
     Landing 50° Down (Pre Mod 7760) 
     Landing 35° Down (Post  Mod 7760) 
     Lift Dump 70° Down

Page 8 of 12 A21EU 
DATA PERTINENT TO ALL MODELS 
 
Serial Nos. Eligible.  The United Kingdom Certificate of Airworthiness for Export endorsed as noted under  
    “Import Requirements” must be submitted for each individual aircraft for which  
    application for certification is made. 
     
Model HP.137 Jetstream Mk.1: Only those aircraft serials holding a standard 
airworthiness certificate issued prior to January 1, 2013 are eligible. 
 
    
Import Requirements.  A United States Airworthiness Certificate may be issued on the basis of a United 
    Kingdom Certificate of Airworthiness for Export signed by a representative of the 
    United Kingdom Civil Aviation Authority containing the following statement: “The 
    airplane covered by this certificate has been examined, tested and found to conform to 
the 14 CFR Part 23 design approved under US Type Certificate A21EU and is in a 
condition for safe operation.”  (See NOTE 6). 
 
Refer to the applicable bilateral agreement to verify eligibility for import into the United 
States of both new and used aircraft based on the scope of the agreement, to identify any 
required statements by the exporting authority on the export certificate of airworthiness 
(or equivalent document), and for procedures for coordinating exceptions to conformity 
statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification 
of Aircraft, for requirements for issuance of an airworthiness certificate for imported 
aircraft 
 
    Model HP.137 Jetstream Mk.1:None eligible after January 1, 2013. 
 
Certification Basis.   For Models HP.137 Jetstream Mk 1 and Jetstream Series 200 (See NOTE 7). 
 
FAR 21.29 and FAR 23, effective February 1, 1965, including Amendments 23-1 
through 23-3, plus Special Conditions notified by the U.S. Government to the 
Government of the United Kingdom in FAA letter of October 30, 1967. 
 
Compliance has been demonstrated with the requirements of 14 CFR Section 25.1419:  
Ice Protection. 
 
Date of Application for original Type Certificate:  February 15, 1966. 
Request for extension granted in accordance with FAR 21.17(b)(2). 
 
Date of application for amended Type Certificate Jetstream Series 200:  November 22, 
1973. 
 
Compliance has been demonstrated with the Special Federal Aviation requirements 
SFAR-41C effective September 13, 1982 (See NOTE 7). 
 
Date of application for amended Type Certificate Model HP.137 Jetstream MK1 Mod 
5168-SFAR-41C:  May 11, 1981. 
 
The United Kingdom CAA originally type certificated this aircraft under is type 
certificate Number BA15.  The FAA validated this product under U.S. Type Certificate 
number A21EU.  Effective September 28, 2003, the European Aviation Safety Agency 
(EASA) began oversight of this product on behalf of the United Kingdom CAA. 
 
For Jetstream Model 3101: 
FAR 21.29 and FAR 23, effective February 1, 1965 including Amendments 23-1 through 
23-3. 
Special Conditions notified by the U.S. Government to the Government of the United 
Kingdom in FAA letter of October 30, 1967. 
Special Federal Aviation Regulation No. 41, effective October 17, 1979 including 
Amendments 41-A and 41-C. 
Federal Aviation Administration Exemption No. 3548, issued on June 10, 1982.

Page 9 of 12 A21EU 
Special Federal Aviation Regulation No. 27, effective February 1, 1974, including 
Amendments 27-1 through 27-4 (Fuel Venting). 
-  The Airesearch TPE 331 approved engines comply with the fuel venting emission  
    requirements of SFAR 27 with the installation of Garrett Fuel Manifold Purge 
    System Kit No. 3101458-1. 
 
FAR 36, effective December 1, 1969, including Amendments 36-1 through 36-12. 
 
Compliance was demonstrated to the following FAR 25 requirements in effect of 8 May 
1970, in lieu of the FAR 23 ground load and landing gear requirements. 
 
FAR Sections 25.471, 25.473, 25.477, 25.479, 25.481, 25.483, 25.485, 25.487, 25.489, 
25.491, 25.493, 25.495, 25.499, 25.503, 25.507, 25.509, 25.511, 25.573, 25.723, 25.725, 
25.727, 25.729 (in effect on 7 May 1970), 25.731, 25.733 and 25.735. 
 
Compliance has been demonstrated with the requirements of 14 CFR Section 25.1419: 
Ice Protection. 
 
Compliance has been demonstrated with the requirements of FAR Sections 23.253, 
23.335(b)(4), 23.1505(c) and 23.1545(d), as amended by Amendment 23-7. 
 
Compliance has been demonstrated with the requirements of Special Federal Aviation 
Regulations SFAR-41c when supplements are incorporated into the Flight Manual 
Document No. HP.4.10 (See NOTE 6). 
 
Compliance has been demonstrated with FAA Special Conditions Reference 23/ACE/9 
effective 1 February 1985, when BAe MOD Kit 3299, Automatic Performance Reserve 
(with BAe MOD. No. 7376), or BAe MOD KIT 3359/1: 
Automatic Performance Reserve (with BAe MODS No. 7376 and 7472) have been 
embodied and when Supplement No. 4 is incorporated into Flight Manual Doc. No. 
HP.4.10. 
 
Date of Application for amended Type Certificate Jetstream Model 3101: 
February 21, 1980. 
 
Type Certificate No. A21EU issued April 25, 1969 for the HP.137 Jetstream Mk 1, 
amended May 17, 1977 for the Jetstream Series 200, and amended November 30, 1982 
for the Jetstream Model 3101, and amended April 19, 1985 for Mod. No. 5168. 
 
Certification basis for the water-methanol systems BAe MOD KIT 3147/2 and BAe 
MOD KIT 3358 is as follows (See NOTE 8). 
 
23.901(a) and (d); 23.903 (a)(1) and (c); 23.1041; 23.1141(a); 23.1143(a),(b),(c),(d), 
and (e); 23.1182; 23.1183(a); 23.1189(a)(1),(a)(4),(a)(5),(a)(6), and (c); 23.1301; 
23.1309 (a) and (b) effective March 26, 1984, and 25.945 effective May 2, 1977. 
 
FAR Part 135 Appendix A Sections 4(e) and (g); 5; 6(b) and (c); 18, 19(b); 20(a)(b), 
(d)(e), and (f); 35(a), (c), (d) and (h); 38(a)(1) and (a)(3); 46; 59; 60; 63(b) and 64. 
SFAR 41C section 5(h). 
 
The United Kingdom CAA originally type certificated this aircraft under is type 
certificate Number BA6.  The FAA validated this product under U.S. Type Certificate 
number A29EU.  Effective September 28, 2003, the European Aviation Safety Agency 
(EASA) began oversight of this product on behalf of the United Kingdom CAA. 
 
Service Information. Service Information. The Type Certificate for HP.137 Jetstream Mk.1, Jetstream Series 
200 and Jetstream Model 3101 (Series 3100) is held by BAE SYSTEMS (Operations)  
Ltd. of PrestwickInternational Airport. Flight Manuals, Overhaul and Maintenance  
Manuals, Pilot’s or Crew or Manufacturer’s Operating Manuals, Structural Repair 
Manuals, Service Bulletins, Vendor Manuals, including amendments thereto, and related 
documents, issued in respect of HP.137 Jetstream Mk.1 and/or Jetstream Series 200

Page 10 of 12 A21EU 
and/or Jetstream Model 3101 (Series 3100) by either Handley Page Limited, or Handley 
Page Aircraft Limited, or Scottish Aviation Limited, or British Aerospace - Aircraft 
Group - Scottish Division, or British Aerospace PLC -Aircraft Group - Scottish Division, 
or British Aerospace PLC - Aircraft Group – Civil Division - Prestwick, or British 
Aerospace PLC - Civil Division - Prestwick, or British Aerospace PLC - Civil Aircraft 
Division - Prestwick, or British Aerospace (Commercial Aircraft) Limited - Airlines 
Division - Prestwick, or British Aerospace Regional Aircraft Limited - Prestwick, or 
Jetstream Aircraft Limited or BAE SYSTEMS (Operations) Ltd., which contain a  
statement that the document is ARB or CAA approved, or ARB or CAA approved 
through the Manufacturer’s ARB or CAA Approval Ref. AD/1039/39 or DAI/8208/71 or 
AD/1051/44 or DAI/1743/44 or DAI/1011/55 or DAI/9386/92 or JAA JAR 21 Approval 
Ref. CAA.JA02034, are accepted by the FAA and are considered FAA approved. These 
approvals pertain to the type design only. 
 
  Each of the documents listed below must state that it is approved by the European 
Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – 
by the United Kingdom CAA. 
 
• Service bulletins, 
• Structural repair manuals, 
• Vender manuals, 
• Aircraft flight manuals, and 
• Overhaul and maintenance manuals. 
 
  The FAA accepts such documents and considers the FAA -approved unless on of the 
following conditions exits: 
 
• The documents change the limi tations, performance, or procedures of the FAA 
approved manuals: or 
• The documents make an acoustical or emissions change to this product’s U. S. type 
certificate as defined in 14 CFR 21.93. 
 
The FAA uses the post type validation procedures to approve these  documents.  The 
FAA may delegate on case-by -case to EASEA to approve on Behalf of the FAA for the 
U.S. type certificate.  If this is the case it will be noted on the document.  
 
Design changes that are contained in BAE SYSTEMS Service Bulletins and that are 
classified as Level 1 Major in accordance with either the US/UK or US/EASA Bilateral 
Aviation Safety Agreement Implementation Procedures for Airworthiness must be 
approved by the FAA. 
 
Airframe mandatory inspections and component life limits resulting from investigations 
and tests for compliance with damage tolerance requirements are listed in the 
"Airworthiness Limitations" section in Chapter 5 of the  Maintenance Manual.  Material 
covered in this Section must not be changed without FAA approval. 
 
  
 
Equipment.   The basic required equipment as prescribed in the applicable airworthiness regulations  
    (See Certification Basis) must be installed in the aircraft for certification.  Approved  
    equipment is included in HP MD/AIR/137.101/JRF/PC for HP.137 Jetstream Mk 1,  
    SAL MRI No. JS 200 for Jetstream Series 200, and BAe 1379303A/1379304A for  
    Jetstream Model 3101.  In addition the following items of equipment are required. 
    a) Stall Warning Indicators (Safe Flight Ltd. Type No. C77106-3 or C77106-4 or 
     C77106-5). 
    b) Stick Pusher Unit (Dowty Jack 1.03650.004). 
    c) ARB-Approved Airplane Flight Manual, Doc. No. HP.4.3 for HP.137 Jetstream 
     Mk 1. 
     CAA-Approved Airplane Flight Manual, Doc. No. HP.4.8 for Jetstream Series 200. 
     CAA-Approved Airplane Flight Manual, Doc. No. HP.4.10 (CAA-approved on

Page 11 of 12 A21EU 
     November 19, 1982) for Jetstream Model 3101. 
    The CAA (formerly ARB)-Approved Airplane Flight Manuals are also FAA-approved. 
 
NOTE. 
 
NOTE 1.  Current weight and balance report, including list of equipment included in the certified empty weight and  
loading instructions when necessary, 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 and control system). 
  The certificated empty weight and corresponding center of gravity locations must include:  
 
   For Models HP.137 Jetstream Mk 1 and Jetstream Series 200. 
   Unusable fuel of 12 lb. at (+215.5 in.) 
   Unusable oil of 18 lb. at   (+167.0 in.) 
 
   For Model Jetstream Series 3101 
   Unusable fuel of 66 lb. at (+215.5 in.) 
   Unusable oil of 7 lb. at     (+200.0 in.) 
 
NOTE 2.  The following placards must be displayed in full view of the pilot: 
  a) This airplane must be operated as a normal category airplane in compliance with the operating  
   limitations stated in the form of placards, markings and manuals.  No aerobatic maneuvers,  
   including spins, approve.” 
 
   Footnote 
  All placards required in the approved Airplane Flight Manual must be installed in the appropriate  
  locations. 
 
  b) Each individual airplane will be supplied with a placard that specified the kinds of operation, such as  
   VFR or IFR, Day or Night to which the operation of the airplane is limited by the equipment installed.  
 
NOTE 3.  The service life limits for aircraft structural parts which are fatigue critical are listed in    
  the approved Airplane Flight Manual, Doc. No. HP.4.3 for HP.137 Jetstream Mk,  
  Doc.No.HP.4.8 for Jetstream Series 200, and Section 2.5 (dated 10 November 1982) of  
  British Aerospace PLC Doc. No. SA.4-3100/MS/3 for the Jetstream Model 3101.   
 
NOTE 4.  When a Jetstream Model 3101 airplane leaves the British Aerospace - Prestwick factory  
  in the green configuration defined by Modification 76051 (or equivalent Modification),  
  the flight crew is limited to two pilots.  No persons other than the flight crew may be  
  carried.  The CAA-Approved Airplane Flight Manual Doc. No. HP.4.10 must incorporate  
  Amendment No. P/4. 
 
  When a Jetstream Model 3101 airplane leaves the British Aerospace - Prestwick factory  
  in the fully furnished configuration defined by Mod 73101 (or equivalent Modification)  
  no limitations apply. 
 
NOTE 5.  The Astazou XVIF1 engine, (installed to modification ADA D40/137) will deliver more  
  power under certain temperature and altitude conditions than the Astazou XIVC or C1  
  engine.  However, the maximum power available from either installation is the same  
  below 2000 ft.  The approved Flight Manual, Doc. HP.4.3 takes account of this. 
     
NOTE 6.  For Jetstream Model 3101, the United States Airworthiness Certificate shall be endorsed  
  “This airplane at weights in excess of 5,700 kg does not meet the airworthiness  
  requirements of ICAO as prescribed by Annex 8 of the Convention on International Civil Aviation.” 
 
   
For airplane without BAe MOD 7380: 
   No endorsement is required when supplement No. 5 is incorporated into Flight Manual  
   Supplement No. HP.4.10.  Embodiment of the Flight Manual Supplement No. 5 must be  
   recorded by entering BAe modification No. Kit 3278 in the relevant aircraft documents. 
 
   No physical changes are required for embodiment of BAe modification No. Kit 3278.

Page 12 of 12 A21EU 
 
  For airplane with BAe Mod 7380: 
  No endorsement is required when Supplement No. 7 is incorporated into Flight Manual 
  Document No. HP.4.10. 
Airplanes incorporating an Automatic Power Reserve (APR) System (See Certification Basis) 
require the additional incorporation of Supplement No. 9 into Flight Manual Document No. 
HP.4.10. 
Airplanes fitted with a Water Methanol System (See NOTE 8) require the additional incorporation 
of Supplement No. 8 into Flight Manual Document No. HP.4.10. 
Embodiment of only Flight Manual Supplement No. 7 must be recorded by entering BAe 
Modification No. Kit 3378A in the relevant aircraft documents. 
 
Embodiment of Flight Manual Supplements Nos 7 and 8 must be recorded by entering BAe 
Modification No. Kit 3378C in the relevant aircraft documents.  No physical changes are required 
for embodiment of BAe Modifications Nos Kit 3378A, 3378B or 3378C. 
 
For aircraft already in service, after entering BAe Modification No. Kit 3278, Kit 3378A, Kit 
3378B, or Kit 3378C in the relevant aircraft documents request the removal of the endorsement of 
non-compliance with ICAO Annex 8 Regulations from the aircraft’s airworthiness certificate, from 
the local FAA General Aviation District Office. 
 
NOTE 7. Compliance with requirements of: 
FAR 36, effective December 1, 1969, including Amendments 36-1 through 36-12, and SFAR 41 C effective 
September 13, 1982, has been demonstrated for the HP.137 
Jetstream MK1 airplane incorporating British Aerospace Modification No. 5168. 
 
The airworthiness certificate of the HP.137 Jetstream Mk1 airplanes incorporating BAe M No. 5168 must be 
endorsed:  “This airplane at weights in excess of 5700 kg does not meet the airworthiness requirements of 
ICAO, as prescribed by Annex B of the Convention on International Civil Aviation”, And; The CAA 
approved Flight Manual Doc. No. HP.4.3 must include CAA approved particular amendments Nos. P/4, P/6, 
P/7, P/8, P/9, P/10, P/11 and CAA approved supplements No. 15 (also see Equipment). 
 
NOTE 8. Installation of water-methanol system BAe MOD KIT  3147/2 requires the installation of FAA-approved  
 engines model TPE-331-10UF-513H and the embodiment of BAe MOD 7376. 
 
 Installation of water-methanol system BAe MOD KIT 3358 requires the installation of 
 FAA-approved engines model TPE 331-10UG-513H or TPE 331-10UG-514H and the embodiment of BAe  
 MODS 7376 and 7472. 
 
 Installation of either BAe MOD KIT 3147/2 or BAe MOD KIT 3358 requires incorporation of Supplement  
 No. 6 in AFM document No. HP.4.10. 
 
NOTE 9. When engines TPE 331-10UG-513H (BAe MOD 7432), TPE 331-10UGR-513H (Bae MOD 7434), TPE  
 331-10UGR-514H (BAe MOD 7547), or TPE 331-10UG-515H (Bae MOD 7548) are installed, associated  
 BAe MOD 7341 - indicating System for Strain Gauge Torque Sensing System, must be embodied.  The  
 CAA approved Flight Manual Doc. No. HP.4.10 must incorporate Amendment No. P/26. 
 
NOTE 10. TPE 331-10UG-513 H and TPE 331-10UG-514H engines may be interchanged.  TPE 331-10UGR-513H  
 and TPE 331-10UGR-514H engines may be interchanged. 
 
 
 
.....END.....
```

## ADs (108, first 50, in force first)

- [AD 2023-19-05](https://openairdocs.org/ad/2023-19-05): Rudder Tab Control System; Fuselage Main, Plate/Skin · British Aerospace Regional Jetstream Series 3101 and Jetstream 3201. Effective Nov 6, 2023
- [AD 2022-12-09](https://openairdocs.org/ad/2022-12-09): Main Landing Gear Attach Section · BAE Systems Jetstream Series 3101, H.P. 137 Jetstream Mk. 1, Jetstream Series 200 and 1 more. Effective Jul 21, 2022
- [AD 2022-11-16](https://openairdocs.org/ad/2022-11-16): Rudder Control System, Elevator Control System · BAE Systems Jetstream Series 3101 and Jetstream 3201. Effective Jul 13, 2022
- [AD 2022-03-18](https://openairdocs.org/ad/2022-03-18): Gust Lock/Damper System · BAE Systems Jetstream Series 200, Jetstream 3201 and Jetstream Series 3101. Effective Mar 21, 2022
- [AD 2018-02-15](https://openairdocs.org/ad/2018-02-15): Landing Gear · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Mar 5, 2018
- [AD 2017-10-14](https://openairdocs.org/ad/2017-10-14): Landing Gear · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream Series 200 and Jetstream Series 3101. Effective Jul 5, 2017
- [AD 2015-16-05](https://openairdocs.org/ad/2015-16-05): Landing Gear · British Aerospace Regional Jetstream 3201 and Jetstream Series 3101. Effective Sep 21, 2015
- [AD 2015-06-01](https://openairdocs.org/ad/2015-06-01): Landing Gear · British Aerospace Regional Jetstream 3201 and Jetstream Series 3101. Effective Apr 24, 2015
- [AD 2011-11-01](https://openairdocs.org/ad/2011-11-01): Landing Gear · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Jun 22, 2011
- [AD 2010-25-02](https://openairdocs.org/ad/2010-25-02): Landing Gear · British Aerospace Regional Jetstream 3201 and Jetstream Series 3101. Effective Jan 11, 2011
- [AD 2010-09-02](https://openairdocs.org/ad/2010-09-02): Flight Controls · British Aerospace Regional Jetstream 3201 and Jetstream Series 3101. Effective Jun 3, 2010
- [AD 2010-08-04](https://openairdocs.org/ad/2010-08-04): Landing Gear · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective May 19, 2010
- [AD 2009-19-03](https://openairdocs.org/ad/2009-19-03): Landing gear · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Oct 5, 2009
- [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 2008-12-02](https://openairdocs.org/ad/2008-12-02): Nose-wheel · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Jul 16, 2008
- [AD 2008-06-12](https://openairdocs.org/ad/2008-06-12): Steering jack gland housing · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Apr 16, 2008
- [AD 2007-21-17](https://openairdocs.org/ad/2007-21-17): Landing gear radius rods · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Nov 28, 2007
- [AD 2007-15-01](https://openairdocs.org/ad/2007-15-01): Wing spigot post assembly · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Aug 22, 2007
- [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005
- [AD 2003-04-07](https://openairdocs.org/ad/2003-04-07): Horizontal and Vertical Stabilizer Attachment Fittings and Associated Hardware · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Apr 7, 2003
- [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 2002-03-02](https://openairdocs.org/ad/2002-03-02): Main Landing Gear (MLG) Hinge Fittings, Support Angles, and Attachment Bolts · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream Series 200 and Jetstream Series 3101. Effective Apr 2, 2002
- [AD 2002-01-05](https://openairdocs.org/ad/2002-01-05): Main Landing Gear Radius Rods · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Feb 11, 2002
- [AD 2001-03-11](https://openairdocs.org/ad/2001-03-11): Main Landing Gear Radius Rods · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Apr 6, 2001
- [AD 2001-01-02](https://openairdocs.org/ad/2001-01-02): Steering Jack Assembly · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Mar 5, 2001
- [AD 2001-01-03](https://openairdocs.org/ad/2001-01-03): Nose Landing Gear Steering Actuator · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Feb 24, 2001
- [AD 2000-23-33](https://openairdocs.org/ad/2000-23-33): Vertical Stabilizer · British Aerospace Regional H.P. 137 Jetstream Mk. 1 and Jetstream Series 200. Effective Jan 12, 2001
- [AD 2000-20-13](https://openairdocs.org/ad/2000-20-13): Rudder Quadrant Support Structure · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Nov 27, 2000
- [AD 2000-16-13](https://openairdocs.org/ad/2000-16-13): Nose Wheel Steering System · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Sep 29, 2000
- [AD 99-15-11](https://openairdocs.org/ad/99-15-11): NLG Steering Selector Valve · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Sep 10, 1999
- [AD 99-06-11](https://openairdocs.org/ad/99-06-11): Elevator Bias Spring Assembly · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Apr 26, 1999
- [AD 99-06-12](https://openairdocs.org/ad/99-06-12): Nose Landing Gear Steering · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Apr 26, 1999
- [AD 99-04-21](https://openairdocs.org/ad/99-04-21): MLG Brakes Units · British Aerospace Regional Jetstream 3201 and Jetstream Series 3101. Effective Apr 2, 1999
- [AD 99-01-06](https://openairdocs.org/ad/99-01-06): Bonding Socket at Fueling Points · British Aerospace Regional Jetstream Series 3101. Effective Mar 19, 1999
- [AD 99-01-07](https://openairdocs.org/ad/99-01-07): Lower Fuselage Skin Panels · British Aerospace Regional Jetstream Series 3101. Effective Mar 19, 1999
- [AD 98-21-28](https://openairdocs.org/ad/98-21-28): Propeller De-Icing System · British Aerospace Regional Jetstream Series 3101. Effective Jan 15, 1999
- [AD 98-21-25](https://openairdocs.org/ad/98-21-25): Ground Inhibit Relay · British Aerospace Regional Jetstream 3201 and Jetstream Series 3101. Effective Nov 26, 1998
- [AD 98-21-13](https://openairdocs.org/ad/98-21-13): Elevator Trim Servo Motor · British Aerospace Regional Jetstream Series 3101. Effective Nov 20, 1998
- [AD 98-21-14](https://openairdocs.org/ad/98-21-14): Navigation System · British Aerospace Regional Jetstream Series 3101. Effective Nov 2, 1998
- [AD 98-12-31](https://openairdocs.org/ad/98-12-31): Fuel Cross Feed Pipes · British Aerospace Regional Jetstream Series 3101. Effective Sep 10, 1998
- [AD 98-12-23](https://openairdocs.org/ad/98-12-23): Windshield Wiper Arm and NLG Toggle and Axle Bracket Lugs · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Jul 28, 1998
- [AD 98-12-11](https://openairdocs.org/ad/98-12-11): Emergency Hydraulic Hand-Pump · British Aerospace Regional Jetstream Series 3101. Effective Jul 24, 1998
- [AD 98-11-31](https://openairdocs.org/ad/98-11-31): Autopilot Elevator Electric System Relays · British Aerospace Regional Jetstream Series 3101. Effective Jul 17, 1998
- [AD 97-24-07](https://openairdocs.org/ad/97-24-07): Magnetically ltching Relays · British Aerospace Regional Jetstream 3201 and Jetstream Series 3101. Effective Dec 31, 1997
- [AD 97-07-11](https://openairdocs.org/ad/97-07-11): NLG Actuator Support Structure · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective May 23, 1997
- [AD 96-17-12](https://openairdocs.org/ad/96-17-12): Nose Landing Gear Bolts · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Oct 21, 1996
- [AD 96-11-01](https://openairdocs.org/ad/96-11-01): Automatic Airframe De-Ice System · British Aerospace Regional Jetstream 3201 and Jetstream Series 3101. Effective Jul 2, 1996
- [AD 96-11-02](https://openairdocs.org/ad/96-11-02): Inspect Spigot Housing Plate · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream Series 200 and Jetstream Series 3101. Effective Jul 2, 1996
- [AD 96-09-17](https://openairdocs.org/ad/96-09-17): AFM - Icing · British Aerospace Regional Jetstream 3201 and Jetstream Series 3101. Effective Jun 11, 1996
- [AD 95-24-13](https://openairdocs.org/ad/95-24-13): Inspect Mounting Spigots · British Aerospace Regional H.P. 137 Jetstream Mk. 1, Jetstream 3201, Jetstream Series 200 and 1 more. Effective Jan 17, 1996

All 108: https://openairdocs.org/tcds/A21EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [British Aerospace JETSTREAM 3101](https://openairdocs.org/model/british-aerospace-jetstream-3101): 0 aircraft (registry code 1500108)

## STCs approved under this data sheet (115, 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 SA8667SW](https://openairdocs.org/stc/SA8667SW): Installation of Goodrich Avionics Systems TCAS 791. Acron Aviation Inc.
- [STC SA03020AT](https://openairdocs.org/stc/SA03020AT): Installation of a Sandel Model ST3400 Terrain Awareness and Warning System (TAWS). Woven Electronics LLC
- [STC ST03269AT](https://openairdocs.org/stc/ST03269AT): Installation of a Honeywell CAS 67A Traffic Alert and Collision Avoidance System IT (TCAS IT) and Dual MST 67A Mode S Transponder. Woven Electronics LLC
- [STC SA00010SE](https://openairdocs.org/stc/SA00010SE): Mk VI ground proximity warning system installed. Honeywell International Inc
- [STC ST01930LA](https://openairdocs.org/stc/ST01930LA): Installation of Sandel Avionics SN4500 Electronic Horizontal Situation Indicator (EHSI). Sandel Avionics LLC
- [STC SA00063WI-D](https://openairdocs.org/stc/SA00063WI-D): Installation of Bendix/King CAS 66A TCAS I System, or provisions for CAS 66A TCAS I System.. Honeywell International Inc
- [STC SA01452CH](https://openairdocs.org/stc/SA01452CH): Installation of an air ambulance conversion kit.. Med-Pac Inc.
- [STC SA02677LA](https://openairdocs.org/stc/SA02677LA): Modification to upgrade the existing Mode S Transponder system by installing the ACSS NXT-700 Transponder with ADS-B Out and optionally install the ACSS NXG-900 GPS as the position source for ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC SA02678LA](https://openairdocs.org/stc/SA02678LA): Modification to upgrade the existing Mode S Transponder system by installing the ACSS NXT-600 Transponder with ADS-B Out and optionally install the ACSS NXG-900 GPS as the position source for ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC SA00344BO PAGE 2](https://openairdocs.org/stc/SA00344BO%20PAGE%202): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SA00433SE](https://openairdocs.org/stc/SA00433SE): Air medical installation.. LifePort LLC
- [STC ST04340NY](https://openairdocs.org/stc/ST04340NY): Installation of TCAS 7.1 (ACAS II) upgrade of Prior Existing TCAS 7.0. Scandinavian Avionics Design ApS
- [STC ST03776NY](https://openairdocs.org/stc/ST03776NY): Modification to upgrade existing Rockwell Collins TCAS (Model: TTR-920, TTR-921, and TTR-4000) at VERSION 7.0 to Rockwell Collins TCAS (Model: TTR-921, TTR-4000, and TTR-4100) at VERSION 7.1 (ACAS II). Scandinavian Avionics Design ApS
- [STC SA02606CH](https://openairdocs.org/stc/SA02606CH): Install Air Ambulance conversion. Paul/ Lanna Egan LLC
- [STC SA00674WI-D](https://openairdocs.org/stc/SA00674WI-D): Modification of Collins VHF-22A/VHF-22B VHF COMM Receiver Transmitter with CTL-22 Control Pro Line II System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II system installation.. Rockwell Collins Inc
- [STC SA00377DE](https://openairdocs.org/stc/SA00377DE): ONE-ONLY STC, S/N 745: Installation of an oversize convex observer window in the most aft standard cabin window position.. Straight Flight Inc
- [STC SA482NE](https://openairdocs.org/stc/SA482NE): Remove existing starter-generator and install Aircraft Parts starter - generator P/N 300SG121Q.. Shurka Aerospace Inc
- [STC ST02540AT-D](https://openairdocs.org/stc/ST02540AT-D): Installation of replacement fuel tank sealant system. FFC Manufacturing
- [STC SA02621CH](https://openairdocs.org/stc/SA02621CH): Installation of a cargo door. Murray Aircraft Modifications
- [STC SA02593CH](https://openairdocs.org/stc/SA02593CH): Installation of a cargo floor. Murray Aircraft Modifications
- [STC SA02592CH](https://openairdocs.org/stc/SA02592CH): Installation of a pressure bulkhead. Murray Aircraft Modifications
- [STC SA5862NM](https://openairdocs.org/stc/SA5862NM): Installation of interior fluorescent cabin lighting system.. Bruce Aerospace Inc.
- [STC SA02542CH](https://openairdocs.org/stc/SA02542CH): Install Cargo Net. Murray Aircraft Modifications
- [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SA1019GL](https://openairdocs.org/stc/SA1019GL): Installation of Woodward P/N A213796 control box, electrical connector, and remote switch.. Ontic Engineering and Manufacturing Inc.
- [STC SA01306WI-D](https://openairdocs.org/stc/SA01306WI-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.. Rockwell Collins Inc
- [STC ST02284NY](https://openairdocs.org/stc/ST02284NY): Installation of Concorde RG-380 Battery.. Infinion Certification Engineering Inc.
- [STC SP00400SE](https://openairdocs.org/stc/SP00400SE): Installation of various propeller electrical de-icer models. SMR Technologies
- [STC SA01141WI-D](https://openairdocs.org/stc/SA01141WI-D): Modification of a single or dual Collins TDR-94 or TDR-94D Mode S Transponder System installation with CTL-92 control head to a Flight ID capable Collins TDR-94 or TDR-94 Mode S Transponder System installation with CTL-92E control head.. Rockwell Collins Inc
- [STC SA1372GL](https://openairdocs.org/stc/SA1372GL): Installation of McCauley propellers.. McCauley Propeller Systems
- [STC ST03088AT](https://openairdocs.org/stc/ST03088AT): Installation of a Honeywell MK VI Enhanced Ground Proximity Warning Systems (EGPWS). Chippewa Aerospace, Inc.
- [STC SA1055GL](https://openairdocs.org/stc/SA1055GL): Removal of TC P/N 213761 or213763 propeller synchrophaser control box and electrical connector and installation of P/N A213796 control box, electrical connector, and remote switch.. Ontic Engineering and Manufacturing Inc.
- [STC SA01945NY](https://openairdocs.org/stc/SA01945NY): Cockpit voice recorder replacement with Universal CVR 30B or CVR 120.. MidCanada Mod Center
- [STC SA572EA](https://openairdocs.org/stc/SA572EA): Installation of Goodrich Model 5735K deicer kit (P/N 5735 deicer boot, P/N D-5735-1 cable, P/N 5735H hardware kit).  Limited to aircraft which incorporate Goodrich Propeller Deicing Systems equipped with Goodrich Propeller Deicer Boot P/N 4E1185-5 on Hartzell propellers as listed on STC SA572EA eligibility list.. Goodrich Corp.
- [STC SA4963NM](https://openairdocs.org/stc/SA4963NM): Installation of a NSA sunvisor system.. Rosen Sunvisor Systems LLC
- [STC SA3814SW](https://openairdocs.org/stc/SA3814SW): Installation of Sperry SPZ-200B autopilot system.. BAE Systems Regional Aircraft Inc.
- [STC SA5440SW](https://openairdocs.org/stc/SA5440SW): Installation of basic interior.. BAE Systems Regional Aircraft Inc.
- [STC SA5441SW](https://openairdocs.org/stc/SA5441SW): Installation of dual Collins VIR30A navigation receiver, dual Collins VHF20B communication transmitter/receiver, dual Collins DME-40 distance measuring equipment, single Collins TDR-9 ATC transponder, dual Baker M1035 cockpit audio system.. BAE Systems Regional Aircraft Inc.
- [STC SA5442SW](https://openairdocs.org/stc/SA5442SW): Installation of dual SAFT batteries with Foxtronics BTI-600-2A battery temperature system.. BAE Systems Regional Aircraft Inc.
- [STC SA5443SW](https://openairdocs.org/stc/SA5443SW): Installation of dual KGS electronics SPC-60A static inverters.. BAE Systems Regional Aircraft Inc.
- [STC SA5444SW](https://openairdocs.org/stc/SA5444SW): Installation of dual Sperry SPI-501 flight director system with optional Sperry RI-300 radio altimeter, CM-600 comparator and VA-100 voice advisory systems.. BAE Systems Regional Aircraft Inc.
- [STC SA5445SW](https://openairdocs.org/stc/SA5445SW): Installation of Foster AD-612 RNAV computer.. BAE Systems Regional Aircraft Inc.
- [STC SA5446SW](https://openairdocs.org/stc/SA5446SW): Installation of Collins WXR-300 weather radar system and optional RNS-300 radar navigation system.. BAE Systems Regional Aircraft Inc.
- [STC SA5447SW](https://openairdocs.org/stc/SA5447SW): Installation of Fredrickson Jetfone communication system.. BAE Systems Regional Aircraft Inc.
- [STC SA5448SW](https://openairdocs.org/stc/SA5448SW): Installation of dual IDC-523-26700-127 or IDC-523-26700-147/247 airsspeed indicators, Single IDC-570-24929-406 copilot's altimeters, single IDC 40620-E1300 copilot's vertical speed indicator and single Sperry AZ-241 air data computer.. BAE Systems Regional Aircraft Inc.
- [STC SA5449SW](https://openairdocs.org/stc/SA5449SW): Installation of Jet AI-804R standby horizon.. BAE Systems Regional Aircraft Inc.
- [STC SA5450SW](https://openairdocs.org/stc/SA5450SW): Installation of Foxboro fuel flow system.. BAE Systems Regional Aircraft Inc.
- [STC SA5462SW](https://openairdocs.org/stc/SA5462SW): Installation of Dorne-Margolin DMN 4-17-1/A NAV antennae.. BAE Systems Regional Aircraft Inc.
- [STC SA5775SW](https://openairdocs.org/stc/SA5775SW): Installation of dual Sperry EDZ-600 electronic flight instrument system (EFIS).. BAE Systems Regional Aircraft Inc.

All 115: https://openairdocs.org/tcds/A21EU/stcs.md

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