# TCDS A41NM: BAE Systems (Operations) Limited

- Type: Type certificate data sheet
- Status: Current
- Holder: BAE Systems (Operations) Limited
- Revision: 5
- Revised: March 28, 2007
- Product: Aircraft, Large Airplane
- Certification basis: Part 1, Part 3, Part 25, Part 34, Part 36
- Data sheet PDF: https://openairdocs.org/files/sha256/43/e2/43e217812ce6b0c5758ba0a1a97a43d253d8dbb57f228665e3f0a9cd062e9e1f
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C60138EFB3FD295C862572B300721C0C.0001
- Page: https://openairdocs.org/tcds/A41NM

## Models (1)

As the data sheet lists them.

- Jetstream Model 4101

## What the data sheet says

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

```text
DEPARTMENT OF TRANSPORTATION  
FEDERAL AVIATION ADMINISTRATION  
 
A41NM 
Revision  5 
BAE SYSTEMS (Operations ) Limited 
Jetstream Model 4101 
March 28, 2007 
 
TYPE CERTIFICATE DATA SHEET NO. A41NM 
 
This data sheet, which is part of Type Certificate No. A41NM, 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: BAE SYSTEMS (Operations) Limited 
 Prestwick International Airport 
 Ayrshire, Scotland KA9 2RW 
 
Jetstream Model 4101 (Transport Category Airplane) approved 9 April 1993 (see note 7):  
  
Engines:  Left:  TPE331-14GR-XXXX Garrett turbo-propeller, reduction gear  
   ratio 22.97:1, rotates clockwise when viewed from rear. 
 Right: TPE331-14HR-XXXX Garrett turbo-propeller, reduction gear  
   ratio 22.93:1, rotates counter clockwise when viewed from rear. 
  
 Note:  -XXXX = Dash number portion of engine model number (see below) 
 
  
 
Engine Model Number 
Jetstream Aircraft Modification Number 
Signifying Installation of Engines Having the Model Number 
Shown 
 TPE331-14GR/14HR-801H None (Original Build Standard) 
 TPE331-14GR/14HR-802H None (Original Build Standard) 
                                   -803H JM41278 
                                   -804H JM41278 and JM41312 
                                   -805H JM41278, JM41312, JM41333 and JM41300 
                                   -806H JM41333 
                                   -807H JM41278, JM41312 and JM41333 
                                   -901H JM41465 
                                   -808H JM41278, JM41312 and JM41548A or B 
                                   -809H JM41278, JM41312, JM41333, JM41300 and JM41548A or B 
                                   -810H JM41278, JM41312, JM41333 and JM41548A or B 
                                   -903H JM41465 and JM41548A or B 
 
Engine Limits: Propeller Shaft Torque: 
  Pre Mod JM41300: 
  Maximum permissible torque for take-off and continuous operation is  
  100% (5076 Lb-Ft).  This equates to 1119 kW (1500 SHP) at 100% (1552 RPM)  
  propeller rotational speed. 
    
  Post Mod JM41300: 
  Maximum permissible torque for take-off and continuous operation is  
  100% (5584 Lb-Ft).  This equates to 1230 kW (1650 SHP) at 100% (1552 RPM)  
  propeller rotational speed 
 
Page No. 1 2 3 4 5 6 7 8 9 
Rev. No. 5 4 4 4 4 5 5 4 4

A41NM, Rev 5 2 of 9 
Engine Limits: (cont.)
 Engine Propeller Shaft Rotational Speed: 
  Maximum for Take-Off,  Maximum Continuous and APR operation is 101%  
  (1568 RPM). 
 
 Exhaust Gas Temperature (EGT):  
  Maximum permissible Exha ust Gas Temperature (EGT) at any given time is the  
  displayed EGT LIMIT with Integrated Electronic (engine) Control (IEC) selected  
  ON. 
Fuel and Additives: a. Engine fuels approved for use are as follows: 
 
   Kerosene Type: UK:  DERD 2453 (AVTUR/FSII)* 
       DERD 2494 (AVTUR) 
     USA:   ASTM D 1655, Type Jet A or  
       J e t  A - 1  
       MIL-T-83133 Grade JP-8* 
     NATO:   F34* and F35 
     CANADA: CAN/CGSB-3.22-M86 
 
   Kerosene Type: UK:  DERD 2454 (AVTAG/FSII)* 
     USA:   ASTM D 1655, (Jet B)  
       MIL-T-5624, (JP-4) 
     CANADA: CAN/CGSB-3.22-M86 (FSII) 
       CAN/CGSB-3.22-M86 
     NATO:   F40* 
 
 
 b. Each of the following additives is  approved for use with the fuel and 
  must be to the latest standard of th e relevant specification.  Fuel marked   
  with an asterisk (*) already contains fuel system icing inhibitor and further  
  additions to those fuels are not permitted. 
   Icing Inhibitors: Concentrations not to exceed 0.15% by volume. 
      UK:  DERD 2451 (AL-31) 
      USA:  MIL-I-27686 
      ASTM D 1655 
      NATO: S748 
 
   Biocide: Biobor JF Biocide in concentration not greater than 270 parts per  
   million (20 ppm of elemental boron). 
 
Engine Oil: The oil capacity for each engine and oil tank combined is:  
  5.68 liters   
  1.25 UK gallons 
  6  U.S. quarts 
 
 Oil Specifications: 
     USA  NATO
   Type II:  MIL-L-23699C 0-156 
 
 Brands: Mixing of oil brands is not permitted.  The approved brands of oil are:  Mobil Jet  
 Oil II, Exxon (ENCO/ESSO) 2380 Turbo Oil, Castrol 5000, Aeroshell/Royco Turbine  
 Oil 500 or 560. 
 
 Oil Temperature Limits: 
  Minimum for Starting minus 40 °C 
  Maximum Continuous 110 °C 
  Maximum  127 °C (5 minute limit) 
 The minimum permissible oil temperature is 55 °C for all operating conditions   
 other than starting and ground operations.

3 of 9 A41NM, Rev 5 
 
 Oil Pressure Limits:  
     Minimum Pressure  Maximum Pressure 
   Taxi RPM  30 PSI   65 PSI 
   Flight RPM   45 PSI   65 PSI 
 If the oil temperature is cold, a transient oil pressure of 85 PSI is permitted during an  
 engine start. 
Propellers: Pre Mod JM41300: 
  Left:  McCauley B5JFR36C1101-* /* -114GCA-0 
  Right: McCauley C5JFR36C1102-* /* -L114GCA-0 
  Blades:  5 
 Post Mod JM41300: 
  Left:  McCauley B5JFR36C1103-*/* -114HCA-0 
  Right: McCauley C5JFR36C1104-* /* -L114HCA-0 
  Blades:  5 
 
 Notes: (1)  */* = in the propeller mode l number denotes a variable alphabetical  
    suffix which gives the modification state of the propeller.  
   (2) Mod JK42618 permits post Mod JM41300 propellers to be fitted to  
    airplanes with 1500 shp engines at MTOW of 24,000 lb. 
   (3) Mod JK42843 permits post Mod 41300 propellers to be fitted to  
    airplanes with 1500 shp engines at MTOW of 23, 000 lb. 
 
Propeller Limits: Speed Range: 
  All Operations, 101% RPM. 
  Continuous ground operation between 82% and 90% and below 68% rpm   
  is prohibited.  Except for takeoff , c ontinuous ground operation is prohibited when  
  the torque is greater than 60% and the wi nd is greater  than 15 kts unless the wind is  
  from within ±45 degrees of the nose of the airplane. 
 
 Diameter (Nominal): 114.0 inches.  Reduction to a minimum of 112.0 inches permitted. 
 
 Pitch Settings at 42.0 inch radius station: 
  Maximum Reverse: -15 ° 
  Flight Idle: +  7 ° (pre Mod JM41333) 
    + 1 0 ° (post Mod JM41333)  
  Feathered:  +79.7° 
 
Airspeed Limits: V MO/MMO (Maximum Operating Speed) 
  VMO = 250 KIAS 
  MMO = 0.52 (above 17,400 ft altitude) 
 
 V A (Maneuvering Speed - flaps retracted) 
  VA = 180 KIAS 
 
 V FE (Flap Maximum Extended Speeds) 
  VFE =  170 KIAS    9 ° Flap (Pre Mod JK42584) 
    200 KIAS    9 ° Flap (Post Mod JK42584) 
    160 KIAS  15°  Flap 
    140 KIAS  25°  Flap 
 
 V LO (RET)   (Landing Gear, Maximum Speed During Retraction) 
 V LO (EXT)   (Landing Gear, Maximum Speed During Extension) 
 V LE           (Landing Gear, Maximum Operating Speed While Extended)

A41NM, Rev 5 4 of 9 
 
 V LO (RET) = 160 KIAS 
 V LO (EXT) = VLE  = 170 KIAS (Pre Mod JK42584) 
 VLO (EXT) = VLE  = 170 KIAS (Flaps 0°, Post Mod JK42584) 
 V LO (EXT) = VLE  = 200 KIAS (Flaps 9°, Post Mod JK42584) 
 
 V MC (Minimum Control Speed With Critical Engine Inoperative) 
  VMC = 91 KIAS (Pre Mod JM41300) 
  VMC = 92 KIAS (Post Mod JM41300)  
CG Range:
Pre Mod JM41300: 
Weight Fuselage Station Inches 
 Fwd Limit Fwd Limit Aft Limit 
 L/G Up L/G Down L/G Up/Down 
13000 308.35 310.00 322.00 
16150 308.35 310.00 - 
16834 - - 329.10 
18500 - - 329.80 
23000 321.38 322.54 329.80 
Note: Straight line variations between weights and fuselage stations where quoted. 
 
Post Mod JM41300: 
Weight Fuselage Station Inches 
 Fwd Limit Fwd Limit Aft Limit 
 L/G Up L/G Down L/G Up/Down 
13000 308.35 310.00 322.00 
16150 308.35 310.00 - 
16834 - - 329.10 
18500 - - 329.80 
20700 316.82 318.15 329.80 
24000 319.61 320.75 329.80 
Note: Straight line variations between weights and fuselage stations where quoted. 
 
CG Datum: The CG datum is defined as fuselage station zero (Stn 0.0).  This point is 3.556m  
 (11 ft 8 in) forward of the weighing point which is marked by a screw on the   
 bottom of the fuselage on the aircraft center-line at Stn. 140. 
 
Standard Mean Chord (SMC): The length of the SMC is 1.770m (69.69 inch es).  The leading edge of the SMC is  
 7.798m (307.02 inches) aft of Station 0.0.  
 
Leveling Means: Leveling beams are mounted at Station 327 on the passenger seat rails.  See weight and  
 balance manual. 
 
Maximum Weights: Pre Mod JM41300: 
Condition Max Wt  
(kg) 
Max Wt 
(Lb) 
Taxi and Ramp 10483  23110 
Take-off 10433  23000  
Landing 10115  22300 
Zero Fuel 9389  20700  
Jacking Weight 8981  19800

5 of 9 A41NM, Rev 5 
 
 Post Mod JM41300: 
Condition Max Wt 
(Kg) 
Max Wt 
(Lb) 
Taxi and Ramp 10936  24110  
Take-off 10886 24000 
Landing 10569 23300 
Zero Fuel 9707 21400 
Jacking Weight 8981  19800 
 
Minimum Crew: 2 - Pilot and Co-pilot 
 
Maximum No. Passengers: 30 
Maximum Baggage/Cargo: 544 kg (1200 lb) in the rear baggage bay. 
 159 kg (350 lb) in the ventral pod. 
   45 kg (100 lb) in the forward right stowage. 
   23 kg (50 lb) in the forward left stowage. 
 Or as otherwise placarded on the airplane. 
Fuel Capacity: 
 
Fuel Capacity UK Gal US Gal Liters kg lb 
Usable 727 874 3306 2639 5819 
Unusable 4 5 19 15 33 
Total 731 879 3325 2654 5852 
Maximum Operating Altitude: 
 25,000 ft  
 
Airplane Operating Temperature Range: 
 Minimum of minus 40 °C between minus 1000 ft and 16000 ft pressure altitude,  
 decreasing linearly to minus 54 °C at 25000 ft pressure altitude. 
 Maximum of ISA + 40 °C. 
 
Fuel Tank Temperatures: The minimum fuel tank temperature is minus 37 °C. 
 The maximum fuel tank temperature is plus 49 °C. 
 
Flying Control Surface Angular Travel: 
 Measured at right angles to the hinge line: 
  Aileron:  21.4° Up, 14.15° Down 
  Aileron Trim Tabs: 18.2 ° Up, 17.75° Down 
  Flaps: 
   Take-off 0°  with Mod. JM 41400 embodied 
    9 ° or 15° with Mod. JK 42493 or JD42525 embodied 
   Approach 15 ° 
   Landing 25°  
  Elevator: 
   2 8 ° Up, 17° Down 
  Elevator Trim Tab: 
   Left: 5.58 ° Up, 8.4° Down 
   Right: 5.47 ° Up, 8.67° Down 
  Rudder: 
   ±  2 4 ° 
  Rudder Trim Tab: 
   9.24°  Right, 8.25° Left 
 
Operating Limitations: Aircraft shall be operated in compliance with the operating limitations specified in  
 the FAA/CAA approved Airplane Flight Manual Document No. J41.01.

A41NM, Rev 5 6 of 9 
DATA PERTINENT TO ALL MODELS: 
 
Serial Numbers Eligible: A United Kingdom Certificate of Airworthiness for Export endorsed as noted   
 under "Import Requirements" below must be submitted for each individual   
 airplane for which application for United States certification is made. 
 
Import Requirements: The FAA can issue a U.S. airworthiness certificate based on an Export Certificate of 
Airworthiness (Export C of A) signed by a representative of Civil Aviation Authority of 
the United Kingdom (CAA-UK) on behalf of the European Community. The Export C of 
A should contain the following statement: ‘The aircraft covered by this certificate has 
been examined, tested, and found to conform with the Type Design approved under U.S. 
Type Certificate No. A41NM and to be in a condition for safe operation.’  Only Model 
Jetstream 4101 airplanes manufactured in the United Kingdom and accompanied by a 
CAA-UK Export Certificate of Airworthiness are eligible for a United States Certificate 
of Airworthiness. 
 
Certification Basis: -Part 25 of the FAR's dated February 1, 1965, as amended by amendments 25-1 
 through 25-66 (based on the BAe application date to CAA-UK for TC), and 
 
 -Part 25 of the FAR's amendments numbered 25-67, 25-68, 25-69, 25-70, and  
 25-71 , and 
 
 -Part 25 of the FAR's sections 25.361 and 25.729 and paragraphs 25.571(e)(2),  
 25.773(b)(2) and 25.905(d), all as amended by amendment 25-72, and 
 
 -Part 25 of the FAR's, Section 25.1419 as amended by amendments 25-1 through  
 25-66 of the FAR's (BAe elected to comply with this requirement), and  
 
 -FAA Special Conditions (SC's) as follows: 
  -SC's number 25-ANM-45 issued July 9, 1991 and 25-ANM-45A issued   
  November 8, 1994, Cabin Aisle Width 
  -SC's number 25-ANM-48 issued A ugust 29, 1991, Lightning and High   
  Intensity Radiated Fields (HIRF), and 
  -SC’s number 25-ANM-110 issued December 6, 1995, ATTCS power for   
  approach climb performance, see NOTE 8 
  SC number 25-ANM-129, issued June 5, 1997, Continuous Power Reserve (CPR) 
  System, see NOTE 9 
  SC number 25-165-SC, issued September 28, 2000, Seats with Inflatable Lapbelts 
  see NOTE 10 
 
 -FAA Exemptions as follows: 
  Exemption number 5587, head  impact criteria     
  (25.562(c)(5)) for the three most forward passenger seats in the passenger   
  cabin, expired March 31, 2001.  [Exe mption 5587 was issued January 13, 1993].  
  see NOTE 10. 
 
 -FAA Equivalent Safety Findings as follows: 
  -Section 25.349, flight rolling conditions 
  -Paragraph 25.729(e)(2), landing gear aural warning inhibited whenever   
  the airspeed is greater than 145 knots IAS, and 
  -Paragraph 25.811(d)(2), emergenc y exit markings, overwing exits, and 
  -Paragraph 25.1182(a), Nacelle areas behind the firewalls, and 
 
 -Part 34 of the FAR's effective September 10, 1990, and 
 
 -Part 36 of the FAR's effective December 1, 1969 as amended by amendments 36-1  
 through 36-18 including Appendices A, B and C 
 
The CAA-UK originally type certificated this aircraft. The FAA validated this product 
under U.S. Type Certificate Number A41NM. Effective September 28, 2003, the

7 of 9 A41NM, Rev 5 
European Aviation Safety Agency (EASA) began oversight of this product on behalf of 
the United Kingdom. 
 
Required Equipment: 
  The basic required equipment as prescribed in the applicable Federal Aviation Regulations (see  
  "Certification Basis") must be installed in the airplane  for U.S. certification.  All of the required equipment  
  that must be installed as well as optional equipmen t installations approved by the FAA are listed in the  
  Jetstream 4100 Master Equipment List (Document No. AWR/063/JM41 as revised and approved by CAA- 
  UK).  
 
  Federal Aviation Administration (FAA) approved Airplane Flight Manual (AFM), Jetstream Series 4100  
  Flight Manual, Document No. J41.01., published in  the English language (CAA-UK approved on behalf of  
  the FAA on April 1, 1993 or later CAA-UK or  EASA approved revisions), is required. 
 
Service Information: 
Each of the documents listed below that contain a statement that it is approved by the European Aviation 
Safety Agency (EASA) - or for approvals made before September 28, 2003 - by the CAA-UK, are accepted 
by the FAA and are considered FAA approved.  These approvals pertain to the type design only.  
 
• BAE SYSTEMS Service Bulletins, except as noted below,  
• Structural repair manuals,  
• Vendor manuals referenced in BAE SYSTEMS service bulletins 
• Aircraft flight manuals, 
• Repair Instructions. 
 
Note: 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 JS4100 Maintenance Manual. 
 
 Airplane systems and equipment related and engine mandatory Certification Maintenance Requirements  
 (CMR's) are listed in the "Certification Maintenance Requirements" section in Chapter 5 of the JS4100  
 Maintenance Manual.  Material covered in this Section must not be changed without FAA approval. 
 
 
Available Documents:  
 -Airplane Flight Manual, Doc. No. J41.01. 
 -Manufacturers Operations Manual, Doc. No. SA4.4100/MOM/- 
 -Jetstream 4100 Maintenance Review Board (MRB) report, Doc No.J4100/MRB/1 
 -JS4100 Manufacturers Maintenance Manual, Doc No. SA4.4100/AMM/- 
 -Structural Repair Manual, Doc No. SA4.4100/SRM/400 
 -Wiring Diagrams Manual, Doc No. SA4.4100/WM/- 
 -Illustrated Parts Catalogue, Doc No. SA4.4100/IPC/- 
 -Weight and Balance Manual, Doc No. SA4.4100/WBM/- 
 -Master Minimum Equipment List, Doc No. MMEL-J41-01 
 -Service Bulletins CAA approved by the authority of CAA-UK authorization Number CAA JA02034 JAR 
  21 DOA  granted to Jetstream Aircraft Ltd. by CAA-UK 
 -Variant Build Standard, Doc No. JS-4100/VBS XXX/X

A41NM, Rev 5 8 of 9 
 
NOTE 1. Weight and Balance:  
 a. A current Weight and Balance Report, including lis t of equipment included in the certificated empty  
  weight, and loading instructions must be in each  aircraft at the time of original airworthiness  
  certification and at all times thereafter except in the case of an operator having an FAA approved  
  loading system for weight and balance control.  Weight and Bala nce Manual SA4.4100/WBM/-  
  contains all the loading information required fo r each aircraft in its delivery configuration.  
 b. The airplane must be loaded in accordance with limitations in Chapter 2 of the AFM and the CG must  
  remain within the speci fied limits at all times. 
 c. The airplane empty weight and correspondi ng center of gravity location must include:  
   Total engine and gearbox oil:  24.50lb at Sta 263.70 in. 
   Total hydraulic fluid:  45.64 lb at Sta 335.60 in. 
   Unusable fuel (32. 60 lb) listed as follows: 
 
   Unusable Fluid U.S. Gallons  Pounds  Moment Arm (inches ) 
   Drainable:  
   Left Wing 2.28 15.18  337.63  
   Right Wing 2.28 15.18  337.63  
 
   Trapped Fuel: 
   Tanks and fuel lines 0.34   2.25  337.63  
   Total unusable fuel 4.90 32.60  337.63  
 
NOTE 2. All placards specified in the airplane Maintenan ce Manual must be installed in the appropriate locations. 
 
NOTE 3. Mandatory structural inspections, inspection times , and retirement times for structural parts and for  
 components are listed in the "Airworthiness Limitations" section in Chapter 5 of the JS4100 Maintenance  
 Manual, Doc. No. SA4.4100/AMM/-.  Material covered in this Section of the Maintenance Manual must not  
 be changed without FAA approval. 
 
NOTE 4. Mandatory Certification Mainte nance Requirements (CMR's) for airplane systems and equipment are listed  
 in the certification Maintenance Requirements" section in Chapter 5 of the JS4100 Maintenance Manual,  
 Doc. No. SA4.4100/AMM/-.  Material covered in this Section must not be changed without FAA approval. 
 
NOTE 5. Mandatory engine Certification Maintenance Re quirements (CMR's) are listed in the "Certification  
 Maintenance Requirements" section in Chapter 5 of the Jetstream Model 4100 Maintenance Manual, Doc.  
 No. SA4.4100/AMM/-.   Material covered in this Section must not be changed without FAA approval.. 
NOTE 6. The CMR's are also included in an appendix to the Maintenance Review Board Document No.  
 J4100/MRB/1. 
  
NOTE 7. The Jetstream Model 4101 has been  granted U.S. Type Certification approval by the FAA and is a variant 
  of the Jetstream Series 4100 airplane approved by the Civil Aviation Authority of the United Kingdom.   
 The  minimum acceptable configuration of the Jetstream Model 4101 is defined in Jetstream Aircraft  
 Limited Document No. JS-4100/TBS.FAA/- which is titled "Jetstream Model  4101 Type Build Standard  
 for Type Acceptance in the United States". 
 
NOTE 8. Installation of the appropriate amendment in the Airplane Flight Manual (AFM) allows published airplane  
 performance to be based on utilization of ATTCS power for compliance with the approach climb  
 performance requirements in § 25.121(d) of the Federal Aviation Regulations. 
 
NOTE 9. Airplane performance base on us e of CPR power for take-off and enroute conditions after failure of one 
 engine will be published in an applicable Amendment to the Airplane Flight Manual. 
 
NOTE 10. The following BAE Systems m odifications are FAA and CAA approved and satisfy FARs §25.785 (a)  
 and §25.562(c)(5) via compliance with FAA Special Condition number 25-165-SC. 
JK 42997 (Service BulletinJ41-25-082):  Installs an inflatable lapbelt mounted Airbag for each front 
row occupant, designed to minimize the loads on the passenger from impact with the forward passenger 
cabin bulkhead or other adjacent structure. 
JK 412006 (Service bulletin J41-25-081):  Installs improved head pads on the bulkhead. 
42967 (Service BulletinJ41-25-075):  Compliance with Front Row Passenger Head Impact 
Requirements.

9 of 9 A41NM, Rev 5 
Part 1:  Compliance may be achieved by the accomplishment of service bulletins introducing 
shoulder harnesses or seatbelt airbags, or through use of certain corporate seating layouts which 
give adequate clearance from the forward bulkhead/partition.  If none of these are embodied part 2 
must be carried out. 
Part 2:  The seat belts on the front single and front double seats are removed.  Antimacassars (seat 
headrest covers) with “Do Not Occupy” labels are introduced to the front single and front seats. 
Part 3:  If part 2 is accomplished and Service Bulletins, J41-25-064, J41-25-072, J41-25-074 or 
J41-25-076 are subsequently embodied, Part 3 should be used to remove the changes introduced by 
Part 2. 
 
.....END.....
```

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- [AD 2004-14-03](https://openairdocs.org/ad/2004-14-03): Ailerons · BAE Systems Jetstream Model 4101. Effective Aug 13, 2004
- [AD 2004-13-07](https://openairdocs.org/ad/2004-13-07): Main landing gear (MLG) · BAE Systems Jetstream Model 4101. Effective Aug 3, 2004
- [AD 2004-09-18](https://openairdocs.org/ad/2004-09-18): Seat rails · BAE Systems Jetstream Model 4101. Effective Jun 9, 2004
- [AD 2004-08-11](https://openairdocs.org/ad/2004-08-11): Nose landing gear (NLG) · BAE Systems Jetstream Model 4101. Effective May 26, 2004
- [AD 2004-06-17](https://openairdocs.org/ad/2004-06-17): Horizontal and vertical stabilizer · BAE Systems Jetstream Model 4101. Effective May 4, 2004
- [AD 2004-03-04](https://openairdocs.org/ad/2004-03-04): Nose landing gear (NLG) · BAE Systems Jetstream Model 4101. Effective Mar 15, 2004
- [AD 2003-15-04](https://openairdocs.org/ad/2003-15-04): Drive Trunnion Pins for the Main Landing Gear (MLG) Doors · BAE Systems Jetstream Model 4101. Effective Sep 2, 2003
- [AD 2002-12-01](https://openairdocs.org/ad/2002-12-01): Shortening Mechanism of the Nose Landing Gear · BAE Systems Jetstream Model 4101. Effective Jul 16, 2002
- [AD 2001-03-12](https://openairdocs.org/ad/2001-03-12): Elevator Cable Tension Regulators · BAE Systems Jetstream Model 4101. Effective Mar 28, 2001
- [AD 2001-01-08](https://openairdocs.org/ad/2001-01-08): Hydraulic Hand Pump · BAE Systems Jetstream Model 4101. Effective Feb 22, 2001
- [AD 2000-26-08](https://openairdocs.org/ad/2000-26-08): Structural Integrity · BAE Systems Jetstream Model 4101. Effective Feb 7, 2001
- [AD 2000-22-16](https://openairdocs.org/ad/2000-22-16): Rudder Pedals · BAE Systems Jetstream Model 4101. Effective Dec 13, 2000
- [AD 2000-22-09](https://openairdocs.org/ad/2000-22-09): Main Landing Gear · BAE Systems Jetstream Model 4101. Effective Dec 11, 2000
- [AD 2000-02-21](https://openairdocs.org/ad/2000-02-21): Instrument Panel · BAE Systems Jetstream Model 4101. Effective Mar 9, 2000
- [AD 2000-02-05](https://openairdocs.org/ad/2000-02-05): Diaphragm Support Structures · BAE Systems Jetstream Model 4101. Effective Mar 2, 2000
- [AD 99-25-06](https://openairdocs.org/ad/99-25-06): Inspect Main Baggage Bay Door · BAE Systems Jetstream Model 4101. Effective Jan 12, 2000
- [AD 99-21-12](https://openairdocs.org/ad/99-21-12): Fuel Standby Pump Cable Assembly and Conduit Pipes · BAE Systems Jetstream Model 4101. Effective Nov 12, 1999
- [AD 99-10-04](https://openairdocs.org/ad/99-10-04): Pulley Assembly of Elevator and Rudder Control Cables · BAE Systems Jetstream Model 4101. Effective Jun 9, 1999
- [AD 99-09-12](https://openairdocs.org/ad/99-09-12): Inspect Flap Trailing Edge · BAE Systems Jetstream Model 4101. Effective Jun 1, 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 98-26-15](https://openairdocs.org/ad/98-26-15): Inspect Passenger Door Structural Support · BAE Systems Jetstream Model 4101. Effective Jan 25, 1999
- [AD 98-21-03](https://openairdocs.org/ad/98-21-03): Main Baggage Compartment Load Limitation Labels · BAE Systems Jetstream Model 4101. Effective Nov 10, 1998
- [AD 98-20-09](https://openairdocs.org/ad/98-20-09): Main Entrance Door · BAE Systems Jetstream Model 4101. Effective Oct 27, 1998
- [AD 98-20-07](https://openairdocs.org/ad/98-20-07): Hose Assemblies · BAE Systems Jetstream Model 4101. Effective Oct 26, 1998
- [AD 98-18-18](https://openairdocs.org/ad/98-18-18): NLG Uplock System Attach Points · BAE Systems Jetstream Model 4101. Effective Oct 8, 1998
- [AD 98-13-38](https://openairdocs.org/ad/98-13-38): Fire Extinguisher Exhaust Port · BAE Systems Jetstream Model 4101. Effective Jul 30, 1998

All 110: https://openairdocs.org/tcds/A41NM/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [BAE Systems JETSTREAM MODEL 4101](https://openairdocs.org/model/bae-systems-jetstream-model-4101): 0 aircraft (registry code 3940400)

## STCs approved under this data sheet (25)

- [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 ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems
- [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc.
- [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc.
- [STC ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited
- [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 ST02479AK](https://openairdocs.org/stc/ST02479AK): ST02479AK. ADS-B Technologies, LLC
- [STC ST03394AT](https://openairdocs.org/stc/ST03394AT): Installation of a Avionics Innovations Model DMP-100/-200 Digital Media Player (DMP). B/E Aerospace Inc
- [STC ST01984NY-D](https://openairdocs.org/stc/ST01984NY-D): Installation of Honeywell Mk VI Enhanced Ground Proximity Warning System with an Avtech Display Switching Unit.. Contact Aviation LLC
- [STC ST00673WI-D](https://openairdocs.org/stc/ST00673WI-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 ST02781CH](https://openairdocs.org/stc/ST02781CH): Install interior seating reconfiguration. Aerodynamics Inc
- [STC ST02540AT-D](https://openairdocs.org/stc/ST02540AT-D): Installation of replacement fuel tank sealant system. FFC Manufacturing
- [STC ST02428CH](https://openairdocs.org/stc/ST02428CH): Install replacement seat cushions on B/E Aerospace single seat 87069031 and double seat 87070032.. Aerodynamics Inc
- [STC ST01142WI-D](https://openairdocs.org/stc/ST01142WI-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-94D Mode S Transponder System installation with CTL-92E control head.. Rockwell Collins Inc
- [STC ST01866LA](https://openairdocs.org/stc/ST01866LA): Installation of AmSafe Inflatable Restraint System on front row passenger seats of the Jetstream 4101.. AMSAFE Inc.
- [STC ST01307WI-D](https://openairdocs.org/stc/ST01307WI-D): Modification of a Collins TVI-920/TVI-920D Vertical Speed/TCAS Indicator installation. Rockwell Collins Inc
- [STC ST03064AT](https://openairdocs.org/stc/ST03064AT): Installation of a Honeywell MK VI Enhanced Ground Proximity Warning System (EGPWS).. Chippewa Aerospace, Inc.
- [STC ST01617NY](https://openairdocs.org/stc/ST01617NY): Installation provision Delta Engineering sensor, bracket and wire harnesses for flight data recorder update per Delta Engineering Data List 0149-05128-2048 dtd 12/18/2002.. Delta Engineering
- [STC ST01263NY](https://openairdocs.org/stc/ST01263NY): Installation of Autotronics Smoke Detection System with Pacific Scientific Fire Suppressing System (provisions only) as per Phase 1 and 2, 3, 4, and 5 'Provisions' of ACS Modification Data Summary Report #C76100.. Aero Consulting Services Ltd
- [STC SP00922CH](https://openairdocs.org/stc/SP00922CH): Installation of various SMR Technologies electrical propeller de-icer models. (RHFR34C6( ) 53/L106FA-0) (HC-B4T N-5ML/LT10574). SMR Technologies
- [STC ST01086LA](https://openairdocs.org/stc/ST01086LA): Installation of smoke detection and fire suppression systems for conversion of Class "D" cargo compartments to class "C".. Aerocon Engineering Co.
- [STC ST01229AT](https://openairdocs.org/stc/ST01229AT): Installation of a Global Wulfsberg GNS-XLS Flight Management System.. Aircraft Engineering & Installation Services Inc
- [STC ST01230AT](https://openairdocs.org/stc/ST01230AT): Installation of a Global Wulfsberg Airborne Flight Information System.. Aircraft Engineering & Installation Services Inc
- [STC ST432CH](https://openairdocs.org/stc/ST432CH): Install corporate interior.. Gulfstream Aerospace Corporation
- [STC ST277CH](https://openairdocs.org/stc/ST277CH): Installation of landing gear. Aviation Technologies Group

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