# TCDS A49EU: BAE Systems (Operations) Limited

- Type: Type certificate data sheet
- Status: Current
- Holder: BAE Systems (Operations) Limited
- Revision: 19
- Revised: April 23, 2018
- Product: Aircraft, Large Airplane
- Certification basis: Part 21, Part 25, Part 27, Part 36
- Registered aircraft: 25, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/f3/99/f39935491b4b4f19cdd7d2753c5f4742409fe1a3cdfc325b2db966af5da8c0c0
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BF1202CF2015828A8625827900539C5F.0001
- Page: https://openairdocs.org/tcds/A49EU

## Models (6)

As the data sheet lists them.

- Avro 146-RJ85A
- BAe 146-300A
- BAe 146-100A
- Avro 146-RJ70A
- Avro 146-RJ100A
- BAe 146-200A

## What the data sheet says

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

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 
Rev No. 18 18 18 18 18 18 18 18 18 19 19 18 18 
Page No. 14 15 16 17 18 19 20 21 22 23 24 25  
Rev No. 18 18 18 18 18 19 19 18 18 18 18 18  
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A49EU 
Revision 19 
BAE SYSTEMS (Operations) Limited  
BAe 146-Series         - 100* 
-200* 
-300* 
Avro 146-RJ Series      70* 
85* 
100*  
*See Note 19 
April 23, 2018 
 
TYPE CERTIFICATE DATA SHEET NO. A49EU 
 
This data sheet which is part of Type Certificate No. A49EU 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 2WR 
  
  
  
 
I.  Model BAe 146-100A (Transport Category) Approved June 13,  1983 
 
Engines 4 Avco Lycoming Model ALF 502 R-3 Turbine engines 
 or 
 4 Avco Lycoming Model ALF 502 R-3A Turbine engines (See NOTE 7) 
 or 
 4 Avco Lycoming Model ALF 502 R-5 Turbine engines (See NOTE 7) 
 
Fuel See Airplane Flight Manual for approved fuels and additives. 
 
Engine Limits Model ALF 502 R-3 engine 
(Standard day 
Sea Level Conditions) Rating Thrust   Engine    Engine  Turbine Gas 
    lbs.     N1      N2  Temperature * 
  _____ %    (RPM)  %    (RPM) °C      (°F) 
 Takeoff 6700 96.0 (7300)  98.2 (19640) 882  (1620) 
 (5 minutes) 
 Max Continuous 6300 96.0 (7300)  96.9 (19380) 857  (1574) 
 Model ALF 502 R-5 ALF 502 R-3A engines (See NOTE 9) 
 Rating Thrust Engine  Engine  Turbine Gas 
    lbs.    N1     N2  Temperature* 
  _____ % (RPM)  % (RPM)    °C      (°F) 
 Takeoff 6970 96.7 (7350)  98.2 (19640) 882 (1620) 
 (5 minutes) 
 Max. Continuous 6550 96.7 (7350)  96.9 (19380) 857 (1574) 
 *See Airplane Flight Manual for additional N2 speed, start and relight limits.

A49EU, Revision 19 2 
 
I.  Model BAe 146-100A (Transport Category) Approved June 13,  1983  (continued) 
 
Airspeed Limits MMO  (Maximum Operating) 0.70  0.73 with BAe 
     kts. (IAS) Mod HCM40241C 
 VMO   (Maximum Operating to 8000 ft) 250 
   (8,000 to 22,950 ft.)  300 
 VA      (Maneuvering): Flaps Retracted 205 
        Flaps 18° 165 
 VFE     (Flap Speeds): 
   Flaps Deflected 
   Degrees 
 Enroute/Hold    0 VMO 
 T.O./ Approach  18 200 
 T.O./Approach  24 170 
 T.O.   30 160 
 Landing  33 140  prior to embodiment of BAe  
      Modifications HCM00020P and U. 
      145 post BAe Modifications  
      HCM00020P and U. 
 VLO   (Landing Gear Operation) 
   Operation   205 
   Extended    205 
 VLE   (Landing Gear) 
   Extended    205 
 VMC  (Minimum Control Speed) 
  VMCA       95 
  VMCG (up to  65,000 lbs takeoff weight)    87 
              (above 65,000 lbs takeoff weight)     84 
 
C. G. Range  (See Note 8) Landing Gear retraction moment - 8,916 lb. in. (Nose down) 
 Maximum Taxi Weight 76500 lb. 
 FORWARD AFT 
GROSS 
WEIGHT 
LBS 
 
Takeoff and 
Landing 
 
 
Enroute 
 
Takeoff and 
Landing 
 
 
Enroute 
76000   43.5 SMC 
(Arm +0.78 ft.) 
44.5% SMC 
(Arm +0.88 ft.) 
76000  
    to 
70000 
 
28.1% SMC 
 
 
All 
Linear variation 
between 43.5% 
and 44% SMC 
Linear variation 
between 44.5% 
and 45% SMC 
70000  
    to 
66000 
(Arm  -0.70 ft.) weights 
27% SMC 
 
44% SMC 
 
45% SMC 
66000  
    to 
47000 
 
28.0% SMC 
 
 
(Arm 
(Arm  
+0.83 ft.) 
(Arm  
+0.92 ft.) 
47000  
    to 
44000 
(Arm  
-0.71 ft.) 
-0.81 ft.) Linear variation 
between 44% 
and 42.0% SMC 
Linear variation 
between 45% 
and  43%

A49EU, Revision 19 3 
I.  Model BAe 146-100A (Transport Category) Approved June 13,  1983  (continued) 
 
C.G. Range (cont’d) Maximum taxi weight 82,750 lb. 
 This is achieved by the fitment of one of the following: 
  i) Modification HCM 60015Q. 
  ii) Modifications HCM 30071A and HCM 40225B or E (Steel brakes). 
  iii) Modifications HCM 30071A and HCM 40225G (carbon brakes). 
  iv) Modifications HCM 40046L and HCM 40225D (low pressure tires, wheels  
   and steel brakes). 
  v) Modifications HCM 40046L and HCM 40225F (low pressure tires, wheels  
   and carbon brakes). 
 
 Maximum Taxi Weight with BAe Modifications HCM 30071A and HCM 40225B or 
 HCM 40255G; HCM 40046L and HCM 40255D 
 
 FORWARD AFT  
Gross 
Weight 
lbs. 
 
Takeoff and 
Landing 
 
Enroute 
 
Takeoff and 
Landing 
 
Enroute 
Gross 
Weight  
lbs. 
82250   40.4% SMC 
(Arm +0.48 ft.) 
40.4% SMC 
(Arm +0.48 ft) 
82250 
 28.1% SMC  Linear variation 
between 40.4% 
and 40.9% SMC 
Linear variation 
between 40.4% and 
40.9% SMC 
82250 
to 
82000 
to (Arm  
-0.70 ft.) 
All weights  Linear variation 
between 40.9% 
and 44% SMC 
Linear variation 
between 40.9% and 
42% SMC 
82000 
to  
81350 
66000  27% SMC  Linear variation 
between 42% and 
45% SMC 
81350 
    to 
74000 
66000 
 
to 
28.0% SMC (Arm  
-0.81 ft.) 
44% SMC  
(Arm +0.83 ft) 
45% SMC 
(Arm +0.92 ft) 
74000 
    to 
47000 
44000 (Arm  
-0.71 ft.) 
 Linear variation 
between 44% and 
42.0% SMC 
Linear variation 
between 45%  
and 43% SMC 
47000 
    to 
44000 
 
 Maximum taxi weight 84,500 lb with BAe Modification HCM 00020U 
Gross 
Weight 
lbs. 
 
Takeoff and 
Landing 
 
Enroute 
 
Takeoff and 
Landing 
 
Enroute 
Gross 
Weight 
lbs 
84000   43.0% SMC 
(Arm +0.73 ft.) 
44.0% SMC 
(Arm +0.83 ft) 
84000 
 All Weights 
28.0% SMC 
(Arm -0.71 ft.) 
All Weights 
27.0% SMC 
(Arm -0.81 ft.) 
Linear variation 
between 43.0% 
and 44.0% SMC 
Linear variation 
between 44.0% and 
45.0% SMC 
84000 
to  
77500 
   44.0% SMC 
(Arm +0.83 ft) 
45.0% SMC 
(Arm +0.92 ft.) 
77500  
to 47000 
   Linear variation 
between 44.0% 
and 42.0% SMC 
Linear variation 
between 45.0% and 
43.0% SMC 
47000 
to  
44000 
 
Maximum Weights Maximum Taxi Weight 76500 lb 
(See NOTE 8)    lbs kg 
 Taxi   76,500 34,700 
 Takeoff Weight  76,000 34,473 
 Landing Weight  72,350 32,817 
 Zero Fuel Weight  65,000 29,483

A49EU, Revision 19 4 
I.  Model BAe 146-100A (Transport Category) Approved June 13,  1983  (continued) 
 
Maximum Weights (cont’d) Maximum Taxi Weight 82,750 lb 
    lbs kg 
 Taxi   82,750 37,535 
 Takeoff Weight  82,250 37,308 
 Landing Weight  72,350 32,817 
 Zero Fuel Weight  66,000 29,937 
 
 Maximum Taxi Weight 84,500 lb 
 Taxi   84,500 38,328 
 Takeoff Weight  84,000 38,101 
 Landing Weight  77,500 35,153 
 Zero Fuel Weight  68,500 31,070 
 
Maximum Baggage Forward Hold  2580 lbs (Arm -12.7 ft.) 
 Rear Hold  2420 lbs (Arm +11.78 ft.) 
 The maximum floor loading in the baggage compartment is 75 lbs./sq. ft. 
 
Control Surface Movements The specific procedures for rigging each of the aircraft movable surfaces are defined in  
 the documents listed below.  Correct application of these procedures will ensure 
 movement and travel of each surface is as required. 
  HC271H0001 Aileron Rigging 
  HC272H0001 Rudder Rigging 
  HC273H0001 Elevator Rigging 
  HC275H0001 Flap Rigging 
  HC276H0001 Airbrake and Lift Spoiler Rigging 
 
Maximum Passengers 94 maximum, in accordance with approved only setting configuration. 
 BAe modification HCM 60014M provides a 76 seat layout that complies with the 
 Type Certificate Standard.  See drawing HC250H0154.   
 
Engine Oil Capacity Four oil tanks each 3.02 U.S. gallons capacity.  Moment arm - 8.5 ft. 
 See Airplane Flight Manual for Approved Oils. 
 
C.G. Datum Fuselage station AX 448.13 inches.  This is 4 feet forward of the reference point which 
 is indicated by two plates at the rear end of the landing wheel well.  
 
Other Operating Limitations Aircraft shall be operated in compliance with the operating limitations specified in the  
EASA Approved Flight Manual (AFM) Document No. BAE 5.1 dated August 15, 2007 
or later approved revisions.  AFM  BAE 5.1 supersedes CAA Approved Flight Manual 
Document No. BAe 3.3 dated June 13, 1983, or later approved revisions.  
 
 When fitted with BAe modifications HCM 00209A, HCM 40046A, HCM 40046L,  
 together with HCM 40046Z or HCM 40046B, HCM 40046D and HCM 40046M, and 
 operated in accordance with the Approved Flight Manual, Document No. BAe 5. 1 
 Appendix No. 29 the aircraft can be operated on unpaved runways up to a maximum  
 takeoff of 76000 lbs.  
 
 When fitted with BAe modifications HCM 60014G, HCM 60014H, HCM 60014J,  
 HCM 60014Q, and HCM 60014R, the aircraft may be operated in a mixed passenger/ 
 cargo layout.  See BAe report number HTD.R.461-00.DC0097, Issue 3.

A49EU, Revision 19 5 
II.  Model BAe 146 200A (Transport Category) Approved June 13,  1983 
      (Same as 100A except increased gross weight and passenger seating. ) 
 
Engines  4 Avco Lycoming Model ALF 502 R-3 Turbine Engines 
 or 4 Avco Lycoming Model ALF 502 R-3A Turbine Engines (See NOTE 7) 
 or 4 Avco Lycoming Model ALF 502 R-5 Turbine Engines (See NOTE 7) 
 
Fuel See Airplane Flight Manual for approved fuels and additives. 
 
Engine Limits Model ALF 502 R-3 engine 
(Standard Day) Rating  Thrust  Engine  Engine  Turbine Gas 
   lbs. N1  N2*  Temperature* 
    % (RPM)  %(RPM)  °C     (°F)    
 Takeoff 6700 96.0 (7300)  98.2 (19640) 882 (1620) 
 (5 minutes) 
 Max. Continuous 6300 96.0 (7300)  96.1 (19380) 857 (1574) 
 
 Model ALF 502 R-3A and ALF 502 R-5 engines (See NOTE 9) 
 Rating  Thrust  Engine   Engine  Turbine Gas 
   lbs.    N1     N2*  Temperature* 
     % (RPM)  % (RPM)  °C      (°F) 
 Takeoff 6970 96.7 (7350)  98.2 (19640) 882   (1620) 
 (5 minutes)  
 Max. Continuous 6550 96.7 (7350)  96.9 (19380) 857 (1574) 
 *See Airplane Flight Manual for additional N2 speed, start and relight limits  
 
Airspeed Limits MMO  (Maximum Operating)  0.70 0.73 with BAe 
        Mod HCM40241D 
 
      kts. (IAS) 
 VMO  (Maximum Operating to 8000 ft)  250 
  (8000 to 23,900 ft)   295 
 VA    (Maneuvering) 
  Flaps Retracted   225 with BAe Mod. HCM00021B 
      230 with BAe Mod. HCM00021U 
  Flaps 18°    175 
 
 VFE  (Flap Speeds) 
    Flaps Deflected 
       Degrees 
 Enroute/Hold          0  VMO 
 T.O./Approach              18  205 prior to embodiment of BAe   
             modifications HCM 00021M and U. 
      210 post BAe modifications  
              HCM 00021M and U.

A49EU, Revision 19 6 
II.  Model BAe 146 200A (Transport Category) Approved June 13,  1983   (continued)  
  
 T.O./Approach/Climb       24  180 
 Approach          30  170 
 Landing        33  145 
 VLO  (Landing Gear Operation) 
  Operation    205 
  Extended    205 
 VLE  (Landing Gear) 
  Extended    205 
 VMC  (Minimum Control Speed)  
  VMCA      95 
  VMCG  (up to 65,000 lbs takeoff weight)   86 
            (above 65,000 lbs takeoff weight)    82 
 
C.G. Range Landing gear retraction moment - 8,916 lb in (Nose down) 
(See NOTE 8) 
 Maximum Taxi Weight 90,000 lbs. 
  
 FORWARD AFT 
Gross 
Weight 
lbs 
 
Takeoff and 
Landing 
 
 
Enroute 
 
Takeoff and 
Landing 
 
 
Enroute 
89500   44.0% SMC 
(Arm +0.83 ft) 
45.0% SMC 
(Arm +0.92 ft.) 
89500  
to  
85000 
 
28.1% SMC 
 Linear variation 
between 44% 
and 46% SMC 
Linear variation 
between 45% 
and 47% SMC 
85000 
to 
71000 
(Arm -0.70 ft.)  
 
All Weights 
 
 
46% SMC 
 
 
47% SMC 
71000 
to  
48500 
 
 
28.0% SMC 
27% SMC 
 
(Arm -0.81 ft.) 
 
(Arm +1.02 ft.) 
 
(Arm +1.12 ft.) 
48500 
to  
46000 
 
(Arm -0.71 ft) 
 Linear variation 
between 46% 
and 44% SMC 
Linear variation 
between 47% 
and 45.2% 
SMC 
 
 Maximum taxi weight 90,000 lbs. with Bae modifications HCM 00296A & HCM 45018A 
 FORWARD AFT 
Gross Weight 
lb 
Takeoff and 
Landing 
Enroute Takeoff and 
Landing 
Enroute 
89500 28.0% SMC 
(Arm -0.71 ft) 
26.0% SMC 
(Arm -0.90 ft.) 
42.5% SMC 
(Arm +0.70 ft.) 
44.0% SMC 
(Arm +0.81 ft.) 
89500  
to 
78000 
 
Linear 
variation 
 
Linear 
variation  
Linear variation 
between 42.5% 
and 47.0% SMC 
Linear variation 
between 44.0% 
and 48.0% SMC 
78000 
to 
76250 
between 
28.0% and 
27.0% SMC 
between 
26.0% and 
25.0% SMC 
  
76250 
to 
72000 
   
47.0% SMC 
 
48.0% SMC 
72000 
to 
48500 
 
27.0% SMC 
 
 
25.0% SMC 
(Arm +1.12 ft.) (Arm +1.22 ft.) 
48500 
to 
46000 
(Arm -0.80 ft.) (Arm -1.00 ft.) Linear variation 
between 47.0% 
and 45.5% SMC 
Linear variation 
between 48.0% 
and 46.5% SMC

A49EU, Revision 19 7 
II.  Model BAe 146 200A (Transport Category) Approved June 13,  1983   (continued) 
  
 Maximum taxi weight 93,500 lb with BAe Modification HCM00021U 
 FORWARD AFT 
Gross 
Weight 
lbs 
 
Takeoff and 
Landing 
 
 
Enroute 
 
Takeoff and 
Landing 
 
 
Enroute 
93000 28.0% SMC 
(Arm -0.71 ft.) 
26.0% SMC 
(Arm -0.90 ft.) 
42.0% SMC 
(Arm +0.46 ft.) 
42.0% SMC 
(Arm +0.64 ft.) 
93000 
to  
86000 
 
86000 
to 
84600 
 
84600 
to 
73500 
 
73500 
to  
48500 
 
48500 
to 
46000 
 
 
Linear variation 
between 28.0% 
and 27.0% SMC 
 
 
 
 
 
 
 
 
 
27.0% SMC 
(Arm 0.80 ft.) 
 
 
Linear variation 
between 26.0% 
and 25.0% SMC 
 
 
 
 
 
 
 
 
 
25.0% SMC 
(Arm -1.00 ft.) 
Linear variation 
between 42.0% 
and 47.0% SMC 
 
 
47.0% SMC 
(Arm -1.12 ft.) 
 
 
 
 
 
 
 
_____________ 
Linear variation 
between 47.0% 
and 45.5% SMC 
Linear variation 
between 42.0% 
and 48.0% SMC 
 
 
 
 
_____________ 
48.0% SMC 
(Arm +1.22 ft.) 
 
 
 
 
_____________ 
Linear variation 
between 48.0% 
and 46.5% SMC 
 
 
Maximum Weights Maximum Taxi Weight 90,000 lbs. 
(See NOTE 8)    lbs. kg. 
 Taxi   90,000  40,824 
 Takeoff Weight  89,500 40,597 
 Landing Weight  77,500  35,154 
 Zero Fuel Weight  71,000  32,206 
 
 Maximum Taxi Weight 93,500 lbs. 
 Taxi   93,500  42,410 
 Takeoff Weight  93,000  42,184 
 Landing Weight  81,000  36,740 
 Zero Fuel Weight  75,000   34,019 
 
Maximum Baggage Forward Hold  3350 lbs. (Arm -14.76 ft.) 
 Reverse Hold  3320 lbs. (Arm +13.68 ft.) 
 The maximum floor loading in the baggage compartment is 75 lbs./sq. ft. 
 
Control Surface Movements The specific procedures for rigging each of the aircraft moveable surfaces are 
 defined in the documents listed below.  Correct application of these procedures 
 will ensure moment and travel of each surface as required. 
  HC271H0001 Aileron Rigging 
  HC272H0001 Rudder Rigging 
  HC273H0002 Elevator Rigging 
  HC274H0001 Flap Rigging 
  HC275H0001 Airbrake and Lift Spoiler Rigging 
 
Engine Oil Capacity Four oil tanks each 3.02 U.S. gallons capacity.  Moment arm  -  8.5 ft. 
 See Airplane Flight Manual for Approved Oils.

A49EU, Revision 19 8 
 
II.  Model BAe 146 200A (Transport Category) Approved June 13,  1983   (continued) 
 
C.G. Datum Fuselage station AX491.81 inches.  This is 4 feet forward of the reference point which  
 is indicated by two plates at the rear end of the landing wheel well pressure floor.  
 
Maximum Passengers 108 Maximum.  Compliance with FAR 25.803 has been  shown by demonstration and 
 analysis with an aircraft having an interior configuration in accordance with British  
 Aerospace document no. HAW.R.460.AW.0506 or any approved seating configuration. 
  
Other Operating Limitations Aircraft shall be operated in compliance with the operating limitations specified in the 
 EASA Approved Flight Manual Document No. BAE 5.1.dated August 15, 2007 or later 
 approved revisions.  AFM BAE 5.1 Supersedes CAA approved Flight Manual 
Document  
No. BAe  3.6 dated June 13, 1983 or later approved revisions. 
 
 
III.  Model BAe 146 300A (Transport Category) Approved October 28,  1988 
       (Same as  100A except increased gross weight and passenger seating)  
 
Engines 4 Avco Lycoming Model ALF R-3A Turbine Engines (See NOTE 7) 
 or 
 4 Avco Lycoming Model ALF 502 R-5 Turbine Engines (See NOTE 7) 
  
Fuel See Airplane Flight Manual for approved fuels and additives. 
 
Engine Limits MODEL ALF 502 R-3A and ALF 502 R-5 engines (See NOTE 9) 
     Engine   Engine  Turbine Gas 
   Thrust     N1      N2  Temperature* 
 Rating    lbs. % (RPM)  % (RPM)        °C   (°F) 
 Takeoff 6970 96.7 (7350)  98.2 (19640) 882 (1620) 
 (5 minutes) 
 Max. Continuous 6550 96.7 (7350)  96.9 (19380) 857 (1574) 
 * See Airplane Flight Manual for additional N2 speed, start and relight limits.  
 
Airspeed Limits MMO  (Maximum Operating)  0.73 
 
      Kts. (IAS) 
 VMO  (Maximum Operating to 8000 ft.)  250 
  (8000 to 23,900 ft)   295 305 with BAe Mod.  
       HCM36049A 
 VA    (Maneuvering) 
  Flaps Retracted   235 
  Flaps 18°    180

A49EU, Revision 19 9 
III.  Model BAe 146 300A (Transport Category) Approved October 28,  1988   (continued) 
  
 VFE   (Flap Speeds) 
   Flaps Deflected Degrees 
 Enroute/Hold    0 VMO 
 T.O./ Approach  18 210 
 T.O./Approach/Climb 24 180 
 Approach  30 170 
 Landing  33 150 
  
 VLO  (Landing Gear Operation) 
  Operation   205 
  Extended   205 
 VLE  (Landing Gear) 
  Extended   205 
 VMC  (Minimum Control Speed)  
  VMCA     97 
  VMCG     82 
 
C.G. Range Landing Gear retraction moment - 8,916 lb. in. (Nose down) 
(See NOTE 8) 
 Maximum Taxi Weight 95,500 lbs. 
 FORWARD AFT 
Gross Weight 
lbs 
Takeoff and 
Landing 
 
Enroute 
Takeoff and 
Landing 
 
Enroute 
95000 24.5% SMC 
(Arm -1.05 ft) 
22.5% SMC 
(Arm -1.23 ft.) 
44.0% SMC 
(Arm 0.81 ft.) 
45.6% SMC 
(Arm 0.99 ft.) 
95000 
to 
83000 
 
 
Linear   
 
 
Linear  
Linear  
variation 
between 
Linear 
variation 
between  
83000 
to 
77500 
variation 
between 
24.5% and 
22.5% SMC 
variation 
between 
22.5% and 
20.5% SMC 
44.6% and 
48.5% SMC 
45.6% and 
50.0% SMC 
77500 
to  
58000 
 
 
Linear 
variation 
 
 
 
20.5% SMC 
48.5% SMC 
(Arm +1.24 ft.) 
50.0% SMC 
(Arm +1.41 ft.) 
58000 
to  
47000 
between 
22.5% and 
23.0% SMC 
(Arm -1.42 ft.) Linear  
variation 
between 48.5% 
and 44.0% SMC 
Linear 
variation 
between 50.0% 
and 45.4% 
SMC 
  
Maximum Weights Maximum Taxi Weight 95500 lb 
    lbs kg 
 Taxi   95,500   43,318 
 Takeoff Weight  95,000   43.091 
 Landing Weight  83,000  37,648 
 Zero Fuel Weight  77,500  35,153 
 
Maximum Baggage Forward Hold   4215 lbs (Arm -16.93 ft.) 
 Rear Hold  4033 lbs.(Arm +14.20 ft.) 
 The maximum floor loading in the baggage compartment is 75 lbs/sq. ft.

A49EU, Revision 19 10 
III.  Model BAe 146 300A (Transport Category) Approved October 28,  1988   (continued) 
 
Control Surface Movements The specific procedures for rigging each of the aircraft moveable surfaces are defined in  
 the documents listed below.  Correct application of these procedures will ensure  
 movement and travel of each surface is as required. 
  HC271H0001 Aileron Rigging 
  HC272H0001 Rudder Rigging 
  HC273H0567 Elevator Rigging 
  HC274H0001 Flap Rigging 
  HC275H0002  Airbrake and Lift Spoiler Rigging 
 
Engine Oil Capacity Four oil tanks each 3.02 U.S. gallons capacity.  Movement arm -8.5 ft. 
 See Airplane Flight Manual for Approved Oils. 
 
C.G. Datum Fuselage station AX 544.81 inches.  This is 4 feet forward of the reference point which 
 is indicated by two plates at the rear end of the landing wheel well pressure floor.  
 
Maximum Passengers 108 maximum.  Compliance with FAR 25.803 has been shown by demonstration and  
 analysis with an aircraft having an interior configuration in accordance with any  
 British Aerospace approved seating configuration. 
  
Other Operating Limitations Aircraft shall be operated in compliance with the operating limitations specified in the  
EASA Approved Flight Manual Document No. BAE 5.1 dated August 15, 2007 or later 
approved revisions.  AFM BAE 5.1 supersedes CAA approved Flight Manual Document 
No. BAe 3.11 dated June 1988 or later approved revisions. 
 
DATA PERTINENT TO ALL MODELS 
 
Auxiliary Power Unit 1 AiResearch GTCP 36-100 (M) or 1 AiResearch GTCP 36-150(M) or 1 Sundstrand 
 APS1000 T-62T-46C 
 
** Limits *GTCP 36-100(M) GTCP 36-150(M) APS1000 T-62T-46C 
Rated shp, maximum for Standard 
Day, Sea Level conditions 45 shp 50 shp 53.5 shp 
Shaft Speed:   
Maximum (at rated power) 100.5% (59034 RPM) 103% (60499 RPM) 108% (69286 RPM) 
Maximum Exhaust Temperature: 
Continuous Operation: 
Starting: (Up to 10 seconds) 
732oC 
974oC 
870oC 
746oC 
974oC 
870oC 
718oC 
-oC 
1032oC 
*See Note 5 
**See Airplane Flight Manual for additional limitations and Approved Oils.  
 
Minimum Crew 2 - Pilot and Co-Pilot 
Maximum Operating Altitude 30,000 ft. (See NOTE 12) 
 
Usable Fuel Capacity 
 100A 200A 300A 
Wing Tanks 
(Right & Left) 
16,240 lbs 
(Arm +0.008 ft) 
Center Tank 4,400 lbs (Arm -3.243 ft) 
Auxiliary Tanks 
(Right & Left) 
2,064 lbs 
(Arm +4.230 ft) 
  
 Fuel must be loaded symmetrically into the wing tanks. 
 The maximum allowable wing tank fuel asymmetry is 1,500 lbs. 
 See NOTE 1 for information on unusable and undrainable fuel. 
 
Standard Mean Chord (SMC) The Standard Mean Chord is 9.62 ft.  The leading edge of the Standard Mean Chord  
 is 3.405 ft. forward of the C.G. datum.

A49EU, Revision 19 11 
Leveling Means Clinometer on cabin seat rails. 
Certification Basis for the  100A & 200A  
 FAR 21.29, FAR 25, effective February 1,  1965, including Amendment 25-1 through 25-43.  In addition the  
 applicant voluntarily complied with the following later requirements. 
  
FAR Section Amdt.  FAR Section   Amdt.   
 25.305 (d) 54  25.809 (f) (iii, iv, v)   47 
 25.345 (d) 46  25.851 (a) (5)   54 
 25.351 (a) 46  25.853 (c), (d), (e)   51 
 25.365 (e)(1), (e)(2)  54  25.1103(a), (b)(2), (d), (e), (f) 46 
 25.571 45  25.1142    46 
 25.605 (a), (b) 46  25.1207(d)   46 
 25.629 (d)(1), (d)(4) (v & vi)  46  25.1305 (d)   54 
 25.697 (b) 46  25.1329 (h)   46 
 25.701 (a) 46  25.1522    46 
 25.733 (a), (b), (c) 49  25.1561 (c)   46 
 25.735 (b), (f)(2), (g) 48  25.773(b)(2)(ii)   72 
 25.793   51  25.775(e)    72 
 25.803 (c), (d) 46 
 
Certification Basis  (cont'd) Compliance with FAR 25.803 and 25.1419 has been established.  
 
  Compliance with FAR 25.801 has been established for the structure of the  
  aircraft fitted with BAe modifications HCM 00100A or HCM 00166A, plus  
  HCM 00100B for BAe 146-100A or HCM 00100C for BAe 146-200A.  Full 
  compliance will be achieved when survival equipment is installed in accordance with  
  FAR’s 25.1411 through 25.1415 and the appropriate operating equipment. 
 
  FAR 36, effective December 1,  1969, including Amendments 36-1 through 36-13. 
  SFAR 27, 27-1 through 27-4  (see NOTE 4). 
 
For the  300A In addition to the  100A and 200A certification requirements, the following later 
  requirements apply to the  300A certification: 
  FAR 25 Subpart C, Amendments 44 to 54 inclusive. 
 
  FAR Section Amdt.  FAR Section Amdt. 
  25.629  46  25.811  46 
  25.783  54  25.812  46 
  25.787  51  25.853  51 
  25.789  46  25.858  54 
  25.803  46  25.863  46 
 
  FAR Part 36 effective December 1,  1969, including Amendments 36-1 through 36-15. 
  Special Federal Aviation Regulation No. 27 effective February 1,  1974, including 
  amendments 27-1 through 27-5. 
 
For All Bae 146  Equivalent Safety 
  FAR 25.613 (a) - Design Values 
  FAR 25.615 (a) - Design Properties 
  FAR 25.773 (b)(2) - Pilot’s Window(see note 18) 
  FAR 25.1091 (e) - Foreign Object Ingestion 
 
  Exemption No. 3639 regarding FAR 25.807(c)(1) 
 
  Type Certificate No. A49EU, issued June 13,  1983. 
  Effective Date of Application for Type Certificate August 4,  1978. 
 
  The applicable later requirements for the installation of the LF507 -1H engine are 
defined 
  within FAA issue paper G-1 dated January 26,  1993 detailing: 
  FAR 25.903 (a)  Amendment 57 
  FAR 25.1091 (e)  Amendment 57

A49EU, Revision 19 12 
  FAR 25.1093 (b) (2) Amendment 57 
  FAR 25.1163 (a) (3) Amendment 57 
  FAR 25.1305 (d) (1) Amendment 54 
 
 
 
Historical Transition The United Kingdom Civil Aviation Authority originally type certificated this aircraft 
under its type certificate Number BA16. The FAA validated this product under U.S. 
Type Certificate Number A49EU.  Effective September 28, 2003, the European 
Aviation Safety Agency (EASA) began oversight of this product on behalf of the United 
Kingdom. 
 
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 of certification is made. 
 
Import Requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate 
of Airworthiness (Export C of A) signed by a representative of United Kingdom Civil 
Aviation Authority 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 Type Design approved under U.S. Type 
Certificate No. A49EU and to be in a condition for safe operation.’ 
 
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 United Kingdom Civil Aviation Authority, are accepted by the FAA and 
are considered FAA approved.  Additionally, approvals issued by BAE Systems 
(Operations) Limited under the authority of EASA approved Design Organization 
EASA.21J.047 -  or for approvals made before September 28, 2003 under the authority 
of JAA Design Organization Approval No. CAA.JA.02034 or Manufacturers CAA 
Approval Ref. DAI/1011/55 - are considered FAA approved.  These approvals pertain to 
the type design only.  
 
• BAE Systems (Operations) Limited service bulletins, except as noted below,  
• Structural repair manuals,  
• Vendor manuals referenced in BAE Systems (Operations) Limited service bulletins, 
• Aircraft flight manuals, 
• Repair Instructions. 
 
Note: Design changes that are contained in BAE Systems (Operations) Limited Service 
Bulletins and that are classified as Level 1 Major in accordance with either the 
US/United Kingdom or US/EASA Bilateral Aviation Safety Agreement Implementation 
Procedures for Airworthiness must be approved by the FAA. 
 
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 the document: 
   ADE-CES-D-460-00-0011 
 
IV.  Model AVRO 146-RJ70A (Transport Category), Approved September 3,  1993 
 
C.G. Range Maximum Taxi Weight 84,500 lbs  
Gross FORWARD AFT 
 Weight 
lbs 
Takeoff and 
Landing 
 
Enroute 
Takeoff and 
Landing 
 
Enroute 
84000   43.9% SMC 
(Arm +0.82 ft.) 
44.9% SMC 
(Arm +0.91 ft.) 
84000 
to  
 
 
 
 
Linear variation 
between 43.9% 
Linear variation 
between 44.9%

A49EU, Revision 19 13 
83500 28.1% SMC 27.0% SMC and 44.0% SMC 
(Arm +0.83 ft.) 
and 45.0% SMC 
(Arm +0.92 ft.) 
83500 
to  
47000 
 
(Arm  
- 0.70 ft.) 
 
(Arm  
- 0.81 ft.) 
44.0% SMC 
(Arm +0.83 ft.) 
45.0% SMC 
(Arm +0.92 ft.) 
47000 
to 
44000 
  Linear to 42.0% 
SMC 
(Arm +0.64 ft.) 
Linear to 43.0% 
SMC 
(Arm +0.73 ft.) 
IV.  Model AVRO 146-RJ70A (Transport Category), Approved September 3,  1993  (continued) 
 
  Maximum Taxi Weight 90,500 lbs with Bae modifications HCM00020Z or HCM40373C 
 
 FORWARD AFT 
Gross 
Weight lbs 
Takeoff and 
Landing 
Enroute Takeoff and 
Landing 
Enroute 
90000   43.0% SMC 
(Arm +0.73 ft) 
44.0% SMC 
(Arm +0.83 ft) 
90000 
to 
83500 
 
28.0% SMC 
(Arm -0.71ft) 
 
27.0% SMC 
(Arm -0.81 ft.) 
Linear variation 
between 43.0% 
and 44.0% 
SMC 
(Arm +0.83 ft) 
Linear variation 
between 44.0% 
and 45.0% SMC 
(Arm +0.92 ft.) 
83500  
to 
47000 
 
 
 
 
44.0% SMC 
(Arm +0.83 ft.) 
45.0% SMC 
(Arm +0.92 ft) 
47000 
to 
44000 
  Linear variation 
between 44.0% 
and 42.0% 
SMC 
(Arm +0.64 ft.) 
Linear variation 
between 45.0% 
and 43.0% SMC 
(Arm +0.73 ft.) 
 
    Maximum Taxi Weight 95,500 lbs with BAe modification HCM40373A 
 
Gross FORWARD AFT 
Weight Takeoff &  Takeoff &  
lbs Landing Enroute Landing Enroute 
95000   40.2% SMC 41.2% SMC 
   (Arm +0.45 ft) (Arm + 0.55 ft) 
95000   Linear variation  Linear Variation 
to   between 43.0% between 44.0% 
90000   and 44.0% SMC and 45.0% SMC 
   (Arm +0.83 ft) (Arm +0.92 ft) 
90000   Linear variation Linear variation 
to 28.0% SMC 27.0% SMC between 43.0% between 44.0% 
83500 (Arm -0.71 ft) (Arm -0.81 ft) and 44.0% SMC and 45.0% SMC 
   (Arm +0.83 ft) (Arm +0.92 ft) 
83500   44.0% SMC 45.0% SMC 
to   (Arm +0.83 ft) (Arm +0.92 ft) 
47000     
47000   Linear variation Linear variation  
to   between 44.0% between 45.0% 
44000   and 42.0% SMC and 43.0% SMC 
   (Arm +0.64 ft) (Arm +0.73 ft) 
 
Maximum Weights Maximum Taxi Weight 84,500 lbs 
     lbs  kgs 
  Taxi Weight  84,500  38,328

A49EU, Revision 19 14 
  Takeoff Weight  84,000 38,101 
  Landing Weight  83,500 37,874 
  Zero Fuel Weight  71,500 32,431 
  Zero Fuel Weight  74,500 33,792 (with Modification HCM00020X  
       or HCM40373B 
 
   
 
 
 
 
IV.  Model AVRO 146-RJ70A (Transport Category), Approved September 3,  1993  (continued) 
 
Maximum Taxi Weight 90,500 lbs. with BAe modifications HCM00020X and  
  HCM00020Z or HCM40373B and HCM40373C 
     lbs kgs 
  Taxi Weight  90,500 41,050 
  Takeoff Weight  90,000 40,823 
  Landing Weight  83,500 37,874 
  Zero Fuel Weight  74,5000 33,792 
 
  Maximum Taxi Weight 95,500 lbs. with BAe modification HCM40373A 
     lbs kgs 
  Taxi Weight  95,500 43,318 
  Takeoff Weight  95,000 43,091 
  Landing Weight  83,500 37,874 
  Zero Fuel Weight  74,500 33,792 
 
 
V.  Model AVRO 146-RJ85A (Transport Category)  Approved December 1,  1993 
 
C.G. Range Maximum Taxi Weight 93,500 lbs. 
Gross FORWARD AFT 
Weight 
lbs 
Takeoff and 
Landing 
 
Enroute 
Takeoff and 
Landing 
 
Enroute 
93000 27.8% SMC 
(Arm -0.73 ft) 
25.8% SMC 
(Arm -0.92 ft) 
44.8% SMC 
(Arm +0.90 ft) 
44.8% SMC 
(Arm +0.90 ft) 
93000 
to 
90000 
 
 
Linear variation 
between 27.8% 
 
 
Linear variation 
between 25.8% 
Linear variation 
between 44.8% 
and 47.0% SMC 
(Arm +1.12 ft) 
Linear variation 
between 44.8% 
and 47.0% SMC 
(Arm +1.12 ft) 
90000 
to 
88600 
and 27.0% SMC 
(Arm -0.81 ft) 
and 25.0% SMC 
(Arm -1.00 ft) 
 
 
 
Constant 
Linear variation 
between 47.0% 
and 48.0% SMC 
(Arm +1.21 ft.) 
88600 
to 
79000 
 
 
 
 
47.0% SMC 
(Arm +1.12 ft) 
 
 
Constant 
79000 
to 
48500 
 
 
27.0% SMC 
 
 
27.0% SMC 
 48.0% SMC 
(Arm +1.21 ft) 
48500 
to 
46000 
(Arm -0.81 ft) (Arm -1.00 ft) Linear variation 
between 47.0% 
and 45.5% SMC 
(Arm +0.97 ft) 
Linear variation 
between 48.0% 
and 46.5% SMC 
(Arm +1.07 ft)

A49EU, Revision 19 15 
 
 
 
 
 
 
 
 
 
 
 
 
 
V.  Model AVRO 146-RJ85A (Transport Category)  Approved December 1,  1993  (continued) 
 
C.G. Range Maximum Taxi Weight 93,500 lbs. with BAe modification HCM20203B, E2208 only 
  (See Note 15) 
Gross FORWARD AFT 
Weight 
lbs 
Takeoff and 
Landing 
 
Enroute 
Takeoff and 
Landing 
 
Enroute 
93000 28.0% SMC 
(Arm -0.71 ft) 
26.0% SMC 
(Arm -0.90 ft) 
42.0% SMC 
(Arm +0.64 ft) 
42.0% SMC 
(Arm +0.64 ft) 
93000 
to 
 
86000 
 
 
Linear variation 
between 28.0% 
 
 
Linear variation 
between 26.0% 
Linear variation 
between 42.0% 
and 47.0% SMC 
(Arm +1.12 ft) 
Linear variation 
between 42.0% 
and 47.0% SMC 
(Arm +1.12 ft) 
86000 
to 
 
84600 
and 27.0% SMC 
(Arm -0.81 ft) 
and 25.0% SMC 
(Arm -1.00 ft) 
 
 
 
Constant 
Linear variation 
between 47.0% 
and 48.0% SMC 
(Arm +1.21 ft.) 
84600 
to 
75000 
 
 
 
 
47.0% SMC 
(Arm +1.12 ft) 
 
 
Constant 
75000 
to 
48500 
 
Constant 
27.0% SMC 
 
Constant 
27.0% SMC 
 48.0% SMC 
(Arm +1.21 ft) 
48500 
to 
46000 
(Arm -0.81 ft) (Arm -1.00 ft) Linear variation 
between 47.0% 
and 45.5% SMC 
(Arm +0.97 ft) 
Linear variation 
between 48.0% 
and 46.5% SMC 
(Arm +1.07 ft) 
 
C.G. Range Maximum Taxi Weight 97,500 lbs with Modification HCM00021X 
 
Gross FORWARD AFT 
Weight 
lbs 
Takeoff and 
Landing 
 
Enroute 
Takeoff and 
Landing 
 
Enroute 
97000 28.0% SMC 
(Arm  -0.71 ft) 
26.0% SMC 
(Arm -0.90 ft) 
42.0% SMC 
(Arm +0.64 ft) 
42.0% SMC 
(Arm +0.64 ft) 
97000 
to 
90000 
 
 
Linear variation 
between 28.0% 
 
 
Linear variation 
between 26.0% 
Linear variation 
between 42.0% 
and 47.0% SMC 
(Arm +1.12 ft) 
Linear variation 
between 42.0% 
and 47.0% SMC 
(Arm +1.12 ft) 
90000 
to 
88600 
and 27.0% SMC 
(Arm -0.81 ft.) 
and 25.0% SMC 
(Arm -1.00 ft) 
 
 
 
Constant 
Linear variation 
between 47.0% 
and 48.0% SMC 
(Arm +1.21 ft) 
88600 
to 
79000 
  47.0% SMC 
(Arm +1.12 ft) 
 
Constant 
48.0% SMC 
79000    (Arm +1.21 ft)

A49EU, Revision 19 16 
to 
48500 
 
Constant 
 
Constant 
48500 
to 
46000 
27.0% SMC 
(Arm -0.81 ft) 
25.0% SMC 
(Arm -1.00 ft) 
Linear variation 
between 47.0% 
and 45.5% SMC 
(Arm +0.97 ft.) 
Linear variation 
between 48.0% 
and 46.5% SMC  
(Arm +1.07 ft) 
 
Maximum Weights Maximum Taxi Weight 93,500 lbs 
     lbs kgs 
  Taxi Weight  93,500 42,410 
  Takeoff Weight  93,000 42,184 
  Landing Weight  85,000  38,555 
  Zero Fuel Weight  79,000 35,833 
 
V.  Model AVRO 146-RJ85A (Transport Category)  Approved December 1,  1993  (continued) 
 
  Maximum Taxi Weight 93,500 lbs with BAe Modification HCM20203B  (see Note 15) 
  Taxi Weight  93,500 42,410 
  Takeoff Weight  93,000 42,184 
  Landing Weight  81,000 36, 740 
  Zero Fuel Weight  75,000 34,019 
 
  Maximum Taxi Weight 97,500 lbs. with Bae Modification (HCM00021X) 
  Taxi Weight  97,500 44,225 
  Takeoff Weight  97,000 43,998 
  Landing Weight  85,000  38,555 
  Zero Fuel Weight  79,000 35,833 
 
 
VI.  Model AVRO 146-RJ100A (Transport Category) Approved June 10, 1994 
 
C.G. Range Maximum Taxi Weight 98,000 lbs. 
Gross FORWARD AFT 
Weight lbs Takeoff and 
Landing 
Enroute Takeoff and 
Landing 
Enroute 
97500 23.9% SMC 
(Arm -1.11 ft) 
21.9% SMC 
(Arm -1.30 ft) 
46.2% SMC 
(Arm +1.04 ft) 
47.4% SMC 
(Arm +1.15 ft) 
97500 
to 
90000 
 
Linear variation 
between  
23.9% and 
 
 
Linear variation 
between 
Linear variation 
between 46.2% 
and 48.5% SMC 
(Arm +1.26 ft) 
Linear variation 
between 47.4% and 
50.0% SMC  
(Arm +1.41 ft) 
90000 
to 
82500 
22.5% SMC  
(Arm -1.24 ft.) 
21.9% and 
20.5% SMC 
(Arm -1.43 ft) 
 
 
Constant 
 
 
Constant 
82500 
to 
58000 
 
Linear variation 
between 
 
 
Constant 
48.5% SMC 
(Arm +1.26 ft) 
50.0% SMC 
(Arm +1.41 ft) 
58000 
to 
47000 
22.5% and 23.0% 
SMC 
(Arm -1.19 ft) 
20.5% SMC 
(Arm -1.43 ft) 
Linear variation 
between 48.5% 
and 44.0% SMC 
(Arm +0.83 ft) 
Linear variation 
between 50.0% and 
45.5% SMC 
(Arm +0.97 ft) 
 
  Maximum Taxi Weight 98,000 lbs with Bae Modification HCM60346N, E3221 Only (see Note 14) 
Gross FORWARD AFT 
Weight lbs Takeoff and 
Landing 
 
Enroute 
Takeoff and 
Landing 
 
Enroute 
97,500 24.4% SMC 
(Arm -1.06 ft) 
22.4% SMC 
(Arm -1.24 ft) 
44.0% SMC 
(Arm +0.83 ft) 
45.3% SMC 
(Arm +0.92 ft) 
97,500 
to 
86,500 
 
Linear variation 
between 24.4% 
and 22.5% SMC 
 
Linear variation 
between 
22.4% and 
Linear variation 
between 44.0% 
and 48.5% SMC 
(Arm +1.26 ft) 
Linear variation 
between 46.0% 
and 50.0% SMC 
(Arm +1.41 ft)

A49EU, Revision 19 17 
86,500 
to 
80,500 
(Arm -1.24 ft) 20.5% SMC 
(Arm -1.43 ft) 
 
 
Constant 
 
 
Constant 
80,500 
to 
58,000 
 
Linear variation 
between 
 
Constant 
20.5% SMC 
48.5% SMC 
(Arm +1.26 ft) 
50.0% SMC 
(Arm +1.41 ft) 
58,000 
to 
47,000 
22.5% and 
23.0% SMC 
( Arm -1.19 ft) 
(Arm -1.43 ft.) Linear variation 
between 48.5% 
and 44.0% SMC 
(Arm +0.83 ft.) 
Linear variation 
between 50.0% 
and 45.4% SMC 
(Arm +0.98 ft) 
 
   
 
 
 
VI.  Model AVRO 146-RJ100A (Transport Category) Approved June 10, 1994  (continued) 
 
Maximum Taxi Weight 102,000 lbs  with BAe Modification HCM01000L 
 FORWARD AFT 
Gross 
Weight lbs 
Takeoff and 
Landing 
 
Enroute 
Takeoff and 
Landing 
 
Enroute 
101500 24.3% SMC 
(Arm -1.07 ft) 
22.3% SMC 
(Arm -1.26 ft) 
45.0% SMC 
(Arm +0.92 ft) 
46.0% SMC 
(Arm +1.02 ft) 
101500 
to 
90000 
 
Linear variation 
between 24.3% 
and 
 
Linear variation 
between 
22.3% and 
Linear variation 
between 45.0% 
and 48.5% SMC 
(Arm +1.26 ft) 
Linear variation 
between 46.0% 
and 50.0% SMC 
(Arm +1.41 ft) 
90000 
to 
82500 
22.5% SMC 
(Arm -1.24 ft) 
20.5% SMC 
(Arm -1.43 ft) 
 
 
Constant 
 
 
Constant 
82500 
to 
58000 
 
Linear variation 
between 
 
Constant 
48.5% SMC 
(Arm +1.26 ft) 
50.0% SMC 
(Arm +1.41 ft) 
58000 
to 
47000 
22.5% and 
23.0% SMC 
( Arm -1.19 ft) 
 Linear variation 
between 48.5% 
and 44.0% SMC 
(Arm +0.83 ft.) 
Linear variation 
between 50.0% 
and 45.5% SMC 
(Arm +0.97 ft) 
 
Maximum Weight Maximum Taxi Weight 98,000 lbs 
     lbs kgs 
  Taxi Weight  98,000 44,452 
  Takeoff Weight  97,500 44,225 
  Landing Weight  88,500 40,142 
  Zero Fuel Weight  82,500 37,421 
 
  Maximum Taxi Weight 98,000 (with Bae Modification HCM60346N  (see Note 14) 
     lbs kgs 
  Taxi Weight  98,000 44,452 
  Takeoff Weight  97,500 44,225 
  Landing Weight  86,500 39,235 
  Zero Fuel Weight  80,500 36,514 
 
  Maximum Taxi weight 102,000 lbs. with Bae Modification HCM01000L 
     lbs kgs  
  Taxi Weight  102,000 46,266 
  Takeoff Weight  101,500 46,039 
  Landing Weight    88,500 40,142 
  Zero Fuel Weight    82,500 37,421 
 
 
DATA PERTINENT TO ALL AVRO 146 MODELS 
 
Engines  4 Avco Lycoming Model LF507-1F Turbine engines

A49EU, Revision 19 18 
 
Fuel  See Airplane Flight Manual for approved fuels and additives. 
 
Engine Limits  (See NOTE 13) 
Model LF507-1F Engine (Standard day Sea Level Conditions) 
 
Rating 
 
Thrust lbs 
 
Engine N1 
% (RPM) 
 
Engine N2* 
% (RPM) 
Exhaust Gas 
Temperature 
°C       (°F) 
Takeoff (5 minutes) 
Max Continuous 
7000 
6550 
97.0  (7374) 
97.0  (7374) 
98.8  (19760) 
96.9  (19380) 
632    (1170) 
613    (1136) 
  *See Airplane Flight Manual for additional N2 speed, start and relight limits  
 
 
 
 
 
 
Auxiliary Power Unit.  1 AiResearch GTCP 36-150(M) or 1 Sundstrand APS1000 T-62T-46C 
 
** Limits 
 
GTCP 36-150(M) APS1000 T-62T-46C 
Rated shp, maximum for Standard Day, 
Sea level conditions 
 
50 shp 53.5 shp. 
Shaft Speed: 
Maximum (at rated power) 
 
 
103% (60499 RPM) 
 
108% (69286 RPM) 
Maximum Exhaust Temperature: 
Continuous Operation 
Starting:   (Up to 10 seconds) 
                (More than 10 seconds) 
 
746ºC 
974ºC 
870ºC 
 
  718ºC 
   - 
1032ºC 
  ** See Airplane Flight Manual for additional limitations and Approved Oils.  
 
Airspeed Limits. 
 
Limit Aircraft type [speeds in Kts (IAS)] 
 RJ70A RJ85A RJ100A 
MMO (Maximum Operating) [Indicated Mach No] 0.73 0.73 0.73 
VMO (up to 8000 ft) 250 250 250 
           (8,000 to 22,950 ft) 300 300  - 
           (8,000 to TBA) - - 305 
VA (Maneuvering):  Flaps Retracted 205 235 # 245 * 
                                 Flaps 18° 165 175 175 
VFE (Flap speeds):    
          Enroute/Hold                 Flaps   0°  VMO VMO VMO 
          Takeoff/Approach          Flaps 18° 205 215 220 
          Takeoff/Approach          Flaps 24° 170 180 180 
          Takeoff                          Flaps 30°  160 170 170 
          Landing +                      Flaps 33°  150 150 155 
VLO (Landing Gear Operations): Operation 210 210 210 
                                                      Extended 210 210 210 
VLE (Landing Gear):  Extended 210 210 210 
VMC (Minimum Control Speed):    
               VMCA                          Flaps  0°  132 132 132 
                                                    Flaps 18° 97 97 97 
                                                    Flaps 24° 91 91 91 
                                                    Flaps 30° 89 89 89

A49EU, Revision 19 19 
               VMCG (up to 65,000 lbs) 85 84 81 
                             (at and above 65,000 lbs) 83 81 81 
 * For construction number E3221 with Modification HCM60346N, Flaps Retracted VA is 240 Kts (IAS)  
    - See Note 14. 
 
 # For construction number E2208 with Modification HCM20203B, Flaps Retracted VA is 230 Kts (IAS) 
    - See Note 15. 
 
 + Flaps 33° is available as a Take -off setting for aircraft fitted with modification HCM30370A or HCM40391A. 
 
 
C.G. Range.   Landing Gear retraction moment - 8,916 lb. in. (Nose down) 
 
Control Surface   The specific procedures for rigging each of the aircraft movable surfaces are defined in  
Movements.   the documents listed below.  Correct application of these procedures will ensure  
    movement and travel of each surface is as required. 
 
Rigging       RJ70A       RJ85A       RJ100A 
Aileron 
Rudder 
Elevator 
Flap 
Airbrake & Lift Spoiler 
HC271H0001 
HC272H0001 
HC273H0001 
HC275H0001 
HC276H0001 
HC271H0001 
HC272H0001 
HC273H0002 
HC275H0001 
HC276H0001 
HC271H0001 
HC272H0001 
HC273H0567 
HC275H0001 
HC276H0001 
 
Maximum Underfloor Baggage. 
         RJ70A       RJ85A       RJ100A 
Forward Hold 
 
       2580 lbs 
(Arm  -12.73 ft) 
      3350 lbs 
(Arm -14.76 ft) 
      4125 lbs 
(Arm -16.93 ft) 
Rear Hold 
 
       2420 lbs 
(Arm +11.78 ft) 
     3320 lbs 
(Arm +13.68 ft) 
      4033 lbs 
(Arm +15.33 ft) 
Maximum Floor 
Loading 
    75 lbs/sq.ft  
 
Maximum Passengers. 
Model     RJ70A      RJ85A     RJ100A 
Maximum Passengers        94         108         108 
     
Engine Oil Capacity.  Four oil tanks each 3.02 U.S. gallons capacity.  Moment arm - 8.5 ft. 
    See Airplane Flight Manual for Approved Oils. 
 
Weight and Balance Datum.   
Model   RJ70A   RJ85A    RJ100A 
Fuselage Station  
AXO (inches) 
  448.13   491.81    544.81 
 
    This is 4 feet forward of the reference point which is indicated by two plates at the  
    rear end of the main landing gear bay. 
 
Aircraft Flight Manual.  Aircraft shall be operated in compliance with the operating limitations specified in the  
EASA Approved Flight Manual Document BAE 5.1 dated August 15, 2007 or later approved 
revisions.  AFM BAE No. 5.1 supersedes CAA approved Flight Manual Document No. BAe  No. 
4.1, dated April 08, 1993 or later approved revisions.   
 
Minimum Crew.   2 - (Pilot and Co-Pilot) 
 
Maximum Operating Altitude. 31,000 ft (See Notes 16 and 17.) 
 
Usable Fuel Capacity. 
 RJ70A RJ85A RJ100A

A49EU, Revision 19 20 
Wing Tanks 
(Right & Left) 
16,160 lbs 
(Arm +0.008 ft) 
Center Tank 4,160 lbs (Arm -3.24 ft) 
Auxiliary Tanks 
(Right & Light) 
2,064 lbs 
(Arm +4.230 ft) 
 
    Fuel must be loaded symmetrically into the wing tanks.  The maximum allowable wing 
    tank fuel asymmetry is 1,500 lbs.  See Note 1 for information on unusable and  
    undrainable fuel. 
 
Standard Mean Chord.  The Standard Mean Chord is 9.62 ft.  The leading edge of the Standard Mean Chord is  
(SMC).    3,405 ft forward of the C.G. datum. 
 
Leveling Means.   Clinometer on cabin seat rails. 
 
Certification Basis AVRO RJ  FAR 21.29 
      FAR 25 effective 1 February 1965, including Amendments 25-1 through 25-43, 
    FAR 25 Subpart C, Amendments 44 through 54 inclusive. 
 
    In addition the following later requirements apply: 
     FAR Section     Amdt.  
     25.605(a),(b)   46 
     25.629    46 
     25.697(b)    46 
     25.701(b)    46 
     25.733(a), (b), (c)   49 
     25.735(b), (f)(2), (g)  48 
     25.783    54 
     25.787    51 
     25.789    46 
     25.793    51 
     25.803    46 
     25.809(f) (iii, iv, v)   47 
 
     FAR Section     Amdt. 
     25.811    46 
     25.812    46 
     25.851(a) (5)   54 
     25.853    51 
     25.858    54 
     25.863    46 
     25.1103(a), (b)(2), (d), (e), (f) 46 
     25.1142    46 
     25.1207(d)   46 
     25.1305(d)   54 
     25.1329(h)   46 
     25.1522    46 
     25.1561(c)   46 
     25.773(b)(2)(ii)   72 
     25.775(e)    72 
    Equivalent Safety: 
     FAR 25.613(a) - Design Values 
     FAR 25.615(a)  - Design Properties 
     FAR 25.773(b)(2) - Pilot's Window(see note 18) 
     FAR 25.1091(e) - Foreign Object Ingestion 
 
    Exemption No. 3639 regarding FAR 25.807(c)(1). 
    FAR Part 36 effective December 1, 1969, including Amendments 36-1through 36-20. 
    Special Federal Aviation Regulation No. 27 effective February 1, 1974 including  
    Amendments 27-1 through 27-5.

A49EU, Revision 19 21 
 
    FAA Advisory Circular AC120-28C (criteria for Approval of Category III Landing 
    Weather Minima, dated March 1984).  
 
    The applicable later requirements for the installation of the LF507 -1H and -1F engines  
    are: 
     FAR 25.903(a)  Amendment 57 
     FAR 25.1091(e)  Amendment 57 
     FAR 25.1093(b)(2)  Amendment 57 
     FAR 25.1163(a)(3)  Amendment 57 
     FAR 25.1305(d)(1)  Amendment 54 
 
The applicable later requirements for the installati on of phase II avionics are, FAR Part  
    25 effective 1 February 1965 including Amendments 25-1 through 25-66 and Special  
    Conditions as published in the Federal Register October 18, 1991 covering: 
     1) Lightning Protection 
     2) Protection from Unwanted Effects of High Intensity Radiated Field (HIRF) 
 
Historical Transition. The United Kingdom Civil Aviation Authority originally type certificated this aircraft 
under its type certificate Number BA16. The FAA validated this product under U.S. 
Type Certificate Number A49EU.  Effective September 28, 2003, the European 
Aviation Safety Agency (EASA) began oversight of this product on behalf of the United 
Kingdom. 
 
Type Certificate.   Type Certificate No. A49EU, issued June 13, 1983. 
    Effective Date of Application for Type Certificate August 4, 1978. 
 
Serial Nos. Eligible.  The United Kingdom Certificate of Airworthiness for Export issued to aircraft  
    manufactured at Woodford in the United Kingdom and endorsed as noted under "Import  
    Requirements" must be submitted for each individual aircraft for which application of  
    certification is made. 
 
    AVRO 146 aircraft Models will be the following construction numbers: 
    RJ70A:  E1223 and subsequent. 
    RJ85A:  E2226 and subsequent, less E2227 and including E2208. 
    RJ100A:  E3221 and subsequent, less E3222.  
 
    AVRO 146 aircraft minimum type design build standards for certification are defined 
    by the following modifications: 
    RJ70A: HCM60401Z Part Number HC000H1401-002 at Issue 1 and subsequent. 
    RJ85A: HCM60402Z Part Number HC000H1402-002 at Issue 1 and subsequent. 
RJ100A:  HCM60403Z Part Number HC000H1403-002 at Issue 1 and subsequent. 
 
Import Requirements. The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate 
of Airworthiness (Export C of A) signed by a representative of United Kingdom Civil 
Aviation Authority 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 Type Design approved under U.S. Type 
Certificate No. A49EU and to be in a condition for safe operation.’ 
 
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 United Kingdom Civil Aviation Authority, are accepted by the FAA and 
are considered FAA approved.  Additionally, approvals issued by BAE Systems 
(Operations) Limited under the authority of EASA approved Design Organization 
EASA.21J.047 -  or for approvals made before September 28, 2003 under the authority 
of JAA Design Organization Approval No. CAA.JA.02034 or Manufacturers CAA 
Approval Ref. DAI/1011/55 - are considered FAA approved.  These approvals pertain to 
the type design only.  
 
• BAE Systems (Operations) Limited service bulletins, except as noted below,

A49EU, Revision 19 22 
• Structural repair manuals,  
• Vendor manuals referenced in BAE Systems (Operations) Limited service bulletins, 
• Aircraft flight manuals, 
• Repair Instructions. 
 
Note: Design changes that are contained in BAE Systems (Operations) Limited Service 
Bulletins and that are classified as Level 1 Major in accordance with either the 
US/United Kingdom or US/EASA Bilateral Aviation Safety Agreement Implementation 
Procedures for Airworthiness must be approved by the FAA. 
 
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 the following document: 
     ADE-CES-D-460-00-0011 
 
 
 
 
 
NOTES: (Applicable to both BAe 146 and AVRO 146 Models unless indicated otherwise) 
 
NOTE 1.   Weight and Balance. 
(a)  Current Weight and Balance Manual including list of equipment included in certificated 
empty weight and loading instructions must be provided for each aircraft at the time of original 
certification and at all times subsequently.  "Weight and Balance Manu al" No. WBM 146 
contains all the loading information required for each aircraft in its delivery configuration. 
 
(b)  The airplane must be loaded so that the C.G. is within the specified limits at all times when 
all influences on C.G. position have been considered. 
 
(c)  The Weight and Balance Manual defined in (a) above quotes the quantities of unusable fuel 
as determined by the critical conditions of FAR 25.959.  Undrainable fuel, being that remaining 
in the aircraft when all fuel drain valves are opened o n the ground, is also quoted in the Weight 
and Balance Manual. 
 
NOTE 2.   All placards required in the Approved Airplane Flight Manual must be installed in the  
   appropriate location. 
 
NOTE 3. (a) Airframe Component Life Limitations, required Certification Maintenance Requirements  
  (CMR's) and required Structural Inspections are listed in the FAA Approved Airworthiness  
  Limitations Section (Chapter 5) of the BAe 146/AVRO 146 Aircraft Maintenance Manual. 
(b) Engine life limited components are contained in Avro Lycoming Service Bulletin No.  
 ALF 502-72-0002, Revision 6, dated January 10, 1983 or later, approved revision.  
 
NOTE 4.   Compliance with the fuel venting provisions of SFAR 27 is achieved by incorporation of the  
   components listed in Document Number HTD-N-46071SC0071. 
 
NOTE 5. (BAe 146 only Without Modifications HCM35040M and X the Auxiliary Power Unit has not been shown  
                 with GTCP  to fully comply with FAR 25.1093(b)(1) and therefore cannot be considered essential for 
 36-100(M)) dispatch purposes when falling snow or freezing rain conditions exist. 
 
With Modification HCM35040M and X embodied the Auxiliary Power Unit can be operated as 
an essential power source for dispatch purposes in falling snow or freezing rain when the relevant 
information is incorporated in the approved Airplane Flight Manual, Document No. BAE 5.1. 
 
NOTE 6.   
 
NOTE 7. (BAe 146 only) The Model ALF 502 R3A and ALF 502 R-5 engine are physically identical to the Model  
ALF 502 R-3 engine and is eligible without additional installation instructions.  However, the following 
conditions must be observed:

A49EU, Revision 19 23 
(a)  Any combinations of ALF 502 R-3 and R-5 model engines may be fitted to the aircraft 
provided they are all operated at the model ALF 502 R-3 thrust settings and limitations.  Any 
combination of ALF 502 R-3A and R-5 model engines may be fitted to the aircraft and may be 
operated at the model ALF 502 R-5 thrust setting and limitations.  
 
   (b)  When four ALF 502 R-5 engines are fitted, they may be operated at Model ALF 502 R-5  
thrust settings and limitations when BAE Systems modifications HCM0020B for BAe 146-100A, 
or HCM00021B for BAe 146-100A, or HCM0021B for BAe 146-200A, or HCM00083A, 
HCM00083C and HCM00083D for BAe 146-100A and 200A, are incorporated. 
 
(c)  The appropriately revised approved Airplane Flight Manual, Document  No. BAE 5.1 is 
required for operation when BAE Systems modifications HCM50033A, HCM50033B, 
HCM50033C; or HCM00101A, HCM00101B; or HCM00336A, HCM00336B, HCM00336C, 
HCM 00336D; or HCM50046A, HCM50046B, HCM50046C, HCM50046D are incorporated. 
 
(d)  Deleted. 
 
 
 
 
 
NOTE 8. (BAe 146 only) Maximum Weight Increase 
 
(a) The maximum weights all BAe 146 Models may be increased as shown in the following 
tables when the BAE Systems  modification listed against each weight increase is fitted and the 
aircraft is operated in accordance with the FAA Approved Flight manual, Document No. BAE 5.1, 
revised to reflect the associated modification standard.   
 
   (b)   100A 
 Maximum Weight 
     Permitted 
BAe Modification No. 
Maximum Zero 
fuel weight 
 66,000 lb 
 
 67,000 lb 
No modification to 
aircraft 
HCM 00020G    or 
HCM60015Q 
  67,500 lb HCM 00020H 
  68,500 lb HCM 00020J 
Maximum landing 
weight 
 73,350 lb HCM 00020N    or 
HCM 60015Q 
  77,500 lb HCM 00020P 
Maximum take-off 
weight 
 82,250 lb    i) HCM 60015Q or 
  ii) HCM 30071A with  
      HCM 40225B, E or G 
or 
 iii) HCM 40046L with 
      HCM 40225D or F 
  84,0000 lb. HCM 00020U 
 
   (c)   200A. 
 Maximum Weight 
    Permitted 
BAe Modification No. 
Maximum zero 
   fuel weight 
73,500 lb HCM 00021G 
Maximum zero 
   fuel weight 
75,000 lb HCM 00021J 
Maximum Landing 
   weight 
78,900 lb 
81,000 lb 
HCM 40420B 
HCM 00021N 
Maximum takeoff  
weight 
91,200 lb 
93,000 lb 
HCM 40420A 
HCM 00021U 
 
   (d)   300A.

A49EU, Revision 19 24 
 Maximum Weight 
    Permitted 
BAe Modification No. 
Maximum zero 
   fuel weight 
   78,500 lb 
* 79,000 lb 
HCM 01000B 
HCM 01000G 
Maximum landing 
   weight 
   84,500 lb HCM 01000B 
Maximum take-off 
   weight 
   97,500 lb HCM 01000B 
 *Applicable to freighter aircraft only.  HCM 01000G can only be embodied on 
aircraft which incorporate HCM 01000B. 
 
NOTE 9. (BAe 146 only)  The maximum take-off N2 rating is 98.0% (19760 rpm) for aircraft fitted with B AE 
Systems modification HCM35051B and operated in accordance with the Approved 
Flight Manual, Document No. BAE 5.1.   
 
The maximum take-off N2 rating is 98.8% (19760 rpm) with transient overshoots not to 
exceed 10 seconds or 100%, for aircraft fitted with BAE Systems modifications: 
 
     (i) HCM35051D and HCM70080A 
or (ii) HCM01054B 
 
and operated in accordance with the Approved Flight Manual, Document No. BAE 5.1.  
 
For aircraft fitted with BAE Systems modification HCM 60020B, the maximum take-off 
N2 limits of 98.8% (19760 rpm) and the maximum take -off TGT limit of 904ºC are 
authorized, provided the aircraft is operated in accordance with the limitations and 
procedures given in the Approved Flight Manual, Document No. BAE 5.1.  
 
NOTE 10.   Category II & III Operation 
 
BAe 146 Models: (Category II Operation only) 
 
Automatic Pilot/Flight Director System including approach and landing to Category II  
Weather Minimum is authorized for the BAe 146 Models when the following BAE 
Systems modifications are embodied and operated in accordance with the appropriately 
revised approved Airplane Flight Manual, Document No. BAE 5.1. 
 
Model Modification 
100A HCM40350B 
200A HCM40350C 
300A HCM40354A 
 
AVRO 146 Models:  (Category III and II Operation) 
 
    Automatic Pilot/Flight Director System including approach and landing to Category II 
Weather Minimum is authorized for the AVRO 146 Models by virtue of the fitment of 
the Category III Modifications as detailed below: 
 
Model Modification 
RJ70A HCM40356A 
RJ85A: HCM40355A 
RJ100A HCM40354A 
 
Operation for Category III and II is detailed within the appropriately revised approved 
Aircraft Flight Manual Document No. BAE 5.1. 
 
NOTE 11. (BAe 146 only)  Aircraft for Freighter Conversion 
A BAe 146  200A/300A fitted with the BAe modification(s) noted below provides 
provision for converting the basic BAe 146  200A/300A into the freighter configuration.

A49EU, Revision 19 25 
For 200A: HCM 50200A - Deletion of type certification basic features not 
      required on conversion to a freighter aircraft. 
  HCM 50200B - Basic airframe changes. 
  HCM 50200C - Dedicated freighter features. 
 
For 300A: HCM 50213C - To prepare basic 300A  airframe for  
       conversion to freighter role. 
 
Freighter Aircraft 
The BAe 146  300A fitted with the BAe Modification noted below provides full 
conversion to an operational freighter aircraft. 
 
 HCM 50214S - To introduce minimum standard for dedicated freighter  
      aircraft. 
 
Modification HCM 50214S has associated content within approved Airplane Flight 
Manual Document No. BAE 5.1.  
 
NOTE 12. (BAe 146 only)  Aircraft for operation to 31,000 ft:   For aircraft fitted with BAe modification HCM 
50043A and HCM 50043B, or E or F or for aircraft fitted with HCM 50043C, operation to a 
maximum altitude to 31,000 ft in accordance with the Approved Flight Manual is authorized. 
 
 
 
NOTE 13. (AVRO 146-RJ only) On all AVRO 146-RJ Models, the engine is controlled by a fanspeed (N1) Schedule in  
the Digital Flight Guidance Computer or the Aircraft Flight Manual.  When Modification 
HCM00020S is fitted to the RJ70A aircraft, the Schedule produces a thrust of 6,130 lbs at 
sea level (static) and ISA +17.5ºC, (compared to 7,000 lbs without the modification and 
HCM00020R fitted) which is the basis for the performance data in the Aircraft Flight 
Manual. 
 
NOTE 14. (E3221 only)  Construction number E3221 is fitted with Modification HCM60346N which introduces 
reduced Max. Zero Fuel and Max. Landing Weights and a reduction in speed VA to 240 kts 
(IAS) with flaps retracted. 
 
NOTE 15. (E2208 only)  Construction number E2208 is fitted with Modification HCM20203B which introduces 
reduced Max. Zero Fuel and Max. Landing Weights and a reduction in speed VA to 230 kts 
(IAS) with flaps retracted. 
 
NOTE 16. (AVRO 146-RJ only) Aircraft for operation to 33,000 ft:  For aircraft fitted with BAe modification HCM 50070F 
and 
HCM 50258A, operation to a maximum altitude to 33,000 ft in accordance with the 
Approved Flight Manual is authorized. 
 
NOTE 17. (AVRO 146-RJ only) Aircraft for operation to 35,000 ft For aircraft fitted with BAe modification 
HCM 50259A, operation to a maximum altitude to 35,000 ft in accordance with the 
Approved Flight Manuals is authorized. 
 
NOTE 18 In the original certification basis an equivalent safety finding (ESF)  to FAR 25.773(b)(2) 
amendment 25-23 was granted to allow for a non-openable first pilot window based on 
certain compensating design features.  FAR 25.773 (b)(2) was later amended by amendment 
25-72 to delete the need for an ESF for a non-openable first pilot window provided certain 
criteria are met (the criteria and BAe compliance with it are contained in FAA issue paper F -
1 dated July 8, 1998).  Satisfying these criteria also establishes compliance with FAR 
25.773(b)(2)(ii) and 25.775(e) as amended by amendment 25- 72 and the certification basis 
for the BAe/Avro 146 has been amended accordingly. 
 
NOTE 19 The certification differences between aircraft that meet the FAA certification basis (FAA 
TCDS A49EU) and those aircraft that meet the European Aviation Safety Agency (EASA) 
certification basis (EASA TCDS EASA.A.182) are limited to cabin pressure controllers, fuel 
contents indicators, a change of MMO, associated placards and gauges and constructors

A49EU, Revision 19 26 
nameplates and flight manual.  BAE Systems (Operations) Ltd Service Bulletins are 
available to facilitate conversion of an EASA standard aircraft to an FAA standard aircraft 
and vice versa.  (SB01-07-20004A; SB01-37-20004B; SB01-35-20004C)  Aircraft converted 
from the EASA standard to the FAA standard must have an “A” suffix, in the aircraft model 
designation, see table below and on the applicable placards and or nameplates to indicate  
that the converted aircraft meets the FAA certification basis 
 
. 
 
 
 
 
…END… 
BAE 146 Series Avro 146 RJ Series 
FAA EASA FAA EASA 
146-100A 146-100 146-RJ70A 146-RJ70 
146-200A 146-200 146-RJ85A 146-RJ85 
146-300A 146-300 146-RJ100A 146-RJ100
```

## ADs (196, first 50, in force first)

- [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026
- [AD 2010-09-11 R1](https://openairdocs.org/ad/2010-09-11-R1): Wings · BAE Systems BAe 146-100A, BAe 146-200A, BAe 146-300A and 3 more. Effective Aug 5, 2025
- [AD 2024-17-06](https://openairdocs.org/ad/2024-17-06): Fuselage · BAE Systems BAe 146-100A, BAe 146-200A, BAe 146-300A and 3 more. Effective Nov 4, 2024
- [AD 2024-06-10](https://openairdocs.org/ad/2024-06-10): Landing gear · BAE Systems BAe 146-100A, BAe 146-300A, BAe 146-200A and 3 more. Effective May 22, 2024
- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2023-02-16](https://openairdocs.org/ad/2023-02-16): Navigation · BAE Systems Avro 146-RJ70A, Avro 146-RJ85A and Avro 146-RJ100A. Effective Apr 4, 2023
- [AD 2023-02-10](https://openairdocs.org/ad/2023-02-10): Fuselage · BAE Systems BAe 146-100A, BAe 146-200A, BAe 146-300A and 3 more. Effective Mar 17, 2023
- [AD 2022-23-07](https://openairdocs.org/ad/2022-23-07): Auto-Flight · BAE Systems BAe 146-100A, BAe 146-200A and BAe 146-300A. Effective Jan 4, 2023
- [AD 2022-14-13](https://openairdocs.org/ad/2022-14-13): Fuselage · BAE Systems BAe 146-100A, BAe 146-200A, BAe 146-300A and 3 more. Effective Aug 25, 2022
- [AD 2022-06-14](https://openairdocs.org/ad/2022-06-14): Time Limits/Maintenance Checks · BAE Systems BAe 146-100A, BAe 146-200A, BAe 146-300A and 3 more. Effective May 19, 2022
- [AD 2021-10-27](https://openairdocs.org/ad/2021-10-27): Lights · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Jun 17, 2021
- [AD 2018-23-12](https://openairdocs.org/ad/2018-23-12): Equipment/furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 180 more. Effective Dec 28, 2018
- [AD 2017-04-04](https://openairdocs.org/ad/2017-04-04): Air Conditioning · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Mar 29, 2017
- [AD 2016-16-11](https://openairdocs.org/ad/2016-16-11): Wings · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Sep 16, 2016
- [AD 2016-07-06](https://openairdocs.org/ad/2016-07-06): Time Limits/Maintenance Checks · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective May 5, 2016
- [AD 2014-16-18](https://openairdocs.org/ad/2014-16-18): Landing Gear · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Oct 2, 2014
- [AD 2014-01-04](https://openairdocs.org/ad/2014-01-04): Fire protection · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Mar 14, 2014
- [AD 2013-22-08](https://openairdocs.org/ad/2013-22-08): Wings · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Dec 5, 2013
- [AD 2013-04-13](https://openairdocs.org/ad/2013-04-13): Electrical Power · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Apr 11, 2013
- [AD 2013-02-09](https://openairdocs.org/ad/2013-02-09): Ice and rain protection · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Mar 8, 2013
- [AD 2012-21-16](https://openairdocs.org/ad/2012-21-16): Hydraulic power · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Dec 5, 2012
- [AD 2012-12-13](https://openairdocs.org/ad/2012-12-13): Fire Protection · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Jul 30, 2012
- [AD 2012-12-22](https://openairdocs.org/ad/2012-12-22): Fuselage · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Jul 30, 2012
- [AD 2011-20-02](https://openairdocs.org/ad/2011-20-02): Landing gear · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Oct 28, 2011
- [AD 2011-11-06](https://openairdocs.org/ad/2011-11-06): Landing Gear · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Jul 6, 2011
- [AD 2011-08-11](https://openairdocs.org/ad/2011-08-11): Fuselage · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective May 26, 2011
- [AD 2010-21-10](https://openairdocs.org/ad/2010-21-10): Wings · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Nov 18, 2010
- [AD 2010-18-10](https://openairdocs.org/ad/2010-18-10): Flight controls · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Oct 7, 2010
- [AD 2010-16-09](https://openairdocs.org/ad/2010-16-09): Flight Controls · BAE Systems BAe 146-100A and BAe 146-200A. Effective Sep 17, 2010
- [AD 2010-16-10](https://openairdocs.org/ad/2010-16-10): Wings · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Sep 17, 2010
- [AD 2010-02-11](https://openairdocs.org/ad/2010-02-11): Fuselage · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Mar 4, 2010
- [AD 2009-17-03](https://openairdocs.org/ad/2009-17-03): Fuselage · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Sep 22, 2009
- [AD 2009-15-19](https://openairdocs.org/ad/2009-15-19): Stabilizers · BAE Systems BAe 146-100A and BAe 146-200A. Effective Sep 2, 2009
- [AD 2009-15-08](https://openairdocs.org/ad/2009-15-08): Fuselage. · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Aug 25, 2009
- [AD 2009-12-10](https://openairdocs.org/ad/2009-12-10): Fuselage · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Jul 24, 2009
- [AD 2009-02-09](https://openairdocs.org/ad/2009-02-09): Aft wing links · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Apr 2, 2009
- [AD 2008-23-14](https://openairdocs.org/ad/2008-23-14): Bolts · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Dec 26, 2008
- [AD 2008-10-05](https://openairdocs.org/ad/2008-10-05): Leading edge high lift devices. · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Jun 10, 2008
- [AD 2008-06-08](https://openairdocs.org/ad/2008-06-08): Centre fuselage top aft longeron · BAE Systems BAe 146-100A, BAe 146-200A and BAe 146-300A. Effective Apr 16, 2008
- [AD 2008-04-16](https://openairdocs.org/ad/2008-04-16): APU (auxiliary power unit) · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Apr 3, 2008
- [AD 2007-26-18](https://openairdocs.org/ad/2007-26-18): Accumulator cylinder · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Feb 11, 2008
- [AD 2007-13-06](https://openairdocs.org/ad/2007-13-06): Flight deck side consoles · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Jul 25, 2007
- [AD 2007-04-04](https://openairdocs.org/ad/2007-04-04): Wing top skin under the rib 0 joint strap · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Mar 21, 2007
- [AD 2007-01-01](https://openairdocs.org/ad/2007-01-01): Lift spoiler actuators/jacks · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Feb 13, 2007
- [AD 2006-25-10](https://openairdocs.org/ad/2006-25-10): Lift spoiler jack · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Jan 16, 2007
- [AD 2006-23-16](https://openairdocs.org/ad/2006-23-16): Nose wheel assembly · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Dec 21, 2006
- [AD 2006-23-12](https://openairdocs.org/ad/2006-23-12): Hydraulic accumulators · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Dec 18, 2006
- [AD 2006-23-13](https://openairdocs.org/ad/2006-23-13): Three-phase circuit breaker panels · BAE Systems BAe 146-100A, BAe 146-200A and BAe 146-300A. Effective Dec 18, 2006
- [AD 2006-20-05](https://openairdocs.org/ad/2006-20-05): Inspect chafing in skin of wing-to-fuselage fairing · BAE Systems BAe 146-100A, BAe 146-200A and BAe 146-300A. Effective Nov 2, 2006
- [AD 2006-11-08](https://openairdocs.org/ad/2006-11-08): Flap structure and machined ribs · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 3 more. Effective Jun 29, 2006

All 196: https://openairdocs.org/tcds/A49EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [British Aerospace AVRO 146-RJ85A](https://openairdocs.org/model/british-aerospace-avro-146-rj85a): 12 aircraft (registry code 1500097)
- [British Aerospace BAE 146 SERIES 200A](https://openairdocs.org/model/british-aerospace-bae-146-series-200a): 8 aircraft (registry code 1500266)
- [British Aerospace BAE 146-300](https://openairdocs.org/model/british-aerospace-bae-146-300): 3 aircraft (registry code 1500270)
- [BAE Systems AVRO 146-RJ85A](https://openairdocs.org/model/bae-systems-avro-146-rj85a): 2 aircraft (registry code 1500099)
- [BAE Systems AVRO 146-RJ100A](https://openairdocs.org/model/bae-systems-avro-146-rj100a): 0 aircraft (registry code 3940401)
- [British Aerospace AVRO 146-RJ70A](https://openairdocs.org/model/british-aerospace-avro-146-rj70a): 0 aircraft (registry code 1500095)
- [British Aerospace AVRO-146RJ100A](https://openairdocs.org/model/british-aerospace-avro-146rj100a): 0 aircraft (registry code 1500096)
- [British Aerospace BAE 146 SERIES 100A](https://openairdocs.org/model/british-aerospace-bae-146-series-100a): 0 aircraft (registry code 1500260)
- [British Aerospace BAE 146 SERIES 300A](https://openairdocs.org/model/british-aerospace-bae-146-series-300a): 0 aircraft (registry code 1500267)

## STCs approved under this data sheet (78, first 50)

- [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center
- [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 ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc.
- [STC ST00952LA](https://openairdocs.org/stc/ST00952LA): Installation of Mass Systems fire extinguisher cartridges as replacements for Kidde fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON LLC d/b/a MASS Systems
- [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 ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc.
- [STC SA3964NM](https://openairdocs.org/stc/SA3964NM): Installation of closet and class divider.. Safran Cabin Inc.
- [STC SA3414NM](https://openairdocs.org/stc/SA3414NM): Installation of floor proximity emergency escape path marking system.. Bruce Aerospace 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 ST02829LA](https://openairdocs.org/stc/ST02829LA): Conversion of a BAE Systems (Operations) Limited BAe 146-200 passenger configuration to a firefighting airtanker with the installation of a 3000 USG retardant tank system. Airspray USA Ltd.
- [STC ST02080CH](https://openairdocs.org/stc/ST02080CH): Installation of VHF-3 Antenna Structural Provisions.. Amphenol Cable and Interconnect Technologies Inc.
- [STC ST02086CH](https://openairdocs.org/stc/ST02086CH): Installation of a Spectra Lux Dlink Aircraft Communications Addressing and Reporting System (ACARS).. Amphenol Cable and Interconnect Technologies Inc.
- [STC ST01576LA](https://openairdocs.org/stc/ST01576LA): Installation of AirWorks Cockpit Door Surveillance Systems. Aero Technik Inc.
- [STC ST00215IB](https://openairdocs.org/stc/ST00215IB): Installation of saf-Tglo ECO Photoluminescent Aisle Path Marking Systems. STG AEROSPACE GERMANY GmbH
- [STC ST04647CH](https://openairdocs.org/stc/ST04647CH): INSTALL SOLID STATE DIGITAL FLIGHT DATA RECORDER (DFDR) SYSTEM. DAN BUZZ & ASSOCIATES LLC
- [STC ST04562NY](https://openairdocs.org/stc/ST04562NY): Installation of saf-Tglo® SuperSeal UltraLite-X (SSUL-X) Photoluminescent Floor Proximity Emergency Escape Path Marking Systems. STG AEROSPACE GERMANY GmbH
- [STC ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited
- [STC ST02281LA](https://openairdocs.org/stc/ST02281LA): Installation of internal tank, associated systems and support structure for the aerial dispensing of liquids. Neptune Aviation Services
- [STC ST00844SE](https://openairdocs.org/stc/ST00844SE): Installation of a the Honeywell Flight Data Acquisition Management System. Honeywell International Inc
- [STC ST00940SE](https://openairdocs.org/stc/ST00940SE): Installation of a the Honeywell Airborne Flight Information System (AFIS) in accordance with Master Drawing List 756-0129-001, Revision A, dated June 12, 2001, or later FAA approved revisions.. Honeywell International Inc
- [STC ST02699SE](https://openairdocs.org/stc/ST02699SE): Installation of Honeywell Flight Data Acquisition Management 
System (FDAMS) with Flight Control Input Position Sensors. Neptune Aviation Transport Services
- [STC ST00261DE-D](https://openairdocs.org/stc/ST00261DE-D): Installation of dual AlliedSignal GNS-XLs Flight Management System. Honeywell International Inc
- [STC ST00255DE-D](https://openairdocs.org/stc/ST00255DE-D): Installation of AlliedSignal VHF AFIS. Honeywell International Inc
- [STC ST01805WI](https://openairdocs.org/stc/ST01805WI): Modification of Rockwell Collins TCAS II System Installation with DC powered TCAS Transmitter Receiver Processor. Rockwell Collins Inc
- [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 ST02841CH](https://openairdocs.org/stc/ST02841CH): Install air ambulance conversion. Spectrum Aeromed LLC dba Spectrum Aeromed
- [STC ST04301NY](https://openairdocs.org/stc/ST04301NY): Installation of the ADS-B Out Upgrade. Avmax Aviation Services Inc.
- [STC ST04302NY](https://openairdocs.org/stc/ST04302NY): Installation of the ADS-B Out Upgrade. Avmax Aviation Services Inc.
- [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 ST03962NY](https://openairdocs.org/stc/ST03962NY): Installation of the ADS-B Out Upgrade. Avmax Aviation Services Inc
- [STC ST03958NY](https://openairdocs.org/stc/ST03958NY): Installation of the ADS-B Out Upgrade. Avmax Aviation Services Inc
- [STC ST02406LA](https://openairdocs.org/stc/ST02406LA): Installation of TCAS version 7.1. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC ST02793CH](https://openairdocs.org/stc/ST02793CH): Install Aero Medical Products Mfg., Inc. 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 SA7076NM](https://openairdocs.org/stc/SA7076NM): Installation of Stretcher Carrier.. Air Medic LLC
- [STC SA2419NM](https://openairdocs.org/stc/SA2419NM): Installation of seating arrangement.. American Airlines Inc
- [STC SA2418NM](https://openairdocs.org/stc/SA2418NM): Installation of a Collins ARINC communications addressing and reporting system (ACARS). American Airlines Inc
- [STC SA2453NM](https://openairdocs.org/stc/SA2453NM): Installation of a Collins WXR-700X Weather Radar System with Turbulence Detection Mode. American Airlines Inc
- [STC SA2550SO](https://openairdocs.org/stc/SA2550SO): Installation of mixed seating.. American Airlines Inc
- [STC ST02530LA](https://openairdocs.org/stc/ST02530LA): Installation of T2CAS with TCAS version 7.1. Aircraft Communication & Surveillance Systems
- [STC ST02524LA](https://openairdocs.org/stc/ST02524LA): Installation of TCAS version 7.0. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC ST03393NY](https://openairdocs.org/stc/ST03393NY): Conversion of a BAE AVRO 146-RJ85A aircraft into an air-tanker for aerial fire-fighting with the addition of an external retardant tank system. Conair Group Inc
- [STC ST01202WI-D](https://openairdocs.org/stc/ST01202WI-D): Modification of an existing FAA approved Collins TPR-720, TPR-900 or TPR-901 Mode S transponder installation in Part 25 Aircraft using Collins Drawing Index as listed on AML No. ST01202WI-D, latest FAA approved revision.. Rockwell Collins Inc
- [STC ST01256WI-D](https://openairdocs.org/stc/ST01256WI-D): Modification of a Collins TPR-720, TPR-900 or TPR-901 Mode S Transponder System installation with an ATC/TCAS Control Panel to an Elementary Surveillance Compliant Collins TPR-901 Mode S Transponder System installation with a Flight ID/ATC/TCAS Control Panel in accordance with Collins Drawing Index as listed on AML No. ST01256WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc
- [STC ST02248NY](https://openairdocs.org/stc/ST02248NY): Installation of EMS HSD-64, HSD-128, HSD-HCM, and HSD-X. EMS Technologies Canada Ltd
- [STC SA1069GL](https://openairdocs.org/stc/SA1069GL): Installation of Grimes Floor Proximity Lighting System.. Honeywell International Inc.
- [STC ST00579CH](https://openairdocs.org/stc/ST00579CH): Installation of a GTE Airfone Public Telephone System (Genstar).. U.S. Technical Consultants Inc.
- [STC ST00844WI-D](https://openairdocs.org/stc/ST00844WI-D): Modification of Collins TCAS II or TCAS-94 (TCAS II) system installation with Collins TTR-920 Change 7.0 Receiver Transmitter to a Collins TCAS II or TCAS-94 OTCAS II) system installation with Collins TTR-921 or Collins TTR-4000 Change 7.0 TCAS Receiver Transmitter.. Rockwell Collins Inc
- [STC ST00525WI-D](https://openairdocs.org/stc/ST00525WI-D): Modification of Collins 618M-4 VHF COMM Receiver Transmitter Installation to a 618M-5 VHF COMM Receiver Transmitter installation with either a Gables G7406-02 or Avtech 7522-1-2 VHF COMM Receiver Transmitter Control Series using with Collins Installation Instructions as listed on AML No. ST00525WI-D, or later FAA approved revisions.. Rockwell Collins Inc
- [STC ST00626CH](https://openairdocs.org/stc/ST00626CH): Installation of replacement immersion heater.. Aircraft Food Service Equipment Repair

All 78: https://openairdocs.org/tcds/A49EU/stcs.md

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