# TCDS A24EU: BAE Systems (Operations) Limited

- Type: Type certificate data sheet
- Status: Current
- Holder: BAE Systems (Operations) Limited
- Revision: 8
- Revised: July 29, 2011
- Product: Aircraft, Large Airplane
- Certification basis: Part 21, Part 25, Part 26, Part 36
- Registered aircraft: 2, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/45/54/4554635947f3fe580da25d8a3769fc3ab20df12a6e300ca93f2bfc4fe4ca1828
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4B12CA89790612E6862578DC00695949.0001
- Page: https://openairdocs.org/tcds/A24EU

## Models (2)

As the data sheet lists them.

- HS 748 Series 2B
- HS 748 Series 2A

## What the data sheet says

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

```text
DEPARTM
ENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A24EU 
BRITISH AEROSPACE 
Revision 8 
HS 748 Series 
2A 
2B 
 
July 29, 2011 
 
TYPE CERTIFICATE DATA SHEET NO. A24EU 
 
This data sheet which is a part of type certificate No. A24EU 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 
 
 
I - Model HS 748 Series 2A (Transport Category) Approved 7 April 1972 
 
Engines 2 Rolls-Royce Dart MK 532-2L Turbo-Propeller. 
Reduction gear ratio:  0.093 to 1. 
or  
2 Rolls-Royce Dart MK 535-2 Turbo Propeller. 
Reduction gear ratio:  0.093 to 1. 
 
Fuel  Aviation Kerosene Specifications (as revised): 
 
American MIL-T-5624 (Grade JP-5) 
ASTM D.1655-68 Jet A or Jet A-1 
 
I.A.T.A. Kerosene type fuel 
Canadian 3-GP-23.  Kerosene type. 
British D.Eng.R.D. 2494, 2498 or 2453. 
 
Note:  The following departures from specification, D.Eng.R.D. 2494 are acceptable. 
 
Flash Point - Minimum 70°F 
Mercaptan sulphur percentage weight maximum 0.005% by weight. 
 
Aviation wide-cut fuel specification (as revised): 
 
American MIL-T-5624 (Grade JP-4) 
ASTM D. 1655 Jet-B 
 
I.A.T.A. Wide-cut (JP-4) Type fuel Canadian 3-GP-22. 
wide-cut type.  British D.Eng.R.D. 2486 or 2454. 
Page No. 1 2 3 4 5 6 7 8 9 
Rev. No. 5 5 5 5 5 7 6 7 8

A24EU   - 2 - 
Engine Limits: 
  
 
Rating 
 
Shaft 
HP 
 
Jet 
Thrust 
 
Engine 
r.p.m. 
 
Propeller 
r.p.m. 
Turbine Gas 
Temperature 
C 
Rolls Royce Max. Takeoff      
Dart MK 532-
2L 
(WET)  2040 520 15000 1395 905 
 (DRY) 1835 485 15000 1395 810 
       
 Max. 
Continuous 
1835 485 15000 1395 920 
       
Rolls Royce Max. Takeoff      
Dart MK 535-2 (WET) 2040 520 15000 1395 920 
 (DRY) 1835 485 15000 1395 810 
       
 Max. 
Continuous 
2030 485 15000 1395 920 
 
Propeller and Limits: 2 Dowty Rotol Type CR.212/4-30-4/22 or CR 251/4-30-4/49, R.A.  
25953-1 Blades 
Diameter 12 feet 
Pitch settings at 0.7 radius station 
Ground Fine 0° Fine 18°, feathered 84°21', Low pitch warning 16°.   
Restricted speed range:  Continuous  operation between 8500 and 9500 engine 
r.p.m. is to be avoided during ground operations. 
 
Airspeed limits: Vmo (Maximum Operating) 
From sea level to  15000 feet 225 kts. 
Above  15000 feet 215 kts. 
 
Va  (Maneuvering)   155 kts. 
 
Vfe (Flap Speeds) 
Flap deflection  7 1/2°  180 kts. 
Flap deflection 15°  180 kts. 
Flap deflection 22 1/2° 140 kts. 
Flap deflection 27 1/2° 120 kts. 
 
Vlo (Landing Gear Operation) 
Operation 160 kts. 
Extended 160 kts. 
 
Vllo (Landing Light Operation) 
Operation 140 kts. 
Extended 140 kts. 
 
Vmc (Minimum Control Speed) 
82 kts. (Flaps 0 < 22 ½ O) 
81 kts. (Flaps = or >22 1/2°)

3 A24EU 
C.G. range: Landing gear retraction moment - 68,564 lb. in. (Nose down) 
(Landing gear extended) 
 
 Forward Aft 
Weight 
   (lb.) 
% 
S.M.C. 
Aft of 
Datum 
(ins) 
% 
S.M.C. 
Aft of 
Datum (ins) 
24,000 12.20 57.00 32.20 76.78 
27,000 12.20 57.00 32.20 76.78 
30,000 13.70 58.50 32.20 76.78 
40,000 19.00 63.75 35.20 79.80 
44,495 21.30 66.00 35.20 79.80 
Straight line variation between weights 
 
Maximum weights: Maximum Take-off weight 44,495 lb. 
Maximum Landing Weight 43,000 lb. 
Maximum Zero Fuel Weights 37,500 lb. 
38,500 lb. (with Modification 4080) 
 
Maximum baggage: Baggage holds located  according to the passenger layout. 
 
Between fuselage formers 252 in. forward and 126 in. forward of the fuselage 
datum the maximum permissible floor loading is 110 lb. per sq. ft. over full 
width of fuselage, or 155 lb. per sq. ft. with an unloaded 20 inch central aisle. 
 
Between fuselage formers 126 in. forward of the fuselage datum to 306 in. aft of 
fuselage datum the maximum permissible floor loading is 100 lb. per sq. ft. over 
full width of fuselage, or 130 lb. per sq. ft. with an unloaded 20 inch central 
aisle. 
 
Control surface movements: Elevator Up 22° Down 8.5° 
Trim Tabs Up   7° Down 10° 
Geared Tab Up   3.4° Down   8.8° 
  (0.4 Basic Gearing) 
 
Rudder  Right 20° Left 20° 
Spring Tab Right 28° Left 28°(Rudder Locked)   
Trim Tab Right 19.5° Left 13.5° 
 
Ailerons Up 18.5° Down 18.5° 
Trim Tabs Up 10° Down 10° (Starboard Aileron Only) 
Geared Tabs Up   9° Down   9° (0.45 Basic Gearing) 
 
Flaps    27.5° total angle of travel 
 
The rigging instructions including tolerances are given in the CAA Approved 
Maintenance Manual.

A24EU   - 4 - 
II - Model HS 748 Series 2B (Transport Category) Approved December 19, 1980 
 
Engines 2 Rolls-Royce Dart MK 535-2 Thrub-Propeller. 
Reduction gear ratio:  0.093 to 1. 
 
Fuel See Section I. 
 
Engine limits See Section I. 
 
Propeller and Limits: See Section I. 
 
 
Airspeed limits (I.A.S.) Vmo (Maximum Operating) 
From sea level to  15,000 feet 220 kts .225 kts. (with Mod. 6751) 
Above  15,000 feet 215 kts. 
 
Va  (Maneuvering) 155 kts. 
 
Vfe (Flap Speeds) 
Flap deflection  7 1/2° 180 kts. 
Flap deflection 15° 180 kts. 
Flap deflection 22 1/2° 140 kts. 
Flap deflection 27 1/2° 120 kts. 
 
Vlo (Landing Gear Operation) 
Operation 160 kts. 
Extended 160 kts. 
 
Vllo (Landing Light Operation) 
Operation 140 kts. 
Extended 140 kts. 
 
Vmc (Minimum Control Speed) 
82 kts. (Flaps 0 < 22 ½ O) 
81 kts. (Flaps = or >22 1/2°) 
 
C.G. range Landing gear retraction moment - 68,564 lb. in. (Nose down) 
(Landing gear extended) 
 Forward Aft 
Weight 
   (lb.) 
% 
S.M.C. 
Aft of 
Datum 
(ins) 
% 
S.M.C. 
Aft of 
Datum (ins) 
24,000 12.20 57.00 32.20 76.78 
27,000 12.20 57.00 32.20 76.78 
30,000 13.70 58.50 32.20 76.78 
38,500 18.20 63.00 37.80 82.30 
46,500 22.30 67.00 37.80 82.30 
Straight line variation between weights 
 
Maximum weights Maximum Takeoff weight 46,500 lb. 
Maximum Landing Weight 43,000 lb. 
Maximum Zero Fuel Weights 37,500 lb. 
38,500 lb. (with Modification 4080)

5 A24EU 
 
Maximum baggage Baggage holds located  according to the passenger layout. 
 
Between fuselage formers 252 in. forward and 198 in. aft of the fuselage datum, 
the maximum permissible floor loading is 200 lb. per sq. ft. over full width of 
fuselage except the areas between fuselage formers 162 in. forward and 180 in. 
aft outside a 34 in. center aisle where th e maximum permissible floor loading is 
150 lb. per sq. ft. 
 
Between fuselage formers 198 in. aft and 306 in. aft of fuselage datum the 
maximum permissible floor loading is 100 lb. per sq. ft.  
 
Control surface movements Elevator Up 22  Down   8.5  
Trim Tabs Up   7° Down 10° 
Geared Tab Up   4.25° Down 11°(0.4 Basic Gearing) 
 
Rudder  Right 20° Left 20° 
Spring Tab Right 28° Left 28° (Rudder Locked) 
Trim Tab Right 19.5° Left 13.5° 
 
Ailerons Up 18.5° Down 18.5° 
Trim Tabs Up 10° Down 10°  (Starboard Aileron Only) 
Geared Tabs Up   6.5° Down   6.5°  (0.35 Basic Gearing) 
 
Flaps    27.5° total angle of travel 
 
The rigging instructions including tolerances are given n the CAA Approved 
Maintenance Manual. 
 
DATA PERTINENT TO ALL MODELS 
 
Minimum crew: 2 - (Pilot and Co-Pilot) 
 
Maximum passengers: 50 with one (1) flight a ttendant 52 with two (2) flight attendants 
 
Maximum operating altitude: 25,000 ft. 
 
Fuel capacity: Two integral wing fuel tanks each 840 U. S. gallons.  Moment arm plus 82.3 in. (i.e. aft 
of C.G. datum point).  See NOTE 1(b) for data on system fuel and oil. 
 
Oil capacity: Two oil tanks each 3.977 U.S. gallons capacity, including propeller feathering oil of 1.20 
U.S. gallons.  The oil tank is integral with the Rolls-Royce Dart Engines.  Moment arm - 
48.0 in. (i.e. forward of C.G. datum point).  See NOTE 1 (b) for data on system fuel and 
oil. 
 
Datum: Zero moment datum located on the center line of the aircraft 108.3 in. forward of the 
fuselage and datum (the datum face of the fuse lage former at the rear spar).  The C.G. 
datum point is a mushroom headed bolt marked C.G. origin on each side of the fuselage.  
The C.G. datum point is also 263.7 in. aft of the extreme forward tip of the fuselage and 
108.3 inches forward of the fuselage datum.

A24EU   - 6 - 
 
Standard mean chord:  The standard mean chord is 98.77 in. and the leading edge of the standard mean 
chord (S.M.C.) is 43.15 in aft of the C.G. datum. 
 
Leveling means: The seat rail in the forward fuselage adjacent to the forward freight door. 
 
Other operating limitations:  Aircraft shall be operated in compliance with the operating limitations 
specified in the  CAA Approved Flight Manual Document No. A01.10. 
 
1.  Series 2A with Rolls Royce Dart MK 532-2L engines installed, 
Amendments G/5 and P/3 of AFM are required. 
 
2.  Series 2A with Rolls Royce Dart MK 535-2 engines installed, 
Amendment G/5 of AFM are required. 
 
3.  Series 2B with Rolls Royce Dart MK 535-2 engines installed, 
Amendments G/5 and P/4 are required. 
 
Certification basis: FAR 21.19, FAR 25, effective 1 February 1965, including Amendments 25-1 
through 25-20, Special Conditions No. 25-24-EU-4 dated 9 June 1970. 
 
Part 26 of the Federal Aviation Regulations: 
  Per 21.29(a), applicable provision of part 26. 
 
FAR 36, effective 1 December 1969, including Amendments 36-1 through 36-9. 
 
Compliance with FAR 25, Amendments 25-7 through 25-20 which were not 
required based on the effective appli cation date in accordance with FAR 
21.17(c)(2) was elected by the manufacturer in accordance with FAR 21.17(d). 
Type Certificate No. A24EU, issued 7 April 1972.  Effective Date of 
Application for Type Certificate per FAR 21.17(c)(2):  7 April 1967. 
Compliance with FAR 25.1419 has been shown. 
 
Exemption No. 9802 docket No FAA-2008-0738 concerning EAPAS 26.11, AASR 
26.43, 26.45, and 26.49. 
 
Pursuant to FAR 21.29(a)(1)(ii), Type Certificate A24EU was issued in 
validation of the United Kingdom Civil Aviation Authority Certification of 
Compliance with the following standards which were found to provide a level of 
safety to the above "Certification Basis". 
 
1. BCAR Sections D and J in effect on 15 September 1966. 
 
2.   FAA additional requirements lis ted in ARB Validation Arrangements 
(V.A. Note 1) Issue 2, dated 21 May 1967. 
 
3.   Revised paragraphs of FAR 25 as amended by Amendments 25-7 
through 25-20. 
 
4.   Special Conditions No. 25-24-EU-4 dated 9 June 1970. 
 
5. FAR 36 effective 1 December 1969, including Amendments 36-1 
through 36-9.

7 A24EU 
   
Serial Nos. eligible: The United Kingdom Certificate of Airworthiness for Export endorsed as noted 
under "Import Requirements" must be submitted for each indivi dual aircraft for 
which application of certification is made. 
Transition Statement: The United Kingdom Civil Aviation Authority originally type certificated this 
aircraft under its type certificate Number AAN10059 (HS 748 Series 2A) and 
ANN16479 (HS 748 Series 2B) .  The FAA validated this product under U.S. 
Type Certificate Number A24EU.   Effective September 28, 2003, the European 
Aviation Safety Agency (EASA) began oversight of this product on behalf The 
United Kingdom.  
Import requirement 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 the 
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.  A24EU 
and to be in a condition for safe operation.’  
 
The U.S. airworthiness certification basis for aircraft type certificated under 
FAR Section 21.29 and exported by the country of manufacture is FAR 
Sections 21.183(c) or 21.185(c).  The U.S. airworthiness certification basis for 
aircraft type certificated under FAR Section 21.29 but exported from 
countries other than the country of ma nufacture (e.g., third party country) is 
FAR Sections 21.183(d) or 21.183(b).  These sections provide that U.S. 
airworthiness certification are issued only if the Administrator finds, “that the 
aircraft conforms to the type design and is in a condition for safe operation.” 
 
In order for the FAA to make the finding that an HS 748 aircraft is in a 
condition for safe operation, the FAA certificating inspector or other 
authorized person must contact the Manager, International Branch, ANM-
116, FAA Transport Airplane Director ate; 1601 Lind Avenue Southwest; 
Renton, Washington 98055; telephone (425) 227-1263; fax (425) 227-1149, 
prior to issuance of the U.S. airworthiness certificate to obtain the FAA 
Required Modification List (RML) for the HS 748. Prior to issuance of a 
Standard Airworthiness Certificate on any HS 748 model aircraft, all 
modifications shown in the model HS 748 RML must be accomplished in the 
interest of safety before the aircraft can be found to be in a condition for safe 
operation. 
 
Authority for these required modifications is given per the airworthiness 
certification provisions of 49 U.S.C. 44704 (c), which states "the 
Administrator may include in an airworthiness certificate terms required in 
the interest of safety".  “Terms required in the interest of safety” include 
actions to correct unsafe conditions issued by the foreign authority of the state 
of design that also meet FAA criteria for corrective action. This law also gives 
the FAA the authority to adopt FAR § 21.183(c) and (d), which form the 
regulatory basis for the issue of standard U.S. airworthiness certificates on 
imported products. 14 CFR §21.183(c) and (d) provide that airworthiness 
certificates are issued only if the Administrator finds “that the aircraft 
conforms to the type design and is in a condition for safe operation.” The 
modifications identified in the Model HS 748 RML are required in the interest 
of safety and are necessary for this airplane to be in a condition for safe 
operation.

A24EU   - 8 - 
A Notice of  policy Statement announcing the FAA’s policy with respect to 
foreign mandatory continued airworthiness information, when no aircraft of 
the affected design are currently operating in the U.S. was published in the 
Federal Register on May 1, 1998.  A dditional guidance is contained in the 
FAA advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, 
Engines, Propellers, and Related Products Imported  into the United States. 
 
 
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 United Kingdom Civil 
Aviation Authority or JAA Design Organization Approval No. CAA.JA.02034  
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 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 Civil Aviation Authority or US/EASA Bilateral 
Aviation Safety Agreement Implementation Procedures for Airworthiness must 
be approved by the FAA. 
 
 
Equipment The basic required equipment as pr escribed in the applicable airworthiness 
regulations (see Certification Basis) must be installed in the aircraft for 
certification.  Approved equipment is included in the Schedule of Equipment 
Drawing No. A 3767. 
 
In addition, the following items of equipment are required. 
 
Control Column stick shaker Safe Flight - Pt. No. C74002  
Lift Transducer    Safe Flight - Pt. No. C74007 (2 required).

9 A24EU 
NOTES: 
 
NOTE 1. (a)  Current weight and balance report, including list of equipment included in the 
certificated empty weight and loading instructions when necessary, must be in each 
aircraft at the time of original certification. 
 
(b)  "Unusable Fuel and System Oil"  and all hydraulic fluid must be included with 
certificated empty weight. 
Unusable fuel is that quantity of fuel in the system and in the tanks which is unavailable 
to the engine under critical f light conditions as defined in FAR 25.959. This unusable 
fuel includes "system fuel" which is defined as the quantity required to fill the system 
and tanks outlet level when the airplane is in the ground level attitude.  The fuel gauges 
are calibrated to read zero during level flight with the unusable fuel in the tanks. 
 
  The total amount of fuel is as follows: 
 
Usable Fuel   Unusable Fuel  
@ 6.75 lb./gal.  @ 6.75 lb./gal.  
 
1680 U.S. gallons 3.6 U.S. gallons 
 
System Oil is that amount of oil required to fill the oil system and tanks which is not 
available for normal engine lubrication.  The propeller feathering oil is not considered 
usable oil and is included in "System Oil".  System oil weight is 37 lb. The oil tank 
capacity shown in this specification is the to tal oil for which the tanks are placarded.  
Dipstick readings indicate the amount of oil required to fill the tank. 
 
NOTE 2. All placards required in the Approved Airp lane Flight Manual must be installed in the 
appropriate location. 
 
NOTE 3. The service life for aircraft  structural parts which are fati gue critical are listed in the HS 
748 Recommended Maintenance Schedule, page s 12 to 18 inclusive, and may not be 
changed without FAA approval. 
 
NOTE 4. The approval fuel additives are listed in the CAA Approved Flight Manual Document 
A01.10. 
 
 
.....END.....
```

## ADs (54, first 50, in force first)

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- [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 2011-05-10](https://openairdocs.org/ad/2011-05-10): Flight Controls · BAE Systems ATP, HS 748 Series 2A and HS 748 Series 2B. Effective Mar 25, 2011
- [AD 2009-11-07](https://openairdocs.org/ad/2009-11-07): Fuel · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jun 12, 2009
- [AD 2006-03-11](https://openairdocs.org/ad/2006-03-11): Elevator gust lock · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Feb 24, 2006
- [AD 2005-23-22](https://openairdocs.org/ad/2005-23-22): Rear pressure bulkhead · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Dec 6, 2005
- [AD 2005-20-34](https://openairdocs.org/ad/2005-20-34): Battery earth posts. · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Oct 27, 2005
- [AD 2005-19-26](https://openairdocs.org/ad/2005-19-26): Fuel cross feed system · BAE Systems ATP, HS 748 Series 2A and HS 748 Series 2B. Effective Oct 12, 2005
- [AD 2005-19-13](https://openairdocs.org/ad/2005-19-13): Nose landing gear (NLG) · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Oct 6, 2005
- [AD 99-19-13](https://openairdocs.org/ad/99-19-13): AFM - Limitations Section - Ice Protection System · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Dec 27, 1999
- [AD 98-07-22](https://openairdocs.org/ad/98-07-22): AFM - Limitations Section - Stop Lever · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Apr 16, 1998
- [AD 98-06-09](https://openairdocs.org/ad/98-06-09): Inspect Aileron Operating Arm Bracket · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Mar 30, 1998
- [AD 98-03-17](https://openairdocs.org/ad/98-03-17): Inspect Aileron, Rudder and Elevator Gust Locks · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Feb 23, 1998
- [AD 98-01-05](https://openairdocs.org/ad/98-01-05): Aileron Cable Support Block · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jan 15, 1998
- [AD 97-25-13](https://openairdocs.org/ad/97-25-13): Inspect Main Hydraulic Accumulator for Corrosion · BAE Systems ATP, HS 748 Series 2A and HS 748 Series 2B. Effective Jan 14, 1998
- [AD 97-26-05](https://openairdocs.org/ad/97-26-05): Inspect Inspection Locations · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jan 2, 1998
- [AD 97-23-03](https://openairdocs.org/ad/97-23-03): Bearing Cap Attachment Bolts · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Nov 19, 1997
- [AD 97-20-05](https://openairdocs.org/ad/97-20-05): Aileron Cable Pulley Guard & Rubbing Strips · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Oct 15, 1997
- [AD 96-25-12](https://openairdocs.org/ad/96-25-12): Auxiliary Power Units · BAE Systems HS 748 Series 2A, HS 748 Series 2B, 707-100 Long Body and 74 more. Effective Jan 13, 1997
- [AD 96-20-09](https://openairdocs.org/ad/96-20-09): Flight Control Cable Tension Regulators · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Oct 25, 1996
- [AD 96-09-20](https://openairdocs.org/ad/96-09-20): AFM - Icing · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jun 11, 1996
- [AD 94-23-08](https://openairdocs.org/ad/94-23-08): Nose Landing Gear and Main Landing Gear · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Dec 6, 1994
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- [AD 87-26-07](https://openairdocs.org/ad/87-26-07): Escape Hatch Locking Mechanism · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Feb 1, 1988
- [AD 87-25-11](https://openairdocs.org/ad/87-25-11): Bearing Installations · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jan 25, 1988
- [AD 87-25-13](https://openairdocs.org/ad/87-25-13): Nose Landing Gear · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jan 25, 1988
- [AD 87-25-06](https://openairdocs.org/ad/87-25-06): Jet Pipe Manifold · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jan 19, 1988
- [AD 87-25-07](https://openairdocs.org/ad/87-25-07): Engine Support Structure · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jan 19, 1988
- [AD 87-22-05](https://openairdocs.org/ad/87-22-05): Freight Door Lever · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Nov 13, 1987
- [AD 86-14-09](https://openairdocs.org/ad/86-14-09): Microswitch Rocker Arm Assemblies · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Aug 4, 1986
- [AD 86-10-06](https://openairdocs.org/ad/86-10-06): Overwing Escape Hatches · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jun 16, 1986
- [AD 86-09-04](https://openairdocs.org/ad/86-09-04): Emergency Lighting System · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective May 26, 1986
- [AD 86-07-05](https://openairdocs.org/ad/86-07-05): Wing Structure · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective May 8, 1986
- [AD 86-06-05](https://openairdocs.org/ad/86-06-05): Windshield Actuating Arm · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective May 2, 1986
- [AD 85-03-05](https://openairdocs.org/ad/85-03-05): Baggage Door · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Mar 11, 1985
- [AD 83-26-01](https://openairdocs.org/ad/83-26-01): Unsafe Condition Prevention · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jan 30, 1984
- [AD 83-24-08](https://openairdocs.org/ad/83-24-08): Wing Structure · BAE Systems HS 748 Series 2A. Effective Jan 15, 1984
- [AD 83-26-04](https://openairdocs.org/ad/83-26-04): Lock Levers Replacement · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Jan 11, 1984
- [AD 83-24-01](https://openairdocs.org/ad/83-24-01): Wing Structure · BAE Systems HS 748 Series 2A. Effective Dec 23, 1983
- [AD 83-23-06](https://openairdocs.org/ad/83-23-06): Engine Subframe Struts · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Dec 15, 1983
- [AD 83-17-03](https://openairdocs.org/ad/83-17-03): Rib/Stringer Bracket Fasteners · BAE Systems HS 748 Series 2A. Effective Sep 19, 1983
- [AD 83-15-01](https://openairdocs.org/ad/83-15-01): Relay Replacement Check · BAE Systems HS 748 Series 2A. Effective Aug 1, 1983
- [AD 82-25-06](https://openairdocs.org/ad/82-25-06): Cabin Wiring · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Dec 6, 1982
- [AD 82-19-04](https://openairdocs.org/ad/82-19-04): Overwing Exit Panel · BAE Systems HS 748 Series 2A. Effective Sep 28, 1982
- [AD 81-15-52 R1](https://openairdocs.org/ad/81-15-52-R1): Securing Of Entry/Cargo Doors · BAE Systems HS 748 Series 2A and HS 748 Series 2B. Effective Sep 9, 1981
- [AD 77-23-02](https://openairdocs.org/ad/77-23-02): Propeller Feathering System · BAE Systems HS 748 Series 2A. Effective Dec 7, 1977

All 54: https://openairdocs.org/tcds/A24EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [British Aerospace HS-748-2A](https://openairdocs.org/model/british-aerospace-hs-748-2a): 2 aircraft (registry code 1500249)
- [British Aerospace HS748 SERIES 2B](https://openairdocs.org/model/british-aerospace-hs748-series-2b): 0 aircraft (registry code 1500248)
- [Hawker Siddeley HS.748 SERIES 2A](https://openairdocs.org/model/hawker-siddeley-hs-748-series-2a): 0 aircraft (registry code 4231008)

## STCs approved under this data sheet (12)

- [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center
- [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 SA3956NM](https://openairdocs.org/stc/SA3956NM): Installation of Floor Proximity Emergency Escape Path Marking System. Bruce Aerospace Inc.
- [STC ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited
- [STC ST02632LA](https://openairdocs.org/stc/ST02632LA): Modification to replace the existing Mode S Transponder system with ACSS NXT-700 Mode S Transponder with ADS-B Out and optionally install ACSS NXG-900 GPS as a position source for ADS-B Out. Aviation Communications and Surveillance Systems
- [STC SA302WE](https://openairdocs.org/stc/SA302WE): Incorporate a de-icing system (as manufactured by applicant) externally on Rotol propeller spinner as an alternate to Dowty Rotol internal elements. If applied to original spinner, Montgomery Systems Tech., Inc. P/N 72196-2 will apply. If applied to a new aluminum nose spinner P/N 72196-1 will apply. Dowty Rotol Service Bulletin Section 61-170 pages 1 and 2 outlines a revised spinner de-icing system. This is a Napier external system. Approval of the A.R.B. is indicated. (Continued on page 3). ROBERT W. MURRAY
- [STC SA4574NM](https://openairdocs.org/stc/SA4574NM): Installation of a de-icing system on the Rolls Royce P/N RK29954A or P/N RK48279A (MO) 1800 engine inlet cowl.. ROBERT W. MURRAY
- [STC SA1474NM](https://openairdocs.org/stc/SA1474NM): Installation of galley, P/N ATI75201. Gottlieb Corporation dba Air Transport Industries
- [STC SA2944WE](https://openairdocs.org/stc/SA2944WE): Installation of DeVore emblem lights on horizontal stabilizer tips.. DeVore Aviation Corporation of America, a New Mexico Corporation
- [STC ST00291NY](https://openairdocs.org/stc/ST00291NY): Installation of windscreen heat relay replacement.. Northern Aero Industries
- [STC SA45GL](https://openairdocs.org/stc/SA45GL): Install AMF inverter MGH 549-1.. Leland Electrosystems, Inc
- [STC SA125GL](https://openairdocs.org/stc/SA125GL): Installation of Plessey Company P/N 612-1-39863 ground proximity warning system.. Air Illinois, Inc

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