# TCDS A27NM: BAE Systems (Operations) Limited

- Type: Type certificate data sheet
- Status: Current
- Holder: BAE Systems (Operations) Limited
- Revision: 5
- Revised: July 29, 2011
- Product: Aircraft, Large Airplane
- Certification basis: Part 21, Part 25, Part 26, Part 27, Part 36
- Data sheet PDF: https://openairdocs.org/files/sha256/7f/2e/7f2e9f246fafd5d26d1d299cffbc98a0bb56fad19041c36498aa9084b09cb8ac
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DCC761BB5475AD7D862578DC006985D7.0001
- Page: https://openairdocs.org/tcds/A27NM

## Models (1)

As the data sheet lists them.

- ATP (BAE ATP)

## 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 
Rev. No. 2 1 1 1 3 5 5 5 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A27NM 
Revision 5 
BAE Systems 
Model ATP 
July 29, 2011 
 
TYPE CERTIFICATE DATA SHEET NO. A27NM 
 
This data sheet, which is part of Type Certificate No. A27NM, 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 
 
 
British Aerospace ATP (Transport Category) approved August 31, 1988; 
 
Engines: Two Pratt & Whitney Canada , Model PW 124A, or  
Model PW 126A, (Modification 05000A)  
Turbo Propeller, Reduction gear ratio:  0.06 to 1. 
 
 
Engine Limits:   PW 124A 
 ENGINE  /  PROPELLER   OPERATING     LIMITS 
OPERATING 
CONDITION 
MAX 
TORQ   
(g)  
MAX 
NP (a)  
 
MAX 
NH  
 
MAX 
NL 
 
MAX 
ITT   
 
OIL 
PRESSURE  
 
OIL (b) 
TEMP   
 
TIME 
LIMIT 
 % % % % C PSI C  
Maximum 
Takeoff 
97.7 101.0 101.5 102.4 800 56 to 64 (c) 0 to 115 5 minutes 
Maximum 
Continuous 
90.8 101.0 101.5 102.4 800 56 to 64 (c) 0 to 115 unlimited 
Normal 
Takeoff 
87.9 101.0 101.5 102.4 770 56 to 64 (c) 0 to 115 5 minutes 
Min Idle - - Min 66 - - Min 41(d) -40 to 115 (f) unlimited 
Starting - - - - 950 (e) - Min -54 - 
Transient 120.0 115.0 - - 840 41 to 100 - 20 seconds 
Other - - - - - - Max 120 20 minutes 
 
 
Engine Limits:  PW 126A (Modification 05000A) 
Maximum 
Takeoff 
108.3 
(h) 
101.0 102.1 103.8 800 56 to 64 (c) 0 to 115 5 minutes 
Maximum 
Continuous 
108.3 
(h) 
101.0 102.1 103.8 800 56 to 64 (c) 0 to 115 unlimited 
Normal 
Takeoff 
108.3 
(h) 
101.0 100.6 101.5 765 56 to 64 (c) 0 to 115 5 minutes 
Min Idle - - Min 66 - - Min 41 (d) Max 115 unlimited 
Starting - - - - 950 (e) - Min  -54 - 
Transient 120.0 115.0 103.1 103.8 840 41 to 100 - 20 seconds 
Other - - - - - - Max 120 20 minutes

A27NM 2
NOTE: MAXIMUM TAKEOFF rating is the maximum certif ied for takeoff operation.  This rating is  
referred to as Max Contingency in airplane markings and the Airplane Flight Manual.  When the TAKEOFF 
mode is selected the MAXIMUM TAKEOFF rating is available through actuation of the fuel control 
Automatic Takeoff Power Control System (ATCPS) when engine is operating at the NORMAL TAKEOFF 
rating or manually by throttle movement. 
 
NORMAL TAKEOFF rating is the maximum thrust to be set for takeoff operation with the aircraft 
Automatic Takeoff Power Control System (ATPCS) operative.  This rating is referred to asTakeoff in 
airplane markings and the Airplane Flight Manual.  When set, this rating ensures that the MAXIMUM 
TAKEOFF rating will be achieved upon actuation of ATPCS. 
 
(a) Overspeed due to propeller system malfunction permissible up to 115% for Max 15 minutes subject to 
maintenance action. 
(b) Oil temperature must be maintained above 45C to ensure protection against intake icing. 
(c) Below 56 psi reduce power (NH less than 75%), below 41 psi shutdown. 
(d) Below flight idle. 
(e) 5 seconds 
(f) Power above flight idle not allowed for oil temperature below 0C. 
(g) Never exceed torque limit (excluding transients) - 103.9% at a maximum NP of 85%. 
(h) The above limitations are defined by the torque capacity of the engine/gearbox combination.  The 
torque settings for normal operation are given in the airplane flight manual. 
Fuel: 
 Grade (Type)  Specification  
 Kerosene Type D Eng RD 2453 Issue 4 Am 1 
 (AVTUR:JP1) D Eng RD 2494 Issue 8 Am 1 
  ASTM D1655-74 Jet A 
  ASTM D1655-74 Jet A-1 
  3-GP-23h 
  IATA Nov 1978: Kerosene Type 
   
 Wide Cut Fuels D Eng RD 2454 Issue 4 Am 1 
 (AVTAG:JP4) D Eng RD 2486 Issue 9 Am 1 
  ASTM D1655 
  IATA Nov 1978 JP 4 type 3-GP-22h 
  MIL-T-5624J JP4 grade 
  AIR 3407/8 (French) 
  TL 9130-006 Issue 4 (German) 
  CAN 2-3 22M 78 (Canadian) 
   
 High Flash Point D Eng RD 2498 Issue 7 
 (AVCAT:  JP5) D Eng RD 2452 Issue 2 
  3-GP-24g (Canadian) 
  MIL-T-5624J  JP5 grade 
  AIR 3404/C (French) 
  TL 9130-007 Issue 4 (German) 
   
 Emergency Fuels MIL-G-5572 aviation gasoline 
  Limited to 150 hours use. 
  Engines to be removed for overhaul after this time period. 
 
Fuel Temperature Limits:  Aircraft must not be operated with fuel temperature exceeding 54 C or below -48C.

A27NM 3
Propeller and Propeller Limits: Two British Aerospace Hamilton Standard 6/5500/F-1. 
Diameter   13.75 feet. 
Pitch settings at 0.75 radius station. 
Maximum reverse   -16,  Ground Idle   -7.9 
Flight Idle  12.5  
Takeoff  10.5 
Low pitch warning below 10, Feathered  76 
 
Speed range: Takeoff, maximum continuous  and maximum takeoff 1,212 rpm.   
Climb and cruise 1,020 rpm.  Flight Range 950 to 1,212 rpm. Quiet taxi 
mode 825 to 1,212 rpm.  
Any ground check requiring continuous operation above 920 prop rpm or 
between 620 and 720 prop rpm is prohibited except for pre-flight checks 
of short duration. 
 
Airspeed Limits: V MO  (Maximum  Operating) 
227 knots IAS  at sea level increasing linearly to  
230 knots IAS up to 15,000 ft. 
220 knots IAS above 15,000 ft increasing linearly to 
221 knots IAS up to 22,000 ft decreasing linearly to 
208 knots IAS at 25,000 ft. 
VA  (Maneuvering - flaps retracted) 
170 knots IAS at all altitudes 
VFE    (Flap Speeds) 
180 knots IAS   7  flap 
180 knots IAS 15  flap 
150 knots IAS 20  flap (with Mod 05000A) 
140 knots IAS 22  flap 
130 knots IAS 27  flap 
140 knots IAS 29  flap (with Mod 05000A) 
VLO    (Landing Gear Operation) 
180 knots IAS  Lowering 
150 knots IAS Retraction 
VLE  (Landing Gear Extended) 
180 knots IAS 
 
VMC  Minimum Control Speeds: 
In the air, VMC= 97 knots IAS 0  or 7 flap 
92 knots IAS 15  flap 
On or near the ground Vmcg = 99 knots IAS   7  flap up to 38,500 lbs increasing linearly to 
101.5 knots IAS at 50,500 lbs 
 
With 15 flap Vmcg =  95 knots IAS        at 38,500 lbs. increasing linearly to  
100 knots IAS        at 50,550 lbs. 
 
  During landing Vmcl =  90 knots IAS with 20  flap (with Mod 05000A) 
90 knots IAS with 22  flap 
88 knots IAS with 27  flap 
88 knots IAS with 29  flap (with Mod 05000A)

A27NM 4
CG Range (Landing Gear Extended): 
 Landing Gear Retraction Moment - 81,719 lb. in. 
Weight  
(lb) 
Forward 
(In Flight) 
Forward 
(Takeoff & Landing) 
 
AFT 
 Aft of Datum (ins) Aft of Datum (ins) Aft of Datum (ins) 
28,000 49.0 51.4 66.5 
30,000 - - 66.5 
33,070 49.0 - - 
33,400 - 51.4 - 
38,000 - - 75.5 
46,800 60.05 62.2 76.85 
50,550 61.7 63.7 77.25 
Straight line variations between weights. 
 
NOTE:With 27 or 29 flap selected for landing, the forward CG limit is 58.0 inches aft of 
Datum below 41,430 lbs. 
 
Maximum Weights: Maximum Ramp Weight  50,700 lbs 
Maximum Takeoff Weight 50,550 lbs 
Maximum Landing Weight 49,050 lbs 
Maximum Zero Fuel Weight 46,800 lbs 
 
Maximum Baggage: Baggage hold located according to passenger layout. 
 
Between fuselage formers 378 in. forward and 252 in. forward of the fuselage datum, maximum 
permissible floor loading is 100 lb/ft2 over the full width of the fuselage and a maximum load of 
1,700 lbs. 
 
Between fuselage formers 308 in. aft and 378 in. aft of the fuselage datum, maximum permissible 
floor loading is 100 lb/ft2 over the full width of the fuselage and a maximum load of 2,325 lbs. 
 
Flying Control Surface Angular Travel: 
      Rudder  19  + 1 -    0   Right 19  + 1 -  0       Left 
            Spring Tab (rudder locked)  20  +  3 - 1.5  Right 20  + 3 -1.5      Left 
Geared Trim Tab (trim movement)    9.15  + 1 - 0 Right 15.15  + 1 - 0  Left 
 
             Ailerons 20     0.5 Up 20 + 0.5   Down 
      Trim Tabs (right aileron only) 15.5  + 1.5 - 0 Up 15.5 + 1.5  - 0 Down 
       Geared Tabs   5                Up 1  to 3.5 Down 
 
                     Elevator 22  + 1 - 0  Up 13.5  + 1 - 0 Down 
       Tab (Balance mode) 5.0    1 Up 8.1   1 Down 
             Tab (trim mode) 3.2    1 Up 11.2  1 Down 
Flaps total angle of travel 27 or 29 (with Mod 05000A)  The rigging instructions including 
tolerances are given in the Manufacturers Recommended Maintenance Manual. 
 
Minimum Crew:   2 - Pilot and Co-pilot 
 
Maximum Passengers:  68 
 
Maximum Operating Altitude: 25,000 ft 
 
Fuel Capacity: Two integral wing fuel tanks each of 854 US usable gallons capacity.  Moment arm  plus 
82.3 in. (i.e. aft of CG datum point). 
Maximum fuel density 7.1 lb/U.S. gallon 
Minimum fuel density 6.0 lb./ U.S. gallon

A27NM 5
Oil Capacity Movement: Two oil tanks each 5.72 US gallons capacity, including propeller pitch control oil. arm -
10 in. (i.e. forward of CG datum point). 
 
Datum: The zero datum of the airplane is the forward face of the rear spar former.  The CG 
datum is 108.3 in. forward of zero datum. 
 
Standard Mean Chord (SMC): The standard  mean chord is 100.632 in.  The leading edge of the standard mean chord is 
44 in. aft of the CG datum. 
 
Leveling Means: The seat rail in the forward fuselage adjacent to the left hand forward passenger  door. 
 
Operating Limitations: Aircraft shall be operated in compliance with the operating limitations specified in the 
CAA approved Flight Manual Document No ATP 002 dated August 25,  1988, or for 
aircraft with Mod 05000A Flight Manual  Document No. ATP 0004 dated December 14, 
1989 or later approved revisions. 
 
Serial Nos. Eligible: A United Kingdom Certificate of Airworthiness for Export endorsed as noted under 
“Import Requirements” below must be submitted for each individual airplane  for which 
application for United States certification is made. 
Transition Statement: The United Kingdom Civil Aviation Authority originally type certificated this 
aircraft under its type certificate Number BA23.  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.  A27NM 
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 manufacture (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 ATP 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 Directorate; 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 ATP. Prior to issuance of a 
Standard Airworthiness Certificate on any ATP model aircraft, all 
modifications shown in the model ATP 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

A27NM 6
the interest o
f 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 ATP RML are required in the interest of 
safety and are necessary for this airplane to be in a condition for safe 
operation.   
 
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.  Additional 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 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. 
 
Certification Basis: 1. JAR 25  including changes 1 through 10 
2. The following section of FAR Part 25 effective February 1,  1965 as amended  
through Amendment 25-56: 
 
25.1041 25.671(c)(1) 25.954 25.1305 (c)(6) and (7) 
25.1091 25.693 25.993 (c) 25.1309 (a), (b), (c), (d), (e) 
25.1093 (b)(1)(i) and (ii), (b)(2) 25.729 (e) 25.994 25.1331 (a)(3) 
25.1103 25.735 (f)(1) 25.1013 25.1337 (a)(1) and (3) 
25.119 (b) 25.773 (b)(1)(ii), (b)(2) 25.1015 25.1353 (a), (c)(5), (c)(6) 
25.125 (a) 25.777 (e), (g) 25.1019 25.1401 (b), (f) 
25.201(d) 25.781 25.1041 25.1411 (a)(2) 
25.331 (c)(1) 25.783(f) 25.1091 25.1415 (d), (e)

A27NM 7
25.351 (a)(1) 25.785 (g) 25.1093 (b)(1)(i) and (ii), (b)(2) 25.1438 (a),(b), (c) 
25.361 (b) 25.787 (a) 25.1103 25.1501 
25.335 (b)(2) 25.803 25.1121 25.1513 
25.365 (a), (d) 25.809(j) 25.1123 25.1521 (b) and (c) 
25.511 (b)(6) 25.832 25.1141 (f)(2) 25.1522 
25.571 (b)(6) 25.843 (a) 25.1142 25.1547 (c) 
25.581 25.901 (c) 25.1143 (f) 25.1549 
25.613 25.903 (d)(1) 25.1181 25.1583 (a) (4) , (I) 
25.615 25.939 (a) 25.1191 25.1585 (a)(1) through (10) 
25.621 25.943  25.1195 25.1587 (a), (b) (4) 
25.631 25.951 (a) 25.1303 (c)(1)  
    
 
3. The applicant elected to have the followi ng later requirements added to the TC basis: 
25.812 as amended by Amendment 25-58 
25.853 as amended by Amendment 25-59 
25.904 as amended by Amendment 25-62 
 
4. Special Condition 25-ANM-17 dated March 9,  1988,  concerning engine control lightning protection. 
 
5. Exemptions: 
No. 4812 Docket No 013NM concerning 25.571 (e)(2) sustaining structural damage from the loss of a propeller 
blade impact.  
No. 9798 Docket No 2008-0714 concerning EAPAS 26.11, AASR 26.43, 26.45, and 26.49. 
 
6. Equivalent safety findings exist with respect to the following sections of the FAR: 
Section 25.783 (f) via pressurization test. 
Section 25.773 (b)(2) by additional design requirements and flight evaluation. 
 
7. Special Federal Aviation Regulation No 27, effec tive February 1, 1974, including Amendments 27-1 through 
27-6 (Fuel Venting and exhaust Emissions). 
 
8. Part 36, effective December 1,  1969, including Amendment 36-1 through 36-14.  Amendment 36-1 through 
36-16 (Mod  050004). 
 
9. BAE elected to demonstrate compliance with 25.1419:  Ice Protection.  Date of Application for Type 
Certificate April 5, 1982. 
 
10. Part 26 of the Federal Aviation Regulations: 
Per 21.29(a), applicable provision of part 26. 
 
In accordance with 14 CFR Section 21.29, the, FAA has determined the above noted certification basis item 1 through 6 are 
equivalent to or exceed FAR Part 25 as amended through 25-56 requirements.

A27NM 8
Required Equipment: The basic required e quipment as prescribed in the applicable airworthiness regulations (see 
Certification Basis) must be installed in the aircraft for certification. 
 
Federal Aviation Administration (FAA) approved Airplane Flight Manual, BAE Model ATP, 
Document No ATP 002 dated August 25,  1988, published in the English language (CAA-UK 
approved on behalf of the FAA) or later  CAA-UK approved revision, is required. 
 
For aircraft with Modification 05000A Federal Aviation Administration (FAA) approved Airplane 
Flight Manual, Bae Model ATP, Document No ATP 004 dated December 14,  1989 published in 
the English language (CAA approved on behalf of the FAA) or later CAA-UK approved revision, 
is required. 
 
Airplane Weight and Balance Manual Number BAe-MWE-R-ATP-2000 series. 
 
Available Documents: Maintenance Review  Board Report, Document No MRB ATP-01 
 
NOTE 1 Weight and Balance: 
(a) Current Weight and Balance Manual included in cer tificated empty weight and loading instructions 
must be provided for each aircraft at the time of original certification and at all times subsequently.  
British Aerospace “Weight and Balance Manual” No BAe-MWE-R-ATP-2000 series contains all the 
loading information required for each aircraft in its delivery configuration. 
 
(b) The airplane must be loaded so that the CG is  within the specified limits at all times when all 
influences on CG position have been considered. 
 
(c) The Weight and Balance defined in (a) above quotes the quantities of usable 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 on 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. 
 
 
…..END…..
```

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- [AD 2015-15-14](https://openairdocs.org/ad/2015-15-14): Fire Protection · BAE Systems ATP. Effective Aug 19, 2015
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- [AD 2007-15-08](https://openairdocs.org/ad/2007-15-08): Airworthiness Limitations Section (ALS) · BAE Systems ATP. Effective Aug 8, 2007
- [AD 2005-20-19](https://openairdocs.org/ad/2005-20-19): Engine sub-frame tubes · BAE Systems ATP. Effective Oct 21, 2005
- [AD 2005-20-22](https://openairdocs.org/ad/2005-20-22): Fuselage and wing structure · BAE Systems ATP. Effective Oct 21, 2005
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- [AD 2003-12-02](https://openairdocs.org/ad/2003-12-02): Nose landing gear (NLG) · BAE Systems ATP. Effective Jul 17, 2003
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- [AD 2000-21-05](https://openairdocs.org/ad/2000-21-05): Main Landing Gear · BAE Systems ATP. Effective Nov 6, 2000
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- [AD 98-05-12](https://openairdocs.org/ad/98-05-12): AFM - Limitations Section - Roll-Over Lever · BAE Systems ATP. Effective Apr 8, 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 97-24-13](https://openairdocs.org/ad/97-24-13): Inspect Flap Drive Torque Tubes · BAE Systems ATP. Effective Jan 2, 1998
- [AD 97-16-09](https://openairdocs.org/ad/97-16-09): Hydraulic System · BAE Systems ATP. Effective Sep 22, 1997
- [AD 97-09-10](https://openairdocs.org/ad/97-09-10): Standby Elevator Control System · BAE Systems ATP. Effective Jun 6, 1997
- [AD 97-02-18](https://openairdocs.org/ad/97-02-18): Antenna Mounting Reinforcing Plates · BAE Systems ATP. Effective Mar 4, 1997
- [AD 96-22-02](https://openairdocs.org/ad/96-22-02): Inspect Right and Left Ram Air Inlet Ducts · BAE Systems ATP. Effective Dec 11, 1996
- [AD 96-09-18](https://openairdocs.org/ad/96-09-18): AFM - Icing · BAE Systems ATP. Effective Jun 11, 1996
- [AD 96-03-06](https://openairdocs.org/ad/96-03-06): Inspect Gussets of Rear Passenger Door · BAE Systems ATP. Effective Mar 13, 1996
- [AD 95-22-02](https://openairdocs.org/ad/95-22-02): Inspect Main Landing Gear Wheels · BAE Systems ATP. Effective Nov 29, 1995
- [AD 95-21-18](https://openairdocs.org/ad/95-21-18): NLG Bracket Attachment Assembly · BAE Systems ATP. Effective Nov 17, 1995
- [AD 95-19-06](https://openairdocs.org/ad/95-19-06): Inspect Rib Boom Angles For Cracks · BAE Systems ATP. Effective Nov 1, 1995
- [AD 95-19-14](https://openairdocs.org/ad/95-19-14): Passenger and Aft Baggage Door · BAE Systems ATP. Effective Oct 20, 1995
- [AD 95-17-04](https://openairdocs.org/ad/95-17-04): AFM Limitations - Freezing Precipitation · BAE Systems ATP. Effective Sep 13, 1995
- [AD 95-16-09](https://openairdocs.org/ad/95-16-09): Oil Filter Switches · BAE Systems ATP. Effective Aug 18, 1995
- [AD 95-12-13](https://openairdocs.org/ad/95-12-13): De-Ice Timers for Engines · BAE Systems ATP. Effective Jul 26, 1995
- [AD 95-02-09](https://openairdocs.org/ad/95-02-09): Electrical Power · BAE Systems ATP. Effective Mar 16, 1995

All 92: https://openairdocs.org/tcds/A27NM/ads.md

## STCs approved under this data sheet (9)

- [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 ST00030IB](https://openairdocs.org/stc/ST00030IB): Installation of Test Tech ELT. APTOZ EHF
- [STC ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited
- [STC ST04340NY](https://openairdocs.org/stc/ST04340NY): Installation of TCAS 7.1 (ACAS II) upgrade of Prior Existing TCAS 7.0. Scandinavian Avionics Design ApS
- [STC ST01297SE](https://openairdocs.org/stc/ST01297SE): Installation of increased security cockpit door. Cascade Aviation Services Inc
- [STC ST02252CH](https://openairdocs.org/stc/ST02252CH): Install Main Deck Cargo Loading System. Telair US LLC
- [STC ST02540AT-D](https://openairdocs.org/stc/ST02540AT-D): Installation of replacement fuel tank sealant system. FFC Manufacturing
- [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 ST00017WI-D](https://openairdocs.org/stc/ST00017WI-D): Installation of alternate Collins TTR-920 TCAS R/T and dual Collins TDR-94D Mode S transponders.. Rockwell Collins Inc

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