# TCDS A45NM: Deutsche Aircraft GmbH

- Type: Type certificate data sheet
- Status: Current
- Holder: Deutsche Aircraft GmbH
- Revision: 9
- Revised: February 10, 2022
- Product: Aircraft, Large Airplane
- Certification basis: Part 25
- Registered aircraft: 27, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/8e/b4/8eb4f01b5e13cc723e6c7a89c05b328a26a6158145ef97f9d30d17246bfd9d6c
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4ECEDF11BA854F0986258868006C8FD5.0001
- Page: https://openairdocs.org/tcds/A45NM

## Models (1)

As the data sheet lists them.

- 328-100

## What the data sheet says

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

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A45NM 
Revision 9 
Deutsche Aircraft GmbH 
Dornier Model 328-100 
February 10, 2022 
 
FAA TYPE CERTIFICATE DATA SHEET NO. A45NM 
 
This data sheet which is part of Type Certificate No. A45NM prescribes conditions and limitations under which the product for 
which the Type Certificate was issued meets the airworthiness requirements of the US Federal Aviation Regulations. 
 
Type Certificate Holder Deutsche Aircraft GmbH  
 Sonderflughafen Oberpfaffenhofen 
D-82234 Wessling 
Germany 
 
Type Certificate Holder Record Dornier Luftfahrt GmbH transferred TC A45NM to Fairchild Dornier GmbH, effective 
August 8, 2000. 
 
Fairchild Dornier GmbH transferred TC A45NM to AvCraft Aerospace GmbH, effective 
July 28, 2003. 
 
AvCraft Aerospace GmbH transferred TC A45NM to 328 Support Services GmbH, 
effective June 7, 2006. 
 
328 Support Service GmbH re-named to Deutsche Aircraft GmbH, effective 
October 6, 2021. 
 
 
Dornier 328-100 (Transport Category Airplane) approved November 10, 1993 
 
Note: Major Modification "Mod 10" was approved November 3, 1994.  Major Modification “Mod 20” was approved August 
5, 1996.  Pre "Mod 10" airplanes are designated by Dornier as "Mod 00.") Type Design Definition Document TD- 
00300 is the basis for the definition of the type design.  The information in this data sheet applies to all Dornier 328- 
100 airplanes, unless otherwise noted. 
 
Engines 2 Pratt and Whitney of Canada Ltd. PW 119B turboprops. Refer to Engine FAA-
Type Certificate E20NE. 
 
Mod 10: Same engines as the basic model. 
 
Mod 20: Two (2) Pratt and Whitney of Canada Ltd. PW 119C.  Refer to Engine 
FAA Type Certificate E20NE 
 
Fuel (a)  Specifications: 
ASTM (D 1655) Jet A ASTM (D 1655) Jet A1 
ASTM (D 1655) Jet B ASTM (D 1655) Jet A-2 
 
(b) Additives: 
According to latest version of Dornier 328 Aircraft Maintenance Manual. 
 
Oil Types of approved oils for use in PW 100 engines are: 
- 5 Centistoke oils (conforming to specification PWA 521, Type II). 
- 4 Centistoke oils. 
- Third generation oils. 
 
 
 
Page No. 1 2 3 4 5 6 7 
Rev. No. 9 8 8 8 8 8 8

A45NM 2  
Mod 00: The following engine limits table applies to the Mod 00 airplane only. 
 
Engine Limits   (Mod 00 airplane only): 
 
Conditions Operating Limits 
 POWER TQ ITT RPM RPM RPM OIL OIL 
 % TQ at % 
Np 
(%) °C High 
Press 
Rotor 
 
NH 
(%) 
Low 
Press 
Rotor 
 
NL 
(%) 
Prop 
 
 
 
NP 
(%) 
Oil Press 
 
 
PSID 
Oil Temp 
 
 
°C (8) 
BEST PERF 
TAKEOFF(1) 
100 at 100 100 800 102.7 104.4 102.5 55 to 65 0 to 115 
MAX CONT. 
OPER. (2) 
85 at 100 100 800 102.7 104.4 102.5 55 to 65 0 to 115 
GND IDLE - - - min 64 - - min 40 
(3) 
-54 to 115 
STARTING - - 950 
(4) 
- - - 200 min 
-54 
TRANSIENT (5) - 120 850 104.2 105.9 110 40 to 100 - 
OTHER - - - - - 110  (7) - 125 (6) 
 
Table references: 
(1) Operation is limited to 5 minutes. 
(2) Power limit is 1851 SHP. Operation between 85% and 100% TQ with NP below 100% is not time limited provided the 
power limit is not exceeded. (Refer to Power Torque Setting Charts in Airplane Flight Manual (AFM) Section 6 - 
Performance). 
(3) Up to 75% NH only. 
(4) 5 seconds maximum starting only. 
(5) 20 seconds maximum. 
(6) 20 minutes maximum. 
(7) In case of a propeller or propeller governor malfunction the flight can be completed with the indicated Np speed. 
Power must be set not to exceed 75% torque. 
(8) Under icing conditions oil temperature must be maintained above 45°C to ensure intake strut deicing.  
Mod 10; Mod 20: The following engine limits table applies to the Mod 10 and Mod 20 airplanes. 
Engine Limits   (Mod 10 and Mod 20 airplane): 
 
Conditions Operating Limits 
 POWER TQ ITT RPM RPM RPM OIL OIL 
 % TQ at % 
Np 
(%) °C High 
Press 
Rotor 
 
NH 
(%) 
Low 
Press 
Rotor 
 
NL 
(%) 
Prop 
 
 
 
NP 
(%) 
Oil Press 
 
 
PSID 
Oil Temp 
 
 
°C (7) 
BEST PERF 
TAKEOFF (1) 
100 at 100 100 800 102.7 104.4 102.5 55 to 65 0 to 115 
MAX CONT. 
OPER.  
85 at 100 
100 at 85 or 
below 
100 800 102.7 104.4 102.5 55 to 65 0 to 115 
GND IDLE - - - min 64 - - min 40 
(2) 
-54 to 115 
STARTING - - 950 
(3) 
- - - 200 min 
-54 
TRANSIENT (4) - 120 850 104.2 105.9 110 40 to 100 - 
OTHER - - - - - 110 (6) - 125 (5)

3 A45NM  
 
Table references: 
(1) Operation is limited to 5 minutes duration, but may be used up to 10 minutes for single engine operation. 
(2) Up to 75% NH only. 
(3) 850° C to 950° C for 5 seconds maximum. 
(4) 20 seconds maximum. 
(5) 20 minutes maximum. 
(6) In case of a propeller or propeller governor malfunction maximum power is 75% torque provided Np does not 
exceed110%. 
(7)  Under icing conditions oil temperature must be maintained above 45° C to ensure intake strut deicing. 
 
Propellers and Propeller Limits Mod 00: 2 Hartzell six bladed HD-E6C-3A  
 Diameter: 11 ft 6 in (3.5 m). Refer to propeller FAA-Type Certificate P34NE 
 
Mod 10, Mod 20: 2 Hartzell six bladed HD-E6C-3B.  
Diameter: 11 ft 10 in (3.6 m). Refer to propeller FAA-Type Certificate P34NE 
 
Mod 10, Mod 20:  For propeller limits table refer to AFM 02-06-00, Page 2, April 25, 
1996. 
 
Airspeed Limits (I.A.S.) VD 324 KIAS 
VMO 270 KIAS 
MMO .59 (above 
20,000 ft pressure altitude) 
VA (Maneuvering) (Mod 00) 170 KIAS 
VA (Maneuvering) (Mod 10, 20) 180 KIAS 
VFE (Flaps Extended) 12° 200 KIAS 
20° 180 KIAS 
In addition for Mod 10, 20: 32° 160 KIAS 
VMC (Minimum Control)  Refer to AFM 
VLE = VLO 200 KIAS 
Tire Speed 165 KIAS 
Windshield wiper operating speed 166 KIAS 
 
Datum The aircraft reference zero datum point is located 375.39 in. forward of the fuselage frame 
23, 98.425 in. under the fuselage centerline and the aircraft buttock line.  
 
Leveling Means Plumb line in rear open and latched baggage door.

A45NM 4  
Weight and Center of Gravity Limits: The following weight and center of gravity limits apply to the Mod 00 airplane only. 
 
 WEIGHT CENTER OF GRAVITY LIMITS 
Forward Limit Rear Limit 
Flight Takeoff/ 
Landing 
 
 
MAC 
ARM 
MAC 
ARM 
MAC 
ARM 
MIN. FLIGHT WEIGHT 9,600 kg 
21,164 lb 
14.0 % 
9.663 m 
380.44 in 
16.0 % 
9.704 m 
382.04 in 
 
 
 
 
 
 
 
 
 
 
40.0 % 
10.193 m 
401.29 in 
up to WEIGHT 11,000 kg 
24,251 lb 
14.0 % 
9.663 m 
380.44 in 
 
up to WEIGHT 10712 kg 
23616 lb 
 16.0 % 
9.704 m 
382.04 in 
connected by line up to MAX. 
ZERO FUEL WEIGHT 
12,260 kg 
27,029 lb 
16.4 % 
9.711 m 
382.34 in 
19.5 % 
9.776 m 
384.87 in 
connected by line up to MAX 
LANDING WEIGHT 
13,230 kg 
29,167 lb 
17.9 % 
9.742 m 
383.55 in 
21.3 % 
9.812 m 
386.31 in 
 
connected by line up to MAX. 
TAKEOFF WEIGHT 
13,640 kg 
30,071 lb 
18.5 % 
9.754 m 
384.01 in 
22.0 % 
9.826 m 
386.85 in 
 
connected by line up to MAX. 
RAMP WEIGHT 
13,720 kg 
30,247 lb 
 22.1 % 
9.829 m 
386.96 in 
 
 
Note 1: The limits are valid for the allowable flap positions corresponding to the flight speeds for takeoff, climb, cruise, 
approach, and landing.  The envelope may be limited for operational conditions due to "In-Flight Movement."  
Note that takeoff and landing have different limits than the flight limits. 
 
Note 2: 0% MAC is located 369.213 in. from the datum line. 
100% MAC is located 80.197 in. from 0% MAC.

5 A45NM  
Weight and Center of Gravity Limits: The following weight and center of gravity limits apply to the Mod 10 and Mod 20 
airplanes. 
 
 WEIGHT CENTER OF GRAVITY LIMITS 
Forward Limit Rear Limit 
Flight Takeoff & 
Landing 
Takeoff  & 
Landing 
Flight 
MAC 
ARM 
MAC 
ARM 
MAC 
ARM 
MAC 
ARM 
MIN. FLIGHT WEIGHT 9,400 kg 
20,724 lb 
14.0 % 
9.663 m 
380.44 in 
16.0 % 
9.704 m 
382.04 in 
 
 
 
 
 
 
 
 
 
 
 
 
40.0 % 
10.193 m 
401.29 in 
 
 
 
 
 
 
 
 
 
 
 
 
44.0 % 
10.274 m 
404.50 in 
up to WEIGHT 10,712 kg 
23,616 lb 
 
 
14.0 % 
9.663 m 
380.44 in 
 
16.0 % 
9.704 m 
382.04 in 
up to WEIGHT 11,000 kg 
24,251 lb 
 
connected by line up to MAX. 
ZERO FUEL WEIGHT 
12,610 kg 
27,800 lb 
16.9 % 
9.723 m 
382.80 in 
20.2 % 
9.790 m 
385.42 in 
connected by line up to MAX 
LANDING WEIGHT 
13,230 kg 
29,167 lb 
17.9 % 
9.742 m 
383.55 in 
21.3 % 
9.812 m 
386.31 in 
connected by line up to MAX. 
TAKEOFF WEIGHT 
13,990 kg 
30,843 lb 
18.9 % 
9.763 m 
384.39 in 
22.5 % 
9.837 m 
387.30 in 
connected by line up to MAX. 
RAMP WEIGHT 
14,070 kg 
31,019 lb 
 22.7 % 
9.840 m 
387.39 in 
 
 
Note 1: The limits are valid for the allowable flap positions corresponding to the flight speeds for takeoff, climb, cruise, 
approach, and landing.  The envelope may be limited for operational conditions due to "In-Flight Movement." 
Note that takeoff and landing have different limits than the flight limits. 
 
Note 2: 0% MAC is located 369.213 in from the datum line. 
 100% MAC is located 80.197 in. from 0% MAC. 
Minimum Crew 2 - Pilot and copilot 
Maximum Passengers 33 
Front row passenger seats must be equipped with integral three-point safety 
harnesses (reference change notice CN-00281, dated February 21, 1995) 
 
Type of Baggage Compartment Class "D" Compartment 
 
Maximum Baggage Total of 1653 lbs (750 kg) in the rear baggage compartment 
- 882 lbs (400 kg) in the forward part 
- 771 lbs (350 kg) in the aft part 
- max. floor loading = 75 lb/ft2 
 
Fuel Capacity 7531 lbs usable (gravity refueled) 
7300 lbs usable (pressure refueled)

A45NM 6  
Oil Capacity Oil capacity per Engine (incl. Propeller Oil System) 
 
 TOTAL 
OIL TANK 
MIN to MAX 
ON SIGHT GLASS 
TOTAL 
OIL SYSTEM 
US Gallons 4.70 0.75 5.60 
Liters 17.70 2.84 21.00 
 
Maximum Operating  Altitude 31,000 ft. 
 
Control Surface Movements 
 
Wing Flaps  
Wing Flaps 
Ailerons  
Elevator  
Stabilizer  
Rudder  
Rudder 
 
 
12° and 20° (Mod 00)  
12°, 20°, and 32° (Mod 10, 20) 
30° up (+1°), 25° down (+1°) 
30° up (-2°), 25° down (-1°) 
Fixed 
18°right, 16° left  (Mod 00)  
24° right (+1°), 20° left (-1°) (Mod 10,20) 
 
Serial Numbers Mod 00: 3006 through 3030. All former Mod 00 airplanes are modified to Mod 10 
in accordance with Service Bulletin SB 328-00-053 
 
Mod 10:  Production aircraft manufactured to the Mod 10 configuration begin at 
serial number 3031 and subsequent.  Previous serial number aircraft are eligible to 
operate to the Mod 10 specifications if service bulletin SB328-00-053 is installed. 
 
Mod 20: Mod 20 aircraft are produced by incorporation of Service Bulletin SB 
328-00-175. 
 
The following serial numbers are declared Non-TC compliant aircraft and 
excluded from the TCDS due to production details and known non-conformities: 
 
Former test article aircraft S/No’s.: 3001, 3002, 3003, and 3004. 
 
Import Requirements The FAA can issue a U.S. airworthiness certificate based on an Export Certificate 
of Airworthiness (Export C of A) signed by a representative of the LBA on behalf 
of the European Community. 
The Export C of A should contain the following statement: ‘The aircraft 
covered by this certificate has been examined, tested, and found to conform 
with the Type Design approved under U.S. Type Certificate No. A45NM and 
to be in a condition for safe operation.’ 
 
The U.S. airworthiness certification basis for aircraft type certificated under 14 
CFR part 21, section 21.29, exported by country of manufacture is section 
21.183(c) or 21.185(c). 
 
The U.S. airworthiness certification basis for aircraft type certificated under 
section 21.29 exported from countries other than the country of manufacture (e.g., 
third party country) is section 21.183(d) or 21.185(b). 
Certification Basis Mod 00: FAR Part 25 Effective February 1, 1965, including Amendments 25-1 
through 25-61, plus Amendments 25-62, -63, and –64, which were requested to be 
added to the Certification Basis by Dornier, with the exception of Sections 
25.21(b) and 25.205 (removed from Part 25 by Amendment 25-72).  In addition, 
the following paragraphs apply: 
 
Section 25.571(e)(3) as amended by Amendment 25-72, effective 
August 20, 1990, and Section 25.905(d), as amended by Amendment 
25-72. 
 
Section 25.729(e)(2) as amended by Amendment 25-75, effective 
November 26, 1991. 
 
Section 25.365 as amended by Amendment 25-71, effective April 
10, 1990.

7 A45NM  
FAA Special Condition 25-ANM-76 dated August 31, 1993 (Lightning and 
HIRF). 
 
FAA Grant Of exemption No. 5785 regarding Section 25.161(d), granted 
November 5, 1993. 
 
Equivalent Level of Safety Finding for flight crew top hatch emergency exit 
markings (FAR 25.811(f)) 
 
Dornier elected to comply with the following optional requirement: Section 
25.1419 for icing. 
 
FAR Part 36 effective December 1, 1969, including Amendments 36-1 through 
36-20. 
 
FAR Part 34 effective September 10, 1990.  SFAR 27-5 has been recodified 
as FAR Part 34, which is intended to continue the enforcement of 40 CFR 
Part 87 and make Part 34 a permanent part in the FAR's. 
 
Mod 10, Mod 20:  The certification basis for the Mod 10 and Mod 20 
airplanes is the same as for the basic Mod 00 airplane. 
 
All Variants 
Based on 14 CFR section 21.29(a) for new import TCs, or section 21.101(g) for 
changes to TCs, applicable provisions of 14 CFR Part 26 are included in the 
certification basis. For any future 14 CFR Part 26 amendments, the holder of this 
TC must demonstrate compliance with the applicable sections. 
 
The Luftfahrt-Bundesamt (LBA) originally type certificated this aircraft under its 
type certificate Number 2534.  The FAA validated this product under U.S. Type 
Certificate number A45NM.  Effective September 28, 2003, the European 
Aviation Safety Agency (EASA) began oversight of this product on behalf of the 
Federal Republic of Germany. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness 
regulations (see the Certification Basis) must be installed in the aircraft for 
certification. 
 
 Equipment approved for the Model Dornier 328-100 is listed in Document No. 
TD-34000, Equipment Register Document. 
 
Airplane Flight Manual Refer to AM-AFM-050893-ENV. 
 
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 LBA, are accepted by the FAA and are considered 
FAA approved.  Additionally, the type certificate holder has contracted with 328 
Design GmbH (328DO) as the EASA approved DOA holder.  Approvals issued 
by 328DO or by the TC holder under the authority of EASA approved design 
organization EASA.21J.438 – or for approvals made prior to September 28, 2003 
– by the TC holder under the authority of LBA approved design organization 
LBA.JA.002, are considered FAA approved. These approvals pertain to the 
design data only. 
 
 TC holder Service Bulletins, except as noted below, 
 Structural repair manuals 
 Vendor manuals referenced in TC holder Service Bulletins 
 Airplane flight manuals 
 Repair instructions. 
 
Note: Design changes that are contained in TC holder Service Bulletins and that 
are classified as Level 1 Major in accordance with the FAA/EASA agreed 
Technical Implementation Procedures for Airworthiness and Environmental

A45NM 8  
Certification (TIP latest Revision), must be approved by the FAA. 
 
NOTES 
 
NOTE 1. Current weight and balance report including a list of equipment included in 
certificated e mpty weight, and loading instructions when necess ary must be 
provided for each aircraft at its delivery. 
 
For further information see Weight & Balance Manual TM-WBM-190793- 
ALL 
 
NOTE 2. Airworthiness Limitations including structural inspections and retirement times 
for safe-life parts are listed in Dornier Airworthiness Limitations Document TM-
ALD-010693-ALL. 
 
NOTE 3. Certification Maintenance Requirements (CMR) are listed in Document TM- 
CMR-010793-ALL. 
 
NOTE 4. Compliance with the optional ditching requirements of FAR 25.801, FAR 
25.1411, and FAR 25.1415 has not been shown. 
 
END
```

## ADs (115, first 50, in force first)

- [AD 2025-15-05](https://openairdocs.org/ad/2025-15-05): Fuel · Deutsche 328-100 and 328-300. Effective Sep 3, 2025
- [AD 2025-06-08](https://openairdocs.org/ad/2025-06-08): Landing gear · Deutsche 328-100 and 328-300. Effective May 8, 2025
- [AD 2024-19-16](https://openairdocs.org/ad/2024-19-16): Equipment/furnishings · Deutsche 328-100 and 328-300. Effective Nov 26, 2024
- [AD 2023-23-07](https://openairdocs.org/ad/2023-23-07): Flight Controls · Deutsche 328-100 and 328-300. Effective Jan 16, 2024
- [AD 2023-22-07](https://openairdocs.org/ad/2023-22-07): Fuselage · Deutsche 328-100. Effective Dec 26, 2023
- [AD 2022-21-07](https://openairdocs.org/ad/2022-21-07): Placards and markings, Equipment/furnishings · Deutsche 328-100 and 328-300. Effective Dec 15, 2022
- [AD 2020-07-20](https://openairdocs.org/ad/2020-07-20): Time Limits/Maintenance Checks · 328 Support Services 328-100. Effective May 26, 2020
- [AD 2019-24-14](https://openairdocs.org/ad/2019-24-14): Wings · 328 Support Services 328-100. Effective Feb 3, 2020
- [AD 2019-15-03](https://openairdocs.org/ad/2019-15-03): Wings · 328 Support Services 328-100. Effective Sep 19, 2019
- [AD 2018-19-13](https://openairdocs.org/ad/2018-19-13): Stabilizers · 328 Support Services 328-100 and 328-300. Effective Oct 31, 2018
- [AD 2017-21-06](https://openairdocs.org/ad/2017-21-06): Fuel · 328 Support Services 328-100 and 328-300. Effective Dec 20, 2017
- [AD 2014-03-15](https://openairdocs.org/ad/2014-03-15): Placards and Markings; and Doors. · 328 Support Services 328-100 and 328-300. Effective Apr 9, 2014
- [AD 2012-07-03](https://openairdocs.org/ad/2012-07-03): Equipment/Furnishings · 328 Support Services 328-100 and 328-300. Effective May 10, 2012
- [AD 2012-04-06](https://openairdocs.org/ad/2012-04-06): Engine Controls · 328 Support Services 328-100. Effective Apr 4, 2012
- [AD 2012-01-08](https://openairdocs.org/ad/2012-01-08): Flight Controls · 328 Support Services 328-100 and 328-300. Effective Feb 29, 2012
- [AD 2011-18-13](https://openairdocs.org/ad/2011-18-13): Wings · 328 Support Services 328-100 and 328-300. Effective Oct 25, 2011
- [AD 2011-15-07](https://openairdocs.org/ad/2011-15-07): Stabilizers · 328 Support Services 328-100 and 328-300. Effective Aug 22, 2011
- [AD 2010-07-02](https://openairdocs.org/ad/2010-07-02): Integrated navigation units (INUs) · 328 Support Services 328-100, 328-300, Jetstream Model 4101 and 26 more. Effective May 3, 2010
- [AD 2008-17-01 R1](https://openairdocs.org/ad/2008-17-01-R1): Fuel system · 328 Support Services 328-100. Effective Dec 21, 2009
- [AD 2009-18-14](https://openairdocs.org/ad/2009-18-14): Flight controls · 328 Support Services 328-100 and 328-300. Effective Oct 14, 2009
- [AD 2009-10-03](https://openairdocs.org/ad/2009-10-03): Flight controls · 328 Support Services 328-100 and 328-300. Effective May 26, 2009
- [AD 2008-13-23](https://openairdocs.org/ad/2008-13-23): Elevator assembly · 328 Support Services 328-100. Effective Aug 6, 2008
- [AD 2005-13-03](https://openairdocs.org/ad/2005-13-03): Flight control systems · 328 Support Services 328-100 and 328-300. Effective Jul 26, 2005
- [AD 2005-13-04](https://openairdocs.org/ad/2005-13-04): Fuselage drain line · 328 Support Services 328-100 and 328-300. Effective Jul 26, 2005
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 2004-22-06](https://openairdocs.org/ad/2004-22-06): Metal oxide varistor (MOV) modules · 328 Support Services 328-100 and 328-300. Effective Dec 2, 2004
- [AD 2004-20-15](https://openairdocs.org/ad/2004-20-15): Engine Air Inlet De-icing System · 328 Support Services 328-100. Effective Nov 17, 2004
- [AD 2004-12-14](https://openairdocs.org/ad/2004-12-14): AC power cables · 328 Support Services 328-100. Effective Jul 22, 2004
- [AD 2004-09-12](https://openairdocs.org/ad/2004-09-12): Passenger seats · 328 Support Services 328-100 and 328-300. Effective Jun 9, 2004
- [AD 2004-09-17](https://openairdocs.org/ad/2004-09-17): Rudder spirng tab · 328 Support Services 328-100 and 328-300. Effective Jun 9, 2004
- [AD 2004-06-16](https://openairdocs.org/ad/2004-06-16): Ground spoiler assembly · 328 Support Services 328-100. Effective May 4, 2004
- [AD 2004-03-36](https://openairdocs.org/ad/2004-03-36): Engine control cables · 328 Support Services 328-100. Effective Mar 24, 2004
- [AD 2003-19-03](https://openairdocs.org/ad/2003-19-03): Nose landing gear (NLG) · 328 Support Services 328-100 and 328-300. Effective Oct 27, 2003
- [AD 2003-11-24](https://openairdocs.org/ad/2003-11-24): Upper and lower torsion bars of the rudder tab · 328 Support Services 328-100. Effective Jun 23, 2003
- [AD 2003-05-08](https://openairdocs.org/ad/2003-05-08): Flight Data Recorder (FDR) and Cockpit Voice Recorder (CVR) Impact Switches · 328 Support Services 328-100 and 328-300. Effective Apr 18, 2003
- [AD 2003-03-17](https://openairdocs.org/ad/2003-03-17): Aileron, Elevator, Rudder Trim Tabs, and Rudder Spring Tab Screws · 328 Support Services 328-100 and 328-300. Effective Mar 12, 2003
- [AD 2002-26-21](https://openairdocs.org/ad/2002-26-21): Electrical wire harness · 328 Support Services 328-100 and 328-300. Effective Feb 12, 2003
- [AD 2002-16-16](https://openairdocs.org/ad/2002-16-16): Actuating cartridge on the auxiliary power unit (APU) · 328 Support Services 328-100 and 328-300. Effective Sep 23, 2002
- [AD 2002-16-13](https://openairdocs.org/ad/2002-16-13): Rudder spring tab · 328 Support Services 328-100 and 328-300. Effective Sep 20, 2002
- [AD 2002-03-15](https://openairdocs.org/ad/2002-03-15): Left- and Right-Hand Potentiometer Levers of the Aileron Flight Control System · 328 Support Services 328-100 and 328-300. Effective Mar 27, 2002
- [AD 2002-01-17](https://openairdocs.org/ad/2002-01-17): AC Pump of Main Hydraulic System · 328 Support Services 328-100. Effective Feb 14, 2002
- [AD 2001-26-14](https://openairdocs.org/ad/2001-26-14): Honeywell GP-300 Guidance and Display Controller · 328 Support Services 328-100. Effective Feb 8, 2002
- [AD 2001-15-04](https://openairdocs.org/ad/2001-15-04): Roll Spoiler Actuators · 328 Support Services 328-100. Effective Aug 29, 2001
- [AD 2000-26-09 R1](https://openairdocs.org/ad/2000-26-09-R1): Structural Integrity · 328 Support Services 328-100. Effective Feb 7, 2001
- [AD 2000-24-03 R1](https://openairdocs.org/ad/2000-24-03-R1): Airplane flight manual (AFM) · 328 Support Services 328-100. Effective Jan 8, 2001
- [AD 2000-07-04](https://openairdocs.org/ad/2000-07-04): Flight Idle Backup System · 328 Support Services 328-100. Effective May 16, 2000
- [AD 2000-04-23](https://openairdocs.org/ad/2000-04-23): Rudder Spring Tab · 328 Support Services 328-100 and 328-300. Effective Mar 22, 2000
- [AD 2000-02-08](https://openairdocs.org/ad/2000-02-08): Ground Spoiler Actuator · 328 Support Services 328-100. Effective Mar 2, 2000
- [AD 99-19-16](https://openairdocs.org/ad/99-19-16): AFM - Limitations Section - Ice Protection System · 328 Support Services 328-100. Effective Dec 27, 1999
- [AD 99-23-12](https://openairdocs.org/ad/99-23-12): Co-Pilot Control Cables And Fairleads/Swivel Guides · 328 Support Services 328-100. Effective Dec 17, 1999

All 115: https://openairdocs.org/tcds/A45NM/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Dornier Luftfahrt 328-100](https://openairdocs.org/model/dornier-luftfahrt-328-100): 19 aircraft (registry code 2996100)
- [Fairchild Dornier 328-100](https://openairdocs.org/model/fairchild-dornier-328-100): 4 aircraft (registry code 3370603)
- [Dornier Luftfahrt DO 328-100](https://openairdocs.org/model/dornier-luftfahrt-do-328-100): 3 aircraft (registry code 2996000)
- [Fairchild Dornier DORNIER 328-100](https://openairdocs.org/model/fairchild-dornier-dornier-328-100): 1 aircraft (registry code 3370605)

## STCs approved under this data sheet (37)

- [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 ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC
- [STC ST12070MC](https://openairdocs.org/stc/ST12070MC): Installation of non-essential, not required communications equipment. Sierra Nevada Company LLC
- [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc.
- [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc.
- [STC ST04159CH](https://openairdocs.org/stc/ST04159CH): Upgrade of Honeywell Primus II Communications Units RCZ-8XX Transponders to support Certification of Automatic Dependent Surveillance -Broadcast (ADS-B) Out. CMD Flight Solutions LLC
- [STC ST00069MC](https://openairdocs.org/stc/ST00069MC): Installation of barriers for various cabin configurations and non-required communications equipment. 3S Certification LLC
- [STC ST00120MC](https://openairdocs.org/stc/ST00120MC): Installation of multiple mission configuration options, including power and mission equipment racks, non-required communications equipment, mission power distribution system, antennas, optional operator console, and provisions for sponsons with the carriage of external stores. Sierra Nevada Corporation
- [STC ST02389AK](https://openairdocs.org/stc/ST02389AK): Installation of a Max-Viz  EVS-1500 System and associated hardware. Sierra Nevada Corporation
- [STC ST03911AT](https://openairdocs.org/stc/ST03911AT): Installation of a Honeywell MK V Enhanced Ground Proximity Warning System (EGPWS). Woven Electronics LLC
- [STC ST04508NY](https://openairdocs.org/stc/ST04508NY): Installation of ADS-B Upgrade. Scandinavian Avionics Design ApS
- [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 ST03654NY](https://openairdocs.org/stc/ST03654NY): Installation of Control Horn Anti-Icers. SMR Technologies Inc
- [STC ST00361BO](https://openairdocs.org/stc/ST00361BO): Installation of a Honeywell Primus II (XS-852) ADS-B Out System. Pro Star Aviation, LLC
- [STC ST00204BO](https://openairdocs.org/stc/ST00204BO): Installation of Honeywell Mark V Enhanced Ground Proximity Warning System (EGPWS) (Master Document List 1 configuration) with optional Runway Awareness Advisory System (RAAS) (Master Document List 2 configuration).. Pro Star Aviation, LLC
- [STC ST00134MC](https://openairdocs.org/stc/ST00134MC): Installation of a Trimble TA-24S Global Positioning System Receiver.. Sierra Nevada Corporation
- [STC ST11138SC](https://openairdocs.org/stc/ST11138SC): This aircraft employs night vision imaging system (NVIS) lighting that has been certified to ensure the aircraft is compatible with NVG. REB Technologies Inc
- [STC ST01181SE](https://openairdocs.org/stc/ST01181SE): Installation of increased security cockpit door. Cascade Aviation Services Inc
- [STC ST00138MC](https://openairdocs.org/stc/ST00138MC): Installation of a cargo door latch capability from inside the aircraft.. Sierra Nevada Corporation
- [STC ST00128MC](https://openairdocs.org/stc/ST00128MC): Establishment of procedures and performance data for operations on unpaved runways.. Sierra Nevada Corporation
- [STC ST11118SC](https://openairdocs.org/stc/ST11118SC): Installation of a cargo conversion. STC 338 LLC
- [STC ST00121MC](https://openairdocs.org/stc/ST00121MC): Installation of a Ku Band Satellite Communications System and Radome. Sierra Nevada Corporation
- [STC ST00324SE](https://openairdocs.org/stc/ST00324SE): Installation of HUD Guidance System (HGS), Model 2700. (DO 328-100 MOD 10CONFIGURATION). Rockwell Collins Aerospace & Electronics Inc.
Flight Dynmics Division
- [STC ST00732DE](https://openairdocs.org/stc/ST00732DE): Replacement of the original equipment nickel cadmium batteries with Concorde Model RG-380E/44LS Lead Acid Batteries in accordance with Concorde Battery Corporation Master Drawing List 5-0353, Revision B, dated September 15, 2011 or later FAA approved revision.. Concorde Battery Corporation
- [STC ST02636NY](https://openairdocs.org/stc/ST02636NY): Installation of Self Illuminating Floor Path Marking System. Lufthansa Technik AG
- [STC ST00669CH-D](https://openairdocs.org/stc/ST00669CH-D): Installation of a 19 Passenger Corporate Interior.. Duncan Aviation Inc
- [STC ST00125SE](https://openairdocs.org/stc/ST00125SE): Installation of a closet.. Composite Solutions Corporation
- [STC ST00249SE](https://openairdocs.org/stc/ST00249SE): Modify aft galley by adding a stowage door NTP to close out an existing compartment.. Composite Solutions Corporation
- [STC ST09465AC](https://openairdocs.org/stc/ST09465AC): Modification of the cabin floor to be the same level through out the cabin in accordance with Fairchild Aircraft Report R1530, Revision D, dated April 20, 1999, or later FAA approved revision.. AvCraft Aviation LLC
- [STC ST09468AC](https://openairdocs.org/stc/ST09468AC): Installation of a corporate/executive interior in accordance with Fairchild Aircraft Incorporated Engineering Change Package (ECP) 3000, Revision AN, dated 8/26/1999, or later FAA approved revision.. AvCraft Aviation LLC
- [STC ST09562AC](https://openairdocs.org/stc/ST09562AC): Installation of an engine inlet mounting enhancement to increase the mounting flange service life in accordance with Fairchild Aircraft Inc. Drawing No. SATA716G0001, Rev. IR dated 05/19/2000, including Engineering Order A-2 dated 07/30/2001, or later FAA approved revision.. AvCraft Aviation LLC
- [STC SA00340LA](https://openairdocs.org/stc/SA00340LA): Modifies the aircraft by installing wiring and antenna provisions for installation of the Magellan Communication, Navigation, and Surveillance System CNS-12.. US Technical
- [STC ST00028LB](https://openairdocs.org/stc/ST00028LB): Installation of Honeywell traffic alert and collision avoidance system. (TCAS II). (DO 328-100 MOD 00, MOD 10 AND 20 SERIES). Dornier Lufthart GmbH
- [STC ST0684SE](https://openairdocs.org/stc/ST0684SE): Installation of HUD guidance system (HGS), Model 2700. (DO 328-100 MOD 10 CONFIGURATION). Flight Dynamics, Inc
- [STC ST444CH](https://openairdocs.org/stc/ST444CH): Installation of Bendix/King TCAS II(Model CAS67A).. Mayday Avionics Inc
- [STC ST410CH](https://openairdocs.org/stc/ST410CH): Installation of a 14-passenger seat corporate interior.. Duncan Aviation

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