# TCDS R00004RD: Leonardo S.p.A.

- Type: Type certificate data sheet
- Status: Current
- Holder: Leonardo S.p.A.
- Revision: 6
- Revised: December 3, 2025
- Product: Aircraft, Rotorcraft
- Certification basis: Part 29, Part 21
- Registered aircraft: 6, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/7b/db/7bdbe1555185b5a5873bf5defdb3561e660110dd0d4960eb952c64663a326d3a
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID120940149320251209153354.0001
- Page: https://openairdocs.org/tcds/R00004RD

## Models (1)

As the data sheet lists them.

- AW189

## What the data sheet says

Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers.

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 
TYPE CERTIFICATE DATA SHEET NO. R00004RD 
 
This data sheet which is a part of Type Certificate No.R00004RD 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 Leonardo S.p.a. 
Helicopter Division 
Piazza Monte Grappa, 4 
00195 – Rome, Italy 
 
Type Certificate Holder Record: AgustaWestland S.p.A. was previous name of TC holder. The company name change 
history is presented below. 
 
Type Certificate Holder Period 
AgustaWestland S.p.A. Via Giovanni Agusta, 520; 21017 
Cascina Costa di Samarate (VA) – Italy 
1 June 2011 - 
30 July 2014 
AgustaWestland S.p.A. Piazza Monte Grappa, 4; 00195 
Roma - Italy 
31 July 2014 - 
31 December 2015 
Finmeccanica S.p.A., Helicopter Division Piazza Monte 
Grappa, 4; 00195 Roma - Italy 
1 January 2016 - 
14 July 2016 
Leonardo S.p.A., Helicopters Piazza Monte Grappa, 4; 
00195 Roma - Italy 
since 15 July 2016 
 
 
I. Model AW189 (Transport Helicopter: Category A and Category B), Approved 27 February 2015 
Engine Two (2) General Electric CT7-2E1 
FAA Engine Type Certificate Data Sheet No E8NE 
Free turbine turboshaft engines with FADEC 
For Limitations Ref. to GE Operating Instructions No. GEK112766 
 
Auxiliary Power Unit (APU) One (1) Microturbo model e-APU60 model 342 (FAA TSO C77b) 
• Max. Continuous = 41.9 hp (31.25 kW) at APU gearbox. 
• See e-APU60 for AW189 Installation Manual No. 0342/09/012, 
issue /Ed. 06, dated 5/21/14 or later approved issue for detail 
 
Fuel JET A, JET A1, JP5, JP8, JP8+100, No. 3 Jet Fuel (for code no. specification and 
more details refer to approved Rotorcraft Flight Manual) 
  
Fuel icing inhibitors are mandatory for ambient temperatures below -15°C 
See Section I of the approved Rotorcraft Flight Manual for fuel mixture and fuel 
temperature limitations 
 
 
 
 
 
R00004RD 
REVISION 6 
Leonardo S.p.a. 
AW189  
December 03, 2025 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 
Rev. No. 6 5 4 4 4 4 4 6 4 4 4 4

R00004RD 2  Rev. 5  
 
 
Oil 
Hydraulics 
 
MIL-PRF-83282; MIL-PRF-5606, as alternative in low temperature environments 
below -20° C (See NOTE 7) 
Transmissions 
 
Engine 
APU 
Additives 
 
Coolant 
AEROSHELL TURBO OIL 555 (DoD-L-85734). No different specification or brand 
is allowed 
 
Ref. to GE Operating Instructions No. GEK112766 
MIL-PRF-23699, MIL-PRF-7808 
MIL-DTL-27686, MIL-DTL-85470, MIL-I-25017, Biobor JF 
 
R134a 
See Section I of the approved Rotorcraft Flight Manual for detailed information 
 
Fluid capacities  
Fuel 
AW189 equipped with Core Avionics SW Release up to 6.0 
 
 Total A/C capacity 
litres [kg (lb) (*)] 
Unusable 
litres [kg (lb) (*)] 
Two main fuel tanks (LH and RH) 1295 [1036 (2284.0)] 24 [19 (41.9)] 
Two main fuel tanks (LH and RH) 
plus Forward Tanks 1533 [1272 (2804.3)] 28 [22 (48.5)] 
Two main fuel tanks (LH and RH) 
plus Auxiliary Central Tank 1823 [1458 (3214.316)] 30 [24 (41.9)] 
Two main fuel tanks (LH and RH) 
plus Forward Tanks plus Auxiliary 
Central Tank 
 
2061 [1649 (3635.4)] 
 
34 [27(59.5)] 
Extended Range (See Note 11) 
Two main fuel tanks (LH and RH) 
Plus underbelly tanks 
 
2569 [2055 (4530.0)] 
 
9 [7 (15.4)] 
(*) Considering a medium density between different fuels of 0.8kg/l  
AW189 equipped with Core Avionics SW Release 7.0 or later approved 
 
 Total A/C capacity 
litres [kg (lb) (*)] 
Unusable 
litres [kg (lb) (*)] 
Two main fuel tanks (LH and RH) 1295 [1036 (2284.0)] 24 [19 (41.9)] 
Two main fuel tanks (LH and RH) 
plus Forward Tanks 1533 [1272 (2804.3)] 24 [19 (41.9)] 
Two main fuel tanks (LH and RH) 
plus Auxiliary Central Tank 1823 [145876 (3214.3.0)] 24[19 (41.9)] 
Two main fuel tanks (LH and RH) 
plus Forward Tanks plus Auxiliary 
Central Tank 
 
2061 [1649 (3635.4)] 
 
24 [19 (41.9)] 
Extended Range (See Note 11) 
Two main fuel tanks (LH and RH) 
Plus underbelly tanks 
 
2569 [2055 (4530.0)] 
 
9 [7 (15.4)] 
(*) Considering a medium density between different fuels of 0.8kg/l  
 
Oil 
 Quantity 
litres [kg (lb)] 
ENGINE (each) minimum 3.6 [3.59 (7.91)] – maximum 5.5 [5.49 
(12.10)] 
MAIN GEARBOX 
(minimum/maximum) 
minimum 21.5 [21.46 (47.31)] - maximum 27 
[26.95 (59.41)] 
(24.5 + 2.5 for oil cooler, oil ducts and filter) 
INTERMEDIATE GEARBOX 1.22 [1.217 (2.683)] 
TAIL GEARBOX 1.87 [1.866 (4.114)] 
HYDRAULIC 
(per each Power Control Module) 3.20 [2.72 (6.00)] 
 
Coolant system capacity 2.9kg

R00004RD 3  Rev. 5  
 
 
 
Installed Engine Limits  
General Electric CT7-2E1 with EECU SW up to V5.0  
 
    
Rating 
Max TQ 
[Lb-ft] 
Max ITT 
[°C (°F)] 
Max NG 
[% (rpm)] 
AEO 
Take-off 5 
min. 
515 968 
(1774.4) 102.7 (45907) 
Maximum 
Continuous 
490 942 
(1727.6) 102.7 (45907) 
OEI 
30 sec. 575 1078 (1972.4) 105 (46935) 
2 min. 575 1078 (1972.4) 105 (46935) 
Continuous 515 968 (1774.4) 102.7 (45907) 
 
            General Electric CT7-2E1 with GE EECU SW 6.0 or later: 
    
Rating 
Max TQ 
[Lb-ft] 
Max ITT 
[°C (°F)] 
Max NG 
[% (rpm)] 
Max NF 
[% (rpm)] 
AEO 
Continuous 490 957 (1754,6 ) 102.7 (45 907) 104.7 (22 000) 
Take-off 5 
min. 
515 983 (1801.4) 102.7 (45 907) - - - 
OEI 
Continuous 515 983 (1801,4) 102.7 (45 907) 104.7 (22 000) 
2.5 min. 575 1101 (2013.8) 105 (46 935) - - - 
 
 
 
Transmission Limits 
   AW189 with GE CT7-2E1 and Core Avionics Phase 3.0 SW Release  
 
Rating Max torque 
% (Lb-ft) 
Power (SHP) 
@ 102% NR 
OEI 30 sec. 1 x 164% 
(1 x 502.66) 
2050.07 
2min. 1 x 155% 
(1 x 475.08) 
1937.59 
Continuous 1 x 135% 
(1 x 413.78) 
1687.58 
AEO 30 min. (below 90 KIAS) 2 x116% 
(2 x 355.54 ) 
1450.05 
30min. (above 90 KIAS) 2 x112% 
(2 x 343.28) 
1400.05 
Maximum continuous 2 x100% 
(2 x 306.5 ) 
1250.04 
 
AW189 with GE CT7-2E1 and Core Avionics Phase 4.0 SW Release (or later) 
 
Rating Max Torque  
[%] 
Input Speed  
[rpm] 
Input Power  
[shp] 
AEO Max continuous 2 x 100 21, 420 2,500  
30 min. 2 x 116 (*) 2,907 
OEI Max continuous 1 x 142 21, 420 1,775 
2.5 min. 1 x 172 (**) 2,150 
 
(*) For airspeeds less than 90 KIAS. For airspeeds greater than 90 KIAS refer to RFM.  
(**) Between 164% and 175% allowed for 30 sec and once per 2.5 min. event

R00004RD 4  Rev. 5  
 
 
 
Rotor Limits 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
Air Speed Limits VNE Power On AEO = 169 KIAS 
 
VNE Power On OEI = 139 KIAS 
 
VNE Power Off = 120 KIAS 
 
VLE/VLO (gear extended/gear operating) = 150 KIAS/150 KIAS 
 
See approved Rotorcraft Flight Manual for variations with altitude, OAT and 
weight. 
POWER ON AEO 
CONDITION (RPM) (%) 
Minimum Continuous 284.75 100.0 
Maximum Continuous 296.14 104.0 
POWER ON OEI 
CONDITION (RPM) (%) 
Minimum Cautionary 256.28 90.0 
Minimum Continuous 284.75 100.0 
Maximum Continuous 296.14 104.0 
POWER OFF 
CONDITION (RPM) (%) 
Minimum Continuous 270.51 95.0 
Maximum Continuous 313.23 110.0

R00004RD  Rev. 5
AIRSPEED LIMITATION
POWER OFF
140  150  160
PRESSURE ALTITUDE [It X 1000]  NE [KIAS]  ICN:-89-4-151000-0-A0128-00002-4-02-1
Center of Gravity (C. G.) Range
5.503 г  5.570 m  7100 kc  5.55  8600 -
5400 kg  0.09 m  +0.106 m
5.477 ₩  8400  8300 kg  8300 kg
8200
5.45  8000
7800
7600
7400
7200
· 7000
+0.122 m
6843 kg
6800  -0.097 m
6529 kg
6400
5.15
5.138 m  8300 kg  8200  8000
5.053 m  6425 kg  5800
MAST  5600
5400
-0.026 MAST  +0.048 m
5400 kg  5400kg
5200•
5200  -0.12  -0.08  -0.04  BL [m]  0.04  0.08  0.12
189G1560A001 Iss A  ICN-89-A-151000-G-A0126-00002-A-01-1
Weight And Longitudinal Cg Envelope  Weight And Lateral Cg Envelope

R00004RD  Rev. 5
Ambient Temperature Limitations
AW189
FLIGHT ENVELOPE
OAT - [°F]
-50-40-30-20-10 0 10 20 30 40 50 60 70 80  100  120  140
10000
3000
Minimum GW
9000  permitted  2800
for area A
6000 kg  - 2600
(13228lb)
8000  1MIP 18800 K  2400
2200
7000
HALIMIT 8000 H  2000
6000
Pressure Altitude - [ft]  5000  MINIMUM OAT LIMIT  1600  Pressure Altitude
TAKE OFF and
1400
LANDING
ENVELOPE
1200
1000
3000
800
2000  600
400
1000
200
-200
-50  -40  -30  -20 • 10  10 20  30 40  50  60
OAT - [°C]
189G1560A001 Rev.C  ICN-89-A-151000-G-A0126-00004-A-02-1
Maximum Operating Altitude and Temperature
Altitude
Maximum operating altitude 10000 ft (pressure/density altitude whichever
occurs first)
For aircraft equipped with Core Avionics Phase 5.0 SW release (or later) and
Altitude Extension Kit P/N 8G0000F00511 the Maximum Operating Altitude is
extended to 15 000 ft PA/DA (whichever comes first).
Maximum Take-off and Landing altitude 8000 ft (pressure/density altitude
whichever occurs first)
Temperature
-40°C ÷ +55°C (ISA+40°C)
For variation of Temperature limitations with altitude, see the approved Rotorcraft
FlightManual and applicable supplement

R00004RD 7  Rev. 5  
 
 
Datum Longitudinal Datum (STA 0) is located at 2830 mm forward to the 
front jack point 
On the Extended Range configuration (see Note 11) 
the longitudinal datum line (STA 0) is located at 
3009 mm forward to the front jack point. 
 
Lateral Datum (BL 0) is located at +/- 275 mm inboard of LH/RH front jack 
points 
 
Leveling Means Plumb line from ceiling reference point to index plate on floor of passenger cabin 
Maximum weights - Taxi and Towing 8350 kg (See Note 12) 
- Take-off and Landing   8300 kg (See Note 12) 
 
Minimum Crew One (1) for VFR; 
Two (2) for IFR. 
(See also “Equipment” and NOTE 5.) 
 
For Cat. A operations, two (2) pilots are required if take-off and landing is to 
be carried out from the left seat. 
 
For NVG operations, two (2) pilots or one (1) pilot and one (1) crew member  
are required. Both pilot and crew member must be equipped with NVGs (see  
NOTE 10). 
 
Number of Seats 21 (2 crew – 19 passengers maximum) 
 
Maximum Baggage 300 kg (660 lb) located in the Baggage compartment (See Note 13) 
 
Baggage compartment max pressure load 550 kg/m2 (110 lb/sq. ft) 
Baggage compartment max load height 600 mm (2 ft) (See Note 13) 
 
 
Rotor Blades and Control Movements For rigging information, refer to the AW189 Maintenance Manual. 
 
Import Requirements To be considered eligible for operation in the United States, each aircraft 
manufactured under this Type Certificate must be accompanied by a 
Certificate of Airworthiness for Export or certifying statement endorsed by the 
exporting foreign civil airworthiness authority which states the following (in 
the English language): 
 
 Refer to the applicable bilateral agreement to verify eligibility for import into 
the United States of both new and used aircraft based on the scope of the 
agreement, to identify any required statements by the exporting authority on 
the export certificate of airworthiness (or equivalent document), and for 
procedures for coordinating exceptions to conformity statements on these 
documents. Refer to FAA Order 8130.2, Airworthiness Certification of 
Aircraft, for requirements for issuance of an airworthiness certificate for 
imported aircraft. 
 
“The rotorcraft covered by this certificate has been examined, tested and 
found to conform to the type design approved under FAA Type Certificate 
No. R00004RD and to be in condition for safe operation.” 
 
The only aircraft eligible for import into the United States are those aircraft 
with the configuration defined in Leonardo S.p.a. Report No. 189G0000P005, 
“AW189 - FAA Type Design Definition,” dated 26 February 2015 or latest 
issue.. 
 
Certification Basis (1) 14 CFR Part 21.29. 
 
(2) 14 CFR Part 29 Amendment 29-1 through 29-52, dated 30 March 2010 
(See Note 16) 
 
(3) 14 CFR Part 36 Appendix H, Amendment 36-1 through 36-29 dated 11 
March 2013. 
 
 
 
 
(4) Special Condition: 
• 30 Minute All Engines Operating (AEO) Power Rating: 14 CFR 
29.1049, 29.1305, 29.1521

R00004RD 8  Rev. 5  
 
 
(5) Equivalent Level of Safety Findings issued against: 
• 14 CFR § 29.807(c) Passenger emergency exits  
 (documented in ELOS Memo TC4265RD-R-C-01) 
• 14 CFR § 29.813(c) Passenger access to each emergency 
exit (documented in ELOS Memo TC4265RD-R-C-02). 
• 14 CFR § 29.807 (d)(2) & (d)(3) Ditching emergency exits 
for passengers (documented in ELOS Memo TC4265RD- 
R-C-04). 
• 14 CFR § 29.815 Main aisle width (documented in ELOS 
Memo TC4265RD-R-C-05). 
• 14 CFR § 29.1545(b) Airspeed indicator (documented in 
ELOS Memo TC4265RD-R-F-01). 
• 14CFR §29.1305 and §29.1549 Power Index (documented in ELOS 
Memo TC4265RD-R-F-03) 
• 14CFR §29.1505(c) (2) Power-Off VNE (documented in ELOS 
Memo AT04309RD-R-F-1 
• 14CFR §29.1505(c) (2) Power-Off VNE (documented in ELOS 
Memo AT11392IB-R-F-1 
• 14CFR §29.923 and §29.927 Rotor drive system and control 
mechanism tests: Endurance and additional tests by test rig 
(documented in ELOS Memo AT19460IB-R-29.923 & 29.927  
 
 
(6) Core Avionics SW Release Phase 7.0 and later 
For Core Avionics SW Release 7.0 and later compliance has been shown for the 
following requirements: 
• 29.1317 Amdt. 29-52 
• Appendix E to Part 29, Amdt 29-52 
• 29.610 Amdt. 29-53 
• 29.1316 Amdt. 29-53 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness 
regulations (See Certification Basis) must be installed in the helicopter for 
certification. 
 
The installation of the followings is mandatory for Ditching Operations (see 
Supplement 6 of the RFM): 
• Life rafts (life rafts P/N 8G2560F00511 have been approved for use by 
Leonardo S.p.a. The use of other life raft installations must be in 
accordance with CS/FAR 29 and must be approved) 
• Survival type Emergency Locator Transmitter 
• Life preservers (the following life preservers installations have been 
approved by Leonardo S.p.a: 8G2560F00611, 8G2560F00711, 
8G2560F00811. Different life preserver installations must be in 
accordance with CS/FAR 29 and must be approved). 
 
The installation of the followings is mandatory for Night Vision Goggles 
Operations (see Supplement 14 of the RFM): 
• Aviator’s Night Vision Goggles as specified in 189G3360A001 
“AW189 NVG Compatibility Reference Handbook” 
• Helmet with NVG mount suitable for NVG Model being used 
• Cockpit/Cabin physical separation device as defined in 189G3360A001 
“AW189 NVG Compatibility Reference Handbook”. 
 
The installation of the following is mandatory for operations in Full Icing 
Conditions: 
• Kit Full Ice Protection System P/N 8G3000F00111 with DGCU 
P/N 8G2420V00351 (see RFM Supplement 44 or 49, according to 
the relevant aircraft configuration) 
The aircraft configuration approved for use in full icing condition is described 
in the Report 189G3000A001”AW189 Icing Compatibility Reference 
Handbook” 
 
Refer to approved Rotorcraft Flight Manual and related supplements for other 
approved mandatory and optional equipment. 
 
Refer to Kit Compatibility  Handbook 189G0000A002 for incompatibilities and  
restrictions between optional equipment. 
 
AW189 Software Configuration is managed within the Software Handbook 
189G0000X007.

R00004RD 9  Rev. 5  
 
 
 
 
 
Personal Electronic Device (PED)-sensitive equipment, which is under the 
responsibility of the TC Holder and is declared as NON-PED tolerant, or has PED 
tolerance limitations, is reported in the document 189G9850A005 “PED Compatibility 
Reference Handbook”. 
 
 
Service information Leonardo S.p.a. Service bulletins, structural repair manuals, vendor manuals, 
Rotorcraft Flight Manual, and overhaul and maintenance manuals, which 
contain a statement that the document is EASA approved, are accepted by the 
FAA and are considered FAA approved. These approvals pertain to the 
approved type design only. 
 
Flight Manual EASA approved on behalf of FAA Rotorcraft Flight Manual, 189G0290X002, 
Issue 1 Revision 3 or later approved revision (See NOTE 5). 
 
 
Maintenance Manual Maintenance Planning Information 89-B-AMPI-00-P 
Maintenance Publication 89-A-AMP-00-X.

R00004RD 10 Rev. 5 
 
 
NOTES 
 
NOTE 1 A current weight and balance report, including a list of equipment included in the certificated empty weight, must be  
provided for each helicopter at the time of original airworthiness certification in accordance with 14 CFR 29.25, 29.27 
and 29.29. 
NOTE 2 All placards required by either FAA Approved Rotorcraft Flight Manual, the applicable operating rules, or the 
Certification Basis must be installed in the helicopter. 
NOTE 3 Information essential to the proper maintenance of the helicopter is contained in the Manufacturer’s Maintenance 
Manual provided with each helicopter. Life limited components and associated retirement times are presented in 
Chapter 4 and must be replaced accordingly. 
NOTE 4 The model AW189 rotorcraft employs electronic engine controls, commonly named Full authority Digital Engine 
Controls (FADEC), that are recognized to be more susceptible to Electromagnetic Interference (EMI) than rotorcraft 
that have non-electronic controls. (EMI may be the result of radiated or conducted interference.) For this reason 
modifications that add or change systems that have the potential for EMI, must either be qualified to a standard 
acceptable to the FAA or tested at the time of installation for interference with the FADEC. This type of testing must 
employ the particular FADEC diagnostic techniques and external diagnostic techniques. The test procedure must be 
FAA approved. 
NOTE 5 The FAA approved Rotorcraft Flight Manual (RFM) is identical to the EASA approved RFM; any exceptions unique 
for FAA are presented on yellow pages marked “EASA approved on behalf of FAA” or “FAA Approved”. They must 
be included in the FAA manual to reflect the differences noted below: 
1. Section 1, LIMITATIONS, MINIMUM FLIGHT CREW: 
Requires two pilots for IFR 
2. Section 4, Performance Data, NOISE CHARACTERISTICS: 
 
Model: AW189 General Electric GE CT7-2E1 Gross Weight 8300 kg 
 
Configuration Level Flyover EPNL Take Off EPNL Approach EPNL (EPNdB) (EPNdB) (EPNdB) 
 
102% NR 102% NR 102% NR 
Clean aircraft 
No external kits installed 95.2 91.3 99.1 
 
NOTE 6 
 
The Leonardo S.p.a. Model AW189 incorporates an integrated avionics system using software-based line replaceable 
units (LRU) which share a digital signal transmission bus. The software configuration of the AW189, as delivered 
from production, is critical to the proper operation of the avionics and cockpit instrumentation system. Modification 
to the LRU software supplied with the AW189, replacement of an LRU with a different LRU, addition of new LRU, 
or alteration of an LRU interface could adversely affect the airworthiness of the certified software. No changes to the 
integrated avionics system should be made without coordination with the FAA Aircraft Certification Office (ACO) 
having jurisdiction over the modifier. 
NOTE 7 The hydraulic fluids must conform to MIL-PRF-83282 or MIL-PRF-5606 which is an alternate for low Temperature 
operation - see LIMITATIONS Section of the approved Rotorcraft Flight Manual. 
NOTE 8 Any changes to the type design of this helicopter by means of a amended type certificate (TC), supplemental type 
certificate (STC), or amended STC, requiring instructions for continued airworthiness (ICA's) must be submitted thru 
the project aircraft certification office (ACO) for review and acceptance by the Fort Worth -Aircraft Evaluation Group 
(FTW-AEG) Flight Standards District Office (FSDO) prior to the aircraft delivery, or upon issuance of the first 
standard airworthiness certificate for the affected aircraft, whichever occurs later as prescribed by Title 14 CFR 21.50. 
Type design changes by means of a field approval that require ICA's must have those ICA's reviewed by the field 
approving FSDO. 
NOTE 9 The AW189 name identifies production batches manufactured in conformity with the same Type Design. Applicable 
serial numbers: 
• S/N 49007: and subsequent, manufactured by AgustaWestland S.p.A. or Finmeccanica S.p.A., or Leonardo 
S.p.a. in Italy. 
• S/N 89001: and subsequent, manufactured by AgustaWestland S.p.A. or Finmeccanica S.p.A., or Leonardo 
S.p.a. in Italy. (See Note 11) 
• S/N 91001: and subsequent, manufactured by AgustaWestland S.p.A or Finmeccanica S.p.A., or Leonardo 
S.p.a. in UK. 
• S/N 92001 and subsequent, manufactured by AgustaWestland S.p.A. or Finmeccanica S.p.A.,or Leonardo 
S.p.a. in UK. (See Note 11). It should be noted that S/N 92001 and 92003 have been manufactured by 
AgustaWestland Ltd in UK.

R00004RD 11 Rev. 5 
 
 
 
NOTE 10 Night Vision Goggle operations may be granted by the local civil aviation authority if the rotorcraft is operated 
according to the limitations and procedures of RFM 189G0290X002 Supplement 14. The rotorcraft configuration 
 involving internal and external light emitting and reflecting equipment approved for use with NVGs is described in 
Report 189G3360A001 “AW189 NVG Compatibility Reference Handbook”. Subsequent modifications and 
deviations to the NVG helicopter configuration shall be managed in accordance with AgustaWestland document 
189G3360E001 “AW189 Helicopter NVG Policy” 
 
NOTE 11 Applicable to the extended range configuration when installed in accordance with Drawing 8G0000X00831 and 
Drawing 8G0000X00931. For detailed information, refer to Supplement 22 of the approved Rotorcraft Flight 
Manual. 
 
NOTE 12 Operation of the aircraft with a maximum weight up to 8600 kg is permitted provided kit P/N 8G0000F00111 is 
installed, and the limitation and procedures within RFM 189G0290X002 Supplement 21 are adhered to. 
 
NOTE 13 The installation of Vertical Cargo Net restrain system P/N 8G2550F00311 permits the maximum load to be carried 
in the baggage compartment to be increased to 360 Kg, and the maximum cargo height to be extended up to 700 mm 
(2 ft 3 ins). For detailed information, refer to approved Rotorcraft Flight Manual Section 1 – Baggage Compartment 
Limitations. 
The installation of the Heavy Duty Baggage Compartment Kit p/n 8G5010F00411, according to RFM Supplement 
46, permits the maximum load in the baggage compartment to be increased to 460 kg. 
 
The installation of the Heavy Duty Baggage Compartment Kit p/n 8G5010F00511, according to RFM Supplement 
46, permits maximum load in the baggage compartment of 280 kg. 
 
NOTE 14 
NOTE 15 
Removed. 
Removed 
 
NOTE 16 Kit Rescue Hoist and FIPS: 
For Kit Single Rescue Hoist (P/N 8G2591F00111), Kit Double Rescue Hoist (P/N 8G2591F00311), Kit Foldable 
Single Hoist (P/N 8G2591F00211) and Kit Full Ice Protection System (P/N 8G3000F00111, 8G3000F00311) 
design changes compliance to 14 CFR Part 29 Amendment 29-1 through 29-55, dated 31 January 2012 has been 
provided for the following requirements: 
• 29.571 Amdt.55 – Fatigue Tolerance Evaluation of Metallic Structure 
• 29.573 Amdt.54 – Damage Tolerance and Fatigue Evaluation of Composite Rotorcraft Structures. 
• Appendix A, A 29.4 Amdt.54 – Airworthiness Limitations Section 
Comparison between 14 CFR Part 29 Amendment 29-1 through 29-55 (dated 31 January 2012) and CS 29 Amdt.3 
(dated 11 December 2012) is provided in LH report 189G0274A001.

R00004RD 12 Rev. 5 
 
 
 
Acronyms and Abbreviations 
 
AEO All Engines Operative 
CS Certification Specification 
CFR Code of Federal Regulations 
Doc. Document 
EASA European Union Aviation Safety Agency 
FAA Federal Aviation Administration 
GE General Electric 
ICAO International Civil Aviation Organisation 
IFR Instrument Flight Rules 
ISA International Standard Atmosphere 
LH 
Max 
Left Hand 
Maximum 
min.  minute 
No. Number 
NVG Night Vision Goggle 
OAT Outside Air Temperature 
OEI One Engine Inoperative 
RFM Rotorcraft Flight Manual 
RH Right Hand 
sec. second 
SL Sea Level 
STA Station 
VNE Velocity Never Exceed 
VFR Visual Flight Rules 
 
 
 
….END….
```

## ADs (34, in force first)

- [AD 2026-17-05](https://openairdocs.org/ad/2026-17-05): Cabin Equipment/Furnishings · Airbus Helicopters H160-B, EC225LP, AS 365 N3 and 18 more. Effective Oct 2, 2026
- [AD 2026-15-15](https://openairdocs.org/ad/2026-15-15): Engine exhaust system · Leonardo AW189. Effective Sep 3, 2026
- [AD 2026-10-03](https://openairdocs.org/ad/2026-10-03): Tail rotor control system · Leonardo AB139, AW139 and AW189. Effective Jun 25, 2026
- [AD 2025-19-10](https://openairdocs.org/ad/2025-19-10): Engine Air Intake System · Leonardo AW189. Effective Oct 9, 2025
- [AD 2025-07-01](https://openairdocs.org/ad/2025-07-01): Air Data Computer · Synthetic Vision Electronic Flight Information System (Arrow STC SR09595RC or ST01523WI). Effective May 15, 2025
- [AD 2024-10-08](https://openairdocs.org/ad/2024-10-08): Glide slope system · Leonardo AW189. Effective Aug 13, 2024
- [AD 2024-10-02](https://openairdocs.org/ad/2024-10-02): Life Raft · Leonardo AW189. Effective Jul 22, 2024
- [AD 2024-05-07](https://openairdocs.org/ad/2024-05-07): Main rotor gearbox · Leonardo AW189. Effective May 14, 2024
- [AD 2023-11-07](https://openairdocs.org/ad/2023-11-07): Ground Proximity System · Airbus Helicopters 47, 206, 210 and 237 more. Effective Jun 22, 2023
- [AD 2022-01-03](https://openairdocs.org/ad/2022-01-03): Fire Bottle, Portable · Airbus Helicopters AS332C, AS332C1, AS332L and 35 more. Effective Mar 7, 2022
- [AD 2021-25-08](https://openairdocs.org/ad/2021-25-08): Lighting System · Leonardo AW189. Effective Jan 4, 2022
- [AD 2021-22-09](https://openairdocs.org/ad/2021-22-09): Engine Drains · Leonardo AW189. Effective Dec 27, 2021
- [AD 2021-20-05](https://openairdocs.org/ad/2021-20-05): Emergency Flotation Section, Emergency Equipment · Leonardo AW189. Effective Nov 22, 2021
- [AD 2021-20-17](https://openairdocs.org/ad/2021-20-17): Tail Rotor System · Leonardo AW169 and AW189. Effective Nov 22, 2021
- [AD 2021-22-07](https://openairdocs.org/ad/2021-22-07): Fire Bottle, Portable · Airbus A319-111, A319-112, A319-113 and 127 more. Effective Nov 18, 2021
- [AD 2021-16-09](https://openairdocs.org/ad/2021-16-09): Emergency Flotation Section · Leonardo AW189. Effective Oct 13, 2021
- [AD 2021-17-16](https://openairdocs.org/ad/2021-17-16): Tail Rotor Gearbox · Leonardo AW189. Effective Sep 24, 2021
- [AD 2021-13-13](https://openairdocs.org/ad/2021-13-13): Engine fuel and control · Leonardo AW189. Effective Aug 24, 2021
- [AD 2021-13-01](https://openairdocs.org/ad/2021-13-01): Main Rotor System · Leonardo AB139, AW139 and AW189. Effective Aug 3, 2021
- [AD 2021-13-21](https://openairdocs.org/ad/2021-13-21): Main Rotor Mast/Swashplate · Leonardo AB139, AW139 and AW189. Effective Jul 12, 2021
- [AD 2021-12-03](https://openairdocs.org/ad/2021-12-03): Window/Windshield System · Leonardo AW189. Effective Jul 1, 2021
- [AD 2021-05-13](https://openairdocs.org/ad/2021-05-13): Tail Stabilizer · Leonardo AW189. Effective Apr 21, 2021
- [AD 2021-02-03](https://openairdocs.org/ad/2021-02-03): Main Rotor System · Leonardo AW189. Effective Apr 1, 2021
- [AD 2020-19-09](https://openairdocs.org/ad/2020-19-09): Window/windshield system · Leonardo AW169 and AW189. Effective Oct 27, 2020
- [AD 2020-15-18](https://openairdocs.org/ad/2020-15-18): Emergency Flotation Section · Leonardo AB139, AW139, AW169 and 1 more. Effective Sep 3, 2020
- [AD 2020-03-13](https://openairdocs.org/ad/2020-03-13): Tail Rotor System · Leonardo AW189. Effective Mar 12, 2020
- [AD 2019-22-08](https://openairdocs.org/ad/2019-22-08): Tail Rotor System · Leonardo AW169 and AW189. Effective Jan 7, 2020
- [AD 2019-05-03](https://openairdocs.org/ad/2019-05-03): Tail Rotor System · Leonardo AB139, AW139, AW169 and 1 more. Effective Mar 28, 2019
- [AD 2018-24-06](https://openairdocs.org/ad/2018-24-06): Horizontal Stabilizer Structure · Leonardo AW189. Effective Jan 4, 2019
- [AD 2018-19-08](https://openairdocs.org/ad/2018-19-08): Tail Rotor Gearbox · Leonardo AW189. Effective Oct 26, 2018
- [AD 2018-03-18](https://openairdocs.org/ad/2018-03-18): Emergency Flotation Section · Leonardo AW189. Effective Apr 16, 2018
- [AD 2018-05-02](https://openairdocs.org/ad/2018-05-02): Window/Windshield System · Leonardo AW189. Effective Apr 4, 2018
- [AD 2021-23-13](https://openairdocs.org/ad/2021-23-13) (historical): Ground Proximity System · Airbus Helicopters K-225, K-190A, K-240 and 237 more. Effective Dec 9, 2021
- [AD 2018-23-52](https://openairdocs.org/ad/2018-23-52) (historical): Leonardo AW169 and AW189

## Registered aircraft by registry model (OpenAirDocs)

- [Leonardo S P A AW189](https://openairdocs.org/model/leonardo-s-p-a-aw189): 4 aircraft (registry code 33601QF)
- [Agustawestland AW189](https://openairdocs.org/model/agustawestland-aw189): 2 aircraft (registry code 0260350)

## STCs approved under this data sheet (1)

- [STC SR00228IB](https://openairdocs.org/stc/SR00228IB): Installation of Actuator Assembly Replacement Kit P/N 318783a for Floats Inflation System. AERO SEKUR S.P.A

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.