# TCDS R00007RD: Leonardo S.p.a.

- Type: Type certificate data sheet
- Status: Current
- Holder: Leonardo S.p.a.
- Revision: 3
- Revised: March 30, 2026
- Product: Aircraft, Rotorcraft
- Certification basis: Part 21, Part 29
- Registered aircraft: 22, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/ce/01/ce01e775a6641ca338355f864911e8a7248e118e6ce35a58e3a165216acfcbe3
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID122057602620260410162553.0001
- Page: https://openairdocs.org/tcds/R00007RD

## Models (1)

As the data sheet lists them.

- AW169

## 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. R00007RD 
 
This data sheet which is a part of Type Certificate No. R00007RD 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. 
Piazza Monte Grappa, 4 
00195 – Roma, ITALY 
 
I. Model AW169 (Transport Helicopter: Category A and Category B), Approved 2 February 2017 
 
Engine Two (2) Pratt&Whitney Canada PW210A 
FAA Engine Type Certificate Data Sheet No E00083EN 
For Limitations Ref. to PW210A Pratt&Whitney Canada installation 
Manual (Ref. to 30L2374) 
 
Auxiliary Power Unit (APU) N/A 
 
 
Fuel JET A, JET A1, JP8, JP8+100, No. 3 Jet Fuel (for code no. specification and more 
details refer to Rotorcraft Flight Manual) 
 
Oil 
Hydraulics 
 
 
MIL-PRF-83282, MIL-PRF-87257 (as alternative) 
Transmissions 
 
Engine 
APU 
Additives 
 
Coolant 
AEROSHELL TURBO OIL 555 (DoD-L-85734). No different specification or brand 
is allowed 
 
Refer to approved Rotorcraft Flight Manual 
N/A 
Refer to approved Rotorcraft Flight Manual 
 
R134a 
 
 
 
 
 
 
 
 
                                                       
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 
Rev. No. 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 
R00007RD 
REVISION 3 
Leonardo S.p.a. 
AW169 
 March 30, 2026

R00007RD 2 Rev.3 
 
 
Fuel 
 
 
 Total A/C capacity 
litres (Kg (*)) 
Unusable 
litres (Kg (*)) 
Two main fuel tanks (LH and RH) 1130 (904) 20 (16) 
(*) Above fuel mass has been defined assuming a standard fuel density of 0,8 kg/l. 
 
Oil 
 
 Quantity 
litres (kg) (*) 
ENGINE (each) min 5.25 (4.948) - max 5.78 (5.448) 
MAIN GEARBOX (min/max) min 17 (16.968) - max 19 (18.964) (16.8 + 2.2 for oil cooler, oil ducts and filter) 
INTERMEDIATE GEARBOX 0.77( 0.768) 
TAIL GEARBOX 1.10 (1.098) 
HYDRAULIC 
(per each Power Control Module) 
 
1.3 (1.1) 
(*) litres (kg at 80°C) 
 
Coolant system capacity 2.1kg 
 
Installed Engine Limits 
PW210A 
 
 
RATING 
MAX TORQUE 
[% - Nm (lb ft)] 
MAX 
ITT 
[C] 
MAX NG 
[% - RPM] 
MAX NF 
[% - RPM] 
 
AEO 
Continuous 118.6 – 395.9 (292) 868 96.5 – 49200  
107 - 28120 
Take-off 5 min 
Take-off 30 min* 
125.9 – 420.3 (309.9) 930 98.2 - 50100 
 
OEI 
Continuous 148.3% - 494.9 (365) 941 98.9 - 50430  
107 - 28120 
2.5 min 174.7% - 583 (429.9) 1020 100.7 - 51360 
(*)If Core Avionic SW phase 4.0 p/n 6F4600A00114, or later, is installed. 
 
     PW210A1 (helicopters with Kit Enhanced Performance installed) 
 
 
RATING 
MAX TORQUE 
[% - Nm (lb ft)] 
MAX 
ITT 
[C] 
MAX NG 
[% - RPM] 
MAX NF 
[% - RPM] 
 
AEO 
Continuous 118.6 – 395.9 (292) 868 96.5 – 49200  
107 - 28120 
Take-off 5 min 
Take-off 30 min* 
125.9 – 420.3 (309.9) 937 98.2 - 50100 
 
OEI 
Continuous 148.3% - 494.9 (365) 937 98.8 - 50400  
107 - 28120 
2.5 min 
 
   185 - 618.3 1020 100.7 - 51360

R00007RD 3 Rev.3 
 
Transmission Limits 
PW210A 
 
RATING MAX TORQUE [% - Nm (lb ft)] INPUT SPEED [RPM] INPUT POWER [Hp] 
AEO Maximum Continuous 100 – 334 (246.3) (x2) 14400 1350 (675x2) 
30 min* 111 – 371 (273.6) (x2) 14400 1500 (750x2) 
5 min 
OEI Maximum Continuous 140 – 470 (346.6) 14400 950 
2.5 min 174 – 583 (429.9) 14400 1180 
(*)If Core Avionic SW phase 4.0 p/n 6F4600A00114, or later, is installed. 
 
    PW210A1 (helicopters with Kit Enhanced Performance installed) 
 
 
RATING MAX TORQUE [% - Nm (lb ft)] INPUT SPEED [RPM] INPUT POWER [Hp] 
AEO Maximum Continuous 2 x 100(334) 14400 1350 (675 x 2) 
30 min* 2x 122 (407) 14400 1650 (825 x2) 
5 min 
OEI Maximum Continuous 148 (493) 14400 1000 
2.5 min 185 (618) 14400 1250 
 
Rotor Limits 
 
 
 
 
 
 
 
 
 
 
 
 
 
(*) Maximum and minimum continuous values of the flight envelope. AVSR provides a 
governing of the rotor speed at different values depending on airspeed (TAS/IAS**) 
and density altitude. As the NR datum is variable, NR green band is variable as well 
(±2% across the datum value). 
See RFM for additional rotor speed limitations 
 
 
(**) IAS if Core Avionics SW Phase 6.0, or later is installed 
Power On AEO (*) 
Condition (RPM) (%) 
Minimum Continuous 317.56 96.0 
Maximum Continuous 354.72 103.0 
   
Power On OEI 
Condition (RPM) (%) 
Minimum Cautionary 304.05 90.0 
Minimum Continuous 341.21 101.0 
Maximum Continuous 354.72 105.0 
Power Off 
Condition (RPM) (%) 
Minimum Continuous 304.05 90.0 
Maximum Continuous 371.61 110.0

R00007RD  4  Rev.3
Air Speed Limits  VNE Power On AEO = 165 KIAS
VNE Power On AEO*= 160 KIAS
VNE Power On OEI = 135 KIAS
VNE Power Off = 125 KIAS
VIr/VLo (gear extended/gear operating) = VNE -8 KIAS/80 KIAS
See approved Rotorcraft Flight Manual for variations with altitude,
OAT and weight.
(*) if Core Avionics SW Phase 6.0, or later is installed.
AW 169  Document N°  AW 169 RFM
169F0290X001
AIRSPEED LIMITATION
PRESSURE ALTITUDE (m X 100]
ISA +35°C
PRESSURE ALTITUDE (N1 X 1000]
Figure 1-7 Airs  er ON, OEI/Power OFF)
08-07-2015 Page 1-13
AIRSPEED LIMITATION
PRESSURE ALTITUDE A 100E
PRESSURE ALTITUDE [ft X 1000]

R00007RD  Rev.3
AIRSPEED LIMITATION
VNE TAS km/h]
240  260
OAT - [°C]
ISA+35°C
-1 0  * PRESSURE ALTITUDE (f1 × 1000]  140  150  160  170
169G1580A007 RevA  VNE [IAS KI]  ICN-69-A-155030-G-A0126-00034-A-01-1

R00007RD  6  Rev.3
Center of Gravity (C. G.) Range
AW 169  AW169 - RFM  Document N  Limitations  Section 1
169F0290X001
0.10
3600  0.060  0.02 0.04 0.06 0.08
3300  0.044
Weight / Lateral C.G. Envelope  MAST  +0.06 -0.04 -0.02 0.00  BL [m]
3300  - 0.025
4600  - 0.045
3700  -0.055
-0.08
-0.10
5000  300  00  4400  4200  4000  3800  3600  3400  3200  3000  2800  2600  2400
GW [kg]
Figure 1-4 Weight and Lateral CG Limitations
Issue 1 Page 1-7
Weight And Lateral Cg Envelope

R00007RD  7  Rev.3
Limitations  Section 1  AW169 - RFM  Document N°  AW 169
169F0290X001
3300  5.426  4.95 5.00 5.05 5.10 5.15 5.20 5.25 5.30 5.35 5.40 5.45 5.50 5.55 5.60
Weight / Longitudinal C.G. Envelope  STA [m]
33.00  5.206
4600  5.120
MAST
4200  5.040  3800  5.040
5000  4800  4600  4400  4200  4000  3800  3600  3400  3200  3000  2800  2600  2400
GW [kg]
Figure 1-3 Weight and Longitudinal CG Limitations
Page 1-6 08-07-2015  EASA Approved
Weight And Longitudinal Cg Envelope

R00007RD  8  Rev.3
Weight / Longitudinal C.G. Envelope
5200
5000
4800  4800
4800  5.160  5.460
4600
4600
4400
4200
4200
5.040  4065
4000  5.475
GW Ikg]  3800  3800
5,040
3600
3400
3300  3300
3200  5.206  5.426
3000
2800
2600  MAST
4.95 5.00  5.05 5.10 5.15 5.20 5.25 5.30 5.35 5.40 5.45 5.50 5.55 5.60
STA [m]
ICN-69-A-155630-G-A0126-00001-A-01-1
Fig. 1: Weight / Longitudinal C.G. envelope
Weight / Lateral C.G. Envelope
5200
5000  4800  4800
-0.043  0.048
4800
4600
4600
4400
4200
4000
3800
3700
3600  -0.055  - 3600
0.060
3400
3200  - 3300  3300
3000  -0.025  0.044
2800
MAST
2600
-0.08  -0.06  -0.04  -0.02  0.00  0.02  0.04  0.06  0.08
BL [m]  ICN-69-A-155630-G-A0126-00002-A-01-1
Fig. 2: Weight / Lateral C.G. Envelope

R00007RD  9  Rev.3
Ambient Temperature Limitations
AW 169  Document N°  AW169 - RFM  Limitations  Section 1
169F0290X001
AW169
FLIGHT ENVELOPE
OAT - [°F]
15 50 30 10 9 10203040 50 60 7080 100 120 140
- 44
14  Minimum GW
permitted  • 42
for area A  40
000 н  3550 kg
Pressure Altitude - [ft x 1000]  NIMUM OAT  Pressure Altitude - Im x 100]
TAKE OFF and
LANDING
ENVELOPE
-50 -40 -30 -20 -10 0  10  20 30 40 50 60
OAT - [°C]
169F1560A001 Rev.D  ICN-89-A-151000-G-A0126-00004-A-03-1
Figure 1-8 Altitude and OAT Limitations
Approved  Issue 2 Page 1-15

R00007RD  10  Rev.3
OAT - [°F]
-50  -30 -10  10  30 50  70  90 110 130
15
14
13
12
Pressure Altitude - [ft x 1000]  MINIMUM OAT LIMIT  HO LIMIT 10000 fL  Pressure Altitude - [m x 100]
-2
-50-40 -30 -20 -10  10  20 30 40 50  60
OAT - [°C]
169F1580A007 Rev.D  ICN-69-A-155030-G-A0126-00001-A-02-1
Fig. B 6: Flight Envelope for GW above 4600 kg up to 4800 kg

R00007RD 11 Rev.3 
 
Maximum Operating Altitude and Temperature 
Altitude 
 
 
 
 
 
 
 
 
 
 
Temperature 
Maximum Operating altitude: 
15 000 ft* for operation at gross mass up to 4 600 kg, and,  
10 000 ft* for operation at gross mass above 4 600 kg without Kit 
Enhanced Performance installed, or,  
15 000 ft* for operation at gross mass above 4 600 kg with Kit 
Enhanced Performance is installed. 
 
Maximum Take-Off and Landing altitude: 
15 000 ft* for operation at gross mass up to 4 600 kg, and,  
10 000 ft* for operation at gross mass above 4 600 kg without Kit 
Enhanced Performance installed, or,  
15 000 ft* for operation at gross mass above 4 600 kg with Kit 
Enhanced Performance is installed. 
 
*altitude in PA/DA (whichever occurs first) 
 
 
-40°C ÷ +50°C (ISA+35°C) 
-15°C ÷ +50°C (ISA+35°C) for Cat. A operations 
For variation of Temperature limitations with altitude, see the 
Rotorcraft Flight Manual and applicable supplement
 
Datum Longitudinal Datum (STA 0) is located at 3528 mm forward to the 
front jack point 
 
Lateral Datum (BL 0) is located at +/- 225 mm inboard of LH/RH 
front jack points 
 
Levelling Means Plumb line from ceiling reference point to index plate on floor of 
baggage compartment 
 
Maximum weights Without Kit P/N 6F0000F00211 installed: 
 - Taxi and Towing 4650 kg 
- Take-off and Landing 4600 kg 
 
          With Kit P/N 6F0000F00211 installed: 
          - Taxi and Towing           4850 kg 
          - Take-off and Landing 4800 kg 
 
Minimum Crew One (1) for VFR day and One (1) for VFR night and IFR. 
 
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 Without Kit P/N 6F2520F00111 installed: 
  10 (2 crew – 8 passengers maximum) 
 
 With Kit P/N 6F2520F00111 installed: 
  12 (2 crew – 10 passengers maximum) 
 
Maximum Baggage 250 kg (550 lb) located in the Baggage compartment 
 
Baggage compartment max pressure load 450 kg/m2 (92 lb/sq. ft) 
Baggage compartment max load height 600 mm (2 ft) 
 
 
Rotor Blades and Control Movements For rigging information, refer to the AW169 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,

R00007RD 12 Rev.3 
 
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. R00007RD 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 AW Report No. 
169F0272N003, “AW169 - FAA Type Design Definition,” dated 
23 January 2017 or later issue..

R00007RD 13 Rev.3 
 
Certification Basis (1) 14 CFR Part 21.29. 
 
(2) 14 CFR Part 29 Amendment 29-1 through 29-52, dated 30 
March 2010. 
 
(3) 14 CFR Part 36 Appendix H, Amendment 36-1 through 36-28 
dated 11 March 2013. 
 
(4) 14 CFR Part 29 Amendment 29-1 through 29-55 only for Hoist 
Installation 
 
(5) Equivalent Level of Safety Findings issued against: 
• 14 CFR § 29.807(c) Emergency Exits Access 
(documented in ELOS Memo TC4266RD-R-C- 
01). 
• 14 CFR  § 29.807(d) Ditching emergency exits 
for passengers (documented in ELOS 
Certification Review Item D-07). 
• 14 CFR § 29.813(c) Passenger access to each 
emergency exit (documented in ELOS Memo 
TC4266RD-R-C-02). 
• CFR § 29.811(c) Emergency exit marking 
(documented in ELOS Memo TC4266RD-R-C- 
03) 
• 14 CFR § 29 Subpart B, § 29.1305, § 29.1549 “Engine 
Training Mode” (documented in ELOS Memo 
TC4266RD-R-F-01) 
• 14 CFR § 29.1545(b)4 Airspeed indicator green 
arcs(documented in ELOS Memo TC4266RD- 
R-F-02). 
• 14CFR §29.1305 and §29.1549 Power Index 
(documented in ELOS Memo TC4266RD-R-F-06) 
• 14 CFR §29.923, §29.927  Rotor drive system and 
control mechanism tests: Main gearbox endurance 
and additional tests (documented in ELOS Memo 
AT12017IB-R-P-1) 
 
 
Equipment As per compliance with certification basis and included in Type 
Design Definition standard. 
Refer to approved Rotorcraft Flight Manual and MMEL 
Refer to EASA Approved Rotorcraft Flight Manual and related 
supplements for other approved mandatory and optional 
equipment. 
 
Night Vision Goggle Operations are permitted according to RFM 
169F0290X001 Supplement No. 16. The aircraft configuration 
involving internal/external emitting/reflecting equipment approved 
for use with NVG is described in the Report N. 169F3360A001 
«AW169 NVG Compatibility Reference Handbook». Subsequent 
modifications and deviations to the NVG helicopter configuration 
shall be managed in accordance with document 169F3360E001 «  
AW169 Helicopter NVG Policy » 
 
Service information Lenonardo S.p.a. service bulletins, structural repair manuals, 
vendor manuals, aircraft flight manuals, 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 For helicopters with wheeled landing gear without kit Enhanced 
Performance installed: EASA approved of behalf of FAA Rotorcraft 
Flight Manual 169F0290X001 Issue 3 Rev 2 or later approved 
revision (See Note 5). 
 
 For helicopters with wheeled landing gear with kit Enhanced 
Performance installed: EASA approved of behalf of FAA Rotorcraft 
Flight Manual 169F0290X012 Issue 1 Rev 5 or later approved 
revision. 
.

R00007RD 14 Rev.3 
 
Maintenance Manual Maintenance Planning Information 69-A-AMPI-00-P 
Maintenance Publication 69-A-AMP-00-X.

R00007RD 15 Rev.3 
 
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 AW169 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 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”. They must be included in the FAA 
manual to reflect the differences noted below: 
1. Section 1, LIMITATIONS, MINIMUM FLIGHT CREW: 
One pilot 
2. Section 4, Performance Data, NOISE CHARACTERISTICS: 
 
  
Model: AW169 PW210A Gross Weight 4600 kg up to 5.0 
 
Configuration Level Flyover EPNL 
(EPNdB) 
Take Off EPNL 
(EPNdB) 
Approach EPNL 
(EPNdB) 
Clean aircraft 
No external kits installed 
103% NR 96% NR 96% NR 
89.3 88.8 94.4 
Model: AW169 PW210A Gross Weight 4800 kg up to AP 5.0 
 
Configuration Level Flyover EPNL 
(EPNdB) 
Take Off EPNL 
(EPNdB) 
Approach EPNL 
(EPNdB) 
Clean aircraft 
No external kits installed 
103% NR 96% NR 96% NR 
89.3 88.9 94.2 
Model: AW169 PW210A Gross Weight 4600 kg AP 6.0 
 
Configuration Level Flyover EPNL 
(EPNdB) 
Take Off EPNL 
(EPNdB) 
Approach EPNL 
(EPNdB) 
Clean aircraft 
No external kits installed 
100% NR 100% NR 100% NR 
88.8 86.9 96.0 
Model: AW169 PW210A Gross Weight 4800 kg AP 6.0 
 
Configuration Level Flyover EPNL 
(EPNdB) 
Take Off EPNL 
(EPNdB) 
Approach EPNL 
(EPNdB) 
Clean aircraft 
No external kits installed 
100% NR 100% NR 100% NR 
88.8 86.9 96.0 
Model: AW169 PW210A1 Gross Weight 4600 kg AP 7.0 
 
Configuration Level Flyover EPNL 
(EPNdB) 
Take Off EPNL 
(EPNdB) 
Approach EPNL 
(EPNdB) 
Clean aircraft 
No external kits installed 
100% NR 100% NR 100% NR 
88.8 86.9 96.0 
Model: AW169 PW210A1 Gross Weight 4800 kg AP 7.0 
 
Configuration Level Flyover EPNL Take Off EPNL Approach EPNL 
Clean aircraft 
No external kits installed 
100% NR 100% NR 100% NR 
88.8 86.9 96.0 
 
 
NOTE 6 
 
The Model AW169 incorporates an integrated avionics system using software-based line replaceable units (LRU) 
which share a digital signal transmission bus. The software configuration of the AW169, 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 AW169, 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-87257 n - see LIMITATIONS Section of the 
approved Rotorcraft Flight Manual.

R00007RD 16 Rev.3 
 
NOTE 8 Any changes to the type design of this helicopter by means of an 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 AW169 name identifies production batches manufactured in conformity with the same Type Design. Applicable 
serial numbers: 
• S/N 69005: and subsequent, manufactured by Leonardo S.p.a. in Italy. 
 
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 169F0290X001Supplement 16. The rotorcraft configuration 
involving internal and external light emitting and reflecting equipment approved for use with NVGs is described in 
Report 169F3360A001 “AW169 NVG Compatibility Reference Handbook”.

R00007RD 17 Rev.3 
 
 
Acronyms and Abbreviations 
 
AEO All Engines Operative 
CFR Code of Federal Regulations 
Doc. Document 
EASA European Union Aviation Safety Agency 
FAA Federal Aviation Administration 
ICA Instructions for Continued Airworthiness  
ICAO International Civil Aviation Organisation 
IFR Instrument Flight Rules 
ISA International Standard Atmosphere 
LH Left Hand  
min. minute 
No. Number 
NVG Night Vision Goggle 
P/N Part Number 
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….
```

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- [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 2019-22-08](https://openairdocs.org/ad/2019-22-08): Tail Rotor System · Leonardo AW169 and AW189. Effective Jan 7, 2020
- [AD 2019-18-02](https://openairdocs.org/ad/2019-18-02): Emergency Exits · Leonardo AW169. Effective Oct 16, 2019
- [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 2018-16-01](https://openairdocs.org/ad/2018-16-01): Equipment · B/E Aerospace Fischer A109, AW169, Attendant seats NG and 1 more. Effective Aug 31, 2018
- [AD 2024-09-02](https://openairdocs.org/ad/2024-09-02) (historical): Life Raft · Leonardo AW169. Effective Jun 5, 2024
- [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 AW169](https://openairdocs.org/model/leonardo-aw169): 20 aircraft (registry code 33601QC)
- [Agustawestland S P A AW169](https://openairdocs.org/model/agustawestland-s-p-a-aw169): 1 aircraft (registry code 0260433)
- [Leonardo S P A AW119 MKII](https://openairdocs.org/model/leonardo-s-p-a-aw119-mkii): 1 aircraft (registry code 33601QH)

## STCs approved under this data sheet (8)

- [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
- [STC SR09932AC](https://openairdocs.org/stc/SR09932AC): Installation of Night Vision Imaging System (NVlS) I Night Vision Goggle (NVG) Compatible Lighting System. REB Technologies, Inc.
- [STC SR00066IB](https://openairdocs.org/stc/SR00066IB): Installation of the ISAT-200A and DAL-200. SkyTrac Systems Ltd.
- [STC SR04292NY](https://openairdocs.org/stc/SR04292NY): Installation of Cabin Steps. Aviation Completion Innovations, Inc.
- [STC SR04290NY](https://openairdocs.org/stc/SR04290NY): Installation of Cabin Interior Sound Reduction Wall Panel System (SRWPS). Aviation Completion Innovations, Inc.
- [STC SR04286NY](https://openairdocs.org/stc/SR04286NY): Installation of Engine Wash Kit. Aviation Completion Innovations, Inc.
- [STC SA04282NY](https://openairdocs.org/stc/SA04282NY): Installation of a Class 2 Electronic Flight Bag (EFB) mounting devise arm-mounted system. Aviation Completion Innovations, Inc.
- [STC SR04262NY](https://openairdocs.org/stc/SR04262NY): Installation of EMS Equipment Part Number 169-0040200-501. Aerolite AG

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