# TCDS E21EU: CFM International S.A.

- Type: Type certificate data sheet
- Status: Current
- Holder: CFM International S.A.
- Revision: 13
- Revised: February 17, 2022
- Product: Engine
- Certification basis: Part 33
- Data sheet PDF: https://openairdocs.org/files/sha256/57/8b/578bdb98f6cfb2a217944374b216b89781793d8a2814856b430d2812edd1389b
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/962114ACAA05711C862587F300570FC1.0001
- Page: https://openairdocs.org/tcds/E21EU

## Models (6)

As the data sheet lists them.

- CFM56-2B
- CFM56-2
- CFM56-3B
- CFM56-2A
- CFM56-3
- CFM56-3C

## What the data sheet says

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

```text
I 
TCDS NUMBER E21EU 
U.S. DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
TYPE CERTIFICATE DATA SHEET E21EU 
REVISION: 13* 
DATE: February 17, 2022 
CFM INTERNATIONAL, S.A. 
MODELS: 
CFM56-2 CFM56-3 
CFM56-2A CFM56-3B 
CFM56-2B CFM56-3C 
Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E21EU) and other 
approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in 
accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided they are installed, 
operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. 
TYPE CERTIFICATE (TC) HOLDER: CFM International, S.A. 
2 Boulevard du General Martial Valin 
75015 Paris, France 
I. MODELS (See NOTE 12) CFM56-2 CFM56-2B CFM56-2A CFM56-3 CFM56-3B 
TYPE 
RATINGS (See NOTE 4) 
High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, 
multi-stage compressor with one stage turbine and annular combustor. 
Takeoff (5 min., see NOTE 16), 
sea level, static thrust, lb./daN. 
Maximum continuous, sea level 
static thrust, lb. 
Flat rating 
Takeoff 
Maximum continuous 
FUEL SYSTEM 
Fuel Control, Woodward 
24,000/10,676 
23,000/10,230 
22,000/9,786 
21,580/9,599 
24,000/10,676 
23,405/10,411 
20,100/8,941 
18,900/8,407 
22,100/9,830 
20,500/9,118 
AMBIENT TEMPERATURE 
86oF / 30oC 
77oF / 25oC 90oF/32.2oC - - 95oF / 35oC - - 86oF / 30oC - - - -- -
See NOTE 8 for approved fuels 
GE PART NO. 
9378M47 9278M96 1323M36 9368M57 9387M15 
9275M73 
CIT Sensor, Woodward 9178M37 - - - - 9334M96 - -
Power Management Control, GE 7076M20 7084M61 7129M23 7090M98 7125M15 
7157M60 7157M61 7157M64 7139M84 7139M91 
7045M91 --- --- 7157M62 7157M63 
7157M66 7157M67 
* 
PAGE 1 2 3 4 5 6 7 8 
REV. 13 12 12 12 11 12 12 11 
LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
"---" NOT APPLICABLE 
NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN.

I 
I 
TCDS E21EU PAGE 2 
II. MODELS (See NOTE 12) CFM56-3C 
TYPE 
RATINGS (See NOTE 4) 
High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, 
multi-stage compressor with one stage turbine and annular combustor. 
Takeoff (5 min., see NOTE 16), 
sea level, static thrust, lb./daN 
Maximum continuous, sea level 
static thrust, lb. 
Flat rating 
Takeoff 
Maximum continuous 
FUEL SYSTEM 
Fuel Control, Woodward 
23,515/10,460 
21,850/9,719 
AMBIENT TEMPERATURE 
86oF / 30oC 
77oF / 25oC 
See NOTE 8 for approved fuels 
GE PART NO. 
1459M27 
9387M15 
CIT Sensor, Woodward 9334M96 
Power Management Control, GE 7147M10 
7157M68 
I. MODELS (Continued) CFM56-2 CFM56-2B CFM56-2A CFM56-3 CFM56-3B 
FUEL SYSTEM (Cont.) 
Fuel Pump, TRW 
SAFRAN PART NUMBER 
301-776-101-0 301-776-101-0 301-779-101-0 301-778-801-0 - -
Combined boost and single 301-776-102-0 301-776-102-0 301-779-102-0 301-778-802-0 - -
element gear type pump 301-776-103-0 301-776-104-0 301-779-103-0 301-778-804-0 - -
301-776-104-0 301-776-105-0 --- 301-778-805-0 - -
301-776-105-0 301-776-106-0 --- 301-778-806-0 - -
301-776-106-0 301-776-109-0 --- 301-779-001-0 - -
301-776-108-0 301-776-111-0 --- 301-779-002-0 - -
301-776-109-0 301-776-112-0 --- 301-779-005-0 - -
301-776-110-0 301-776-113-0 --- 301-779-006-0 - -
301-776-111-0 301-776-114-0 --- 301-779-007-0 - -
301-776-112-0 301-776-115-0 --- --- ---
301-776-113-0 301-779-001-0 --- --- ---
301-776-114-0 301-779-005-0 --- --- ---
301-776-115-0 301-779-007-0 --- --- ---
301-778-801-0 301-779-101-0 --- --- ---
301-778-802-0 301-779-102-0 --- --- ---
301-778-804-0 301-779-103-0 --- --- ---
301-778-805-0 --- --- --- ---
301-778-806-0 --- --- --- ---
301-779-001-0 --- --- --- ---
301-779-002-0 --- --- --- ---
301-779-005-0 --- --- --- ---
301-779-006-0 --- --- --- ---
301-779-007-0 --- --- --- ---
Fuel/Oil Heat Exchanger 301-771-402-0 301-771-402-0 301-779-401-0 301-776-401-0 - -
301-771-403-0 301-779-401-0 301-779-402-0 301-776-402-0 - -
301-771-404-0 301-779-402-0 --- 301-776-403-0 - -
301-780-501-0 - -
Servo Fuel Heater 301-772-901-0 301-772-901-0 301-779-501-0 301-776-501-0 - -
301-779-501-0 301-779-502-0 301-776-502-0 - -
301-779-502-0 --- --- ---

I 
TCDS E21EU PAGE 3 
I. MODELS (Continued) CFM56-2 CFM56-2B CFM56-2A CFM56-3 CFM56-3B 
OIL 
Models CFM56-2/-2B/-2A 
Models CFM56-3/-3B/-3C 
IGNITION SYSTEM 
Two ignition units 
Synthetic type conforming to GE Specification D50TF1, Type 1 or 2. CFM Service Bulletin 
(CFM56-2) 79-0001 lists approved oil brands. 
Synthetic type conforming to GE Specification D50TF1, Type 1 or 2. CFM Service Bulletin 
(CFM56-3/-3B/-3C) 79-0001 lists approved oil brands. 
GE PART NO. 
9238M66 - - - - - - - -
1538M69 - - - - - - - -
9101M52 
Two igniter plugs 1153M38 9275M71 - - - - - -
1374M12 - - - - - - - -
1153M38 9276M36 - - - - - -
PRINCIPAL DIMENSIONS 
Length, (fan case forward 
flange to LPT rear frame aft 
flange) 
1374M13 - - - - - - - -
INCHES / MILLIMETERS 
95.7/2430 - - - - 93.1/2364 - -
Width, (fan casing forward 
flange diameter) 
72.04/1830 - - - - 63.39/1610 - -
Height, (bottom of accessory 
gearbox to top of fan casing 
forward flange) 
WEIGHT (dry) 
Pounds / Kilograms 
CENTER OF GRAVITY 
LOCATIONS 
Inches 
Millimeters 
84.25/2140 - - - - 66.61/1692 - -
Includes basic engine accessories and optional equipment as listed in manufacturers engine 
specification, including engine mounted portions of the condition monitoring instrumentation. 
4711/2139 - - 4850/2200 4309/1954 4334/1966 
STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) 
206+1 - - 205+1 209+1 - -
5233+25 - - 5220+25 5319+25 - -
II. MODELS (Continued) CFM56-3C 
FUEL SYSTEM (Cont.) 
Fuel Pump, TRW 
SAFRAN PART NUMBER 
301-778-802-0 
Combined boost and single 301-779-001-0 
element gear type pump 301-779-002-0 
Fuel/Oil Heat Exchanger 301-776-401-0 
301-776-402-0 
301-776-403-0 
301-780-501-0 
Servo Fuel Heater 301-776-501-0 
OIL 
Models CFM56-2/-2B/-2A 
Models CFM56-3/-3B/-3C 
IGNITION SYSTEM 
Two ignition units 
301-776-502-0 
Synthetic type conforming to GE Specification D50TF1, Type 1 or 2. CFM Service Bulletin 
(CFM56-2) 79-0001 lists approved oil brands. 
Synthetic type conforming to GE Specification D50TF1, Type 1 or 2. CFM Service Bulletin 
(CFM56-3/-3B/-3C) 79-0001 lists approved oil brands. 
GE PART NO. 
9238M66 
1538M69 
Two igniter plugs 9275M71 
1374M12 
9276M36 
1374M13

I 
-
-
TCDS E21EU PAGE 4 
II. MODELS (Continued) CFM56-3C 
PRINCIPAL DIMENSIONS 
Length, (fan case forward 
flange to LPT rear frame aft 
flange) 
INCHES / MILLIMETERS 
93.1/2364 
Width, (fan casing forward 
flange diameter) 
63.39/1610 
Height, (bottom of accessory 
gearbox to top of fan casing 
forward flange) 
WEIGHT (dry) 
Pounds / Kilograms 
CENTER OF GRAVITY 
LOCATIONS 
Inches 
Millimeters 
66.61/1692 
Includes basic engine accessories and optional equipment as listed in manufacturers engine 
specification, including engine mounted portions of the condition monitoring instrumentation. 
4334/1966 
STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) 
209+1 
5319+25 
CERTIFICATION BASIS Code of Federal Regulations Part 33 effective February 1, 1965, with Amendments 33-1 
through 33-6 thereto. In addition, the engines are in compliance with the emissions 
requirements of Special Federal Aviation Regulation No. 27-5. Exemption No. 2641 from 
compliance with 14 CFR §33.88 issued Nov. 20, 1978, Exemption No. 2850 from 
compliance with 14 CFR §33.7 issued October 31, 1979, and Exemption No. 83-ANE-001E 
from compliance with 14 CFR §33.14 issued July 27, 1983. 
APPLICATION TYPE CERTIFICATE TYPE CERT. 
MODEL DATE ISSUED/AMENDED WITHDRAWN 
CFM56-2 AUG 07, 1975 NOV 08, 1979 
CFM56-2B JUL 28, 1981 JUN 25, 1982 
CFM56-3 SEP 17, 1980 JAN 12, 1984 
CFM56-3B MAR 05, 1984 JUN 19, 1984 
CFM56-2A DEC 15, 1983 JUN 06, 1985 
CFM56-3C APR 07, 1986 DEC 18, 1986 
The Direction Generale de L'Aviation Civile (DGAC) originally type certificated these 
engine models under DGAC Certificate de Type Moteur M9. The FAA validated these 
products under US Type Certificate Number E21EU. Effective September 28, 2003, the 
European Aviation Safety Agency (EASA) began oversight of these products on behalf of 
France. 
PRODUCTION BASIS The original production basis was French "Agreement de Production" No. F.G.007 or P03 
issued by Direction Generale de l'Aviation Civile (DGAC) for engines produced in France by 
SNECMA (now SAFRAN) under license from CFM International, S.A. Effective September 
28, 2004, these engine models were produced under European Aviation Safety Agency 
(EASA) Production Certificate FR.21G.0007. (See NOTE 11). 
IMPORT REQUIREMENTS To be considered for installation on aircraft registered in the United States, each individually 
imported engine must be accompanied by EASA airworthiness approval certificate (EASA 
Form 1 – Authorized Release Certificate) or JAA Form 1 issued by SAFRAN on behalf of 
EASA under EASA Production Certificate FR.21G.0007. 
The EASA Form 1 – Authorized Release Certificate, or JAA Form 1, should contain the 
following statement: ‘The engine covered by this certificate has been examined, tested, and 
found to conform to U.S. Type Certificate Number E21EU and to be in a condition for safe 
operation.’ 
See NOTE 11. For further information.

I 
TCDS E21EU PAGE 5 
NOTES 
MODELS CFM56-2 CFM56-2B CFM56-2A CFM56-3 CFM56-3B CFM56-3C 
NOTE 1. 
TURBINE EXHAUST GAS 
(T495) 
Takeoff (5 min., see NOTE 16) 
Takeoff Transient (20 sec.) 
Maximum continuous 
Starting 
Time temperature envelope 
Refer to model's S.O.I. 
OIL (See NOTE 15) 
Continuous operation 
Transient (15 minutes) 
NOTE 2. 
Fuel limits 
Oil limits 
Refer to model's S.O.I. 
NOTE 3. 
STARTER 
Rotation (1) 
Speed ratio to core 
Maximum torque (in-lbs) 
Continuous 
Static 
Maximum overhung moment 
(in-lbs) 
ELECTRICAL 
Rotation (1) 
Speed ratio to core 
Maximum torque (in-lbs) 
Continuous 
Static 
Maximum overhung moment 
(in-lbs) 
FORWARD HYDRAULIC PUMP 
Rotation (1) 
Speed ratio to core 
Maximum torque (in-lbs) 
Continuous 
Static 
Maximum overhung moment 
(in-lbs) 
AFT HYDRAULIC PUMP 
Rotation (1) 
Speed ratio to core 
Maximum torque (in-lbs) 
Continuous 
Static 
Maximum overhung moment 
(in-lbs) 
MAXIMUM PERMISSIBLE TEMPERATURES 
For engine configurations designated by a suffix for specific installation (see NOTE 12), refer to 
the appropriate S.O.I. for maximum operating temperatures. 
As measured by a harness of six or nine thermocouples located at the second stage low pressure 
turbine vanes. 
905oC 
---
870oC 
TP.O1.6 
- -
---
- -
TP.01.7 
930oC 
---
895oC 
TP.01.10 
- -
940oC 
- -
TP.01.9 
- -
- -
- -
- -
- -
- -
- -
- -
Refer to the appropriate installation manual and S.O.I. 
140oC 
155oC 
160oC 
175oC 
140oC 
155oC 
160oC 
165oC 
- -
- -
- -
- -
FUEL AND OIL PRESSURE LIMITS 
Refer to the appropriate installation manual 
TP.01.6 TP.01.7 TP.01.10 TP.01.9 - - - -
ACCESSORY DRIVE PROVISIONS (see also next page) 
CW 
1.343:1 
4,150 
10,444 
300 
CW 
1.343:1 
4,150 
10,444 
300 
CW 
1.343:1 
4,900 
9,700 
340 
CCW 
0.996:1 
5,400 
13,370 
300 
- -
- -
- -
- -
- -
- -
- -
- -
- -
- -
CW 
0.561:1 
(125 kw) 
10,900 
2,100 
CW 
0.561:1 
(125 kw) 
10,900 
2,100 
CW 
0.5823:1 
165 hp 
7,000 
1,600 
CW 
0.562:1 
2,500/135 kw 
8,800 
2,500 
- -
- -
- -
- -
- -
- -
- -
- -
- -
- -
CCW 
0.254:1 
1,500 
6,398 (2) 
500 
---
---
---
---
---
CW 
0.255:1 
1,000 
4,400 
400 
CW 
0.255:1 
1,500 
4,400 
500 
- -
- -
- -
- -
- -
- -
- -
- -
- -
- -
CW 
0.254:1 
1,000 
6,398 (2) 
400 
CW 
0.254:1 
2,390 
6,398 
400 
---
---
---
---
---
---
---
---
---
---
---
---
---
---
---
---
---
---
---
---
(1) CW = CLOCKWISE / CCW = COUNTERCLOCKWISE 
(2) Total torque for forward and aft hydraulic pump drives must not exceed 6,398 in- 
pounds static.

TCDS E21EU PAGE 6 
NOTE 4. Engine ratings are based on calibrated stand performance under the following conditions: 
For the CFM56-2/-3/-3B/-3C, takeoff thrust is nominally independent of ambient temperature 
(flat rated) up to ambient temperature of Std + 15oC; for the CFM56-2B, Std +17.2oC; and for 
the CFM56-2A, Std +20oC; 
Maximum continuous is nominally independent of ambient temperature (flat rated) to Std 
+10oC; 
Zero customer bleed and horsepower extraction; 
No scrubbing drags; 
100% inlet recovery; and 
Based on CFM International referee separate flow exhaust system. 
NOTE 5. Fan exhaust/reverser system models CFM56-FR02B and CFM56-FR03B are approved for 
incorporation on CFM56-2 and CFM56-2A engine models, respectively, in accordance with 14 
CFR Part 33. 
NOTE 6. 
MODELS CFM56-2 CFM56 
-2B 
CFM56-
2A 
CFM56-3 CFM56-
3B 
CFM56-3C 
MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS 
Low Pressure 
Rotor (N1), rpm 
High Pressure 
Rotor (N2), rpm 
5,280 (102%) 
15,183 (105%) 
- -
- -
- -
- -
5,490 (106%) 
- -
- -
- -
- -
- -
NOTE 7. Maximum permissible air bleed extraction: Refer to the appropriate Installation Manual. 
NOTE 8. Approved fuel conforming to GE Specification D50TF2. MIL-T-5624, Grades JP-4 or JP-5, 
ASTM D1655, Jet A, A1, and B are consistent with this GE specification. 
PRIMARY FUEL 
For the CFM56-2/-3/-3B/-3C, the primary fuel is Jet A. 
For the CFM56-2A/-2B, the primary fuel is JP4. 
AVIATION GASOLINE, MOTOR GASOLINE, EMERGENCY FUELS, AND FUEL 
ADDITIVES 
For the CFM56-2/-3/-3B/-3C use of aviation gasoline is not authorized. Consult appropriate 
Operating Manual for additive usage. 
For the CFM56-2B and -2A use of aviation gasoline and motor gasoline is authorized for periods 
not to exceed six hours. Consult appropriate Operating Manual for action following use of 
emergency fuels and for additive usage. 
For limitations on use of emergency fuels with the CFM56-2B and -2A, consult the appropriate 
Installation Manual. 
NOTE 9. Life limits established for critical rotating components are published in each model's Shop Manual. 
NOTE 10. Power setting, power checks and control of engine thrust output in all operations is to be based on 
CFM engine charts referring to fan speed. Fan speed sensors are included in the engine assembly 
for this purpose.

TCDS E21EU PAGE 7 
NOTE 11. The type certificate holder, CFM International, S.A., is a company established and jointly owned 
by SAFRAN Aircraft Engines, formerly SNECMA, of France and the General Electric Company 
for the certification, sale, and support of CFM56 series engines. With respect to the benefits of 
type certification for production, SAFRAN and General Electricfunction as licensees of CFM 
International, S.A. 
This type certificate applies only to engines produced in France under DGAC Certificate de Type 
Moteur M9. Engines of the same model designation produced in the United States under Type 
Certificate No. E2GL are identical to and fully interchangeable with engines produced under this 
type certificate. Similarly, modules, assemblies, or parts produced in the United States under 
Production Certificate No. 108 are eligible for use in engines produced under this type certificate. 
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. 
For a list of the applicable engine serial numbers refer to the latest revisions of following Service 
Bulletins: 
CFM56-2A Service Bulletin 72-0649 "CFM56-2A Engine Serialization Manufacturing Sequence" 
or 
CFM56-2B Service Bulletin 72-0801 "CFM56-2B Engine Serialization Manufacturing Sequence" 
or 
CFM56-2C Service Bulletin 72-1040 "CFM56-2C Engine Serialization Manufacturing Sequence" 
or 
CFM56-3 Service Bulletin 72-1175 "CFM56-3 Engine Serialization Manufacturing Sequence" 
Effective September 28, 2004, engines produced by SAFRAN were produced under EASA 
Production Certificate FR.21G.0007. 
NOTE 12. A suffix may be added to the basic engine model number on the engine nameplate to identify minor 
variations in engine configuration, installation components or reduced ratings peculiar to aircraft 
installation requirements. For example: CFM56-2-xx. 
Engines that have a suffix added to the basic model number are identified in CFM International 
Service Bulletins, and are summarized below: 
Engine Model Service Bulletin No. Application 
CFM56-2-C1/-C5 72-0001 (CFM56-2) DC8-71/-72/-72F/-73 
CFM56-2-C2 72-0001 (CFM56-2) None 
CFM56-2-C3/-C6 72-0001 (CFM56-2) DC8-72F 
CFM56-2A-2/-3 72-0001 (CFM56-2A) No Commercial Application 
CFM56-2B-1/-2 72-0001 (CFM56-2B) No Commercial Application 
CFM56-3-B1 72-0001(CFM56-3/-3B/-3C) 737-300/-500 
CFM56-3B-2 72-0001 (CFM56-3/-3B/-3C) 737-300/-400 
CFM56-3C-1 72-0001 (CFM56-3/-3B/-3C) 737-300/-400/-500 
NOTE 13. For the CFM56-3/-3B/-3C models, the throat area of the inlet installed on the engine shall not 
exceed 2700 sq. in. (1.742 sq. meters) of area.

TCDS E21EU PAGE 8 
NOTE 14. For inflight operation during icing conditions: 
For the CFM56-2 series engines, the minimum permissible N1 RPM is 37 percent. However, 
momentary N1 excursions below 37 percent, not to exceed 60 seconds duration, are permissible for 
approach and landing operation below 10,000 feet pressure altitude. 
For CFM56-2 series engines which are equipped with 43 percent rich pilot fuel nozzles, in 
accordance with CFM56-2 Service Bulletin Number 73-0047, the minimum permissible N1 RPM 
for inflight operation is 29 percent. 
For CFM56-3/-3B/-3C engines, the minimum permissible N1 RPM for inflight operation during 
icing conditions is 21.8 percent. 
NOTE 15. The oil temperature for the CFM56-2B, CFM56-3, CFM56-3B, and CFM56-3C is measured at the 
scavenge pump discharge. The oil temperature for the CFM56 -2A and CFM56-2-C series engines 
is measured at the supply pump discharge. 
The transient limit is defined as 15 minutes for all models except for the CFM56-2B. The transient 
limit is defined as 10 minutes for the CFM56-2B. 
The continuous operation and transient oil temperature limits for the CFM56-2-C1, -2-C3, 
-2-C5, and -2-C6 is 140oC and 155oC respectively. The continuous operation and transient oil 
temperature limits for the CFM56-2-C2 is 150oC and 155oC respectively. Refer to S.O.I. TO.01.6. 
NOTE 16. The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency for 
the CFM56-3/-3B/-3C. 
NOTE 17. Installation Manuals, Specific Operating Instructions, Service Bulletins, Overhaul and Maintenance 
Manuals, Repair Manuals, Vendor Manuals, and Design Changes which contain a statement that 
the document is EASA approved or approved under authority of DOA No. EASA.21J.086 or for 
approvals made before September 28, 2003 by DGAC are accepted by the FAA and considered 
FAA approved. Repair data and related instructions are considered FAA approved or accepted as 
applicable. These approvals pertain to the type design only. 
----END----
```

## ADs

None name its models.

## STCs approved under this data sheet (3)

- [STC SE00032EN](https://openairdocs.org/stc/SE00032EN): Installation of Pratt & Whitney (P&W) Global Material Solutions (GMS) CFM56-3 Fan/Booster Module.. Pratt & Whitney
- [STC SE00033EN](https://openairdocs.org/stc/SE00033EN): Installation of Pratt & Whitney (P&W) Global Material Solutions (GMS) CFM56-3 High Pressure Compressor Module. Pratt & Whitney
- [STC SE00035EN](https://openairdocs.org/stc/SE00035EN): Installation of Pratt & Whitney (P&W) Global Material Solutions (GMS) CFM56-3 Low Pressure Turbine Module. Pratt & Whitney

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