# TCDS E15NE: General Electric Company GE Aerospace - Type: Type certificate data sheet - Status: Current - Holder: General Electric Company GE Aerospace - Revision: 14 - Revised: July 9, 2024 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 483, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/bc/14/bc1432e2fb4acad418f0ce01b610ef85cd41aaf521c9820550c4125654553e36 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID149810607420240710135834.0001 - Page: https://openairdocs.org/tcds/E15NE ## Models (6) As the data sheet lists them. - CF34-3A1 - CF34-3B - CF34-1A - CF34-3A - CF34-3B1 - CF34-3A2 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E15NE TCDS NUMBER E15NE REVISION: 14 DATE: July 9, 2024 GENERAL ELECTRIC COMPANY MODELS: CF34-1A CF34-3A2 CF34-3A CF34-3B CF34-3A1 CF34-3B1 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E15NE) 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: General Electric Company GE Aerospace 1000 Western Ave Lynn, Massachusetts 01910 1. MODELS CF34-1A CF34-3A CF34-3A2 CF34-3A1 CF34-3B/-3B1 TYPE Turbofan, single stage fan, fourteen stage axial compressor, annular combustion chamber, two stage high pressure turbine, four stage low pressure turbine. RATINGS (See NOTE 5) Sea level static thrust, lb Maximum takeoff (5 min.) (See NOTES 14 and 16) 9140 9220 - - - - - - Normal takeoff (5 min.) (See NOTES 14 and 16) 8650 8729 - - - - - - Maximum continuous (See NOTE 14) 8920 9140 - - - - - - FUEL Control, Woodward Governor GE P/N GE P/N GE P/N GE P/N 6047T74 - - 6091T07 6078T55 6078T55 4147T69 4147T70 FUEL (See NOTE 9) Fuel conforming to GE Jet Fuel Specification No. D50TF2, current revision. See SEI- 579 (CF34) Operating Instructions for specific fuels approved per the subject specifications. OIL Oil conforming to GE Specification No. D50TF1, current revision. See SEI-579 (CF34), Operating Instructions for specific oils approved per the subject specifications. PRINCIPAL DIMENSIONS Length, inches Maximum diameter, inches WEIGHT (dry maximum), pounds 103.19 49.6 1625 - - - - - - - - - - - - - - - - 1655 - - - - 1670 * PAGE 1 2 3 4 5 6 REV. 14 14 8 8 11 14 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. TCDS E15NE PAGE 2 1. MODELS CF34-1A CF34-3A CF34-3A2 CF34-3A1 CF34-3B/- 3B1 CENTER OF GRAVITY LOCATION, inches Forward of combustion chamber forward flange Below horizontal centerline Relative to vertical centerline 6.83 1.00 0.00 - - - - - - - - - - - - 7.9 0.7 -1.0 - - - - - - IGNITION SYSTEM CF34-1A Simmonds type 83311 or Bendix type 10-397550-1ignition exciter with two igniters, Champion type FHE256-10. CF34-3A Same as CF34-1A through engine 350335; from engine 350336, two igniters Champion type GE P/N 4048T30P10. CF34-3A2 Simmonds type GE P/N 1538M69, or Unison type GE P/N 9238M66 ignition exciters, with two igniters, Unison type GE P/N 4096T38P04. CF34-3A1/ Same as CF34-3A2, except may use alternate igniters, -3B/-3B1 Unison type GE P/N 4096T38P01. CERTIFICATION BASIS: 14 CFR Part 33, effective February 1, 1965, as amended by amendments 33- 1through 33-9; amendment 33-10 for 14 CFR Section 33.14; and FAA Grant of Exemption 3473. Type Certificate Model Date of Application No. E15NE Issued CF34-1A October 24, 1980 August 18, 1982 CF34-3A November 26, 1985 September 26, 1986 CF34-3A1 August 16, 1989 July 24, 1991 CF34-3A2 September 3, 1992 October 9, 1992 CF34-3B/-3B1 July 26, 1993 May 31, 1995 The following models comply with 14 CFR part 34, amendment 7A, effective May 24, 2024. See note 18, for detailed summary of the certification basis for fuel venting and exhaust emissions: CF34-3A, CF34-3A1, CF34-3A2, CF34-3B, CF34- 3B1. PRODUCTION BASIS: Production Certificate No. 108 NOTES Notes 1 through 18 applicable to CF34-1A/-3A/-3A2. Notes 1 through 8, and 11 through 18 applicable to CF34-3A1/-3B/-3B1. TCDS E15NE PAGE 3 NOTE 1. Maximum permissible engine operating speeds for the engine rotors are as follows: CF34-1A CF34-3A/-3A2 CF34-3A1 CF34-3B/-3B1 Low pressure rotor (N1), rpm Maximum takeoff 7,300 - - - - - - Normal takeoff 7,120 - - - - - - Maximum continuous 7,300 - - - - - - High pressure rotor (N2), rpm Maximum takeoff 17,710 - - - - - - Normal takeoff 17,510 - - - - - - Maximum continuous 17,674 - - - - - - Refer to GE Maintenance Manual SEI-580 and Overhaul Manual SEI-582 for CF34-1A/-3A/-3A2, and GE Engine Manual SEI-756 for CF34-3A1/-3B/-3B1 for inspection requirements when limits are exceeded. 100 percent N1 rotor speed is 7,400 rpm. 100 percent N2 rotor speed is 17,820 rpm. NOTE 2. Maximum permissible temperatures are as follows: Interturbine temperature (T5)*, oF(oC) CF34-1A CF34-3A/-3A2 CF34-3A1 CF34-3B/-3B1 Maximum takeoff (5 min.) 1,575(857) 1,600(871) 1,650(899) - - Maximum takeoff (2 min. 1,627(886) 1,652(900) 1,702(928) - - transient out of a total of 5 minutes) Normal takeoff (5 min.) 1,548(842) 1,573(856) 1,623(884) - - Normal takeoff (2 min. 1,587(864) 1,613(878) 1,663(906) - - transient out of a total of 5 minutes) Maximum continuous 1,540(838) 1,580(860) 1,630(888) 1650(899) *The interturbine temperature is measured by 10 thermocouples mounted in the low pressure turbine transition casing. Additional transient temperature and time limits of less than 1 minute are defined in GE Operating Instructions SEI-579. Refer to GE Maintenance Manual SEI-580 and Overhaul Manual SEI-582 for CF34-1A/-3A/-3A2, and GE Engine Manual SEI-756 for CF34-3A1/-3B/-3B1, for inspection requirements when limits are exceeded. Oil inlet temperature**, oF (oC) Continuous operation 311(155) - - - - - - Transient operation 358(163) - - - - - - **Transient operation above 311oF(155oC) is limited to 15 minutes. Fuel inlet temperature (at engine fuel filter inlet), oF(oC) Continuous operation JP5 158(70) - - 250(121) - - JP4, JP4/JP5 mixture 158(70) - - 250(121) - - Ground operation 158(70) - - 250(121) - - TCDS E15NE PAGE 4 NOTE 3. Fuel and Oil Pressure Limits Fuel: At engine pump inlet: minimum pressure of 5 PSID above the true vapor pressure of the fuel with a vapor/liquid ratio of zero with aircraft boost operative. Operating range 5 PISG to 50 PSIG. At engine motive flow discharge: minimum pressure of 150 PSIG at idle or above. Operating range is 150 PSIG to 700 PSIG. Oil: CF34-1A/-3A/-3A2: at idle on the ground, 25 PSID minimum to 50 PSID maximum. At takeoff, 40 PSID minimum to 80 PSID maximum. Operating range, 25 PSID to 80 PSID, allowable to 95 PSID above 16,000 feet. CF34-3A1/-3B/-3B1: At idle on the ground, 25 PSID minimum to 75 PSID maximum. At takeoff 45 PSID minimum to 95 PSID maximum. Operating range, 25 PSID to 95 PSID, allowable to 110 PSID above 16,000 feet. NOTE 4. ACCESSORY DRIVE PROVISIONS Accessory Drive Pad Type Speed Ratio to Core Rotor Rotation Facing Pad Maximum Torque (in-lb) Cont. Static Max. Cont. Power (HP) Max. Acc. Wt. (lbs.) O'hung Momen t (in-lb) Gasket Starter (4) AS969A-2S(1) .3987 C 6,000 13,000 - - 80 625 None Hydraulic Pump AS969A-3CT(2) .3288 C 750 (6) 3,750 71 50 350 None Electric Generator AS971A-8CS(3) .9815 C 1,050 5,250 165(5) 150 2,500 None C - clockwise; CC - counterclockwise 1. Pad modified for torque, speed and stud location. 2. Pad modified for torque. 3. Pad modified for speed, power, overhung moment, and stud length and elimination of V-band clamp flange. 4. Pneumatic starter must be fitted with a deflector to prevent impingement of starter discharge air on engine casing. 5. Pad rated at constant horsepower from 9,900 to 17,815 pad RPM with a 5 minute overload rating of 180 horsepower and a 5 second overload rating of 240 horsepower. 6. A short-time overload rating of 1300 in-lb can be applied for six (6) seconds at a time. NOTE 5. Engine ratings are based on calibrated test stand performance under the following conditions: Static sea level standard conditions of 59oF and 29.92 inches Hg. No aircraft accessory loads or air extraction. No anti-icing; no inlet distortion; no inlet screen losses; and 100% ram recovery. Inlet bellmouth per Table in Zone D-8 of Installation Drawing 6036T80, Sheet 6, for CF34-1A/-3A/-3A2; Installation Drawing 6078T61, Sheet 6, for CF34-3A1/-3B/-3B1; contained in GE Installation Manual SEI-567. Referee short cowl system as described in Part A, Appendix I contained in GE Installation Manual SEI-567. Specified fuel having an average lower heating value of 18,400 BTU/lb; specified lube oil. TCDS E15NE PAGE 5 NOTE 6. Air Bleed Extraction - maximum permissible customer air bleed extraction is as follows: Customer bleed air is available from stages 10 and 14 of the compressor at all operating conditions at or above idle. (No compressor bleed is permitted below idle. Location Maximum Bleed Air (% of Total Compressor Airflow Compressor Stage 10, (for cabin condition use) 800oF max. 4 Compressor Stage 14, 1000oF max. 6 Minimum required bleed above 40,000 feet is 2 percent; maximum power extraction above 40,000 feet is 32 HP. NOTE 7. These engines meet FAA requirements for operation in icing provided a minimum core speed (N2) of 11,400 rpm, corrected to 59oF, is maintained. NOTE 8. The maximum permissible inlet distortion for these engines is specified in GE Installation Manual SEI-567. NOTE 9. On CF34-1A/-3A/-3A2, unless the engine is equipped with an optional fuel heater, the following approved fuel additives must be used individually or in combination: Phillips PFA-55MB or anti-icing additives to specification MIL-I-27686E at a concentration of 0.10 to 0.15% by volume. NOTE 10. Reserved. NOTE 11. Life limits, established for critical rotating components, are published in FAA approved GE Maintenance Manual SEI- 580 for CF34-1A/-3A/-3A2, GE Engine Manual SEI-756 for CF34-3A1/-3B1 and GE Service Manual SEI-780 for CF34-3A1/-3B. NOTE 12. Recommend maintenance inspection intervals are published in GE Maintenance Manual SEI-580 for CF34-1A/-3A/- 3A2, GE Engine Manual SEI-756 for CF34-3A1/-3B1 and GE Service Manual SEI-780 for CF34-3A1/-3B. NOTE 13. The operating temperature limit for specific components and accessories specified in Table A-4 of GE Installation Manual SEI-567 must be observed when installing the engine. NOTE 14. The static thrust at sea level are rated at 59oF ambient temperature and below for CF34-1A model and at 70oF ambient temperature and below for CF34-3A/-3A1/-3A2 models. For the CF34-3B, static thrusts at sea level are rated at 86oF ambient temperature and below. For CF34-3B1, static thrusts at sea level is rated at 86oF ambient temperature and below for maximum takeoff and at 73oF and below for normal takeoff and maximum continuous. The c omputer performance decks for calculating engine performance are as follows: Engine Model Computer Deck No. CF34-1A 82070 CF34-3A/-3A1/-3A2 85168A CF34-3B/-3B1 94111D NOTE 15. CF34 engines comply with the applicable fuel venting and exhaust emission requirements of SFAR 27-5 and 40 CFR 87.21 except those engines exempted by Grant of Exemption Nos. 4049 and 4049A under provisions of 40 CFR 87.7(b) and Grant of Exemption Nos. 4594 and 4594A under provisions of 40 CFR 87.7(c). The following engine models manufactured after December 31, 1999 comply with 14 CFR Part 34, effective September 10, 1990, including Amendments 34-1 through 34-3: CF34-3A1, CF34-3B, CF34-3B1. TCDS E15NE PAGE 6 NOTE 16. When the automatic reset mechanism in the fuel control is utilized, operation to the normal takeoff rating operating limits will insure the maximum takeoff rating operating limits are not exceeded when the reset mechanism is actuated. The time limit at the normal takeoff rating is five minutes and shall include any time accumulated above the normal takeoff rating. NOTE 17. The above models incorporate the following general characteristics: Model Characteristics CF34-1A Basic Model CF34-3A Same as -1A except for increased interturbine temperature and rating. The thrust is flat rated to 70oF ambient temperature sea level static. CF34-3A1 Same as -3A except for increased interturbine temperature and improved maintainability and durability features, compatible with airline service requirements. CF34-3A2 Same as -3A except for improved combustor, ignition system, and fuel control 3-D cam, same as -3A1, modified fuel distribution system, and revised starting procedures/ CF34-3B/-3B1 Same as -3A1 except for improved stage 1 compressor and HPT and LPT stator cooling and clearance control modifications. CF34-3B and -3B1 configurations are identical except for flat rating points (see NOTE 14). NOTE 18. The following emissions standards promulgated in 14 CFR part 34, amendment 7A, effective May 24, 2024, and 40 CFR part 1031, effective December 23, 2022, have been complied with for: CF34-3A, CF34-3A1, CF34-3A2, CF34-3B, CF34-3B1. Fuel Venting Emission Standards: 14 CFR 34.11; in addition, 40 CFR 1031.30(b) Smoke Number (SN) Emission Standards: 14 CFR 34.21(e); in addition, 40 CFR 1031.60(a)(5) Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 1031.60(c) Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 1031.60(d) Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(b)(1); in addition, 40 CFR 1031.60(e)(5) (also known as Tier 8 new type) non-volatile Particulate Matter (nvPM) Mass Concentration Emission Standards: 14 CFR 34.25(a)(1); in addition, 40 CFR 1031.60(a)(6) (also known as Tier 10) nvPM Mass and Number Emission Standards: 14 CFR 34.25(a)(2); in addition, 40 CFR 1031.60(b)(2) (also known as Tier 11 in-production) In addition to the FAA's finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Fourth Edition, Amendment 10, effective July 20, 2020, have also been demonstrated for the following: • Part II, Chapter 2 for Fuel Venting • Part III, Chapter 2, Section 2.2.2 for Smoke number, • Part III, Chapter 2, Section 2.3.2 for Carbon monoxide and Hydrocarbons, • Part III, Chapter 2, Section 2.3.2.e for Oxides of Nitrogen (also known as CAEP/8), • Part III, Chapter 4, Section 4.2.2.1 for nvPM Mass Concentration (also known as CAEP/10), and • Part III, Chapter 4, Section 4.2.2.2 for nvPM Mass and Number (also known as CAEP/11) END ``` ## ADs (30, in force first) - [AD 2020-08-01](https://openairdocs.org/ad/2020-08-01): Turbine Engine Inlet Section · General Electric CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective May 15, 2020 - [AD 2009-26-09](https://openairdocs.org/ad/2009-26-09): Fan disks · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Feb 11, 2010 - [AD 2010-01-04](https://openairdocs.org/ad/2010-01-04): Fan blade · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Jan 25, 2010 - [AD 2009-07-12](https://openairdocs.org/ad/2009-07-12): High-pressure (HP) · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective May 7, 2009 - [AD 2006-04-12](https://openairdocs.org/ad/2006-04-12): Stage 5 low pressure turbine (LPT) disks · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Mar 30, 2006 - [AD 2005-18-16](https://openairdocs.org/ad/2005-18-16): High pressure turbine (HPT) rotating components · General Electric Aircraft Engines CF34-3A1. Effective Oct 13, 2005 - [AD 2004-26-02](https://openairdocs.org/ad/2004-26-02): Certain high pressure compressor (HPC) · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Jan 26, 2005 - [AD 2003-05-10 R1](https://openairdocs.org/ad/2003-05-10-R1): B-Sump Scavenge Screens · General Electric Aircraft Engines CF34-3A1, CF34-3B and CF34-3B1. Effective Nov 18, 2003 - [AD 2002-05-02](https://openairdocs.org/ad/2002-05-02): Life-Limited Rotating Parts · General Electric Aircraft Engines CF34-3A1 and CF34-3B1. Effective Apr 12, 2002 - [AD 2001-12-06](https://openairdocs.org/ad/2001-12-06): Lubrication System for the Engine Bearings · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Jul 20, 2001 - [AD 99-23-26 R1](https://openairdocs.org/ad/99-23-26-R1): Main Fuel Control (MFC) · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Feb 17, 2000 - [AD 99-22-10](https://openairdocs.org/ad/99-22-10): High Pressure Compressor (HPC) Spool and Disk · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 1 more. Effective Dec 27, 1999 - [AD 97-06-14](https://openairdocs.org/ad/97-06-14): Fan Disk · General Electric Aircraft Engines CF34-1A, CF34-3A and CF34-3A2. Effective May 27, 1997 - [AD 97-06-15](https://openairdocs.org/ad/97-06-15): HPC Stage 1 rotor disk · General Electric Aircraft Engines CF34-1A, CF34-3A and CF34-3A2. Effective May 27, 1997 - [AD 88-06-07](https://openairdocs.org/ad/88-06-07): Fuel Controls · General Electric Aircraft Engines CF34-1A and CF34-3A. Effective Mar 23, 1988 - [AD 2009-24-11](https://openairdocs.org/ad/2009-24-11) (historical): Fan blades · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Jan 4, 2010 - [AD 2007-07-07 R1](https://openairdocs.org/ad/2007-07-07-R1) (historical): Fan disks · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Sep 12, 2007 - [AD 2007-07-07](https://openairdocs.org/ad/2007-07-07) (historical): Fan disks · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Apr 23, 2007 - [AD 2007-05-16](https://openairdocs.org/ad/2007-05-16) (historical): Fan disks for an arc-out defect · General Electric Aircraft Engines CF34-3A1, CF34-3B and CF34-3B1. Effective Mar 12, 2007 - [AD 2006-05-04](https://openairdocs.org/ad/2006-05-04) (historical): Fan disks · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Apr 7, 2006 - [AD 2004-15-03 R1](https://openairdocs.org/ad/2004-15-03-R1) (historical): Stage 5 low pressure turbine (LPT) disks · General Electric Aircraft Engines CF34-3A1 and CF34-3B1. Effective Aug 31, 2004 - [AD 2004-15-03](https://openairdocs.org/ad/2004-15-03) (historical): Stage 5 Low Pressure Turbine (LPT) Disks · General Electric Aircraft Engines CF34-3A1 and CF34-3B1. Effective Aug 16, 2004 - [AD 2003-05-10](https://openairdocs.org/ad/2003-05-10) (historical): B-sump Oil Scavenge System · General Electric Aircraft Engines CF34-3A1, CF34-3B and CF34-3B1. Effective Apr 2, 2003 - [AD 2001-19-02](https://openairdocs.org/ad/2001-19-02) (historical): B-sump Scavenge Screens · General Electric Aircraft Engines CF34-3A1, CF34-3B and CF34-3B1. Effective Oct 9, 2001 - [AD 2000-03-03 R1](https://openairdocs.org/ad/2000-03-03-R1) (historical): Life-limited Parts · General Electric Aircraft Engines CF34-3A1 and CF34-3B1. Effective Jun 19, 2001 - [AD 2001-10-03](https://openairdocs.org/ad/2001-10-03) (historical): Fan Disks · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective May 31, 2001 - [AD 2000-03-03](https://openairdocs.org/ad/2000-03-03) (historical): Critical Life-Limited Rotating Engine Parts · General Electric Aircraft Engines CF34-3A1 and CF34-3B1. Effective Mar 13, 2000 - [AD 99-23-26](https://openairdocs.org/ad/99-23-26) (historical): Main Fuel Control (MFC) · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Dec 6, 1999 - [AD 99-11-08](https://openairdocs.org/ad/99-11-08) (historical): Main Fuel Control (MFC) · General Electric Aircraft Engines CF34-1A, CF34-3A, CF34-3A1 and 3 more. Effective Jul 27, 1999 - [AD 2007-04-51](https://openairdocs.org/ad/2007-04-51) (historical): Uncontained fan disk failure during flight operation · General Electric Aircraft Engines CF34-3A1, CF34-3B and CF34-3B1 ## Registered aircraft by registry model (OpenAirDocs) - [GE CF34-3B](https://openairdocs.org/engine/ge-cf34-3b): 327 aircraft (registry code 30069) - [GE CF34-3B1](https://openairdocs.org/engine/ge-cf34-3b1): 93 aircraft (registry code 30070) - [GE CF34-3A2](https://openairdocs.org/engine/ge-cf34-3a2): 20 aircraft (registry code 30067) - [GE CF34-3A](https://openairdocs.org/engine/ge-cf34-3a): 15 aircraft (registry code 30066) - [GE CF34-3A1](https://openairdocs.org/engine/ge-cf34-3a1): 15 aircraft (registry code 30068) - [GE CF-34-1A](https://openairdocs.org/engine/ge-cf-34-1a): 13 aircraft (registry code 30033) - [GE CF34-3](https://openairdocs.org/engine/ge-cf34-3-series): 0 aircraft (registry code 30166) ## STCs approved under this data sheet (1) - [STC SE01271LA](https://openairdocs.org/stc/SE01271LA): Installation of anti-ice shut-off/regulator valve p/n 5399-00-1.. 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