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2012-17-05: First stage low-pressure turbine (LPT1) rotor assembly

FAA order 2012-17-05 is an airworthiness directive in force since October 2, 2012. The FAA's subject line: First stage low-pressure turbine (LPT1) rotor assembly. It names the Honeywell TFE-731-series, Honeywell TFE731-4, Honeywell TFE731-4R, Honeywell TFE731-5, Honeywell TFE731-5BR, Honeywell TFE731-5R engines: about 391 aircraft on the U.S. register today across them, though an order usually covers particular versions or serial numbers rather than every one. System: engine.

What it applies to as the FAA lists it

Kind of product: Engine
Makes: Honeywell International Inc.
Models: TFE731-4, TFE731-4R, TFE731-5, TFE731-5AR, TFE731-5BR, TFE731-5R
Engine series: Honeywell TFE-731-series 291 aircraft
Honeywell TFE731-4 1 aircraft
Honeywell TFE731-4R 5 aircraft
Honeywell TFE731-5 1 aircraft
Honeywell TFE731-5BR 87 aircraft
Honeywell TFE731-5R 6 aircraft

Dates and paperwork

In force since: October 2, 2012
Published: August 28, 2012 (signed August 14, 2012)
Docket: FAA-2011-1045
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. models TFE731-4, -4R, -5, -5R, -5AR, and - 5BR series turbofan engines. This AD was prompted by a report of a rim/ web separation of a first stage low-pressure turbine (LPT1) rotor assembly. This AD requires replacing affected LPT1 rotor assemblies with assemblies eligible for installation. We are issuing this AD to prevent uncontained disk separation, engine failure, and damage to the airplane.

The order itself the regulatory text, as published

Show the full text (4,050 characters)

Adoption of the Amendment 

	Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 

PART 39--AIRWORTHINESS DIRECTIVES 

0 1. The authority citation for part 39 continues to read as follows: 

	Authority: 49 U.S.C. 106(g), 40113, 44701. 

Sec.  39.13  [Amended] 

0 2. The FAA amends Sec.  39.13 by adding the following new airworthiness directive (AD): 

2012-17-05 Honeywell International Inc. (formerly AlliedSignal Inc., formerly Garret Turbine Engine Company): Amendment 39-17168; Docket No. FAA-2011-1045; Directorate Identifier 2011-NE-32-AD. 

[[Page 51894]] 

(a) Effective Date 

	This AD is effective October 2, 2012. 

(b) Affected ADs 

	None. 

(c) Applicability 

	This AD applies to Honeywell International Inc.: 
	(1) Model TFE731-5 series turbofan engines, with a first stage low-pressure turbine (LPT1) rotor assembly, part number (P/N) 3075184-2, 3075184-3, or 3075184-4, installed, and 
	(2) Models TFE731-5AR and -5BR series turbofan engines, with a first stage LPT1 rotor assembly, P/N 3075447-1, 3075447-2, 3075447- 4, 3075713-1, 3075713-2, 3075713-3, or 3074748-5, installed, and 
	(3) Models TFE731-4, -4R, -5AR, -5BR, and -5R series turbofan engines, with an LPT1 rotor assembly, P/N 3074748-4, 3074748-5, 3075447-1, 3075447-2, 3075447-4, 3075713-1, 3075713-2, or 3075713-3, installed. 

(d) Unsafe Condition 

	This AD was prompted by a report of a rim/web separation of an LPT1 rotor assembly. We are issuing this AD to prevent uncontained disk separation, engine failure, and damage to the airplane. 

(e) Compliance 

	Comply with this AD within the compliance times specified, unless already done. 

(f) Engines Installed in Dassault-Aviation Falcon 20 and Construcciones Aeronauticas, S.A. (CASA) 101 Airplanes 

	(1) Remove the LPT1 rotor assembly at the next access to the LPT1 rotor assembly or at the next major periodic inspection, not to exceed 2,600 hours-in-service since last major periodic inspection, or 8 years after the effective date of this AD, whichever occurs first. 
	(2) Install an LPT1 rotor assembly that is eligible for installation. 

(g) Engines Not Installed in Dassault-Aviation Falcon 20 or CASA 101 Airplanes 

	(1) Remove the LPT1 rotor assembly at the next core zone inspection, not to exceed 5,100 hours-in-service since last core zone inspection, or at the next time the LPT1 rotor disc is removed for cause, or 8 years after the effective date of this AD, whichever occurs first. 
	(2) Install an LPT1 rotor assembly that is eligible for installation. 

(h) Definitions 

	(1) For the purpose of this AD, ``next access'' is when the low- pressure tie rod is unstretched. 
	(2) For the purpose of this AD, an LPT1 rotor assembly ``eligible for installation'' is an LPT1 rotor assembly not having a P/N listed in this AD. 

(i) Installation Prohibition 

	After the effective date of this AD,do not install any LPT1 rotor assembly listed by P/N in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, into any engine. 

(j) Alternative Methods of Compliance (AMOCs) 

	The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures in 14 CFR 39.19 to request an AMOC. 

(k) Related Information 

	(1) For more information about this AD, contact Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-5210: email: joseph.costa@faa.gov. 
	(2) Honeywell International Inc. Service Bulletin (SB) No. TFE731-72-3768; SB No. TFE731-72-3769; and SB No. TFE731-72-3770, pertain to the subject of this AD. 
	(3) For service information identified in this AD, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034- 2802; Web site: http://portal.honeywell.com; or call Honeywell toll free at phone: 800-601-3099 (U.S./Canada) or 602-365-3099 (International Direct). 

(l) Material Incorporated by Reference 

	None.

Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 7, 2026. Connections as data: /graph/directive/2012-17-05.json · aircraft systems.