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2009-10-01: High-pressure turbine (HPT) vane assemblies

FAA order 2009-10-01 is an airworthiness directive in force since June 9, 2009. The FAA's subject line: High-pressure turbine (HPT) vane assemblies. It names the Pratt & Whitney JT9D series engine: about 13 aircraft on the U.S. register today, 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: Pratt & Whitney Division
Models: JT9D-7R4E1, JT9D-7R4E4, JT9D-7R4G2, JT9D-7R4H1
Engine series: Pratt & Whitney JT9D series 13 aircraft

Dates and paperwork

In force since: June 9, 2009
Published: May 18, 2009 (signed April 23, 2009)
Docket: FAA-2006-23742
Replaces: 2007-17-21
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

The FAA is superseding an existing airworthiness directive (AD) for PW JT9D-7R4 series turbofan engines. That AD currently requires removing certain reduced cooling flow 2nd stage high-pressure turbine (HPT) vane assemblies installed in certain 2nd stage HPT vane cluster assemblies. It also requires a visual and a fluorescent penetrant inspection (FPI) of the 2nd stage HPT air seal assembly, part number (P/N) 815097. This AD requires a visual and FPI of all P/N 2nd stage HPT air seal assemblies that were used with reduced cooling flow 2nd stage HPT vane assemblies. This AD results from PW identifying additional P/N air seal assemblies that are affected by the unsafe condition. We are issuing this AD to prevent uncontained failure of the 2nd stage HPT air seal assembly, leading to engine in-flight shutdown and damage to the airplane.

The order itself the regulatory text, as published

Show the full text (3,046 characters)

2009-10-01 Pratt & Whitney: Amendment 39-15896. Docket No. FAA-2006- 23742; Directorate Identifier 2005-NE-53-AD. 

Effective Date 

	(a) This airworthiness directive (AD) becomes effective June 9, 2009. 

Affected ADs 

	(b) This AD supersedes AD 2007-17-21, Amendment 39-15180. 

Applicability 

	(c) This AD applies to Pratt & Whitney (PW) JT9D-7R4G2, -7R4E1, -7R4E4, and -7R4H1 series turbofan engines. These engines are installed on, but not limited to, Boeing 747-200, -300, 767-200, and Airbus A300-600 and A310-300 series airplanes. 

Unsafe Condition 

	(d) This AD results from the manufacturer identifying additional part number (P/N) air seal assemblies that are affected by the unsafe condition. We are issuing this AD to prevent uncontained failure of the 2nd stage high-pressure turbine (HPT) air seal assembly, leading to engine in-flight shutdown and damage to the airplane. 

Compliance 

	(e) You are responsible for having the actions required by this AD performed at the next HPT module exposure after the effective date of this AD, unless the actions have already been done. 
	(f) At the next HPT module exposure, remove reduced cooling flow 2nd stage HPT vane assemblies P/Ns: 797282, 796972, 800082, 800072, 803182, 803282, and 822582, installed in 2nd stage HPT vane cluster assemblies: P/Ns 797592, 797372, 799872, 799782, and 822572. 
	(g) For 2nd stage HPT air seals that are installed in engines that had a reduced cooling flow HPT vane assembly removed as specified in (f) of this AD, do the following: 
	(1) Perform a onetime visual inspection of the 2nd stage HPT air seal assembly. Information on the visual inspection can be found in the JT9D-7R4 engine manual, Section 72-51-22, Inspection/Check-01, paragraphs 1.D.(1), 1.D.(4), and 1.D.(6). (2) Perform a fluorescent penetrant inspection (FPI) of the 2nd stage HPT air seal assembly for cracks. Information on the FPI can be found in the JT9D-7R4 engine manual, Section 72-51-00, Inspection/Check-03. 

Definition 

	(h) For the purpose of this AD, we define an HPT module exposure as removing the 1st stage HPT rotor or the 2nd stage HPT rotor from the HPT case. 

Alternative Methods of Compliance 

	(i) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. 

Related Information 

	(j) Pratt & Whitney Alert Service Bulletin JT9D-7R4-A72-596, dated September 15, 2005, contains information for modifying the reduced cooling flow 2nd stage HPT vane assemblies. Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565- 8770; fax (860) 565-4503, for a copy of this service information. 
	(k) Contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov; telephone (781) 238-7758; fax (781) 238-7199,for more information about this AD. 

Material Incorporated by Reference 

	(l) 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 5, 2026. Connections as data: /graph/directive/2009-10-01.json · aircraft systems.