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2009-04-18: 2nd stage high pressure turbine (HPT)

FAA order 2009-04-18 is an airworthiness directive in force since May 5, 2009. The FAA's subject line: 2nd stage high pressure turbine (HPT). It names the Pratt & Whitney JT9D-7, Pratt & Whitney JT9D series engines: about 14 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: Pratt & Whitney Division
Models: JT9D-7, JT9D-7A, JT9D-7AH, JT9D-7F, JT9D-7H, JT9D-7J
Engine series: Pratt & Whitney JT9D-7 1 aircraft
Pratt & Whitney JT9D series 13 aircraft

Dates and paperwork

In force since: May 5, 2009
Published: June 25, 2009 (signed March 17, 2009)
Docket: FAA-2008-0759
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

The FAA is adopting a new airworthiness directive (AD) for PW models JT9D-7, -7A, -7AH, -7H, -7F, and -7J turbofan engines. This AD requires initial and repetitive borescope inspections of the 2nd stage high-pressure turbine (HPT) rotor and stator assembly. This AD results from an uncontained failure of a 2nd stage HPT rotor disk that caused the engine to separate from the airplane. We are issuing this AD to prevent failure of the 2nd stage HPT rotor disk, which could result in uncontained engine failure, damage to the airplane, and the engine separating from the airplane.

The order itself the regulatory text, as published

Show the full text (3,997 characters)

2009-04-18 Pratt & Whitney: Amendment 39-15824. Docket No. FAA-2008- 0759; Directorate Identifier 2008-NE-02-AD. 

Effective Date 

	(a) This airworthiness directive (AD) becomes effective May 5, 2009. 

Affected ADs 

	(b) None. 

Applicability 

	(c) This AD applies to Pratt & Whitney (PW) JT9D-7, -7A, -7AH, - 7H, -7F, and -7J turbofan engines. These engines are installed on, but not limited to, Boeing 747 series airplanes. 

Unsafe Condition 

	(d) This AD results from an uncontained failure of a 2nd stage high-pressure turbine (HPT) rotor disk that caused the engine to separate from the airplane. We are issuing this AD to prevent failure of the 2nd stage HPT rotor disk, which could result in uncontained engine failure, damage to the airplane, and the engine separating from the airplane. 

Compliance 

	(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.Initial Borescope Inspection 

	(f) Within 100 cycles-in-service (CIS) after the effective date of this AD, or within 1,000 CIS after the last installation of the second stage HPT vanes, whichever occurs later, do the following: 
	(1) Use the Accomplishment Instructions of PW Alert Service Bulletin (ASB) JT9D A6488, Revision 1, dated April 18, 2008, to borescope-inspect the 2nd stage HPT rotor and stator assembly either on-wing or in the shop. 
	(2) If you see any damage or contact between the 2nd stage HPT vanes and the 2nd stage HPT rotor, remove the engine from service. 

Repetitive Borescope Inspection 

	(g) Thereafter, within 1,000 cycles-since-last inspection, do the following: 
	(1) Use the Accomplishment Instructions of PW ASB JT9D A6488 Revision 1, dated April 18, 2008, to borescope-inspect the 2nd stage HPT rotor and stator assembly either on-wing or in the shop. 
	(2) If you see any damage or contact between the 2nd stage HPT vanes and the 2nd stage HPT rotor,remove the engine from service. 

Optional Terminating Action 

	(h) Installing the 2nd stage HPT vanes as specified in paragraphs 1.B.(1) through 1.B.(32) of Section 72-51-00, Assembly -02 of the JT9D-7 Engine Manual Revision 122, dated February 15, 2008, terminates the repetitive inspection requirement specified in paragraph (g) of this AD. 

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) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199, for more information about this AD. 

Material Incorporated by Reference 

	(k) You must use the service information specified in the following Table 1to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in the following Table 1 in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact 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. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. 

	Table 1--Incorporation by Reference


Service information No. 
Page 
Revision 
Date 




Pratt & Whitney JT9D Engine Maintenance Manual PN 770408, Section 72-51-00, Assembly -02 
Total Pages 36 
1001 through 1036
122 
February 15, 2008. 
Pratt & Whitney PW ASB JT9D A6488, Revision 1, dated April 18, 2008. 
All
1 
April 18, 2008. 
Total Pages - 21

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 8, 2026. Connections as data: /graph/directive/2009-04-18.json · aircraft systems.