AD 2006-17-07R1

AD Final Rules - 2006-17-07R1.pdf
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AD Number:
2006-17-07R1
Document Type:
AD Final Rules
Docket Number:
FAA-2006-25809
Subject Heading:
Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, - 7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, - 217A, -217C,... ...Show more
Subject:
High pressure compressor (HPC) front hubs and HPC disk
Status:
Current
Citation:
(Federal Register: October 18, 2006 (Volume 71, Number 201))
Citation Publish Date:
10/18/2006
Effective Date:
11/02/2006
Make:
Pratt & Whitney Division
Model:
JT8D-1 | JT8D-11 | JT8D-15 | JT8D-15A | JT8D-17 | JT8D-17A | JT8D-17AR | JT8D-17R ...Show more
Product Type:
Engine
Product Subtype:
Affected AD:
Superseded AD:
2006-17-07
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
Updated RGL applicability to match AD applicability; CAR C-11-185
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[Federal Register: October 18, 2006 (Volume 71, Number 201)]


[Rules and Regulations]


[Page 61395-61399]


From the Federal Register Online via GPO Access [wais.access.gpo.gov]


[DOCID:fr18oc06-6]


–––––––––––––––––––––––––––––––––––


DEPARTMENT OF TRANSPORTATION


Federal Aviation Administration


14 CFR Part 39


[Docket No. FAA-2006-25809; Directorate Identifier 2001-NE-30-AD; Amendment 39-14791;


AD 2006-17-07R1]


RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -


15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 Turbofan Engines


AGENCY:
 
Federal Aviation Administration (FAA), Department of Transportation (DOT).


ACTION:
 
Final rule; correction.


–––––––––––––––––––––––––––––––––––


SUMMARY:
 
The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney


(PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -


217A, -217C, and -219 turbofan engines. That AD currently requires either replacing high pressure


compressor (HPC) front hubs and HPC disks that have operated at any time with PWA 110-21


coating and that operated in certain engine models, or, visually inspecting and fluorescent penetrant


inspecting (FMPI) for cracking of those parts and re-plating them if they pass inspection. This AD


requires the same actions, but makes necessary corrections to inadvertent reference errors and


omissions found in AD 2006-17-07, and relaxes some of the compliance times in Table 5. This AD


results from our finding reference errors and omissions in AD 2006-17-07, from determining that the


AD as drafted imposed an unnecessary burden on operators if they have to immediately remove


engines, and from requests to clarify compliance paragraphs. We are issuing this AD to prevent a


rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and


damage to the airplane.


DATES:
 
This AD becomes effective November 2, 2006. The Director of the Federal Register


previously approved the incorporation by reference of certain publications listed in the regulations as


of October 4, 2006 (71 FR 51459, August 30, 2006).


ADDRESSES:
 
You can get the service information identified in this AD from Pratt & Whitney, 400


Main St., East Hartford, CT 06108, telephone (860) 565-7700; fax (860) 565-1605.


You may examine the AD docket on the Internet at
 
http://dms.dot.gov
 
or in Room PL-401 on the


plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC.


1
FOR FURTHER INFORMATION CONTACT:
 
Keith Lardie, Aerospace Engineer, Engine


Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park,


Burlington, MA 01803; telephone (781) 238-7189; fax (781) 238-7199.


SUPPLEMENTARY INFORMATION:
 
On August 21, 2006, the FAA issued AD 2006-17-07,


Amendment 39-14728 (71 FR 51459, August 30, 2006). That AD requires either replacing HPC front


hubs and HPC disks that have operated at any time with PWA 110-21 coating and that operated in


certain engine models, or, visually inspecting and FMPI for cracking of those parts and re-plating


them if they pass inspection. That AD was the result of an investigation by PW, which concluded that


any HPC front hub or HPC disk coated with PWA 110-21 that ever operated on JT8D-15, -15A, -17,


-17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines, could crack before


reaching their published life limit. That condition, if not corrected, could result in an uncontained


engine failure and damage to the airplane.


Examining the AD Docket


You may examine the docket that contains the AD, any comments received, and any final


disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m.,


Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5227) is


located on the plaza level of the Department of Transportation Nassif Building at the street address


stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives


them.


Actions Since AD 2006-17-07 Was Issued


After we issued AD 2006-17-07, we found reference errors and omissions. These errors and


omissions could affect your ability to comply with the AD. The following errors and omissions were


discovered. We made the associated corrections:


•
 
In the third column of Table 1 of this AD, we omitted ''-17A'' in two places. We added the


missing ''-17A'' from AD 2006-17-07 in both places.


•
 
The third column of Table 4 and Table 5 reads ''Paragraph (h)(3) of this AD''. Paragraph (h)(3)


does not exist. We corrected it to read ''Paragraph (j) of this AD.''


We also determined that based on the compliance times in Table 5 of AD 2006-17-07, some


operators might have to immediately remove their engines from service. If so, we concluded that


those immediate removals might impose an unanticipated undue burden. Table 5 of AD 2006-17-07,


appears below.


Table 5 of AD 2006-17-07– HPC Front Hub Inspection Schedule – Hubs Coated With Nickel-


Cadmium


HPC Front Hub CSN


On the Effective Date


of This AD


Inspect Before Additional


CIS or CSN, Whichever


Occurs First


Also Inspect 7
th
 
Stage HPC Disks and


9
th
 
Stage-through-12
 
th
 
Stage HPC


Disks Using:


(i) 19,000 or more.
 
500 CIS or 20,000 CSN.
 
Paragraph (h)(3) of this AD.


(ii) 17,000 or more, but


fewer than 19,000.


1,000 CIS or 19,500 CSN.
 
Paragraph (h)(3) of this AD.


(iii) 9,000 or more, but


fewer than 17,000, that


have not been inspected.


18,000 CSN.
 
Paragraph (h)(3) of this AD.


2