DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

!Docket No. FAA-2014- 1127; Directorate Identifier 2014-NE-16-AD] 

RIN 2 120-AA6.4 

Ainvorthiness Directives; Pratt & Whitney Turbofan 'Engines 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking (NPRM). 

{4910-13-Pl 

SUMMARY: We propose to adopt a new airwOtthincss directive (AD) for all Pratt & 

Whitney (PW) JT8D-2 17C and .JT8D-219 turbofan engines. This proposed AD was 

prompted by reports of cracking in the low-pressure turbine (LPT) shaft. This proposed 

AD establishes a new lower life limit for these parts and would require removing affected 

LPT shafts from service using a drawdown plan. We are proposing this AD to prevent 

failure of the LPT shaft, which could lead to an uncontained engine failure and damage to 

the airplane. 

DATES: We must receive comments on this proposed AD by [fNSERT DATE 60 

DAYS AFTER DATE OF PUBLICATION IN THE Federal Register]. 

ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 

and 11.45, by any of the following methods: 

• federal eRulemaking Portal: Go to http://www.regulations.gov. fo llow the 

instructions for submitting comments. 

• Fax: 202-493-225 1. 

• Mail : U.S. Department ofTransportation, Docket Operations, M-30, West 

Buildi ng Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 

20590. 
• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal holidays. 

For service information identified in this proposed AD, contact Pratt & Whitney, 

400 Main St., East Hartford, CT 06 1 08; phone: 860-565-8770; fax: 860-565-4503. You 

may view this service information at the FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA. For information on the availability of this 

materia l at the FAA, call 78 1-238-7125. 

Examining the AD Docket 

You may examine the AD docket on the Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA-2014-1 127; or in person at the Docket 

Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal 

holidays. The AD docket contai ns this proposed AD, the regulatory evaluation, any 

comments received, and other information. The street address for the Docket Office 

(phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the 

AD docket shortly a fter receipt. 

FOR FURTHER INFORMATION CONTACT: Jo-Ann Theriault, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 01803; phone: 78 1-238-71 05; fax: 78 1-238-

7199; email: jo-ann.theriault@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written relevant data, views, or arguments about this 

NPRM. Send your comments to an address listed under the ADDRESSES section. 

Include " Docket No. F AA-20 14-1127; Directorate Identifier 20 14-NE-16-AD" at the 

beginni ng of your comments. We specifically invite comments on the overall regulatory, 

economic, environmental, and energy aspects of this NPRM. We will consider all 

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comments received by the closing date and may amend this NPRM because of those 

comments. 

We will post all comments we receive, without change, to 

http://www.regul ations.gov, including any personal information you provide. We will 

also post a report summarizing each substantive verbal contact we receive about this 

NPRM. 

Discussion 

We received reports of two LPT shans with in-shop findings of fatigue cracks on 

the No. 4.5 bearing thread undercut adj acent to oil feed holes. The cracks were 

discovered during routine fluorescent penetrant inspections. Both shafts had oil feed hole 

enlargement rework accomplished. The root cause is increased stress on the fillet of the 

tlu·ead undercut region in front of the oi l feed holes caused by oil feed hole rework. The 

increased stress reduces the low cycle fatigue life of the shaft. This condition, if not 

corrected, could result in failure of the LPT shan, which could lead to an uncontained 

engine failure and damage to the airplane. 

Related Service Information under 1 CFR Part 51 

We reviewed PW Service Bulletin (SB) No. JT8D 6504, dated November 5, 201 4. 

The SB contains additional information regarding removal of the LPT shaft. This service 

information is reasonably available; see ADDRESSES for ways to access this service 

information. 

FAA's Determination 

We are proposing this NPRM because we evaluated all the relevant information 

and determined the unsafe condition described previously is likely to exist or develop in 

other products of the same type design. 

Proposed AD Rcquir·ements 

This NPRM would require removing affected LPT shafts from service. 

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Costs of Compliance 

We estimate that this proposed AD would affect about 744 engines installed on 

airplanes of U.S. registry. The average labor rate is $85 per hour. We estimate the prorated replacement cost would be $28,230. We also estimate that shaft replacement would 

be accompl ished during an engine shop visit at no additional labor cost. Based on these 

figures, we estimate the cost of the proposed AD on U.S. operators to be $2 1,003,120. 

Authority for this Rulemaking 

Title 49 of the United States Code specifies the FAA's authority to issue rules on 

aviation safety. Subtitle l, section I 06, describes the authority of the FAA Administrator. 

Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's 

authority. 

We are issuing this rulemaking under the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701 : "General requirements." Under that section, Congress 

charges the r: AA with promoting safe ilight of civil aircraft in air commerce by 

prescribing regulations for practices methods, and procedures the Administrator finds 

necessary for safety in air commerce. This regulation is within the scope of that authority 

because it addresses an unsafe condition that is likely to exist or develop on products 

identified in this rulemaking action. 

Regulatory Findings 

We determined that this proposed AD would not have federalism implications 

under Executive Order 13132. This proposed AD would not have a substantia l direct 

effect on the States, on the relationship between the national Government and the States, 

or on the distribution of power and responsibilities among the various levels of 

government. 

For the reasons discussed above, I certify this proposed regulation: 

(1) Is not a '·significant regulatory action" under Executive Order 12866, 

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(2) Is not a "significant rule" under the DOT Regulatory Policies and Procedures 

( 44 FR I I 034, February 26, 1979), 

(3) Will not affect intrastate aviation in Alaska to the extent that it justifies 

making a rebrulatory distinction, and 

(4) Wi ll not have a significant economic impact, positive or negative, on a 

substantial number of small entities under the criteri a of the Regulatory Flexibility Act. 

List of Subj ects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 

T he Proposed Amendment 

Accordingly, under the authority delegated to me by the Administrator, the FAA 

proposes to amend 14 CFR part 39 as follows: 

PART 39 - AIRWORTHINESS DIRECTIVES 

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

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

§ 39.13 !Amended] 

2. The FAA amends§ 39.13 by adding the fo llowing new airworthiness directive 

(AD): 

I>ratt & Whitney: Docket No. F AA-20 14-11 27; Directorate Identifier 20 14-NE-16-AD. 

(a) Comments Due Date 

We must receive comments by (INSERT OJ\ TE 60 DAYS AFTER DATE OF 

PUBLICATION IN THE Federal Register]. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Pratt & Whitney (PW) JT80-2 17C and JT80-219 turbofan 

engines with low-pressure turbine (LPT) shaft part numbers 783319, 783319-001 , 

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783319-003, 7833 19-004, 783320,783320-001 , 783320-003, 783320-004,820514-001, 

820514-003, 8205 14-004, or 820514-005, insta lled. 

(d) Unsafe Condition 

This AD was prompted by reports of cracking in the LPT shaft. We are issuing 

this AD to prevent failure of the LPT shaft, which could lead to an uncontained engine 

failure and damage to the airplane. 

(c) Compliance 

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

for engines with an LPT shaft part number listed in paragraph (c) of this AD: 

(I) Tf the LPT shaft has 15,000 or fewer cycles since new (CSN) on the effective 

date of this AD, remove it from service before it accumulates 20,000 CSN. 

(2) If the LPT shaft has more than 15,000 CSN on the effective date of this AD, 

remove it from service before it accumulates 5,000 additional cycles in service, or at the 

next piece-part exposure after accumulating 20,000 CSN, whichever occurs first. 

(3) After the effective date of this AD, do not install any LPT shaft listed in 

paragraph (c) of this AD that is at piece-part exposure and exceeds the new life limit of 

20,000 CSN, into any engine. 

(f) Definitions 

For the purpose of this AD, piece-part exposure is when the LPT shaft is 

completely disassembled from the engine. 

(g) Alternative Methods of Compliance (AMOCs) 

The Manager, Engine Certification Office, FAA, may approve AMOCs for this 

AD. Use the procedures found in 14 CFR 39. 19 to make your request. You may email 

your request to: ANE-AD-AMOC@faa.gov. 

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(h) Related Information 

(I) For more information about this /\0, contact Jo-Ann Theriault, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propell er Directorate, 12 New 

England Executi ve Park, Burlington, MA 0 1803; phone: 781-238-7105; fax: 781-238-

7199; email : jo-ann.theriault@faa.gov. 

(2) PW Service Bulletin No. JT8D 6504, dated November 5, 2014, which is not 

incorporated by reference in this proposed AD, can be obtained from PW using the 

contact information in paragraph (h)(3) of this proposed AD. 

(3) For service information identi-fied in this proposed AD, contact Pratt & 

Whitney, 400 Main St., East Hartford, CT 061 08; phone: 860-565-8770; fax: 860-565-

4503. 

(4) You may view this service information at the FAA, Engine & Propeller 

Directorate, 12 New England Executi ve Park, Burlington, MA. For information on the 

availability ofthis material at the FAA, call 78 1-238-7125. 

Issued in Burlington, Massachusetts, on February 20, 2015. 

Colleen M. D' Alessandro, 

Assistant Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certi-fication Service. 

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