Federal Register / Vol. 80, No. 139 / Tuesday, July 21, 2015 / Rules and Regulations 43011 

Done in Washington, DC, this 15th day of 

July 2015. 

Kevin Shea, 

Administrator, Animal and Plant Health 

Inspection Service. 

[FR Doc. 2015–17842 Filed 7–20–15; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1127; Directorate 

Identifier 2014–NE–16–AD; Amendment 39– 

18203; AD 2015–14–05] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all Pratt 

& Whitney (PW) JT8D–217C and JT8D– 

219 turbofan engines. This AD was 

prompted by reports of cracking in the 

low-pressure turbine (LPT) shaft. This 

AD requires removing affected LPT 

shafts from service using a drawdown 

plan. 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. 

DATES: This AD is effective August 25, 

2015. 

ADDRESSES: For service information 

identified in this AD, contact Pratt & 

Whitney, 400 Main St., East Hartford, 

CT 06108; 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 

material at the FAA, call 781–238–7125. 

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– 

1127; 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 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: JoAnn Theriault, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7105; fax: 781–238– 

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

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all PW JT8D–217C and JT8D– 

219 turbofan engines. The NPRM 

published in the Federal Register on 

March 2, 2015 (80 FR 11140). The 

NPRM was prompted by in-shop 

findings of fatigue cracks on the No. 4.5 

bearing thread undercut adjacent to the 

oil feed holes. The cracks were 

discovered during routine fluorescent 

penetrant inspections (FPIs). Both shafts 

had oil feed hole enlargement rework 

accomplished. The root cause is 

increased stress on the fillet of the 

thread undercut region in front of the oil 

feed holes caused by oil feed hole 

rework. The increased stress reduces the 

low cycle fatigue life of the shaft. The 

NPRM proposed to require removing 

affected LPT shafts from service using a 

drawdown plan. 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. 

Related Service Information 

We reviewed PW Service Bulletin 

(SB) No. JT8D 6504, dated November 5, 

2014. The SB contains additional 

information regarding removal of the 

LPT shaft. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 11140, 

March 2, 2015) and the FAA’s response 

to each comment. 

Request To Withdraw the NPRM 

Delta Air Lines (DAL) and Allegiant 

Air requested that the current LPT shaft 

life limit of 25,000 cycles-since-new 

(CSN) be retained rather than removing 

the LPT shaft from service at 20,000 

CSN as proposed in the NPRM. The 

commenters stated that reducing the life 

limit is unjustified because there has not 

been an in-service LPT shaft failure of 

the type addressed. 

We do not agree. We determined that 

an acceptable level of safety would not 

be maintained if LPT shafts are allowed 

to remain in service until accumulating 

25,000 CSN. We reduced the life of the 

LPT shaft to 20,000 CSN to minimize 

the risk of LPT shaft failure. We did not 

change this AD. 

Proposal To Increase Repetitive 

Inspections 

DAL and Allegiant Air proposed 

increasing the occurrence of FPIs to 

increase the opportunity of identifying 

LPT shaft cracks. The commenters 

stated that routine FPIs have been 

successful in detecting LPT shaft cracks 

in the past. 

We do not agree. Recurring 

inspections are not adequate as a final 

corrective action. Relying on recurring 

FPIs to detect cracks, rather than shaft 

removal at 20,000 CSN, would likely 

result in an increased number of LPT 

shafts cracking in service, a greater risk 

of undetected cracked shafts being 

returned to service, and an unacceptable 

risk of shaft failure. We determined that 

long-term continued operational safety 

is enhanced by a terminating action that 

removes affected shafts from service 

rather than by increasing the occurrence 

of repetitive inspections. We did not 

change this AD. 

Request To Reduce Costs 

DAL and Allegiant Air requested 

retaining the existing life limit or 

increasing the occurrence of 

inspections. The commenters stated that 

the life reduction in the NPRM places 

an undue economic burden on the U.S. 

fleet by forcing early engine removals. 

We do not agree. We mitigated the 

operational and financial impacts by 

providing a drawdown plan rather than 

requiring removal before further flight, 

while providing an acceptable level of 

safety. We did not change this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will 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 accomplished 

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 

$21,003,120. 


asabaliauskas on DSK5VPTVN1PROD with RULES
43012 Federal Register / Vol. 80, No. 139 / Tuesday, July 21, 2015 / Rules and Regulations 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, 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 FAA with 

promoting safe flight 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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 

■ 1. 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 following new airworthiness 

directive (AD): 

2015–14–05 Pratt & Whitney: Amendment 

39–18203; Docket No. FAA–2014–1127; 

Directorate Identifier 2014–NE–16–AD. 

(a) Effective Date 

This AD is effective August 25, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Pratt & Whitney 

(PW) JT8D–217C and JT8D–219 turbofan 

engines with low-pressure turbine (LPT) 

shaft part numbers 783319, 783319–001, 

783319–003, 783319–004, 783320, 783320– 

001, 783320–003, 783320–004, 820514–001, 

820514–003, 820514–004, or 820514–005, 

installed. 

(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. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) If 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) Definition 

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. 

(h) Related Information 

(1) For more information about this AD, 

contact Jo-Ann Theriault, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; 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 AD, can be 

obtained from PW using the contact 

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

(3) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

St., East Hartford, CT 06108; phone: 860– 

565–8770; fax: 860–565–4503. 

(4) 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 material at the FAA, call 781–238–7125. 

(i) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

June 26, 2015. 

Ann C. Mollica, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–17710 Filed 7–20–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Parts 91 and 119 

[Docket No. FAA–FAA–2015–0517] 

Policy Regarding Living History Flight 

Experience Exemptions for Passenger 

Carrying Operations Conducted for 

Compensation and Hire in Other Than 

Standard Category Aircraft 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of policy statement. 

SUMMARY: With this document, the 

Federal Aviation Administration (FAA) 

cancels all previous agency policies 

pertaining to the carriage of passengers 

for compensation on Living History 

Flight Experience (LHFE) flights. This 

policy statement announces the end of 

FAA moratorium on new petitions for 

exemption, or amendments to 

exemptions from certain sections of 

Title 14, Code of Federal Regulations 

(14 CFR) for the purpose of carrying 

passengers for compensation or hire on 

LHFE Flights. 

DATES: The moratorium will end on July 

21, 2015. 

FOR FURTHER INFORMATION CONTACT: 

General Aviation and Commercial 

Division, General Aviation Operations 

Branch (AFS–830), Flight Standards 

Service, FAA, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone (202) 267–1100; 9-AFS-800- 

Correspondence-Mail@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA has historically found the 

preservation of U.S. aviation history to 

be in the public interest, including 

preservation of certain former military 


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