65614 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 

Subpart G also issued under 12 U.S.C. 2810 

et seq., 2901 et seq.; 15 U.S.C. 1691; 42 U.S.C. 

1981, 1982, 3601–3619. 

Subpart H also issued under 12 U.S.C. 

1464; 1831y. 

Subpart I also issued under 12 U.S.C. 

1831x. 

Subpart J also issued under 12 U.S.C. 

1831p–1. 

Subpart M also issued under 12 U.S.C. 

1818. 

Subpart N also issued under 12 U.S.C. 

1821. 

Subpart O also issued under 12 U.S.C. 

1828. 

Subpart P also issued under 12 U.S.C. 

1470; 1831e; 1831n; 1831p–1; 3339. 

Subpart Q also issued under 12 U.S.C. 

1462; 1462a; 1463; 1464. 

Subpart R also issued under 12 U.S.C. 

1463; 1464; 1831m; 1831n; 1831p–1. 

Subpart S also issued under 12 U.S.C. 

1462; 1462a; 1463; 1464; 1468a; 1817; 1820; 

1828; 1831e; 1831o; 1831p–1; 1881–1884; 

3207; 3339; 15 U.S.C. 78b; 78 l; 78m; 78n; 

78p; 78q; 78w; 31 U.S.C. 5318; 42 U.S.C. 

4106. 

Subpart T also issued under 12 U.S.C. 

1462a; 1463; 1464; 15 U.S.C. 78c; 78 l; 78m; 

78n; 78w. 

Subpart U also issued under 12 U.S.C. 

1462a; 1463; 1464; 15 U.S.C. 78c; 78 l; 78m; 

78n; 78p; 78w; 78d–1; 7241; 7242; 7243; 

7244; 7261; 7264; 7265. 

Subpart V also issued under 12 U.S.C. 

3201–3208. 

Subpart W also issued under 12 U.S.C. 

1462a; 1463; 1464; 15 U.S.C. 78c; 78 l; 78m; 

78n; 78p; 78w. 

Subpart X also issued under 12 U.S.C. 

1462; 1462a; 1463; 1464; 1828; 3331 et seq. 

Subpart Y also issued under 12 U.S.C. 

1831o. 

Subpart Z also issued under 12 U.S.C. 

1462; 1462a; 1463; 1464; 1828 (note). 

Subpart L—[Removed and Reserved] 

■ 2. Remove and reserve subpart L, 

consisting of §§ 390.220 through 

390.222. 

Dated at Washington, DC, this 22nd day of 

October, 2015. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2015–27292 Filed 10–26–15; 8:45 am] 

BILLING CODE 6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0787; Directorate 

Identifier 2015–NE–10–AD; Amendment 39– 

18307; AD 2015–22–03] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all Pratt 

& Whitney Division (PW) PW4164, 

PW4168, PW4168A, PW4164C, 

PW4164C/B, PW4164–1D, PW4168–1D, 

PW4168A–1D, PW4170, PW4164C–1D, 

PW4164C/B–1D, PW4050, PW4052, 

PW4056, PW4060, PW4060A, 

PW4060C, PW4062, PW4062A, 

PW4152, PW4156, PW4156A, PW4158, 

PW4160, PW4460, PW4462, and 

PW4650 turbofan engines including 

models with a ‘‘–3’’ suffix with a lowpressure turbine (LPT) 4th stage inner 

air seal (IAS), part number (P/N) 

51N038, installed. This AD was 

prompted by the discovery, during 

routine overhaul of the LPT, of cracks in 

the barrel section of the LPT 4th stage 

IAS. This AD requires removal of the 

LPT 4th stage IAS, P/N 51N038, 

according to a prescribed schedule. We 

are issuing this AD to prevent failure of 

the LPT 4th stage IAS, which could lead 

to an uncontained IAS release, damage 

to the engine, and damage to the 

airplane. 

DATES: This AD is effective December 1, 

2015. 

ADDRESSES: For service information 

identified in this AD, contact Pratt & 

Whitney Division, 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–2015– 

0787; 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: 

Katheryn Malatek, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7747; fax: 781–238– 

7199; email: katheryn.malatek@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 PW4164, PW4168, 

PW4168A, PW4164C, PW4164C/B, 

PW4164–1D, PW4168–1D, PW4168A– 

1D, PW4170, PW4164C–1D, PW4164C/

B–1D, PW4050, PW4052, PW4056, 

PW4060, PW4060A, PW4060C, 

PW4062, PW4062A, PW4152, PW4156, 

PW4156A, PW4158, PW4160, PW4460, 

PW4462, and PW4650 turbofan engines 

including models with a ‘‘–3’’ suffix 

with an LPT 4th stage IAS, P/N 51N038, 

installed. The NPRM published in the 

Federal Register on June 1, 2015 (80 FR 

30963). The NPRM was prompted by 

nine occasions of discovering, during 

routine overhaul of the LPT, cracks in 

the barrel section of the LPT 4th stage 

IAS. The NPRM proposed to require 

removal of the LPT 4th stage IAS, P/N 

51N038, according to a prescribed 

schedule. We are issuing this AD to 

prevent failure of the LPT 4th stage IAS, 

which could lead to an uncontained IAS 

release, damage to the engine, and 

damage to the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM (80 FR 30963, 

June 1, 2015) 

The Boeing Company expressed 

support for the NPRM. 

Request To Change Definitions 

United Airlines and Delta Airlines 

requested that the Definitions paragraph 

be changed. United Airlines requested 

we change the definition of LPT 

overhaul from ‘‘maintenance which 

involves disassembly of the LPT rotor 

module’’ to ‘‘when the LPT module is 

disassembled sufficiently to gain access 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 65615 

to the LPT 4th stage rotor assembly 

(disk/blade/seal).’’ Delta Airlines 

requested we change the definition of an 

LPT overhaul to ‘‘when all disks in the 

rotor are removed from the engine and 

the blades are removed.’’ 

We agree that the definition of an LPT 

overhaul should be clarified. We 

changed the definition of an LPT 

overhaul to ‘‘An LPT overhaul is 

defined as when all disks in the rotor 

are removed from the engine and the 

blades are removed.’’ 

Request To Change Applicability 

Delta Airlines requested changing the 

applicability to include models with 

any dash number suffix. 

We agree with the intent of this 

request. We changed the Summary, 

Discussion, and Applicability sections 

by adding ‘‘. . . including models with 

a ‘‘–3’’ suffix . . .’’ following the listed 

engine models as required. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 72 

engines installed on airplanes of U.S. 

registry. We also estimate that 9 of the 

engines will require replacement parts 

during shop visit, the pro-rated cost of 

these parts cost will be $23,805 per 

engine, and compliance with this AD 

will require about 49 hours of labor per 

engine. The average labor rate is $85 per 

hour. We also estimate that 63 of the 

engines will require replacement parts 

during LPT overhaul, the pro-rated 

replacement parts cost for these parts is 

$43,545 per engine, and that these 63 

engines will require 0 additional hours 

of labor per engine since the parts are 

already exposed during LPT overhaul. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$2,995,065. 

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): 

2015–22–03 Pratt & Whitney Division: 

Amendment 39–18307; Docket No. 

FAA–2015–0787; Directorate Identifier 

2015–NE–10–AD. 

(a) Effective Date 

This AD is effective December 1, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to: 

(1) All Pratt & Whitney Division PW4164, 

PW4168, PW4168A, PW4164C, PW4164C/B, 

PW4164–1D, PW4168–1D, PW4168A–1D, 

PW4170, PW4164C–1D, and PW4164C/B–1D 

turbofan engines with a low-pressure turbine 

(LPT) 4th stage inner air seal (IAS), part 

number (P/N) 51N038, installed. 

(2) All PW4050, PW4052, PW4056, 

PW4060, PW4060A, PW4060C, PW4062, 

PW4062A, PW4152, PW4156, PW4156A, 

PW4158, PW4160, PW4460, PW4462, and 

PW4650 turbofan engines including models 

with a ‘‘–3’’ suffix with an LPT 4th stage IAS, 

P/N 51N038, installed. 

(d) Unsafe Condition 

This AD was prompted by the discovery, 

during routine overhaul of the LPT, of cracks 

in the barrel section of the LPT 4th stage IAS 

which could, if not corrected, result in 

uncontained IAS release, damage to the 

engine, and damage to the aircraft. We are 

issuing this AD to prevent failure of the LPT 

4th stage IAS, which could lead to an 

uncontained IAS release, damage to the 

engine, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. For the engines listed in paragraph 

(c)(1) of this AD: 

(1) At each LPT overhaul after the effective 

date of this AD, remove from service the LPT 

4th stage IAS, P/N 51N038. 

(2) At each engine shop visit after the 

effective date of this AD, remove from service 

the LPT 4th stage IAS, P/N 51N038, if it has 

more than 10,900 cycles since new. 

(f) Installation Prohibition 

(1) Do not install any LPT 4th stage IAS, 

P/N 51N038, with more than 0 flight cycles 

on any engine listed in paragraph (c)(1) of 

this AD. 

(2) Do not install on any engine listed in 

paragraphs (c)(2) of this AD, any LPT 4th 

stage IAS, P/N 51N038, which was 

previously installed on any engine listed in 

paragraph (c)(1) of this AD. 

(g) Definitions 

For the purposes of this AD: 

(1) An LPT overhaul is defined as when all 

disks in the rotor are removed from the 

engine and the blades are removed. 

(2) An ‘‘engine shop visit’’ is the induction 

of an engine into the shop for maintenance 

involving the separation of pairs of major 

mating engine flanges (lettered flanges). The 

separation of engine flanges solely for the 

purpose of transportation without subsequent 

engine maintenance does not constitute an 

engine shop visit. 

(h) 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. 


tkelley on DSK3SPTVN1PROD with RULES
65616 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 

(i) Related Information 

For more information about this AD, 

contact Katheryn Malatek, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7747; fax: 781–238– 

7199; email: katheryn.malatek@faa.gov. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

October 21, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–27184 Filed 10–26–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0498; Directorate 

Identifier 2014–NM–152–AD; Amendment 

39–18305; AD 2015–22–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2007–16– 

08, which applied to all The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–300, 747–400, 747–400D, and 

747SR series airplanes. AD 2007–16–08 

required repetitive inspections for 

cracking of the station 800 frame 

assembly, and repair if necessary. This 

new AD continues to require repetitive 

inspections for cracking of the station 

800 frame assembly, and repair if 

necessary, and expands the inspection 

area. This AD was prompted by reports 

of cracks found at the forward and aft 

inner chord strap and angles on the 

station 800 frame on the left-side and 

right-side main entry doors. We are 

issuing this AD to detect and correct 

fatigue cracks that could extend and 

fully sever the frame, which could result 

in development of skin cracks that 

could lead to rapid depressurization of 

the airplane. 

DATES: This AD is effective December 1, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 1, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.govby searching for 

and locating Docket No. FAA–2015– 

0498. 

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–2015– 

0498; 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2007–16–08, 

Amendment 39–15147 (72 FR 44728, 

August 9, 2007). AD 2007–16–08 

applied to all The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, and 747SR series 

airplanes. The NPRM published in the 

Federal Register on March 30, 2015 (80 

FR 16606). The NPRM was prompted by 

reports of cracks found at the forward 

and aft inner chord strap and angles on 

the station 800 frame on the left-side 

and right-side main entry doors. The 

NPRM proposed to continue to require 

repetitive inspections for cracking of the 

station 800 frame assembly, and repair 

if necessary, and expand the inspection 

area. We are issuing this AD to detect 

and correct fatigue cracks that could 

extend and fully sever the frame, which 

could result in development of skin 

cracks that could lead to rapid 

depressurization of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 16606, 

March 30, 2015) and the FAA’s response 

to each comment. 

Support for the NPRM (80 FR 16606, 

March 30, 2015) 

Boeing stated that it concurred with 

the contents of the NPRM (80 FR 16606, 

March 30, 2015). 

Statement Regarding the NPRM (80 FR 

16606, March 30, 2015) 

United Airlines stated that it has 

reviewed the NPRM (80 FR 16606, 

March 30, 2015), and has no comment 

to submit. 

Request To Clarify Inspection 

Requirements 

UPS requested that we add an 

additional statement to paragraph (i) of 

the proposed AD (‘‘Exception to the 

Service Information,’’) to clarify that the 

removal of fasteners is not required for 

performing the surface high-frequency 

eddy current (HFEC) inspections 

specified by paragraph (g) of the 

proposed AD (80 FR 16606, March 30, 

2015). UPS stated that by adding the 

clarification that the removal of 

fasteners is not required, significant 

time and materials would be saved by 

operators when accomplishing this 

inspection and prevent unnecessary 

alternative method of compliance 

(AMOC) requests. UPS explained that 

Boeing agreed in a response to a service 

request that fastener removal is not 

required for performing surface HFEC 

inspections. 

We agree because the clarification 

will reduce costs while ensuring the 

same level of safety. We have added the 

following sentence to paragraph (g) of 

this AD: ‘‘It is not necessary to remove 

fasteners while performing the surface 

HFEC inspections.’’ 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the change described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 


tkelley on DSK3SPTVN1PROD with RULES